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
2001021300034	20010213	00034	EU  	2001	2	13	20001227SH025    	1	19960329	G	2731	PC43402A0	WIRE            			EXTRA 	EA300 	EA300       	70218DI	EU  										TRIM CONTR LEVER	BENT            	B			UV4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	301NL	459  				059				ELEVATOR TRIM FORWARD SPRING STEEL WIRE WAS FOUND BENT CLOSE TO THE TRIM CONTROL LEVER.  THIS RENDERED THE SYSTEM UNUSAB	LE AND UNAIRWORTHY DUE TO THE POSITION IT WAS IN WHEN IT WAS BENT REMAINS.  THE PILOT COULD POSSIBLY NOT KNOW IT WAS BEN	T AS IT FEELS FREE WHEN OPERATED IN THE COCKPIT.  (X)				1	M	7	1 	3O			NC	A67EU   					 
2001021300035	20010213	00035	EU  	2001	2	13	20001227SH026    	1	19960627	G	2731	PC43402A0	WIRE            			EXTRA 	EA300 	EA300       	70218DI	EU  										TRIM CONTR LEVER	BENT            	B			UV4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	303NL	400  				056				ELEVATOR TRIM FORWARD SPRING STEEL WIRE WAS FOUND BENT CLOSE TO THE TRIM CONTROL LEVER.  THIS RENDERED THE SYSTEM UNUSAB	LE AND UNAIRWORTHY DUE TO THE POSITION IT WAS IN WHEN IT WAS BENT REMAINS.  THE PILOT COULD POSSIBLY NOT KNOW IT WAS BEN	T AS IT FEELS FREE WHEN OPERATED IN THE COCKPIT.  (X)				1	M	7	1 	3O			NC	A67EU   					 
2001021300036	20010213	00036	EU  	2001	2	13	20001227SH027    	1	19960627	G	2731	PC43402A0	WIRE            			EXTRA 	EA300 	EA300S      	1130864	EU  										TRIM CONTR LEVER	BENT            	B			UV4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	76PK	300  				15				ELEVATOR TRIM FORWARD SPRING STEEL WIRE WAS FOUND BENT CLOSE TO THE TRIM CONTROL LEVER. THIS RENDERED THE SYSTEM UNUSABL	E AND UNAIRWORTHY DUE TO THE POSITION IT WAS IN WHEN IT WAS BENT REMAINS.  THE PILOT COULD POSSIBLY NOT KNOW IT WAS BENT	 AS IT FEELS FREE WHEN OPERATED IN THE COCKPIT.  (X)				1	M	7	1 	3O			NC	A67EU   					 
2001021300037	20010213	00037	EU  	2001	2	13	20001227SH028    	1	19960220	G	2731	PC43402A0	WIRE            			EXTRA 	EA300 	EA300       	70218DI	EU  										TRIM CONTR LEVER	BENT            	B			UV4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	302NL	420  				062				ELEVATOR TRIM FORWARD SPRING STEEL WIRE WAS FOUND BENT CLOSE TO THE TRIM CONTROL LEVER.  THIS RENDERED THE SYSTEM UNUSAB	LE AND UNAIRWORTHY DUE TO THE POSITION IT WAS IN WHEN IT WAS BENT REMAINS.  THE PILOT COULD POSSIBLY NOT KNOW IT WAS BEN	T AS IT FEELS FREE WHEN OPERATED IN THE COCKPIT.  (X)				1	M	7	1 	3O			NC	A67EU   					 
1996062700386	19960627	00386	SW  	1996	6	27	9667             	1	19960307	G	2840	222366621103	SWITCH          			BELL  	206   	206L        	1181522	SW  										FUEL SYS	FAULTY          	H				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			FS	01	108W					52034				AIRFRAME FUEL FILTER IMPENDING BYPASS SWITCH MALFUNCTIONING.  BYPASS LIGHT COMES ON AND OFF WITH NO CONTAMINATION FOUND 	IN FILTER.  REPLACED WITH NEW FILTER.					1	G	7	1 	3U				H2SW    					 
1996062700387	19960627	00387	SW  	1996	6	27	9668             	1	19960307	G	6310	289051098	SEAL            			BELL  	206   	206B        	1181511	SW  										FREEWHEEL	WORN EXCESS     	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	345RR					2107				PART IS WORN EXCESSIVELY.  CUSTOMER COMPLAINT IS THAT ALL OF THE "2890" SERIES SEALS  WITH THE BLACK MATERIAL SEEM TO WE	AR DEEPER GROOVES AT A FASTER RATE THAN THE CHICAGO RAWHIDE SEALS WITH THE RED MATERIAL.					1	G	7	1 	3U				H2SW    					 
1996062000439	19960620	00439	WP  	1996	6	20	96ZZZM1000       	1	19960416	G	5340	APB7177	TRAPEZOIDAL FTG 			DOUG  	DC10  	DC1030      	3023501	WP  										RT MLG WW	CORROSION       	A			NWAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	229NW	88344	23313			46551				DURING CHECK, RIGHT MLG FIXED SIDE BRACE ATTACH FITTING INBOARD ATTACH BOLT HOLE SHOWS EVIDENCE OF CORROSION IN TRAP FIT	TING.  REMOVED CORROSION AND REPAIRED INBOARD ATTACH HOLES IAW SRM 57-20-00 FIG 20.					2	L	7	3 	4F				A22WE   					 
1996062000440	19960620	00440	WP  	1996	6	20	96ZZZM1001       	1	19960416	G	5340	APB7177	TRAPEZOIDAL FTG 			DOUG  	DC10  	DC1030      	3023501	WP  										LT MLG WW	CORROSION       	A			NWAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	229NW	88344				46551				DURING CHECK, LEFT MLG FIXED SIDE BRACE ATTACH FITTING INBOARD ATTCH BOLT HOLE SHOW EVIDENCE OF CORROSION IN TRAP FITTIN	G.  REPAIRED BOLT HOLE ON LEFT MLG FIXED SIDE BRACE ATTACH FITTING IAW SRM 57-20-00 FIG 20.  (M)					2	L	7	3 	4F				A22WE   					 
1996062000441	19960620	00441	WP  	1996	6	20	96ZZZM1002       	1	19960416	G	5343		ATTACH FITTING  			DOUG  	DC10  	DC1030      	3023501	WP  										RT MLG WW	CORROSION       	A			NWAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	229NW	88344	23313			46551				DURING CHECK, RIGHT MLG SIDE (FIXED) ATTACH FITTING INBOARD BOLT BARREL NUT HOLE IS BLEEDING RUST.  REPAIRED MLG SIDE BR	ACE ATTACH FITTING BARREL/NUT HOLE INBOARD SIDE IAW SRM 57-20-00 FIG 20.  (M)					2	L	7	3 	4F				A22WE   					 
1996062000442	19960620	00442	WP  	1996	6	20	96ZZZM1003       	1	19960319	G	5313		LONGERON        			DOUG  	DC10  	DC1030      	3023501	WP  										FS 1877-1893	CRACKED         	A			NWAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	229NW	88344				46551				DURING CHECK, AFT BULK CARGO STRINGER 42R HAS 4 INCH CRACK AND 4 SQUARE INCHES OF INTERGRANULAR CORROSION ON INBOARD SID	E OF STRINGER 42R AT SPLICE FS 1877.  REMOVED CORRODED SECTION OF LONGERON 42R, FS 1877 TO FS 1893, FABRICATED LONGERON 	AND LONG.  SPLICE AND INSTALLED PER SRM 53-10-00 FIG 2  TYPE I, INSTALLED CLASS I EXTERNAL REPAIR PER SRM 53-20-00 FIG 6	 DOUBLERS AND FINGER DOUBLERS.			2	L	7	3 	4F				A22WE   					 
1996062000443	19960620	00443	WP  	1996	6	20	96ZZZM1004       	1	19960311	G	5313	ADA7020559	LONGERON        			DOUG  	DC10  	DC1030      	3023501	WP  										FS 791-824	CORROSION       	A			NWAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	229NW					46551				DURING CHECK 53 SQUARE INCHES OF INTERGRANULAR CORROSION ON LONGERON 38 LEFT AFT FS 791-798 AND AT FS 807-824, LONGERON 	IS IN SKIN AND LONGERON INSTALLATION.  REMOVED CORROSION, FABRICATED REPAIR FITTINGS IAW SRM 53-10-00 PG 1-9 AND INSTALL	ED REPAIR IAW 53-10-00.  (M)				2	L	7	3 	4F				A22WE   					 
1996062000444	19960620	00444	WP  	1996	6	20	96ZZZM1005       	1	19960416	G	5343		ATTACH FITTING  			DOUG  	DC10  	DC1030      	3023501	WP  										LT MLG WW	CORROSION       	A			NWAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	229NW	88344	23313			46551				DURING CHECK, TRAPEZOIDAL OUTBOARD FITTING SIDE BRACE ATTACH POINT BARREL NUT HOLE CORRODED RIGHT SIDE.  REPAIRED OUTBOA	RD TRAPEZOIDAL SIDE BRACE ATTACH POINT BARREL NUT HOLE IAW SRM 57-20-00 FIG 20.					2	L	7	3 	4F				A22WE   					 
1996082200404	19960822	00404	NE  	1996	8	22	96ZZZM1243       	2	19960717	G	7320		P3 LINE         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	LOOSE           	A			AMWA	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CE	07	182YV					UE182				FLT 5627 - AFTER TAKEOFF RIGHT ENGINE ROLLED BACK TORQUE AND THEN STABILIZED AT ABOUT 1000 FT/LBS OF TORQUE, AIRCRAFT. R	ETURNED TO FIELD AT MCI.  MAINTENANCE TIGHTENED P3 LINE C/W FLIGHT TEST RETURNED AIRCRAFT TO SERVICE.  (M)					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1996082900638	19960829	00638	NM  	1996	8	29	96ZZZM1254       	1	19960731	G	3350	079123	LENS            			BOEING	747   	747212B     	1384886	NM  										CABIN	MISSING         	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND EMERGENCY LIGHT INOP AT SEAT 45C.  REPLACED LAMP AND LENS ASSY.  OPS CHECKED GOOD PER MM 33-51	-00 PG 501.  REFERENCE TWRA96256.					2	L	7	4 	4F				A20WE   					 
1996092600389	19960926	00389	EA  	1996	9	26	96ZZZM1323       	1	19960624	G	2133	722924E	OUTFLOW VLV     			CNDAIR	CL600 	CL6001A11   	1900302	EA  										CABIN	MALFUNCTIONED   	A			WH6A	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NE	03	601WW				158	1076				APPROX TWO HOURS INTO FLIGHT, CABIN PRESSURIZATION BEGAN TO FLUCTUATE 300 FEET IN AUTO MODE.  AIR RUSHING NOISE COULD BE	 HEARD IN BAGAGE AREA.  THE ELECTRO/PNEUMATIC OUTFLOW VALVE WAS REPLACED DURING AT 1200 HOUR INSPECTION APPROXIMATELY (8	) FLIGHT HOURS PRIOR.  PRESSURIZATION IS OK IN MANUAL MODE.  AIRCRAFT DIVERTED TO BOMBARDIER IN TUCSON, AZ.  OUTFLOW VLV	 WAS REPLACED.  THE ORIGINAL INSTALLED WAS PREVIOUSLY REPAIRED FOR INTERMITTENT PRESSURIZATION FLUCTUATION.			2	L	7	2 	4F			RT	A21EA   					 
1996100300460	19961003	00460	NM  	1996	10	3	96ZZZM1386       	1	19960829	G	3350	ML7715	BULB            			BOEING	747   	747212B     	1384886	NM  										CABIN	INOP            	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND SEAT 21C EVAC LIGHT INOP.  REPLACED SOCKET AND RELAMPED.  OPS CHECKED NORMAL AS PER MM 33-51-0	0.  REFERENCE TWRA96304.					2	L	7	4 	4F				A20WE   					 
1996032200592	19960322	00592	EU  	1996	3	22	96ZZZM319        	1	19960218	G	2910	137311D1443	HYD LINE        			BAG   	JETSTM	JETSTM3201  	1500217	EU  										ACFT BELLY	CHAFED          	A			NVEA	O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		AP	APPROACH       	1			SO	03	920AE					920				FLT NR 4501 - TRI - PILOT REPORTED, THE LANDING GEAR DID NOT EXTEND AFTER SELECTING DOWN.  CREW NOTICED THAT THE HYD PRE	SSURE WAS AT 0 PSI AND THAT THE FLAPS WERE ALSO INOP.  CREW MANUALLY EXTENDED THE GEAR AND LANDED WITHOUT FURTHER INCIDE	NT.  MAINTENANCE INSPECTED AND FOUND HYD LINE CHAFED NEXT TO THE RIGHT AC PACK.  REPLACED AND RESECURED A NEW HYD LINE S	O AS TO PREVENT FUTURE CHAFING.  (M)			2	L	7	2 	4T			RT	A56EU   					 
1996041200496	19960412	00496	WP  	1996	4	12	96ZZZM638        	2	19960128	G	7260	3588941	BEARING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					LT GEARBOX	FAILED          	A			PNSA	E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			AL	03	640PA	4729 				AC759B	P44691			DURING CRUISE FLIGHT, LEFT ENGINE FUEL CONTROL DRIVE GEARBOX BEARING FAILED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1996041200509	19960412	00509		1996	4	12	96ZZZM651        	4	19960218	G	6122	8210212	PROP GOV        			BEECH 	1900  	1900C       	1154161	CE  										LT ENG	LEAKING         	A		A	GPPA	E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CE	09	34010					UC3				NR 1 ENGINE SHUT DOWN IN FLIGHT DUE TO DROPPING OIL PRESSURE.  CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT. U	PON INSPECTION MECHANIC FOUND PRIMARY PROP GOVERNOR LEAKING AT THE INBOARD AFT CORNER.  TIGHTENED NUT CLEANED LEAK CHECK	ED AND RETURNED TO SERVICE.				2	L	7	2 	4T			RT	A24CE   					 
1996062000481	19960620	00481	WP  	1996	6	20	96ZZZM999        	1	19960416	G	5343		ATTACH FITTING  			DOUG  	DC10  	DC1030      	3023501	WP  										LT MLG WW	CORROSION       	A			NWAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	229NW	88344	23313			46551				DURING CHECK, LEFT MLG FIXED SIDE BRACE ATTACH BOLT HOLE SHOWS EVIDENCE OF CORROSION IN TRAP FITTING.  REPAIRED LEFT MLG	 FIXED SIDE BRACE ATTACH FITTING INBOARD BARREL NUT HOLE IAW SRM 57-20-00 FIG 20.					2	L	7	3 	4F				A22WE   					 
1996031500069	19960315	00069	EU  	1996	3	15	96ZZZX1017       	1	19960122	G	5311	1053025152	FRAME           			BOLKMS	105   	BO105S      	5626006	EU  										T/R PYLON	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8776	6616 				S776				DURING A ROUTINE INSPECTION, THE TAIL PYLON FRAME 11L WAS FOUND CRACKED COMPLETELY THROUGH LEFT SIDE OF FRAME.  THE CRAC	K WAS THROUGH THE LOWER RIVET LINE AT THE ATTACHMENT OF DOUBLER PLATE, PN 105-30412.01.  REPAIRED PER DER APPROVED 8110-	3.				1	G	7	2 	3U				H3EU    					 
1996031500071	19960315	00071	WP  	1996	3	15	96ZZZX1019       	1	19960126	G	5330	369H30109	PANEL           			HUGHES	369   	369D        	4470706	WP  										AIRFRAME	CRACKED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	7686 				1151D				DURING REMOVAL OF ENGINE, A CRACK WAS FOUND STARTING FROM THE RELIEF HOLE ON PANEL FORWARD .50 INCH AND .3750 INCH.  REP	AIR PANEL WITH A PATCH.  IT APPEARS THE CLEARANCE BETWEEN THE RELIEF HOLE AND THE 369D23007-5 ANGLE WERE TOO TIGHT.					1	G	7	1 	3U				H3WE    					 
1996031500072	19960315	00072	GL  	1996	3	15	96ZZZX1020       	2	19960216	G	7230	6877410	CASE HALF       			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	ERODED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		1673 		14914	1151D	CAE832750			DURING ANNUAL INSPECTION, THE COMPRESSOR CASE HALVES WERE FOUND ERODED BEYOND LIMITS.  CASE HALVES WERE REMOVED AND SENT	 IN FOR OVERHAUL.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996031500073	19960315	00073	GL  	1996	3	15	96ZZZX1021       	2	19960220	G	7313	6895021	NOZZLE          		6898735     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1	BURNED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		513  		C114422	1151D	CAE832750			NR 1 NOZZLE WAS REPLACED DUE TO EROSION AND CRACKING BEYOND LIMITS.  NOZZLE SENT IN FOR OVERHAUL.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996031500074	19960315	00074	WP  	1996	3	15	96ZZZX1022       	1	19960126	G	2820	369H81443	SWITCH          			HUGHES	369   	369D        	4470706	WP  										FUEL BYPASS	INOPERATIVE     	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING ENGINE REMOVAL, THE FUEL BYPASS SWITCH WAS REMOVED AND CHECKED, FOUND INOPERATIVE.						1	G	7	1 	3U				H3WE    					 
1996031500075	19960315	00075	GL  	1996	3	15	96ZZZX1023       	2	19960126	G	7230	6871534	CHIP PLUG       			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	LEAKING         	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	5074R					1151D	CAE832750			DURING REMOVAL OF COMPRESSOR, CHIP PLUG FOUND LEAKING PAST THE INSULATOR.  REPLACED CHIP PLUG.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996031500076	19960315	00076	GL  	1996	3	15	96ZZZX1024       	2	19960220	G	7250	6890040	SHIELD          		6898735     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1 TURB NOZZLE	WARPED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		513  			1151D	CAE832750			DURING REPLACEMENT OF NR 1 TURBINE NOZZLE, THE NOZZLE SHIELD WAS FOUND WARPED OUT OF SHAPE.  PART SENT IN FOR OVERHAUL.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996031500164	19960315	00164	SW  	1996	3	15	96ZZZX1026       	1	19960131	G	6510	206040339009	BEARING         			BELL  	206   	206B        	1181511	SW  										T/R DRV SYS	ROUGH           	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	527TK	1500 				4198				TAIL ROTOR DRIVE SHAFT BEARINGS ROUGH.  REPLACED WTIH NEW PARTS.						1	G	7	1 	3U				H2SW    					 
1996031500166	19960315	00166	NE  	1996	3	15	96ZZZX1028       	1	19960215	G	6220	S611223022002	VERTICAL HINGE  			SKRSKY	S61   	S61A        	814210C	NE  										M/R HEAD	CRACKED         	B			JYER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1048Y	8116 	2640 			61161				CRACK FOUND DURING OVERHAUL OF MAIN ROTOR HEAD.  VERTICAL HINGE WAS MAGNETIC PARTICAL.  INSPECTED PER OVERHAUL MANUAL. C	RACK WAS LOCATED ABOUT .75 INCH BELOW THREADED AREA IN 2.6238 BEARING JOURNAL.  THE CRACK WAS ABOUT .75 INCH LONG, GOING	 UP THROUGH THE THREADS, AND WAS A FINE SURFACE-TYPE CRACK.				2	G	7	2 	4U				H2EA    					 
1996031500167	19960315	00167	NE  	1996	3	15	96ZZZX1029       	2	19960201	G	7260	430110701	BEARING         			BELL  	222   	222         	1182122	SW  	LYC   	LTS101	LTS101650C3 	41560	NE  					ACCY GEARBOX	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	29KH	2554 			79K027	47053	LE41123			ENGINE REMOVED FOR PT WHEEL REPLACEMENT.  DURING DISASSEMBLY, SPUR GEAR PLAY FOUND EXCESSIVE.  GEARBOX DISASSEMBLED AND 	SPUR GEAR ASSY REMOVED.  THE NR 19 BEARING HAD BEEN SPINNING IN ITS BORE, WEARING AND ELONGATING BORE.  SUBMITTER RECOMM	ENDS PINNING OR SECURING BEARING OUTER RACE IN CASE.				1	G	7	2 	3U	3	U		H9SW    	E5NE				 
1996031500169	19960315	00169	NE  	1996	3	15	96ZZZX1031       	1	19960116	G	6320	7635109002048	HOUSING         			SKRSKY	S76   	S76         	8143010	NE  										SERVO MOUNT	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		3856 	932  							REWORK PERFORMED TO SERVO MOUNT PADS BEYOND LIMITS OF OVERHAUL MANUAL SA4047-76-7-8.  REWORK AREAS MEASURE IN LENGTH FRO	M .063 INCH LONG TO 2.957 INCH LONG, WIDTHS MEASURE FROM .063 INCH TO .352 INCH.  DEPTHS MEASURE FROM .015 INCH TO .028 	INCH AND REWORKED AREAS ARE WITHIN 1 INCH OF EACH OTHER.  SUBMITTER STATED, DO NOT REWORK SERVO PAD BEYOND THE LIMITS OF	 THE OVERHAUL MANUAL.  COMPONENT WAS LAST OVERHAULED BY CANADIAN COMPONENT SERVICES ON FEBRUARY 2, 1993, AT TT OF 6,379.	5 HOURS.		1	G	7	2 	3U				H1NE    					 
1996031500171	19960315	00171	SW  	1996	3	15	96ZZZX1033       	1	19960131	G	6320	214040810003	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										M/R XMSN FILTER	DEFECTIVE       	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	617DE	1500 				51138				INDICATOR EXTENDS IN COLD WEATHER GIVING FALSE INDICATION OF BYPASS CONDITION IN M/R TRANSMISSION OIL FILTER.  REPLACED 	WITH NEW P/N INDICATOR.					1	G	7	1 	3U				H2SW    					 
1996031500172	19960315	00172	SW  	1996	3	15	96ZZZX1034       	1	19960131	G	6510	327211	DISC ASSY       			BELL  	206   	206L3       	1182108	SW  										T/R DRIVE	CORRODED        	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	617DE	5984 				51138				DISC ASSY TRAPS MOISTURE BETWEEN THE LAMINATIONS AND EVENTUALLY CAUSES CORROSION PITS IN LAMINATIONS.  REPLACED WITH NEW	 ASSYS.					1	G	7	1 	3U				H2SW    					 
1996031500173	19960315	00173	SW  	1996	3	15	96ZZZX1035       	1	19960131	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	DEBONDED        	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	617DE		3000 			51138				TRANSMISSION RESTRAINT - RUBBER SHOWING CRACKING AND DEBONDING DUE TO NORMAL WEAR AND AGE.  REPLACED WITH OHC UNIT FROM 	LORD.					1	G	7	1 	3U				H2SW    					 
1996031500174	19960315	00174	WP  	1996	3	15	96ZZZX1036       	1	19960122	G	6310	269A55909	CLUTCH CABLE    			HUGHES	269   	269C        	4470504	WP  										M/R	BROKEN          	G		A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	17	363U	2044 				S1568				WHILE HERDING CATTLE, PILOT LANDED TO OPEN GATE.  PILOT HEARD A LOUD POP.  ON INVESTIGATION, HE FOUND THE CLUTCH CABLE B	ROKEN.  FURTHER INVESTIGATION REVEALED THE CABLE BROKE AT SWAGED BALL END.  THIS CABLE ASSY IS NOT INSPECTED UNTIL THE 4	00-HOUR INSPECTION EVENT FOR DAMAGE.  RECOMMEND A TIME-LIMIT REPLACEMENT BE SET AT 1,200 HOURS.  THE 400-HOUR INSPECTION	 REQUIRES DISASSEMBLY OF CLUTCH ASSEMBLY FOR THE COMPLETE INSPECTION OF THE CABLE.			1	G	7	1 	3O				4H12    					 
1996031500175	19960315	00175	NE  	1996	3	15	96ZZZX1037       	2	19960113	G	7314	430112810	FUEL PUMP       	BENDIX      		BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	LEAKAGE         	B		A	BAQR	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	03	39181	129  			3AFP1001B	7003	45060			INTERNAL LEAKAGE OF FUEL PUMP WASHED GREASE FROM BEARING OF FUEL CONTROL CAUSING AN ENGINE TO OVERSPEED.  THERE WAS NO I	NDICATION PRIOR TO THE FAILURE.  THE FUEL CONTOL SEIZED AND THE NYLON COUPLING SPLINES SHEARED.					1	G	7	2 	3U	3	U		H13EU   	E5NE				 
1996031500176	19960315	00176	NE  	1996	3	15	96ZZZX1038       	2	19960119	G	7314	430112810	PUMP            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENG FUEL	LEAKAGE         	B		A	BAQR	O				OTHER                   				Y	K		ENGINE STOPPAGE           	FLUID LOSS                		NR	NOT REPORTED   	1			EA	03	952CJ	500  			4AFP738B	7052	45061			INTERNAL LEAKAGE OF FUEL PUMP WASHED GREASE FROM BEARING IN THE FUEL CONTROL UNIT CAUSING IT TO FAIL, CAUSING THE ENGINE	 TO FAIL GOING INTO AN OVERSPEED CONDITION.  SUBMITTER STATED THIS HAS BEEN THE SECOND INCIDENT IN A 6-DAY PERIOD.					1	G	7	2 	3U	3	U		H13EU   	E5NE				 
1996031500177	19960315	00177	GL  	1996	3	15	96ZZZX1039       	2	19960110	G	7323		SPLINE SHAFT    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					N2 GOVERNOR	CAP DETACHED    	D	P			A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	13	8625F		1338 		13605	470111D	CAE830515			WHILE RETURNING TO BASE DURING FLIGHT, N2 RPM DROOPED.  PILOT LANDED AIRCRAFT AND REPORTED MALFUNCTION TO THE MECHANIC. 	 UPON INSPECTION OF GOVERNOR AND ATTACHING AIR LINES, THE DRIVE SPLINE RETAINING CAP WAS FOUND DETACHED AND SMALLER SHAF	T FOUND PARTIALLY FAILED AND TWISTED.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996031500178	19960315	00178	SW  	1996	3	15	96ZZZX1041       	1	19960201	G	6420	222012701119	HUB ASSY        			BELL  	230   	230         	1182149	SW  										BLADE FEATHER	BEARING BIND    	B		A	BAQR	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			EA	03	231UM	843  			A327	23012				DURING A FINAL APPROACH TO A ROOF-TOP HELIPAD, THE PILOT LOST ALL CONTROL OF THE TAIL ROTOR.  AFTER A SUCCESSFUL LANDING	 AT THE AIRPORT, HE REGAINED CONTROL OF THE TAIL ROTOR.  AFTER A THOROUGH INSPECTION OF THE T/R CONTROL SYSTEM, IT WAS D	ETERMINED THE FEATHER BEARINGS IN THE TAIL ROTOR BLADES WERE ON A BIND.				1	G	7	2 	3U			NC	H9SW    					 
1996031500179	19960315	00179	WP  	1996	3	15	96ZZZX1042       	1	19960112	G	6310	269A55909	CLUTCH CABLE    			HUGHES	269   	269C        	4470504	WP  										M/R	FAILED          	G		A		A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SW	17	3623T	2269 				S1567				WHILE HERDING CATTLE AT 75 FEET, AGL.  PILOT HEARD A LOUD BANG AND ROTOR RPM DECREASED AND ENGINE RPM INCREASED.  AIRCRA	FT IMPACTED GROUND CAUSING SUBSTANTIAL DAMAGE TO THE AIRCRAFT.  INVESTIGATION OF THE NOISE REVEALED THE CLUTCH CABLE HAD	 BROKEN AT CABLE END SWAGED BALL.  THIS CABLE ASSEMBLY IS NOT INSPECTED UNTIL THE 400-HOUR EVENT FOR DAMAGE.  RECOMMEND 	A TIME-LIMIT REPLACEMENT OF 1,200 HOURS.  THE 400-HOUR INSPECTION CALLS OUT FOR DISMANTLING OF THE CLUTCH ASSY FOR COMPL	ETE INSPECTION OF THE CABLE.		1	G	7	1 	3O				4H12    					 
1996031500181	19960315	00181	SW  	1996	3	15	96ZZZX1044       	1	19960130	G	7160	222062211113	DUCT            			BELL  	222   	222U        	1182140	SW  										LT ENG INLET	DELAMINATED     	B		A	QMLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	911ED	5906 			47	47551				DURING C/W ASB NR 222U93-34, FOUND UPPER AFT CORNER OF INLET DUCT DELAMINATED DUE TO CONTACT WITH THE COWLING DOOR.  SUB	MITTER SUGGESTS DUCT BE MADE OUT OF A MORE DURABLE MATERIAL LIKE STAINLESS STEEL.					1	G	7	2 	3U				H9SW    					 
1996031500182	19960315	00182	SW  	1996	3	15	96ZZZX1045       	1	19960130	G	7160	222062211114	DUCT            			BELL  	222   	222U        	1182140	SW  										RT ENG INLET	DELAMINATED     	B		A	QMLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	911ED	5906 			33	45771				DURING C/W ASB NR 222U-95-34, FOUND UPPER AFT CORNER OF THE INLET DUCT DELAMINATED DUE TO CONTACT WITH THE COWLING DOOR.	  SUBMITTER SUGGESTS DUCT BE MADE OUT OF A MORE DURABLE MATERIAL LIKE STAINLESS STEEL.					1	G	7	2 	3U				H9SW    					 
1996031500365	19960315	00365	SO  	1996	3	15	96ZZZX1047       	2	19960223	G	8550	S123660550	HOSE            			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					WASTEGATE OIL	CHAFED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	666SW					21062120	572351			WASTEGATE OIL RETURN HOSE CHAFED THROUGH AT FORWARD RIGHT ENGINE MOUNT.  SUBMITTER STATES CORRECTIVE ACTION - CLAMP HOSE	 OFF FOR PROPER CLEARANCE.					1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996031500366	19960315	00366	SO  	1996	3	15	96ZZZX1048       	2	19960227	G	8530	642619F	PISTON          			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					NR 2 CYLINDER	RINGS BROKEN    	H				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	09	83828	1540 				348133089	315090			ENGINE LOST OIL PRESSURE DURING FLIGHT.  PILOT SHUT DOWN ENGINE AND MADE UNEVENTFUL LANDING.  LARGE AMOUNT OF OIL WAS FO	UND UNDER THE ENGINE AND UNDER THE WING.  COMPRESSION CHECK SHOWED ZERO COMPRESSION ON NR 2 CYLINDER.  CYLINDER REMOVED 	AND DISCOVERED ALL RINGS BROKEN AND THE RING GLANDS SEVERELY BROKEN AND WORN.  A SUBSTANTIAL AMOUNT OF ALUMINUM WAS FOUN	D IN THE FILTER AND SCREEN.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996031500367	19960315	00367		1996	3	15	96ZZZX1049       	4	19960131	G	6122	C299506B0104	CONTROL ASSY    	MCAULY      	C290D3      	CESSNA	172   	R172K       	2072431	CE  										PROP GOV	FROZEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	7585X	2    				R1723334				INSTALLED NEW CONTROL CABLE ASSY AS SUPPLIED BY CESSNA AIRCRAFT.  INSTALLED AND RIGGED PER CESSNA R172K SERVICE MANUAL. 	 ALL OPS CHECK OK ON GROUND PRIOR TO FLIGHT.  RUN-UP OPS CHECK OK.  FLOWN FOR 2.0 HOURS FOR ENGINE BREAK-IN.  ALL OPS NO	RMAL.  UPON RETURN TO GROUND.  OPS CHECK OF ENGINE CONTROLS REVEALED FROZEN SOLID GOVERNOR CONTROL CABLE ASSY.  CABLE NR	 1 RETURNED TO CESSNA FOR EVALUATION.			1	H	7	1 	3O				3A17    					 
1996031500368	19960315	00368		1996	3	15	96ZZZX1050       	4	19960131	G	6122	C299506B0104	CONTROL ASSY    	MCAULY      	C29003      	CESSNA	172   	R172K       	2072431	CE  										PROP GOV	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	7585X	2    				R1723334				THIRD TIME TO INSTALL NEW CONTROL CABLE ASSY AS SUPPLIED BY CESSNA AIRCRAFT.  INSTALLED AND RIGGED PER CESSNA R172K SERV	ICE MANUAL.  ALL OPS CHECK OK ON GROUND.  RUN-UP OPS CHECK OK.  FLOWN FOR 2 HOURS, NO ATTEMPT TO MOVE CONTROL WHILE IN-F	LIGHT.  UPON RETURN TO GROUND, GOVERNOR CONTROL CABLE ASSY FROZEN SOLID.  REMOVE AND INSPECT, NO MARKS, CUTS, ABRASIONS,	 KINKS OR SIGNS OF OVERHEAT.  SUSPECT NORMAL HEAT IN AREA CAUSING INTERNAL COMPONENTS IN CABLE TO EITHER MELT OR SWELL C	AUSING CABLE CONTROL TO FREEZE UP.  CABLE NR 3 RETURNED TO CESSNA FOR EVALUATION.		1	H	7	1 	3O				3A17    					 
1996031500369	19960315	00369	SW  	1996	3	15	96ZZZX1051       	1	19960220	G	6300	412340102101	SEAL            			BELL  	412   	412         	1182202	SW  										DRIVE SHAFT	DEBONDED        	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	2FOR	11   				36112				DRIVE SHAFT SEAL DEBONDED.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500370	19960315	00370	SW  	1996	3	15	96ZZZX1052       	1	19960201	G	6300	412340102101	SEAL            			BELL  	412   	412         	1182202	SW  										DRIVE SHAFT	SEPARATED       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	2FOR	17   				36111				REPLACED WITH NEW FIXTURE.  DRIVE SHAFT SEAL BOOT SEPARATION (2 EACH).						1	G	7	2 	4U				H4SW    					 
1996031500371	19960315	00371	SW  	1996	3	15	96ZZZX1053       	1	19960220	G	6300	412040657003	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R DRIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	2FOR	11   			A668	36112				DRIVE SHAFT COUPLING PITTED.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500372	19960315	00372	SW  	1996	3	15	96ZZZX1054       	1	19960220	G	6300	214040675003	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R DRIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	2FOR	13   			A713	36114				INTER DRIVE COUPLING PITTED.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500373	19960315	00373	SW  	1996	3	15	96ZZZX1055       	1	19960220	G	6300	214040659003	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R DRIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	2FOR	13   			A917	36114				DRIVE SHAFT COUPLING HAS PITTED TEETH.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500374	19960315	00374	SW  	1996	3	15	96ZZZX1056       	1	19960220	G	6300	412340102101	SEAL            			BELL  	412   	412         	1182202	SW  										DRIVE SHAFT	DEBONDED        	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	2FOR	13   				36114				DRIVE SHAFT SEAL DEBONDED (2 EACH).  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500375	19960315	00375	SW  	1996	3	15	96ZZZX1057       	1	19960220	G	6300	214040659005	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R DRIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	2FOR	11   				36112				DRIVE COUPLING PITTED.  REPLACED WTIH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500376	19960315	00376	SW  	1996	3	15	96ZZZX1058       	1	19960220	G	6320	205040230003	SUN GEAR TOOTH  			BELL  	412   	412         	1182202	SW  										TRANSMISSION	FAILURE         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	900BH	1147 			A2733	33195				TRANSMISSION SUN GEAR TOOTH FAILURE.  REPLACED WTIH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500377	19960315	00377	SW  	1996	3	15	96ZZZX1059       	1	19960220	G	6220	206011105001	TRUNNION        			BELL  	206   	206B3       	1181506	SW  										M/R	ROUGH           	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	221GP	520  			RXFS1298	4309				M/R TRUNNION ROUGH AND BINDING.  REPLACED WITH NEW FIXTURE.						1	G	7	1 	3U				H2SW    					 
1996031500378	19960315	00378		1996	3	15	96ZZZX1060       	4	19960131	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT ATTITUDE	STICKS          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	3292N	16   			89869	36109				COCKPIT ATTITUDE INDICATOR STICKS.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500379	19960315	00379	SW  	1996	3	15	96ZZZX1061       	1	19960220	G	2140	205072277009	MIXING VALVE    			BELL  	412   	412         	1182202	SW  										HEATER	DEFECTIVE       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	3293G	15   			GWD12874	36115				HEATER FAILED DUE TO MIXING VALVE DEFECTIVE.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500380	19960315	00380	SW  	1996	3	15	96ZZZX1062       	1	19960220	G	6300	214040657003	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R DRIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	3293G	13   			A704	36115				M/R DRIVE COUPLING PITTED.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500381	19960315	00381	SW  	1996	3	15	96ZZZX1063       	1	19960220	G	6300	214040659005	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R DRIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	3293G	13   			A977	36115				DRIVE SHAFT COUPLING PITTED.  S/N A977 AND A906.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500382	19960315	00382		1996	3	15	96ZZZX1064       	4	19960220	G	3460	412375013101	FDAU            			BELL  	412   	412         	1182202	SW  										COCKPIT	DEFECTIVE       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	145H	19   			10015	36116				FDAU DEFECTIVE.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500383	19960315	00383	SW  	1996	3	15	96ZZZX1065       	1	19960220	G	2422	412075101103	INVERTER        			BELL  	412   	412         	1182202	SW  										AC SYSTEM	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	145H	19   			1052	36116				STATIC INVERTER FAILED.  REPLACED WTIH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500384	19960315	00384	SW  	1996	3	15	96ZZZX1066       	1	19960220	G	6300	214040659005S	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R DRIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	145H	16   			A984	36116				DRIVE SHAFT COUPLING (2 EACH PITTED).  S/N A984 AND A981.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500385	19960315	00385	SW  	1996	3	15	96ZZZX1067       	1	19960220	G	6300	214040657003	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R RIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	145H	16   			A719	36116				DRIVE SHAFT COUPLING (2 EACH) PITTED.  S/N A719 AND A714.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500386	19960315	00386	NE  	1996	3	15	96ZZZX1068       	1	19960212	G	6520	S613566602	HOUSING         		S61356660011	SKRSKY	S61   	S61N        	8142104	NE  										T/R GRBOX MT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	612RM		2228 		A16926	61744				DURING ROUTINE INSPECTION, A .75 INCH LONG CRACK WAS FOUND IN THE FORWARD RT ATTACHMENT MOUNT.  THIS HOUSING IS MANUFACT	URED FROM MAGNESIUM WHICH REQUIRES A ROUTINE INSPECTION.  C/W SB 61B35-48 REPLACES THIS ITEM WITH AN ALUMINUM HOUSING WI	TH MUCH THICKER MOUNT LUGS.				2	G	7	2 	4U				1H15    					 
1996031500387	19960315	00387	NE  	1996	3	15	96ZZZX1069       	1	19960212	G	6330	S61207626113	FITTING         		S6120762651 	SKRSKY	S61   	S61N        	8142104	NE  										INTERMED G/B MT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	612RM					61744				DURING ROUTINE INSPECTION, A CRACK IN THE WEB ON THE INTERMEDIATE GEARBOX MOUNT WAS FOUND.  THE CRACK IS .75 INCH LONG A	ND EXTENDS FROM THE WEB RADIUS TO A FASTENER HOLE.  THIS WEB HAS BEEN REPLACED PER SB 61B20-31, WHICH CHANGES THE MATERI	AL TO 7075-T73.				2	G	7	2 	4U				1H15    					 
1996031500388	19960315	00388	SW  	1996	3	15	96ZZZX1070       	1	19960220	G	6330	222031605105	FLEXTURE ASSY   			BELL  	222   	222         	1182122	SW  										XMSN MOUNT	DEBONDED        	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	51Q	917  			BW567	47151				TRANSMISSION MOUNT FLEXTURE DEBONDED.  S/N BW567 AND BW570.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	3U				H9SW    					 
1996031500389	19960315	00389	SW  	1996	3	15	96ZZZX1071       	1	19960220	G	2841	206075740107	INDICATOR       			BELL  	206   	206B        	1181511	SW  										FUEL QUANTITY	STICKS          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	221GP	185  				4309				FUEL INDICATOR STICKS.  REPLACED WITH NEW FIXTURE.						1	G	7	1 	3U				H2SW    					 
1996031500390	19960315	00390		1996	3	15	96ZZZX1072       	4	19960220	G	3421	1113034	INDICATOR       			FRCHLD	42    	42          	3370702	EA  										COCKPIT	FLAG INOP       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	92130	20   			89849	36118				ATTITUDE DIRECTOR FLAG INOPERATIVE.  REPLACED WITH NEW FIXTURE.						1	H	7	1 	3R				ATC242  					 
1996031500391	19960315	00391	SW  	1996	3	15	96ZZZX1073       	1	19960220	G	6300	214040657003	COUPLING        			BELL  	412   	412         	1182202	SW  										M/R DRIVE	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	92130	20   			A732	36118				DRIVE SHAFT COUPLING PITTED (2 EACH).  S/N A732 AND A730.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500392	19960315	00392		1996	3	15	96ZZZX1074       	4	19960220	G	3416	1003511424	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	ERRATIC         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	92130	19   			152022	36118				ALTIMETER ERRATIC.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996031500393	19960315	00393	SW  	1996	3	15	96ZZZX1075       	1	19960220	G	3230	222031206105	BELLCRANK       			BELL  	230   	230         	1182149	SW  										MLG	BEARING FAULTY  	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	230GN	35   				23034				MLG BELLCRANK BEARING FAULTY.  REPLACED WTIH NEW FIXTURE.						1	G	7	2 	3U			NC	H9SW    					 
1996031500394	19960315	00394	SW  	1996	3	15	96ZZZX1076       	1	19960220	G	3222	222336001123	STRUT           			BELL  	230   	230         	1182149	SW  										NLG	LEAKING         	B			GS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	230GN	38   			0021	23034				NLG STRUT LEAKING.  REPLACED WTIH NEW FIXTURE.						1	G	7	2 	3U			NC	H9SW    					 
1996031500395	19960315	00395	SW  	1996	3	15	96ZZZX1077       	1	19960220	G	6410	222016001111	BLADE           			BELL  	230   	230         	1182149	SW  										T/R	DENTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	230GN	81   			A554	23034				T/R BLADE DENTED.  S/N A554 AND A535.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	3U			NC	H9SW    					 
1996031500396	19960315	00396	WP  	1996	3	15	96ZZZX1078       	1	19960120	G	3610	6876667	TUBE            			HUGHES	369   	369D        	4470706	WP  										AIR DISCHARGE	WORN SLEEVE     	B	S		EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4571V	11214			97697	490487D				DURING ANNUAL INSPECTION, THE ENGINE AIR DISCHARGE TUBES (2 EACH) WERE FOUND WORN BEYOND LIMITS AT THE FORWARD SEAL RETA	INING SLEEVE.  REPLACED AIR TUBES.					1	G	7	1 	3U				H3WE    					 
1996031500397	19960315	00397	WP  	1996	3	15	96ZZZX1079       	1	19960120	G	3610	6876667	TUBE            			HUGHES	369   	369D        	4470706	WP  										AIR DISCHARGE	WORN SLEEVE     	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4571V	11214			97647	490487D				DURING ANNUAL INSPECTION, THE ENGINE AIR DISCHARGE TUBES (2 EACH) WERE FOUND WORN BEYOND LIMITS AT THE FORWARD SEAL RETA	INING SLEEVE.  REPLACED AIR TUBES.					1	G	7	1 	3U				H3WE    					 
1996031500398	19960315	00398	GL  	1996	3	15	96ZZZX1080       	2	19960120	G	7323	369A795155	ROD END         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GOV/THROTTLE	STIFF           	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4571V					4904870				DURING ANNUAL INSPECTION, THE ROD ENDS FROM THE GOVERNOR THROTTLE SHAFT TO THE BELLCRANK WERE FOUND EXTREMELY STIFF WITH	 SOME TEFLON RESIDUE COMING FROM THE ROD ENDS.  REPLACED PARTS.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996031500399	19960315	00399	NE  	1996	3	15	96ZZZX1081       	2	19960216	G	7321	0164348230	FUEL CONTROL    			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	MALFUNCTION     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	900SK	2900 			B678B	760304	3078			AFTER ENGINE START, ALL OPS NORMAL IDLE PLUS OR MINUS 2 PERCENT.  ADVANCED POWER LEVER TO FLY POSITION, ENGINE RPM STAYE	D AT IDLE 50 PLUS OR MINUS 2 PERCENT.  STAYED IN FLY POSITION FOR 10 MINUTES, NO CHANGE IN RPM.   BROUGHT POWER LEVER BA	CK TO IDLE FOR 10 MINUTES, THEN ADVANCED POWER LEVER TO FLY AND ENGINE RESPONDED NORMALLY.  NOTE:  AIRCRAFT WAS PARKED O	UTSIDE IN BELOW ZERO TEMPS FOR OVER 3 HOURS.  TEMPS APPROX 10-20 DEGREES FAHRENHEIT.			1	G	7	2 	3U	3	U		H1NE    	E19EU				 
1996031500400	19960315	00400	SW  	1996	3	15	96ZZZX1082       	1	19960214	G	6220	204011302105	FRAME           		212010300001	BELL  	212   	212         	1181420	SW  										STABILIZER BAR	MISMANUFACTURED 	B	L	A	ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					EAFS187					DURING INSTALLATION OF STABILIZER BAR, MECHANIC NOTICED THE BOLT THAT ATTACHES DAMPER CONTROL ARM TO THE STABILIZER BAR 	FRAME WAS TOO SHORT.  FURTHER INVESTIGATION REVEALED THE STABILIZER FRAME WAS APPROXIMATELY .125 INCH THICKER AT THE ATT	ACHMENT POINT THAN OTHER FRAMES.  STABILIZER BAR ASSY HAD JUST BEEN REASSEMBLED AFTER INSTALLING NEW FRAMES.  FRAME RETU	RNED TO MFG, WHO, IN TURN, SHIPPED A REPLACEMENT FRAME.  WHEN RECEIVED, REPLACEMENT FRAME WAS ALSO TOO THICK IN THE SAME	 AREA.  BOTH FRAMES PURCHASED DIRECTLY FROM BELL HELICOPTER.		1	G	7	1 	4U				H4SW    					 
1996031500632	19960315	00632	SO  	1996	3	15	96ZZZX1083       	2	19960217	G	8550		PUMP            			CESSNA	210   	T210H       	2073438	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE OIL	MISOVERHAULED   	D				E				ENGINE SHUTDOWN         				J	W		WARNING INDICATION        	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	13	65093					21061844	293717R			ON THE 6TH RUN FOR GROUND ADJUSTMENTS, OIL PRESSURE DROPPED TO 30 THEN 10 PSI AND ENGINE SECURED.  REPEATED ATTEMPTS TO 	PRIME OIL SYSTEM, COULD NOT GET OIL PRESSURE UP.  PUMP WAS REMOVED AND INSPECTED WITH NO OBVIOUS DEFECTS.  OIL PAN WAS R	EMOVED AND PICK-UP TUBE INSPECTED WITH NO DEFECTS.  ONLY DEFECT NOTED WAS THAT OIL PUMP WAS PROBABLY INCORRECTLY SILK TH	READED ALLOWING AIR TO BE SUCKED INTO SYSTEM AROUND ORIFICE.  AFTER REINSTALLATION OF COMPONENTS, NO FURTHER PROBLEMS EN	COUNTERED AND ACFT FLOWN WITH NO PROBLEMS.		1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996031500633	19960315	00633	SO  	1996	3	15	96ZZZX1084       	2	19960101	G	8530	641917	CYLINDER        			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					NR 4 EXH PORT	CRACKED         	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			CE	01	3824J					15065124	648346A			PILOT REPORTED A ROUGH ENGINE AND A PARTIAL LOSS OF POWER.  A PRECAUTIONARY LANDING MADE ON A COUNTY ROAD.  NO DAMAGE TO	 AIRCRAFT, PERSONNEL, OR PROPERTY.  FOUND NR 4 CYLINDER CRACKED AFTER CYLINDER REMOVED.  CRACK WENT THROUGH VALVE GUIDE 	BOSS ALLOWING GUIDE TO MOVE IN OPERATION, UNSEATING VALVE.  ENGINE TT, 6,193 HOURS.				1	H	7	1 	3O	3	O		3A19    	E252				 
1996031500634	19960315	00634	CE  	1996	3	15	96ZZZX1085       	1	19960227	G	7602	5038901021	CONTROL CABLE   			BEECH 	55    	95B55       	1152706	CE  										MIXTURE	END PARTED      	H			JT8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	255WP	18   				TF38				RT MIXTURE CONTROL ASSY SWAGED END PARTED FROM ROD ON ENGINE END OF CABLE.						1	L	7	2 	3O				3A16    					 
1996031500636	19960315	00636		1996	3	15	96ZZZX1087       	4	19960206	G	2215	2N5632	TRANSISTOR      		KS271A      	PIPER 	PA31  	PA31310     	7103103	SO  										PRIMARY SERVO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	27987				31641	317912054				PRIMARY SERVO TRANSISTOR HAS FAILED IN THREE DIFFERENT SERVOS, OVERHAULED BY TWO SEPARATE VENDORS.  CONTACT WITH ALLIED 	SIGNAL DID NOT RECOGNIZE THE USE OF THIS TRANSISTOR.  SUBMITTER STATED MOTOROLA REPLACEMENTS BE USED.					1	L	7	1 	3O			RT	A20SO   					 
1996031500637	19960315	00637	CE  	1996	3	15	96ZZZX1088       	1	19960223	G	7603	C299500401	CONTROL CABLE   			CESSNA	177   	177RG       	2073709	CE  										THROTTLE	FAILED          	B			TRKR	O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SO	15	2575V	3037 				177RG0622				PILOT REDUCED POWER TO LAND WITH NO RESPONSE TO ENGINE.  LANDED UNEVENTFULLY.  THROTTLE CONTROL CABLE BROKEN.						1	H	7	1 	3O			 	A20CE   					 
1996031500638	19960315	00638	EA  	1996	3	15	96ZZZX1089       	2	19960205	G	8520	SL72877	LIFTER          			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					CAM FOLLOWER	FAILED          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	15	711BD	786  				287205271	L1664636A			ENGINE POWER LOST IN-FLIGHT.  AIRCRAFT LANDED WITHOUT INCIDENT.  ENGINE REMOVED AND DISASSEMBLED.  FIVE OF EIGHT LIFTER 	BODIES BROKEN AT THE CAM FOLLOWING FACE.  SUBMITTER'S OPINION IS THAT ONLY ONE FAILURE OCCURRED.  THE OTHER DAMAGE WAS D	UE TO FOD FROM THE FIRST FAILURE.				1	L	7	1 	3O	3	O		2A13    	E286				 
1996031500639	19960315	00639	SO  	1996	3	15	96ZZZX1090       	1	19960215	G	3230	3815100	ROD ASSY        			PIPER 	PA32  	PA32R300    	7103213	SO  										NLG	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	5910V					32R7780377				ROD DISCOVERED BADLY BENT DURING ANNUAL INSPECTION.  PILOT PREVIOUSLY REPORTED AND HAD AIRCRAFT INSPECTED FOR 'HARD LAND	ING'.  ROD BENT IN FORWARD PORTION.					1	L	7	1 	3O				A3SO    					 
1996031500642	19960315	00642	SO  	1996	3	15	96ZZZX1093       	2	19960226	G	7310		LINE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 3 CYLINDER	B-NUT LOOSE     	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	211TB					421C0903	685024			NR 3 CYLINDER FUEL INJECTOR LINE ATTACH B-NUT, BACKED OFF A DISTRIBUTOR VALVE CAUSING FUEL LEAK.						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996031500643	19960315	00643	NM  	1996	3	15	96ZZZX1094       	1	19960201	G	5102	S272700	GAUGE           		HP25        	RAVEN 	S55   	S55A        	7480402	NM  										BURNER PSI	FAILED          	B			RG1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4226F	448  			HP25116	S55A1035				FAILURE OF PRESSURE GAUGE DURING FLIGHT AS A RESULT OF EXCESSIVE USE OF THE METERING VALVE.  A SERVICE BULLETIN ADDRESSE	S THIS ISSUE, BUT WAS NEVER INSTALLED ON THIS PARTICULAR BURNER.					1	B	0	0 					A15CE   					 
1996031500645	19960315	00645	NM  	1996	3	15	96ZZZX1096       	1	19960131	G	3243	4408B4	CYLINDER        	SCOTT       		CHRIS 	HUSKY 	A1          	221020X	NM  										BRAKE	OUTLET FAILED   	D				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			NM	11	2898D	1823 				1019				AFTER LANDING, PILOT COMPLAINED OF NO LEFT BRAKE.  INSPECTION REVEALED LEFT BRAKE MASTER CYLINDER OUTLET THREAD BOSS HAD	 SEPARATED FROM THE MASTER CYLINDER, DISCONNECTING THE LEFT BRAKE HOSE.					1	H	7	1 	3O			NC	A22NM   					 
1996031500646	19960315	00646	CE  	1996	3	15	96ZZZX1097       	1	19960218	G	2434	DGR3	CONTROL UNIT    			CESSNA	172   	172RG       	2072438	CE  										ALTERNATOR	FAILED          	B			DJFR	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			EA	23	9343D				4310	172RG1128				PILOT REPORTED LOSS OF ELECTRICAL POWER.  AFTER LANDING, UNCOWLED ENGINE AND FOUND THE ACU WAS SMOKED.  TROUBLESHOT AND 	FOUND THE ALTERNATOR WINDINGS OPEN.  INSTALLED A NEW ACU AND INSTALLED A SERVICEABLE ALTERNATOR, PN C611503-0102.  PERFO	RMED GROUND RUN, OPERATIONAL CHECK OF THE ALTERNATOR CHARGING SYSTEM FOUND OK.				1	H	7	1 	3O				3A17    					 
1996031500647	19960315	00647	SO  	1996	3	15	96ZZZX1098       	1	19960215	G	2497		BATTERY CABLE   			PIPER 	PA28  	PA28151     	7102805	SO  										DC GEN SYSTEM	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	32439					287515156				DURING ANNUAL INSPECTION, THE BATTERY TO MASTER SOLENOID, SOLENOID TO STARTER CONTACTOR, BATTERY TO GROUND, AND AIRFRAME	 TO ENGINE GROUND CABLES WERE FOUND FABRICATED FROM INDUSTRIAL GRADE 600 VOLT COPPER TRANSMISSION CABLE.  LOG RECORDS IN	DICATED THESE CABLES WERE INSTALLED IN PLACE OF ORIGINAL ALUMINUM CABLES IN 1989.  PIPER SB 836A SPECIFIES COPPER CABLE 	MEETING MIL-W-22759.			1	L	7	1 	3O			 	2A13    					 
1996031500648	19960315	00648	EA  	1996	3	15	96ZZZX1099       	2	19960128	G	7322	MA3AU	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	757UK	4625 	2552 		CR0665	15280012	L1307415			INSPECTION FOUND CARBURETOR COMPOSITE FLOATS BLACK AND CARBONED.  IN ADDITION, THROTTLE ARM WORN.  TWO PIECE VENTURI WAS	 INSTALLED.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996031500652	19960315	00652	SO  	1996	3	15	96ZZZX1103       	1	19960223	G	5522		SKIN            			PIPER 	PA23  	PA23        	7102302	SO  										ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	3070P				1944607	23988				WHILE INSPECTING LEFT LOWER ELEVATOR SKIN, NOTICED A 2 INCH CRACK.  REMOVED SKIN TO INSPECT INTERNAL COMPONENTS.  ALL OK	.  SKIN HAD CHAFED THROUGH BY RIB IN ELEVATOR RIB LOCATION 19676-00.  REPLACED SKIN ON LOWER ELEVATOR WITH NEW.					1	L	7	2 	3O				1A10    					 
1996031500654	19960315	00654	SO  	1996	3	15	96ZZZX1105       	2	19960126	G	8520	649134	CRNAKSHAFT      			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					NR 2 MAIN	FAILED          	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	03	4691E	975  	325  		B089312N	18503842	175052R			CRANKSHAFT BROKE AFT OF NR 2 MAIN JOURNAL AT OIL TRANSFER TUBE.  PARTS SET TO TCM FOR DETERMINATION OF FAILURE.  CAUSE W	AS DETERMINED TO BE LOW THROUGH-BOLT TORQUE WHICH, IN TURN, CAUSED BEARING TO SHIFT AND CRANKSHAFT TO VIBRATE.  AIRCRAFT	 HAD DEPARTED NORMALLY, WHEN LEVELLING AND SETTING CRUISE CONDITION VIBRATION WAS NOTICED.  WHEN AIRCRAFT TURNED TO RETU	RN TO BASE, ENGINE FAILED.  AIRCRAFT LANDED WITHOUT INCIDENT.  (SEAPLANE).  VAR TYPE CRANKSHAFT.  CUT .010 INCH UNDER.			1	H	7	1 	3O	3	O		3A24    	E5CE				 
1996031500655	19960315	00655	SO  	1996	3	15	96ZZZX1106       	1	19960223	G	7110	4180400	BRACKET         			PIPER 	PA31  	PA31        	7103102	SO  										RT COWL FLAP	ELONGATED HOLE  	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19	2FOR					31157				WHILE INSPECTING RIGHT COWL FLAP FOR EXCESSIVE PLAY, FOUND IMPROPER BOLT USED WHICH ELONGATED HOLES ON ATTACH BRACKETS. 	 REPLACED BRACKETS WITH NEW AND REPLACED BOLTS WITH PROPER CLEVIS PINS AND WASHERS PER PARTS BOOK.					1	L	7	2 	3O				A20SO   					 
1996031500656	19960315	00656	CE  	1996	3	15	96ZZZX1107       	1	19960201	G	3230	1683800821	SWIVEL ROD      			BEECH 	23    	A24R        	1151252	CE  										NLG	BROKEN          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	9710Q					MC66				NOSE WHEEL DID NOT EXTEND NORMALLY.  FOUND NOSE WHEEL SWIVEL ROD BROKEN WHICH DID NOT ALLOW WHEEL TO STRAIGHTEN OUT AS I	T LEFT WHEELWELL.  FOUND ONE CLEVIS, PN 169-820037-3, TIGHTENED TO THE POINT WHERE IT WOULD HARDLY MOVE WITH THE ROD HOO	KED.  THIS TIGHTNESS HAD BEEN LOADING THE BEARING THREAD END TO THE POINT OF BENDING, THEN FINALLY CRACKING.				1	L	7	1 	3O				A1CE    					 
1996031500658	19960315	00658	CE  	1996	3	15	96ZZZX1109       	1	19960221	G	5720	0823400109	BULKHEAD        			CESSNA	402   	402B        	207590P	CE  										TIP TANK ATTACH	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	3131K	6800 				402B0248				DURING A ROUTINE INSPECTION, THE LT WING TIP FUEL TANK ATTACH BULKHEAD WAS FOUND CRACKED.  THE CRACK WAS LOCATED TWO INC	HES OUTBOARD OF THE WING ATTACH BOLT.  SUBMITTER STATED THIS CONDITION GOING UNREPAIRED, WOULD RESULT IN LOSS OF WING TI	P FUEL TANK AND LOSS OF CONTROL OF AIRCRAFT.				1	L	7	2 	3O				A7CE    					 
1996031500659	19960315	00659	SO  	1996	3	15	96ZZZX1110       	1	19960123	G	2710		BUSHING         			STOLAM	RC3   	RC3         	3080202	SO  										CONTROL YOKE	SEIZED          	B		A	HI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	6713K					996				DURING FLIGHT, AILERON TORQUE TUBE BUSHING SEIZED IN CONTROL YOKE TUBE EFFECTIVELY LOCKING AILERONS.  BUSHING AND SHAFT 	ARE BOTH STEEL, RELATIVELY CLOSE FITTING AND HAVE NO MEANS OF LUBRICATION EXCEPT COMPLETE DISASSEMBLY.  SUBMITTER RECOMM	ENDS OWNERS OF THE AIRCRAFT HAVE THIS AREA CHECKED AT THE EARLIEST POSSIBLE TIME.				1	H	7	1 	3O				A769    					 
1996031500660	19960315	00660	SO  	1996	3	15	96ZZZX1111       	1	19960214	G	7810	1961300	COLLECTOR       			PIPER 	PA23  	PA23160     	7102304	SO  										LT EXHAUST	WRAP FAILED     	B		A	XA13	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	4062P					231540				LEFT EXHAUST COLLECTOR INSULATION WRAP DETERIORATED ALLOWING EXHAUST TO MELT EXTERNAL SHROUD AND DAMAGE NACELLE SKIN INT	O WHEELWELL AND TIRE.  SUBMITTER STATED PROPER INSPECTION OF COLLECTOR WOULD HAVE PREVENTED FAILURE.					1	L	7	2 	3O				1A10    					 
1996031500661	19960315	00661	SO  	1996	3	15	96ZZZX1112       	1	19960130	G	5541	40226T100	RUDDER          			AYRES 	S2    	S2RR1820    	0970215	SO  										SPAR WEB	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	61285	844  			1091	R1820036				INSPECTION FOUND CRACKED UPPER RUDDER HINGE AT SPAR WEB AND ALL DOUBLERS.  RIB ALSO BROKEN.  SUBMITTER STATED RUDDER SPA	R BEEF-UP NECESSARY TO PREVENT CRACKING.					1	L	7	1 	4R				A4SW    					 
1996031500662	19960315	00662	EA  	1996	3	15	96ZZZX1113       	2	19960119	G	7414	1068256011	MAGNETO         	BENDIX      		PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					MAG MOUNT	FLANGE FAILED   	H		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			WP	05	2476Y				E109008GR	288511016	RL2277540A			BOTH MOUNTING FLANGES OF THE SINGLE DRIVE DUAL MAGNETO WERE BROKEN.  MAGNETO BACKED OUT OF ENGINE GEAR DRIVE CAUSING ENG	INE TO STOP.  AIRCRAFT LANDED IN OCEAN.					1	L	7	1 	3O	3	O		2A13    	E295				 
1996031500663	19960315	00663	CE  	1996	3	15	96ZZZX1114       	1	19960213	G	2820	S14956	HOSE            			CESSNA	182   	182Q        	2072732	CE  										PILOT DR POST	DETERIORATED    	D		A		K				NONE                    				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		IN	INSP/MAINT     	1			SO	09	95853	6805 				18266656				PILOT COMPLAINED OF FUEL SMELL.  WHILE INVESTIGATING SMELL, FOUND S1495-6 HOSE SEEPING FUEL AT THE AFT DOORPOST PILOT'S 	SIDE NEXT TO A BUNDLE OF WIRES GOING TO THE OVERHEAD LIGHTS.  SUBMITTER SUGGESTS CLOSER ATTENTION BE PAYED TO ALL RUBBER	 HOSES CARRYING FLAMMABLE FLUIDS.				1	H	7	1 	3O			NT	3A13    					 
1996031500664	19960315	00664		1996	3	15	96ZZZX1115       	1	19960219	G	2421	952B9561	WEDGE           	SUNDSTRANDEM	915F7181    															ARMATURE	MISSING         	B	L		MG4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										ARMATURE ROTOR, PN 915F718-1, WAS RECEIVED BY SUNDSTRAND FROM NORTHWEST AIRLINES UNDER WORK ORDER NR 63462300.  SAID ROT	OR HAS BEEN WOUND BY PERSON UNKNOWN WITHOUT 8 EACH BOTTOM WEDGES AS REQUIRED IN THE SUNDSTRAND DRAINING OF THE ABOVE ROT	OR, PN 915F718-1.																	 
1996031500665	19960315	00665	NE  	1996	3	15	96ZZZX1116       	2	19960207	G	7210	310709001	BEARING         								PWA   	118   	PW118A      		NE  					RGB NR 19	SPALLED         	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		8360 			73C029		115608			INSPECTION FOUND REMOTE GEARBOX NR 19 BEARING SPALLED.											4	T			E20NE				 
1996031500666	19960315	00666	NE  	1996	3	15	96ZZZX1117       	2	19960215	G	7210	310924401	BEARING         								PWA   	118   	PW118A      		NE  					RGB NR 15	SPALLED         	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		8486 			RH475		121119			INSPECTION FOUND RGB NR 15 BEARING SPALLED.											4	T			E20NE				 
1996031500667	19960315	00667	EU  	1996	3	15	96ZZZX1118       	2	19960215	G	7250	3053556220	BEARING         								CFMINT	CFM56 	CFM563B2    	13802	EU  					HPT ROTOR	DAMAGED         	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					RR10056		721339			ENGINE WAS REMOVED FROM SERVICE DUE TO IN-FLIGHT SHUT DOWN.  DISASSEMBLY OF THE ENGINE REVEALED THE NR 4 BEARING AREA WI	THIN THE HPT ROTOR REAR SHAFT AND LPT NR 4 BEARING ROTATING SEALS HAD HEAVY DAMAGE.  FURTHER INVESTIGATION IS IN PROCESS	 AT AVIALL.									4	F			E21EU				 
1996031500668	19960315	00668		1996	3	15	96ZZZX1119       	1	19960219	G	2421	952B9561	WEDGE           		915F7181    															ARMATURE	MISSING         	B			MG4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										ARMATURE ROTOR PN 915F718-1 RECEIVED BY SUNDSTRAND FROM DELTA AIRLINES UNDER WORK ORDER NR 63462100.  SAID ROTOR HAS BEE	N WOUND BY PERSON UNKNOWN WITHOUT 8 EACH BOTTOM WEDGES AS REQUIRED IN THE SUNDSTRAND DRAWING OF THE ABOVE PN 915F7181.																		 
1996031500671	19960315	00671	SO  	1996	3	15	96ZZZX1122       	2	19960221	G	7414	S6LN25	MAGNETO         	BENDIX      		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					MAGNETO COIL	CLAMP BROKEN    	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4490F		1489 		B119325DR	747670339				COIL CLAMP FOUND BROKEN AT BEND RADIUS DURING MAGNETO 500-HOUR INSPECTION.  NOTE:  CLAMP HAD WHITE DYKEM MARK PER TCM MA	NUAL PAGE 7-6, PARAGRAPH 7.2.G(D).					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996031500672	19960315	00672	EA  	1996	3	15	96ZZZX1123       	2	19960223	G	7414	D6LN2230	MAGNETO         	BENDIX      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RETARD LEAD	DEFECTIVE       	B			APCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	27343					317752163	RL727061A			MAGNETO CAME INSTALLED ON FACTORY OVERHAULED ENGINE.  WHEN CONNECTING IGNITION HARNESS, NOTED RETARD LEAD COULD BE PUSHE	D ALL THE WAY INTO THE MAG WITHOUT TOUCHING CONTACT FINGER SPRING.  REAR COVER REMOVED TO ADJUST FINGER AND RIGHT POINT 	SET FOUND LOOSE, AND FIVE DEGREE SPLIT BETWEEN LEFT AND RIGHT POINTS.  INSTALLER MADE NECESSARY ADJUSTMENTS AND SECURED 	POINT ATTACHING SCREWS.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996031500673	19960315	00673	CE  	1996	3	15	96ZZZX1124       	1	19960226	G	5711		SPAR            			BEECH 	33    	F33A        	1151425	CE  										CARRY-THROUGH	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8240T	5840 				CE1542				CRACK IN SPAR CARRY-THROUGH STRUCTURE AD 95-04-03 NOT VALID BY SERIAL NUMBER.						1	L	7	1 	3O				3A15    					 
1996031500674	19960315	00674	CE  	1996	3	15	96ZZZX1125       	1	19960227	G	5711		SPAR            			BEECH 	33    	F33A        	1151425	CE  										CARRY-THROUGH	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8112T	5840 				CE1539				CRACK IN SPAR CARRY-THROUGH STRUCTURE AD 95-04-03 NOT VALID BY SERIAL NUMBER.						1	L	7	1 	3O				3A15    					 
1996031500675	19960315	00675	SO  	1996	3	15	96ZZZX1126       	1	19960207	G	2913	765457	SWITCH          	PARKERHANFIN		PIPER 	PA46  	PA46350P    		SO  										UP PRESSURE	DEFECTIVE       	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	09	8167Q	78   				4622031				PILOT COMPLAINED OF LANDING GEAR NOT RETRACTING.  FOUND HYDRAULIC 'UP' PRESSURE SWITCH TO HAVE 165 OHMS RESISTANCE WHICH	 IS PREVENTING A GOOD GROUND FOR THE PUMP.  REPLACED SWITCH.  OPS CHECK OK.  SWITCH WAS REPLACED 78.2 HOURS PREVIOUSLY A	S PART OF PIPER SB 964A.				1	L	7	1 	3O			RT	A25SO   					 
1996031500676	19960315	00676	SO  	1996	3	15	96ZZZX1127       	1	19960220	G	3310	456732	RHEOSTAT        			PIPER 	PA28  	PA28181     	7102807	SO  										COCKPIT LIGHTS	INOPERATIVE     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	91075	120  				288690021				INSTRUMENT FLOOD LIGHTING SYSTEM'S RHEOSTAT FAILED IN 120 HOURS.  PART APPEARS TO HAVE GOTTEN HOT BEFORE FAILURE.						1	L	7	1 	3O				2A13    					 
1996032200001	19960322	00001	CE  	1996	3	22	96ZZZX1128       	1	19960216	G	3242	50820020	DAMPENER        			BEECH 	300   	300BEECH    	1152930	CE  										NLG	EXCESS PLAY     	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09										NLG SHIMMY DAMPENER PISTON HEAD APPEARS TO HAVE EXCESSIVE SIDE PLAY WHICH COULD CAUSE IT TO COCK TO ONE SIDE IN DAMPENER	 HOUSING.					2	L	7	2 	4T				A24CE   					 
1996032200002	19960322	00002	NE  	1996	3	22	96ZZZX1129       	2	19960222	G	7200		ENGINE          			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE7313B    	01518	NE  					FWD FAN GRBOX	OIL LOSS        	B			MUCR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	13	275GC	2316 				6500162	87437			ENGINE EXHIBITED LOW OIL PRESSURE AND ENGINE WAS SHUT DOWN.  AIRCRAFT MADE NORMAL LANDING ON SINGLE ENGINE.  FOUND TWO Q	UARTS OF OIL IN ENGINE.  NORMAL CAPAPCITY (6 QUARTS).  COULD NOT DUPLICATE ANY MALFUNCTIONS DURING TROUBLESHOOTING, BUT 	SUSPECT OIL SYSTEM PRESSURIZED FORCING OIL OUT BREATHER AS THE RESULT OF EITHER BREATHER PRESSURIZING VALVE STICKING OR 	UNSEATED CARBON SEAL.  REPLACED NR 1 AND NR 3 CARBON SEAL AND BREATHER PRESSURIZING VALVE.			2	L	7	2 	4F	4	F		A9NM    	E6WE				 
1996032200003	19960322	00003	CE  	1996	3	22	96ZZZX1130       	1	19960213	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										WING CANTED RIB	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	441GE	5724 				4410116				WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN WING CANTED RIBS.  CRACK EXTENDS FROM THE AFT SIDE OF THE FORWARD SPAR,	 REARWARD ALONG THE BEND RADIUS, 1.0 INCHES.  CESSNA'S REPAIR IS TO STOP-DRILL END OF CRACK AND REINSPECT EACH 200 HOURS	.				1	L	7	2 	3T			RT	A28CE   					 
1996032200004	19960322	00004	CE  	1996	3	22	96ZZZX1131       	1	19960213	G	5712	57222062	RIB             			CESSNA	441   	441         	2076020	CE  										WING CANTED RIB	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	441GE	5724 				4410116				WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN WING CANTED RIBS.  CRACK EXTENDS FROM THE AFT SIDE OF THE FORWARD SPAR,	 REARWARD ALONG THE BEND RADIUS, 1.0 INCHES.  CESSNA'S REPAIR IS TO STOP-DRILL END OF CRACK AND REINSPECT EACH 200 HOURS	 ACCORDING TO THE SUBMITTER.				1	L	7	2 	3T			RT	A28CE   					 
1996032200005	19960322	00005	CE  	1996	3	22	96ZZZX1132       	1	19960215	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										WING CANTED RIB	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8617K	5541 				4410307				WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN WING CANTED RIBS.  CRACKS EXTEND FROM THE AFT SIDE OF THE FORWARD SPAR,	 REARWARD ALONG THE BEND RADIUS, 1.0 INCHES.  CESSNA'S REPAIR IS TO STOP-DRILL THE ENDS OF THE CRACKS AND REINSPECT AT 2	00-HOUR INTERVALS.				1	L	7	2 	3T			RT	A28CE   					 
1996032200006	19960322	00006	CE  	1996	3	22	96ZZZX1133       	1	19960215	G	5712	57222062	RIB             			CESSNA	441   	441         	2076020	CE  										WING CANTED RIB	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8617K	5541 				4410307				WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN WING CANTED RIBS.  CRACKS EXTEND FROM THE AFT SIDE OF THE FORWARD SPAR,	 REARWARD ALONG THE BEND RADIUS, 1.0 INCHES.  CESSNA'S REPAIR IS TO STOP-DRILL THE ENDS OF THE CRACKS AND REINSPECT AT 2	00-HOUR INTERVALS.				1	L	7	2 	3T			RT	A28CE   					 
1996032200007	19960322	00007	CE  	1996	3	22	96ZZZX1134       	1	19960213	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										LT WING CANTED	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	171SP	2430 				4410326				WHILE DOING A PHASE INSPECTION, FOUND A CRACK IN THE LT WING CANTED RIB, PN 5722206-1.  CRACK EXTENDS FROM THE AFT SIDE 	OF THE FORWARD SPAR, REARWARD ALONG THE BEND RADIUS, 1.0 INCH.  CESSNAS' REPAIR IS TO STOP-DRILL THE ENDS OF THE CRACK A	ND REINSPECT EACH 200 HOURS.				1	L	7	2 	3T			RT	A28CE   					 
1996032200008	19960322	00008	WP  	1996	3	22	96ZZZX1135       	2	19960207	G	7260	30702192	GEARSHAFT       		30700934    	BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					TRANSFER GRBOX	FAILED          	D				A				UNSCHED LANDING         				J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			CE	05	1910H	5314 			P4880	258023	P91118			AIRCRAFT WAS IN CRUISE FLIGHT AT 39,000 FEET WHEN MASTER WARNING FLASHER CAME ON AND WOULD NOT CANCEL.  SEVERAL SECONDS 	LATER, RT N2 INDICATION DROPPED TO ZERO FOLLOWED BY SHUT DOWN OF RT ENGINE.  AIRCRAFT LANDED SAFELY WITHOUT INCIDENT.  C	AUSE OF SHUT DOWN WAS FAILURE OF BEVEL GEAR ON VERTICAL GEARSHAFT, PN 3070219-2, INSIDE TRANSFER GEARBOX, PN 3070093-4. 	 THERE IS NO REQUIREMENT TO DISASSEMBLE AND DETAIL INSPECT THE GEARBOX ON CIVILIAN AIRCRAFT.  AN ANALYSIS OF THE FAILED 	GEAR IS BENG PERFORMED BY ALLIED SIGNAL.		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
1996032200010	19960322	00010	CE  	1996	3	22	96ZZZX1137       	1	19960201	G	5711		SPAR            			BEECH 	90    	C90         	1152913	CE  										UNDER FLOOR	FASTENER SHEARED	B			DP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	2FOR					LJ519				INSPECTION FOUND SPAR WITH 2 FASTENERS BROKEN (SHEARED) APPROXIMATELY 14 INCHES FROM CENTER LINE UNDER LEFT SEAT IN COCK	PIT AREA (FORWARD FLANGE).					1	L	7	2 	3T				3A20    					 
1996032200011	19960322	00011	EA  	1996	3	22	96ZZZX1138       	1	19960222	G	2730	27719852	BEARING         	PARKERHANFIN	6007510221  	CNDAIR	CL600 	CL6001A11   	1900302	EA  										ELEVATOR PCU	LOOSE FIT       	B			SH5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	678ML	3695 			0124	1011				UPON INSPECTION, FOUND THREE OUT OF FOUR ELEVATOR P.C.U.'S, ACTUATORS, WITH THE FORWARD BEARING LOOSE.  UPON REMOVAL OF 	THE ACTUATORS, ALL OF THE BEARINGS CITED COULD BE REMOVED WITH LIGHT FINGER PRESSURE.  CMM 27-30-01, PARAGRAPH E, STOP 6	.D STATES BEARINGS SHOULD WITHSTAND 500-INCH POUND AXIAL LOAD.  ALL THREE ACTUATORS WERE REPLACED.  LANDINGS, 2,138.				2	L	7	2 	4F			RT	A21EA   					 
1996032200012	19960322	00012	EA  	1996	3	22	96ZZZX1139       	1	19960222	G	2730	27719852	BEARING         			CNDAIR	CL600 	CL6001A11   	1900302	EA  										ELEVATOR PCU	LOOSE FIT       	B			SH5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	678ML	3695 			0131	1011				UPON INSPECTION, FOUND THREE OUT OF FOUR ELEVATOR P.C.U'S, ACTUATORS, WITH FORWARD BEARINGS LOOSE.  UPON REMOVAL OF THE 	ACTUATORS, ALL OF THE SIGHTED BEARINGS WOULD BE REMOVED WITH LIGHT FINGER PRESSURE.  CMM 27-30-01, PARAGRPAH E, STEP 6.D	 STATES BEARING SHOULD WITHSTAND 500-INCH POUND AXIAL LOAD.  ALL THREE ACTUATORS WERE REPLACED.  LANDINGS, 2,138.				2	L	7	2 	4F			RT	A21EA   					 
1996032200013	19960322	00013	EA  	1996	3	22	96ZZZX1140       	1	19960222	G	2730	27719852	BEARING         			CNDAIR	CL600 	CL6001A11   	1900302	EA  										ELEVATOR PCU	LOOSE FIT       	B			SH5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	678ML	286  				1011				UPON INSPECTION, FOUND THREE OUT OF FOUR ELEVATOR P.C.U.'S, ACTUATORS, WITH FORWARD BEARINGS LOOSE.  UPON REMOVAL OF THE	 ACTUATORS, ALL OF THE SIGHTED BEARINGS COULD BE REMOVED WITH LIGHT FINGER PRESSURE.  LANDINGS, 136.					2	L	7	2 	4F			RT	A21EA   					 
1996032200014	19960322	00014		1996	3	22	96ZZZX1141       	4	19960116	G	3418	600591997	ACCELEROMETER   	SYSTRONDONNR		CNDAIR	CL600 	CL6001A11   	1900302	EA  										STALL WARNING	FAILED          	B			SH5R	O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			NE	03	1045X				1348	1038				FLASHING STALL LIGHTS ON TAKEOFF.  FOUND NR 2 LATERAL ACCELEROMETER STICKING AT MINUS 10.8 VDC.  THIS IS ABOUT THE TENTH	 ACCELEROMETER TO BE CHANGED IN THIS AIRCRAFT.  THIS ACCELEROMETER WAS A CND UNIT FROM THE VENDOR.  REMOVED AND REPLACED	 ACCELEROMETER.				2	L	7	2 	4F			RT	A21EA   					 
1996032200015	19960322	00015	NE  	1996	3	22	96ZZZX1142       	2	19960220	G	8520		CAMSHAFT        			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183092     	52020	NE  					RT ENGINE	FAILED          	E				E				ENGINE SHUTDOWN         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SW	11	59316		715  			18986	BP462185			RIGHT ENGINE STARTED TO BACKFIRE AND RUN ROUGH.  ENGINE WAS SHUT DOWN IN-FLIGHT AND PROP FEATHERED.  UPON TROUBLESHOOTIN	G, FOUND VALVES ON REAR CYLINDERS NOT ACTUATING.  SUSPECT BROKEN CAM GEAR.  ENGINE WAS REMOVED FOR REPAIR AND A SERVICEA	BLE ENGINE WAS INSTALLED.				2	L	7	2 	4R	4	R		A669    	5E4				 
1996032200016	19960322	00016	EA  	1996	3	22	96ZZZX1143       	1	19960221	G	2432	117BC1021	CONTROL BOARD   			CNDAIR	CL600 	CL600*      		EA  										BATTERY CHARGER	MISMANUFACTURED 	B			SH5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03					932					BATTERY CHARGER MFG BY URDC DEFECTIVE.  INCORRECTLY INSTALLED TRANSISTORS ON THE CONTROL BOARD.  Q1 WAS INSTALLED INCORR	ECTLY.  SUBMITTER STATED ABOUT A 30 PERCENT FAILURE RATE FROM STOCK ON THESE CONTROL BOARDS.					2	L	7	2 	4F			RT	A21EA   					 
1996032200017	19960322	00017	EA  	1996	3	22	96ZZZX1144       	1	19960221	G	2432	117BC1021	CONTROL BOARD   			CNDAIR	CL600 	CL600*      		EA  										BATTERY CHARGER	MISMANUFACTURED 	B			SH5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03					933					BATTERY CHARGER MFG BY URCD DEFECTIVE.  INCORRECT INSTALLATION OF TRANSISTORS ON THE CONTROL BOARD.  Q5 WAS INSTALLED IN	CORRECTLY.  THERE IS ABOUT A 30 PERCENT FAILURE RATE FROM STOCK ON THESE CONTROL BOARDS.					2	L	7	2 	4F			RT	A21EA   					 
1996032200018	19960322	00018	NE  	1996	3	22	96ZZZX1145       	2	19960221	G	7260		GEARBOX         			BOEING	747   	747SP09     	1384903	NM  	PWA   	JT9   	JT9D7A      	52054	NE  					NR 1 ENGINE	WORN            	D				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	4522V					22805	P695756			FEBRUARY 21, 1996, CI-641, HKG/BKK.  NR 1 ENGINE SHUT DOWN DUE TO OIL QUANTITY DROP TO ZERO AND OIL PRESSURE 20 PSI, WIN	DMILL AT FL 390 7 MINS MINUS 59 DEGREES CELSIUS.  GROUND CHECK FOUND MAIN GEAR BOX WORN.  NR 1 ENGINE CHANGED.					2	L	7	4 	4F	4	F		A20WE   	E20EA				 
1996032200019	19960322	00019	NM  	1996	3	22	96ZZZX1146       	1	19960227	G	2915	V25W712077501	VALVE           			ISRAEL	1125  	1125        		NM  										HYD RESERVOIR	DEFECTIVE       	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	19	705MA	4320 				011				UPON GEAR RETRACTION, BOTH HYDRAULIC PUMP AMBER LIGHTS AND HYDRAULIC LEVEL AMBER LIGHT ILLUMINATED.  FLIGHT WAS ABORTED 	AND AIRCRAFT RETURNED TO BASE AIRPORT.  ON GEAR EXTENSION BY NORMAL PROCEDURES, ALL LIGHTS EXTINGUISHED.  WHEN GEAR WAS 	DOWN AND LOCKED, FOUND AIR RELEASE VALVE AT TOP OF MAIN RESERVOIR NOT SEATED ALLOWING FLUID TO VENT OVERBOARD.  RECOMMEN	D IAI TO LOOK AT AFFECTED PART DESIGN FOR A MORE RELIABLE SEAL.			2	L	7	2 	4F			RT	A16NM   					 
1996032200020	19960322	00020	EU  	1996	3	22	96ZZZX1147       	1	19960208	G	5751	AK11A501	AILERON         			BAC   	111   	111419EP    	1480280	EU  										LT AILERON TOP	DELAMINATED     	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5751	8543 			VH015	BAC120				WHILE C/W AD 67-19-02, FOUND DELAMINATION ON TOP AFT AREA OF LEFT AILERON.  TWO AREAS OF APPROXIMATELY 2 INCHES BY 5 INC	HES WERE FOUND.  AILERON WAS REPAIRED IAW STRUCTURAL REPAIR MANUAL AND RE-BALANCED.					2	L	7	2 	4F				A5EU    					 
1996032200021	19960322	00021		1996	3	22	96ZZZX1148       	4	19960201	G	3410	LMD6004P	BUSS MODULE     			BEECH 	1900  	1900D       	1154162	CE  										BM 72	PIN DEFECT      	B			PAIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	995WS	98   				UE175				BOTH TRANSPONDERS AND BOTH ENCODERS WERE INTERMITTENTLY REPORTING INCORRECT ALTITUDE ABOVE 14,700 FEET DUE TO PIN 1 OF B	M-72 BEING INTERMITTENTLY OPEN ON BUSS MODULE.  BOTH GRAY CODE INFORMATION IS PARALLELED AT BUSS MODULES WHICH, IF ANY O	NE PIN WOULD OPEN, IT WOULD HAMPER BOTH TRANSPONDERS MODE 'C' READ-OUT FROM EITHER ENCODER.  REPLACED BM-72 BUSS MODULE 	TO REPAIR PROBLEM.  RECOMMEND GRAY CODE LINES BE ISOLATED WITH RELAY SWITCHING TO FURTHER PROVIDE DUAL ISOLATION.			2	L	7	2 	4T			RT	A24CE   					 
1996032200025	19960322	00025		1996	3	22	96ZZZX1152       	1	19960207	G	4920	304071	GEAR            	SUNDSTRANDEM	T62T40C8D1  															APU GRBOX	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	2FOR	399  			SPE925285					APU RECEIVED AND AN INVESTIGATION CONDUCTED DUE TO OIL CONTAMINATION AND HARD TO ROTATE.  UPON DISASSEMBLY OF THE GEARBO	X ASSEMBLY, PN 160192-100, SN 5002-1206, THE INTERNAL GEAR WAS FOUND CRACKED AND SPLIT IN THREE PLACES FROM THE BASE TO 	THE HOLES.  ALL THREE BEARINGS, PN 9524301, WERE SPINNING IN THE CARRIER HOUSING ASSY.  THE PINION SHAFT, PN 44647-0, DI	D NOT SHEER, BUT THE TEETH WERE GROUND OFF.  THE COVER DRAIN, PN 32896-1, WAS BENT/MANGLED AND THE BOTTOM THIRD WAS GROU	ND OFF.  SUBMITTER STATED CAUSE IS UNKNOWN AT THIS TIME.															 
1996032200027	19960322	00027	EU  	1996	3	22	96ZZZX1154       	1	19960226	G	5520	DHS1465200	BOLT            			BRAERO	1000  	BAE1251000  	1500287	EU  										LT ELEV HINGE	WRONG LENGTH    	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	100U					NA1001				DURING A RECENT 2,400 HOUR-INSPECTION, THE LT ELEVATOR UPPER MID-ATTACH HINGE SEAL BOLTS WERE REPLACED WITH 5 EACH, DHS 	1465-2DD, PER MOD 253410A DRAWING.  AT 84 HRS FROM INSP DURING A PILOT PREFLT CHECK, A BINDING, AND SUBSEQUENT INSP REVE	ALED AT EXTREME AFT FLT SURFACE MOVEMENT, 5 BOLTS ARE MAKING CONTACT WITH ELEV PLATE SEAL, PN 25-9TP27-5.  NOTIFICIATION	 SENT TO RCJ CUSTOMER SUPPORT, AND REPAIR DESIGN OFFICE WITH DETAILS OF FINDINGS.  THEIR DETERMINATION WAS THE SEAL PLAT	E IS REPAIRABLE BY BLENDING AND SMOOTHING DAMAGED PROFILE AND REPLACEMENT OF SCREWS WITH 5 EACH, PN DHS 1465-1, 1/2 DD (	SHORTER).	2	L	7	2 	4F			RT	A3EU    					 
1996032200028	19960322	00028	GL  	1996	3	22	96ZZZX1155       	2	19960124	G	7250	6878426	NOZZLE          								ALLSN 	250C  	250C20      	03013	GL  					2ND STAGE TURB	DEFECTIVE       	B		A	XZNR	A				UNSCHED LANDING         				J	W		WARNING INDICATION        	INADEQUATE Q C            		CR	CRUISE         	1			WP	07			27   		X25103		CAE830145			THE NR 2 TURBINE NOZZLE EXPERIENCED A NR 2 BLADE TIP PATH SEPARATION IN-FLIGHT.  THE PILOT REPORTED A 30 DEGREE RISE IN 	TOT AND RETURNED TO THE MAINTENANCE BASE.  VENDOR'S ENGINEERING DEPARTMENT DETERMINED THE METAL SPRAY APPLICATION PROCES	S WAS THE PRIMARY CAUSE OF THE FAILURE.  MODIFICATION OF THE SPRAY PARAMETERS AND THOROUGH TESTING HAS PRODUCED A MORE R	ELIABLE COATING.  ALL NOZZLES FROM THE SUSPECT LOT HAVE BEEN RECALLED FOR RE-APPLICATION OF THE METAL SPRAY FOR BLADE TI	P PATH RESTORATION.							3	U			E4CE				 
1996032200029	19960322	00029	GL  	1996	3	22	96ZZZX1156       	2	19960221	G	7323	23054628	TUBE ASSY       			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					SCROLL-TO-FILTER	MISMANUFACTURED 	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	5238C					0151E	CAE835599			IN AN ATTEMPT TO C/W ALLISION CEB-A-1323 INSTALLATION OF NEW SCROLL-TO-PC FILTER TUBE, FOUND NEW TUBE ASSY MISSED FITTIN	G THE FLARES BY .350 INCH.  DISTORTION OR STRETCHING OF THE PC FILTER-TO-GOVERNOR TUBE ASSY WOULD BE NEEDED TO INSTALL T	HE NEW TUBE AS THE FIT OF THE 6848471 TUBE ASSY (ORIGINAL) WAS PERFECT, REINSTALLED IT.  ALSO, THE CEB-A-1323 DOES NOT M	ENTION WHICH END OF THE TUBE GOES TO THE PC FILTER ALTHOUGH IT IS ETCHED ON ONE B-NUT.			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996032200030	19960322	00030	CE  	1996	3	22	96ZZZX1157       	1	19960217	G	5730		SKIN            			CESSNA	500   	550         	2076604	CE  										RT WS 49	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	26621	5077 				5500593				AFTER AIRCRAFT WAS STRIPPED FOR PAINT JOB, SKIN CRACK FOUND ON UPPER RIGHT WING SURFACE AT WS 49.0, CRACK MEASURED 3 INC	HES 'DIAGONALLY' PASSING THROUGH RIVETS THAT ATTACH FLAP BELLCRANK SUPPORT.  ONE-THIRD OF HEAD OF MIDDLE RIVETS SHEARED.	  CESSNA ENGINEERING SUGGESTS THAT FAILURE IS RESULT OF LOWERING FLAPS AT TOO GREAT AN AIRSPEED.				1	L	7	2 	4F				A22CE   					 
1996032200031	19960322	00031		1996	3	22	96ZZZX1158       	4	19960222	G	2211	KCP320	COMPUTER        			BEECH 	90    	C90A        	1152911	CE  										AUTOPILOT	MALFUNCTIONED   	G	L			O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AL	03	2247R				065001803	LJ1352				GLIDESLOPE TRIES TO COUPLE A SIGNAL BEYOND THE PARAMETERS ESTABLISHED IN THE PILOT'S OPERATING HANDBOOK.  WHEN AUTOPILOT	 IS IN THE APPR CPLD MODE, THE GLIDESLOPE SIGNAL DROPS OUT AND COMES BACK, THE AUTOPILOT COMMANDS THE ACFT PITCH UP OR D	OWN TO INTERCEPT THE GLIDESLOPE AT THE CLOSEST POINT.  IT WAS STRESSED REPEATEDLY TO ALLIED SIGNAL THAT DURING ONE PARTI	CULAR APPROACH, THIS ACFT PITCHED UP AND AIRSPEED DROPPED TO 90 KNOTS BEFORE THE PILOT COULD DISENGAGE THE AUTOPILOT AND	 REGAIN NORMAL FLIGHT PROFILE OF THE AIRCRAFT.		1	L	7	2 	3T			RT	3A20    					 
1996032200122	19960322	00122	EU  	1996	3	22	96ZZZX1161       	1	19960217	G	2612		FIRE WIRE       			AEROSP	AS355 	AS355F2     	8680812	EU  										FUEL PUMP	BROKEN          	D				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			EA	03	355DU					5489				DURING APPROACH, NR 1 FIRE LIGHT DIMLY ILLUMINATED THEN EXTINGUISHED.  DURING HOVER, NR 1 FIRE LIGHT DIMLY ILLUMINATED O	NCE MORE AND ON ENGINE SHUT-DOWN, CAME ON FULL BRIGHT.  NO FIRE WITNESSED.  FOUND/REPAIRED BROKEN WIRE TO FIRE DETECTOR 	TO FUEL PUMP STATION.				1	G	7	2 	3U				H11EU   					 
1996032200123	19960322	00123	WP  	1996	3	22	96ZZZX1162       	1	19960220	G	7722	6887761	HARNESS         			HUGHES	369   	369D        	4470706	WP  										TURB TOT	FAILED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		513  		FF0L08	1151D				TURBINE REMOVED FROM AIRCRAFT EARLIER AND REPLACED.  DURING INSPECTION, TOT HARNESS FOUND CRACKED AT ONE OF THE PROBES (	2:30 O'CLOCK POSITION).  PART WAS SCRAPPED.					1	G	7	1 	3U				H3WE    					 
1996032200124	19960322	00124	GL  	1996	3	22	96ZZZX1163       	2	19960223	G	7323	23057870	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	5074R		457  		24622	1151D	CAE880976			PILOT COMPLAINED MANUAL BEEPING WAS REQUIRED FOR TAKEOFF, POWER CHANGES, AND LANDING.  GOVERNOR UNIT REPLACED AND SENT I	N FOR REPAIR.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996032200125	19960322	00125	WP  	1996	3	22	96ZZZX1164       	1	19960208	G	6320	369D25140	BEARING         		369D25100   	HUGHES	369   	369D        	4470706	WP  										M/R XMSN	SPALLED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	5001 	14   		0184	1151D				MAIN ROTOR TRANSMISSION DISASSEMBLED AFTER CHIPS DISCOVERED ON THE CHIP DETECTOR.  BEARING, 369D25140, FOUND HEAVILY SPA	LLED.  REPLACED BEARING.					1	G	7	1 	3U				H3WE    					 
1996032200126	19960322	00126	WP  	1996	3	22	96ZZZX1165       	1	19960220	G	6320	369D25100505	TRANSMISSION    			HUGHES	369   	369D        	4470706	WP  										M/R	MAKING METAL    	B			EOOR	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AL	03	5074R	8534 	2433 		1260044	1151D				PILOT GOT A FLICKER ON M/R TRANSMISSION CHIP LIGHT, THEN IT STAYED OUT.  PILOT CHECKED CHIP PLUG ON LANDING WITH THE LIG	HT STILL OFF AND FOUND SEVERAL LARGE CHIPS ON BOTH PLUGS.  UNIT REMOVED AND RETURNED FOR REPAIR.					1	G	7	1 	3U				H3WE    					 
1996032200127	19960322	00127	WP  	1996	3	22	96ZZZX1166       	1	19960126	G	7920	174H1014	HOSE            			HUGHES	369   	369D        	4470706	WP  										SCAVENGE OIL	LEAKING         	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING ENGINE REMOVAL, THE SCAVENGE OIL HOSE FOUND SET WITH OIL.  SUBSEQUENT INSPECTION FOUND IT WAS LEAKING.  REPLACED 	HOSE.					1	G	7	1 	3U				H3WE    					 
1996032200128	19960322	00128	GL  	1996	3	22	96ZZZX1167       	2	19960101	G	7240	23056130	COMBUSTION LINER			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	BURNED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D	CAE832750			WHILE REMOVING TURBINE, THE COMBUSTION LINER WAS FOUND BURNED, WARPED, AND CRACKED.  PART REPLACED.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996032200129	19960322	00129	WP  	1996	3	22	96ZZZX1168       	1	19960202	G	6320	369D25100505	TRANSMISSION    			HUGHES	369   	369D        	4470706	WP  										M/R	MAKING METAL    	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	5001 	14   		0466	1151D				DURING ANNUAL INSPECTION, CHIPS FOUND ON UPPER CHIP PLUG.  UNIT REMOVED AND SENT FOR REPAIR.						1	G	7	1 	3U				H3WE    					 
1996032200130	19960322	00130	GL  	1996	3	22	96ZZZX1169       	2	19960202	G	7261	6853301	SUMP            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					NR 6-7 BEARING	WARPED          	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	5074R		1436 			1151D	CAE832750			DURING ANNUAL INSPECTION, NR 6 AND NR 7 BEARING SUMP ON THE TURBINE FOUND LEAKING AT THE MATING SURFACE.  SUBSEQUENT INS	PECTION REVEALED FLANGE WAS WARPED.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996032200131	19960322	00131	GL  	1996	3	22	96ZZZX1170       	2	19960211	G	7323	230574869	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	5074R		591  		24657	1151D	CAE832750			DURING RUN-UP, PILOT WAS ADJUSTING ENGINE 'BEEP' AND THE GOVERNOR HESITATED, BUT WHEN AN INCREASE WAS NOTED, IT JUMPED U	P 3 PERCENT TO 4 PERCENT AND WAS NOT A SMOOTH TRANSITION.  PART SENT IN FOR REPAIR.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996032200132	19960322	00132	WP  	1996	3	22	96ZZZX1171       	1	19960220	G	6320	369D25100505	TRANSMISSION    			HUGHES	369   	369D        	4470706	WP  										M/R	SEALS LEAK      	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	4571V	5927 	1927 		U0296	490487D				TRANSMISSION REMOVED TO REPLACE ALL OIL SEALS DUE TO LEAKING.						1	G	7	1 	3U				H3WE    					 
1996032200133	19960322	00133	NE  	1996	3	22	96ZZZX1172       	1	19960112	G	2910	0711311111	PISTON          			SKRSKY	S76   	S76A        	8143006	NE  										BOOT STRAP	BOLT BROKEN     	B	L		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL	4372 	2872 			760002				DURING SHOP INSPECTION (3,000-HOUR) AND REPAIR AND AFTER UPGRADE TO DASH 104 ASSEMBLY DURING BENCH TESTING, FOUND BOOT S	TRAP PISTON RESTRAINING BOLT (PN MS24678-9) BROKEN AND RETAINER PLATE (PN 0711311-209) DEFORMED DURING DISASSEMBLY OF MO	DULE.  THESE DAMAGED PARTS WERE REPLACED DURING UPGRADE OF MODULE ASSY FROM DASH 103 TO DASH 104 CONFIGURATION.				1	G	7	2 	3U				H1NE    					 
1996032200134	19960322	00134	WP  	1996	3	22	96ZZZX1173       	1	19960126	G	3610	369H9014981	TUBE            			HUGHES	369   	369D        	4470706	WP  										SCAVENGE AIR	CRACKED         	B		A	EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING INSPECTION OF SCAVENGE AIR SYSTEM, THE AIR TUBE WAS FOUND CRACKED ABOUT 4 INCHES ABOVE THE SOLENOID.  IT APPEARS 	TO HAVE HAD WATER FROZEN AT THAT POINT AS THE TUBE IS EXPANDED ALONG THE CRACKED AREA AND RECENT TEMPERATURES HAVE BEEN 	SUB-ZERO.				1	G	7	1 	3U				H3WE    					 
1996032200436	19960322	00436	CE  	1996	3	22	96ZZZX1246       	1	19960228	G	5551	12326232	BRACKET         		1232600201  	CESSNA	210   	P210N       	2073454	CE  										LT HORIZ STAB	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	677PC	2789 				P21000677				DURING ROUTINE INSPECTION, LT HORIZONTAL STABILIZER ATTACH BRACKET REINFORCEMENT WAS FOUND CRACKED .50 INCH IN THE LOWER	 LT RADIUS.  CESSNA SERVICE INFORMATION LETTER SE84-17R1 CALLS FOR A REPETITIVE 100-HOUR INSPECTION OF THIS AREA, BUT IT	 DOES NOT LIST THE 'P210' WHICH HAS THE SAME COMPONENT PARTS AND PINS INSTALLED.  REPLACED BRACKETS WITH NEW STYLE P/N 1	232624-1 BRACKET.			1	H	7	1 	3O				3A21    					 
1996032200437	19960322	00437	SO  	1996	3	22	96ZZZX1247       	1	19960301	G	2410	7848300	STRUT           			PIPER 	PA28  	PA28161     	7102803	SO  										ALTERNATOR BRKT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	8198Z					288216146				ALTERNATOR TO STARTER STRUT CRACKED.  SUSPECT DUE TO ENGINE VIBRATION.  SUBMITTER NOTICED THIS ON 4 OTHER AIRCRAFT ON MO	RE THAN ONE OCCASION.  ALSO, ELONGATED BOLT HOLES THROUGH ALTERNATOR BRACKETS ON THE SAME (PA28-161) TYPE AIRCRAFT.  THE	SE ELONGATED HOLES CANNOT BE DETECTED WITHOUT REMOVING THE BRACKETS AND ALTERNATOR FROM AIRCRAFT.  SUBMITTER RECOMMENDS 	INSPECTING BY REMOVAL EVERY 100 HOURS.			1	L	7	1 	3O				2A13    					 
1996032200439	19960322	00439	CE  	1996	3	22	96ZZZX1249       	1	19960204	G	2913	98812011	SOLENOID        		12808021    	CESSNA	210   	T210L       	2073449	CE  										POWER PACK	DEFECTIVE       	D	S	A		O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SW	99	381DS	2924 				21060255				ON FEBRUARY 4, 1996, GEAR-UP LANDING WAS MADE.  NO INJURIES.  ALL LANDING GEAR DOORS OPENED, BUT GEAR FAILED TO EXTEND B	Y ELECTRIC HYDRAULIC OR MANUAL HYDRAULIC.  FAILURE CAUSED BY SOLENOID RESIDUE BUILD UP ON SHAFT OF SOLENOID PREVENTED OP	ERATION OF MANIFOLD ON POWER PACK.  RESIDUE PROBABLY DRIED HYDRAULIC FLUID.  AFTER SOLENOID SHAFT CLEANED, LANDING GEAR 	OPERATED BOTH BY ELECTRIC HYDRAULIC PACK AND MANUAL HYDRAULIC PUMP SATISFACTORILY.  SUGGEST CLEANING/INSPECTING SOLENOID	 SHAFT AT 1,000-HOUR INTERVALS.		1	H	7	1 	3O				3A21    					 
1996032200440	19960322	00440	SO  	1996	3	22	96ZZZX1250       	1	19960226	G	2510	440785	LATCH           	AMERICANSFTY		PIPER 	PA28  	PA28151     	7102805	SO  										SEAT BELT	DEFECTIVE       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	41287	6300 				287415159				ON ANNUAL INSPECTION, FOUND LATCH NOT POSITIVELY ENGAGING.  ON FURTHER INSPECTION, FOUND ONE SMALL SECONDARY SPRING MISS	ING (PILOT'S BELT).  OTHER BELT LATCH FOUND SMALL SECONDARY SPRING DAMAGED (COPILOT'S).  CHECKED SEAT BELT LATCHES IN RE	ST OF FLEET, ALL USED AMERICAN SAFETY LATCHES WITH MANY OF SAME PART NUMBER OR DESIGN.  SUBMITTER RECOMMENDS CLOSER INSP	ECTION ON LATCHES.			1	L	7	1 	3O				2A13    					 
1996032200442	19960322	00442	GL  	1996	3	22	96ZZZX1252       	1	19960223	G	3222		STRUT           			AMTR  	LANCAR	LANCAIR     	05616TS	GL  										NLG	COLLAPSED       	H				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CE	05	444WH					100				DURING TAKEOFF AND GEAR RETRACTION, THE FREE CASTERING NOSE GEAR TURNED SIDEWAYS, AND, THEREFORE UPON EXTENSION, THE NOS	E GEAR STAYED SIDEWAYS AND COLLAPSED ON ROLL-OUT.  THE SUSPECT CAUSE IS NO SELF-CENTERNG MECHANISM IN THE STRUT ASSY.  A	N ADDITIONAL CAUSE FOR COLLAPSED GEAR ARE GEAR SUPPORT LINKS, P/N 6M027-4, FOR NOT HAVING ENOUGH STRENGTH FOR SHARP TURN	ING FORCES.			1	L	7	1 	3O			RT	EXPA1L71					 
1996032200444	19960322	00444	EA  	1996	3	22	96ZZZX1254       	2	19960227	G	8530	60828	PISTON PIN PLUG 			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CYLINDER	FAILED          	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			GL	19	99263	25   				17276424	L1141539A			PISTON PIN PLUG, PN 60828, IS NOT CORRECT, BUT LOCATION IS CORRECT.  ENGINE OVERHAULED 24.8 HRS AGO.  COMPLAINT OF LOSS 	OF POWER.  GROUND RUN SEEMED OK, NOTHING OBVIOUS.  COMPRESSION TEST FOUND LOW COMPRESSION ON ONE CYLINDER.  BORESCOPED A	ND COULD SEE METAL FLAKES.  UPON DISASSEMBLY OF CYLINDER, FOUND SMALL ALUMINUM BALL IN CHEWED UP PISTON.  AREA FROM NR 2	 RING DOWN TO TOP OF PISTON PIN, HOLE WORN AWAY.  SECTION OF BOTTOM RING BROKE OFF.  CYLINDER WALL IN THIS AREA DAMAGED.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996032200445	19960322	00445	CE  	1996	3	22	96ZZZX1255       	1	19960131	G	5321	04150211	FLOOR PANEL     			CESSNA	150   	152         	2071835	CE  										COCKPIT	CORRODED        	B			VT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	48650	77   				15280926				DURING ROUTINE INSPECTION, CARPET WAS REMOVED.  FOUND CORROSION ON FLOOR.  FURTHER INSPECTION REVEALED CORROSION ON 5 OF	 6 FUEL LINES UNDER FLOOR AND ALONG DOOR SILLS AND DOOR POST.  SUBMITTER SUSPECTS IMPROPER FLAMEPROOFING ON CARPET CAUSE	D CORROSION.				1	H	7	1 	3O			NT	3A19    					 
1996032200447	19960322	00447	SO  	1996	3	22	96ZZZX1257       	1	19960222	G	5312	62413000	FITTING         			PIPER 	PA32  	PA32260     	7103206	SO  										AFT BLKHD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	3927W	3961 				32874				THESE FITTINGS ARE MADE OF STEEL, DISSIMILAR METAL CORROSION HAD STARTED BETWEEN SKIN AND FITTINGS WHERE THEY ATTACH.  O	N TWO OF FITTINGS, SEVERAL RIVETS HAD POPPED THE HEADS OFF WHERE ATTACHED TO SKIN.  THESE FITTINGS ATTACH FORWARD OF THE	 AFT BULKHEAD WHERE THE STABILATOR ATTACH BRACKETS ARE.				1	L	7	1 	3O				A3SO    					 
1996032200448	19960322	00448	SO  	1996	3	22	96ZZZX1258       	1	19960222	G	5312	62413010	FITTING         			PIPER 	PA32  	PA32260     	7103206	SO  										AFT BLKHD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	3927W	3961 				32874				THESE FITTINGS ARE MADE OF STEEL, DISSIMILAR METAL CORROSION HAD STARTED BETWEEN SKIN AND FITTINGS WHERE THEY ATTACH.  O	N TWO OF FITTINGS, SEVERAL RIVETS HAD POPPED THE HEADS OFF WHERE ATTACHED TO SKIN.  THESE FITTINGS ATTACH FORWARD OF THE	 AFT BULKHEAD WHERE THE STABILATOR ATTACH BRACKETS ARE.				1	L	7	1 	3O				A3SO    					 
1996032200449	19960322	00449	SO  	1996	3	22	96ZZZX1259       	1	19960222	G	5312	62414000	FITTING         			PIPER 	PA32  	PA32260     	7103206	SO  										AFT BLKHD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	3927W	3961 				32874				THESE FITTINGS ARE MADE OF STEEL, DISSIMILAR METAL CORROSION HAD STARTED BETWEEN SKIN AND FITTINGS WHERE THEY ATTACH.  O	N TWO OF FITTINGS, SEVERAL RIVETS HAD POPPED THE HEADS OFF WHERE ATTACHED TO SKIN.  THESE FITTINGS ATTACH FORWARD OF THE	 AFT BULKHEAD WHERE THE STABILATOR ATTACH BRACKETS ARE.				1	L	7	1 	3O				A3SO    					 
1996032200450	19960322	00450	SO  	1996	3	22	96ZZZX1260       	1	19960222	G	5312	62414010	FITTING         			PIPER 	PA32  	PA32260     	7103206	SO  										AFT BLKHD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	3927W	3961 				32874				THESE FITTINGS ARE MADE OF STEEL, DISSIMILAR METAL CORROSION HAD STARTED BETWEEN SKIN AND FITTINGS WHERE THEY ATTACH.  O	N TWO OF FITTINGS, SEVERAL RIVETS HAD POPPED THE HEADS OFF WHERE ATTACHED TO SKIN.  THESE FITTINGS ATTACH FORWARD OF THE	 AFT BULKHEAD WHERE THE STABILATOR ATTACH BRACKETS ARE.				1	L	7	1 	3O				A3SO    					 
1996032200451	19960322	00451	CE  	1996	3	22	96ZZZX1261       	1	19960217	G	3260	15410382	DOWNLOCK STOP   			CESSNA	337   	337E        	2075721	CE  										RT MLG	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	1275M	1738 				33701275				DURING ANNUAL INSPECTION, BOTH RT AND LT LANDING GEAR DOWNLOCK STOPS FOUND LOOSE ON MLG STRUTS.  STOPS ARE ATTACHED WITH	 ONE BOLT EACH AND, ALSO, BONDED WITH EPOXY TO INBD LOWER L/E OF STEEL STRUT.  LOCK PIN, ACTUATED HYDRAULICALLY, PIVOTS 	UP AGAINST WEDGE ON BOTTOM OF STOP TO LOCK GEAR IN DOWN POSITION.  EPOXY BOND SEPARATES STOP FROM STRUT, USUALLY DUE TO 	RUST BETWEEN PARTS.  IF STOP ROTATES FORWARD DUE TO FAILED BOND, IT CAN BE DISTORTED BY GEAR MOVEMENT AND STRUT CANNOT L	OCK.		1	H	7	2 	3O				A6CE    					 
1996032200452	19960322	00452	CE  	1996	3	22	96ZZZX1262       	1	19960217	G	3260	15410381	DOWNLOCK STOP   			CESSNA	337   	337E        	2075721	CE  										LT MLG	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	1275M	1738 				33701275				DURING ANNUAL INSPECTION, BOTH RT AND LT LANDING GEAR DOWNLOCK STOPS FOUND LOOSE ON MLG STRUTS.  STOPS ARE ATTACHED WITH	 ONE BOLT EACH AND, ALSO, BONDED WITH EPOXY TO INBD LOWER L/E OF STEEL STRUT.  LOCK PIN, ACTUATED HYDRAULICALLY, PIVOTS 	UP AGAINST WEDGE ON BOTTOM OF STOP TO LOCK GEAR IN DOWN POSITION.  EPOXY BOND SEPARATES STOP FROM STRUT, USUALLY DUE TO 	RUST BETWEEN PARTS.  IF STOP ROTATES FORWARD DUE TO FAILED BOND, IT CAN BE DISTORTED BY GEAR MOVEMENT AND STRUT CANNOT L	OCK.		1	H	7	2 	3O				A6CE    					 
1996032200453	19960322	00453	CE  	1996	3	22	96ZZZX1263       	1	19960301	G	5347		SEAT RAIL       			CESSNA	182   	182P        	2075816	CE  										COCKPIT	MISREPAIRED     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	9894E	500  				18263955				UPON ANNUAL INSPECTION, FOUND SEAT RAILS INSTALLED BY PERSONS UNKNOWN.  RAILS WERE INSTALLED WITH MANY MIS-SIZED RIVETS 	AND SEVERAL WERE NOT BUCKED.  TWO FLANGES OR RIBS WERE SMASHED OUT OF PLACE DUE TO PUNCHING OUT THE OLD RIVETS, AND NOT 	REPAIRED.  UPON REMOVAL OF SEAT RAILS, FOUND EXTENSIVE CORROSION UNDERNEATH RAILS.  REMOVED CORROSION, APPLIED ZINC CHRO	MATE AND INSTALLED RAILS.  RIBS WERE STRAIGHTENED OUT.			1	H	7	1 	3O			NT	TA13    					 
1996032200454	19960322	00454	SO  	1996	3	22	96ZZZX1264       	1	19960228	G	2842	550695	TRANSMITTER     			PIPER 	PA31  	PA31350     	7103110	SO  										LT INBD FUEL	DEFECTIVE       	B			FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	41049					318252025				WITH FUEL DRAINED OUT OF LT AND RT INBOARD TANKS, HAD ONE-FOURTH TANK INDICATIONS ON FUEL GAUGES (INBOARD TANK).  FOUND 	INBOARD FUEL SENDER TO BE OUT OF TOLERANCES AT EMPTY AND FULL.  OUTBOARD FUEL TRANSMITTERS WERE REPLACED DUE TO FLOAT WE	AR/DETERIORATION, PN 550-695, MFG PN 6427512.  SUBMITTER SUGGESTS PERIODIC INSPECTION OF FUEL TRANSMITTER FOR FLOAT WEAR	 AND TOLERANCES IS RECOMMENDED.			1	L	7	2 	3O				A20SO   					 
1996032200455	19960322	00455	SO  	1996	3	22	96ZZZX1265       	1	19960228	G	2842	550696	TRANSMITTER     			PIPER 	PA31  	PA31350     	7103110	SO  										RT INBD FUEL	DEFECTIVE       	B			FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	41049					318252025				WITH FUEL DRAINED OUT OF LT AND RT INBOARD TANKS, HAD ONE-FOURTH TANK INDICATIONS ON FUEL GAUGES (INBOARD TANK).  FOUND 	INBOARD FUEL SENDER TO BE OUT OF TOLERANCES AT EMPTY AND FULL.  OUTBOARD FUEL TRANSMITTERS WERE REPLACED DUE TO FLOAT WE	AR/DETERIORATION, PN 550-695, MFG PN 6427512.  SUBMITTER SUGGESTS PERIODIC INSPECTION OF FUEL TRANSMITTER FOR FLOAT WEAR	 AND TOLERANCES IS RECOMMENDED.			1	L	7	2 	3O				A20SO   					 
1996032200456	19960322	00456	CE  	1996	3	22	96ZZZX1266       	1	19960206	G	3220	2316	BRACKET ASSY    	SCOTT       		CESSNA	170   	170B        	2072306	CE  										TAIL GEAR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	4373B	3759 			3200	26717				WHILE REMOVING AIRCRAFT FROM HANGAR, TAIL WHEEL SWIVELED AND ASSY SEPARATED FROM BRACKET AND SPRING ASSY.  AFTER INVESTI	GATING, FOUND BOLT IN THE BRACKET ASSY WAS PARTLY FRACTURED AND THE SUDDEN JOLT FROM THE SWIVEL BROKE THE TAIL WHEEL ASS	Y OFF THE AIRCRAFT.  SUBMITTER SUGGESTS ALL TAIL WHEEL BRACKET ASSYS BE REMOVED, INSPECTED, AND DYE-PENETRANT BOLTS FOR 	CRACKS.			1	H	7	1 	3O				A799    					 
1996032200457	19960322	00457	SO  	1996	3	22	96ZZZX1267       	2	19960228	G	8550	CH48109	OIL FILTER      	CHAMPION    	641639      	BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      		SO  					LT/RT ENGINES	MISINSTALLED    	B			ERY2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	123ZM	22   				TH1768	676924			DURING FIRST ROUTINE ENGINE OIL AND FILTER CHANGE, THE OIL FILTER WAS EXTREMELY DIFFICULT TO REMOVE FROM THE ADAPTER ASS	Y.  SUBMITTER SUSPECTS CAUSE FOR PROBLEM:  NO LUBRICATION AT INSTALLATION AS ENGINE WAS READIED FOR SERVICE.  SUGGEST FO	LLOW RECOMMENDED PROCEDURE PER MFG.  SAME PROBLEM ENCOUNTERED WITH RIGHT ENGINE.  (RIGHT ENGINE SN 676926, SAME TOTAL TI	ME).			1	L	7	2 	3O	3	O		3A16    	E3SO				 
1996032200458	19960322	00458	CE  	1996	3	22	96ZZZX1268       	1	19960212	G	2701	12708441	CABLE ASSY      			CESSNA	210   	T210M       	2073451	CE  										FWD YOKE TUBE	BOUND YOKE      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6276B	2600 				21062730				UPON PREPARATION FOR TAKEOFF, PILOT CHECKED CONTROLS AND YOKE LOCKED UP ON NEAR TO A FULL FORWARD POSITION.  ROLL WAS OK	.  UPON INSPECTION, YOKE ELECTRICAL RIBBON ASSY FOUND BOUND IN 2 OF THE 4 YOKE TUBE ROLLERS.  PHYSICAL FORCE COULD NOT D	ISLODGE.  ROLLERS REMOVED AND REINSTALLED AFTER CLEARING RIBBON ASSY.				1	H	7	1 	3O				3A21    					 
1996032200459	19960322	00459	CE  	1996	3	22	96ZZZX1269       	1	19960201	G	3230	08411011	FITTING         		08411004    	CESSNA	310   	310L        	2074230	CE  										LT MLG	FAILED          	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	09	2201F					310L0001				LEFT MLG END FITTING (SIDE BRACE LOCK) FAILED ON LANDING.  THE LEFT MLG COLLAPSED ON LANDING DUE TO THE GEAR NOT BEING A	BLE TO LOCK PROPERLY.  IT APPEARS THE THREADED ROD PORTION OF THE END FITTING FAILED UNDER STRESS LOAD.					1	L	7	2 	3O				3A10    					 
1996032200460	19960322	00460	CE  	1996	3	22	96ZZZX1270       	1	19960226	G	2460	26700045	BUS BAR         		261318118   	CESSNA	208   	208         	2073702	CE  										PANEL ASSY	DEFECTIVE       	B			VT3R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	09	9617F					20800107				DURING FLIGHT IN IMC ATC NOTED MODE 'C' INOPERATIVE.  CONFIRMED PROBLEM, ALSO FOUND RT FUEL QUANTITY FUEL FLOW AND ITT I	NOPERATIVE.  DURING DESCENT, PROBLEM DISAPPEARED.  EXTENSIVE TROUBLESHOOTING REVEALED WIRE WHICH JUMPS TO THE BUS THAT C	ONTROLS THE INTERMITTENT SYSTEMS WAS LOOSE AT THE CIRCUIT BREAKER.  FOUND THE THREADS IN THE TAB WHICH THE JUMPER ATTACH	ES TO WERE DAMAGED.  THE SCREW WOULD 'BOTTOM OUT' AND GET TIGHT, BUT THE CONNECTOR WAS FREE TO ROTATE CAUSING INTERMITTE	NT CONDITION.		1	H	7	1 	3T			NT	A37CE   					 
1996032200461	19960322	00461	CE  	1996	3	22	96ZZZX1271       	1	19960207	G	8010	08504691	RELAY           	CUTLERHAM   		CESSNA	404   	404CESSNA   	2075901	CE  										STARTER	FAILED          	B			APCR	K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			NM	01	48SA	11133				4040417				LEFT ENGINE STARTER BURNED UP DUE TO RUNNING CONTINUOUSLY DUE TO RELAY STICKING.  POOR DIAGNOSIS CAUSED STARTER TO BE RE	PLACED WITHOUT REPLACING SOLENOID.  SECOND STARTER FAILED ALSO.  SAME CONDITION.  RELAY REPLACED WITH SECOND NEW STARTER	.  SUBMITTER SUGGESTS MANUFACTURERS INSTALL WARNING LIGHT IN STARTER POWER CIRCUIT TO ALERT PILOT WHEN UNIT IS ENERGIZED	.  PILOT CANNOT TELL IF POWER IS REACHING STARTER MOTOR, OTHERWISE.			1	L	7	2 	3O				A25CE   					 
1996032200462	19960322	00462	CE  	1996	3	22	96ZZZX1272       	1	19960229	G	2750	169524071101	ACTUATOR TUBE   		D151003     	BEECH 	76    	76          	1153005	CE  										FLAP ACTUATOR	DISCONNECTED    	B			UC2R	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	19	6632J	4321 				ME337				PILOT REPORTED FLAPS WOULD NOT EXTEND IN-FLIGHT.  EXAMINED FLAP SYSTEM AND FOUND TUBE ACTUATOR DISCONNECTED FROM ACTUATO	R ASSEMBLY.  RECONNECTED TUBE AND FUNCTIONAL CHECK OF FLAPS SATISFACTORY.  SUBMITTER SUGGESTS A METHOD BE DEVELOPED BY B	EECH TO SAFETY TUBE ACTUATOR TO ACTUATOR ASSEMBLY.				1	L	7	2 	3O				A29CE   					 
1996032200463	19960322	00463		1996	3	22	96ZZZX1273       	4	19960229	G	3432	096107402	CAPACITOR       	KING        	KI525       															G.S. IND	SHORED          	B			PG2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11					32625					SUBMITTER STATED THEY HAVE OBSERVED MANY KI525 AND KI525A GLIDESLOPE POINTERS' POSITION AFFECTED BY THE AMOUNT OF FLAG C	URRENT THAT THE INDICATOR RECEIVES FROM THE GLIDESLOPE RECEIVER.  IN ALL CASES, C110 HAS BEEN DETERMINED TO BE THE SUSPE	CT CAUSE OF THIS PROBLEM.  DUE TO SIZE AND CIRCUITRY CONSTRAINTS, THE ONLY FIX IS TO REPLACE THE CAPACITOR WITH THE ORIG	INAL PART.  SUBMITTER STATED THERE WERE 5 INCIDENTS IN 1995, 1 SO FAR IN 1996.																 
1996032200464	19960322	00464	SO  	1996	3	22	96ZZZX1274       	1	19960220	G	2430	688169	SWITCH          			PIPER 	PA28  	PA28161     	7102803	SO  										BAT MASTER	FAILED          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	15	96PF	9951 				288116266				BATTERY HALF ROCKER OF MASTER SWITCH BROKE IN HALF ALLOWING ELECTRICAL CONTACT BAR TO DROP OUT OF SWITCH BODY RESULTING 	IN COMPLETE LOSS OF ELECTRIC POWER.  THIS FAILURE OCCURRED DURING GROUND OPERATIONS AT NIGHT.  CAUSE OF FAILURE COULD NO	T BE DETERMINED AS PILOT MISPLACED BROKEN PIECES.  SUBMITTER SUGGESTS A CLOSE VISUAL INSPECTION OF CENTER AREA OF ROCKER	 FOR FINE CRACKS AT 100-HOUR INTERVALS FOR AIRCRAFT HAVING A HIGH NUMBER OF HOURS.			1	L	7	1 	3O				2A13    					 
1996032200466	19960322	00466		1996	3	22	96ZZZX1276       	4	19960228	G	2562	BP1045	BATTERY PACK    	MERL        	EBC102A     															ELT	DEFECTIVE       	B			SF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										THIS ELT CAME ON BY ITSELF IN THE GARAGE OF CUSTOMER.  FAA/CAP WENT TO CUSTOMER'S HOUSE AND FOUND ELT GOING ON.  FAA REP	 REMOVED ONE SCREW FROM BACK COVER OF ELT AND THE ELT SHUT OFF.  REP PUT SCREW BACK IN AND ELT WENT OFF AGAIN.  ELT AND 	BATTERY WIRES WERE ATTACHED PROPERLY WITH WIRE NUTS.  UPON INVESTIGATION AT EBC PLANT, FOUND MERL BATTERY HAD AN EXPOSED	 TAB-WELD SPOT AND THE SCREW FROM THE BACK COVER, WHEN INSTALLED, HIT THE SPOT AND SHORTED THE ELT ON.																 
1996032200467	19960322	00467	CE  	1996	3	22	96ZZZX1277       	1	19960131	G	6120	C299506B0104	CONTROL ASSY    			CESSNA	172   	R172K       	2072431	CE  										GOVERNOR	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	7585X	2    				R1723334				INSTALL NEW CONTROL CABLE ASSY AS SUPPLIED BY CESSNA AIRCRAFT.  INSTALLED AND RIGGED PER CESSNA R172K SM AND UNDER THE S	UPERVISION OF A CESSNA FIELD SERVICE ENGINEER.  ALL OPS CHECK OK ON GROUND.  RUN-UPS CHECK OK.  FLOWN FOR 2.0 HRS, NO AT	TEMPT MADE TO ADJUST OR MOVE CONTROL WHILE IN-FLIGHT.  UPON RETURN TO GROUND, GOVERNOR CONTROL CABLE ASSY FOUND FROZEN S	OLID.  CURRENT CABLE (CABLE NR 4) AWAITING REINSPECTION BY FIELD ENGINEER.			1	H	7	1 	3O				3A17    					 
1996032200468	19960322	00468	WP  	1996	3	22	96ZZZX1278       	1	19960228	G	3210	PC531014	CLAMP           			RHNFLU	EXT300	EXTRA300    	05616CV	WP  										MLG LOWER	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	05	300EM					044				LOWER LANDING GEAR CLAMP SEPARATED FORM UPPER CLAMP AT REAR ATTACH POINT (BOLT WAS STILL INTACT).  SUSPECT CAUSE:  FATIG	UE CRACKS ALONG THE INSIDE EDGE OF THE BOXED AFT ATTACHING BOLT AREA OF LOWER CLAMPS (BOTH LT AND RT SIDES AFFECTED) WHI	CH CAUSED AFT SECTION OF LOWER CLAMP TO TEAR AWAY FROM UPPER CLAMP UPON LANDING.  RECOMMEND DISASSEMBLY AND INSPECTION (	N.D.T.) OF LOWER CLAMP BRACKETS AT 500-HOUR INTERVALS OR HARD LANDINGS.  (DYE PENETRANT INSPECTION NEEDED).  TT ON AIRCR	AFT, 629.4 HOURS.		1	M	7	1 	3O			NC	EXPA1M71					 
1996032200469	19960322	00469	SO  	1996	3	22	96ZZZX1279       	2	19960215	G	7322	30764	FLOAT           		103965121   	CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470L       	17026	SO  					CARBURETOR	DETACHED        	B			KC2R	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	03					4000457					ENGINE QUIT IN-FLIGHT ONCE AND ON THE GROUND ONCE.  FOUND ONE PONTOON OF FLOAT ASSEMBLY HAD BROKEN OFF.  DATE CODE STAMP	ED IN FLOAT BRACKET IS 884.  IT IS A FACTORY MANUFACTURED FLOAT; NOT A PMA.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996032200470	19960322	00470	CE  	1996	3	22	96ZZZX1280       	1	19960201	G	2730	12604757	CONTROL CABLE   			CESSNA	210   	T210K       	2073447	CE  										ELEVATOR UP	WORN            	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	8209M	6468 				21059209				DURING ANNUAL INSPECTION, FOUND ELEVATOR 'UP' CABLE WORN THROUGH AT PULLEY JUST FORWARD OF GEARBOX.  PULLEY WAS NOT TURN	ING DUE TO BRACKET THAT HOLDS PULLEY WAS INSTALLED AT AN ANGLE.  IT APPEARS BRACKET WAS INSTALLED THAT WAY FROM FACTORY.	  LOG BOOKS SHOW NO DATA ON CABLE OR BRACKET REPLACEMENT.  CABLE WAS WORN FROM PULLEY AND PULLEY WAS NOT WORN AT ALL.  C	ABLE HAD 2 STRANDS LEFT HOLDING IT.			1	H	7	1 	3O			 	3A21    					 
1996032200471	19960322	00471	CE  	1996	3	22	96ZZZX1281       	1	19960228	G	2710	05232193	SUPPORT         			CESSNA	182   	182A        	2072704	CE  										AIL BELLCRANK	ELONGATED HOLES 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	6362B	3500 				34262				DURING ANNUAL INSPECTION, FOUND RT AILERON BELLCRANK BOLT HOLES ON THE SUPPORT CHANNELS TO BE ELONGATED.  ONLY THE PIVOT	 HOLES WERE BAD, NOT THE STOP-PIN HOLES.  SUSPECT CAUSED BY NOT INSTALLING CONTROL LOCK WHEN ACFT ON GROUND.					1	H	7	1 	3O			NT	3A13    					 
1996032200472	19960322	00472	CE  	1996	3	22	96ZZZX1282       	1	19960228	G	2710	05232194	SUPPORT         			CESSNA	182   	182A        	2072704	CE  										AIL BELLCRANK	ELONGATED HOLES 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	6362B	3500 				34262				DURING ANNUAL INSPECTION, FOUND RT AILERON BELLCRANK BOLT HOLES ON THE SUPPORT CHANNELS TO BE ELONGATED.  ONLY THE PIVOT	 HOLES WERE BAD, NOT THE STOP-PIN HOLES.  SUSPECT CAUSED BY NOT INSTALLING CONTROL LOCK WHEN ACFT ON GROUND.					1	H	7	1 	3O			NT	3A13    					 
1996032200473	19960322	00473	EA  	1996	3	22	96ZZZX1283       	1	19960119	G	2810	TA12C60W	CLAMP           			DHAV  	DHC7  	DHC7102     	2802708	EA  										MAIN/AUX BAY	DETERIORATED    	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	59AG					59				WHILE PERFORMING MAINTENANCE IN THE FUEL BAY, FOREIGN MATERIAL WAS SEEN IN THE RESIDUAL FUEL.  INSPECTION OF THE MATERIA	L REVEALED IT TO BE RUBBBER IN COMPOSITION.  INVESTIGATION REVEALED THE CLAMPS INSTALLED WERE TA12C60W AND THE CUSHION W	AS DISTORTED AND DETERIORATED.  THE CLAMPS WERE PART OF THE BRANSON FUEL MOD AND WERE IDENTIFIED AS DSC-162-32 AS SUPPLI	ED BY BRANSON.  CLAMPS WERE REPLACED WITH DSC-162-32-1, AND FUEL BAYS WERE CLEANED OF ALL DEBRIS.  REF. STC NR ST00180DE	.		2	H	7	4 	4T				A20EA   					 
1996032200930	19960322	00930		1996	3	22	96ZZZX1328       	4	19960114	G	3424	214075244001	GYRO            			BELL  	212   	212         	1181420	SW  										TURN RATE	FAULTY          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	705H		101  		1992B	35088				TURN NEEDLE STAYS IN THE CENTER ALL THE TIME.  IT WILL NOT FUNCTION.						1	G	7	1 	4U				H4SW    					 
1996032900214	19960329	00214	CE  	1996	3	29	96ZZZX1329       	1	19960228	G	2844	10138901823	SWITCH          			BEECH 	200   	B200        	1152922	CE  										RT ENG FUEL	FAILED          	B			FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	93ME	2194 			5410	BB1345				RT ENGINE FUEL PRESSURE SWITCH FAILED IN OPEN POSITION.  TT:  2,193.9 HRS.  SUBMITTER STATED THIS IS THE 2ND SWITCH TO F	AIL IN FLEET.					1	L	7	2 	4T				A24CE   					 
1996032900215	19960329	00215	CE  	1996	3	29	96ZZZX1330       	1	19960229	G	5711		SPAR CAP        			CESSNA	500   	500CESSNA   	2076602	CE  										WS 34-61	CORRODED        	B			SI6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	500TM	4705 				5000112				WHEN PERFORMING SL500-28-08, FOUND THE SPAR CAP TO BE CORRODED REQUIRING REPAIR.  THE SUSPECTED CAUSE WAS LOOSE SEALANT 	AND POOR PRIMER ADHESION.  SUBMITTER RECOMMENDS C/W SL500-28-10.					1	L	7	2 	4F				A22CE   					 
1996032900216	19960329	00216	CE  	1996	3	29	96ZZZX1331       	1	19960229	G	5711		SPAR CAP        			CESSNA	500   	500CESSNA   	2076602	CE  										WS 34-61	CORRODED        	B			SI6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	501KG	6046 				5000279				WHEN PERFORMING SL500-28-08, FOUND LOWER SPAR CAP CORRODED REQUIRING REPAIR.  THE SUSPECT CAUSE WAS LOOSE SEALANT AND PO	OR PRIMER ADHESION.  RECOMMEND C/W SL500-28-10.					1	L	7	2 	4F				A22CE   					 
1996032900217	19960329	00217	CE  	1996	3	29	96ZZZX1332       	1	19960229	G	5711		SPAR CAP        			CESSNA	500   	500CESSNA   	2076602	CE  										WS 34-61	CORRODED        	B			SI6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	700MP	6482 				5000198				WHEN PERFORMING SL500-28-08, FOUND SPAR CAP CORRODED REQUIRING REPAIR.  THE SUSPECT CAUSE WAS LOOSE SEALANT AND POOR PRI	MER ADHESION.  RECOMMEND C/W SL500-28-10.					1	L	7	2 	4F				A22CE   					 
1996032900218	19960329	00218	CE  	1996	3	29	96ZZZX1333       	1	19960228	G	2844	10138901823	SWITCH          			BEECH 	200   	B200        	1152922	CE  										LT ENG FUEL	FAILED          	B			FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	700WP	2132 			3050	BB1313				LT ENGINE FUEL PRESSURE SWITCH FAILED IN OPEN POSITION.  TT:  2,131.8 HRS.						1	L	7	2 	4T				A24CE   					 
1996032900219	19960329	00219		1996	3	29	96ZZZX1334       	4	19960209	G	3457	1283800781	ANTIICE SYSTEM  			BEECH 	MU300 	400BEECH    		CE  										LT STAB LE	FAILED          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3196N	153  			BT0035	RK96				LEFT HORIZONTAL STABILIZER ANTI-ICE FAILED DUE TO INOPERATIVE OVERTEMP SENSOR.  INSTALLED NEW LEADING EDGE ASSY.  BEECH 	KIT 128-4014-5, INSTALLED AT ACFT TT, 911.2 HOURS.  CURRENT ACFT TT, 1,064.6 HRS.					2	H	7	2 	4F			RT	A16SW   					 
1996032900220	19960329	00220	CE  	1996	3	29	96ZZZX1335       	1	19960201	G	2435	303001380	BRUSH           	LUCAS       	23048016    	BEECH 	200   	200BEECH    	1152920	CE  										NR 1 GENERATOR	EXCESS WORN     	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CE	03	6689D		982  		12768	BB623				AIRCRAFT EXPERIENCED NR 1 GENERATOR DROP OFF LINE AT NIGHT WITH HEATS ON.  UNABLE TO RESET.  APPROXIMATELY 30 MINUTES LA	TER, NR 2 GENERATOR DROPPED OFF LINE.  UNABLE TO RESET.  DIVERTED TO VFR AIRPORT AND LANDED.  FOUND NR 2 GENERATOR BRUSH	ES WORN PAST LIMITS AND THEY SHOWED SIGNS OF HEAT DAMAGE TO BRUSH LEADS.  NR 1 GENERATOR BRUSHES WORN TO LIMITS, BUT WAS	 ABLE TO RESET ON GROUND AND IT DID WORK.			1	L	7	2 	4T				A24CE   					 
1996032900221	19960329	00221	CE  	1996	3	29	96ZZZX1336       	1	19960201	G	2435	303001380	BRUSH           	LUCAS       	23048016    	BEECH 	200   	200BEECH    	1152920	CE  										NR 2 GENERATOR	EXCESS WORN     	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CE	03	6689D		982  		15623	BB623				AIRCRAFT EXPERIENCED NR 1 GENERATOR DROP OFF LINE AT NIGHT WITH HEATS ON.  UNABLE TO RESET.  APPROXIMATELY 30 MINUTES LA	TER, NR 2 GENERATOR DROPPED OFF LINE.  UNABLE TO RESET.  DIVERTED TO VFR AIRPORT AND LANDED.  FOUND NR 2 GENERATOR BRUSH	ES WORN PAST LIMITS AND THEY SHOWED SIGNS OF HEAT DAMAGE TO BRUSH LEADS.  NR 1 GENERATOR BRUSHES WORN TO LIMITS, BUT WAS	 ABLE TO RESET ON GROUND AND IT DID WORK.			1	L	7	2 	4T				A24CE   					 
1996032900222	19960329	00222		1996	3	29	96ZZZX1337       	4	19960223	G	3457	071015450200	ANTENNA         	KING        	KA91        	BEECH 	200   	200BEECH    	1152920	CE  										GPS	FAILED          	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	200BE	830  			12187	BB832				GPS ANTENNA FAILED AFTER ONLY 2 YEARS IN USE.  UNIT IS USED WITH KING KLN90.						1	L	7	2 	4T				A24CE   					 
1996032900223	19960329	00223	CE  	1996	3	29	96ZZZX1338       	1	19960229	G	3260	1EN18	SWITCH          			LEAR  	35    	35LEAR      	5170600	CE  										LT MLG DOWNLK	FAILED          	D				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	07	8040A					048				LEFT MAIN GEAR, NO DOWN AND LOCK INDICATION.  REMOVED AND REPLACED SWITCH, OPS OK.						2	L	7	2 	4F				A10CE   					 
1996032900224	19960329	00224	CE  	1996	3	29	96ZZZX1339       	1	19960220	G	3220	23420117	GEAR ASSY       			LEAR  	35    	35A         	5170602	CE  										NLG	MALFUNCTION     	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	07	118DA	14251			2162	081				NOSE GEAR UNSAFE LIGHT ON.  REMOVED AND REPLACED NOSE GEAR ASSY.  CYCLED GEAR.  OPS CHECK GOOD.						2	L	7	2 	4F				A10CE   					 
1996032900225	19960329	00225	CE  	1996	3	29	96ZZZX1340       	1	19960223	G	3230	582212716	ANGLE           			CESSNA	441   	441         	2076020	CE  										UPLOCK HOOK	CRACKED         	B	S		WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	88GW	7929 				4410187				DURING PHASE INSPECTION, FOUND CRACK IN OUTBOARD END OF RT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE THAT ATTACHES TO FORWARD 	WING SPAR WEB.  CRACK ORIGINATES AT OUTBOARD HILOK HOLE AND EXTENDS FOR A TOTAL LENGTH OF 1.5 INCHES.					1	L	7	2 	3T			RT	A28CE   					 
1996032900226	19960329	00226	EA  	1996	3	29	96ZZZX1341       	2	19960227	G	7414	1051676	CAPACITOR       	BENDIX      	S6RN23      	HILLER	UH12  	UH12B       	4360110	WP  	FRNKLN	6AV335	6V335B      	27020	EA  					RT MAG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4785C	7    			430043	312				WHEN RT MAG SELECTED DURING ENGINE RUN-UP CHECK, ENGINE FAILED.  OBSERVED EXCESSIVE SPARKING AND POINT WEAR (7 HRS SINCE	 NEW).  ENGINE RAN NORMALLY AFTER REPLACEMENT OF CAPACITOR AND POINT ADJUSTMENT.  SUSPECT MANUFACTURING DEFECT OF PMA CA	PACITOR.				1	G	7	1 	3O	3	O		6H2     	E244				 
1996032900227	19960329	00227		1996	3	29	96ZZZX1342       	4	19960304	G	3421	5040045901	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT ATTITUDE	DEFECTIVE       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	32936	18   			25017	36115				ATTITUDE GYRO DEFECTIVE.  REPLACED WITH NEW FIXTURE.						1	G	7	2 	4U				H4SW    					 
1996032900228	19960329	00228	GL  	1996	3	29	96ZZZX1343       	3	19960219	G	6114		HUB ASSY        			UNIVAR	415   	415C        	0420302	NM  						MCAULY	1A90	1A90CF      	GL  	PROP	FAILED          	D				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CE	07	99224	1500 				1847				HUB CRACKED ALONG KEYWAY AND PROGRESSED UP PROP FLANGE TO WITHIN .50 INCH OF BOLT HOLE.  ASSUME THIS ALLOWED THE HUB TO 	BECOME LOOSE AND LET NUT, PN 21202, LOOSEN AND WEAR ON SAFETY PIN, PN AN 392-11, CAUSING IT TO BREAK AND ALLOW NUT TO UN	SCREW AND LET PROP AND HUB ASSY TO DEPART AIRPLANE.				1	L	7	1 	3O				A718    		5	N	P842	 
1996032900229	19960329	00229	CE  	1996	3	29	96ZZZX1344       	1	19960130	G	5730	3701301213	SKIN            			RKWELL	NA265 	NA26580     	7630108	CE  										TOP LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	221PH	6083 				38049				DURING REPAINT OF AIRCRAFT WITH SUPER CRITICAL WING, FOUND EXISTING SEALANT CRACKED AND DETERIORATED.  AT CUSTOMER REQUE	ST, REMOVED SEALANT AND FOUND ALUMINUM SKIN SURFACE AT EDGE OF OVERLAY CORRODED BEYOND MANUFACTURER'S ALLOWABLE LIMITS. 	 ONE AREA APPEARED TO GO UNDERNEATH ONE OVERLAY.  REMOVED OVERLAY AND FOUND PREVIOUS DELAMINATION REPAIR AREA WHICH CONT	AINED DRILL MARKS IN TOP EXTERIOR SKIN SURFACE DEEPER THAN .003 INCH (MAXIMUM DEPTH).   SUSPECT AGE AND DETERIORATION OF	 SEALANT ALLOWED CONTAMINATION AND EVENTUAL CORROSION TO EXPOSED SKIN SURFACES.  DRILL MARKS RESULT FROM PREVIOUS DELAMI	NATION REPAIR OF SKIN OVERLAY.	2	L	7	2 	4F				A2WE    					 
1996032900230	19960329	00230	CE  	1996	3	29	96ZZZX1345       	1	19960130	G	5730	3701301214	SKIN            			RKWELL	NA265 	NA26580     	7630108	CE  										TOP RT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	221PH	6083 				38049				DURING REPAINT OF AIRCRAFT WITH SUPER CRITICAL WING, FOUND EXISTING SEALANT CRACKED AND DETERIORATED.  AT CUSTOMER REQUE	ST, REMOVED SEALANT AND FOUND ALUMINUM SKIN SURFACE AT EDGE OF OVERLAY CORRODED BEYOND MANUFACTURER'S ALLOWABLE LIMITS. 	 ONE AREA APPEARED TO GO UNDERNEATH ONE OVERLAY.  REMOVED OVERLAY AND FOUND PREVIOUS DELAMINATION REPAIR AREA WHICH CONT	AINED DRILL MARKS IN TOP EXTERIOR SKIN SURFACE DEEPER THAN .003 INCH (MAXIMUM DEPTH).   SUSPECT AGE AND DETERIORATION OF	 SEALANT ALLOWED CONTAMINATION AND EVENTUAL CORROSION TO EXPOSED SKIN SURFACES.  DRILL MARKS RESULT FROM PREVIOUS DELAMI	NATION REPAIR OF SKIN OVERLAY.	2	L	7	2 	4F				A2WE    					 
1996032900231	19960329	00231	WP  	1996	3	29	96ZZZX1346       	1	19960125	G	2913	938951	PUMP            			DOUG  	DC3   	DC3C        	3021457	WP  										RT ENG HYD	FAILED          	H			BG7P	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	115Z	1608 			A029	33567				ENGINE DRIVEN HYDRAULIC PUMP FAILED DURING ENGINE START.  THE ROTARY PISTON-TYPE PUMP FAILED DURING ENGINE START.  THE R	OTARY PISTON-TYPE PUMP SEIZED; THUS, SHEARING ITS DRIVE SHAFT.  METAL PARTICLES FROM THE PUMP'S VANE SENT DOWNSTREAM IN 	THE HYDRAULIC SYSTEM WERE CAUGHT BY THE HYD FILTER.  LINES WERE FLUSHED CLEAN AND NEW FILTER INSTALLED.  FIRST REPLACEME	NT PUMP (YELLOW TAGGED AS OVERHAULED) WOULD NOT BUILD UP PRESSURE DUE TO STICKING HIGH-BYPASS VALVE.  THE SECOND UNIT (A	LSO TAGGED AS OVERHAULED), OPERATED AT TOO HIGH A PRESSURE.  THE THIRD UNIT (FACTORY NEW), FINALLY OPS CHECKED OK.		2	L	7	2 	4R				A669    					 
1996032900232	19960329	00232	CE  	1996	3	29	96ZZZX1347       	1	19960201	G	5711	45A10209007	SPAR CAP        			BEECH 	MU300 	400BEECH    		CE  										LT WING	CRACKED         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07	3240J	559  				RK92				WHILE TROUBLESHOOTING LT WING FUEL LEAK, FOUND A 40-INCH CRACK IN LT SPAR AT CHANNEL OF UPPER SPAR CAP.  FURTHER INVESTI	GATION REVEALED THIS AIRCRAFT HAD BEEN SUBJECT TO A HARD LANDING.  PHASE 1 HARD LANDING INSPECTION WAS COMPLETED ON THE 	FUSELAGE AND A PHASE 2 HARD LANDING INSPECTION WAS COMPLETED ON THE WINGS.  SUBMITTER RECOMMENDS INSPECTION OF WING SPAR	S IN CONJUNCTION WITH HARD LANDING INSPECTION AND IF CRACK IS SUSPECTED, PERFORM NDI.			2	H	7	2 	4F			RT	A16SW   					 
1996032900233	19960329	00233	EU  	1996	3	29	96ZZZX1348       	1	19960215	G	2130	5511172251	TRANSFORMER     		6331166395  	AIRBUS	320   	A320231     	3930325	EU  										PRESS SYS	DEFECTIVE       	B	L		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					4919					TR1 TRANSFORMER EXHIBITS FRACTURE SOLDER JOINTS.  MAXIMUM SOLDER CONNECTS IS 11.  THIS CONDITION CAUSES AN INTERMITTENT 	FAILURE OF THE AIRCRAFT PRESSURIZATION SYSTEM.  SPECIFICALLY, THIS CONDITION WILL CAUSE ONE OR BOTH OF THE ELECTRONIC AC	TUATOR BOXES WHICH DRIVE THE OUTFLOW GATE TO SHUT DOWN.				2	L	7	2 	4F			RT	A28NM   					 
1996032900234	19960329	00234	EU  	1996	3	29	96ZZZX1349       	1	19960226	G	2130		TRANSFORMER     		6331166395  	AIRBUS	320   	A320231     	3930325	EU  										PRESS SYS	DEFECTIVE       	B	L		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		8371 			4471					TR1 TRANSFORMER EXHIBITS FRACTURE SOLDER JOINTS.  MAXIMUM SOLDLER CONNECTIONS IS 11.  THIS CONDITION CAUSES AN INTERMITT	ENT FAILURE OF THE AIRCRAFT PRESSURIZATION SYSTEM.  SPECIFICALLY, THIS CONDITION WILL CAUSE ONE OR BOTH OF THE ELECTRONI	C ACTUATOR BOXES WHICH DRIVE THE OUTFLOW GATE TO SHUT DOWN.				2	L	7	2 	4F			RT	A28NM   					 
1996032900235	19960329	00235	CE  	1996	3	29	96ZZZX1350       	1	19960201	G	5711	45A10209007	SPAR CAP        			BEECH 	MU300 	400BEECH    		CE  										LT WING	CRACKED         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07	3240J	559  				RK92				WHILE TROUBLESHOOTING LT WING FUEL LEAK, FOUND 40-INCH CRACK IN LT SPAR AT CHANNEL OF UPPER SPAR CAP.  FURTHER INVESTIGA	TION REVEALED AIRCRAFT HAD A HARD LANDING.  PERFORMED PHASE 1 HARD LANDING INSPECTION ON FUSELAGE AND PHASE 2 INSPECTION	 ON WINGS TO THIS POINT.  SUBMITTER RECOMMENDS INSPECTING WING SPARS ON HARD LANDING INSPECTION AND IF SUSPECT CRACK, PE	RFORM NDI.			2	H	7	2 	4F			RT	A16SW   					 
1996032900236	19960329	00236	EU  	1996	3	29	96ZZZX1351       	1	19960228	G	5510		BULKHEAD        			AVIONS	R2160 	R2160       	0960101	EU  										STAB BRG BRKT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	216RN					C200				VERTICAL CRACKS FOUND INTERCONNECTING ALL FOUR BOLT HOLES DRILLED IN THE AFT STABILATOR BULKHEAD TO WHICH THE STABILATOR	 BEARING BRACKET ATTACHES TO ON THE RT SIDE.  SUSPECT CAUSE:  EXCESSIVE AIR LOADS ON THE STABILATOR DUE TO AEROBATIC MAN	EUVERS (HAMMER HEADS AND SNAP ROLLS), AND AFT BULKHEAD BEING OF INADEQUATE STRENGTH TO ABSORB STRESSES.  SUBMITTER RECOM	MENDS PERIODIC INSPECTIONS OF AFT BULKHEAD EVERY 100 HOURS OR MORE IF AEROBATIC OR REINFORCEMENT OF BULKHEAD (REFER TO F	ORM 337).  TT ON AIRCRAFT, 3600 HOURS.		1	L	7	1 	3O			RT	A48EU   					 
1996032900237	19960329	00237		1996	3	29	96ZZZX1352       	4	19960305	G	2562	BP1026	BATTERY         	MERL        		BEECH 	58    	58          	1152740	CE  										ELT	MISMFG          	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	05	65FS					TH1084				AN ATTEMPT TO REPLACE A BATTERY PACK IN AN ELT TRANSMITTER FAILED.  EXAMINATION REVEALED THE PACK WAS TOO WIDE AND WOULD	 NOT FIT THE HOUSING OF THE ELT.  ANOTHER WAS ORDERED AND FIT OK.  MANUFACTURER WAS MERL INC., OF CONNECTICUT.					1	L	7	2 	3O				3A16    					 
1996032900238	19960329	00238		1996	3	29	96ZZZX1353       	4	19960222	G	2211	065001803	COMPUTER        		KCP320      	PIPER 	PA42  	PA42720     	7104212	SO  										GLIDESLOPE	FAULTY          	B	L	A	CE4R	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AL	03	2247R				3271	425501005				ON 2-21-96, SUBMITTER MADE A CONFERENCE CALL WHICH INVOLVED ALLIED SIGNAL TO ESTABLISH COHERENT DIALOG CONCERNING GLIDES	LOPE COUPLING PROBLEM.  RESOLVED 2 PROBLEMS MAY EXIST.  NR 1, GLIDESLOPE TRIES TO COUPLE A SIGNAL BEYOND PARAMETERS ESTA	BLISHED IN PILOT'S OPERATING HANDBOOK.  NR 2, WHEN AUTOPILOT IS IN APPR CPLD MODE AND GLIDESLOPE SIGNAL DROPS OUT AND CO	MES BACK, AUTOPILOT COMMANDS ACFT PITCH UP OR DOWN TO INTERCEPT GLIDESLOPE AT CLOSEST POINT.  IT WAS STRESSED REPEATEDLY	 TO ALLIED SIGNAL THAT DURING ONE APPROACH, ACFT PITCHED UP AND AIRSPEED DROPPED TO 90 KNOTS BEFORE PILOT COULD DISENGAG	E AUTOPILOT AND REGAIN NORMAL FLIGHT PROFILE OF ACFT.	1	L	7	2 	4T				A23SO   					 
1996032900239	19960329	00239	GL  	1996	3	29	96ZZZX1354       	3	19960308	G	6114	D7015C93	HUB             													MCAULY	3AF32C	3AF32C93    	GL  	NR 1 SOCKET	CRACKED         	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15								790274		DURING INSPECTION, HUB FOUND CRACKED UNDER WELCH PLUG ON NR 1 BLADE SOCKET.  HUB HAS BEEN SCRAPPED.																5	C	P22EA	 
1996032900241	19960329	00241	CE  	1996	3	29	96ZZZX1356       	1	19960201	G	5610		WINDOW          			LEAR  	35    	35A         	5170602	CE  										COCKPIT LT	OUT OF SPEC     	B			DP2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	2MIL					1008				INSPECTED WINDSHIELD FOR PROPER THICKNESS.  THICKNESS RANGE FELL BELOW LEAR NDT MANUAL SPECIFICATIONS.  MINIMUM ALLOWED 	THICKNESS 1.00 INCH.  TESTED PART THICKNESS .097 INCH.  SUBMITTER STATED RANDOM INSPECTION OF WINDSHIELD IN AREAS REQUES	TED.				2	L	7	2 	4F				A10CE   					 
1996032900244	19960329	00244	NE  	1996	3	29	96ZZZX1359       	2	19960209	G	7230		BLADE           			RKWELL	NA265 	NA26560     	7630106	CE  	PWA   	JT12  	JT12A8      	52042	NE  					COMPRESSOR	RUB             	B			JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	401MS		1210 			30617	P673149NB			DURING INSPECTION OF ENGINE, SN P673149NB, A CRACKED INLET GUIDE VANE PROMPTED REMOVAL OF INLET CASE FOR REPAIRS.  WITH 	CASE REMOVED, A COMPRESSOR BLADE RUB, WHICH RESULTED IN DETERIORATION TO A STATOR, WAS NOTED AND REPORTED.  AUTHORIZATIO	N WAS RECEIVED FROM CUSTOMER TO DISASSEMBLE COMPRESSOR FOR FURTHER INVESTIGATION.  UPON DISASSEMBLY OF COMPRESSOR, SEVER	E CORROSION NOTED ON STEEL COMPONENTS.  A CORROSION INSPECTION AND SUBSEQUENT COMPRESSOR OVERHAUL PER P&WA, SB 1508R16, 	WAS INITIATED.		2	L	7	2 	4J	4	J	RT	A2WE    	1E9				 
1996032900245	19960329	00245	NE  	1996	3	29	96ZZZX1360       	2	19960209	G	7250	566101	BLADE           			RKWELL	NA265 	NA26560     	7630106	CE  	PWA   	JT12  	JT12A8      	52042	NE  					1ST STG TURBINE	OVERLAP         	B	L		JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	401MS		1210 			30617	P673152NB			DUE TO CORROSION DMG DISCOVERED ON RT ENG, CUSTOMER ELECTED TO DISASSEMBLE LT ENG FOR CORROSION INSP, & SUBSEQUENT COMPR	 OVERHAUL PER P&WA.  UPON DISASSEMBLY OF COMPR, SEVERE CORROSION NOTED ON STEEL COMPONENTS.  CORRRODED STEEL DISK REJECT	ED.  CUSTOMER ELECTED TO REPLACE LIFE LIMITED DISKS IN BOTH ENGS TO ALLOW ENGS TO CONTINUE IN SERV TO 3000 HRS TBO; THUS	, PROMPTING TO ACCESS TURB AREA ON ENG, SN P673152NB, TO REPLACE LIFE LIMITED TURB DISKS.  TURB BLADES REMOVED DUE TO RE	PLACMENT OF LIFE LIMITED TURB DISK.  NOTED 76 1ST STG TURB BLADES SHOWED SIGNS OF SHROUD OVERLAP, DISPLACED METAL & META	L SEPARATION IN NOTCH SURFACE OF SHROUD.  14 TURB BLADES PREV INSTALLED IN NEW COND (TT: ZERO) & 2 WERE SERVICEABLE.	2	L	7	2 	4J	4	J	RT	A2WE    	1E9				 
1996032900332	19960329	00332	CE  	1996	3	29	96ZZZX1361       	1	19960118	G	2710	551426049	CABLE GUARD     			CESSNA	500   	560CESSNA   	2076750	CE  										AIL CONT SECTOR	CHAFED          	B		A	EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	141AQ	2409 				5600141				THE AILERON LOWER SECTOR PLATE, CABLE GUARD, WAS CHAFING INTO THE PULLEY BOLT OF THE EMERGENCY GEAR BRACKET (PN 6514160-	109) FROM INSUFFICIENT CLEARANCE.  SHIMMED AILERON SECTOR UPWARD TO PROVIDE CLEARANCE.					2	L	7	2 	4F			RT	A22CE   					 
1996032900335	19960329	00335	CE  	1996	3	29	96ZZZX1364       	1	19960220	G	7603	C800741	BALL JOINT      		1223890413  	BEECH 	2000  	2000        	1152000	CE  										RT ENG PWR LEVER	DISCONNECTED    	D		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	214JB	1083 				NC14				RIGHT ENGINE POWER LEVER CABLE BALL JOINT ASSEMBLY CAME UNSCREWED AT RT ENGINE DISCONNECTING RT POWER LEVER CONTROL TO R	T ENGINE DURING FLIGHT.  THE COLLAR OF BALL JOINT ASSEMBLY IS STAKED TO PROVIDE A FRICTION LOCK BETWEEN OUTER COLLAR AND	 INNER NUT.  SUBMITTER STATES THIS METHOD OF FRICTION LOCK DID NOT HOLD.  TO HELP PREVENT THIS, APPLY LOKTITE TO THREADS	 UPON ASSEMBLY AND INSPECT BALL JOINT ASSEMBLY AT INSPECTIONS.			1	L	7	2 	4T			RT	A38ACE  					 
1996032900336	19960329	00336	EA  	1996	3	29	96ZZZX1365       	1	19960228	G	3310	LH10B	POWER SUPPLY    			CNDAIR	CL600 	CL6002B16   	1900305	EA  										OVERHEAD PANEL	DEFECTIVE       	B			SH5R	K				NONE                    				B	L		SMOKE/FUMES/ODORS/SPARKS  	NO TEST                   		IN	INSP/MAINT     	1			NE	03	604CC				354	5301				NUMEROUS PUSH BUTTON ANNUNCIATORS (PBA'S) WILL NOT LAMP TEST ON OVERHEAD PANEL.  CONFIRMED DISCREPANCY, FOUND TO BE A DE	FECTIVE BRIGHT/DIM POWER SUPPLY.  REMOVED AND REPLACED DEFECTIVE UNIT.  UNIT HAS A BURNING ELECTRICAL SMELL TO IT THAT W	AS NOTICEABLE IN THE COCKPIT.				2	L	7	2 	4F			RT	A21EA   					 
1996032900337	19960329	00337	NM  	1996	3	29	96ZZZX1366       	1	19960226	G	5320	AND101362402	T-CHORD         			BOEING	737   	737247      	138448D	NM  										LT FRAME STR 27	CORRODED        	B			S5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	303VA	54742				20125				DURING SS1D INSPECTION OF E AND E DOOR CUT-OUT AREA, FOUND CORROSION IN T-CHORD FRAME AND SKIN IN LT FRAME STR 27.  SUSP	ECT CAUSE DUE TO LAVATORY DRAIN LEAK AND LACK OF PROPER DRAINAGE.  SUBMITTER STATED ATTENTION SHOULD BE PAID TO ANY FLUI	D LEADS IN FWD GALLEY AND LAV AREA AND ANY DEBRIS BLOCKING DRAIN HOLES IN LOWER FUSELAGE.				2	L	7	2 	4F				A16WE   					 
1996032900339	19960329	00339	EA  	1996	3	29	96ZZZX1368       	1	19960226	G	3250	70263	SERVO VALVE     			CNDAIR	CL601 	CL6013A     	8070802	EA  										NLG STEERING	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	611GS	2096 			292	5082				NLG STEERING FAILED.  FOUND SERVO VALVE SHORTED TO CASE AND SECONDARY WINDING TO HAVE EXTREMELY HIGH RESISTANCE.						2	L	7	2 	4F			RT	A21EA   					 
1996032900340	19960329	00340	EA  	1996	3	29	96ZZZX1369       	1	19960305	G	7830	32725703	SCREW SHAFT     			CNDAIR	CL600 	CL6002B16   	1900305	EA  										BALL SCREW	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	PTOSA					5075				BALLSCREW ACTUATORS SCREW SHAFTS WERE FOUND CORRODED.  NO CORROSION ALLOWED IAW COMPONENT MAINTENANCE.  MANUAL CHAPTER 7	8-30-29, PAGE 505, PARAGRAPH 5B, ITEM NR 5.  (BRAZIL)					2	L	7	2 	4F			RT	A21EA   					 
1996032900341	19960329	00341	CE  	1996	3	29	96ZZZX1370       	1	19960219	G	2435	3143503600919	BEARING         	LUCAS       	23085004    	CESSNA	500   	560CESSNA   	2076750	CE  										START/GEN	FAILED          	D				B	A			EMER. DESCENT           	UNSCHED LANDING         			H	E		ELECT. POWER LOSS-50 PC   	VIBRATION/BUFFET          		CR	CRUISE         	1			GL	03	168CV	1732 	705  		3210	5600168				LEFT GENERATOR FAILURE OCCURRED AT 37,000 FEET.  THE GENERATOR WOULD NOT RESET.  DURING DESCENT, A HUM AND VIBRATION OCC	URRED FROM LEFT ENGINE.  ENGINE WAS IDLED AND LEFT AT IDLE THROUGHOUT DESCENT AND LANDING.  UPON INSPECTION, IT APPEARED	 THE DRIVE END BEARING OF THE START/GENERATOR HAD FAILED TOTALLY DESTROYING THAT END OF THE GENERATOR (UNREPAIRABLE).  S	UBMITTER RECOMMENDS OPERATORS REPLACE BEARINGS ANYTIME BRUSHES ARE REPLACED, USUALLY AROUND 600-700 HOURS AND NOT WAIT U	NTIL 1,000-HOUR OVERHAUL TIME.		2	L	7	2 	4F			RT	A22CE   					 
1996032900342	19960329	00342	SW  	1996	3	29	96ZZZX1371       	1	19960311	G	5751	2734023008	SPAR            		2734000034  	SWRNGN	SA227 	SA227AC     	8780603	SW  										AIL HINGE	CRACKED         	B			HAXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	361AE	15492			C015	AC676				DURING DISASSEMBLY OF AILERON TO REPLACE CRACKED AILERON SKINS, SPAR FOUND TO HAVE 3 CRACKS.  THERE ARE TWO, 1.5 INCH CR	ACKS IN AREA OF OUTBOARD HINGE FITTING ATTACH HOLES AND ONE, .5 INCH CRACK IN AREA OF CENTER HINGE FITTING ATTACH HOLE. 	 CRACKS ARE SUSPECTED TO BE FATIGUE CRACKS.				2	L	7	2 	4T			RT	A8SW    					 
1996032900344	19960329	00344	CE  	1996	3	29	96ZZZX1373       	1	19960124	G	7714	32005	TACH GENERATOR  			CESSNA	500   	550         	2076604	CE  										LT ENG N1 TACH	IMPROPER PART   	B			EBVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	114DS	376  			232324	5500397				THE LT ENGINE N1 TACHOMETER GENERATOR DID NOT RESEMBLE THE OTHER TACHOMETER GENERATORS.  INVESTIGATION FOUND VENDOR-ADVA	NCE POWER, INC., IS NOT AN APPROVED CESSNA/CITATION VENDOR FOR THIS PART.  ENGINE LOG BOOK SHOWS A CITATION PART NUMBER 	WHEN THIS UNIT WAS INSTALLED.  THIS UNIT WAS BLACK IN COLOR AND SMALLER IN DIAMETER THAN THE APPROVED UNITS.				1	L	7	2 	4F				A22CE   					 
1996032900345	19960329	00345	CE  	1996	3	29	96ZZZX1374       	1	19960304	G	5730		PANEL           			LEAR  	35    	35A         	5170602	CE  										LT WING FUEL	LOOSE SCREWS    	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	133EJ					133				OBSERVED FUEL LEAKING FROM LT WING ROOT.  TRACED SOURCE OF LEAK TO LT WING LEADING EDGE BEHIND LEADING EDGE DEICE STRIP.	  FOUND NUMEROUS LOOSE SCREWS.  RETORQUED SCREWS ON BOTH RT AND LT WINGS.  LEAK SEEMED TO STOP.  UPON FURTHER INSPECTION	 APPROXIMATELY 1 WEEK LATER FOUND EDGE SEEPING AGAIN (FRI 3-1-96).  SEEP WAS NOT WITHIN L-35 MINIMUM LIMITS.  SUSPECT LA	CK OF TORQUE ON SCREWS LEADING TO DETERIORATION OF TANK SEALER.			2	L	7	2 	4F				A10CE   					 
1996032900346	19960329	00346	CE  	1996	3	29	96ZZZX1375       	1	19960201	G	3240	2307006113	HOSE            			LEAR  	25    	25          	5170506	CE  										RT MLG BRAKE	LEAKING         	H				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CE	05	500DL					027				RIGHT OUTBOARD BRAKE HOSE LEAKING AT UPPER END NEAR HOSE (FLEX) FITTING.  OCCURRED IN-FLIGHT, WAS FOUND ON LANDING.  HYD	RAULIC PRESSURE WENT TO ZERO, AND ACFT PULLED TO LEFT DURING BRAKING.					2	L	7	2 	4J				A10CE   					 
1996032900347	19960329	00347	CE  	1996	3	29	96ZZZX1376       	1	19960315	G	5210	1014401041	ANCHOR          			BEECH 	200   	200BEECH    	1152920	CE  										DOOR CABLE ARM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	5559X	1450 				BB1372				PASSENGER WAS DEBOARDING AIRCRAFT WHEN DOOR CABLE ATTACH ANCHOR FAILED CAUSING DOOR TO DROP.  PASSENGER FELL TO GROUND A	ND SUSTAINED MINOR INJURY.  SUBMITTER STATED INSPECT CLOSELY AT INSPECTIONS TO UNCOVER SMALL DEFECTS WHICH COULD LEAD TO	 THIS TYPE OF FAILURE.  ALSO, CHECK TORQUE OF MOUNTING SCREWS WHICH TEND TO LOOSEN.				1	L	7	2 	4T				A24CE   					 
1996032900348	19960329	00348	NE  	1996	3	29	96ZZZX1377       	2	19960210	G	7261	3008127	GEARSHAFT       		3024287     						PWA   	PT6   	PT6A42      	52043	NE  					OIL CAV PMP	SHEARED         	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			GL	17	18260		2730 		D618		PCE93133			PILOT REPORTED A LOW FUEL PRESSURE LIGHT FOLLOWED BY AN AUTOFEATHER ON LEFT ENGINE.  PILOT SHUT DOWN ENGINE AND LANDED W	ITHOUT INCIDENCE.  UPON INVESTIGATION, NOTED THE OIL LEVEL LOW, THERE WAS OIL IN THE EXHAUST CASE, AND METAL PARTICLES A	ND FLAKES PRESENT IN THE OIL FILTER.  FURTHER INVESTIGATION SHOWED SCAVENGE PUMP SHAFT HAD SHEARED.  ENGINE REMOVED FOR 	METAL IN OIL.								4	T			E4EA				 
1996032900349	19960329	00349	CE  	1996	3	29	96ZZZX1378       	1	19960307	G	5730		SKIN            			BEECH 	200   	200CBEECH   	1152926	CE  										LT WS 194.829	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	44MR					BL27				WHILE PERFORMING THE INCOMING INSPECTION ON THIS AIRCRAFT, A SMALL PORTION OF METAL WAS DISCOVERED MISSING FROM THE LOWE	R SURFACE OF THE LEFT WING AT STA 194.829 ALONG THE FWD MAIN SPAR.					1	L	7	2 	4T				A24CE   					 
1996032900350	19960329	00350	EA  	1996	3	29	96ZZZX1379       	2	19960131	G	7250		SHROUD RING     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  					PT SECTION	LUG MISSING     	B			RX8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	203BS					BB476	PCE85365			BINDING, WHEN PROPELLER WAS ROTATED, FOUND DURING MORNING PRE-FLIGHT.  THE POWER SECTION WAS REMOVED AND SENT TO DALLGO 	AIRMOTIVE.  D.A. FOUND A MISSING LOCATING LUG FROM THE PT SHROUD RING THAT WAS BINDING UP THE ROTATION OF THE POWER SECT	ION.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996032900351	19960329	00351	CE  	1996	3	29	96ZZZX1380       	1	19960314	G	3230		GEAR            			LEAR  	25    	25B         	5170511	CE  										MLG	FAIL TO EXTEND  	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	235JW					096				LANDING GEAR FAILED TO EXTEND NORMALLY, BUT WAS EXTENDED MANUALLY.  INVESTIGATION REVEALED MLG SYSTEM HAD BEEN IMPROPERL	Y LUBRICATION SERVICED.					2	L	7	2 	4J				A10CE   					 
1996032900352	19960329	00352	EA  	1996	3	29	96ZZZX1381       	2	19960314	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					PWR SECTION	FAILED          	D				A				UNSCHED LANDING         				O	J		OTHER                     	WARNING INDICATION        		CR	CRUISE         	1			SW	09	89MP	6581 	602  			BB166	PCE80363			PILOT REPORTED HE WAS IN LEVEL FLIGHT WITH CRUISE POWER AT OVER 20,000 FEET, WHEN HE HEARD A LOUD BANG AND NOTICED THE I	.T.T. CLIMBING RAPIDLY.  WHEN TURNING THE PROP BY HAND, A GRINDING NOISE COULD BE HEARD IN THE POWER SECTION.  AFTER REM	OVING THE COWLING, IT WAS NOTICED THE INLET TO THE GAS GENERATOR HAD NUMEROUS CRACKS AROUND IT AND THE GAS GENERATOR AND	 ACCESSORY GEARBOX WERE SEIZED.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996032900353	19960329	00353	EA  	1996	3	29	96ZZZX1382       	2	19960315	G	7200		ENGINE          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					LT ENG PT SECT	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			SW	09	4200A	5978 	3101 			B64	PCE50129			PILOT REPORTED LOUD NOISE FOLLOWED BY CHIP DETECTOR WARNING WHILE DESCENDING THROUGH 9,000 FEET.  WHEN VIEWED THROUGH EX	HAUST OPENINGS, ENGINE HAS SEVERE THERMAL AND MECHANICAL DAMAGE.  ALL POWER TURBINE BLADES BROKEN.  SOME POWER TURBINE G	UIDE VANES MISSING AND COMPRESSOR TURBINE BLADES BROKEN.  ENGINE WAS NOT DISASSEMBLED AT THIS LOCATION.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1996032900354	19960329	00354	EA  	1996	3	29	96ZZZX1383       	1	19960314	G	7603	2100140003	GEARBOX         			CNDAIR	CL600 	CL6002B16   	1900305	EA  										RT ENG THROTTLE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	80BF	148  			518	5117				PILOTS WERE REPORTING A STIFFNESS OR RESISTANCE WHEN MOVING THE THROTTLE ABOVE IDLE.  THIS RESISTANCE WOULD COME AND GO.	  LATER, FOUND TO OCCUR AFTER RT THRUST REVERSER ACTUATION.  INSPECTION REVEALED THE RT ENGINE THROTTLE CONTROL GEARBOX 	HAD FAILED.  SPECIFICALLY, THE SPRING INSIDE THAT ATTACHES TO THE THRUST REVERSER AUTOMATIC THROTTLE RETARD CABLE HAD BR	OKEN.  THERE WAS NO TENSION ON CABLE OR THE THROTTLE RETARD BELLCRANK.  RESISTANCE APPARENTLY COMING FROM SLACK IN THIS 	CABLE.		2	L	7	2 	4F			RT	A21EA   					 
1996032900355	19960329	00355	NE  	1996	3	29	96ZZZX1384       	2	19960201	G	7532	34A39709	COVER           		A39710K     						PWA   	JT9   	JT9*        	52054	NE  					PRBC	IMPROPER WELD   	B			SF3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03					1151823					RECEIVED CECO P.R.B.C. FROM TOWER AIR INC., FOR ZERO TIME OVERHAUL 8-30-95.  DISASSEMBLY AND INSPECTION OF COVER REVEALE	D UNAUTHORIZED REWORK HAD BEEN PERFORMED (WELD).										4	F			E20EA				 
1996032900356	19960329	00356		1996	3	29	96ZZZX1385       	4	19960122	G	2562	1104	ELT             	ARTEX       		HUGHES	369   	OH6A        		WP  										ANTENNA	WIRE BROKEN     	B			EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1874M				42600	691183				WEAK TRANSMISSION BATTERY VOLTAGE GOOD.  WIRE BROKEN OFF ANTENNA CONNECTOR INSIDE TRANSMITTER FROM CIRCUIT BOARD.  RETUR	NED TO MANUFACTURER FOR REPAIR.					1	G	7	1 	3U				H3WE    					 
1996032900358	19960329	00358	NE  	1996	3	29	96ZZZX1387       	2	19960227	G	7261		OIL LINE        			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					GP INLET	BLOCKED         	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	13	352HH					2714	4453			LOW ENGINE OIL PRESSURE LIGHT ON, LOW OIL PRESSURE INDICATION DURING FLIGHT.  COKE BLOCKING OIL LINE AT THE INLET FITTIN	G OF THE GAS PRODUCER REAR BEARING CHIP DETECTOR SCREEN.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
1996032900359	19960329	00359	EU  	1996	3	29	96ZZZX1388       	1	19960226	G	2913	350A35103004	SHAFT           		20117224    	SNIAS 	350   	AS350BA     	8680817	EU  										HYD PUMP	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	353HH	3074 				2707				HYDRAULIC FAILURE DUE TO WEAR OF HYDRAULIC PUMP AND SHAFT SPLINES AND SHAFT COUPLING SPLINES.  HYDRAULIC PUMP HARD TO RO	TATE AFTER REMOVAL.  REPLACED PUMP, COUPLING SHAFT, AND BEARING.					1	G	7	1 	3U			NC	H9EU    					 
1996032900360	19960329	00360		1996	3	29	96ZZZX1389       	4	19960223	G	3421	111303	INDICATOR       	ASTRONAUTICS		BELL  	412   	412         	1182202	SW  										PILOT ATTITUDE	WIRE CHAFED     	B		A	FE6R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	11	412DE	1982 				36033				PILOTS ATTITUDE INDICATOR STARTED SPINNING, SMOKE DETECTED IN COCKPIT.  FOUND PILOTS ATTITUDE INDICATOR ISOLATION AMP FA	ILED AND SOURCE OF SMOKE.  FOUND WIRING AT ATTITUDE INDICATOR HAD CHAFED ON DEFOGGER MOUNTING BOLT SHORTING AMP SIGNAL T	O GROUND AND CAUSING AMP FAILURE AND ATTITUDE INDICATION TO SPIN LATERALLY.  REPAIRED WIRE AND APPLIED CHAFE PROTECTION 	TO WIRE HARNESS.  SUBMITTER STATED THERE IS INSUFFICIENT SPACE BETWEEN BOLT HEAD AND REAR OF CONNECTOR.			1	G	7	2 	4U				H4SW    					 
1996032900361	19960329	00361	SW  	1996	3	29	96ZZZX1390       	1	19960220	G	6730	206076062003	SERVO           			BELL  	206   	206L        	1181522	SW  										CYCLIC	WATER CONTAM    	B		A	XJ2R	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	01	700EA	1299 			RH3904A	51497				CYCLIC STICK WOULD PULL HARD FORWARD WHEN COLD.  CUSTOMER REMOVED SERVO AND SENT IN FOR REPAIR.  RECEIVED UNIT AND BOOT 	WAS TORN AROUND INPUT VALVE.  FUNCTIONAL TEST UNIT FOUND, NO PROBLEM.  PUT UNIT IN FREEZER AND INPUT WOULD BECOME LOCKED	 UP.  DISASSEMBLED UNIT AND FOUND WATER BEHIND INPUT VALVE.  TORN BOOT ALLOWED WATER TO ENTER INPUT VALVE.				1	G	7	1 	3U				H2SW    					 
1996040500002	19960405	00002	SW  	1996	4	5	96ZZZX1391       	1	19960201	G	6320	430136201	BEARING         			BELL  	222   	222U        	1182140	SW  										GEARBOX NR 2	FAILED          	B			BAQR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			EA	03	587MC	776  				47566				DURING FLIGHT, BOTH GEARBOX AND REAR BEARING SUPPORT HOUSING CHIP LIGHTS ILLUMINATED.  UPON DISASSEMBLY OF THE ENGINE, F	OUND THE NR 2 BEARING ROLLER CAGE SPLIT IN TWO.					1	G	7	2 	3U				H9SW    					 
1996040500029	19960405	00029	SW  	1996	4	5	96ZZZX1418       	1	19960111	G	6410	206016201127	BLADE           			BELL  	206   	206L1       	1182107	SW  										T/R	BEARINGS CRACKED	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577E	1196 			CS6376	45577				DURING ROUTINE MAINTENANCE, FOUND TAIL ROTOR BLADE INBOARD BEARINGS CRACKED.  TSI:  743.8 HOURS.						1	G	7	1 	3U				H2SW    					 
1996040500030	19960405	00030	SW  	1996	4	5	96ZZZX1419       	1	19960111	G	6410	206016201127	BLADE           			BELL  	206   	206L1       	1182107	SW  										T/R	BEARINGS CRACKED	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577E	1196 			CS6372	45577				DURING ROUTINE MAINTENANCE, FOUND TAIL ROTOR BLADE INBOARD BEARINGS CRACKED.  TSI:  743.8 HOURS.						1	G	7	1 	3U				H2SW    					 
1996040500031	19960405	00031	NM  	1996	4	5	96ZZZX1420       	1	19960106	G	5320	PO100092	SUPPORT         			BOEING	727   	727259      	138408J	NM  										BS 389	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				FLOOR SUPPORT STRUCTURE AT STA 389, RBL 10 INCHES TO RBL 42 INCHES HAS LEVEL 2 CORROSION.  REMOVED AND REPLACED FLOOR SU	PPORT PER SRM 53-10-2, SRM 51-10-2, AND SRM 51-30-2.					2	L	7	3 	4F				A3WE    					 
1996040500032	19960405	00032	NM  	1996	4	5	96ZZZX1421       	1	19960107	G	5320	69403752	SUPPORT         			BOEING	727   	727259      	138408J	NM  										BS 360-460	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				STA 360-STA 460 - RBL 10, FLOOR SUPPORT STRUCTURE HAS LEVEL 2 CORROSION, ALSO LEVEL 1 ON STA 360 FLOOR BEAM UPPER SURFAC	E AT RBL 10.  REPLACED FLOOR SUPPORT STRUCTURE, PN 69-40375-2 (3 EACH) PER 51-10-1, FIG 14, CORROSION REMOVED AND MATERI	AL IS IN-LIMITS PER 53-10-1 FLOOR BEAM.				2	L	7	3 	4F				A3WE    					 
1996040500033	19960405	00033	NM  	1996	4	5	96ZZZX1422       	1	19960106	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 340-460	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				SEAT TRACK RBL 42, STA 340 TO STA 460, SEVERAL AREAS OF LEVEL 2 CORROSION ALONG TOP OF SEAT TRACK; ALSO, UNDERSIDE OF FL	ANGE.  REMOVED AND REPLACED SEAT TRACK PER SRM 51-10-4 AND SRM 53-10-05.					2	L	7	3 	4F				A3WE    					 
1996040500034	19960405	00034	NM  	1996	4	5	96ZZZX1423       	1	19960107	G	5320		ANGLE           			BOEING	727   	727259      	138408J	NM  										BS 1040-1060	CORROSION       	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				AFT MAIN ENTRY DOOR L2 SUPPORT ANGLE FOR L2 DOOR SCUFF PLATE HAS LIGHT LEVEL 1 AND EXFOLIATION LEVEL 2 CORROSION AROUND 	FASTENER HOLES, STA 1040.0 - STA 1060.0, LBL 62.0.  REMOVED CORROSION AND TREATED AND INSTALLED 'L' ANGLE DOUBLER PER SR	M 51-40-2.				2	L	7	3 	4F				A3WE    					 
1996040500035	19960405	00035	NM  	1996	4	5	96ZZZX1424       	1	19960106	G	5320		ANGLE           			BOEING	727   	727259      	138408J	NM  										BS 440-470	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				FORWARD CABIN 'L' ANGLE AT RBL 60, STA 440 - STA 470, HAS LEVEL 2 CORROSION.  CUT OUT CORRODED AREA AND FABRICATED AND S	PLICED NEW 'L' ANGLE AND INSTALLED PER SRM 51-10-1.					2	L	7	3 	4F				A3WE    					 
1996040500036	19960405	00036	NM  	1996	4	5	96ZZZX1425       	1	19960106	G	5320		SUPPORT         			BOEING	727   	727259      	138408J	NM  										BS 1030-1050	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				FLOOR SUPPORT STRUCTURE AT STA 1030 - STA 1050.0, RBL 10 HAS LEVEL 2 CORROSION.  FABRICATED AND INSTALLED FLOOR SUPPORT 	PER SRM 51-10-1 AND SRM 51-40-2.					2	L	7	3 	4F				A3WE    					 
1996040500040	19960405	00040	NM  	1996	4	5	96ZZZX1429       	1	19960106	G	5320		ANGLE           			BOEING	727   	727259      	138408J	NM  										BS 1060	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				AFT SERVICE DOOR, R2, L-ANGLE FOR R2 DOOR SCUFF PLATE SUPPORT HAS LEVEL 2 CORROSION AT BS 1060.						2	L	7	3 	4F				A3WE    					 
1996040500041	19960405	00041	NM  	1996	4	5	96ZZZX1430       	1	19960105	G	5315		FLOOR BEAM      			BOEING	727   	727259      	138408J	NM  										BS 970-990	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				AFT CABIN FLOORING FASTENER HOLES ON FLOOR BEAM AT STA 950, LBL 25 - RBL 25, HAS LIGHT SURFACE CORROSION; ALSO, ON INTER	COSTAL AT BL ZERO, STA 970 - STA 990, LEVEL 1 CORROSION.  REMOVED CORROSION AND TREATED AND PRIMED STOP DRILLED CRACKS A	ND FABRICATED L-ANGLE DOUBLER AND INSTALLED PER SRM 51-10-02, SRM 51-10-06, SRM 53-10-01, AND SRM 51-20-02.				2	L	7	3 	4F				A3WE    					 
1996040500042	19960405	00042	NM  	1996	4	5	96ZZZX1431       	1	19960104	G	5320		SPLICE          			BOEING	727   	727259      	138408J	NM  										CABIN	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				BS MS, RBL 52, FLOOR SUPPORT SPLICE HAS LEVEL 2 CORROSION (NEXT TO FRAME).  REMOVED AND REPLACED SUPPORT SPLICE PER SRM 	51-10-1 AND SRM 51-30-2.  REMOVED CORROSION, TREATED AND PRIMED IN AREA SPLICE PER SRM 51-10-6.					2	L	7	3 	4F				A3WE    					 
1996040500043	19960405	00043	NM  	1996	4	5	96ZZZX1432       	1	19960105	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 1030-1070	CORRODED        	B			S3BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	203AV					22474				AFT CABIN FLOOR STA 1030 - STA 1070, RBL 26, LEVEL 2 CORROSION ON FLANGE OF SEAT TRACK.  REMOVED TRACK, INSTALLED FABBED	 SEAT TRACK PER SRM 51-10-1 AND SRM 51-30-2.					2	L	7	3 	4F				A3WE    					 
1996040500402	19960405	00402	EA  	1996	4	5	96ZZZX1467       	2	19960301	G	8520	SL75060	ROD BOLT        			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 4	FAILED          	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SO	16	8951N					3240753	L762248			NR 4 TOP ROD BOLT FAILED IN-FLIGHT.  SEE AD NOTE 95-7-1 TW SMITH SENT LETTER TO SATISFY AD, THAT BOLT WAS NOT INSTALLED 	AT ENGINE OVERHAUL.  TIME SINCE O/H WAS ABOUT 120 HRS.					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996040500403	19960405	00403	SO  	1996	4	5	96ZZZX1468       	2	19960314	G	8530	653446A6	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					NR 2	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	6650D	1531 				TH1375	282375R			FINDING STEEL CYLINDERS ARE CRACKING FROM THE FUEL INJECTOR BOSS ACROSS TO THE SPARK PLUG BOSS ON A REGULAR BASIS.  SUBM	ITTER REPORTS SOME CYLINDERS WITH AS LITTLE AS 600.0 TT CRACKED.  SUBMITTER BELIEVES THERE MUST BE SOME TYPE OF MANUFACT	URING PROBLEM.				1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996040500404	19960405	00404		1996	4	5	96ZZZX1469       	4	19960312	G	2562	006062	BATTERY PACK    	DORNEMARGLN 	DMELT1411   															ELT	WRONG PART      	B			ODMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	11					0451A					WHEN UNIT WAS RETURNED TO DORNE AND MARGOLIN FOR REPAIR DUE TO NO OUTPUT, IT WAS FOUND THAT THE ARTEX BATTERY INSTALLED 	IN THE UNIT WAS ONLY APPROVED TO TSO C91.  SUBMITTER STATED THIS BATTERY PACK DOES NOT FIT PROPERLY IN THE D & M ELT 14-	1-1 AND THIS MAY HAVE CAUSED THE FAILURE IN THIS UNIT AS THE WIRE FOR THE BATTERY WAS DAMAGED CAUSING THE FAILURE.																	 
1996040500405	19960405	00405	CE  	1996	4	5	96ZZZX1470       	1	19960121	G	3297		WIRE            			BEECH 	23    	C24R        	1151254	CE  										NLG DOWNLOCK SW	BROKEN          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	17	18909	2008 				MC524				BROKEN WIRE IN NLG DOWNLOCK SWITCH AT SPLICE WHERE NG SWITCH IS SPLICED IN (IN ENG COMP) CAUSED PUMP TO STOP TOO SOON; N	OSE GEAR WOULD NOT LOCK DOWN, AIRCRAFT LANDED WITH NG NOT LOCKED, COLLAPSED.  SUBMITTER RECOMMENDS VINYL TUBING AROUND S	PLICES BE CHANGED PERIODICALLY SO IT DOES NOT GET STIFF.  ALSO, SPLICES CAN BE CHECKED FOR CONDITION.				1	L	7	1 	3O			 	A1CE    					 
1996040500406	19960405	00406	CE  	1996	4	5	96ZZZX1471       	1	19960209	G	7603		CONTROL CABLE   			BEECH 	23    	C23         	1151242	CE  										THROTTLE	BINDING         	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			GL	17	2149W					M1532				THROTTLE AUTHORITY BECAME INTERMITTENT, JAMMED, THEN UNRESPONSIVE IN-FLIGHT.  CONDITIONS 2,800 MSL, (MINUS) 15 DEGREES F	AHRENHEIT, NIGHT CLEAR.  OFF-AIRPORT LANDING MADE WITH THROTTLE STUCK AT 1,600 RPM.  CHECKED CONTROL, FOUND JAMMED.  THA	WED CABLE CONTROL AND GOT SOME MOVEMENT, BUT STILL BINDING.  REMOVED AND REPLACED CABLE ASSY.  DISASSEMBLED, FOUND INTER	MOST CABLE BENT, STRETCHED, AND DIRTY.  CAUSE LIKELY DUE TO DIRT AND MOISTURE BUILD-UP AND LOW O.A.T.  INSTALLED BEECH C	ABLE, PN 169-380084-13.		1	L	7	1 	3O			 	A1CE    					 
1996040500407	19960405	00407	SO  	1996	4	5	96ZZZX1472       	2	19960319	G	7310		LINE            			BEECH 	33    	35B33       	1151406	CE  	CONT  	O470  	IO470K      	17026	SO  					NR 3-5 BAFFLE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	97374	4000 				CD604				FUEL METERED PR LINE FROM FUEL CONTROL TO DIST BLOCK CHAFED AT CYL BAFFLE BETWEEN NR 3 AND NR 5 CYLINDERS.  ADDED LEATHE	R TO LINE TO ADD PROTECTION.  SUBMITTER STATED PRESENT METHOD ADOPTED BY BEECHCRAFT CORP USING FIRE SLEEVING IS NOT ADEQ	UATE ANTI-CHAFE PROTECTION.				1	L	7	1 	3O	3	O		3A15    	3E1				 
1996040500408	19960405	00408	CE  	1996	4	5	96ZZZX1473       	1	19960319	G	5521		SPAR            			CESSNA	150   	150L        	2071826	CE  										ELEV HINGE	HOLES ELONGATED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	11831	7661 				15075658				INSPECTION OF OUTER HINGE FITTING ON ELEVATORS FOUND HOLES ELONGATED.  REQUIRED NEW ELEVATOR SPAR.  SUSPECT THIS AREA BE	 CHECKED CLOSELY ON INSPECTION AND THAT BOLT BE CHECKED FOR PROPER TORQUE.  BOTH ELEVATOR SPARS BADLY CORRODED, REPLACED	.  SUBMITTER STATED THIS CESSNA HAD SEVERAL AREAS OF SEVERE CORROSION.				1	H	7	1 	3O				3A19    					 
1996040500409	19960405	00409	SO  	1996	4	5	96ZZZX1474       	1	19960116	G	3230	2106100	SOLENOID        			PIPER 	PA30  	PA30        	7103002	SO  										MLG MOTOR	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	07	7338Y					30387				DURING INSPECTION AND OPERATIONAL CHECK OF THE LANDING GEAR RETRACTION AND EXTENSION SYSTEMS AFTER A GEAR COLLAPSE ON LA	NDING, THE GEAR MOTOR SOLENOID FAILED TO 'CLOSE' SEVERAL TIMES (PREVENTING OPERATION OF THE GEAR ELECTRICALLY).					1	L	7	2 	3O				A1EA    					 
1996040500410	19960405	00410	CE  	1996	4	5	96ZZZX1475       	1	19960319	G	5312		BULKHEAD        			CESSNA	150   	150L        	2071826	CE  										FS 95	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	11831	7661 				15075658				INSPECTION FOUND CRACKS IN CORNERS AT BULKHEAD STA 95 UPPER CORNERS.						1	H	7	1 	3O				3A19    					 
1996040500411	19960405	00411	SO  	1996	4	5	96ZZZX1476       	2	19960225	G	7322	46512	VENTURI         	FACET       	MA35PA      	CESSNA	150   	150         	2071802	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR	CASTING FLAW    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	11831				DE2216306R	15075658				INSPECTION OF A NEW PMA CARBURETOR VENTURI FOUND CASTING FLAWS.  SUBMITTER STATES HAS SEEN THIS DEFECT FREQUENTLY.						1	H	7	1 	3O	3	O	NT	3A19    	E252				 
1996040500412	19960405	00412	CE  	1996	4	5	96ZZZX1477       	1	19960208	G	3260	1CH16	SWITCH          			CESSNA	310   	310R        	2074245	CE  										NLG	FAILED          	D				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	17	5119J					310R0996				WHILE ATTEMPTING TO LAND, THE NOSE GEAR DOWN AND LOCK LIGHT DID NOT ILLUMINATE WHEN GEAR WAS EXTENDED.  SEVERAL CYCLES W	ERE ATTEMPTED, BUT STILL NO LIGHT.  A SUCCESSFUL LANDING WAS MADE.  INVESTIGATION FOUND THAT ALL THREE GEARS WERE DOWN A	ND LOCKED.  THE NOSE GEAR DOWN AND LOCK SWITCH HAD FAILED INTERNALLY TO THE POINT WHERE NEITHER UNLOCK OR DOWN AND LOCK 	INDICATION COULD BE ACHIEVED.  REPLACEMENT OF THE SWITCH SOLVED THE PROBLEM.			1	L	7	2 	3O				3A10    					 
1996040500413	19960405	00413	SO  	1996	4	5	96ZZZX1478       	1	19960314	G	2460		BREAKERS        			PIPER 	PA31T 	PA31T2      	7103127	SO  										CB PANEL	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	2325W					31T8166075				CIRCUIT BREAKERS BURN UP/MELT INTERNALLY BEFORE TRIPPING, THEN REMAIN OPEN WHEN RESET.						1	L	7	2 	3T			RT	A8EA    					 
1996040500414	19960405	00414	SO  	1996	4	5	96ZZZX1479       	1	19960317	G	2730	7105602	SPRING          			PIPER 	PA31  	PA31350     	7103110	SO  										ELEV DOWN	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3588Z	6098 				318052130				FOUND ELEVATOR DOWN SPRING AND SPRING FORWARD ATTACH TAB WORN.  TAB WAS WORN WORSE THAN SPRING HOOK.  SUBMITTER RECOMMEN	DS STAINLESS STEEL ATTACH TABS AND CLOSE INSPECTION OF SPRING AND TABS.					1	L	7	2 	3O				A20SO   					 
1996040500415	19960405	00415	CE  	1996	4	5	96ZZZX1480       	1	19960308	G	3240	B302781	TORQUE PLATE    	MCAULY      	C1630320207 	CESSNA	206   	U206F       	2073333	CE  										LT MLG	BUSHING PARTED  	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	1523U	5948 				U20602234				DURING AN ANNUAL INSPECTION, GUIDE BUSHING ON BRAKE TORQUE PLATE FOUND SEPARATED.						1	H	7	1 	3O				A4CE    					 
1996040500416	19960405	00416	SO  	1996	4	5	96ZZZX1481       	1	19960301	G	5321	37829800	PANEL ASSY      			PIPER 	PA32  	PA32R301    	7103218	SO  										CENTER SEAT	DETERIORATED    	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9779J	1243 				32R13024				FLOOR PANEL FOR CENTER SEATS IS A FOAM PANEL WITH METAL TOP AND BOTTOM.  FOAM FILLER COMING OUT OF MIDDLE.  FOAM FILLER 	SEEMS TO DRY OUT AND FLAKE APART.  SUBMITTER STATED FLOORS FORMERLY MADE OF WOOD.  A WOOD FLOOR WITH METAL TOP AND BOTTO	M WOULD BE MUCH BETTER.				1	L	7	1 	3O				A3SO    					 
1996040500624	19960405	00624	SO  	1996	4	5	96ZZZX1501       	2	19960219	G	8500		ENGINE          			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					LT	ROUGHNESS       	I				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			NE	05	3249M	760  				402C0296	290143R			FLIGHT CREW NOTICED ROUGHNESS IN LEFT ENGINE.  INSPECTED MAGS, COMPRESSION TESTED CYLINDERS, CHECKED SPARK PLUGS.  ENGIN	E WAS GROUND RUN.  FLIGHT OK'D.  NOTED NO PROBLEMS.  RETURNED TO SERVICE.  NOTED:  MINUS 21 DEGREES FAHRENHEIT TEMPERATU	RE.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996040500625	19960405	00625	CE  	1996	4	5	96ZZZX1502       	1	19960308	G	3221	3216	BRACKET ASSY    	SCOTT       	3200        	CESSNA	170   	170B        	2072306	CE  										TAILWHEEL	BOLT SHEARED    	D				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			AL	03	4387B	1000 			ARLOFOR	26731				BRACKET ASSY BOLT APPEARS AS METAL HAS CRYSTALLIZED THROUGH AGE.  BOLT THEN SHEARED ALLOWING TAILWHEEL TO FALL OFF AIRCR	AFT ON TAKEOFF.					1	H	7	1 	3O				A799    					 
1996040500626	19960405	00626	CE  	1996	4	5	96ZZZX1503       	1	19960229	G	3211		TRUNNION        			CESSNA	182   	R182        	2072734	CE  										NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NE	01	6465T	2044 				R1820233				NOSE GEAR COLLAPSED AFTER LANDING.  CRACKED NOSE GEAR TRUNNION.  SUSPECT PREVIOUS HARD LANDINGS, EVIDENCE OF OLD CRACK. 	 CLOSE INSPECTION DURING SCHEDULED MAINTENANCE.					1	H	7	1 	3O			RT	3A13    					 
1996040500627	19960405	00627	SO  	1996	4	5	96ZZZX1504       	1	19960130	G	5712	7847503	RIB             			PIPER 	PA32  	PA32R300    	7103213	SO  										WS 49.25 RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	1919H	5837 				32R7780202				DURING C/W AD 95-20-07, FOUND AFT RIB ASSEMBLIES, LEFT AND RIGHT, CRACKED AFTER REMOVING MAIN GEAR SIDE BRACE STUD BRACK	ET, PN 75643-06.  SUBMITTER REPORTED SAME PROBLEM WITH SEVERAL OTHER AIRCRAFT.					1	L	7	1 	3O				A3SO    					 
1996040500628	19960405	00628	SO  	1996	4	5	96ZZZX1505       	1	19960130	G	5712	7847502	RIB             			PIPER 	PA32  	PA32R300    	7103213	SO  										WS 49.25 LT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	1919H	5837 				32R7780202				DURING C/W AD 95-20-07, FOUND AFT RIB ASSEMBLIES, LEFT AND RIGHT, CRACKED AFTER REMOVING MAIN GEAR SIDE BRACE STUD BRACK	ET, PN 75643-06.  SUBMITTER REPORTED SAME PROBLEM WITH SEVERAL OTHER ARICRAFT.					1	L	7	1 	3O				A3SO    					 
1996040500630	19960405	00630	CE  	1996	4	5	96ZZZX1507       	1	19960228	G	5711	082260039	SPAR            		08220441    	CESSNA	310   	310Q        	2074242	CE  										LT WS 85-111.5	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	199JJ	4295 				310Q01080				DURING AN ANNUAL INSPECTION OF AIRCRAFT, NOTED THE REAR SPAR UPPER AFT CAP HAD CORROSION THAT APPEARED TO BE INTERGRANUL	AR FROM WS 85.0 TO WS 111.5 (APPROX) LEFT WING.  AIRCRAFT FERRIED TO ANOTHER FACILITY FOR EVALUATION AND POSSIBLE REPAIR	.				1	L	7	2 	3O				3A10    					 
1996040500631	19960405	00631	CE  	1996	4	5	96ZZZX1508       	1	19960220	G	5711		SPAR            			BEECH 	18    	E18S        	1151006	CE  										WS 90 LT-RT	CORRODED        	B			DP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	125X					BA192				INSPECTION FOUND WS 90 RT UPPER - LIGHT CORROSION AND INDICATION OF .750 INCH CRACK FROM WELD INTO SPAR.  FOLLOW-UP INSP	ECTION WS 90 RT UPPER WITH DYE PENETRANT AND ULTRASONICS WITH NO CRACK INDICATIONS NOTED.					1	L	7	2 	3R				A765    					 
1996040500632	19960405	00632	CE  	1996	4	5	96ZZZX1509       	1	19960204	G	5313		STRUT           			BEECH 	23    	C23         	1151242	CE  										CABANE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2009D	3175 				M2053				LOWER END OF CABANE STRUTS CORRODED DUE TO WINDSHIELD LEAKING.  THIS PART IS VERY HARD TO SEE UNLESS GLARE SHIELD AND WI	NDSHIELD ARE REMOVED.  CORROSION FOUND DURING WINDSHIELD REPLACEMENT.  RUST WAS NEARLY THROUGH METAL WALL OF STRUT.  SUB	MITTER STATED SINCE THIS PART IS NOT CLEARLY VISIBLE, AN AD IS PERHAPS IN ORDER AS THIS IS STRUCTURE.				1	L	7	1 	3O				A1CE    					 
1996040500633	19960405	00633	SO  	1996	4	5	96ZZZX1510       	1	19960312	G	3230	400218	BOLT            		7642603     	PIPER 	PA28  	PA28R201    	7102816	SO  										UPPER NLG LINK	MISINSTALLED    	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	2247M	2470 				28R7837073				ATTACHING HARDWARE FOR NLG UPPER DRAG LINK TO ENGINE MOUNT INSTALLED INCORRECTLY, WASHER SKIN BUSHING, ETC.  ARRANGEMENT	 INCORRECT.					1	L	7	1 	3O				2A13    					 
1996040500634	19960405	00634	SO  	1996	4	5	96ZZZX1511       	1	19960312	G	6120	LW162662538	CLAMP           			PIPER 	PA28  	PA28R201    	7102816	SO  										PROP GOV LINE	INCORRECT       	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	2247M					28R7837073				CLAMP POSITION FOR REAR MOUNT PROP GOVERNOR EXTERNAL OIL LINE NOT POSITIONED PER AD 90-4-6.						1	L	7	1 	3O				2A13    					 
1996040500635	19960405	00635	SO  	1996	4	5	96ZZZX1512       	1	19960312	G	7820	6751700	MUFFLER         			PIPER 	PA28  	PA28R201    	7102816	SO  										ENG EXHAUST	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	2247M	2490 				28R7837073				FRONT MUFFLER INTERNAL BAFFLE MISSING.  AFT MUFFLER INTERNAL BAFFLE DISTORTED, PARTIALLY BLOCKING OUTLET.						1	L	7	1 	3O				2A13    					 
1996040500638	19960405	00638	CE  	1996	4	5	96ZZZX1515       	1	19960308	G	2730	50935001	CONTROL ARM     			CESSNA	421   	421C        	2076016	CE  										ELEVATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	40ME	5542 				421C1241				FOUND HOLES ELONGATED WHERE ELEVATOR CONTROL ARM ATTACHES TO BRACKET ON THE AFT SPAR OF HORIZONTAL STABILIZER.  SUSPECT 	CAUSE, LOOSE AND WORKING BOLTS AND TIME ON PART.					1	L	7	2 	3O				A7CE    					 
1996040500639	19960405	00639	CE  	1996	4	5	96ZZZX1516       	1	19960220	G	2752	511523716	ACTUATOR        			CESSNA	414   	414A        	2075907	CE  										FLAP	FAILED          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	4686N	8066 				414A0075				FLAPS WERE BEING LOWERED.  A POPPING SOUND WAS HEARD.  IT WAS DISCOVERED THE FLAP ACTUATOR HAD FAILED INTERNALLY.  FLAP 	ACTUATOR REPLACED.					1	L	7	2 	3O				A7CE    					 
1996040500640	19960405	00640		1996	4	5	96ZZZX1517       	4	19960308	G	3416	3431	CASTING         	UNITEDINST  	5934P       	PIPER 	PA32  	PA32RT300   	7103215	SO  										ALTIMETER	OUT OF SPEC     	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	457SC				M8448	32R7885139				TWO OF THE CRITICAL SHAFTS IN THE MECHANISM WERE UNDER THE MINIMUM END SHAKE CALLED OUT IN THE OVERHAUL MANUAL.  THEY ME	ASURED .0005 INCH AND .0009 INCH (O/H MANUAL CALLS OUT .0020 INCH MINIMUM).  SUBMITTER STATED THIS UNDER ENDSHAKE CONDIT	ION COULD CAUSE A POINTER HANG-UP UNDER COLD CONDITIONS.				1	L	7	1 	3O				A3SO    					 
1996040500641	19960405	00641	CE  	1996	4	5	96ZZZX1518       	1	19960220	G	2823	99102011	VALVE           			CESSNA	414   	414A        	2075907	CE  										FUEL SELECT	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	4686N	8069 				414A0075				FUEL SELECTION WAS MOVED FROM LEFT ENGINE TO CROSS-FEED.  AFTER FLIGHT, THE FUEL SELECTOR WAS MOVED FROM CROSS-FEED BACK	 TO LEFT ENGINE.  FUEL SELECTION WOULD NOT MOVE.  IT WAS DISCOVERED THE FUEL SHUT-OFF VALVE HAD FAILED INTERNALLY AND WA	S STUCK IN THIS POSITION.  VALVE REPLACED.				1	L	7	2 	3O				A7CE    					 
1996040500642	19960405	00642	SW  	1996	4	5	96ZZZX1519       	1	19960216	G	5541	442283	SPAR            			GULSTM	112   	114         	7630314	SW  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	4895W	2000 				14225				AIRCRAFT CAME IN FOR AN ANNUAL.  AFTER SEEING JANUARY, 1996 ALERTS, DECIDED TO CHECK THIS AREA AND FOUND A 2.50 INCH CRA	CK ON LT SIDE OF RUDDER FITTING ATTACH HOLES.					1	L	7	1 	3O				A12SO   					 
1996040500643	19960405	00643	SO  	1996	4	5	96ZZZX1520       	1	19960223	G	2720	6342004	PEDAL ATTACH    			PIPER 	PA32  	PA32300     	7103212	SO  										PILOT LT RUDDER	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	4182R	4011 				3240513				PILOT'S LT RUDDER PEDAL ATTACH ARM FAILED AROUND CROSS-OVER TUBE ATTACHMENT.  SUBMITTER STATED INSPECTING ALL WELDS FOR 	CONDITION AT 100-HOUR INTERVALS OR ANNUAL, AND LUBING ALL LUBE HOLES ON RUDDER BAR SUPPORT ASSY.					1	L	7	1 	3O				A3SO    					 
1996040500644	19960405	00644	GL  	1996	4	5	96ZZZX1521       	3	19960223	G	6111	BCE2020	BEARING         			UNIVAC	GC1   	GC1B        	9230104	NM  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROP BLADE	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	44S		68   			1251		CH10736		PROPELLER SUBMITTED FOR INSPECTION DUE TO COMPLAINTS OF VIBRATION AND ONE LOOSE BLADE.  WHEN DISASSEMBLED, DISCOVERED TH	E BCE 2020 BEARINGS WERE LEFT OUT DURING THE LAST OVERHAUL 68.0 HRS AGO.  INSPECTED SHANKS FOR CRACKS AND DAMAGE.  NONE 	FOUND, ALTHOUGH THE 2222 TORQUE PLATES WERE DAMAGED BEYOND REPAIR DUE TO THE SIGNIFICANT LOADS APPLIED BY THE LOOSE BLAD	ES.  REPAIRED PROPELLER INSTALLING CORRECT PARTS, SEALS, GASKETS, AND HARDWARE.			1	L	7	1 	3O				A766    		5	C	P920	 
1996040500645	19960405	00645	SO  	1996	4	5	96ZZZX1522       	1	19960123	G	2720	63451000	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  										RUDDER PEDAL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	42161	3058 				287425312				DURING ANNUAL INSPECTION, MOVEMENT WAS NOTICED BACK AND FORTH ON RUDDER PEDAL ASSY.  FURTHER INSPECTION REVEALED 4 CRACK	S IN SUPPORT.  SUBMITTER STATED THIS PROBLEM WAS SUBMITTED PREVIOUSLY ON JANUARY, 1996, COPY OF WESTERN FLYER.					1	L	7	1 	3O				2A13    					 
1996040500647	19960405	00647	SO  	1996	4	5	96ZZZX1524       	2	19960301	G	8550	CH48108	OIL FILTER      			CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520E    	17040	SO  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	13	401GB	50   				401B0004				WHILE AIRCRAFT IN-FLIGHT, PILOT REPORTED OIL LEAKING FROM LEFT ENGINE.  DURING INSPECTION OF LEFT ENGINE, FOUND OIL FILT	ER AND SURROUNDING AREA OIL SOAKED.  AFTER CLEANING AND RUNNING ENGINE FOUND OIL LEAKING FROM HEXHEAD OF OIL FILTER (CH4	8108).  REMOVED FILTER AND REPLACED WITH CH48108.  AFTER RUNNING UP, ENGINE AGAIN, NO OIL LEAKS WERE NOTED.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996040500648	19960405	00648	CE  	1996	4	5	96ZZZX1525       	1	19960126	G	5730		SKIN            			CESSNA	310   	310R        	2074245	CE  										LT/RT WING	BUCKLED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4113A					310R1307				PRE-INSPECTION REVEALED BUCKLED WING SKIN OUTBOARD OF GEAR DOORS, UNDERSIDE LT AND RT WINGS.  SUSPECT CAUSE:  PILOT STAT	ED, ENCOUNTERED SEVERE TURBULENCE.					1	L	7	2 	3O				3A10    					 
1996040500649	19960405	00649	CE  	1996	4	5	96ZZZX1526       	1	19960228	G	3230	08421043	BELLCRANK       			CESSNA	421   	421B        	2076014	CE  										NLG	FAILED          	H				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SW	99	42AG	1275 				421B0425				NOSE LANDING GEAR FAILED TO EXTEND DUE TO FAILURE OF NOSE GEAR RETRACTION BELLCRANK.  SUSPECT CAUSED BY NOSE STRUT DEFLA	TION EITHER PRIOR TO TAKEOFF, DURING TAXI, OR AFTER TAKEOFF WHICH ALLOWED THE STRUT TO STAY COMPRESSED ON RETRACTION AND	 GEAR CONTACTED PART OF RETRACTION MECHANISM JAMMING IN PLACE BEFORE COMPLETE RETRACTION.  THIS CAUSED BELLCRANK TO FAIL	 BECAUSE MOTOR CONTINUED TO RUN UNTIL HITTING ITS LIMIT SWITCH AND THE BELLCRANK IS OBVIOUSLY THE WEAKEST LINK IN THE NO	SE RETRACTION MECHANISM.		1	L	7	2 	3O				A7CE    					 
1996040500651	19960405	00651	GL  	1996	4	5	96ZZZX1528       	3	19960109	G	6111	A31505	PIN             			CESSNA	185   	A185F       	2072821	CE  						MCAULY	D3A34	D3A34C401   	GL  	NR 2 BLADE	MISSING         	G				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			SW	99	4026Y	6    				1850226		950360		DURING TAKEOFF, ENGINE STARTED TO RUN ROUGH AND SHAKE.  THE TAKEOFF WAS ABORTED AND ACFT RETURNED TO RAMP.  ENGINE AND P	ROP WERE THEN INSPECTED FOR ABNORMALTIES.  WHILE INSPECTING THE PROP, A MECHANIC DISCOVERD THE NR 2 PROP BLADE COULD BE 	ROTATED INDEPENDENTLY OF THE OTHER BLADE.  THE PROPELLER WAS THEN REMOVED AND SENT IN FOR INSPECTION.  THE TEAR-DOWN REV	EALED A SAFETY PIN (A-3150-5) THAT SECURES THE BLADE ACTUATING LINK PIN (A-4738) IN PLACE WAS NOT INSTALLED DURING PROPE	LLER BUILD-UP.		1	H	7	1 	3O				3A24    		5	C	P47GL	 
1996040500652	19960405	00652	SO  	1996	4	5	96ZZZX1529       	2	19960301	G	8530		CYLINDER        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					ENGINE	HEAD SEPARATED  	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	5009J		1428 			310R0730	266054R			CYLINDER HEAD SEPARATED FROM BARREL.						1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996040500654	19960405	00654	SO  	1996	4	5	96ZZZX1531       	1	19960117	G	2140	880942	COMBUSTION TUBE 	JANITROL    	B3040       	PIPER 	PA34  	PA34200T    	7103406	SO  										HEATER	CRACKED         	D				A				UNSCHED LANDING         				C			F.O.D.                    			CL	CLIMB          	1			GL	13	501DM				4781452	347870375				AFTER TAKEOFF WITH HEATER SELECTED ON, SPARKS WERE SEEN COMING OUT OF THE HEATER VENTS.  THE HEATER WAS SHUT OFF AND AIR	CRAFT RETURNED TO BASE WITHOUT FURTHER INCIDENT.  HEATER REMOVED AND INSPECTED.  DURING INSPECTION, A CRACK ABOUT 3 INCH	ES LONG WAS SEEN 6 INCHES FROM EXIT END.  TIME SINCE LAST HEATER DECAY TEST WAS 45.7 HEATER HRS.  LAST HEATER O/H RECORD	ED WAS 10-15-80.  NO RECORD OF WHAT HEATER OVERHAUL INVOLVED IS AVAILABLE.			1	L	7	2 	3O				A7SO    					 
1996040500655	19960405	00655		1996	4	5	96ZZZX1532       	4	19960118	G	2215	6024	MOUNT BRACKET   	STEC        		CESSNA	182   	TR182       	2072735	CE  										ROLL SERVO	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	5276S	3486 				R182201531				UPON REPLACEMENT OF ROLL SERVO, FOUND LOWER BRACKET HAD COMPLETELY CRACKED THROUGH.  THE SERVO WAS ONLY BEING HELD IN PL	ACE BY THE UPPER MOUNTING BRACKET.  ORDERED NEW REPLACMENT PART AND FOUND IT HAS BOTTOM ADJUSTMENT SLOTS FOR SERVO POSIT	ION ADJUSTMENT.  RECOMMEND INSPECTION OF OLDER S-TEC AUTOPILOT ROLL SERVO BRACKET AND REPLACEMENT WITH NEW IMPROVED PART	.			1	H	7	1 	3O				3A13    					 
1996040500657	19960405	00657	EA  	1996	4	5	96ZZZX1534       	2	19960322	G	7322	30766	FLOAT           	FACET       	MA3PA       	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR	CRACKED         	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	15	5366B	864  			DM0922	15283849				CARBURETOR FLOAT FILLED WITH FUEL AND SANK IN-FLIGHT RESULTING IN ENGINE STOPPAGE AND FORCED LANDING.  FLOAT WAS IN C/W 	AD 93-19-04.  FLOAT CRACKED AND FILLED WITH FUEL.  RECOMMEND RE-ENGINEERED FLOAT NOT PRONE TO CRACKING.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996040500658	19960405	00658	SO  	1996	4	5	96ZZZX1535       	2	19960313	G	8520	643627	CRANKSHAFT      			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360GB   	17025	SO  					FLANGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5764S	1706 			A614M2	250831	316047			WHILE CONDUCTING AN ANNUAL INSPECTION, DISCOVERED SEVERAL SUSPICIOUS BROWN STAINS.  AREA WAS CLEANED AND A DYE PENTRANT 	INSPECTION PERFORMED.  CRACKS WERE FOUND RADIATING CIRCUMFERENTIALLY AROUND CRANKSHAFT AND FLANGE IN THE AREA OF THE FLA	NGE RADIUS.  PROP HAD BEEN REMOVED TO DETERMINE CRANKSHAFT SERIAL NUMBER FOR EVALUATION OF OVERHAUL AND SB COMPLIANCE.				1	L	7	1 	3O	3	O		2A3     	E9CE				 
1996040500659	19960405	00659	CE  	1996	4	5	96ZZZX1536       	1	19960208	G	2434	F3FF10300AA	ALTERNATOR      	FORD        		CESSNA	210   	T210N       	2073456	CE  										DC SYSTEM	WARNING LIGHT   	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	6611c		780  			21063930				LOW VOTLAGE LIGHT WITH FULL LOAD.  (PROP ICE, PITOT HEAT).  AIRCRAFT LANDED.  MECHANIC INSPECTED ALTERNATOR ATTACHMENTS,	 WIRING, AND BELT TENSION.  NO DISCREPANCIES WERE NOTED.  AIRCRAFT WAS TEST RUN ON THE GROUND AT SEVERAL POWER SETTINGS 	AND VARIOUS LOADS.  MECHANIC COULD NOT DUPLICATE PROBLEM AND RETURNED ACFT TO SERVICE.				1	H	7	1 	3O				3A21    					 
1996040500660	19960405	00660	CE  	1996	4	5	96ZZZX1537       	1	19960208	G	3260		SWITCH          			CESSNA	210   	T210N       	2073456	CE  										NLG SQUAT	OUT OF RIG      	D				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			GL	03	6611C					21063930				GEAR FAILED TO RETRACT.  UPON INSPECTION, FOUND SQUAT SWITCH OUT OF RIG.  JACKED ACFT, RE-RIGGED PER MM.  OPERATIONALLY 	TESTED GOOD.  SUBMITTER RECOMMENDS CLOSE INSPECTION OF SWITCH AT SCHEDULED INSPECTIONS.					1	H	7	1 	3O				3A21    					 
1996040500661	19960405	00661	SO  	1996	4	5	96ZZZX1538       	2	19960124	G	8520		MOUNT STUD      			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  					NR 4 CYLINDER	BROKEN          	B			EBVR	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			GL	09	61JK					340A0333	509498			PILOT COMPLAINED RT ENGINE WAS ROUGH RUNNING.  FOUND NR 1 CYLINDER HELD ON BY ONLY AFT TWO THROUGH-BOLTS.  ALL OTHER MOU	NT STUDS WERE BROKEN.  REMOVED CYLINDER AND THROUGH-BOLTS.  PENETRATE CHECK OF CASE MOUNTING AREA REVEALED TWO CRACKS (1	 O'CLOCK AND 7 O'CLOCK) AT MOUNT STUD HOLES AND MAG PARTICLE OF THROUGH-BOLTS REVEALED ONE CRACKED.				1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996040500662	19960405	00662	CE  	1996	4	5	96ZZZX1539       	1	19960301	G	8011	CC150	CLUTCH          	PRESTOLITE  	MZ4214      	CESSNA	150   	150M        	2071830	CE  										STARTER	SEIZED          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SO	05	63157				7E000015	15077145				CLUTCH ENGAGED IN-FLIGHT.  PILOT NOTED REDUCTION IN ENGINE RPM.  AFTER LANDING AND POWER WAS REDUCED TO IDLE, ENGINE INS	TALLED.  INSPECTION OF CLUTCH AND STARTER REVEALED THAT CLUTCH HAD 'FROZEN' TO STARTER GEAR AND HAD DRIVEN STARTER ARMAT	URE TO A HIGH SPEED.  ARMATURE WINDINGS SEPARATED FROM ARMATURE.  OVERHAUL RECORDS STATE THAT ALL APPLICABLE MANUFACTURE	RS SB'S ARE C/W (12-20-94).  NO DIRECT REFERENCE TO CONTINENTAL SB 79-10 STARTER CLUTCH AND MODIFICATION.  SUBMITTER SUS	PECTS LACK OF LUBRICATION AND/OR SPECIFIC TIME INTERVALS AND CRITERIA FOR INSPECTION OF CLUTCH.		1	H	7	1 	3O				3A19    					 
1996040500663	19960405	00663	CE  	1996	4	5	96ZZZX1540       	1	19960227	G	2571	07120591	SUPPORT         			CESSNA	182   	182R        	2072731	CE  										BAT HOLD DOWN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	6396E	1167 				18268367				BOTH BATTERY HOLD-DOWN SUPPORTS WERE FOUND CRACKED DURING A ROUTINE INSPECTION.  CRACKS WERE AT BOTH ENDS OF THE SUPPORT	S AND APPROXIMATELY 1 INCH IN LENGTH.  SUBMITTER STATED THIS IS THE SECOND AIRCRAFT FOUND WITH THIS DEFECT.  IF FAILURE 	HAD OCCURED, BATTERY COULD HAVE FALLEN INTO CONTROL CABLES.  SUGGEST CLOSE INSPECTION WHENEVER REAR BULKHEAD IS REMOVED.				1	L	7	1 	3O			NT	3A13    					 
1996040500664	19960405	00664	SO  	1996	4	5	96ZZZX1541       	1	19960307	G	6120	1998700	BALL JOINT      			PIPER 	PA24  	PA24250     	7102404	SO  										PROP CONTROL	SEPARATED       	B			KQ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	6849P					244983				IN-FLIGHT, PROP WENT TO 2700 RPM FROM 2350 RPM.  UNABLE TO DECREASE WITH PROP CONTROL.  FOUND BALL JOINT SEPARATED FROM 	PROPELLER GOVERNOR.  PROPELLER CONTROL WAS CHANGED LAST OCTOBER, 1995, USING SAME BALL JOINT AT THE LAST ANNUAL.  THE BA	LL JOINT WAS VERY RUSTY AND APPEARED TO HAVE NEVER BEEN LUBRICATED.  SUBMITTER STATED THE MM REQUIRES THIS BALL JOINT TO	 BE LUBRICATED EVERY 100 HOURS.  RECURRENCE OF THIS DEFECT CAN BE AVERTED BY FOLLOWING THE LUBRICATION REQUIREMENTS IN T	HE AIRCRAFT MM.		1	L	7	1 	3O				1A15    					 
1996040500665	19960405	00665	EA  	1996	4	5	96ZZZX1542       	2	19960311	G	8530		CYLINDER        			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  					NR 2	FAILED          	E				E				ENGINE SHUTDOWN         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			CE	07	615MT	802  				9112	RL505348			NR 2 CYLINDER BROKE AT BASE.   CYLINDER CAME LOOSE FROM THE CRANKCASE CAUSING ENGINE VIBRATION.  PILOT SHUT DOWN ENGINE 	IN-FLIGHT.  ON DISASSEMBLY, FOUND CRANKCASE AND PISTON DAMAGED.  THE ENGINE WAS REMOVED FROM SERVICE.					1	H	7	2 	3O	3	O		6A1     	1E4				 
1996040500667	19960405	00667	SO  	1996	4	5	96ZZZX1544       	1	19960202	G	3222		NOSE GEAR       			PIPER 	PA31  	PA31350     	7103110	SO  										TRUNNION	COLLAPSED       	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	05	7694L					317305024				NOSE GEAR COLLAPSED ON LANDING.  SUSPECT AIRCRAFT TOW LIMITS EXCEEDED.  DAMAGED TRUNNION, SHIMMY DAMPENER, AND UPPER RET	RACT CENTERLINE TRACK.  TOTAL TIME, 16,511.5 HOURS.					1	L	7	2 	3O				A20SO   					 
1996040500668	19960405	00668	SO  	1996	4	5	96ZZZX1545       	2	19960305	G	8550		OIL FILTER      			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  					CONNECTION	WRONG PART      	B			FE6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	7824K					18052758	464271			DURING AN ANNUAL INSPECTION, NOTED A CHAMPION CH 48103 (.8125 INCH BY 16 INCH FEMALE THREAD) OIL FILTER WAS INSTALLED. T	HE CORRECT OIL FILTER FOR THIS INSTALLATION SHOULD HAVE BEEN A CH-48110 (.75 INCH BY 16 INCH MALE THREAD).  IT IS BELIEV	ED THAT THE THREADED ADAPTER CAME OUT OF AN OIL FILTER (BRAND UNKNOWN) IN TIMES PAST (RECORDS SHOW CH 48103 FILTER INSTA	LLED AT LEAST SINCE MARCH 1993) AND BECAME STUCK IN THE FEMALE THREADS OF THE OIL FILTER ADAPTER.  PERSONNEL, AT THAT TI	ME, OBTAINED A FILTER THAT FIT, ALBEIT POORLY.  MAINTENANCE PERSONNEL, AFTER THAT TIME, REINSTALLED THE SAME PART NUMBER	 THAT WAS REMOVED.	1	H	7	1 	3O	3	O		5A6     	E273				 
1996040500669	19960405	00669	SO  	1996	4	5	96ZZZX1546       	2	19960305	G	8540	635050A4	ADAPTER         			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					STARTER	FAILED          	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	841LL		1397 			18263908	463648			WHEN STARTER WAS ENGAGED, THE PROPELLER MADE APPROXIMATELY ONE-EIGHTH REVOLUTION AND STOPPED.  FURTHER ATTEMPTS WITH STA	RTER WOULD NOT TURN PROPELLER.  PROP WAS 'STIFF' TURNING IN DIRECTION OF NORMAL ROTATION.  PROP COULD NOT BE TURNED AT A	LL IN OPPOSITE DIRECTION.  REMOVED STARTER ADAPTER FROM ENGINE AND PROP ROTATION FELT NORMAL IN BOTH DIRECTIONS.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1996040500671	19960405	00671	GL  	1996	4	5	96ZZZX1548       	3	19960304	G	6114	D4344	HUB             													MCAULY	3AF32C	3AF32C93    	GL  	NR 2 BLD SOCKET	CRACKED         	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23								777473		DURING C/W AD 95-24-05, FOUND HUB CRACKED IN THREADS, NR 2 BLADE SOCKET.  TOTAL TIME SINCE OVERHAUL, 1,226.8 HOURS.																5	C	P22EA	 
1996040500672	19960405	00672		1996	4	5	96ZZZX1549       	4	19960301	G	3454	023009800	METER ASSY      	KING        	KI208       															FLAG WARNING	FADED           	B			PG2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11					2929					HAVE NOTICED IN MANY OLDER KI208 AND KI209 INDICATORS, THE RED WARNING STRIPES ON THE VOR/LOC TO-OFF-FROM METER AND THE 	GLIDESLOPE FLAG METER FADE OUT TO WHITE.  ON THE KI208, IT IS POSSIBLE TO HAVE AN INDICATION OF HALF-'TO' AND HALF-'FROM	' AT THE SAME TIME.  ON THE KI209, THE VOR/LOC MAY BE THE SAME AS THE KI208, BUT THE GLIDESLOPE FLAG MAY POSSIBLY BE MIS	TAKEN FOR A 'TO' OR 'FROM' INDICATION.																 
1996040500673	19960405	00673		1996	4	5	96ZZZX1550       	4	19960301	G	3454	023012500	METER ASSY      	KING        	KI209       															FLAG WARNING	FADED           	B			PG2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11					1771					HAVE NOTICED IN MANY OLDER KI208 AND KI209 INDICATORS, THE RED WARNING STRIPES ON THE VOR/LOC TO-OFF-FROM METER AND THE 	GLIDESLOPE FLAG METER FADE OUT TO WHITE.  ON THE KI208, IT IS POSSIBLE TO HAVE AN INDICATION OF HALF-'TO' AND HALF-'FROM	' AT THE SAME TIME.  ON THE KI209, THE VOR/LOC MAY BE THE SAME AS THE KI208, BUT THE GLIDESLOPE FLAG MAY POSSIBLY BE MIS	TAKEN FOR A 'TO' OR 'FROM' INDICATION.																 
1996040500674	19960405	00674		1996	4	5	96ZZZX1551       	4	19960202	G	2564		RAFT            		69FAAV      															CO2 BOTTLE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					07200					DURING AN EXERCISE, RAFT FAILED TO INFLATE.  INSPECTION SHOWED CO2 BOTTLE VALVE DID NOT OPEN TO EXPEL CO2.  CERTIFICATIO	N DUE DATE WAS 2-15-96.																		 
1996040500675	19960405	00675		1996	4	5	96ZZZX1552       	4	19960229	G	2562	DMELT6	ELT             	DORNEMARGLN 																G-SWITCH	DEFECTIVE       	B			CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					55221					FOUND DEFECTIVE G-SWITCHES ON SEVERAL UNITS DURING THE LAST 6 MONTHS.  THE SWITCHES WILL ACTIVATE THE ELT, BUT THE ELT W	ILL STOP WHEN THE UNIT IS TILTED 20 DEGREES TO 30 DEGREES IN THE ROLL AXIS.  ON SOME UNITS, THE G-SWITCH WOULD NOT ACTIV	ATE THE ELT.   UNITS WERE SENT TO THE MANUFACTURER AND REPAIRED.  UNITS THEN TESTED CORRECTLY.																	 
1996040500676	19960405	00676		1996	4	5	96ZZZX1553       	4	19960229	G	2562	DMELT6	ELT             	DORNEMARGLN 																G-SWITCH	DEFECTIVE       	B			CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					39153					FOUND DEFECTIVE G-SWITCHES ON SEVERAL UNITS DURING THE LAST 6 MONTHS.  THE SWITCHES WILL ACTIVATE THE ELT, BUT THE ELT W	ILL STOP WHEN THE UNIT IS TILTED 20 DEGREES TO 30 DEGREES IN THE ROLL AXIS.  ON SOME UNITS, THE G-SWITCH WOULD NOT ACTIV	ATE THE ELT.   UNITS WERE SENT TO THE MANUFACTURER AND REPAIRED.  UNITS THEN TESTED CORRECTLY.																	 
1996040500677	19960405	00677		1996	4	5	96ZZZX1554       	4	19960229	G	2562	DMELT6	ELT             	DORNEMARGLN 																G-SWITCH	DEFECTIVE       	B			CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					39040					FOUND DEFECTIVE G-SWITCHES ON SEVERAL UNITS DURING THE LAST 6 MONTHS.  THE SWITCHES WILL ACTIVATE THE ELT, BUT THE ELT W	ILL STOP WHEN THE UNIT IS TILTED 20 DEGREES TO 30 DEGREES IN THE ROLL AXIS.  ON SOME UNITS, THE G-SWITCH WOULD NOT ACTIV	ATE THE ELT.   UNITS WERE SENT TO THE MANUFACTURER AND REPAIRED.  UNITS THEN TESTED CORRECTLY.																	 
1996040500679	19960405	00679		1996	4	5	96ZZZX1556       	4	19960129	G	3452	AT50	TRANSPONDER     	NARCO       																CAVITY	BOGUS MOD       	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09					11HP0					UNIT WAS INSPECTED AND FOUND TO HAVE AN UNAPPROVED MODIFICATION THAT ALLOWED INSTALLATION OF A 250W CAVITY.  THIS UNIT W	AS DESIGNED FOR 125W ONLY.  THE UNIT WAS TAGGED AS SERVICEABLE.																		 
1996040500680	19960405	00680	EU  	1996	4	5	96ZZZX1557       	1	19960221	G	7160	TB1050002163	TUBE            			SOCATA	TB9   	TB9         	8680694	EU  										CARB AIR BOX	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		50   								CARBURETOR HEAT TUBE ERODING DUE TO SUPER HEATED AIR FROM MUFFLER SHROUD.  TUBE WIRE SUPPORT AND DEBRIS FROM TUBE COULD 	BE INJECTED DIRECTLY INTO CARB AND ENGINE.  DIFFICULT TO INSPECT DUE TO FIRE SLEEVE WRAPPED AROUND TUBE.  SUBMITTER SUGG	ESTS DIFFERENT TYPE OF TUBE OR MATERIAL.				1	L	7	1 	3O			NT	AS1EU   					 
1996040500681	19960405	00681	CE  	1996	4	5	96ZZZX1558       	1	19960301	G	2720	0733100	TORQUE TUBE     			CESSNA	185   	185         	2072802	CE  										RUDDER	CORRODED        	B			P2MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										SUBMITTER REPORTS FINDING NUMEROUS RUDDER TORQUE TUBES SEVERLY CORRODED.  DIFFICULT, BUT CAN BE SEEN ON INSPECTION.						1	H	7	1 	3O			NC	3A24    					 
1996040500682	19960405	00682	SO  	1996	4	5	96ZZZX1559       	2	19960301	G	8520	115721	CRANKCASE       			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT ENGINE	CRACKED         	B	L		VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	12455	2080 	677  		1A688P	414A1207	800530			ENGINE CRANKCASE 1157-21 DEFECTIVE DUE TO CRACKS AFT OF NR 2 CYLINDER.  ALSO, NR 2 AND NR 3 BEARING SADDLES HAVE CRACKS.	  CRANKCASE PN 643202 MODIFIED TO 1157-21 PER STC SE 3630SW.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996040500683	19960405	00683	CE  	1996	4	5	96ZZZX1560       	1	19960204	G	2913	9881201	SOLENOID        		12808021    	CESSNA	210   	T210L       	2073449	CE  										MLG POWER PAC	MALFUNCTION     	D		A		O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			GL	03	381DS	2924 				21060255				GEAR-UP LANDING ON ASPHALT RUNWAY.  NO INJURIES.  ALL LANDING GEAR DOORS OPENED, BUT GEAR FAILED TO EXTEND EITHER ELECTR	ICALLY OR MANUALLY.  FAILURE CAUSED BY RESIDUE BUILT-UP ON SHAFT OF SOLENOID PN 9881201-1 PREVENTING OPERATION OF MANIFO	LD ON POWER PACK.  AFTER SOLENOID SHAFT CLEANED, LANDING GEAR EXTENDED BOTH ELECTRICALLY AND MANUALLY.  SUBMITTER SUGGES	TS INSPECTING/CLEANING SOLENOID SHAFT AT 1,000-HOUR INTERVALS.			1	H	7	1 	3O				3A21    					 
1996040500685	19960405	00685	SO  	1996	4	5	96ZZZX1562       	1	19960304	G	5730	4065910	SKIN            			PIPER 	PA31  	PA31310     	7103103	SO  										WS 147-174	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	59984	7402 				317512042				WING LEADING EDGE SKIN CRACKED AT STATIONS 147.50, 160.50, AND 174.50.  CRACKS OF .1250 INCH LENGTH RADIATING FROM COUNT	ERSUNK RIVETS FASTENING SKIN TO NOSE RIBS IN EITHER SIDE OF CUT-OUTS (IN NOSE-RIBS' TOP SURFACES).					1	L	7	1 	3O			RT	A20SO   					 
1996041200030	19960412	00030	SW  	1996	4	12	96ZZZX1592       	1	19960311	G	2550	206072903101	WIRE ROPE       			BELL  	206   	206L4       	1182110	SW  										CARGO HOOK	BROKEN          	B	S		GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	108W	1421 				52034				DURING A FUEL STOP ON A NORMAL WALK-AROUND, PILOT NOTICED SOMETHING HANGING DOWN BELOW THE CARGO HOOK.  FURTHER INVESTIG	ATION FOUND THE CARGO HOOK EMERGENCY RELEASE CABLE BROKE COMPLETELY THROUGH 2 INCHES FROM CONNECTION ON CARGO HOOK.					1	G	7	1 	3U			NC	H2SW    					 
1996041200083	19960412	00083	CE  	1996	4	12	96ZZZX1622       	1	19960301	G	7922	07560221	VALVE           			CESSNA	210   	T210L       	2073449	CE  										OIL BYPASS	SPRING WORN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	59218	2087 	750  			21060168				THE OIL FILTER BYPASS VALVE SPRING WAS FOUND WORN IN-HALF.  THE BYPASS VALVE WAS OPEN ALLOWING OIL TO BYPASS THE FILTER.						1	H	7	1 	3O				3A21    					 
1996041200084	19960412	00084	GL  	1996	4	12	96ZZZX1623       	3	19960308	G	6114	D5347C73	HUB             													MCAULY	2A34C	E2A34C73    	GL  	OIL PLUG	MISDRILLED      	B			ME4D	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15								764095		DURING INSPECTION, OIL PLUG HOLE WAS FOUND DRILLED IN WRONG LOCATION.  (SL 1995-14.)  HUB HAS BEEN SCRAPPED.																5	C	P3EA9	 
1996041200085	19960412	00085	SO  	1996	4	12	96ZZZX1624       	1	19960228	G	5711	20207T902	SPAR CAP        			AYRES 	S2    	S2RNORMAL   	7630202	SO  										RT WING	CORRODED        	B	P		FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11										A RIGHT WING WAS RECEIVED BY THIS REPAIR STATION FOR MINOR MODIFICATION TO THE SPAR WEB.  IT WAS DETERMINED THE LOWER FO	RWARD SPAR CAP, AT THE WING ATTACH FITTING, HAD SEVERE RUSTING, PIT CORROSION.  A MAJOR EFFORT HAS BEEN MADE TO HIDE THI	S DAMAGE BY USE OF AUTO-BODY FILLERS AND PAINT.  IT IS UNKNOWN WHAT AIRCRAFT REGISTRATION OR SERIAL NUMBER THIS WING WAS	 REMOVED FROM AS WING WAS PURCHASED INDIVIDUALLY.  STEEL SPAR CAP TO BE REPLACED WITH FACTORY NEW PART.			1	L	7	1 	3R			NC	A3SW    					 
1996041200086	19960412	00086	CE  	1996	4	12	96ZZZX1625       	1	19960302	G	5210	95380010	HANDLE          			BEECH 	36    	A36         	1151604	CE  										AFT DOOR	MISINSTALLED    	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	3122U					E2431				THE AFT DOOR HANDLE INSIDE AFT CABIN ON BEECH A36 BONANZA AND BEECH 58 BARON AIRCRAFT USE A HANDLE WITH A PUSH BUTTON. A	 PROBLEM WAS FOUND ON THE AIRCRAFT IN QUESTION DURING A PRE-PURCHASE INSPECTION.  THE DOOR HANDLE WAS IMPROPERLY INDEXED	 ON THE SQUARE MOUNTING SHAFT.  THE RESULT WAS A DOOR HANDLE WHICH OPERATED IN A MANNER OPPOSITE TO THE INTENDED DESIGN.	  IT WOULD ONLY LATCH BY DEPRESSING THE RELEASE BUTTON, BUT WOULD UNLATCH WITH A SINGLE MOTION.			1	L	7	1 	3O				3A15    					 
1996041200090	19960412	00090	NE  	1996	4	12	96ZZZX1629       	2	19960301	G	7270	DC6050001	BIDUCT          			DOUG  	DC8   	DC8*        		WP  	PWA   	JT3D  	JT3D7       	52039	NE  					ENGINE	MISREPAIRED     	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19					0153					BI-DUCT COMPONENT ARRIVED WITH TRANSITION SECTION OF BI-DUCT REPAIRED IN A MANNER NOT CONSISTENT WITH DOUGLAS AIRCRAFT C	O. SRM OR THE NACELLE CORP. SRM.  DELAMINATED INNER BONDED PANEL ASSEMBLIES BEING SECURED WITH 'STRAPS'.  SUSPECT CAUSE 	WAS MOST LIKELY REPAIR STATION ATTEMPTING REPAIR IT WAS NOT FAMILIAR WITH OR AUTHORIZED TO ACCOMPLISH.  TO PREVENT RECUR	RENCE, COMPONENT SHOULD BE ROUTED TO PROPER REPAIR STATION.			2	L	7	4 	4J	4	F	F	4A25    	1E8				 
1996041200091	19960412	00091	NE  	1996	4	12	96ZZZX1630       	2	19960228	G	7321	7280774	SPIDER VALVE    								PWA   	JT8   	JT8*        	52044	NE  					FUEL CONTROL	SEIZED          	B			RD43	K				NONE                    				Y			ENGINE STOPPAGE           			IN	INSP/MAINT     	1			SW	05					21J		F9606			ENGINE SHUT DOWN IN TEST CELL DURING POST-RENTAL INSPECTION TEST.  THE ENGINE WAS AT FULL POWER AT THE TIME OF SHUT DOWN	.  REMOVAL OF THE FUEL CONTROL SHOWED A SHEARED DRIVE SHAFT.  REMOVAL OF THE HYDRAULIC HOUSING FROM THE LINKAGE HOUSING 	ON THE CONTROL SHOWED A SEIZED SPEED GOVERNOR PILOT VALVE IN THE SPIDER.  THE CONTROL WAS RE-ASSEMBLED AND IS BEING ROUT	ED TO AAR FOR INVESTIGATION.								4	F			E2EA				 
1996041200092	19960412	00092	WP  	1996	4	12	96ZZZX1631       	1	19960315	G	2752	YS181	BEARING         		57726913    	DOUG  	DC8   	DC862       	3021970	WP  										INB FLAP ACT CYL	BROKEN          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					19					BEARING ON FLAP ACTUATOR CYLINDER BARREL RECEIVED BROKEN.  SUSPECT DUE TO HIGH STRESS IN THIS AREA AS WELL AS POSSIBLE M	ETAL FATIGUE.					2	L	7	4 	4F				4A25    					 
1996041200093	19960412	00093	WP  	1996	4	12	96ZZZX1632       	1	19960315	G	2750	37741723	CRANK           		57726913    	DOUG  	DC8   	DC861       	3021952	WP  										LT INBD FLAP	BROKEN          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					71881					CRANK RECIEVED WITH BROKEN LINK MOUNT.  SUSPECT DUE TO HIGH STRESS IN THIS AREA AS WELL AS POSSIBLE METAL FATIGUE.						2	L	7	4 	4F				4A25    					 
1996041200094	19960412	00094	CE  	1996	4	12	96ZZZX1633       	1	19960311	G	2910	991242322	LOADING VALVE   		991242323   	CESSNA	525   	525         	2076601	CE  										MANIFOLD ASSY	FAILED          	B			IW1R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	25	94MZ	311  			119	5250094				AFTER TAKEOFF, LANDING GEAR FAILED TO RETRACT.  PRIOR TO TAKEOFF, PILOT REPORTED FLAPS SEEMED SLUGGISH.  AFTER RECYCLING	 GEAR SEVERAL TIMES, SYSTEM APPEARED TO BE WORKING PROPERLY.  AFTER NEXT TAKEOFF, GEAR RETRACTED NORMALLY, BUT WHEN GEAR	 WAS SELECTED DOWN, GEAR FAILED TO EXTEND.  GEAR WAS BLOWN DOWN SUCCESSFULLY.  REPLACED VALVE, OPERATIONAL CHECKED OKAY.				1	L	7	2 	4F			RT	A1WI    					 
1996041200095	19960412	00095	EU  	1996	4	12	96ZZZX1634       	1	19960301	G	2450	21650	SCREW JACK      			AMD   	FALC20	FALCON20C5  	2730107	EU  										RT FLAP	STRIPPED        	B		A	DELR	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CE	03	100HG	9206 			362	54				DURING APROACH, PILOT MOVED FLAP HANDLE TO FIRST DETENT.  THE AIRCRAFT ROLLED RIGHT.  PILOT USED OVERCENTER ON CONTROL W	HEEL TO LEFT TO MAINTAIN STRAIGHT AND LEVEL FLIGHT.  INVESTIGATION FOUND RT FLAP INBD SCREW JACK GEARS STRIPPED AND DAMA	GED.				2	L	7	2 	4F			RT	A7EU    					 
1996041200096	19960412	00096	NE  	1996	4	12	96ZZZX1635       	2	19960209	G	7250	569551	VANE            								PWA   	JT12  	JT12A8      	52042	NE  					1ST STG TURB	PLATING PEEL    	B	L		IV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15							P637109NB			REPORTED CAUSE FOR REMOVAL OF ENGINE FROM AIRCRAFT WAS TURBINE BLADE FAILURE.  INVESTIGATION FINDINGS:  ENGINE DISASSEMB	LED AS NECESSARY AND REPAIRED DUE TO TURBINE BLADE FAILURE.  DISCREPANCY NOTED DURING INSPECTION WAS PLATING PEELING OFF	 23 EACH, PN 569551, FIRST STAGE TURBINE VANES WITH A TOTAL TIME OF 396.6 HRS, AND 10 EACH REWORKED (OVERHAULED) PN 5695	51 VANES WITH 396.6 HRS TSO (REF P & WA PN 435108 OVERHAUL MANUAL, PAGES 6-92, PARA 6-229).  SUBJECT VANES WERE REPLACED	.							4	J			1E9				 
1996041200097	19960412	00097	EU  	1996	4	12	96ZZZX1636       	1	19960228	G	5753	258WF2512A	FLAP            			BRAERO	DH125 	BAE125800A  	1500285	EU  										RT WING	DAMAGED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	801CE	67   			SDD263	258253				AIRCRAFT ARRIVED FOR FLAP CHANGE.  BOTH LT AND RT FLAPS REMOVED AND NEW FLAPS INSTALLED.  BOTH FLAPS WERE FOUND CRACKED 	AND UPPER SKIN TORN FROM THE LEADING EDGE TO THE TRAILING EDGE AT THE INBD ATTACH FITTING AREA.  PILOTS REPORTED POSSIBL	E CAUSE, OPERATION OF FLAPS ON THE GROUND WITH ICE AND SNOW BUILD-UP OR AIRCRAFT BEING TOWED OVER SNOW BANKS.				2	L	7	2 	4F			RT	A3EU    					 
1996041200098	19960412	00098	EU  	1996	4	12	96ZZZX1637       	1	19960228	G	5753	258WF2511A	FLAP            			BRAERO	DH125 	BAE125800A  	1500285	EU  										LT WING	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	801CE	67   			SDD253	258253				AIRCRAFT ARRIVED FOR FLAP CHANGE.  BOTH LT AND RT FLAPS REMOVED AND NEW FLAPS INSTALLED.  BOTH FLAPS WERE FOUND CRACKED 	AND UPPER SKIN TORN FROM THE LEADING EDGE TO THE TRAILING EDGE AT THE INBD ATTACH FITTING AREA.  PILOTS REPORTED POSSIBL	E CAUSE, OPERATION OF FLAPS ON THE GROUND WITH ICE AND SNOW BUILD-UP OR AIRCRAFT BEING TOWED OVER SNOW BANKS.				2	L	7	2 	4F			RT	A3EU    					 
1996041200099	19960412	00099	EU  	1996	4	12	96ZZZX1638       	1	19960227	G	2742	AM3C103	MOTOR           	LUCAS       	47142203    	AIRBUS	310   	A310*       		EU  										H STAB ACTUATOR	MISASSEMBLED    	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25					180					ON 2-27-96, TWO HORIZ STAB ACTUATOR MOTORS, SN AH-57563 AND SN AH-57871, WERE RECEIVED FROM REPAIR STATION AFTER INSPECT	ION AND VERIFICATION IAW REF AD AND AIRBUS AOT REFERENCED THEREIN.  THESE MOTORS WERE ASSEMBLED TO AN A310 TAILPLANE ACT	UATOR, PN 47142-203, SN 180.  THE ACTUATOR WAS RETURNED TO LUCAS ENGLEWOOD FROM CANADIAN AIRLINES FOR ACCOMPLISHMENT OF 	THE SUBJECT AD 96-01-52.  UPON TEST OF ACTUATOR, IT WAS FOUND TO RUN BACKWARDS TO THE COMMANDED INPUT.  CLOSER INSP AND 	COMPARISON TO ANOTHER KNOWN GOOD A310 ACTUATOR DISCLOSED THE BODIES OF 2 MOTORS APPEARED TO BE ASSEMBLED 180 DEGREES OUT	 OF POSITION (NAMEPLATE AND MOD PLATES ARE 180 DEGREES OUT OF POSITION).	2	L	7	2 	4F			RT	A35EU   					 
1996041200689	19960412	00689	NM  	1996	4	12	96ZZZX1696       	1	19960313	G	2752	673D10021	FLAP DRIVE      			ISRAEL	1125  	1125        		NM  										FLAP SYSTEM	FAILED          	D				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			GL	11	550M	26   			137	061				LOST USE OF FLAP SYSTEM DUE TO BROKEN SHAFT OR BAD CLUTCH IN POWER DRIVE UNIT.  UNIT FAILED DUE TO ACTUATORS BINDING UP 	BY FREEZING TEMP AT ALTITUDE.  UNITS WERE TESTED PER S.I.L. 1125-27-082 PRIOR TO INSTALLING.  CHANGED NR 3 RT ACTUATOR, 	OK FOR 26 HRS, THEN, FAILED AGAIN.  TESTED AGAIN UNDER REVISED SIL 1125-27-082.  FOUND ACTUATOR PER S.I.L. IN QUESTION. 	 CHANGED 3 EACH ACTUATORS, RETURNED TO SERVICE.			2	L	7	2 	4F			RT	A16NM   					 
1996041200690	19960412	00690	NM  	1996	4	12	96ZZZX1697       	1	19960313	G	2752	674D10017	ACTUATOR        	EEMCO       		ISRAEL	1125  	1125        		NM  										NR 3 FLAP	FREEZE UP       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	550M	1697 			288	061				PART WOULD NOT PASS TESTING FOLLOWING SIL 1125-27-082 R2 FREEZE-UP TEST.  ACTUATE GREASE IN WORM GEAR DRIVE TO MIX PC-10	.  FREEZE TO MINUS 50 DEGREES FAHRENEIT, MINUS 60 DEGREES FAHRENHEIT FOR 1.5 HRS.  BRAKE AWAY TORQUE OF 18 INCH/POUNDS O	K.  RUN TORQUE OF 12 INCH/POUNDS WOULD NOT PASS.				2	L	7	2 	4F			RT	A16NM   					 
1996041200691	19960412	00691	NM  	1996	4	12	96ZZZX1698       	1	19960313	G	2752	674D10013	ACTUATOR        	EEMCO       		ISRAEL	1125  	1125        		NM  										NR 1 FLAP	FREEZE UP       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	550M	1697 			480	061				PART WOULD NOT PASS TESTING FOLLOWING SIL 125-27-082 R2 FREEZE TEST.  ACTUATE GREASE TO MIX THE PC-10 IN WORM GEAR DRIVE	 FULL TRAVEL.  FREEZE TO MINUS 50 DEGREES FAHRENHEIT, 60 DEGREES FAHRENHEIT FOR 1.5 HRS.  BREAK AWAY TORQUE OF 18 INCH/P	OUNDS OK.  RUN TORQUE OF 12 INCH/POUNDS WOULD NOT PASS.				2	L	7	2 	4F			RT	A16NM   					 
1996041200692	19960412	00692	NM  	1996	4	12	96ZZZX1699       	1	19960313	G	2752	674D10015	ACTUATOR        	EEMCO       		ISRAEL	1125  	1125        		NM  										FLAP	FREEZE UP       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	550M	1697 			484	061				PART WOULD NOT PASS TESTING FOLLOWING SIL 1125-27-082 R2 FREEZE TEST.  ACTUATE GREASE MIXTURE PC-10 IN GEAR WORM DRIVE F	ULL TRAVEL, FREEZE TO MINUS 50 DEGREES FAHRENHEIT, MINUS 60 DEGREES FAHRENHEIT FOR 1.5 HRS.  BRAKE AWAY TORQUE 18 INCH/P	OUNDS OK.  RUN TORQUE 12 INCH/POUNDS WOULD NOT PASS.				2	L	7	2 	4F			RT	A16NM   					 
1996041200693	19960412	00693	NM  	1996	4	12	96ZZZX1700       	1	19960313	G	2752	673D10021	ACTUATOR        	EEMCO       		ISRAEL	1125  	1125        		NM  										NR 3 FLAP	SHEARED SHAFT   	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	550M	634  			175	061				FLAP POWER DRIVE UNIT FAILED.  NR 3 ACTUATOR PN 674D100-18 RIGHT SIDE HAD HIGH INPUT TORQUE WHEN COLD-SOAKED FOLLOWING S	IL 1125-27-082.  CHANGED POWER DRIVE UNIT AND ACTUATOR FAILED SN 137 PDU, 26 HRS LATER.  SUBMITTER SUGGESTS TO REVISE TE	STING INSTRUCTIONS.				2	L	7	2 	4F			RT	A16NM   					 
1996041200694	19960412	00694	NM  	1996	4	12	96ZZZX1701       	1	19960313	G	2752	674D10017	ACTUATOR        			ISRAEL	1125  	1125        		NM  										FLAP NR 3	DEFECTIVE       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	550M				551	061				ACTUATOR WAS SHIPPED AS A SERVICEABLE UNIT.  TEST PER SIL 1125-27-082 R2.  ACTUATED WORM GEAR DRIVE TO MIX THE PC-10 GRE	ASE, FULL TRAVEL BOTH DIRECTIONS.  FROZE TO MINUS 50 DEGREES FAHRENHEIT, MINUS 60 DEGREES FAHRENHEIT FOR 1.5 HRS.  BRAKE	 AWAY TORQUE OF 18 INCH/POUNDS OK.  RUN TORQUE 12 INCH/POUNDS WAS VERY CLOSE.  EEMCO SAYS THAT ACTUATOR PASSES THEIR TES	T TO MINUS 65 DEGREES FAHRENHEIT.  ACTUATOR WAS INSTALLED PER ASTRA JET CORP.  SUBMITTER RECOMMENDS BETTER FIELD TESTING	 INSTRUCTIONS.		2	L	7	2 	4F			RT	A16NM   					 
1996041200695	19960412	00695	NM  	1996	4	12	96ZZZX1702       	1	19960315	G	2721	D25W582050005	ACTUATOR        			ISRAEL	1125  	1125        		NM  										RUDDER TRIM	FREEZE UP       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	550M	1724 			068	061				TRIM ACTUATOR FREEZING UP AT ALT. IN COLD WEATHER CONDITIONS, 10 DEGREES FAHRENHEIT OR SO.						2	L	7	2 	4F			RT	A16NM   					 
1996041200696	19960412	00696	CE  	1996	4	12	96ZZZX1703       	1	19960313	G	2440	MS353061	POWER RECEPTACLE			LEAR  	60    	60LEAR      	5170707	CE  										EXT POWER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	65BL	224  				054				AIRCRAFT EXTERNAL POWER RECEPTACLE POSITIVE PROBE CORRODED AND LOOSE.  EVIDENCE OF HIGH HEAT WAS APPARENT AT THE TERMINA	L ATTACHING CABLES INSIDE THE AIRCRAFT.  SUBMITTER RECOMMENDS THAT LR60 OPERATORS INSPECT THIS AREA ASAP.  REPLACED THE 	TERMINALS AND POWER RECEPTACLE.				2	L	7	2 	4F			RT	A10CE   					 
1996041200697	19960412	00697	NM  	1996	4	12	96ZZZX1704       	1	19960313	G	2752	674D10018	ACTUATOR        	EEMCO       		ISRAEL	1125  	1125        		NM  										NR 3 RT FLAP	FREEZE UP       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	550M				495	061				ACTUATOR WAS SHIPPED AS A SERVICEABLE UNIT.  TEST PER SIL 1125-27-082 R2 ACTUATED WORM GEAR DRIVE TO MIX PC-10.  FULL TR	AVEL, BOTH DIRECTIONS.  FROZE TO MINUS 50 DEGREES FAHRENHEIT, MINUS 60 DEGREES FAHRENHEIT FOR 1.5 HRS.  BRAKE AWAY TORQU	E OF 18 INCH/POUNDS OK.  RUN TEST OF 12 INCH/POUNDS WOULD NOT PASS.  UNIT WAS TESTED AND REPAIRED AND SHIPPED H6-96.				2	L	7	2 	4F			RT	A16NM   					 
1996041200698	19960412	00698	EA  	1996	4	12	96ZZZX1705       	2	19960315	G	8500		ENGINE          			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					PWR SECTION	SEIZED          	H				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	99	1940Y					247	L60951			AIRCRAFT WAS IN LEVEL FLIGHT AT 13,500 FEET, HAD COMPLETE ENGINE FAILURE AND SEIZED WITH NO PRIOR WARNING.  DECLARED EME	RGENCY.  GLIDED 17.2 NM BACK TO AIRPORT, LANDED WITHOUT FURTHER INCIDENT.  NO DAMAGE TO AIRCRAFT AND NO INJURIES.  ENGIN	E SCHEDULED TO BE REPLACED 3-28-96.				1	L	7	1 	3O	3	O		2A3     	1E10				 
1996041200699	19960412	00699	CE  	1996	4	12	96ZZZX1706       	1	19960315	G	2810	182001	BLADDER         			CESSNA	206   	P206        	2073304	CE  										WING FUEL CELL	LEAKS           	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07	2639X					P2060139				OLD RUBBER BLADDERS LEAKED GAS OUT AND HAD LARGE WRINKLES ON BOTTOM OF TANKS.  SN 0977 AND SN 0978.						1	H	7	1 	3O				A4CE    					 
1996041200700	19960412	00700	CE  	1996	4	12	96ZZZX1707       	1	19960320	G	2437		AMMETER         			CESSNA	172   	172M        	2072418	CE  										DC SYSTEM	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	64262	750  				17265135				AMMETER NEEDLE FROZEN.  WOULD NOT SHOW ANY SIGN OF CHARGE OR DISCHARGE.  NO LOW VOLTAGE INDICATOR ON 172M.  1975 MODEL S	KYHAWK.					1	H	7	1 	3O			NT	3A12    					 
1996041200702	19960412	00702	EA  	1996	4	12	96ZZZX1709       	2	19960303	G	8530		CYLINDER        								LYC   	O320  	O320E2A     	41508	EA  					SKIRT AREA	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01			100  							DURING A TEAR DOWN OF AN ENGINE, FOUND CYLINDERS WERE VERY HARD TO MOVE.  AFTER THEY WERE TAKEN OFF, NOTICED ENGRAVED ET	CHING ON CYLINDER SKIRT WAS RAISED AND VERY MUCH HIGHER THAN THE SURROUNDING AREA.  THE VIBRATING PENCIL WAS VERY SHARP 	AND SET TO CUT MAXIMUM.  STONING THE EFFECTED AREA AND SMOOTHING THE CRANKCASE TO RELIEVE STRESS SOLVED THE PROBLEM.									3	O			E274				 
1996041200703	19960412	00703	EA  	1996	4	12	96ZZZX1710       	2	19960214	G	7414	10382894	GEARTOOTH       	BENDIX      	DYRN2021    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					LT MAGNETO	BROKEN          	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	21	1465E		343  		5023753R	17271012	L122176T			REMOVED MAGNETO DUE TO ROUGH ENGINE.  FOUND A TOOTH BROKEN OFF OF LEFT DISTRIBUTOR GEAR.  MAGNETO WAS ON A LYCOMING FACT	ORY OVERHAUL.  MAGNETO WAS OVERHAULED BY ELECTRO SYSTEMS, INC.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996041200704	19960412	00704	SO  	1996	4	12	96ZZZX1711       	2	19960314	G	8530		VALVE           			PIPER 	PA28  	PA28R200    	7102811	SO  	CONT  	O360  	IO360C      	17025	SO  					NR 4 INT	FAILED          	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			EA	27	32481	1526 				28R7535061	L2220251A			ON TAKEOFF, ENGINE BEGAN TO VIBRATE (AT FULL POWER SETTINGS).  RETURNED TO AIRPORT.  UPON INSPECTION, FOUND NR 4 INTAKE 	VALVE BROKEN IN HALF ON FACE AREA.  NR 4 PISTON SEVERELY DAMAGED, COULD NOT LOCATE PARTS OF MISSING VALVE.  SUSPECT INJE	STED INTO ENGINE THOUGH NO METAL WAS FOUND IN OIL FILTER OR SUMP SCREEN.  TT 1,526.0 HOURS ON ENGINE.				1	L	7	1 	3O	3	O		2A13    	E1CE				 
1996041200705	19960412	00705	EA  	1996	4	12	96ZZZX1712       	2	19960316	G	7414	M3525	COIL            	SLICK       	4270        	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					RT MAGNETO	OPEN            	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			NE	05	217LM	4270 			21689	2821972	L2406227AC			DURING RUN-UP, PILOT EXPERIENCED RT MAGNETO EXCESSIVE DROP.  ON REMOVAL BY MAINTENANCE, ENGINE WOULD NOT RUN ON RT MAGNE	TO.  FOUND OPEN IN SECONDARY COIL WINDINGS.					1	L	7	1 	3O	3	O		2A13    	E274				 
1996041200706	19960412	00706	CE  	1996	4	12	96ZZZX1713       	1	19960316	G	7603	5038901223	CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					THROTTLE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	511CF	474  				TH833				CONTROL CABLE SOLID SHAFT BROKE NEAR ROD END THREADS ASSY - WHERE THIS ASSY IS SWEDGED TO SOLID SHAFT.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
1996041200707	19960412	00707	SO  	1996	4	12	96ZZZX1714       	2	19960321	G	8520	634505	STUD NUT        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					NR 6 CYLINDER	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9579E	993  				18268428	286862R			TWELVE-POINT NUT ON THROUGH-BOLT, PN 641931-10.75, CRACKED.  NUT IS LOWER FORWARD NUT ON NR 6 CYLINDER.  SUBMITTER RECOM	MENDS USING 6-POINT NUT ONLY.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996041200708	19960412	00708	CE  	1996	4	12	96ZZZX1715       	1	19960320	G	2820		PRIMER SYSTEM   			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					PRIMER NOZZLE	LEAKAGE         	D		A		O				OTHER                   				A			FLAME/FIRE                			IN	INSP/MAINT     	1			NM	01	5164N					18267554	286603R			ENGINE HAD FIRE DURING START-UP.  FUEL FROM PRIMER NOZZLES RAN DOWN FLOW DIVIDER ABOVE CARBURETOR INTO CARBURETOR THROAT	 AND THEN INTO CARBURETOR HEAT BOX AND OUT CARBURETOR HEAT DRAIN HOLE INTO COWLING.  AFTER START, BACKFIRE IGNITED FUEL.	  NOTE:  EARLIER STYLE 182Q WITH PRIMER SYSTEM AND DISTRIBUTION SPIDER INJECT FUEL DIRECTLY INTO CYLINDERS AVOIDING FUEL	 DRAINING INTO COWL.			1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996041200719	19960412	00719	WP  	1996	4	12	96ZZZX1726       	2	19960103	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		7217 			1233151952		P70104			DURING INSPECTION FOR METAL CONTAMINATION, FOUND AIR SEAL CRACKED AT SEALING FLANGE.  THIS IS A CRITICAL LIFE-LIMITED CO	MPONENT.  LIFE-LIMIT IS 20,000 CYCLES.  SUBMITTER STATES THIS IS THE 24TH MALFUNCTION/DEFECT REPORT SUBMITTED ON THIS PA	RT BY THIS REPAIR STATION.  PART TOTAL CYCLES, 7,541.									4	T			E4WE				 
1996041200720	19960412	00720	WP  	1996	4	12	96ZZZX1727       	2	19960212	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		7318 			1233151936		P70112			DURING SCHEDULED CAM INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE.  THIS IS A CRITICAL LIFE-LIMITED COMPONENT.  LIFE-LIM	IT IS 20,000 CYCLES.  SUBMITTER SUGGESTS THIS IS THE 26TH MALFUNCTION/DEFECT REPORT ON THIS PART BY THIS FACILITY.  PART	 TOTAL CYCLES, 7,435.									4	T			E4WE				 
1996041200721	19960412	00721	WP  	1996	4	12	96ZZZX1728       	2	19960104	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		9588 			9233151520		P70035			DURING INSPECTION FOR BIRD INGESTION, FOUND AIR SEAL CRACKED AT FLANGE.  THIS IS A CRITICAL LIFE-LIMITED COMPONENT.  LIM	IT - 20,000 CYCLES.  SUBMITTER STATES THIS IS THE 27TH MALFUNCTION/DEFECT REPORT ON THIS PART BY THIS FACILITY.  PART TO	TAL CYCLES, 9,859.									4	T			E4WE				 
1996041200722	19960412	00722	WP  	1996	4	12	96ZZZX1729       	2	19960314	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		7286 			1233151992		P70108			DURING SCHEDULED CAM INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE.  CRACKING RESULTED IN DEFLECTION OF SEALING SURFACE O	F .040 INCH CAUSING LOSS OF COOLING AIR FOR TURBINE SECTION.  THIS IS A CRITICAL LIFE-LIMITED COMPONENT.  LIFE-LIMIT IS 	20,000 CYCLES.  SUBMITTER SUGGESTS THIS IS THE 28TH MALFUNCTION/DEFECT REPORT SUBMITTED BY THIS FACILITY ON THIS DISCREP	ANCY.  PART TOTAL CYCLES, 8,461.								4	T			E4WE				 
1996041200723	19960412	00723	WP  	1996	4	12	96ZZZX1730       	2	19960314	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		7144 			1233151935		P70111C			DURING SCHEDULED CAM INSPECTION, FOUND ROTATING AIR SEAL CRACKED AT FLANGE.  THIS IS A CRITICAL LIFE-LIMITED COMPONENT. 	 LIFE-LIMIT IS 20,000 CYCLES.  SUBMITTER STATES THIS IS THE 29TH MALFUNCTION/DEFECT REPORT SUBMITTED BY THIS FACILITY ON	 THIS DISCREPANCY.  PART TOTAL CYCLES, 7,125.									4	T			E4WE				 
1996041800121	19960418	00121	NE  	1996	4	18	96ZZZX1753       	3	19960210	G	6111		BLADE           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	SPLIT           	A			AMWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	182YV	1054 				UE182		HJ425		DURING ROUTINE MAINTENANCE, PROPELLER BLADE, SN 1655, WAS FOUND TO HAVE A 4 INCH SPLIT ON TRAILING EDGE.  REPAIRED IAW H	ARTZELL MM AND FORM 8110-3 FROM HARTZELL.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1996041800122	19960418	00122	NE  	1996	4	18	96ZZZX1754       	3	19960218	G	6111	E10950PK	BLADE           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	RT PROPELLER	SPLIT           	A			AMWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	182YV	1155 				UE182		HJ425		DURING ROUTINE MAINTENANCE, THE TRAILING EDGE WAS FOUND SPLIT APROXIMATELY 1.5 INCHES.  REPAIRED IAW HARTZELL MM AND FOR	M 8110-3.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1996041800132	19960418	00132	EU  	1996	4	18	96ZZZX1764       	1	19960120	G	3340	A402AR	LIGHT           			BOLKMS	105   	BO105S      	5626006	EU  										ANTI COLLISON	LENS UNGLUED    	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5352Y	252  				S781				ANTI-COLLISION LIGHT LENS CAME UNGLUED AT SEAM.  COULD GO INTO TAIL ROTOR.  REPLACED LENS.						1	G	7	2 	3U				H3EU    					 
1996041800151	19960418	00151	CE  	1996	4	18	96ZZZX1770       	1	19960227	G	5511	04320016	RIB             			CESSNA	150   	152         	2071835	CE  										LT-RT HORIZ STAB	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	89812	5550 				15282879				LEFT AND RIGHT HORIZONTAL STABILIZER ATTACH RIBS WERE CRACKED IN REAR FLANGE AND NEXT TO PLATE NUT.  NEW PARTS ARE MADE 	DIFFERENT.  SUBMITTER SUGGESTS HIGH TIME, PUSHING ON TAIL, EXCESSIVE GAP BETWEEN BULKHEAD AND RIBS MAY BE CAUSING CRACKS	.				1	H	7	1 	3O			NT	3A19    					 
1996041800152	19960418	00152	CE  	1996	4	18	96ZZZX1771       	1	19960227	G	5511	043200146	RIB             			CESSNA	150   	152         	2071835	CE  										LT-RT HORIZ STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	89812	5550 				15282879				LEFT AND RIGHT HORIZONTAL STABILIZER ATTACH RIBS WERE CRACKED IN REAR FLANGE AND NEXT TO PLATE NUT.  NEW PARTS ARE MADE 	DIFFERENT.  SUBMITTER SUGGESTS HIGH TIME, PUSHING ON TAIL, EXCESSIVE GAP BETWEEN BULKHEAD AND RIBS MAY BE CAUSING CRACKS	.				1	H	7	1 	3O			NT	3A19    					 
1996041800153	19960418	00153	CE  	1996	4	18	96ZZZX1772       	1	19960219	G	2820	05560203	VENT LINE       			CESSNA	172   	172N        	2072434	CE  										WING ROOT	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	2165E					17271174				FUEL VENT LINE CONNECTING HOSES DETERIORATED TO THE POINT OF LEAKAGE OF FUEL IN THE WING ROOT AREA.  ALL 3 HOSES ON BOTH	 SIDES NEEDED REPLACING DUE TO AGE.					1	H	7	1 	3O			NT	3A12    					 
1996041800154	19960418	00154	SO  	1996	4	18	96ZZZX1773       	1	19960301	G	5751	6237301	DOUBLER         		6810500     	PIPER 	PA32  	PA32260     	7103206	SO  										RT AIL HINGE	CRACKED         	H	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	3855W					321057				OUTBOARD DOUBLER HOLDING AILERON TO WING (REINFORCES MOUNT) HAS CRACKS.  FOUND ON THREE CONSECUTIVE AIRCRAFT DURING ANNU	AL INSPECTION.  THREE RIGHT OUTBOARD AND ONE LEFT OUTBOARD.  SUBMITTER SUGGESTS COUNTERWEIGHTS FOR THE AILERON MAY BE CA	USING STRESS FRACTURES.  SUGGEST AN ADDITIONAL PRE-FLIGHT CARD ITEM SHOULD BE ADDED TO PRE-FLIGHT CHECK LIST.  CAN BE RE	ADILY SEEN IF LOOKED FOR.			1	L	7	1 	3O				A3SO    					 
1996041800155	19960418	00155	SO  	1996	4	18	96ZZZX1774       	1	19960301	G	5751	6237301	DOUBLER         		6810500     	PIPER 	PA32  	PA32260     	7103206	SO  										RT AIL HINGE	CRACKED         	H	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	5517J					32949				OUTBOARD DOUBLER HOLDING AILERON TO WING (REINFORCES MOUNT) HAS CRACKS.  FOUND ON THREE CONSECUTIVE AIRCRAFT DURING ANNU	AL INSPECTION.  THREE RIGHT OUTBOARD AND ONE LEFT OUTBOARD.  SUBMITTER SUGGESTS COUNTERWEIGHTS FOR THE AILERON MAY BE CA	USING STRESS FRACTURES.  SUGGEST AN ADDITIONAL PRE-FLIGHT CARD ITEM SHOULD BE ADDED TO PRE-FLIGHT CHECK LIST.  CAN BE RE	ADILY SEEN IF LOOKED FOR.			1	L	7	1 	3O				A3SO    					 
1996041800156	19960418	00156	SO  	1996	4	18	96ZZZX1775       	1	19960301	G	5751	6237301	DOUBLER         		6810500     	PIPER 	PA32  	PA32260     	7103206	SO  										RT AIL HINGE	CRACKED         	H	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	3258W					3281				OUTBOARD DOUBLER HOLDING AILERON TO WING (REINFORCES MOUNT) HAS CRACKS.  FOUND ON THREE CONSECUTIVE AIRCRAFT DURING ANNU	AL INSPECTION.  THREE RIGHT OUTBOARD AND ONE LEFT OUTBOARD.  SUBMITTER SUGGESTS COUNTERWEIGHTS FOR THE AILERON MAY BE CA	USING STRESS FRACTURES.  SUGGEST AN ADDITIONAL PRE-FLIGHT CARD ITEM SHOULD BE ADDED TO PRE-FLIGHT CHECK LIST.  CAN BE RE	ADILY SEEN IF LOOKED FOR.			1	L	7	1 	3O				A3SO    					 
1996041800157	19960418	00157	CE  	1996	4	18	96ZZZX1776       	1	19960306	G	7603	10052417715	CONDITION LEVER 			BEECH 	90    	C90         	1152913	CE  										LT SIDE PEDESTAL	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2050A	8015 				LJ813				INSPECTED CONDITION LEVER AFTER OPPOSITE SIDE FAILED.  FOUND LEVER WORN MORE THAN 50 PERCENT THROUGH.  SUBMITTER RECOMME	NDS MORE FREQUENT INSPECTIONS, I.E., EACH 150 HOURS.					1	L	7	2 	3T				3A20    					 
1996041800158	19960418	00158	SO  	1996	4	18	96ZZZX1777       	1	19960216	G	1210	35669163	PLACARD         			PIPER 	PA32  	PA32301     	7103207	SO  										FUEL PORT	WRONG PART      	B	S		BDTR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	8442H					328106098				PARTS BOOK SHOWS 2 DIFFERENT FUEL PORT PLACARDS.  WHEN ORDERING THE PLACARD REQUIRED BY THE P.O.H., THE PIPER FACTORY SU	PERCEDES TO THE PLACARD FOR THE NEWER MODEL.  THIS IS IN ERROR AND PIPER IS CREATING AN UNAIRWORTHY ANSWER -- PN 45-682 	IS S/S FROM PN 35669-163.				1	L	7	1 	3O				A3SO    					 
1996041800159	19960418	00159	CE  	1996	4	18	96ZZZX1778       	1	19960321	G	5312	05121871	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  										CABIN DOORPOST	CRACKED         	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1600 								DURING AN ANNUAL INSPECTION, THE LOWER REAR CABIN DOORPOST BULKHEAD WAS FOUND CRACKED ON THE LEFT AND RIGHT SIDES AT THE	 POINT WHERE THE CABIN FLOOR AND BULKHEAD MEET.  THE CRACK BEGINS AT A RADIUS RELIEF POINT AND PROPAGATES TO THE UPPER M	OUNTING HOLE OF THE LANDING GEAR SUPPORT. THE BULKHEAD PART NUMERS ARE 0512187-1 AND 0512187-2.  THE AIRCRAFT THIS CONDI	TION HAS BEEN FOUND ON ARE CESSNA MODELS 172N, Q, AND P.  THE LOWEST TIME AIRCRAFT HAS 1,600 HOURS TOTAL TIME, THE REST 	OF THE AIRCRAFT INSPECTED HAD IN EXCESS OF 4,100 HOURS.		1	H	7	1 	3O			NT	3A12    					 
1996041800160	19960418	00160	CE  	1996	4	18	96ZZZX1779       	1	19960304	G	5230	5213007200	HINGE           			CESSNA	402   	402C        	207590R	CE  										BAGG DOOR	CRACKED         	I				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3249M	9789 				402C0296				BAGGAGE DOOR WAS OPERATED AND FLIGHT CREW NOTICED BROKEN HINGE.  HINGE IS WHITE METAL AND SUSPECTED TO BE OLD STYLE SLID	E LOCKS THAT CAUSED FRACTURE.  CURRENTLY, S.K. KIT OF HYD ACTUATOR INSTALLED.  SUBMITTER SUGGESTS WHEN LOADING, MAKE SUR	E BAGGAGE DOES NOT STRESS DOOR.				1	L	7	2 	3O				A7CE    					 
1996041800161	19960418	00161	SO  	1996	4	18	96ZZZX1780       	1	19960207	G	7820	6689400	MUFFLER         			PIPER 	PA28  	PA28180     	7102808	SO  										FWD POSITION	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	32103	3623 				287505026				UPON ANNUAL INSPECTION, REMOVAL OF EXHAUST SHROUD FOUND MUFFLER CRACKED AT POINT WHERE SHROUD CHAFED MUFFLER.  YEAR AFTE	R YEAR OF REMOVAL AND REINSTALLATION OF SHROUD TO MUFFLERS FINALLY WORE MUFFLER MATERIAL THIN ENOUGH TO CRACK AND LEAK. 	 SUBMITTER SUGGESTS THOROUGH INSPECTION EACH TIME SHROUD REMOVED (ANYTIME) ESPECIALLY AT CLAMP POINTS.				1	L	7	1 	3O				2A13    					 
1996041800162	19960418	00162	EU  	1996	4	18	96ZZZX1781       	1	19960311	G	7730	GEM610	ENGINE MONITOR  			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										COCKPIT COMM	INTERFERENCE    	B			BF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	25SW	50   				360				GRAPHIC ENGINE MONITOR (MODEL GEM610) RADIATING RF1 TO BOTH COMM RADIOS ON 132.05 MHZ.						1	L	7	1 	3O			RT	A51EU   					 
1996041800163	19960418	00163	EA  	1996	4	18	96ZZZX1782       	2	19960307	G	8520	LW19332S	CONNECTING ROD  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 1 CYLINDER	FAILED          	G				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			CE	09	23NP	1903 				318352007	L40668A			CONNECTING ROD NR 1 CYLINDER FAILED AND CAME THROUGH THE CASE.  THE ROD BEARING HAD NOT SPUN, THE ONLY ROD BOLT FOUND AP	PEARED TO HAVE FAILED AFTER THE FACT.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996041800164	19960418	00164	CE  	1996	4	18	96ZZZX1783       	1	19960112	G	7714	D11125025	TACHOMETER      	MITCH       		CESSNA	172   	172P        	2072436	CE  										ENG TACHOMETER	STICKS          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	97LP	21   			5481	17274398				INSTALLED NEW MITCHELL TACHOMETER IN AIRCRAFT.  NEXT MORNING, TACHOMETER WAS STICKING UNTIL A SHORT WARM-UP.  THREE FLIG	HTS LATER, STRIKING RECURRED.  AT 21.1 TACHOMETER HOURS, STICKING OCCURRED AGAIN ALONG WITH ERRATIC READINGS.  REPLACED 	MITCHELL TACHOMETER WITH RECONDITIONED AC UNIT, NO FURTHER PROBLEMS.				1	H	7	1 	3O			NT	3A12    					 
1996041800165	19960418	00165	CE  	1996	4	18	96ZZZX1784       	1	19960317	G	2822	8110C	PUMP            	WELDON      		BBAVIA	7     	7KCAB       	21101P3	CE  										MAIN SHAFT	SEAL LEAK       	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	13	1840G				15101	79				SEAL FAILED CAUSING FUEL TO VENT THROUGH ELECTRIC (DC) MOTOR, PAST ARCING BRUSHES.  ASSEMBLY INSTALLED ORIGINALLY WITHOU	T CASE VENT AND DRAIN TUBE.  SUBMITTER RECOMMENDS OWNERS OF OLD 7KCAB CITABRIAS BE ADVISED TO CHECK INSTALLATION FOR LEA	KING AND PRESENCE OF CASE VENT AND DRAIN TUBE.  -- FIRE HAZARD --.				1	H	7	1 	3O				A759    					 
1996041800166	19960418	00166	SO  	1996	4	18	96ZZZX1785       	1	19960223	G	5513	MS2106123K	NUTPLATE        		65248000    	PIPER 	PA28  	PA28140     	7102802	SO  										LT/RT STAB TRIM	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	9791W	4113 				2823284				NUT BODY OF ALL 4 NUTPLATES SECURING ARM ASSY STABILIZER TRIM, PN 65248-000, TO LEFT AND RIGHT STABILATOR TRIM TABS EATE	N THROUGH WITH RUST AND SPLIT OPEN.  SUSPECT MOISTURE.  RECOMMENDATION - SPLIT TRIM TABS AND INSPECT NUTPLATES AT EACH A	NNUAL INSPECTION.				1	L	7	1 	3O				2A13    					 
1996041800167	19960418	00167	SO  	1996	4	18	96ZZZX1786       	1	19960301	G	5741		ATTACH FITTING  			PIPER 	PA25  	PA25235     	7102504	SO  										WING FWD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	7685Z	5000 				253838				DURING C/W AD 95-12-01, (FWD SPAR FITTING INSPECTION), HEAVY RUST FOUND INSIDE RT TUBE CLUSTER; MAINLY BEHIND THE CLOSE-	OUT PLATE BETWEEN THE ATTACH FITTING LUGS.  THIS AREA USUALLY CANNOT BE INSPECTED, BUT IN THIS CASE, THE CLOSE-OUT PLATE	 WAS EASILY REMOVED DUE TO THE CORROSION.  THE CARRY-THROUGH TUBE BEHIND THE PLATE WAS FOUND RUSTED THROUGH, BUT EXTERNA	LLY, THE CLUSTER SHOWED NO SIGN OF CORROSION.  THE CLOSE-OUT PLATE HAD TWO SMALL RUST HOLES AT ITS UPPER EDGE.  THIS PLA	TE IS ONLY PARTIALLY WELDED INTO PLACE AND IT APPEARS TO TRAP MOISTURE AGAINST THE LOWER CARRY-THROUGH TUBE.  SUBMITTER 	STATES AD 95-12-01 SHOULD BE REVISED TO ADDRESS THIS AREA REQUIRING REMOVAL OF CLOSE-OUT PLATES.	1	L	7	1 	3O				2A10    					 
1996041800168	19960418	00168	CE  	1996	4	18	96ZZZX1787       	1	19960306	G	5541	04330106	SPAR            			CESSNA	150   	152         	2071835	CE  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	4686L	5738 				15284216				PERFORMING RUDDER SPAR INSPECTION IAW CESSNA SB SEB 94-3, AND FOUND RUDDER SPAR CRACKED.  REPLACED RUDDER IAW SEB 94-3.						1	H	7	1 	3O			NT	3A19    					 
1996041800169	19960418	00169		1996	4	18	96ZZZX1788       	2	19960226	G	7314	5006484	DRIVE GEAR      	LUCAS       	5009986     															FUEL PUMP	FAILED          	B			OL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27					1830					SQUAWK NO FUEL FLOW.  PUMP SHUT DOWN.  FOUND THERE IS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR.  DRIVE SHAFT EASILY T	URNS BY HAND.  SUBMITTER STATED C/W SB NO-21087R5 COULD HAVE PREVENTED EXCESSIVE WEAR ON DRIVE SHAFT INTERNAL SPLINE.																		 
1996041800170	19960418	00170		1996	4	18	96ZZZX1789       	2	19960226	G	7314	5006485	DRIVE SHAFT     	LUCAS       	5009986     															FUEL PUMP	FAILED          	B			OL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27					1830					SQUAWK NO FUEL FLOW.  PUMP SHUT DOWN.  FOUND THERE IS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR.  DRIVE SHAFT EASILY T	URNS BY HAND.  SUBMITTER STATED C/W SB NO-21087R5 COULD HAVE PREVENTED EXCESSIVE WEAR ON DRIVE SHAFT INTERNAL SPLINE.																		 
1996041800171	19960418	00171	EA  	1996	4	18	96ZZZX1790       	2	19960306	G	8530	LW11800	SPRING          			CESSNA	175   	175         	2072502	CE  	LYC   	O360  	O360A1A     	41514	EA  					NR 4 CYL EXH VLV	BROKEN          	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	27	9462B		400  			55262	L1471536A			ROUGH ENGINE OPERATION ABOVE 2,500 RPM'S.  FOUND NR 4 CYLINDER OUTER EXHAUST VALVE SPRING BROKEN.						1	H	7	1 	3O	3	O	NT	3A17    	E286				 
1996041800172	19960418	00172	CE  	1996	4	18	96ZZZX1791       	1	19960321	G	3222	968200183	RETAINER        			BEECH 	58    	58          	1152740	CE  										NLG STRUT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	126LF	2371 				TH440				UPPER NLG COLLAR FOUND CRACKED.  NOSE GEAR REMOVED, UPPER STRUT RETAINER (COLLAR) REPLACED WITH FACTORY NEW.  NLG REINST	ALLED AND CYLCED SHOWING PROPER OPERATION.					1	L	7	2 	3O				3A16    					 
1996041800173	19960418	00173	CE  	1996	4	18	96ZZZX1792       	1	19960306	G	7603	10052417717	CONDITION LEVER 			BEECH 	90    	C90         	1152913	CE  										RT PEDESTAL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2050A	8015 				LJ813				PILOT WAS STARTING RT ENGINE AND WHEN FUEL CONDITION LEVER WAS ADVANCED, THE LEVER BROKE OFF FLUSH WITH THE PEDESTAL.  T	HE ONLY WAY TO SHUT DOWN ENGINE WAS TO CLOSE FIREWALL SHUT-OFF VALVE.  SUBMITTER STATED NEED SET INSPECTION INTERVAL.					1	L	7	2 	3T				3A20    					 
1996041800174	19960418	00174	CE  	1996	4	18	96ZZZX1793       	1	19960306	G	7603	10052417715	CONDITION LEVER 			BEECH 	100   	A100        	1152915	CE  										LT SIDE PEDESTAL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	41BE	9709 				B245				INSPECTED CONDITION LEVER AFTER FAILURE ON OTHER AIRCRAFT.  FOUND WORN 50 PERCENT THROUGH.  SUBMITTER RECOMMENDS INSPECT	IONS AT 150-HOUR INTERVALS.					1	L	7	2 	3T				A14CE   					 
1996041800175	19960418	00175	CE  	1996	4	18	96ZZZX1794       	1	19960306	G	7603	10052417717	CONDITION LEVER 			BEECH 	100   	A100        	1152915	CE  										RT SIDE PEDESTAL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	41BE	9709 				B245				INSPECTED CONDITION LEVERS WHERE WEARS ON PEDESTAL.  FOUND LEVER WORN APPROXIMATELY 50 PERCENT THROUGH.  SUBMITTER RECOM	MENDS MORE FREQUENT INSPECTION.					1	L	7	2 	3T				A14CE   					 
1996041800176	19960418	00176	CE  	1996	4	18	96ZZZX1795       	1	19960310	G	5312	24130013	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										LOWER FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	115HM	4887 				172RG0490				DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED	ALS.  FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 	AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND CO-PILOT SIDE.  SUSPECT CAUSE IS	 INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT.  RECOMMEND INSPECTION OF	 BULKHEAD FOR CRACKS.		1	H	7	1 	3O				3A17    					 
1996041800177	19960418	00177	CE  	1996	4	18	96ZZZX1796       	1	19960310	G	5312	24130014	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										LOWER FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	115HM	4887 				172RG0490				DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED	ALS.  FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS, 172RG PART CATALOG, FIGURE 19, INDEX 16 	AND INDEX 20), BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND CO-PILOT SIDE.  SUSPECT CAUSE I	S INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT.  RECOMMEND INSPECTION O	F BULKHEAD FOR CRACKS.		1	H	7	1 	3O				3A17    					 
1996041800178	19960418	00178	CE  	1996	4	18	96ZZZX1797       	1	19960310	G	5312	24130013	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										LOWER FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9303D	3995 				172RG1113				DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED	ALS.  FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 	AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND COPILOT SIDE.  SUSPECT CAUSE IS 	INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT.  RECOMMEND INSPECTION OF 	BULKHEAD FOR CRACKS.		1	H	7	1 	3O				3A17    					 
1996041800179	19960418	00179	CE  	1996	4	18	96ZZZX1798       	1	19960310	G	5312	24130014	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										LOWER FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9303D	3995 				172RG1113				DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED	ALS.  FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 	AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND COPILOT SIDE.  SUSPECT CAUSE IS 	INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT.  RECOMMEND INSPECTION OF 	BULKHEAD FOR CRACKS.		1	H	7	1 	3O				3A17    					 
1996041800180	19960418	00180	CE  	1996	4	18	96ZZZX1799       	1	19960310	G	5312	24130013	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										LOWER FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9561B	5666 				172RG0881				DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED	ALS.  FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 	AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND COPILOT SIDE.  SUSPECT CAUSE IS 	INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT.  RECOMMEND INSPECTION OF 	BULKHEAD FOR CRACKS.		1	H	7	1 	3O				3A17    					 
1996041800181	19960418	00181	CE  	1996	4	18	96ZZZX1800       	1	19960310	G	5312	241300112	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										LOWER FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9561B	5666 				172RG0881				DURING 100-HOUR INSPECTION, FOUND RUDDER PEDAL TUBE MOUNTING BLOCKS FLEXING UP AND DOWN WHEN PRESSURE WAS APPLIED TO PED	ALS.  FURTHER INSPECTION OF THE PROBLEM REVEALED CRACKS IN THE LOWER BULKHEADS (172RG PART CATALOG, FIGURE 19, INDEX 16 	AND INDEX 20) BELOW THE INBOARD RUDDER PEDAL TUBE MOUNTING BLOCKS ON BOTH THE PILOT AND COPILOT SIDE.  SUSPECT CAUSE IS 	INSUFFICIENT MATERIAL THICKNESS OF BULKHEAD OR BEARING SURFACE UNDER MOUNTING BLOCK BOLT, NUT.  RECOMMEND INSPECTION OF 	BULKHEAD FOR CRACKS.		1	H	7	1 	3O				3A17    					 
1996041800182	19960418	00182	CE  	1996	4	18	96ZZZX1801       	1	19960205	G	3230	EPG185	BRUSH SET       	PRESTOLITE  	105932B     	BEECH 	23    	B24R        	1151253	CE  										GEAR MOTOR	WORN            	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	17	93485	2723 				MC350				AFTER TAKEOFF, GEAR SELECTOR MOVED TO RETRACT POSTION.  GEAR DOWN (GREEN) INDICATORS TURNED OFF, BUT MALFUNCTION (RED) I	NDICATOR ILLUMINATED.  ACFT RETURNED.  GEAR SELECTOR MOVED TO DOWN POSITION.  MALFUNCTION (RED) INDICATOR STILL ILLUMINA	TED AND GEAR FAILED TO EXTEND.  C/B'S CHECKED AND CYCLED, GEAR SELECTOR RECYCLED, STILL GEAR FAILED TO EXTEND.  L/G EXTE	NDED USING EMERG GEAR EXT PROCEDURES.  UPON INSP OF L/G SYS, LANDING GEAR PUMP MOTOR REMOVED.  BOTH OF THE MOTOR'S BRUSH	ES FND WORN.  BRUSHES REPLACED AND COMMUTATOR POLISHED.  REINSTALLED IN ACFT AND CYCLED WITH NO FURTHER PROBLEMS.  BEECH	CRAFT SM, PN 169-590015G, REISSUED:  11-30-79, HAS NO LISTING FOR BRUSH WEAR OR INSP/OH OF GEAR PUMP ASSY.	1	L	7	1 	3O				A1CE    					 
1996041800183	19960418	00183	GL  	1996	4	18	96ZZZX1802       	2	19960214	G	7200		ENGINE          			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					CHIP PLUG	MAKING METAL    	B			LX5R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			GL	19	781LL					45079	CAE830497			HEAVY METAL CONTAMINATION ON UPPER AND LOWER CHIP PLUGS.  METAL FOUND IN NICAD EXTERNAL OIL FILTER ALSO.  ALL CONTAMINAT	ION WAS FERROUS METAL.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996041800185	19960418	00185	EU  	1996	4	18	96ZZZX1804       	1	19960312	G	6220	350A31183107	FLANGE          		31190703    	SNIAS 	350   	AS350B2     	8680813	EU  										M/R STARFLEX	LOOSE BUSHING   	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6095U	800  			M1973	2699				UPON REMOVAL OF RED AND YELLOW STAR-FLEX ASSEMBLY, ONE BUSHING WAS FOUND UNSCREWED FROM THE UPPER ARM.  THE CAUSE MAY BE	 EITHER A POOR BOND OF BUSHING TO STAR-FLEX ARM OR A POOR CLEANING OF BOLT PRIOR TO USE OF NEW MASTONOX AT LAST BEARING 	CHANGE.  SUBMITTER STATED TO ALWAYS CLEAN AND INSPECT PARTS PRIOR TO RE-USE.				1	G	7	1 	3U				H9EU    					 
1996041800240	19960418	00240	SW  	1996	4	18	96ZZZX1805       	1	19960327	G	5400	214031202101	BEAM            			BELL  	214   	214ST       	1182106	SW  										WL 65	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	391AL					28103				THE RT PYLON SUPPORT IS CRACKED 14.50 INCHES FROM THE FORWARD TRANSMISSION ISLAND AFT.  THE CRACK WAS DISCOVERED DURING 	REPLACEMENT OF THE RT CYCLIC SERVO.  THE FOLLOWING COMPONENTS OF THE PYLON STRUCTURE WERE CRACKED:  BEAM (W.O. 65.00). P	YLON SUPPORT ASSY, RT.  BULKHEAD (STA 227.10).				2	G	7	2 	4U				H10SW   					 
1996041800241	19960418	00241	SW  	1996	4	18	96ZZZX1806       	1	19960327	G	5400	214031810108	PYLON SUPPORT   			BELL  	214   	214ST       	1182106	SW  										PYLON RT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	391AL					28103				THE RT PYLON SUPPORT IS CRACKED 14.50 INCHES FROM THE FORWARD TRANSMISSION ISLAND AFT.  THE CRACK WAS DISCOVERED DURING 	REPLACEMENT OF THE RT CYCLIC SERVO.  THE FOLLOWING COMPONENTS OF THE PYLON STRUCTURE WERE CRACKED:  BEAM (W.O. 65.00). P	YLON SUPPORT ASSY, RT.  BULKHEAD (STA 227.10).				2	G	7	2 	4U				H10SW   					 
1996041800242	19960418	00242	SW  	1996	4	18	96ZZZX1807       	1	19960327	G	5412	214031208109	BULKHEAD        			BELL  	214   	214ST       	1182106	SW  										FS 227.10	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	391AL					28103				THE RT PYLON SUPPORT IS CRACKED 14.50 INCHES FROM THE FORWARD TRANSMISSION ISLAND AFT.  THE CRACK WAS DISCOVERED DURING 	REPLACEMENT OF THE RT CYCLIC SERVO.  THE FOLLOWING COMPONENTS OF THE PYLON STRUCTURE WERE CRACKED:  BEAM (W.O. 65.00). P	YLON SUPPORT ASSY, RT.  BULKHEAD (STA 227.10).				2	G	7	2 	4U				H10SW   					 
1996041800243	19960418	00243	EU  	1996	4	18	96ZZZX1808       	1	19960408	G	6220	350A37124420	BOLT            			AEROSP	AS355 	AS355F1     	8680810	EU  										M/R STARFLEX	BROKEN          	B	S	A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376E	1719 				5213				FOUR BOLTS THAT SECURE THE MAIN ROTOR STARFLEX TO THE MAIN ROTOR MAST WERE FOUND BROKEN DURING TROUBLESHOOTING OF AN OUT	-OF-BALANCE CONDITION WITH THE MAIN ROTOR SYSTEM.  THERE ARE A TOTAL OF 12 BOLTS IN THE SYSTEM.  AN ADDITIONAL 3 BOLTS F	AILED WHEN THE SYSTEM WAS BEING DISASEMBLED.  ALL OF THE BOLTS IN THE MAST WERE FOUND SEVERELY CORRODED.				1	G	7	2 	3U				H11EU   					 
1996041800244	19960418	00244	EU  	1996	4	18	96ZZZX1809       	1	19960408	G	6220	350A37124520	BOLT            			AEROSP	AS355 	AS355F1     	8680810	EU  										M/R STARFLEX	BROKEN          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376E	1719 				5213				FOUR BOLTS THAT SECURE THE MAIN ROTOR STARFLEX TO THE MAIN ROTOR MAST WERE FOUND BROKEN DURING TROUBLESHOOTING OF AN OUT	-OF-BALANCE CONDITION WITH THE MAIN ROTOR SYSTEM.  THERE ARE A TOTAL OF 12 BOLTS IN THE SYSTEM.  AN ADDITIONAL 3 BOLTS F	AILED WHEN THE SYSTEM WAS BEING DISASEMBLED.  ALL OF THE BOLTS IN THE MAST WERE FOUND SEVERELY CORRODED.				1	G	7	2 	3U				H11EU   					 
1996041800247	19960418	00247	SW  	1996	4	18	96ZZZX1812       	1	19960226	G	6230	206340101101	SEAL            		206040014105	BELL  	206   	206L1       	1182107	SW  										MAST PLATE	LEAK            	B			ALGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1084Y	27   				45433				SEAL WAS FOUND LEAKING BY MAINTENANCE.  NEW STYLE SEAL, PN 206-340-101-101, WAS LEAKING.						1	G	7	1 	3U				H2SW    					 
1996041800248	19960418	00248	SW  	1996	4	18	96ZZZX1813       	1	19960206	G	6230	206040576105	BEARING         			BELL  	206   	206L4       	1182110	SW  										MAST	PITTED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	171AL	2954 			MB207	52064				FOUND AT 3,000-HOUR OVERHAUL, MAST BEARING OUTER RACE THRUST AREA HAS PITTED AREA - SCRAPPED BEARING.						1	G	7	1 	3U			NC	H2SW    					 
1996041800251	19960418	00251	EU  	1996	4	18	96ZZZX1816       	1	19960209	G	6730	D133768II	ACTUATOR        		10545023    	BOLKMS	105   	BO105C      	5626005	EU  										SERVO DRAIN	CONTAMINATED    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	90761	9254 	27   		0916	S160				DURING BENCH TEST OF ACTUATOR, SERVO VALVE DRAIN CHAMBER SCREW PLUG, PN EE3-2042, REMOVED TO CHECK FOR OIL LEAKAGE.  DRA	IN CHAMBER ABOVE SERVO VALVE AND INSIDE OF SCREW PLUG FOUND FULL OF A HEAVY, GREASE-LIKE CONTAMINATION.  SUSPSECT FORMED	 FOR WATER AND OIL COLLECTING IN CHAMBER FOR A LONG PERIOD OF TIME.				1	G	7	2 	3U				H3EU    					 
1996041800252	19960418	00252	NE  	1996	4	18	96ZZZX1817       	1	19960219	G	2930	07113111321	PRESSURE SWITCH 		0711311104  	SKRSKY	S76   	S76A        	8143006	NE  										SYSTEM 2	STUCK           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476AL	1605 			1514	760003				IN SHOP.  BENCH TEST OF MODULE PERFORMED DUE TO REPORTED DROP OF HYDRAULIC PRESSURE TO ZERO P.S.I. IN SYSTEM 2.  ALL TES	T RESULTS WERE WITHIN LIMITS EXCEPT PRESSURE SWITCH TEST.  ONE-HALF OF SWITCH STUCK ON HIGH PRESSURE SIDE.  (FAILURE OF 	SWITCH NOT RELATED TO ZERO P.S.I. REPORT).				1	G	7	2 	3U				H1NE    					 
1996041800253	19960418	00253	NE  	1996	4	18	96ZZZX1818       	1	19960226	G	5530	7620120049101	BULKHEAD        			SKRSKY	S76   	S76A        	8143006	NE  										VERTICAL PYLON	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N	11732				760088				MAJOR INSPECTION FOUND FORWARD CANTED BULKHEAD WITH INTERGRANULAR CORROSION.  BULKHEAD WAS REPLACED.						1	G	7	2 	3U				H1NE    					 
1996041800254	19960418	00254	NE  	1996	4	18	96ZZZX1819       	1	19960226	G	5531	7620205001106	RIB             			SKRSKY	S76   	S76A        	8143006	NE  										VERTICAL PYLON	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N	11732				760088				MAJOR INSPECTION FOUND VERTICAL STABILIZER RIB WITH INTERGRANULAR CORROSION.  RIB WAS REPLACED.						1	G	7	2 	3U				H1NE    					 
1996041800255	19960418	00255	NE  	1996	4	18	96ZZZX1820       	1	19960226	G	5531	7620105001107	SPAR WEB        			SKRSKY	S76   	S76A        	8143006	NE  										VERTICAL STAB	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N	11732				760088				MAJOR INSPECTION FOUND VERTICAL STABILIZER SPAR WEB DOUBLER WITH INTERGRANULAR CORROSION.  DOUBLER WAS REPLACED.						1	G	7	2 	3U				H1NE    					 
1996041800256	19960418	00256	NE  	1996	4	18	96ZZZX1821       	1	19960226	G	5530	7620205002109	SUPORT          			SKRSKY	S76   	S76A        	8143006	NE  										VERTICAL STAB	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N	11732				760088				MAJOR INSPECTION FOUND VERTICAL STABILIZER SUPPORT, AFT LOWER, CORRODED.  SUPPORT WAS REPLACED.						1	G	7	2 	3U				H1NE    					 
1996041800257	19960418	00257	NE  	1996	4	18	96ZZZX1822       	1	19960226	G	2612	473205	DETECTOR        			SKRSKY	S76   	S76A        	8143006	NE  										NR 1 ENGINE	MALFUNCTION     	B			ALGR	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			SW	03	768AL				0563	760031				DURING LEVEL FLIGHT, NR 1 ENGINE FIRE T-HANDLE ILLUMINATED.  PERFORMED TIGHT TURN, LOOKING FOR INDICATION OF SMOKE.  NOT	ED NO SMOKE, ALL ENGINE INDICATIONS WERE NORMAL.  DURING TROUBLESHOOTING, FOUND ENGINE NR 1 FLAME DETECTOR BAD.  REPLACE	D FLAME DETECTOR.  OPS CHECKED GOOD.				1	G	7	2 	3U				H1NE    					 
1996041800259	19960418	00259	GL  	1996	4	18	96ZZZX1824       	2	19960302	G	7210	23039793	SCAVENGE BODY   		23035179    	SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30S     	03013	GL  					SCAVENGE TUBE	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	701AL	1833 				760238	890772S			UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY.  VISUALLY INSPECTED, SHOWED WEAR AT SCAVENGE BODY SURFACE, AND IN TH	E TUBE BONE.  SCAVENGE TUBE WORN IN SCAVENGE BODY.  SUSPECT CAUSE IS DUE TO IMPROPER FIT OR ALIGNMENT BRACKETS.					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996041800260	19960418	00260	SW  	1996	4	18	96ZZZX1825       	1	19960301	G	5511	222035401101	WEIGHT          			BELL  	230   	230         	1182149	SW  										STABILIZER END	LOOSE           	B			SL3R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	230TX	540  				23014				SCREW WHICH HOLDS STABILIZER END WEIGHT BROKE.  WEIGHT PIVOTED ON REMAINING ATTACH SCREW DURING FLIGHT, THIS MOVEMENT CA	USED WEIGHT TO DEFORM.  NO DAMAGE TO SURROUNDING STRUCTURE OCCURRED.  NEW WEIGHT AND ATTACH SCREW, PN MS27039-1-13, INST	ALLED.				1	G	7	2 	3U			NC	H9SW    					 
1996041800261	19960418	00261	SW  	1996	4	18	96ZZZX1826       	1	19960322	G	2910	MS21910D6	TEE FITTING     			BELL  	230   	230         	1182149	SW  										HYDRAULIC SYSTEM	CRACKED         	B			SL3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	230TX	559  				23014				HYDRAULIC TEE FITTING ON FUSELAGE UPPER DECK SEEPING HYDRAULIC OIL (SYSTEM NR 1).  TEE FITTING FOUND CRACKED, INSTALLED 	NEW TEE FITTING OF HIGHER STRENGTH PER BHT.					1	G	7	2 	3U			NC	H9SW    					 
1996041800267	19960418	00267	GL  	1996	4	18	96ZZZX1832       	2	19960320	G	7323	23057869	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	5074R		916  		28419	1151D	CAE832750			THIS IS THE SECOND TIME THIS UNIT HAS BEEN REMOVED FOR ERRATIC CONDITION.  PILOT MUST MAKE CONSTANT ADJUSTMENTS TO THE G	OVERNOR 'BEEP' WITH EVERY POWER CHANGE.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996042500286	19960425	00286	CE  	1996	4	25	96ZZZX1933       	1	19960305	G	2720	R365240795	CONTROL CABLE   			BEECH 	36    	A36         	1151604	CE  										RT RUDDER	BROKE           	B		A	FV1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	11	999PL					E2577				RIGHT RUDDER CABLE BROKE IN TAIL SECTION AT THE LAST PULLEY.  APPARENTLY, THE CABLE HAD BEEN ROUTED INCORRECTLY FROM THE	 FACTORY.  THE ROUTING OF THIS CABLE AT THE PULLEY IS VERY DIFFICULT TO SEE UNDER NORMAL INSPECTION CONDITIONS.  THERE W	AS NEVER ANY CONTROL PROBLEM OF THE ELEVATOR.  THIS WAS FOUND DURING A PRE-FLIGHT.  SPECIAL INSPECTION SHOULD BE DEVELOP	ED FOR THIS PULLEY.			1	L	7	1 	3O				3A15    					 
1996042500287	19960425	00287	SO  	1996	4	25	96ZZZX1934       	1	19960312	G	6123	A856	MUSHROOM        			PIPER 	PA23  	PA23160     	7102304	SO  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CRACKED         	B	P		UCXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	76HK	11863	5920 			231423		334R		THE PART THAT IS DEFECTIVE INSIDE OF THE PROPELLER IS CALLED THE MUSHROOM, PN A856.  WHILE DISASSEMBLING THE FEATHER SPR	ING KIT DURING IRAN (INSPECT, REPAIR AS NECESSARY) INSPECTION, THE MUSHROOM WAS FOUND BROKEN.  WHILE PERFORMING A DYE-PE	NETRANT INSPECTION ON THE SAME PART OF THE OTHER PROPELLER, FOUND IT, TOO, WAS CRACKED.				1	L	7	2 	3O				1A10    		5	C	P23EA	 
1996042500288	19960425	00288	SO  	1996	4	25	96ZZZX1935       	1	19960312	G	6123	A856	MUSHROOM        			PIPER 	PA23  	PA23160     	7102304	SO  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CRACKED         	B	P		UCXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	76HK	11863	5920 			231423		K1596		BOTH PROPELLERS HAVE APPROXIMATELY 11,863 TOTAL HOURS SINCE NEW AND 5,920.1 HOURS SINCE OVERHAUL.  HOWEVER, BOTH PROPELL	ERS HAVE HAD ROUTINE INTERNAL CORROSION INSPECTIONS OR IRAN INSPECTIONS (INSPECT, REPAIR AS NECESSARY) APPROXIMATELY EVE	RY 2 YEARS AND/OR 2,000 HOURS.				1	L	7	2 	3O				1A10    		5	C	P23EA	 
1996042500289	19960425	00289	SO  	1996	4	25	96ZZZX1936       	1	19960321	G	3250	751501	COLLAR          			PIPER 	PA23  	PA23250     	7102308	SO  										STEERING LIMIT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	204RD					273994				WHILE TROUBLESHOOTING COLLAR NLG SHIMMY PROBLEM, MECHANIC NOTICED THE AFT SHIMMY COLLAR TAB, WHICH LIMITS NLG STEERING, 	WAS BROKEN OFF.  SUSPECT CAUSE WAS EXCEEDING LIMITS WHILE TOWING AIRCRAFT.					1	L	7	2 	3O				1A10    					 
1996042500291	19960425	00291	CE  	1996	4	25	96ZZZX1938       	1	19960321	G	3260	S13771	SWITCH          			CESSNA	210   	T210L       	2073449	CE  										RT DOWNLOCK	INOPERATIVE     	B			CS3R	O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			WP	17	51TP					21060598				PILOT REPORTED NO DOWN AND LOCK INDICATION.  TROUBLESHOT SYSTEM, AND FOUND THE RT MLG DOWNLOCK SWITCH INOPERATIVE.  REPL	ACED SWITCH, OPS CHECKED OK.					1	H	7	1 	3O				3A21    					 
1996042500292	19960425	00292	CE  	1996	4	25	96ZZZX1939       	1	19960226	G	3230	52130285	BRACKET         			CESSNA	421   	421B        	2076014	CE  										LT NLG BRACE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5414J	2366 				421B0873				DURING REMOVAL OF OXYGEN BOTTLE FOR HYDROSTATIC TEST, MECHANIC FOUND THE NOSE GEAR LT DRAG BRACE SUPPORT BRACKET BROKEN.	  AFTER FURTHER INSPECTION, NO OTHER DAMAGE FOUND.  ALSO, THERE WERE SEVERAL FLAT SPOTS ON NOSE TIRE.  SUBMITTER SUSPECT	S THIS HAPPENED DURING HARD NOSE LANDING OR TURNING WHEN GOING TOO FAST.  INSPECTION REVEALED NO DEFECTS ON THE RIGHT DR	AG BRACE SUPPORT BRACKET.			1	L	7	2 	3O				A7CE    					 
1996042500293	19960425	00293	CE  	1996	4	25	96ZZZX1940       	1	19960322	G	5712		RIB             			CESSNA	421   	421B        	2076014	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	53685	5112 				421B0918				TWO CRACKS IN WING RIB AT MLG SIDE BRACE ATTACHMENT AREA WHERE UPLOCK PUSH/PULL TUBE GOES THROUGH RIB.  CESSNA SB ME76-2	 ADDRESSES THIS PROBLEM.					1	L	7	2 	3O				A7CE    					 
1996042500296	19960425	00296	CE  	1996	4	25	96ZZZX1943       	1	19960318	G	7714	A6532	TACH GENERATOR  			CESSNA	421   	421C        	2076016	CE  										ENGINE	BRUSH WEAR      	B			YXRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	781TC				H9414	421C0083				TACHOMETER GENERATOR INTERNAL GEARS ARE WEARING PREMATURELY CAUSING BRUSHES TO FAIL.  NEW REPLACEMENT PART FROM SHELF AV	ERAGED LESS THAN 100 HOURS TIS, BEFORE FAILURE.					1	L	7	2 	3O				A7CE    					 
1996042500297	19960425	00297	SO  	1996	4	25	96ZZZX1944       	1	19960321	G	3250	3227406	TORQUE TUBE     			PIPER 	PA23  	PA23250     	7102308	SO  										NLG STEERING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	6881Y					274230				WHILE INSPECTING NLG AREA, MECHANIC NOTICED STEERING TORQUE TUBE ASSY WAS CRACKED WHERE TUBE FOR TAXI LIGHT CONNECTION I	S MADE.  FURTHER INVESTIGATION FOUND EXCESSIVE FORCE WAS APPLIED WHILE STEERING.  SUBMITTER SUGGESTS CAUSE OF CRACK COUL	D BE FROM EXCEEDING STEERING LIMITS WHILE TOWING AIRCRAFT.				1	L	7	2 	3O				1A10    					 
1996042500298	19960425	00298	EU  	1996	4	25	96ZZZX1945       	1	19960401	G	5280		BRACKET         			SOCATA	TBM   	TBM700      	8682000	EU  										RT MLG DR HINGE	FAILED          	B	S	A	RL8R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	15	292RG	750  				014				RIGHT MAIN GEAR DOOR LIGHT DID NOT EXTINGUISH AFTER TAKEOFF RETRACTION, GEAR WAS CYCLED DOWN, NO GEAR SAFE-LIGHT ON RT M	AIN.  FLY-BY INSPECTION VERIFIED GEAR (RT) NOT EXTENDING.  GEAR-UP LANDING HAD TO BE MADE.  AT RECOVERY OF AIRCRAFT FROM	 RUNWAY, RT FORWARD GEAR INBOARD DOOR HINGE BRACKET WAS FOUND BROKEN AND DOOR LOCKED IN WELL.  PASSENGERS OK.  SUBMITTER	 RECOMMENDED AD TO IMPROVE INBOARD DOORS IAW SB 70-073-32 IMMEDIATELY.			1	L	7	1 	3T			RT	A60EU   					 
1996042500299	19960425	00299	CE  	1996	4	25	96ZZZX1946       	1	19960214	G	2910	651710552	LINE            			CESSNA	500   	S550        	2076607	CE  										MLG RETRACT	CHAFED          	B		A	EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	204A	2477 				S5500008				DURING ACCOMPLISHMENT OF A PHASE INSPECTION, THE LANDING GEAR HYDRAULIC RETRACT LINE WAS FOUND CHAFING ON TWO NUT CLIPS 	LOCATED ON THE COPILOT'S INBOARD SEAT TRACK, FORWARD END.  THE DEFECT TO THE LINE WAS SUCH THAT THE LINE HAD TO BE REPLA	CED.  SUBMITTER STATED THIS IS THE SECOND AIRCRAFT IN RECENT MONTHS FOUND WITH THIS PROBLEM.  THE FIRST WAS A MODEL CE-5	60.  RECOMMEND THIS LINE BE INSPECTED ON S550 AND 560 AIRCRAFT AT FIRST OPPORTUNITY AND REPOSITION OR PROTECT THE LINE A	S NECESSARY.		1	L	7	2 	4F			RT	A22CE   					 
1996042500300	19960425	00300	NE  	1996	4	25	96ZZZX1947       	2	19960408	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A      	30015	NE  					NR 1	FAILED          	B			VU2R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			GL	05	4PG	2734 				5052	350341			LOW OIL PRESSURE LIGHT CAME ON IN CRUISE FLIGHT.  ENGINE SECURED AND LANDED AT IND.  INVESTIGATION DISCLOSED INTERNAL FA	ILURE.  ENGINE REPLACED.  INSPECTION/INVESTIGATION REPORT TO FOLLOW.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1996042500301	19960425	00301	EU  	1996	4	25	96ZZZX1948       	1	19960401	G	2450	LDA150A8C	CONTACTOR       			BRAERO	DH125 	BAE125800A  	1500285	EU  										BUS TIE	TRIPS BREAKER   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	60PM		30   		1251	NA0453				AFTER REPLACING BUS TIE CONTACTOR ON 2-26-96 FOR INTERMITTENT POPPING OF CIRCUIT BREAKER REPLACEMENT, UNIT STARTED RANDO	MLY OPENING FOR NO REASON.  REPLACED AFTER 30 HOURS OF SERVICE.					2	L	7	2 	4F			RT	A3EU    					 
1996042500302	19960425	00302	CE  	1996	4	25	96ZZZX1949       	1	19960325	G	2760	20544470	FILTER          			CESSNA	650   	650         	2076802	CE  										LT WING SPOILER	FAILED          	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	39WP	5517 				6500039				DURING MAINTENANCE INSPECTION OPERATION 10, ITEM CARD 27-20 INSPECTION REVEALED FILTER SEPARATED FROM MOUNTING FLANGE IN	 THE END OF ELBOW FITTING PERMITTING IT TO SLIDE BACK AND FORTH WITHIN THE FITTING.  THIS NEGATES FILTERING.  REPLACED E	LBOW FILTER FITTING.  SUBMITTER STATED IT APPEARS TO BE POOR DESIGN.  THIS IS THE 2ND FITTING FOUND FAILED IN A 6-MONTH 	PERIOD AND 323 FLIGHT HOURS.  (LT WING.)			2	L	7	2 	4F				A9NM    					 
1996042500303	19960425	00303	CE  	1996	4	25	96ZZZX1950       	1	19960328	G	5610	55112854	WINDOW          			CESSNA	501   	501         	2076603	CE  										COPILOT SIDE	CRACKED         	B			KJ4R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	99CK	320  				5010153				IN FLIGHT, PILOT HEARD A LOUD NOISE, THEN NOTICED THE RT COCKPIT WINDOW CRACKED ACROSS THE TOP FORWARD TO AFT.  UPON REM	OVAL, FOUND WINDOW HAD COMPLETELY SEPARATED.  THIS WINDOW HAD ONLY BEEN INSTALLED LESS THAN 2 YEARS.  IT APPEARED ONE RE	TAINER BOLT WAS HARD AGAINST THE MOUNTING HOLE IN THE WINDOW.  THIS AIRCRAFT HAD JUST RECENTLY HAD A PHASE INSPECTION TH	AT INCLUDED AN INSPECTION OF THIS WINDOW.			1	L	7	2 	4F				A27CE   					 
1996042500304	19960425	00304	SW  	1996	4	25	96ZZZX1951       	1	19960321	G	2150	5903828	SEAL            	SUNDSTRANDEM	736778      	GULSTM	690TP 	690C        	7630517	SW  										ACM	FAILED          	B			BOER	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	19	600BM		1076 		0113	11734				AT 18,000 FEET, PILOT SMELLED SMOKE.  CABIN TEMP WENT FULL HOT.  SHUT DOWN ENVIRONMENTAL CONTROL UNIT.  WHEN ON GROUND, 	TROUBLESHOOTING FOUND THE CARBON FACE SEAL OF THE AIR CYCLE MACHINE HAD FAILED ON THE OUTPUT SIDE ALLOWING OIL INTO THE 	CABIN AIR.				1	H	7	2 	3T				2A4     					 
1996042500305	19960425	00305	CE  	1996	4	25	96ZZZX1952       	1	19960209	G	3260	1003810061	SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  										NLG DOWNLOCK	DEFECTIVE       	B			LX5R	O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			GL	19	971LL					BB572				NO NOSE GEAR DOWN AND LOCKED INDICATION AND INTRANSIT LIGHT IN HANDLE REMAINED ON DURING NORMAL EXTENSION.  AN EMERGENCY	 EXTENSION PROVIDED A DOWN AND LOCK LIGHT, BUT INTRANSIT LIGHT STILL REMAINED ON.  INSPECTION AFTER LANDING SHOWED NOSE 	GEAR DOWNLOCK SWITCH DEFECTIVE.  REPLACED SWITCH AND PERFORMED FUNCTIONAL CHECK OF SYSTEM AND RETURNED AIRCRAFT TO SERVI	CE.			1	L	7	2 	4T				A24CE   					 
1996042500306	19960425	00306	EU  	1996	4	25	96ZZZX1953       	2	19960325	G	7310		REGULATOR       			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					ENG FUEL FLOW	MALFUNCTIONED   	B			UA9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	125JJ		906  		B1669R	15	8674			ENGINE WAS INSPECTED FOR SUSPECTED OVERTEMPERATURE PER CREW REPORT.  INSPECTION ACCOMPLISHED PER ROLLS ROYCE OVERHAUL MA	NUAL.  RESULTS SHOWED NO OVERTEMPERATURE EFFECTS.  PRIOR TO DISASSEMBLY, NOTED THE P2 TOWER ON THE FUEL FLOW REGULATOR W	AS LOOSE.  THREE MOUNTING BOLTS HAD PULLED OUT OF THE HOUSING.  THE P2 PORT WAS EXPOSED TO ATMOSPHERE, LOSS OF P2 SIGNAL	 WOULD EFFECT THE ENGINE'S ABILITY TO CORRECTLY METER FUEL.			2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
1996042500307	19960425	00307	EU  	1996	4	25	96ZZZX1954       	1	19960216	G	7830	C41B302133	BUCKET          			ISRAEL	1124  	1124        	4500102	EU  										LT ENG T/R	CORRODED        	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	75BC	4498 			2015	426				DURING A C-CHECK/4,800 HOUR-INSPECTION, FOUND LEFT ENGINE'S LOWER T/R BUCKET, OUTER SKIN HAD CORRSION HOLES FROM INSIDE 	OUT IN TWO SEPARATE LOCATIONS.					2	M	7	2 	4F				A2SW    					 
1996042500308	19960425	00308	SW  	1996	4	25	96ZZZX1955       	1	19960214	G	7332	99120332	SWITCH WIRE     			GULSTM	560   	560         	0141402	SW  	LYC   	O540  	IGO540B1A   	41532	EA  					LT BOOST PRESS	CHAFED          	B			EBVR	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	09	60GL	1152 				0187				AIRCRAFT WAS EXPERIENCING PERIODIC UNCOMMANDED LT BOOST PUMP OPERATION WITH LT BOOST PUMP AND LT FUEL LOW PRESSURE ANNUN	CIATOR LIGHTS COMING ON.  PROBLEM FOUND TO BE CAUSED BY THE LT ENGINE FUEL PRESSURE SWITCH WIRES HAD CHAFED THROUGH AGAI	NST THE SHARP EDGE OF THE FUEL FLOW TRANSMITTER.  SUBMITTER STATED WIRES SHOULD BE INSPECTED ON THESE AIRCRAFT FOR CHAFE	 DAMAGE, PROTECT AND REROUTE AS ABLE.			1	H	7	2 	3O	3	O		6A1     	1E11				 
1996042500309	19960425	00309	NE  	1996	4	25	96ZZZX1956       	2	19960216	G	7250		TURBINE         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE HPT	DAMAGED         	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	402ST	5814 	1362 			5500068	PCE70539			AT THE CUSTOMER'S REQUEST, A BORESCOPE INSPECTION OF THE HIGH PRESSURE TURBINE, IMPELLER, AND THE NR 4 BEARING WAS PERFO	RMED.  THE HIGH PRESSURE TURBINE SHOWED SIGNS OF FOD DAMAGE.  REMOVED THE ENGINE'S HOT SECTION AND FOUND THE H.P. TURBIN	E DAMAGED.  THE DIFFUSER TUBES WORN BEYOND LIMITS.  THE DEFLECTOR RING AND SEGMENTS BROKEN WITH MISSING PIECES, ALSO, TH	E L.P. TURBINE AND STATOR WERE DAMAGED.  SUSPECT MISSING PIECES CAUSED FOD DAMAGE.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1996042500310	19960425	00310	SO  	1996	4	25	96ZZZX1957       	1	19960320	G	4940	103811602	EXCITER         	GARRTT      	GTCP366     	GULSTM	G1159 	G1159       	3953505	SO  										APU IGNITION	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	57HJ	2738 			409247	0194				IGNITION EXCITER WILL NOT PRODUCE OUTPUT VOLTAGE TO PROVIDE APU START.  FAILED TO OPERATE.						2	L	7	2 	4F			RT	A12EA   					 
1996042500311	19960425	00311	EA  	1996	4	25	96ZZZX1958       	1	19960301	G	7920		LINE            			DHAV  	DHC3  	DHC3        	2800202	EA  										ENG OIL SUPPLY	RUPTURED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2634Y					59				AFTER HARD STARTING PROBLEM, ENGINE WAS TURNED BACKWARDS TO CLEAR CYLINDERS.  MAIN OIL SUPPLY LINE WAS HYDRAULICED APART	 AT HOSE AND CLAMP CONNECTION AT CHECK VALVE LOCATED BETWEEN ENGINE AND OIL TANK.  SUBMITTER STATES 'DO NOT TURN ENGINE 	BACKWARDS'.				1	H	7	1 	3R				A815    					 
1996042500312	19960425	00312	CE  	1996	4	25	96ZZZX1959       	1	19960313	G	3320	CR511	DIODE           			CESSNA	441   	441         	2076020	CE  										CABIN INFO	BURNED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			SO	05	33DE	3640 				4410308				PILOT REPORTED DESCENDING THROUGH 12,000 FEET, SMOKE OBSERVED COMING FROM UNDER COPILOT'S INSTRUMENT PANEL.  DECLARED AN	 EMERGENCY, LANDED WITHOUT INCIDENT.  FOUND DIODE ACROSS THE 'NO SMOKE' AND 'FASTEN SEAT BELT'.  SWITCH WAS OVERHEATED A	ND THE CABIN INFO CIRCUIT BREAKER TRIPPED.   REPLACED DIODE, RESET BREAKER SYSTEM, OPERATED NORMAL.				1	L	7	2 	3T			RT	A28CE   					 
1996042500313	19960425	00313	SO  	1996	4	25	96ZZZX1960       	1	19960313	G	2910	1159H201112	GASKET          			GULSTM	G1159 	G1159A      	3970109	SO  										HYD PRESS SYS	FAILED          	B			RO3R	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	03	2MIL					481				DURING NORMAL ENGINE GROUND RUNS PRIOR TO SHUT DOWN, GASKET FAILED.  THE GASKET FITS ON THE T-FITTING, PN AN924-12D, WIT	H REDUCER, PN AN919-16.  THE REDUCER IS CONNECTED TO A LINE WHICH GOES TO THE HYDRAULIC PRESSURE TRANSMITTER FOR THE FLI	GHT HYDRAULIC SYSTEM.  THE FAILURE OF THE GASKET CAUSED BOTH STATIC CONVERTERS TO BE SATURATED WITH SKYDROL FLUID.  BOTH	 CONVERTERS HAD TO BE REPLACED.  CAUSE OF GASKET FAILURE UNKNOWN.  SUBMITTER RECOMMENDS A COVER BE PLACED OVER THE CONVE	RTERS TO PREVENT SKYDROL FLUID FROM COMING IN CONTACT IF THE GASKET WERE TO FAIL IN-FLIGHT.  THIS WOULD PREVENT AN ELECT	RICAL FAILURE AND POSSIBLY A FIRE IN-FLIGHT.	2	L	7	2 	4F				A12EA   					 
1996042500314	19960425	00314	EA  	1996	4	25	96ZZZX1961       	2	19960301	G	7250	3027301	BLADE           		3028821     	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					CT WHEEL	ERODED          	B			CWBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	6739P		993  		2F642	BB628	PCE81899			BORESCOPE INSPECTION FOUND EVIDENCE OF COATING LOSS FROM COMPRESSOR TURBINE BLADES.  COATING WAS ERODED FROM LEADING EDG	ES OF SOME BLADES.  ENGINE WAS SPLIT AT 'C' FLANGE, HOT SECTION INSPECTED FURTHER.  CT WHEEL REMOVED AND SHIPPED TO PRAT	T AND WHITNEY FOR INSPECTION AND DETERMINATION OF CAUSE FOR COATING LOSS.  CT BLADES WERE INSTALLED AT OVERHAUL IN SERVI	CEABLE CONDITION.  THESE BLADES WILL NOT BE REINSTALLED IN THIS ENGINE.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996042500315	19960425	00315	CE  	1996	4	25	96ZZZX1962       	1	19960401	G	7711	PG12A9	TRANSDUCERS     	HONEYWELL   		RKWELL	NA265 	NA26540     	6402608	CE  										ENGINE EPR	ERRATIC         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	308NT				K0136	282090				TRANSDUCER WAS INSTALLED IN AIRCRAFT, TESTED DURING GROUND RUN, AND REMOVED WITH ZERO HOURS TIME IN SERVICE SINCE OVERHA	UL.  E.P.R. READINGS WERE ERRATIC IN ALL POWER RANGES.  UNIT WAS OVERHAULED BY REPAIR STATION ON 3-17-96.  SUBMITTER STA	TED RELIABILITY OF OVERHAULED AND REPAIRED TRANSDUCERS HAS BEEN POOR.  AIRCRAFT TOTAL TIME:  8,602.8 HRS.				2	L	7	2 	4J				A2WE    					 
1996042500316	19960425	00316	CE  	1996	4	25	96ZZZX1963       	1	19960301	G	2150	206SZZC	BEARING         	FAFNIR      		BEECH 	200   	B200        	1152922	CE  										AC DRV SHAFT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8093W	249  				BB1396				AIR CONDITIONING DRIVE PULLEY SUPPORT BEARING ON FORWARD END FAILED AND CAUSED THE QUILL SHAFT TO SHEAR.  SUBMITTER STAT	ED THIS IS THE FOURTH SUCH FAILURE IN 1,390 HOURS OF AIRCRAFT OPERATION.  BEECHCRAFT RECOMMENDS THE QUILL SHAFT BE LUBED	 AT 600 HOURS AND THE BEARINGS BE INSPECTED.				1	L	7	2 	4T				A24CE   					 
1996042500317	19960425	00317	CE  	1996	4	25	96ZZZX1964       	1	19960325	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		195  		1001263D	282019				PUMP WAS REMOVED AND REPLACED DUE TO AFTER SEVERAL MINUTES OF OPERATION, PUMP BECAME EXTREMELY NOISY AND ROUGH INDICATIN	G A POSSIBLE IMPENDING FAILURE.  TIME IN SERVICE AT TIME OF REMOVAL (T.S.M.O.N.):  195.4 HOURS.  PUMP WAS OVERHAULED 10-	2-95.  SUBMITTER STATED THESE PUMPS ARE A 2,000 HOUR TIME-CHANGE ITEM, AND LOW-TIME FAILURES SUCH AS THIS HAVE OCCURRED 	IN FLEET OF 17 AIRCRAFT.  AIRCRAFT TT:  13,406.0 HRS.			2	L	7	2 	4J				A2WE    					 
1996042500318	19960425	00318	CE  	1996	4	25	96ZZZX1965       	1	19960318	G	7120	95910005	MOUNT           			BEECH 	95    	95          	1153402	CE  										TOP RT ATTACH	CRACKED         	B			A14R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										MAIN DYNA FOCAL ATTACH RING TUBE AT TIME OF INSPECTION WAS FOUND TO HAVE CRACKS AT TOP RT ATTACH POINT AND AFT OF ATTACH	 PLATE APPROXIMATELY .75 INCH AND .50 INCH LONG. THIS MOUNT WAS TAGGED UNSERVICEABLE, RED TAG.  REPLACEMENT OF UNIT WAS 	SUGGESTED.				1	L	7	2 	3O				3A16    					 
1996042500319	19960425	00319	CE  	1996	4	25	96ZZZX1966       	1	19960328	G	3060	4E30971	BRUSH BLOCK     			BEECH 	1900  	1900        	1154160	CE  										PROPELLER	ARCING          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										ARCING BETWEEN PROPELLER DEICE BRUSHES CAUSED DAMAGE BEYOND REPAIR.						2	L	7	2 	4T			RT	A24CE   					 
1996042500320	19960425	00320	EU  	1996	4	25	96ZZZX1967       	1	19960409	G	3241	40921	TRANSDUCER      			ISRAEL	1124  	1124        	4500102	EU  										ANTISKID	CORRODED        	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	24SR	6072 			406	332				TRANSDUCER IS CORRODED (SEVERELY PITTED).  THIS CORROSION APPEARS TO START AT THE ETCHING USED TO INSTALL PART NUMBER OR	 SERIAL NUMBER.  THE CORROSION NORMALLY SPREADS ONTO CONNECTOR PLUG AND TENDS TO TRANSFER ONTO AXLE, CORRODING IT.  S/N 	406 AND S/N 431.				2	M	7	2 	4F				A2SW    					 
1996042500321	19960425	00321	SW  	1996	4	25	96ZZZX1968       	1	19960311	G	7120	20606210114	MOUNT           			BELL  	206   	206B3       	1181506	SW  										ENGINE	BROKEN          	B		A	PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	3186N	5036 				3805				PREFLIGHT INSPECTION, MECHANIC FOUND ENGINE LOOSE.  FURTHER INVESTIGATION REVEALED FORWARD RT MOUNT SEVERELY CORRODED AN	D BROKEN IN HALF.  CORROSION AND BREAK WAS CONCEALED BY CLAMSHELL DAMPER.  CORRODED MOUNT GIVEN TO BELL TECH REP.  MOUNT	 WAS REPLACED AND CLAMSHELL REMOVED PER TB 206-89-129A.				1	G	7	1 	3U				H2SW    					 
1996042500322	19960425	00322	EU  	1996	4	25	96ZZZX1969       	1	19960307	G	6220	350A31190703	STARFLEX        			SNIAS 	350   	AS350B1     	8680811	EU  										M/R	SPLINTERED      	B		A	UE3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	216LA	1962 			M2851	2251				ACFT TT:  6,360.8 HRS.  YELLOW AND BLUE LEGS OF STARFLEX SPLINTERED AT MIDPOINT OF LEADING EDGES AND TOP SIDE.  BEYOND L	IMITS PER AS350 MWC 62-20-00-601, PAGE 2.  STARFLEX IS A 2,200-HOUR RETIRE AND HAD 1,961.5 HRS AT OCCURRENCE.  STARFLEX 	WAS REMOVED AND REPLACED WITH SERVICEABLE ONE.  STARFLEX, SN M-2498, TT 1,961.5 HRS WAS SENT TO AMERICAN EUROCOPTER FOR 	EVALUATION.			1	G	7	1 	3U				H9EU    					 
1996042500323	19960425	00323	WP  	1996	4	25	96ZZZX1970       	1	19960330	G	6220	369D21210501	STRAP ASSY      			HUGHES	369   	369F        	4470708	WP  										M/R HUB	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	530R	2078 			0033434519	0005F				AT ACFT TT:  4,378.1 RS, MARCH 30, 1996, DURING POST-FLIGHT INSPECTION OF M/R HUB ASSY - TWO BROKEN STRAPS WERE NOTED ON	 YELLOW BLADE PITCH HOUSING, STRAPS WERE BROKEN AT LEAD-LAG BOLT STACK-UP.  NO BROKEN STRAPS ARE ALLOWED IN THIS AREA. M	/R HUB WAS REMOVED FROM SERVICE.  M/R HUB WAS INSTALLED AUGUST 16, 1993, ACFT TT, 3,120.6 HRS.  TIME IN SERVICE THIS INS	TALLATION, 1,207.5 HRS.  S/N 003343-4519 THROUGH 4523.			1	G	7	1 	3U				H3WE    					 
1996042500324	19960425	00324	EU  	1996	4	25	96ZZZX1971       	1	19960219	G	5512	350A13002061	SKIN            			SNIAS 	350   	AS350B      	8680801	EU  										HORIZ STAB AFT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	37SH	5604 				1288				DURING REPLACEMENT OF HORIZONTAL STABILIZER SKINS AFT, FOUND SKINS CRACKED AT THE UPPER, INBOARD ATTACHMENT AREA.  REPLA	CING THE SKINS DETAILED ABOVE DUE TO OTHER DEFECTS, BUT HAPPENED TO FIND THESE CRACKS.  RECOMMEND CLOSER ATTENTION TO TH	E AREA ADJACENT THE STABILIZER ATTACHMENT UPPER AND LOWER SURFACES DURING ROUTINE INSPECTIONS.				1	G	7	1 	3U				H9EU    					 
1996042500325	19960425	00325	EU  	1996	4	25	96ZZZX1972       	1	19960219	G	5512	350A13002062	SKIN            			SNIAS 	350   	AS350B      	8680801	EU  										HORIZ STAB AFT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	37SH	5604 				1288				DURING REPLACEMENT OF HORIZONTAL STABILIZER SKINS AFT, FOUND SKINS CRACKED AT THE UPPER, INBOARD ATTACHMENT AREA.  REPLA	CING THE SKINS DETAILED ABOVE DUE TO OTHER DEFECTS, BUT HAPPENED TO FIND THESE CRACKS.  RECOMMEND CLOSER ATTENTION TO TH	E AREA ADJACENT THE STABILIZER ATTACHMENT UPPER AND LOWER SURFACES DURING ROUTINE INSPECTIONS.				1	G	7	1 	3U				H9EU    					 
1996042500326	19960425	00326	WP  	1996	4	25	96ZZZX1973       	1	19960402	G	6220	369D21334501	PIVOT BEARING   			HUGHES	369   	369D        	4470706	WP  										M/R HUB	PLATE WORN      	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3115Y		89   			500716D				DURING ANNUAL INSPECTION, 3 STRIKER PLATES FOUND WORN BEYOND LIMITS AND ALL 5 PIVOT BEARINGS WORN FROM .030 INCH TO .040	 INCH BEARING TO PART NUMBER FIT.					1	G	7	1 	3U				H3WE    					 
1996042500327	19960425	00327	SW  	1996	4	25	96ZZZX1974       	1	19960325	G	6510	412340102001	BOOT            			BELL  	412   	412         	1182202	SW  										T/R DRIVE	DEBONDED        	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	92115	39   			CB1067	36117				INSPECTION FOUND BOOT DEBONDED.  REPLACED WITH NEW BOOT.						1	G	7	2 	4U				H4SW    					 
1996042500328	19960425	00328	SW  	1996	4	25	96ZZZX1975       	1	19960325	G	6510	214040659005	COUPLING        			BELL  	412   	412         	1182202	SW  										T/R	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	92115	39   			A964	36117				INSPECTION FOUND COUPLING TEETH PITTED.  REPLACED WITH NEW COUPLING.						1	G	7	2 	4U				H4SW    					 
1996042500329	19960425	00329	SW  	1996	4	25	96ZZZX1976       	1	19960325	G	6510	214040657003	COUPLING        			BELL  	412   	412         	1182202	SW  										T/R	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	92115	39   			A716	36117				INSPECTION FOUND COUPLING TEETH PITTED.  REPLACED WITH NEW COUPLING.						1	G	7	2 	4U				H4SW    					 
1996042500330	19960425	00330	SW  	1996	4	25	96ZZZX1977       	1	19960325	G	6510	214040657003	COUPLING        			BELL  	412   	412         	1182202	SW  										T/R	PITTED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	92115	39   			A710	36117				INSPECTION FOUND COUPLING TEETH PITTED.  REPLACED WITH NEW COUPLING.						1	G	7	2 	4U				H4SW    					 
1996042500331	19960425	00331	SW  	1996	4	25	96ZZZX1978       	1	19960313	G	6410	206010765001	BEARING         		206016201127	BELL  	206   	206L3       	1182108	SW  										T/R BLADE	CRACKED         	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	617DE				CS6338	51138				INNER RACE CRACKED FROM EDGE OF RACE TOWARDS CENTER OF BALL.  REPLACED WITH NEW PN 206-310-105-101 BEARINGS WITH REDUCED	 CROSS-SECTION OF INNER RACE.					1	G	7	1 	3U				H2SW    					 
1996042500332	19960425	00332	SW  	1996	4	25	96ZZZX1979       	1	19960313	G	6410	206010765001	BEARING         		206016201127	BELL  	206   	206L3       	1182108	SW  										T/R BLADE	CRACKED         	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	617DE				CS6364	51138				INNER RACE CRACKED FROM EDGE OF RACE TOWARDS CENTER OF BALL.  REPLACED WITH NEW PN 206-310-105-101 BEARINGS WITH REDUCED	 CROSS-SECTION OF INNER RACE.					1	G	7	1 	3U				H2SW    					 
1996042500333	19960425	00333	WP  	1996	4	25	96ZZZX1980       	1	19960403	G	6420	369D21800501	SWASHPLATE      			HUGHES	369   	369D        	4470706	WP  										T/R DRIVE	BEARING ROUGH   	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3115Y				SH0715	500716D				DURING ANNUAL INSPECTION, THE T/R SWASHPLATE BEARING WAS FOUND ROUGH.  REPLACED THE T/R SWASHPLATE.						1	G	7	1 	3U				H3WE    					 
1996042500334	19960425	00334	EU  	1996	4	25	96ZZZX1981       	1	19960330	G	5520	10902000293	ELEVATOR        			AGUSTA	A109  	A109A2      	0260120	EU  										LT SYNC ELEV	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1VH	3574 				7273				LEFT SYNC ELEVATOR SHOWED CRACKS ALONG EDGE AND INTO ATTACH FITTING HOLES.  RIB PN 109-0200-04-7 AND PN 109-0200-02-59. 	 FURTHER DISASSEMBLY REVEALED CRACKS IN FORWARD SPAR AND SPAR DOUBLER PN 104-0200-02-49 AND AFT SPAR AND AFT SPAR DOUBLE	R PN 109-0200-02-33.  CRACKING APPEARS TO DEVELOP FROM LOOSENING OF THE ATTACH ANGLES LOCATED ON THE SPARS AND ATTACHED 	TO THE INBOARD RIB.			1	G	7	2 	3U				H7EU    					 
1996042500335	19960425	00335	EU  	1996	4	25	96ZZZX1982       	1	19960330	G	5520	10902000294	ELEVATOR        			AGUSTA	A109  	A109A2      	0260120	EU  										RT SYNC ELEV	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	55NW	3580 				7267				RIGHT SYNC ELEVATOR CRACKS SHOWED ALONG EDGE OF INBOARD RIB.  RIB PN 109-8200-02-59 AND PN 109-0200-04-7.  FURTHER DISAS	SEMBLY REVEALED CRACKS IN FORWARD SPAR AND SPAR DOUBLER PN 109-0200-02-49 AND AFT SPAR AND DOUBLER PN 109-0200-02-33.  C	RACKING APPEARS TO DEVELOP FROM LOOSENING OF THE ATTACH ANGLES LOCATED ON THE SPARS AND ATTACHED TO THE INBOARD RIB.				1	G	7	2 	3U				H7EU    					 
1996042500336	19960425	00336	EU  	1996	4	25	96ZZZX1983       	1	19960330	G	6520	1090372401	ATTACH FITTING  			AGUSTA	A109  	A109A2      	0260120	EU  										90 DEG GRBOX	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1VH	3574 				7273				INSPECTION FOUND A CRACK IN THE 90 DEGREE GEARBOX ATTACH FITTING UPPER LT CORNER RUNNING LATERALLY ACROSS TO THE UPPER V	ERTICAL FIN ATTACH PLATE.  ADDITIONAL PORTS CRACKED INCLUDE PN 109-0372-41-5 AND PN 109-0372-41-3.					1	G	7	2 	3U				H7EU    					 
1996042500363	19960425	00363	CE  	1996	4	25	96ZZZX1984       	1	19960301	G	5741	0411129	BLOCK           			CESSNA	170   	170B        	2072306	CE  										SPAR BEARING	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2364C					20352				SPAR BEARING BLOCK (FWD WING SPAR ATTACH POINT) FOUND SEVERELY CORRODED.						1	H	7	1 	3O				A799    					 
1996042500364	19960425	00364	CE  	1996	4	25	96ZZZX1985       	1	19960325	G	2510	05112421	SEAT STOP       			CESSNA	172   	172         	2072402	CE  										PILOT AFT STOP	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4642J					17273658				FOUND PILOT'S AFT SEAT STOP BROKEN.  IF UNNOTICED, REAR SEAT ROLLERS MAY DISCONNECT FROM RAILS MAKING SEAT PINS NON-FUNC	TIONAL.  WITH SEAT PINS NOT POSITIONED PROPERLY, SEAT MAY SLIDE AFT ON TAKEOFF AND CREATE POSSIBLE DEPARTURE STALL CONFI	GURATION.				1	H	7	1 	3O			NT	3A12    					 
1996042500365	19960425	00365	CE  	1996	4	25	96ZZZX1986       	1	19960329	G	2720	15371	RUDDER PEDAL    			BBAVIA	8     	8KCAB       	2110612	CE  										LT FORWARD	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	5061K	65   				56079				SUBMITTER STATES THIS IS THE THIRD FAILURE OF THE NEW STYLE RUDDER PEDALS FROM AMERICAN CHAMPION AIRCRAFT.  IT IS THE TH	IRD BROKEN RUDDER PEDAL IN 298.0 HRS.					1	H	7	1 	3O				A21CE   					 
1996042500367	19960425	00367	GL  	1996	4	25	96ZZZX1988       	3	19960307	G	6110	A18916	PILOT TUBE      			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP TUBE NR 3	CRACKED         	B	S		LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17								BU3996		INSPECTION FOUND PROPELLER PILOT TUBE NR 3 CRACKED.						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1996042500368	19960425	00368	CE  	1996	4	25	96ZZZX1989       	1	19960314	G	2710	051010513	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  										LT AILERON	FRAYED          	B	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	9197H	2856 				17266009				DURING ROUTINE ANNUAL INSPECTION, THE AILERON BALANCE CABLE WAS FOUND FRAYED WITH APPROXIMATELY 50 PERCENT OF THE STRAND	S BROKEN.  LOCATION OF THIS DEFECT WAS WHERE THE CABLE PASSED BY THE THREE NYLON CABLE PULLEYS IN THE CENTER FUSELAGE AR	EA, ACCESSED THROUGH THE CABIN HEADLINER.  THERE WERE NO MARKS ON ANY ADJACENT COMPONENTS TO INDICATE CHAFING.  THE PULL	EY WAS FREE AND ROTATING NORMALLY.  NO SPECIFIC CAUSE COULD BE DETERMINED.			1	H	7	1 	3O			NT	3A12    					 
1996042500369	19960425	00369		1996	4	25	96ZZZX1990       	4	19960130	G	6122	B20258	FLYWEIGHT BASE  	MCAULY      	DCFS290D2BT6	CESSNA	421   	421C        	2076016	CE  										GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	145CP				770233	421C0329				INSPECTION FOUND GOVERNOR FLYWEIGHT BASE CRACKED.						1	L	7	2 	3O				A7CE    					 
1996042500370	19960425	00370		1996	4	25	96ZZZX1991       	4	19960130	G	6122	B20431	DRIVE DISC      	MCAULY      	DCFS290D2BT6	CESSNA	421   	421C        	2076016	CE  										GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	145CP				770233	421C0329				INSPECTION FOUND GOVERNOR DAMPENER DRIVE DISC CRACKED.  SUSPECT CAUSE AS POSSIBLE DETONATION OF ENGINE.						1	L	7	2 	3O				A7CE    					 
1996042500371	19960425	00371		1996	4	25	96ZZZX1992       	4	19960130	G	6122	B20431	DRIVE DISC      	MCAULY      	DCFS290D2BT6	CESSNA	421   	421C        	2076016	CE  										GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	145CP				770234	421C0329				INSPECTION FOUND GOVERNOR DAMPENER DRIVE DISC CRACKED.  SUSPECT CAUSE AS POSSIBLE DETONATION OF ENGINE.						1	L	7	2 	3O				A7CE    					 
1996042500372	19960425	00372		1996	4	25	96ZZZX1994       	4	19960130	G	6122	B20258	FLYWEIGHT BASE  	MCAULY      	DCFS290D2BT6	CESSNA	421   	421C        	2076016	CE  										GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	145CP				770234	421C0329				INSPECTION FOUND GOVERNOR FLYWEIGHT BASE CRACKED.						1	L	7	2 	3O				A7CE    					 
1996042500373	19960425	00373	GL  	1996	4	25	96ZZZX1995       	3	19960214	G	6114	771226	HUB             			CESSNA	206   	U206F       	2073333	CE  						MCAULY	3A32C	3A32C*      	GL  	BLADE RETAIN	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	8498Q	4513 				U20603356		771226		INSPECTION FOUND CRACK IN BLADE RETENTION THREAD OF HUB SOCKET.						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1996042500374	19960425	00374	GL  	1996	4	25	96ZZZX1996       	3	19960130	G	6114	B3252	FORK            			GULSTM	G1159 	GIV         	3980115	SO  						HARTZL	HCC3Y	HCC3YR      	GL  	90-DEG RADIUS	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	500DJ	2984 	1429 			1169		CK1256		INSPECTION FOUND ACTUATING FORK IS CRACKED WHERE THE BLADE BLOCKS REST IN FORK AT THE 90-DEGREE RADIUS.						2	L	7	2 	4F			RT	A12EA   		5	C	P25EA	 
1996042500375	19960425	00375	GL  	1996	4	25	96ZZZX1997       	3	19960214	G	6110	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	BEARING SEAT	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	68239					340A1276		702328		PROPELLER INSPECTION FOUND FERRULE CRACKED AT BEARING SEAT.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1996042500376	19960425	00376	GL  	1996	4	25	96ZZZX1998       	3	19960214	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	BLADE RETAIN	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		2274 	924  					801427		INSPECTION FOUND CRACK IN BLADE RETENTION THREADS.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1996042500377	19960425	00377	GL  	1996	4	25	96ZZZX1999       	3	19960130	G	6110	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BEARING SEAT	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17								739572		INSPECTION FOUND PROPELLER FERRULE CRACKED WHERE BEARING SEATS IN FERRULE RADIUS.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1996042500378	19960425	00378	GL  	1996	4	25	96ZZZX2000       	3	19960329	G	6110	A251314	BOLT            			CESSNA	172   	172         	2072402	CE  						MCAULY	1C172	1C172EM     	GL  	PROPELLER	DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17								E5566		PROPELLER FORGING FOLD NEAR FULL LENGTH OF BOLTS, QUANTITY, 2 EACH.						1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1996042500379	19960425	00379	GL  	1996	4	25	96ZZZX2001       	3	19960130	G	6114	676237	HUB             			CESSNA	310   	310L        	2074230	CE  						MCAULY	3AF32C	3AF32C*     	GL  	NR 3 SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	167JS	1466 	393  			310L0129		676237		INSPECTION FOUND CRACK IN BLADE RETENTION THREADS OF NR 3 HUB SOCKET.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1996042500380	19960425	00380		1996	4	25	96ZZZX2002       	4	19960320	G	6122	B3124	CONTROL SHAFT   		F411B       															GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					D2067U					INSPECTION FOUND GOVERNOR CONTROL SHAFT WITH FOUR RADIAL CRACKS IN FLANGE.																			 
1996042500381	19960425	00381		1996	4	25	96ZZZX2003       	4	19960329	G	6122	42832	FLYWEIGHT BASE  	HARTZL      	F23A        															GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					11361T					INSPECTION FOUND GOVERNOR FLYWEIGHT CRACKED.																			 
1996042500382	19960425	00382		1996	4	25	96ZZZX2004       	4	19960329	G	6122	B20591	DRIVE GEAR      	MCAULY      	C2920D4T2   															GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					811954					INSPECTION FOUND GOVERNOR DRIVE GEAR CRACKED.																			 
1996042500383	19960425	00383		1996	4	25	96ZZZX2005       	4	19960328	G	6122	20155	FLYWEIGHT       	MCAULY      	DCFS290D1ATE	CESSNA	414   	414         	2075908	CE  										GOVERNOR	WELD CRACKED    	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					721284					INSPECTION FOUND CRACKED WELD ON FLYWEIGHT IN THE GOVERNOR.						1	L	7	2 	3O			RT	A7CE    					 
1996042500384	19960425	00384		1996	4	25	96ZZZX2006       	4	19960329	G	6122	20155	FLYWEIGHT       	MCAULY      	DCFS2902BT6 															GOVERNOR	WELDS CRACKED   	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					750722					INSPECTION FOUND GOVERNOR FLYWEIGHT WELDS CRACKED.																			 
1996042500385	19960425	00385		1996	4	25	96ZZZX2007       	4	19960307	G	6122	41832	FLYWEIGHT BASE  	HARTZL      	F624Z       	PIPER 	PA31  	PA31350     	7103110	SO  										GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					D178T					INSPECTION FOUND GOVERNOR FLYWEIGHTS CRACKED.						1	L	7	2 	3O				A20SO   					 
1996042500386	19960425	00386		1996	4	25	96ZZZX2008       	4	19960307	G	6122	42832	FLYWEIGHT BASE  	HARTZL      	F411B       															GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B482U					INSPECTION FOUND GOVERNOR FLYWEIGHT BASE CRACKED.																			 
1996042500387	19960425	00387		1996	4	25	96ZZZX2009       	4	19960307	G	6122	B3124	CONTROL SHAFT   	HARTZL      	F411B       	PIPER 	PA32  	PA32*       		SO  										GOVERNOR SPEED	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B982U					INSPECTION FOUND GOVERNOR SPEED CONTROL SHAFT CRACKED.						1	L	7	1 	3O				A3SO    					 
1996042500388	19960425	00388		1996	4	25	96ZZZX2010       	4	19960307	G	6122	41832	FLYWEIGHT BASE  	HARTZL      	F411B       	PIPER 	PA32  	PA32R300    	7103213	SO  										GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B123811					INSPECTION FOUND GOVERNOR FLYWEIGHT BASE CRACKED.						1	L	7	1 	3O				A3SO    					 
1996042500389	19960425	00389		1996	4	25	96ZZZX2011       	4	19960307	G	6122	C4191	DRIVE SHAFT     	HARTZL      	F411B       															GOVERNOR	GEAR CRACKED    	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B982U					INSPECTION FOUND GOVERNOR DRIVE GEAR CRACKED.																			 
1996042500390	19960425	00390		1996	4	25	96ZZZX2012       	4	19960307	G	6122	D4191	IDLER GEAR      	HARTZL      	F624Z       															GOVERNOR	TEETH CRACKED   	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					A4913T					INSPECTION FOUND GOVERNOR IDLER GEAR TEETH CRACKED.																			 
1996042500391	19960425	00391		1996	4	25	96ZZZX2013       	4	19960307	G	6122	D20541	DRIVE SHAFT     	MCAULY      	C290D4T4    															GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					784396					INSPECTION FOUND GOVERNOR DRIVE SHAFT CRACKED.																			 
1996042500392	19960425	00392		1996	4	25	96ZZZX2014       	4	19960307	G	6122	D20432	DRIVE SHAFT     	MCAULY      	DCFS290D2T3 															GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					751481					INSPECTION FOUND GOVERNOR DRIVE SHAFT CRACKED.																			 
1996042500393	19960425	00393		1996	4	25	96ZZZX2015       	4	19960307	G	6122	B20431	SPRING DRIVE    	MCAULY      	DCFS290D2T3 															GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					761993					INSPECTION FOUND GOVERNOR CRACKED AT SPRING HOLE.																			 
1996042500394	19960425	00394		1996	4	25	96ZZZX2016       	4	19960307	G	6122	B20431	SPRING DRIVE    	MCAULY      	DCFS290D2T6 	CESSNA	421   	421C        	2076016	CE  										GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					770234					INSPECTION FOUND GOVERNOR SPRING DRIVE HOLDING FLYWEIGHTS CRACKED AT SPRING HOLE.						1	L	7	2 	3O				A7CE    					 
1996042500396	19960425	00396	GL  	1996	4	25	96ZZZX2018       	3	19960307	G	6110	A18912	PILOT TUBE      			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP TUBE NR 3	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	118WC	4712 				31T8020020		BU3995		INSPECTION FOUND PROPELLER PILOT TUBE, NR 3, HAS LONGITUDINAL CRACK.						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1996042500397	19960425	00397	GL  	1996	4	25	96ZZZX2019       	3	19960307	G	6110	A18912	PILOT TUBE      			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP TUBE NR 1	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	118WC	4712 				31T8020020		BU3995		INSPECTION FOUND PROPELLER PILOT TUBE, NR 1, HAS LONGITUDINAL CRACK.						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1996042500398	19960425	00398	EA  	1996	4	25	96ZZZX2020       	2	19960401	G	7414	M3056	DISTRIBUTOR GEAR	SLICK       	6363        	PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					MAGNETO	DAMAGED         	B			WC7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	202SE					4622092	C908761A			'ENGINE WON'T START' - 766.8 HRS HOBBS.  FOUND DISTRIBUTOR GEAR M3056 BURNED.  FOUND THE MS20822 FITTING TO PRESSURIZE T	HE MAGNETO HAD BEEN SCREWED INTO THE OUTER CASE AND BOTTOMED OUT AGAINST THE DISTRIBUTOR HEAD M3820.  SUBMITTER SURMISES	 THE LACK OF PRESSURIZING AIR CAUSED ARCING THAT, IN TURN, BURNED THE NYLON DISTRIBUTOR GEAR M3056.  REPLACED MAGNETO, T	RIMMED FITTING MS20822 SO IT WOULD NOT COME IN CONTACT WITH DISTRIBUTOR HEAD.  REF:  40-2350.			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
1996042500399	19960425	00399	SO  	1996	4	25	96ZZZX2021       	1	19960206	G	3411		STATIC SYSTEM   			PIPER 	PA28  	PA28151     	7102805	SO  										ENCODER	NOT CONNECTED   	B			JA6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	32367					287515139				BLIND ALTITUDE ENCODER HAD BEEN DISCONNECTED FROM STATIC SYSTEM AND WAS SAMPLING CABIN AIR RATHER THAN THAT WHICH THE AL	TIMETER WAS SENSING.  RECONNECTED WITH APPROVED HARDWARE, LEAK TESTED STATIC SYSTEM, AND PERFORMED TEST PER FAR 43 APPEN	DICES E AND F.  CERTIFIED AIRCRAFT TO BE IN C/W FAR 91.411 AND 91.413.				1	L	7	1 	3O				2A13    					 
1996042500400	19960425	00400	CE  	1996	4	25	96ZZZX2022       	1	19960321	G	2810	41534	TANK            			BBAVIA	8     	8KCAB       	2110612	CE  										LT FUEL SYSTEM	BAFFLE BROKEN   	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	67ND	1728 				66792				WITH LEFT TANK FULL, FUEL GAUGE READ 'ZERO' GALLONS.  REMOVED SENDER AND CHECKED, OPERATION NORMAL.  FOUND FUEL TANK BAF	FLE BROKEN OFF AND LAYING ON BOTTOM OF TANK.  SENDER PROBLEM TRACED TO FLOAT BEING CAUGHT ON LOOSE BAFFLE LAYING IN TANK	.  (REMOVED TANK FOR REPAIR).				1	H	7	1 	3O				A21CE   					 
1996042500401	19960425	00401	SO  	1996	4	25	96ZZZX2023       	1	19960206	G	3411		TUBING          			PIPER 	PA28  	PA28151     	7102805	SO  										STATIC SYSTEM	WRONG PART      	B			JA6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	32367					287515139				FOUND DEGRADED/LEAKY SURGICAL RUBBER-TYPE TUBING STRETCHED OVER 'AN' THREADED FITTINGS.  THE MATERIAL AND METHOD USED IS	 UNACCEPTABLE FOR THE APPLICATION.  REPLACED WITH AN/MS FITTINGS AND MIL-H HOSE.					1	L	7	1 	3O				2A13    					 
1996042500402	19960425	00402	SO  	1996	4	25	96ZZZX2024       	1	19960321	G	5741	644120	ATTACH          			PIPER 	PA25  	PA25235     	7102504	SO  										RT WING FWD ATT	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	7318Z	2075 				253265				INSPECTED AIRCRAFT FOR NDT-UTT PER AD 95-12-01, RIGHT FORWARD WING SPAR ATTACH.  PRELIMINARY INSPECTION SHOWED VISIBLE P	OCKET INBETWEEN THE STEEL PLATES.  WHEN TESTING UTT, A LOW READING WAS DETECTED IN THIS AREA WHICH WAS BELOW THE MINIMUM	 THICKNESS ALLOWED.  THE EAR HAD BEEN WELDED AT ONE TIME TO REPAIR WHAT LOOKED LIKE IT COULD HAVE BEEN A CRACK.				1	L	7	1 	3O				2A10    					 
1996042500403	19960425	00403	EA  	1996	4	25	96ZZZX2025       	2	19960319	G	8530		PISTON ROD      			STOLAM	RC3   	RC3         	3080202	SO  	FRNKLN	6A8215	6A8215B9F   	27030	EA  					FWD RT CYLINDER	FAILED          	G				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CL	CLIMB          	1			WP	25	6496K	1020 	30   			762	23714			AIRCRAFT LOST POWER ON TAKEOFF.  PILOT LANDED IN FIELD AT END OF RUNWAY.  FOUND FORWARD RIGHT PISTON ROD HAD LOST END CA	P (BOLTS FAILED) AND WENT THROUGH CRANKCASE BREAKING STARTER.  ENGINE HAD ONLY 30.0 HRS SMOH.					1	H	7	1 	3O	3	O		A769    	E242				 
1996042500405	19960425	00405	SO  	1996	4	25	96ZZZX2027       	1	19960403	G	3230	95219902	STUD            			PIPER 	PA34  	PA34200     	7103405	SO  										RT MLG BRACE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	15839	3214 				347350100				IAW AD 95-20-07, MLG SIDE BRACE STUD INSPECTION, RT STUD MAGNETIC PARTICLE INSPECTION FOUND STUD CRACKED; THUS, REMOVED 	FROM SERVICE.  RECORDS REVIEWED NOTED RT MLG TRUNNION REPLACED MARCH, 1994, REASON NOT MENTIONED.  AFT WING MOD PIPER KI	T 760-977 OUTBOARD OF GEAR AND WING RIB INSTALLED OUTBOARD OF TRUNNION.  POSSIBLE GEAR-UP ACCIDENT MAY HAVE WEAKENED SID	E BRACE STUD.			1	L	7	2 	3O				A7SO    					 
1996042500406	19960425	00406	SO  	1996	4	25	96ZZZX2028       	2	19960326	G	8530		CYLINDER        			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	9438M		1117 			U20604546	248770R			WHEN TRYING TO REMOVE CYLINDERS FOR A TOP OVERHAUL, FOUND TORQUES VERY HIGH TO ALMOST FINGER TIGHT ON CYLINDER STUDS AND	 THROUGH-BOLTS.  THIS ENGINE HAS TORQUE PASTE STILL IN PLACE - ONE-HALF INCH DRIVE AIR WRENCH DID NOTHING - HAD TO CHISE	L TWO NUTS OFF SO FAR - TWO CYLINDERS TO GO.  SUBMITTER SUGGESTS QUALITY CONTROL SEVERELY LACKING ON THIS FACTORY REMANU	FACTURED ENGINE.  ENGINE WAS INSTALLED JUNE '89.  NO PRIOR PROBLEMS.  BROKE CYLINDER WRENCH ON NR 2 CYLINDER.			1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1996042500681	19960425	00681	CE  	1996	4	25	96ZZZX2029       	1	19960325	G	2810		FUEL CAP        			CESSNA	182   	182E        	2072712	CE  										FUEL TANK	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	3308Y	2793 				18254308				FUEL CAPS ARE ALLOWING WATER TO BE INTRODUCED INTO THE FUEL TANKS.  SUBMITTER STATED THIS CAN CAUSE ENGINE FAILURE.						1	H	7	1 	3O			NT	3A13    					 
1996042500682	19960425	00682	CE  	1996	4	25	96ZZZX2030       	1	19960318	G	3230		DOWNLOCK        			BEECH 	55    	95B55       	1152706	CE  										LT MLG	LOW TENSION     	B			K5SR	K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	11	193L					TC1055				LEFT MAIN TIRE WAS SKIDDED ON RUNWAY TO THE POINT OF TIRE FAILURE.  LEFT MAIN GEAR THEN COLLAPSED.  INVESTIGATION REVEAL	ED LANDING GEAR DOWNLOCK TENSION WAS 15-20 POUNDS.  BEECHCRAFT SM REQUIRES DOWNLOCK TENSION TO BE 45-65 POUNDS.  IT IS S	UPPOSED THE ADDITIONAL LOADS IMPOSED BY THE TIRE FAILURE CAUSED THE DOWNLOCK TO MOVE OVER CENTER DUE TO THE LOW DOWNLOCK	 TENSION.			1	L	7	2 	3O				3A16    					 
1996042500683	19960425	00683	NE  	1996	4	25	96ZZZX2031       	1	19960401	G	3233	180029005	ACTUATOR        			CONAER	LA4   	LA4200      	5110310	NE  										NLG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	85213	307  				1094				NOSE GEAR ACTUATOR PISTON ASSY (ROD AND PISTON) RECEIVES A SIDE LOAD AT THE THREADED END OF ACTUATOR ROD.  NOSE GEAR ACT	UATES AT A VERY FAST RATE WHICH MAY CAUSE A 'BOUNCE' AT THE TRAVEL LIMIT WHICH BENDS AND CRACKS, AND ULTIMATELY BREAKS T	HE END OF THE ACTUATOR.  SUBMITTER STATED THIS IS 6TH OCCURRENCE (DIFFERENT AIRCRAFT) THIS YEAR.				1	H	7	1 	3O				1A13    					 
1996042500684	19960425	00684	SO  	1996	4	25	96ZZZX2032       	1	19960301	G	3233		ACTUATOR        	GARKENYON   		PIPER 	PA28  	PA28R200    	7102811	SO  										NLG	HOUSING CRACKED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01										HAVE FOUND VARIOUS ACTUATOR HOUSINGS CRACKED AT THE FITTING BOSS.  INITIALLY, IT APPEARS THE UNIT HAS A BAD SEAL, BUT TH	EN INSPECTION REVEALS A HAIRLINE CRACK.					1	L	7	1 	3O				2A13    					 
1996042500685	19960425	00685		1996	4	25	96ZZZX2033       	1	19960325	G	2822	2B729	PUMP            	AIRBORNE    																FUEL SYSTEM	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					11AJ198					FUEL PUMP ARMATURE SHORTED, BRUSH BLOCK MELTED, OVERHEATED.  ARMATURE CAUSES POTTING TO SWELL.  SUBMITTER SUGGESTS MAY H	AVE BEEN CAUSED BY RUNNING PUMP DRY.																		 
1996042500687	19960425	00687	CE  	1996	4	25	96ZZZX2035       	1	19960330	G	5350	04310241791	FAIRING         			CESSNA	150   	150L        	2071826	CE  										DORSAL FIN	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	18609					1573984				TRAILING END OF FAIRING IS NOT TALL ENOUGH TO FIT OVER DORSAL FIN.						1	H	7	1 	3O				3A19    					 
1996042500688	19960425	00688	EA  	1996	4	25	96ZZZX2036       	2	19960326	G	8530	LW18729	PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 3 CYL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	69265	1745 				15282590	RL2333815			ENGINE WAS 'REMANUFACTURED' BY LYCOMING, DATED 12-13-90.  REMOVAL OF NR 3 CYLINDER TO INVESTIGATE AN OIL FOULING PROBLEM	 REVEALED A BROKEN PISTON.  PISTON SKIRT HAD BROKEN OFF ON THRUST SIDE (TOP) OF PISTON BETWEEN THE PISTON PIN BOSSES AND	 UP TO OIL CONTROL RING GROOVE.  PISTON APPEARS TO HAVE BEEN CRACKED BETWEEN THE 2 OIL CONTROL RING GROOVE OIL DRAIN HOL	ES FOR SOME TIME BEFORE BREAKING.  ENGINE RAN FINE WITH NO INDICATIONS OF A SERIOUS PROBLEM EXCEPT FOR OIL FOULING OF TH	E BOTTOM SPARK PLUG.  A COMPRESSION CHECK DONE HOT JUST BEFORE CYLINDER REMOVAL SHOWED 76/80 PSI.		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996042500689	19960425	00689	CE  	1996	4	25	96ZZZX2037       	1	19960328	G	8011	MHB4016R	STARTER         	ELECTROSYS  	MHB4016R    	CESSNA	172   	172RG       	2072438	CE  										REAR CASE	BOLTS MISSING   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	9367D	1900 			9P000141	172RG1139				DURING A 100-HOUR INSPECTION, THE STARTER REAR CASE WAS FOUND LOOSE.  THREE OF THE FOUR SCREWS THAT SECURE FRONT BENDIX 	HOUSING TO REAR CASE FOUND MISSING.  SUBMITTER STATED CAUSED BY VIBRATION OR POOR ASSEMBLY TORQUES OR LOCK WASHERS WHEN 	STARTER WAS BUILT.  RECOMMEND TORQUING SCREWS AT EACH 100-HOUR INSPECTION.				1	H	7	1 	3O				3A17    					 
1996042500690	19960425	00690	GL  	1996	4	25	96ZZZX2038       	1	19960301	G	2510	0200016	SEAT PAN        			AMTR  	PITTS 	PITTSSPECIAL		GL  										PILOT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01										SEATS CONTINUALLY CRACK, APPARENTLY, UNDER THE HIGH 'G' LOAD.						1	Q	7	1 	3O				EXPA1Q71					 
1996042500691	19960425	00691	SO  	1996	4	25	96ZZZX2039       	1	19960325	G	7603	3174700	BALL JOINT      			PIPER 	PA24  	PA24260     	7102406	SO  										THROTTLE CABLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8967P	8400 				244424				COMPLAINTS OF STIFF THROTTLE OPERATON LED TO LUBING THROTTLE CABLE, HOWEVER, AFTER SHORT TIME, CABLE BECAME STIFF AGAIN.	  WHILE REPLACING CABLE, DISCOVERED THE BALL JOINT WHICH CONNECTS THE CABLE TO THROTTLE METERING ARM BENT AND CRACKED AP	PROXIMATELY TWO-THIRDS THROUGH BALL JOINT.  IT IS SUSPECTED THE ROUGH OPERATION PERMITTED EXTRA STRESS ON CONNECTION WIT	HOUT PILOT'S KNOWLEDGE.  SUBMITTER STATES CLOSE INSPECTION OF ALL ENGINE CONTROLS AND OPERATION SHOULD ELIMINATE POSSIBI	LITY OF FAILURES.		1	L	7	1 	3O				1A15    					 
1996042500692	19960425	00692	CE  	1996	4	25	96ZZZX2040       	1	19960325	G	3211	0541153	U-BOLT          			CESSNA	172   	172K        	2072430	CE  										MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	7119G	5800 				17258819				DURING 100-HOUR INSPECTION, FOUND MAIN GEAR ATTACHMENT U-BOLT BROKEN ON ONE END.  UPON REMOVAL OF THE MAIN GEAR LEG, THE	 REMAINING AN6-15A BOLT ATTACHING THE GEAR WAS FOUND BENT.  SUBMITTER STATED HIGH/TIME FATIGUE IS SUSPECT CAUSE AND A TI	ME LIMIT ON THIS PART WOULD MORE THAN LIKELY PREVENT RECURRENCE.				1	H	7	1 	3O			NT	3A12    					 
1996042500693	19960425	00693	SO  	1996	4	25	96ZZZX2041       	1	19960322	G	2822	2B663	PUMP            	AIRBORNE    		PIPER 	PA31  	PA31350     	7103110	SO  										FUEL SYSTEM	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13			10   		9E698					FUEL PUMP INSPECTION FOUND PIPE SEALER USED ON INLET AND OUTLET.  PUMP HAD PIPE SEALER ALL OVER THE INSIDE WHICH CAUSED 	THE VANES TO STICK.  PUMP FITTINGS ARE SEALED WITH AN O-RING AND DO NOT REQUIRE PIPE SEALER.					1	L	7	2 	3O				A20SO   					 
1996042500694	19960425	00694	CE  	1996	4	25	96ZZZX2042       	1	19960325	G	3211	05411212	FITTING         			CESSNA	172   	172K        	2072430	CE  										RT INBD MLG LEG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	7119G	5800 				17258819				DURING 100-HOUR INSPECTION, THE RT INBOARD MAIN GEAR LEG SUPPORT FITTING WAS FOUND CRACKED AT U-BOLT ATTACH HOLE.  REMOV	AL OF GEAR LEG REVEALED THE CRACK STARTED UNDER THE NUT.  SUSPECT CAUSE IS HIGH TIME/FATIGUE.  SUBMITTER STATED CLOSE AT	TENTION TO THIS AREA WILL PREVENT RECURRENCE.				1	H	7	1 	3O			NT	3A12    					 
1996042500695	19960425	00695	SO  	1996	4	25	96ZZZX2043       	1	19960319	G	5700		LIFT STRUT      			MAULE 	M5    	M5210C      	5460134	SO  										WING NR 1	CORRODED        	B			CO4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	51569					6025C				INSPECTION OF LIFT STRUTS PER AD 93-10-06 FOUND NR 1 STRUT UNAIRWORTHY DUE TO LOWER 8 INCH OF STRUT DEFECTIVE DUE TO COR	ROSION.					1	H	7	1 	3O				3A23    					 
1996042500696	19960425	00696		1996	4	25	96ZZZX2044       	4	19960112	G	2210	30B200	BRIDLE CABLE    	CENTURY     		PIPER 	PA28  	PA28180     	7102808	SO  										AUTOPILOT	PIN SLIPPAGE    	B			BCBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6589J	5370 				285048				C/W CENTURY FLT SYSTEM SB CFS-95-01 DATED 10-11-95.  BRIDLE CABLE INSPECTION FOUND PIN SLIPPAGE ON CABLE.  REPLACED CABL	E.					1	L	7	1 	3O				2A13    					 
1996042500697	19960425	00697		1996	4	25	96ZZZX2045       	4	19960112	G	2210	30B200	BRIDLE CABLE    	CENTURY     		PIPER 	PA32  	PA32260     	7103206	SO  										AUTOPILOT	PIN SLIPPAGE    	B			BCBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	5598J	2444 				321065				C/W CENTURY FLT SYSTEM SB CFS-95-01 DATED 10-11-95.  BRIDLE CABLE INSPECTION FOUND PIN SLIPPAGE ON CABLE.  REPLACED CABL	E.					1	L	7	1 	3O				A3SO    					 
1996042500698	19960425	00698	CE  	1996	4	25	96ZZZX2046       	1	19960202	G	3710	IG44	INDICATOR       	AIRBORNE    		BEECH 	58    	58          	1152740	CE  										SOURCE PRESSURE	DEFECTIVE       	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	66432	2904 				TH1056				DURING ANNUAL INSPECTION, INSTRUMENT AIR PRESSURE GAUGE READ NORMAL WHEN EITHER ENGINE WAS RUN INDIVIDUALLY, BUT INDICAT	ED HIGH WHEN BOTH ENGINES OPERATING.  ALSO, NOTICED ACTIVATION OF DEICE SYS CAUSED INSTRUMENT TO 'PEG' FOR DURATION OF C	YCLE.  T/S SYS DISCLOSED ACTUAL PRESS DELIVERED TO GYROS WAS WELL BELOW NORMAL (APPROX 3.0 INCH HG) AND INSTRUMENT AIR R	EGULATOR SET TO MINIMUM, I.E., SCREWED ALL THE WAY IN.  WHEN THE INSTRUMENT REGULATOR ADJUSTED TO PROVIDE CORRECT PRESS 	TO GYROS, ACFT PRESS GAUGE READING WENT 'OFF THE SCALE'.  INVEST REVEALED SOURCE INDICATORS OF INSTR AIR PRESS GAUGE LEA	KING & PRESSURIZING INSTR CASE INTERNALLY CAUSING ABNORMALLY HIGH INDICATIONS.  DEFECTIVE INSTR REPLACED WITH O/H UNIT.	1	L	7	2 	3O				3A16    					 
1996042500699	19960425	00699	SO  	1996	4	25	96ZZZX2047       	1	19960411	G	2810	63913194	HOSE            			PIPER 	PA28  	PA28R180    	7102809	SO  										FUEL TANK VENT	DETERIORATED    	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	3486R	2801 				28R5701				PULLED BOTH FUEL TANKS PRIOR TO HAVING AIRCRAFT PAINTED TO REPAIR VENT HOSE CONNECTIONS AND SENDER GASKETS.  FOUND VENT 	HOSES BADLY DETERIORATED ESPECIALLY OF UPPER CONNECTION.  1970 YEAR AIRCRAFT, FIRST REPLACEMENT OF THESE HOSES.  SUBMITT	ER STATED NEED AN AD ON THIS.				1	L	7	1 	3O				2A13    					 
1996042500700	19960425	00700	SO  	1996	4	25	96ZZZX2048       	1	19960411	G	2810	63913193	HOSE            			PIPER 	PA28  	PA28R180    	7102809	SO  										FUEL TANK VENT	DETERIORATED    	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	3486R	2801 				28R5701				PULLED BOTH FUEL TANKS PRIOR TO HAVING AIRCRAFT PAINTED TO REPAIR VENT HOSE CONNECTIONS AND SENDER GASKETS.  FOUND VENT 	HOSES BADLY DETERIORATED ESPECIALLY OF UPPER CONNECTION.  1970 YEAR AIRCRAFT, FIRST REPLACEMENT OF THESE HOSES.  SUBMITT	ER STATED NEED AN AD ON THIS.				1	L	7	1 	3O				2A13    					 
1996042500701	19960425	00701	SO  	1996	4	25	96ZZZX2049       	1	19960411	G	2810	63913193	HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  										FUEL TANK VENT	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	1690T	4992 				287125007				PULLED FUEL TANKS DUE TO FUEL SMELL IN COCKPIT AFTER TANKS ARE TOPPED OFF.  FOUND VENT HOSE CONNECTIONS VERY BADLY SPLIT	 DUE TO AGE OF HOSES.  1971 YEAR AIRCRAFT, FIRST REPLACEMENT.  NEED AD ON THIS SUBJECT AS THE USE OF THESE AIRCRAFT IN T	HE FIELD INCREASES.				1	L	7	1 	3O				2A13    					 
1996042500702	19960425	00702	SO  	1996	4	25	96ZZZX2050       	1	19960411	G	2810	63913194	HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  										FUEL TANK VENT	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	1690T	4992 				287125007				PULLED FUEL TANKS DUE TO FUEL SMELL IN COCKPIT AFTER TANKS ARE TOPPED OFF.  FOUND VENT HOSE CONNECTIONS VERY BADLY SPLIT	 DUE TO AGE OF HOSES.  1971 YEAR AIRCRAFT, FIRST REPLACEMENT.  NEED AD ON THIS SUBJECT AS THE USE OF THESE AIRCRAFT IN T	HE FIELD INCREASES.				1	L	7	1 	3O				2A13    					 
1996042500703	19960425	00703	CE  	1996	4	25	96ZZZX2051       	1	19960414	G	2731	07125002	ACTUATOR        			CESSNA	185   	A185F       	2072821	CE  										STABILIZER TRIM	STUCK           	D		A		K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SO	07										THE OWNER COMPLAINED HE COULD NOT TRIM PLANE FOR NOSE DOWN.  UPON INSPECTION, TRIM SYSTEM WOULD BECOME STUCK REQUIRING E	XTREME FORCE TO FREE SYSTEM.  UPON STABILIZER REMOVAL, FOUND ACTUATOR WOULD BIND IN APPROXIMATELY NEUTRAL POSITION.  AFT	ER SOAKING PARTS IN PENETRATING FLUID AND APPLYING EXTREME FORCE, PARTS WERE FINALLY SEPARATED.  SUBMITTER SUSPECTED CAU	SE - NO LUBRICATION TO ASSEMBLY DUE TO DIFFICULTY OF ACCESS.  THIS COULD CAUSE A DANGEROUS CONDITIONIN FLIGHT!.			1	H	7	1 	3O				3A24    					 
1996042500704	19960425	00704	CE  	1996	4	25	96ZZZX2052       	1	19960414	G	2731	07125001	ACTUATOR        			CESSNA	185   	A185F       	2072821	CE  										STABILIZER TRIM	STUCK           	D				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SO	07										THE OWNER COMPLAINED HE COULD NOT TRIM PLANE FOR NOSE DOWN.  UPON INSPECTION, TRIM SYSTEM WOULD BECOME STUCK REQUIRING E	XTREME FORCE TO FREE SYSTEM.  UPON STABILIZER REMOVAL, FOUND ACTUATOR WOULD BIND IN APPROXIMATELY NEUTRAL POSITION.  AFT	ER SOAKING PARTS IN PENETRATING FLUID AND APPLYING EXTREME FORCE, PARTS WERE FINALLY SEPARATED.  SUBMITTER SUSPECTED CAU	SE - NO LUBRICATION TO ASSEMBLY DUE TO DIFFICULTY OF ACCESS.  THIS COULD CAUSE A DANGEROUS CONDITIONIN FLIGHT!.			1	H	7	1 	3O				3A24    					 
1996042500705	19960425	00705	SO  	1996	4	25	96ZZZX2053       	1	19960405	G	3233	837693E	ACTUATOR        	PARKERHANFIN		PIPER 	PA46  	PA46310P    	7104605	SO  										NLG	MISSING O-RING  	B	L		WC7R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	188RW				285	4608133				HOBBS, 1,124.1 HOURS.  NOSE GEAR DOORS WOULD NOT RETRACT (CLOSE) AFTER GEAR RETRACTION.  NOSE GEAR DOOR ACTUATOR FOUND L	EAKING HYDRAULIC FLUID SEVERELY.  DISASSEMBLED ACTUATOR, FOUND A BACK-UP RING MISSING ON PISTON ALLOWING O-RING TO ROLL 	AND SPLIT.  UNIT REQUIRES TWO BACK-UP RINGS.  INSTALLED PIPER REPAIR KIT PN 765-330 IAW 32-30-00, PAGES 21-22.  SWUNG GE	AR, OPS CHECK GOOD.			1	L	7	1 	3O				A25SO   					 
1996042500706	19960425	00706	CE  	1996	4	25	96ZZZX2054       	1	19960315	G	3221	05430131	CASTING         			CESSNA	172   	172K        	2072430	CE  										NLG BUTTERFLY	SHEARED RIVETS  	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05		2000 								A 1971 MODEL AND 1980 MODEL 172, FOUND WITH RIVETS SHEARED AND LOOSE WHICH ATTACH NOSE GEAR BUTTERFLY CASTING; THUS, CAU	SING CASTING TO WORK AGAINST FIREWALL.  THE TOP TWO BOLTS AT TOP WERE ONLY ATTACHING POINTS LEFT.  CESSNA SM ALLOWS RIVE	T HOLES TO BE DRILLED AND REPLACED WITH AN-3 BOLTS.  SUBMITTER RECOMMENDS MORE FREQUENT INSPECTIONS.				1	H	7	1 	3O			NT	3A12    					 
1996042500707	19960425	00707	EA  	1996	4	25	96ZZZX2055       	2	19960318	G	8550		SUMP PLUG       			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  					ENGINE OIL	MISSING         	D		A		E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			GL	15	2127D	45   				447995131	L18572T			AIRCRAFT WAS FLYING WHEN RT ENGINE LOST ALL OIL PRESSURE.  ENGINE WAS SECURED.  MAINTENANCE DISCOVERED MISSING SUMP PLUG	 ON OIL SUMP.  SUBMITTER STATED UNIT WAS NOT SECURED AT FACTORY.  CHECKED LT ENGINE, PLUG WAS NOT SAFETIED.  SECURED PLU	G WITH SAFETY WIRE AND RELEASED AIRCRAFT FOR SERVICE.				1	L	7	2 	3O	3	O		A19S0   	E286				 
1996042500708	19960425	00708	CE  	1996	4	25	96ZZZX2056       	1	19960322	G	2720	04115264	RUDDER BAR      			CESSNA	150   	152         	2071835	CE  										PILOT RT RUDDER	WELD BROKEN     	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6502H	8753 				15284171				DURING RUN-UP FOR FLIGHT, PILOT'S RIGHT RUDDER PEDAL WOULD NOT MOVE RUDDER.  THE WELD ASSEMBLY OF RUDDER BAR WAS BROKEN 	AT ARM ASSEMBLY FOR RUDDER PEDAL.  METAL FATIGUE AROUND LOWER END OF WELDED AREA.  NEW PART WAS MODIFIED TO INCREASE STR	ENGTH.				1	H	7	1 	3O			NT	3A19    					 
1996042500709	19960425	00709	SW  	1996	4	25	96ZZZX2057       	1	19960319	G	2810	CCA1650	FUEL DRAIN      	CURTIS      		AIRTRC	AT400 	AT402       	0390205	SW  										FUEL SYSTEM	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	6076U	463  				4020971				AFTER PERFORMING NUMEROUS ANNUALS ON AIRCRAFT USING THIS TYPE OF FUEL DRAIN, SUBMITTER FOUND CLOSE TO 15 PERCENT OF THE 	FUEL DRAINS CRACKED AT THE TOP OF THE DRAIN NEAR THE SEALING SURFACE.  IF UNDETECTED, THIS COULD LEAD TO THE INNER PARTS	 OF THE DRAIN FALLING OUT AND DRAINING FUEL.  SUBMITTER RECOMMENDS CLOSE INSPECTION OF THE DRAIN WHENEVER IT IS REMOVED 	FOR ANY REASON.			1	L	7	1 	3T			NC	A17SW   					 
1996042500710	19960425	00710	CE  	1996	4	25	96ZZZX2058       	1	19960213	G	3221	169810000663	HOUSING ASSY    		169810000661	BEECH 	23    	C23         	1151242	CE  										NLG	CRACKED         	G		A		O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			SW	09	66710	4190 				2387				NOSE LANDING GEAR DEPARTED AIRCRAFT WHILE DOING TOUCH-AND-GO LANDINGS DUE TO ATTACH HOLES FOR NLG HOUSING ASSEMBLY BEING	 CRACKED OUT.  TWO HOLES HAD BEEN CRACKED PREVIOUSLY.  SUBMITTER STATED THIS AREA IS NOT ACCESSIBLE DURING INSPECTIONS.					1	L	7	1 	3O				A1CE    					 
1996042500711	19960425	00711	CE  	1996	4	25	96ZZZX2059       	1	19960328	G	2571	07120591	SUPPORT         			CESSNA	182   	182Q        	2072732	CE  										BATTERY	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	4821N	2389 				18267393				THE SUPPORTS THAT HOLD THE BATTERY WERE FOUND CRACKED.  SEPARATION OF THESE SUPPORTS WOULD CAUSE THE BATTERY TO MOVE ARO	UND BEHIND THE REAR BULKHEAD, POSSIBLY GOING INTO CONTROL CABLES OR SHORTING THE ELECTRICAL SYSTEM.  SUBMITTER STATED TH	IS IS THE THIRD AIRCRAFT IN A ROW THAT THIS PROBLEM WAS FOUND.				1	H	7	1 	3O			NT	3A13    					 
1996042500712	19960425	00712	SO  	1996	4	25	96ZZZX2060       	1	19960320	G	2710	6755001	SUPPORT         			PIPER 	PA28  	PA28R180    	7102809	SO  										AIL BELLCRANK	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	7614J	5431 				28R31006				DURING A ROUTINE ANNUAL INSPECTION, BOTH LOWER AILERON BELLCRANK BRACKETS WERE FOUND CRACKED BY THE FORWARD BOLT.  SUBMI	TTER STATED THIS IS MOST LIKELY CAUSED BY EITHER IMPROPERLY ADJUSTED AILERON STOPS OR BY NOT 'TYING' THE CONTROLS WHILE 	THE AIRCRAFT IS PARKED.  THIS WAS FOUND TWO OTHER TIMES ON PA28-180'S.  FAILURE OF THIS BRACKET WILL CAUSE LOSS OF AILER	ON CONTROL.			1	L	7	1 	3O				2A13    					 
1996042500713	19960425	00713	SO  	1996	4	25	96ZZZX2061       	1	19960319	G	5230	99938002	LATCH ROD       			PIPER 	PA34  	PA34200T    	7103406	SO  										FWD BAG DOOR	WORN            	B	S		APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4490F					347670339				FORWARD BAGGAGE DOOR AFT LATCH ROD IS WORN PARTIALLY THROUGH JUST BEHIND COTTER PIN HOLE.						1	L	7	2 	3O				A7SO    					 
1996042500714	19960425	00714	CE  	1996	4	25	96ZZZX2062       	1	19960301	G	2822		FITTING         			CESSNA	182   	TR182       	2072735	CE  										FUEL PUMP	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11	150DB	1560 				R18201641				WRONG TYPE FITTING IN ELECTRIC FUEL PUMP RESTRICTED FUEL FLOW.						1	H	7	1 	3O				3A13    					 
1996042500715	19960425	00715	EA  	1996	4	25	96ZZZX2063       	2	19960327	G	7414	ES10382585	CONTACT ASSY    	BENDIX      	S1227       	PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					MAGNETO	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	7693C				907002	28R7635113	L657751A			DURING 100-HOUR INSPECTION AND C/W AD 78-9-7R3 (BENDIX IMPULSE COUPLING AND PIN INSP), THE MAIN CONTACT ASSY WAS FOUND L	OOSE AND SURROUNDING AREA FROSTED.  AGAIN, THE MOUNTING SCREWS WERE TIGHT, BUT THE MFG ASSY SCREW AND NUT WERE LOOSE CAU	SING CONTACT HALVES TO DRIFT FROM ALIGNMENT.  THE CONTACTS TOTAL TIME WAS UNKNOWN, BUT ESTIMATING BY THE LOOKS, THEY HAD	 NO MORE THAN 500 HOURS ON THEM.  DATE FOUND WAS 3-22-96.			1	L	7	1 	3O	3	O		2A13    	1E10				 
1996042500716	19960425	00716	EA  	1996	4	25	96ZZZX2064       	2	19960327	G	7414	ES10382585	CONTACT ASSY    	BENDIX      	D2000       	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO	LOOSE           	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	25	739NT	413  			8324738	17270680	RL460276T			ENGINE FAILED TO MAKE FULL STATIC RPM ON GROUND.  UPON FURTHER INSPECTION, IT WAS DETERMINED TO BE A MAGNETO PROBLEM.  U	PON OPENING MAG COVER, BOTH SETS OF CONTACTS WERE FOUND TO BE LOOSE.  THE CONTACT ASSY SCREW (NOT MOUNTING SCREWS) WERE 	DETERMINED TO BE LOOSE.  CONTACT HALVES WERE MISALIGNED WITH ONE ANOTHER CAUSING EXCESSIVE FROSTING AROUND ENTIRE CONTAC	T AREA AND ON DISTRIBUTOR CAP.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996042500717	19960425	00717		1996	4	25	96ZZZX2065       	1	19960406	G	3510	89501077	OXYGEN CYLINDER 	SCOTT       																OXYGEN SYSTEM	IMPROPER MARK   	B			RU2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03					281009					OXYGEN CYLINDER ASSY WAS RECEIVED FOR HYDROTEST.  UPON RECEIVING, INSPECTION COULD NOT LOCATE DOT NR OR RATING FOR CYLIN	DER.  SUSPECT THAT THIS CYLINDER WAS A PROTOTYPE NOT INTENDED FOR USE, BUT IT HAS BEEN IN SERVICE SINCE 3-84.																		 
1996042500718	19960425	00718	SO  	1996	4	25	96ZZZX2066       	2	19960308	G	8520	633620	CRANKSHAFT      			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520J    	17040	SO  					NR 3 MAIN BRG	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	23	78S	6209 	1140 		10991	3400151	20818870J			AFTER TAKEOFF WHILE IN LEVEL FLIGHT, THE PILOT EXPERIENCED A SUDDEN ENGINE SEIZURE ON THE RT ENGINE.  AN UNEVENTFUL LAND	ING WAS MADE.  THE CRANK WAS FOUND BROKEN AT THE NR 3 MAIN BEARING SADDLE BETWEEN THE NR 4 AND NR 5 ROD THROW.  THERE WA	S CATASTROPHIC DAMAGE INSIDE AND OUTSIDE THE ENGINE TO CASES, CYLINDERS, AND COMPONENTS.  THE NR 5 ROD WAS TORN LOOSE FR	OM ITS THROW.  LOGS SHOWED THE CRANK TO BE OF AIRMELT TYPE AND HAD BEEN GROUND .010 INCH UNDER AT LAST OVERHAUL 1,140 HR	S AGO.  CAUSE OF CRACK COULD NOT BE DETERMINED.  ENGINE WAS A R.A.M. CONVERSION.		1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996042500719	19960425	00719	SO  	1996	4	25	96ZZZX2067       	1	19960331	G	3230		UPLOCK HOOK     			PIPER 	PA31T 	PA31T3      	7103128	SO  										NLG	ICED OVER       	D				A	O			UNSCHED LANDING         	OTHER                   			O			OTHER                     			CL	CLIMB          	1			AL	01	217CS	8915 				31T8275014				AFTER TAKEOFF, PILOT REPORTED NOSE GEAR WOULD NOT LOCK UP.  LOWERED GEAR AND RETURNED WITHOUT INCIDENT.  FOUND ICE ON UP	LOCK HOOK AND UPLOCK ROLLER, CLEANED, AND LUBRICATED NOSE GEAR, RETRACT TEST OK.					1	L	7	2 	3T				A8EA    					 
1996042500720	19960425	00720	SO  	1996	4	25	96ZZZX2068       	2	19960325	G	8540	SA539800M15	CLUTCH SPRING   		641348A8    						CONT  	O360  	TSIO360EB   	17025	SO  					STARTER	FAILED          	B			QX2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11		1    					311356			CLUTCH SPRING WOUND ITSELF AROUND STARTER SHAFT GEAR AND WOULD NOT ALLOW ENGINE TO START.											3	O			E9CE				 
1996050200102	19960502	00102	CE  	1996	5	2	96ZZZX2069       	1	19960327	G	2120	1013841733	CHECK VALVE     			BEECH 	300   	300BEECH    	1152930	CE  										CABIN AIR	BROKEN          	B			SJ7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	194LJ	3949 				FA89				THE TWO FLAPPER VALVES THAT STOP AIR FROM EXITING TO ENGINE BROKE LOOSE AND LODGED IN DUCT WORK.  VALVES MIGRATED TO THE	 END OF DUCT AND SLOWED THE FLOW OF PRESSURE AIR TO THE AFT CABIN AND ROUTED ALL TO THE COCKPIT CAUSING TEMPERATURE TO B	E VERY HOT IN COCKPIT.				2	L	7	2 	4T				A24CE   					 
1996050200103	19960502	00103	CE  	1996	5	2	96ZZZX2070       	1	19960403	G	5541	04330106	SPAR            			CESSNA	150   	150M        	2071830	CE  										RUD UPPER HINGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	8313U	5608 				15077918				CRACKS ORIGINATING FROM BOTH SIDES OF 1 INCH HOLE IN SPAR JUST BELOW THE UPPER HINGE BRACKETS.  THE NEW SPAR (SAME PART 	NR) DOES NOT HAVE THIS HOLE.  REFER TO ALERTS 180, 192, AND 205, AND SB 94-3A.  THE SUBMITTER'S SPECULATION IN ALERT 192	 IS PROBABLY CORRECT, WIND GUSTS CAN SLAM THE RUDDER AGAINST ITS STOPS LOCATED ON THE HORN AT THE BOTTOM OF THE RUDDER W	HILE THE INERTIA OF THE WEIGHT AT THE TOP OF THE RUDDER APPLIED A TWISTING MOTION THROUGH THE SPAR.  THE NEAREST WEAK PO	INT IS THIS 1 INCH HOLE.		1	H	7	1 	3O				3A19    					 
1996050200104	19960502	00104	CE  	1996	5	2	96ZZZX2071       	1	19960408	G	5540	04310282	BRACKET         			CESSNA	150   	A152        	2071836	CE  										RUD HINGE ATTACH	EXCESS WEAR     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	761UA	4375 				1520986				APRIL 8, 1996 - 4,375.0 TACHOMETER.  4,350.0 TTAF.  WHILE INSPECTING RUDDER SPAR PER CESSNA SB SEB-94-3, FOUND RUDDER SP	AR IN NEED OF REPLACING PER THE DESCRIPTION OF THE SB.  UPON DISASSEMBLY OF RUDDER AND SPAR, FOUND ALL OF THE UPPER RUDD	ER HINGE PIVOT ATTACHMENT BRACKETS SEVERELY WORN AT POINT OF CONTACT TO VERTICAL FIN.  SUBMITTER RECOMMENDS ALL RUDDER A	TTACHMENT BRACKETS BE INSPECTED ON AIRCRAFT WITH MORE THAN 4,000 HRS TIME IN SERVICE AND DURING THE CESSNA SB SEB-94 INS	PECTION.		1	H	7	1 	3O				3A19    					 
1996050200105	19960502	00105	CE  	1996	5	2	96ZZZX2072       	1	19960408	G	5540	04310284	BRACKET         			CESSNA	150   	A152        	2071836	CE  										RUD HINGE ATTACH	EXCESS WEAR     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	761UA	4375 				1520986				APRIL 8, 1996 - 4,375.0 TACHOMETER.  4,350.0 TTAF.  WHILE INSPECTING RUDDER SPAR PER CESSNA SB SEB-94-3, FOUND RUDDER SP	AR IN NEED OF REPLACING PER THE DESCRIPTION OF THE SB.  UPON DISASSEMBLY OF RUDDER AND SPAR, FOUND ALL OF THE UPPER RUDD	ER HINGE PIVOT ATTACHMENT BRACKETS SEVERELY WORN AT POINT OF CONTACT TO VERTICAL FIN.  SUBMITTER RECOMMENDS ALL RUDDER A	TTACHMENT BRACKETS BE INSPECTED ON AIRCRAFT WITH MORE THAN 4,000 HRS TIME IN SERVICE AND DURING THE CESSNA SB SEB-94 INS	PECTION.		1	H	7	1 	3O				3A19    					 
1996050200106	19960502	00106	CE  	1996	5	2	96ZZZX2073       	1	19960408	G	5540	04310286	BRACKET         			CESSNA	150   	A152        	2071836	CE  										RUD HINGE ATTACH	EXCESS WEAR     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	761UA	4375 				1520986				APRIL 8, 1996 - 4,375.0 TACHOMETER.  4,350.0 TTAF.  WHILE INSPECTING RUDDER SPAR PER CESSNA SB SEB-94-3, FOUND RUDDER SP	AR IN NEED OF REPLACING PER THE DESCRIPTION OF THE SB.  UPON DISASSEMBLY OF RUDDER AND SPAR, FOUND ALL OF THE UPPER RUDD	ER HINGE PIVOT ATTACHMENT BRACKETS SEVERELY WORN AT POINT OF CONTACT TO VERTICAL FIN.  SUBMITTER RECOMMENDS ALL RUDDER A	TTACHMENT BRACKETS BE INSPECTED ON AIRCRAFT WITH MORE THAN 4,000 HRS TIME IN SERVICE AND DURING THE CESSNA SB SEB-94 INS	PECTION.		1	H	7	1 	3O				3A19    					 
1996050200107	19960502	00107	EA  	1996	5	2	96ZZZX2074       	2	19960228	G	8530	LW13561	CYLINDER        			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					NR 4 EXH ROCKER	FAILED          	B			BKHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	294D	829  				P451	RL98559			DURING ENGINE RUN-UP FOR TAKEOFF, ENGINE QUIT.  INVESTIGATION BY BORESCOPE FOUND NR 4 CYLINDER EXHAUST VALVE NOT WORKING	.  REMOVED ROCKER BOSS AND FOUND EXHAUST VALVE ROCKER SHAFT INBOARD ROCKER BOSS CASTING AND COVER TAB FAILED.  OUTBOARD 	CASTING OK.  ALL OTHER CYLINDERS ROCKER CASTINGS OK.  SUSPECT ROCKER RETAIN CLIP FAILED INITIALLY.				1	L	7	2 	3O	3	O		A12CE   	E10EA				 
1996050200108	19960502	00108	CE  	1996	5	2	96ZZZX2075       	1	19960411	G	5521		RIB             			BEECH 	90    	E90         	1152914	CE  										LT ELEVATOR	MISINSTALLED    	B			FTKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	20S					LW267				DURING ROUTINE INSPECTION AFTER AIRCRAFT WAS PAINTED, FOUND CRACK IN HINGE.  FOUND UPPER RIVETS WORKING ON OUTBOARD RIB 	FLANGE.  REMOVED ELEVATOR TIP CAP AND FOUND OUTBOARD RIB ATTACHMENT HOLES MISSING REAR PART OF RIB.  REPLACED RIB AND RI	B FLANGE.  STOP DRILLED CRACK AND INSTALLED SURFACE PATCH.  BALANCED ELEVATOR AND REINSTALLED.  SUSPECT CAUSE DUE TO IMP	ROPER ASSEMBLY DURING MANUFACTURE AND ELEVATOR OUT OF BALANCE AFTER BEING PAINTED.			1	L	7	2 	3T				3A20    					 
1996050200109	19960502	00109	CE  	1996	5	2	96ZZZX2076       	1	19960411	G	5521		SKIN            			BEECH 	90    	E90         	1152914	CE  										LT ELEVATOR	CRACKED         	B			FTKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	20S					LW267				DURING ROUTINE INSPECTION AFTER AIRCRAFT WAS PAINTED, FOUND CRACK IN HINGE.  FOUND UPPER RIVETS WORKING ON OUTBOARD RIB 	FLANGE.  REMOVED ELEVATOR TIP CAP AND FOUND OUTBOARD RIB ATTACHMENT HOLES MISSING REAR PART OF RIB.  REPLACED RIB AND RI	B FLANGE.  STOP DRILLED CRACK AND INSTALLED SURFACE PATCH.  BALANCED ELEVATOR AND REINSTALLED.  SUSPECT CAUSE DUE TO IMP	ROPER ASSEMBLY DURING MANUFACTURE AND ELEVATOR OUT OF BALANCE AFTER BEING PAINTED.			1	L	7	2 	3T				3A20    					 
1996050200110	19960502	00110	GL  	1996	5	2	96ZZZX2077       	3	19960401	G	6114	MS150011	GREASE FITTING  			PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	21113		338  			447995040		AU8050		WRITE-UP BY PILOT STATED PROPELLER WAS SLINGING GREASE ON BLADES.  MAINTENANCE INSPECTION FOUND GREASE ZERK FITTING HAD 	FAILED INTERNALLY AND THE CHECK BALL AND SPRING WAS PUSHED INTO THE PROPELLER HUB BY GREASE PRESSURE WHEN HUB WAS SERVIC	ED AT LAST 100-HOUR INSPECTION.				1	L	7	2 	3O				A19S0   		5	C	P920	 
1996050200111	19960502	00111	CE  	1996	5	2	96ZZZX2078       	1	19960404	G	3246	C1630060103	WHEEL ASSY      			CESSNA	206   	U206G       	2073356	CE  										RT MLG	CRACKED         	B			WWKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	732PT	529  	61   			U20604705				AIRCRAFT WAS MODIFIED BY INSTALLING GAR-AERO WHEEL ADAPTERS AND 8:50X10 TIRES PER STC SA4305WE WITH THE EXCEPTION - INST	ALLED ON MCCAULEY WHEELS INSTEAD OF CLEVELAND WHEELS WITH A FIELD APPROVAL, 60.5 HRS AGO.  THIS AIRCRAFT HAD A LIGHT DUT	Y WHEEL, PN C163006-0103, ON RT SIDE THAT FAILED (INNER WEBBING AND PARTING SURFACES CRACKED).  THE LEFT SIDE HAD HEAVY 	DUTY PN C163006-0102 THAT DID NOT FAIL BUT SHOWED SIGNS ON MATING SURFACE OF FRETTING AND BOLTS LOOSE.			1	H	7	1 	3O				A4CE    					 
1996050200113	19960502	00113	SO  	1996	5	2	96ZZZX2080       	1	19960402	G	5712	7847504	RIB ASSY        			PIPER 	PA28  	PA28R180    	7102809	SO  										WS 49.25 RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	7614J	5431 				28R31006				DURING C/W PIPER AD 95-20-7, THE RIB ASSYS ON BOTH SIDES WERE FOUND CRACKED UNDERNEATH THE DRAG BRACE STUD BRACKETS.  CR	ACKS WERE APPROXIMATELY 2 TO 3 INCHES LONG.  REPLACEMENT OF THE RIB ASSYS ARE REQUIRED.  SUBMITTER STATED THE NEW RIBS A	RE MADE OF THICKER MATERIAL IN THIS AREA.				1	L	7	1 	3O				2A13    					 
1996050200114	19960502	00114	SO  	1996	5	2	96ZZZX2081       	1	19960402	G	5712	7847505	RIB ASSY        			PIPER 	PA28  	PA28R180    	7102809	SO  										WS 49.25 LT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	7614J	5431 				28R31006				DURING C/W PIPER AD 95-20-7, THE RIB ASSYS ON BOTH SIDES WERE FOUND CRACKED UNDERNEATH THE DRAG BRACE STUD BRACKETS.  CR	ACKS WERE APPROXIMATELY 2 TO 3 INCHES LONG.  REPLACEMENT OF THE RIB ASSYS ARE REQUIRED.  SUBMITTER STATED THE NEW RIBS A	RE MADE OF THICKER MATERIAL IN THIS AREA.				1	L	7	1 	3O				2A13    					 
1996050200115	19960502	00115	SO  	1996	5	2	96ZZZX2082       	2	19960403	G	8550	640726	TUBE ASSY       			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					FUEL MANIFOLD	FAILED          	C				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			SW	99	6867L	890  				421C1087	R610188			DURING FLIGHT, OIL WAS NOTICED ON THE RIGHT NACELLE, THE AIRCRAFT LANDED SAFELY AND THE PROPELLER WAS FEATHERED.  INVEST	IGATION REVEALED TUBE ASSEMBLY FROM THE CRANKCASE TO THE FUEL MANIFOLD HAD BROKEN FROM THE SOLDER JOINT CLOSEST TO THE F	UEL MANIFOLD.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996050200116	19960502	00116	SW  	1996	5	2	96ZZZX2083       	1	19960404	G	3233	321400	ACTUATOR        	DUKES       		MOONEY	M20   	M20F        	5870214	SW  										MLG	FAILED          	B			FMOR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	15	24KD	2804 				700047				LANDING GEAR FAILED TO EXTEND ELECTRICALLY.  MANUAL EXTENSION WAS ATTEMPTED WITH NO EXTENSION.  AIRCRAFT LANDED WITH WHE	ELS UP.  INVESTIGATION REVEALED DUKES ACTUATOR (PN 3214-00) PINION GEAR (ADDRESSED IN AD 75-23-04) WORN BEYOND LIMITS CA	USING PINION AND DRIVE GEAR TO SLIP UNDER LOAD RESULTING IN TOTAL ELECTRIC AND MANUAL BACKUP FAILURE.  RECORDS INDICATE 	C/W AD 75-23-04, 33 HOURS PRIOR.			1	L	7	1 	3O				2A3     					 
1996050200117	19960502	00117		1996	5	2	96ZZZX2084       	1	19960326	G	2822	1D212	PUMP            	AIRBORNE    																FUEL BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	13					5K198					FUEL PUMP MOTOR ARMATURE SEGMENT FAILED CAUSING EXCESSIVE BRUSH WEAR.																			 
1996050200118	19960502	00118	SO  	1996	5	2	96ZZZX2085       	1	19960328	G	7922	75944	VALVE           			PIPER 	PA31  	PA31325     	7103105	SO  										THERMO BYPASS	NUT MISSING     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3539C	1714 				317912109				LOCKNUT ON VALVE CAME LOOSE.  UPON INSPECTION, NUT WAS MISSING.  C/W SB 518C.  SUBMITTER SUGGESTS BETTER QUALITY CONTROL	 AT MFG.					1	L	7	2 	3O				A20SO   					 
1996050200119	19960502	00119	SO  	1996	5	2	96ZZZX2086       	1	19960304	G	5230		DOOR LATCH      			PIPER 	PA34  	PA34200T    	7103406	SO  										NOSE BAG	CHAFE DOOR      	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	666HL	11839				347770235				NOSE BAGGAGE DOOR, LOWER CENTER LATCH HAS WORN A NOTCH IN FIBERGLASS DOOR, AFT OF LATCH.  ALLOWS KEY TO BE REMOVED WHEN 	DOOR IS OPENED AND UNLOCKED.  SITUATION APPLIES TO AD 88-04-05 AND SB 872.					1	L	7	2 	3O				A7SO    					 
1996050200120	19960502	00120	SO  	1996	5	2	96ZZZX2087       	1	19960304	G	5230	96937003	LATCH ROD       			PIPER 	PA34  	PA34200T    	7103406	SO  										NOSE BAG DOOR	WORN            	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	666HL	11839				347770235				DURING INSPECTION OF AIRFRAME FOUND EXCESSIVE PLAY IN NOSE BAGGAGE DOOR LOCK PUSHRODS.  WHERE RODS ATTACH TO LOCKING MEC	HANISM JUST AFT OF COTTER PIN HOLE, WORN THROUGH 50 PERCENT.  (AD 88-04-05 AND SB 872 AND SB 633B APPLIES TO THIS AREA.)					1	L	7	2 	3O				A7SO    					 
1996050200121	19960502	00121	SO  	1996	5	2	96ZZZX2088       	1	19960304	G	5230	96938002	LATCH ROD       			PIPER 	PA34  	PA34200T    	7103406	SO  										NOSE BAG DOOR	WORN            	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	666HL	11839				347770235				DURING INSPECTION OF AIRFRAME, FOUND EXCESSIVE PLAY IN NOSE BAGGAGE DOOR LOCK PUSHRODS.  WHERE RODS ATTACH TO LOCKING ME	CHANISM JUST AFT OF COTTER PIN HOLE, WORN THROUGH 50 PERCENT.  (AD 88-04-05 AND SB 872 AND SB 633B APPLIES TO THIS AREA.	)				1	L	7	2 	3O				A7SO    					 
1996050200122	19960502	00122	SO  	1996	5	2	96ZZZX2089       	1	19960319	G	5230	96938003	LATCH ROD       			PIPER 	PA34  	PA34200T    	7103406	SO  										FWD BAG DOOR	WORN            	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4490F					347670339				FORWARD BAGGAGE DOOR, FORWARD LATCH ROD IS PARTIALLY WORN THROUGH JUST BEHIND COTTER PIN HOLE.						1	L	7	2 	3O				A7SO    					 
1996050200123	19960502	00123	NE  	1996	5	2	96ZZZX2090       	2	19960402	G	7314	105970	NOZZLE          		MFP45       	BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL PUMP	FRACTURED       	H				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	05	616AW		6108 			E3145	LF05016			ENGINE SHUT DOWN IN-FLIGHT.  FOUND NOZZLE FRACTURED AND ENTERED GEARS CAUSING DRIVE SHAFT TO SHEAR.  PUMP IS BEING SENT 	TO C.E.C.O. (MANUFACTURER) FOR INVESTIGATION.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996050200124	19960502	00124	CE  	1996	5	2	96ZZZX2091       	1	19960403	G	3230	2307006166	HOSE            			LEAR  	35    	31A         	5170531	CE  										RT MLG ACTUATOR	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	789SR	225  				31083				HOSE LEAKING FROM BOTH SWAGED ENDS WHEN LANDING GEAR IS EXTENDED.						2	L	7	2 	4F			RT	A10CE   					 
1996050200125	19960502	00125	CE  	1996	5	2	96ZZZX2092       	1	19960403	G	3240	2307006113	HOSE            			LEAR  	35    	31A         	5170531	CE  										RT BRAKE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	789SR	225  				31083				HOSE ASSEMBLY LEAKING HYDRAULIC FLUID THROUGH THE WALLS OF THE NOSE WHEN THE BRAKES ARE APPLIED.						2	L	7	2 	4F			RT	A10CE   					 
1996050200126	19960502	00126	NE  	1996	5	2	96ZZZX2093       	2	19960409	G	7530	8008311001L7	CONTROL         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					BLEED VALVE	MALFUNCTIONED   	E				A				UNSCHED LANDING         				R	M		PARTIAL RPM/PWR LOSS      	OVER TEMP                 		CL	CLIMB          	1			GL	07	312QS	740  				5600312	500109			ON TAKEOFF, THE RIGHT ENGINE RPM ROLLED BACK 10 PERCENT AND THE I.T.T. INCREASED TO 700 DEGREES.  AIRCRAFT RETURNED AND 	ENGINE WAS INSPECTED.  NO PROBLEM WAS FOUND.  AIRCRAFT WAS TEST FLOWN AND NR 2 ENGINE I.T.T. WAS 50 DEGREES HIGHER.  FOU	ND BLEED VALVE OPERATING ON GROUND WHEN NOT CALLED FOR.  BLEED VALVE CONTROL AND BLEED VALVE ACTUATOR WERE REPLACED AND 	PROBLEM CORRECTED.			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
1996050200127	19960502	00127	NE  	1996	5	2	96ZZZX2094       	2	19960409	G	7532	F008881L1	ACTUATOR        			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					BLEED VALVE	MALFUNCTIONED   	E				A				UNSCHED LANDING         				R	M		PARTIAL RPM/PWR LOSS      	OVER TEMP                 		CL	CLIMB          	1			GL	07	312QS	740  			F22028	5600312	500109			ON TAKEOFF, THE RIGHT ENGINE RPM ROLLED BACK 10 PERCENT AND THE I.T.T. INCREASED TO 700 DEGREES.  AIRCRAFT RETURNED AND 	ENGINE WAS INSPECTED.  NO PROBLEM WAS FOUND.  AIRCRAFT WAS TEST FLOWN AND NR 2 ENGINE I.T.T. WAS 50 DEGREES HIGHER.  FOU	ND BLEED VALVE OPERATING ON GROUND WHEN NOT CALLED FOR.  BLEED VALVE CONTROL AND BLEED VALVE ACTUATOR WERE REPLACED AND 	PROBLEM CORRECTED.			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
1996050200128	19960502	00128	CE  	1996	5	2	96ZZZX2095       	1	19960410	G	5280	45A3038110	HINGE           			BEECH 	MU300 	400BEECH    		CE  										LT MLG DOOR	CRACKED         	B			AWKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	510WS	1459 				RJ24				DURING AN 'A' INSPECTION, HAIR LINE CRACKS WERE DETECTED ON THE END CAP BEAM AT THE FORWARD GEAR DOOR HINGE LOCATION (PN	 45A30314-005 AND 006).  FURTHER INVESTIGATION REVEALED FORWARD GEAR DOOR HINGES TO BE CRACKED ON THE RT AND LT MAIN GEA	R DOORS.				2	H	7	2 	4F			RT	A16SW   					 
1996050200129	19960502	00129	CE  	1996	5	2	96ZZZX2096       	1	19960410	G	5280	45A303819	HINGE           			BEECH 	MU300 	400BEECH    		CE  										RT MLG DOOR	CRACKED         	B			AWKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	510WS	1459 				RJ24				DURING AN 'A' INSPECTION, HAIR LINE CRACKS WERE DETECTED ON THE END CAP BEAM AT THE FORWARD GEAR DOOR HINGE LOCATION (PN	 45A30314-005 AND 006).  FURTHER INVESTIGATION REVEALED FORWARD GEAR DOOR HINGES TO BE CRACKED ON THE RT AND LT MAIN GEA	R DOORS.				2	H	7	2 	4F			RT	A16SW   					 
1996050200130	19960502	00130	CE  	1996	5	2	96ZZZX2097       	1	19960207	G	3010	45AS66010009	HEATER TIP      			BEECH 	MU300 	400BEECH    		CE  										LT ELEV HORN	BURNED          	B			VIB3	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SO	03	445CC	801  				RK45				THE WIRE INSIDE THE HEATED ELEVATOR HORN TIP SHORT CIRCUITED AND BURNED.  SUBMITTER SUGGESTS THE SHORT MAY HAVE BEEN CAU	SED FROM THE HEATED HORN ASSY CHAFING ON THE ELEVATOR.					2	H	7	2 	4F			RT	A16SW   					 
1996050200131	19960502	00131	NE  	1996	5	2	96ZZZX2098       	2	19960329	G	7261	3030391	OIL PUMP        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT ENGINE	DEFECTIVE       	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	245CC	2029 				5500212	70663			RIGHT ENGINE WOULD SMOKE DURING ENGINE START.  TROUBLSHOOTING SHOWED OIL SCAVAGE PUMP WAS WEAK.  REMOVED AND REPLACED OI	L PUMP ASSY.  SB 7185 HAD BEEN C/W.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1996050200132	19960502	00132	EA  	1996	5	2	96ZZZX2099       	1	19960329	G	7110	215M0000501	COWL            			CNDAIR	CL600 	CL6001A11   	1900302	EA  										LT NACELLE	CRACKED         	B			JO1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	91UC				020096041	1051				FOUND 12 INCH CRACK ON NOSE COWL REAR FRAME TO BARREL ATTACH ANGLE AT ABOUT 10 O'CLOCK POSITION LOOKING FORWARD.  SUBMIT	TER STATED CAUSE UNKNOWN.  ENGINE VIBS WELL WITHIN LIMITS.  NOSE COWL HAD EXTENSIVE REPAIRS.					2	L	7	2 	4F			RT	A21EA   					 
1996050200133	19960502	00133	EA  	1996	5	2	96ZZZX2100       	1	19960322	G	5280	MS20253P5100L	PIN             		600316661   	CNDAIR	CL600 	CL6002A12   	1900304	EA  										LT GEAR DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	999JR	2852 				3061				PIN WAS FOUND BROKEN ON 600-HOUR INSPECTION.  THIS IS THE LATEST PART.  THE OLDER STYLE PIN AND HINGE WERE BREAKING THE 	HINGE PORTION.  NO HINGE FROM ALERT SB A601-0329.					2	L	7	2 	4F			RT	A21EA   					 
1996050200134	19960502	00134	CE  	1996	5	2	96ZZZX2101       	1	19960320	G	2913	710501	MOTOR           	AIRIGHT     	10138800515 	BEECH 	300   	300BEECH    	1152930	CE  										POWER PACK	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	03	63LB		933  		58	FA18				LANDING GEAR WOULD NOT EXTEND.  PUMPED GEAR DOWN MANUALLY WITH NO PROBLEM.  FOUND MOTOR ON POWER PACK WAS FROZEN.  POSSI	BLE SEAL LEAKAGE ON POWER PACK HAD EFFECT ON MOTOR.					2	L	7	2 	4T				A24CE   					 
1996050200135	19960502	00135	CE  	1996	5	2	96ZZZX2102       	1	19960320	G	2913	HP50A1	POWER PACK      			BEECH 	300   	300BEECH    	1152930	CE  										LANDING GEAR	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	63LB		2    		174C	FA18				POWER PACK WAS INSTALLED PER 300 MM.  AFTER FIRST HOUR, THE GEAR WOULD CYCLE EVERY 15-20 SECONDS.  NO EXTERNAL LEAKAGE F	OUND.  REMOVED AND REPLACED POWER PACK AND NEW POWER PACK FUNCTIONED OK.					2	L	7	2 	4T				A24CE   					 
1996050200137	19960502	00137	CE  	1996	5	2	96ZZZX2104       	1	19960404	G	5210		SEAL            			CESSNA	500   	S550        	2076607	CE  										DOOR	LEAKAGE         	D				G	B	A		O2 MASK DEPLOYED        	EMER. DESCENT           	UNSCHED LANDING         		J			WARNING INDICATION        			CR	CRUISE         	1			GL	07	106QS	9367 				S5500106				AIRCRAFT FLYING AT 37,000 FEET.  LOST PRESSURIZATION.  MASK DROPPED AND AIRCRAFT DESCENDED.  PASSENGERS WERE ON BOARD. A	IRCRAFT INSPECTED BY MAINTENANCE PERSONNEL FROM A CESSNA SERVICE CENTER AND NO PROBLEM COULD BE FOUND.  AIRCRAFT WAS FER	RIED TO SERVICE CENTER.  FOUND SEVERAL SMALL LEAKS AND A SMALL HOLE IN THE DOOR SEAL.  SEALED THE LEAKS, REPLACED THE DO	OR SEAL, AND BUILT THE DOOR FRAME UP TO GIVE THE SEAL A MORE POSITIVE SEAT.			1	L	7	2 	4F			RT	A22CE   					 
1996050200138	19960502	00138	CE  	1996	5	2	96ZZZX2105       	1	19960404	G	3222	084200036	AXLE            			CESSNA	500   	560CESSNA   	2076750	CE  										NLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	39N	254  				5600243				NOSE LANDING GEAR AXLE WAS INSTALLED NEW, 12-27-95, 1716.4 ACFT HRS.  REMOVED FROM SERVICE 4-3-96, 1970.4 ACFT HRS.  SEV	ERE CORROSION ON INNER WALLS OF TUBE.					2	L	7	2 	4F			RT	A22CE   					 
1996050200140	19960502	00140	EU  	1996	5	2	96ZZZX2107       	1	19960326	G	2844	Z00M7809178074	TRANSDUCER      			SOCATA	TBM   	TBM700      	8682000	EU  										FUEL PRESSURE	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	15	300AF	203  			03940037	97				FUEL PRESSURE WOULD DROP TO ZERO POUNDS IN-FLIGHT AT TIMES.  NOTE:  THIS IS THE THIRD TRANSDUCER TO GO BAD ON THIS AIRCR	AFT.  FIRST ONE LASTED 155 HRS.  SECOND ONE LASTED 120 HRS, AND THE THIRD ONE LASTED 203 HRS.					1	L	7	1 	3T			RT	A60EU   					 
1996050200141	19960502	00141	GL  	1996	5	2	96ZZZX2108       	3	19960307	G	6110		COUNTERWEIGHT   			MTSBSI	MU2   	MU2B35      	5780411	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	DOWEL PIN HOLE	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6569L					645		BU2089		PROPELLER COUNTERWEIGHT DOWEL PIN HOLE IS CRACKED.						1	H	7	2 	3T			RT	A10SW   		6	C	P15EA	 
1996050200142	19960502	00142	GL  	1996	5	2	96ZZZX2109       	3	19960307	G	6110	B30283	BRACKET         			MTSBSI	MU2   	MU2B35      	5780411	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP START LOCK	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6569L					645		BU2120		PROPELLER INSPECTION FOUND 2 EACH START LOCK BRACKETS CRACKED.						1	H	7	2 	3T			RT	A10SW   		6	C	P15EA	 
1996050200143	19960502	00143	GL  	1996	5	2	96ZZZX2110       	3	19960307	G	6110	1901	LINK ARM        			MTSBSI	MU2   	MU2B35      	5780411	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6569L					645		BU2089		PROPELLER LINK ARM IS CRACKED BETWEEN HOLES IN LINK ARM.						1	H	7	2 	3T			RT	A10SW   		6	C	P15EA	 
1996050200144	19960502	00144	GL  	1996	5	2	96ZZZX2111       	3	19960307	G	6110	1891	PILOT TUBE      			MTSBSI	MU2   	MU2B35      	5780411	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NR 2 SPIDER ARM	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6569L					645		BU2120		LONGITUDINAL CRACKS FOUND IN PILOT TUBE OF NR 2 SPIDER ARM.						1	H	7	2 	3T			RT	A10SW   		6	C	P15EA	 
1996050200145	19960502	00145	GL  	1996	5	2	96ZZZX2112       	3	19960307	G	6110	1891	PILOT TUBE      			MTSBSI	MU2   	MU2B35      	5780411	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NR 3 SPIDER ARM	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6569L					645		BU2120		LONGITUDINAL CRACKS FOUND IN PILOT TUBE OF NR 3 SPIDER ARM.						1	H	7	2 	3T			RT	A10SW   		6	C	P15EA	 
1996050200146	19960502	00146		1996	5	2	96ZZZX2113       	4	19960410	G	3416	2056011	INDICATOR       	SMITHSIND   		BOEING	737   	737*        		NM  										SERVOED ALTITUDE	WRONG CONNECTOR 	D	P			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15					150					THIS UNIT WAS RECEIVED FOR OVERHAUL.  WHEN THE UNIT WAS OPENED, FOUND THE CONNECTORS P3 AND J3 WERE NOT THE CORRECT TYPE	 PER CMM 34-10-16.					2	L	7	2 	4F			RT	A16WE   					 
1996050200147	19960502	00147	SW  	1996	5	2	96ZZZX2114       	1	19960410	G	5220	2622107001	SEAL            		2622105001  	SWRNGN	SA226 	SA226T      	8780122	SW  										EMERGENCY HATCH	MISINSTALLED    	G		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	200SN					T354				ATTEMPT TO REMOVE THE EMERGENCY EXIT FOR ACCESS FOR OTHER MAINTENANCE WAS UNSUCCESSFUL BY ONE PERSON.  EXIT HAD TO BE PR	IED FROM ACFT USING A SCREWDRIVER WHILE 2 PERSONS PULLED ON THE EXIT FROM WITHIN CABIN.  INSPECTION OF EXIT REVEALED SOM	E FORM OF SEALANT HAD BEEN APPLIED TO THE CORNERS OF THE EXIT SEAL BONDING THE EXIT TO ACFT AND PREVENTING ITS REQUIRED 	OPERATION.  THE ACFT HAD UNDERGONE A LETTER CHECK 'B' INSPECTION WITHIN 5 HOURS PRIOR TO THIS OCCURRENCE WHICH REQUIRES 	THE EMERGENCY EXIT BE FUNCTIONAL TESTED AND INSPECTED FOR OPERATION.		2	L	7	2 	4T			RT	A5SW    					 
1996050200148	19960502	00148	NE  	1996	5	2	96ZZZX2115       	2	19960209	G	7313	231001101	NOZZLE          		2163620     	BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL MANIFOLD	FLANGE CRACKED  	B	S		PGLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13										NOZZLE FLANGE CRACKED APPROXIMATELY 75 PERCENT OF DISTANCE AROUND CIRCUMFERENCE.  FOUND USING FPI.  VISIBLE ON BOTH SIDE	S OF FLANGE UNDER BLACK LIGHT.  SUSPECT CAUSE, IMPROPER TORQUE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996050200263	19960502	00263	SO  	1996	5	2	96ZZZX2141       	1	19960301	G	7603	455358	CONTROL CABLE   		PS501461313 	PIPER 	PA32  	PA32300     	7103212	SO  										THROTTLE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	21183	1981 				327840184				BROKEN THROTTLE CABLE.  THE THROTTLE CABLE BROKE WHILE IN THE SHOP BEING CHECKED FOR STIFFNESS IN MOVEMENT.						1	L	7	1 	3O			 	A3SO    					 
1996050200264	19960502	00264	SO  	1996	5	2	96ZZZX2142       	1	19960321	G	2434	ALU8421LS	ALTERNATOR      	PRESTOLITE  		PIPER 	PA32  	PA32R301    	7103218	SO  										DC SYSTEM	WRONG PART      	B			G9NR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	9779J	1243 			8Y000133	3213024				DURING THE COURSE OF AN ANNUAL INSPECTION, DISCOVERED A 24-VOLT ALTERNATOR WAS INSTALLED ON A 12-VOLT SYSTEM.  PART INST	ALLED WAS ALU-8421LS, 24-VOLT, 70-AMP.  ACCORDING TO THE PARTS BOOK PER SERIAL NUMBER OF AIRCRAFT, UNIT SHOULD BE A P/N 	ALY6421, 12-VOLT, 60-AMP ALTERNATOR.				1	L	7	1 	3O				A3SO    					 
1996050200265	19960502	00265	CE  	1996	5	2	96ZZZX2143       	1	19960419	G	2497		WIRE            			BEECH 	18    	E18S        	1151006	CE  										COPILOT PANEL	CHAFED          	G				A	B	F		UNSCHED LANDING         	EMER. DESCENT           	ACTIVATE FIRE EXT.      		A			FLAME/FIRE                			CR	CRUISE         	1			EA	03										PILOT REPORTED COCKPIT FIRE/SMOKE AND MADE EMERG DESCENT CONTAINING FIRE WITH HAND EXTINGUISHER.  SPARKS AND ENG OIL OBS	ERVED COMING FROM BEHIND COPILOT'S INSTRUMENT PANEL AND RT ENG WAS SHUT DOWN.  ULTIMATELY, PILOT EXECUTED EMERG LANDING 	WITH NO INJURIES OR DAMAGE.  INVESTIGATION REVEALED A WIRE BUNDLE BEHIND CO-PILOT'S INSTRUMENT PANEL HAD CHAFED AGAINST 	A 'HARD' LINE FOR RT ENG OIL PRESS PLUMBING SHORTING OUT AND CAUSING FIRE (A/C TIME, 15,400 HRS).  INVESTIGATING FSDO CO	NTACTED A BE-18 OPERATOR AND RELATED INCIDENT ASKING OPER TO CHK AREA ON A/C.  OPER RESPONDED THAT A SIMILAR SITUATION W	AS OBSERVED, 'BUS' WIRE BUNDLE FND RESTING AGAINST OIL PRESS GAUGE PLUMBING & HAD EVIDENCE OF CHAFING (A/C TIME, 13,777)	1	L	7	2 	3R			 	A765    					 
1996050200266	19960502	00266	SO  	1996	5	2	96ZZZX2144       	1	19960207	G	2430	9937705	SWITCH          			PIPER 	PA32  	PA32RT300T  	7103216	SO  										MASTER	FAILED          	D	S	A		A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			SW	99	132RR	1655 				32R7987098				AIRCRAFT LOST ALL ELECTRICAL POWER AFTER GEAR WAS RETRACTED ON DEPARTURE.  GEAR EXTENDED USING OVERRIDE AND UNEVENTFUL L	ANDING MADE.  INSPECTION REVEALED THAT BATTERY SIDE OF MASTER SWITCH WAS INOPERATIVE NOT ALLOWING THE MASTER SOLENOID TO	 FIND GROUND AND KEEP THE ELECTRICAL SYSTEM ON LINE.  LANDING LIGHT SWITCH ON THE SAME PANEL WAS REPLACED DUE TO FAILURE	 57 HOURS EARLIER.  NUMEROUS CORRODED SCREWS AND MOISTURE WERE FOUND IN THE SAME GENERAL AREA.  MASTER SWITCH HAD SLIGHT	 CORROSION.  RECOMMEND INSPECTION OF SIDE PANEL AND REPLACEMENT OF CRITICAL SWITCHES IF ANY EVIDENCE OF CORROSION IS FOU	ND.	1	L	7	1 	3O				A3SO    					 
1996050200267	19960502	00267	CE  	1996	5	2	96ZZZX2145       	1	19960409	G	7810	3595000539	EXHAUST         			BEECH 	36    	A36         	1151604	CE  										RT EXHAUST	CRACKED         	B	S		WC7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7230D					E2281				TAT:  1,999.5 HRS.  DURING REGULAR ENGINE OIL CHANGE, MECHANIC NOTICED EXHAUST STAINS ON VACUUM PUMP.  UPON CLOSER INSPE	CTION, FOUND RT EXHAUST STACK CRACKED AND SPLIT.  LENGTH ABOUT 4 INCHES BY .50 INCH WIDE.  SPLIT WAS DIRECTLY BELOW AREA	 WHERE ALL 3 CYLINDERS DUMP INTO STACK.  STARTED ALONG WELD SEAM.				1	L	7	1 	3O				3A15    					 
1996050200268	19960502	00268	SO  	1996	5	2	96ZZZX2146       	1	19960410	G	3230	452853	ROD END BEARING 			PIPER 	PA46  	PA46310P    	7104605	SO  										NLG ACTUATOR	BROKEN          	D	L			K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			SO	15	701TF					4608140				PILOT LANDED AIRCRAFT ON SOD RUNWAY WITH NUMEROUS SOFT SAND PITS CAUSING ACTUATOR SHAFT TO BEND.  PLANS WERE MADE FOR TA	KEOFF WITH SHORT FIELD EFFORT.  UPON RELEASING THE BRAKES, AIRCRAFT MOVED FORWARD 14 FEET BEFORE ROD END FAILED.  PILOT 	COULD HAVE SAVED PROPELLER AND ENGINE IF ACTUATOR SHAFT HAD BEEN VISUALLY CHECKED PRIOR TO TAKEOFF.  HAVE NO REASON TO B	ELIEVE THE PART WAS DEFECTIVE NOR WAS THE ACTUATOR BENT PRIOR TO LANDING.  GEAR RETRACTED AND EXTENDED PROPERLY AT THE L	AST POINT OF DEPARTURE.		1	L	7	1 	3O				A25SO   					 
1996050200271	19960502	00271	CE  	1996	5	2	96ZZZX2149       	1	19960408	G	2730	07341102AGW	TORQUE TUBE     			CESSNA	188   	A188B       	2073005	CE  										RT ELEVATOR	LOOSE RIVETS    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	731VX	2916 				18803200T				DURING ANNUAL INSPECTION, FOUND 6 EACH LOOSE ('WORKING') AN470AD5 RIVETS IN RIGHT ELEVATOR TORQUE TUBE ASSY AT TUBE/ATTA	CH FLANGE JOINT TO ELEVATOR ARM, PN 1234029-1AGW.  FOUND DEFECT BY MOVING TRAILING EDGE OF LT AND RT ELEVATOR IN OPPOSIT	E UP AND DOWN MOTION USING LIGHT TO MODERATE FORCE AND FELT AS WELL AS SAW MOTION IN RIVET JOINT.  REMOVED RIVETS AND FO	UND 'SHEAR' DAMAGE TO RIVET GRIPS.  REPLACED RIVETS TO REPAIR.			1	L	7	1 	3O				A9CE    					 
1996050200272	19960502	00272	SO  	1996	5	2	96ZZZX2150       	2	19960320	G	8530	652954A1	CYLINDER        			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520A      	17032	SO  					CYLS 2,6,1,3,5	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4975U	778  				U20605179	284679R			NR 2, NR 6, NR 1, NR 3, AND NR 5 CYLINDERS WERE FOUND CRACKED AT INTAKE SEAT.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996050200273	19960502	00273	SO  	1996	5	2	96ZZZX2151       	2	19960301	G	8530	652954A1	CYLINDER        			CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520A      	17032	SO  					CYLS NR 4, 1	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4672U	540  				U20605046	284695R			NR 4 AND NR 1 CYLINDERS WERE FOUND CRACKED AT INTAKE SEAT.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996050200274	19960502	00274	SO  	1996	5	2	96ZZZX2152       	2	19960320	G	8530	652954A1	CYLINDER        			CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520A      	17032	SO  					CYLS NR 3, 2, 5	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	244PL	760  				4371	28468R			NR 3, NR 2, AND NR 5 CYLINDERS WERE FOUND CRACKED AT INTAKE SEAT.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996050200275	19960502	00275	GL  	1996	5	2	96ZZZX2153       	3	19960409	G	6111	FC8465B6	BLADE           			BEECH 	55    	95B55       	1152706	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	SHANK	UNDER SIZE      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	17978				D22145	TC2063		AN252		INSPECTION FOUND BOTH BLADES OF THE PROPELLER ASSEMBLY TO BE UNDER MINIMUM SHANK DIAMETER.  SUBMITTER STATED BLADE SHANK	S WERE PROBABLY REWORKED UNDER DIMENSION AT LAST PROPELLER SERVICE.					1	L	7	2 	3O				3A16    		5	C	P920	 
1996050200276	19960502	00276	GL  	1996	5	2	96ZZZX2154       	3	19960409	G	6111	FC8465B6	BLADE           			BEECH 	55    	95B55       	1152706	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	SHANK	UNDER SIZE      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	17978				D22161	TC2063		AN252		INSPECTION FOUND BOTH BLADES OF THE PROPELLER ASSEMBLY TO BE UNDER MINIMUM SHANK DIAMETER.  SUBMITTER STATED BLADE SHANK	S WERE PROBABLY REWORKED UNDER DIMENSION AT LAST PROPELLER SERVICE.					1	L	7	2 	3O				3A16    		5	C	P920	 
1996050200277	19960502	00277	GL  	1996	5	2	96ZZZX2155       	3	19960409	G	6114	D220118	HUB             			BEECH 	55    	95B55       	1152706	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PRELOAD AREA	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	17978					TC2063		AN252		HUB WAS FOUND TO HAVE DAMAGE TO PRELOAD RETENTION AREA.  SUBMITTER STATED DAMAGE POSSIBLY OCCURRED FROM STRIKE DAMAGE TO	 ONE OR MORE BLADES.					1	L	7	2 	3O				3A16    		5	C	P920	 
1996050200278	19960502	00278	GL  	1996	5	2	96ZZZX2156       	3	19960409	G	6111	FC8465B6	BLADE           			BEECH 	55    	95B55       	1152706	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	SHANK	UNDER SIZE      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	17978				D22142	TC2063		AN3264		BOTH BLADES OF THE PROPELLER ASSEMBLY WERE FOUND TO BE UNDER MINIMUM SHANK DIAMETER.  SUBMITTER STATED BLADE SHANKS WERE	 PROBABLY REWORKED UNDER DIMENSION AT LAST PROPELLER SERVICE.					1	L	7	2 	3O				3A16    		5	C	P920	 
1996050200279	19960502	00279	GL  	1996	5	2	96ZZZX2157       	3	19960409	G	6111	FC8465B6	BLADE           			BEECH 	55    	95B55       	1152706	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	SHANK	UNDER SIZE      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	17978				D22444	TC2063		AN3264		BOTH BLADES OF THE PROPELLER ASSEMBLY WERE FOUND TO BE UNDER MINIMUM SHANK DIAMETER.  SUBMITTER STATED BLADE SHANKS WERE	 PROBABLY REWORKED UNDER DIMENSION AT LAST PROPELLER SERVICE.					1	L	7	2 	3O				3A16    		5	C	P920	 
1996050200281	19960502	00281	EA  	1996	5	2	96ZZZX2159       	2	19960223	G	8530	LW11634	VALVE           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 CYL EXH	STUCK           	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			WP	09	757CM	2581 				15279633	L1480515			AIRCRAFT WAS ON TRAINING FLIGHT AFTER PERFORMING ROUTINE MANEUVERS.  ENGINE BEGAN TO RUN ROUGH.  A FORCED OFF-FIELD LAND	ING WAS MADE WITHOUT DAMAGE TO AIRCRAFT, HOWEVER, INSPECTION ON ENGINE REVEALED STUCK VALVE (EXHAUST) ON NR 1 CYLINDER.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996050200283	19960502	00283	SO  	1996	5	2	96ZZZX2161       	2	19960401	G	7414		CONTACT POINTS  	SLICK       	6320        	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT ENG LT MAG	CORRODED        	B			CRJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	135BG				92080002	414A0419	521195			JUST PRIOR TO AIRCRAFT BEING INDUCTED FOR 100-HOUR INSPECTION, PILOT INFORMED MAINTENANCE OF ROUGH RT MAG ON RT ENGINE. 	 INVESTIGATION SHOWED SEVERE CORROSION ON POINTS, GEARS, CAPACITOR, AND BEARINGS.  CHECK REMAINING 3 MAGNETOS AND FOUND 	IDENTICAL CONDITIONS OF SEVERE CORROSION.  ALL FOUR MAGNETOS WERE CLEANED AND AFFECTED PARTS WERE REPLACED.  PROBLEM BEL	IEVED TO BE CAUSED BY PRESSURIZED AIR FROM TURBOS.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996050200284	19960502	00284	SO  	1996	5	2	96ZZZX2162       	2	19960401	G	7414		CONTACT POINTS  	SLICK       	6320        	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RT ENG LT MAG	CORRODED        	B			CRJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	135BG				93020037	414A0419	521195			JUST PRIOR TO AIRCRAFT BEING INDUCTED FOR 100-HOUR INSPECTION, PILOT INFORMED MAINTENANCE OF ROUGH RT MAG ON RT ENGINE. 	 INVESTIGATION SHOWED SEVERE CORROSION ON POINTS, GEARS, CAPACITOR, AND BEARINGS.  CHECK REMAINING 3 MAGNETOS AND FOUND 	IDENTICAL CONDITIONS OF SEVERE CORROSION.  ALL FOUR MAGNETOS WERE CLEANED AND AFFECTED PARTS WERE REPLACED.  PROBLEM BEL	IEVED TO BE CAUSED BY PRESSURIZED AIR FROM TURBOS.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996050200285	19960502	00285	SO  	1996	5	2	96ZZZX2163       	2	19960401	G	7414		CONTACT POINTS  	SLICK       	6320        	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT ENG RT MAG	CORRODED        	B			CRJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	135BG				92080010	414A0419	521195			JUST PRIOR TO AIRCRAFT BEING INDUCTED FOR 100-HOUR INSPECTION, PILOT INFORMED MAINTENANCE OF ROUGH RT MAG ON RT ENGINE. 	 INVESTIGATION SHOWED SEVERE CORROSION ON POINTS, GEARS, CAPACITOR, AND BEARINGS.  CHECK REMAINING 3 MAGNETOS AND FOUND 	IDENTICAL CONDITIONS OF SEVERE CORROSION.  ALL FOUR MAGNETOS WERE CLEANED AND AFFECTED PARTS WERE REPLACED.  PROBLEM BEL	IEVED TO BE CAUSED BY PRESSURIZED AIR FROM TURBOS.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996050200286	19960502	00286	SO  	1996	5	2	96ZZZX2164       	2	19960401	G	7414		CONTACT POINTS  	SLICK       	6320        	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RT ENG RT MAG	CORRODED        	B			CRJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	135BG				93020044	414A0419	521195			JUST PRIOR TO AIRCRAFT BEING INDUCTED FOR 100-HOUR INSPECTION, PILOT INFORMED MAINTENANCE OF ROUGH RT MAG ON RT ENGINE. 	 INVESTIGATION SHOWED SEVERE CORROSION ON POINTS, GEARS, CAPACITOR, AND BEARINGS.  CHECK REMAINING 3 MAGNETOS AND FOUND 	IDENTICAL CONDITIONS OF SEVERE CORROSION.  ALL FOUR MAGNETOS WERE CLEANED AND AFFECTED PARTS WERE REPLACED.  PROBLEM BEL	IEVED TO BE CAUSED BY PRESSURIZED AIR FROM TURBOS.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996050200287	19960502	00287	CE  	1996	5	2	96ZZZX2165       	1	19960329	G	2520	521912514	SEAT            			CESSNA	402   	402C        	207590R	CE  										PAX NR 4	FAILED          	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	2610Z	244  				402C0068				WHEN LOADING PASSENGERS, A PASSENGER WAS LEANING ON THE SEAT BACK OF NR 4 SEAT AND THE SEAT BUCKET SEPARATED FROM THE PE	DESTAL.  THIS SEAT WAS A REPLACEMENT SEAT INSTALLED APPROXIMATELY 3 MONTHS AGO AFTER THE EXACT SAME PROBLEM OCCURRED.  T	HE STC'D SEATS WERE ORIGINALLY INSTALLED IN THIS AIRCRAFT ON DECEMBER 18, 1995 AT 9,805 HRS TOTAL TIME.  THE STC NR IS S	A 2715CE FOR THE SINGLE PASSENGER SEAT.  SUBMITTER RECOMMENDS DAILY INSPECTIONS BE MADE TO THE SEATS ESPECIALLY AREA OF 	THE 'HOURGLASS' SEAT PEDESTAL.  ALSO, RECOMMEND CESSNA MULTIENGINE BULLETIN MEB 87-9 BE CONSIDERED A MANDATORY INSTALLAT	ION.  AIRCRAFT TOTAL TIME FOR THIS REPORT IS 10,048.8 HOURS.	1	L	7	2 	3O				A7CE    					 
1996050200288	19960502	00288	CE  	1996	5	2	96ZZZX2166       	1	19960324	G	3250	AN4H4AM	BOLT            		960000601   	BEECH 	55    	95C55       	1152708	CE  										NLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	65AC	8000 				TE242				NOSE LANDING GEAR BOLTS, 2 EACH, BROKE CAUSING STEERING PROBLEMS WHICH CAUSED KNEE (SCISSORS) PN 96-820020-1 TO BREAK ON	 LANDING.  SUSPECT CAUSE OF BOLTS TO BREAK WAS TURNING NOSE GEAR TOO MUCH TO THE LEFT OR RIGHT WHEN THE AIRCRAFT WAS TOW	ED PRIOR TO FLIGHT.				1	L	7	2 	3O				3A16    					 
1996050200289	19960502	00289	CE  	1996	5	2	96ZZZX2167       	1	19960205	G	5102		CABLE           			HEAD  	AX888 	AX888HEAD   	05637T7	CE  										BASKET	ELONGATED       	B			RG1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	8307M	82   				218				THE MALFUNCTION CONSISTS OF ELONGATION OF THE EYES ON THE BASKET SUSPENSION CABLES.  THIS CONDITION WAS FOUND DURING A R	OUTINE ANNUAL INSPECTION AND CLEARLY FALLS OUTSIDE THE MANUFACTURER'S CRITERIA FOR AIRWORTHINESS.  WHEN THE MANUFACTURER	 SENT REPLACEMENT PARTS, IT WAS EVIDENT THAT INCORRECT PARTS WERE ORIGINALLY INSTALLED.				1	B	0	0 	  			 	A29SO2  					 
1996050200290	19960502	00290	SO  	1996	5	2	96ZZZX2168       	1	19960205	G	2435	8013C	GENERATOR       			PIPER 	PA31T 	PA31T       	7103124	SO  										START/GEN RT	SHORTED         	D	L			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	515BA	2989 	251  		161	31T8120044				INVESTIGATION FOR UNCONTROLLED OVERVOLTAGE CONDITION FOUND SHORTED STARTER/GENERATOR ON RT ENGINE.						1	L	7	2 	3T				A8EA    					 
1996050200291	19960502	00291	SO  	1996	5	2	96ZZZX2169       	2	19960208	G	7314	50611043	VANE            		6462103     	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					FUEL PUMP	WRONG PART      	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	255CS	240  			K179403BR	4040019	276435R			SUBMITTER STATES NUMEROUS FAILURES WITH FUEL PUMP VANE PN 50611043.  CORRECT VANE PN IS 635549.  FURTHER STATES PROBLEM 	REQUIRES URGENT ACTION DUE TO NUMBERS AND TYPE OF FAILURES.					1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996050200292	19960502	00292	CE  	1996	5	2	96ZZZX2170       	1	19960205	G	2730	05133711	BRACKET         			CESSNA	172   	172G        	2072420	CE  										ELEV BELLCRANK	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4250L	6731 				17254319				DURING ANNUAL INSPECTION, NOTED EXCESS MOVEMENT REQUIRED IN ELEVATOR CONTROL TO PRODUCE ANY MOVEMENT IN ELEVATOR.  INVES	TIGATION SHOWED ELEVATOR BELLCRANK BRACKET BROKEN LOOSE FROM FRONT STRINGER AND ALL BUT ONE RIVET ON THE REAR STRINGER. 	 REPLACED BRACKET WITH NEW ITEM WHICH HAS BEEN SUBSTANTIALLY STRENGTHENED.  SUBMITTER STATED THIS BRACKET HAS BEEN SUBJE	CT OF NO FEWER THAN 5 PREVIOUS MDR'S.  NO CAUSE DETERMINED.  RECOMMEND ONE TIME INSPECTION OF ALL AIRCRAFT WITH THIS BRA	CKET INSTALLED.		1	H	7	1 	3O			NT	3A12    					 
1996050200293	19960502	00293	SW  	1996	5	2	96ZZZX2171       	1	19960404	G	3244	650X8	TIRE            	MCCREARY    		RKWELL	700   	700         	7630520	SW  										RIM BEAD	RUPTURED        	H		A		O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	11	4EP	32   			B3L6335	00032				TIRE BLEW OUT ON TAXI AFTER NORMAL LANDING.  FRACTURE AT THE OUTER EDGE OF RIM BEAD.  FOUR LANDINGS LATER ON TAXI TO TAK	EOFF, OTHER TIRE FAILED IN THE SAME PLACE.  BOTH TIRES WERE INSTALLED 11-20-95 AND FAILED 3-19-96 AND 3-26-96.					1	L	7	2 	3O				A12SW   					 
1996050200294	19960502	00294	CE  	1996	5	2	96ZZZX2172       	1	19960327	G	2730	05130633	BRACKET         			CESSNA	172   	172F        	2072414	CE  										ELEV BELLCRANK	FAILURE         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5682R	5000 				17253323				FOUND FATIGUE FAILURE OF THE ELEVATOR FORWARD BELLCRANK BRACKET.  SUSPECT CAUSED BY A STRONG TAIL WIND AT THE TIE-DOWN L	OCATION, FLEXING THE ELEVATOR AGAINST THE CONTROL COLUMN LOCK.					1	H	7	1 	3O			NT	3A12    					 
1996050200295	19960502	00295	CE  	1996	5	2	96ZZZX2173       	1	19960416	G	3230	504501019	TORQUE TUBE     			CESSNA	340   	340A        	2076405	CE  										LT MLG WELL	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	6311X	3706 				340A0482				DURING ROUTINE ANNUAL INSPECTION, LT LANDING GEAR TORQUE TUBE FOUND CRACKED APPROXIMATELY 2 INCHES AROUND WELD AT CLEVIS	 BOSS FOR OVERCENTER LINK.  SUBMITTER REPORTS FINDING THIS CONDITION ON 4 OTHER MODEL 340 AIRCRAFT.					1	L	7	2 	3O				3A25    					 
1996050200296	19960502	00296	CE  	1996	5	2	96ZZZX2174       	1	19960401	G	2720		PEDAL           			BBAVIA	8     	8KCAB       	2110612	CE  										LT FWD RUDDER	FAILED          	H		A	LP8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	5061K	35   				56079				INSTALLED THE 4TH RUDDER PEDAL.  THIRTY-FIVE HOURS TACH TIME ON THE THIRD RUDDER PEDAL BEFORE FAILURE.						1	H	7	1 	3O				A21CE   					 
1996050200297	19960502	00297	EA  	1996	5	2	96ZZZX2175       	1	19960402	G	3020	601970975	VALVE           			CNDAIR	CL601 	CL6013A     	8070802	EA  										COWL ANTI-ICE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	417CL				033	5107				RECEIVED AND INSTALLED REPAIRED COWL ANTI-ICE VALVE.  VALVE FAILED ON FIRST FLIGHT.  SUBMITTER STATED THESE VALVES HAVE 	A VERY HIGH FAILURE RATE.					2	L	7	2 	4F			RT	A21EA   					 
1996050200298	19960502	00298	EA  	1996	5	2	96ZZZX2176       	2	19960328	G	8530	65007	RETAINER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					INTAKE PUSHROD	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	17	8172Q		500  			288090263	L2803436A			PUSHROD TUBE ON NR 2 CYLINDER INTAKE HAS A PERSISTENT OIL LEAK NEAR THE CRANKCASE.  WHEN CHANGING THE PUSHROD TUBE SEAL 	THIS TIME, THE PUSHROD TUBE RETAINER WHICH IS PRESSED INTO THE CRANKCASE WAS FOUND CRACKED ABOUT ONE-FOURTH OF THE WAY A	ROUND THE CIRCUMFERENCE.				1	L	7	1 	3O	3	O		2A13    	E286				 
1996050200300	19960502	00300	EA  	1996	5	2	96ZZZX2178       	2	19960412	G	7322	3472	VALVE SEAT      		MA45        	CESSNA	182   	182R        	2072731	CE  	LYC   	O540  	O540L3C5    	41532	EA  					PUMP DISCHARGE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	58JK	656  			75030510	18268286				ENGINE RUNNING EXTREMELY RICH.  FOUND PUMP DISCHARGE CHECK VALVE SEAT WORN OFF.						1	L	7	1 	3O	3	O	NT	3A13    	E295				 
1996050200301	19960502	00301	EA  	1996	5	2	96ZZZX2179       	2	19960412	G	7322	3472	VALVE SEAT      			CESSNA	182   	182R        	2072731	CE  	LYC   	O540  	O540L3C5    	41532	EA  					PUMP DISCHARGE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2427E	880  				18268202				ENGINE RUNNING EXCESSIVELY RICH.  FOUND PUMP DISCHARGE CHECK VALVE SEAT WORN OFF.						1	L	7	1 	3O	3	O	NT	3A13    	E295				 
1996050200302	19960502	00302	SO  	1996	5	2	96ZZZX2180       	1	19960408	G	7160		HEAT VALVE      			MAULE 	MX7   	MX7180      	5460185	SO  										CARBURETOR AIR	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	5666N	808  				11024C				DURING HEAT VALVE INSPECTION PER MAULE SB 16 (2-20-96) REFERENCE SL NR 56 (2-27-96) FOUND ON VISUAL INSPECTION, NO DEFEC	TS, BUT WHEN SLIGHT PULL PRESSURE APPLIED, THE RED SILICONE RUBBER SEPARATED.					1	H	7	1 	3O			NC	3A23    					 
1996050200303	19960502	00303	SO  	1996	5	2	96ZZZX2181       	1	19960404	G	7922	75944	VALVE           			PIPER 	PA23  	PA23250     	7102308	SO  										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6256Y	3828 			69503	273495				LYCOMING SB 518C APPLIES.  NUT LOOSE ON END OF VERNATHERM, PROBABLY DUE TO VIBRATION.  REPLACED DEFECTIVE PART WITH A NE	W PART NOT CALLED OUT IN THE SERVICE BULLETIN.					1	L	7	2 	3O				1A10    					 
1996050200304	19960502	00304	CE  	1996	5	2	96ZZZX2182       	1	19960404	G	7922	75944	VALVE           			CESSNA	150   	152         	2071835	CE  										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	65464	4021 			9255	15281567				LYCOMING SB 518C APPLIES.  NUT LOOSE ON END OF VERNATHERM, PROBABLY DUE TO VIBRATION.  REPLACED DEFECTIVE PART WITH A NE	W PART NOT CALLED OUT IN THE SERVICE BULLETIN.					1	H	7	1 	3O			NT	3A19    					 
1996050200305	19960502	00305	CE  	1996	5	2	96ZZZX2183       	1	19960404	G	7922	75944	VALVE           			CESSNA	172   	172P        	2072436	CE  										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	51804	2721 			105188	17274351				LYCOMING SB 518C APPLIES, NUT LOOSE ON END OF VERNATHERM.  PROBABLY DUE TO VIBRATION.  REPLACED DEFECTIVE PART WITH A NE	W PART NOT CALLED OUT IN THE SERVICE BULLETIN.					1	H	7	1 	3O			NT	3A12    					 
1996050200306	19960502	00306	SO  	1996	5	2	96ZZZX2184       	1	19960404	G	7922	75944	VALVE           			GULSTM	AA5   	AA5B        	3960105	SO  										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	28395	2261 			94320	AA5B0588				LYCOMING SB 518C APPLIES, NUT LOOSE ON END OF VERNATHERM.  PROBABLY DUE TO VIBRATION.  REPLACED DEFECTIVE PART WITH A NE	W PART NOT CALLED OUT IN THE SERVICE BULLETIN.					1	L	7	1 	3O				A16EA   					 
1996050200307	19960502	00307	CE  	1996	5	2	96ZZZX2185       	1	19960404	G	7922	75944	VALVE           			CESSNA	172   	172K        	2072430	CE  										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	7410G	3861 				17259110				LYCOMING SB 518C APPLIES, NUT LOOSE ON END OF VERNATHERM, PROBABLY DUE TO VIBRATION.  REPLACED DEFECTIVE PART WITH A NEW	 PART NOT CALLED OUT IN THE SERVICE BULLETIN.					1	H	7	1 	3O			NT	3A12    					 
1996050200308	19960502	00308	CE  	1996	5	2	96ZZZX2186       	1	19960405	G	6123	99103233	BALL JOINT      			CESSNA	441   	441         	2076020	CE  										PROP CONTROL	FAILED          	B			FEHR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	13	910EA					4410070				AFTER LANDING WHEN REVERSE WAS SELECTED, THE LEFT ENGINE DID NOT REVERSE.  INVESTIGATION REVEALED BALL SOCKET HAD WORN T	O THE POINT THE BALL FELL OUT OF SOCKET AS PROPELLER CONTROL WAS MOVING AFT.  THIS IS A SWAGED JOINT WITH NO SAFETY CLIP	S TO PREVENT TOTAL SEPARATION.  INSPECTION IS ONLY REQUIRED ON PHASE 2 AND A POSITIVE EVALUATION IS NOT POSSIBLE UNLESS 	INSPECTION EXCEEDS REQUIREMENTS AND ROD END IS DISCONNECTED TO ACCURATELY ASSESS WEAR BY DETERMINING ACTUAL AMOUNT OF LI	NEAR MOVEMENT.		1	L	7	2 	3T			RT	A28CE   					 
1996050200309	19960502	00309	CE  	1996	5	2	96ZZZX2187       	1	19960222	G	2434	6203BRS	BEARING         	PRESTOLITE  	ALV9510ECH  	CESSNA	402   	402C        	207590R	CE  										LT ALTERNATOR	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SO	13	51SC	289  			9050464	402C0106				SHORTLY AFTER START-UP, THE LEFT ALTERNATOR LIGHT ILLUMINATED.  ACFT WAS SHUT DOWN AND INSPECTED.  OUTBOARD BEARING OF A	LTERNATOR FOUND FAILED.  UPON ALTERNATOR REMOVAL, DRIVE HUB (PN 640934) WAS ALSO FOUND FAILED.  THIS ALTERNATOR DOES NOT	 REQUIRE THE 100-HOUR LUBE.  THE RIGHT ALTERNATOR BEARING WAS INSPECTED ALSO AND FOUND SERVICEABLE, BUT NOT VERY MUCH GR	EASE WAS FOUND.  BOTH UNITS WERE INSTALLED AT THE SAME TIME.			1	L	7	2 	3O				A7CE    					 
1996050200310	19960502	00310	CE  	1996	5	2	96ZZZX2188       	1	19960222	G	2434	640934	HUB             	PRESTOLITE  	ALV9510ECH  	CESSNA	402   	402C        	207590R	CE  										ALTERNATOR DRIVE	FAILED          	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SO	13	51SC	289  			9050464	402C0106				SHORTLY AFTER START-UP, THE LEFT ALTERNATOR LIGHT ILLUMINATED.  ACFT WAS SHUT DOWN AND INSPECTED.  OUTBOARD BEARING OF A	LTERNATOR FOUND FAILED.  UPON ALTERNATOR REMOVAL, DRIVE HUB (PN 640934) WAS ALSO FOUND FAILED.  THIS ALTERNATOR DOES NOT	 REQUIRE THE 100-HOUR LUBE.  THE RIGHT ALTERNATOR BEARING WAS INSPECTED ALSO AND FOUND SERVICEABLE, BUT NOT VERY MUCH GR	EASE WAS FOUND.  BOTH UNITS WERE INSTALLED AT THE SAME TIME.			1	L	7	2 	3O				A7CE    					 
1996050200311	19960502	00311	EA  	1996	5	2	96ZZZX2189       	2	19960322	G	8520	75060	CONNECT ROD     			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 6, NR 1 ROD	BOLT NOT MARKED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	4053R		339  			3240355	L794448			ENGINE DISASSEMBLED AND FOUND 3 BOLTS WITH NO HEAD MARKING.  ONE EACH LOCATED ON NR 6 ROD.  TWO EACH LOCATED ON NR 1 ROD	.					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996050200312	19960502	00312	SW  	1996	5	2	96ZZZX2190       	1	19960325	G	8120	LW10098L	CONTROLLER      			MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540AF1A  	41532	EA  					TURBO	DEFECTIVE       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NE	05	1086D	1165 			SK0121L	270041	L920561A			ENGINE SURGES AT FLIGHT LEVELS.  SURGES 200 RPM AND 2 INCH MAP.  REPLACED DIFFERENTIAL PRESSURE CONTROLLER TO C/W LYC SB	 WITH PN 48B21935.					1	L	7	1 	30	3	O	RT	2A3     	E14EA				 
1996050200570	19960502	00570	SW  	1996	5	2	96ZZZX2196       	1	19960312	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	445  				45433				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 445.4 HOURS	.			1	G	7	1 	3U				H2SW    					 
1996050200571	19960502	00571	SW  	1996	5	2	96ZZZX2197       	1	19960312	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	445  				45433				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 445.4 HOURS	.			1	G	7	1 	3U				H2SW    					 
1996050200574	19960502	00574	SW  	1996	5	2	96ZZZX2200       	1	19960320	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	532  				52063				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 532.0 HOURS	.			1	G	7	1 	3U			NC	H2SW    					 
1996050200575	19960502	00575	SW  	1996	5	2	96ZZZX2201       	1	19960320	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	532  				52063				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 532 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1996050200576	19960502	00576	SW  	1996	5	2	96ZZZX2202       	1	19960312	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	456  				52066				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 456.0 HOURS	.			1	G	7	1 	3U			NC	H2SW    					 
1996050200577	19960502	00577	SW  	1996	5	2	96ZZZX2203       	1	19960312	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	456  				52066				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 456 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1996050200578	19960502	00578	SW  	1996	5	2	96ZZZX2204       	1	19960320	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	206SL	360  				45245				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 360.0 HOURS	.			1	G	7	1 	3U				H2SW    					 
1996050200579	19960502	00579	SW  	1996	5	2	96ZZZX2205       	1	19960320	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	206SL	360  				45245				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 360.0 HOURS	.			1	G	7	1 	3U				H2SW    					 
1996050200582	19960502	00582	SW  	1996	5	2	96ZZZX2208       	1	19960320	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	610  				51460				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 609.6 HOURS	.			1	G	7	1 	3U				H2SW    					 
1996050200583	19960502	00583	SW  	1996	5	2	96ZZZX2209       	1	19960320	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	610  				51460				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 609.6 HOURS	.			1	G	7	1 	3U				H2SW    					 
1996050200584	19960502	00584	SW  	1996	5	2	96ZZZX2210       	1	19960312	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	3890B	315  				45480				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 314.7 HOURS	.			1	G	7	1 	3U				H2SW    					 
1996050200585	19960502	00585	SW  	1996	5	2	96ZZZX2211       	1	19960312	G	6230	206101336005	LINK IDLER      		206010350021	BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3890B	315  				45480				DAILY INSPECTION FOUND BUSHINGS AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH PN 206-010-338-00	1 SPACERS, 4 EACH PN 206-010-337-001 BEARINGS, 2 EACH PN 206-010-338-003 BUSHINGS, 2 EACH PN NAS6605D64 BOLTS, AND 1 EAC	H PN 206-010-470-101 BEARING.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 314.7 HOURS	.			1	G	7	1 	3U				H2SW    					 
1996050200586	19960502	00586	SW  	1996	5	2	96ZZZX2212       	1	19960304	G	6310	206040272101	BOOT            		206010015015	BELL  	206   	206L3       	1182108	SW  										DRIVE SHAFT	TORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	364AL	792  	499  		9193B	51434				DAILY AAIP FOUND BOOT TORN.  DRIVE SHAFT SLINGING GREASE.						1	G	7	1 	3U				H2SW    					 
1996050200587	19960502	00587	NE  	1996	5	2	96ZZZX2213       	1	19960328	G	2910	7665109007060	TUBE ASSY       			SKRSKY	S76   	S76A        	8143006	NE  										NR 1 HYD PUMP	CHAFED          	B			ALGR	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	376AL					760002				DURING GROUND RUN, NR 1 SERVO CAUTION LIGHT ILLUMINATED.  AIRCRAFT WAS SHUT DOWN.  DURING TROUBLESHOOTING, HYDRAULIC LIN	E WAS FOUND CHAFING ON THE FIREWALL.  REPLACED LINE ASSY.  SERVICED AND GROUND RUN.  LEAK CHECK OK.					1	G	7	2 	3U				H1NE    					 
1996050200588	19960502	00588	SW  	1996	5	2	96ZZZX2214       	1	19960313	G	5302	214021209127	SUPPORT ANGLE   			BELL  	214   	214ST       	1182106	SW  										TAILBOOM AFT LT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	390AL	3612 				28198				PHASE INSPECTION FOUND ANGLE CRACKED ON FORWARD END APPROXIMATELY 2 INCHES FROM END OF ANGLE.  THE SUSPECT CAUSE WAS VIB	RATION.					2	G	7	2 	4U				H10SW   					 
1996050200591	19960502	00591	NE  	1996	5	2	96ZZZX2217       	1	19960318	G	6210	761500900047A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	768AL	7122 	469  		A08600103	760031				DURING 500-HOUR INSPECTION, FOUND BLADE SPAR CRACKED AT ROOT END BUSHING HOLE.  SUBMITTER STATED CAUSE UNKNOWN.						1	G	7	2 	3U				H1NE    					 
1996050200592	19960502	00592	GL  	1996	5	2	96ZZZX2218       	2	19960307	G	7210	6889326	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	768AL				MP02911	760031	890074S			UPON DISASSEMBLY OF GEARBOX, CLEANED AND INSPECTED PARTS AS REQUIRED.  FOUND EXCESSIVE GALLING ON PTO AFT, BEARING INNER	 RACE.  EXCESSIVE GALLING, BEARING INNER RACE, POSSIBLY DUE TO BEARING CAGE OUT-OF-ROUND CAUSING TIGHT FIT BETWEEN INNER	 AND OUTER RACE AND BALLS.				1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996050900095	19960509	00095	EU  	1996	5	9	96ZZZX2220       	1	19960325	G	5320		FRAME           			SAAB  	SF340 	340B        	7860101	EU  										AFT CARGO DOOR	DAMAGED         	B	S		DP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	312AE	8473 				340B312				FUSELAGE AFT CARGO DOOR FRAME DAMAGED ON GROUND.  IMPACTED AREA REVEALED DELAMINATION AND SEPARATION OF SKIN LAYER, APPR	OXIMATELY 5 INCHES BY 3.50 INCHES AT BS 685 AND WL 781.  INSPECTED TRANSMISSION THROUGH ULTRASONIC.					2	L	7	2 	4T			RT	A52EU   					 
1996050900096	19960509	00096	EU  	1996	5	9	96ZZZX2221       	1	19960409	G	3010	T700A3013002101	DEICE TUBE      			SOCATA	TBM   	TBM700      	8682000	EU  										RT HORIZ STAB	CHAFED          	B		A	JAVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	57HC	759  				90				DURING ANNUAL INSPECTION, RIGHT ELEVATOR HORN DEICE BOOT AIR TUBE FOUND CHAFED AT THE 90 DEGREE BEND WHERE IT ENTERS THE	 ELEVATOR TIP.  THE CHAFED AREA HAD CREATED A SMALL HOLE IN THE TUBE.  NEW TUBE INSTALLED AND ELEVATOR OPENING FOR TUBE 	SLIGHTLY ENLARGED TO PREVENT CONTACT.  SYSTEM OPERATIONALLY CHECKED NORMAL.  ELEVATORS ARE REMOVED AT ANNUAL AND AREA SH	OULD BE CHECKED.  THIS LINE IS STANDARD ON S/N 50 AND UP, IT IS REQUIRED BY AD 95-11-16 SOCATA AND SB 70-020-30 FOR SERI	AL NUMBERS 1 THROUGH 49.  FAILURE OF LINE COULD CAUSE ELEVATOR JAMMING IN ICING CONDITIONS.		1	L	7	1 	3T			RT	A60EU   					 
1996050900097	19960509	00097	SW  	1996	5	9	96ZZZX2222       	1	19960315	G	2720	500012253	CONTROL CABLE   			GULSTM	690TP 	690B        	7630516	SW  										AFT RUDDER RT	FRAYED          	B		A	FB2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	100AM	2400 				11361				DURING C/W TWIN COMMANDER SB 195B, FOUND BOTH AFT RUDDER CABLES TO HAVE NUMEROUS CABLE STRANDS BROKEN.  THE INSTRUCTIONS	 IN THE SB DO NOT ADDRESS THE REMOVAL OR INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14. T	HIS PROCEDURE IS THE ONLY WAY TO PROPERLY INSPECT THESE CABLES.  SUBMITTER HAS FOUND MANY AIRCRAFT WITH CABLE STRANDS BR	OKEN BEYOND THE LIMITS IN THE SB WHILE INSPECTING THE CABLES IN THIS MANNER.  SUBMITTER SUGGESTS OWNERS C/W SI-199 WHICH	 INSTALLS LARGER PULLEYS AT THIS LOCATION.		1	H	7	2 	3T			 	2A4     					 
1996050900098	19960509	00098	SW  	1996	5	9	96ZZZX2223       	1	19960315	G	2720	500012251	CONTROL CABLE   			GULSTM	690TP 	690B        	7630516	SW  										AFT RUDDER LT	FRAYED          	B			FB2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	100AM	2400 				11361				DURING C/W TWIN COMMANDER SB 195B, FOUND BOTH AFT RUDDER CABLES TO HAVE NUMEROUS CABLE STRANDS BROKEN.  THE INSTRUCTIONS	 IN THE SB DO NOT ADDRESS THE REMOVAL OR INSPECTION AS OUTLINED IN AC 43.13-1A, CHAPTER 4, PARAGRAPH 198, FIGURE 4.14. T	HIS PROCEDURE IS THE ONLY WAY TO PROPERLY INSPECT THESE CABLES.  SUBMITTER HAS FOUND MANY AIRCRAFT WITH CABLE STRANDS BR	OKEN BEYOND THE LIMITS IN THE SB WHILE INSPECTING THE CABLES IN THIS MANNER.  SUBMITTER SUGGESTS OWNERS C/W SI-199 WHICH	 INSTALLS LARGER PULLEYS AT THIS LOCATION.		1	H	7	2 	3T			 	2A4     					 
1996050900099	19960509	00099	CE  	1996	5	9	96ZZZX2224       	1	19960319	G	2150	631430534	ACTUATOR        			CESSNA	525   	525         	2076601	CE  										PRECOOLER	FAIL TEST       	B	L		JGVR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CE	09	216CJ	551  				5250016				PRE-COOLER ACTUATORS FAILED FUNCTIONAL TEST FOLLOWING COMPLETION OF SB 525-36-02.  FOUND P/N 6314305-34 FITTING ORIFICE 	PLUGGED WITH ADHESIVE MATERIAL.  ADHESIVE PRESUMED TO HAVE BEEN BLOCKING FITTING ORIFICE SINCE ORIGINAL AIRCRAFT MANUFAC	TURE.  SUBMITTER RECOMMENDS ONE-TIME FUNCTIONAL TEST OF ALL MODEL 525 AIRCRAFT TO DETERMINE IF OTHER AIRCRAFT ARE SIMILA	RLY AFFECTED.  CLEANED ADHESIVE FROM ORIFICE SYSTEM, FUNCTIONALLY CHECKED NORMALLY.			1	L	7	2 	4F			RT	A1WI    					 
1996050900100	19960509	00100	CE  	1996	5	9	96ZZZX2225       	1	19960306	G	2824	10138901133	CHECK VALVE     			BEECH 	200   	200BEECH    	1152920	CE  										AUX XSFER PUMP	LEAKING         	H	L			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	26G	8479 				BB787				FUEL CHECK VALVE HAD SOME DIRT IN THE SEAT ALLOWING FUEL TO PRESSURIZE THE AUXILIARY FUEL CELL AND LEAK AROUND THE TOP M	ANHOLE PANEL.  FUEL TRAVELED THROUGH THE WIRING CONDUIT ALLOWING SOME FUEL AND FUMES INTO THE CABIN AREA.					1	L	7	2 	4T				A24CE   					 
1996050900101	19960509	00101	CE  	1996	5	9	96ZZZX2226       	1	19960306	G	5620	57190421	CLIP            			CESSNA	441   	441         	2076020	CE  										CABIN WINDOW	RUSTED          	B	P	A	CGFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	441ND					4410123				DURING THE REMOVAL OF THE INTERIOR AND HEADLINER IN PREPARATION FOR INSPECTION, NOTED THE SPRING STEEL CLIPS THAT RETAIN	 THE INNER WINDOWS WERE EXTENSIVELY RUSTED, SEVERAL TO A POINT OF TOTAL DESTRUCTION.  IN ADDITION, THE MAIN CABIN STRUCT	URE (TO WHICH THE CLIPS ARE RIVETED), WAS SEVERELY CORRODED.  THE SPRING CLIPS ARE A STANDARD CESSNA PART, SIX CLIPS ARE	 USED ON EACH WINDOW.  UPPER CLIPS, CESSNA, P/N 571-9042-1.  LOWER CLIPS, CESSNA, P/N 571-9042-2.			1	L	7	2 	3T			RT	A28CE   					 
1996050900102	19960509	00102	CE  	1996	5	9	96ZZZX2227       	1	19960306	G	5620	57190422	CLIP            			CESSNA	441   	441         	2076020	CE  										CABIN WINDOW	RUSTED          	B	P		CGFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	441ND	5994 				4410123				DURING THE REMOVAL OF THE INTERIOR AND HEADLINER IN PREPARATION FOR INSPECTION, NOTED THE SPRING STEEL CLIPS THAT RETAIN	 THE INNER WINDOWS WERE EXTENSIVELY RUSTED, SEVERAL TO A POINT OF TOTAL DESTRUCTION.  IN ADDITION, THE MAIN CABIN STRUCT	URE (TO WHICH THE CLIPS ARE RIVETED), WAS SEVERELY CORRODED.  THE SPRING CLIPS ARE A STANDARD CESSNA PART, SIX CLIPS ARE	 USED ON EACH WINDOW.  UPPER CLIPS, CESSNA, P/N 571-9042-1.  LOWER CLIPS, CESSNA, P/N 571-9042-2.			1	L	7	2 	3T			RT	A28CE   					 
1996050900103	19960509	00103	NE  	1996	5	9	96ZZZX2228       	2	19960403	G	7240	4059T02601	RETAINER        			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343A      	30015	NE  					NR 5 BEARING	FAILED          	E	S			A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			GL	03	826JP	2656 				5050	350353			PILOTS NOTICED ABNORMAL VIBRATION ON LT ENGINE OVER THE NORTH ATLANTIC.  UNSCHEDULED LANDING.  GE WAS CONTACTED AND ENGI	NE WAS REPLACED.  ON TEAR-DOWN, NR 5 BEARING RETAINER LOCK PIN FOUND TO HAVE BROKEN OFF ALLOWING BEARING TO SPIN IN ITS 	SEAT, SUBSEQUENTLY, DAMAGING MOST OF THE ROTATING COMPONENTS ATTACHED.  THE PTO SHAFT WAS FOUND LOOSE IN THE ENGINE, AND	 MAY HAVE BEEN A CONTRIBUTING FACTOR DUE TO VIBRATION.  THIS PTO CONDITION WAS FOUND ON THE AIRCRAFT'S OTHER ENGINE AT 3	75 TTSN.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1996050900104	19960509	00104	SW  	1996	5	9	96ZZZX2229       	1	19960401	G	3210	7300626	TRUSS SUPPORT   			GULSTM	690TP 	695A        	7630519	SW  										RT OUBOARD	DAMAGED         	B			VE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	79PH	4682 				96029				AFTER RIGHT AFT LOWER NACELLE REMOVED TO FACILITATE MAINTENANCE, DISCOVERED THAT DURING A PREVIOUS LANDING GEAR REMOVAL,	 THE LEFT AND RIGHT OUTBOARD MLG TRUSS SUPPORTS WERE ACCIDENTLY DRILLED WHEN THE OUTBOARD TRUNNION PIN COVER WAS DRILLED	 OFF.  THE LEFT TRUSS WAS REPAIRED BY BLENDING, BUT THE RIGHT TRUSS WAS FOUND TO BE DRILLED AS MUCH AS 0.299 INCH IN DEP	TH.  THE RIGHT SUPPORT WAS REPLACED WITH A NEW PART NR 730062-504.  THIS DAMAGE WOULD HAVE BEEN AVOIDED BY USING A DRILL	 STOP OR A PROTECTIVE COVER DURING DRILLING.		1	H	7	2 	4T				2A4     					 
1996050900106	19960509	00106	CE  	1996	5	9	96ZZZX2231       	1	19960417	G	3246	43667	TIE BOLT        		314901      	CESSNA	500   	560CESSNA   	2076750	CE  										MLG WHEEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	68881	143  			1804	560173				INSPECTION FOUND 2 ADJACENT WHEEL TIE BOLTS FAILED AT 4 THREADS FROM SHANK.  BOLTS 43.5 HRS OUT OF MAG PARTICLE CHECK AT	 42 CYCLES.  BOLTS TT SINCE NEW, 1,462.7 HRS.  BOLTS HAD BEEN THROUGH 7 NEW TIRE CHANGES.  PROPER LUBE USED DURING TORQU	E.  NO EVIDENCE OF OVERTORQUE.  NUTS AND WASHERS MISSING.				2	L	7	2 	4F			RT	A22CE   					 
1996050900107	19960509	00107	CE  	1996	5	9	96ZZZX2232       	1	19960402	G	2430	6608513	CONTROL UNIT    			BEECH 	60    	60          	1153602	CE  										START/GEN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	65BL	239  				60054				LEFT STARTER WOULD NOT ROTATE WHEN START WAS SELECTED.  REPLACED GENERATOR CONTROL UNIT.  SYSTEM WAS RESTORED TO NORMAL.						1	L	7	2 	3O				A12CE   					 
1996050900108	19960509	00108		1996	5	9	96ZZZX2233       	4	19960415	G	3424	9550B	INDICATOR       			BEECH 	B300  	B300        	1159232	CE  										TURN/SLIP	FAILED          	B			KI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	65CR		45   		887	FL60				THIS MODEL OF TURN AND SLIP INDICATOR HAS A HIGH FAILURE RATE.  (BOTH THE PILOT'S AND COPILOT'S USE THE SAME INDICATOR.)	  SUBMITTER STATES CHANGED 6 UNITS SINCE THE FIRST OF THE YEAR.  THE HIGH TIME UNIT HAS 45 HOURS ON IT SINCE OVERHAUL, M	OST HAD LESS.				2	L	7	2 	4T			RT	A24CE   					 
1996050900109	19960509	00109	SW  	1996	5	9	96ZZZX2234       	1	19960405	G	5610	360012501	WINDOW          			GULSTM	690TP 	690         	0141720	SW  										COPILOT SIDE	FAILED          	B			GFER	O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	09	9175N					11071				AT 13,000 FEET, 4.2 PSID CABIN DIFFERENTIAL RPESSURE AND APPROXIMATELY 250 KIAS, THE COPILOT'S SIDE WINDOW FAILED CATAST	ROPHICALLY.  APPROXIMATELY 50 PERCENT OF THE WINDOW WAS LOST CAUSING SOME SECONDARY DAMAGE TO THE PROPELLER LEADING EDGE	 AND FUSELAGE.  THE CAUSE COULD NOT BE READILY IDENTIFIED BY EXAMINATION OF THE WINDOW OR FRAME.  SUBMITTER RECOMMENDS A	 PRISM/OIL CHECK OF ALL PRESSURE WINDOWS AT NEXT 100-HOUR INSPECTION TO DETERMINE IF CRACKS HAVE DEVELOPED AT THE FASTEN	ER HOLES.		1	H	7	2 	3T				2A4     					 
1996050900110	19960509	00110	SW  	1996	5	9	96ZZZX2235       	1	19960401	G	5412		FIREWALL        			GULSTM	690TP 	695A        	7630519	SW  										LT/RT NACELE	CRACKED         	B			VE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	79PH					96029				THE LT AND RT ENGINE FIREWALLS FOUND TO HAVE CRACKS IN THE ALUMINUM PORTION OF FIREWALL AT THE AFT ENGINE MOUNT UPPER AT	TACH FASTENERS DURING OTHER MAINTENANCE REQUIRING THE LOWER AFT NACELLES TO BE REMOVED.  WITH THE NACELLES REMOVED, THE 	CRACKS ARE VISIBLE.  ACCOMPLISHED A DER REPAIR SIMILAR TO REPAIR IN SB 217 REQUIRED ON EARLIER MODEL AND S/N AIRCRAFT. S	UBMITTER SUGGESTS CAUSE AS ENGINE/PROP VIBRATION.  ACCOMPLISHED REINFORCEMENT REPAIR AT EARLIEST ACCESS.			1	H	7	2 	4T				2A4     					 
1996050900111	19960509	00111	SW  	1996	5	9	96ZZZX2236       	1	19960401	G	5743	73005834	ANGLE           			GULSTM	690TP 	695A        	7630519	SW  										RT NACELLE	CRACKED         	B			VE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	79PH	4682 				96029				DURING A 100-HOUR INSPECTION, THE RT MLG INBOARD TRUSS ATTACH ANGLE WAS FOUND TO HAVE A 0.9 INCH RADIUS CRACK 1.0 INCH F	ROM AFT END.  THIS CRACK WAS STOP DRILLED AND A DOUBLER AND RADIUS BLOCK WAS INSTALLED PER DER'S REPAIR SCHEME.  CRACKS 	APPEAR TO BE ASSOCIATED WITH AIRCRAFT HAVING MORE THAN 2,000 FLIGHT HOURS.  SUBMITTER RECOMMENDS CLOSE INSPECTION OF ALL	 4 ANGLES ON AIRCRAFT AT REGULAR INTERVALS.			1	H	7	2 	4T				2A4     					 
1996050900114	19960509	00114	SW  	1996	5	9	96ZZZX2239       	1	19960410	G	5530	41000885	CHANNEL         			GULSTM	690TP 	690A        	0141722	SW  										VERTICAL STAB	CRACKED         	B			W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	333CA	4132 				11136				DURING C/W AD 95-13-02 IAW SB 218 PART 2, VERTICAL STABILIZER CHANNEL WAS FOUND CRACKED AT THE BEND RADIUS.  A NEW PART 	WAS MADE FROM THE SAME MATERIAL AND TO THE SAME DIMENSIONS IAW 43.131A.  REASSEMBLY WAS C/W - NO PROBLEMS.  THIS CHANNEL	 WAS NOT IN THE AREA TO BE INSPECTED PER SB 218.  NOTE:  THIS WAS THE 3RD AIRCRAFT FOUND WITH THE SAME CHANNEL CRACKED. 	 SUGGEST A MUCH FURTHER INSPECTION OF VERTICAL STABILIZER WHILE C/W SB 218.			1	H	7	2 	3T				2A4     					 
1996050900115	19960509	00115	CE  	1996	5	9	96ZZZX2240       	1	19960315	G	2133	13024	CHECK VALVE     			BEECH 	200   	200BEECH    	1152920	CE  										PRESSURIZATION	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	130PA					BB330				AIRCRAFT WOULD NOT PRESSURIZE.  FOUND PRESSURIZATION CHECK VALVES MISSING.  FOUND MISSING CHECK VALVES JAMMED INSIDE OF 	PN 50-380053-1 VENTURI.  REMOVED CHECK VALVES, INSTALLED SERVICEABLE PRESSURIZATION VALVE ASSY, PN 1302-2.  SYSTEM OPS C	HECK SATISFACTORY.  SUGGEST A POSSIBLE 10-YEAR LIFE LIMIT ON THIS STYLE VALVE ASSEMBLY.				1	L	7	2 	4T				A24CE   					 
1996050900116	19960509	00116	WP  	1996	5	9	96ZZZX2241       	2	19960412	G	7200		ENGINE          			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					NR 2	FAILED          	B			YL1R	E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	11	662D	4962 	584  			200	P73550			NR 2 ENGINE HAD HIGH VIBRATION AND EGT 1 HOUR INTO THE FLIGHT.  AIRCRAFT WAS EN ROUTE AT CRUISE GOING FROM 33,000 FEET T	O 35,000 FEET.  THE PILOT MADE A MANUAL ENGINE SHUT DOWN AND LANDED.  INSPECTION OF NR 2 ENGINE UPON LANDING SHOWS METAL	 IN THE TAIL PIPE.  SUSPECT CAUSE:  HP BLADE FAILURE.  NOTE:  DOW CHEMICAL (OPERATOR).				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1996050900117	19960509	00117	NE  	1996	5	9	96ZZZX2242       	2	19960228	G	7321		EEC             	SMITHSIND   		LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       		NE  					LT ENGINE	MALFUNCTION     	C				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	09	799SC	54   			Y7545	067	PCE305250			AMBER AND WHITE COMPUTER LIGHTS CAME ON AND ITT INDICATION WAS LOST FOR THE LEFT ENGINE; OTHERWISE, OPERATION WAS NORMAL	 IN-FLIGHT.  ENGINE WOULD NOT START ON GROUND.  NO ITT INDICATION CAUSED THE FADER TO ABORT START ATTEMPTS.  REPLACED E.	E.C.  OPERATION NORMAL.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
1996050900118	19960509	00118	SO  	1996	5	9	96ZZZX2243       	1	19960328	G	4980	38460912	EXHAUST PIPE    	GARRTT      	GTCP36100G  	GULSTM	G1159 	GIV         	3980115	SO  										APU PLENUM	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1086	1802 			P467	1086				LARGE DISTORTION IN PLENUM EXHAUST PIPE, 12 O'CLOCK POSITION, DID NOT EXCEED MFG LIMIT OF .50 INCH.  APU REMOVED FOR REP	AIR AND 2,100 HOUR OVERHAUL C/W.  SUSPECT CAUSE, HOT AIR LEAK INSIDE OF PLENUM.  TEAR DOWN REVEALED CRACK IN TURBINE NOZ	ZLE.				2	L	7	2 	4F			RT	A12EA   					 
1996050900119	19960509	00119	CE  	1996	5	9	96ZZZX2244       	1	19960403	G	3020	45A6619621	DUCT            			BEECH 	MU300 	400BEECH    		CE  										LT ENG NAC	CRACKED         	B	S		ERY2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	425K	862  				RK28				WHILE C/W BEECH SB 2654 INSPECTING THE WELD AREAS OF THE ANTI-ICE DUCT ASSY ATTACH BRACKETS, CRACKS WERE FOUND AROUND TH	E WELD OF THE FLANGE AREA.  THIS AREA SHOULD ALSO BE INSPECTED AT THE TIME OF C/W THIS BULLETIN.					2	H	7	2 	4F			RT	A16SW   					 
1996050900120	19960509	00120		1996	5	9	96ZZZX2245       	4	19960410	G	3418	1N1201825	DIODE           			CESSNA	500   	550         	2076604	CE  										AOA HEATER	BURNED          	D		A		A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SW	03	777FL	7033 				5500070				AIRCRAFT RETURNED TO MAINTENANCE WHEN COCKPIT FILLED WITH SMOKE SHORTLY AFTER TAKEOFF.  AOA HEATER CIRCUIT BREAKER TRIPP	ED AND WOULD NOT RESET.  INVESTIGATION REVEALED TWO DIODES IN AOA HEAT CIRCUIT TOUCHING GROUND THROUGH RIGHT PITOT STATI	C HEAT SWITCH.  A REPLACEMENT SWITCH WAS INSTALLED AND DIODES WERE REMOVED FROM THE CIRCUIT IAW WIRING DIAGRAM NOTE AT T	HE BOTTOM OF THE DIAGRAM.  NO OTHER INFORMATION REGARDING REMOVAL OF THESE DIODES COULD BE FOUND.  SUBMITTER RECOMMENDS 	REMOVAL OF THESE DIIODES IF STILL INSTALLED ON OLDER MODEL CITATIONS.		1	L	7	2 	4F				A22CE   					 
1996050900306	19960509	00306	WP  	1996	5	9	96ZZZX2274       	1	19960401	G	6220	369H120331	LEAD/LAG LINK   		369D21200   	HUGHES	369   	369F        	4470708	WP  										M/R HUB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5205G	2387 			619	0011F				PILOT FOUND BROKEN LINK ON PRE-FLIGHT.  REMOVED BROKEN LINK AND INSTALLED NEW.  FOUND LINK SHIMS .024 INCH OVER MAXIMUM.	  REMOVED SHIMS AS REQUIRED TO OBTAIN CORRECT DIMENSION.  NO FURTHER OCCURRENCE.					1	G	7	1 	3U				H3WE    					 
1996050900307	19960509	00307	WP  	1996	5	9	96ZZZX2275       	1	19960410	G	1100		DATA PLATE      			HUGHES	369   	369D        	4470706	WP  										VERTICAL STAB	MISSING         	B		A	EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4571V					490487D				DURING ANNUAL INSPECTION, FOUND THE DATA PLATE FOR THE VERTICAL STABILIZER WAS MISSING.  THESE ARE FOIL STRIPS THAT ARE 	GLUED ON AND ARE ROUTINELY FOUND MISSING AT INSPECTION.					1	G	7	1 	3U				H3WE    					 
1996050900308	19960509	00308	EU  	1996	5	9	96ZZZX2276       	1	19960408	G	6310	109041506101	SHAFT ASSY      			AGUSTA	A109  	A109K2      	0260502	EU  										XMSN DRIVE	DAMAGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	911RX	1226 			0026U	10017				DURING THE ENGINE 100-HOUR INSPECTION, DAMAGE TO THE ENGINE TO TRANSMISSION DRIVE SHAFT WAS OBSERVED.  THE DAMAGE WAS FU	LL CIRCUMFERENCE AND WAS CAUSED BY CONTACT WITH THE FIREWALL.  THE SHAFT PASSES THROUGH TWO HALF FLANGE ASSEMBLIES.  THE	 CLEARANCE BETWEEN THE HALF FLANGE ASSEMBLIES AND THE SHAFT IS NOT SYMMETRICAL AND RANGES FROM APPROXIMATELY .25 INCH TO	 .50 INCH.			1	G	7	2 	3U			RT	H7EU    					 
1996050900309	19960509	00309	WP  	1996	5	9	96ZZZX2277       	1	19960325	G	3213	430013	SKID TUBE       			HILLER	UH12  	OH23G       	4360121	WP  										SKID SHOE	CORRODED        	B		A	PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	603RA					1527				INSPECTION FOUND 2 EACH SKID TUBES CORRODED THROUGH BETWEEN SKID SHOE AND TUBE.  SUSPECT DUE TO TRAPPED SPRAY CHEMICALS 	AND WATER FROM WASHING THE AIRCRAFT.					1	G	7	1 	3O				4H11    					 
1996050900310	19960509	00310		1996	5	9	96ZZZX2278       	4	19960322	G	3421	RCA26AK4	GYRO            	RCALLEN     		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT HORIZ	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	518SS	12   				10073				ARTIFICAL HORIZON BANKS TO LEFT IN STRAIGHT AND LEVEL FLIGHT.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900311	19960509	00311		1996	5	9	96ZZZX2279       	4	19960322	G	3421	RCA26AK4	GYRO            	RCALLEN     		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT GYRO	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	518SS	24   			95K1158	10073				GYRO WILL NOT MAINTAIN LEVEL INDICATION IN STRIAGHT AND LEVEL FLIGHT.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900312	19960509	00312		1996	5	9	96ZZZX2280       	4	19960322	G	3120		HOURMETER       	MITCH       		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	520SS	94   			1082	10075				HOURMETER ODOMETER STOPPED RECORDING TIME.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900313	19960509	00313		1996	5	9	96ZZZX2281       	4	19960322	G	3421		GYRO            	RCALLEN     		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT HORIZ	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	526SS	74   				10085				GYRO ARTIFICAL HORIZON WILL NOT STAY UPRIGHT.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900314	19960509	00314	GL  	1996	5	9	96ZZZX2282       	1	19960322	G	7931	956355	SENSOR          			DIAMON	DA20A1	DA20A1      	05626UX	GL  										ENG OIL PRESSURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	526SS	17   				10085				OIL PRESSURE SENSOR HAS OPEN RESISTANCE CONDITION INTERNALLY.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900315	19960509	00315		1996	5	9	96ZZZX2283       	4	19960322	G	3120		HOURMETER       	MITCH       		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	521SS	38   			1153	10081				HOURMETER ODOMETER QUIT RECORDING TIME.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900316	19960509	00316		1996	5	9	96ZZZX2284       	4	19960322	G	3120	D11125240	HOURMETER       	MITCH       		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	521SS	127  			1108	10081				HOURMETER ODOMETER QUIT RECORDING TIME.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900317	19960509	00317	GL  	1996	5	9	96ZZZX2285       	1	19960322	G	7931	956355	SENDER          			DIAMON	DA20A1	DA20A1      	05626UX	GL  										ENG OIL PRESS	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	521SS	47   				10081				OIL PRESSURE SENDER HAS OPEN RESISTENCE CONDITION INTERNALLY.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900318	19960509	00318	GL  	1996	5	9	96ZZZX2286       	1	19960322	G	7931	956355	SENDER          			DIAMON	DA20A1	DA20A1      	05626UX	GL  										ENG OIL PRESS	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	528SS	9    				10092				OIL PRESSURE SENDER HAS OPEN RESISTENCE CONDITION INTERALLY.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900319	19960509	00319		1996	5	9	96ZZZX2287       	4	19960322	G	3120	D11125240	HOURMETER       	MITCH       		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	528SS	8    			1154	10092				HOURMETER ODOMETER STOPPED RECORDING TIME.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900320	19960509	00320	GL  	1996	5	9	96ZZZX2288       	1	19960322	G	7931	956355	SENDER          			DIAMON	DA20A1	DA20A1      	05626UX	GL  										ENG OIL PRESS	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	528SS					10092				OIL PRESSURE SENDER HAS OPEN RESISTANCE CONDITION INTERNALLY.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900321	19960509	00321		1996	5	9	96ZZZX2289       	4	19960322	G	3421	RCA26AK4	GYRO            	RCALLEN     		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT HORIZ	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	524SS	65   			95K1223	10084				ARTIFICAL HORIZON GYRO WILL NOT TURN ON.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900322	19960509	00322		1996	5	9	96ZZZX2290       	4	19960322	G	3421	RCA26AK4	GYRO            	RCALLEN     		DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT HORIZ	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	527SS	16   			95K1201	10090				ARTIFICAL HORIZON WILL NOT SAY UPRIGHT.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900323	19960509	00323	GL  	1996	5	9	96ZZZX2291       	1	19960322	G	7713	710020	GAUGE           			DIAMON	DA20A1	DA20A1      	05626UX	GL  										ENG MANIFOLD	ERROR           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	531SS	31   			A7504	10105				ENGINE MANIFOLD PRESSURE READING INCORRECT.						1	L	7	1 	3O			NT	TA4CH   					 
1996050900324	19960509	00324	SO  	1996	5	9	96ZZZX2292       	2	19960329	G	7414	10349271	COIL            	BENDIX      	S6RN1225    	BEECH 	55    	95B55       	1152706	CE  	CONT  	O470  	IO470L      	17026	SO  					MAGNETO	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	2023Z				A224421	TC2171	465369			DURING ANNUAL INSPECTION, FOUND MAGNETO COIL CRACKED IN NUMEROUS PLACES.  AD 94-01-03 R2 REQUIRES REPLACEMENT OF THESE C	OILS, BUT THIS SERIAL NUMBER MAGENTO IS NOT COVERED BY THE AD (COIL IS AN OPAQUE AMBER COLOR AS REFERENCED IN TELEDYNE C	ONTINENTAL IGNITION SYSTEMS SB MSB644).  THERE ARE NO MAINTENANCE RECORD ENTRIES OF THESE COILS HAVING BEEN PREVIOUSLY R	EPLACED.			1	L	7	2 	3O	3	O		3A16    	3E1				 
1996050900325	19960509	00325	SO  	1996	5	9	96ZZZX2293       	2	19960411	G	7414	104001664	IMPULSE CAM     		S6RN25      	CESSNA	182   	182B        	2072706	CE  	CONT  	O470  	O470L       	17026	SO  					LT MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	7244E	596  			K149104DR	52244	069744R			UPON INSPECTION OF CAMS IN IMPULSE COUPLINGS FOR WEAR PER AD 78-09-07, FOUND ONE FLYWEIGHT AND RIVET WORN WELL BEYOND LI	MITS.  THIS IS NEW STYLE CAM WITH SNAP RING ASSEMBLY.  FOR A TOTAL TIME OF ONLY 595 HOURS, FEEL THIS TO BE SIGNIFICANT W	EAR AND WOULD ALSO QUESTION THE HARDNESS OF METAL.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996050900326	19960509	00326	EA  	1996	5	9	96ZZZX2294       	2	19960317	G	8530		VALVE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					NR 1 CYL INTAKE	HEAD SEPARATED  	D				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	15	8347C	1734 				287690121	L2101336A			ENGINE ROUGHNESS DURING FLIGHT FOUND BENT PUSHROD HOUSING AND PUSHROD.  REMOVED CYLINDER AND FOUND VALVE HEAD SEPARATED 	FORM STEM INTAKE SIDE.					1	L	7	1 	3O	3	O		2A13    	E286				 
1996050900327	19960509	00327	CE  	1996	5	9	96ZZZX2295       	1	19960401	G	3411		STATIC PORT     			CESSNA	210   	2105        	2073404	CE  										STATIC SYSTEM	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5875					2050014				THE SEALANT BETWEEN STATIC PORT AND SKIN OF AIRCRAFT HAD TURNED TO POWDER MAKING A LEAK IN THE STATIC SYTSEM.  DRILLED R	IVETS OUT OF STATIC PORT, SEALED WITH PR-1422 SEALANT.  STARTED STATIC CHECK AGAIN, GOT UP TO 11,000 FEET AND A SEVERE L	EAK STARTED AGAIN.  FOUND LEAK AT SAME LOCATION ON OTHER STATIC PORT.  WITH THIS STYLE STATIC PORT WHICH PROTRUDES FROM 	SKIN ABOUT .25 INCH, IT COULD POSSIBLY BUILD PRESSURE IN STATIC LINE AND GIVE FALSE READING.			1	H	7	1 	3O				3A21    					 
1996050900328	19960509	00328	EA  	1996	5	9	96ZZZX2296       	2	19960404	G	7414		BEARING         		S6LN2230    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAG DIST BLK	LOOSE           	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	27343		17   		5062990R	317752163	RL727061A			ROTORSHAFT CAM-END BEARING FIT TOO LOOSE.  SHAFT AND CAM MOVE LATERALLY GIVING VARYING POINT GAP AND TIMING.  TIMING FOU	ND OUT-OF-TOLERANCE DURING CHECK OF TCM SB 643(1). THIS MAGNETO FURNISHED ON LYCOMING FACTORY REMANUFACTURED ENGINE.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996050900329	19960509	00329	SO  	1996	5	9	96ZZZX2297       	1	19960210	G	7120	J961355	MOUNT           			PIPER 	PA46  	PA46310P    	7104605	SO  										ENGINE RT AFT	DAMAGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	9220T					468608016				WHILE C/W PIPER SB NR 960, RIGHT REAR ENGINE MOUNT RUBBER ISOLATOR WAS FOUND BADLY DETERIORATED.  THE MOUNT IS IN CLOSE 	PROXIMITY TO THE EXHAUST SYSTEM AND EXCESSIVE HEAT IS SUSPECTED AS THE CAUSE.  THE PARTS MANUAL CALLS OUT A HEAT SHIELD 	FOR THE LEFT REAR MOUNT, BUT NONE FOR THE RIGHT.  A CALL TO PIPER CONFIRMED THERE IS NO HEAT SHIELD FOR THE RIGHT REAR M	OUNT.  SOME TYPE OF HEAT SHIELD SHOULD BE INSTALLED TO PREVENT THIS TYPE OF DETERIORATION.			1	L	7	1 	3O				A25SO   					 
1996050900330	19960509	00330	SW  	1996	5	9	96ZZZX2298       	1	19960417	G	2730	M3414	ROD END BEARING 		915007005   	MOONEY	M20   	M20E        	5870212	SW  										ELEV CONTRL TUBE	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	5638Q	2329 				675				WHILE PERFORMING A FLIGHT CONTROL OPERATIONAL INSPECTION DURING AN ANNUAL, RESTRICTED MOVEMENT OF ELEVATOR CONTROL WAS N	OTED.  AFTER MOVING THE ELEVATOR CONTROL THROUGH ITS FULL RANGE OF MOTION 4 TO 5 CYCLES, MOVEMENT BECAME UNRESTRICTED. I	T WAS DISCOVERED THE THREADED ROD END BEARING BECAME DETACHED FROM THE ELEVATOR CONTROL TUBE LOCATED AFT OF THE ADJUSTAB	LE TAIL SECTION JOINT.  THE FRACTURE OCCURRED IN THREADED SECTION OF THE BEARING APPROXIMATELY 6 THREADS FROM THE END WI	THIN THE JAM NUT.  THE BEARING WAS FROZEN DUE TO CORROSION AND LACK OF LUBRICATION.  SUBMITTER STATED TO PREVENT RECURRE	NCE OF THIS DEFECT, RECOMMEND THE APPROVED SILICON SPRAY LUBRICANT BE APPLIED TO ALL ROD END BEARINGS.	1	L	7	1 	3O				2A3     					 
1996050900331	19960509	00331	CE  	1996	5	9	96ZZZX2299       	1	19960404	G	5720	12200509	V-CHANNEL       			CESSNA	206   	U206        	2073306	CE  										LT OB AIL HINGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	569QL	10655				U2060608				V-CHANNEL CRACKED WHERE AILERON HINGE RIVETED TO IT.  DIFFICULT TO SEE CRACK.  SUSPECT DEFECTIVE IF MOVEMENT NOTICED WHE	N PRESSURE APPLIED UPWARD TO FLAT OF AILERON LOWER SURFACE.					1	H	7	1 	3O				A4CE    					 
1996050900332	19960509	00332	NE  	1996	5	9	96ZZZX2300       	2	19960304	G	7210	7757571	BEARING         		5074T6LG10  	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GEARCASE	CRACKED         	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	202KD	1073 			9376	340B202				GEAR CASE WAS RETURNED FOR OIL CONTAMINATION.  UNIT WAS DISASSEMBLED AND AN EXAMINATION OF INTERNAL HARDWARE REVEALED A 	CRACKED INNER RACE ON THE PROPELLER SHAFT FORWARD ROLLER BEARING RACE.  LEFT - TSI 4,239.5 HRS.  CSI, 4,048.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1996050900333	19960509	00333	SW  	1996	5	9	96ZZZX2301       	1	19960328	G	6320	476206283	BEARING         		4762060029  	BELL  	47    	47G5A       	1181034	SW  										TRANSMISSION	MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	615BH	303  			MB17046	25126				UPON FINDING METAL IN OIL SCREEN, TRANSMISSION WAS REMOVED AND DISASSEMBLED.  LOWER SUN GEAR BEARING WAS FOUND TO BE MAK	ING METAL.  SUBMITTER STATES THIS HAS BEEN THE SIXTH FAILURE IN TRANSMISSION.					1	G	7	1 	3O				2H3     					 
1996050900334	19960509	00334	EU  	1996	5	9	96ZZZX2302       	1	19960422	G	5520		ELEVATOR        			DORNER	DO228 	DO228201    	2992020	EU  										ELEV TOP LT	FABRIC MISSING  	D		A		O				OTHER                   				D	F	E	INFLIGHT SEPARATION       	FLT CONT AFFECTED         	VIBRATION/BUFFET          	CR	CRUISE         	1			SW	05	279MC		2486 			8120				THE PILOT REPORTED AT APPROXIMATELY 100 MILES FROM BNA, EN ROUTE FROM CVG, THAT HE EXPERIENCED A HARD NOSE DOWN ELEVATOR	 CONDITION AND SOME AIRFRAME VIBRATION.  THE PILOT ADJUSTED ELEVATOR TRIM TO HELP THE NOSE DOWN CONDITION AND TRIED TO I	SOLATE THE VIBRATION WITH ENGINE POWER CHANGES WITH NO SUCCESS.  HE CONTINUED TO BNA AT MINIMUM CRUISE SPEED.  A BNA PIL	OT C/W A VISUAL CHECK OF THE AIRCRAFT AND FOUND APPROXIMATELY 3 FEET OF THE UPPER LEFT ELEVATOR FABRIC MISSING.  ELEVATO	R, S/N 5577, HAD BEEN RECOVERED 2,485.9 HRS AGO ON 5-9-91, WITH COOPER SUPERFLITE 102 FABRIC IAW WITH STC SA 1326GL.  AI	RCRAFT HAD ALSO BEEN PRESSURE DEICED BEFORE DEPARTING FROM CVG.	2	H	7	2 	4T			RT	A16EU   					 
1996050900335	19960509	00335	WP  	1996	5	9	96ZZZX2303       	2	19960329	G	7250	3587502	BEARING         			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					TURBINE NR 6	SPALLED         	B			IY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	190GC		195  			35014	P74124C			195 HOURS AFTER INSTALLING OVERHAULED NR 6 TURBINE BEARING, BEARING WAS REMOVED FORM SERVICE DUE TO SPALLED ROLLERS.  TH	IS PROBLEM WAS DISCOVERED DURING A ROUTINE 150-HOUR OIL FILTER ANALYSIS.  THE ANALYSIS REVEALED M50 TOOL STEEL PLATELETS	, WHICH IS MAIN BEARING MATERIAL.  THE REMOVED BEARING WAS RETURNED TO THE OVERHAUL FACILITY.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1996051600041	19960516	00041	SW  	1996	5	16	96ZZZX2340       	1	19960206	G	6310	406040532101	BEARING         			BELL  	206   	206L4       	1182110	SW  										FREEWHEEL	GROOVED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	171AL	2954 			MB490	52064				AT 3,000-HOUR OVERHAUL, BEARING ROLLER FOUND TO HAVE DEEP GROOVE ON ONE ROLLER, SCRAPPED BEARING.						1	G	7	1 	3U			NC	H2SW    					 
1996051600042	19960516	00042	SW  	1996	5	16	96ZZZX2341       	1	19960110	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	283  				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 283.4 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1996051600043	19960516	00043	SW  	1996	5	16	96ZZZX2342       	1	19960110	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	283  				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 283.4 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1996051600044	19960516	00044	SW  	1996	5	16	96ZZZX2343       	1	19960129	G	6230	206010335001	LEVER ASSY      			BELL  	206   	206L4       	1182110	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	175AL	382  				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 382.3 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1996051600045	19960516	00045	SW  	1996	5	16	96ZZZX2344       	1	19960129	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	382  				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 382.3 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1996051600046	19960516	00046	SW  	1996	5	16	96ZZZX2345       	1	19960129	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	375  				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 374.7 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600047	19960516	00047	SW  	1996	5	16	96ZZZX2346       	1	19960129	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	375  				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 374.7 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600048	19960516	00048	SW  	1996	5	16	96ZZZX2347       	1	19960110	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	3179S	551  				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 NAS6605D64 BOLTS, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 551.2 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600049	19960516	00049	SW  	1996	5	16	96ZZZX2348       	1	19960110	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	551  				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 NAS6605D64 BOLTS, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 551.2 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600050	19960516	00050	SW  	1996	5	16	96ZZZX2349       	1	19960129	G	6230	206010335001	LEVER ASSY      		206010335001	BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3184P	412  				45774				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 412.1 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600051	19960516	00051	SW  	1996	5	16	96ZZZX2350       	1	19960129	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	3184P	412  				45774				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 412.1 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600052	19960516	00052	SW  	1996	5	16	96ZZZX2351       	1	19960129	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	350AL	415  				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 415.4 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600053	19960516	00053	SW  	1996	5	16	96ZZZX2352       	1	19960129	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	350AL	415  				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 415.4 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600054	19960516	00054	SW  	1996	5	16	96ZZZX2353       	1	19960110	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	363AL	437  				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 NAS6605D64 BOLTS, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 436.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600055	19960516	00055	SW  	1996	5	16	96ZZZX2354       	1	19960110	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	437  				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 NAS6605D64 BOLTS, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 436.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600056	19960516	00056	SW  	1996	5	16	96ZZZX2355       	1	19960110	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	365AL	437  				51376				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 436.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600057	19960516	00057	SW  	1996	5	16	96ZZZX2356       	1	19960110	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	365AL	437  				51376				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, AND 1 EACH 206-010-47	0-101 BEARING.  SUSPECT NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 436.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600058	19960516	00058	GL  	1996	5	16	96ZZZX2357       	2	19960207	G	7210	23030994	SCAVENGE TUBE   		23035178    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					GEARBOX	BRACKET BROKEN  	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	366AL	4181 				51470	CAE895428			UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY, AND SCAVENGE TUBE.  FOUND ALIGNMENT BRACKET ON SCAVENGE TUBE BROKEN.	  ALIGNMENT BRACKET AT LOWER END OF SCAVENGE TUBE WAS FOUND BROKEN AT WELD AREA.  SUSPECT CAUSE IS DUE TO IMPROPER FIT O	N ALIGNMENT BRACKETS.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1996051600059	19960516	00059	GL  	1996	5	16	96ZZZX2358       	2	19960202	G	7250	6851531	4TH STAGE NOZZLE		6898735     	AEROSP	AS355 	AS355F      	8680806	EU  	ALLSN 	250C  	250C20F     	03013	GL  					PT SECTION	DEFECTIVE       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	378E		1303 		WX46323	5214	CAE840026			UPON 1,750-HOUR INSPECTION, FOUND DIAPHRAGM CRACKED AND THE PART WAS SENT FOR OVERHAUL.						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1996051600060	19960516	00060	EU  	1996	5	16	96ZZZX2359       	1	19960118	G	6520	4619210902	BEVEL GEAR SET  			BOLKMS	105   	BO105S      	5626006	EU  										GEARBOX ASSY	MAKING METAL    	B			ALGR	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SW	03	4572V	4143 			1213	S665				ON LANDING AT DESTINATION, THROTTLE AT FLIGHT IDLE.  INTERMEDIATE TAIL ROTOR DRIVE GEARBOX CHIP DETECTOR LIGHT ILLUMINAT	ED.  FOUND LARGE CHIP MISSING FROM BEVEL GEAR.					1	G	7	2 	3U				H3EU    					 
1996051600061	19960516	00061	SW  	1996	5	16	96ZZZX2360       	1	19960122	G	6310	206040272101	BOOT            		206040015015	BELL  	206   	206L1       	1182107	SW  										DRIVESHAFT	LEAKING         	B			ALGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	57334	336  	36   			45445				SCHEDULED INSPECTION, FOUND THE BOOT WAS LEAKING AND SEAL WAS TORN.						1	G	7	1 	3U				H2SW    					 
1996051600063	19960516	00063	GL  	1996	5	16	96ZZZX2362       	2	19960207	G	7261	23039793	SCAVENGE BODY   		23035179    	SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GEARBOX	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	769AL	2570 				760048	CAE890253S			UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY.  VISUALLY INSPECTED, SHOWED WEAR AT SCAVENGE BODY AND SCAVENGE TUBE 	MATING SURFACE.  SCAVENGE TUBE WORE INTO SCAVENGE BODY.  SUSPECT CAUSE IS DUE TO IMPROPER FIT ON ALIGNMENT BRACKETS.					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996051600064	19960516	00064	EU  	1996	5	16	96ZZZX2363       	1	19960206	G	5311	10520501077	FRAME NR 9      		10520001    	BOLKMS	105   	BO105C      	5626005	EU  										SIDE PANEL RT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	90761	14557				S160				DURING 1200-HOUR INSPECTION, FOUND RT FRAME NR 9 CRACKED.  THE NR 9 FRAME IS STRUCTURAL SUPPORT FOR THE TRANSMISSION MOU	NT.					1	G	7	2 	3U				H3EU    					 
1996052100002	19960521	00002	EA  	1996	5	21	96ZZZX2365       	2	19960415	G	7322	1044011	CARBURETOR      		MA6AA       	HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					ENGINE	FLOAT STICKS    	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	14634		175  		AC31707	1782				INSPECTION FOUND CARBURETOR FLOAT WAS RUBBING ON LOWER HOUSING AND STICKING OPEN.						1	G	7	1 	3O	3	O		4H11    	E304				 
1996052100003	19960521	00003	EA  	1996	5	21	96ZZZX2366       	2	19960415	G	7322	MA6AA	CARBURETOR      			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					ENGINE	FLOAT STICKS    	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	14634		175  		AC31784	1782				INSPECTION FOUND CARBURETOR FLOAT WAS RUBBING ON LOWER HOUSING AND STICKING OPEN.						1	G	7	1 	3O	3	O		4H11    	E304				 
1996052100004	19960521	00004	GL  	1996	5	21	96ZZZX2367       	2	19960319	G	7260	6859435	BEARING         			AGUSTA	A109  	A109A2      	0260120	EU  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	FAILED          	B			KUVR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	19	8WH	266  				7256	CAE832739			CHIP LIGHT ILLUMINATED IN-FLIGHT.  SHORTLY THEREAFTER, ENGINE FAILED.  MAINTENANCE FOUND THE BEARINGS ON EITHER END OF T	HE FUEL CONTROL AND OIL PUMP SPUR GEARSHAFT FELL APART STOPPING FUEL CONTROL OPERATION.  EXACT CAUSE UNKNOWN AT THIS TIM	E.  UNUSUAL BECAUSE SHAFT IS SUPPORTED ON BOTH ENDS.  SUSPECT ONE BEARING FAILED ALLOWING SHAFT TO WOBBLE AND DESTROY SE	COND BEARING.			1	G	7	2 	3U	3	U		H7EU    	E4CE				 
1996052100006	19960521	00006	WP  	1996	5	21	96ZZZX2369       	1	19960411	G	5753	ARC23121	FITTING         			DOUG  	DC10  	DC10*       		WP  										IB FLAP VANE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07										HANGAR MOUNT FITTINGS THAT ARE RIVETED TO TWO RIBS AND THEN THE RIB AND FITTING ASSYS ARE BONDED TO THE CORE AND SKIN. T	HIS IS WHAT ATTACHES THE VANE TO THE FLAP.  UPON COMPLETION OF DISASSEMBLING THE VANE, THE FITTINGS WERE FOUND TO HAVE E	XCESSIVE DISSIMILAR METAL CORROSION IN THE AREA UNDER THE BOLT HEADS.  EXCESSIVE CORROSION WAS ALSO FOUND ON THE 3 EACH 	FITTINGS THROUGH AND AROUND THE HI-LOK ATTACHMENT HOLES THAT ATTACHES THE FITTINGS TO THE RIBS.			2	L	7	3 	4F				A22WE   					 
1996052100007	19960521	00007	WP  	1996	5	21	96ZZZX2370       	1	19960411	G	5753	ARC27151	FITTING         			DOUG  	DC10  	DC10*       		WP  										IB FLAP VANE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07										HANGAR MOUNT FITTINGS THAT ARE RIVETED TO TWO RIBS AND THEN THE RIB AND FITTING ASSYS ARE BONDED TO THE CORE AND SKIN. T	HIS IS WHAT ATTACHES THE VANE TO THE FLAP.  UPON COMPLETION OF DISASSEMBLING THE VANE, THE FITTINGS WERE FOUND TO HAVE E	XCESSIVE DISSIMILAR METAL CORROSION IN THE AREA UNDER THE BOLT HEADS.  EXCESSIVE CORROSION WAS ALSO FOUND ON THE 3 EACH 	FITTINGS THROUGH AND AROUND THE HI-LOK ATTACHMENT HOLES THAT ATTACHES THE FITTINGS TO THE RIBS.			2	L	7	3 	4F				A22WE   					 
1996052100008	19960521	00008	EA  	1996	5	21	96ZZZX2371       	2	19960415	G	8530		CYLINDER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					NR 3	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	39609	2800 	400  			287890542	L2519936A			NR 3 CYLINDER BARREL BROKEN.  BARREL FAILED 75 PERCENT OF RADIUS ABOUT 2 INCHES DOWN FROM TOP OF CYLINDER BARREL.						1	L	7	1 	3O	3	O		2A13    	E286				 
1996052100010	19960521	00010	SO  	1996	5	21	96ZZZX2373       	1	19960410	G	5700		LIFT STRUT      			PIPER 	PA12  	PA12        	7101202	SO  										LT REAR	DEFECTIVE       	B			CO4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2526M					121017				PARAGRAPH 'A' OF AD NOTE 93-10-06 HAS BEEN ACCOMPLISHED USING AN FAA APPROVED X-RAY METHOD.  REMARKS:  LT FRONT STRUT AI	RWORTHY, LT REAR STRUT UNAIRWORTHY, RT FRONT STRUT AIRWORTHY, RT REAR STRUT AIRWORTHY.  X-RAYS ARE ON FILE AT THIS REPAI	R STATION.				1	H	7	1 	3O				A780    					 
1996052100011	19960521	00011	SW  	1996	5	21	96ZZZX2374       	1	19960412	G	8011	MZ4218R	STARTER         			MOONEY	M20   	M20J        	5870219	SW  										FRAME	SCREWS FAILED   	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	57413		40   		5054342	241450				STARTER FRAME TO GEAR HOUSING SCREWS SHEARED ALLOWING REAR OF STARTER TO DROP JAMMING MIXTURE CONTROL AT SERVO.						1	L	7	1 	3O				2A3     					 
1996052100012	19960521	00012	WP  	1996	5	21	96ZZZX2375       	1	19960417	G	3233	3775836501	GLAND ASSY      		57740355507 	DOUG  	DC8   	DC8*        		WP  										MLG ACT CYL	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										MAIN LANDING GEAR ACTUATING CYLINDER GLAND RECEIVED CRACKED IN HALF COMPLETELY.  PART HAS EVIDENCE OF PREVIOUS CHROME RE	WORK ON OUTSIDE DIAMETER OF SEAL AREA.					2	L	7	4 	4J			F	4A25    					 
1996052100013	19960521	00013	SO  	1996	5	21	96ZZZX2376       	2	19960311	G	7414	10357586	DISTRIBUTOR GEAR	BENDIX      	S6RN205     	CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470VO     	17026	SO  					ENG RT MAG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	7742Q		1300 		628473	310Q0242				ENGINE WOULD NOT RUN WHEN RIGHT MAGNETO SELECTED.  INSPECTION REVEALED TEETH ON DISTRIBUTOR GEAR (PLASTIC) HAD SHEARED O	FF.  GEAR DID APPEAR TO BE YELLOWED FROM AGE AS IF IT HAD NOT BEEN REPLACED AT LAST OVERHAUL.					1	L	7	2 	3O	3	O		3A10    	3E1				 
1996052100014	19960521	00014	SW  	1996	5	21	96ZZZX2377       	1	19960403	G	3213	AN522A	AXLE BOLT       			BBAVIA	8     	8GCBC       	1220803	SW  										MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	09	86928					3274				UPON LANDING, THE AXLE BOLT NUTS STRIPPED OFF OF THE BOLTS CAUSING THE AXLE AND WHEEL TO DEPART THE AIRCRAFT.  THIS CAUS	ED THE GEAR TO DIG INTO THE GROUND AND FLIP THE AIRCRAFT ON ITS BACK.					1	H	7	1 	3O				A21CE   					 
1996052100015	19960521	00015	CE  	1996	5	21	96ZZZX2378       	1	19960426	G	7160	2652000817	SEPARATOR       			CESSNA	208   	208B        	2073701	CE  										ENGINE INLET	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	950FE	7000 				208B0056				SUBMITTER MAINTAINS 12 CESSNA 208B AIRCRAFT AND ARE FINDING CRACKS IN SEVERAL INERTIAL SEPARATORS.  SINCE THIS AIRCRAFT 	IS NIGHT IFR 135 SINGLE ENGINE, CRACKS IN THE ENGINE INLET ARE OF GREAT CONCERN.  SUBMITTER HAS SEEN ONE OF THESE INTAKE	S WITH A SCAB PATCH INSIDE WHICH IS UNACCEPTABLE.  SUBMITTER BELIEVES THE CRACKS ARE DUE TO VIBRATION OR THE DESIGN OR A	 COMBINATION.  THE ONLY FIX AT THIS TIME IS TO BUY A NEW PART.			1	H	7	1 	3T				A37CE   					 
1996052100016	19960521	00016	SO  	1996	5	21	96ZZZX2379       	2	19960409	G	8530	649543	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					NR 1	CRACKED         	D				K				NONE                    				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	IN	INSP/MAINT     	1			SO	13	9432U	1274 				15078380	254712A48			EXAMINATION TO DETERMINE CAUSE OF ENGINE FAILURE DISCLOSED NR 1 CYLINDER HAD CRACKED APPROXIMATELY THREE-FOURTHS OF THE 	BARREL CIRCUMFERENCE CAUSING LOSS OF OIL QUANTITY AND PRESSURE.					1	H	7	1 	3O	3	O		3A19    	E252				 
1996052100017	19960521	00017	GL  	1996	5	21	96ZZZX2380       	3	19960321	G	6111	V84334R	BLADE           			BEECH 	35    	V35         	1151538	CE  						HARTZL	HCA3V	PHCA3VF4    	GL  	SHANK	CRACKED         	B		A	WN1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	999ER		1092 		A79341	D8304		BR408		BLADE DYE CHECKED IAW AD 68-13-02.  NO CRACKS INDICATED.  CHECKED OK.  FOUND ONE INCH LONG CRACK IN BLADE, USING EDDY CU	RRENT, APPROXIMATELY .040 INCH DEEP.  SUBMITTER SUGGESTED MAKING EDDY CURRENT INSPECTION MANDATORY.					1	L	7	1 	3O				3A15    		5	C	P6EA	 
1996052100018	19960521	00018	GL  	1996	5	21	96ZZZX2381       	3	19960325	G	6111	V843311	BLADE           			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	SHANK	CRACKED         	B		A	WN1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	5071Y		300  		A36438	272085		H1276		BLADE CRACK FOUND DURING OVERHAUL WITH EDDY CURRENT.  PART OF CRACK SHOWS UP DURING DYE CHECK.  CRACK IS APPROXIMATELY 6	 INCHES LONG.  SUBMITTER SUGGESTED REVISING AD 68-19-04 AND AD 68-13-02 TO MAKE EDDY CURRENT MANDATORY.  THIRD CRACKED B	LADE FOUND IN 10 DAYS.				1	L	7	2 	3O				1A10    		5	C	P24EA	 
1996052100019	19960521	00019	SO  	1996	5	21	96ZZZX2382       	1	19960222	G	2720	6342004	RUDDER BAR      			PIPER 	PA32  	PA32300     	7103212	SO  										PILOT LT	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	4182R	4011 				3240513				DURING ANNUAL INSPECTION, THE RUDDER PEDAL FELT SPONGY ON PILOT'S LEFT SIDE.  A CLOSER INSPECTION REVEALED A 1.500 INCH 	CRACK AT THE POINT WHERE THE CROSS-TUBE WELDS TO THE TORQUE TUBE.  AGE AND FATIGUE ARE MAJOR FACTORS FOR TUBE CRACKING.					1	L	7	1 	3O				A3SO    					 
1996052100020	19960521	00020	SO  	1996	5	21	96ZZZX2383       	1	19960325	G	5510		BALANCE WEIGHT  			PIPER 	PA28  	PA28140     	7102802	SO  										HORIZ STAB	BOLTS WORN      	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4475N	3863 				2825599				THROUGH-BOLT HOLDING ELEVATOR BALANCE WEIGHT TO TUBE FOUND TO BE BADLY WORN FROM LOOSE FIT TO TUBE.  AD 70-26-04 DOES NO	T CALL FOR BOLT INSPECTION.					1	L	7	1 	3O				2A13    					 
1996052100021	19960521	00021	SO  	1996	5	21	96ZZZX2384       	1	19960318	G	3411	1J46	FILTER          			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  					PITOT STATIC	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	27934					317912042	L161968A			SUBJECT FILTER REMOVED FROM AIRCRAFT AFTER 6 MONTHS AND 200 HOURS.  FAILURE OF FILTER RESULTED IN FAILURE OF PILOT'S KFC	 200 ATTITUDE INDICATOR, COPILOT'S ATTITUDE INDICATOR, AND DIRECTIONAL GYRO.  THE CAUSE OF THE PROBLEM WAS A DETERIORATI	NG PRESSURE PUMP 442CW-6.  HOWEVER, NO FAILURE WAS NOTED IN THE COCKPIT UNTIL GYROS STARTED FAILING.   PUMP WAS STILL PU	TTING OUT SYSTEM PRESSURE.  SUBMITTER RECOMMENDS FILTER BE INSPECTED TO DETERMINE CAUSE OF FAILURE AND CORRECTIONS BE MA	DE ACCORDINGLY.		1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996052100022	19960521	00022	SW  	1996	5	21	96ZZZX2385       	1	19960328	G	5711	5147	SPAR            			BBAVIA	7     	7AC         	2110102	SW  										LT/RT WING SPAR	DAMAGED         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	83032	3721 				7AC1688				DISMANTLED LEFT AND RIGHT WING FOR THE PURPOSE OF RECOVERING.  WITH THE OLD FABRIC REMOVED, FOUND BOTH REAR SPARS HAD BE	EN CHEWED BY MICE MIDWAY BETWEEN THE WING ROOT AND THE STRUT ATTACH FITTING.  IT APPEARS THIS DAMAGE WAS PRESENT WHEN TH	E WINGS WERE LAST RECOVERED IN 1982 BECAUSE THE CHEW MARKS WERE VARNISHED OVER.  THE MAXIMUM DAMAGE THAT CAN EXIST BETWE	EN THE SPAR ROOT AND STRUT ATTACH POINT IS .0937 INCH IN DEPTH.  ALSO, NO SPAR SPLICING IS ALLOWED IN THIS AREA.			1	H	7	1 	3O				A759    					 
1996052100023	19960521	00023	SW  	1996	5	21	96ZZZX2386       	1	19960328	G	5711	5146	SPAR            			BBAVIA	7     	7AC         	2110102	SW  										WING LT FRONT	CRACKED         	G	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	83032	3721 				7AC1688				DISMANTLED BOTH LEFT AND RIGHT WINGS FOR RECOVERING.  ALL SPARS WERE REMOVED FOR CLEANING, INSPECTION, AND VARNISHING. W	ITH THE WING SPAR FITTINGS REMOVED, FOUND THE SPAR FITTING HOLES HAD CRACKS EMANATING FROM THE TWO INBOARD HOLES THROUGH	 THE BUTT OF THE SPAR.  ALL FOUR SPARS WERE REPLACED WITH NEW.  SUBMITTER RECOMMENDS CLOSE INSPECTION OF ALL ATTACHMENT 	AREAS OF THE SPARS AT EACH TIME THE WINGS ARE RECOVERED OR REBUILT DUE TO WING IMPACT OR ROLL-OVER.			1	H	7	1 	3O				A759    					 
1996052100024	19960521	00024	SW  	1996	5	21	96ZZZX2387       	1	19960328	G	5711	2701	FITTING         			BBAVIA	7     	7AC         	2110102	SW  										LT FRONT SPAR	CRACKED         	F	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	83032	3721 				7AC1688				DISMANTLED LEFT WING FOR THE PURPOSE OF RECOVERING.  AS A PRECAUTION, THE WING SPAR ATTACHMENT FITTINGS WERE MAGNAFLUXED	.  THE LEFT FRONT WING SPAR ATTACHMENT FITTING WAS FOUND TO HAVE SEVERAL IMPERFECTIONS IN THE WELDED AREA OF BOTH THE TO	P AND BOTTOM GUSSETS.  THE FITTING WAS REPLACED WITH A NEW PART.  IT APPEARS SOME OF THE IMPERFECTIONS ARE FROM PITTING 	(CORROSION) AND SOME ARE VERY SMALL CRACKS.  RECOMMEND NDT AT EACH TIME OF RECOVERING OR REBUILDING AFTER WING IMPACT OF	 ROLL-OVER DAMAGE.		1	H	7	1 	3O				A759    					 
1996051600256	19960516	00256	GL  	1996	5	16	96ZZZX2388       	3	19960223	G	6114	C4239C66	HUB             			CESSNA	182   	182K        	2072724	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	3182Q	896  				18258182		805135		PROPELLER WAS SENT IN FOR OVERHAUL DUE TO CALENDAR TIME.  HUB WAS FOUND CRACKED FROM MOUNTING STUD HOLE.  NEW HUB WAS RE	INSTALLED.					1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1996051600257	19960516	00257	SO  	1996	5	16	96ZZZX2389       	2	19960319	G	8550		ENGINE          								CONT  	O470  	O470R       	17026	SO  					OIL SYSTEM	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	03							987908RR			ENGINE 235.3 SMOH, 7.6 HRS AFTER NR 4 CYLINDER REMOVED FOR REPAIR.  PHILLIPS XC OIL BEING USED.  AV BLEND PUT IN ENGINE 	AFTER CYLINDER WAS REPAIRED.  IN-FLIGHT, OIL PRESSURE STARTED TO DECREASE.  LANDING MADE OK.  AT IDLE, OIL PRESSURE DROP	PED TO  ZERO PSI, TOTAL FLIGHT TIME, 7 MINUTES.  OIL DRAINED, FOUND SLUDGE OF UNKNOWN SUBSTANCE, ABOUT 1-2 TABLESPOONS O	F MATERIAL, BROWNISH COLOR, DRAINED OUT WITH OIL.  OIL SCREEN WAS VERY CLEAN.  NONE OF THIS MATERIAL IN SCREEN.								3	O			E273				 
1996051600258	19960516	00258	EA  	1996	5	16	96ZZZX2390       	2	19960321	G	8530	SL14995	RETAINER        								LYC   	O320  	O320E2D     	41508	EA  					CYL PUSH ROD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17										AFTER INSTALLATION AND PROPER TORQUE, THE SPRING RETAINER CRACKED INTO 2 PIECES THROUGH THE STUD HOLE.											3	O			E274				 
1996051600259	19960516	00259	GL  	1996	5	16	96ZZZX2391       	2	19960220	G	7261		ENGINE          			CESSNA	206   	U206G       	2073356	CE  	ALLSN 	250C  	250C20      	03013	GL  					OIL SYSTEM	CHIP LIGHT      	B			LX5R	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	19	891LL	829  				U206G06937	CAE290031			RECEIVED OIL CHIP LIGHT INDICATION.  PERFORMED REQUIRED MAINTENANCE PER ALLISON 250-C20S AND SOLOY/CESSNA MAINTENANCE AN	D OVERHAUL MANUALS.  RECEIVED SECOND CHIP LIGHT INDICATION 3.9 HRS TIS LATER.  ENGINE REMOVED AND SENT OUT FOR INSPECTIO	N/REPAIR PER ALLISON 250-C20S MAINTENANCE AND OVERHAUL MANUALS.				1	H	7	1 	3O	3	U		A4CE    	E4CE				 
1996051600260	19960516	00260	CE  	1996	5	16	96ZZZX2392       	1	19960308	G	5312	07126161	BULKHEAD        			CESSNA	182   	182M        	2072728	CE  										LT CUTOUT FS 230	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	70802	3327 				18259369				DURING ANNUAL INSPECTION, FOUND AFT BULKHEAD AT FS 230.18 CRACKED AT LEFT RUDDER CABLE CUT OUT.  THIS BULKHEAD HAD PREVI	OUSLY CRACKED AT THE RIGHT RUDDER CABLE CUT OUT AND WAS REPAIRED.  AD 72-07-09 AND CESSNA SB SE72-3 BOTH PERTAIN TO THIS	 AREA AND DO NOT ALLOW ANY REPAIRS TO THE BULKHEAD.  REPLACED BULKHEAD WITH FACTORY NEW PART.  AIRCRAFT RETURNED TO SERV	ICE.			1	H	7	1 	3O			NT	3A13    					 
1996051600262	19960516	00262	EA  	1996	5	16	96ZZZX2394       	2	19960319	G	8530	31C12	STUD            			GULSTM	112   	112A        	7630302	SW  	LYC   	O360  	IO360C1D6   	41514	EA  					NR 4 CYLINDER	DETACHED        	B			DWSR	L	O			ABORTED APPROACH        	OTHER                   			J			WARNING INDICATION        			AP	APPROACH       	1			SO	05	1189J					189	L1252051A			PILOT REPORTED IN-FLIGHT:  NOSE GEAR WILL NOT EXTEND NORMALLY, FLY-BY, TOWER VERIFIED NOSE GEAR NOT DOWN.  EMERGENCY GEA	R EXTENDED, ALL GEAR EXTENDED, SAFE LANDING.  FINDINGS:  EXHAUST STUD FROM NR 4 CYLINDER FELL OUT AND LODGED IN HINGE SL	OT FOR NOSE GEAR DOORS PREVENTING GEAR FROM EXTENDING NORMALLY.  COWLING AFT MOUNT DAMAGED, BUT REPAIRABLE.  LOGS SHOWED	 NR 4 EXHAUST GASKET PREVIOUSLY REPLACED.  NUT STILL ATTACHED TO STUD AND HELICOIL ON THREADS.			1	L	7	1 	3O	3	O		A12SO   	1E10				 
1996051600263	19960516	00263	CE  	1996	5	16	96ZZZX2395       	1	19960401	G	2740	NAS56138	ROLL PIN        			CESSNA	185   	A185F       	2072821	CE  										STABILIZER TRIM	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	101AM	2858 				18502390				STABILIZER TRIM CONTROL WHEEL/SHAFT HAD EXCESSIVE PLAY.  UPON INSPECTION, FOUND ROLL PINS, P/N NAS561-3-8, BOTH SHEARED 	AND ONLY RETAINED BY THE SAFETY WIRE PASSED THROUGH THE ROLL PIN PER CESSNA MM FOR ROLL PIN RETENTION.  TRIM WHEEL SHAFT	 HAD THE HOLES OR THE ROLL PINS SEVERELY WORN OBLONG.  SUSPECT CAUSE:  ROLL PINS SHOULD BE OF DIFFERENT DESIGN OR SOLID 	PINS INSTALLED.			1	H	7	1 	3O				3A24    					 
1996051600264	19960516	00264	CE  	1996	5	16	96ZZZX2396       	1	19960401	G	2740	07612059	SHAFT           			CESSNA	185   	A185F       	2072821	CE  										STABILIZER TRIM	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	101AM	2858 				18502390				STABILIZER TRIM CONTROL WHEEL/SHAFT HAD EXCESSIVE PLAY.  UPON INSPECTION, FOUND ROLL PINS, P/N NAS561-3-8, BOTH SHEARED 	AND ONLY RETAINED BY THE SAFETY WIRE PASSED THROUGH THE ROLL PIN PER CESSNA MM FOR ROLL PIN RETENTION.  TRIM WHEEL SHAFT	 HAD THE HOLES OR THE ROLL PINS SEVERELY WORN OBLONG.  SUSPECT CAUSE:  ROLL PINS SHOULD BE OF DIFFERENT DESIGN OR SOLID 	PINS INSTALLED.			1	H	7	1 	3O				3A24    					 
1996051600265	19960516	00265	CE  	1996	5	16	96ZZZX2397       	1	19960125	G	5522	123463315	ELEVATOR EDGE   		123463321   	CESSNA	210   	210M        	2073450	CE  										LT ELEVATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	761AQ					21062105				DURING INSPECTION PRIOR TO PAINTING, FOUND CORROSION ON INBOARD LOWER SURFACE OF ELEVATOR TRAILING EDGE.  TWO HOLES APPR	OXIMATELY .125 INCH DIAMETER ALONG WITH SMALLER PIN HOLES WERE FOUND.  SUSPECT CAUSE, FOAM IN TRAILING EDGE RETAINING WA	TER INSIDE TRAILING EDGE ASSY.  SUGGEST CLOSE INSPECTION OF FOAM FILLED SURFACES.				1	H	7	1 	3O				3A21    					 
1996051600267	19960516	00267	EA  	1996	5	16	96ZZZX2399       	2	19960225	G	8550	62817	FILTER SCREEN   			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					ACCESSORY CASE	SPLIT           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	7821V					2805	RL1289236A			DURING ANNUAL, OIL PRESSURE SCREEN WAS REMOVED AND CHECKED FOR METAL, ETC.  AFTER SCREEN WAS CLEANED IN PARTS WASHER, IT	 WAS NOTED THE SOLDERED SEAM OF THE INNER FINE MESH SCREEN WAS SPLIT.  ON CLOSER INSPECTION, THE OUTER SCREEN SHOWED APP	ROXIMATELY FOUR STRANDS SEPARATED FROM THE SOLDER.  THE AREA OF SEPARATION IS MIDWAY AND THE SCREEN LOOKS AS IF IT WAS S	WOLLEN.  SUSPECT AGE, HEAT CHANGES, AND DIFFERENTIAL OF PRESSURES ON THE INNER AND OUTER SIDES OF SCREEN FROM DIRT, GRIT	, AND COLD THICK OIL WERE CAUSES.  SUBMITTER STATED MORE FREQUENT AND THOROUGH CLEANING OF SCREEN OR REPLACMENT AT INTER	VALS (500 HOURS OR 5 YEARS).	1	L	7	1 	3O	3	O		2A3     	E286				 
1996051600268	19960516	00268	SO  	1996	5	16	96ZZZX2400       	1	19960308	G	3510		BRACKET         			PIPER 	PA32  	PA32R301T   	7103220	SO  										OXYGEN BOTTLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4383M					32R8529002				TOTAL TIME, 2,400 HOURS.  ALL 4 BRACKETS USED TO ATTACH THE OXYGEN BOTTLE RACK TO THE SIDES OF THE REAR FUSELAGE WERE FO	UND CRACKED DURING ANNUAL INSPECTION.  SUSPECT CAUSE:  BRACKETS NOT STRONG ENOUGH TO SUPPORT WEIGHT.  REMAKE BRACKETS OU	T OF THICKER MATERIAL AND BEND A LARGER 'L' SHAPED BRACKET.  BRACKETS INSTALLED ON AFT FUSELAGE SIDE SKINS, PN 99470-800	 AND PN 99470-01, FS 210.00.			1	L	7	1 	3O				A3SO    					 
1996051600269	19960516	00269	CE  	1996	5	16	96ZZZX2401       	1	19960320	G	7714	MS3106A10S	CONNECTOR PLUG  		MS250382    	CESSNA	414   	414A        	2075907	CE  										TACHOMETER GEN	PINS STRIPPED   	D				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			WP	13	6604C				A12356	414A0030				LEFT ENGINE TACHOMETER FAILED ON TAKEOFF ROLL.  PRE-INSPECTION, CONNECTOR PLUG SECURED AND SAFETIED.  IT WAS DISCOVERED 	THE LEFT TACHOMETER GENERATOR ELECTRICAL CONNECTOR PLUG ELECTRICAL PINS HAD STRIPPED.  CONNECTOR PLUG REPLACED.  AIRCRAF	T RETURNED TO SERVICE.				1	L	7	2 	3O				A7CE    					 
1996051600273	19960516	00273	CE  	1996	5	16	96ZZZX2405       	1	19960201	G	2810		FUEL CAP        			CESSNA	180   	180J        	2072622	CE  										LT TANK	DEFECTIVE       	C				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	07	6WH					18052492				THE ORIGINAL FLUSH FUEL CAPS AND PLATES WERE REPLACED SEVERAL YEARS AGO WITH 'UMBRELLA' CAPS AND PLATES SOLD BY CESSNA. 	 THE CAPS WERE RED PLASTIC.  DURING A FLIGHT IN FEBRUARY OF THIS YEAR, APPROXIMATELY 6 GALLONS OF GAS SIPHONED OUT OF LE	FT TANK.  DURATION OF THE FLIGHT WAS 5.50 HOURS.  SENDING THE ASSY FOR EXAMINATION.				1	H	7	1 	3O				5A6     					 
1996051600274	19960516	00274	CE  	1996	5	16	96ZZZX2406       	1	19960322	G	2913	571302	MOTOR           			BEECH 	B300  	B300        	1159232	CE  										HYD POWER PACK	FAILED          	B			AKGR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CE	05	8116N	1696 			929A	FL58				GEAR WOULD NOT COME UP.  JACKED AIRCRAFT, GROUND OPERATION NORMAL.  REPLACED HYDRAULIC POWER PACK MOTOR.  TEAR DOWN OF R	EMOVED MOTOR FOUND SPLICE USED TO CONNECT THE B-PLUS WIRE COMING FROM THE RF FILTER TO THE SOLID WIRES OF THE MOTORS, WA	S NOT THE PROPER TYPE AND ONE OF THE WIRES WAS NOT EVEN IN THE SPLICE CRIMPED AREA.				2	L	7	2 	4T			RT	A24CE   					 
1996051600275	19960516	00275	SO  	1996	5	16	96ZZZX2407       	2	19960402	G	8530	646303	PISTON          			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					LT ENG NR 5	BURNED          	B			ITWR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	07	67934		900  			421C1026	610051			AIRCRAFT LOST POWER ON NR 1 ENGINE.  REMOVAL OF NR 5 CYLINDER REVEALED PISTON DOME EDGE BURNED AWAY FROM 6:00 POSITION T	O 12:00 POSITION.  AT 9:00 POSITION, PISTON DOME BURNED COMPLETELY THROUGH, APPROXIMATELY 1 INCH OF PISTON MATERIAL MISS	ING FROM EDGE TOWARDS CENTER OF DOME.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996051600276	19960516	00276	SO  	1996	5	16	96ZZZX2408       	2	19960320	G	8530		CYLINDER        			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					ROCKER BOSS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	732DZ	1669 				21061446	567326			FIVE OF SIX CYLINDERS HAVE CRACKS IN ROCKER BOSS AREA UP TO THE ROCKER SHAFT RETAINING BOLTS.  TWO OF THESE FIVE HAVE CR	ACKS ON INTAKE AND EXHAUST BOSSES.  THIS ENGINE DOES NOT INCORPORATE LONG BOLTS AND SOLID SHAFTS.					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996051600277	19960516	00277	CE  	1996	5	16	96ZZZX2409       	1	19960307	G	2720	031019613	SPRING          			CESSNA	150   	150K        	2071822	CE  										RUDDER RETURN	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5738G	6130 				15071238				RUDDER RETURN SPRING ON COPILOT'S LEFT PEDAL WAS FOUND BROKEN.  NO RECORD OF SPRING EVER BEING REPLACED.  SUSPECT CAUSE 	WAS METAL FATIGUE.					1	H	7	1 	3O				3A19    					 
1996051600278	19960516	00278	SO  	1996	5	16	96ZZZX2410       	2	19960307	G	8540	99101371	SHAFT           			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					RT ENG HYD	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	215MP					421C1231				FOUND DRIVE SHAFT ON AIR CONDITIONING, HYDRAULIC PUMP SHEARED.  UPON REMOVAL, SYSTEM HYDRAULIC PUMP SHAFT SPLINES WERE F	OUND WORN OUT AND RUSTED.  SUBMITTER SUGGESTS SPLINES BE LUBED AT 200-HOUR INTERVALS TO PREVENT THIS PROBLEM FROM RECURR	ING.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996051600279	19960516	00279	CE  	1996	5	16	96ZZZX2411       	1	19960311	G	3211		SCREWS          			CESSNA	310   	310R        	2074245	CE  										TRUNNION SUPPORT	LOOSE           	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	200LE					310R1842				DURING AN UNRELATED INSPECTION, THE 4 MAIN GEAR TRUNNION SUPPORT (PN'S LT AFT, 0822724-11, LT FWD, 0822720-19, RT AFT, 0	822724-10, RT FWD, 0822720-18) VERTICAL MOUNTING NAS SCREWS SECURING THE MOUNTS TO THE WING RIBS (PN'S LT, 5022104-51, R	T, 5022104-52) WERE FOUND LOOSE AND WORKING.  CLOSER INSPECTION FOUND ALL BUT 7 SCREWS OUT OF ABOUT 50, THE NUTS WERE BO	TTOMED ON THE THREADS.  MINIMAL WORKING DAMAGE, WASHERS WERE ADDED, AND SCREWS TORQUED TO SPECS.			1	L	7	2 	3O				3A10    					 
1996051600280	19960516	00280	SO  	1996	5	16	96ZZZX2412       	2	19960320	G	8530		ENGINE          			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					CYLINDER	DEFECTIVE       	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	761TF	1975 				21062499				PRE-PURCHASE INSPECTION OF AIRCRAFT REVEALED ENGINE COMPRESSION WELL BELOW ACCEPTABLE LIMITS, SEAT RAILS WERE WORN BEYON	D LIMITS.  ESTABLISHED BY AIRWORTHINESS DIRECTIVE.  ELEVATOR TRIM TAB WITH HOLES CORRODED THROUGH THE TAB SKIN.  AIRCRAF	T WAS ANNUALLED THE FIRST WEEK OF MARCH, 1996, AND LESS THAN 2 HOURS AGO.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996051600281	19960516	00281	CE  	1996	5	16	96ZZZX2413       	1	19960329	G	3520		OXYGEN MASK     			BEECH 	90    	F90         	1152909	CE  										HEADLINER	FAIL DEPLOY     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	7775					LA117				DURING ROUTINE MAINTENANCE, THE OXYGEN AUTO-DEPLOY SYSTEM WAS ACTIVATED.  ALL MASKS FAILED TO DEPLOY.  THE CAUSE WAS THE	 NEW HEADLINER MATERIAL THICKNESS WHICH PREVENTED THE ACTUATOR PLUNGER FROM CONTACTING THE STRIKER PLATE ON THE MASK CON	TAINER.  THIS IS THE FIRST TIME THIS SYSTEM HAD BEEN ACTIVATED SINCE THE AIRCRAFT HAS BEEN RE-TRIMMED ON 11-11-93.				1	L	7	2 	4T				A31CE   					 
1996051600282	19960516	00282	SO  	1996	5	16	96ZZZX2414       	2	19960417	G	7414	10357586	DISTRIBUTOR GEAR	BENDIX      	S6RN201     	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					RT MAGNETO	TEETH MISSING   	I				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			NE	05	3249M	1161 			K1411M	402C0296				ENGINE ROUGNESS NOTED.  INSPECTION REVEALED RIGHT MAGNETO DISTRIBUTOR GEAR MISSING SOME OF ITS TEETH (NOTED 259.6 HRS SI	NCE ITS LAST INSPECTION).  CAUSE UNKNOWN.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996051600283	19960516	00283	CE  	1996	5	16	96ZZZX2415       	1	19960408	G	2820		LINE            			CESSNA	402   	402B        	207590P	CE  										FUEL CROSS FEED	LEAKING         	I				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			NE	05	87147	7001 				402B1003				UPON LANDING, FLIGHT CREW SMELLED FUEL.  AFTER PULLING PANEL TO REVEAL CROSS-FEED LINE, FOUND A PIN HOLE, EVER SO SMALL,	 SPRAYING FUEL.  THIS IS AN OPEN ACCESS LINE AND EVEN WITH A GOOD INSPECTION FINDING FUEL STAINS, ARE THE ONLY CLUES OF 	THIS LINE DETERIORATING.  NOTE:  MEB 87-7-R1.				1	L	7	2 	3O				A7CE    					 
1996051600284	19960516	00284	EU  	1996	5	16	96ZZZX2416       	1	19960413	G	7810		MUFFLER         			MRCHTI	S205  	S20522R     	8120412	EU  										BAFFLE	DEFECTIVE       	G				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			GL	15	954W	919  				4154				DURING AN ACCIDENT INVESTIGATION, FOUND LEFT SIDE EXHAUST MUFFLER HAD AN INTERNAL BAFFLE/END PLUG THAT WAS NOT SECURED A	ND, THUS, ALLOWED EXHAUST GAS TO BE VENTED DIRECTLY TO THE EXHAUST PIPE.  IT IS SPECULATED THIS CONDITION WOULD ALLOW IM	PROPER EXHAUST BACK PRESSURE AND DEGRADE ENGINE PERFORMANCE.  DURING THE REQUIRED INSPECTIONS, IT IS RECOMMENDED THAT A 	CAREFUL INSPECTION BE MADE OF THE BAFFLE AND DIFFUSSERS TO ASSURE INTERNAL SECURITY OF THESE ITEMS.			1	L	7	1 	3O				A9EU    					 
1996051600287	19960516	00287		1996	5	16	96ZZZX2419       	1	19960420	G	2822	3B74	FUEL PUMP       	AIRBORNE    																BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					5AC29					FUEL PUMP CAVITY WORN, VANES BROKEN DUE TO UNBALANCED CONDITION OF ARMATURE.																			 
1996051600288	19960516	00288		1996	5	16	96ZZZX2420       	1	19960420	G	2822	1C61	FUEL PUMP       	AIRBORNE    																BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					2T824					FUEL PUMP IMPELLER CAME APART, POSSIBLE GLUE OR EPOXY FAILURE.  EPOXIED BACK TOGETHER.																			 
1996051600289	19960516	00289		1996	5	16	96ZZZX2421       	1	19960420	G	2822	1C61	FUEL PUMP       	AIRBORNE    																BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					2T863					FUEL PUMP IMPELLER CAME APART, POSSIBLE GLUE OR EPOXY FAILURE.  EPOXIED BACK TOGETHER.																			 
1996051600290	19960516	00290		1996	5	16	96ZZZX2422       	1	19960420	G	2822	1C61	FUEL PUMP       	AIRBORNE    																BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					5P135					FUEL PUMP IMPELLER CAME APART, POSSIBLE GLUE OR EPOXY FAILURE.  EPOXIED BACK TOGETHER.																			 
1996051600291	19960516	00291		1996	5	16	96ZZZX2423       	1	19960420	G	2822	2B729	FUEL PUMP       	AIRBORNE    																BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					3AB77					FUEL PUMP CAVITY WORN, VANES BROKEN DUE TO UNBALANCED CONDITION OF ARMATURE.																			 
1996051600292	19960516	00292		1996	5	16	96ZZZX2424       	1	19960420	G	2822	1B56	FUEL PUMP       	AIRBORNE    																BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					4T321					FUEL PUMP CAVITY WORN, VANES BROKEN DUE TO UNBALANCED CONDITION OF ARMATURE.																			 
1996051600293	19960516	00293		1996	5	16	96ZZZX2425       	1	19960420	G	2822	2B664	FUEL PUMP       	AIRBORNE    																BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					8AF110					FUEL PUMP CAVITY WORN, VANES BROKEN DUE TO UNBALANCED CONDITION OF ARMATURE.																			 
1996051600294	19960516	00294	GL  	1996	5	16	96ZZZX2426       	3	19960419	G	6114	D7019C92	HUB             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF32C	3AF32C*     	GL  	BLADE SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	112SW	1642 			805941	421B0350		805841		INSPECTION FOUND BLADE SOCKET THREADS CRACKED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996051600295	19960516	00295	CE  	1996	5	16	96ZZZX2427       	1	19960417	G	3230	12436351	TORQUE LINK     			CESSNA	206   	U206G       	2073356	CE  										NLG UPPER	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	756TE					U20604337				CRACKED UPPER TORQUE LINK ON NOSE GEAR.  DEFECT FOUND DURING 100-HOUR INSPECTION AND LUBRICATION OF NOSE GEAR.  SUSPECT 	CAUSE MAY BE WORN STOP LUG ON SCISSORS.  THE TWO CRACKS LOCATED APPROXIMATELY 2 INCHES FROM END OF SCISSORS BOTTOM SIDE.					1	H	7	1 	3O				A4CE    					 
1996051600296	19960516	00296	SO  	1996	5	16	96ZZZX2428       	1	19960225	G	7120	65000000	MOUNT           			PIPER 	PA28  	PA28235     	7102810	SO  										NLG	SUPPORT FAILED  	G		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	27	8831W	3196 				2810378				DURING LANDING AT AIRPORT, NOSE GEAR COLLAPSED.  PILOT SHUT DOWN THE ENGINE, AIRCRAFT CAME TO REST ABOUT 210 FEET FROM T	HE INCIDENT.  THE PILOT AND THE OCCUPANTS SUFFERED NO INJURIES.  THE AIRCRAFT WAS TAKEN TO THE HANGAR.  BLADE TIPS AND T	HE BOTTOM ENGINE COWL HAD MINOR DAMAGE.  A TEAR-DOWN INSPECTION OF THE NOSE GEAR REVEALED CORROSION UNDER THE SUPPORT BR	ACKET.  THE ENGINE SENT FOR A HIDDEN DAMAGE INSPECTION.			1	L	7	1 	3O				2A13    					 
1996051600297	19960516	00297	SO  	1996	5	16	96ZZZX2429       	1	19960325	G	3230	6774803	ACTUATOR        			PIPER 	PA28  	PA28RT201   	7102818	SO  										EMERG EXTENSION	ARM DISENGAGED  	D	L	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	8162S	2191 				28R8018042				GEAR ACTUATOR ARM BECAME DISENGAGED FROM PUSH ROD ARM; THUS, DISABLING EMERGENCY EXTENSION FUNCTION OF MAIN LANDING GEAR	.					1	L	7	1 	3O				2A13    					 
1996051600298	19960516	00298	CE  	1996	5	16	96ZZZX2431       	1	19960415	G	3230	35815109	UPLOCK CABLE    			BEECH 	36    	A36         	1151604	CE  										MLG UPLOCK	FRAYED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	1058W	2966 				E409				DURING ANNUAL INSPECTION, UPLOCK CABLE, LEFT GEAR, CABLE TENSION LOW.  FOUND 3 BROKEN CABLE STRANDS AND FITTING MS20667-	2 BENT IN THREADED AREA.  CHECKED RIGHT UPLOCK ALSO.  FOUND TERMINAL MS20667-2 BENT.  IT APPEARS THAT THE DAMAGE OCCURS 	WHEN TERMINAL MS20667-2 IS SCREWED IN TOO FAR TO TERMINAL MS201259-2R.  SUBMITTER RECOMMENDS CHANGING TO BEECHCRAFT MM G	EAR RIGGING PROCEDURES.			1	L	7	1 	3O			 	3A15    					 
1996051600299	19960516	00299	CE  	1996	5	16	96ZZZX2432       	1	19960415	G	3230	MS206672	FITTING         			BEECH 	36    	A36         	1151604	CE  										UPLOCK CABLE	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	1058W	2966 				E409				DURING ANNUAL INSPECTION, UPLOCK CABLE, LEFT GEAR, CABLE TENSION LOW.  FOUND 3 BROKEN CABLE STRANDS AND FITTING MS20667-	2 BENT IN THREADED AREA.  CHECKED RIGHT UPLOCK ALSO.  FOUND TERMINAL MS20667-2 BENT.  IT APPEARS THAT THE DAMAGE OCCURS 	WHEN TERMINAL MS20667-2 IS SCREWED IN TOO FAR TO TERMINAL MS201259-2R.  SUBMITTER RECOMMENDS CHANGING TO BEECHCRAFT MM G	EAR RIGGING PROCEDURES.			1	L	7	1 	3O				3A15    					 
1996051600300	19960516	00300	SO  	1996	5	16	96ZZZX2433       	1	19960214	G	2140	460755	FUEL STRAINER   		481666      	PIPER 	PA23  	PA23        	7102302	SO  										HEATER	LEAKING         	B	L	A	RX7R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	2018P					23590				HEATER FUEL STRAINER CRACKED/CORRODED.  WHEN FUEL VALVE TO HEATER WAS OPENED, FUEL POURED OUT INTO NOSE CONE SECTION.  V	ERY SEVERE LEAK.  PILOT IMMEDIATELY SMELLED FUEL AND SHUT VALVE OFF.  HAD HE NOT, THERE COULD HAVE BEEN A FIRE AND/OR EX	PLOSION.  APPEARED CLAMPING NUT HAD BEEN OVERTORQUED.  ALSO, FUEL STRAINER APPEARED NOT TO HAVE BEEN REMOVED AND CLEANED	 RECENTLY.  SEVERE CORROSION.  SKINNER PURIFIER FUEL SCREEN.			1	L	7	2 	3O				1A10    					 
1996051600301	19960516	00301	SO  	1996	5	16	96ZZZX2434       	1	19960308	G	5712	6202100	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  										RT WING	CRACKED         	B		A	OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	805ND	5928 				2837008				FOUND BOTH RIBS CRACKED WHERE FLANGE RIVETS AND BOLTS TO MAIN SPAR.  CRACK IS APPROXIMATELY 1 INCH LONG AND ORIGINATES B	Y EDGE OF WASHER/NUT FOR TOP BOLT OF GEAR FITTING PN 95643-06 AND PN 95643-07.					1	L	7	1 	3O				2A13    					 
1996051600302	19960516	00302	SO  	1996	5	16	96ZZZX2435       	1	19960308	G	5712	6202101	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  										LT WING	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	805ND	5928 				2837008				FOUND BOTH RIBS CRACKED WHERE FLANGE RIVETS AND BOLTS TO MAIN SPAR.  CRACK IS APPROXIMATELY 1 INCH LONG AND ORIGINATES B	Y EDGE OF WASHER/NUT FOR TOP BOLT OF GEAR FITTING PN 95643-06 AND PN 95643-07.					1	L	7	1 	3O				2A13    					 
1996051600303	19960516	00303	GL  	1996	5	16	96ZZZX2436       	3	19960325	G	6111	V84334	BLADE           			GULSTM	500   	500S        	0141107	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	SHANK	CRACKED         	B		A	WN1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	4860E		3100 		B29226	180717		BJ851		BLADE CRACK FOUND WITH EDDY CURRENT.  WOULD NOT SHOW UP WITH DYE CHECK.  SUBMITTER SUGGESTS REVISING AD 68-19-04 AND AD 	68-13-02 TO MAKE EDDY CURRENT MANDATORY.					1	H	7	2 	3O				6A1     		5	C	P6EA	 
1996051600304	19960516	00304	EU  	1996	5	16	96ZZZX2437       	2	19960322	G	7314	996590	PUMP            			DIAMON	DA20A1	DA20A1      	05626UX	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	OIL LEAK        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	526SS	24   				10085				FUEL PUMP STARTED LEAKING OIL AT SEAM WHERE DIAPHRAM WAS IN PUMP.						1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
1996051600305	19960516	00305	NE  	1996	5	16	96ZZZX2438       	1	19960116	G	3212	7625100702042	EXPLOSIVE LINK  			SKRSKY	S76   	S76A        	8143006	NE  										MLG	MALFUNCTION     	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5446E				0375	76075				INADVERTENT FLOAT DEPLOYMENT.  SQUIBS FIRED, BUT LINK FAILED TO SEPARATE.  WHEN FLOATS WERE INADVERTENTLY INFLATED, THE 	EXPLOSIVE LINK FAILED TO SEPARATE ON ONE GEAR DOOR.  UNABLE TO DETERMINE WHY THE LINK FAILED TO SEPARATE.					1	G	7	2 	3U				H1NE    					 
1996051600365	19960516	00365	SW  	1996	5	16	96ZZZX2447       	1	19960415	G	3213	206030104123	FITTING         			BELL  	206   	206L4       	1182110	SW  										FWD LANDING GEAR	CRACKED         	B	S	A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	170AL	2750 				52063				DURING SERVICE CHECK, NOTED MLG FITTING WAS CRACKED.  FITTING WAS FOUND CRACKED IN THE SAME AREA AS REPORTED ON MDR SUBM	ITTED ON 2-7-94.  THE FITTING WAS MANUFACTURED IN OCTOBER, 1992, WHICH IS DIFFERENT FROM THE PREVIOUSLY REPORTED CRACKED	 FITTINGS.				1	G	7	1 	3U			NC	H2SW    					 
1996051600366	19960516	00366	SW  	1996	5	16	96ZZZX2448       	1	19960320	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	362AL		505  			51471				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.  SUSPECT NORMAL USE CAUSES PART TO WEAR OUT TOO SOON.  WORN PARTS TT 505.1 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600367	19960516	00367	SW  	1996	5	16	96ZZZX2449       	1	19960320	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	362AL		505  			51471				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.  SUSPECT NORMAL USE CAUSES PART TO WEAR OUT TOO SOON.  WORN PARTS TT 505.1 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600368	19960516	00368	SW  	1996	5	16	96ZZZX2450       	1	19960320	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		701  			45449				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.  SUSPECT NORMAL USE CAUSES PART TO WEAR OUT TOO SOON.  WORN PARTS TT 701.2 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600369	19960516	00369	SW  	1996	5	16	96ZZZX2451       	1	19960320	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		701  			45449				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.  SUSPECT NORMAL USE CAUSES PART TO WEAR OUT TOO SOON.  WORN PARTS TT 701.2 HOURS.				1	G	7	1 	3U				H2SW    					 
1996051600370	19960516	00370	SW  	1996	5	16	96ZZZX2452       	1	19960415	G	3213	206030104123	FITTING         			BELL  	206   	206L1       	1182107	SW  										FWD LANDING GEAR	CRACKED         	B	S	A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5734M	2198 				45449				DURING SERVICE CHECK, NOTED MLG FITTING WAS CRACKED.  FITTING WAS FOUND CRACKED IN THE SAME AREA AS REPORTED ON MDR SUBM	ITTED ON 2-7-94.  THE FITTING WAS MANUFACTURED IN OCTOBER, 1992, WHICH IS DIFFERENT FROM THE PREVIOUSY REPORTED CRACKED 	FITTINGS.				1	G	7	1 	3U				H2SW    					 
1996051600371	19960516	00371	EU  	1996	5	16	96ZZZX2453       	1	19960410	G	6230	350A37100205	NON ROTATE STAR 		355A37000001	AEROSP	AS355 	AS355F      	8680806	EU  										SWASHPLATE	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5787E	6624 			M433	5058				DAILY INSPECTION FOUND SERVO TO STAR ATTACH POINT WORN BEYOND LIMITS AND SERVO ROD END WEARING INTO STAR.						1	G	7	2 	3U				H11EU   					 
1996051600506	19960516	00506		1996	5	16	96ZZZX2454       	4	19960322	G	2215	0107P5	SERVO           	STEC        		CESSNA	206   	U206F       	2073333	CE  										PITCH SERVO	LEADS SHORTING  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	2216U				4536A	U20602355				SERVO MOTOR LEADS SHORTING TO FRAME OF PITCH SERVO ONLY WHEN TORQUE APPLIED ON MOTOR WHICH CAUSES PITCH OSCILLATION, PLU	S OR MINUS 1,500 FEET/MINUTE.  SUBMITTER RECOMMENDS ROUTING TO PREVENT TOUCHING FRAME.					1	H	7	1 	3O				A4CE    					 
1996051600507	19960516	00507		1996	5	16	96ZZZX2455       	4	19960415	G	6113	1250030R201	SPINNER         			CESSNA	207   	207A        	2073604	CE  						MCAULY	D3A34	D3A34C404   	GL  	PROPELLER DOME	FAILED          	E				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			WP	19	73426	13600				20700588		796960		FORWARD THIRD OF SPINNER DEPARTED AIRPLANE IN-FLIGHT.  FOUND SPINNER DOME STABILIZER PN 0550340-1 HAD WORN THROUGH THE S	PINNER CAUSING A WEAK SPOT WHICH EVENTUALLY CAUSED THE FAILURE.  SUBMITTER SUGGESTS THE POSSIBLE CAUSE WAS IMPROPER SHIM	MING OF THE STABILIZER OVER THE YEARS.  WHENEVER THE SPINNER IS REMOVED AND REINSTALLED IT SHOULD BE DONE PER CESSNA MM.				1	H	7	1 	3O				A16CE   		5	C	P47GL	 
1996051600508	19960516	00508		1996	5	16	96ZZZX2456       	4	19960310	G	2562	BP1025	BATTERY         	MERL        		BEECH 	36    	A36         	1151604	CE  										ELT	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	601SW					E904				CONDUCTING A 91.207 INSPECTION OF ELT, FOUND BATTERY LEAKING 12 MONTHS AFTER INSTALLATION.  THIS IS THE SECOND MERL BATT	ERY FOUND IN THIS CONDITION.					1	L	7	1 	3O				3A15    					 
1996051600509	19960516	00509	CE  	1996	5	16	96ZZZX2457       	1	19960415	G	3250	35825005	BOLT            		35825196    	BEECH 	36    	A36         	1151604	CE  										NLG STEERING	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	1058W	2966 				E409				OWNER INDICATED NOSE GEAR HIT AN OBSTRUCTION ON THE RUNWAY.  REMOVED NOSE GEAR ASSY PN 35-825196.  FOUND BOLT BENT.  NO 	OTHER DAMAGE FOUND.					1	L	7	1 	3O				3A15    					 
1996051600510	19960516	00510	SO  	1996	5	16	96ZZZX2458       	1	19960412	G	3210	AN6H14A	SADDLE BOLT     			PIPER 	PA38  	PA38112     	7103812	SO  										LT/RT MLG	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	9171A					3882A0119				BOTH LEFT AND RIGHT MAIN GEAR BOLTS (AN7-17A) AND ONE SADDLE BOLT FROM EACH SIDE (AN6H-14A) WERE BENT.						1	L	7	1 	3O				A18SO   					 
1996051600511	19960516	00511	SO  	1996	5	16	96ZZZX2459       	1	19960412	G	3210	AN717A	BOLT            			PIPER 	PA38  	PA38112     	7103812	SO  										LT/RT MLG	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	9171A					3882A0119				BOTH LEFT AND RIGHT MAIN GEAR BOLTS (AN7-17A) AND ONE SADDLE BOLT FROM EACH SIDE (AN6H-14A) WERE BENT.						1	L	7	1 	3O				A18SO   					 
1996051600512	19960516	00512	CE  	1996	5	16	96ZZZX2460       	1	19960319	G	3240		BRAKE FLUID     			CESSNA	182   	182Q        	2072732	CE  										BRAKE SYSTEM	CONTAMINATED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	97523					18267119				PILOT REPORTED NO BRAKING ACTION, SUSPECTED ICE AND SNOW IN BRAKE CYLINDER.  NONE FOUND.  AIRCRAFT BROUGHT INTO HEATED H	ANGAR.  BOTH BRAKES WERE BLED DOWN OF ALL FLUID, FOUND TO HAVE MORE WATER THAN BRAKE FLUID.  SYSTEM FLUSHED COMPLETE AND	 SERVICED WITH 5606 HYDRAULIC FLUID.  CONDENSATION NOT SUSPECTED DUE TO AMOUNT OF WATER.  SUSPECT POSSIBLY DUE TO CONTAM	INATED SERVICE EQUIPMENT.			1	H	7	1 	3O			NT	3A13    					 
1996051600513	19960516	00513	SO  	1996	5	16	96ZZZX2461       	1	19960415	G	3230	8194702	ROD ASSY        			PIPER 	PA31T 	PA31T3      	7103128	SO  										NLG RETRACT	FROZE UP        	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AL	01	218CS	8061 				31T8275016				NOSE GEAR WOULD NOT STAY UP AND LOCKED AFTER GEAR SELECTOR RETURNED TO NEUTRAL IN-FLIGHT.  ALL OTHER GEAR FUNCTIONS WERE	 NORMAL.  FOUND MOISTURE UNDER DUST BOOTS ON NORMAL AND EMERGENCY UPLOCK HOOK RETRACT RODS.  DRIED ROD ASSYS AND BOOTS W	ITH COMPRESSSED AIR, LUBED RODS, AND REINSTALLED BOOTS.  RETRACT TEST OK.  FLIGHT WAS CONDUCTED UNDER FREEZING TEMPS.  R	OD ASSY FROZE IN RETRACTED POSITION.			1	L	7	2 	3T				A8EA    					 
1996051600514	19960516	00514	SO  	1996	5	16	96ZZZX2462       	1	19960415	G	3230	4194900	ROD ASSY        			PIPER 	PA31T 	PA31T3      	7103128	SO  										NLG RETRACT	FROZE UP        	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AL	01	218CS	8061 				31T8275016				NOSE GEAR WOULD NOT STAY UP AND LOCKED AFTER GEAR SELECTOR RETURNED TO NEUTRAL IN-FLIGHT.  ALL OTHER GEAR FUNCTIONS WERE	 NORMAL.  FOUND MOISTURE UNDER DUST BOOTS ON NORMAL AND EMERGENCY UPLOCK HOOK RETRACT RODS.  DRIED ROD ASSYS AND BOOTS W	ITH COMPRESSSED AIR, LUBED RODS, AND REINSTALLED BOOTS.  RETRACT TEST OK.  FLIGHT WAS CONDUCTED UNDER FREEZING TEMPS.  R	OD ASSY FROZE IN RETRACTED POSITION.			1	L	7	2 	3T				A8EA    					 
1996051600516	19960516	00516	CE  	1996	5	16	96ZZZX2464       	1	19960502	G	2842	C6680500802	TRANSMITTER     			CESSNA	172   	172P        	2072436	CE  										LT FUEL QTY	FLOAT DAMAGED   	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03	6601K	1034 				17274218				DURING 100-HOUR INSPECTION, THE LT FUEL QUANTITY TRANSMITTER WAS REMOVED TO REPLACE LEAKING GASKET AND SCREW SEALS.  UPO	N REMOVAL OF THE ROCHESTER TRANMSITTER, FOUND THE FLOAT WAS CONTACTING THE TOP AND BOTTOM OF THE FUEL TANK CAUSING THE C	OMPOSITE FLOAT TO DISINTEGRATE.  BLACK FLOAT RESIDUE WAS IN THE BOTTOM OF THE FUEL TANK AND IN THE MAIN FUEL STRAINER. N	EW TRANSMITTER KIT SK 172-117 IS INSTALLED WITH 1034.1 HOURS TOTAL TIME.			1	H	7	1 	3O			NT	3A12    					 
1996051600517	19960516	00517	CE  	1996	5	16	96ZZZX2465       	1	19960318	G	5541	04330106	SPAR SKIN       			CESSNA	150   	152         	2071835	CE  										RUDDER FWD	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4713Q	7687 				15285054				RUDDER FORWARD SKIN CRACKED JUST BELOW UPPER HINGE POINT.  THIS ACTS AS THE FORWARD RUDDER SPAR.  SKIN (SPAR) WAS CRACKE	D ON BOTH SIDES, AND CRACKS EXTENDED HORIZONTALLY FROM THE LIGHTENING HOLE TO THE BEND RADIUS.					1	H	7	1 	3O			NT	3A19    					 
1996051600518	19960516	00518	CE  	1996	5	16	96ZZZX2466       	1	19960401	G	2710	NAS428310	BOLT            			CESSNA	177   	177RG       	2073709	CE  										RT WING AILERON	WEDGED AILERON  	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	50478					177RG1134				AILERON STOP BOLT NAS428-3-10 SECURED TO A NUTPLATE ON A BRACKET ASSSEMBLY PN 1221088-8 SECURED TO MAIN SPAR ASSEMBLY AN	D IS USED AS A STOP FOR UP-AILERON TRAVEL, FAILED TO STOP THE UP-TRAVEL OF THE RIGHT AILERON.  BOLT DEFLECTED AND BOLT H	EAD BECAME WEDGED ON AILERON BELLCRANK PN 122187-2 WHICH, IN TURN, LOCKED THE AILERON CONTROL SYSYEM IN FULL UPRIGHT AIL	ERON.  NO AMOUNT OF PRESSURE APPLIED TO CONTROL WHEELS WOULD FREE LOCKED AILERON BELLCRANK.  PRESS APPLIED TO AILERON WO	ULD ALSO NOT FREE LOCKED BELLCRANK.  THIS INCIDENT TOOK PLACE ON THE GROUND.  INSP OF AFFECTED AREAS REVEALED STOP BOLT 	HAD SLIGHT BEND, PROBABLY DUE TO HARD AND VIOLENT MOVEMENT OF AILERONS FROM STOP-TO-STOP OVER A PERIOD OF TIME.	1	H	7	1 	3O				A20CE   					 
1996051600519	19960516	00519	SW  	1996	5	16	96ZZZX2467       	1	19960328	G	5711	2703	FITTING         			BBAVIA	7     	7AC         	2110102	SW  										LT AFT SPAR	CRACKED         	G	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	83032	3721 				7AC1688				DISMANTLED LEFT WING FOR THE PURPOSE OF RECOVERING.  AS A PRECAUTION, THE WING SPAR ATTACHMENT FITTINGS WERE MAGNAFLUXED	.  THE LEFT REAR SPAR ATTACHMENT FITTING WAS FOUND TO HAVE SEVERAL IMPERFECTIONS IN THE WELD AREAS OF BOTH THE TOP AND B	OTTOM GUSSETS.  THE FITTING WAS REPLACED WITH A NEW PART.				1	H	7	1 	3O				A759    					 
1996051600520	19960516	00520	SO  	1996	5	16	96ZZZX2468       	1	19960403	G	2913	105476	POWER PACK      			PIPER 	PA28  	PA28R200    	7102811	SO  										HYDRAULIC SYS	DEFECTIVE       	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	75340	5500 	500  		AH4295	28R7635292				AFTER OPERATING FOR 500 HOURS, THE HYDRAULIC POWER PACK BEGAN TO CAVITATE EITHER BECAUSE OF AIR OR CONTAMINATION.  THE S	M INSTRUCTIONS CLEARLY STATE 'OPERATE PUMP TO PURGE AIR FROM SYSTEM' WHENEVER REPLACING THE PUMP, A CYLINDER, OR A LINE.	  UNFORTUNATELY, THESE STEPS WILL NOT PURGE AIR NOR CONTAMINATION FROM THE ACTUATING CYLINDERS.				1	L	7	1 	3O				2A13    					 
1996051600521	19960516	00521	SW  	1996	5	16	96ZZZX2469       	1	19960328	G	5712	5142	RIB             			BBAVIA	7     	7AC         	2110102	SW  										LT NR 3 INBD	CRACKED         	G	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	83032	3721 				7AC1688				DISMANTLED BOTH LT AND RT WINGS FOR THE PURPOSE OF RECOVERING.  IN THE PROCESS OF REMOVING OLD COVER, DETERMINED THAT AL	L THE SCREWS THAT SECURE THE FABRIC TO THE RIBS FOR THE NR 2 AND NR 3 INBOARD RIBS OF EACH WING, HAD ELONGATED THE HOLES	 IN THE RIBS AND WAS NOT SERVING THE INTENDED PURPOSE OF SECURING THE FABRIC.  THE SCREW HOLES WERE ELONGATED THE ENTIRE	 WIDTH OF THE RIB CAP FLANGE AND HAD SEVERAL WITH CRACKS EMITTING FROM THEM.  THE NR 3 INBOARD RIB ON LEFT WING WAS CRAC	KED COMPLETELY THROUGH THE LIGHTENING HOLE WHICH ORIGINATED FROM THE SCREW HOLE.  SUBMITTER RECOMMENDS WHEN RECOVERING, 	THAT SCREW HOLES ARE OF PROPER SIZE.	1	H	7	1 	3O				A759    					 
1996051600522	19960516	00522	SW  	1996	5	16	96ZZZX2470       	1	19960328	G	5712	5142	RIB             			BBAVIA	7     	7AC         	2110102	SW  										LT/RT NR 2-3 INB	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	83032	3721 				7AC1688				DISMANTLED BOTH LT AND RT WINGS FOR THE PURPOSE OF RECOVERING.  IN THE PROCESS OF REMOVING OLD COVER, DETERMINED THAT AL	L THE SCREWS THAT SECURE THE FABRIC TO THE RIBS FOR THE NR 2 AND NR 3 INBOARD RIBS OF EACH WING, HAD ELONGATED THE HOLES	 IN THE RIBS AND WAS NOT SERVING THE INTENDED PURPOSE OF SECURING THE FABRIC.  THE SCREW HOLES WERE ELONGATED THE ENTIRE	 WIDTH OF THE RIB CAP FLANGE AND HAD SEVERAL WITH CRACKS EMITTING FROM THEM.  THE NR 3 INBOARD RIB ON LEFT WING WAS CRAC	KED COMPLETELY THROUGH THE LIGHTENING HOLE WHICH ORIGINATED FROM THE SCREW HOLE.  SUBMITTER RECOMMENDS WHEN RECOVERING, 	THAT SCREW HOLES ARE OF PROPER SIZE.	1	H	7	1 	3O				A759    					 
1996051600523	19960516	00523	CE  	1996	5	16	96ZZZX2471       	1	19960423	G	5312	551104013	BULKHEAD        			CESSNA	500   	500CESSNA   	2076602	CE  										FWD PRESS BULKHD	CRACKED         	B	S	A	R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	153JP	5466 				5000153				WHILE PERFORMING 900 HOUR/36 MONTH PRESSURE BULKHEAD INSPECTIONS, FOUND SMALL CRACK AT RIVET HOLE ON FORWARD PRESSURE BU	LKHEAD.  CRACK WAS ON AIR BOX.  AIRCRAFT HAD ABOUT 7,500 CYCLES.  REPAIR DATA OBTAINED FROM DER TO INSTALL PATCH.  SUBMI	TTER STATED THIS IS THE THIRD AIRCRAFT FOUND WITH THIS FAILURE AT THIS REPAIR STATION RECENTLY.				1	L	7	2 	4F				A22CE   					 
1996051600524	19960516	00524	CE  	1996	5	16	96ZZZX2472       	1	19960422	G	5730	58250171	FITTING         		582500514   	CESSNA	441   	441         	2076020	CE  										RT INBD FLAP	CHAFED SKIN     	B			CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	6860C	3800 				4410304				INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO THE SKIN AT THE WING STUB.  FITTING PN 5825017-1 OR PN 582501	7-2, WHICH IS RIVETED TO THE FORWARD INBOARD SIDE OF THE RIGHT INBOARD FLAP, IS CHAFING AGAINST THE WING SKIN.					1	L	7	2 	3T			RT	A28CE   					 
1996051600525	19960516	00525	CE  	1996	5	16	96ZZZX2473       	1	19960315	G	3010	45AS660105	HEATER MAT      			BEECH 	MU300 	400BEECH    		CE  										LT HORIZ STAB AI	BURNED OUT      	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3038V	251  			9543363	RK93				HEATER MAT BURNED OUT/FAILED (LEFT SIDE).  AIRCRAFT HAS IMPROVED ANTI-ICE KIT PREVIOUSLY INSTALLED.						2	H	7	2 	4F			RT	A16SW   					 
1996051600526	19960516	00526	SW  	1996	5	16	96ZZZX2474       	1	19960418	G	5610	36004311S	WINDSHIELD      	PPG         		GULSTM	690TP 	695         	7630518	SW  										COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	CGMMO	40   			96003H1265	96034				WINDSHIELD CRACKED UNDER NORMAL AND PROPER OPERATING CONDITIONS WITH ONLY 40 HOURS OPERATING TIME.						1	H	7	2 	3T				2A4     					 
1996051600527	19960516	00527	SW  	1996	5	16	96ZZZX2475       	1	19960418	G	5610	36004312	WINDSHIELD      	PPG         		GULSTM	690TP 	690B        	7630516	SW  										COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	177EM	3400 			90173H1785	11471				WINDSHIELD CRACKED UNDER NORMAL AND PROPER OPERATING CONDITIONS WITH 3,400 HOURS ON WINDSHIELD.						1	H	7	2 	3T				2A4     					 
1996051600528	19960516	00528	SW  	1996	5	16	96ZZZX2476       	1	19960418	G	5610	36004312	WINDSHIELD      	PPG         		GULSTM	690TP 	690B        	7630516	SW  										COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	690WM	550  			91037H5355	11399				WINDSHIELD CRACKED UNDER NORMAL AND PROPER OPERATING CONDITONS WITH ONLY 550 HOURS ON WINDSHIELD.						1	H	7	2 	3T				2A4     					 
1996051600529	19960516	00529	SW  	1996	5	16	96ZZZX2477       	1	19960418	G	5610	36004311S	WINDSHIELD      	PPG         		GULSTM	690TP 	695         	7630518	SW  										COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			SW	11	980WM	312  			95006H1256	95034				WINDSHIELD CRACKED ON DESCENT UNDER ALL NORMAL AND PROPER OPERATING CONDITIONS WITH ONLY 311.8 HOURS ON WINDSHIELD.						1	H	7	2 	3T				2A4     					 
1996051600530	19960516	00530	SO  	1996	5	16	96ZZZX2478       	1	19960411	G	5320	4564802	DOOR SILL       			PIPER 	PA42  	PA42720     	7104212	SO  										AIRSTAIR	CRACKED         	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2247R	4540 				425501005				DOOR SILL DOUBLER FOUND CRACKED.  CONNECTED CABIN BULKHEADS ALSO FOUND CRACKED.						1	L	7	2 	4T				A23SO   					 
1996051600531	19960516	00531	SO  	1996	5	16	96ZZZX2479       	1	19960411	G	5312		BULKHEAD        			PIPER 	PA42  	PA42720     	7104212	SO  										CABIN	CRACKED         	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2247R	4540 				425501005				DOOR SILL DOUBLER FOUND CRACKED.  CONNECTED CABIN BULKHEADS ALSO FOUND CRACKED.						1	L	7	2 	4T				A23SO   					 
1996051600532	19960516	00532	SO  	1996	5	16	96ZZZX2480       	1	19960410	G	5320	4686700	CHANNEL         			PIPER 	PA42  	PA42720     	7104212	SO  										NLG WELL	CRACKED         	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2247R	4540 				425501005				CHANNELS AND WHEELWELL SIDE WALL CRACKED AT NOSE GEAR STEERING TORQUE TUBE BEARING BLOCK FLANGES.						1	L	7	2 	4T				A23SO   					 
1996051600533	19960516	00533	SO  	1996	5	16	96ZZZX2481       	1	19960410	G	5620	5667602	WINDOW          			PIPER 	PA42  	PA42720     	7104212	SO  										CABIN	CRACKED         	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2247R	4540 				425501005				FOUR CABIN EXTERIOR SIDE WINDOWS FOUND CRACKED WHILE PERFORMING THE INSPECTION REQUIRED BY PIPER SB 984.						1	L	7	2 	4T				A23SO   					 
1996051600534	19960516	00534	GL  	1996	5	16	96ZZZX2482       	2	19960425	G	7250	6899373	WHEEL           								ALLSN 	250C  	250C20B     	03013	GL  					THIRD STAGE	SHROUD CRACKED  	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17					HX58891		CAE820030			TURBINE WAS DISASSEMBLED AS PART OF ENGINE REPAIR FOR COMPRESSOR STALLS.  FOUND THE SHROUD ON THE THIRD STAGE WHEEL CRAC	KED ALL THE WAY THROUGH.										3	U			E4CE				 
1996051600535	19960516	00535	EA  	1996	5	16	96ZZZX2483       	2	19960316	G	7250	3024502CL9	GEAR            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					2ND STAGE	MAKING METAL    	B			MASR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	160YV		14761		39A030	UC160	3144PS			THE POWER SECTION AND GAS GENERATOR WOULD NOT ROTATE AT TIME OF DISASSEMBLY.  THE CHIP DETECTOR AND AGB HAD BRONZE METAL	 PIECES.  WHEN THE MODULES WERE SEPARATED THERE WAS A HEAVY SMELL OF HYDRAULIC FLUID COMING FROM THE OIL THAT WAS DRAINE	D FROM THE MODULES.  WHEN THE RGB HOUSING WAS SPLIT, IT WAS FULL OF BRONZE METAL PARTICLES THAT CAME FROM THE PLANET GEA	R SLEEVE BUSHINGS ON THE NR 2 CARRIER ASSY.  THE GAS GENERATOR PROBLEMS WERE FOUND TO BE SECONDARY DAMAGE RELATED.  OIL 	SAMPLES SENT IN FOR ANALYSIS.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1996051600536	19960516	00536	SO  	1996	5	16	96ZZZX2484       	1	19960418	G	5270	MS250851	SWITCH          			EMB   	120   	EMB120RT    		SO  										CARGO DOOR	MISRIGGED       	G				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			N			FALSE WARNING             			TO	TAKEOFF        	1			GL	03	267UE	3934 				120071				AIRCRAFT ABORTED TAKEOFF DUE TO CARGO DOOR WARNING LIGHT MALFUNCTION.  THE FORWARD AND AFT MICROSWITCHES ON THE CARGO DO	OR WERE ADJUSTED AND OPS CHECKED GOOD.					2	L	7	2 	4T			RT	A31SO   					 
1996051600537	19960516	00537	CE  	1996	5	16	96ZZZX2485       	1	19960424	G	7810	1019500193	STACK           			BEECH 	200   	200BEECH    	1152920	CE  										RT ENG RT EXH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	1553M					BB1328				RIGHT EXHAUST STACK CRACKED APPROXIMATELY 80 PERCENT OF CIRCUMFERENCE OF MOUNTING FLANGE.  INSTALL NEW UNIT.						1	L	7	2 	4T				A24CE   					 
1996051600538	19960516	00538	NE  	1996	5	16	96ZZZX2486       	2	19960424	G	7314	105970	NOZZLE          	CHNDLREVANS 	MFP45       	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL PUMP	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15			1106 		AFR0837		5853			INSPECTION FOUND METAL CHIPS IN FILTER.  PUMP NOZZLE IS FRACTURED AND HAS ENTERED MAIN GEAR ASSEMBLY.  PUMP IS BEING SEN	T TO C.E.C.O. (MANUFACTURER) FOR TEAR DOWN AND INVESTIGATION.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996051600539	19960516	00539	NM  	1996	5	16	96ZZZX2487       	1	19960103	G	5320		T-CHORD         			BOEING	727   	72722       	1384002	NM  										BS 294-344	CORRODED        	B			LVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	40482					18330				T-CHORD COMMON TO NOSE LANDING GEAR WHEELWELL IN LEFT SIDE OF NOSE COMPARTMENT AT FLOOR LEVEL (WL 170 APPROXIMATELY) WAS	 FOUND CORRODED IN 6 DIFFERENT AREAS.  ALSO, NOSE GEAR WALL ABOVE T-CHORD WAS FOUND TO HAVE SURFACE CORROSION.  CORROSIO	N RANGED FROM SURFACE TO EXFOLIATION.  MAXIMUM MATERIAL LOSS WAS 22 PERCENT.				2	L	7	3 	4F				A3WE    					 
1996051600540	19960516	00540	NM  	1996	5	16	96ZZZX2488       	1	19960108	G	5347		SEAT TRACK      			BOEING	727   	72722       	1384002	NM  										BS 540	CORRODED        	B			LVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	40482					18330				DURING ROUTINE INSPECTION OF AIRCRAFT, THE FORWARD CARGO COMPARTMENT'S LEFT TIE-DOWN TRACK WAS FOUND CORRODED OVER A 20 	INCH AREA CENTERED AROUND BS 540.  EVALUATION OF PART COST VERSUS REPAIR COST LED TO REPLACEMENT OF PART WITH NEW.					2	L	7	3 	4F				A3WE    					 
1996051600541	19960516	00541	NM  	1996	5	16	96ZZZX2489       	1	19960108	G	5313		STRINGER        			BOEING	727   	72722       	1384002	NM  										FS 1030-1090	CORRODED        	B			LVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	40482					18330				DURING ROUTINE INSPECTION OF AIRCRAFT, 5 EACH FASTENER HEADS WERE FOUND PULLING THROUGH THE SKIN ALONG FUSELAGE STR 28R 	AND BS 1030, BS 1060, AND FUSELAGE SKIN WAS FOUND BULGING DUE TO CORROSION.  ONCE THE AREA WAS DISASSEMBLED, DAMAGE WAS 	FOUND TO EXTEND BACK TO BS 1090 REQUIRING A STRINGER REPAIR.  REMAINDER OF CORROSION WAS REMOVED, FOUND TO BE WITHIN NEG	LIGIBLE DAMAGE LIMITS PER SRM, AND TREATED FOR CORROSION PREVENTION.			2	L	7	3 	4F				A3WE    					 
1996051600542	19960516	00542	NM  	1996	5	16	96ZZZX2490       	1	19960108	G	5330		SKIN            			BOEING	727   	72722       	1384002	NM  										BS 480-500	CORRODED        	B			LVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	40482					18330				DURING INSPECTION OF AIRCRAFT, A FASTENER WITH ITS HEAD POPPED OFF AND 2 EACH FASTENERS AFT OF THE FIRST FASTENER WERE A	LMOST PULLED THROUGH THE FUSELAGE SKIN AT BS 480 NEAR STR 29L.  INTERNAL INSPECTION REVEALED CORROSION OF THE FUSELAGE S	KIN AROUND THE FASTENERS.  DAMAGED AREA WAS REMOVED AND REPAIR ACCOMPLISHED PER THE SRM.				2	L	7	3 	4F				A3WE    					 
1996051600543	19960516	00543	NM  	1996	5	16	96ZZZX2491       	1	19960108	G	5330		SKIN            			BOEING	727   	72722       	1384002	NM  										BS 420-460	CORRODED        	B			LVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	40482					18330				DURING ROUTINE INSPECTION OF AIRCRAFT, 3 EACH FASTENER HEADS FOUND WITH HEADS POPPED OFF ALONG THE SKIN LAP JOINT AT STR	 28R BETWEEN BS 420 - BS 460.  ALSO, BULGING OF THE SKIN WAS EVIDENT AROUND THE FASTENERS INDICATING CORROSION.  AREA WA	S REPAIRED PER BOEING SIB 727-53-0072, FIGURE 4.				2	L	7	3 	4F				A3WE    					 
1996051600544	19960516	00544	NM  	1996	5	16	96ZZZX2492       	1	19960108	G	5311		FRAME           			BOEING	727   	72722       	1384002	NM  										BS 540-STR 27L	CORRODED        	B			LVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	40482	67961				18330				FUSELAGE FRAME AT BS 540 AT STR 27L HAS EXFOLIATION CORROSION ON VERTICAL PORTION OF FRAME.  CORROSION HAS LEFT A 1.50 I	NCH HOLE IN FRAME.					2	L	7	3 	4F				A3WE    					 
1996051600545	19960516	00545		1996	5	16	96ZZZX2493       	1	19960410	G	8011	7381436	ROTOR TURBINE   	HAMSTD      	PS70046     															STARTER	DEFECTIVE       	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					59U					ROTOR HAS STOCK REMOVAL BELOW .020 INCH MINIMUM VIOLATING OVERHAUL MANUAL 80-10-01 REQUIREMENT FOR STOCK REMOVAL DURING 	BALANCING.  REF:  FIGURE 4, ITEM 5, PAGES 1142, 1144, AND FIGURE 306, PAGE 308B OF OVERHAUL MANUAL.  STARTER S/N JL39288	.																	 
1996051600546	19960516	00546		1996	5	16	96ZZZX2494       	1	19960410	G	8011	7831431	ROTOR TURBINE   	HAMSTD      	PS70046     															STARTER	DEFECTIVE       	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					1336R					ROTOR HAS STOCK REMOVAL BELOW .020 INCH MINIMUM VIOLATING OVERHAUL MANUAL 80-10-01 REQUIREMENT FOR STOCK REMOVAL DURING 	BALANCING.  REF:  FIGURE 4, ITEM 5, PAGES 1142, 1144 AND FIGURE 306, PAGE 308B OF OVERHAUL MANUAL.  STARTER S/N FC28301.																		 
1996051600547	19960516	00547		1996	5	16	96ZZZX2496       	1	19960410	G	8011	7381436	ROTOR TURBINE   	HAMSTD      	PS70046     															STARTER	DEFECTIVE       	B	L		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					18					ROTOR HAS STOCK REMOVAL BELOW .020 INCH MINIMUM VIOLATING OVERHAUL MANUAL 80-10-01 REQUIREMENT FOR STOCK REMOVAL DURING 	BALANCING.  REF:  FIGURE 4, ITEM 5, PAGES 1142, 1144 AND FIGURE 306, PAGE 308B OF OVERHAUL MANUAL.  STARTER S/N 830819.																		 
1996051600548	19960516	00548	CE  	1996	5	16	96ZZZX2497       	1	19960210	G	2840	595602710	BRACKET         			CESSNA	425   	425         	2076018	CE  										FUEL TANK PROBE	BROKEN          	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	425DC	3268 				4250185				FOUND THE RT WING NACELLE FUEL TANK PROBES MOUNTING BRACKETS BROKEN AND LEFT ONE BENT.  THIS CONDITION CAUSES ERRONEOUS 	FUEL QUANTITY INDICATION.  FOUND THE WEIGHT OF THE TOP OF THE FUEL TANK BLADDER TANK BEARS AGAINST THIS BRACKET WHEN THE	 TANK IS PARTIALLY OR COMPLETELY EMPTY.  PATCHED THE BROKEN AREA OF THE RIGHT BRACKET AND THE BENT AREA OF THE LEFT BRAC	KET.			1	L	7	2 	3T			RT	A7CE    					 
1996051600549	19960516	00549	CE  	1996	5	16	96ZZZX2498       	1	19960426	G	5343	354003043	FITTING         			BEECH 	58    	58          	1152740	CE  										DRAG LEG KEEL RT	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4626A	6000 				TH39				FITTING CORRODED SEVERELY AND CRACKED ON BOTTOM, HOLE ELONGATED AND CORRODED.  BOTTOM OF FITTING CORRODED ON BOTTOM BOLT	 ATTACH AREA DUE TO WATER AND/OR BATTERY ACID BEING TRAPPED IN AREA.  FITTING IS LOCATED DIRECTLY BELOW BATTERY BOX.  HI	NGE BOLT WAS FOUND LOOSE AT ANNUAL INSPECTION.				1	L	7	2 	3O				3A16    					 
1996051600550	19960516	00550	SO  	1996	5	16	96ZZZX2499       	1	19960228	G	5730	62061002	SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  										WING WALK	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	2545U					288016032				DOUBLER UNDER WING WALK SKIN CRACKED IN SEVERAL PLACES.  SUBMITTER STATED TWO AIRCRAFT FOUND WITH THIS CONDITION.						1	L	7	1 	3O				2A13    					 
1996051600551	19960516	00551	SO  	1996	5	16	96ZZZX2500       	1	19960416	G	5720	62086005	STIFFENER       			PIPER 	PA28  	PA28161     	7102803	SO  										INBD RT WING	CRACKED         	B	S		Y2BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	302FG	2677 				288016274				RIGHT WING INBOARD LOWER FORWARD SKIN STIFFENER CRACKED ACROSS STIFFENER.  SUBMITTER STATED THIS IS THE THIRD CRACKED ST	IFFENER FOUND IN APRIL, 1996.					1	L	7	1 	3O				2A13    					 
1996051600552	19960516	00552	CE  	1996	5	16	96ZZZX2501       	1	19960306	G	2410	530406	HUB             			CESSNA	337   	337H        	2075732	CE  										ALTERNATOR DRIVE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	26FG	1377 				33701921				THIS FAILURE OCCURRED DESPITE C/W TCM SB 95-3.  THE BUSHING AND RETAINER WERE SHOWING WEAR, HOWEVER, NOT NEAR FAILURE. S	USPECT THIS FAILURE IS A BY-PRODUCT OF THE SLOP IN THE BUSHING. THIS AREA SHOULD GET A CLOSE INSPECTION AT C/W SERVICE B	ULLETIN.				1	H	7	2 	3O				A6CE    					 
1996051600553	19960516	00553	SO  	1996	5	16	96ZZZX2502       	1	19960417	G	2820	639010107	HOSE ASSY       			PIPER 	PA28  	PA28R180    	7102809	SO  										STRAINER	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	4605J					28R30485				DURING ANNUAL INSPECTION, FOUND FUEL LINE FROM FIREWALL STRAINER TO ELECTRIC PUMP VERY STIFF.  ORIGINAL TAG DATED 1Q67, 	STILL ATTACHED.  UPON REMOVAL FOR REPLACEMENT, FOUND OUTER JACKET AND INNER STEEL BRAIDING DETERIORATED AND COMING APART	.				1	L	7	1 	3O				2A13    					 
1996051600554	19960516	00554	CE  	1996	5	16	96ZZZX2503       	1	19960419	G	2436	C6110050103	REGULATOR       	ELECTRODELTA	VR515GC     	CESSNA	172   	172P        	2072436	CE  										DC SYSTEM	DEFECTIVE       	H				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			NM	01	52139	111  			5022911	17274421				LOW VOLTAGE WARNING FAILED AND WOULD NOT ILLUMINATE.  LOW VOLTAGE WARNING LIGHT ON INSTRUMENT PANEL.  DISSASSEMBLED REGU	LATOR TO INSPECT, AS IT IS OUT OF WARRANTY.  FOUND COLD SOLDER JOINTS IN SEVERAL LOCATIONS.  REGULATOR MANUFACTURED MAY,	 1995.				1	H	7	1 	3O			NT	3A12    					 
1996051600555	19960516	00555	WP  	1996	5	16	96ZZZX2504       	1	19960426	G	2750	37741721	CRANK ASSY      			DOUG  	DC8   	DC862       	3021970	WP  										FLAP ACTUATING	BROKEN          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										FLAP CRANK ASSY IS BROKEN ON LUG AREA WHERE BOLT P/N NAS1105-23 GOES THROUGH.  SUSPECT CAUSE, METAL FATIGUE AND CORROSIO	N.					2	L	7	4 	4F				4A25    					 
1996051600556	19960516	00556	SO  	1996	5	16	96ZZZX2505       	2	19960425	G	8530	653445A11	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					PLUG BOSS	CRACKED         	I				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	3695V	1216 				TH1183	282447R			THE CONTINENTAL CYLINDER CRACKED WITH ONLY 1,216.4 HOURS ON IT.  THE CRACK ORIGINATED AT THE SPARK PLUG BOSS AND WAS TRA	VELLING TO THE FUEL INJECTION NOZZLE.  THE COMPRESSION WAS STILL IN THE UPPER 60'S.  SUBMITTER STATED THEY HAVE BEEN EXP	ERIENCING ALOT OF THIS TYPE OF CRACKING AND BELIEVE IT TO BE A PROBLEM WITH THE MANUFACTURING PROCESS AT CONTINENTAL OR 	THEIR SUB-CONTRACTORS.			1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996051600557	19960516	00557	SO  	1996	5	16	96ZZZX2506       	2	19960410	G	8530		CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					NR 1 CYL EXH RKR	BOSS CRACKED    	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	27	9264U		1438 			15078214	254467			DURING POST 100 HOUR OPERATIONAL RUN AND LEAK CHECK, NOTED A NOISE SIMILAR TO A 'BAFFLE RATTLE' BEING MADE.  AFTER SHUT 	DOWN, NO LOOSE BAFFLES WERE FOUND.  THE ROCKER BOX COVERS WERE REMOVED TO REPLACE THE GASKETS FOUND LEAKING.  WHEN NR 1 	COVER REMOVED, A SMALL 'HALF-MOON' SHAPED PIECE OF CASTING WAS FOUND.  THE OUTER EXHAUST ROCKER SHAFT BOSS HAD BROKEN OF	F THROUGH ITS DIAMETER PARALLEL WITH THE ROCKER ARM.  AD 94-05-05 ADDRESSES THIS PROBLEM AT OVERHAUL.			1	H	7	1 	3O	3	O		3A19    	E252				 
1996051600558	19960516	00558	SO  	1996	5	16	96ZZZX2507       	1	19960423	G	5330	5212700	SKIN            			PIPER 	PA31  	PA31350     	7103110	SO  										BELLY	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	25	44AC	70   				318052147				DURING REPAIR TO BELLY OF AIRCRAFT AFTER A GEAR UP LANDING, BELLY SKIN FOUND TO BE A FACTORY MADE SKIN THAT WAS MEASURED	 AT 0.032 INCH THICK.  ACCORDING TO PIPER SM, PN 761-448, FIGURE 4-21, THIS SKIN SHOULD BE 0.040 INCH THICK.  THE ADJOIN	ING SKINS WERE CHECKED AND FOUND SIMILAR DISCREPANCIES.  THESE SKINS WERE ALL FACTORY MADE, BUT INSTALLED PREVIOUSLY IN 	THE FIELD.			1	L	7	2 	3O				A20SO   					 
1996051600559	19960516	00559	CE  	1996	5	16	96ZZZX2508       	1	19960423	G	3010		LINE            			CESSNA	208   	208         	2073702	CE  										DEICE SUPPLY	MISDRILLED      	B			APCR	K				NONE                    				W	P		INADEQUATE Q C            	NO WARNING INDICATION     		IN	INSP/MAINT     	1			NM	01	9536F	7400 				20800090				PNEUMATIC SURFACE DE-ICE SYSTEM WOULD NOT BUILD ENOUGH PRESSURE TO ACTIVATE ANNUNCIATOR LIGHTS.  FOUND .1250 INCH DRAIN 	HOLES DRILLED INTO ALUMINUM SUPPLY LINES CAUSING PRESSURE LOSS.  SEALING HOLES CURED THIS PROBLEM.					1	H	7	1 	3T			NT	A37CE   					 
1996051600560	19960516	00560		1996	5	16	96ZZZX2509       	4	19960425	G	3418	1869	LIFT DETECTOR   			CESSNA	404   	404CESSNA   	2075901	CE  										LT WING	SHORTED         	B			APCR	O				OTHER                   				N			FALSE WARNING             			IN	INSP/MAINT     	1			NM	01	48SA		168  			4040417				AFTER FLIGHT THROUGH RAIN, WATER ENTERS LIFT DETECTOR AND CAUSES STALL WARNING HORN TO SOUND CONTINUOUSLY.  UNIT IS NOT 	EASY TO DRY OUT REQUIRING REPLACEMENT.  SUBMITTER STATED THIS IS A RECURRING PROBLEM.  RECOMMEND IMPROVED INTERNAL SEALI	NG OF LIFT DETECTOR.  MANUFACTURED BY 'SAFE-FLIGHT'.  PROBLEM OCCURS WITH SEVERAL PART NUMBERED UNITS.				1	L	7	2 	3O				A25CE   					 
1996051600561	19960516	00561	SO  	1996	5	16	96ZZZX2510       	2	19960423	G	8520		CRANKCASE       			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					RT NR 5 CYL	CRACKED         	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8407C	15133	1266 			347670137	265901R			SMALL CRACK FOUND IN RIGHT SIDE OF CRANKCASE NEXT TO THROUGH-BOLT JUST FORWARD OF CYLINDER NR 5.  CONSIDERED NON-CRITICA	L AREA PER SB M90-17.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996051600562	19960516	00562	EA  	1996	5	16	96ZZZX2511       	2	19960423	G	7414	M2637	POINTS          	SLICK       	6393        						LYC   	O540  	IO540C4B5   	41532	EA  					LT MAG	DEFORMED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05		392  			94020017		RL1924648A			AIRCRAFT WAS BEING RUN BEFORE FLIGHT.  WHEN SHUTTING RIGHT MAG OFF ON LEFT ENGINE, ENGINE QUIT.  CHECKED P-LEADS FOR GRO	UNDING AND PROPER INSTALLATION.  REMOVED MAG AND CHECKED COIL, POINT GAP AND REPLACED CONDENSER.  UPON CHECKING E-GAP FO	UND POINTS NOT CLOSING.  REPLACED POINTS WHICH CORRECTED DISCREPANCY.  SUSPECT CAUSE:  INSPECTING POINTS WRONG.  WHEN OP	ENING POINTS TO INSPECT, BE CAREFUL NOT TO OPEN TOO FAR.								3	O			1E4				 
1996051600563	19960516	00563	SO  	1996	5	16	96ZZZX2512       	2	19960426	G	8520	653877	LIFTER          			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					LIFTER FACE	GALLED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	61368	433  				18504159	282672R			WHILE DOING TOP OVERHAUL, FOUND 3 HYDRAULIC LIFTERS PITTED AND GALLED.  SUBMITTER RECOMMENDS CLOSER INSPECTION OF LIFTER	S AT OVERHAUL.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
1996051600564	19960516	00564	CE  	1996	5	16	96ZZZX2513       	1	19960411	G	7921	8406E	COOLER          	STWARNER    		CESSNA	177   	177RG       	2073709	CE  										ENGINE OIL	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	34161	1627 			24756	177RG0976				OIL COOLER WAS REMOVED DUE TO LEAKING.  THERE WAS NO APPARENT REASON FOR THE LEAK SUCH AS EXTERNAL DAMAGE.						1	H	7	1 	3O				A20CE   					 
1996051600565	19960516	00565		1996	5	16	96ZZZX2514       	4	19960416	G	2216	6270197	CONTROL CABLE   			PIPER 	PA34  	PA34200T    	7103406	SO  										TRIM SERVO	BROKEN          	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	20BC					347570233				ELECTRIC TRIM CABLE BROKE.  FOUND THE SERVO CAPSTAN BEGAN TO SLIP.  THE SLIPPING CAUSED THE CABLE TO BREAK DOWN AND FAIL	.  REPLACED THE CABLE AND THE TRIM SERVO.					1	L	7	2 	3O			 	A7SO    					 
1996051600566	19960516	00566	EA  	1996	5	16	96ZZZX2515       	2	19960413	G	7414		MAGNETO         	BENDIX      	2000        	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ENGINE	MISINSTALLED    	H				A				UNSCHED LANDING         				Y	W		ENGINE STOPPAGE           	INADEQUATE Q C            		CL	CLIMB          	1			EA	17	4244H					240679				ENGINE FAILURE OCCURRED UPON REACHING 4,500 FEET.  EMERGENCY LANDING AT AIRPORT WAS MADE.  INVESTIGATION DETERMINED MAGN	ETO HAD FALLEN OFF ENGINE.  INSPECTION REVEALED MAGNETO HAD BEEN REMOVED 4 MONTHS EARLIER TO C/W AD 78-09-07RE.  UPON RE	INSTALLATION OF MAGNETO, A FLANGED TYPE GASKET P/N 62224 HAD BEEN USED INSTEAD OF PROPER ROUND GASKET, P/N CW12681.  THI	S ALLOWED GASKET MATERIAL TO BE COMPRESSED BETWEEN MAGNETO HOLD-DOWN CLAMPS AND ACCESSORY HOUSING RESULTING IN IMPROPER 	TORQUING AND SUBSEQUENT FAILURE.		1	L	7	1 	3O	3	O		2A3     	1E10				 
1996051600567	19960516	00567	CE  	1996	5	16	96ZZZX2516       	1	19960311	G	2410	1100715	SHAFT           	DELCO       		BEECH 	35    	V35A        	1151544	CE  										ALT DRIVE	SHEARED PIN     	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	8388N				A94668	D8772				AIRCRAFT ALTERNATOR WAS REPORTED INOPERATIVE.  TROUBLESHOT AND FOUND ALTERNATOR GEAR RETAINING NUT HAD UNSCREWED FROM TH	E ARMATURE SHAFT.  DISCOVERED INTERNAL CONDITION OF ARMATURE SHAFT TO BE WORN AT BEARING POINT.  ALTERNATOR SHAFT SEIZED	 AND ROTATION OF THE GEAR SHEARED THE COTTER PIN AND ALLOWED THE RETAINER NUT TO COME OFF.  THIS ALTERNATOR HAD APPROXIM	ATELY 130 HOURS SINCE OVERHAUL.			1	L	7	1 	3O				3A15    					 
1996051600568	19960516	00568	SO  	1996	5	16	96ZZZX2517       	1	19960328	G	2720	9621200	TORQUE TUBE     		9631900     	PIPER 	PA34  	PA34200T    	7103406	SO  										STAB FITTING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	18TP					347970431				BY C/W AD 80-09-04 REPLACING THE TORQUE TUBE FITTING, WIND COULD AND DID BREAK TORQUE TUBE FARTHER UP THE TORQUE TUBE WH	ERE IT CANNOT BE SEEN ON PRE-FLIGHT INSPECTIONS OR OTHER WITHOUT REMOVING RUDDER.					1	L	7	2 	3O				A7SO    					 
1996051600569	19960516	00569	CE  	1996	5	16	96ZZZX2518       	1	19960220	G	3222	16981001123	HOUSING         			BEECH 	23    	C23         	1151242	CE  										NLG UPPER	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	09	66710	4079 				M2387				NOSE GEAR LANDING GEAR HOUSING FAILED ON LANDING.  STRUCTURE FAILED AT BOLT HOLES ON UPPER END OF UNIT WHERE STEERING CO	LLAR IS FASTENED.					1	L	7	1 	3O				A1CE    					 
1996051600570	19960516	00570	SO  	1996	5	16	96ZZZX2519       	2	19960424	G	8520		CRANKSHAFT      			BBAVIA	7     	7BCM        	2110106	SW  	CONT  	C85   	C858        	17008	SO  					PROPELLER ATTACH	FAILED          	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	46AC		120  			7AC3382				PROPELLER SEPARATED FROM ENGINE DUE TO CRANKSHAFT FAILURE. INDICATION OF PREVIOUS CRACK AT AREA OF FRACTURE.						1	H	7	1 	3O	3	O		A759    	E233				 
1996051600572	19960516	00572	GL  	1996	5	16	96ZZZX2521       	2	19960404	G	7250	23055438	2ND STG NOZZLE  		23035128    						ALLSN 	250C  	250C30      	03013	GL  					GP SEC	DIAPHRAGM LOOSE 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					X61641					UPON RECEIVING FROM ALLISON (NEW) 3-8-96, NOZZLE HAD A DIAPHRAGM MOVEMENT OF .004 INCH.  ACCORDING TO CEB-3188, THE DIAP	HRAGM SHOULD HAVE A MAXIMUM MOVEMENT OF .003 INCH.  THIS NOZZLE IS UNACCEPTABLE AND WAS SENT BACK TO ALLISON FOR WARRANT	Y.  TIGHTENED THE KEY ON THE DIAPHRAGM INNER RING.									3	U			E1GL				 
1996051600573	19960516	00573	GL  	1996	5	16	96ZZZX2522       	2	19960404	G	7250	23055438	2ND STG NOZZLE  								ALLSN 	250C  	250C30      	03013	GL  					GP SEC	DIAPHRAGM LOOSE 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					X61606					UPON RECEIVING FROM ALLISON (NEW) 3-5-96, NOZZLE HAD A DIAPHRAGM MOVEMENT OF .005 INCH.  ACCORDING TO CEB-72-3188, THE D	IAPHRAGM SHOULD HAVE A RADIAL MOVEMENT OF .003 INCH MAXIMUM.  THE NOZZLE WAS SENT BACK TO ADDISON FOR WARRANTY.  TIGHTEN	ED THE KEYS ON THE DIAPHRAGM INNER RING.									3	U			E1GL				 
1996051600574	19960516	00574	GL  	1996	5	16	96ZZZX2523       	2	19960404	G	7250	23055438	2ND STG NOZZLE  		23035128    						ALLSN 	250C  	250C30      	03013	GL  					GP SEC	DIAPHRAGM LOOSE 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					X61647					UPON RECEIVING FROM ALLISON (NEW) 3-5-96, NOZZLE HAD A DIAPHRAGM MOVEMENT OF .005 INCH.  ACCORDING TO CEB-72-3188, THE D	IAPHRAGM SHOULD HAVE A MAXIMUM MOVEMENT OF .003 INCH.  THE NOZZLE WAS SENT BACK TO ALLISON FOR WARRANTY. TIGHTENED THE K	EYS ON THE DIAPHRAGM INNER RING.									3	U			E1GL				 
1996051600575	19960516	00575	GL  	1996	5	16	96ZZZX2524       	2	19960404	G	7250	23055438	2ND STG NOZZLE  		2305128     						ALLSN 	250C  	250C30      	03013	GL  					GP SEC	DIAPHRAGM LOOSE 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					X61626					UPON RECEIVING FROM ALLISON (NEW) 3-8-96, NOZZLE HAD A DIAPHRAGM MOVEMENT OF .004 INCH.  ACCORDING TO CEB-72-3188, THE D	IAPHRAGM SHOULD HAVE A MAXIMUM MOVEMENT OF .003 INCH.  THIS IS UNACCEPTABLE.  THE NOZZLE WAS SENT BACK TO ALLISON FOR WA	RRANTY.  TIGHTENED THE KEYS ON THE DIAPHRAGM INNER RING.									3	U			E1GL				 
1996052300093	19960523	00093	SW  	1996	5	23	96ZZZX2533       	1	19960129	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	5750Y		451  			45517				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 206-010-470-101 BEARING.  SUSPECT NOR	MAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 451.1.				1	G	7	1 	3U				H2SW    					 
1996052300094	19960523	00094	SW  	1996	5	23	96ZZZX2534       	1	19960129	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	5750Y		451  			45517				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 206-010-470-101 BEARING.  SUSPECT NOR	MAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 451.1.				1	G	7	1 	3U				H2SW    					 
1996052300095	19960523	00095	SW  	1996	5	23	96ZZZX2535       	1	19960325	G	6230	206040576103	BEARING         		206040014103	BELL  	206   	206L3       	1182108	SW  										MAST	SPALLED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	367AL	808  			ZV1434	51443				FOUND METAL ON UPPER TRANSMISSION CHIP PLUG.  FOUND MAST BEARING OUTER RACE SPALLING.						1	G	7	1 	3U				H2SW    					 
1996061800001	19960618	00001	SW  	1996	6	18	96ZZZX2536       	1	19960312	G	5400	212030154101	FITTING ASSY    		205030845367	BELL  	212   	212         	1181420	SW  										LIFT BEAM	BROKEN          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	XASQ					30818				MAJOR INSPECTION FOUND FORWARD LEG OF FITTING BROKEN THROUGH BOLT HOLE.  AIRCRAFT TOTAL TIME 7775.6 HOURS.  REPORTED AS:	  N NR NXA-SQH (MEXICO).					1	G	7	1 	4U				H4SW    					 
1996052300218	19960523	00218	EU  	1996	5	23	96ZZZX2551       	1	19960219	G	2730	10604319	Q UNIT          			AMD   	FALC50	FALCON50MYST	2730106	EU  										ELEVATOR FEEL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	09	599SC	704  				242				DURING PRE-FLIGHT, FOUND ELEVATOR AUTHORIZATION 'Q' UNIT 'ARTIFICIAL FEEL' LEAKING AT SWIVEL FITTING.						2	L	7	3 	4F				A46EU   					 
1996052300220	19960523	00220	CE  	1996	5	23	96ZZZX2553       	1	19960301	G	2810		FUEL CAP        			CESSNA	210   	210L        	2073448	CE  										FUEL TANK	WATER LEAK      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2498S					21061306				FUEL CAPS LEAKING WATER INTO FUEL TANKS WHEN EXPOSED TO INCLEMENT WEATHER.  CORRECTED BY INSTALLING CESSNA T210L, (WW OV	AL PLATES) FROM MONARCH AIR AND DEVELOPMENT, INC.					1	H	7	1 	3O				3A21    					 
1996052300222	19960523	00222	SO  	1996	5	23	96ZZZX2555       	2	19960228	G	8530		VALVE GUIDE     			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					NR 1 CYLINDER	LOOSE           	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SO	16	52727		390  			18262801	462760			VALVE GUIDE LOOSENED IN CYLINDER HEAD ALLOWING CYLINDER TO MISFIRE.  NOTE:  DIFFICULT TO DIAGNOSE.  COMPRESSION WAS 55/8	0 UNTIL SPRING ASSY WAS MOVED.  SUBMITTER RECOMMENDS CHECKING SPRING ASSYS FOR SIDE PLAY WHEN VALVE COVERS REMOVED FOR A	NY REASON.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1996052300223	19960523	00223	SO  	1996	5	23	96ZZZX2556       	1	19960312	G	7922	77944	VALVE           			PIPER 	PA31  	PA31325     	7103105	SO  										THERMO BYPASS	CRIMP NUT GONE  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	413TC		560  			317912040				ON REMOVAL TO C/W SB 518C, FOUND NUT HAD FALLEN OFF OF VALVE, SPRING AND SEAT WERE SEPARATED FROM VALVE WITH NUT LODGED 	IN OIL PASSAGE FROM VALVE.  THE ONLY CONTAMINANTS IN OIL FILTER WAS SOME BRASS FROM THE SEAT WORKING AGAINST NUT.					1	L	7	2 	3O				A20SO   					 
1996052300224	19960523	00224	CE  	1996	5	23	96ZZZX2557       	1	19960302	G	2842	C6680500802	TRANSMITTER     			CESSNA	172   	172P        	2072436	CE  										LT FUEL TANK	FLOAT DAMAGE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	6601K	1034 				17274218				DURING 100-HOUR INSPECTION, THE LT FUEL QUANTITY TRANSMITTER WAS REMOVED TO REPLACE LEAKING GASKET AND SCREW SEALS.  UPO	N REMOVAL OF THE ROCHESTER TRANSMITTER, FOUND THE FLOAT WAS CONTACTING THE TOP AND BOTTOM OF THE FUEL TANK CAUSING THE C	OMPOSITE FLOAT TO DISINTEGRATE.  BLACK FLOAT RESIDUE WAS IN THE BOTTOM OF THE FUEL TANK AND IN THE MAIN FUEL STRAINER. N	EW TRANSMITTER KIT SK 172-117 IS INSTALLED WITH 1034.1 HRS TOTAL TIME.			1	H	7	1 	3O			NT	3A12    					 
1996052300225	19960523	00225	EA  	1996	5	23	96ZZZX2558       	2	19960124	G	8520	SL18840	CAMSHAFT        			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320E2A    	41508	EA  					LOBES	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	8643	84   				35473	L495755A			ANNUAL INSPECTION - LARGE AMOUNT OF METAL FRAGMENTS IN OIL PRESSURE AND OIL SUCTION SCREENS.  CYLINDERS REMOVED, 7 LIFTE	R BODIES NOT TURNING, ENGINE TEAR-DOWN REVEALED VERY LITTLE TAPER ON CAM LOBE TIPS EXCEPT NR 4 EXHAUST LUBE.  IT HAD .00	1 INCH TAPER AND WAS TURNING.  FURTHER INVESTIGATION REVEALED NR 3 CONNECTING ROD AND NR 3 ROD JOURNAL SCORED BADLY REND	ERING CRANKSHAFT AND NR 3 ROD UNREPAIRABLE DUE TO LARGE FRAGMENT FROM NR 2 INTAKE LIFTER BODY PASSING THROUGH OIL SUCTIO	N SCREEN AND BACK INTO OIL SYSTEM.		1	H	7	1 	3O	3	O		A759    	1E12				 
1996052300226	19960523	00226	EA  	1996	5	23	96ZZZX2559       	2	19960124	G	8520	SL72877	LIFTER          			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320E2A    	41508	EA  					FACE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	8643	84   				35473	L495755A			ANNUAL INSPECTION - LARGE AMOUNT OF METAL FRAGMENTS IN OIL PRESSURE AND OIL SUCTION SCREENS.  CYLINDERS REMOVED, 7 LIFTE	R BODIES NOT TURNING, ENGINE TEAR-DOWN REVEALED VERY LITTLE TAPER ON CAM LOBE TIPS EXCEPT NR 4 EXHAUST LUBE.  IT HAD .00	1 INCH TAPER AND WAS TURNING.  FURTHER INVESTIGATION REVEALED NR 3 CONNECTING ROD AND NR 3 ROD JOURNAL SCORED BADLY REND	ERING CRANKSHAFT AND NR 3 ROD UNREPAIRABLE DUE TO LARGE FRAGMENT FROM NR 2 INTAKE LIFTER BODY PASSING THROUGH OIL SUCTIO	N SCREEN AND BACK INTO OIL SYSTEM.		1	H	7	1 	3O	3	O		A759    	1E12				 
1996052300228	19960523	00228	CE  	1996	5	23	96ZZZX2561       	1	19960509	G	3213	22411001	FITTING         			CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	9437D	4533 				172RG1161				FOUND 2 CRACKS IN FITTING THAT HOLDS AXLE STUB TO LANDING GEAR DURING A 100-HOUR INSPECTION.						1	H	7	1 	3O				3A17    					 
1996052300319	19960523	00319	CE  	1996	5	23	96ZZZX2563       	1	19960306	G	2730	0510105125	CONTROL CABLE   			CESSNA	185   	A185F       	2072821	CE  										ELEV FS 140	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	25FG	3188 				18502425				ELEVATOR CABLE WORN.  SUBMITTER STATED PROBLEM IS TYPICAL OF ALL 185'S.  CABLE CHAFES ON RIB AND IS JUST A MATTER OF TIM	E UNTIL STRANDS IN CABLE BREAK.  SUBMITTER SUGGESTS INSTALLING PULLEY AT THIS LOCATION (FS 140.0).					1	H	7	1 	3O			 	3A24    					 
1996052300320	19960523	00320		1996	5	23	96ZZZX2564       	4	19960415	G	2562	910	ELT             	NARCO       		CESSNA	177   	177RG       	2073709	CE  										CASE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	34674	34   			10725	177RG1012				ELT HAS CORROSION ON MOUNT FOR THE CASE COVER ATTACHMENT AND ON THE CASE COVER.  APPEARS TO BE DISSIMILAR METAL CORROSIO	N FROM COPPER MOUNTING SURFACE AND ALUMINUM MOUNT BRACKET.  SUBMITTER STATED TO CORROSION-PROOF MOUNT BRACKET BY PAINTIN	G OR ALODINING.				1	H	7	1 	3O				A20CE   					 
1996052300321	19960523	00321	GL  	1996	5	23	96ZZZX2565       	3	19960430	G	6114		STUD            			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	OVER TORQUE     	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	123RA					310R0221		755779		THESE MCCAULEY PROPELLERS COME PLACARDED TO LUBE TORQUE TO 40-45 FEET/POUNDS.  THE CESSNA MM SPECIFIES 80-85 FEET/POUNDS	 DRY TORQUE.  THE CESSNA TECH SAID BOTH ARE ACCEPTABLE, BUT DO NOT MIX THE TWO.  TECH SAID 80 POUNDS LUBE TORQUE WILL PU	LL THE STUD OUT OF THE HUB.  THIS COULD BE CONFUSING, AND HAS CAUSED EXPENSIVE PROBLEMS.				1	L	7	2 	3O				3A10    		5	C	P22EA	 
1996061800002	19960618	00002	SO  	1996	6	18	96ZZZX2569       	1	19960430	G	2720	36270109	CONTROL CABLE   			PIPER 	PA28  	PA28140     	7102802	SO  										RUDDER AFT	STRETCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	6072W	3282 				2820085				INSPECTION FOUND RT RUDDER CABLE STRETCHED NOT ALLOWING FOR PROPER PEDAL ALIGNMENT OF 8 DEGREES.  SUSPECT CAUSE, STRETCH	ING OF CABLE DURING TOWING AND/OR OVERTURNING STOPS THAT ARE NOT PROPERLY ADJUSTED.  THRASHING OF RUDDER IN CROSS WIND. 	 SUBMITTER STATED PREVENTION BY PLACARDED WARNING ON TURN DEGREE AND MORE APPROPRIATE INSPECTION PROCEDURE.				1	L	7	1 	3O			 	2A13    					 
1996052300325	19960523	00325		1996	5	23	96ZZZX2571       	4	19960504	G	2312	742240001	IC DRIVER       	NARCO       	MK120       	BEECH 	55    	95C55       	1152708	CE  										NAV COMM	FAILED          	B			QA9R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	13	2787T	992  			75248	TE388				TRANSMITTER MODULATOR TRANSISTOR Q3702 FAILED (SHORTED) CAUSING IC DRIVER U3701 TO FAIL.  BOTH OF THESE COMPONENTS WERE 	BURNED CAUSING AN ELECTRICAL FIRE SMOKE ODOR TO BE PRESENT IN THE AIRCRAFT COCKPIT.  SUBMITTER SUGGESTS THIS APPEARS TO 	BE AN ISOLATED INCIDENT AS HAVE NOT SEEN THIS PARTICULAR FAILURE MODE IN THE MK-12D RADIOS BEFORE.  SUSPECT A VOLTAGE SP	IKE ON THE AIRCRAFT AVIONICS POWER BUSS COULD HAVE CAUSED THIS RADIO FAILURE.			1	L	7	2 	3O				3A16    					 
1996052300326	19960523	00326		1996	5	23	96ZZZX2572       	4	19960504	G	2312	756320001	TRANSISTOR      	NARCO       		BEECH 	55    	95C55       	1152708	CE  										NAV COMM	FAILED          	B			QA9R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	13	2787T	992  				TE388				TRANSMITTER MODULATOR TRANSISTOR Q3702 FAILED (SHORTED) CAUSING IC DRIVER U3701 TO FAIL.  BOTH OF THESE COMPONENTS WERE 	BURNED CAUSING AN ELECTRICAL FIRE SMOKE ODOR TO BE PRESENT IN THE AIRCRAFT COCKPIT.  SUBMITTER SUGGESTS THIS APPEARS TO 	BE AN ISOLATED INCIDENT AS HAVE NOT SEEN THIS PARTICULAR FAILURE MODE IN THE MK-12D RADIOS BEFORE.  SUSPECT A VOLTAGE SP	IKE ON THE AIRCRAFT AVIONICS POWER BUSS COULD HAVE CAUSED THIS RADIO FAILURE.			1	L	7	2 	3O				3A16    					 
1996052300327	19960523	00327	EU  	1996	5	23	96ZZZX2573       	1	19960424	G	3246	AH52206	WHEEL ASSY      	DUNLOP      		HWKSLY	DH125 	BH125400A   	4230138	EU  										RT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	808CC					NA779				FOUND RT MLG OUTBOARD WHEEL BROKEN ON BRAKE SIDE OF ASSY.  APPROXIMATELY 8 INCHES OF THE RIM HAD BROKEN OFF DURING LANDI	NG.  THIS CONDITION WAS FOUND DURING A POST-FLIGHT INSPECTION.  LANDING WAS UNEVENTFUL AND NO DAMAGE OCCURRED IN THE ARE	A OF WING.				2	L	7	2 	4J				A3EU    					 
1996052300329	19960523	00329	NM  	1996	5	23	96ZZZX2575       	1	19960329	G	2701	1083041100	CONTROL COLUMN  			UNIVAR	108   	1081        	9230404	NM  										LOWER END	DRAIN PLUGGED   	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	8525K	2456 				1081525				FOUND CONDENSATION DRAIN HOLE PLUGGED RESULTING IN WATER ACCUMULATION IN CONTROL COLUMN (ABOUT ONE-FOURTH CUP OF WATER R	ELEASED WHEN DRAIN HOLE UNPLUGGED).  THIS PROBLEM HAS CAUSED ONE IN-FLIGHT FAILURE RESULTING IN SEVERELY DAMAGED AIRCRAF	T.  THE ALUMINUM PLUG IN THE BOTTOM OF CONTROL COLUMN MUST BE REMOVED TO TREAT AND INSPECT THIS AREA.				1	H	7	1 	3O				A767    					 
1996052300330	19960523	00330		1996	5	23	96ZZZX2576       	4	19960314	G	6122	B20258	DRIVE DISC      	MCAULY      		CESSNA	402   	402C        	207590R	CE  										PROP GOVERNOR	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					771309					INSPECTION OF PROPELLER GOVERNOR FOUND DRIVE DISC CRACKED.						1	L	7	2 	3O				A7CE    					 
1996052300331	19960523	00331	CE  	1996	5	23	96ZZZX2577       	1	19960328	G	3230	98820022	SECTOR GEAR     		24411001    	CESSNA	172   	172RG       	2072438	CE  										LT MLG	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	6461V	3000 				172RG0716				DURING C/W SEB 90-1 AND SUBSEQUENT REASSEMBLY OF MAIN LANDING GEAR ACTUATOR AND PIVOT ASSY, NOTICED THE SECTOR GEARS AND	 THE PIVOT ASSY SHAFT WERE NOT MARKED FOR PROPER ALIGNMENT PER CESSNA SERVICE MANUAL SECTION 5, PARAGRAPH 75, AND FIGURE	 5-12.  THE RT GEAR WAS MARKED AS INDICATED, BUT THE LT GEAR WAS MARKED ON THE BACK SIDE.  ALSO, NEITHER PIVOT ASSY WAS 	MARKED WITH ANY REFERENCE TO THE CORRESPONDING SECTOR GEAR ALIGNMENT.  ASSEMBLIES WERE INSTALLED BY TRIAL AND INSPECTION	.  PROPER OPERATION WAS VERIFIED.		1	H	7	1 	3O				3A17    					 
1996052300332	19960523	00332	CE  	1996	5	23	96ZZZX2578       	1	19960426	G	5711		SPAR            			BEECH 	23    	B19         	1151215	CE  										LT/RT WING	CORRODED        	B			AW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	59BW					MB508				INSPECTION FOUND WING SPARS WITH HEAVY CORROSION AND EXFOLIATION.  SUSPECT CAUSE, SALT INTRUSION.						1	L	7	1 	3O				A1CE    					 
1996052300333	19960523	00333	EA  	1996	5	23	96ZZZX2579       	2	19960402	G	7414	103493704	IMPULSE COUPLER 			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1B5   	41532	EA  					MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	3044K					327940025	960402			MAGNETO SQAWKED AS DEAD.  REMOVED AND DISASSEMBLED MAGNETO, FOUND COIL TAB BENT UPWARD TO MAKE UP FOR THE ERODED CONDITI	ON OF TAB.  TAB HAD COME IN CONTACT WITH METAL AREA OF ROTOR.  WORN THROUGH, GROUNDING MAG.  IMPULSE COUPLING WORN SO BA	DLY AS TO NARROWLY MISS CONTACT WITH STOP POSTS DURING ENGINE RUN MODE.  IMPULSE COUPLING SPRING BROKEN.  THIS MAGNETO H	AS 250 HRS SINCE ENGINE OVERHAUL.  WHILE SERVICING TIRES TO MOVE AIRCRAFT OUT OF HANGAR, NOTED MISSING SCREWS ON LEFT FU	EL TANK.		1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996052300334	19960523	00334	SO  	1996	5	23	96ZZZX2580       	2	19960426	G	8530		CYLINDER        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					ROCKER SHAFT	BOLTS FAILED    	B			FCPR	E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	421CW					421C0137	292087R			ENGINE WAS SHUT DOWN IN-FLIGHT BY PILOT.  FOUND ROCKER SHAFT BOLTS BROKEN, AND BENT PUSH ROD.  VALVES, GUIDES AND PISTON	 WERE INSPECTED.  ALL PARTS FOUND IN GOOD CONDITION.  REINSTALLED CYLINDER AND GROUND RUN.  ALL FOUND GOOD.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996052300709	19960523	00709	SW  	1996	5	23	96ZZZX2581       	1	19960412	G	5321	212030101003	PANEL           			BELL  	212   	212         	1181420	SW  										FUSELAGE	DAMAGED         	H		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										PANEL WAS RECEIVED WITH NO MANUFACTURER'S PART NUMBER OR SERIAL NUMBER TAGS, NOR ANY TRACEABILITY TO A REGISTERED TYPE C	ERTIFICATED AIRCRAFT.  PART APPEARS TO HAVE BEEN REPAIRED OR OVERHAULED, THEN DAMAGED.  PANEL IS COVERED WITH DENTS.  PA	NEL WAS RECEIVED AS AN EXCHANGE CORE FOR HOUSTON HELICOPTERS FROM DODS, INC.				1	G	7	1 	4U				H4SW    					 
1996052300710	19960523	00710	SW  	1996	5	23	96ZZZX2582       	1	19960418	G	6300	M832481235	PACKING         			BELL  	206   	206L3       	1182108	SW  										M/R DRIVE BOOT	WRONG PART      	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	112TV	36   			A810	51123				PACKING LABELED AS M83248-1-235 WERE RECEIVED AND INSTALLED.  BOOT PACKING WAS CUT ON INSTALLATION.  THIS IS CORRECT DIA	METER, BUT SOFTER MATERIAL.  ALSO, INCORRECT PACKING IS BLUE IN COLOR.  SUBMITTER STATED THIS TO BE LIMITED TO HIS P. O.	 ONLY AND HAS ASKED VENDOR TO VERIFY.				1	G	7	1 	3U				H2SW    					 
1996052300711	19960523	00711	NE  	1996	5	23	96ZZZX2583       	1	19960423	G	6420	S6110334061	SPINDLE         			SKRSKY	S61   	S61A        	814210C	NE  										T/R HEAD	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1043T	7313 	283  			61083				SPINDLE WAS FOUND CRACKED IN AREA OF FIRST THREAD.  SPINDLE HAS BEEN SENT TO SIKORSKY AIRCRAFT.						2	G	7	2 	4U				H2EA    					 
1996052300712	19960523	00712	SW  	1996	5	23	96ZZZX2584       	1	19960401	G	5302	206031329103	FITTING         			BELL  	206   	206L1       	1182107	SW  										TB STA 230 BL 28	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	23PJ	4799 				45269				DURING 100-HOUR INSPECTION, TAILBOOM ACCESS PANEL REMOVED FOR FITTING INSPECTION.  AT THIS TIME, THE UPPER LEFT FUSELAGE	 SIDE TAILBOOM ATTACH FITTING WAS DISCOVERED BROKEN.  PILOT REPORTED ON LAST FLIGHT PRIOR TO INSPECTION, MODERATE TO HEA	VY TURBULENCE.				1	G	7	1 	3U				H2SW    					 
1996052300713	19960523	00713	EU  	1996	5	23	96ZZZX2585       	1	19960411	G	6720	704A34130058	CONTROL CABLE   			SNIAS 	350   	AS350B1     	8680811	EU  										T/R	BINDING         	D		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	01	216LA	6584 				2251				PILOT EXPERIENCED BINDING IN T/R PEDALS AND MADE A PRECAUTIONARY RUNNING LANDING.  INSPECTION FOUND BINDING IN TELEFLEX 	CONTROL CABLE.  CABLE WAS REPLACED.					1	G	7	1 	3U			 	H9EU    					 
1996052300714	19960523	00714	GL  	1996	5	23	96ZZZX2586       	2	19960426	G	7313	6898735	TURBINE         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1	NOZZLE FAILED   	H		A		A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	09	3187D	6260 	3284 			1326	CAE833935			DURING CRUISE FLIGHT, TORQUE YAW WAS EXPERIENCED ALONG WITH TOT RISES TO 890 DEGREES CELSIUS.  TORQUE WAS REDUCED TO 60 	PERCENT AND TOT STABILIZED TO 800 DEGREES CELSIUS.  PILOT RETURNED TO OIL PLATFORM WHERE HE SAFELY LANDED.  INSPECTION O	F ENGINE REVEALED NR 1 NOZZLE (ON CONDITION PART) HAD FAILED.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996052300715	19960523	00715	SW  	1996	5	23	96ZZZX2587       	1	19960327	G	5510	NAS464P1027	BOLT            		2040113267  	BELL  	204   	UH1H        	1181407	SW  										STAB BAR	DEFECTIVE       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	398M					6509984				DURING C/W ARMY BULLETIN 95-ASAM-05 ON STABILIZER BAR PIVOT BOLTS, THE NUTS WERE FOUND BOTTOMED OUT ON THE BOLT SHANK. N	EW PARTS IAW ARMY PART MANUAL DID NOT PROPERLY SOLVE THE PROBLEM, HOWEVER, INSTALLATION OF BELL'S COMMERCIAL 205 BOLTS 2	0-057-10S27D AND SPECIAL WASHERS 140-007-41S38C4 WOULD, PROVIDING APPROPRIATE APPROVAL WAS OBTAINED.				1	G	7	1 	4U				EXPA1G71					 
1996052300716	19960523	00716	WP  	1996	5	23	96ZZZX2588       	1	19960323	G	6210	369D26012	ADAPTER SLEEVE  			HUGHES	369   	369E        	4470707	WP  										LT SKID	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	5247S	3849 				0119E				DURING INSPECTION, FOUND LEFT SKID SLEEVE LOOSE.  UPON REMOVAL, NOTED IT WAS SEVERELY CORRODED TO THE POINT OF PENETRATI	ON AND FAILURE OF SLEEVE.  SUBMITTER STATED THIS IS THE SECOND SLEEVE THAT HAS BEEN FOUND IN THIS CONDITION, ON 2 HELICO	PTERS.				1	G	7	1 	3U				H3WE    					 
1996052300717	19960523	00717	WP  	1996	5	23	96ZZZX2589       	1	19960401	G	6210	36921400513	BLADE           			HUGHES	369   	369E        	4470707	WP  										M/R NR 5	DAMAGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	5247S					0119E				DURING A PRE-FLIGHT INSPECTION, A MECHANIC FOUND M/R BLADE LEADING EDGE TORN AND RIPPED ABOUT 2I INCHES FROM THE LEADING	 EDGE ABRASION STRIP.  THE METAL WAS IN THE PROCESS OF PEELING AWAY FROM THE BLADE.  IT WAS DETERMINED THAT FOD CAUSED T	HE INITIAL DENT.  THE FOLLOW BLADE (NR 1) WAS ALSO DENTED.				1	G	7	1 	3U				H3WE    					 
1996052300718	19960523	00718	SW  	1996	5	23	96ZZZX2590       	1	19960416	G	6320	206040037001	BEARING         			BELL  	206   	206L3       	1182108	SW  										XMSN SUN GEAR	SCORED          	B		A	LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	721LL	4669 	2887 		5269	51164				FOUND LOWER MAST ALIGNMENT BEARING BAD WHEN PERFORMING THE SUN GEAR INSPECTION.  TRANSMISSION, S/N BMC 00687.						1	G	7	1 	3U				H2SW    					 
1996052300719	19960523	00719	SW  	1996	5	23	96ZZZX2591       	1	19960503	G	6230	206010454109	SLEEVE ASSY     			BELL  	206   	206B        	1181511	SW  										SWASHPLATE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	82FC	4231 			EA45	2216				DURING A WEEKLY INSPECTION, MECHANIC FOUND THE SWASHPLATE SLEEVE UNIBALL CRACKED AT THE COLLECTIVE LEVER BEARING.  REMOV	ED SWASHPLATE ASSY, PN 206-010-450-113, SN EAJG-111249, TT 4,230.7 HRS TSO.  TSN AIRCRAFT TT, 8,304.5 HRS.  INSTALLED SE	RVICEABLE SWASHPLATE ASSY, PN 206-010-450-113, SN GDJD-90286, TT, 7,701.1 HRS, TSO 2,919.1 HRS AT AIRCRAFT TT, 8,304.5 H	RS.  ALL WORK DONE IAW 206B MM.			1	G	7	1 	3U				H2SW    					 
1996052300720	19960523	00720	SW  	1996	5	23	96ZZZX2592       	1	19960503	G	2550	206072903001	RELEASE CABLE   			BELL  	206   	206B        	1181511	SW  										CARGO HOOK	KINKED          	B		A	GJQR	O				OTHER                   				O			OTHER                     			EX	EXTERNAL LOAD  	1			NM	01	86W	2633 				4142				ENCOUNTERED AN UNEXPECTED CARGO HOOK RELEASE, DROPPING THE LOAD.  INVESTIGATION REVEALED CABLE KINKED ABOUT 3 INCHES FRO	M HOOK FRAME DISCONNECT RESTRICTING THE HOOK LOAD BEAM FROM LOCKING IN CLOSED POSITION.  AS KINKED AREA ENTERS HOUSING, 	IT RESTRICTS HOOK FROM LATCHING.  SUBMITTER RECOMMENDS OPERATORS AND MECHANICS BE AWARE OF NEED FOR SMOOTH OPERATION OF 	CABLE WITHIN HOUSING WITH NO RESTRICTIVE KINKS IN CABLE.			1	G	7	1 	3U				H2SW    					 
1996052300721	19960523	00721	NE  	1996	5	23	96ZZZX2593       	2	19960304	G	7250	0292507640	COVER           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MODULE 3	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	869AC	518  				1695	652			ENGINE NOISE DURING START-UP AND SHUT-DOWN.  REMOVED AND DISASSEMBLED MO5, 4, AND 3.  FOUND COVER AND DEFLECTOR BROKEN A	ND RUBBING ON MO4 TURBINE DISC.  THIS IS 2ND TIME THIS ENGINE SERIAL NUMBER HAS HAD A COVER AND DEFLECTOR BROKEN.  SUBMI	TTER SUGGESTS A DIFFERENT STYLE COVER AND DEFLECTOR ABLE TO WITHSTAND ENGINE HEAT AND NORMAL VIBRATION LEVELS.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1996052300722	19960523	00722	NE  	1996	5	23	96ZZZX2594       	2	19960304	G	7250	0292502390	DEFLECTOR       			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MODULE 3	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	869AC	518  				1695	652			ENGINE NOISE DURING START-UP AND SHUT DOWN.  REMOVED AND DISASSEMBLED MO5, 4, AND 3.  FOUND COVER AND DEFLECTOR BROKEN A	ND RUBBING ON MO4 TURBINE DISC.  THIS IS 2ND TIME THIS ENGINE SERIAL NUMBER HAS HAD A COVER AND DEFLECTOR BROKEN.  SUBMI	TTER SUGGESTS A DIFFERENT STYLE COVER AND DEFLECTOR ABLE TO WITHSTAND ENGINE HEAT AND NORMAL VIBRATION LEVELS.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1996052300723	19960523	00723	GL  	1996	5	23	96ZZZX2595       	2	19960424	G	7230	A23034784	GEARSHAFT RACE  		6890550     	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					SPUR ADAPTER	SPALLED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	205LF	489  			010	S146				THE RACE OF THIS SPUR ADAPTER GEARSHAFT SUPPORTS THE TWO AND ONE-HALF BEARING.  THE TWO AND ONE-HALF BEARING CAGE FAILED	 SPALLING THE RACE.  THIS GEARSHAFT DRIVES THE TURBINE AND COMPRESSOR.  THIS IS AN FAA PMA PART MFG BY SUPERIOR PARTS.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996052300724	19960523	00724	WP  	1996	5	23	96ZZZX2596       	1	19960412	G	6320	369D25100501	TRANSMISSION    			HUGHES	369   	369D        	4470706	WP  										M/R	LEAKING         	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	5074R	6030 	2030 		40296	1151D				REMOVED MAIN ROTOR TRANSMISSION FOR LEAKY INPUT SEAL.  THIS IS THE SECOND TIME IN 102.8 HOURS THIS HAS BEEN DONE.  SUBMI	TTER STATED THIS IS NOT AN ISOLATED INCIDENT EITHER.					1	G	7	1 	3U				H3WE    					 
1996052300725	19960523	00725	GL  	1996	5	23	96ZZZX2597       	2	19960307	G	7323	23007506	GOVERNOR        	BENDIX      		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					INPUT LEVER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	211WP		509  		6740	3225	CAE833581			DURING A DAILY INSPECTION, MECHANIC FOUND GOVERNOR WITH .75 INCH CRACK AT AREA OF INPUT LEVER BUSHING.  GOVERNOR WAS REM	OVED AND REPLACED.  THESE GOVERNORS HAVE A 2,000-HOUR OVERHAUL.  ENGINE HAD BEEN OPERATING NORMALLY.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996052300726	19960523	00726	GL  	1996	5	23	96ZZZX2598       	2	19960410	G	7261	206075659001	TUBE ASSY       			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE OIL	CHAFED          	B			PN5R	A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	03	617DE	6133 				51138	895179			FREEWHEEL RETURN HOSE CHAFED THROUGH ENGINE OIL PRESSURE TUBE CAUSING OIL TO LEAK ONTO DECK.  PRECAUTIONARY LANDING MADE	, LINE REPLACED AND RETURNED AIRCRAFT TO SERVICE.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1996052300727	19960523	00727	SW  	1996	5	23	96ZZZX2599       	1	19960227	G	2821	222366621101	FILTER          			BELL  	206   	206B        	1181511	SW  										FUEL SYSTEM	DEFECTIVE       	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	09	67939					5228				PRECAUTIONARY LANDING DUE TO FUEL FILTER CAUTION/WARNING LIGHT ILLUMINATED.						1	G	7	1 	3U				H2SW    					 
1996052300728	19960523	00728	SW  	1996	5	23	96ZZZX2600       	1	19960213	G	2121	JBS2761	FAN ASSY        			BELL  	206   	206B        	1181511	SW  										INST PANEL	FAILED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	09	67606					5177				PRECAUTIONARY LANDING DUE TO SMOKE COMING FROM BEHIND INSTRUMENT PANEL.  FOUND FAN ASSY FAILED.						1	G	7	1 	3U				H2SW    					 
1996052300729	19960523	00729	SW  	1996	5	23	96ZZZX2601       	1	19960224	G	6322	476205302	GEAR            		47620160027 	BELL  	47    	47J2A       	1181106	SW  										FAN DRIVE	MAKING METAL    	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	13	8552F	3102 	404  		B12298	3705				THE ENGINE CHIP LIGHT CAME ON IN-FLIGHT TWICE.  EACH TIME THE OIL SCREEN HAD ALUMINUM AND SOME STEEL.  AN INVESIGATION F	OUND THE PULLEY ON THE FAN DRIVE QUILL MOVING IN AND OUT .25 INCH.  UPON REMOVAL OF QUILL FROM THE TRANSMISSION, 2 BROKE	N TEETH FROM THE GEAR AND SHAVED ALUMINUM FROM THE TRANSMISSION WERE NOTED.  SUSPECT CAUSE IS AN IMPROPERLY TORQUED NUT 	47-620565-1 WHICH ALLOWED GEARSHAFT TO MOVE.  RECOMMEND INSTALLER INSURE PROPER TORQUE AND SAFETY.			1	G	7	1 	3O				2H1     					 
1996052300730	19960523	00730	EU  	1996	5	23	96ZZZX2602       	1	19960405	G	2150	JBS30011	MOUNT           			BOLKMS	BK117 	BK117C1     	5626025	EU  										AC EVAP COIL	FLANGE CRACKED  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	911TG	381  				7506				FORWARD AND REAR MOUNT BRACKETS CRACKED DUE TO VIBRATION AND SB 133-1 HAD NOT BEEN ISSUED YET AND HAD NOT BEEN C/W AT TH	E TIME.  INSTALLED NEW COIL ASSY, PN JBS3001-3, AND C/W SIB 133-1.					1	G	7	2 	3U			NC	H13EU   					 
1996052300731	19960523	00731	NE  	1996	5	23	96ZZZX2603       	1	19960401	G	6410	7610105101041	TAIL ROTOR ASSY 			SKRSKY	S76   	S76         	8143010	NE  										TIP WEIGHT	SEPARATION      	B			RW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	CG1MR	5408 			A13700212					SEPARATION BETWEEN TIP WEIGHT SUPPORT BLOCK AND BLADE SKIN.  RECOMMEND ALL IN SERVICE BLADES BE INSPECTED FOR DEBONDING 	OF TIP WEIGHT CHAMBER.					1	G	7	2 	3U				H1NE    					 
1996052300732	19960523	00732	NE  	1996	5	23	96ZZZX2604       	1	19960401	G	6410	7610105101041	TAIL ROTOR ASSY 			SKRSKY	S76   	S76         	8143010	NE  										TIP WEIGHT	SEPARATION      	B			RW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	PTHOR	7938 			A13700151					SEPARATION BETWEEN TIP WEIGHT SUPPORT BLOCK AND BLADE SKIN.  RECOMMEND ALL IN SERVICE BLADES BE INSPECTED FOR DEBONDING 	OF TIP WEIGHT CHAMBER.					1	G	7	2 	3U				H1NE    					 
1996052300733	19960523	00733	SW  	1996	5	23	96ZZZX2605       	1	19960425	G	3340	A469B	BULB            		A470        	BELL  	206   	206L1       	1182107	SW  										STROBE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2611					45417				ON DAILY AIRWORTHY INSPECTION, FOUND STROBE LIGHT BULB BURNED OUT.  HAD REPLACED BULB LAST WEEK.  CAUSE OF PROBLEM UNKNO	WN AT THIS TIME.					1	G	7	1 	3U				H2SW    					 
1996052300734	19960523	00734	GL  	1996	5	23	96ZZZX2606       	2	19960315	G	7261	23057790	SEAL            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					OIL JET	LEAK            	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			SO	09		381  					CAC42587			UPON LANDING FOR STUDENT CHANGE, SMOKE WAS SEEN COMING FROM ENGINE COMPARTMENT.  REPLACED NR 6 AND NR 7 ENGINE OIL JET S	EAL.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996052300735	19960523	00735	GL  	1996	5	23	96ZZZX2607       	2	19960424	G	7230	A23034787	BEARING         		6894171     	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE GRBX	FAILED          	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CE	03	205LF	489  			034	S146	831080			PART IS AN FAA PMA BEARING.  BEARING CAGE CAME APART CAUSING 'CHIP' LIGHT.  BEARING FAILURE ALSO CAUSED SPALLING OF THE 	INNER RACE ON SPUR ADAPTER GEARSHAFT.  THIS GEARSHAFT COUPLES (DRIVES) TURBINE AND COMPRESSOR.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996052300736	19960523	00736	WP  	1996	5	23	96ZZZX2608       	1	19960411	G	3213	369H600151	STRUT           			HUGHES	369   	369D        	4470706	WP  										BRACE ATTACH	FAILED          	D	S	A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	13	8625F					470111D				AFTER LANDING, PILOT LOWERED COLLECTIVE, AIRCRAFT SETTLED AND SHORTLY AFTER, AFT LEFT LANDING GEAR STRUT FAILED SLOWLY S	ETTLING UNTIL STRINGER CONTACTED THE GROUND.  UPON FURTHER INVESTIGATION A CRACK WAS FOUND EMANATING FROM THE BRACE TO S	TRUT ATTACHING BOLT HOLE.				1	G	7	1 	3U				H3WE    					 
1996052300741	19960523	00741	CE  	1996	5	23	96ZZZX2613       	1	19960508	G	7603	C800791	BALL JOINT      			BEECH 	2000  	2000        	1152000	CE  										LT ENG THROTTLE	DETACHED        	D		A		E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	8244L	1364 				NC29				THROTTLE BALL SWIVEL HAD BACKED OFF FROM THREADED ROD END ON CABLE END.  SWEDGE STAKES HAD COME LOOSE ALLOWING ROD TO BA	CK OFF AND DISENGAGE THROTTLE.  PILOT SHUT ENGINE OFF.  ALL NORMAL, LANDING, ETC.  SUBMITTER SUGGESTS EITHER DRILLING HO	LE CLOSE TO SWIVEL END FOR SAFETY WIRE OR POSSIBLY PINNING LOWER ASSY WITH COTTER PIN.				1	L	7	2 	4T			RT	A38ACE  					 
1996052300743	19960523	00743	NE  	1996	5	23	96ZZZX2615       	2	19960402	G	7321	32448512	FUEL CONTROL    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NR 1 ENGINE	DEFECTIVE       	H	L			O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	502T	3281 			B29352	5600153	108317			FOLLOWING POWER REDUCTION FOR DESCENT, WHEN THROTTLE ADVANCED, NO ENGINE RESPONSE.  SELECTED ANTI-ICE OFF AND ENGINE RES	PONSE INCREASED TO NORMAL OPERATION.  SERVICE CENTER REPLACED BOTH ENGINE FUEL CONTROLS.  TEST FLIGHT, ENGINE OPERATED, 	NORMAL AT ALL ALTITUDES.				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
1996052300744	19960523	00744	NE  	1996	5	23	96ZZZX2616       	2	19960402	G	7321	32448512	FUEL CONTROL    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					NR 2 ENGINE	DEFECTIVE       	H	L			O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	502T	3281 			B29358	5600153	108316			FOLLOWING POWER REDUCTION FOR DESCENT, WHEN THROTTLE ADVANCED, NO ENGINE RESPONSE.  SELECTED ANTI-ICE OFF AND ENGINE RES	PONSE INCREASED TO NORMAL OPERATION.  SERVICE CENTER REPLACED BOTH ENGINE FUEL CONTROLS.  TEST FLIGHT, ENGINE OPERATED, 	NORMAL AT ALL ALTITUDES.				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
1996052300745	19960523	00745	SO  	1996	5	23	96ZZZX2617       	1	19960515	G	2731	430838182	TORQUE TUBE     			GULSTM	G1159 	GIV         	3980115	SO  										ELEVATOR TRIM	DEFECTIVE       	B		A	JU2R	O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CR	CRUISE         	1			GL	23	300K	215  				1266				ELEVATOR TRIM RAN TO FULL NOSE UP INDICATION AT FL 43,000 FEET, WITH NO MANUAL CONTROL OF THE ELEVATOR TRIM.  UPON INVES	TIGATION, FOUND TWO RIVETS WERE NOT INSTALLED DURING PRODUCTION IN THE ELEVATOR TRIM TORQUE TUBE ASSY LOWER UNIVERSAL TO	 DRIVE ADAPTER.  THIS ALLOWED THE SHAFT TO TURN INSIDE THE SHAFT, BUT NOT THE ELEVATOR CABLE DRUM.				2	L	7	2 	4F			RT	A12EA   					 
1996052300746	19960523	00746	WP  	1996	5	23	96ZZZX2618       	1	19960426	G	5313	2597242318000	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 26 RT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CORROSION LEVEL 2 AT LONGERON 26 RT BETWEEN FS 208.00 TO FS 270.00.  REMOVED AND REPLACED LONGERON	.					2	L	7	4 	4F				4A25    					 
1996052300747	19960523	00747	WP  	1996	5	23	96ZZZX2619       	1	19960426	G	5313	2597242318000	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 25 RT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CORROSION LEVEL 2 AT LONGERON 25 RT BETWEEN FS 208.00 AND FS 270.00.  REMOVED AND REPLACED LONGERO	N IAW SRM 53-2-0, SRM 51-1-21, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996052300748	19960523	00748	WP  	1996	5	23	96ZZZX2620       	1	19960426	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										CARGO COMP DOOR	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEVEL 2 CORROSION AT AFT CARGO COMPARTMENT DOOR.  REPAIRED IAW SRM 51-1-8, SRM 53-2-0, AND SRM 52-	2-0.					2	L	7	4 	4F				4A25    					 
1996052300749	19960523	00749	WP  	1996	5	23	96ZZZX2621       	1	19960426	G	5320		FINGER DOUBLER  			DOUG  	DC8   	DC862       	3021970	WP  										COCKPIT FS 188	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CORROSION ON COCKPIT SUB-FLOOR BEAM FS 188.00 TO FS 208.00.  REPAIRED IAW DER DRAWING 950087-0083,	 JOSSIAR, CO.					2	L	7	4 	4F				4A25    					 
1996052300750	19960523	00750	WP  	1996	5	23	96ZZZX2622       	1	19960426	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 208 L29	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE SKIN WITH CORROSION FUSELAGE STA 208.00 BETWEEN L29 AND L31.  REMOVED CORROSION, REPAIRED	 IAW E.O. NR 961ALE.005D-7.					2	L	7	4 	4F				4A25    					 
1996052300751	19960523	00751	WP  	1996	5	23	96ZZZX2623       	1	19960426	G	5730		PANEL           			DOUG  	DC8   	DC862       	3021970	WP  										LT WING TRAP	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				ITEM NR 1080.  LEFT WING TOP TRAPEZOID PANEL CORRODED.  FABRICATED AND INSTALLED NEW PANEL PER DER DRAWING A/R/W/ 950051	-0203 AND SRM 51-1-20.					2	L	7	4 	4F				4A25    					 
1996052300752	19960523	00752	WP  	1996	5	23	96ZZZX2624       	1	19960426	G	5320		CIRCUMFERENTIAL 			DOUG  	DC8   	DC862       	3021970	WP  										FUSELAGE	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CIRCUMFERENTIAL LEVEL 2 CORROSION.  CUT OUT DAMAGED AREA FABRICATED FROM 7075T6.  INSTALLED NEW SE	CTION IAW 53-2-5 AND 51-1-21, 51-3-0.					2	L	7	4 	4F				4A25    					 
1996052300753	19960523	00753	WP  	1996	5	23	96ZZZX2625       	1	19960426	G	5311	56119433N	FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										FS 270 RT L36	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE RT SIDE STRUCTURAL FRAME STA 270 HAS CORROSION FROM L21R TO L36R.  INSTALLED NEW SECTION 	OF FRAME AT FS 270 FROM L21R TO L36R IAW SRM 53-2-5, FIGURE 8C-2, AND SRM 51-1-21, SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996052300754	19960523	00754	WP  	1996	5	23	96ZZZX2626       	1	19960426	G	5320		DOUBLER         			DOUG  	DC8   	DC862       	3021970	WP  										FS 188-209 L24R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK FUSELAGE RT SIDE, STRUCTURAL DOUBLER HAS CORROSION AROUND IT, BETWEEN FS 188 TO FS 208 AND BETWEEN L24R A	ND L28R.  REMOVED DOUBLER WITH CORROSION, FABRICATED NEW DOUBLER FROM 7075-T6 .065 INCH.  TREATED AND PRIMED IAW SRM 51-	1-8.  INSTALLED DOUBLER IAW SRM 51-1-21.				2	L	7	4 	4F				4A25    					 
1996052300755	19960523	00755	WP  	1996	5	23	96ZZZX2627       	1	19960426	G	5210		DOUBLER         			DOUG  	DC8   	DC862       	3021970	WP  										DOOR NR 60	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					47070				DURING C-CHECK, FOUND DOUBLER AROUND DOOR NR 60 IS EXFOLIATED.  REMOVED DOUBLER, FABRICATED NEW ONE IAW SRM 53-1-0 AND S	RM 53-5-2, FIGURE 1.  TREATED AND PRIMED IAW SRM 51-1-8 AND INSTALLED IAW SRM 51-1-21.					2	L	7	4 	4F				4A25    					 
1996052300756	19960523	00756	WP  	1996	5	23	96ZZZX2628       	1	19960426	G	5530		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FREON EXH DOOR	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE SKIN BELOW FREON EXHAUST DOOR HAS WORKING FASTENERS, LT SIDE.  REMOVED INTERCOSTAL, FABRI	CATED NEW INTERCOSTAL, CLEANED CORROSION IN AREA, FOUND WITHIN LIMITS.  TREATED AND PRIMED AREA AND INTERCOSTAL IAW SRM 	51-1-8.  INSTALLED REPAIR IAW SRM 51-1-8, SRM 53-3-2, SRM 51-1-21, AND SRM 51-1-20D.  REF:  OPERATOR CONTROL NR 0248.				2	L	7	4 	4F				4A25    					 
1996052300757	19960523	00757	WP  	1996	5	23	96ZZZX2629       	1	19960426	G	5532		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										VERT STAB LE	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969V					46070				DURING C-CHECK, FOUND VERTICAL STABILIZER, L/E CORRODED AT APPROXIMATELY STA 179.750.  CUT OUT DAMAGED SECTION AND REPAI	RED IAW SRM 55-2-1, TREATED AND PRIMED IAW 51-1-8.  SEALED AREA IAW SRM 51-1-16.  REF:  OPERATOR CONTROL NR 1707.					2	L	7	4 	4F				4A25    					 
1996052300758	19960523	00758	WP  	1996	5	23	96ZZZX2630       	1	19960426	G	5532		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										VERTICAL FIN	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND VERTICAL FIN, RT FORWARD EDGE WITH CORROSION ON SKIN AND SCREWS.  REMOVED DAMAGED AREA AND FABRICA	TED DOUBLER PER SRM 53-2-1.  INSTALLED DOUBLER PER SRM 53-2-1.  REF:  OPERATOR CONTROL NR 0683.					2	L	7	4 	4F				4A25    					 
1996052300759	19960523	00759	WP  	1996	5	23	96ZZZX2631       	1	19960503	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										XRS 107-189	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK FOUND RT UPPER WING SURFACE HAS SEVERAL AREAS WITH CORROSION.  AREAS ARE BETWEEN STA XRS 107.000 AND XRS 	139.000, AT REAR SPAR APPROXIMATELY (DOT-6022).  REMOVED CORROSION, FOUND AREA OUT OF LIMITS.  REPAIRED AREA IAW DER NR 	961ALE.005D-2.  REF:  OPERATOR CONTROL NR 07068.				2	L	7	4 	4F				4A25    					 
1996052300760	19960523	00760	WP  	1996	5	23	96ZZZX2632       	1	19960426	G	5313	S2641455	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 27 RT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CORROSION LEVEL 2 AT LONGERON 27 RT BETWEEN FS 208.00 TO FS 270.00.  REMOVED AND REPLACED LONGERON	 IAW 53-2-0, SRM 51-1-21, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996052300761	19960523	00761	WP  	1996	5	23	96ZZZX2633       	1	19960426	G	5311		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										FS 270 L28R-L29R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FORWARD CARGO COMPARTMENT AREA RT SIDE AT FRAME/STA 270 AND BETWEEN L28R AND L29R.  FRAME HAS LOCA	L CORROSION.  FOUND CORROSION BEYOND LIMITS.  CUT OUT CORRODED AREA, FABRICATED NEW FRAME SECTION AND EXTERNAL DOUBLER S	TRAP IAW SRM 52-2-5, FIGURE 8C-2.				2	L	7	4 	4F				4A25    					 
1996052300762	19960523	00762	WP  	1996	5	23	96ZZZX2634       	1	19960426	G	5311		BULKHEAD        			DOUG  	DC8   	DC862       	3021970	WP  										LONGERON 10R WEB	CRACKED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				WEB IS CRACKED, AFT SIDE OF FLAT AFT PRESSURE BULKHEAD AT LONGERON 10R, INSTALLED DOUBLERS AND FILLER IAW SRM 53-2-5 AND	 SRM 51-1-20.					2	L	7	4 	4F				4A25    					 
1996052300763	19960523	00763	WP  	1996	5	23	96ZZZX2635       	1	19960426	G	5320		DOUBLER         			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 L31R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AIR CONDITIONING COMPARTMENT INTERNAL DOUBLER LOCATED BETWEEN FS 208 AND FS 270 AT L31R WITH A WID	E SPREAD.  REMOVED INTERNAL DOUBLER, FABRICATED AND INSTALLED NEW DOUBLER IAW DAC DRAWING NR 5613862 AND SRM 51-1-21 AND	 SRM 51-1-20D.				2	L	7	4 	4F				4A25    					 
1996052300764	19960523	00764	WP  	1996	5	23	96ZZZX2636       	1	19960426	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FWD LAV AREA	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FORWARD LAVATORY WASTE DISPOSAL SERVICE AREA SKIN AROUND SERVICE NIPPLE WITH EXFOLIATION CORROSION	.  REMOVED INTERNAL PANEL.  FABRICATED NEW INTERNAL PANEL PLATE IAW SRM 53-2-0.  TREATED AND PRIMED IAW SRM 51-1-8.  INS	TALLED IAW SRM 51-1-14.				2	L	7	4 	4F				4A25    					 
1996052300765	19960523	00765	WP  	1996	5	23	96ZZZX2637       	1	19960426	G	5312	5772638103	BULKHEAD        			DOUG  	DC8   	DC862       	3021970	WP  										RBL 7-RBL 15	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND SKIN HAS CORROSION LEVEL 2 AT AFT BULKHEAD WALL FORWARD SIDE FLOOR LEVEL, RBL 7 INCHES AND RBL 15 	INCHES.  REPAIRED IAW DACO ACTION NR 291159.					2	L	7	4 	4F				4A25    					 
1996053000001	19960530	00001	CE  	1996	5	30	96ZZZX2638       	1	19960507	G	2913	PF24390615BCE	PUMP            			RKWELL	NA265 	NA26540     	6402608	CE  											SEAL FAILED     	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	16	303NT				X347724	282029				PUMP WAS INSTALLED, TEST RUN FOR 30 SECONDS, AND REMOVED WITH ZERO HOURS TIME IN SERVICE SINCE OVERHAUL.  PUMP WAS REMOV	ED DUE TO SHAFT SEAL FAILED WHICH PUMPED FLUID OUT THROUGH THE CASE DRAIN AND CONTAMINATED THE DRIVE MOTOR.  PUMP WAS OV	ERHAULED ON 1-19-96.  AIRCRAFT TOTAL TIME:  10,462. HRS.				2	L	7	2 	4J				A2WE    					 
1996053000002	19960530	00002	CE  	1996	5	30	96ZZZX2639       	1	19960401	G	2750	556517531	GEARBOX         			CESSNA	500   	500CESSNA   	2076602	CE  										FLAP	GEAR STRIPPED   	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	10UH		117  		052893	5000304				FLAP GEARBOX, GEARS STRIP OUT AFTER 100 HOURS TO 200 HOURS.  SUBMITTER STATES ONGOING PROBLEM.  LANDINGS, 209.						1	L	7	2 	4F				A22CE   					 
1996053000003	19960530	00003	CE  	1996	5	30	96ZZZX2640       	1	19960401	G	2750	556517531	GEARBOX         			CESSNA	500   	500CESSNA   	2076602	CE  										FLAP	GEAR STRIPPED   	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	10UH		117  		PAL037	5000304				FLAP GEARBOX, GEARS STRIP OUT AFTER 100 HOURS TO 200 HOURS.  SUBMITTER STATES ONGOING PROBLEM.  LANDINGS, 2O9.						1	L	7	2 	4F				A22CE   					 
1996053000004	19960530	00004	CE  	1996	5	30	96ZZZX2641       	1	19960430	G	2150	206S22C	BEARING         			BEECH 	200   	200BEECH    	1152920	CE  										AC COMP DRV	SEIZED          	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	200BE	6011 				BB832				THE FORWARD SEALED BEARING ON THE AIR CONDITIONER COMPRESSOR DRIVE SEIZED AND CAUSED THE QUILL SHAFT TO SHEAR.						1	L	7	2 	4T				A24CE   					 
1996053000005	19960530	00005	EU  	1996	5	30	96ZZZX2642       	1	19960501	G	3213	253505202	STRUT           			ISRAEL	1124  	1124        	4500102	EU  										RT MLG	CORRODED        	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	789TE	5660 				241				RT MLG TRUNNION WOULD NOT TAKE GREASE.  TRIED UNSUCCESSFULLY TO REMOVE TRUNNION PIN.  PIN HAD TO BE CUT TO FACILITATE RE	MOVAL.  REPLACED UPPER BODY OF MLG, PIN, AND BUSHINGS DUE TO CORROSION.  SUBMITTER STATED 2ND AIRCRAFT THIS YEAR WITH SA	ME PROBLEM.  REF:  OPERATOR CONTROL NR 9601.				2	M	7	2 	4F				A2SW    					 
1996053000006	19960530	00006	EU  	1996	5	30	96ZZZX2643       	1	19960501	G	3213	139862ED	TRUNNION PIN    			ISRAEL	1124  	1124        	4500102	EU  										UPPER MLG	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	789TE	5660 			130972ED	241				RT MLG TRUNNION WOULD NOT TAKE GREASE.  TRIED UNSUCCESSFULLY TO REMOVE TRUNNION PIN.  PIN HAD TO BE CUT TO FACILITATE RE	MOVAL.  REPLACED UPPER BODY OF MLG, PIN, AND BUSHINGS DUE TO CORROSION.  SUBMITTER STATED 2ND AIRCRAFT THIS YEAR WITH SA	ME PROBLEM.  REF:  OPERATOR CONTROL NR 9601.				2	M	7	2 	4F				A2SW    					 
1996053000007	19960530	00007	CE  	1996	5	30	96ZZZX2644       	1	19960426	G	3260	MS244201	SWITCH          			BEECH 	MU300 	400BEECH    		CE  										LT MLG DOOR	INOPERATIVE     	B			OG5R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	21	3038V	377  				RK93				LANDING GEAR FAILED TO EXTEND.  FOUND LANDING GEAR DOOR OPEN SWITCH (LEFT) DEFECTIVE.  PERFORMED GEAR FREEFALL.  THIS IS	 SECOND OCCURRENCE OF LEFT SWITCH ON THIS AIRCRAFT.  PREVIOUS FAILURE AT ACFT TT, 1,096.5 HRS.  CURRENT ACFT TT, 1,473.3	 HRS.  VENDOR P/N 41EN106.				2	H	7	2 	4F			RT	A16SW   					 
1996053000008	19960530	00008	CE  	1996	5	30	96ZZZX2645       	1	19960427	G	3260	MS243311	SWITCH          			BEECH 	MU300 	400BEECH    		CE  										LT MLG	FAILED          	B			OG5R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	21	3196N	866  				RK96				AIRCRAFT HAD REPETITIVE GEAR UNSAFE INDICATIONS.  FOUND LEFT GEAR DOWN INDICATOR SWITCH FAULTY.  INSTALLED NEW SWITCH. T	HIS IS SECOND SWITCH TO FAIL.  FIRST FAILURE OCCURRED AT AIRCRAFT TT, 535.1 HRS.  AIRCRAFT TT, 1,397.4 HRS.					2	H	7	2 	4F			RT	A16SW   					 
1996053000009	19960530	00009	NE  	1996	5	30	96ZZZX2646       	2	19960422	G	8520	11768	CAM             			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	CRACKED         	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SO	09	36503					3010258	39831			ENGINE RAN ROUGH AND BACK-FIRED CAUSING THE PILOT TO MAKE AN EMERGENCY LANDING.  THE ENGINE (FRONT) WAS DISASSEMBLED FIN	DING THE CAM CRACKED.					1	L	7	1 	3R	3	R		A9SW    	5E2				 
1996053000011	19960530	00011	SO  	1996	5	30	96ZZZX2648       	2	19960514	G	8530	653445	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					PLUG BOSS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1847F	1019 				TH1291	298505R			THE CONTINENTAL STEEL CYLINDER CRACKED FROM THE SPARK PLUG BOSS TO THE AREA BEHIND THE FUEL NOZZLE.  THE CYLINDER HAD A 	TOTAL TIME OF ONLY 1,019.0 HRS.  THE CYLINDER STILL HELD GOOD COMPRESSION, BUT WITH A SOAP CHECK, THE AIR LEAK WAS EVIDE	NT.  SUBMITTER STATES HAVE BEEN HAVING A SERIOUS PROBLEM WITH CYLINDERS CRACKING IN THIS POSITION.  BELIEVE THIS IS A SE	RIOUS PROBLEM AND SHOULD BE INVESTIGATED FURTHER.			1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996053000012	19960530	00012	CE  	1996	5	30	96ZZZX2649       	1	19960402	G	3040	53032ARX	SOLENOID        			CESSNA	441   	441         	2076020	CE  										WIPER/DEICE	STUCK           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	90GC				1584	44100889				WIPER/DEICE SOLENOID STUCK.  CYCLED UNIT 2 TIMES, UNIT STUCK IN OPEN POSITION.  SOLENOID FAILED AFTER 2 TIMES.  UNIT WOU	LD RESET AFTER PRESSURE WAS OFF.  SUBMITTER STATED NEWLY OVERHAULED UNIT.					1	L	7	2 	3T			RT	A28CE   					 
1996053000013	19960530	00013	CE  	1996	5	30	96ZZZX2650       	1	19960402	G	3040	53032ARX	SOLENOID        			CESSNA	441   	441         	2076020	CE  										WIPER/DEICE	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	90GC	228  			1420	4410089				WIPER/DEICE SOLENOID UNIT FAILED STUCK OPEN.						1	L	7	2 	3T			RT	A28CE   					 
1996053000014	19960530	00014	CE  	1996	5	30	96ZZZX2651       	1	19960402	G	3040	53032ARX	SOLENOID        			CESSNA	441   	441         	2076020	CE  										WIPER/DEICE	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	90GC	22   			0334	4410089				WIPER/DEICE SOLENOID FAILED STUCK OPEN.						1	L	7	2 	3T			RT	A28CE   					 
1996053000015	19960530	00015	CE  	1996	5	30	96ZZZX2652       	1	19960402	G	3040	53032ARX	SOLENOID        			CESSNA	441   	441         	2076020	CE  										WIPER/DEICE	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	90GC	28   			0966	4410089				WIPER/DEICE SOLENOID FAILED STUCK OPEN.						1	L	7	2 	3T			RT	A28CE   					 
1996053000016	19960530	00016	SO  	1996	5	30	96ZZZX2653       	1	19960410	G	3231	3147100	LINKAGE         			PIPER 	PA23  	PA23250     	7102308	SO  										LT MLG DOOR	DISCONNECTED    	G		A		O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SW	99	2337M	8185 				277954042				LEFT GEAR DOOR CONNECTOR LINKAGE BECAME DISCONNECTED PREVENTING DOOR FROM OPENING.  GEAR-UP LANDING RESULTED.  CLEVIS PI	N HAD BECOME DISENGAGED FROM LINKAGE.  THE PIPER INSPECTION REPORT DOES NOT SPECIFY THIS AREA, AND THE GEAR DOOR LINKAGE	 PINS ARE DIFFUCLT TO SEE.  INSPECTION REPORT SHOULD BE AMMENDED TO SPECIFICALLY INCLUDE THESE CLEVIS PINS FOR SAFETY AN	D SECURITY.			1	L	7	2 	3O				1A10    					 
1996053000017	19960530	00017	SO  	1996	5	30	96ZZZX2654       	1	19960406	G	5720	62086005	STIFFENER       			PIPER 	PA28  	PA28161     	7102803	SO  										INBD RT WING	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	84400	6697 				288216004				LOWER RIGHT INBOARD SKIN STIFFENER AT REAR OF WING FOUND CRACKED.						1	L	7	1 	3O				2A13    					 
1996053000018	19960530	00018		1996	5	30	96ZZZX2655       	1	19960501	G	2822	1C610	PUMP            	AIRBORNE    																FUEL	WATER CONTAM    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13			10   		12W1828					INSPECTION FOUND FUEL PUMP FULL OF WATER AND RUST.																			 
1996053000019	19960530	00019	SO  	1996	5	30	96ZZZX2656       	1	19960430	G	8120		CLAMP           			PIPER 	PA46  	PA46310P    	7104605	SO  										INTERCOOLER	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	03	4384T					468508028				HOSE CLAMP SECURING SONIC TUBE SCAT AT INTERCOOLER FAILED CAUSING LOSS OF 5 INCHES OF MANIFOLD PRESSURE ON TAKEOFF.  CLA	MP NOT FOUND (AREA DIRECTLY OVER COWL OPENING - PRESUMED LOST IN-FLIGHT).					1	L	7	1 	3O				A25SO   					 
1996053000020	19960530	00020	NE  	1996	5	30	96ZZZX2657       	2	19960502	G	8500		ENGINE          			BEECH 	18    	RC45J       	1151021	CE  	PWA   	R985  	R985*       	52008	NE  					RT WHEELWELL	FIRE            	D				O				OTHER                   				A			FLAME/FIRE                			LD	LANDING        	1			SO	19	64819					523762	JP1956			FIRE IN RIGHT WHEELWELL DURING LANDING.  WHILE LANDING, TOWER INFORMED THE PILOT THERE WAS FIRE COMING OUT OF WHAT APPEA	RED TO BE THE RIGHT ENGINE.  AT THIS POINT, THE CAUSE OF THE FIRE HAS NOT BEEN DETERMINED AND IS UNDER IVNESTIGATION BY 	THE NTSB AND THE FAA.				1	L	7	2 	3R	3	R		A765    	5E1				 
1996053000021	19960530	00021	EA  	1996	5	30	96ZZZX2658       	2	19960507	G	8530	SL14995	SPRING          		LW12427     						LYC   	O360  	LO360A1G6   	41514	EA  					NR 4 PUSH ROD	BROKEN          	B			ZM3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07							L26771A			ENGINE WAS ASSEMBLED AND TEST CELL RUN 1-24-96.  ENGINE WAS NOT INSTALLED UNTIL 5-6-96.  WHILE INSTALLING ENGINE, PUSH R	OD TUBES ON NR 4 CYLINDER WERE FOUND LOOSE.  REMOVAL OF VALVE COVER AND CLOSE INSPECTION FOUND SPRING BROKEN IN 2 PLACES	.									3	O			1E10				 
1996053000022	19960530	00022	SO  	1996	5	30	96ZZZX2659       	1	19960509	G	2821	62305000	LINE            		87477002    	PIPER 	PA28  	PA28181     	7102807	SO  										FUEL STRAINER	LEAK            	H		A		K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			GL	15	4365F	968  				288490082				A PERSISTANT FUEL STAIN WAS NOTICED AT THE FIREWALL.  UPON REMOVAL OF THE FUEL STRAINER ASSY, DISCOVERED THE FITTING ON 	THE INSIDE WAS CROSS-THREADED AND WEEPING FUEL.  THE REASON IT WAS CROSS-THREADED IS THAT THE FUEL LINE FROM THE FUEL SE	LECTOR TO THE FUEL STRAINER WAS INCORRECTLY BENT.  UPON RECEIPT OF THE NEW PART, THE STRAINER TOP WAS FOUND TO HAVE THRE	ADS OF POOR QUALITY AND NOT ENOUGH THREADS.  PIPER CHECKED STOCK AND FOUND ALL THEIR STOCK DEFECTIVE.  FINALLY, A PROPER	 PART ARRIVED.  THIS WAS A FACTORY DEFECT.		1	L	7	1 	3O				2A13    					 
1996053000023	19960530	00023		1996	5	30	96ZZZX2660       	4	19960401	G	2562	BS2190	ELT             	NARCO       	SHARC7      															ELT	MISMANUFACTURED 	B		A	CU4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03										RED WIRE CONNECTING BATTERIES WAS NOT SOLDERED PROPERLY ON 3 SETS OF BATTERIES THAT WERE RECEIVED.  MOUNDS OF SOLDER APP	EAR TO HAVE BEEN PLACED ON THE TERMINAL CONNECTION OF THE BATTERIES AND THE WIRES INSERTED RESULTING IN COLD SOLDER CONN	ECTIONS.  WIRES PULLED OUT OF SOLDER CLEAN.																	 
1996053000024	19960530	00024	WP  	1996	5	30	96ZZZX2661       	1	19960426	G	5320		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										NR 25 LT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CABIN WINDOW NR 25 LEFT, INNER FRAME SURFACE HAS CORROSION.  REMOVED CORROSION AND REPAIRED IAW DR	W SR 08530014.  TREATED AND PRIMED AREA IAW SRM 51-1-8 AND REPLACED FASTENERS IAW 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000025	19960530	00025	WP  	1996	5	30	96ZZZX2662       	1	19960426	G	5320	S2613996	STIFFENER       			DOUG  	DC8   	DC862       	3021970	WP  										AFT BLKHD LBL 22	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK FOUND AFT BULKHEAD WALL, FORWARD SIDE VERTICAL STIFFENER AT LBL 22 HAS CORROSION, BOTTOM END.  REMOVED AN	D REPLACED CORRODED STIFFENER IAW SRM 51-1-21.					2	L	7	4 	4F				4A25    					 
1996053000026	19960530	00026	WP  	1996	5	30	96ZZZX2663       	1	19960426	G	5313	S1415997	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1670 32L	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERON 32L BETWEEN STATIONS 1530-1670 HAS LEVEL 2 CORROSION.   REMOVED AND REPLACED LONGERON IAW	 SRM 51-1-21, ARM 51-1-8, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000027	19960530	00027	WP  	1996	5	30	96ZZZX2664       	1	19960426	G	5313	S141599712000	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1066 30R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERON 30R BETWEEN STATIONS 1530 TO 1606 HAS LEVEL 2 CORROSION.  REMOVED AND REPLACED LONGERON I	AW SRM 51-1-2, SRM 51-1-20D, SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000028	19960530	00028	WP  	1996	5	30	96ZZZX2665       	1	19960426	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										RUDDER AREA	DENTED          	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FOUND DURING C-CHECK, FUSELAGE AREA UNDER RUDDER HAS MAJOR DENTS IN SKIN.  REMOVED AND REPLACED SKIN SEGMENT IAW DER 950	087-0699.					2	L	7	4 	4F				4A25    					 
1996053000029	19960530	00029	WP  	1996	5	30	96ZZZX2666       	1	19960426	G	5313	S1415997	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1380 30R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LOWER AFT FUSELAGE COMPARTMENT, FS 1380 AND 30R LONGERON HAS CORROSION.  CUT OUT DAMAGED SECTION, 	FABRICATED REPAIR AND SPLICES IAW SRM 53-2-2, TREATED AND PRIMED IAW SRM 51-1-8.  INSTALLED NEW LONGERON SECTION WITH FA	STENERS IAW SRM 53-4-1 AND SRM 53-2-2.				2	L	7	4 	4F				4A25    					 
1996053000030	19960530	00030	WP  	1996	5	30	96ZZZX2667       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										RT WS XRS 74.869	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND RT WING UPPER SURFACE HAS CORROSION FORWARD OF CENTER SPAR AND XRS 74.869 (APPROXIMATELY).  REPAIR	ED RT WING UPPER SKIN AT APPROXIMATELY XRS 74.869 IAW DER 961ALE.005D-1.					2	L	7	4 	4F				4A25    					 
1996053000031	19960530	00031	WP  	1996	5	30	96ZZZX2668       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										LT WS XRS 311	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LT WING UPPER SKIN HAS CORROSION 10 INCHES AFT OF CENTER SPAR BETWEEN XRS 311.656 AND XRS 351.000.	  REPAIRED DAMAGED SKIN IAW DER NR 961 ALE.005D-3.					2	L	7	4 	4F				4A25    					 
1996053000032	19960530	00032	WP  	1996	5	30	96ZZZX2669       	1	19960426	G	5751		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										LT WING AILERON	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEFT WING OUTBOARD AILERON, INBOARD LOWER SURFACE SKIN BULGED.  REPAIRED AILERON IAW DER DRW 95008	2-4066.					2	L	7	4 	4F				4A25    					 
1996053000033	19960530	00033	WP  	1996	5	30	96ZZZX2671       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										WS XRS 172	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEVEL 2 CORROSION UPPER WING AT STA XRS 172.000.  REPAIRED IAW DER DRAWING FROM AVITAS NR 961ALE.0	05D-6.					2	L	7	4 	4F				4A25    					 
1996053000034	19960530	00034	WP  	1996	5	30	96ZZZX2672       	1	19960426	G	5313	141599712000	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1670 34R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERON 34R BETWEEN STA 1530 TO STA 1670 WITH CORROSION, LEVEL 2.  REMOVED AND REPLACED LONGERON 	IAW SRM 51-1-21 AND SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000035	19960530	00035	WP  	1996	5	30	96ZZZX2673       	1	19960426	G	5320		FLOOR WEB       			DOUG  	DC8   	DC862       	3021970	WP  										FS 1420	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AT FS 1420, FLOOR WEB HAS CORROSION LEVEL 1 LOCAL/TYPE.  REMOVED CORROSION IAW 51-1-8 AND TREATED 	AND PRIMED.  REPAIRED DAMAGE IAW 53-2-0.  INSTALLED DOUBLER IAW SRM 53-2-6.					2	L	7	4 	4F				4A25    					 
1996053000036	19960530	00036	WP  	1996	5	30	96ZZZX2674       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										WS 329.000 TE	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				RIGHT WING, UPPER SURFACE LEADING EDGE ASSY - TRAILING EDGE HAS CORROSION AT FS 329.000, APPROXIMATE.  REMOVED CORROSION	.  AREA FOUND BEYOND LIMITS.  REMOVED DAMAGED AREA, FABRICATED DOUBLER AND REPAIRS IAW 57-201.  REPAIRED DAMAGE IAW SRM 	5-1-8, SRM 57-2-0, SRM 57-2-1, FIGURE 38, PAGES 137/138.				2	L	7	4 	4F				4A25    					 
1996053000037	19960530	00037	WP  	1996	5	30	96ZZZX2677       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										WS XRS 238-255	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEFT WING UPPER SKIN HAS SEVERAL SPOTS WITH CORROSION BETWEEN FRONT SPAR AND CENTER SPAR BETWEEN X	RS 238.000 AND XRS 255.000.  REMOVED CORROSION, FOUND BEYOND LIMITS.  FABRICATED DOUBLERS AND INSTALLED IAW DER NR 961AL	E005 D-5.				2	L	7	4 	4F				4A25    					 
1996053000038	19960530	00038	WP  	1996	5	30	96ZZZX2678       	1	19960426	G	5311		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										FS 225 L21R-36R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE, RT SIDE FRAME FS 225, HAS CORROSION APPROXIMATELY BETWEEN L21R AND L36R.  REMOVED SECTIO	N OF FRAME WITH CORROSION FABRICATED NEW FRAME SECTION AND SPLICE IAW SRM 53-2-0, FIGURE 2, PAGE 5.  TREATED, PRIMED, AN	D INSTALLED IAW SRM 51-1-8 AND SRM 53-2-0, FIGURE 2.				2	L	7	4 	4F				4A25    					 
1996053000039	19960530	00039	WP  	1996	5	30	96ZZZX2679       	1	19960426	G	5320		INTERCOSTAL     			DOUG  	DC8   	DC862       	3021970	WP  										FS 188 L27R-L28R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FORWARD RT LOWER SIDE OF INTERNAL FUSELAGE BETWEN FS 168 TO FS 188, AND BETWEEN L27R AND L28R, SMA	LL INTERCOSTAL HAS CORROSION.  REMOVED INTERCOSTAL WITH CORROSION, FABRICATED NEW INTERCOSTAL IAW SRM 53-2-0, TREATED, P	RIMED, AND INSTALLED IAW SRM 51-1-21, SRM 51-1-18, AND SRM 51-1-20D.				2	L	7	4 	4F				4A25    					 
1996053000040	19960530	00040	WP  	1996	5	30	96ZZZX2680       	1	19960426	G	5240		DOOR            			DOUG  	DC8   	DC862       	3021970	WP  										RT FUS LAV SERV	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FORWARD RT FUSELAGE LAVATORY SERVICE DOOR AND DOOR CUT-OUT HAVE CORROSION.  REMOVED DOOR, FABRICAT	ED NEW DOOR AND INSTALLED IAW SRM 51-1-0 AND SRM 53-4-1.  REMOVED CORROSION ON CUT-OUT, TREATED AND PRIMED IAW SRM 51-1-	8.				2	L	7	4 	4F				4A25    					 
1996053000041	19960530	00041	WP  	1996	5	30	96ZZZX2681       	1	19960426	G	5720		STRAP           			DOUG  	DC8   	DC862       	3021970	WP  										LT WING LE INBD	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEFT WING LEADING EDGE, INBOARD SLOT AREA OUTBOARD END HAS TWO AREAS OF EXFOLIATION WITH CORROSION	 ON STRAP.  REMOVED CORROSION, FOUND BEYOND LIMITS IAW SRM 57-3-0.  FABRICATED NEW STRAP IAW SRM 57-3-0.  TREATED, PRIME	D, AND INSTALLED IAW SRM 51-1-21D.				2	L	7	4 	4F				4A25    					 
1996053000042	19960530	00042	WP  	1996	5	30	96ZZZX2682       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										LT WS XRS 22.750	RUSTED          	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEFT WING UPPER SKIN HAS BARE METAL AND RUSTED FASTENERS AT CTR SPAR AND XRS 22.750.  REPAIRED UPP	ER SKIN IAW E.O. NR 961ALE.005D-4.					2	L	7	4 	4F				4A25    					 
1996053000043	19960530	00043	WP  	1996	5	30	96ZZZX2683       	1	19960426	G	5400	57530057W	BRACE           			DOUG  	DC8   	DC862       	3021970	WP  										NR 2 INBD PYLON	DAMAGED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND NR 2 INBOARD PYLON SIDE, BRACE DAMAGED AND GOUGED.  REMOVED AND REPLACED NEW THRUST LINK BRACE IAW	 SB 54-90-00 AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000044	19960530	00044	WP  	1996	5	30	96ZZZX2684       	1	19960426	G	5313	2597242318000	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 29R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEVEL 2 CORROSION ON LONGERON 29R, FS 208.00 TO FS 270.00.  REMOVED AND REPLACED LONGERON IAW SRM 	53-2-0, SRM 51-1-21, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000045	19960530	00045	WP  	1996	5	30	96ZZZX2685       	1	19960426	G	5751		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										RT OTBD AILERON	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND RT OUTBOARD AILERON SKIN BULGING.  CUT OUT DAMAGED AREA, REPAIRED IAW DER DRAWING ARW 950082-0289.						2	L	7	4 	4F				4A25    					 
1996053000046	19960530	00046	WP  	1996	5	30	96ZZZX2686       	1	19960426	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 1420 LON 30L	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LOWER AFT FUSELAGE SKIN AT STA 1420.00, LONGERON 30L, BULGING.  REPAIRED IAW SRM 53-2-1 AND SRM 51	-1-8.					2	L	7	4 	4F				4A25    					 
1996053000047	19960530	00047	WP  	1996	5	30	96ZZZX2687       	1	19960426	G	5313	14159971200	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1670 32R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERON 32R, BETWEEN STA 1530 AN STA 1670, WITH CORROSION, LEVEL 2.  REMOVED AND REPLACED IAW 51-	1-21, SRM 51-1-20D, SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000048	19960530	00048	WP  	1996	5	30	96ZZZX2688       	1	19960426	G	5320	47731461	FITTING         			DOUG  	DC8   	DC862       	3021970	WP  										FS 1500 LON 21R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CORROSION FUSELAGE FITTING STA 1500.00 AT LONGERON 21R.  REMOVED AND REPLACED FITTING IAW SRM 51-1	-20D, 51-1-8. 53-2-0, 51-1-21, AND 51-3-0.					2	L	7	4 	4F				4A25    					 
1996053000049	19960530	00049	WP  	1996	5	30	96ZZZX2689       	1	19960426	G	5320		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										WINDOW LT FS 610	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FS 610 LT WINDOW FRAME HAS A CRACK AT LOWER SIDE FROM CORROSION LEVEL 1 LOCAL TYPE.  BLENDED OUT A	ND REMOVED CORROSION.  FOUND AREA BEYOND LIMITS IAW DAC SR.08530014 DRAWING.  FABRICATED EXTERNAL DOUBLER FROM 7075.T6 .	190 INCH.  INSTALLED IAW DAC SR.08530014 AND SRM 51-1-20.				2	L	7	4 	4F				4A25    					 
1996053000050	19960530	00050	WP  	1996	5	30	96ZZZX2690       	1	19960426	G	5320		INTERCOSTAL     			DOUG  	DC8   	DC862       	3021970	WP  										FS 822 L19L	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FS 822 L19L HAS CORROSION LEVEL 1 LOCAL TYPE.  REMOVED INTERCOSTAL, FABRICATED NEW ONE, TREATED, A	LODINED, AND PRIMED.  INSTALLED NEW INTERCOSTAL IAW SRM 53-2-0 AND SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000051	19960530	00051	WP  	1996	5	30	96ZZZX2691       	1	19960426	G	5320		ANGLE           			DOUG  	DC8   	DC862       	3021970	WP  										AFT BLKHD FWD	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AFT BULKHEAD, FORWARD SIDE, FLOOR PANEL ATTACH ANGLE ON LEFT SIDE OF CENTER IS CORRODED.  REMOVED 	ANGLE AND FABRICATED NEW ONE PER SRM 53-2-0.  INSTALLED ANGLE PER SRM 51-1-21.					2	L	7	4 	4F				4A25    					 
1996053000052	19960530	00052	WP  	1996	5	30	96ZZZX2692       	1	19960426	G	5320		FLANGE          			DOUG  	DC8   	DC862       	3021970	WP  										FS 420 L5R-L6R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FS 420 HAS CORROSION AT THE LOWER FLANGE BETWEEN L5R AND L6R.  REMOVED CORROSION IAW SRM 51-1-8. F	OUND OUT OF LIMITS IAW SRM 53-2-0.  CUT OUT DAMAGED AREA, FABRICATED FILLER AND DOUBLER IAW 53-2-1.  PARTS HEAT TREATED 	ATI P.O. 2407.  TREATED AND PRIMED IAW SRM 51-1-8. INSTALLED REPAIRED IAW SRM 53-20-10.				2	L	7	4 	4F				4A25    					 
1996053000053	19960530	00053	WP  	1996	5	30	96ZZZX2693       	1	19960426	G	5320		WEB             			DOUG  	DC8   	DC862       	3021970	WP  										FS 235 L21R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE RT SIDE, A/C COMPARTMENT AREA UNDER CABIN FLOOR PANEL AT FS 235 AND L21R INTERCOSTAL (WEB	) HAS CORROSION.  REMOVED, FABRICATED NEW WEB, AND INSTALLED IAW SRM 53-20-6 AND SRM 51-1-21.					2	L	7	4 	4F				4A25    					 
1996053000054	19960530	00054	WP  	1996	5	30	96ZZZX2694       	1	19960426	G	5313	S2593956	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 31R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CORROSION LEVEL 2 ON LONGERON 31R BETWEEN FS 208.00 AND FS 270.00.  REMOVED AND REPLACED LONGERON 	IAW SRM 53-2-0, SRM 51-1-21, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000055	19960530	00055	WP  	1996	5	30	96ZZZX2695       	1	19960426	G	5720		T-ANGLE         			DOUG  	DC8   	DC862       	3021970	WP  										LT WS XW 33	CRACKED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEFT WING AUXILIARY SPAR AREA INBD LOWER VERTICAL SUPPORT T-ANGLE CRACKED AT STA XW 33.000.  INSTA	LLED NEW VERTICAL SUPPORT T-ANGLE IAW SRM 51-1-20, SRM 53-1-0, AND SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000056	19960530	00056	WP  	1996	5	30	96ZZZX2696       	1	19960426	G	5313	2597242318000	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 L24R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CORROSION LEVEL 2 ON LONGERON 24R BETWEEN FS 208.00 AND FS 270.00.  REMOVED AND REPLACED LONGERON 	IAW SRM 53-2-0, SRM 51-1-21, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000057	19960530	00057	WP  	1996	5	30	96ZZZX2697       	1	19960426	G	5313	2597424318000	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 270 8L-7L	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERONS CRACKED AT FS 270.00, LONGERONS 8L AND 7L.  REPAIRED IAW SRM 53-2-2.						2	L	7	4 	4F				4A25    					 
1996053000231	19960530	00231	NE  	1996	5	30	96ZZZX2698       	2	19960507	G	7261	2380	OIL             			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ENGINE	METAL FOD       	H		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	207R					FL14	PCE95489			WHEN ADDING OIL TO ENGINE (EXXON 2380 LOT NR B652 11-29-95) NOTICED METAL CONTAMINATION IN STRAINER USED TO POUR OIL INT	O ENGINE.  INVESTIGATED OIL IN CAN, FOUND PARTICLES COULD BE PICKED UP BY A MAGNET.  DRAINED AND FLUSHED ENGINE OIL SYST	EM.  INFORMED EXXON AND FAA.  OIL SAMPLE SUPPLIED TO EXXON.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1996053000232	19960530	00232	SO  	1996	5	30	96ZZZX2699       	1	19960514	G	2432	MA5	BATTERY         			GULSTM	G1159 	G1159A      	3970109	SO  										NR 2	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	313RG				9103408	321				DURING ROUTINE INSPECTION, THE NR 2 BATTERY FAILED THE CAPACITY CHECK.  FIVE OF 19 CELLS NEED REPLACING.  THE BATTERY IS	 LESS THAN ONE YEAR OLD.  THIS HAS BEEN AN ONGOING CONDITION FOR THIS TYPE OF BATTERY.  'A NEW AND IMPROVED BATTERY'.  A	LSO, 3 CELLS SHOWED EVIDENCE OF EXTREME HEAT (MELTING OBSERVED).				2	L	7	2 	4F				A12EA   					 
1996053000233	19960530	00233	EA  	1996	5	30	96ZZZX2700       	2	19960430	G	7321	2528973	BEARING         	BENDIX      	DPF2        	BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  					RT ENG FUEL CONT	FAILED          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			WP	23	388MC		322  		194208	LJ383	PCE22420			RIGHT ENGINE FLUCTUATIONS 2-3 SECONDS, 3 TIMES.  AIRCRAFT YAW.  FIFTEEN MINUTES LATER, FLUCTUATINS OCCURRED THEN FUEL FL	OW WENT TO ZERO.  ENGINE QUIT.  RESTARTED ON GROUND, NO RESPONSE TO THROTTLE.  DISASSEMBLED FUEL CONTROL, FOUND BUSHING 	ASSY BEARING FAILED.				1	L	7	2 	3T	3	T		3A20    	E4EA				 
1996053000234	19960530	00234	CE  	1996	5	30	96ZZZX2701       	1	19960314	G	2910	6000100287	TUBE ASSY       			LEAR  	60    	60LEAR      	5170707	CE  										HYD SYS	CHAFED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	799SC	80   				067				THE EXTERNAL HYD CART PRESSURE LINE BETWEEN THE QUICK DISCONNECT AND THE HYD SYSTEM WAS FOUND CHAFING ON THE RT HYD ACCU	MULATOR.  A LEAK HERE WOULD CAUSE TOTAL LOSS OF FLUID.  DAMAGE WAS ALSO FOUND AT THE UPPER B-NUT FERRULE AREA.  DEPTH (A	PPROXIMATE) OF CHAFE - 0.008 INCH.  DEPTH (APPROXIMATE) OF B-NUT AREA TOOL DAMAGE - 0.005 INCH.				2	L	7	2 	4F			RT	A10CE   					 
1996053000235	19960530	00235	WP  	1996	5	30	96ZZZX2702       	1	19960426	G	5320	3610130501	FITTING         			DOUG  	DC8   	DC862       	3021970	WP  										FS 270 LON 21R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, LEVEL 2 CORROSION ON FITTING AT FS 270.00, LONGERON 21R.  REPAIRED IAW DAC FAX 287337, 288375, AND 25181	9/01, SRM 51-1-20D AND SRM 51-3-0.					2	L	7	4 	4F				4A25    					 
1996053000236	19960530	00236	WP  	1996	5	30	96ZZZX2703       	1	19960426	G	5320		FINGER DOUBLER  			DOUG  	DC8   	DC862       	3021970	WP  										FS 188-270 RT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FUSELAGE RT SIDE, L21R, HAS CORROSION AT INTERNAL FINGER DOUBLER BETWEEN STA 188 TO STA 270.  REMOVED, FABRICATED, INSTA	LLED NEW FINGER DOUBLER IAW SRM 51-1-21, SRM 53-3-2, SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000237	19960530	00237	WP  	1996	5	30	96ZZZX2704       	1	19960426	G	5320		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										WINDOW NR 30 LT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				CABIN WINDOW, NR 30 LT, CORRODED.  REPAIRED FRAME IAW DAC SRO 8530014.						2	L	7	4 	4F				4A25    					 
1996053000238	19960530	00238	WP  	1996	5	30	96ZZZX2705       	1	19960426	G	5620		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										WINDOW NR 28 LT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				CABIN WINDOW NR 28 LT, FRAME CORRODED.  REPLACED WINDOW FRAME IAW SRM 51-1-20D, SRM 51-1-8.						2	L	7	4 	4F				4A25    					 
1996053000239	19960530	00239	WP  	1996	5	30	96ZZZX2706       	1	19960426	G	5400		THRUST LINK     			DOUG  	DC8   	DC862       	3021970	WP  										NR 4 ENG PYLON	CHAFED          	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				NR 4 ENGINE PYLON THRUST LINK CHAFED.  REMOVED AND REPLACED THRUST LINK IAW SB 54-92-00, SRM 51-1-20D.						2	L	7	4 	4F				4A25    					 
1996053000240	19960530	00240	CE  	1996	5	30	96ZZZX2707       	1	19960506	G	3097		WIRE            			LEAR  	60    	60LEAR      	5170707	CE  										V STAB TIP CAP	CHAFED          	D		A		K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	05	638LJ	879  				038				ACFT HAD FAILURES OF HORIZ STAB ANTI-ICE SYS.  EACH FAILURE COULD NOT BE VERIFIED TO WORK AFTER REPLACEMENT OF FL-94 CUR	RENT LIMITER WHICH WAS BLOWN FROM OVERCURRENT SITUATION, T/S FND WIRE NR 10 FROM TERM BLK TB-5 JUNC IN AREA OF VERT STAB	 TIP CAP CHAFED & BURNED DUE TO CONTACT WITH STRUCT, FS-651.455.  LOOP FROM HEAT BLANKET TO TERM BLK NOT CORRECT, ALLOWE	D WIRE BUNDLE TO CONTACT ACFT STRUCT WHEN STAB TRIM WAS MOVED & RUBBED INSULATION AWAY ALLOWING WIRE TO SHORT OUT WHEN S	YS ENERGIZED & STAB POSITION ALLOWED CONTACT OF WIRE.  ARCING BURNED FLANGE OFF STIFFENER AN INCH & DAMAGED INSULATION O	F WIRES IN BUNDLE.  ONE-TIME INSP OF RT & LT STAB HEAT SYS WIRING IS CALLED FOR TO PREVENT DAMAGE TO SURROUNDING STRUCT.	2	L	7	2 	4F			RT	A10CE   					 
1996053000241	19960530	00241	WP  	1996	5	30	96ZZZX2708       	1	19960426	G	5320		SUPPORT CHANNEL 			DOUG  	DC8   	DC862       	3021970	WP  										AFT LAV FS 1574	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				CABIN, AFT LAVATORY AREA, FLOOR SUPPORT CHANNEL CORRODED.  FABRICATED AND INSTALLED NEW CHANNEL IAW SRM 53-2-0, SRM 51-1	-8, SRM 51-3-0.					2	L	7	4 	4F				4A25    					 
1996053000242	19960530	00242	WP  	1996	5	30	96ZZZX2709       	1	19960426	G	5620		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										WINDOW NR 26 LT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				CABIN WINDOW FRAME EXFOLIATED AROUND 1 BOLT HOLE.  INSTALLED DOUBLER IAW DER NR SRO8530014 AND SRM 51-1-20D.						2	L	7	4 	4F				4A25    					 
1996053000243	19960530	00243	WP  	1996	5	30	96ZZZX2710       	1	19960426	G	5313		LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1670 34L	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERON 34L BETWEEN STA 1530 - STA 1670 HAS CORROSION, LEVEL 2.  REMOVED AND REPLACED LONGERON IA	W SRM 51-1-21, SRM 51-1-20D, AND SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000244	19960530	00244	WP  	1996	5	30	96ZZZX2711       	1	19960426	G	5313	14159971200	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1670	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERON 36 BETWEEN FS 1530 TO FS 1670 WITH LEVEL 2 CORROSION.  REMOVED AND REPLACED LONGERON IAW 	SRM 51-1-21 AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000245	19960530	00245	WP  	1996	5	30	96ZZZX2712       	1	19960426	G	5313	S2641455	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 L30R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEVEL 2 CORROSION AT LONGERON L30R, FS 208.00 TO FS 270.00.  REMOVED AND REPLACED LONGERON IAW SRM	 53-2-0, SRM 51-1-21, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000246	19960530	00246	WP  	1996	5	30	96ZZZX2713       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										LT WS XRS 45	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LT UPPER WING SKIN HAS CORROSION AT CTR SPAR AND XRS 45.000.  REPAIRED SKIN IAW E.O. 96IALE.005D-4	.					2	L	7	4 	4F				4A25    					 
1996053000247	19960530	00247	WP  	1996	5	30	96ZZZX2714       	1	19960426	G	5320		ANGLE           			DOUG  	DC8   	DC862       	3021970	WP  										FS 1606 AFT BLK	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LOWER AFT FUSELAGE COMPARTMENT AT STA 1606, ANGLE ATTACHED TO THE AFT BULKHEAD AT FLOOR LEVEL HAS 	CORROSION.  FABRICATED NEW ANGLE AND INSTALLED IAW SRM 53-2-0, SRM 51-1-8, SRM 51-1-20D, SRM 51-1-21.					2	L	7	4 	4F				4A25    					 
1996053000248	19960530	00248	WP  	1996	5	30	96ZZZX2715       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										LT WS XRS 22.75	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LT WING UPPER SKIN HAS CORROSION AT CTR SPAR AND XRS 22.750.  REPAIRED SKIN IAW E.O. 961 ALE.005D-	4.					2	L	7	4 	4F				4A25    					 
1996053000249	19960530	00249	WP  	1996	5	30	96ZZZX2716       	1	19960426	G	5320		ANGLE           			DOUG  	DC8   	DC862       	3021970	WP  										FS 834.5 XCW 0	CRACKED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LOWER FUSELAGE LT ADF SENSE ANTENNA COMPARTMENT, FORWARD ATTACH ANGLE, CRACKED AT STA 834.500 BETW	EEN XCW ZERO AND XCW 23.  INSTALLED REPAIR ANGLE IAW SRM 53-2-0, SRM 53-2-0, AND SRM 51-1-20.					2	L	7	4 	4F				4A25    					 
1996053000250	19960530	00250	WP  	1996	5	30	96ZZZX2717       	1	19960426	G	5320	46401621N	FITTING         			DOUG  	DC8   	DC862       	3021970	WP  										FS 1260 CUSP	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CABIN UPPER SURFACE OF THE RT SIDE CUSP AREA, FS 1260 AT FLOOR LEVEL, FITTING HAS CORROSION. REMOV	ED DAMAGED FITTING, REMOVED CORROSION AREA, FOUND WITHIN LIMITS.  ALODINED AND PRIMED AREA.  INSTALLED NEW FITTING, PN 4	640162-1N, IAW SRM 51-1-20D, SRM 51-3-0, SRM 51-1-8, AND SRM 53-2-0.				2	L	7	4 	4F				4A25    					 
1996053000251	19960530	00251	WP  	1996	5	30	96ZZZX2718       	1	19960426	G	5320		INTERCOSTAL     			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-225 L28R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE RT SIDE, INTERCOSTAL RT L28R BETWEEN FS 209 TO FS 225, HAS CORROSION.  REMOVED INTERCOSTA	L IAW SRM 53-2-0, SRM 5-1-21, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000252	19960530	00252	WP  	1996	5	30	96ZZZX2719       	1	19960426	G	5320		STIFFENER       			DOUG  	DC8   	DC862       	3021970	WP  										FS 208 RT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND A/C COMPARTMENT RT SIDE AT FS 208, BULKHEAD STIFFENER HAS EXFOLIATON CORROSION IN DIFFERENT LOCATI	ON.  REMOVED STIFFENER WITH CORROSION, FABRICATED NEW IAW SRM 53-2-0.  TREATED, PRIMED, AND INSTALLED IAW SRM 51-1-8, SR	M 51-1-21, AND SRM 51-1-20D.				2	L	7	4 	4F				4A25    					 
1996053000253	19960530	00253	WP  	1996	5	30	96ZZZX2720       	1	19960426	G	5313	1415997	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1670 L30	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERON 30L BETWEEN FS 1530 TO FS 1670, HAS CORROSION, LEVEL 2.  REMOVED AND REPLACED DAMAGED LON	GERON AND FITTING IAW SRM 51-1-21 AND SRM 51-1-20D.  TREATED AND PRIMED IAW SRM 51-1-8 AND SRM 53-10-0.					2	L	7	4 	4F				4A25    					 
1996053000254	19960530	00254	WP  	1996	5	30	96ZZZX2721       	1	19960426	G	5320	4641324N	FITTING         			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1670 L30	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LONGERON 30L BETWEEN FS 1530 TO FS 1670, HAS CORROSION, LEVEL 2.  REMOVED AND REPLACED DAMAGED LON	GERON AND FITTING IAW SRM 51-1-21 AND SRM 51-1-20D.  TREATED AND PRIMED IAW SRM 51-1-8 AND SRM 53-10-0.					2	L	7	4 	4F				4A25    					 
1996053000255	19960530	00255	WP  	1996	5	30	96ZZZX2722       	1	19960426	G	5320		INTERCOSTAL     			DOUG  	DC8   	DC862       	3021970	WP  										FS 188-208	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE RT SIDE, STRUCTURAL INTERCOSTAL RT L30R AND BETWEEN FS 188 AND FS 208, HAS CORROSION AT L	OWER FLANGE.  REMOVED INTERCOSTAL, FABRICATED NEW INTERCOSTAL IAW SRM 53-20-0, TREATED, PRIMED, AND INSTALLED IAW SRM 51	-1-8, SRM 51-1-21, AND SRM 51-1-20D.				2	L	7	4 	4F				4A25    					 
1996053000256	19960530	00256	WP  	1996	5	30	96ZZZX2723       	1	19960426	G	5313	2593956	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 L31R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE RT SIDE, L31R, HAS CORROSION BETWEEN FS 208 TO FS 270.  REMOVED CORRODED LONGERON AND INS	TALLED NEW LONGERON IAW 53-2-0, SRM 51-1-21, AND SRM 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000257	19960530	00257	WP  	1996	5	30	96ZZZX2724       	1	19960426	G	5320	47731471	FITTING         			DOUG  	DC8   	DC862       	3021970	WP  										FS 1500	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CABIN UPPER SURFACE OF THE RT CUSP AREA, FS 1500, INSIDE DOOR JAM AFT LOWER CORNER, SMALL FITTING 	HAS CORROSION.  REMOVED DAMAGED FITTING, REMOVED CORROSION FROM AREA, AREA FOUND WITHIN LIMITS.  TREATED AND PRIMED AREA	.  INSTALLED NEW FITTING, PN 4773147-1, AND CLOSED AREA IAW SRM 51-1-8, SRM 51-1-20, SRM 53-2-0, AND SRM 51-1-21.				2	L	7	4 	4F				4A25    					 
1996053000258	19960530	00258	WP  	1996	5	30	96ZZZX2725       	1	19960426	G	5320	S643396501	FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										FS 1010 LT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEVEL 2 CORROSION AT WINDOW FRAME FS 1010, LT SIDE.  REPAIRED IAW DOUGLAS DRAWING SR08530010-7085.						2	L	7	4 	4F				4A25    					 
1996053000259	19960530	00259	WP  	1996	5	30	96ZZZX2726       	1	19960426	G	5315		FLOOR BEAM      			DOUG  	DC8   	DC862       	3021970	WP  										FS 160-188	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEVEL 2 CORROSION AT COCKPIT FLOOR BEAM AND FINGER DOUBLERS, FS 160 TO FS 188.  REPAIRED IAW DER D	RAWING ARW 950087-0083.					2	L	7	4 	4F				4A25    					 
1996053000260	19960530	00260	WP  	1996	5	30	96ZZZX2727       	1	19960426	G	5230		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										AFT CARGO DOOR	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND CORROSION AT AFT LOWER CARGO DOOR SKIN NEAR HANDLE.  REPAIRED IAW SRM'S 52-2-0, 51-1-21, 51-1-0, A	ND 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000261	19960530	00261	WP  	1996	5	30	96ZZZX2728       	1	19960426	G	5313		LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 L28R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FUSELAGE RT SIDE L28R HAS CORROSION BETWEEN STA 208-STA 270.  REMOVED AND REPLACED LONGERON IAW SRM'S 53-2-0, 51-1-21, A	ND 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000262	19960530	00262	WP  	1996	5	30	96ZZZX2729       	1	19960426	G	5313	25972423	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 L23R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FUSELAGE, RT SIDE L23R, HAS CORROSION ON THE CTR FLANGE BETWEEN STA 208-STA 270.  REMOVED AND INSTALLED NEW SECTION OF L	ONGERON IAW SRM'S 53-2-2, 51-1-20D, 51-1-21, AND 51-3-0.					2	L	7	4 	4F				4A25    					 
1996053000263	19960530	00263	WP  	1996	5	30	96ZZZX2730       	1	19960426	G	5313		LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 208-270 L22R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FUSELAGE, RT SIDE, L22R, HAS CORROSION BETWEEN STA 208-STA 270.  REMOVED AND INSTALLED NEW LONGERON IAW SRM'S 51-1-8, 53	-2-0, AND 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000264	19960530	00264	WP  	1996	5	30	96ZZZX2731       	1	19960426	G	5320		SUPPORT BRACKET 			DOUG  	DC8   	DC862       	3021970	WP  										FS 208 L22R	CRACKED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FRAME CAP SUPPORT BRACKET CRACKED, STA 208, L22R.  REMOVED, FABRICATED, AND INSTALLED NEW BRACKET IAW DAC CL-P63-ATM-025	 AND SRM'S 51-1-20D AND 51-1-21.					2	L	7	4 	4F				4A25    					 
1996053000265	19960530	00265	WP  	1996	5	30	96ZZZX2732       	1	19960426	G	5400		THRUST LINK     			DOUG  	DC8   	DC862       	3021970	WP  										NR 1 PYLON LOWER	DAMAGED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				NR 1 PYLON THRUST LINK, LOWER FORWARD FLANGE, IS GOUGED.  REMOVED AND REPLACED THRUST LINK IAW SB 54-92-00 AND SRM 51-1-	20D.					2	L	7	4 	4F				4A25    					 
1996053000266	19960530	00266	WP  	1996	5	30	96ZZZX2733       	1	19960426	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										WS XRS 50 LT	DAMAGED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				LEFT WING UPPER SKIN HAS DEEP BLEND-OUTS 20 INCHES FORWARD OF CTR SPAR AND XRS 50.000, APPROXIMATE.  FABRICATED DOUBLER 	FROM 7075-T6 .125 INCH IAW SRM 57-2-1, PAGES 59, 60, AND FILLER, SRM'S 51-1-20D AND 51-1-12 AND INSTALLED.					2	L	7	4 	4F				4A25    					 
1996053000267	19960530	00267	WP  	1996	5	30	96ZZZX2734       	1	19960426	G	5315		FLOOR BEAM      			DOUG  	DC8   	DC862       	3021970	WP  										FS 1568 AFT LAV	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				AFT LAVATORY AREA, FLOOR BEAM AT FS 1568, HAS CORROSION ON TOP CAP.  REPLACED FLOOR BEAM IAW SRM'S 53-2-0, 51-1-0, 51-1-	8, 51-1-3, 51-1-21.					2	L	7	4 	4F				4A25    					 
1996053000268	19960530	00268	WP  	1996	5	30	96ZZZX2735       	1	19960426	G	5320		CLIP            			DOUG  	DC8   	DC862       	3021970	WP  										FS 1040 LT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FS 1040, LEFT, FRAME TO LONGERON CLIPS HAVE CORROSION, LEVEL 2.  REMOVED, FABRICATED NEW LONGERONS, REINSTALLED CLIPS IA	W SRM'S 51-1-8, 51-2-0, 51-1-21D.					2	L	7	4 	4F				4A25    					 
1996053000269	19960530	00269	WP  	1996	5	30	96ZZZX2736       	1	19960426	G	5320		BATHTUB FITTING 			DOUG  	DC8   	DC862       	3021970	WP  										FS 270 L25	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				BATHTUB FITTING HAS LEVEL 2 CORROSION, FS 270, L25.  REMOVED FITTING, REMOVED CORROSION, REINSTALLED FITTING IAW SRM'S 5	1-1-3, 51-1-8, 51-1-20D.					2	L	7	4 	4F				4A25    					 
1996053000270	19960530	00270	WP  	1996	5	30	96ZZZX2737       	1	19960426	G	5320		INTERCOSTAL     			DOUG  	DC8   	DC862       	3021970	WP  										FS 335 L30	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FS 335, L30, INTERCOSTAL HAS LEVEL 2 CORROSION.  REMOVED AND REPLACED DAMAGED INTERCOSTAL IAW SRM'S 53-20, 51-1-8, AND 5	1-20-0.					2	L	7	4 	4F				4A25    					 
1996053000271	19960530	00271	WP  	1996	5	30	96ZZZX2738       	1	19960426	G	5320		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										WINDOW NR 27L	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				FUSELAGE CUT-OUT FOR WINDOW NR 27L, INTERIOR SKIN CORRODED.  REPLACED WINDOW FRAME IAW SRM 51-1-20D.						2	L	7	4 	4F				4A25    					 
1996053000272	19960530	00272	WP  	1996	5	30	96ZZZX2739       	1	19960426	G	5313		LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 1380 LON L32L	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				LOWER AFT FUSELAGE COMPARTMENT, FS 1380, LONGERON L32L, HAS CORROSION.  INSTALLED NEW SECTION OF LONGERON AND SPLICED IA	W SRM 53-2-2.					2	L	7	4 	4F				4A25    					 
1996053000273	19960530	00273	WP  	1996	5	30	96ZZZX2740       	1	19960426	G	5320		FILLER          			DOUG  	DC8   	DC862       	3021970	WP  										FS 1500 LT DOOR	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK IN CABIN, FOUND UPPER SURFACE OF THE LT CUSP EXTENSION AREA, FS 1500, LT, SERVICE DOOR AFT LOWER CORNER I	NSIDE SCUFF PLATE, HAS CORROSION BELOW.  FILLER FOUND BEYOND LIMITS, FABRICATED NEW FILLER AND INSTALLED FILLER AND SCUF	F PLATE IAW SRM'S 51-3-0, 51-1-8, 53-2-0, 51-1-0.				2	L	7	4 	4F				4A25    					 
1996053000274	19960530	00274	WP  	1996	5	30	96ZZZX2741       	1	19960426	G	5320		ANGLE           			DOUG  	DC8   	DC862       	3021970	WP  										FS 1568 RBL 16	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AFT LAVATORY AREA AT FS 1568, RBL 16 TO RBL 34, HAS CORRODED ANGLE.  REMOVED DAMAGED ANGLE.  FABRI	CATED NEW ONE IAW SRM 53-2-0 PER ORIGINAL.  INSTALLED IAW SRM 51-3-0.					2	L	7	4 	4F				4A25    					 
1996053000275	19960530	00275	CE  	1996	5	30	96ZZZX2742       	1	19960507	G	3310	10836401111	DIMMER CONTROL  			BEECH 	23    	C23         	1151242	CE  										INST PANEL	MISWIRED        	G		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	3841T					M2307				REPLACEMENT BEECH SUNDOWNER INSTRUMENT LIGHT DIMMER CONTROL WAS FOUND MISWIRED AS SHIPPED FROM BEECHCRAFT.  BEECHCRAFT F	OUND ALL IN STOCK MISWIRED AND CORRECTED PROBLEM.  REPAIR FACILITIES WITH PN 108-364011-11 IN STOCK SHOULD COORDINATE WI	TH BEECHCRAFT TO DETERMINE WIRING STATUS OF THE PARTS.				1	L	7	1 	3O				A1CE    					 
1996053000276	19960530	00276	CE  	1996	5	30	96ZZZX2743       	1	19960228	G	5540	3364000045	ARM ASSY        			BEECH 	33    	F33A        	1151425	CE  										UPPER RUD HINGE	MISMANUFACTURED 	B	S		BKHR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	01	17RE	1056 				CE1128				WHEN INSTALLING UPPER HINGE PER STC, FOUND WHEN NEW HINGE INSTALLED, RUDDER UPPER MOUNT WOULD NOT LINE UP STRAIGHT.  VIS	UAL INSPECTION OF ARM REVEALED BEARING BOSS IN ARM DRILLED OFF CENTER CAUSING THIS PROBLEM ALONG WITH RUDDER CHAFING ON 	VERTICAL STABILIZER SKIN WHEN RUDDER AT EXTREME RIGHT TRAVEL.  PART CAME FROM FACTORY LIKE THIS.  REPLACED ARM WITH NEW 	WITH NO DISCREPANCIES NOTED.			1	L	7	1 	3O				3A15    					 
1996053000277	19960530	00277	CE  	1996	5	30	96ZZZX2744       	1	19960308	G	2810	1013890113	CHECK VALVE     	AIRBORNE    	1D212       	BEECH 	200   	200BEECH    	1152920	CE  										AUX XFER PUMP	LEAKING         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	26G	8417 				BB787				AIRCRAFT HAS FUEL ODOR IN CABIN.  INSPECTED AND FOUND FUEL SEEPING INTO CABIN THROUGH FUEL PROBE WIRING CONDUIT.  FOUND 	FUEL TANKS FILLED IN VERY COLD CONDITIONS AND THEN PLACED IN WARM HANGAR.  FOUND CHECK VALVE WITH SOME DIRT IN IT CAUSIN	G THE FUEL EXPANSION TO FORCE ITS WAY OUT FUEL CELL ACCESS PANEL INSTEAD OF OUTBOARD VENT.				1	L	7	2 	4T				A24CE   					 
1996053000278	19960530	00278	SO  	1996	5	30	96ZZZX2745       	1	19960426	G	3230	402960	BOLT            			PIPER 	PA28  	PA28R200    	7102811	SO  										BRACE LINK	DEFECTIVE       	B	L		AMYR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05	2981R	1343 				28R35370				DURING INSPECTION REPLACEMENT OF MLG BRACE LINK ROD END BOLT TO TRUNNION HOUSING, FOUND OLD STYLE CLEVIS HEAD BOLT, PN 4	00-810, INSTALLED.  IF REPLACEMENT WITH NEW STYLE HEX HEAD BOLT, PN 3772202, IS DONE, THE GEAR DOOR RETRACT ROD WILL NOT	 CLEAR BOLT HEAD DURING RETRACTION/EXTENSION.				1	L	7	1 	3O				2A13    					 
1996053000279	19960530	00279	SO  	1996	5	30	96ZZZX2746       	1	19960310	G	5741	9010443	SHOULDER BOLT   			GULSTM	AA5   	AA5A        	3960106	SO  										INBD WING ATTACH	MISMANUFACTURED 	B		A	NZBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05	26655	3162 				AA5A0623				DURING C/W AD 95-19-15, ONE OF THE FOUR INBOARD WING ATTACH BOLTS WAS FOUND TO HAVE BEEN INCORRECTLY MANUFACTURED, WITH 	AN AREA OF THE THREADED SHANK MISSING, AND AN AREA OF THE HEX HEAD MIS-MACHINED.					1	L	7	1 	3O				A16EA   					 
1996053000280	19960530	00280	SO  	1996	5	30	96ZZZX2747       	1	19960429	G	2140	88D934	COMBUSTION TUB  	JANITROL    	90D381      	PIPER 	PA34  	PA34200T    	7103406	SO  										HEATER	CRACKED         	B	S		APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	666HL				8771387	347770235				HEATER FAILED PDT REQUIREMENT OF AD 82-07-3.  SUBSEQUENT VISUAL INSPECTION SHOWED LARGE CRACK IN COMBUSTION TUBE 2.50 IN	CHES FROM EXHAUST END.					1	L	7	2 	3O				A7SO    					 
1996053000291	19960530	00291	CE  	1996	5	30	96ZZZX2757       	1	19960513	G	3211	24411001	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	D	S			K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			NM	01	5252V	4993 				172RG0485				PIVOT CRACKED NEARLY THE ENTIRE CIRCUMFERENCE IN THE RADIUS UNDER PN 2241111-2 INNER RACE.  IT IS NOT KNOWN IF A HARD LA	NDING OCCURRED.  PART HAD SOME AREAS OF INTERGRANULAR CORROSION AND IS IN THE EXHAUST STREAM.  NO EVIDENCE OF CORROSION 	IN AREA OF CRACK.  CRACK WAS DISCOVERED DUE TO SPONGY RT BRAKE AND 5606 FLUID LEAK INTO RACK AND PINION CHAMBER OF ASSOC	IATED HYDRAULIC ACTUATOR.			1	H	7	1 	3O				3A17    					 
1996053000292	19960530	00292	CE  	1996	5	30	96ZZZX2758       	1	19960509	G	2730	53608014	BELLCRANK       			CESSNA	340   	340A        	2076405	CE  										ELEV FS 360.2	BEARING FAILED  	B		A	JBER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	6829K					340A1233				DURING ANNUAL INSPECTION, FOUND EXCESSIVE SIDE-PLAY IN ELEVATOR BELLCRANK ASSY, FURTHER INVESTIGATION FOUND BEARING AT F	AULT.  REMOVAL OF BELLCRANK REVEALED BENT BOLT WHICH ADDED DIFFICULTY IN REMOVING ASSY.  SUSPECT CAUSE COULD BE NOT USIN	G ELEVATOR CONTROL LOCK IN WINDY CONDITIONS.				1	L	7	2 	3O				3A25    					 
1996053000293	19960530	00293	GL  	1996	5	30	96ZZZX2759       	3	19960417	G	6110		PROPELLER       			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	HUB AREA	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6359M	4994 				15284693		776529		WHILE C/W AD 95-21-01 AND SB 219, THE PROPELLER WAS FOUND CRACKED PAST THE ACCEPTABLE LIMITS.  THIS PROPELLER HAS NO HIS	TORY OF DAMAGE.  PROPELLER WAS REMOVED FROM SERVICE.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1996053000294	19960530	00294	CE  	1996	5	30	96ZZZX2760       	1	19960419	G	3221	24130023	CASTING         			CESSNA	172   	172RG       	2072438	CE  										NLG STRUT ANCHOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9516B	5150 				172RG0847				DURING A 100-HOUR INSPECTION WHILE CHECKING THE BELLY SKIN AFT OF THE NOSE GEAR, NOTICED BLACK STAINING FROM THE 6 SCREW	S THAT ARE ON THE LOWER EDGE OF CASTING.  REMOVED SCREWS AND FOUND ALL MOUNTING HOLES OF SKIN NR 2413000-5 ELONGATED.  I	NSPECTED CASTING WITH A MIRROR AND FOUND A CRACK EXTENDING FROM THE LEFT INBOARD SCREW HOLE FORWARD TO EDGE OF CASTING. 	 SUSPECT CRACKING AND ELONGATIONS DUE TO SCREW LOOSENING DUE TO VIBRATIONS.  SUBMITTER RECOMMENDS KEEPING CASTING AREA C	LEAN, CHECK SCREW TORQUE, VISUAL INSPECTION OF CASTING, POSSIBLE DYE CHECKS AT 500-HOUR INTERVALS.  SUBMITTER STATED THI	S IS THE 2ND AIRCRAFT FOUND WITH THIS CRACK.	1	H	7	1 	3O				3A17    					 
1996053000295	19960530	00295	SO  	1996	5	30	96ZZZX2761       	1	19960505	G	5610	549015	WINDOW          			PIPER 	PA31T 	PA31T1      	7103126	SO  										COPILOT RT SIDE	DEPARTED        	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	05	121BE					31T18004036				PILOT REPORTED AT ALTITUDE OF 27,000 FEET, THE RIGHT SIDE COCKPIT SIDE WINDOW BLEW OUT.  PILOT FURTHER REPORTED THAT UP 	TO THIS TIME, ALL SYSTEMS WERE NORMAL WITH NO INDICATION OF TROUBLE.  PILOT RETURNED TO AIRFIELD WITHOUT FURTHER INCIDEN	T.  CAUSE UNKNOWN FOR WINDOW FAILURE.  AIRCRAFT TT, 1,916.2 HOURS.				1	L	7	2 	3T				A8EA    					 
1996053000296	19960530	00296	SO  	1996	5	30	96ZZZX2762       	2	19960513	G	7414	104001664	IMPULSE COUPLER 	BENDIX      	S6RN25      	PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					MAGNETO	CAM SPLIT       	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	5384F	1751 			V149214DR	347770013				MAGNETO IMPULSE COUPLER CAM SPLIT IN HALF DURING RE-INSTALLATION ON MAGNETO DURING MAGNETO 500-HOUR INSPECTION AND IMPUL	SE COUPLER AD 78-09-07R3.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996053000297	19960530	00297	SO  	1996	5	30	96ZZZX2763       	2	19960405	G	7322	T194593	ACCELERATOR     	PRECISION   	048941      	CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR	WORN            	D				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			NM	01	19396	2878 	649  		BE2421667	15074391	254532A48			ACCELERATOR PUMP WORN AND CHECK VALVE LEAKING CAUSING CARBURETOR TO BE EXCESSIVELY RICH RESULTING IN ENGINE FAILURE.  LA	ST OVERHAUL DATE, 5-6-82.					1	H	7	1 	3O	3	O		3A19    	E252				 
1996053000298	19960530	00298	SO  	1996	5	30	96ZZZX2764       	2	19960501	G	7322	194593	ACCELERATOR PUMP	FACET       	MA5PA       	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR	PLUNGER RUSTED  	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			NM	01	3936V		2297 		2422161	15076658	251114A48			ENGINE QUIT CAUSING FORCED LANDING.  INVESTIGATION REVEALED PLUNGER RUSTED AND CHECK VALVE WITH BROKEN SPRING INTERNALLY	.  ACCELERATOR PUMP WAS INOPERABLE AND ENGINE RAN EXCESSIVELY RICH.  CARBURETOR LAST OVERHAULED, 8-5-76.  SUBMITTER RECO	MMENDS CARBURETORS BE REQUIRED TO BE OVERHAULED AT TIMES RECOMMENDED BY PRECISION AIRMOTIVE BULLETIN NR MSA-3.  SOME TBO	 RECOMMENDED ON INSTALLED ENGINE OR 10 YEARS SINCE PLACED IN SERVICE OR LAST OVERHAUL.			1	H	7	1 	3O	3	O		3A19    	E252				 
1996053000299	19960530	00299	SO  	1996	5	30	96ZZZX2765       	2	19960504	G	8530		PISTON PIN      			CESSNA	337   	337C        	2075712	CE  	CONT  	O360  	IO360C      	17025	SO  					NR 2 CYLINDER	FAILED          	D				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			AL	03	2615S	312  				3370915	501398C			IT APPEARS THE PISTON PIN BROKE AND THE PISTON HIT THE CRANKSHAFT COUNTERWEIGHT WHICH BROKE A LARGE HOLE IN THE TOP OF T	HE CRANKCASE.  THE AIRCRAFT WAS ON A CROSS-COUNTRY FLIGHT AT NORMAL CRUISE.  WHEN THE VIBRATION STARTED, THE PILOT REDUC	ED POWER, BUT THE VIBRATION CONTINUED SO THE PROPELLER WAS FEATHERED AND FLIGHT CONTINUED WITH REAR ENGINE OPERATING.				1	H	7	2 	3O	3	O		A6CE    	E1CE				 
1996053000300	19960530	00300	SO  	1996	5	30	96ZZZX2766       	2	19960507	G	8540	539800	SPRING CLUTCH   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RT START ADAPTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	4677N	26   				414A0068	290873R			TWENTY-SIX HOURS AFTER INSTALLING A TCM OVERHAULED ENGINE, STARTER ADAPTER FAILED.  INSPECTION SHOWED THAT SPRING CLUTCH	 FAILED AND WAS UNCOILING INTO ENGINE ACC CASE.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996053000301	19960530	00301	CE  	1996	5	30	96ZZZX2767       	1	19960425	G	2434	C6FF10335B	ROTOR ASSY      			CESSNA	182   	R182        	2072734	CE  										ALTERNATOR	SHAFT SHEARED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	5545T	1310 				R18201894				C/W REMOVAL OF ALTERNATOR FOR 500-HOUR INSPECTION.  UPON DISASSEMBLY, ROTOR SHAFT SHEARED OFF IN AREA OF NUT (PULLEY RET	AINING) THREADS.  EVIDENCE OF CRACK BEING VERY OLD EXISTS.  MATERIAL CORRODED IN AREA OF CRACK (SHEAR AREA).					1	H	7	1 	3O			RT	3A13    					 
1996053000303	19960530	00303	CE  	1996	5	30	96ZZZX2769       	1	19960510	G	3242	C306152	BRAKE DISC      			CESSNA	180   	180K        	2072624	CE  										LT MLG	FAILED          	D				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			SW	11	24SL	3758 				18053187				UPON STARING TAKEOFF ROLL, LOUD NOISE AND LEFT BRAKE MALFUNCTION OCCURRED.  TAKEOFF ABORTED.  LEFT MAIN BRAKE DISC HAD B	ROKEN LOOSE FROM MAIN WHEEL BOLTS.  SUSPECT CAUSE WAS CRACKS IN DISC.  SUBMITTER RECOMMENDS INSPECTION OF DISC FOR CRACK	S.				1	H	7	1 	3O				5A6     					 
1996053000304	19960530	00304	CE  	1996	5	30	96ZZZX2770       	1	19960401	G	3231	0024100381	SHAFT ASSY      			BEECH 	58    	58P         	1152744	CE  										NLG DR ACTUATOR	FAILED          	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			NE	05	6648K					TJ204				PILOT NOTICED ODD NOISE DURING GEAR RETRACTION AND SUBSEQUENT EXTENSION.  INSPECTION ON GROUND REVEALED PART OF SHAFT AS	SY THAT CLOSES GEAR DOORS BROKEN ALLOWING DOORS TO FLAP IN FLIGHT.  SUBMITTER SUSPECTS NOISE HEARD BY PILOT WAS NOSE GEA	R FORCING ITS WAY THROUGH DOORS HELD CLOSED BY AIR PRESSURE AS AIRCRAFT WAS FLYING.				1	L	7	2 	3O				A23CE   					 
1996053000305	19960530	00305	CE  	1996	5	30	96ZZZX2771       	1	19960401	G	8120	641284	COUPLING        			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520L    	17040	SO  					TURBO EXHAUST	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	4269S					TJ96	237270R			CLAMP WAS FOUND CRACKED WHEN REMOVED FOR OTHER MAINTENANCE ON THE EXHAUST SYSTEM.  SUBMITTER SUSPECTS CLAMP WAS OVERTORQ	UED AT PRIOR INSTALLATION.  FAILURE OF THIS CLAMP COULD ALLOW HOT EXHAUST GASES TO BE RELEASED IN THE ENGINE COMPARTMENT	.  SUBMITTER RECOMMENDS CLOSE INSPECTION OF ALL V-BAND STYLE CLAMPS DURING SCHEDULED MAINTENANCE INSPECTION.  DEFECT WOU	LD BE DETECTABLE WITHOUT REMOVAL.			1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1996053000306	19960530	00306	CE  	1996	5	30	96ZZZX2772       	1	19960228	G	7602	S17771	MIXTURE CONTROL 			CESSNA	150   	150         	2071802	CE  										SHROUD	BROKEN          	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CE	07	45166					15076764				PILOT HAD TO MAKE EMERGENCY LANDING AND WAS BARELY ABLE TO MAKE IT DUE TO ENGINE BARELY RUNNING AND INTERMITTENTLY QUITT	ING ENTIRELY.  INSPECTION FOUND MIXTURE CONTROL WIRE BROKEN WHERE IT EXITS CONTROL SHROUD TO ATTACH TO MIXTURE.  CAUSE W	AS FROM NORMAL WEAR AND FATIGUE.  SUBMITTER SUGGESTS CLOSER INSPECTION OF ACTUAL CONTROL WIRE FOR WEAR AGAINST SHROUD AT	 REGULAR MAINTENANCE INTERVALS.			1	H	7	1 	3O			NT	3A19    					 
1996053000307	19960530	00307	CE  	1996	5	30	96ZZZX2773       	1	19960507	G	7160	AM107635FP	AIR FILTER      	AIRMAZE     		CESSNA	177   	177RG       	2073709	CE  										ENG INDUCTION	MOUNT FAILED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	52908	196  				177RG1306				DURING ROUTINE OIL CHANGE, OBSERVED AIR INDUCTION FILTER 'LAYING' IN ENGINE BAFFLE.  UPON FURTHER INVETSIGATION, FOUND B	OTH MOUNTING BRACKETS HAD BROKEN/SHEARED FROM THE INDUCTION FILTER BODY.  SUSPECT CAUSE, INADEQUATE METHOD OF ATTACHMENT	 OF BRACKETS TO FILTER BODY/ASSY.  SUBMITTER STATED METHOD OF ATTACHMENT APPEARS TO BE 'SPOT WELDS'.  PERHAPS RIVETING O	F THE BRACKETS TO THE FILTER ASSY MAY BE MORE SUITABLE.			1	H	7	1 	3O				A20CE   					 
1996060600121	19960606	00121	CE  	1996	6	6	96ZZZX2774       	1	19960513	G	5551	12121271	DOUBLER         			CESSNA	210   	T210N       	2073456	CE  										H STAB ATTACH	RIVETS DEFECTIVE	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	7353C	1825 				21063943				TOP RIVET ABOVE PLATE.  NUT POPPED ON RIGHT SIDE AND WORKING ON LEFTSIDE.  RECOMMEND PERIODIC INSPECTION.						1	H	7	1 	3O				3A21    					 
1996060600122	19960606	00122	CE  	1996	6	6	96ZZZX2775       	1	19960513	G	5551	12121273	DOUBLER         			CESSNA	210   	T210N       	2073456	CE  										H STAB ATTACH	RIVETS DEFECTIVE	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	7353C	1825 				21063943				TOP RIVET ABOVE PLATE.  NUT POPPED ON RIGHT SIDE AND WORKING ON LEFTSIDE.  RECOMMEND PERIODIC INSPECTION.						1	H	7	1 	3O				3A21    					 
1996060600128	19960606	00128	CE  	1996	6	6	96ZZZX2781       	1	19960501	G	3240	0301890	BRAKE ASSY      			CESSNA	500   	550         	2076604	CE  										MLG RT	WRONG DISK      	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	09	533MA				1154	5500078				INSTALLED STC SA 4954NM, CLEVELAND WHEELS AND BRAKES.  AFTER 1 LANDING, THE BRAKES ALMOST LOCKED UP.  BOTH BRAKES:  AFTE	R INSPECTION, FOUND DISKS FROZEN IN WHEELS.  THE DISKS WERE FOUND TO BE THE WRONG TYPE TO BE INSTALLED.  BOTH BRAKES WER	E NEW AND ASSEMBLED AT FACTORY. THE P/N 159-03500 DISK WAS SUPPOSED TO BE INSTALLED.  REPLACING BOTH WHEEL AND BRAKE ASS	YS WITH REPLACEMENT COMPONENTS.  LANDINGS, 1.			1	L	7	2 	4F				A22CE   					 
1996060600129	19960606	00129	CE  	1996	6	6	96ZZZX2782       	1	19960501	G	3240	0301890	BRAKE ASSY      			CESSNA	500   	550         	2076604	CE  										MLG RT	WRONG DISK      	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	09	533MA				1155	5500078				INSTALLED STC SA 4954NM, CLEVELAND WHEELS AND BRAKES.  AFTER 1 LANDING, THE BRAKES ALMOST LOCKED UP.  BOTH BRAKES:  AFTE	R INSPECTION, FOUND DISKS FROZEN IN WHEELS.  THE DISKS WERE FOUND TO BE THE WRONG TYPE TO BE INSTALLED.  BOTH BRAKES WER	E NEW AND ASSEMBLED AT FACTORY. THE P/N 159-03500 DISK WAS SUPPOSED TO BE INSTALLED.  REPLACING BOTH WHEEL AND BRAKE ASS	YS WITH REPLACEMENT COMPONENTS.  LANDINGS, 1.			1	L	7	2 	4F				A22CE   					 
1996060600130	19960606	00130	SW  	1996	6	6	96ZZZX2784       	1	19960501	G	3230	MS17152B	ROLL PIN        			GULSTM	690TP 	690A        	0141722	SW  										GEAR HANDLE	SHEARED         	B		A	R2JR	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			EA	21	53RF	9980 				11153				IN-FLIGHT, AFTER LANDING GEAR FAILED TO RETRACT PROPERLY, LANDING GEAR SELECTED DOWN AND FAILED TO EXTEND.  NO LANDING G	EAR EXTENSION OCCURRED UNTIL UPHOLSTERY WAS REMOVED AND LANDING GEAR CONTROL VALVE MANUALLY MOVED TO EXTEND LANDING GEAR	.  SAFE LANDING MADE.  MAINTENANCE FOUND ROLL PIN SHEARED IN HANDLE MECHANISM.  NO PARTS BREAK DOWN IN IPC.  FACTORY PRO	VIDED PART NUMBER FOR PIN.  SUGGEST TIME CHANGE OF THIS PART AND AFM SUPPLEMENT INSTRUCTING CREW HOW TO GAIN ACCESS AND 	MANUALLY MOVE LANDING GEAR CONTROL VALVE IN CASE OF HANDLE FAILURE.  VERY DANGEROUS SITUATION.		1	H	7	2 	3T				2A4     					 
1996060600131	19960606	00131	CE  	1996	6	6	96ZZZX2785       	1	19960422	G	2810	MS29513338	O-RING          			CESSNA	206   	U206G       	2073356	CE  										FUEL CAP	DEFECTIVE       	B	L		UKJR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23	9814G	2    				U20603831				OWNER COMPLAINT FOR FUEL CAP O-RINGS BEING TOO LARGE.  INVESTIGATION REVEALED RINGS .25 INCH IN DIAMETER TOO LARGE.  O-R	INGS HAD BEEN INSTALLED ABOUT 30 DAYS, 1.5 HOURS TT.  INSTALLED NEW O-RINGS.  INSPECTED ACFT 3 WEEKS LATER AND FOUND SAM	E CONDITION.  INSPECTED O-RINGS REMOVED EARLIER, FOUND THEY HAD SHRUNK BACK TO ORIGINAL SIZE.  REMOVED ALL O-RINGS FROM 	STOCK (SAME BATCH NR) AND RETURNED TO VENDOR.			1	H	7	1 	3O				A4CE    					 
1996060600132	19960606	00132	EA  	1996	6	6	96ZZZX2786       	2	19960423	G	7414	67542	BEARING         			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					MAG DRIVE	MISINSTALLED    	D	L			A				UNSCHED LANDING         				Y	W		ENGINE STOPPAGE           	INADEQUATE Q C            		CR	CRUISE         	1			SO	16	107FC					31612	L807761			WHILE IN LEVEL FLIGHT, THE RIGHT ENGINE QUIT WITHOUT WARNING.  UPON INVESTIGATION, DETERMINED THE DRIVE DOWEL PIN (STD-1	065) HAD BEEN SHEARED, AND THE LEFT IDLER GEAR (71668) HAD LOST A TOOTH AND JAMMED THE MAGNETO DRIVE GEAR (GEAR RETAINER	 ASSY LW-19102 OR LW 19096). WHEN THE LEFT MAGNETO (S6LN-1208) WAS REMOVED, THE MAGNETO HAD A BURNED APPEARANCE.  UPON D	ISASSEMBLY, FOUND THE ROTOR HAD CONTACTED THE POLE SHOES IN THE HOUSING.  AFTER SENDING THE MAGNETO TO THE BENDIX FACTOR	Y, DISCOVERED THE DRIVE GEAR HAD A SIDE LOAD PLACED ON IT CAUSING THIS TO OCCUR.		1	L	7	1 	3O	3	O	RT	A20SO   	E14EA				 
1996060600133	19960606	00133	CE  	1996	6	6	96ZZZX2787       	1	19960105	G	5312	121340711	BULKHEAD        			CESSNA	206   	U206F       	2073333	CE  										LT-RT DOORPOST	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	1372V	5231 				U20602588				DURING ROUTINE ANNUAL INSP, DISCOVERED FWD CABIN DOORPOST BULKHEAD CRACKED ON LT AND RT SIDES AT WING LIFT STRUT ATTACH 	FITTINGS.  INSP WAS DONE IAW CESSNA SEB 93-5 R1.  PREVIOUS INSP OF THIS AREA DURING ANNUAL AND WHEN C/W CESSNA SEB 93-5,	 FAILED TO FIND THIS DAMAGE.  DAMAGE WAS ONLY VISIBLE BY REMOVING LT AND RT UPHOLSTERY SIDE PANELS, CARPETING, AND DIRT 	THAT BLOCKED THE VIEWING AREA FROM DIRECTLY ABOVE CRACKS.  FURTHER INSP REVEALED DAMAGE TO SUPPORTING STRUCTURE OF BULKH	EAD ON RT SIDE.  REPAIRED CRACKS BY MODIFYING LT AND RT AREAS OF BULKHEAD IAW CESSNA SEB 93-5 R1 BY INSTALLING SERVICE K	IT SK 206-42C.  DAMAGED SUPPORTING STRUCTURE REPLACED (ANGLE PN 1213408-3 AND DOUBLER PN 1213806-2 (RT SIDE).	1	H	7	1 	3O				A4CE    					 
1996060600134	19960606	00134	CE  	1996	6	6	96ZZZX2788       	1	19960509	G	3211	0541153	U-BOLT          			CESSNA	182   	182A        	2072704	CE  										RT MAIN GEAR	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	6191B					34191				DURING ROUTINE INSPECTION, RT MAIN LANDING GEAR U-BOLT WAS FOUND SHEARED AT AFT END.  THIS MAY BE DUE TO PARACHUTISTS ST	ANDING ON RT MAIN GEAR PRIOR TO DEPARTURE FROM AIRCRAFT.					1	H	7	1 	3O			NT	3A13    					 
1996060600135	19960606	00135	GL  	1996	6	6	96ZZZX2789       	1	19960401	G	6720	28163511	CONTROL CABLE   			ENSTRM	F28   	F28F        	3300412	GL  										T/R	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	8627J	1200 				760				INFORMATION APPLICABLE TO MODELS, F28C, F28C-2 F28-F, 280F, 280FX.  INSPECTION FOUND TAIL ROTOR CABLES FRAYED WHERE THEY	 PASS OVER THE AFT ALIGNMENT PULLEYS IN THE TAIL CONE.  PULLEYS WERE LUBED, FREE AND TURNING.  SUSPECT VIBRATION WAS CAU	SING CABLES TO RATTLE IN PULLEY AND GUIDE, FATIGUING THE CABLE.  SUBMITTER RECOMMENDS CAREFUL INSPECTION OF CABLES IN TH	IS AREA AT 100-HOUR INSPECTION OR ANNUAL.			1	G	7	1 	3O			 	H1CE    					 
1996060600163	19960606	00163	GL  	1996	6	6	96ZZZX2796       	1	19960408	G	8120	28125523	WASTEGATE       			ENSTRM	F28   	F28F        	3300412	GL  										BUTTERFLY	FAILED          	C			PP0M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8624G	1100 				745				BUTTERFLY IN WASTEGATE WARPED AND LOSE FROM CRACKED WELDS JAMMING THROTTLE.  BUTTERFLY SHAFT WORN AT PIVOT POINTS ALSO C	AUSING THROTTLE BINDING.  SUBMITTER STATES COMMON TO ALL F28F AND F280FX MODELS.  REQUIRES REPLACEMENT OF WASTEGATE.					1	G	7	1 	3O				H1CE    					 
1996060600166	19960606	00166	NE  	1996	6	6	96ZZZX2799       	2	19960301	G	7310	9550147560	ELECTROVALVE    			AEROSP	SA365 	SA365N1     	8680668	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					NR 2 ENG START	FAILED          	B			KY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	92MD	2906 			3521	6311	5094			NR 2 ENGINE WOULD NOT HAVE T4 CLIMB UNTIL NG SHOWED 30 PERCENT, THEN RAPID RISE ONCE IGNITION OCCURRED.  REPLACED START 	FUEL ELECTROVALVE.					1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1996060600167	19960606	00167		1996	6	6	96ZZZX2800       	4	19960302	G	2210	41800562312	DUPLEX ACTUATOR 			AEROSP	SA365 	SA365N1     	8680668	EU  										AUTOFLT	FAULTY          	B			KY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	92MD	379  				6311				PITCH CHANNEL DISENGAGEMENT AND PITCH C5 FAULT.						1	G	7	2 	3U				H10EU   					 
1996060600168	19960606	00168		1996	6	6	96ZZZX2801       	4	19960229	G	2210	41800562312	DUPLEX ACTUATOR 			AEROSP	SA365 	SA365N1     	8680668	EU  										AUTOFLIGHT	FAILED          	B			KY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	97MD				413	6330				FAILED INSULATION TEST LOW MEG CHECK.						1	G	7	2 	3U				H10EU   					 
1996060600861	19960606	00861		1996	6	6	96ZZZX2854       	1	19960506	G	3520	417T42631	MASK            	BOEING      	417T4202    															PULL STREAMER	DEFECTIVE       	B		A	GUMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19										PULL STREAMERS FOR ACTIVATING PASSENGER OXYGEN SYSTEMS FAILED THE PULL TEST.  INSPECTION OF ALL STREAMERS IN STOCK RESUL	TED IN IDENTIFYING APPROXIMATELY 20 PERCENT DEFECTIVE, I.E., BAD CRIMPS, CRIMPS SLIPPING AND FRAYED STRINGS.  BOEING AIR	CRAFT HAS BEEN NOTIFIED AND IS INVESTIGATING THE PROBLEM.  NOTE:  THE DEFECTIVE STREAMERS WERE FOUND PRIOR TO BEING INST	ALLED IN AN AIRCRAFT.																 
1996060600862	19960606	00862	CE  	1996	6	6	96ZZZX2855       	1	19960508	G	3252	22430211	EYE BOLT        			CESSNA	182   	R182        	2072734	CE  										SHIMMY DAMPENER	FAILED          	D	S			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NE	03	6319T					R18201977				SHIMMY DAMPENER EYE BOLT FAILED ON ROLL-OUT ON NORMAL LANDING.  NO ACCIDENT RESULTED.						1	H	7	1 	3O			RT	3A13    					 
1996060600863	19960606	00863	EA  	1996	6	6	96ZZZX2856       	2	19960514	G	8530	SL17236M294Z	VALVE           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYL INTAKE	PITTED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	5120H	287  				15284063	L2052015			EDGE OF INTAKE VALVE APPEARS TO BE BREAKING OFF.  EDGE IS ALSO CRACKED IN SEVERAL PLACES.  VALVE FACE HAS PITTING ON ENT	IRE SEALING SURFACE.  METAL ON VALVE APPEARS TO HAVE CONTAMINATES UPON INVESTIGATION WITH 30X MAGNIFIER.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996060600864	19960606	00864	EA  	1996	6	6	96ZZZX2857       	2	19960514	G	8520	SL72877	TAPPET          			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					CAMSHAFT	SPALLED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1630J	113  				2824017	L2022427A			ENGINE DISASSEMBLED.  CAMSHAFT LOBE AND HYDRAULIC BODY TAPPET FURNISHED BY SUPERIOR AIR PARTS WERE REMOVED.  THE CAM LOB	E WAS WORN BELOW TOLERANCE, THE HYD BODY WAS BADLY PITTED.  THE CAMSHAFT AND BODY HAD BEEN INSTALLED ABOUT 30 MONTHS AGO	 AND HAD A TOTAL OF 113 HRS SINCE NEW.  SUBMITTER STATED THE BODY WAS PITTED FROM THE BODY NOT BEING UP TO SPECS.				1	L	7	1 	3O	3	O		2A13    	E274				 
1996060600867	19960606	00867	EU  	1996	6	6	96ZZZX2860       	1	19960501	G	3230	AIR134702	DRAG BRACE LINK 			SAAB  	2000  	2000SAAB    	7860200	EU  										LT MLG	BEARING SHIFT   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	5125					2000030				DURING A POST-FLIGHT INSPECTION, THE UPPER BEARING IN THE LINK ASSY HAD SHIFTED APPROXIMTAELY .050 INCH.  REPLACED DRAG 	BRACE LINK AND PERFORMED A GEAR SWING.  ACFT TT:  1,647 HRS.  LANDINGS, 196.  REF:  OPERATOR CONTROL NR 96-002.					2	L	7	2 	4T			RT	A47NM   					 
1996060600868	19960606	00868	EU  	1996	6	6	96ZZZX2861       	1	19960212	G	3230	AIR843683	DRAG BRACE      			SAAB  	2000  	2000SAAB    	7860200	EU  										LT MLG	BEARING DEFECT  	B			GMCR	O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	23	5124				OZ9560042	200027				WHEN THE GEAR WAS SELECTED DOWN, THE CREW DID NOT HAVE A GREEN INDICATION ON THE LEFT GEAR.  CYCLED GEAR, NO HELP, THEN 	PERFORMED AN EMERGENCY EXTENSION.  THE AIRCRAFT LANDED SAFELY AND WAS TOWED TO THE HANGAR.  THE LOWER DRAG BRACE BEARING	 HAD SHIFTED IN THE CASTING.  REF:  OPERATOR CONTROL NR 96-001.				2	L	7	2 	4T			RT	A47NM   					 
1996060600870	19960606	00870	EU  	1996	6	6	96ZZZX2864       	1	19960229	G	5302	355A2305000507	SKIN            			AEROSP	AS355 	AS355N      		EU  										TAILBOOM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	54HG	376  				5567				FOUND 2 INCH SKIN CRACK FORWARD OF HORIZONTAL STABILIZER.  CRACK THROUGH AFT RIVET ATTACHING STRAKE ON RIGHT SIDE OF TAI	LBOOM.					1	G	7	2 	3U				H11GU   					 
1996060600871	19960606	00871	CE  	1996	6	6	96ZZZX2865       	1	19960514	G	7603	5038901229	CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  										ENG THROTTLE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	329H					TH219				THROTTLE CABLE BROKE BETWEEN CLAMP AND THROTTLE ARM.  AIRCRAFT TT, 5,931 HOURS.  CABLE WAS PREVIOUSLY REPLACED AT AIRCRA	FT TT, 5,638.2 HOURS.  CABLE TIME IS SERVICE SINCE NEW WAS 293 HOURS.					1	L	7	2 	3O			 	3A16    					 
1996060600872	19960606	00872	SO  	1996	6	6	96ZZZX2866       	1	19960515	G	2810	493063	DRAIN VALVE     			PIPER 	PA24  	PA24260     	7102406	SO  										FUEL SYSTEM	FAULTY          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	8632P					244074				THE FUEL DRAIN VALVE WOULD NOT OPERATE, THE PROBLEM WAS THE VALVE ITSELF, BUT WAS NOT EVIDENT UNTIL THE OVERBOARD HOSE B	ECAME STIFF FROM AGE AND TEMPERATURE.  WHILE INVESTIGATING, FOUND IF THE VALVE WAS OPENED BY A GREAT DEAL OF FORCE, THE 	VALVE COULD STICK OPEN.  FROM INSIDE THE AIRCRAFT THERE IS NO WAY TO SEE THIS OVERBOARD HOSE OR FUEL COMING OUT OF IT.				1	L	7	1 	3O				1A15    					 
1996060600873	19960606	00873	CE  	1996	6	6	96ZZZX2867       	1	19960520	G	5230		DOOR            			CESSNA	402   	402C        	207590R	CE  										RT NAC CARGO	BRACKET BROKE   	D				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	17	161TA	14505				402C0070				RIGHT NACELLE BAGGAGE COMPARTMENT HOLD-DOWN BRACKET BROKEN CAUSING DOOR TO TRIP OPEN CAUSING A VIBRATION IN THE AIRFRAME	.  PART NOT LISTED IN CESSNA I.P.B.					1	L	7	2 	3O				A7CE    					 
1996060600874	19960606	00874	EA  	1996	6	6	96ZZZX2868       	2	19960513	G	8530		VALVE SEAT      			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  					LT ENG NR 2 CYL	DISLODGED       	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	25	62992		554  		LW12967	317712013	L631961AC			ON A SHORT FLIGHT, A ROUGHNESS DEVELOPED IN THE LEFT ENGINE.  NO EMERGENCY ACTION WAS REQUIRED.  AFTER PERFORMING A COMP	RESSION CHECK, FOUND THE EXHAUST VALVE SEAT ON NR 2 CYLINDER HAD BECOME DISLODGED CAUSING THE EXHAUST VALVE TO REMAIN PA	RTIALLY OPEN.  THE CYLINDER (HEAD) IN THE AREA OF THE EXHAUST SEAT WAS DAMAGED BEYOND REPAIR, AND THE VALVE OR SEAT CAUS	ED MINOR DAMAGE TO THE PISTON.  NO CAUSE FOR THE SEAT BECOMING DISLODGED HAS BEEN DETERMINED.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996060600875	19960606	00875	CE  	1996	6	6	96ZZZX2869       	1	19960510	G	7714	332000002	TACHOMETER      	BFGOODRICH  		CESSNA	206   	TU206B      	2073324	CE  										ENGINE RPM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4991F	1    			332000022505	U2060691				NEW TACHOMETER INSTALLED FROM CESSNA SUPPLIED BY B. F. GOODRICH.  TACHOMETER FAILED WITHIN 1.0 HOURS.  NEEDLE AT 1,500 R	PM WITH ENGINE OFF.  REMOVED CABLE AT ENGINE.  TACHOMETER READS ZERO.  REMOVED TACHOMETER, TURNED BY HAND, AND PUSHED LI	GHTLY ON INPUT SHAFT.  NEEDLE STOPS INDICATION.  RELEASE PRESSURE, TACH GOES TO ZERO.  LOCK-WASHER WRONG TYPE FOR NUT AN	D NUT LOOSE ALLOWING TACH TO FLOAT INSIDE CASE.  THIS IS THE 2ND TACHOMETER INSTALLED AND FAILED WITHIN 10.0 HOURS.			1	H	7	1 	3O				A4CE    					 
1996060600876	19960606	00876	CE  	1996	6	6	96ZZZX2870       	1	19960510	G	7714	08503305	TACH/GENERATOR  	VICKERS     		CESSNA	340   	340A        	2076405	CE  										THRU SCREWS	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	4326C	550  			1090	340A0075				THIS IS THE SECOND TACHOMETER/GENERATOR OF THIS MODEL THAT HAD LOOSE THROUGH-SCREWS EVEN THOUGH THEY WERE SAFELY WIRED. 	 BOTH UNITS FAILED AND THE SAFETY WIRE WAS DONE AT THE MANUFACTURER.  PART TOTAL TIME, 550.2 HRS, 24 MONTHS.					1	L	7	2 	3O				3A25    					 
1996060600877	19960606	00877	SO  	1996	6	6	96ZZZX2871       	1	19960511	G	7120	1607304	SUPPORT ASSY    			PIPER 	PA23  	PA23250     	7102308	SO  										ENG MOUNT	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	14217					274775				SUBMITTER SUSPECTS HARD LANDING RT MLG SIDE.  FOUND BENT ENGINE MOUNT SUPPORT ASSY AT ACTUATOR BRACKET.  REPLACED WITH S	ERVICEABLE PART.  DAMAGED RT INBOARD GEAR DOOR.  REPLACED WITH SERVICEABLE UNIT.  NO FURTHER DAMAGE FOUND.					1	L	7	2 	3O				1A10    					 
1996060600878	19960606	00878	NM  	1996	6	6	96ZZZX2872       	1	19960513	G	7160	BA4111	SCREEN          	BRACKETT    	BA4106      	CHRIS 	HUSKY 	A1          	221020X	NM  										INDUCT FILTER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	2908U	481  				1023				MECHANIC REMOVED THE FILTER ELEMENT FOR NORMAL REPLACMENT DURING AN ANNUAL, HE NOTICED A 3.5 INCH CRACK RUNNING VERTICAL	LY IN THE ELEMENT RETAINING SCREEN.  IF PIECES BROKE LOOSE, THEY WOULD BE INGESTED INTO THE CARBURETOR.  THIS WAS A STEE	L MESH SCREEN NOT COVERED BY AD 81-15-03.				1	H	7	1 	3O			NC	A22NM   					 
1996060600879	19960606	00879		1996	6	6	96ZZZX2873       	1	19960501	G	2822	1C2710	FUEL PUMP       	AIRBORNE    																IMPELLER BEARING	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13					4AG140					FUEL PUMP IMPELLER BEARING INSTALLED INCORRECTLY.  (WRONG SIDE UP.)  FROM THE WEAR PATTERN ON IT, IT APPEARS TO HAVE COM	E FROM THE FACTORY IN THIS CONDITION.  RECOMMEND INSTALL CORRECTLY.																		 
1996060600880	19960606	00880		1996	6	6	96ZZZX2874       	4	19960508	G	2562	450014	MOUNT CLAMP     	AMERIKING   	AK450       															ELT	RIVETS FAILED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					4502406					RIVETS ATTACHING LATCH TO MOUNTING CLAMP FAILED WHEN ELT CLAMPED TO MOUNTING TRAY.  RIVETS IMPROPERLY DRIVEN.  SUBMITTER	 SUGGESTS INSPECTING ALL HARDWARE PRIOR TO INSTALLATION.																		 
1996060600881	19960606	00881	SO  	1996	6	6	96ZZZX2875       	2	19960324	G	8520	639243	CRANKSHAFT      			BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520BA     	17032	SO  					1ST MAIN BEARING	BROKEN          	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SW	09	9440Q	2301 			34	D9319	20085971B			SIXTY-FIVE PERCENT POWER IN LEVEL FLIGHT, IFR CONDITIONS.  CRANKSHAFT BROKE AT FIRST MAIN BEARING AFT NOSE BEARING THROU	GH CHEEK.  CRANKSHAFT TOTAL TIME, 2,301 HOURS.  INSPECTED, MAGNAFLUXED, AND PERFORMED ULTRASONIC INSPECTION AT 1,485 HOU	RS.  SUSPECT FATIGUE AND STRESS FAILURE.  SUBMITTER STATED CRANKSHAFT DESIGN NOT ADEQUATE FOR 285 HORSEPOWER RATING.  RE	COMMEND NR IO520BB FOR THIS HORSEPOWER RATING.  MAGNAFLUX AND ULTRASONIC PER SB M87-5 ARE NOT SUFFICIENT TO PREVENT NR I	O520BA CRANKSHAFTS FROM BREAKING.		1	L	7	1 	3O	3	O		3A15    	E5CE				 
1996060600882	19960606	00882	CE  	1996	6	6	96ZZZX2876       	1	19960510	G	3230	204101744	DOWNLOCK SUPPORT			CESSNA	177   	177RG       	2073709	CE  										RT MLG	PIN BROKEN      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	8271G	2486 				177RB0171				DOWNLOCK SUPPORT LOWER PIN FOUND BROKEN OFF CAUSING POWERPACK MOTOR TO NOT SHUT OFF.  BATTERY DRAINED VERY LOW.  ELECTRI	CAL SYSTEMS OPERATED VERY MARGINAL DURING IFR FLIGHT.  FOUND LEFT DOWNLOCK SUPPORT LOWER PIN CRACKED.  THIS CRACK NOT VI	SIBLE WITH DOWNLOCK ASSEMBLED.  SUSPECT CAUSE, AIRCRAFT OPERATED ON ROUGH LANDING STRIP.  SUBMITTER RECOMMENDS DISASSEMB	LY OF LOCK TO ZYGLOW PINS IF ACFT IS OPERATED ON ROUGH LANDING STRIPS.			1	H	7	1 	3O				A20CE   					 
1996060600883	19960606	00883	SO  	1996	6	6	96ZZZX2877       	1	19960417	G	2434	ALX8421LS	ALTERNATOR      			PIPER 	PA44  	PA44180     	7104402	SO  										LT ENGINE	FAN FAILED      	B			OG5R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	854ND	1833 			89320049	4495008				LEFT ALTERNATOR COOLING FAN FAILED.  FAN APPEARS TO HAVE LOST FIT BETWEEN SHAFT SHOULDER AND PULLEY.  FAN BECAME OFF-CEN	TER AND BROKE THROUGH/SEPARATED SHAFT.  FOUND FAN SEPARATED FROM ALTERNATOR AND LODGED BETWEEN ALTERNATOR BRACKET AND ST	ARTER RING GEAR.				1	L	7	2 	3O				A19S0   					 
1996060600884	19960606	00884	SO  	1996	6	6	96ZZZX2878       	1	19960429	G	7603	455322	CABLE           			PIPER 	PA28  	PA28R201    	7102816	SO  										THROTTLE	BROKE           	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	172ND	5702 				2837007				THROTTLE CABLE BROKE AT ENGINE END WHERE CONTROL CONNECTS TO FUEL INJECTOR.  FOUND STANDS BROKE WHERE CABLE END SWAGES O	NTO CABLE CORE STRANDS.  CABLE IS ORIGINAL PART.  EXTRA ATTENTION IS BEING PLACED ON HIGH TIME CABLES.  THIS SAME CABLE 	IS USED FOR PROPELLER AND MIXTURE CONTROLS.				1	L	7	1 	3O				2A13    					 
1996060600885	19960606	00885	SO  	1996	6	6	96ZZZX2879       	2	19960508	G	8530		CYLINDER        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 1 CYLINDER	HEAD SEPARATED  	B			ETER	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			SO	11	49TD					421C0025	241033R			ON TAKEOFF, NR 1 CYLINDER SEPARATED AT THE HEAD CAUSING ENGINE POWER LOSS.  PILOT SHUT DOWN LEFT ENGINE AND RETURNED TO 	AIRPORT.  ENGINE AND CYLINDER HAD 757 HOURS SINCE OVERHAUL WITH .010 INCH OVERSIZED BARRELS.  CYLINDER TOTAL TIME UNKNOW	N.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996060600886	19960606	00886	CE  	1996	6	6	96ZZZX2880       	1	19960503	G	3710	212CW	PUMP            	AIRBORNE    	OLAL002303  	BEECH 	58    	58          	1152740	CE  										RT ENG VAC	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	666SH	36   				TH1083				FIRST PUMP REPLACED APPEARED TO HAVE OVER 800 HRS IN SERVICE.  REPLACED WITH NEW AIRBORNE PUMP 10/95.  IT LASTED 35.9 HR	S. REPLACED AGAIN 12/95 LASTED 31.9 HRS.  SYSTEM CHECKED WITH AIRBORNE 343 TEST KIT.  PUMP LASTED 16.0 HRS.  REPLACED AN	D SYSTEM CHECKED, LASTED 23.3 HRS.  LAST 3 PUMPS SENT DIRECTLY TO AIRBORNE FOR ANALYSIS.  ALL PUMPS WARRANTIED, BUT HAVE	 BEEN UNABLE TO DETERMINE A CAUSE FOR CONTINUED FAILURES.  HAVE DISCUSSED PROBLEM WITH BEECH, CONTINENTAL, AND AIRBORNE.	  AT THIS POINT, SUSPECT FAULTY PUMPS.		1	L	7	2 	3O				3A16    					 
1996060600887	19960606	00887	SO  	1996	6	6	96ZZZX2881       	1	19960515	G	5610	5490105	WINDOW          			PIPER 	PA31T 	PA31T1      	7103126	SO  										COCKPIT RT SIDE	DEPARTED        	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	05	121BE	1919 				31T8004036				PILOT REPORTS THAT AT 27,000 FEET, RIGHT SIDE COPILOT'S SIDE WINDOW BLEW OUT.  PILOT FURTHER REPORTS THAT UNTIL THIS TIM	E, ALL SYSTEMS WERE NORMAL.  PILOT THEN RETURNED TO BASE WITHOUT FURTHER INCIDENT.  CAUSE FOR WINDOW FAILURE UNKNOWN.					1	L	7	2 	3T				A8EA    					 
1996060600888	19960606	00888	CE  	1996	6	6	96ZZZX2882       	1	19960422	G	5753	58250171	FITTING         		582500514   	CESSNA	441   	441         	2076020	CE  										RT INBD FLAP	CHAFE WING      	B			CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	434AE					4410097				INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO THE SKIN AT THE WING STUB.  FITTING WHICH IS RIVETED TO THE F	ORWARD INBOARD SIDE OF THE RIGHT INBOARD FLAP IS CHAFING AGAINST THE WING SKIN.					1	L	7	2 	3T			RT	A28CE   					 
1996060600889	19960606	00889	CE  	1996	6	6	96ZZZX2883       	1	19960422	G	5753	58250172	FITTING         		582500514   	CESSNA	441   	441         	2076020	CE  										RT INBD FLAP	CHAFE WING      	B			CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	434AE					4410097				INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO THE SKIN AT THE WING STUB.  FITTING WHICH IS RIVETED TO THE F	ORWARD INBOARD SIDE OF THE RIGHT INBOARD FLAP IS CHAFING AGAINST THE WING SKIN.					1	L	7	2 	3T			RT	A28CE   					 
1996060600890	19960606	00890	CE  	1996	6	6	96ZZZX2884       	1	19960422	G	5753	58250171	FITTING         		582500514   	CESSNA	441   	441         	2076020	CE  										RT FLAP	CHAFE WING      	B			CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	441AR	3480 				4410360				INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO SKIN ON WING STUB.  FITTING WHICH IS RIVETED TO THE FORWARD I	NBOARD SIDE OF THE RIGHT INBOARD FLAP IS CHAFING AGAINST THE WING SKIN.					1	L	7	2 	3T			RT	A28CE   					 
1996060600891	19960606	00891	CE  	1996	6	6	96ZZZX2885       	1	19960422	G	5753	58250172	FITTING         		582500514   	CESSNA	441   	441         	2076020	CE  										RT FLAP	CHAFE WING      	B			CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	441AR	3480 				4410360				INBOARD FORWARD SIDE OF RIGHT INBOARD FLAP IS CHAFING INTO SKIN ON WING STUB.  FITTING WHICH IS RIVETED TO THE FORWARD I	NBOARD SIDE OF THE RIGHT INBOARD FLAP IS CHAFING AGAINST THE WING SKIN.					1	L	7	2 	3T			RT	A28CE   					 
1996060600892	19960606	00892	EA  	1996	6	6	96ZZZX2886       	2	19960410	G	7322	8618	LOCKWIRE        	FACET       	MA4SPA      	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					CARB MIX CONTROL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	3567P	2200 			CK815279	288016202	L1271039A			CARBURETOR MIXTURE CONTROL DID NOT FUNCTION PROPERLY.  UPON INSPECTION, PN 86-18 LOCKWIRE, FOUND FATIGUED, CRACKED IN HA	LF, NOT ALLOWING FOR MIXTURE CONTROL SHAFT TO BE PROPERLY OPERATED.					1	L	7	1 	3O	3	O		2A13    	E274				 
1996060600893	19960606	00893	EA  	1996	6	6	96ZZZX2887       	2	19960501	G	8500		ENGINE          			SLNSBY	T67   	T67M260     	8323006	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					POWER PLANT	FAILED          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			AB	AEROBATIC      	1			SW	17	3193K	100  				2233	L2559748A			ENGINE STOPPED IN-FLIGHT AFTER POWER REDUCTION IN SPIN DURING POWER ON OF THE SPIN DEMONSTRATION SORTIE.  ENGINE RESTART	ED WITH START BUTTON.					1	L	7	1 	3O	3	O	NT	A73EU   	1E4				 
1996060600894	19960606	00894	EA  	1996	6	6	96ZZZX2888       	2	19960508	G	7414	M3525	COIL            	SLICK       	4271        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					LT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	8089C	220  			89100029	28769002	RL3247136A			AFTER FLIGHT, ENGINE WOULD NOT START.  BOTH MAGNETOS FOUND TO BE INOPERATIVE, NO SPARK.  IT HAS BEEN FOUND THAT ONE MAG 	GOES INOP.  ENGINE STARTS ON THE GOOD ONE, UNTIL IT FAILS.  AFTER THE ENGINE RPM MEETS OR EXCEEDS 600 RPM, THESE COILS W	ILL MAG CHECK OK.  INSTALLED FACTORY NEW COILS, PN M3975.  OPS SATISFACTORY.				1	L	7	1 	3O	3	O		2A13    	E286				 
1996060600895	19960606	00895	EA  	1996	6	6	96ZZZX2889       	2	19960508	G	7414	M3525	COIL            	SLICK       	4271        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					RT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	8089C	220  			89100015	28769002	RL3247136A			AFTER FLIGHT, ENGINE WOULD NOT START.  BOTH MAGNETOS FOUND TO BE INOPERATIVE, NO SPARK.  IT HAS BEEN FOUND THAT ONE MAG 	GOES INOP.  ENGINE STARTS ON THE GOOD ONE, UNTIL IT FAILS.  AFTER THE ENGINE RPM MEETS OR EXCEEDS 600 RPM, THESE COILS W	ILL MAG CHECK OK.  INSTALLED FACTORY NEW COILS, PN M3975.  OPS SATISFACTORY.				1	L	7	1 	3O	3	O		2A13    	E286				 
1996060600896	19960606	00896	GL  	1996	6	6	96ZZZX2890       	3	19960430	G	6114	D24841	HUB             			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ2Y	BHCJ2YF2    	GL  	PROPELLER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								D2149		INSPECTION FOUND CORROSION ON EXTERIOR AND INTERIOR OF HUB.  SUBMITTER RECOMMENDS REGULAR MAINTENANCE.						1	L	7	2 	3O				3A16    		5	C	P37EA	 
1996060600897	19960606	00897	GL  	1996	6	6	96ZZZX2891       	3	19960430	G	6114	D4887	HUB             													MCAULY	2AF34C	D2AF34C81   	GL  	PROPELLER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								643154		INSPECTION FOUND CORROSION ON EXTERIOR OF HUB WELL OVER .010 INCH DEEP.																5	C	P5EA	 
1996060600898	19960606	00898	GL  	1996	6	6	96ZZZX2892       	3	19960430	G	6111	S82NC2	BLADE           			CESSNA	185   	185         	2072802	CE  						MCAULY	3A32C	D3A32C90    	GL  	THREADS	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					796156			796156		INSPECTION FOUND CORROSION IN BOTTOM OF BLADE THREADS.  SUBMITTER RECOMMENDS REGULAR MAINTENANCE.						1	H	7	1 	3O			NC	3A24    		5	C	P21EA	 
1996060600899	19960606	00899		1996	6	6	96ZZZX2893       	1	19960506	G	3520	417T42633	MASK            	BOEING      	417T4204    															PULL STREAMER	DEFECTIVE       	B			GUMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19										PULL STREAMERS FOR ACTIVATING PASSENGER OXYGEN SYSTEMS FAILED THE PULL TEST.  INSPECTION OF ALL STREAMERS IN STOCK RESUL	TED IN IDENTIFYING APPROXIMATELY 20 PERCENT DEFECTIVE, I.E., BAD CRIMPS, CRIMPS SLIPPING AND FRAYED STRINGS.  BOEING AIR	CRAFT HAS BEEN NOTIFIED AND IS INVESTIGATING THE PROBLEM.  NOTE:  THE DEFECTIVE STREAMERS WERE FOUND PRIOR TO BEING INST	ALLED IN AN AIRCRAFT.																 
1996060600900	19960606	00900	NE  	1996	6	6	96ZZZX2894       	2	19960501	G	7320		P3 LINE         			LEAR  	24    	24D         	5170311	CE  	GE    	CJ610 	CJ6106      	30006	NE  					LT ENGINE	LOOSE           	E				O				OTHER                   				X			ENGINE FLAMEOUT           			CL	CLIMB          	1			SW	15	453					323	240C208A			ON CLIMB-OUT AT 44,000 FEET, THE LT ENGINE FLAMED OUT.  RESTARTED ENGINE AND UPON LANDING, MAINTENANCE INSPECTED THE LEF	T ENGINE INLET, COMPRESSOR BLADES, TURBINE BLADES, INLET GUIDE VANES, INLET GUIDE VANE RIGGING, T-2 HOSE, AND P-3 LINE. 	 FOUND P-3 LINE LOOSE.  TIGHTENED P-3 LINE.				2	L	7	2 	4J	4	J		A10CE   	1E16				 
1996060600901	19960606	00901	SO  	1996	6	6	96ZZZX2895       	1	19960508	G	4940	MS27433300	RELAY           	ALLIEDCONTRL	36100       	GULSTM	G159  	G159        	3952202	SO  										APU	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	5NA				P110	125				APU WOULD NOT START.  FOUND RELAY BURNED.  REPLACED RELAY AND SHORT SECTION OF BATTERY LEAD WIRE, APU WORKS.						2	L	7	2 	4T				1A17    					 
1996060600902	19960606	00902	EA  	1996	6	6	96ZZZX2896       	1	19960430	G	2420		WIRE            			DHAV  	DHC7  	DHC7102     	2802708	EA  										NR 2 AC GEN	CHAFED          	B			WVER	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	09	89068	14957				88				ON TEST FLIGHT, AC NR 2 GENERATOR LIGHT CAME ON.  DURING TROUBLESHOOTING OF SYSTEM, FOUND WIRE 2420-20001E12A-1 GROUNDED	 OUT.  CONDUIT PASSES BETWEEN REAR SPAR AND FLAP PRIMARY CONTROL TUBE.  AREA WHERE WIRES PASS THROUGH IS PRESSED AND WIR	E RUBS CONDUIT.  SUBMITTER STATED IF AC GENERATOR LIGHT COMES ON OR GENERATOR WILL NOT COME ON LINE, THIS IS AN AREA TO 	LOOK AT.			2	H	7	4 	4T			 	A20EA   					 
1996060600903	19960606	00903	SO  	1996	6	6	96ZZZX2897       	1	19960423	G	2910	JPS33513	TUBE ASSY       			LKHEED	1329  	132925      	5263125	SO  										NR 1 ENG T/R	CORRODED        	B			VJ1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	901C	7725 				5218				DURING POST-MAINTENANCE ENGINE RUNS, HYDRAULIC FLUID WAS NOTICED LEAKING FROM LINE.  FURTHER INVESTIGATION REVEALED A SE	RIES OF CORRODED PIN HOLES LOCATED UNDER THE LINE IDENTIFIER TAPE PLACARD.  THIS SITUATION IS SIMILAR TO THE PROBLEM THA	T AFFECTED THE RUDDER BIAS BLEED AIR LINES ON THE RC1125-700 (SB 27-157R2).  SUBMITTER RECOMMENDS PLACARDING TAPE BE REM	OVED FROM LINES AND SURFACES AND BE VISUALLY INSPECTED FOR CORROSION.  OPERATOR CONTROL NR 96-002.			2	L	7	4 	4F				2A1SO   					 
1996060600904	19960606	00904	NM  	1996	6	6	96ZZZX2898       	1	19960130	G	5610	SPSF900272	WINDSHIELD      			AMD   	FALC50	FALCON2000  	2730170	NM  										PILOT	DELAMINATED     	B			CW1R	B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			EA	25	790L	41   				15				PILOT'S FRONT WINDSHIELD OUTER PLY DELAMINATED AT FL 450.  AN UNEVENTFUL EMERGENCY DESCENT AND LANDING WAS PERFORMED INT	O WICHITA, KS.  WINDSHIELD WAS SUBSEQUENTLY REPLACED AND AIRCRAFT RETURNED TO SERVICE.					2	K	7	3 	4F			RT	A50NM   					 
1996060600905	19960606	00905	GL  	1996	6	6	96ZZZX2899       	2	19960513	G	7250	6892828	NOZZLE SHIELD   		23031925    						ALLSN 	250C  	250C30      	03013	GL  					1ST STAGE TURB	CRACKED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17					CAT90284		CAE890278			DURING REPAIR OF THE TURBINE, NOTED THE DEFLECTOR ON THE FIRST STAGE NOZZLE SHIELD WAS BURNED.  CLOSER EXAMINATION REVEA	LED 2 CRACKS IN THE DOME DETAIL.  THE DOME WAS CHECKED FOR PROPER MATERIAL PER DEB A-72-3208 AND WAS FOUND TO CONFORM. S	USPECT THE CAUSE COULD BE A STREAKING FUEL NOZZLE.									3	U			E1GL				 
1996060600906	19960606	00906	NE  	1996	6	6	96ZZZX2900       	2	19960506	G	7200		ENGINE          			LEAR  	25    	25          	5170506	CE  	GE    	CJ610 	CJ6106      	30006	NE  					LT/RT ENGINE	FLAME OUT       	E				B	A			EMER. DESCENT           	UNSCHED LANDING         			X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SW	99	28CK	10530				045	251763			LEFT AND RIGHT ENGINES EXPERIENCED TURBINE AIR FLAME-OUTS.  AIRCRAFT DESCENDED AND ENGINES RESTARTED, UNEVENTFUL LANDING	 MADE.  ENGINES INSPECTED, AND GROUND PERFORMANCE RUN CARRIED OUT.  NO DEFECTS NOTED.  OPERATOR CONTROL NR 5-6-96-28CK.					2	L	7	2 	4J	4	J		A10CE   	1E16				 
1996060600907	19960606	00907	CE  	1996	6	6	96ZZZX2901       	1	19960214	G	3397		WIRE HARNESS    			LEAR  	60    	60LEAR      	5170707	CE  										ELECT PLUG P728	CHAFED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	210FX	55   				064				PILOT REPORTED INTERMITTENT PROBLEMS WITH EXTERIOR LIGHTS AND FLUCTUATION IN HYDRAULIC PRESSURE INDICATION.  TROUBLESHOO	TING FOUND SEVERAL CHAFED AND BROKEN WIRES FROM ELECTRICAL CONNECTOR PLUG NR P-728 GOING TO CONNECTOR J2 ON THE COCKPIT 	CENTER SWITCH PANEL.  THE WIRE BUNDLE WAS HITTING A JUCTION BOX BEHIND THE CENTER INSTRUMENT PANEL.  REPAIRED BY SPLICIN	G IN NEW SECTIONS OF WIRE, AND RE-ROUTING AND SECURING BUNDLE.  OPS CHECKS GOOD.  SUSPECT CAUSE AS INATTENTION TO DETAIL	, LAX QUALITY CONTROL AT THE FACTORY.  SUBMITTER RECOMMENDS INSPECTION OF OTHER LEAR 60'S FOR SIMILAR PROBLEMS IN THE AR	EA AROUND THE ELECTRICAL J-BOX BEHIND THE PANEL.	2	L	7	2 	4F			RT	A10CE   					 
1996060600908	19960606	00908	CE  	1996	6	6	96ZZZX2902       	1	19960213	G	2497		WIRE            			LEAR  	60    	60LEAR      	5170707	CE  										ELEC CONN P10	BURNED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	205FX					005				WHILE TROUBLESHOOTING UNRELATED ELECTRICAL PROBLEM, FOUND 4 INCORRECT PLASTIC WIRE SPLICES TO ELECTRICAL CONNECTOR PLUG 	NR P-10 AT UPPER RT CORNER OF AFT PRESSURE BULKHEAD.  ALL 4 SPLICES WERE BURNED, 2 SEVERED IN HALF.  INSTALLED 4 NEW TEF	LON TYPE WIRE SPLICES PER LEARJET FIELD SERVICE.  SUSPECT CAUSE AS INATTENTION TO DETAIL, OR LAX QUALITY CONTROL EITHER 	AT THE FACTORY OR ANOTHER MAINTENANCE SHOP.  (UNKNOWN WHERE SPLICES INSTALLED.)  SUBMITTER RECOMMENDS INSPECTION OF OTHE	R LEAR 60'S FOR CORRECT HARDWARE AND CHECK LEAR FACTORY TO MAKE SURE INCORRECT HARDWARE IS NO BEING USED ON ASSY LINE.		2	L	7	2 	4F			RT	A10CE   					 
1996060600909	19960606	00909	CE  	1996	6	6	96ZZZX2903       	1	19960430	G	2750	NAS464P413	BOLT            			CESSNA	500   	S550        	2076607	CE  										FLAP CONTROL	MISINSTALLED    	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	9GT					S5500159				PHASE INSPECTION.  INSPECTOR WAS CHECKING FLAP TENSION AND FOUND FLAP CABLE MISALIGNED WHEN FLAPS RETRACTED.  FURTHER IN	VESTIGATION REVEALED INBD FLAP CONTROL BELLCRANK FWD PUSHROD BOLT INSTALLED WITH HEAD OF BOLT UP.  THIS CAUSED INTERFERE	NCE WITH THE SHANK, HITTING FLAP CABLE.  PARTS AND MM SHOWS PROPER INSTALLATION WITH HEAD OF BOLT DOWN.  TO PROVIDE CLEA	RANCE - NOTE:  ONLY THE INBD BELLCRANK BOLT IS INSTALLED WITH HEAD DOWN.  OTBD BELLCRANKS, THE BOLT HEAD IS INSTALLED IN	 THE 'UP' POSITION.		1	L	7	2 	4F			RT	A22CE   					 
1996060600910	19960606	00910	WP  	1996	6	6	96ZZZX2904       	2	19960315	G	7250	3587591	BEARING         			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENG NR 4	FAILED          	B	L		MJ1R	E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			EA	11	130F	2399 				044	P74225			DURING DESCENT, FLT CREW OBSERVED FLUCTUATING FUEL FLOW ON RT ENG FOLLOWED BY VIBRATION AND NOISE.  CREW REDUCED POWER S	ETTING TO IDLE AND CONTINUED FLT.  DURING FINAL APROACH, OIL PRESSURE BEGAN TO FLUCTUATE AND LOW OIL PRESSURE CAUTION LI	GHT ILLUMINATED.  PILOT COMMANDED A SHUT-DOWN AND LANDED ACFT WITHOUT FURTHER INCIDENCE.  UNABLE TO ROTATE EITHER THE LP	 OR HP SPOOLS.  EXAMINATION OF INLET AREA SHOWED NO EVIDENCE OF FOREIGN OBJECT INGESTION.  METAL CONTAMINATION FND IN OI	L TANK, XSFER GEARBOX AND OIL FILTER, FILTER BYPASS BUTTON WAS NOT OUT.  UNABLE TO DISASSEMBLE OIL PUMP DUE TO INTERNAL 	DAMAGE.  ENG IN-FLT SHUTDOWN CAUSED BY FAILURE OF NR 4 BEARING AND SUBSEQUENT INTERNAL DOMESTIC OBJECT DAMAGE TO ENGINE.	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1996060600911	19960606	00911	EU  	1996	6	6	96ZZZX2905       	1	19960321	G	2730		BELLCRANK       			SUKHOI	SU29  	SU29        	9850103	EU  										ELEVATOR	BOLT MISSNG     	G	L	A		A				UNSCHED LANDING         				O			OTHER                     			AB	AEROBATIC      	1			SW	03	729SU					7804				ALNOT ISSUED ON A SINGLE ENGINE SUKHOI SU-29 WHEN 3 HRS OVERDUE.  ALNOT REPORTED MISSING AIRCRAFT HAD BEEN OVER AN AEROB	ATICS PRACTICE AREA.  ACFT HAD CRASHED, FATALLY INJURING PILOT AND DESTROYING ACFT.  DURING EXAMINATION OF REMNANTS OF E	LEVATOR CONTROL SYSTEM, A BELLCRANK WAS FND WITH UPPER ATTACHING HOLES SHOWING NO VISIBLE DEFORMATION AND NO VISIBLE BEN	DING OF THE EARS, ATTACH BOLT AND ROD END WERE MISSING.  BELLCRANK ONLY ITEM IN ELEVATOR OR AILERON CONTROL SYS THAT DID	 NOT DISPLAY SOME IMPACT DAMAGE.  BELLCRANK REMOVED AND SENT TO NTSB LAB FOR EXAMINATION, PRELIMINARY REPORT INDICATES A	LTHOUGH A BOLT HAD BEEN INSTALLED AT ONE TIME, NO INDICATION A BOLT WAS INSTALLED AT TIME OF IMPACT.	1	L	7	1 	3R			NC	USSR    					 
1996061300039	19960613	00039	SO  	1996	6	13	96ZZZX2906       	1	19960520	G	2432	36H120	CELL            	MARATHON    	MA5         	GULSTM	G1159 	G1159       	3953505	SO  										BATTERY	DAMAGED         	B		A	JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2HF				9404268	221				THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND SENT TO A BATTERY FACILITY FOR SCHEDULED MAINTENANCE.  DISCOVERED ALL 19 C	ELLS HAD TO BE CONDEMNED DUE TO CELL SEPARATOR DAMAGE.  ALL 19 CELLS WERE REPLACED AND THE SCHEDULED MAINTENANCE CONTINU	ED.  THE BATTERY WAS RETURNED TO SERVICE AND REINSTALLED IN THE AIRCRAFT.  THE AIRCRAFT WAS RETURNED TO SERVICE.  (NOTE:	  NO PROBLEMS WERE REPORTED BY THE CREW CONCERNING THIS BATTERY WHILE IN SERVICE.  THIS IS ONE OF SEVERAL MA5 BATTERIES 	EXPERIENCING THIS PROBLEM.   SUBMITTER RECOMMENDS IMPROVED CELL SEPARATOR QUALITY AND CHECK OF CURRENT SERVICING PROCEDU	RES.  200 HOURS SINCE DEEP CYCLE, (CELL S/N 9404268).	2	L	7	2 	4F			RT	A12EA   					 
1996061300040	19960613	00040	SO  	1996	6	13	96ZZZX2907       	1	19960520	G	2432	36H120	CELL            	MARATHON    	MA5         	GULSTM	G1159 	G1159       	3953505	SO  										BATTERY	DAMAGED         	B		A	JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	711RL				9404267	025				THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND SENT TO A BATTERY FACILITY FOR SCHEDULED MAINTENANCE.  DISCOVERED THAT ALL	 19 CELLS HAD TO BE CONDEMNED DUE TO CELL SEPARATOR DAMAGE.  ALL 19 CELLS WERE REPLACED AND THE SCHEDULED MAINTENANCE CO	NTINUED.  THE BATTERY WAS RETURNED TO SERVICE AND REINSTALLED IN THE AIRCRAFT.  THE AIRCRAFT WAS RETURNED TO SERVICE.  (	NOTE:  NO PROBLEMS WERE REPORTED BY THE CREW CONCERNING THIS BATTERY WHILE IN SERVICE.  THIS IS ONE OF SEVERAL MA5 BATTE	RIES EXPERIENCING THIS PROBLEM.  SUBMITTER RECOMMENDS IMPROVED CELL SEPARATOR QUALITY AND CHECK OF CURRENT SERVICING PRO	CEDURES.  200 HOURS SINCE DEEP CYCLE, (CELL S/N 9404267).	2	L	7	2 	4F			RT	A12EA   					 
1996061300041	19960613	00041	SO  	1996	6	13	96ZZZX2908       	1	19960520	G	2432	36H120	CELL            	MARATHON    	MA5         	GULSTM	G1159 	G1159       	3953505	SO  										BATTERY	DAMAGED         	B		A	JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2HF				9404271	221				THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND SENT TO A BATTERY FACILITY FOR SCHEDULED MAINTENANCE.  DISCOVERED ALL 19 C	ELLS HAD TO BE CONDEMNED DUE TO CELL SEPARATOR DAMAGE.  ALL 19 CELLS WERE REPLACED AND THE SCHEDULED MAINTENANCE CONTINU	ED.  THE BATTERY WAS RETURNED TO SERVICE AND REINSTALLED IN THE AIRCRAFT.  AIRCRAFT WAS RETURNED TO SERVICE.  (NOTE:  NO	 PROBLEMS WERE REPORTED BY THE CREW CONCERNING THIS BATTERY WHILE IN SERVICE.  THIS IS ONE OF SEVERAL MA5 BATTERIES EXPE	RIENCING THIS PROBLEM.  SUBMITTER RECOMMENDS IMPROVED CELL SEPARATOR QUALITY AND CHECK OF CURRENT SERVICING PROCEDURES. 	 200 HOURS SINCE DEEP CYCLE, (CELL S/N 9404271).	2	L	7	2 	4F			RT	A12EA   					 
1996061300042	19960613	00042	SO  	1996	6	13	96ZZZX2909       	1	19960520	G	2432	36H120	CELL            	MARATHON    	MA5         	GULSTM	G1159 	G1159       	3953505	SO  										BATTERY	DAMAGED         	B		A	JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	711RL				9403011	25				THE BATTERY WAS REMOVED FROM THE AIRCRAFT AND SENT TO A BATTERY FACILITY FOR SCHEDULED MAINTENANCE.  DISCOVERED ALL 19 C	ELLS HAD TO BE CONDEMNED DUE TO CELL SEPARATOR DAMAGE.  ALL 19 CELLS WERE REPLACED AND THE SCHEDULED MAINTENANCE CONTINU	ED.  THE BATTERY WAS RETURNED TO SERVICE AND REINSTALLED IN THE AIRCRAFT.  THE AIRCRAFT WAS RETURNED TO SERVICE.  (NOTE:	  NO PROBLEMS WERE REPORTED BY THE CREW CONCERNING THIS BATTERY WHILE IN SERVICE.  SUBMITTER RECOMMENDS IMPROVED CELL SE	PARATOR QUALITY AND CHECK OF CURRENT SERVICING PROCEDURES.  200 HOURS SINCE DEEP CYCLE, (CELL S/N 9403011).		2	L	7	2 	4F			RT	A12EA   					 
1996061300043	19960613	00043	CE  	1996	6	13	96ZZZX2910       	1	19960513	G	2160	12958010	LIMITER         			LEAR  	35    	35A         	5170602	CE  										DUCT TEMPERATURE	FAILED          	B			XNJR	O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			WP	21	137RS	7663 			1213	183				PILOT REPORT CABIN TEMPERATURE UNCONTROLLABLE IN MANUAL MODE, FULL HOT IN AUTO.  FOUND DUCT TEMPERATURE LIMITER HAD FAIL	ED.  UPON LIMITER REMOVAL, FOUND PART HAD COMPLETELY SEPARATED CAUSING THE BELLOWS TO EXPAND AND MELT.					2	L	7	2 	4F				A10CE   					 
1996061300044	19960613	00044	WP  	1996	6	13	96ZZZX2912       	1	19960509	G	5320		SHEAR CLIP      			DOUG  	DC9   	DC931       	3022065	WP  										FS 945 L15R	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	977ML					47329				DURING A SCHEDULED INSPECTION, SHEAR CLIP LOCATED BETWEEN LONGERONS 15R AND 16R WAS FOUND CRACKED 2 INCHES.  REMOVED CRA	CKED SHEAR, FABRICATED AND INSTALLED NEW CLIP IAW DC-9 SRM 53-03, FIGURE 28 AND DC-9, MM 55-00.					2	L	7	2 	4F				A6WE    					 
1996061300045	19960613	00045	WP  	1996	6	13	96ZZZX2913       	1	19960509	G	5311		FRAME           			DOUG  	DC9   	DC931       	3022065	WP  										FS 1074	CRACKED         	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	977ML					47239				DURING A SCHEDULED INSPECTION, CANTED FRAME WAS FOUND CRACKED AT FS 1074 L3 LT.  STOP DRILLED CRACK.  FABRICATED AND INS	TALLED 5 EACH REPAIR PARTS IAW DC-9 SR 09530086.					2	L	7	2 	4F				A6WE    					 
1996061300046	19960613	00046	CE  	1996	6	13	96ZZZX2914       	1	19960520	G	3251	4291006	ACTUATOR        			BEECH 	99    	99          	1154002	CE  										NLG STEERING	FAULTY          	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2880A	448  			1007	U109				NOSE GEAR STEERING ACTUATOR FAILED INTERNALLY - WILL NOT GO FULL TRAVEL EITHER DIRECTION.						1	L	7	2 	3T				A14CE   					 
1996061300047	19960613	00047	WP  	1996	6	13	96ZZZX2915       	1	19960514	G	5320		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										WINDOW NR 28 LT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND WINDOW NR 28 LEFT HAS EVIDENCE OF CORROSION AROUND FRAME INNER SURFACE.  REMOVED DAMAGED FRAME AND	 INSTALLED NEW ONE IAW SRM 51-1-20D.  TREATED AND PRIMED IAW SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996061300048	19960613	00048	CE  	1996	6	13	96ZZZX2916       	1	19960427	G	2133	21034012	REGULATOR       			BEECH 	MU300 	400BEECH    		CE  										CABIN ALTITUDE	FAULTY          	B			QMZR	O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			EA	05	295FA	1013 			0564	RK68				CABIN ALTITUDE WOULD NOT DESCEND WITH AIRCRAFT.  MAINTENANCE FOUND NO VACUUM ON TEST PORT NR 3.  FURTHER TROUBLESHOOTING	 ISOLATED FAULTY VACUUM REGULATOR.  SUSPECT CAUSE:  STICKY BELLOWS INSIDE REGULATOR.  'COLD-SOAKING' CAN BE RULED OUT.					2	H	7	2 	4F			RT	A16SW   					 
1996061300050	19960613	00050	WP  	1996	6	13	96ZZZX2918       	1	19960517	G	7120	39357391	BOLT            			DOUG  	DC9   	DC983       	3022083	WP  										LT ENG MOUNT	CRACKED         	B		A	JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	832RA					53044				ULTRASONIC INSPECTION OF LT FORWARD UPPER NR 1 ENGINE MOUNT (YOKE) BOLT FOUND CRACKED.  REF:  OPERATOR CONTROL NR 00001.						2	L	7	2 	4F			RT	A6WE    					 
1996061300051	19960613	00051	NE  	1996	6	13	96ZZZX2919       	2	19960510	G	7210	7757535	IDLER GEAR      		7758002     	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					LT PROP GRBOX	FAILED          	B	S	A	SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		3863 			C6411160					DISASSEMBLY OF THE PROPELLER GEARBOX REVEALED THE LT IDLER GEAR (775753-5 ITEM 40 OF FIG 5 IN MANUAL 72-11-02) WEB FAILE	D AND THE GEAR HAD BROKEN THROUGH THE GEARBOX HOUSING.  THE FORWARD INPUT ROLLER BEARING (775765-1 ITEM 180 OF FIG 8) HA	D BROKEN AND THE ROLLERS FOUND IN THE BOTTOM OF THE GEAR CASE.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6				 
1996061300052	19960613	00052	EU  	1996	6	13	96ZZZX2920       	1	19960517	G	5312		BULKHEAD        			AGUSTA	A109  	A109A2      	0260120	EU  										AFT CABIN	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	109TS	2234 				7276				INSPECTION FOUND AFT CABIN BULKHEAD LOCATED AT STA + 3.5 METERS, AT WATERLINE + 1 METER (LEFT SIDE), 3 INCH CRACK FROM I	NSPECTION LIGHTENING HOLE TO BOTTOM OF LT MAIN ROTOR TRANSMISSION VERTICAL STRUT ATTACH BRACKET.  SUSPECT BULKHEAD FABRI	CATED FROM MATERIAL TOO 'THIN' TO ALLOW FOR HIGH GROSS-WEIGHT OPERATION, OR MANUFACTURING FLAW.				1	G	7	2 	3U				H7EU    					 
1996061300053	19960613	00053	SW  	1996	6	13	96ZZZX2921       	1	19960514	G	7120	74612171123	MOUNT           			BELL  	47    	47G5A       	1181034	SW  										ENGINE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	715BH	1736 	506  		822185	25105				DURING 100-HOUR ANNUAL INSPECTION, CRACK NOTED AT FORWARD TRUNNION CLUSTER.  AREA WAS STRIPPED OF PAINT AND DYE CHECKED.	  CRACK CONFIRMED.  A BULLETIN WAS ISSUED BY THE MFG 3-7-96.  THIS WAS A PMA'D PART.					1	G	7	1 	3O				2H3     					 
1996061300054	19960613	00054	WP  	1996	6	13	96ZZZX2922       	1	19960425	G	5302	269A232011	ATTACH FITTING  			HUGHES	269   	269C        	4470504	WP  										TAILBOOM	CRACKED         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	300KY	700  			S825	S1433				DURING ROUTINE INSPECTION, FOUND EXCESSIVE PLAY WHEN INSPECTING SECURITY OF VERTICAL STABILIZER.  DISCOVERED LOOSE ATTAC	HMENT HARDWARE AT FORWARD END OF THE ATTACHMENT OF THE TAILBOOM ASSEMBLY.  SUBMITTER RECOMMENDS A RETORQUE OF ATTACHMENT	 HARDWARE AT A CERTAIN TIME FOLLOWING INITIAL INSTALLATION OF TAILBOOM ASSEMBLY.				1	G	7	1 	3O				4H12    					 
1996061300055	19960613	00055	NE  	1996	6	13	96ZZZX2923       	1	19960420	G	6320	8528613	THERMOSTAT      			SKRSKY	S64   	S64F        		NE  										MAIN GEARBOX	FAULTY          	B			JYDR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	09	163AC	3893 	78   		A6111	64093				AIRCRAFT IN FORWARD FERRY FLIGHT ATTITUDE.  OIL COOLER SYSTEM FUNCTIONING PROPERLY.  OVERTEMP OF MGB INDICATION OBSERVED	 ON MASTER CAUTION PANEL.  FLIGHT CREW SECURED SAFE LANDING LOCATION AND OBTAINED SAFE LANDING WITHOUT INCIDENT IN LESS 	THAN 1 MINUTE OF INITIAL WARNING LIGHT.				2	G	7	2 	4U				H6EA    					 
1996061300217	19960613	00217	GL  	1996	6	13	96ZZZX2935       	2	19960510	G	7230		ROTOR ASSY      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	DEFECTIVE       	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			WP	07	911FT	3888 	1257 			811036D	CAE836410			POWER CHECK RESULTS - LOW POWER.  COMPRESSOR ASSY REPLACED, DISCREPANCY CLEARED.  (ALLISON MODEL 250 REPORT NR A 134718)	.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996061300218	19960613	00218	GL  	1996	6	13	96ZZZX2936       	1	19960521	G	6700	KUP14D5524	RELAY           			ENSTRM	F28   	F28F        	3300412	GL  										FLT CONTROL	FAILED          	C			PP0M	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	01	8626S	1057 				786				POINTS IN RELAY FUSE TOGETHER CAUSING RUNAWAY TRIM ACTION RESULTING IN UNCONTROLLED ATTITUDES OF AIRCRAFT.  REQUIRES BOT	H PILOTS ON CYCLIC TO OVERRIDE.  RELAY MFG HAS INDICATED THIS IS NOT THE CORRECT RELAY FOR THIS APPLICATION.  INSTALLED 	NEW RELAY PER MM.				1	G	7	1 	3O				H1CE    					 
1996061300219	19960613	00219	GL  	1996	6	13	96ZZZX2937       	1	19960502	G	6320	28131709R	TRANSMISSION    			ENSTRM	F28   	F28F        	3300412	GL  										MAIN ROTOR	MAKING METAL    	C			PP0M	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	01	8626S	558  			9332281C	786				TRANSMISSION GENERATING CHIP LIGHTS EVERY FIVE MINUTES OF OPERATION.  TOOTH OF RING GEAR HAD CHUNK MISSING 1.25 INCHES L	ONG BY .25 INCH DEEP.  INSTALLED ZERO TIME OVERHAUL TRANSMISSION.					1	G	7	1 	3O				H1CE    					 
1996061300377	19960613	00377	GL  	1996	6	13	96ZZZX2943       	2	19960507	G	7200		ENGINE          			AGUSTA	A109  	A109C       	0260118	EU  	ALLSN 	250C  	250C20      	03013	GL  					NR 2	MAKING METAL    	D		A		K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	03	97CH	337  				7657	CAE295546			NR 2 ENGINE REMOVED DUE TO EXCESSIVE CHIP LIGHTS.  THIS IS THE 3RD OCCURRENCE WITH THIS ENGINE.  ENGINE TT, 336.5 HRS SI	NCE NEW.					1	G	7	2 	3U	3	U		H7EU    	E4CE				 
1996061300378	19960613	00378	SW  	1996	6	13	96ZZZX2944       	1	19960520	G	6230	214040260105	ADAPTER         			BELL  	214   	214ST       	1182106	SW  										MAST ASSY	CRACKED         	B			HEER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				MAST ASSY ADAPTER HAS CRACK AROUND 90 DEGREES OF CIRCUMFERENCE ON LOWER OR BOTTOM SURFACE, CRACK VISIBLE ON TOP SURFACE.	  NOTE:  ACFT DELIVERY DATE IS 12/27/94.					2	G	7	2 	4U				H10SW   					 
1996061300379	19960613	00379	WP  	1996	6	13	96ZZZX2945       	1	19960515	G	6220	514397	HUB             			HILLER	UH12  	UH12E       	4360122	WP  										M/R	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	48219	2340 	800  		1153	2166				HUB FOUND CRACKED INSIDE HUB AT CONTROL ROTOR TRUNNION STUD HOLE.  CRACK FOUND AT 50-HOUR DYE PENETRANT INSPECTION DURIN	G C/W AD 73-20-3.  SUBMITTER STATED CRACKS IN THIS AREA OCCUR ON OCCASION.					1	G	7	1 	3O				4H11    					 
1996061300380	19960613	00380	CE  	1996	6	13	96ZZZX2946       	1	19960507	G	3230	08401253	TUBE ASSY       			CESSNA	310   	310L        	2074230	CE  										NLG GEAR DRIVE	BENT            	G	L			O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	05	3305X	3911 				310L0155				NOSE LANDING GEAR WAS EXTENDED, BUT DID NOT LOCK IN THE DOWN POSITION.  SUBSEQUENT INVESTIGATION REVEALED THE NLG INTERM	EDIATE GEAR DRIVE TUBE ASSY WAS BENT.  THE ANNUAL AND 100-HOUR INSPECTION WERE COMPLETED APRIL 19, 1996.  TACHOMETER TIM	E 766.3.  TOTAL TIME:  3,900.8 HRS.  AIRCRAFT WAS PAINTED DECEMBER 22, 1995.  THE NLG MAIN DRIVE TUBE ASSY WAS BROKEN. S	UBMITTER STATED IMPROPER RIGGING MAY BE THE CAUSE.			1	L	7	2 	3O				3A10    					 
1996061300381	19960613	00381	CE  	1996	6	13	96ZZZX2947       	1	19960522	G	2710	581510324CR	CONTROL CABLE   			CESSNA	404   	404CESSNA   	2075901	CE  										AILERONS	WORN            	B	S	A	APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	41SA	547  				4040023				ALL FOUR AILERON CABLES CONTINUALLY WEAR RAPIDLY AT PULLEYS IN WING TRAILING EDGE.  PULLEYS ACT AS FAIR LEADS, NO CABLE 	ANGLE CHANGE.  SUBMITTER STATES AIRFLOW CAUSES CABLES TO VIBRATE ON PULLEYS AND WEAR THROUGH STRANDS.					1	L	7	2 	3O			 	A25CE   					 
1996061300382	19960613	00382	CE  	1996	6	13	96ZZZX2948       	1	19960522	G	2710	581510320CR	CONTROL CABLE   			CESSNA	404   	404CESSNA   	2075901	CE  										AIL WS 92.28	WORN            	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	41SA	547  				4040023				ALL FOUR AILERON CABLES CONTINUALLY WEAR RAPIDLY AT PULLEYS IN WING TRAILING EDGE.  PULLEYS ACT AS FAIR LEADS, NO CABLE 	ANGLE CHANGE.  SUBMITTER STATES AIRFLOW CAUSES CABLES TO VIBRATE ON PULLEYS AND WEAR THROUGH STRANDS.					1	L	7	2 	3O			 	A25CE   					 
1996061300383	19960613	00383	SO  	1996	6	13	96ZZZX2949       	1	19960405	G	3230	40336000	LINK            			PIPER 	PA31T 	PA31T1      	7103126	SO  										NLG RT DRAG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	200FB	4970 				31T7904037				CHECKED DRAG LINK FOR CRACKS AFTER READING REPORT IN AIRWORTHINESS ALERTS.  PAINT HAD FAINT CRACK IN IT, SO PART WAS STR	IPPED AND DYE CHECKED AT WHICH TIME A DEEP CRACK ACROSS THE FRONT END OF THE LEFT EAR WAS FOUND.  DRAG LINK WAS REPLACED	 BY NEW PART AND NOSE GEAR RIGGED.				1	L	7	2 	3T				A8EA    					 
1996061300384	19960613	00384	SO  	1996	6	13	96ZZZX2950       	1	19960503	G	2710	62102001	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  										RT AIL BELLCRANK	CRACKED         	B		A	NCLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	6777W	4400 				2820905				BELLCRANK SUPPORT WAS FOUND CRACKED AT THE FORWARD BOLT HOLE.  LEFT AND RIGHT BELLCRANKS WERE NOT MAKING CONTACT WITH TH	E AFT STOPS.  STOPS WERE APPROXIMATELY .50 INCH AWAY FROM THE BELLCRANKS.  BOTH BELLCRANKS APPEAR TO BE IMPROPERLY RIGGE	D BECAUSE THE STOPS ARE ALMOST ALL THE WAY OUT OF THE NUT BEFORE THEY CONTACT THE BELLCRANK.				1	L	7	1 	3O				2A13    					 
1996061300385	19960613	00385	SO  	1996	6	13	96ZZZX2951       	1	19960429	G	2730	452855	BEARING         			PIPER 	PA38  	PA38112     	7103812	SO  										ELEV HORZ STAB	MISMANUFACTURED 	D	L	A		K				NONE                    				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			SW	15	91BA					3878A0240				ORIGINAL BEARING WAS A BALL BEARING TYPE WITH PIPER PN 25704-00.  PART NUMBER HAS BEEN SUPERCEDED ON PN 452-855.  THE NE	W REPLACEMENT BEARINGS ARE A ROD END TYPE OF BEARING.  THE OUTSIDE DIAMETER OF THE ORIGINAL TYPE IS .686 INCH.  THE NEW 	TYPE MEASURES .6875 INCH O.D.  PRESSING THE NEW BEARING IN CAUSED THE REMOVAL OF MATERIAL IN THE INSIDE DIAMETER OF BEAR	ING BOSSES.  IT ALSO LOCKED UP THE BEARING AND CAUSED SEVERE STIFFNESS IN THE CONTROL YOKE WHICH, IN TURN, MADE CONTROLL	ING THE PITCH OF ACFT DIFFICULT.  (4 EACH REPORTS RECEIVED ON THIS P/N AND CONDITION).  SUBMITTER STATED PIPER SHOULD RE	TURN TO ORIGINAL TYPE BEARING OR PROVIDE FURTHER INSTRUCTIONS FOR SUCCESSFUL INSTALLATION OF NEW TYPE BEARING.	1	L	7	1 	3O				A18SO   					 
1996061300386	19960613	00386	EA  	1996	6	13	96ZZZX2952       	2	19960501	G	8520	AL12186	NUT             			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					CON ROD BOLT	MISMANUFACTURED 	H	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	2586Y					328506007	L2254348A			ASSEMBLING THIS ENGINE DURING NORMAL OVERHAUL, THE ROD BOLT NUT WAS TORQUED AND THE BOLT MEASURED FOR STRETCH LENGTH.  T	HE MICROMETER DID NOT SMOOTHLY SNUG UP.  THE BOLT'S OUTBOARD EDGE MEASURED 2.255 INCHES AND INBOARD EDGE MEASURED, 2.259	 INCHES.  BELIEVING THE BOLT TO BE DEFECTIVE, IT WAS REMOVED.  WHEN SPUN, THE NUT HAD A WOBBLE.  INSPECTION FOUND THE TH	READS OF THE NUT WERE NOT SQUARE WITH THE FACE AND THIS CAUSED THE BOLT TO BE BENT WHEN TORQUED.  THE BOLT WAS STRAIGHT 	WHEN UNTORQUED.  REPLACED BOTH THE NUT AND BOLT WITH NEW PARTS.		1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996061300387	19960613	00387	SO  	1996	6	13	96ZZZX2953       	1	19960510	G	2710		CONTROL CABLE   			MAULE 	M5    	M5235C      	5460135	SO  										LEFT AILERON	MISROUTED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	10SY	528  				7487C				DURING ANNUAL INSPECTION, LT AILERON CABLE WAS FOUND ROUTED OVER LIFT STRUT BRACKET.  THESE CABLES ARE PART OF SB 12, BU	T NOT LISTED FOR THIS MODEL AIRCRAFT.  CABLE WAS REMOVED AND INSPECTED FOR DAMAGE.  NONE WAS FOUND.  CABLE HAD 84 HRS TI	ME SINCE REASSEMBLY OF WINGS.  CABLE REINSTALLED AND CORRECT CABLE TENSION SET.				1	H	7	1 	3O			 	3A23    					 
1996061300388	19960613	00388	CE  	1996	6	13	96ZZZX2954       	1	19960521	G	5711	35410158	SPAR            			BEECH 	35    	A35         	1151504	CE  										AFT CARRY THRU	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	8426A	4505 				D1863				DURING ANNUAL INSPECTION, MECHANIC BEGAN TO REPAIR FLOORBOARD UNDER FUSELAGE AUXILIARY FUEL TANK.  UPON REMOVAL OF AUXIL	IARY FUEL TANK AND FLOORBOARD, DISCOVERED THE REAR CARRY-THROUGH SPAR WAS CORRODED BEYOND REPAIR.  MECHANIC NOTES THAT A	CCESS TO THIS AREA FOR ROUTINE INSPECTION IS NOT ACCESSIBLE.  MECHANIC SUGGESTS INSTALLATION OF INSPECTION PANELS IN THI	S AREA TO ALLOW VISUAL INSPECTION CAPABILITIES OF REAR CARRY-THROUGH SPAR AFT FACE.			1	L	7	1 	3O				A777    					 
1996061300389	19960613	00389	SO  	1996	6	13	96ZZZX2955       	1	19960426	G	7160	P151936	AIR FILTER      	DONALDSON   		PIPER 	PA46  	PA46310P    	7104605	SO  										INDUCT AIR	SEAL SEPARATION 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	05	6908P					468508062				FOUND AIR FILTER, PN B13151936, MATING FOAM SEAL ONE-THIRD UNGLUED WHEN REMOVED FROM NEW SHIPPING BOX.  SUBMITTER STATES	 THIS IS THE SAME PROBLEM TYPE AS BRACKETT MFG SEAL (AD 95-03-02).					1	L	7	1 	3O				A25SO   					 
1996061300390	19960613	00390	SO  	1996	6	13	96ZZZX2956       	1	19960520	G	2710	62102001	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  										RT AIL BELLCRANK	CRACKED         	B			NCLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	38194	2840 				287725268				SUPPORT WAS FOUND CRACKED AT THE FORWARD BOLT HOLE.  LEFT AND RIGHT BELLCRANKS WERE NOT MAKING CONTACT WITH THE AFT STOP	S.  STOPS WERE APPROXIMATELY .50 INCH AWAY FROM THE BELLCRANKS.  BOTH BELLCRANKS APPEAR TO BE IMPROPERLY RIGGED BECAUSE 	THE STOPS ARE ALMOST ALL THE WAY OUT OF THE NUT BEFORE THEY CONTACT THE BELLCRANK.				1	L	7	1 	3O				2A13    					 
1996061300391	19960613	00391	SO  	1996	6	13	96ZZZX2957       	1	19960503	G	2710	67550000	SUPPORT         			PIPER 	PA28  	PA28R180    	7102809	SO  										RT AIL BELLCRANK	CRACKED         	B			NCLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4573J	3453 				28R30438				BELLCRANK SUPPORT FOUND CRACKED AT THE FORWARD BOLT HOLE.  LEFT AND RIGHT BELLCRANKS WERE NOT MAKING CONTACT WITH THE AF	T STOPS.  STOPS WERE APPROXIMATELY .50 INCH AWAY FROM THE BELLCRANKS.  BOTH BELLCRANKS APPEAR TO BE IMPROPERLY RIGGED BE	CAUSE THE STOPS ARE ALMOST ALL THE WAY OUT OF THE NUT BEFORE THEY CONTACT THE BELLCRANK.				1	L	7	1 	3O				2A13    					 
1996061300392	19960613	00392	SW  	1996	6	13	96ZZZX2958       	1	19960515	G	2823	506251	VALVE           			AIRTRC	AT500 	AT501       		SW  										FUEL SELECT	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1006T	1355 				5010030				DURING OPERATIONS FOR WEIGHT & BAL PURPOSES, FUEL VALVE TURNED TO 'OFF'.  AS VALVE WAS BEING TURNED BACK TO 'ON', IT BEC	AME STUCK IN INTERMEDIATE POS.  LINKAGE BTWN COCKPIT & VALVE CHKD & FND IN PROPER ORDER.  AFTER 2 OR 3 ATTEMPTS, VALVE R	ETND TO 'ON'.  WHILE PERFORMING A COLD FUEL TEST, VALVE AGAIN BECAME STUCK & COULD NOT BE RETND TO OPEN.  AFTER SEVERAL 	ATTEMPTS, VALVE WAS RETND TO OPEN.  FUEL BOOST PUMP TURNED ON BUT COULD NOT GET FUEL TO ENG LINE.  VALVE REMVD & COVER P	LATE REMVD FROM VALVE.  CAM THAT POSITIONS INTERNAL PLUNGERS BROKEN & JAMMED IN OUTLET PORT.  PLUNGERS BEING SPRING LOAD	ED TO CLOSED POS WERE PREVENTING FUEL TO FLOW TO ENG.  HAD MALFUNCTION OCCURRED DURING FLIGHT, ENG WOULD HAVE QUIT.	1	L	7	1 	3T			NC	A17SW   					 
1996061300393	19960613	00393	CE  	1996	6	13	96ZZZX2959       	1	19960516	G	5711		SPAR            			CESSNA	500   	550         	2076604	CE  										LOWER CAP	CORRODED        	B	P		GQVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	45ME	9941 				5500080				UPON REMOVING A SKIN PANEL FROM RT WING AFT OF LANDING GEARWELL TO FACILITATE REPAIR OF SMALL CRACKS IN WING SKIN, DISCO	VERED CORROSION ON LOWER AFT SPAR CAP FROM WING ROOT TO WS 74.5.  REMOVED CORROSION FROM AFFECTED AREAS OF SPAR CAP AFTE	R CONTACTING CESSNA ENGINEERING FOR APPROVAL.  DEPTH OF CORRODED AREAS WAS UP TO 20 PERCENT OF SPAR CAP THICKNESS FROM W	S 31.00 TO WS 34.00 AND 10 PERCENT OF SPAR CAP THICKNESS FROM WS 34.00 TO WS 74.5.  THERE WAS NO OBVIOUS REASON FOR CORR	OSION IN THIS AREA.  THE SAME WING SKIN SECTION WAS REMOVED FROM LT WING AND NO CORROSION NOTED ON LT LOWER AFT SPAR CAP	.	1	L	7	2 	4F				A22CE   					 
1996061300394	19960613	00394	NE  	1996	6	13	96ZZZX2960       	2	19960514	G	8550		CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 8	CRACKED         	H	S		MWRG	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			EA	17	6620Q					1693	10419			PILOT EXPERIENCED POPPING, MISFIRING, AND POWER LOSS DURING TAKEOFF.  AN UNSUCCESSFUL OFF AIRPORT LANDING MADE.  AIRCRAF	T FLIPPED OVER AND WAS SUBSTANTIALLY DAMAGED.  INSPECTION REVEALED NR 8 CYLINDER CRACKED BETWEEN SPARK PLUG BOSSES AND D	OWN TO BARREL ON BACK SIDE OF CYLINDER.  AIRCRAFT HAD BEEN OPERATED SEVERAL TIMES DURING AG OPERATIONS ON THIS DAY.  SMO	H:  930.0 HRS.			1	Q	7	1 	3R	3	R		1A16    	5E2				 
1996061300395	19960613	00395	GL  	1996	6	13	96ZZZX2961       	3	19960517	G	6111		BLADE           			BEECH 	100   	B100        	1152919	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP BACKSIDE	CRACKED         	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	86TR		1910 			BE22		CD1028		CORPORATE TECHNICIAN NOTICED A FLAW IN BACKSIDE OF A PROPELLER BLADE.  UPON FURTHER INSPECTION, FLAW WAS DISCOVERED TO B	E A CRACK APPROXIMATELY 3.25 INCHES IN LENGTH, AND 14.3750 INCHES FROM THE TIP OF THE BLADE.  CRACK SPAN WIDTHWISE, AND 	COULD BE SEEN TO OPEN UP WHEN BLADE WAS FLEXED BY HAND.  PROPELLER BLADE SPANS ONLY 7 INCHES AT POSITION OF CRACK.  CRAC	K WAS APPROXIMATELY CENTER OF BLADE, AND HAS NOT PROPAGATED TO THE LEADING AND TRAILING EDGES.  ALSO, CRACK CANNOT BE SE	EN OR DETECTED WITH EDDY CURRENT MACHINE ON THE FACE SIDE OF THE PROPELLER BLADE.		1	L	7	2 	4T				A14CE   		6	C	P40EA	 
1996061300396	19960613	00396	CE  	1996	6	13	96ZZZX2962       	1	19960510	G	2435	1013690113	TERMINAL STUD   	LEARSIEGLER 	23048016    	BEECH 	200   	200BEECH    	1152920	CE  										START/GEN	THREADS WEAR    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	971LL				11727	BB572				WHEN INSTALLING PLASTIC TERMINAL COVER, COVER HOLD-DOWN NUTS TEND TO WEAR THREADS ON STUDS CAUSING THE TERMINAL NUT TO S	TRIP THE STUD UPON NEXT INSTALLATION.  TIMES UNKNOWN, SHOULD NOT BE A FACTOR.					1	L	7	2 	4T				A24CE   					 
1996061300397	19960613	00397	CE  	1996	6	13	96ZZZX2963       	1	19960522	G	2931	156739XP500	GAUGE           	AMETEK      		BEECH 	200   	200BEECH    	1152920	CE  										ACCUM IND	WORN            	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	981LL	388  			N9837C	BB602				GAUGE MOVEMENT VERY LOOSE CAUSING NEEDLE TO SLIP TOWARD HIGHER READING.						1	L	7	2 	4T				A24CE   					 
1996061300398	19960613	00398	CE  	1996	6	13	96ZZZX2964       	1	19960501	G	3244	226K083	TIRE            			CESSNA	650   	650         	2076802	CE  										MLG	DEFECTIVE       	B			IW1R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			EA	25	650SB	231  			71260982	6500018				ON TAKEOFF FROM PBI, GEAR UNSAFE LIGHT REMAINED ON WHEN GEAR WAS RETRACTED.  OPERATOR FLEW BY TOWER FOR CONDITION CHECK.	  GEAR WAS REPORTED UP AND LOCKED.  AFTER SEVERAL GEAR CYCLES, GEAR UNSAFE LIGHT WENT OUT.  AFTER LANDING AT MORRISTOWN,	 NR 2 TIRE FOUND TO HAVE OUTER BEAD SEPARATION, AND DAMAGED FLAP AND GEAR UPLOCK SWITCH.  AIRCRAFT TOTAL TIME, 3,691.2 H	RS.  LANDINGS, 145.			2	L	7	2 	4F				A9NM    					 
1996061300399	19960613	00399	SO  	1996	6	13	96ZZZX2965       	1	19960529	G	2910		SOLENOID VALVE  			GULSTM	G1159 	G1159       	3953505	SO  										HYDRAULIC SYSTEM	SEAL LEAK       	B			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	26WP	339  			1081	024				AIRCRAFT RETURNED FROM A FLIGHT AND WHILE UNLOADING BAGGAGE, A SKYDROL FLUID LEAK WAS NOTED NEAR BATTERY COMPARTMENT.  I	NVESTIGATION REVEALED SEAL BLOWN OUT WHERE VALVE BODY AND SOLENOID MEET.  REPLACED VALVE ASSEMBLY.  SUBMITTER SUSPECTS P	ROBLEM OCCURRED AS A RESULT OF THREAD BURR RESULTING IN IMPROPER OR INCOMPLETE ASSEMBLY LETTING O-RING SEAL TO BLOW OUTW	ARD.			2	L	7	2 	4F			RT	A12EA   					 
1996061300400	19960613	00400	NM  	1996	6	13	96ZZZX2966       	1	19960501	G	5313		KEEL STRINGER   			BOEING	727   	727243      	138408D	NM  										FS 950A S29R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	34415					22167				DURING C-10 CHECK, NOTED KEEL STRINGER S29R HAS INTERGRANULAR CORROSION EXTENDING FROM STA 950A TO STA 950D.						2	L	7	3 	4F			RT	A3WE    					 
1996061300401	19960613	00401	NM  	1996	6	13	96ZZZX2967       	1	19960501	G	5313		STRINGER        			BOEING	727   	727243      	138408D	NM  										FS 480-500 S28R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	34415					22167				DURING A C-10 INSPECTION, STRINGER S28R, BETWEEN STA 480 AND STA 500, WAS NOTED TO HAVE HEAVY INTERGRANULAR CORROSION.						2	L	7	3 	4F			RT	A3WE    					 
1996061300404	19960613	00404	SO  	1996	6	13	96ZZZX2970       	1	19960501	G	3213	583831	GEAR LEG        			LUSCOM	8     	8A          	8190104	SO  										MLG RT	CRACKED         	G	S			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	93CK	1476 				4036				LOWER GEAR LEG CRACKED AT BOLT HOLE AT ATTACHMENT TO UPPER ARM ASSEMBLY.  CRACK CAUSED GEAR LEG TO FAIL ON LANDING.  CRA	CK WAS NOT DETECTED BECAUSE OF SKI ATTACHMENT BRACKET COVERING GEAR LEG AT THIS AREA.  SUBMITTER SUGGESTS FOR MECHANIC T	O INSPECT BOLT HOLE AREAS FOR CRACKING.				1	H	7	1 	3O				A694    					 
1996061300405	19960613	00405	CE  	1996	6	13	96ZZZX2971       	1	19960515	G	5341	08113508	FITTING         			CESSNA	402   	402C        	207590R	CE  										WING ATTACH	CORRODED        	C	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	121PB	12316				402C0507				DURING ROUTINE INSPECTION, NOTED LOWER FORWARD CARRY-THROUGH SPAR FITITNG EXFOLIATING DUE TO INTERGRANULAR CORROSION.						1	L	7	2 	3O				A7CE    					 
1996061300406	19960613	00406	SO  	1996	6	13	96ZZZX2972       	1	19960517	G	5320	18110	BRACKET         			LUSCOM	8     	8A          	8190104	SO  										NR 8 BULKHEAD	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	25236					1411				FOUND CRACK IN FLANGE OF PART WHERE LOWER RUDDER HINGE ATTACH BOLT PASSES THROUGH PART.  SUBMITTER STATED CAUSED BY FLEX	ING OF PART IN NORMAL USE.  LATER STYLE II SERIES LUSCOMBES USED DIFFERENT DESIGN TO DISTRIBUTE STRESS BETTER.					1	H	7	1 	3O				A694    					 
1996061300407	19960613	00407	CE  	1996	6	13	96ZZZX2973       	1	19960517	G	3250	12606311	ROD END         			CESSNA	206   	U206G       	2073356	CE  										NLG STEERING	BROKEN          	D	S	A		O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	05	756HK	1068 				U20604102				PILOT HEARD A LOUD NOISE WHILE TAXIING AFTER LANDING.  HE ALSO NOTICED LOSS OF NOSE WHEEL STEERING AND VERY FREE MOVEMEN	T OF RUDDER CONTROL.  INVESTIGATION FOUND THE ROD END ON AFT STEERING BUNGEE HAD BROKEN OFF AND TRIM CHAIN WAS OFF OF SP	ROCKET.  THIS IS THE SECOND INCIDENCE KNOWN OF THIS HAPPENING ON THIS AIRCRAFT.  THERE HAVE BEEN 2 OTHER INCIDENCES OF T	HIS ON OTHER AIRCRAFT.  SUBMITTER STATED THE PROBLEM COULD BE FROM IMPROPER GROUND HANDLING, BUT SUSPECT THE DIAMETER .2	5 INCH IS VERY SMALL FOR THE DEMANDS PUT ON IT.		1	H	7	1 	3O				A4CE    					 
1996061300408	19960613	00408	CE  	1996	6	13	96ZZZX2974       	1	19960515	G	5740	951100171	FITTING         			BEECH 	58    	58          	1152740	CE  										LT OTBD WING	DAMAGED         	B	S		EHHR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	7353R					TH486				WHEN PERFORMING 5-YEAR WING BOLT AND FITTING INSPECTION, DISCOVERED THE LOWER AFT RADIUS WASHERS, PN 95-110025-1, WERE N	OT INSTALLED.  INSTEAD, 2 EACH, PN NAS143-12, WASHERS WERE INSTALLED.  WHEN TORQUED, THE WASHERS MADE IMPRESSIONS IN BOT	H LOWER AFT OUTBOARD FITTINGS.				1	L	7	2 	3O				3A16    					 
1996061300409	19960613	00409	CE  	1996	6	13	96ZZZX2975       	1	19960515	G	5740	951100172	FITTING         			BEECH 	58    	58          	1152740	CE  										RT OTBD WING	DAMAGED         	B			EHHR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	7353R					TH486				WHEN PERFORMING 5-YEAR WING BOLT AND FITTING INSPECTION, DISCOVERED THE LOWER AFT RADIUS WASHERS, PN 95-110025-1, WERE N	OT INSTALLED.  INSTEAD, 2 EACH, PN NAS143-12, WASHERS WERE INSTALLED.  WHEN TORQUED, THE WASHERS MADE IMPRESSIONS IN BOT	H LOWER AFT OUTBOARD FITTINGS.				1	L	7	2 	3O				3A16    					 
1996061300410	19960613	00410	EA  	1996	6	13	96ZZZX2976       	2	19960423	G	7322	105135	CARBURETOR ARM  	FACET       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					THROTTLE	DETACHED        	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	3457Q	250  			CK815086	287716157	L732439A			CARBURETOR THROTTLE ARM CAME LOOSE FROM THROTTLE SHAFT DUE TO ATTACHMENT NUT LOOSENING OFF OF ARM.  THE SUSPECT CAUSE OF	 THE NUT COMING LOOSE WAS IMPROPER INSTALLATION OF KOTTER KEY INTO NUT.					1	L	7	1 	3O	3	O		2A13    	E274				 
1996061300411	19960613	00411	SO  	1996	6	13	96ZZZX2977       	2	19960514	G	7414	1051324	SPRING          		10400307    	CESSNA	182   	182C        	2072708	CE  	CONT  	O470  	O470R       	17026	SO  					MAG IMPULSE COUP	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8617T	7    				52517	988558RR			TWO NEW SNAP-RING COUPLINGS INSTALLED AT ANNUAL INSPECTION.  SEVEN HOURS LATER BOTH COUPLING SPRINGS FAILED ON CONSECUTI	VE ENGINE STARTS.  SPRING FAILURES APPEAR TO BE IDENTICAL.  COUPLINGS WERE BOUGHT AND INSTALLED AS ASSEMBLIES PREVENTING	 INSPECTION OF SPRINGS PRIOR TO INSTALLATION.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996061300412	19960613	00412	CE  	1996	6	13	96ZZZX2978       	1	19960521	G	3230	20846007	BUNGEE ARM      			PIPER 	PA24  	PA24180     	7102402	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	7114P					242272				FOUND BOTH LANDING GEAR BUNGEE ARMS CRACKED AT PIN SLOTS AND WELDED ATTACHMENT AREA.  CRACKS APPEARED TO HAVE EXISTED FO	R SOME TIME, JUDGING BY APPEARANCE.  REPLACED BOTH BUNGEE ARMS WITH NEW PARTS, LT W20846-006, RT W20846-007.  SUSPECT CA	USE OF CRACKS APPEARS TO BE AGE-FATIGUE.  THE ONLY WAY OF BEING SURE PART IS NOT CRACKED IS TO REMOVE BUNGEE ARMS COMPLE	TELY FOR VISUAL INSPECTION.			1	L	7	1 	3O			NT	1A15    					 
1996061300413	19960613	00413	CE  	1996	6	13	96ZZZX2979       	1	19960521	G	3230	20846006	BUNGEE ARM      			PIPER 	PA24  	PA24180     	7102402	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	7114P					242272				FOUND BOTH LANDING GEAR BUNGEE ARMS CRACKED AT PIN SLOTS AND WELDED ATTACHMENT AREA.  CRACKS APPEARED TO HAVE EXISTED FO	R SOME TIME, JUDGING BY APPEARANCE.  REPLACED BOTH BUNGEE ARMS WITH NEW PARTS, LT W20846-006, RT W20846-007.  SUSPECT CA	USE OF CRACKS APPEARS TO BE AGE-FATIGUE.  THE ONLY WAY OF BEING SURE PART IS NOT CRACKED IS TO REMOVE BUNGEE ARMS COMPLE	TELY FOR VISUAL INSPECTION.			1	L	7	1 	3O			NT	1A15    					 
1996061300414	19960613	00414	SO  	1996	6	13	96ZZZX2980       	1	19960419	G	2820	11141760124	FUEL LINE       			PIPER 	PA28  	PA28180     	7102808	SO  										FUEL TANK	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	1261T	2670 				287205273				PIPER CHEROKEE FUEL TANKS WERE PULLED TO PUT NEW GASKETS ON THE FUEL QUANTITY SENDERS.  AT THIS TIME, THE FUEL LINES (ST	RATOFLEX FLEXIBLE HOSE) WERE FOUND CHAFED, RUSTED, AND VERY BRITTLE.  WHEN THE ONE HOSE WAS FLEXED, IT BROKE IN HALF.  B	OTH HOSES WERE ORIGINAL EQUIPMENT WITH DATE CODES OF 2/72.  SUBMITTER RECOMMENDS THAT ALL TANKS OF THIS TYPE (PA-32-34-4	4) BE PULLED AND CHECKED FOR THIS CONDITION.			1	L	7	1 	3O				2A13    					 
1996061300677	19960613	00677	CE  	1996	6	13	96ZZZX2981       	1	19960424	G	2840	1200106263	LINE            			CESSNA	210   	210M        	2073450	CE  										INST PANEL GAUGE	CHAFED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	09	823AR					21062661				ROUTINE MAINTENANCE, NOTICED FUEL DRIPPING ONTO FLAP HANDLE WIRING BEHIND INSTRUMENT PANEL.  INVESTIGATION FOUND LINE CH	AFING ON ADF RADIO RACK.  THIS LINE RUNS FROM FIRE WALL TO FUEL PRESSURE GAUGE.  TOTAL TIME ON AIRFRAME 11,404 HRS.  TT 	ON PART, UNKNOWN.				1	H	7	1 	3O				3A21    					 
1996061300678	19960613	00678	SO  	1996	6	13	96ZZZX2982       	1	19960427	G	6120		CONTROL SHAFT   	HARTZL      	F27A        	PIPER 	PA28  	PA28R200    	7102811	SO  										PROPELLER GOV	NUT BACKED OFF  	G				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			GL	15	33047		1671 		4961W	28R7535111				DURING FLIGHT, CONTROL SHAFT NUT BACKED OUT CAUSING LOSS OF ENGINE OIL AND SUBSEQUENT ENGINE DESTRUCTION.  IT HAS BEEN D	ETERMINED THE CONTROL SHAFT GASKET WAS NOT PROPERLY BENT TO PROVIDE A MEANS TO SAFETY THE CONTROL SHAFT NUT TO PREVENT I	T FROM LOOSENING/BACKING OFF.  ITEM 18, PN B-4739, IN HARTZELL MANUAL.				1	L	7	1 	3O				2A13    					 
1996061300679	19960613	00679	CE  	1996	6	13	96ZZZX2983       	1	19960430	G	3230	504501019	TORQUE TUBE     			CESSNA	340   	340A        	2076405	CE  										LT MLG	WELD BROKEN     	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	05	1920E	5406 				340A0669				LEFT MAIN GEAR WOULD NOT RETRACT AFTER TAKEOFF.  PILOT EXTENDED GEAR AND RETURNED TO AIRPORT.  INSPECTED LT GEAR RETRACT	ION LINKAGE, AND FOUND AFT FORK ASSY WELD BROKEN AND TUBE WITH SPIRAL TEAR.  SUBMITTER SUGGESTS FATIGUE TO WELDED AREA, 	WEAKENING SURROUNDED AREA.  AREA SHOULD BE INSPECTED AT EACH INSPECTION.				1	L	7	2 	3O				3A25    					 
1996061300681	19960613	00681	EU  	1996	6	13	96ZZZX2985       	1	19960520	G	2150	ES611301	BLOWER MOTOR    			SLNSBY	T67   	T67M260     	8323006	EU  										AIR COND	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		100  								SUBMITTER REPORTS SEVERAL CONDENSER BLOWER MOTORS QUIT.  SEVEN INSPECTED MOTORS FOUND BRUSHES COMPLETELY WORN.  SUBMITTE	R STATES NO RECOMMENDATIONS AT THIS TIME.  (ALL HAVE HAD LESS THAN 100 HRS, TT).					1	L	7	1 	3O			NT	A73EU   					 
1996061300682	19960613	00682	CE  	1996	6	13	96ZZZX2986       	1	19960520	G	7810	991029521	EXHAUST RISER   			CESSNA	404   	404CESSNA   	2075901	CE  										SLIP JOINT	MISOVERHAULED   	B			APCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	48SA					4040417				RECEIVED OVERHAULED EXHAUST RISER FROM OVERHAULER.  DURING INSPECTION PRIOR TO INSTALLATION, FOUND MOUTH FOR SLIP JOINT 	MANUFACTURED TOO SMALL AND NOT ALLOWING SLIP JOINT TUBE TO SLIDE IN.  SUSPECT CAUSE IS POOR MANUFACTURING AND QUALITY CO	NTROL PRACTICES.  SUBMITTER RECOMMENDS COMPANY CHECK THEIR WORK BEFORE IT IS TAGGED OVERHAULED AND SHIPPED.				1	L	7	2 	3O				A25CE   					 
1996061300683	19960613	00683	CE  	1996	6	13	96ZZZX2987       	1	19960417	G	2750	086210051	ACTUATE ROD     			CESSNA	320   	320E        	2074514	CE  										RT INBD FLAP	BENT            	D				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			WP	01	3439Q	3568 				320E0039				RIGHT INBOARD FLAP ACTUATING RODS FOUND BENT DURING AN ANNUAL INSPECTION.  PILOT COMPLAINED OF AIRCRAFT ROLLING LEFT WHE	N FLAPS DEPLOYED ZERO DEGREES TO 15 DEGREES.  AD SEARCH FOUND AIRCRAFT NOT PLACARDED TO 140 MPH FOR FLAP DEPLOYMENT FROM	 15 DEGREES TO 35 DEGREES (MAXIMUM SPEED).  AIRCRAFT PLACARDED AND RODS REPLACED.				1	L	7	2 	3O				3A25    					 
1996061300684	19960613	00684	CE  	1996	6	13	96ZZZX2988       	1	19960417	G	2750	086210050	ACTUATE ROD     			CESSNA	320   	320E        	2074514	CE  										RT INBD FLAP	BENT            	D				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			WP	01	3439Q	3568 				320E0039				RIGHT INBOARD FLAP ACTUATING RODS FOUND BENT DURING AN ANNUAL INSPECTION.  PILOT COMPLAINED OF AIRCRAFT ROLLING LEFT WHE	N FLAPS DEPLOYED ZERO DEGREES TO 15 DEGREES.  AD SEARCH FOUND AIRCRAFT NOT PLACARDED TO 140 MPH FOR FLAP DEPLOYMENT FROM	 15 DEGREES TO 35 DEGREES (MAXIMUM SPEED).  AIRCRAFT PLACARDED AND RODS REPLACED.				1	L	7	2 	3O				3A25    					 
1996061300685	19960613	00685	CE  	1996	6	13	96ZZZX2989       	1	19960512	G	2510	S20415016	RESISTOR        			CESSNA	172   	172P        	2072436	CE  										LIGHTER CIRCUIT	DAMAGED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	53111	8718 				17274685				CIGAR LIGHTER WAS WIRED TO THE LANDING LIGHT CIRCUIT BREAKER.  THE RESISTOR WAS WIRED TO A GROUND ON ONE END AND TO THE 	7.5 AMP FUSE HOLDER, THEN TO THE BUS BAR.  THERE WAS NO FUSE IN THE FUSE HOLDER.  WHEN THE CONTACTS IN THE FUSE HOLDER T	OUCHED, THE CURRENT (UNPROTECTED) CAUSED THE RESISTOR TO FAIL AND BLOW ONE END OUT.  THE LOOSE END BURNED 2 WIRES RUNNIN	G UNDER THE CIRCUIT BREAKERS, BEHIND THE PANEL.  IT WAS DECIDED IT WOULD BE BEST TO REMOVE ALL ASSOCIATED COMPONENTS AND	 WIRING.		1	H	7	1 	3O			NT	3A12    					 
1996061300686	19960613	00686	CE  	1996	6	13	96ZZZX2990       	1	19960524	G	2460	CM358950	SWITCH          			CESSNA	402   	402C        	207590R	CE  										AVIONICS MASTER	FAILED          	C				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			NE	01	7037E	13100				402C0471				AFTER TAKEOFF, AIRCRAFT EXPERIENCED COMPLETE AVIONICS ELECTRICAL FAILURE DUE TO AVIONICS MASTER SWITCH FAILURE.  EMERGEN	CY AVIONICS BUS WAS ACTIVATED AND POWER WAS RESTORED.					1	L	7	2 	3O				A7CE    					 
1996061300687	19960613	00687	CE  	1996	6	13	96ZZZX2991       	1	19960417	G	5312	08130228	BULKHEAD        			CESSNA	320   	320E        	2074514	CE  										FS 27.25	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	3439Q	3568 				320E0039				DURING ANNUAL INSPECTION, RT BULKHEAD AT FS 27.25 WAS FOUND CRACKED.  THIS AND THE OPPOSITE PART ON THE LT SIDE ARE WHER	E THE NLG STEERING CABLES ATTACH VIA STEEL PULLEY BRACKETS.  SUBMITTER SUGGESTS MFG EITHER PRODUCE REINFORCEMENT KIT OR 	STRENGTHEN NEW COMPONENTS.  PART WAS REPLACED WITH A SERVICEABLE BULKHEAD OF THE SAME PART NUMBER.				1	L	7	2 	3O				3A25    					 
1996061300688	19960613	00688	EA  	1996	6	13	96ZZZX2992       	2	19960419	G	8520		LIFTER BODY     			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 2 CYL EXHAUST	COLLAPSED       	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	03	89594	46   				17276009	L1253439A			45.9 HOURS AFTER OVERHAUL, PILOT FLYING AN X-C EXPERIENCED VERY ROUGH ENGINE.  AFTER TROUBLESHOOTING ALL POSSIBLE ASPECT	S, FOUND NR 2 CYLINDER EXHAUST HYDRAULIC LIFTER COLLAPSED AND DAMAGED PUSH ROD.  A NEW LIFTER AND PUSH ROD WAS INSTALLED	.  OPS CHECK WAS PERFECT.  20 MINUTES INTO RETURN FLIGHT, SAME ROUGHNESS OCCURRED.  FURTHER INVESTIGATION REVEALED .50 I	NCH OF LIFTER BODY WAS BROKEN WHICH CAUSED THE TAPPET TO FLOP AROUND AND NOT GET ANY OIL.  ALL 8 LIFTER BODIES WERE SENT	 TO LYCOMING FOR INSPECTION.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996061300689	19960613	00689	EU  	1996	6	13	96ZZZX2993       	1	19960514	G	3230	Z00N7733690395	RELAY           			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										MLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	11	20FF					1032				ON APPROACH, OPERATOR ATTEMPTED TO LOWER GEAR.  GEAR DID NOT RESPOND.  SEVERAL ATTEMPTS WERE MADE TO LOWER GEAR NORMALLY	.  GEARS WERE THEN LOWERED WITH EMERGENCY GEAR EXTENSION HANDLE.  BOTH MAIN GEARS WERE DOWN AND LOCKED, BUT NOSE GEAR WO	ULD NOT LOCK DOWN.  OPERATOR SUBSEQUENTLY MADE AN EMERGENCY LANDING WHERE NOSE GEAR FAILED.  TROUBLESHOOTING REVEALED TH	AT CAUSE OF NORMAL GEAR EXTENSION FAILURE WAS THE RESULT OF THE UP RELAY FAILING IN THE CLOSED POSITION.  NOSE GEAR EXTE	NSION FAILURE IN EMERGENCY CONFIGURATION WAS CAUSED BY ONE OF THE TWO NOSE GEAR EMERGENCY COMPENSATING ACTUATORS HAVING 	LOST ITS CHARGE.	1	L	7	1 	3O			RT	A51EU   					 
1996061300690	19960613	00690	EU  	1996	6	13	96ZZZX2994       	1	19960517	G	3232	Z00N7070110709	ACTUATOR        			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										NLG EXTENSION	LOST CHARGE     	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	11	20FF					1032				ON APPROACH, OPERATOR ATTEMPTED TO LOWER GEAR.  GEAR DID NOT RESPOND.  SEVERAL ATTEMPTS WERE MADE TO LOWER GEAR NORMALLY	.  GEARS WERE THEN LOWERED WITH EMERGENCY GEAR EXTENSION HANDLE.  BOTH MAIN GEARS WERE DOWN AND LOCKED, BUT NOSE GEAR WO	ULD NOT LOCK DOWN.  OPERATOR SUBSEQUENTLY MADE AN EMERGENCY LANDING WHERE NOSE GEAR FAILED.  TROUBLESHOOTING REVEALED TH	AT CAUSE OF NORMAL GEAR EXTENSION FAILURE WAS THE RESULT OF THE UP RELAY FAILING IN THE CLOSED POSITION.  NOSE GEAR EXTE	NSION FAILURE IN EMERGENCY CONFIGURATION WAS CAUSED BY ONE OF THE TWO NOSE GEAR EMERGENCY COMPENSATING ACTUATORS HAVING 	LOST ITS CHARGE.	1	L	7	1 	3O			RT	A51EU   					 
1996061300691	19960613	00691	SO  	1996	6	13	96ZZZX2995       	2	19960426	G	8530	625393	RETAINER        			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					NR 6 CYL VALVE	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6908P	1350 				468508062	528156			ON REMOVAL OF NR 6 CYLINDER DUE TO METAL FOUND IN OIL FILTER, FOUND PIECES IN ROCKER AREA.  THIS WAS VERIFIED AS CONTAMI	NANTS THROUGH T.C.M.  NO SERVICE INFO ISSUED TO DATE ON AN ONGOING PROBLEM OF THIS PART.					1	L	7	1 	3O	3	O		A25SO   	E8CE				 
1996061300692	19960613	00692	CE  	1996	6	13	96ZZZX2996       	1	19960601	G	7920		HOSE            			BEECH 	95    	B95A        	1153406	CE  	LYC   	O360  	IO360B1A    	41514	EA  					OIL COOLER	CHAFE           	H				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SW	99		10   								GROUND PERSONNEL NOTED FUEL TYPE VAPORS TRAILING BEHIND TAXIING BEECH TRAVEL AIR.  ACFT RETURNED TO AIRPORT.  INVESTIGAT	ION REVEALED VAPOR WAS, IN FACT, BURNING OIL FROM CHAFED THROUGH OIL LINES FROM COOLER.  LINE WAS CHAFED AND BURNED THRO	UGH BY UNSHIELDED EXHAUST.  REPLACED OIL LINE WITH LONGER HOSE AND ADDED AN ADEL CLAMP, ROUTING HOSE FURTHER DOWN IN COW	L.  A NEW OIL HOSE HAD BEEN INSTALLED ONLY 10 HOURS PREVIOUSLY.			1	L	7	2 	3O	3	O		3A16    	1E10				 
1996061300693	19960613	00693	NE  	1996	6	13	96ZZZX2997       	2	19960517	G	8530		PISTON          			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 1 CYLINDER	RING BROKE      	D				A				UNSCHED LANDING         				R	K		PARTIAL RPM/PWR LOSS      	FLUID LOSS                		NR	NOT REPORTED   	1			EA	17	6565		1921 			722	38065			FIRST OR SECOND COMPRESSION RING BROKE CAUSING RING LANDS TO WEAR BETWEEN FIRST AND SECOND RING LAND AND THROUGH PISTON 	HEAD.  COMBUSTION HEAT BURNED HOLE LARGER DIRECTING PRESSURE TO ENGINE CASE.  THIS PRESSURE BLEW THE ENGINE OIL OVERBOAR	D.  THIS RESULTED IN AN EMERGENCY LANDING.				1	Q	7	1 	3R	3	R		1A16    	5E2				 
1996061300694	19960613	00694	NE  	1996	6	13	96ZZZX2998       	2	19960528	G	7322	67019	MIXTURE CONTROL 	BENDIX      	P012H4      	DOUG  	DC3   	DC3A        	3021433	WP  	PWA   	R1830 	R1830*      	52020	NE  					CARB AUTO MIX	MALFUNCTION     	H				O				OTHER                   				M	E	R	OVER TEMP                 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	CR	CRUISE         	1			SW	17	32MS		844  		5682114A	4978				CYLINDER HEAD TEMPERATURE RUNNING HIGHER THAN NORMAL AND ENGINE ERRATIC WHEN AUTO LEAN SELECTED AT CRUISE.  AMC TIME IN 	SERVICE, 843.9 HRS.					2	L	7	2 	4R	4	R		A669    	5E4				 
1996061300695	19960613	00695	GL  	1996	6	13	96ZZZX2999       	3	19960409	G	6112		CLAMP           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	DE-ICE LEAD	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	3UR					310R0061		760064		BOTH PROPS OVERHAULED ON 1-20-96 TO C/W AD 95-24-05, SB 209, SL 1993-11-OIL FILL-AT OVERHAUL.  ALL 6 DE-ICER BOOT LEADS 	REPLACED.  THESE LEADS APPEAR TO BE LARGER IN DIAMETER AND HEAVIER THAN LEADS REMOVED AT OVERHAUL.  CABLE ENDS SECURED W	ITH NR 6 ADEL CLAMP TO PROP HUB PER CESSNA MANUAL.  AFTER APPROXIMATELY 20 HRS OPERATION, ALL 6 CLAMPS BROKE AT FLANGE B	OLT HOLE AREA.  REPLACED ALL 6 CLAMPS WITH LIKE PART AND THEY AGAIN BROKE AT APPROXIMATELY 4 HRS.  AFTER REPLACEMENT, AP	PEARS NEW CABLE IS HEAVIER THAN ORIGINAL AND CENTRIFUGAL FORCE IS CRACKING ORIGINAL CLAMPS.  CURRENTLY REPLACING ORIGINA	L ALUMINUM ADEL CLAMPS WITH STAINLESS STEEL ADEL CLAMPS.	1	L	7	2 	3O				3A10    		5	C	P22EA	 
1996061300696	19960613	00696		1996	6	13	96ZZZX3000       	4	19960515	G	3450	KNS80	R NAV SYS       	KING        		CESSNA	310   	310R        	2074245	CE  										COCKPIT NAV	FAULTY          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13	6209X				17983	310R1339				PILOT REPORTED INOPERATIVE NAV/LOCALIZER ON 109.50 MHZ AND A LOUD SQUEAL IN AUDIO.  PROBLEM WAS PECULIAR TO THAT FREQUEN	CY AND DID NOT APPEAR IN OTHER NAV RADIO.  DETERMINED PROBLEM TO BE IN THE UNIT AND NOT IN THE AIRCRAFT.  TESTED 3 OTHER	 KNS-80'S AND ALL DISPLAYED SAME PROBLEM, ALTHOUGH IT WAS NOT BAD ENOUGH TO DEGRADE THE NAV PERFORMANCE.  CONSULTED THE 	MANUFACTURER.  MFG AWARE OF THE PROBLEM AND HAVE A FIX FOR IT.  CONTACT LOCAL BENDIX/KING DEALER OR ALLIED SIGNAL FOR FU	RTHER INFORMATION.  SUBMITTER RECOMMENDS MFG RELEASE A SB AS SOON AS POSSIBLE.  COULD BE A PROBLEM IN IMC.		1	L	7	2 	3O				3A10    					 
1996061300697	19960613	00697	EU  	1996	6	13	96ZZZX3001       	1	19960528	G	7921	96490432	COOLER          	LORINORDAM  		SLNSBY	T67   	T67M260     	8323006	EU  										ENGINE OIL	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	17	3192F	105  				2228				AFTER FIRST FLIGHT OF THE DAY, AIR CREW NOTICED OIL ON WING WALK.  COWLING WAS REMOVED AND OIL WAS SEEN DRIPPING FROM OI	L COOLER FINS.  REMOVED AND REPLACED OIL COOLER.					1	L	7	1 	3O			NT	A73EU   					 
1996061300698	19960613	00698	CE  	1996	6	13	96ZZZX3002       	1	19960531	G	2810		FUEL CAP        			CESSNA	182   	182K        	2072724	CE  										FUEL TANK	FAULTY          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2836R					18258436				REMOVED ORIGINAL CESSNA FLUSH FUEL CAPS AND INSTALLED DOME CAPS WITH REDUCED OPENING.  STC KIT SA 2376CE FC-1 (B).						1	H	7	1 	3O			NT	3A13    					 
1996061300699	19960613	00699	CE  	1996	6	13	96ZZZX3003       	1	19960507	G	3230	12802091	PIN             			CESSNA	182   	R182        	2072734	CE  										NLG ACTUATOR	BROKEN          	D				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	15	1727R	3185 				R18200537				WHEN GEAR WAS EXTENDED, NO GREEN LIGHT.  EMERGENCY PROCEDURE, STILL NO GREEN LIGHT.  NOSE GEAR COLLAPSED ON LANDING.  FO	UND DOWNLOCK PIN BROKEN AND MIGRATED INBOARD BLOCKING ACTUATOR FROM RETRACTING FULLY AND NOSE GEAR LOCKING.  FOUND OTHER	 PIN ALSO BROKEN, BUT NOT MIGRATED OUT.				1	H	7	1 	3O			RT	3A13    					 
1996061300700	19960613	00700	EA  	1996	6	13	96ZZZX3004       	2	19960503	G	8530	S117235TT67	VALVE           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE EXHAUST	FAILED          	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	15	6132H					15284133	L2057015			INSTRUCTOR AND STUDENT WERE FLYING APPROXIMATELY 5 MILES FROM AIRPORT WHEN THE ENGINE FAILED.  BY ADJUSTING MIXTURE, THE	 INSTRUCTOR WAS ABLE TO GET THE ENGINE RUNNING AGAIN (1,600 RPM) WHICH GOT THEM BACK TO THE AIRPORT.  THE ENGINE WAS GIV	EN A COMPRESSION CHECK AND FOUND TO HAVE A FAILED EXHAUST VALVE WHICH BROKE OFF AT THE BOTTOM OF THE STEM.  TSMOH WAS 1,	917.5 HRS.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996061300701	19960613	00701		1996	6	13	96ZZZX3005       	4	19960515	G	3452	001560033	RESISTOR        	KING        	KT76A       															HI VOLT BLEED	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										SUBMITTER NOTED SEVERAL INSTANCES OF DEFECTIVE HIGH VOLTAGE BLEEDER RESISTORS IN THE KT-76A, ESPECIALLY THE HIGHER SERIA	L NUMBER UNITS.  FOUND THE FIRST ONE THE HARD WAY, ZAPPED WHILE PUTTING UNIT TOGETHER.  THIS DOES NOT POSE A FLIGHT HAZA	RD, BUT CAN BE DANGEROUS TO AN UNWARY TECHNICIAN.																	 
1996061300702	19960613	00702	CE  	1996	6	13	96ZZZX3006       	1	19960502	G	3213	12414231	SADDLE          			CESSNA	210   	T210F       	2073422	CE  										MLG	CRACKED         	B			CGFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	6782R	660  				T2100182				DUE TO THE RELATIVELY LOW TOTAL TIME ON THIS AIRCRAFT (1,399 HRS) AND THE FACT THE LANDING GEAR SADDLES HAD BEEN REPLACE	D AT 739 HOURS, AD 76-14-07 R2 DID NOT APPLY AT THIS TIME, HOWEVER, THE PART IN QUESTION HAD A CRACK THAT WAS EVIDENT WI	THOUT DYE PENETRANT INSPECTION AND WOULD HAVE EVENTUALLY FAILED LEADING TO A GEAR UP LANDING.				1	H	7	1 	3O				3A21    					 
1996061300703	19960613	00703	GL  	1996	6	13	96ZZZX3007       	1	19960509	G	2731	O8610005	SWITCH          			DIAMON	DA20A1	DA20A1      	05626UX	GL  										NOSE TRIM	FAILED          	H			CB9T	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	529SS					10095				TRIM SWITCH FAILS TO OPERATE WHEN SELECTING NOSE UP SETTING.						1	L	7	1 	3O			NT	TA4CH   					 
1996061300704	19960613	00704	EA  	1996	6	13	96ZZZX3008       	2	19960525	G	7314	41270175	FUEL PUMP       			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					ENGINE	FAILED          	H				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SW	99	40933					327400025	L48648			PILOT REPORTED LOSS OF ENGINE POWER ON TAKEOFF AND ELECTED TO LAND ON GOLF COURSE.  DURING INVESTIGATION, ENGINE WAS OPE	RATED AND ENGINE DRIVEN FUEL PUMP FOUND INOPERATIVE.					1	L	7	1 	3O	3	O		A3SO    	E295				 
1996061300705	19960613	00705		1996	6	13	96ZZZX3009       	4	19960522	G	2562	79007P	ELT             	MERL        		PIPER 	PA28  	PA28161     	7102803	SO  										BATTERY PACK	BATTERY LEAKED  	H			HW8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	8091K		1005 			288016076				AIRCRAFT WAS REMOVED FROM SERVICE NOVEMBER, 1995, FOR RESTORATION.  ELT EXPIRATION DATE WAS FEBRUARY, 1996.  DECIDED TO 	C/W FAR 91.207(D).  DISCOVERED THIS UNIT IS SEALED, AND THERE IS NO WAY TO INSPECT BATTERIES.  THE BATTERIES WERE ABOUT 	3 MONTHS OVER EXPIRATION DATE, BUT BELIEVE THEY WERE BAD BEFORE THAT DATE.  THERE IS NO WAY TO INSPECT THIS TYPE OF BATT	ERY.  THERE WAS NO OUTSIDE INDICATION OF A LEAK.  IF THE UNIT HAD BEEN WITHIN ITS EXPIRATION DATE AND HAD BEEN OPENED AN	D FOUND OK, THEN WOULD NOT HAVE BEEN ABLE TO PROPERLY RESEAL IT.		1	L	7	1 	3O				2A13    					 
1996061300706	19960613	00706	CE  	1996	6	13	96ZZZX3010       	1	19960507	G	3230	08421201	TUBE ASSY       			CESSNA	310   	310L        	2074230	CE  										NLG	BROKEN          	G	L	A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			WP	05	3305X	3911 				310L0155				NOSE LANDING GEAR WAS EXTENDED, BUT DID NOT LOCK IN THE DOWN POSITION.  SUBSEQUENT INVESTIGATION REVEALED THAT THE NLG M	AIN DRIVE ASSY WAS BROKEN.  THE ANNUAL AND 100-HOUR INSPECTION WERE COMPLETED APRIL 19, 1996.  TACHOMETER 766.3.  TOTAL 	TIME:  3,900.8 HOURS.  AIRCRAFT WAS PAINTED DECEMBER 22, 1995.  THE INTERMEDIATE GEAR DRIVE TABLE ASSY WAS BENT.  SUBMIT	TER STATED IMPROPER RIGGING MAY BE THE CAUSE.			1	L	7	2 	3O				3A10    					 
1996061300707	19960613	00707	EU  	1996	6	13	96ZZZX3011       	1	19960527	G	3211	C48710	TRUNNION PIN    			AMD   	FALC20	FALCON20C5  	2730107	EU  										GEAR	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										GEAR IN FOR OVERHAUL.  NDT TEST REVEALED TRUNNION PIN CRACK.						2	L	7	2 	4F			RT	A7EU    					 
1996061300709	19960613	00709	CE  	1996	6	13	96ZZZX3013       	1	19960529	G	5540	23330072	PANEL           		263300112   	LEAR  	25    	25D         	5170514	CE  										RUDDER BAL WT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	1U	5132 			1733	371				DURING 12-YEAR INSPECTION, FOUND THE RUDDER INSPECTION PANEL THAT CONTAINS THE RUDDER BALANCE WEIGHT WAS CRACKED AT 4 OU	T OF 6 WEIGHT ATTACH HOLES.  SOME OF THE CRACKS WERE NOT VISIBLE UNTIL THE BALANCE WEIGHT WAS REMOVED.					2	L	7	2 	4J				A10CE   					 
1996061300710	19960613	00710	CE  	1996	6	13	96ZZZX3014       	1	19960528	G	5320	551124920	FRAME           			CESSNA	500   	550         	2076604	CE  										PILOT WINDOW	CRACKED         	B			PAZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	80AW	6976 				5500186				DURING REMOVAL OF PILOT'S WINDSHIELD TO INSTALL A NEW WINDSHIELD, APPROXIMATELY 3 CRACKS WERE FOUND IN THE SIDE WINDOW F	RAME, THE LARGEST OF WHICH WAS APPROXIMATELY 2.5 INCHES LONG AND HAD BEEN PREVIOUSLY STOP DRILLED.  THERE WERE ALSO NUME	ROUS DEEP GOUGES AND SCRATCHES WHICH APPEAR TO HAVE BEEN CAUSED BY TOOLS USED TO REMOVE THE WINDOW RETAINERS PREVIOUSLY.	  THE CRACKS ALL APPEAR TO HAVE STARTED AT A POINT WHERE THE GOUGES OR SCRATCHES WERE.  THE WINDOW FRAME WAS REMOVED AND	 REPLACED WITH A NEW PART FROM CESSNA.  CITATION DOES NOT ALLOW ANY CRACKS IN THE AREA AND NO REPAIRS ARE ALLOWED OTHER 	THAN REPLACEMENT.	1	L	7	2 	4F				A22CE   					 
1996061300712	19960613	00712	CE  	1996	6	13	96ZZZX3016       	1	19960514	G	7711	PG12A9	TRANSDUCER      	HONEYWELL   		RKWELL	NA265 	NA26540     	6402608	CE  										ENGINE EPR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	306NT				K1507	282030				TRANSDUCER WAS INSTALLED IN THE AIRCRAFT, TESTED, AND REMOVED WITH ZERO HOURS SINCE OVERHAUL.  UNIT WAS REMOVED DUE TO E	PR INDICATION WOULD STICK AT 2.0 AND WOULD NOT CHANGE WITH CHANGES IN ENGINE POWER SETTING.  UNIT WAS OVERHAULED 3-29-96	.  SUBMITTER STATED RELIABILITY OF OVERHAULED AND REPAIRED UNITS HAS BEEN POOR.  AIRCRAFT TOTAL TIME:  1,095.0 HRS.				2	L	7	2 	4J				A2WE    					 
1996061300713	19960613	00713	CE  	1996	6	13	96ZZZX3017       	1	19960503	G	3340	G99501	BEACON ASSY     	GRIMES      		RKWELL	NA265 	NA26540     	6402608	CE  										EXT LIGHT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	302NT		27   		6725	282081				BEACON WAS REMOVED FROM SERVICE WITH 27.0 HRS SINCE OVERHAUL DUE TO WOULD NOT ROTATE.  UNIT WAS OVERHAULED BY REPAIR STA	TION.  SUBMITTER STATED RELIABILITY OF REPAIRED AND OVERHAULED UNITS HAS BEEN POOR.  AIRCRAFT TT:  1,683.0 HRS.					2	L	7	2 	4J				A2WE    					 
1996061300714	19960613	00714	EA  	1996	6	13	96ZZZX3018       	1	19960509	G	7110	204318004	SUPPORT         			CNDAIR	CL600 	CL6001A11   	1900302	EA  										ENGINE COWL	CRACKED         	B			QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	68SD	2162 				1062				DURING 300-HOUR ENGINE INSPECTION, A 6.5 INCH HORIZONTAL CRACK WAS FOUND IN THE FAN COWL SUPPORT AT 3 O'CLOCK POSITION. 	 ALSO, VARIOUS BRACKETRY ATTACHED TO COWL ASSY FOUND TO HAVE SMALL CRACKS.					2	L	7	2 	4F			RT	A21EA   					 
1996062000077	19960620	00077	SW  	1996	6	20	96ZZZX3019       	1	19960430	G	3213	206033108001	FITTING         			BELL  	206   	206L4       	1182110	SW  										FWD CROSS TUBE	CHAFED          	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	108W	1122 				52034				FORWARD CROSS TUBE STRAP ASSY WORN INTO RIGHT FORWARD CROSS TUBE FITTING.  REPLACED FITTING PER PRODUCT SUPPORT WEAR LIM	ITS.					1	G	7	1 	3U			NC	H2SW    					 
1996062000422	19960620	00422	CE  	1996	6	20	96ZZZX3041       	1	19960606	G	7120	2651011	MOUNT BEAM      			LEAR  	35    	35A         	5170602	CE  										PYLON	CHAFE           	B		A	AN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	754GL				673	197				MOUNT BEAM CHAFING ON PYLON SIDE PANEL MOUNT FEED-THROUGH DOUBLER RING UPPER 3 ATTACH RIVETS.  SUSPECT CAUSE:  PYLON SID	E PANEL MOVEMENT.  SUBMITTER STATES TO REMOVE OLD RIVETS AND INSTALL NEW RIVETS IN A DOUBLE FLUSH MANNER.					2	L	7	2 	4F				A10CE   					 
1996062000423	19960620	00423	CE  	1996	6	20	96ZZZX3042       	1	19960606	G	7120	2651011	MOUNT BEAM      			LEAR  	35    	35A         	5170602	CE  										PYLON	CHAFE           	B		A	AN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	19LH				889	279				MOUNT BEAM CHAFING ON PYLON SIDE PANEL MOUNT FEED THROUGH DOUBLER RING UPPER 3 ATTACH RIVETS.  SUSPECT CAUSE:  PYLON SID	E PANEL MOVEMENT.  SUBMITTER STATED TO REMOVE OLD RIVETS AND INSTALL NEW RIVETS IN A DOUBLE FLUSH MANNER.					2	L	7	2 	4F				A10CE   					 
1996062000424	19960620	00424	CE  	1996	6	20	96ZZZX3043       	1	19960606	G	7120	2651011	MOUNT BEAM      			LEAR  	35    	36A         	5170603	CE  										PYLON	CHAFE           	B		A	AN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	14TX					033				MOUNT BEAM CHAFING ON PYLON SIDE PANEL MOUNT FEED THROUGH DOUBLER RING UPPER 3 ATTACH RIVETS.  SUSPECT CAUSE:  PYLON SID	E PANEL MOVEMENT.  SUBMITTER STATES TO REMOVE OLD RIVETS AND INSTALL NEW RIVETS IN A DOUBLER FLUSH MANNER.					2	L	7	2 	4F				A10CE   					 
1996062000425	19960620	00425	CE  	1996	6	20	96ZZZX3044       	1	19960606	G	7120	2651011	MOUNT BEAM      			LEAR  	35    	36A         	5170603	CE  										PYLON	CHAFE           	B		A	AN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	14TX				453	033				MOUNT BEAM CHAFING ON PYLON SIDE PANEL MOUNT FEED-THROUGH DOUBLER RING UPPER 3 ATTACH RIVETS.  SUSPECT PYLON SIDE PANEL 	MOVEMENT.  SUBMITTER STATES TO REMOVE OLD RIVETS AND INSTALL NEW RIVETS IN A DOUBLE FLUSH MANNER.					2	L	7	2 	4F				A10CE   					 
1996062000426	19960620	00426	WP  	1996	6	20	96ZZZX3045       	2	19960509	G	7260	8968042	GEARSHAFT       		31017262    	MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					FUEL PUMP	SHEARED         	B			IZ2R	O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SW	15	175CA	4942 			3P9426	736SA	P36014			AIRCRAFT EXPERIENCED AN UNCOMMANDED ENGINE SHUT DOWN.  ENGINE DISASSEMBLY REVEALED GEARSHAFT HAD SHEARED CAUSING FUEL PU	MP TO STOP TURNING.  REFERENCE:  1PC 72-01-16, SECTION 72-10-17, PAGE 2, ITEM 40.					1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
1996062000427	19960620	00427	WP  	1996	6	20	96ZZZX3046       	1	19960523	G	3320	BR9661103	POWER SUPPLY    	BRUCE       	BC50447907  	DOUG  	DC9   	DC931       	3022065	WP  										TAIL CONE	FAILED          	B			ZZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11										POWER SUPPLY FOR EXIT ID FAILED DUE TO EXPOSURE TO CHEMICAL ACTION FROM HYDRAULIC FLUID.  SUBMITTER STATED DEVICE IS NOT	 DESIGNED FOR THIS TYPE OF EXPOSURE AND NEEDS TO BE REDESIGNED FOR TAIL CONE MOUNTING.					2	L	7	2 	4F				A6WE    					 
1996062000428	19960620	00428	NE  	1996	6	20	96ZZZX3047       	2	19960510	G	7200		ENGINE          			LEAR  	25    	25          	5170506	CE  	GE    	CJ610 	CJ6106      	30006	NE  					LT ENGINE	FLAME OUT       	H		A		B	O			EMER. DESCENT           	OTHER                   			X			ENGINE FLAMEOUT           			CR	CRUISE         	1			GL	07	88NJ					008	240091			LEFT ENGINE FLAMED OUT AT FL 44,500 FEET GOING TO STP.  DROPPED DOWN TO 25,000 FEET, RELIT ENGINE, CONTINUED TO STP.  MA	INTENANCE INSPECTED ENGINE PER GE MM.  NO DEFECTS NOTED.  RETURNED TO SERVICE.					2	L	7	2 	4J	4	J		A10CE   	1E16				 
1996062000429	19960620	00429	EU  	1996	6	20	96ZZZX3048       	1	19960501	G	4920	25V13996	DUCT            			HWKSLY	DH125 	BH125400A   	4230138	EU  										APU RAM DUCT	CRACKED         	B	P		RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	345GL				BHB650	NA753				WHILE ACCOMPLISHING 500-HOUR AIRFRAME INSPECTION, ONE OF THE INSPECTION REQUIREMENTS CALLED OUT TO INSPECT THE APU.  DUR	ING INSPECTION, LARGE PIECES OF METAL WERE FOUND BEHIND THE APU.  APU REMOVED WHICH REVEALED THE CRACKED RAM AIR DUCT AS	SY.  THE RT SIDE OF THE DUCT CONTAINED A CRACK 5 INCHES BY 8 INCHES IN DIAMETER WITH ADDITIONAL CRACKS THROUGHOUT THE DU	CT ASSY.  THE APU IS NOT NORMALLY REMOVED DURING THIS INSPECTION WHICH COULD GO FOR NUMEROUS INSPECTIONS UNDETECTED.  SU	BMITTER SUGGESTS THE HIGH VIBTRATION LEVEL ASSOCIATED WITH THE APU CAUSED THE DUCT ASSY TO CRACK.  RECOMMEND THE DUCT AS	SY BE INSPECTED ON A REGULARLY SCHEDULED INTERVAL.	2	L	7	2 	4J				A3EU    					 
1996062000430	19960620	00430	CE  	1996	6	20	96ZZZX3049       	1	19960506	G	3246	9524796	O-RING          			RKWELL	NA265 	NA26540     	6402608	CE  										WHEEL PLUG ASSY	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	303NT		11   		AUG752183	28229				WHEEL ASSY OVERHAULED 4-5-96.  UNITS FUSIBLE PLUG O-RING NOT REPLACED DURING OVERHAUL.						2	L	7	2 	4J				A2WE    					 
1996062000431	19960620	00431	CE  	1996	6	20	96ZZZX3050       	1	19960513	G	2822	2017002	PUMP            	TRW         		RKWELL	NA265 	NA26540     	6402608	CE  										FUEL BOOST	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	09	303NT		15   		1001683D	28229				UNIT FAILED IN-FLIGHT WITHOUT INCIDENT, SUSPECT INTERNAL MOTOR BRUSH OR COMMUTATOR FAILURE.  UNIT OVERHAULED.						2	L	7	2 	4J				A2WE    					 
1996062000432	19960620	00432	NE  	1996	6	20	96ZZZX3051       	2	19960513	G	7250	597622	BLADE           			RKWELL	NA265 	NA26540     	6402608	CE  	PWA   	JT12  	JT12A8      	52042	NE  					2ND STG TURBINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	09	311NT	331  				28219	P673094NB			SECOND STAGE TURBINE ROTOR BLADE FAILURE IN-FLIGHT, WITHOUT INCIDENT.  ENGINE TT, 11,164.7 HRS, CYCLES, 8,081, TSO, 330.	9 HRS, TTHSI, 330.9 HRS, TOTAL PART TIME 330.9 HRS.  UNIT WAS OVERHAULED 4-12-95.					2	L	7	2 	4J	4	J		A2WE    	1E9				 
1996062000433	19960620	00433	CE  	1996	6	20	96ZZZX3052       	1	19960506	G	3246	9524796	O-RING          	LORAL       		RKWELL	NA265 	NA26540     	6402608	CE  										WHEEL PLUG ASSY	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	313NT		5    		MAY801162	28294				WHEEL ASSY OVERHAULED 4-11-96.  UNITS FUSIBLE PLUG O-RING, PN 9524796, NOT REPLACED DURING OVERHAUL.						2	L	7	2 	4J				A2WE    					 
1996062000434	19960620	00434	EU  	1996	6	20	96ZZZX3053       	1	19960530	G	3241	60026143	CONTROL BOX     	LORAL       		AMD   	FALC50	FALCON50MYST	2730106	EU  										ANTI-SKID	PINS CORRODED   	D		a		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	450K				137	186				IMPROPER ANTI-SKID OPERATION AND INVALID TEST.  FOUND OXIDIZATION ON CONTROL BOX CONNECTOR J1 AND J2 PINS.  BOX, SN 137,	 ORDERED EXCHANGE BOX AND EXCHANGE BOX SHIPPED.  ALSO, HAD OXIDIZED PINS.  BOX, SN DASH 064.  CLEANED OXIDIZATION FROM P	INS, MALE AND FEMALE CONNECTOR, AND INSTALLED BOX AND OPS CHECKED OK.  AIRCRAFT HISTORY SHOWS CONTROL BOX 6002614, SN'S 	DASH 454 AND DASH 458 WERE ALSO REPLACED FOR SAME PROBLEM IN THE LAST 2 YEARS.  SUBMITTER RECOMMENDS PINS, BOTH MALE AND	 FEMALE, BE REPLACED WITH GOLD PLATED PINS DUE TO ENVIRONMENT (HOT-COLD) AND LOCATION OF CONTROL BOX.		2	L	7	3 	4F				A46EU   					 
1996062000435	19960620	00435	SO  	1996	6	20	96ZZZX3054       	1	19960507	G	5553		FITTING         			GULSTM	G1159 	GIV         	3980115	SO  										V-STAB ATTACH	BUSHING GROOVED 	B			RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	7RP	1743 				1064				WHILE C/W THE VERTICAL STABILIZER ATTACH FITTING INSPECTION IAW GULFSTREAM IV MM, CHAPTER 5, SECTION 55, THE BUSHINGS WE	RE FOUND TO HAVE DEEP GROOVES ON THE OUTER SURFACE.  FURTHER EXAMINATION OF THE ATTACH FITTINGS FOUND THE HOLES OVERSIZE	D AND OUT-OF-ROUND, AND FORWARD STRAPS WERE FOUND GOUGED (THIS WAS THE FIRST INSPECTION OF THIS AREA SINCE NEW).  SUBMIT	TER RECOMMENDS INSPECTING THE ATTACHING BOLTS, BUSHINGS, AND STRAPS FOR GOUGES, AND THE ATTACH FITTING FOR MISALIGNMENT.	  NEW STAINLESS STEEL FITTINGS WERE INSTALLED.		2	L	7	2 	4F			RT	A12EA   					 
1996062000436	19960620	00436	CE  	1996	6	20	96ZZZX3055       	1	19960531	G	3260	444EN496	SWITCH          			BEECH 	90    	C90         	1152913	CE  										LT DOWNLOCK	WIRE BROKEN     	B	L		AKGR	K				NONE                    				P			NO WARNING INDICATION     			AP	APPROACH       	1			CE	05	115KU					LJ1040				CREW REPORTED NOT HAVING LEFT DOWN AND LOCK INDICATION.  MADE AN UNEVENTFUL LANDING, AIRCRAFT INSPECTED AND FOUND A BROK	EN WIRE IN THE AREA OF THE TOP END OF THE LEFT GEAR DRAG BRACE.  WIRING WAS REPAIRED AND GEAR SYSTEM OPERATION FOUND NOR	MAL.				1	L	7	2 	3T				3A20    					 
1996062000437	19960620	00437	SO  	1996	6	20	96ZZZX3056       	1	19960424	G	2761	5802402	TORQUE TUBE     			PIPER 	PA42  	PA42720     	7104212	SO  										CONTROL COLUMN	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	777YP	4702 				425501008				EXPERIENCED MOVEMENT OF PILOT'S CONTROL COLUMN WITH COPILOT'S CONTROL COLUMN HELD SECURELY IN PLACE.  SIDE PLAY AND FORE	/AFT MOVEMENT NOTED IN PILOT'S CONTROL COLUMN.  MOVEMENT OF PILOT'S CONTROL COLUMN TRACED TO WEAR BETWEEN LEFT CONTROL C	OLUMN PIVOT FITTING ASSY, AND STEEL INTERCONNECT TUBE EXHIBITED SIGNS OF LOOSENESS.  REF:  PIPER ACFT PA 42/42-720 AIRPL	ANE PARTS CATALOG, FIG 102, DATED 2-1-91, FOR ILLUSTRATIONS.  NEW CONTROL COLUMN INTERCONNECT TORQUE TUBE ASSY INSTALLED	 ON 2-13-96.  ACFT TT:  5,595.3 HRS, 3,984 LANDINGS.  PN 58024-02 PREVIOUSLY REPLACED ON 1-17-86, ACFT TT:  893.4 HRS FO	R SAME DISCREPANCY.	1	L	7	2 	4T				A23SO   					 
1996062000438	19960620	00438	SO  	1996	6	20	96ZZZX3057       	2	19960513	G	8550	643716	FILTER ADAPTER  			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					WASTEGATE OIL	WRONG CONN      	B	L		EVGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	33	2FOR					U20606295				EXPERIENCED INCONSISTENT MANIFOLD PRESS & FUEL FLOWS.  LOOKED AT SOURCE OF OIL TO WASTEGATE FROM OIL PUMP HSNG P/N 64371	6, & FND PORT USED SUPPLIED UNFILTERED OIL.  OIL PUMP HSNG IS NEW P/N WHICH USES FULL FLOW OIL FILTER.  NEW HSNG HAS, BE	LOW FILTER BASE, A 2ND PORT THAT WILL PROVIDE FILTERED OIL.  OLD P/N 632770 OIL PMP HSNG WHICH USES OTHER STYLE OF FILTE	R (CESSNA SUPPLIED OIL FILTER ADAPTER P/N 1250922-4) HAS 1 PORT FOR FILTERED OIL SUPPLY TO W/G.  PORT IS IN SAME LOCALE 	AS UNFILTERED PORT ON NEW P/N HSNG.  PROBLEM DEVELOPED WHEN REPLACING ENG WITH OLD HSNG WITH ENG HAVING NEW.  ASSUMED FI	LTERED OIL WOULD COME OUT OF SAME LOCALE, PORT IS DIFFERENT INSIDE.  PORT IS PLUGGED WITH ALLEN HEAD PLUG.	1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1996062000742	19960620	00742	NM  	1996	6	20	96ZZZX3058       	1	19960506	G	5210		DOOR            			PIPER 	PA60  	PA60600     	7106001	NM  										TOP CABIN	DEPARTED        	D		A		A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			GL	07	222KD					600557181				TOP CABIN DOOR CAME OPEN IN-FLIGHT, SEPARATED FROM AIRCRAFT.  LANDED AIRCRAFT IN SYR.  INSTALLED NEW DOOR ASSEMBLY AND R	ETURNED TO SERVICE.					1	M	7	2 	3O			RT	A17WE   					 
1996062000743	19960620	00743	SW  	1996	6	20	96ZZZX3059       	1	19960609	G	2460	727422	BREAKER         			SWRNGN	SA226 	SA226TC     	8780404	SW  										ENCODE ALTIMETER	DEFECTIVE       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	240NM					T240				CIRCUIT BREAKER WAS INTERMITTENT EVEN THOUGH THE BREAKER HAD NOT TRIPPED.  THIS INTERMITTENT POWER CAUSED ENCODING ALTIM	ETER TO FLUCTUATE WITH INTERMITTENT FLAGS.  ENCODING ALTIMETER SENT OUT ALTITUDE 300 FEET HIGHER THAN INDICATED, THEN FL	AGGED AND WENT OFF-LINE.  RESETTING BREAKER CAUSED FAULT TO DISAPPEAR THEN PROBLEM CAME BACK.  BELIEVED TO BE DUE TO HIG	H AMBIENT TEMPERATURE AT TAKEOFF (110).			2	L	7	2 	4T			RT	A8SW    					 
1996062000744	19960620	00744	CE  	1996	6	20	96ZZZX3060       	1	19960328	G	2820	3592122169	LINE            			BEECH 	35    	G35         	1151516	CE  										RT GEAR WELL	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4575D	5325 				D4727				DURING ANNUAL INSPECTION AND GEAR RETRACTION TEST, DISCOVERED RT AUXILIARY FUEL TANK LINE WHICH PASSES ACROSS THE TOP OF	 THE LANDING GEAR HAD BEEN CHAFED ABOUT ONE-HALF OF ITS THICKNESS DUE FROM A GREASE FITTING ON THE FORWARD ROLLER WHICH 	WAS RUBBING EACH TIME THE GEAR WAS RETRACTED.  IT WAS APPARENT THERE WAS NOT ENOUGH CLEARANCE BETWEEN GEAR AND LINE.  SU	BMITTER STATES THIS COULD HAVE CAUSED A SERIOUS ACCIDENT HAD IT GONE UNDETECTED.  THIS AREA NEEDS TO BE CHECKED AT EACH 	ANNUAL/OR PRE-FLIGHT.		1	L	7	1 	3O				A777    					 
1996062000745	19960620	00745	CE  	1996	6	20	96ZZZX3061       	1	19960328	G	2820		LINE            			BEECH 	35    	G35         	1151516	CE  										FUEL	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4575D	5325 				D4727				DURING ANNUAL INSPECTION, ALL FLEXIBLE FUEL AND BRAKE LINES WERE FOUND SEVERELY DETERIORATED.  SUBMITTER STATES THIS IS 	AN ONGOING PROBLEM.  A TIME LIMIT SHOULD BE PLACED ON THESE ITEMS.  RECOMMEND 10 YEARS OR 1500 HRS.  THESE LINES APPEARE	D TO BE ORIGINAL.				1	L	7	1 	3O				A777    					 
1996062000746	19960620	00746	SO  	1996	6	20	96ZZZX3062       	1	19960521	G	5512	6358600	SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  										TAIL LT TRIM TAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	529PU					2841194				ONGOING CRACKS ON TRIM TAB LOWER SKINS AND INBOARD RIBS AT TRIM TAB CONTROL ARM ATTACH POINT,  SKIN AND/OR RIB HAS CRACK	ED FROM 2500-4000 HOURS.  FIRST REPAIR WAS TO REPLACE SKIN AND RIBS WITH NEW PIPER PARTS AND THESE LASTED 1000-1500 HOUR	S BEFORE CRACKING AGAIN IN THE SAME PLACE.  CURRENTLY HAVE ADDED .040 INCH ALUMINUM DOUBLER ON SEVERAL AIRCRAFT FOR LONG	ER LIFE.  AIRCRAFT USED FOR FLIGHT TRAINING 1,000 HOURS PER YEAR.  SUBMITTER STATES OLDER AIRCRAFT DO NOT DISPLAY THIS P	ROBLEM TOO WELL AFTER 6000 HOURS.		1	L	7	1 	3O				2A13    					 
1996062000747	19960620	00747	SO  	1996	6	20	96ZZZX3063       	1	19960521	G	5512	6358601	SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  										TAIL RT TRIM TAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	529PU					2841194				ONGOING CRACKS ON TRIM TAB LOWER SKINS AND INBOARD RIBS AT TRIM TAB CONTROL ARM ATTACH POINT,  SKIN AND/OR RIB HAS CRACK	ED FROM 2500-4000 HOURS.  FIRST REPAIR WAS TO REPLACE SKIN AND RIBS WITH NEW PIPER PARTS AND THESE LASTED 1000-1500 HOUR	S BEFORE CRACKING AGAIN IN THE SAME PLACE.  CURRENTLY HAVE ADDED .040 INCH ALUMINUM DOUBLER ON SEVERAL AIRCRAFT FOR LONG	ER LIFE.  AIRCRAFT USED FOR FLIGHT TRAINING 1,000 HOURS PER YEAR.  SUBMITTER STATES OLDER AIRCRAFT DO NOT DISPLAY THIS P	ROBLEM TOO WELL AFTER 6000 HOURS.		1	L	7	1 	3O				2A13    					 
1996062000748	19960620	00748	SO  	1996	6	20	96ZZZX3064       	1	19960521	G	5512	6358601	SKIN            			PIPER 	PA28  	PA28R201    	7102816	SO  										TAIL RT TAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	532PU					2837040				ONGOING CRACKS ON TRIM TAB LOWER SKINS AND INBOARD RIBS AT TRIM TAB CONTROL ARM ATTACH POINT.  SKIN AND/OR RIB HAS CRACK	ED FROM 2500-4000 HOURS.  FIRST REPAIR WAS TO REPLACE SKIN AND RIBS WITH NEW PIPER PARTS AND THESE LASTED 1000-1500 HOUR	S BEFORE CRACKING AGAIN IN THE SAME PLACE.  CURRENTLY, HAVE ADDED .040 INCH ALUMINUM DOUBLER ON ONE AIRCRAFT FOR LONGER 	LIFE.  AIRCRAFT USED FOR FLIGHT TRAINING 750 HOURS PER YEAR.			1	L	7	1 	3O				2A13    					 
1996062000749	19960620	00749	SO  	1996	6	20	96ZZZX3065       	1	19960521	G	5512	6358600	SKIN            			PIPER 	PA28  	PA28R201    	7102816	SO  										TAIL LT TAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	532PU					2837040				ONGOING CRACKS ON TRIM TAB LOWER SKINS AND INBOARD RIBS AT TRIM TAB CONTROL ARM ATTACH POINT.  SKIN AND/OR RIB HAS CRACK	ED FROM 2500-4000 HOURS.  FIRST REPAIR WAS TO REPLACE SKIN AND RIBS WITH NEW PIPER PARTS AND THESE LASTED 1000-1500 HOUR	S BEFORE CRACKING AGAIN IN THE SAME PLACE.  CURRENTLY, HAVE ADDED .040 INCH ALUMINUM DOUBLER ON ONE AIRCRAFT FOR LONGER 	LIFE.  AIRCRAFT USED FOR FLIGHT TRAINING 750 HOURS PER YEAR.			1	L	7	1 	3O				2A13    					 
1996062000750	19960620	00750	CE  	1996	6	20	96ZZZX3066       	1	19960425	G	2430	C593000101	SENSOR          	HOPKINSENG  	0337        	CESSNA	172   	172M        	2072418	CE  										OVERVOLTS	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	4649Q	1310 			3031006	17261735				OVERVOLTAGE SENSOR DEFECTIVE:  NO POWER OUT ON ORANGE WIRE TO ALTERNATOR FIELD SWITCH TO ENERGIZE ALTERNATOR FIELDS - NO	 CHARGING.					1	H	7	1 	3O			NT	3A12    					 
1996062000751	19960620	00751	CE  	1996	6	20	96ZZZX3067       	1	19960514	G	5540	S16751	BEARING BLOCK   			CESSNA	172   	172F        	2072414	CE  										RUDDER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	8739U	2200 				17252643				COMPLAINT AT ANNUAL THAT AIRCRAFT IS HARD TO STEER.  FOUND RUDDER BEARING BLOCKS CORRODED RESTRICTING MOVEMENT OF RUDDER	 PEDALS.  LACK OF LUBRICATION ON RUDDER BAR AT BEARING BLOCKS.  REPLACEMENT CESSNA UNITS ARE NO LONGER METAL.					1	H	7	1 	3O			NT	3A12    					 
1996062000753	19960620	00753	SO  	1996	6	20	96ZZZX3069       	1	19960503	G	5610	41543	WINDSHIELD      	PPG         		PIPER 	PA31  	PA31350     	7103110	SO  										COCKPIT	CORRODED        	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	84859	2250 			90030H4826	317305043				THE CORROSION STARTED ON THE TERMINAL STRIP WHICH IS LAMINATED BETWEEN 2 PLATES OF PPG GLASS.  THE CORROSION THEN SPREAD	 TO THE 50-GAUGE GOLD HEATED WIRES RUNNING HORIZONTALLY THROUGH THE GLASS AT EYE LEVEL.  AS THE 50-GAUGE GOLD WIRE CORRO	DES,THE DIAMETER OF THE WIRE IS REDUCED CAUSING THE RESISTANCE TO GO UP WHICH, IN TURN, CAUSES THE WIRE TO HEAT AND BURN	.  THIS THEN RENDERS THE WINDSHIELD UNAIRWORTHY FOR THE CONDITIONS.  SUBMITTER STATES THE SOLUTION FOR PPG PIPER WINDSHI	ELDS SHOULD BE AN OHM AND VISUAL CHECK TO PPG HEATED WINDSHIELDS EVERY 12 MONTHS BECAUSE THE PPG WORKMANSHIP WARRANTY IS	 48 MONTHS.	1	L	7	2 	3O				A20SO   					 
1996062000754	19960620	00754	SO  	1996	6	20	96ZZZX3070       	1	19960523	G	3230	4198300	HOOK            			PIPER 	PA31  	PA31350     	7103110	SO  										LT DOWNLOCK	MALFUNCTION     	B			BONR	O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	19	88AJ	3250 				318252048				ON TRAINING FLIGHT, PILOT WAS UNABLE TO GET GREEN DOWN LIGHTS ON BOTH MLG.  CYCLED GEAR - NO CHANGE.  TOWER SAID INBOARD	 GEAR DOORS OPEN ON FLYBY.  HAND PUMP OPERATION WAS VERY HARD AS IF ACTING AGAINST SYSTEM.  LANDING WAS MADE WITHOUT INC	IDENT.  PUT AIRCRAFT ON JACKS, FOUND BOTH LT AND RT DOWNLOCK HOOKS NOT ENGAGED.  FOUND PIVOT BOLTS VERY DIRTY AND STICKY	.  CLEANED AND OPS CHECKS GOOD.			1	L	7	2 	3O				A20SO   					 
1996062000755	19960620	00755	SO  	1996	6	20	96ZZZX3071       	1	19960523	G	3230	4198301	HOOK            			PIPER 	PA31  	PA31350     	7103110	SO  										RT DOWNLOCK	MALFUNCTION     	B			BONR	O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	19	88AJ	3250 				318252048				ON TRAINING FLIGHT, PILOT WAS UNABLE TO GET GREEN DOWN LIGHTS ON BOTH MLG.  CYCLED GEAR - NO CHANGE.  TOWER SAID INBOARD	 GEAR DOORS OPEN ON FLYBY.  HAND PUMP OPERATION WAS VERY HARD AS IF ACTING AGAINST SYSTEM.  LANDING WAS MADE WITHOUT INC	IDENT.  PUT AIRCRAFT ON JACKS, FOUND BOTH LT AND RT DOWNLOCK HOOKS NOT ENGAGED.  FOUND PIVOT BOLTS VERY DIRTY AND STICKY	.  CLEANED AND OPS CHECKS GOOD.			1	L	7	2 	3O				A20SO   					 
1996062000756	19960620	00756	SO  	1996	6	20	96ZZZX3072       	2	19960528	G	7414	10357281H	COIL            			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					ENGINE RT MAG	WIRE BROKEN     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05	42946					28R8331025	299532R			INSTALLED NEW MAGNETO, WAS INOPERATIVE.  TROUBLESHOOTING REVEALED THE COIL WIRE WAS BROKEN AT THE TERMINAL END.  (INSULA	TION WAS STILL INTACT).  SUBMITTER STATED CAUSE WAS DUE TO THE TERMINAL END BEING CRIMPED TOO HARD RESULTING IN BROKEN W	IRE.  RECOMMEND MANUFACTURER BE INFORMED.				1	L	7	1 	3O	3	O		2A13    	E9CE				 
1996062000757	19960620	00757	SO  	1996	6	20	96ZZZX3073       	2	19960526	G	7414	107902018R	MAGNETO         			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					ENG RT MAG	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	42946	59   				28R8331025	299532R			MAGNETO FAILED.  DID NOT TROUBLESHOOT MAG DUE TO IT BEING UNDER WARRANTY.						1	L	7	1 	3O	3	O		2A13    	E9CE				 
1996062000758	19960620	00758	SO  	1996	6	20	96ZZZX3074       	2	19960528	G	7414		CONDENSER       		107902018R  	PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					ENG LT MAG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	42946	90   				28R8331025	299532R			INVESTIGATION FOR MAG PROBLEM FOUND CONDENSER HAD NO CONTINUITY.						1	L	7	1 	3O	3	O		2A13    	E9CE				 
1996062000759	19960620	00759	SO  	1996	6	20	96ZZZX3075       	2	19960528	G	7414	10357281H	CONDENSER       		107902018R  	PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					ENG RT MAG	WIRE BROKEN     	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05	42946	59   				28R8331025	299532R			RT MAG INOPERATIVE.  INSTALLED NEW MAG, SN 1069532DR.  THIS NEW MAG WAS INOPERATIVE.  TROUBLESHOOTING BOTH MAGS REVEALED	 ORIGINAL MAG HAD BAD CONSENSER AND THE NEW MAGNETO HAD A BAD COIL.  BOTH NEW MAGNETOS HAD A BAD COIL.  BOTH THE CONDENS	ER AND COIL PROBLEMS RESULTED FROM THE TERMINAL ENDS BEING CRIMPED TOO HARD CAUSING THE WIRE TO FAIL.  SUBMITTER RECOMME	NDS THE MANUFACTURER BE INFORMED ON THIS PROBLEM.			1	L	7	1 	3O	3	O		2A13    	E9CE				 
1996062000760	19960620	00760	WP  	1996	6	20	96ZZZX3076       	1	19960501	G	3710	33E02	AIR PUMP        		2           	GRUMAN	C1A   	C1A         	3951014	WP  										ENGINE	FAILED          	H				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	99	26GH		1    		1509M	136791				PUMP INSTALLED AND TESTED.  APPROXIMATELY 15 MINUTES INTO FLIGHT, PUMP SHAFT SHEARED AFTER SPLITTING PUMP BODY RESULTING	 IN COMPLETE OIL LOSS IN ENGINE.  SUBMITTER UNABLE TO DETERMINE EXACT CAUSE OF FAILURE.					2	H	7	2 	4R			RT	EXPA2H72					 
1996062000761	19960620	00761	EA  	1996	6	20	96ZZZX3077       	2	19960529	G	8530		CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ROCKER STUD	DEFECTIVE       	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SW	01	75616		209  		05K21119	17267852	2205276			ROCKER STUD BACKED OUT CAUSING EXCESSIVE VALVE CLEARANCE WHICH CAUSED THE PUSHROD TO GET JAMMED AND BENT.  CYLINDER WAS 	IN C/W SB 412B (AD 77-20-07) WHICH REQUIRES STUDS TO BE LOCKTITE INTO POSITION.  CYLINDER WAS MARKED IAW THIS PROCEDURE.	  SUBMITTER SUGGESTS BETTER WAY OF SECURING STUD.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996062000762	19960620	00762	SO  	1996	6	20	96ZZZX3078       	1	19960528	G	3246	40131	WHEEL           	PARKERHANFIN		PIPER 	PA23  	PA23250     	7102308	SO  										MLG	RIM MISSING     	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	09	6921A	3500 				277954112				GROUND PERSONNEL STATED THAT THE LEFT WHEEL WAS WOBBLING ON TAXI.  INSPECTION FOUND ONE-THIRD OF THE RIM OF THE WHEEL WH	ICH HOLDS THE TIRE ON WAS MISSING.  TIRE WAS RUBBING BRAKE CALIPER.  SUBMITTER STATED TIRE COULD HAVE BLOWN COMPLETELY O	FF RIM IF NOT SEEN BY GROUND PERSONNEL.				1	L	7	2 	3O				1A10    					 
1996062000763	19960620	00763	SO  	1996	6	20	96ZZZX3079       	1	19960425	G	2434		ALTERNATOR      			PIPER 	PA28  	PA28140     	7102802	SO  										DC SYSTEM	FLUCTUATION     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23	55498					287325420				REMOVED ALTERNATOR DUE TO AMPMETER FLUCTUATION.  INSPECTED AND DETERMINED AUTOMOTIVE TYPE.  COOLING FINS WERE INSTALLED 	IN OPPOSITE DIRECTION AS COMPARED TO O/H AERO ELECTRIC UNITS.  ALTERNATOR REMOVED, HAD NO DATA PLATE OR ANY MARKINGS.  U	NIT REMOVED AND DISCARDED.				1	L	7	1 	3O				2A13    					 
1996062000764	19960620	00764	CE  	1996	6	20	96ZZZX3080       	1	19960601	G	3233	24130023	FITTING         			CESSNA	172   	172RG       	2072438	CE  										NLG ACTUATOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4636V					172RG0345				WHEN ON JACKS, FORE AND AFT FORCE ON THE NOSE GEAR REVEALED A ROCKING MOTION OF THE NOSE GEAR ACTUATOR REAR FITTING TO F	USELAGE ON ITS 20 ATTACHMENT BOLTS.  WITH NUTS TORQUED, COULD EASILY TURN BOLTS AS THEY HAD RUN OUT OF THREADS AND NUT W	AS JAMMED AGAINST SHANK.  ONE ADDITIONAL AN-960-10 WASHER IS REQUIRED UNDER EACH OF THE 20 NUTS.  AD 72-7-9 REFERS TO LO	OSE BOLTS THAT REQUIRES ANOTHER WASHER TO SECURE THEM.			1	H	7	1 	3O				3A17    					 
1996062000765	19960620	00765	GL  	1996	6	20	96ZZZX3081       	2	19960515	G	7322		CARBURETOR      			AMTR  	SONERI	SONERAI     		GL  	AMTRVW	VOLKS 	VW1700VOLKS 	99999	GL  					ENGINE	BLOCKED VENT    	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CE	05	283SX	55   				283				DURING TAKEOFF ENGINE HAD POWER LOSS.  FUEL STARVATION DUE TO BLOCKED VENT SUSPECTED.  SPARK PLUGS CONFIRM EXCESSIVE LEA	N MIXTURE CAUSED POWER LOSS.					1	M	7	1 	3O	3	O		EXPA1M71	EXP3O				 
1996062000768	19960620	00768	SO  	1996	6	20	96ZZZX3084       	1	19960513	G	5712	78475005	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  										RT WING	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	170ND	6357 				2837005				FOUND RIB CRACKED DURING SCHEDULED INSPECTION.  CRACK WAS ON RIB FLANGE WHERE BOLTS GO THROUGH DRAG BRACE FITTING THAT B	OLTS TO WING SPAR.  SUBMITTER STATES THIS OPERATOR HAS ALSO FOUND NUMEROUS NOSE RIBS CRACKED ON FORWARD SIDE OF SPAR WHE	RE NOSE RIB BOLTS TO SAME GEAR FITTING.				1	L	7	1 	3O				2A13    					 
1996062000769	19960620	00769	EA  	1996	6	20	96ZZZX3085       	2	19960521	G	8550	STD1686	SCREEN          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	DEFECTIVE       	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	63ND	178  				317852098	L697361A			DURING SCHEDULED MAINTENANCE FOUND SCREW AND GASKET MATERIAL IN SUCTION SCREEN.  REMOVED OIL SUMP/PAN, INSTALLED SCREW P	ER LYCOMING INSTRUCTIONS.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996062000770	19960620	00770	CE  	1996	6	20	96ZZZX3086       	1	19960603	G	2822		BOOST PUMP      	DUKES       		BEECH 	58    	58          	1152740	CE  										FUEL BOOST	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	85BE		3696 		1367	TH1455				FUEL LEAKING FROM BOOST PUMP DRAIN.						1	L	7	2 	3O				3A16    					 
1996062000771	19960620	00771	SO  	1996	6	20	96ZZZX3087       	1	19960531	G	3230	AN17633	BOLT            			PIPER 	PA23  	PA23        	7102302	SO  										LT MLG DRAG LINK	SHEARED         	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	13	2060P	1000 				23647				LEFT MAIN GEAR DRAG LINK UPPER BOLT, ITEM NR 61, FIGURE NR 37, SHEARED IN CENTER ON LANDING.  SUBSEQUENT GEAR COLLAPSE A	ND PROPELLER STRIKE.  SUBMITTER STATED POSSIBLE MANDATORY BOLT INSPECTION AND/OR REPLACEMENT AT 1,000 HRS MAY BE SUFFICI	ENT.				1	L	7	2 	3O				1A10    					 
1996062000772	19960620	00772	SO  	1996	6	20	96ZZZX3088       	1	19960603	G	7922	53E19600	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  										THERMO BYPASS	WORN            	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3582X	562  			57328	318052105				INSPECTION FOUND THE CENTER SPRING ASSY RETAINING CLIP LOOSE ON THE VERNATHERM BODY.						1	L	7	2 	3O				A20SO   					 
1996062000773	19960620	00773	CE  	1996	6	20	96ZZZX3089       	1	19960528	G	2434	902014	BEARING         	PRESTOLITE  	ALT9422     	CESSNA	310   	310R        	2074245	CE  										RT ENG ALT	FAILED          	D				A				UNSCHED LANDING         				B	O	H	SMOKE/FUMES/ODORS/SPARKS  	OTHER                     	ELECT. POWER LOSS-50 PC   	CL	CLIMB          	1			SO	11	610Z		319  			310R0071				CATASTROPHIC BEARING FAILURE OF ALTERNATOR ON RIGHT ENGINE AFTER TAKEOFF.  PILOT RETURNED TO AIRPORT WITHOUT COMMUNICATI	ON RADIOS.  ONLY ADF AND GPS WAS STILL WORKING.  PILOT REPORTED SEEING SPARKS FROM THE ALTERNATOR AND INTERIOR LIGHT FLI	CKERED.  RADIOS WENT OUT AND RETURNED TO AIRPORT WITH NO PROBLEM LANDING.  SUBMITTER STATED THIS IS THE SECOND LIKE INCI	DENT REPORTED ON ALT 9422 ALTERNATORS.			1	L	7	2 	3O				3A10    					 
1996062000774	19960620	00774	CE  	1996	6	20	96ZZZX3090       	1	19960602	G	3220		WHEEL ASSY      			CESSNA	120   	120         	2071402	CE  										TAIL WHEEL	DEPARTED        	D				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			NE	03	120PG					11978				TAIL WHEEL ASSY DEPARTED AIRCRAFT.  LEAF SPRING WAS BROKEN.						1	H	7	1 	3O				A768    					 
1996062000775	19960620	00775	SO  	1996	6	20	96ZZZX3091       	1	19960603	G	7922	53ED22144	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  										THERMO BYPASS	NUT LOOSE       	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3582X	289  			68464	318052105				THE END RETAINING NUT ON THE VERNATHERM IS LOOSE.  LYCOMING SB 518C DOES NOT APPLY TO THIS PART NUMBERED VERNATHERM.						1	L	7	2 	3O				A20SO   					 
1996062000776	19960620	00776	SO  	1996	6	20	96ZZZX3092       	1	19960603	G	7922	53E19600	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  										THERMO BYPASS	NUT STRIPPED    	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	777KT	531  				317552053				VERNATHERM VALVE SEAT RETAINING NUT STRIPPED AND SEPARATED FOR SHAFT OF VALVE.  ALSO, RETAINING CLIP FOR VERNATHERM BODY	 BROKEN INTO 2 PARTS, AND BODY BROKEN AT CLIP ATTACH AREA.					1	L	7	2 	3O				A20SO   					 
1996062000777	19960620	00777	SO  	1996	6	20	96ZZZX3093       	1	19960603	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	777KT	531  				317552053				VERNATHERM VALVE SEAT RETAINING NUT LOOOSE AND WORKING ON RETAINING SHAFT THREADS.						1	L	7	2 	3O				A20SO   					 
1996062000778	19960620	00778	NE  	1996	6	20	96ZZZX3094       	2	19960605	G	7414	GE52120	DISTRIBUTOR GEAR	BOSCH       	5B9RU3      	BEECH 	18    	E18S        	1151006	CE  	PWA   	R985  	R985AN14B   	52008	NE  					MAG	TEETH SHEARED   	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	5611D	1228 			B46676	BA316	22664			COMPLETE FAILURE OF THE MAGNETO DUE TO SHEARING OF ALL TEETH OF THE DISTRIBUTER GEAR.						1	L	7	2 	3R	3	R		A765    	5E1				 
1996062700342	19960627	00342	EU  	1996	6	27	96ZZZX3156       	1	19960531	G	5521	10902000259	RIB             		10902000293 	AGUSTA	A109  	A109A2      	0260120	EU  										LT SYNC ELEV	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1YH	4183 			EM151	7264				LEFT SYNC ELEVATOR CRACKS APPEARING ALONG EDGE OF THE INBOARD RIB, PN 109-0200-02-59, AND PN 109-0200-04-7.  DISASSEMBLY	 REVEALED LOOSE ATTACH ANGLES ON SPAR.  CRACKED FRONT AND REAR SPAR.  CRACKED SPAR DOUBLERS, PN 109-0200-02-49 AND DASH 	33.  RECURRING PROBLEM, 5 THIS FLEET.				1	G	7	2 	3U				H7EU    					 
1996062700343	19960627	00343	EU  	1996	6	27	96ZZZX3157       	1	19960531	G	5521	10902000259	RIB             		10902000294 	AGUSTA	A109  	A109A2      	0260120	EU  										RT SYNC ELEV	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1YH	4183 			EM151	7264				RIGHT SYNC ELEVATOR CRACKS APPEARING ALONG EDGE OF THE INBOARD RIB, PN 109-0200-02-59 AND PN 109-0200-04-7.  DISASSEMBLY	 REVEALED LOOSE ATTACH ANGLES AND CRACKS IN FRONT SPAR AREA.  RECURRING PROBLEM.					1	G	7	2 	3U				H7EU    					 
1996062700344	19960627	00344	WP  	1996	6	27	96ZZZX3158       	1	19960521	G	6720	369D21832	BEARING         		369D21800501	HUGHES	369   	369D        	4470706	WP  										T/R PITCH	LOOSE           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	911FT					811036D				DURING ROUTINE INSPECTION OF AD 94-24-04, THE DUPLEX BEARING WAS LOOSE (AXIALLY) INSIDE OF PITCH CONTROL HOUSING (369A18	02) - THE ENTIRE BEARING INCLUDING THE OUTER HOUSING OF THE BEARING.  THIS COULD ALLOW THE BEARING TO SPIN INSIDE THE HO	USING.  SUBMITTER STATED SHOULD BE PRESSURE FIT.				1	G	7	1 	3U				H3WE    					 
1996062700345	19960627	00345	EU  	1996	6	27	96ZZZX3159       	1	19960531	G	3230	10905021515	BRACE           			AGUSTA	A109  	A109A2      	0260120	EU  										MLG	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	55NW	3580 				7267				MAIN LANDING GEAR BRACE HAS CRACK LOCATED AT OUTBOARD BEARING BORE.  SUBMITTER STATED DIFFICULT TO SEE UNLESS UNIT IS RE	MOVED.					1	G	7	2 	3U				H7EU    					 
1996062700346	19960627	00346	SW  	1996	6	27	96ZZZX3160       	1	19960509	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		550  			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.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 549.7 HOURS.				1	G	7	1 	3U				H2SW    					 
1996062700347	19960627	00347	SW  	1996	6	27	96ZZZX3161       	1	19960509	G	6230	206010336005	LINK IDLER      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1081G	550  				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.  SUBMITTER STATED NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT, 549.7 HOURS.				1	G	7	1 	3U				H2SW    					 
1996062700349	19960627	00349	SW  	1996	6	27	96ZZZX3164       	1	19960507	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										M/R	SKIN SEPARATED  	B		A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	365AL				A720	51376				INSPECTION FOUND UPPER SURFACE SKIN SEPARATED FROM SPAR AT BLADE TIP.  UPON FURTHER INSPECTION, INNER SPAR WAS FOUND HEA	VILY CORRODED.  SUBMITTER STATED BEFORE NEW BLADE IS PUT INTO SERVICE, REMOVE TIP WEIGHT ASSY, TREAT INSIDE OF SPAR WITH	 ALODINE AND KORPON PRIMER.  WRAP TIP WEIGHTS WITH BARRIER TAPE.  REINSTALL TIP WEIGHTS AND SEAL WITH 890 PROSEAL TO ELI	MINATE MOISTURE INTRUSION.			1	G	7	1 	3U				H2SW    					 
1996062700350	19960627	00350	SW  	1996	6	27	96ZZZX3165       	1	19960509	G	6230	2060103353001	LEVER ASSY      		206010350021	BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5740L		600  			45459				DAILY INSPECTION FOUND BUSHING AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-101	 BEARING.  SUBMITTER STATES NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 599.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1996062700351	19960627	00351	SW  	1996	6	27	96ZZZX3166       	1	19960509	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		600  			45459				DAILY INSPECTION FOUND BUSHING AND BEARINGS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH 206-010-338-003 BUSHINGS, 2 EACH NAS6605D64 BOLTS, 1 EACH 206-010-470-101	 BEARING.  SUBMITTER STATES NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 599.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1996062700354	19960627	00354	EU  	1996	6	27	96ZZZX3169       	1	19960328	G	6240	117945641	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										MAST MOMENT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117VU	33   			ED70655	7211				WHEN POWER IS APPLIED, RED LIGHT DOES NOT COME ON EACH TIME PRIOR TO TEST.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996062700355	19960627	00355		1996	6	27	96ZZZX3170       	4	19960323	G	3421	4021541671	GYRO            			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT ATTITUDE	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	214AE	4    			84081138	7206				GYRO BACKLIGHTING INOPERATIVE.  SLOW TO SPIN UP.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996062700356	19960627	00356		1996	6	27	96ZZZX3171       	4	19960424	G	2312	064101905	TRANSCEIVER     			BELL  	222   	222U        	1182140	SW  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM				16181	47573				RADIO REC. AND CANNOT CHANGE FREQUENCY.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW    					 
1996062700357	19960627	00357		1996	6	27	96ZZZX3172       	4	19960503	G	3457	066040310111	GPS             		KLN90A      	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	495LF				13398	S645				SHOWS RECEIVER HARDWARE ERROR CODE 0200.  REPAIR AS NECESSARY.						1	G	7	2 	3U				H3EU    					 
1996062700358	19960627	00358		1996	6	27	96ZZZX3173       	4	19960426	G	3421	5040017926	GYRO            			BOLKMS	117   	BK117A3     	5626015	EU  										COCKIT ATTITUDE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	527MB	144  			3427	7103				SLOW TO OPERATE, PULL THREE OR FOUR TIMES TO ERECT.  REPAIR AS NECESSARY.						1	G	7	2 	3U				H13EU   					 
1996062700364	19960627	00364		1996	6	27	96ZZZX3179       	4	19960214	G	2312	40001452500	TRANSCEIVER     		RT138F      	BOLKMS	117   	BK117B1     	5626012	EU  										CONTROL HEAD	DEFECTIVE       	B			TI1R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	05	170MC				297	7217				ON INSTALLATION IN A/C, CONTROL HEAD GUARD INDICATOR LIGHT ILLUMINATED AND STAYED LIT EVEN WITH NO GUARD MODULE INSTALLE	D.  REMOVED AND REPLACED.					1	G	7	2 	3U				H13EU   					 
1996062700365	19960627	00365		1996	6	27	96ZZZX3180       	4	19960416	G	2312	40001452500	TRANSCEIVER     		RT138F      	BOLKMS	117   	BK117B1     	5626012	EU  										SIDE TONE	POT MISSING     	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	170MC				269	7217				RECEIVED THIS UNIT WITH SIDE TONE ADJ. POT MISSING FROM AUDIO BOARD.  INSTALLED AUDIO SIDE TONE MISSING POT, BENCH ALIGN	 AND CHECK.  REMOVED AND REPLACED.					1	G	7	2 	3U				H13EU   					 
1996062700366	19960627	00366	EU  	1996	6	27	96ZZZX3181       	1	19960406	G	5210	1172428111	CATCHER         			BOLKMS	BK117 	BK117C1     	5626025	EU  										LT DOOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				WORN LT CATCHER.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700367	19960627	00367	EU  	1996	6	27	96ZZZX3182       	1	19960406	G	5210	1172428211	CATCHER         			BOLKMS	BK117 	BK117C1     	5626025	EU  										LT DOOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				WORN LT CATCHER.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700368	19960627	00368	EU  	1996	6	27	96ZZZX3183       	1	19960412	G	6720	117317171	BELL CRANK      			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				BEARING WORN AND STIFF.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700369	19960627	00369	EU  	1996	6	27	96ZZZX3184       	1	19960413	G	2430	171BS1011	POWER SUPPLY    			BOLKMS	BK117 	BK117C1     	5626025	EU  										DC SYSTEM	FAILED          	B			TI1R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	05	317MC				1117	7505				WOULD NOT HOLD CHARGE.  WARNING LIGHT CAME ON IN COCKPIT.  NO CHARGE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700370	19960627	00370		1996	6	27	96ZZZX3185       	4	19960325	G	2210	701240901	ACTUATOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  										DUPLEX PITCH	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				94030194	7505				NR 1 AUTOPILOT FAILURE, 1E47.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700371	19960627	00371		1996	6	27	96ZZZX3186       	4	19960325	G	2210	7012693901	SERVO MONITOR   			BOLKMS	BK117 	BK117C1     	5626025	EU  										NR 1 AUTOPILOT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				88110105	7505				NR 1 AUTOPILOT FAILURE, 1E47.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700372	19960627	00372	EU  	1996	6	27	96ZZZX3187       	1	19960325	G	2140	HTE920018	VALVE           			BOLKMS	BK117 	BK117C1     	5626025	EU  										HEAT SYSTEM	STICKS          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				371	7505				VALVE STICKS OPEN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700373	19960627	00373	EU  	1996	6	27	96ZZZX3188       	1	19960307	G	2140	HTE920018	ACTUATOR VALVE  			BOLKMS	BK117 	BK117C1     	5626025	EU  										CARGO HEAT	STICKS          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				688GB2494	7505				STICKS OPEN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700374	19960627	00374	EU  	1996	6	27	96ZZZX3189       	1	19960227	G	2822	1176415103	PUMP            			BOLKMS	BK117 	BK117C1     	5626025	EU  										BOOST	DEFECTIVE       	B			TI1R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	05	317MC				172207	7505				INTERMITTENT TRANSFER PUMP LIGHT IN-FLIGHT (FULL TANK).  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700375	19960627	00375	EU  	1996	6	27	96ZZZX3190       	1	19960326	G	3213	1175000212	SKID PLATE      			BOLKMS	BK117 	BK117C1     	5626025	EU  										GEAR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				WORN SKID PLATE.  REMOVED AND REPLACED 2 EACH.						1	G	7	2 	3U			NC	H13EU   					 
1996062700376	19960627	00376	EU  	1996	6	27	96ZZZX3191       	1	19960202	G	5530	11730641	VERTICAL FIN    			BOLKMS	BK117 	BK117C1     	5626025	EU  										V FIN	PLUG LOOSE      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				064	7505				BREAK OUT PLUG LOOSE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700377	19960627	00377	EU  	1996	6	27	96ZZZX3192       	1	19960413	G	5210	1172428212	CATCHER         			BOLKMS	BK117 	BK117C1     	5626025	EU  										DOOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				WORN RT CATCHER.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996062700640	19960627	00640	SO  	1996	6	27	96ZZZX3193       	1	19960516	G	3211		ATTACH FITTING  			PIPER 	PA34  	PA34200T    	7103406	SO  										MLG TRUNNION	LOOSE BOLTS     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	812JA	5394 				347970422				PIPER SB956, PART 2, IS A PROCEDURE FOR PERMANENT COMPLIANCE WITH NEW THICKER BOLTS.  THIS RELIEVES THE REPETITIVE INSPE	CTIONS OF THE SB.  SUBMITTER STATED THE NEW BOLTS ARE ALSO COMING LOOSE.  THIS IS THE CONCERN OF THE SB.					1	L	7	2 	3O				A7SO    					 
1996062700641	19960627	00641	GL  	1996	6	27	96ZZZX3194       	3	19960604	G	6111	S82NC4	BLADE           													MCAULY	3AF32C	3AF32C87    	GL  	NR 1	CRACKED         	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					F03928YS			789172		UPON PROPELLER INSPECTION, NR 1 BLADE WAS FOUND CRACKED IN THE THREADS.  BLADE HAS BEEN SCRAPPED.																5	C	P22EA	 
1996062700642	19960627	00642	CE  	1996	6	27	96ZZZX3195       	1	19960511	G	3231	08411066	BELLCRANK       			CESSNA	421   	421B        	2076014	CE  										RT MLG DOOR	BROKEN          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4050Q	5806 				421B0274				RT MLG DOOR OPERATING BELLCRANK BROKEN.  ARM THAT CONNECTS TO LINKAGE FOR DOOR BROKE OFF ALLOWING DOOR TO REMAIN OPEN. E	VIDENCE OF SMALL PREVIOUS CRACK PRIOR TO FAILURE.					1	L	7	2 	3O				A7CE    					 
1996062700643	19960627	00643	CE  	1996	6	27	96ZZZX3196       	1	19960603	G	3232	9581001723	ACTUATOR        			BEECH 	33    	F33A        	1151425	CE  										GEAR DOOR	BINDING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	8252T				96B033	CE1545				FOUND ACTUATOR HAS INTERNAL BIND - 4 TO 6 TURNS BEFORE UP AND 4 TO 6 TURNS BEFORE BOTTOMING ON THE DOWN SIDE.  COMPONENT	 OVERHAULED BY BEECHCRAFT.					1	L	7	1 	3O				3A15    					 
1996062700644	19960627	00644	CE  	1996	6	27	96ZZZX3197       	1	19960603	G	3232	9581001723	ACTUATOR        			BEECH 	33    	F33A        	1151425	CE  										GEAR DOORS	INDEX WRONG     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	8252T				94B560	CE1545				GEAR DOORS WILL NOT CLOSE PROPERLY.  FOUND IMPROPER INDEXING ON ACTUATOR FROM BEECHCRAFT FOLLOWING OVERHAUL.						1	L	7	1 	3O				3A15    					 
1996062700645	19960627	00645	EA  	1996	6	27	96ZZZX3198       	2	19960530	G	7414	10382896	GEAR ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT MAG	TEETH MISSING   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	59829		1071 			317652081	L521661A			MAGNETO CHECK PRIOR TO TAKEOFF.  ENGINE WOULD NOT RUN ON RT MAGNETO.  INSPECTION OF MAGNETO FOUND 4 TEETH MISSING, RT SI	DE DISTRIBUTOR GEAR ASSY.  ALL TEETH ON RT AND LT GEAR ASSYS BADLY WORN AND CHIPPED.  SUSPECT CAUSE, AGE, HEAT, AND LACK	 OF LUB ON DRIVE GEAR.  CLOSER INSPECTION OF MAG GEARS ON INSPECTION.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996062700646	19960627	00646	EA  	1996	6	27	96ZZZX3199       	2	19960522	G	8530		PISTON          			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 3 CYLINDER	RINGS WORN      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4170R	4065 	141  			3240502	L465848A			LOWER SPARK PLUG FOWLED WITH OIL.  REMOVED CYLINDER ASSY AND FOUND UPPER FACE OF RINGS KNIFE EDGED.  REMOVED AND REPLACE	D CYLINDER ASSY.					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996062700647	19960627	00647	CE  	1996	6	27	96ZZZX3200       	1	19960521	G	3230	00282001631	BRACE ASSY      			BEECH 	55    	95C55       	1152708	CE  										RETRACT ROD	FORK BROKE      	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	7959M	5952 				TE189				THE FORK (FITTING) WHICH ATTACHES RETRACT ROD TO DRAG BRACE BROKE.  ONE SIDE OF FORK APPEARED TO HAVE BEEN BROKEN FOR SO	ME TIME.  THIS WAS OLDER STYLE FITTING WELDED TO BRACE.  THIS IS DIFFICULT TO INSPECT WITHOUT DISCONNECTING RETRACT ROD.					1	L	7	2 	3O				3A16    					 
1996062700648	19960627	00648	CE  	1996	6	27	96ZZZX3201       	1	19960425	G	7810	99102999	WYE PIPE        			CESSNA	414   	414A        	2075907	CE  										EXHAUST	DIVIDER BROKE   	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SO	13	2735A					414A0463				THE FLOW DIVIDER IN THE WYE EXHAUST PIPE GOING TO THE TURBO SUPER CHARGER BROKE CAUSING A PIECE OF METAL APPROXIMATELY 1	.50 INCHES BY 2.50 INCHES LONG TO ENTER THE EXHAUST HOUSING SIDE OF THE TURBO.  THIS LIMITED THE TURBOCHARGER MAX OUTPUT	 TO 5,000 FEET MSL.  NO INTERNAL DAMAGE OF TURBOCHARGER TURBINE.  SUBMITTER STATED SHOULD INSPECT INSIDE OF WYE PIPE IF 	MAXIMUM BOOST CANNOT BE ATTAINED.			1	L	7	2 	3O				A7CE    					 
1996062700649	19960627	00649	CE  	1996	6	27	96ZZZX3202       	1	19960514	G	2720	04310031	BELLCRANK       			CESSNA	150   	150D        	2071810	CE  										RUDDER	HOLES ELONGATED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	6006T	3977 				15060706				DURING ANNUAL INSPECTION, HORIZONTAL STABILIZER WAS FOUND TO HAVE LOOSE MOTION.  A DOUBLER KIT FROM CESSNA WAS INSTALLED	 TO CORRECT THIS PROBLEM.  HOWEVER, DURING REPAIR, IT WAS NOTED THE RUDDER BELLCRANK HAD ELONGATED HOLES WHERE THE CABLE	S ATTACHED AND THE TRIM TAB.  HORN HAD AN ENLONGATED HOLE TO THE POINT IT WAS ALMOST BROKEN.  THE BULKHEAD (REAR) HAD A 	CRACK .50 INCH LONG NEAR ONE NUTPLATE WHERE THE RUDDER ATTACHED.  REPAIRS WERE MADE.  TIME SINCE LAST ANNUAL, 195 HOURS.			1	H	7	1 	3O				3A19    					 
1996062700650	19960627	00650	CE  	1996	6	27	96ZZZX3203       	1	19960514	G	2721	04125271	TAB HORN        			CESSNA	150   	150D        	2071810	CE  										RUDDER	HOLE ELONGATED  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	6006T	3977 				15060706				DURING ANNUAL INSPECTION, HORIZONTAL STABILIZER WAS FOUND TO HAVE LOOSE MOTION.  A DOUBLER KIT FROM CESSNA WAS INSTALLED	 TO CORRECT THIS PROBLEM.  HOWEVER, DURING REPAIR, IT WAS NOTED THE RUDDER BELLCRANK HAD ELONGATED HOLES WHERE THE CABLE	S ATTACHED AND THE TRIM TAB.  HORN HAD AN ENLONGATED HOLE TO THE POINT IT WAS ALMOST BROKEN.  THE BULKHEAD (REAR) HAD A 	CRACK .50 INCH LONG NEAR ONE NUTPLATE WHERE THE RUDDER ATTACHED.  REPAIRS WERE MADE.  TIME SINCE LAST ANNUAL, 195 HOURS.			1	H	7	1 	3O				3A19    					 
1996062700651	19960627	00651	CE  	1996	6	27	96ZZZX3204       	1	19960514	G	5312	04121751	BULKHEAD        			CESSNA	150   	150D        	2071810	CE  										AFT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	6006T	3977 				15060706				DURING ANNUAL INSPECTION, HORIZONTAL STABILIZER WAS FOUND TO HAVE LOOSE MOTION.  A DOUBLER KIT FROM CESSNA WAS INSTALLED	 TO CORRECT THIS PROBLEM.  HOWEVER, DURING REPAIR, IT WAS NOTED THE RUDDER BELLCRANK HAD ELONGATED HOLES WHERE THE CABLE	S ATTACHED AND THE TRIM TAB.  HORN HAD AN ENLONGATED HOLE TO THE POINT IT WAS ALMOST BROKEN.  THE BULKHEAD (REAR) HAD A 	CRACK .50 INCH LONG NEAR ONE NUTPLATE WHERE THE RUDDER ATTACHED.  REPAIRS WERE MADE.  TIME SINCE LAST ANNUAL, 195 HOURS.			1	H	7	1 	3O				3A19    					 
1996062700652	19960627	00652	SO  	1996	6	27	96ZZZX3205       	2	19960514	G	7322	3232	FLOAT SHAFT     	FACET       	MA35PA      	CESSNA	150   	150D        	2071810	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	6006T	3978 	1493 			15060706	2048879A			DURING CARBURETOR TEAR DOWN, FLOAT SHAFT WAS FOUND WITH ONE END BROKEN, PUMP PLUNGER, PN 194-593, WAS ALSO FOUND DETERIO	RATED, AS WELL AS THE BOWL BEING FULL OF TRASH.  SUBMITTER STATED CARBURETORS, AS WELL AS ALL OTHER ACCESSORIES, SHOULD 	BE OVERHAULED OR HAVE A CLOSE INSPECTION EACH 500-800 HRS OF OPERATION.				1	H	7	1 	3O	3	O		3A19    	E252				 
1996062700653	19960627	00653	CE  	1996	6	27	96ZZZX3206       	1	19960331	G	2810		FUEL CAP        			CESSNA	182   	182L        	2072726	CE  										WING	WATER LEAK      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	42876					18259229				FUEL CAPS LEAKING WATER INTO FUEL TANKS WHEN EXPOSED TO RAINY WEATHER.  CORRECTED BY INSTALLING CESSNA 182L, SN 59229, (	WW OVAL PLATES) FROM MONARCH AIR AND DEVELOPMENT, INC.					1	H	7	1 	3O			NT	3A13    					 
1996062700654	19960627	00654	SO  	1996	6	27	96ZZZX3207       	2	19960529	G	8550		FILL TUBE       								CONT  	O360  	TSIO360FB   	17025	SO  					ENGINE OIL	RUSTY           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		2135 					305857			THE INSIDE OF THE OIL FILLER TUBE AND OIL CAP WERE RUSTED TO THE POINT OF FLAKES OF RUST BEING KNOCKED OFF OF THE SURFAC	E AND FALLING INTO THE CRANKCASE.  SUBMITTER STATED THESE ASSEMBLIES SHOULD PROBABLY BE MADE OF STAINLESS STEEL.  THEY A	RE CADMIUM PLATED WHEN NEW, AND THAT DOESN'T SEEM TO PREVENT THE CORROSION.									3	O			E9CE				 
1996062700655	19960627	00655	SO  	1996	6	27	96ZZZX3208       	1	19960529	G	2821	144280	COVER           			PIPER 	PA28  	PA28140     	7102802	SO  										GASCOLATOR	BOWED FIT       	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	432FL	4600 				287125219				DURING 100-HOUR INSPECTION, NOTICED FUEL STAINS ON GASCOLATOR BOWL.  REPLACED GASKET BETWEEN BOWL AND COVER, BUT COULD N	OT SEAL.  FURTHER INSPECTION WITH A STRAIGHT EDGE REVEALED COVER WAS BOWED, NOT FLAT AT MATING SURFACE.  SUSPECT CAUSE: 	 MANY YEARS OF OVERTIGHTENING THE BALE WIRE.  FOUND SAME CONDITION ON 2 OTHER PA28140 AIRCRAFT.  REPLACED GASCOLATOR COV	ERS.  RECOMMEND AN INITIAL AND EACH 500 HOURS, INSPECTION OF MATING SURFACES WITH A STRAIGHT EDGE.			1	L	7	1 	3O				2A13    					 
1996062700656	19960627	00656	CE  	1996	6	27	96ZZZX3209       	1	19960510	G	3230	204101743	SUPPORT         			CESSNA	177   	177RG       	2073709	CE  										LT MLG DOWNLOCK	PIN CRACKED     	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	8271G	2486 				177RG0171				DOWNLOCK SUPPORT LOWER PIN FOUND CRACKED.  THIS CONDITION WAS FOUND AFTER FINDING RT DOWNLOCK SUPPORT LOWER PIN BROKEN O	FF.  THIS CRACK NOT VISIBLE WITH DOWNLOCK ASSEMBLED ON AIRCRAFT.  SUSPECT CAUSE:  AIRCRAFT OPERATED ON ROUGH LANDING STR	IP.  RECOMMEND DISASSEMBLY OF LOCK TO ZYGLOW PINS IF A/C IS OPERATED ON ROUGH LANDING STRIPS.				1	H	7	1 	3O				A20CE   					 
1996062700657	19960627	00657	GL  	1996	6	27	96ZZZX3210       	1	19960509	G	2822	478360	PUMP            	FACET       		DIAMON	DA20A1	DA20A1      	05626UX	GL  										FUEL	DEFECTIVE       	H			CB9T	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	524SS					10084				FUEL PUMP WILL NOT RUN AND TRIPS CIRCUIT BREAKER.						1	L	7	1 	3O			NT	TA4CH   					 
1996062700658	19960627	00658	EA  	1996	6	27	96ZZZX3211       	2	19960515	G	8530	LW19281	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 4 CYL EXH	CRACKED         	B			KD4R	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	17	350MP		342  			318152116	L606961A			PILOT REPORTED OIL LEAK ON THE LT ENGINE FOLLOWING A FLIGHT OF APPROXIMATELY 1 HOUR.  MAINTENANCE UNCOWLED ENGINE AND DI	SCOVERED AN EXHAUST STUD FROM THE NR 4 CYLINDER HAD BACKED OUT OF EXHAUST FLANGE.  STUD BOUNCED AGAINST THE PUSH ROD HOU	SING WEARING A HOLE THROUGH IT APPROX THE SAME SIZE AS THE STUD DIAMETER CAUSING THE OIL LEAK.  ENGINE WAS OPERATING NOR	MALLY WITH THE EXCEPTION OF THE REPORTED OIL LEAK.  AN INVESTIGATION REVEALED A CRACK EXTENDING FROM THE EXHAUST PORT TO	 STUD RETENTION AREA.  CRACK RELIEVED TENSION ON THE STUD CAUSING IT TO BECOME DISLODGED.  FURTHER INVESTIGATION REVEALE	D 4 OF 6 CYLINDERS HAD CRACKS IN SAME GENERAL AREA.	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996062700659	19960627	00659	SW  	1996	6	27	96ZZZX3212       	1	19960530	G	3230	560247501	CONTROL CABLE   			MOONEY	M20   	M20J        	5870219	SW  										EMERG EXTEND	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	201QK	3524 				240290				DURING A ROUTINE CHECK RIDE, PILOT COULD NOT EMERGENCY EXTEND THE GEAR.  GEAR WAS EXTENDED ELECTRICALLY WITHOUT INCIDENT	.  DURING INSPECTION OF GEAR EMERGENCY CABLE ASSY, FOUND A BROKEN SWAGE FITTING AT GEAR MOTOR.  CABLE ASSY WAS REPLACED.	  NO FURTHER ACTION TAKEN.				1	L	7	1 	3O			 	2A3     					 
1996062700660	19960627	00660	CE  	1996	6	27	96ZZZX3213       	1	19960603	G	2910	128050981	LINE            			CESSNA	210   	T210M       	2073451	CE  										MLG	RUPTURED        	E	L			L	O			ABORTED APPROACH        	OTHER                   			K	P		FLUID LOSS                	NO WARNING INDICATION     		AP	APPROACH       	1			GL	03	7398M	9000 				G2018				SUBJECT HYDRAULIC LINE FAILED IN SERVICE CAUSING HYDRAULIC FLUID LEAK.  LANDING GEAR COULD NOT BE HAND PUMPED DOWN.  SUB	MITTER RECOMMENDS CLOSE INSPECTION OF ALL HYDRAULIC LINES DURING ROUTINE INSPECTIONS.					1	H	7	1 	3O				3A21    					 
1996062700661	19960627	00661	CE  	1996	6	27	96ZZZX3214       	1	19960612	G	2710		CONTROL CABLE   			CESSNA	188   	A188B       	2073005	CE  										AILERON	DEFECTIVE       	B	P	A	FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05		474  								DURING ANNUAL INSPECTION, SERVICE BULLETINS WERE BEING REVIEWED.  DURING REVIEW OF THESE BULLETINS, THERE WERE NUMEROUS 	REFERENCES TO PROBLEMS WITH PULLEYS AND CABLES IN THE AILERON SYSTEM.  UPON INSPECTION OF THE AILERON CABLES, THERE WAS 	A CABLE FOUND TO BE AT LEAST 60 PERCENT COMPROMISED.  THE SB RECOMMENDS REPLACEMENT OF THE CABLES ON OR BEFORE 500 HOURS	.  SUBMITTER STATED AFTER SEEING THE CONDITION OF THIS COMPROMISED CABLE, IT MIGHT BE WORTH REVIEWING THE RECOMMENDED TI	ME CHANGE AND LOWERING THE HOURS.		1	L	7	1 	3O			 	A9CE    					 
1996062700662	19960627	00662	SO  	1996	6	27	96ZZZX3215       	1	19960508	G	5730	6206102	SKIN            			PIPER 	PA28  	PA28151     	7102805	SO  										WING WALK	CRACKED         	B	S		RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	1195X	9135 				287515324				DURING NORMAL INSPECTION, CRACKS WERE FOUND IN STIFFENER CORRIGATION ENDS IN DOUBLER SKIN UNDER WING WALK.  WING WALK WA	S SOFT (SPRUNG DOWN) WHEN IT WAS STEPPED ON.  THIS AIRCRAFT HAS INSPECTION HOLES BELOW AND OUTBOARD OF CRACKED PARTS.  H	OWEVER, MOST OF THE CRACKS WERE INBOARD OF A WING RIB INBOARD OF THESE INSPECTION HOLES.  WING WAS REMOVED, PARTS REPLAC	ED, AND AIRCRAFT RETURNED TO SERVICE.			1	L	7	1 	3O				2A13    					 
1996062700663	19960627	00663	SO  	1996	6	27	96ZZZX3216       	1	19960508	G	5730	6206104	SKIN            			PIPER 	PA28  	PA28151     	7102805	SO  										WING WALK	CRACKED         	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	1195X	9135 				287515324				DURING NORMAL INSPECTION, CRACKS WERE FOUND IN STIFFENER CORRIGATION ENDS IN DOUBLER SKIN UNDER WING WALK.  WING WALK WA	S SOFT (SPRUNG DOWN) WHEN IT WAS STEPPED ON.  THIS AIRCRAFT HAS INSPECTION HOLES BELOW AND OUTBOARD OF CRACKED PARTS.  H	OWEVER, MOST OF THE CRACKS WERE INBOARD OF A WING RIB INBOARD OF THESE INSPECTION HOLES.  WING WAS REMOVED, PARTS REPLAC	ED, AND AIRCRAFT RETURNED TO SERVICE.			1	L	7	1 	3O				2A13    					 
1996062700664	19960627	00664	CE  	1996	6	27	96ZZZX3217       	1	19960604	G	7603	63255534	LEVER           			CESSNA	185   	A185F       	2072821	CE  										THROTTLE CABLE	WORN            	D		A		A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AL	03	124KT	381  				18503765				'AN' BOLT/CASTLE NUT RETAINING HARDWARE FOR THROTTLE CABLE ROD END TO LEVER, LOOSENED AND WORE ITSELF THROUGH LEVER.  FA	ILURE OCCURRED AT LIFT-OFF, SUCCESSFUL ON-FIELD LANDING WAS MADE.  ASSY WAS 85 HOURS OUT OF 100 HOUR INSPECTION.  SUBMIT	TER SUGGESTS IMPROVING LEVER BY MANUFACTURING OUT OF STEEL INSTEAD OF BRASS WOULD HELP.				1	H	7	1 	3O				3A24    					 
1996062700665	19960627	00665	SO  	1996	6	27	96ZZZX3218       	1	19960606	G	2731	4173436	CONTROL CABLE   			PIPER 	PA31T 	PA31T1      	7103126	SO  										ELEVATOR TRIM	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	633AB	4509 				31T8104021				ELEVATOR TRIM CABLE FRAYED AND BROKEN STRANDS AROUND THE TRIM DRUM - NOT VISIBLE TO INSPECTION UNLESS REMOVED FROM THE T	RIM DRUM.  SUBMITTER RECOMMENDS REMOVAL AND INSPECT EVERY 2,000 HOURS OR FIVE YEARS.					1	L	7	2 	3T			 	A8EA    					 
1996062700666	19960627	00666	CE  	1996	6	27	96ZZZX3219       	1	19960525	G	7160	BA5110	FILTER ASSY     	BRACKETT    		CESSNA	172   	172M        	2072418	CE  										CARBURETOR AIR	DEFECTIVE       	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	20582					17261414				IN C/W AD 96-09-06 TO REPLACE BRACKETT FILTER ASSY, NEW OUT-OF-BOX INSPECTION FOUND GLUE USED FOR GASKET ON BACK SIDE OF	 MESH SCREEN.  REMOVED DRIED GLUE MATERIAL AND INSTALLED.  SUBMITTER STATED THIS I.A. HAS FOUND NEW PARTS INFERIOR IN QU	ALITY CONTROL.  JUST BECAUSE ITS NEW DOESN'T MEAN IT'S RIGHT.  INSPECT IN DETAIL ANY NEW PART TO BE INSTALLED ON AIRCRAF	T.  MAKE USE OF M OR D'S IF A PART ISN'T RIGHT.  ONLY THEN, CAN THE FAA DO THEIR JOB.			1	H	7	1 	3O			NT	3A12    					 
1996062700667	19960627	00667	CE  	1996	6	27	96ZZZX3220       	1	19960618	G	2810		FUEL CAP        			CESSNA	185   	A185F       	2072821	CE  										WING TANK	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	9463N					18504361				DESIGN OF THESE FUEL CAPS ALLOWS WATER TO COLLECT IN FILL AREA AFTER RAINS.  NEXT REMOVAL OF CAP ALLOWS WATER TO ENTER F	UEL TANK.					1	H	7	1 	3O				3A24    					 
1996062700668	19960627	00668	CE  	1996	6	27	96ZZZX3221       	1	19960603	G	7160	05521644	AIR BOX         			CESSNA	172   	172P        	2072436	CE  										CARBURETOR	RIVETS LOOSE    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	62274	4228 				17275240				WHILE DOING AN ANNUAL INSPECTION ON AIRCRAFT ENGINE, MECHANIC NOTICED 2 LOOSE RIVETS HOLDING AIR BOX TOGETHER.  REMOVED 	AIR BOX TO REPAIR AND NOTICED THAT CARBURETOR HEAT FLAPPER WAS HELD BY ONLY ONE RIVET.  SUSPECT CAUSE AS IMPROPER RIGGIN	G OF CARBURETOR HEAT CONTROL CABLE.  SUBMITTER ALSO FINDS THAT IF BOX WAS NOT REMOVED FOR REPAIR, THE FLAPPER DAMAGE MIG	HT HAVE GONE UNNOTICED.			1	H	7	1 	3O			NT	3A12    					 
1996062700669	19960627	00669	SO  	1996	6	27	96ZZZX3222       	1	19960528	G	3230	4198301	HOOK ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  										RT DOWNLOCK	REQUIRED LUBE   	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NE	03	27475	4352 				317852021				MAIN LANDING GEAR WOULD NOT LOCK IN THE DOWN POSITION.  AFTER AN UNEVENTFUL LANDING, AIRCRAFT WAS PLACED ON JACKS AND TH	E DOWNLOCKS WERE FOUND WITHOUT LUBRICATION AND STUCK IN THE UNLOCKED POSITION.  IT WAS FOUND THE OPERATOR REQUIRES THE L	ANDING GEAR TO BE CLEANED WEEKLY; THUS, REMOVING ALL LUBRICANT.  IT IS RECOMMENDED THAT ALL LANDING GEAR PIVOT POINTS BE	 PROPERLY LUBED AFTER EACH CLEANING.			1	L	7	2 	3O				A20SO   					 
1996062700670	19960627	00670	SO  	1996	6	27	96ZZZX3223       	1	19960528	G	3230	4198300	HOOK ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  										LT DOWNLOCK	REQUIRED LUBE   	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NE	03	27475	4352 				317852021				MAIN LANDING GEAR WOULD NOT LOCK IN THE DOWN POSITION.  AFTER AN UNEVENTFUL LANDING, AIRCRAFT WAS PLACED ON JACKS AND TH	E DOWNLOCKS WERE FOUND WITHOUT LUBRICATION AND STUCK IN THE UNLOCKED POSITION.  IT WAS FOUND THE OPERATOR REQUIRES THE L	ANDING GEAR TO BE CLEANED WEEKLY; THUS, REMOVING ALL LUBRICANT.  IT IS RECOMMENDED THAT ALL LANDING GEAR PIVOT POINTS BE	 PROPERLY LUBED AFTER EACH CLEANING.			1	L	7	2 	3O				A20SO   					 
1996062700671	19960627	00671	CE  	1996	6	27	96ZZZX3224       	1	19960529	G	3260	63210075	SWITCH          			CESSNA	414   	414A        	2075907	CE  										NLG UPLOCK	WIRE BURNED     	B			MGOR	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CE	09	575JB	3538 				414A0426				PILOT REPORTED ALL MLG GREEN LIGHTS ILLUMINATED AND GEAR UNSAFE LIGHT ILLUMINATED IN-FLIGHT.  EMERGENCY EXTENSION PERFOR	MED, NO CHANGE IN INDICATOR STATUS.  AIRCRAFT LANDED WITHOUT INCIDENT.  TROUBLESHOOTING REVEALED HIGH RESISTANCE IN THE 	NLG UPLOCK CIRCUITRY.  FURTHER INVESTIGATION FOUND SEVERAL BURNED WIRES IIN THE HEATER BAY.  WIRE REPAIRED, GEAR OPERATO	NAL CHECK SATISFACTORY.			1	L	7	2 	3O				A7CE    					 
1996062700672	19960627	00672	CE  	1996	6	27	96ZZZX3225       	1	19960501	G	3230	MS244614	BEARING         		08421211    	CESSNA	310   	T310R       	2074246	CE  										NLG RODS	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	6126C	3811 				310R1293				WHILE INSPECTING NOSE LANDING GEAR RODS AND ATTACHMENTS, FOUND NEEDLE BEARINGS SHOWING AND ROD END SITTING HIGHER THAN N	ORMAL IN THE IDLER BELLCRANK.  REMOVED BOLT RETAINING THE PUSH/PULL ROD AND FOUND BEARING RETAINER SHEARED ON THE UPPER 	SECTION OF BEARING.				1	L	7	2 	3O				3A10    					 
1996062700673	19960627	00673	EA  	1996	6	27	96ZZZX3226       	1	19960611	G	5510		FLANGE          			DHAV  	DHC3  	DHC3        	2800202	EA  										RIB ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	84SF	6001 				284				THE TAILPLANE STRUCTURE MAIN RIB FORWARD FLANGES AT THE TAILPLANE LOWER RIB ATTACHMENT FITTING FOUND CRACKED.  THE CRACK	ING IS FATIGUE RELATED.  SUBMITTER STATED TO CORRECT PROBLEM, INSTALL MOD. 3/935 IAW DHC-3 SB 3/50.  NOTE:  THE DYE PENE	TRANT METHOD PER SB 3/46 WOULD NOT DETECT CRACKING ON MAIN RIB DUE TO BEARING PLATES COVERING CRACKS.				1	H	7	1 	3R				A815    					 
1996062700674	19960627	00674	CE  	1996	6	27	96ZZZX3227       	1	19960606	G	5210	99120754	SEAL            		551123079   	CESSNA	500   	560CESSNA   	2076750	CE  										CABIN ENTRY	FAILED          	D				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			SW	05	898CB	2114 				5600097				PRESSURIZED ENTRY DOOR SEAL FAILED AT CRUISE ALTITUDE.  AIRCRAFT DESCENDED TO 22,000 FEET WHERE THE SECONDARY SEAL FAILE	D.  AFTER LANDING, WATER WAS DRAINED FROM SEAL CHECK VALVE DRAIN.  BOTH SEALS AND AIR LINE GROMMET WERE FOUND WORN AND C	RACKED.  INSTALLED NEW SEALS AND GROMMET.  RE-RIGGED DOOR TO ALLOW BETTER FIT OF SECONDARY SEAL.  OPS CHECKS WITH GROUND	 PRESSURIZATION CART WERE NORMAL.  SUSPECT CAUSE:  WORN PARTS AND MIS-RIGGED DOOR ALLOWED WATER TO ENTER AND FREEZE IN P	RESSURE SEAL; AND, MIS-RIGGED DOOR CAUSED SECONDARY SEAL TO FAIL.  SUBMITTER RECOMMENDS CLOSER ATTENTION TO MAINTENANCE 	AND INSPECTION REQUIREMENTS; AND, TROUBLESHOOTING TECHNIQUES.	2	L	7	2 	4F			RT	A22CE   					 
1996062700675	19960627	00675	SO  	1996	6	27	96ZZZX3228       	1	19960530	G	3230	491949	SHUTTLE VALVE   			PIPER 	PA42  	PA42720     	7104212	SO  										NLG ACTUATOR	CRACKED         	B			SO5R	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	03	775CA	4000 			281	425501004				NOSE GEAR SHUTTLE VALVE FITTING CRACKED (FRACTURED) CAUSING A HYDRAULIC LEAK.  THE FITTING IN QUESTION SCREWS INTO THE N	OSE GEAR ACTUATOR, PN 40874-5, PIPER SB 859 DATED, HAD BEEN COMPLETED.  SB 859 CALLS FOR THE INSTALLATION OF A SUPPORT B	RACKET.  SHUTTLE VALVE, PIPER PN 491-949, WAS REPLACED WITH NEW PART.  SUBMITTER STATED THE DEFECTIVE PART MAY HAVE BEEN	 DAMAGED BEFORE THE SB WAS C/W AND WAS UNDECTABLE.			1	L	7	2 	4T				A23SO   					 
1996062700676	19960627	00676	SO  	1996	6	27	96ZZZX3229       	1	19960422	G	2430	BD63	CONNECTOR       	ELCON       		GULSTM	G1159 	G1159       	3953505	SO  										NR 2 BATTERY	LOOSE           	D				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			EA	23	565KC					046				ON TAXI FOR DEPARTURE, THE NR 2 ELECTRICAL SYSTEM WENT TO ZERO VOLTS.  UPON INVESTIGATION, FOUND NR 2 BATTERY CONNECTOR 	SOCKETS LOOSE ACCORDING TO BATTERY TERMINAL GO-NO GO GAUGE.  SUBMITTER SUGGESTS THAT ELCON TYPE CONNECTORS BE CHECKED PE	RIODICALLY WITH TELEDYNE BATTERY GAUGE, PN TBP2132 OR EQUIVALENT.				2	L	7	2 	4F			RT	A12EA   					 
1996062700677	19960627	00677	SW  	1996	6	27	96ZZZX3230       	1	19960606	G	2432	SP900	BATTERY         	MARATHON    		SWRNGN	SA226 	SA226TC     	8780404	SW  										NR 2-3 CELLS	OVERHEAT        	B			QTVR	O				OTHER                   				J	M		WARNING INDICATION        	OVER TEMP                 		NR	NOT REPORTED   	1			NM	11	341PL		100  		9105060	TC334				BATTERY HOT LIGHT CAME ON DURING TRAINING FLIGHT.  REMOVED BATTERY, FOUND 2 CELLS WENT THERMAL.  INSTALLED SERVICEABLE B	ATTERY.  OPS CHECK GOOD.					2	L	7	2 	4T			RT	A8SW    					 
1996062700678	19960627	00678	CE  	1996	6	27	96ZZZX3231       	1	19960529	G	3230	MS287784	O-RING          		66003616    	LEAR  	24    	24B         	5170306	CE  										MLG VALVE	WORN            	C				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			AL	03	335JW					226				O-RING IN MAIN GEAR CONTROL VALVE FAILED CAUSING LOSS OF HYDRAULIC FLUID.  FLIGHT CREW BLEW GEAR DOWN.  NO DAMAGE TO AIR	CRAFT OCCURRED.  SUBMITTER STATED O-RING WILL BE INSPECTED MORE FREQUENTLY.					2	L	7	2 	4J				A10CE   					 
1996062700679	19960627	00679	NM  	1996	6	27	96ZZZX3232       	1	19960501	G	5753		CARRIAGE        			BOEING	747   	747273C     	1384896	NM  										RT INBD FOREFLAP	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	471EV					20651				FLAP SEQUENCE CARRIAGE FOUND SHEARED DURING INSPECTION.  DAMAGE APPEARS TO HAVE HAPPENED A CONSIDERABLE TIME EARLIER.						2	L	7	4 	4F				A20WE   					 
1996062700680	19960627	00680	CE  	1996	6	27	96ZZZX3233       	1	19960608	G	3230	1228200321	UPLOCK HOOK     		1228200223  	BEECH 	2000  	2000        	1152000	CE  										NLG	CRACKED         	B	S		PAIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	8025L	1027 				NC19				A BULGE WAS FOUND WHERE THE UPLOCK ROLLER STRIKES THE UPLOCK HOOK.  THE HOOK HAD STARTED CRACKING AT THE BULGE.  REPLACE	D UPLOCK HOOK.					1	L	7	2 	4T			RT	A38ACE  					 
1996062700681	19960627	00681	EU  	1996	6	27	96ZZZX3234       	1	19960509	G	2730	P310450002	GUST DAMPER     			BAG   	BAE146	BAE146200A  	1500266	EU  										RT/LT ELEVATOR	FAILED          	B		A	NO1Y	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			EA	35	173US				E48	E2031				ON ARRIVAL, ELEVATORS COULD MOVE UNDAMPED FROM STOP-TO-STOP.  ON INVESTIGATION, THE HYDRAULIC GUST DAMPERS WERE FOUND FU	LLY DISCHARGED AND INEFFECTIVE.  THE RIGHT ELEVATOR NR 1 HINGE BRACKET ASSY WAS FRACTURED, REF IPC 55-50-01-05.  THE RIG	HT ELEVATOR FDR POSITION TRANSMITTER ROD WAS BROKEN AND SOME DAMAGE TO THE SKIN HAD OCCURRED DUE TO OVER-TRAVEL.  INVEST	IGATION CONTINUES.  ON RECOVERY FROM STORAGE, ELEVATOR GUST DAMPERS SHOULD BE CHECKED FOR CHARGE AND LEAKAGE PRIOR TO FE	RRY FLIGHT (S/N E48).		2	H	7	4 	4F			RT	A49EU   					 
1996062700682	19960627	00682	EU  	1996	6	27	96ZZZX3235       	1	19960509	G	2730	P310450002	GUST DAMPER     			BAG   	BAE146	BAE146200A  	1500266	EU  										RT/LT ELEVATOR	FAILED          	B		A	NO1Y	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			EA	35	173US				E73	E2031				ON ARRIVAL, ELEVATORS COULD MOVE UNDAMPED FROM STOP-TO-STOP.  ON INVESTIGATION, THE HYDRAULIC GUST DAMPERS WERE FOUND FU	LLY DISCHARGED AND INEFFECTIVE.  THE RIGHT ELEVATOR NR 1 HINGE BRACKET ASSY WAS FRACTURED, REF IPC 55-50-01-05.  THE RIG	HT ELEVATOR FDR POSITION TRANSMITTER ROD WAS BROKEN AND SOME DAMAGE TO THE SKIN HAD OCCURRED DUE TO OVER-TRAVEL.  INVEST	IGATION CONTINUES.  ON RECOVERY FROM STORAGE, ELEVATOR GUST DAMPERS SHOULD BE CHECKED FOR CHARGE AND LEAKAGE PRIOR TO FE	RRY FLIGHT (S/N E73).		2	H	7	4 	4F			RT	A49EU   					 
1996062700683	19960627	00683	WP  	1996	6	27	96ZZZX3236       	1	19960607	G	6320	369D2512111	PINION SHAFT    		369D28100507	HUGHES	369   	369E        	4470707	WP  										M/R GEARBOX	WORN            	B		A	WG3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	220PD	1353 			6655701000	509E				OIL COOLER DRIVE BELT PULLEY HAD WORN THE SPLINES TO BELOW THE 'OVER-PIN' LIMITS.  THE PULLEY WAS SEIZED ON THE PINION S	HAFT.					1	G	7	1 	3U				H3WE    					 
1996062700684	19960627	00684	WP  	1996	6	27	96ZZZX3237       	1	19960430	G	6220	5143711	HUB             		5143915     	HILLER	UH12  	UH12D       	4360118	WP  										M/R	CRACKED         	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	58BA	2279 	586  		2918B	969				WHILE C/W AD 73-20-03 10/30/73, DYE PEN AND VISUAL INSPECTION OF M/R HUB, A CRACK WAS FOUND ABOUT .75 INCHES LONG.  M/R 	HUB WAS REMOVED AND SCRAPPED AND A SERVICEABLE ZERO TSO M/R HEAD ASSY WAS INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE	.				1	G	7	1 	3O				4H10    					 
1996062700686	19960627	00686		1996	6	27	96ZZZX3239       	4	19960520	G	2562	EB2BCD	ELT             			BELL  	206   	206B        	1181511	SW  										COCKPIT	MALFUNCTION     	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	4TD	9431 			35485	3431				ELT WENT OFF WHILE AIRCRAFT WAS IN HANGAR.  ELT BATTERY WAS REMOVED TO TURN OFF UNIT.  WHEN BATTERY WAS REINSTALLED, THE	 UNIT WENT OFF AGAIN.  ELT WAS REPLACED WITH NEW INSTALLATION AND THIS ONE RETURNED TO MANUFACTURER FOR INSPECTION AND R	EPAIR.				1	G	7	1 	3U				H2SW    					 
1996062700687	19960627	00687	SW  	1996	6	27	96ZZZX3240       	1	19960529	G	7714	2060626273	GENERATOR       	GLOBE       		BELL  	206   	206B        	1181511	SW  										GAS PROD TACH	FAILED          	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CE	09	2778R	2646 				2803				PART FAILED AT CRUISE POWER.  ENGINE OUT LIGHT ILLUMINATED WITH AUDIO IN HEADSET.  RECOMMEND A TIME REPLACEMENT CRITERIA	 BE ESTABLISHED.					1	G	7	1 	3U				H2SW    					 
1996062700688	19960627	00688	EU  	1996	6	27	96ZZZX3241       	1	19960531	G	7120	SD3510005E	SUPPORT TUBE    			STBROS	SD3   	SD360       	8100606	EU  										ENG LT OTBD	CORRODED        	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	631KC					SH3407				DURING A MAJOR MODIFICATION OF AIRCRAFT, FOUND CORROSION INSIDE LEFT LOWER OUTBOARD ENGINE SUPPORT TUBE WHERE TUBE JOINS	 FOOT MOUNT.  CORROSION IS PITTED AREA ONE INCH BY ONE INCH.  CORROSION MAY BE FROM WATER.					2	H	7	2 	4T				A41EU   					 
1996062700689	19960627	00689	GL  	1996	6	27	96ZZZX3242       	1	19960501	G	2730	283M	SLEEVE          			AMTR  	CH600 	CH600       	05623RC	GL  										ELEVATOR CABLE	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CE	05	596WC					6964				A-28-3M NICOPRESS SLEEVE WAS IMPROPERLY INSTALLED CAUSING CABLE TO RETRACT LEAVING ELEVATOR WITHOUT ANY CONTROL.  THIS E	ND OF CABLE IS NEXT TO CONTROL STICK.  SUBMITTER RECOMMENDS ALL CABLE CONNECTIONS BE INSTALLED WITH TWO SLEEVES ON CONVE	NTIONAL AIRCRAFT AS A SAFETY FACTOR.  ALL CH-600 AND CH-601 ZODIAC AIRCRAFT.				1	L	7	1 	30			NT	EXPA1L71					 
1996070300069	19960703	00069	EU  	1996	7	3	96ZZZX3244       	1	19960422	G	7714	1179405303	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										TRIPLE TACH	STICKING        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117LU	67   			282	7144				TRIPLE TACHOMETER NR 2 NEEDLE STICKING.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996070300070	19960703	00070	EU  	1996	7	3	96ZZZX3245       	1	19960510	G	3150	1179405211	PANEL           			BOLKMS	117   	BK117A3     	5626015	EU  										ANNUNCIATOR	SEGMENTS BROKEN 	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117UC				0021	7098				SEVERAL SEGMENTS BROKEN ON ANNUNCIATOR PANEL.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996070300071	19960703	00071	EU  	1996	7	3	96ZZZX3246       	1	19960519	G	3310	11792039	POWER SUPPLY    			BOLKMS	117   	BK117B1     	5626012	EU  										LIGHT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117VU	19   			1168	7211				LIGHTS WEAK.  BATTERY WILL NOT CHARGE.  SPARKS OCCUR WHEN UNIT IS TOUCHED TO A/C AND HOOKED UP.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996070300072	19960703	00072	EU  	1996	7	3	96ZZZX3247       	1	19960416	G	7714	1179405303	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										TRIPLE TACH	NEEDLE STICKS   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1140H	22   			426	7078				NR NEEDLE STICKING WHEN STARTING ENGINES, 21.8 HOURS SINCE REPAIR.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996070300073	19960703	00073	EU  	1996	7	3	96ZZZX3248       	1	19960404	G	7714	1179405303	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										TRIPLE TACH	READS HIGH      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1140H				524	7078				NR TACHOMETER NEEDLE READING 15 PERCENT HIGH.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996070300074	19960703	00074	EU  	1996	7	3	96ZZZX3250       	1	19960419	G	7931	53408A	TRANSMITTER     			AEROSP	SA365 	SA365N1     	8680668	EU  										ENG OIL PRESS	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	365SC				1035	6298				OUT OF CALIBRATION.  AT FLIGHT IDLE (70 PERCENT NG), OIL PRESSURE INDICATING AT BOTTOM RED LINE.  SWAPPED ENGINES, SAME 	RESULTS.					1	G	7	2 	3U				H10EU   					 
1996070300075	19960703	00075	NE  	1996	7	3	96ZZZX3251       	1	19960328	G	6420	7610305015104	RETAIN WASHER   			SKRSKY	S76   	S76         	8143010	NE  										T/R	LOOSE           	B		A	AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T					760140				TAIL ROTOR PITCH BEAM WAS FOUND LOOSE ON PITCH SHAFT WITH .1250 INCH GAP BETWEEN WASHER-RETAINER AND NUT.  INSPECTION RE	VEALED PITCH BEAM NUT WAS BOTTOMING OUT ON PITCH SHAFT, PREVENTING PITCH BEAM AND WASHER FROM SEATING.  THE PITCH SHAFT 	HAD 80 HOURS SINCE INSTALLATION WITH TAIL GEARBOX.  (NUT WAS PROPERLY TORQUED).  REPLACED PITCH SHAFT ASSY, PITCH BEAM A	ND WASHER-RETAINER.			1	G	7	2 	3U				H1NE    					 
1996070300076	19960703	00076	NE  	1996	7	3	96ZZZX3252       	1	19960328	G	6420	7635805121042	PITCH SHAFT     			SKRSKY	S76   	S76         	8143010	NE  										T/R	LOOSE           	B		A	AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T	80   			C06400165	760140				TAIL ROTOR PITCH BEAM WAS FOUND LOOSE ON PITCH SHAFT WITH .1250 INCH GAP BETWEEN WASHER AND NUT.  INSPECTION REVEALED PI	TCH BEAM NUT WAS BOTTOMING OUT ON PITCH SHAFT, PREVENTING PITCH BEAM AND WASHER-RETAINER FROM SEATING.  THE PITCH SHAFT 	HAD 80 HOURS SINCE INSTALLATION WITH TAIL ROTOR.  GEARBOX, PITCH SHAFT, PITCH BEAM, AND WASHER-RETAINER ARE WORN (NUT WA	S PROPERLY TORQUED).  REPLACED PITCH SHAFT ASSY, PITCH BEAM, AND WASHER-RETAINER.			1	G	7	2 	3U				H1NE    					 
1996070300077	19960703	00077	NE  	1996	7	3	96ZZZX3253       	1	19960328	G	6420	7610305001101	PITCH BEAM      			SKRSKY	S76   	S76         	8143010	NE  										T/R	LOOSE           	B		A	AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T				D05700129	760140				TAIL ROTOR PITCH BEAM WAS FOUND LOOSE ON PITCH SHAFT, WITH .1250 INCH GAP BETWEEN WASHER-RETAINER AND NUT.  INSPECTION R	EVEALED PITCH BEAM NUT WAS BOTTOMING OUT ON PITCH SHAFT, PREVENTING PITCH BEAM AND WASHER FROM SEATING.  THE PITCH SHAFT	 HAD 80 HOURS SINCE INSTALLATION WITH TAIL GEARBOX (NUT WAS PROPERLY TORQUED).  REPLACED PITCH SHAFT ASSY, PITCH BEAM, A	ND WASHER-RETAINER.			1	G	7	2 	3U				H1NE    					 
1996070300078	19960703	00078	SW  	1996	7	3	96ZZZX3254       	1	19960511	G	6330	2060333506101	RESTRAINT       			BELL  	206   	206L1       	1182107	SW  										M/R XMSN	BEARING WORN    	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2618	586  			LK2694	45503				RESTRAINT SPRING BEARINGS 2 EACH WORN BEYOND LIMITS.  REPLACED BEARINGS, PN 206-033-509-003.						1	G	7	1 	3U				H2SW    					 
1996070300079	19960703	00079	EU  	1996	7	3	96ZZZX3255       	1	19960210	G	2436	51530001EI	REGULATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										DC GENERATOR	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1068 			14031	7505				GENERATOR WILL NOT COME ON LINE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996070300080	19960703	00080		1996	7	3	96ZZZX3256       	4	19960429	G	3416	B4553110004	ALTIMETER       			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	FAULTY          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				4877	7505				ADJUSTMENT KNOB DIFFICULT TO TURN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996070300081	19960703	00081	EU  	1996	7	3	96ZZZX3257       	1	19960425	G	5210	1172428403	STOP            			BOLKMS	BK117 	BK117C1     	5626025	EU  										DOOR	BROKE           	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				DOOR STOP BROKE OFF REAR PART OF STOP.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996070300082	19960703	00082	EU  	1996	7	3	96ZZZX3258       	1	19960315	G	3340	A490ATSCF	POWER SUPPLY    			BOLKMS	105   	BO105S      	5626006	EU  										ANTI COLLISION	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LF				03157	S663				UPPER ANTI-COLLISION LIGHT INOPERATIVE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H3EU    					 
1996070300083	19960703	00083	SW  	1996	7	3	96ZZZX3259       	1	19960512	G	6330	222031605109	FLEXTURE        			BELL  	222   	222         	1182122	SW  										M/R XMSN	DEBONDED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW				LK0077	47520				BOTH UNITS DEBONDED AT END FITTING.						1	G	7	2 	3U				H9SW    					 
1996070300084	19960703	00084	SW  	1996	7	3	96ZZZX3260       	1	19960512	G	6330	222031605109	FLEXTURE        			BELL  	222   	222         	1182122	SW  										M/R XMSN	DEBONDED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW				LK0063	47520				BOTH UNITS DEBONDED AT END FITTING.						1	G	7	2 	3U				H9SW    					 
1996070300085	19960703	00085	SW  	1996	7	3	96ZZZX3261       	1	19960512	G	6330	222031605109	FLEXTURE        			BELL  	222   	222         	1182122	SW  										M/R XMSN	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW	5    			LK0126	47520				AS FLEXTURE ASSY MOVES AT END FITTING, ONE FITTING DOES NOT HAVE PROPER CLEARANCE CAUSING A LOUD 'POP' TO BE HEARD AND F	ELT THROUGHOUT THE AIRFRAME.					1	G	7	2 	3U				H9SW    					 
1996070300390	19960703	00390	SO  	1996	7	3	96ZZZX3319       	2	19960618	G	8530	653452A9	CYLINDER        			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					NR 2	HEAD CRACKED    	B	S		APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	48SA	163  				4040417	276408R			FOUND NR 2 CYLINDER HEAD CRACKED AT LOWER SPARK PLUG HOLE.						1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996070300391	19960703	00391	CE  	1996	7	3	96ZZZX3320       	1	19960606	G	3252	22430151	ATTACH CLAMP    		2243001203  	CESSNA	182   	TR182       	2072735	CE  										SHIMMY DAMPENER	FAILED          	D		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	4594S	2742 				R18201351				THE SHIMMY DAMPENER CLAMP ASSY, PN 2243015-1, ALIGNMENT PIN FAILED AND CAUSED THE SHIMMY DAMPENER TO ROTATE ON THE STRUT	 HOUSING AND IMPROPERLY ALIGN THE DAMPENER CAUSING THE DAMPENER TO JAM THE LANDING GEAR IN THE UP POSITION.  NOTE:  THE 	DAMPENER CLAMP LOOKS TO HAVE BEEN REPAIRED AT ONE TIME.				1	H	7	1 	3O				3A13    					 
1996070300392	19960703	00392	EA  	1996	7	3	96ZZZX3321       	2	19960503	G	8550		FITTING         			GULSTM	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					ACCESSORY CASE	FAILED          	D		A		K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	15	28462	125  				AA5B0626	L2208436A			OIL PRESSURE FITTING AT ENGINE TO GAUGE HAD BRASS FITTING AND THEN 90 DEGREE RESTRICTIVE FITTING.  APPEARS TO HAVE BEEN 	TOO CLOSE TO MOUNT.  BRASS FITTING BROKE FLUSH AT ACCESSORY CASE AND OIL PUMPED OUT OF ENGINE.  BRASS FITTING APPEARED T	O BE INCORRECT PART NUMBER.				1	L	7	1 	3O	3	O		A16EA   	E286				 
1996070300393	19960703	00393	CE  	1996	7	3	96ZZZX3322       	1	19960601	G	3260	608100832	SUPPORT ASSY    			BEECH 	58    	58TC        	1152746	CE  										RT MLG	WORN            	B	L	A	GOGR	O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SW	11	60234	2649 				TK92				MLG MALFUNCTIONED, ACFT EXAMINED AND FND FOLLOWING PARTS DAMAGED:  RT RETRACT ROD (35-81512547), RT INBD GEAR DOOR (35-8	150055-169), RT BRAKE ASSY (03014500) FLAP SHAFT (3X5K8720A63-5/16), AND FLAP ACT WIRES.  RT WING, STEP, AILERON, PROP, 	AND ENG SUSTAINED DAMAGES.  DAMAGED PARTS REPLACED.  LANDING GEAR TESTED MANUALLY TO INVESTIGATE RIGGING OF SYS AND ELEC	 OPERATED 20 TIMES WHEN SYS AGAIN FAILED TO EXTEND BENDING RT RETRACT ROD (35-815125-47) AND PUSHING IT INTO REAR SPAR W	EB OF FWD CABIN WING CARRY-THRU SPAR IN CENTER WING SECT DAMAGING SPAR WEB.  FND RT GEAR (60-810028-17) HAD HUNG ON A NU	T WHICH SECURES UPLOCK STOP (60-810092-14) WHICH IS ATTACHED TO DOWNLOCK SUPPORT ASSY (60-810083-2).	1	L	7	2 	3O				A23CE   					 
1996070300394	19960703	00394	EA  	1996	7	3	96ZZZX3323       	2	19960618	G	8530	LW12993	CYLINDER        			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ROCKER BOX DRAIN	CRACKED         	D	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	201RP				A319521	240215	L1725451AC			FOUR NEW LW-12993 CYLINDERS HAVE CRACKS AT THE ROCKER BOX DRAIN FITTING BOSS.  THESE CRACKS OCCUR AT A CASTING FLAW.  TH	IS MAY BE CAUSED BY THE TAPERED THREAD OF THE MS-20823-6D ELBOW FITTING.					1	L	7	1 	3O	3	O		2A3     	1E10				 
1996070300395	19960703	00395	EA  	1996	7	3	96ZZZX3324       	2	19960618	G	8530	LW12993	CYLINDER        			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ROCKER BOX DRAIN	CRACKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	201RP				A300517	240215	L1725451AC			FOUR NEW LW-12993 CYLINDERS HAVE CRACKS AT THE ROCKER BOX DRAIN FITTING BOSS.  THESE CRACKS OCCUR AT A CASTING FLAW.  TH	IS MAY BE CAUSED BY THE TAPERED THREAD OF THE MS-20823-6D ELBOW FITTING.					1	L	7	1 	3O	3	O		2A3     	1E10				 
1996070300396	19960703	00396	EA  	1996	7	3	96ZZZX3325       	2	19960618	G	8530	LW12993	CYLINDER        			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ROCKER BOX DRAIN	CRACKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	201RP				A340519	240215	L1725451AC			FOUR NEW LW-12993 CYLINDERS HAVE CRACKS AT THE ROCKER BOX DRAIN FITTING BOSS.  THESE CRACKS OCCUR AT A CASTING FLAW.  TH	IS MAY BE CAUSED BY THE TAPERED THREAD OF THE MS-20823-6D ELBOW FITTING.					1	L	7	1 	3O	3	O		2A3     	1E10				 
1996070300397	19960703	00397	EA  	1996	7	3	96ZZZX3326       	2	19960618	G	8530	LW12993	CYLINDER        			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ROCKER BOX DRAIN	CRACKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	201RP				A167521	240215	L1725451AC			FOUR NEW LW-12993 CYLINDERS HAVE CRACKS AT THE ROCKER BOX DRAIN FITTING BOSS.  THESE CRACKS OCCUR AT A CASTING FLAW.  TH	IS MAY BE CAUSED BY THE TAPERED THREAD OF THE MS-20823-6D ELBOW FITTING.					1	L	7	1 	3O	3	O		2A3     	1E10				 
1996070300398	19960703	00398	CE  	1996	7	3	96ZZZX3327       	1	19960603	G	2910	128050981	LINE            			CESSNA	210   	T210M       	2073451	CE  										HYDRAULIC SYS	RUPTURED        	E				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			GL	03	7398M	9000 				21062018				HYDRAULIC LINE FAILED IN SERVICE CAUSING HYDRAULIC FLUID LEAK.  LANDING GEAR COULD NOT BE HAND PUMPED DOWN.  SUBMITTER R	ECOMMENDS CLOSE INSPECTION OF ALL HYDRAULIC LINES DURING ROUTINE INSPECTIONS.					1	H	7	1 	3O				3A21    					 
1996070300400	19960703	00400	SO  	1996	7	3	96ZZZX3329       	1	19960601	G	5500		TUBE            			PIPER 	PA22  	PA22150     	7102210	SO  										TAIL POST	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	7257D					225084				CONVERTED FROM TRI-PACER TO PACER CONFIG BY STC 5A45RM, TIME AS PACER, APPROXIMATELY 1,220 HRS.  TAIL POST TUBE CRACKED 	AT .25 INCH HOLE THAT FORMERLY HELD TAIL SKID IN PLACE, NO PROVISION IN STC TO BEEF UP HOLE AREA OF TAIL POST.					1	H	7	1 	3O				1A6     					 
1996070300401	19960703	00401	EA  	1996	7	3	96ZZZX3330       	3	19960601	G	6110		BOLT            			BEECH 	23    	B19         	1151215	CE  						SNSNCH	74D	74DM        	EA  	PROPELLER ATTACH	STRETCHED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	5098M					MB889		A47894		DURING ANNUAL INSPECTION, COULD NOT DETERMINE PROPELLER TIME, SO REMOVED FOR GENERAL CLEAN UP PAINT AND INSPECTING.  WHE	N PROCEEDING TO INSTALL PROP, FOUND 2 BOLTS BADLY STRETCHED IN THREAD AREA.  REPLACED ALL BOLTS WITH NEW.  AIRCRAFT RECO	RDS POOR, SO WOULD RECOMMEND COMPLETE INSPECTION OF PROP WHEN TIME UNKNOWN.				1	L	7	1 	3O				A1CE    		5	N	P88614	 
1996070300402	19960703	00402	SO  	1996	7	3	96ZZZX3331       	2	19960612	G	8520	628488	LIFTER          			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					NR 7 CYLINDER	CHIPPED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	732LW	1256 				21061606	294583R			WHILE CLEANING-INSPECTING LIFTER FOR REINSTALLATION, FOUND CAMSHAFT FACE OF LIFTER CHIPPED.						1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996070300403	19960703	00403	CE  	1996	7	3	96ZZZX3332       	1	19960607	G	5320	071349566	STIFFENER       		05133745    	CESSNA	172   	172M        	2072418	CE  										AFT BULKHEAD	CORRODED        	B			CSVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	6702H	1285 				17265545				UPON ANNUAL INSPECTION, RT WING STRUT LOWER AFT BULKHEAD STIFFENER WAS FOUND WITH SURFACE CORROSION (RUST) ON LOWER 60 P	ERCENT OF PART.  AIRCRAFT HANGARED ON FARM STRIP AND HAS HAD RODENT (MICE) PROBLEMS IN THE PAST.  DROPPINGS AND ODOR ACC	OUNT FOR THIS.  COMBINATION OF RODENTS AND HUMIDITY SUSPECT CAUSE.  RODENT CONTROL AND INSPECTION REQUIRED.				1	H	7	1 	3O			NT	3A12    					 
1996070300404	19960703	00404	SO  	1996	7	3	96ZZZX3333       	1	19960606	G	2731	4173436	CONTROL CABLE   			PIPER 	PA31T 	PA31T1      	7103126	SO  										ELEV TRIM	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	633AB	4509 				31T8104021				RUDDER AND ELEVATOR TRIM CABLES RUSTED.  LOCATED UNDER THE CABIN FLOORBOARD AREA.  REMOVAL FROM THE AIRCRAFT GAVE A BETT	ER VIEW OF THIS CORROSION.  THESE CABLES WERE IN AN UNSAFE CONDITION.  SUBMITTER SUGGESTS REMOVAL OF THESE CABLES EVERY 	2,000 HOURS/5-YEAR INSPECTION.  FAA AND NEW PIPER SHOULD RESPOND TO THIS SAFETY OF FLIGHT ITEM ASAP.				1	L	7	2 	3T			 	A8EA    					 
1996070300405	19960703	00405	SO  	1996	7	3	96ZZZX3334       	1	19960606	G	2721	4173418	CONTROL CABLE   			PIPER 	PA31T 	PA31T1      	7103126	SO  										RUDDER TRIM	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	633AB	4509 				31T8104021				RUDDER AND ELEVATOR TRIM CABLES RUSTED.  LOCATED UNDER THE CABIN FLOORBOARD AREA.  REMOVAL FROM THE AIRCRAFT GAVE A BETT	ER VIEW OF THIS CORROSION.  THESE CABLES WERE IN AN UNSAFE CONDITION.  SUBMITTER SUGGESTS REMOVAL OF THESE CABLES EVERY 	2,000 HOURS/5-YEAR INSPECTION.  FAA AND NEW PIPER SHOULD RESPOND TO THIS SAFETY OF FLIGHT ITEM ASAP.				1	L	7	2 	3T			 	A8EA    					 
1996070300406	19960703	00406		1996	7	3	96ZZZX3335       	4	19960620	G	6122	2102064	GEAR            	WOODWARD    	D210688     															GOVERNOR	WORN            	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					1949087M					UPON INPSECTION, DRIVE GEAR SPLINE WAS FOUND WORN BEYOND REPAIR.  PART HAS BEEN SCRAPPED.																			 
1996070300407	19960703	00407		1996	7	3	96ZZZX3336       	4	19960620	G	6122	C290D36T23	GOVERNOR        	MCAULY      																PUMP BODY	EXCESS WEAR     	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23										DISASSEMBLED GOVERNOR FOR INSPECTION AND FLUSH DUE TO USE OF MOBIL AV 1 OIL.  FOUND SEVERE WEAR ON FLYWEIGHTS AND PINS N	EARING FAILURE.  EXCESSIVE TO SEVERE WEAR ON MAIN BODY DUE TO IDLER GEAR WEAR.  PUMP BODY CAVITY WORN OVER SIZE AND EXCE	SSIVE WEAR ON MAIN SHAFT SPLINE.  WEAR APPEARS TO BE DUE TO LACK OF PROPER LUBRICATION.  ADVISED CUSTOMER TO DO THOROUGH	 INSPECTIONS ON ENGINE AND PARTICULARLY THE COUNTERWEIGHTS.																 
1996070300409	19960703	00409	SO  	1996	7	3	96ZZZX3338       	2	19960614	G	8520	6525384	CRANKCASE       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					LT SIDE NR 4 CYL	CRACKED         	B			AU3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	114PC	1506 				TH661	1260357C			CRANKCASE FOUND CRACKED, LEFT SIDE, ABOVE NR 4 CYLINDER.  THIS IS THE 'HEAVY' STYLE CRANKCASE AND IS NOT COVERED BY AD 7	7-13-22.  SUBMITTER RECOMMENDS INCLUDING THIS SERIES CRANKCASE IN AD 77-13-22.					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996070300410	19960703	00410	GL  	1996	7	3	96ZZZX3339       	3	19960315	G	6114	A3267	BUSHING         			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	HUB	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03			250  					804734		PROPELLER HAD AN INTERNAL LEAK AFTER 250 HRS OPERATION SINCE LAST OVERHAUL.  THE ROD HAD BEEN RUBBING ON THE BUSHING IN 	THE BACK OF THE HUB WHICH IS A REPAIR FROM ORIGINAL MANUFACTURER OF ALL ALUMINUM HUBS.  THE BUSHING INSTALLED FOR REPAIR	 IS MADE OF STEEL.  MAXIMUM REPAIR DIMENSION FOR HUB OR REPLACEMENT OF BUSHING IS .754 INCH.  THE BUSHING MEASURED .762 	INCH AND THE ROD HAD WORN TO MINIMUM DIMENSION OF .748 INCH.  THIS CAUSED LARGE TOLERANCE AND ALLOWED OIL INTO THE CAVIT	Y OF HUB.  ROD WAS REPLACED AND BUSHING WAS REPLACED WITH NEW AND RETURNED TO SERVICE.		1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1996070300411	19960703	00411	EA  	1996	7	3	96ZZZX3340       	2	19960605	G	7414		P-LEAD          			PIPER 	PA24  	PA24180     	7102402	CE  	LYC   	O360  	O360A1A     	41514	EA  					LT MAGNETO	DETERIORATED    	G				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			GL	05	5984P	2222 				241077	L143836			ENGINE INTERMITTENT, ROUGHNESS, WAS BELIEVED CAUSED BY LEFT MAGNETO P-LEAD SHORTING OUT AGAINST OUTSIDE SHIELDING.  BOTH	 LT AND RT P-LEADS INTERNAL INSULATION HAD DETERIORATED TO POWDER.  THIS CONTRIBUTED TO ACCIDENT.  P-LEADS APPEARED TO B	E ORIGINAL EQUIPMENT ON AIRCRAFT.				1	L	7	1 	3O	3	O	NT	1A15    	E286				 
1996070300412	19960703	00412	SO  	1996	7	3	96ZZZX3341       	1	19960611	G	7120		MOUNT           			PIPER 	PA30  	PA30        	7103002	SO  										RT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	411EL					30786				FOUND AT ANNUAL, A CRACK ACROSS THE RING ON RT ENGINE MOUNT LOWER RT SIDE.  IT HAD BEEN OVERHAULED JUST 92 HRS BEFORE AN	D REPAIRED IN THIS AREA.  SUBMITTER STATED ENGINE MOUNTS SHOULD BE THOROUGHLY CHECKED WHEN REPAIRED IN THIS AREA.  CRACK	S NOT EASILY SEEN.  PAINTING MOUNTS A DIFFERENT COLOR WOULD MAKE CRACKS MORE EASILY SEEN.  WHITE WOULD BE HIGHLY RECOMME	NDED.  CRACK NOT ASSOCIATED WITH ANY WELD.			1	L	7	2 	3O				A1EA    					 
1996070300413	19960703	00413	EA  	1996	7	3	96ZZZX3342       	2	19960424	G	8530		HELICOIL        			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 6 CYL PLUG	CAME LOOSE      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4170R	3965 	41   			3240502	L465848A			SPARK PLUG UPPER HELICOIL CAME LOOSE WITH SPARK PLUG.  REMOVED CYLINDER ASSEMBLY AND REPLACED WITH OVERHAULED CYLINDER A	SSY.					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996070300414	19960703	00414	EA  	1996	7	3	96ZZZX3343       	2	19960617	G	8530	LW11633	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 3 CYL LOWER	HELICOIL FAILED 	B			CBCR	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			NM	03	93069		1356 			1285389	L1405315			LOWER SPARK PLUG HELICOIL BLEW OUT ON NR 3 CYLINDER RESULTING IN LOSS OF THAT CYLINDER COMRPESSION AND LOSS OF ENGINE PO	WER.  AIRCRAFT LANDED ON HIGHWAY WITHOUT INCIDENT.  SUSPECT CAUSE:  OVERTORQUE OR UNDERTORQUE OF SPARK PLUG ALLOWING PLU	G TO MOVE IF UNDERTORQUED, OR PULLED THREADS IF OVERTORQUED.  THIS ENGINE HAS STC SE792NW AND SA1008NW - HIGHER COMPRESS	ION PISTONS AND WOULD AGGRAVATE THE SUGGESTED CAUSE.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996070300415	19960703	00415	GL  	1996	7	3	96ZZZX3344       	3	19960612	G	6114		HUB             			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	BLADE SEAL	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03								BG712		PROPELLER HAD LEAKY DOME PRESSURE.  ENTIRE PROPELLER HAD BEEN PAINTED.  AFTER TEAR DOWN, THE INTERNAL OF THE HUB ON BOTH	 PROPS HAD SEVERE CORROSION IN BLADE SEAL AREA AND NEAR OPENING WHERE BLADE COMES OUT OF HUB SOCKET.					1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1996070300416	19960703	00416	CE  	1996	7	3	96ZZZX3345       	1	19960605	G	3500	C1660080101	FILLER VALVE    			CESSNA	310   	310P        	2074238	CE  										OXYGEN SYS	GREASE CONTAM   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	21012					310P0135				FOUND OXYGEN FILLER VALVE IN TOP OF GREASY NOSE WHEELWELL.  FOUND VERY DIFFICULT LOCATION TO SERVICE OXYGEN AND KEEP OXY	GEN SERVICE EQUIPMENT CLEAN WHILE DOING SERVICING.  FEEL THIS IS A DANGEROUS LOCATION FOR OXYGEN EQUIPMENT TO BE INSTALL	ED AND CERTIFIED.				1	L	7	2 	3O				3A10    					 
1996070300417	19960703	00417	CE  	1996	7	3	96ZZZX3346       	1	19960614	G	5743	MS21044N3	BOLT            			CESSNA	310   	310Q        	2074242	CE  										LT WS 57.50	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	7754Q					310Q0254				GEAR SUPPORT LOCK NUTS WORKING LOOSE FROM BOLTS.  SUBMITTER STATED ALSO HAVE FOUND BOLTS LOOSE ON OTHER AIRCRAFT.  LOOSE	NING MAY BE CAUSED BY FLEXING OF THIS AREA.					1	L	7	2 	3O				3A10    					 
1996070300418	19960703	00418	CE  	1996	7	3	96ZZZX3347       	1	19960614	G	5743	AN36A	BOLT            			CESSNA	310   	310Q        	2074242	CE  										RT WS 57.50	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	7754Q					310Q0254				GEAR SUPPORT LOCK NUTS WORKING LOOSE FROM BOLTS.  SUBMITTER STATED ALSO HAVE FOUND BOLTS LOOSE ON OTHER AIRCRAFT.  LOOSE	NING MAY BE CAUSED BY FLEXING OF THIS AREA.					1	L	7	2 	3O				3A10    					 
1996070300419	19960703	00419		1996	7	3	96ZZZX3348       	4	19960601	G	6113	35323800	BULKHEAD        			PIPER 	PA28  	PA28161     	7102803	SO  										PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	9888K					287816207				DURING ANNUAL INSPECTION, FOUND SEVERELY CRACKED FORWARD SPINNER BULKHEAD.						1	L	7	1 	3O				2A13    					 
1996070300420	19960703	00420	SW  	1996	7	3	96ZZZX3349       	1	19960111	G	3220	540015001	FITTING         			MOONEY	M20   	M20G        	5870316	SW  										NLG	RUSTY           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	9145V	4850 				690011				DISASSEMBLY TO CHANGE NLG BISCUITS FOUND CORROSION INSIDE FITTING WHICH GOES UP THROUGH BISCUIT.  MLG OK.  RUST HAS PENE	TRATED THROUGH OVER ONE-HALF OF TUBE WELL.  THIS TUBE WAS WET WITH MOISTURE AND HAD A RUSTY PASTE.  NEW PART WAS UNPAINT	ED INSIDE TUBE.  SUBMITTER RECOMMENDS PERIODIC INSPECTION AND PERIODIC APPLICATION OF LINSEED OIL.  EST PART TIS:  4,850	.0 HRS, 27 YEARS.			1	L	7	1 	3O				2A3     					 
1996070300421	19960703	00421	SO  	1996	7	3	96ZZZX3350       	1	19960515	G	3232	AN8374D	FITTING         		OAS29241    	PIPER 	PA31  	PA31        	7103102	SO  										GEAR DOOR CYL	FAILED          	D				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			NM	11	2336V					31135				WHEN LANDING GEAR WAS SELECTED DOWN, GEAR NEVER MOVED.  EMERGENCY GEAR EXTENSION WORKED PROPERLY, BUT ALL FLUID WAS GONE	 WHEN THIRD GREEN LIGHT CAME ON.  FOUND DOOR CLOSE 'AN' FITTING HAD BROKEN AND DUMPED FLUID WHEN GEAR COMPLETED UP CYCLE	.  PIPER PARTS LIST SHOWS AN ALUMINUM FITTING.  TT ON ACFT, 7,151.7 HRS.  TIME ON ACTUAL FITTING IS UNKNOWN.  FITTING BR	EAK LOOKED LIKE COMPLETE FAILURE SUDDENLY - NO PRIOR CRACK PATTERN SHOWN.  GEAR WORKED NORMALLY AFTER FITTING REPLACED A	ND FLUID REPLENISHED.		1	L	7	2 	3O				A20SO   					 
1996070300422	19960703	00422	SO  	1996	7	3	96ZZZX3351       	1	19960520	G	5511		RIB             			AYRES 	S2    	S2RNORMAL   	7630202	SO  										HORZ STAB TUBES	RUSTED          	B		A	ILIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	331U					2136S				DURING HORIZ STAB FABRIC REMOVAL, FND RUST HAD STAINED THE WHITE FABRIC INTERIOR WHICH CONTACTS TUBING STRUCTURE.  AFTER	 BEAD BLASTING PAINT OFF, 4 RIB TUBES WERE BLOWN THROUGH RUSTED FROM THE INSIDE OUT.  REMAINING TUBES DRILLED TO FACILIT	ATE OILING TUBE INTERIORS AS SPECIFIED IN AC 43-13-1A, CHAP 6.  AS TUBES WERE BEING DRILLED, 1 ADDITIONAL RIB TUBE WAS C	UT OFF STRUCTURE AND ITS INTERIOR WAS FND TO HAVE A CONSIDERABLE AMT OF RUST.  5 TUBES WERE REPLACED AND ALL TUBES WERE 	OILED AND PART WAS RECOVERED WITH FABRIC.  RECOMMEND CLOSE INSPECTION DURING FABRIC REPLACEMENT FOR LEAKING OR RUSTING T	UBES.	1	L	7	1 	3R			NC	A3SW    					 
1996070300423	19960703	00423	SO  	1996	7	3	96ZZZX3352       	1	19960612	G	7930	AN9111	NIPPLE          			PIPER 	PA38  	PA38112     	7103812	SO  										OIL INDICATOR	BROKEN          	D		A		A				UNSCHED LANDING         				Y	K		ENGINE STOPPAGE           	FLUID LOSS                		NR	NOT REPORTED   	1			SW	17	4327E	1049 				3878A0553				DURING FLIGHT, THE NIPPLE THAT ATTACHES OIL PRESSURE SENDER AND HOBBS METER SWITCH ASSEMBLY TO A 90 DEGREE ELBOW, BROKE.	  THE BROKEN NIPPLE CAUSED COMPLETE ENGINE FAILURE.  SUBMITTER RECOMMENDS, PN AN911-1J WHICH IS MADE OF STAINLESS STEEL,	 BE USED TO PREVENT RECURRENCE.  NOTE:  AN911-1 IS MADE OF COPPER ALLOY.				1	L	7	1 	3O				A18SO   					 
1996070300424	19960703	00424	NM  	1996	7	3	96ZZZX3353       	1	19960605	G	2823	10844745	VALVE           			UNIVAR	108   	1082        	9230406	NM  										FUEL SELECTOR	STUCK           	D		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	9609K	22   				1082609				PILOT REPORTED FUEL SELECTOR VALVE STUCK BETWEEN DETENTS WHILE ATTEMPTING TO CHANGE FROM RT TO LT FUEL TANK.  AFTER PUTT	ING BOTH HANDS ON VALVE HANDLE, THE PASSENGER AND PILOT WERE ABLE TO ROTATE THE VALVE TO THE LT TANK.  DISASSEMBLED THE 	VALVE AND FOUND SCORING AND GALLING BETWEEN THE VALVE BODY AND ROTATING PLUG, 'FUEL LUBE' WAS PRESENT.  SUBMITTER STATES	 THIS VALVE WAS MANUFACTURED POORLY, PERHAPS A FINISHING STEP WAS MISSED.  THIS IS THE SECOND VALVE SEEN DO THIS IN 1 YE	AR (ALSO A STINSON).		1	H	7	1 	3O				A767    					 
1996070300425	19960703	00425	SO  	1996	7	3	96ZZZX3354       	1	19960611	G	2910	465204	HOSE ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	RUPTURED        	D		A		O				OTHER                   				P	K		NO WARNING INDICATION     	FLUID LOSS                		AP	APPROACH       	1			SO	05	3581C	5945 				318052091				PILOT EXTENDED THE LANDING GEAR AND HAD NO NOSE GEAR DOWN AND LOCKED INDICATION.  PILOT REPORTED LANDNG GEAR HANDLE FELT	 SOFT WHEN HANDLE MOVED TO THE NEUTRAL POSITION 'BY HAND'.  MANY ATTEMPTS WERE MADE TO GET THE NOSE GEAR DOWN AND LOCKED	.  EMERGENCY GEAR HAD NO EFFECT.  AIRCRAFT LANDED AND NOSE GEAR COLLAPSED.  UPON INSPECTION, FOUND AIRCRAFT LOST HYDRAUL	IC SYSTEM FLUID, RT MAIN GEAR ACTUATOR HOSE, PIPER PN 465-204 FAILED.  THIS NOSE ASSY WAS MFG IN 1979.			1	L	7	2 	3O				A20SO   					 
1996070300426	19960703	00426	SO  	1996	7	3	96ZZZX3355       	1	19960618	G	5711		BOLT            			PIPER 	PA34  	PA34200T    	7103406	SO  										WING SPAR	BROKEN          	B		A	APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	666HL					347770235				RIGHT WING SPAR LOWER BOLT BROKEN CAUSED BY MOISTURE SETTLING AROUND NUT AND THREADS AND CORRODING BOLT.  CORROSION EVID	ENT AT BREAK THROUGH 99 PERCENT OF BOLT DIAMETER.  SUBMITTER STATES RECURRING PROBLEM ON OLDER AIRCRAFT.  OPERATOR KNOWS	 OF MULTIPLE LIKE FAILURES.  RECOMMEND TIME OR CALENDAR LEFT ON THESE BOLTS, 10,000 HRS OR 15 YEARS.				1	L	7	2 	3O				A7SO    					 
1996070300427	19960703	00427	SO  	1996	7	3	96ZZZX3356       	1	19960618	G	2750	95509000	BRACKET         			PIPER 	PA34  	PA34200T    	7103406	SO  										FLAP DETENT	CRACKED         	B		A	APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	666HL	12035				347770235				FLAP HANDLE DETENT BRACKET CRACKED AT DETENT NOTCH RADII, AND AT LOWER BASE FLANGE RADII.  OPERATOR KNOWS OF 2 OTHER SIM	ILAR UNITS WITH SAME PROBLEM.					1	L	7	2 	3O				A7SO    					 
1996070300428	19960703	00428	SO  	1996	7	3	96ZZZX3357       	1	19960529	G	3213	6792612	TRUNNION        			PIPER 	PA32  	PA32RT300   	7103215	SO  										LT MLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	3421W	4715 				32R7885276				LEFT MAIN GEAR STRUT FOUND COLLAPSED.  FURTHER INSPECTION REVEALED TRUNNION ASSY PN 67926-12 CRACKED AND LEAKING.  CRACK	 EXTENDED 90 PERCENT AROUND TRUNNION.  CAUSE IS SUSPECTED TO BE FATIGUE.  NOTE AD 94-13-11 ONLY EFFECTS PA34 AND PA44 AI	RCRAFT.  SUBMITTER STATED ATTENTION TO THIS AREA SHOULD BE KEPT IN MIND WHEN INSPECTING AIRCRAFT WITH EARLY/LIGHT TYPE S	TYLE CASTINGS NOT EFFECTED BY AD 94-13-11 OR PIPER SB 787B.  SUGGEST EXPANSION OF AD COVERAGE TO INCLUDE ALL AIRCRAFT WI	TH LIGHT STYLE TRUNNIONS.		1	L	7	1 	3O				A3SO    					 
1996070300429	19960703	00429	EA  	1996	7	3	96ZZZX3358       	2	19960426	G	7322	46A226	VENTURI         		MA45        	CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					CARBURETOR	FRACTURED       	B	S		ZM3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	260ER	3991 	1985 		75034605	17270223	L3261636A			DURING INSPECTION FOR OVERHAUL, VENTURI WAS FOUND BROKEN AT 3 SUPPORT LEGS AT CENTER OF THE VENTURI.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
1996071000001	19960710	00001	SO  	1996	7	10	96ZZZX3359       	1	19960402	G	5720	6208605	STIFFENER       			PIPER 	PA28  	PA28161     	7102803	SO  										RT WING	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	4325V	4402 				288416017				FOUND LOWER INBOARD WING SKIN STIFFENER ON RT WING CRACKED.						1	L	7	1 	3O				2A13    					 
1996071000002	19960710	00002	SW  	1996	7	10	96ZZZX3360       	1	19960605	G	7160		INLET           			BBAVIA	8     	8GCBC       	1220803	SW  										CARBURETOR AIR	CRACKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	15	495DB	134  				37295				DURING INSPECTION, THE BONDO OVERLAY ON FIBERGLASS CARBURETOR AIR INLET WAS FOUND CRACKING.  FURTHER INSPECTION SHOWED T	HE BONDO WAS LOOSE.  USING A PICK, AN AREA .50 INCH BY 1.50 INCH WAS REMOVED.  THERE WAS A LARGE AIR POCKET THE OVERLAY 	DID NOT ADHERE TO.  IF THESE PIECES HAD COME LOOSE, THEY WOULD HAVE BEEN SUCKED INTO THE ENGINE.  NOTE:  AIRCRAFT IS ONL	Y ONE YEAR OLD.			1	H	7	1 	3O				A21CE   					 
1996071000003	19960710	00003		1996	7	10	96ZZZX3361       	1	19960601	G	2432	VP400KH	CELL            	SAFT        	401767      															BATTERY	CRACKED         	B			RD4D	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25					9509010R					INBOUND INSPECTON OF BATTERY SHOWS ALL 20 CELLS INSTALLED TO BE 'REBUILT'.  DATA PLATE INSTALLED INDICATES BATTERY WAS '	FUNCTIONALLY BENCH CHECKED AND REBUILT' ON 2-28-95.  BATTERY WAS FUNCTIONALLY CHECKED AND FAILED CAPACITY EACH TIME AFTE	R 3 DEEP CYCLES.  ALL HARDWARE (LINKS, NUTS, AND WASHERS) FOUND EXCESSIVELY CORRODED AND NICKELPLATING DELAMINATING AND 	PEELING FROM NUTS.  SEVEN CELLS FOUND CRACKED AND LEAKING ELECTROLYTE.  SAFT MM STATES SECTION 7, PARA 7.2 E.  'REPLACE 	EACH DEFECTIVE CELL WITH A FACTORY NEW SAFT CELL'.  BATTERY FOUND ILLEGAL ACCORDING TO SAFT MANUAL, DOC N 09.94-V 220172	.														 
1996071000004	19960710	00004	SO  	1996	7	10	96ZZZX3362       	1	19960604	G	5520	717002	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  										LT OTBD STAB	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	28RW	3755 				318152103				DURING PHASE 1 INSPECTION 'SMOKING' RIVETS WERE NOTED AT LEFT OUTBOARD ELEVATOR HINGE (ON HORIZONTAL STABILIZER).  REMOV	ED ELEVATORS AND FOUND HINGE CRACKED APPROXIMATELY '.25 INCH' VERTICALLY.  HINGE WAS REPLACED.					1	L	7	2 	3O				A20SO   					 
1996071000005	19960710	00005		1996	7	10	96ZZZX3363       	4	19960611	G	6113	05503401	STABILIZER      			CESSNA	172   	R172K       	2072431	CE  										SPINNER	MISSING         	B			JGVR	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			CE	09	7334K					R172258				CUSTOMER COMPLAINED OF ROUGH RUNNING ENGINE DURING SHORT FINAL UPON LANDING.  FOUND SPINNER BULKHEAD TO BE CRACKED APPRO	XIMATELY 95 PERCENT AROUND ATTACHMENT TO CRANKSHAFT.   FURTHER INSPECTION FOUND THE SPINNER BULKHEAD STABILIZER MISSING 	FROM PROELLER HUB INSIDE SPINNER.  BULKHEAD STABIIZER PN 0550340-1.				1	H	7	1 	3O				3A17    					 
1996071000006	19960710	00006		1996	7	10	96ZZZX3364       	4	19960611	G	6113	05503391	BULKHEAD        			CESSNA	172   	R172K       	2072431	CE  										PROP SPINNER	CRACKED         	B			JGVR	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			CE	09	7334K					R172258				CUSTOMER COMPLAINED OF ROUGH RUNNING ENGINE DURING SHORT FINAL UPON LANDING.  FOUND SPINNER BULKHEAD TO BE CRACKED APPRO	XIMATELY 95 PERCENT AROUND ATTACHMENT TO CRANKSHAFT.   FURTHER INSPECTION FOUND THE SPINNER BULKHEAD STABILIZER MISSING 	FROM PROELLER HUB INSIDE SPINNER.  BULKHEAD STABIIZER PN 0550340-1.				1	H	7	1 	3O				3A17    					 
1996071000007	19960710	00007	SO  	1996	7	10	96ZZZX3365       	1	19960531	G	5730		SKIN            			LUSCOM	8     	8E          	8190112	SO  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2508K	1600 				5235				CORROSION FOUND ON WING SKIN (LOWER) CAUSED BY MOUSE NEST.  AIRCRAFT INACTIVE FOR 4 YEARS.  INSTALLED WING INSPECTION KI	T.					1	H	7	1 	3O				A694    					 
1996071000008	19960710	00008	CE  	1996	7	10	96ZZZX3366       	1	19960611	G	3231	1048200503	RETRACT ARM     			BEECH 	58    	58P         	1152744	CE  										NLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1563L	3832 				TJ84				DURING THE ANNUAL INSPECTION LANDING GEAR RETRACTION TEST, THE NOSE GEAR DOORS WERE OPEN 1.50 INCHES AND NOSE GEAR TIRE 	WAS MAKING CONTACT WITH THE RT GEAR DOOR. WITH A SLIGHT BIT OF HAND PRESSURE, THE NOSE GEAR RETRACTED AND DOORS CLOSED. 	 A THOROUGH INVESTIGATION WAS PERFORMED AND FOUND NOSE GEAR RETRACT ARM ASSY SERIOUSLY CRACKED.  A NEW PART WAS INSTALLE	D AND GER FUNCTINED PROPERLY.  DUE TO THE HEAVY WHITE PAINT ON THE DEFECTIVE PART, THE CRACK COULD HAE GONE UNNOTICED FO	R QUITE SOME TIME.  RECOMMEND THIS PART BE PAINTED WITH PRIMER PAINT ONLY.		1	L	7	2 	3O				A23CE   					 
1996071000009	19960710	00009	NM  	1996	7	10	96ZZZX3367       	1	19960613	G	5102	13864	LINE            		HP3D        	RAVEN 	S57   	S57A        	7485057	NM  										BURNER	LEAKING         	B			GL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	90792	129  			HP3D3356	S57A3145				DURING PRESSURE CHECK OF FUEL LINES, DISCOVERED LEAKING THROUGH SHEATHING OF FUEL LINES.  FUEL LINES AEROQUIP FC 321-06,	 MANFACTURED 2Q93.					1	B	0	0 					A15CE   					 
1996071000010	19960710	00010	CE  	1996	7	10	96ZZZX3368       	1	19960604	G	2133	10357620RX	VALVE           	ALIDSIGNAL  		CESSNA	441   	441         	2076020	CE  										OUTFLOW	FAILED          	B			PAZR	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CE	03	36955		250  		32608	4410028				PILOT REPORTED AIRCRAFT WOULD PRESSURIZE ON TAKEOFF UNTIL MAXIMUM DIFFERENTIAL WAS REACHED AND SAFETY VALVE WOULD ACTUAT	E.  PILOT HAD NO CONTROL OVER RATE.  GAINED ACCESS TO OUTFLOW VALVE AND FOUND SCREWS HOLDING THE DIFFERENTIAL SECTION OF	 CONTROLLER PULLED OUT OF VALVE ALLOWING SPRING TO UNSEAT THIS SECTION.  SCREWS WERE NOT LOOSE, BUT HAD PULLED THE THREA	DS OUT OF THE PLASTIC BODY OF VALVE.			1	L	7	2 	3T			RT	A28CE   					 
1996071000011	19960710	00011	SO  	1996	7	10	96ZZZX3369       	2	19960425	G	8520	642395	CRANKSHAFT      								CONT  	O520  	TSIO520*    	17040	SO  					NR 2 MAIN BRG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13					A132M2					REMOVED CRANKSHAFT FROM ENGINE AT 1,425 HOURS FOR OVERHAUL.  VISIBLE CRACKS AROUND OIL TRANSFER HOLE AT MAIN BEARING BEH	IND ALTERNATOR GEAR.  VISIBLE WITH NAKED EYE.  CONFIRMED WITH MAGNAFLUX.  THIS WAS A FACTORY REBUILT ENGINE.										3	O			E8CE				 
1996071000012	19960710	00012	SW  	1996	7	10	96ZZZX3370       	1	19960611	G	3220	540015001	FITTING         			MOONEY	M20   	M20C        	5870208	SW  										NLG	RUSTY           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	9313V	2656 				690091				ON DISASSEMBLY TO CHANGE NLG BISCUITS, FOUND CORROSION INSIDE FITTING WHICH GOES UP THROUGH BISCUITS - MAIN GEAR WERE OK	.  RUST APPEARS TO HAVE PENETRATED OVER HALF WAY THROUGH TUBE WALL.  SUBMITTER RECOMMENDS PERIODIC INSPECTION AND PERIOD	IC ADDITION OF LINSEED OIL IN CAVITY.  NEW PARTS WERE PAINTED OUTSIDE, BUT NO PAINT IN TUBE.  TUBE POINTS UPWARD, SO WAT	ER OR MOISTURE WILL NOT DRAIN OUT.  ESTIMATE PART TIS:  2,656.0/27 YEARS.			1	L	7	1 	3O				2A3     					 
1996071000013	19960710	00013	SO  	1996	7	10	96ZZZX3371       	2	19960426	G	8550		ENGINE          			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BB     	17032	SO  					OIL SYSTEM	EXCESS SLUDGE   	B			ZM3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3869A	1760 				E1853	2745064			ENGINE WAS DISASSEMBLED FOR MAJOR OVERHAUL.  FOUND EXCESSIVE SLUDGE BUILD-UP IN CRANKSHAFT AND OIL SUMP.  SLUDGE BUILD-U	P IN OIL SUMP HAD IMPACTED ALL P/U TUBE SCREENS TO THE POINT OF 80 PERCENT RESTRICTION.  THE OIL DRAIN IS FORWARD OF THE	 OIL P/U TUBE, SO WHEN NOSE OF AIRCRAFT IS UP WHEN DRAINING OIL, IT DOES NOT ALLOW PROPER DRAINAGE OF CONTAMINATION.  SU	GGEST LOWERING NOSE OF AIRCRAFT AND ALLOWING OIL TO DRAIN OVERNIGHT.			1	L	7	1 	3O	3	O		3A15    	E5CE				 
1996071000015	19960710	00015	SO  	1996	7	10	96ZZZX3373       	2	19960610	G	7414	ES10349276	CONDENSER       	ELECTROSYS  		BEECH 	55    	95B55       	1152706	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE MAGNETO	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	99DC					TC1490	CS20158672L			MAGNETOS OVERHAULED WITH NEW ELECTROSYSTEM CONDENSER, PN E510-349276, CODE NR 03108 AND NR 9544.  MAGNETOS CHECKED ON TE	ST STAND, OPERATED NORMALLY.  MAGS INSTALLED AND TIMED TO ENGINE.  DURING GROUND RUN, 3 MAGS CHECKED NORMAL.  FOURTH MAG	 DEVELOPED A 1,000 RPM DROP.  CHECKED MAG, FOUND BAD CONDENSER.  REPLACED CONDENSER WITH NEW CONDENSER.  GROUND RUN, SAM	E PROBLEM DEVELOPED.  REPLACED CONDENSER WITH A USED BENDIX CONDENSER.  ENGINE RAN NORMAL.			1	L	7	2 	3O	3	O		3A16    	3E1				 
1996071000016	19960710	00016	CE  	1996	7	10	96ZZZX3374       	1	19960602	G	3710	442CW4	PUMP            	AIRBORNE    		BEECH 	58    	58P         	1152744	CE  										GYRO PRESSURE	DRIVE SHEARED   	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	2110A		7    		57651	TJ129				PILOT REPORTED LEFT GYRO PRESSURE INOPERATIVE.  INSPECTED AND FOUND SHEARED LEFT PUMP.  WHILE REPLACING SYSTEM FILTERS, 	FOUND IN-LINE FILTER INSTALLED BACKWARDS.  THIS IS BELIEVED TO HAVE CAUSED FAILURE.					1	L	7	2 	3O				A23CE   					 
1996071000017	19960710	00017	SO  	1996	7	10	96ZZZX3375       	1	19960607	G	3340	A490TCFM1428	POWER SUPPLY    			PIPER 	PA31  	PA31350     	7103110	SO  										STROBE	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	984PA	295  			00158	317305104				AIRCRAFT TAIL STROBE WAS OBSERVED NOT TO BE OPERATING.  STROBE POWER UNIT WAS FOUND TO BE INOPERATIVE.  REMOVED POWER SU	PPLY AND REPLACED.  POWER SUPPLY WAS OPENED AND FOUND CIRCUIT BOARD BURNED AROUND CAPACITOR.  SUSPECT CAPACITOR NEVER DI	SCHARGED CAUSING IT TO BECOME HOT.				1	L	7	2 	3O				A20SO   					 
1996071000018	19960710	00018	SO  	1996	7	10	96ZZZX3376       	1	19960423	G	7920		HOSE            	AEROQUIP    		PIPER 	PA23  	PA23250     	7102308	SO  										RT OIL COOLER	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	412DC	1300 				278054008				HOSE GOING TO OIL COOLER FOUND LEAKING.  (AEROQUIP 303-8.)						1	L	7	2 	3O				1A10    					 
1996071000020	19960710	00020	CE  	1996	7	10	96ZZZX3378       	1	19960611	G	2810	531010	FUEL CAP        			CESSNA	210   	210L        	2073448	CE  										WING TANK	DEFECTIVE       	B			EATR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	2220S					21061165				COMPLIANCE WITH AD 94-12-08.  AD NO LONGER APPLIES TO THIS AIRCRAFT.						1	H	7	1 	3O				3A21    					 
1996071000021	19960710	00021	EA  	1996	7	10	96ZZZX3379       	2	19960411	G	8530		CYLINDER        			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 2-6 CYLINDERS	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	9000N	148  				3240883	L1338348A			INSPECTION FOUND CYLINDER ASSEMBLIES WERE STEPPED AT TOP OF BORE.  RINGS HAD KNIFE EDGE AT TOP FACE OF RING.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996071000022	19960710	00022	SO  	1996	7	10	96ZZZX3380       	2	19960610	G	8520	641931	BOLT            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					ENG THROUGH-STUD	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	1473F		637  			18502851	293042R			THIS THROUGH-BOLT HOLDS CYLINDERS NR 3 AND NR 2 TOGETHER AT TOP OF CLYLINDER, ALSO, BOLT CLAMPS THE CASE TOGETHER.  THE 	THREADS ON THE STUD AND NUT FAILED CAUSING OIL TO LEAK.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
1996071000023	19960710	00023	EU  	1996	7	10	96ZZZX3381       	1	19960420	G	5610	2601114711	CANOPY RAIL     		260005001   	MRCHTI	SF260 	SF260       	8121206	EU  										COCKPIT LT	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			EA	21	13FD	1912 				1009				FIFTEEN MINUTES AFTER DEPARTURE, LEFT RAIL OF CANOPY FAILED.  RIGHT SIDE OF CANOPY STAYED ATTACHED.  INCURRED DAMAGE TO 	THE HORIZONTAL STABILIZER, LEFT SIDE RAIL NOT FOUND.  INSPECTED MECHANICAL EMERGENCY RELEASE OF CANOPY.  OPERATED NORMAL	LY.  SUSPECT EXCESSIVE WEAR OF A CRACK ON THE EYELET OF THE CANOPY RAIL.				1	L	7	1 	3O				A10EU   					 
1996071000024	19960710	00024	CE  	1996	7	10	96ZZZX3382       	1	19960528	G	2434	1169	BRUSH BLOCK     		649304R     	CESSNA	310   	310R        	2074245	CE  										ALTERNATOR	EXCESS WEAR     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	103FS		141  		H3095080R	310R1834				DISASSEMBLY AFTER ALTERNATOR FAILURE REVEALED PREMATURE AND EXCESSIVE WEAR ON BRUSHES.  TIME SINCE OVERHAUL 141.0 HOURS.	  SUBMITTER STATED POSSIBLE DEFECTIVE BRUSHES OR IMPROPER INSTALLATION.					1	L	7	2 	3O				3A10    					 
1996071000025	19960710	00025	SO  	1996	7	10	96ZZZX3383       	1	19960610	G	8120	TH08A60	TURBOCHARGER    	GARRTT      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					SHAFT	FAILED          	D		A		K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			GL	25	123MA		20   		40917D9001	318152024	L839961A			TURBO OVERHAULED 12-7-92, PLACED IN SERVICE 5-17-96.  AFTER TWENTY HOURS IN SERVICE, REPORTED INCREASED VIBRATION LEVEL,	 FOLLOWED BY MANIFOLD PRESSURE REDUCTION, THEN BY ENGINE COMPARMTENT FIRE.  FOUND TURBOSHAFT SHEARED, COMPRESSOR AND TUR	BINE WHEELS DAMAGED.  ALL ATTACHING HARDWARE HAD SHAKEN LOOSE FROM TURBO, ALL SAFETY PLATES, LOCK WASHERS, ETC., FOUND I	N PLACE.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996071000027	19960710	00027	CE  	1996	7	10	96ZZZX3385       	1	19960610	G	5330		SKIN            			CESSNA	170   	170B        	2072306	CE  										AFT LT MLG LEG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3487D					27030				UPON INSPECTION, A 3 INCH CRACK WAS DISCOVERED AFT OF THE LEFT LANDING GEAR LEG ADJACENT TO THE GEARBOX.  WAS DIFFICULT 	TO SEE, DUE TO CLOSE PROXIMITY TO OVERLAPPING EXTERIOR GEARBOX SKIN.  WOULD RECOMMEND USE OF LIGHT BELOW FUSELAGE WHILE 	INSPECTING THROUGH CABIN FLOOR PANELS.				1	H	7	1 	3O				A799    					 
1996071000028	19960710	00028		1996	7	10	96ZZZX3386       	1	19960501	G	2460	W31X2M1G5	BREAKER         	AMF         																HOUSING	CRACKED         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07										WHEN PREPARING TO INSTALL BREAKER ON AN AIRCRAFT, ATTEMPTED TO REMOVE THE TERMINAL'S SCREWS ON BACK OF BREAKERS.  ALL 4 	BREAKER HOUSINGS CRACKED DUE TO THE SCREWS BEING TOO TIGHT FROM THE FACTORY.  BEFORE REMOVING SCREWS, PLACE TERMINAL IN 	A VISE TO HOLD TERMINAL FROM TWISTING.																	 
1996071000029	19960710	00029	WP  	1996	7	10	96ZZZX3387       	1	19960617	G	2910	15807D	SEAL RING       		AV16A1173A  	DOUG  	DC8   	DC8*        		WP  										HYD GATE VALVE	FAILED          	B			DM4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										TEN EACH NEW SEALS WERE RECEIVED FROM THE AUTHORIZED DISTRIBUTOR FOR THE MANUFACTURER.  THIS SEAL IS USED IN SKYDROL HYD	RAULIC FLUID, BUT THE NEW SEALS FAILED UPON INSTALLATION (WOULD NOT SEAL).  THE SEALS SWELL WHEN INTRODUCED TO SKYDROL F	LUID.  SUBMITTER STATED SEAL IS MADE OF WRONG MATERIAL.				2	L	7	4 	4J			F	4A25    					 
1996071000030	19960710	00030	SO  	1996	7	10	96ZZZX3388       	1	19960612	G	5751	902010501	SUPPORT ASSY    			GULSTM	AA5   	AA5B        	3960105	SO  										LT AIL BRG OTBD	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	4533Q	6549 				1186				DURING ANNUAL INSPECTION ON GRUMMAN TIGER AA5B, FOUND LEFT AILERON OUTBOARD BEARING SUPPORT ASSY CRACKED APPROXIMATELY .	25 INCH INBOARD OF LOWER BOLT HOLE.					1	L	7	1 	3O				A16EA   					 
1996071000031	19960710	00031	CE  	1996	7	10	96ZZZX3389       	1	19960613	G	7920	62402312D	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  										OIL SYSTEM	DISINTEGRATED   	D		A		A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	13	29HF				0280	BB685				INNER LINER OF AEROQUIP HOSE DISINTEGRATED, PLUGGED THE BYPASS VALVE AND SCREEN, AND CONTAMINATED OIL SYSTEM, TORQUEMETE	R FLUCTUATED AND OIL PRESSURE FELL TO 60 PSI AND ENIGNE WAS SHUT DOWN IN-FLIGHT.  PIECES OF HOSE WERE FOUND IN OIL COOLE	R, 6 INCHES BY 1 INCH IN SIZE.  ENGINE WAS REMOVED AND SENT TO PRATT AND WHITNEY FOR DISASSEMBLY, CLEAN AND REPAIR AS NE	CESSARY.  REPAIRS INCLUDED SUN GEAR, REDUCTION GEARS, OIL PUMP, PROP GOVERNOR, SCAVENGE PUMP, OIL COOLER, AND NOZZLE SCR	EENS, ETC.		1	L	7	2 	4T				A24CE   					 
1996071000033	19960710	00033	SO  	1996	7	10	96ZZZX3391       	1	19960610	G	2910	1159P2051813	TUBE ASSY       			GULSTM	G1159 	G1159A      	3970109	SO  										LT PYLON	CHAFED          	B	S		RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	XAMEY					252				WHILE GAINING ACCESS TO THE LT PYLON AREA, NOTED MAIN HYDRAULIC LINE LOCATED IN AFT SECTION OF PYLON AREA FOUND CHAFING 	THE OUTER WALL AT POINTS WHERE ADEL CLAMPS ATTACH.  ALSO, ADDITIONAL CHAFING WAS FOUND ON THE SAME LINE WHICH APPEARED T	O BE CAUSED BY WIRE BUNDLE STRAPS CHAFING AGAINST THE LINE.  PROPER SIZE ADEL CLAMPS WITH PROPER PROTECTIVE COATINGS WER	E INSTALLED (TEFLON COATED); MAIN HYDRAULIC LINE AND WIRE AND WIRE BUNDLE WERE REPOSITIONED TO PREVENT FUTURE CHAFING.			2	L	7	2 	4F				A12EA   					 
1996071000034	19960710	00034	SO  	1996	7	10	96ZZZX3392       	1	19960610	G	2910	1159P2051814	TUBE ASSY       			GULSTM	G1159 	G1159A      	3970109	SO  										RT PYLON	CHAFED          	B	S		RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	375NM					375				WHILE GAINING ACCESS TO THE PYLON AREA, NOTED THE MAIN HYDRAULIC LINE LOCATED IN THE AFT SECTION OF THE PYLON AREA WAS F	OUND CHAFING THE OUTER WALL.  CHAFING APPEARED TO BE CAUSED BY WIRE BUNDLE STRAPS CHAFING AGAINST THE LINE.  MAIN HYDRAU	LIC LINE AND WIRE BUNDLE WERE REPOSITIONED TO PREVENT FUTURE CHAFING.				2	L	7	2 	4F				A12EA   					 
1996071000035	19960710	00035	EU  	1996	7	10	96ZZZX3393       	1	19960531	G	3213	256UM57	PLUG            			BRAERO	DH125 	HS125700A   	4230170	EU  										MLG STRUT	CRACKED         	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	151AE	8728 				NA0263				UPON SERVICING OF THE MAIN GEAR STRUTS, THE PLUGS THAT THE SHRADER VALVES SCREW INTO WERE FOUND CRACKED FROM THE THREADE	D AREA OUTWARD.  THE LT SIDE WAS FOUND VISUALLY, THE RT SIDE WAS FOUND WITH DYE PENETRANT.  SUSPECT THE SHRADER VALVES M	AY HAVE BEEN OVERTORQUED.				2	L	7	2 	4F				A3EU    					 
1996071000036	19960710	00036	WP  	1996	7	10	96ZZZX3394       	2	19960604	G	7421	CH31815	IGNITER         	CHAMPION    		AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   		WP  					ENGINE IGNITER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	523AC	852  				139				DURING ROUTINE MAINTENANCE, THE IGNITER FIRING TIP OF THE CENTER ELECTRODE WAS FOUND LOOSE.  THE IGNITER IS AN EXTENDED 	LIFE IRIDIUM IGNITER.  THIS WAS A NON-SERIALIZED IGNITER, BUT THE 'TST' INDICATES PREVIOUS SPECIAL TESTING FOR LOOSE CEN	TER ELECTRODE WAS COMPLIED WITH BY CHAMPION, THE MANUFACTURER.				2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
1996071000037	19960710	00037	EU  	1996	7	10	96ZZZX3395       	1	19960603	G	5620		FRAME           			AEROSP	ATR42 	ATR42300    	8680920	EU  										CABIN WINDOW	CORRODED        	B			FI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	19AE					015				TWENTY-SEVEN EACH CABIN WINDOW FRAMES CORRODED BEYOND LIMITS PER ATR42 SRM 53-51-00, FIGURE 301, PAGE 309, AT LOCATIONS 	WINDOW LT NRS 2, 3, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, AND 16; RT NRS 1, 2, 4, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, AND 	17.  THIS AIRCRAFT OPERATES IN A SALT WATER ENVIRONMENT AND IT APPEARS THE MOISTURE IS BEING TRAPPED BETWEEN THE WINDOW 	SEAL AND FRAME ALONG THE WINDOW LOWER RADIUS.			2	H	7	2 	4T			RT	A53EU   					 
1996071000038	19960710	00038	CE  	1996	7	10	96ZZZX3396       	1	19960618	G	3230	9000111	BEARING         	ELECTROMECH 		BEECH 	100   	A100        	1152915	CE  										LG MOTOR	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	100GV		200  		69	B116				BEARING (AFT) FAILED.  PART NUMBER AS ORDERED FROM BEECH WOULD BE 9000-11.  BEARING SUPPLIED BY BEECH IS IDENTIFIED AS (	PEER CHINA 600ZD).  SUBMITTER SUSPECTS QUALITY CONTROL MAY BE LACKING.					1	L	7	2 	3T				A14CE   					 
1996071000039	19960710	00039	CE  	1996	7	10	96ZZZX3397       	1	19960608	G	3213	1228100791	AXLE            		A228100791  	BEECH 	2000  	2000        	1152000	CE  										RT MLG	RUSTED          	B			PAIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	8025L	1027 				NC19				DURING AN ABC PHASE INSPECTION, THE RT OUTBOARD WHEEL AND BRAKE WERE REMOVED.  CORROSION (RUST) WAS FOUND ON THE AXLE WH	ERE THE BRAKE CALIPER RIDES.  THE RUST WAS .300 INCH WIDE AND FORMED A BAND ALL THE WAY AROUND THE AXLE.  THE DEPTH OF T	HE PIT MEASURED .030 INCH.  THE INBOARD SIDE OF AXLE SHOWED SIGNS OF CORROSION JUST BEGINNING.  THE AXLE WAS REPLACED.				1	L	7	2 	4T			RT	A38ACE  					 
1996071000041	19960710	00041	CE  	1996	7	10	96ZZZX3399       	1	19960605	G	7620	99120142C	VALVE           			CESSNA	500   	500CESSNA   	2076602	CE  										FIREWALL SOV	FAILED          	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SO	09	95Q		535  		565	5000119				LEFT ENIGNE WOULD NOT START, LEFT LOW FUEL PRESSURE ANNUNCIATOR LIGHT DID NOT EXTINGUISH DURING START ATTEMPT.  FOUND LE	FT FIREWALL FUEL SHUT-OFF VALVE IN CLOSED POSITION.  PILOT TESTED FIREWALL SHUT-OFF VALVES DURING PRE-FLIGHT.  LEFT VALV	E STAYED CLOSED AFTER SWITCH WAS RESET TO NORMAL.  VALVE FAILED IN CLOSED POSITION.				1	L	7	2 	4F				A22CE   					 
1996071000042	19960710	00042	NM  	1996	7	10	96ZZZX3400       	1	19960625	G	2121	13863352	BEARING         	SUNDSTRANDEM	5007024620  	BOEING	727   	727         	1384001	NM  										CABIN FAN	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		69   			AA31148					BEARING COMPLETELY DESTROYED.  BEARING WAS INSTALLED NEW AND FAILED AFTER 69.02 HOURS OF OPERATION.  CAUSED FAN TO OPERA	TE LOUD AND SMELL LIKE IT IS BURNED.  IMPELLER LOCKS UP.					2	L	7	3 	4F				A3WE    					 
1996071000043	19960710	00043	NM  	1996	7	10	96ZZZX3401       	1	19960625	G	2121	13863352	BEARING         	SUNDSTRANDEM	5007024620  	BOEING	737   	737*        		NM  										CABIN FAN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		39   			AA25289					BEARING VERY ROUGH CAUSING IMPELLER TO LOCK UP AND FAN PUTS OUT ELECTRICAL SMOKE.  BEARING FAILED AFTER 39.01 HOURS OF O	PERATION.					2	L	7	2 	4F			RT	A16WE   					 
1996071000044	19960710	00044	EA  	1996	7	10	96ZZZX3402       	2	19960315	G	7323	1412654	BEARING         		8210002     						PWA   	PT6   	PT6*        	52043	EA  					GOV FLYWEIGHT	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03										DURING ASSEMBLY OF AN 8210-002 GOVERNOR, THE FACTORY NEW 1412-654 BEARINGS JUST FELL APART.  SUBMITTER RECOMMENDS NEW QC	 CONTROL.										3	T			E2NE				 
1996071000045	19960710	00045	SW  	1996	7	10	96ZZZX3403       	1	19960513	G	6321	5009212	LINING          		4000397     	BELL  	206   	206L3       	1182108	SW  										ROTOR BRAKE	WORN HOLE       	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	617DE					51138				MOUNTING BAR CAME LOOSE FROM LINING ALLOWING IT TO FLOAT LOOSE BETWEEN PISTON AND BRAKE DISK.  WHEN THE ROTOR BRAKE WAS 	APPLIED, THE LINING COULD BE FORCED DOWN AND WEDGE BETWEEN THE DISK AND THE CALIPER AND ACT LIKE THE BRAKE WAS ON.  REPL	ACED LININGS AND O-RINGS AND REASSEMBLED.  OPS CHECKED OK.				1	G	7	1 	3U				H2SW    					 
1996071000281	19960710	00281	SW  	1996	7	10	96ZZZX3404       	1	19960520	G	6320	206040151015	CASE ASSY       			BELL  	206   	206BELL     	1181502	SW  										TRANSMISSION	MFG DEFECT      	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	01					B10881					PLUGS AT CASE-TO-MAST MATING SURFACE DRIVEN UP BY BOLTS DURING INSTALLATION OF MAST CHIP DETECTOR.  DEBRIS IN PAN.  SUBM	ITTER STATED IT WAS DETERMINED TO BE MANUFACTURING DEFECT.					1	G	7	1 	3U				H2SW    					 
1996071000283	19960710	00283	GL  	1996	7	10	96ZZZX3406       	1	19960618	G	6230		SHAFT           			AMTR  	RWEXEC	ROTORWAYEXEC		GL  										M/R	FAILED          	G	S			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	7182Z	100  				RW1522008				INVESTIGATION OF AN EXPERIMENTAL HELICOPTER ACCIDENT FOUND FOLLOWING PROBLEM:  BEARING ASSY SHAFT INSERT BROKEN OFF INSI	DE OF MAIN ROTOR SHAFT.  STUB SHAFT FELL OUT THE MAIN ROTOR SHAFT.  MAIN SHAFT AND SPROCKET AND CHAIN DUG INTO FUEL TANK	.  TOP OF MAIN BEARING WAS ALSO ROTATED TO REAR AND LEFT.  COLLECTIVE SCISSORS BASE SUPPORT WAS BROKEN AND ROTATED UP, T	HE 3-ROLLER DRIVE CHAIN JUMPED UP ONE SET OF ROLLERS ON THE SPROCKET.  THIS MAIN ROTOR SHAFT ASSY WAS REPLACED ON 1-'95.	  THE REPLACEMENT ASSY INDICATIONS ARE THAT PARTS DO NOT MEET THE ORIGINAL SPECIFICATION.		1	G	7	1 	3O				EXPA1G71					 
1996071000285	19960710	00285	CE  	1996	7	10	96ZZZX3408       	1	19960502	G	2434	ES4118	BRUSH KIT       	FORD        	DOFF10300B  	CESSNA	172   	172         	2072402	CE  										ALTERNATOR	FAILED          	B		A	ZM3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07		163  			508244T					COMPONENT WAS RECENTLY OVERHAULED.  INSPECTION REVEALED BRUSHES WERE INSTALLED UPSIDE DOWN CAUSING WEAR INTO BRUSH LEADS	 AND PREMATURE FAILURE.  SUBMITTER STATED THIS IS THE FOURTH FAILURE IN THE LAST SIX MONTHS DUE TO IMPROPER BRUSH INSTAL	LATION.  ALL UNITS WERE OVERHAULED BY SAME OVERHAULER.  ALL WITH LESS THAN 200 HOURS.				1	H	7	1 	3O			NT	3A12    					 
1996071000286	19960710	00286	CE  	1996	7	10	96ZZZX3409       	1	19960612	G	2752	505212223	ACTUATOR        			BEECH 	300   	300BEECH    	1152930	CE  										LT OTBD FLAP	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	350TW	416  			808J90	FM2				DURING INSPECTION FLAPS MOVED ERRATICALLY.  UPON FURTHER INSPECTION OF LEFT OUTBOARD FLAP ACTUATOR, FOUND 5.50 INCH CRAC	K RUNNING THE LENGTH OF THE PISTON ACTUATOR (REF:  BEECH B300 IPC, CHAPTER 27-50-00, PAGE 2, ITEM NR 19).  RECOMMEND CLO	SER INSPECTION OF FLAP ACTUATOR PISTONS IN THE EXTENDED POSITION.				2	L	7	2 	4T				A24CE   					 
1996071000287	19960710	00287	EU  	1996	7	10	96ZZZX3410       	1	19960614	G	3520	17408057	LANYARD         			AIRBUS	310   	A310300     		EU  										OXYGEN MASK	FAIL TEST       	B	S	A	GUMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19	V8DPD					431				OXYGEN MASK LANYARDS FOR ACTIVATING PASSENGER OXYGEN SYSTEMS FAILED THE PULL TEST.  INSPECTION OF ALL LANYARDS WITH THIS	 PART NUMBER BOX RESULTED IN IDENTIFYING 100 PERCENT DEFECTIVE, I.E., BAD CRIMPS AND CRIMPS SLIPPING.  PURITAN BENNETT H	AS BEEN NOTIFIED AND IS INVESTIGATING THE PROBLEM.				2	L	7	2 	4F			RT	A35EU   					 
1996071000288	19960710	00288	NE  	1996	7	10	96ZZZX3411       	2	19960503	G	7230	9136M89G19	ROTOR SPOOL     								GE    	CF6   	CF650*      	30018	NE  					HP COMP	CRACKED         	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01							517842			DURING NDT INSPECTION, A CRACK WAS FOUND IN THE 3-9 HPC SPOOL.  THE CRACK IS NOT IN THE AREA DESCRIBED IN THE AD ON SPOO	LS.										4	F			E23EA				 
1996071000289	19960710	00289	SW  	1996	7	10	96ZZZX3412       	1	19960501	G	3213	206030104023	FITTING         			BELL  	206   	206L4       	1182110	SW  										FWD CROSSTUBE	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	174AL	2528 				52067				DURING SERVICE CHECK, NOTED FORWARD CROSSTUBE FITTING WAS CRACKED.  FITTING WAS FOUND CRACKED IN THE SAME AREA AS REPORT	ED ON MDR SUBMITTED ON 2-7-94.  THE FITTING WAS MANUFACTURED IN OCTOBER, 1992, WHICH IS DIFFERENT FROM THE PREVIOUSLY RE	PORTED CRACKED FITTINGS.				1	G	7	1 	3U			NC	H2SW    					 
1996071000292	19960710	00292	SW  	1996	7	10	96ZZZX3415       	1	19960506	G	6230	20601044304	DUPLEX BEARING  		206010450117	BELL  	206   	206L3       	1182108	SW  										SWASHPLATE	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2616	1083 			17620	51418				THIS IS THE SECOND DUPLEX BEARING FAILURE OF THIS TYPE IN LAST 6 MONTHS.  BEARINGS FAILED WITH 1,000 HOURS OR LESS.  PRE	VIOUS BEARING, SN 17910, FAILED AT 915.1 HOURS.  BEARINGS ARE NORMALLY CONDITIONAL ITEMS AND SELDOM NEED CHANGING AT 4,8	00-HOUR OVERHAUL PERIOD OF SWASHPLATE.				1	G	7	1 	3U				H2SW    					 
1996071000294	19960710	00294	GL  	1996	7	10	96ZZZX3417       	2	19960424	G	7323	252466713	GOVERNOR        			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEFECTIVE       	B			EOPR	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			AL	01	493HL				26236	S809				GOVERNOR REQUIRED TO BE RETRIMMED FREQUENTLY, THEN ENGINE FELL TO IDLE ON DESCENT FOR FINAL.  GOVERNOR WAS CLOSE TO OVER	HAUL, 56.0 HOURS LEFT.  REPLACED GOVERNOR.					1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
1996071800007	19960718	00007	SO  	1996	7	18	96ZZZX3419       	2	19960508	G	8530	401852	STUDS           			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360GB   	17025	SO  					NR 1 CYL EXH RKR	FAILED          	B		A	JC9R	O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SO	07	231PB	1729 	552  			250163	309837			ENGINE SUDDENLY STARTED RUNNING ROUGH, LOSS OF POWER (PARTIAL) WHILE IN CRUISE FLIGHT 210.  FOUND NR 1 CYLINDER EXHAUST 	ROCKER SHAFT HOLD-DOWN STUDS BROKEN.  INVESTIGATION REVEALED IMPROPER TORQUE ON ROCKER SHAFT HOLD-DOWN STUDS.					1	L	7	1 	3O	3	O		2A3     	E9CE				 
1996071800008	19960718	00008	EU  	1996	7	18	96ZZZX3420       	1	19960620	G	3520	C3512000	MASK            			BRAERO	1000  	BAE1251000  	1500287	EU  										PAX CABIN OXY	TORN            	B	S	A	YK1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	81AB	1142 				259005				RUBBER FACE CUP TORN.  FOUR EACH PASSENGER FACE MASKS.  ALL TORN IN THE SAME LOCATION.  FOUND DURING 12-MONTH INSPECTION	.					2	L	7	2 	4F			RT	A3EU    					 
1996071800009	19960718	00009	GL  	1996	7	18	96ZZZX3421       	3	19960605	G	6111		BLADE           			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	NR 1	CRACKED         	B		A	HLWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	89922	2781 				15282916		R774697		FOUND CRACK AT BOLT HOLE OF BLADE NR 1 LEADING EDGE BY LIQUID PENETRANT INSPECTION WHEN OVERHAULING PROPELLER.  CRACK IS	 ABOUT .185 INCH LONG AND .060 INCH FROM EDGE OF BOLT HOLE.  RETURNED TO SERVICE IAW AD 95-21-01 PER SB 219.  RECOMMEND 	THAT LIQUID PENETRANT INSPECTION BE PERFORMED INSTEAD OF VISUAL INSPECTION PER SB 219.				1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1996071800010	19960718	00010	EU  	1996	7	18	96ZZZX3422       	1	19960703	G	3520	C3512000	MASK            			BRAERO	DH125 	BAE125800A  	1500285	EU  										PASSENGER CABIN	TORN            	B	S	A	UH6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	801CE	923  				258253				RUBBER FACE CUP TORN.  TWO EACH PASSENGER FACE MASKS.  BOTH MASKS TORN IN SAME LOCATION.  FOUND DURING 24-MONTH INSPECTI	ON.  MFG PURITAN BENNETT.					2	L	7	2 	4F			RT	A3EU    					 
1996071800012	19960718	00012	GL  	1996	7	18	96ZZZX3424       	3	19960604	G	6111		BEARING         			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	BLADE	BROKEN          	B			HLWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4929V	1470 				172RG0148		941182		PROPELLER WAS NOT CYCLING PROPERLY.  REMOVED TO BENCH TEST.  BLADES WERE BINDING WHEN TESTED.  DISASSEMBLED AND FOUND BL	ADE BEARINGS DRY AND BROKEN, BALL BEARINGS PITTED, AND PITCH CHANGE LINKS AND ACTUATING PINS WORN BADLY.  SUBMITTER STAT	ED PROP MAY NOT HAVE BEEN LUBRICATED PROPERLY AT ASSEMBLY.  THE PROPELLER SHOULD HAVE BEEN REMOVED AND REPAIRED WHEN PRO	BLEMS WITH CYCLING FIRST STARTED.			1	H	7	1 	3O				3A17    		5	C	P7EA	 
1996071800013	19960718	00013	CE  	1996	7	18	96ZZZX3425       	1	19960606	G	7920	S116720370	HOSE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					OIL COOLER	SOFT            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	69269					15282593				DURING ANNUAL INSPECTION, OIL COOLER HOSES WERE FOUND SOFT AND STICKY.  HOSES WOULD NOT HAVE GONE ANOTHER YEAR.  HOSES H	AD BEEN REPLACED 5 YEARS AGO AND HAD ABOUT 250 HOURS ON THEM.  INSTALLER REPLACED HOSES AND INSTALLED FIRE SHIELD ON THE	M.  INSTALLER RECOMMENDS THAT FIRE SHIELDS BE INSTALLED ON ALL HOSES BECAUSE OF PROXIMITY TO ENGINE AND HEAT.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996071800014	19960718	00014	EA  	1996	7	18	96ZZZX3426       	2	19960601	G	8520	SL13792	SEAL            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CRANKSHAFT	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	67658					15285305	1656615			OUTER CIRCUMFERENCE OF SEAL IS NOT A TIGHT FIT TO THE CRANKCASE.  AFTER SEAL IS INSTALLED, SEAL IS ABLE TO ROTATE.  NO S	EALANT IS RECOMMENDED IN THE OVERHAUL OR SERVICE MANUALS, PN 13792 AND SL 13792 SEALS.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996071800015	19960718	00015	EA  	1996	7	18	96ZZZX3427       	2	19960624	G	8520	LW13792	SEAL            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					CRANKSHAFT	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	8318H					288116121	RL1077639A			OUTER CIRCUMFERENCE OF SEAL IS NOT A TIGHT FIT TO THE CRANKCASE.  AFTER SEAL IS INSTALLED, SEAL IS ABLE TO ROTATE.  NO S	EALANT IS RECOMMENDED IN THE OVERHAUL OR SERVICE MANUALS, P/N LW13792 AND SL 13792 SEALS.					1	L	7	1 	3O	3	O		2A13    	E274				 
1996071800016	19960718	00016		1996	7	18	96ZZZX3428       	1	19960613	G	2822	1C610	PUMP            	AIRBORNE    																FUEL SYSTEM	LEAD FAILED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					6AE259					FOUND LEAD WIRE TWISTED OFF.  CAUSED BY INSTALLATION ERROR BY BOTTOMING OUT LEAD WIRE SCREW OR USING A FAULTY SCREW.  TH	IS CAUSED POWER LEAD TO TWIST OFF.																		 
1996071800017	19960718	00017		1996	7	18	96ZZZX3429       	1	19960527	G	2752	505212223	ACTUATOR        	BEECH       																FLAP	MISLABELED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13					3115943					ACTUATOR WAS OVERHAULED AS A 50-521222-3, BUT WAS LABELED AS A 101-521016-2.																			 
1996071800018	19960718	00018		1996	7	18	96ZZZX3430       	1	19960523	G	2822	1C1232	PUMP            	AIRBORNE    																FUEL SYSTEM	IMPELLER BROKEN 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					12AD169					MOLDED PLASTIC IMPELLER BROKEN AT ARMATURE 'D' CUT KEYWAY.  SUBMITTER SUGGESTS STRONGER MATERIAL.																			 
1996071800019	19960718	00019		1996	7	18	96ZZZX3431       	1	19960523	G	2822	1C1232	PUMP            	AIRBORNE    																FUEL SYSTEM	IMPELLER BROKEN 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					11AD101					MOLDED PLASTIC IMPELLER BROKEN AT ARMATURE 'D' CUT KEYWAY.  SUBMITTER SUGGESTS STRONGER MATERIAL.																			 
1996071800020	19960718	00020		1996	7	18	96ZZZX3432       	1	19960523	G	2822	1C1232	PUMP            	AIRBORNE    																FUEL SYSTEM	IMPELLER BROKEN 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					1AF3					MOLDED PLASTIC IMPELLER BROKEN AT ARMATURE 'D' CUT KEYWAY.  SUBMITTER SUGGESTS STRONGER MATERIAL.																			 
1996071800021	19960718	00021	CE  	1996	7	18	96ZZZX3433       	1	19960606	G	2710		CONTROL CABLE   			CESSNA	150   	150G        	2071816	CE  										AILERON	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21						64919				DURING A 100-HOUR INSPECTION, THE FOLLOWING DEFECTS WERE FOUND:  THE AILERON CONTROL CABLE WAS SCRAPING THE PRIMER LINE(	S) LOCATED IN THE FIREWALL AND A CRACK IN THE CONTROL CABLE SUPPORT BETWEEN THE INSTRUMENT PANEL AND THE FIREWALL ON THE	 PILOT'S SIDE.				1	H	7	1 	3O			 	3A19    					 
1996071800022	19960718	00022	CE  	1996	7	18	96ZZZX3434       	1	19960306	G	5320		SUPPORT         			CESSNA	150   	150E        	2071812	CE  										RUDDER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21						61385				DURING A 100-HOUR INSPECTION A CRACK WAS FOUND IN THE SUPPORT UNDER THE RUDDER.						1	H	7	1 	3O				3A19    					 
1996071800023	19960718	00023	CE  	1996	7	18	96ZZZX3435       	1	19960601	G	2750	98600582	CONTROL CABLE   			CESSNA	207   	207         	2073602	CE  										FLAP FOLLOW-UP	BINDS           	B		A	AX0R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	1658U					20700258				CABLE WAS OF A DIFFERENT DESIGN THAN THE ORIGINAL CABLE REMOVED.  NEW CABLE WOULD BIND IN THE HOUSING WHEN INSTALLED IN 	AIRCRAFT.  A SECOND CABLE WAS PURCHASED AOG AND FOUND TO HAVE THE SAME PROBLEMS.					1	H	7	1 	3O			 	A16CE   					 
1996071800024	19960718	00024	GL  	1996	7	18	96ZZZX3436       	3	19960323	G	6111		BLADE           			TCRAFK	D     	DC65TCRAFT  	8850402	EA  						UNIVAC	72	72A         	GL  	PROPELLER	TIP DEPARTED    	G		A		O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	27	36354					4091		A24608E		PROPELLER'S METAL TIPPING BECAME LOOSE AND SEPARATED FROM PROPELLER IN-FLIGHT.  THE SEPARATION WAS DUE TO WOOD DETERIORA	TION.  SUBMITTER RECOMMENDATION:  INSPECT PROPELLER FOR DETERIORATION OF WOOD AND METAL TIPPING OR METAL TIPPING RIVETS 	FOR LOOSENESS.  INDICATION:  DARK STREAKS ALONG PROPELLER DARK LINES ALONG EDGE OF METAL TIPPING.				1	H	7	1 	3O				A746    		5	N	802	 
1996071800025	19960718	00025	EA  	1996	7	18	96ZZZX3437       	2	19960613	G	8540	74996	GEAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					MAG DRIVE	BROKEN          	B	S		CMXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	5109B	7761 				15283750	L1377515			FOUND BROKEN IDLER GEAR IN THE ENGINE THAT DRIVES THE MAGNETO.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996071800026	19960718	00026	SW  	1996	7	18	96ZZZX3438       	1	19960624	G	3230	5286501	DOWNLOCK        			MOONEY	M20   	M20C        	5870208	SW  										MLG	DISENGAGED      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	78981	5703 				2015				DURING GROUND HANDLING AS PLANE WAS BEING PUSHED INTO HANGAR WHEN MAIN GEAR HIT THE HUMP AT HANGAR ENTRANCE, LANDING GEA	R DISENGAGED AND AIRCRAFT SLOWLY SETTLED TO GROUND.  SUSPECT DOWNLOCK NOT PROPERLY ENGAGED.					1	L	7	1 	3O				2A3     					 
1996071800027	19960718	00027	CE  	1996	7	18	96ZZZX3439       	1	19960606	G	8010	S1577A111	CONTACTOR       			CESSNA	182   	TR182       	2072735	CE  										STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	2294R	1527 				R18200584				AFTER A SCHEDULED OIL CHANGE, THE MASTER SWITCH WAS PLACED IN THE 'ON' POSITION FOR STARTING.  AS SOON AS THE MASTER WAS	 TURNED ON, THE STARTER ROTATED THE PROPELLER.  ROTATION OF THE PROPELLER COULD ONLY BE STOPPED BY TURNING THE MASTER SW	ITCH TO THE 'OFF' POSITION.  THE STARTER CONTACTOR ACTIVATION WIRE WAS DISCONNECTED TO CHECK FOR FAULTY SWITCH.  THE PRO	PELLER ROTATION CONTINUED.  IT WAS FOUND THAT THE STARTER CONTACTOR HAD FAILED TO RETURN TO AN 'OPEN' POSITION.			1	H	7	1 	3O				3A13    					 
1996071800028	19960718	00028	CE  	1996	7	18	96ZZZX3440       	1	19960530	G	5720	0823400109	BULKHEAD        			CESSNA	340   	340CESSNA   	2076404	CE  										TIP TANK AFT MT	CRACKED         	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	123KK	5497 				3400251				FOUND TIP TANK MOUNTING BULKHEAD CRACKED.  REPLACED BULKHEAD.  SUBMITTER STATES CRACKING MAY HAVE BEEN CAUSED BY AN UPWA	RD FORCE APPLIED TO AFT END OF TIP TANK.					1	L	7	2 	3O				3A25    					 
1996071800029	19960718	00029	SO  	1996	7	18	96ZZZX3441       	2	19960624	G	8530	648005CP	RING            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					PISTON	BROKEN          	E				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	25	33247					U20602692	553910			TEMPORARY POWER LOSS DURING CRUISE.  SUSPECT CAUSE:  BROKEN PISTON RING WHICH BECAME WEDGED BETWEEN PISTON AND CYLINDER 	WALL.  REPLACED COMPLETE CYLINDER ASSY.					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996071800030	19960718	00030	SO  	1996	7	18	96ZZZX3442       	2	19960212	G	8520		CRANKCASE       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					NR 1-2 CYLINDERS	FAILED          	E		A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	25	4520S	1086 				TH660	287021R			DIPSTICK DEPARTED AIRCRAFT ON FINAL.  MAINTENANCE UNCOWLED ENGINE TO PERFORM COMPRESSION TEST.  ENGINE CRANKCASE HAD ERU	PTED BETWEEN NR 1 AND NR 2 CYLINDER.  BOTH MAGNETOS TORN FROM MOUNTING PADS NR 1 AND NR 2 CYLINDER ROD CAPS AND ROD BOLT	S SHEARED FROM RODS AND 1 COUNTERWEIGHT DETACHED FROM CRANKSHAFT.  SUSPECT CAUSE:  COUNTERWEIGHT PIN FAILURE.  ENGINE MA	NUFACTURER NOTIFED AND REP TO EXAMINE ENGINE TEAR DOWN INSPECTION REQUESTED BY OWNER, OPERATOR, AND MAINTENANCE.			1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996071800031	19960718	00031	SO  	1996	7	18	96ZZZX3443       	2	19960620	G	7322	182022111	SUPPORT         			CESSNA	182   	182R        	2072731	CE  	CONT  	O520  	IO520D      	17032	SO  					THROTTLE BODY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	5442N	85   				18267718				THIS AIRCRAFT IS MODIFIED PER STC SA00152W1 AND THE ITEM IS PART OF THE MODIFICATION.  THE ENGINE QUIT IN-FLIGHT, AND WA	S RESTARTED WITH NO OTHER PROBLEMS.  THE PART WAS FOUND CRACKED IN TWO AND WAS THOUGHT TO CAUSE THE MIXTURE CONTROL TO L	EAN THE MIXTURE BY LETTING THE FUEL CONTROL UNIT SLIP DOWN.  (THIS PROBLEM TOOK PLACE IN MARCH OF '95).				1	L	7	1 	3O	3	O	NT	3A13    	E5CE				 
1996071800032	19960718	00032	SO  	1996	7	18	96ZZZX3444       	2	19960530	G	8520	643202	CRANKCASE       			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520J    	17040	SO  					LT HALF	CRACKED         	B	S		CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	123KK		809  			3400251	509176			ENGINE CRANKCASE WAS FOUND CRACKED FROM THE CRANKCASE THROUGH-BOLT AT CYLINDER NR 2.  THE CASE WAS REPLACED 4-9-95.  THE	 ENGINE CURRENTLY HAS 1,257 HOURS TSO.					1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996071800033	19960718	00033	CE  	1996	7	18	96ZZZX3445       	1	19960613	G	2720	04115261	RUDDER BAR      			CESSNA	150   	152         	2071835	CE  										LT RD PEDAL	BROKEN          	B	S		AKVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	67568	8022 				15281917				LEFT RUDDER PEDAL ATTACHMENT LINK ON RUDDER BAR IS BROKEN.						1	H	7	1 	3O			NT	3A19    					 
1996071800034	19960718	00034	CE  	1996	7	18	96ZZZX3446       	1	19960604	G	3230	128050981	LINE            			CESSNA	210   	T210M       	2073451	CE  										MLG HYD	BROKEN          	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CE	05	7398M					21062018				ON APPROACH TO LAND, PILOT HAD A LANDING GEAR UNSAFE LIGHT INDICATION.  PILOT NOTED THERE WAS NO GREEN LIGHT ILLUMINATED	 TO INDICATE THE LANDING GEAR WAS IN SAFE DOWN AND LOCK CONDITION.  ALSO, AN INTERMITTENT FLICKERING LIGHT FOR THE LANDI	NG GEAR 'UP' POSITION.  AN EMERGENCY LANDING WAS CONDUCTED WITH THE ACFT RECEIVING MINOR DAMAGE TO THE FUSELAGE.  ON EXA	MINATION, FOUND A BROKEN LANDING GEAR HYDRAULIC LINE HAD RESULTED IN THE LOSS OF FLUID AND LANDING GEAR FAILURE.  THIS L	INE WAS REPLACED AND SEVERAL LANDING GEAR RETRACTION TEST OPERATIONS WERE CONDUCTED.		1	H	7	1 	3O				3A21    					 
1996071800035	19960718	00035	SO  	1996	7	18	96ZZZX3447       	1	19960625	G	2913	2720	MOTOR           	GARKENYON   	953801      	PIPER 	PA46  	PA46310P    	7104605	SO  										POWER PACK	FAILED          	B			JAVR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NE	01	9184F	3679 			87	468408068				PILOT ATTEMPTED TO RETRACT LANDING GEAR, BUT HYDRAULIC POWER PACK DID NOT RUN.  NOSE GEAR BECAME UNLOCKED DUE TO RESIDUA	L HYDRAULIC PRESSURE.  FREE FALL WOULD NOT LOCK NOSE GEAR.  SEVERAL MANEUVERS CAUSED NOSE GEAR TO LOCK DOWN.  AIRCRAFT L	ANDED UNEVENTFULLY.  FOUND HYDRAULIC PUMP MOTOR FAILED TO OPERATE.  BRUSH CIRCUIT OPEN IN MOTOR.  MOTOR TO BE REPLACED.				1	L	7	1 	3O				A25SO   					 
1996071800036	19960718	00036	SO  	1996	7	18	96ZZZX3448       	2	19960620	G	7322	182022111	SUPPORT         			CESSNA	182   	182Q        	2072732	CE  	CONT  	O520  	IO520D      	17032	SO  					THROTTLE BODY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	182PG	58   				18266379	293230R			THIS AIRCRAFT IS MODIFIED PER STC SA00152W1 AND THE ITEM IS PART OF THE MODIFICATION.  THIS SUPPORT WAS CRACKED TWO-THIR	DS THE WAY THROUGH; AND, IF HAD BROKEN OFF, WOULD HAVE LET THE FUEL CONTROL UNIT SLIP DOWN AND CAUSE A VERY LEAN MIXTURE	 AND A POSSIBLE ENGINE CUT-OFF.  THE SUPPORT COULD BE REMOVED COMPLETELY OR MADE OF STEEL.				1	H	7	1 	3O	3	O	NT	3A13    	E5CE				 
1996071800037	19960718	00037		1996	7	18	96ZZZX3449       	1	19960523	G	2822	1C1232	PUMP            	AIRBORNE    																FUEL SYSTEM	IMPELLER BROKEN 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	2822				10AC65					MOLDED PLASTIC IMPELLER BROKEN AT ARMATURE 'D' CUT KEYWAY.  SUBMITTER SUGGESTS STRONGER MATERIAL.																			 
1996071800038	19960718	00038		1996	7	18	96ZZZX3450       	1	19960612	G	2752	1015210162	ACTUATOR        																	FLAP	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13					348I89					ACTUATOR APPEARED AS A FRESH OVERHAUL, BUT THE PISTON USED WAS AN INCORRECT PART NUMBER FOR THIS ACTUATOR.  PART NUMBER 	INSTALLED WAS 50-521151-6 AND THE PART NUMBER TO BE USED IS 50-521195-8.																		 
1996071800039	19960718	00039	CE  	1996	7	18	96ZZZX3451       	1	19960516	G	5751	169110000329	DOUBLER         			BEECH 	23    	B23         	1151240	CE  										WING AIL BUSH	WORN HOLE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	6996Q					M1103				BUSHINGS 169-110000-347 FELL OUT OF DOUBLER WHEN LOOSE AILERONS REMOVED.  NEW PARTS FOR MANUFACTURER FOUND TO HAVE A VER	Y LOOSE INTERFERENCE FIT BETWEEN BUSHING AND DOUBLER.  THIS COULD RESULT IN SAME PROBLEM IN A SHORT TIME.					1	L	7	1 	3O				A1CE    					 
1996071800040	19960718	00040	CE  	1996	7	18	96ZZZX3452       	1	19960611	G	3260	010A391173	DRAG STRUT      			MTSBSI	MU2   	MU2B25      	5780409	CE  										NLG	MISINSTALLED    	B		A	SH5R	O				OTHER                   				W			INADEQUATE Q C            			LD	LANDING        	1			NE	03	728FN					303				DURING LANDING, THE NLG COLLAPSED RESULTING IN SKIN DAMAGE.  INVESTIGATION REVEALED THAT DURING NLG REASSEMBLY, 50 HOURS	 PRIOR TO THIS INCIDENT, THE NOTED COMPONENTS WERE INSTALLED ON THE WRONG SIDES.  THE DASH NUMBERS WERE NOT READABLE ON 	THE PARTS.  THE MAINTENANCE MANUAL DOES NOT MAKE MENTION OF CORRECT POSITIONS FOR THESE COMPONENTS.  SB 200A DOES IDENTI	FY THE PARTS RELATIVE TO INSTALLATION POSITION, HOWEVER, DURING ROUTINE MAINTENANCE, THE SB WOULD NOT BE USED.			1	H	7	2 	3T				A2PC    					 
1996071800041	19960718	00041	CE  	1996	7	18	96ZZZX3453       	1	19960410	G	3297		WIRE            			CESSNA	500   	500CESSNA   	2076602	CE  										MLG INTRANSIT	BROKEN          	B			OS5D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	9AX	4127 				5000016				DURING PHASES 1-4, FOUND GEAR INTRANSIT LIGHT INOPERATIVE.  TROUBLESHOT SYSTEM, FOUND OPEN AT LIGHT AND FORWARD CONNECTO	R PLUGS.  TRACED POWER ROUTING AFT AND FOUND BROKEN WIRE AT AFT BULKHEAD CONNECTOR (P-48).  REPAIRED BROKEN WIRE.  FINAL	 OPERATIONAL CHECK FOUND SATISFACTORY.				1	L	7	2 	4F			 	A22CE   					 
1996071800042	19960718	00042	CE  	1996	7	18	96ZZZX3454       	1	19960410	G	5320	551123924	ANGLE           			CESSNA	500   	500CESSNA   	2076602	CE  										STEP ATTACH	CRACKED         	B	S		OS5D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	9AX	4127 				5000016				DURING A PHASE 1-4 INSPECTION, FOUND THE CABIN DOOR FRAME CRACKED AT LOWER STEP HINGE ATTACHMENT AT 2 PLACES.						1	L	7	2 	4F				A22CE   					 
1996071800043	19960718	00043	SO  	1996	7	18	96ZZZX3455       	1	19960610	G	3241	4215919NC	CIRCUIT BOARD   			LKHEED	1329  	1329        	5263102	SO  										ANTI SKID CONT	FAILED          	B		A	AN3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	74AG					5072				THE CIRCUIT BOARD MAINTENANCE RELEASE TAG WAS IDENTIFIED WITH PN 42-15919NL, SN 351, ACTUAL UNIT WAS IDENTIFIED WITH PN 	42-15919NL, SN 341.  AFTER CIRCUIT BOARD WAS INSTALLED IN CONTROL BOX, IT WAS FOUND DURING SYSTEM CHECK-OUT THAT BOARD H	AD A HARD FAILURE.				2	L	7	4 	4J				2A15    					 
1996071800044	19960718	00044	NM  	1996	7	18	96ZZZX3456       	1	19960628	G	2121	13863352	BEARING         	SUNDSTRANDEM	5007024620  	BOEING	727   	727         	1384001	NM  										FAN MOTOR SHAFT	ROUGH           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1279 			AA81653					BEARING SHIELD PARTIALLY DISLODGED AND THERE WAS NO GREASE PRESENT.  BEARING OPERATES ROUGH, CAUSED FAILURE OF FAN.						2	L	7	3 	4F				A3WE    					 
1996071800045	19960718	00045		1996	7	18	96ZZZX3457       	4	19960627	G	3418	170315	TRANSDUCER      	SAFEFLIGHT  	170315      	GULSTM	560   	560         	0141402	SW  										AOA	OUT OF CALIB    	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	611ST	1611 			242	5600123				COMPARING AOA TRANSDUCER VANE WITH SISTER ACFT, FND VANE TRAVEL SUSPECT.  CHECKED WITH ELEC PROTRACTOR, FND TRANSDUCER O	UT OF CALIBRATION.  INTERNAL STOPS HAD MOVED.  ON PRE-FLIGHT, PILOT'S AOA ROTARY TEST WITH POWER ON ACFT SYS TESTS OK. S	TICK SHAKER, IND, LIGHTS, BUT TEST DOES NOT INCLUDE TRANSDUCER.  IF VANE IS OUT OF CALIBRATION, THERE ARE EXTERNAL LIMIT	 MARKS TO CHECK VISUALLY.  ACFT FLEW OK WITH NO INDICATION OF PROBLEM AS CREW NEVER FLEW ACFT BELOW REF.  SUBMITTER STAT	ED THIS TRANSDUCER NEEDS AN EXTERNAL INDEX TO CHECK VANE FOR PROPER TRAVEL LIMIT.  THIS SHOULD BE A GO-NO-GO ITEM.		1	H	7	2 	3O				6A1     					 
1996071800049	19960718	00049	SW  	1996	7	18	96ZZZX3460       	1	19960507	G	6230	206040078103	NUT             		206040014103	BELL  	206   	206L3       	1182108	SW  										MAST BEARING	LOST TORQUE     	B		A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	343AL	4965 	990  			51372				WHEN REMOVING SWASHPLATE, MECHANIC FOUND NUT TO HAVE LOST TORQUE.  (HAND TIGHT.)  HAVE FOUND SEVERAL MAST NUTS ON 206L-3	'S AND 206L-4'S MAST ASSEMBLIES THAT HAVE LOST TORQUE.  BELIEVE THE CONTACT AREA BETWEEN THE MAST NUT AND THE BEARING IN	NER RACE IS TOO SMALL.  THE 206B AND 206L-1 MAST NUTS HAVE A LARGER CONTACT AREA AND DO NOT CAUSE A PROBLEM.  MODIFY MAS	T NUT FOR GREATER CONTACT AREA.			1	G	7	1 	3U				H2SW    					 
1996071800050	19960718	00050	EU  	1996	7	18	96ZZZX3461       	1	19960628	G	6310	4638202007	CLUTCH          		4638001004  	BOLKMS	105   	BO105CBS    	5626008	EU  										FREEWHEEL	FAILED          	B		A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5412J	1927 	447  		3200	S784				WHEN THROTTLES WERE CLOSED FOR SHUT DOWN, NR 2 ENGINE'S N2 NEEDLE ON TRIPLE TACH WAS OBSERVED TO REMAIN WITH THE ROTOR N	EEDLE DURING COAST DOWN WHILE NR 1 ENGINE'S N2 NEEDLE SPLIT AND DECELERATED NORMALLY.  FOUND NR 1 FWU CLUTCH LOCKED UP I	N EITHER DIRECTION (NO FREEWHEELING CAPABILITY).  REMOVED RIGHT FWU, FOUND CLUTCH BROKEN IN SEVERAL PIECES.				1	G	7	2 	3U			NC	H3EU    					 
1996012600424	19960126	00424	SO  	1996	1	26	96ZZZX348        	1	19960104	G	3240	4030103	BRAKE ASSY      		403017502   	GULSTM	AA5   	AA5         	0631410	SO  										LT MLG	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	07	5893L					AA50093				PILOT ATTEMPTED TO LAND.  LEFT BRAKE WAS SOFT CAUSING AIRCRAFT TO SWERVE OFF RUNWAY AND HIT VASI BOARDS.  DAMAGE TO RIGH	T WING AND AILERON.					1	L	7	1 	3O				A16EA   					 
1996071800106	19960718	00106	NE  	1996	7	18	96ZZZX3484       	1	19960610	G	6210	7615009100051A	BLADE SPAR      			SKRSKY	S76   	S76A        	8143006	NE  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL	4015 	480  		A08601314	760002				DISCOVERED DURING 500-HOUR INSPECTION, BLADE SPAR CRACKED AT ROOT END BUSHING HOLE.						1	G	7	2 	3U				H1NE    					 
1996071800107	19960718	00107	SW  	1996	7	18	96ZZZX3485       	1	19960618	G	7120	214060211101	BEARING         		214060209101	BELL  	214   	214ST       	1182106	SW  										ENGINE AREA	CHAFED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	391AL					28103				UNSCHEDULED MAINTENANCE, ENGINES REMOVED TO FACILITATE SHEET METAL REPAIRS TO LONGERON.  FOUND BEARING BODY CHAFED BOTH 	SIDES BY CLEVIS.					2	G	7	2 	4U				H10SW   					 
1996071800108	19960718	00108	GL  	1996	7	18	96ZZZX3486       	2	19960531	G	7323	2523240	BEARING         		23007505    	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20      	03013	GL  					FLYWEIGHTS	FROZEN          	B		A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107AL	1447 				S772				DURING TEAR DOWN INVESTIGATION OF UNIT, FOUND 2523240 BEARINGS FROZEN CAUSING FLYWEIGHTS TO STICK.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996071800109	19960718	00109	SW  	1996	7	18	96ZZZX3487       	1	19960517	G	5302	206032308103S	FRAME           			BELL  	206   	206L3       	1182108	SW  										TAILBOOM	DEFECTIVE       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	366AL					51470				DURING REPLACEMENT OF PART DUE TO WEAR, FOUND EDGE DISTANCE AT HIGH SHEER INSTALLATION POINT TOO SHALLOW.						1	G	7	1 	3U				H2SW    					 
1996072300001	19960723	00001	SW  	1996	7	23	96ZZZX3512       	1	19960614	G	7120	NAS627	BOLT            	LORD        	LM600SA9    	SWRNGN	SA227 	SA227TT     		SW  										ENGINE MOUNT	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	900AK					TT424				DURING SCHEDULED INSPECTION, FOUND ENGINE SIDE MOUNT ISOLATOR THROUGH-BOLTS NOT PROPERLY ENGAGING LOCKING DEVICE IN TRUS	S.  VENDOR (LORD) SPECIFIES NAS627-H46 BOLT WITH .090 INCH BY 1.5 INCH WASHER, FAIRCHILD SPECIFIED NAS627-50 BOLT WITH A	PPROXIMATELY .075 INCH BY .812 INCH WASHER.  COMBINATION OF SHORTER BOLT WITH THICKER WASHER REDUCES EFFECTIVE LENGTH OF	 BOLT BY .265 INCH DUE TO VARIANCE IN WASHER THICKNESS.  HAVE SEEN AS MUCH AS .300 INCH DIFFERENCE.  THIS IS ON AIRCRAFT	 WITH HEAVY TRUSS 27-62078-231.  IF BOLT HEAD HAS SAFETY WIRE HOLE, LOOK CLOSER, ITS THE WRONG BOLT.		2	L	7	2 	4T			RT	A5SW    					 
1996071800206	19960718	00206	CE  	1996	7	18	96ZZZX3513       	1	19960410	G	5551	5532000	STABILIZER      			CESSNA	500   	500CESSNA   	2076602	CE  										FWD ATTACH	BOLTS LOOSE     	B			OS5D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	9AX	4127 				5000016				WHILE REMOVING THE HORIZONTAL STABILIZER TO FACILITATE REPAIRS, NOTED THAT 6 OF THE 8 FORWARD ATTACH BOLTS WERE LOOSE. T	WO OF THE SPACERS USED BETWEEN THE VERTICAL AND HORIZONTAL ATTACHMENT SHOWED SIGNS OF RUBBING.  SUBMITTER RECOMMENDS THA	T A ONE-TIME INSPECTION OF THE FORWARD AND AFT ATTACH BOLTS BE CHECKED FOR PROPER TORQUE.				1	L	7	2 	4F				A22CE   					 
1996071800207	19960718	00207	CE  	1996	7	18	96ZZZX3514       	1	19960410	G	5510	553200019	STRINGER        			CESSNA	500   	500CESSNA   	2076602	CE  										HORIZ STAB	BENT            	B			OS5D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	9AX	4127 				5000016				WHILE PERFORMING A PHASE 1-4 INSPECTION, NOTICED TOP CENTER SKIN OF THE HORIZONTAL STABILIZER WAS BUCKLED BEYOND LIMITS 	AS STATED IN THE SRM.  WHEN SKIN WAS REMOVED FOR REPLACEMENT, A HIDDEN DAMAGE INSPECTION REVEALED UPPER AFT STRINGER WAS	 ALSO BENT AND DISTORTED.  REMOVED AND INSTALLED NEW CENTER SKIN (UPPER) AND UPPER AFT STRINGER.				1	L	7	2 	4F				A22CE   					 
1996071800208	19960718	00208	CE  	1996	7	18	96ZZZX3515       	1	19960410	G	5512	553200063	SKIN            			CESSNA	500   	500CESSNA   	2076602	CE  										HORIZ STAB TOP	BUCKLED         	B			OS5D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	9AX	4127 				5000016				WHILE PERFORMING A PHASE 1-4 INSPECTION, NOTICED TOP CENTER SKIN OF THE HORIZONTAL STABILIZER WAS BUCKLED BEYOND LIMITS 	AS STATED IN THE SRM.  WHEN SKIN WAS REMOVED FOR REPLACEMENT, A HIDDEN DAMAGE INSPECTION REVEALED UPPER AFT STRINGER WAS	 ALSO BENT AND DISTORTED.  REMOVED AND INSTALLED NEW CENTER SKIN (UPPER) AND UPPER AFT STRINGER.				1	L	7	2 	4F				A22CE   					 
1996071800209	19960718	00209	CE  	1996	7	18	96ZZZX3516       	1	19960626	G	7920		LINE            			BEECH 	300   	300BEECH    	1152930	CE  										TORQUE MANIFOLD	LOOSE           	G				A				UNSCHED LANDING         				Y	K		ENGINE STOPPAGE           	FLUID LOSS                		NR	NOT REPORTED   	1			GL	03	1250					FA88				OIL LINE CAME LOOSE AT TORQUE MANIFOLD LINE.  ENGINE SHUT DOWN.  AIRCRAFT LANDED WITHOUT INCIDENT.  LEFT OIL LINE TIGHTE	NED AT TORQUE MANIFOLD.  NO FURTHER PROBLEMS NOTED.					2	L	7	2 	4T				A24CE   					 
1996071800210	19960718	00210	NM  	1996	7	18	96ZZZX3517       	1	19960601	G	5320		WEB             			BOEING	727   	7272J7      	138400E	NM  										FS 560-620	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-CHECK INSPECTION, INTERGRANULAR CORROSION WAS NOTED ON FORWARD BAG PIT LOWER SILL CUT-OUT WEB.  FROM STA 560 TO	 STA 620, LOCATED AT S26R.					2	L	7	3 	4F				A3WE    					 
1996071800211	19960718	00211	NM  	1996	7	18	96ZZZX3518       	1	19960601	G	5320		FITTING         			BOEING	727   	7272J7      	138400E	NM  										FS 570 S26R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-CHECK INSPECTION, NOTED THE SECOND FROM FRONT TIE-DOWN MOUNT FITTING HAD INTERGRANULAR CORROSION AT STA 570 AND	 STA S26R.					2	L	7	3 	4F				A3WE    					 
1996071800212	19960718	00212	NM  	1996	7	18	96ZZZX3519       	1	19960601	G	5320		FITTING         			BOEING	727   	7272J7      	138400E	NM  										FS 560 S26R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-CHECK INSPECTION, NOTED THE FORWARD TIE-DOWN MOUNT FITTING HAD INTERGRANULAR CORROSION AT STA 560, AT S26R.						2	L	7	3 	4F				A3WE    					 
1996012600428	19960126	00428		1996	1	26	96ZZZX352        	4	19960103	G	2562	7103	SWITCH          	LEIGH       	7A1140      	CESSNA	182   	182P        	2075816	CE  										G-SWITCH	FAILED          	B			YXUR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	07	58823	2921 			21243	18262321				ELT G-SWITCH FAILED CRASH TEST IN ARM POSITION.  CHECKED OK IN 'ON' POSITION.						1	H	7	1 	3O			NT	TA13    					 
1996071800213	19960718	00213	NM  	1996	7	18	96ZZZX3520       	1	19960601	G	5314		KEEL STRINGER   			BOEING	737   	737212      	1384461	NM  										FS 727A S27L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	161FN					20521				DURING C-4 CHECK, CORROSION WAS NOTED ON KEEL STRINGER S27L.						2	L	7	2 	4F				A16WE   					 
1996071800214	19960718	00214	NM  	1996	7	18	96ZZZX3521       	1	19960601	G	5320		SHEAR TIE       			BOEING	737   	737212      	1384461	NM  										FS 727A S27L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	161FN					20521				DURING C-4 CHECK, CORROSION WAS NOTED ON SHEAR TIE STA 727A AT S27L.						2	L	7	2 	4F				A16WE   					 
1996071800215	19960718	00215	CE  	1996	7	18	96ZZZX3522       	1	19960524	G	5720	552281063	STIFFENER       			CESSNA	500   	550         	2076604	CE  										WING FLAPWELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26496	3286 				5500607				THIS PART HAS BEEN FOUND CRACKED IN EACH OF FOUR 550'S.  THE CRACKS ARE LOCATED ON THE FLANGES OF THE STIFFENER AND ARE 	VERY MINUTE.  SUBMITTER STATED NOT SURE WHAT THE CAUSE OF THESE CRACKS ARE, THEY ARE ALL IN THE SAME LOCATION AND CAN BE	 SEEN BY LOOKING UP ABOVE THE FLAP INBOARD BELLCRANK.  REF:  SEE CESSNA PARTS ILLUSTRATED 57-20-05, FIGURE 01, ITEM 26.				1	L	7	2 	4F				A22CE   					 
1996071800216	19960718	00216	NE  	1996	7	18	96ZZZX3523       	2	19960611	G	7230		COMPRESSOR      			RKWELL	NA265 	NA26540     	6402608	CE  	PWA   	JT12  	JT12A8      	52042	NE  					ENGINE	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	317NT	10605	322  			282100	P637622NB			COMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT.  INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND.  T	HIS IS A MULTI-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT.  NO FOD NOTED	 AND NO DAMAGE OR DEFECTS NOTED IN TURBINE HOT SECTION.  ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL.				2	L	7	2 	4J	4	J		A2WE    	1E9				 
1996071800217	19960718	00217	NM  	1996	7	18	96ZZZX3524       	1	19960601	G	5312		CHORD           			BOEING	727   	727243      	138408D	NM  										FS 950 S29R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	34415					22167				DURING C-10 CHECK, CORROSION WAS NOTED ON THE 950 BULKHEAD LOWER CHORD AT S29R.						2	L	7	3 	4F			RT	A3WE    					 
1996071800218	19960718	00218	NM  	1996	7	18	96ZZZX3525       	1	19960528	G	5315		FLOOR BEAM      			BOEING	727   	727243      	138408D	NM  										FS 1130 BL 24RT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	34415					22167				EXFOLIATION CORROSION AT END OF SEAT TRACK FLOOR BEAM BL 24.75 RT WHERE IT ATTACHES TO STA 1130, FRAME RT.						2	L	7	3 	4F			RT	A3WE    					 
1996071800219	19960718	00219	SO  	1996	7	18	96ZZZX3526       	1	19960301	G	4990	37344420	GEAR ASSY       	GARRTT      	CTCP85291E  	LKHEED	188   	188C        	5262604	SO  										OIL PASSAGE	FAILED          	B		A	A12R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21					P25816					THE MATING SURFACE OF THE APU FIRST STAGE COMPRESSOR INLET HOUSING AND PLANETARY GEAR ASSY HAVE A RECESSED OIL PASSAGE T	O LOCATE A PACKING TO SEAL THE OIL PASSAGE.  THE S9412-012 PACKING WAS INSTALLED WRONG OR SHRUNK AND WAS COVERING THE OI	L PASSAGE.  OIL STARVATION TO THE PLANETARY GEAR ASSY IS SUSPECTED FOR THE FAILURE.  THIS COULD BE PREVENTED BY USING AL	IGNMENT STUD TO HOLD ALIGNMENT WHILE INSTALLING.			2	L	7	4 	4T				4A22    					 
1996071800220	19960718	00220	EA  	1996	7	18	96ZZZX3527       	2	19960628	G	7414	M3006	BEARING         	SLICK       	4270        	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					RT MAG	ROUGH           	H				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			EA	01	92595	200  			89020072	17261591				ENGINE SUDDENLY BECAME ROUGH.  MAG CHECK INDICATED TROUBLE WITH RIGHT MAG, FLIGHT CONTINUED ON SINGLE MAG.  OPERATION - 	AT TERMINATION OF FLIGHT, MAGS RE-CHECKED.  RT MAG DEAD; OPENING UP MAG REVEALED 'BEARING' GREASE IN MAG HOUSINGS.  COIL	 APPEARED INTACT, BUT DID NOT CHECK OUT.  FRONT BEARING HAD 'ROUGH SPOTS'.  TOTAL TIME SINCE NEW, 200 HOURS.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996071800221	19960718	00221	EA  	1996	7	18	96ZZZX3528       	2	19960628	G	7414	M3525	COIL            	SLICK       	4270        	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					RT MAG	FAILED          	H				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			EA	01	92595	200  			89020072	17261591				ENGINE SUDDENLY BECAME ROUGH.  MAG CHECK INDICATED TROUBLE WITH RIGHT MAG, FLIGHT CONTINUED ON SINGLE MAG.  OPERATION - 	AT TERMINATION OF FLIGHT, MAGS RE-CHECKED.  RT MAG DEAD; OPENING UP MAG REVEALED 'BEARING' GREASE IN MAG HOUSINGS.  COIL	 APPEARED INTACT, BUT DID NOT CHECK OUT.  FRONT BEARING HAD 'ROUGH SPOTS'.  TOTAL TIME SINCE NEW, 200 HOURS.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996071800222	19960718	00222	EA  	1996	7	18	96ZZZX3529       	2	19960619	G	8520		CRANKCASE       			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					NR 2 CYLINDER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	75340		1000 			28R7635292	RL1019351A			DURING 100-HOUR INSPECTION, THE CRANKCASE WAS FOUND CRACKED (2 INCHES).  THIS WAS THE SAME CRACK THAT WAS FOUND 2 YEARS 	AGO WHEN THE ENGINE HAD 1,500 HOURS TSMO.  THE CASE HALVES WERE REPLACED AND NOW 1,000 HOURS LATER, THE SIMILAR CRACK HA	S RE-APPEARED.  SUSPECT VIBRATION PROBLEM.				1	L	7	1 	3O	3	O		2A13    	1E10				 
1996012600429	19960126	00429	CE  	1996	1	26	96ZZZX353        	1	19960102	G	2810		CAP             			CESSNA	182   	182P        	2075816	CE  										FUEL TANK	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	91186					18261964				REPLACED DEFECTIVE STOCK GAS CAPS WITH MONARCH AIR AND DEV. CO., INC.'S CAPS.						1	H	7	1 	3O			NT	TA13    					 
1996071800223	19960718	00223		1996	7	18	96ZZZX3530       	1	19960611	G	2432	2N5156	TRANSISTOR      	JET         	PS823       															EMERG PWR SUPPLY	DEFECTIVE       	B		A	JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09										INVESTIGATION OF USERS COMPLAINT OF EMERGENCY POWER SUPPLY UNITS NOT HOLDING CAPACITY, REVEALED LOW RESISTANCE VALUES BE	TWEEN COLLECTOR AND EMITTER OF THE ISOLATION/SWITCHING TRANSISTOR.  THE DEFECT IS BELIEVED TO BE THE REASON FOR LOW CAPA	CITY OF THE POWER SUPPLY UNITS.  THE POWER SUPPLY IS USED FOR EMERGENCY POWER FOR FLIGHT GYROS, ETC.  RECENTLY, 30 OF 54	 NEW FROM STOCK TRANSISTORS WERE FOUND DEFECTIVE.																 
1996071800224	19960718	00224	GL  	1996	7	18	96ZZZX3531       	3	19960626	G	6114		HUB             			CESSNA	150   	150L        	2071826	CE  						MCAULY	1A100	1A100MCM    	GL  	PROPELLER	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										PROPELLER WAS REMOVED IN ORDER TO STRIP AND PAINT.  FOUND VERY HEAVILY CORRODED INSIDE OF THE CENTER HUB HOLE, 360 DEGRE	ES ALL THE WAY AROUND.  SOME PITS WERE .080 INCH - .090 INCH DEEP OR MORE.  THERE WAS NO OTHER CORROSION FOUND ANYWHERE 	ELSE ON THE PROPELLER.				1	H	7	1 	3O				3A19    		5	N	P918	 
1996071800225	19960718	00225		1996	7	18	96ZZZX3532       	4	19960626	G	2562	7A1142	ELT             	NARCO       	SHARC7      	CESSNA	150   	150L        	2071826	CE  										G-SWITCH	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					23317					DURING ANNUAL INSPECTION, ELT WAS FUNCTION TESTED.  SWITCHING UNIT TO ON, IT WOULD OPERATE FINE.  HOWEVER, UNIT COULD NO	T BE ACTIVATED BY THE BUMP TEST.  SUBMITTER STATED THIS IS ABOUT THE 4TH UNIT IN THE LAST YEAR THAT COULD NOT PASS THIS 	TEST, ALL BEING THIS SAME MODEL.  SENT UNIT TO MANUFACTURER FOR REPAIR.				1	H	7	1 	3O				3A19    					 
1996071800226	19960718	00226	GL  	1996	7	18	96ZZZX3533       	3	19960601	G	6114	D4883C55	HUB             			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	D2AF34C*    	GL  	PROPELLER	CRACKED         	B			MFNY	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	33	IEGEB	1272 	175  					791916		PROPELLER WAS SENT FOR INSPECTION BECAUSE RED OIL COMES OUT FROM THE HUB.  THE REASON, THERE WAS A CRACK ON THE LOWER SI	DE OF THE HUB IN THE AREA OF THE THREAD.					1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1996071800227	19960718	00227	CE  	1996	7	18	96ZZZX3534       	1	19960601	G	3213	508100324	TORQUE KNEE     			BEECH 	80    	65A808800   		CE  										UPPER LT MLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	134BA					LD202				WHILE INSPECTING THE LEFT MLG AREA DURING A ROUTINE INSPECTION, NOTED UPPER TORQUE KNEE WAS CRACKED IN TWO PLACES.  SUBM	ITTER STATED IF GONE UNNOTICED, IT COULD HAVE RESULTED IN THE LOSS OF THE LOWER STRUT ASSY AND SERIOUS DAMAGE TO AIRCRAF	T.  TOTAL TIME ON PART APPROXIMATELY 7,509 HOURS.  A POSSIBLE RECOMMENDATION WOULD BE FOR A CLOSER EXAMINATION OF THE ML	G AREAS DURING PRE-FLIGHT INSPECTION.			1	L	7	2 	3O				3A20    					 
1996071800228	19960718	00228	SW  	1996	7	18	96ZZZX3535       	1	19960702	G	8120	60051004	HOUSING         	ROTOMASTER  	3AT6EE10J2  	MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360GB   	17025	SO  					TURBO	CRACKED         	B		A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	123VW				222449	250447	309450			SUBMITTER RECOMMENDS THAT ROTO-MASTER TURBINE HOUSING P/N 600510-04 (TCM P/N 643931) BE ADDED TO ROTO-MASTER AD 82-27-03	.  AD 82-27-03 STATES THIS INSPECTION MAY BE DISCONTINUED WITH THE INSTALLATION OF P/N 600510-04, BUT SUBMITTER HAS FOUN	D THIS TURBINE HOUSING TO BE CRACKING IN THE SAME AREAS SHOWN IN FIGURE 2 OF AD 82-27-03.				1	L	7	1 	3O	3	O		2A3     	E9CE				 
1996071800229	19960718	00229	EA  	1996	7	18	96ZZZX3536       	2	19960702	G	8530		VALVE           			GULSTM	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320E2G     	41508	EA  					NR 4 CYL INT	BLOCKED OPEN    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	26390	1961 				AA5A0557	L4583127A			ON INITIAL RUN-UP AFTER INSTALLING ENGINE AFTER MAJOR OVERHAUL, ENGINE WAS RUN AROUND 5 MINUTES AT 1,000-1,200 RPM'S.  E	NGINE RPM WAS INCREASED TO 1,700 FOR MAG CHECK.  THE ENGINE STARTED TO RUN EXTREMELY ROUGH.  ENGINE WAS SHUT DOWN.  COMP	RESSION CHECK SHOWED ZERO COMPRESSION ON NR 4 CYLINDER.  FURTHER INSPECTION WAS CONDUCTED AND AN OBJECT WAS FOUND LODGED	 BETWEEN THE VALVE GUIDE BOSS AND THE VALVE WHICH HELD IT OPEN.  IT APPEARED TO BE A ROUND SAND CAST ROD OF ALUMINUM.			1	L	7	1 	3O	3	O		A16EA   	E274				 
1996071800230	19960718	00230		1996	7	18	96ZZZX3537       	4	19960613	G	6113	D5540	BULKHEAD        			BEECH 	33    	F33A        	1151425	CE  										PROP SPINNER	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	3144M	1382 				CE1206				SPINNER BULKHEAD IS CRACKED IN 6 PLACES, EACH AROUND THE PROPELLER ATTACH BOLT HOLES.						1	L	7	1 	3O				3A15    					 
1996071800231	19960718	00231	CE  	1996	7	18	96ZZZX3538       	1	19960522	G	3230	50450101	TORQUE TUBE     			CESSNA	401   	401         	207590C	CE  										LT MLG	CRACKED         	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CE	05	401RW	3902 				401118				LEFT MAIN FAILED TO RETRACT.  TORQUE TUBE WAS FOUND TO HAVE A SPIRAL CRACK STARTING AT THE TOP BY THE BOLT, P/N 5243518-	3, AND TRAVELING AROUND THE TUBE AND TOWARD THE END OF THE TUBE.					1	L	7	2 	3O				A7CE    					 
1996071800232	19960718	00232	CE  	1996	7	18	96ZZZX3539       	1	19960626	G	2810		CAP             			CESSNA	182   	182P        	2075816	CE  										WING TANK	WATER LEAK      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	52876	1250 				18262918				THIS AIRCRAFT HAS HAD A LONG HISTORY OF WATER IN THE FUEL.  AD 84-10-01 ADDRESSES HOW TO DETERMINE HOW MUCH WATER AN AIR	CRAFT WILL OR IS HOLDING, BUT DOES NOT SOLVE THE PROBLEM.  NEW 'ZERO' RING (SEVERAL SETS) DID NOT HELP.  WATER STILL SEE	PED IN AROUND THE CAP.  NEW CAPS AND PANELS FROM MONARCH AIR DEVELOPMENT WERE INSTALLED PER THEIR STC AND NO MORE WATER 	IN THE TANKS.			1	H	7	1 	3O			NT	TA13    					 
1996071800233	19960718	00233	CE  	1996	7	18	96ZZZX3540       	1	19960621	G	6121	SP105B	CONTROL BOX     			CESSNA	340   	340A        	2076405	CE  										PROP SYNC	SHORTED         	D				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SO	03	6221C	3420 				340A0426				DURING CRUISE FLIGHT, SMOKE FILLED THE CABIN.  ELECTRICAL POWER WAS TURNED OFF.  SMOKE CLEARED FROM CABIN.  INVESTIGATIO	N REVEALED THE PROPELLER SYNCROPHASER CONTROL BOX HAD SHORTED AND EMITTED SMOKE.  THE NUTS THAT HOLD THE CANNON PLUG PIN	S HAD VIBRATED OFF AND SHORTED THE CIRCUIT BOARD.				1	L	7	2 	3O				3A25    					 
1996071800234	19960718	00234	SO  	1996	7	18	96ZZZX3541       	1	19960610	G	7160	BA4101	GASKET          	BRACKETT    	BA4106      	PIPER 	PA22  	PA22150     	7102210	SO  										AIR FILTER	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	25	9721D	14   				226638				GASKET SOFT AND CAME APART WHEN TOUCHED.  AIRCRAFT USES AUTOGAS AND WHEN MANUFACTURER CALLED, THEY SAID THEY NEVER CHECK	 THE GASKETS WITH AUTO FUEL AND DID NOT KNOW ANYTHING ABOUT WHAT IT WOULD DO.  THIS WAS FOUND WHILE C/W WITH AD 96-09-06	.  SUBMITTER SUGGESTS ANY FILTER USED WITH AUTO FUEL BE CHECKED AS SOON AS POSSIBLE.				1	H	7	1 	3O				1A6     					 
1996071800235	19960718	00235	SO  	1996	7	18	96ZZZX3542       	1	19960619	G	5513	6358500	TRIM TAB        			PIPER 	PA28  	PA28R200    	7102811	SO  										LT STABILIZER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	75340					28R7635292				DURING 100-HOUR INSPECTION, THE TRIM TAB WAS DISCONNECTED TO ACCOMMODATE REPLACEMENT OF TRIM BARREL HARDWARE, THE TRIM T	AB WAS FOUND CRACKED; UNDER THE ATTACH BRACKET, AT THE EDGE OF THE ATTACH BRACKET, INTO THE SUPPORTING RIBS, AND ON BOTH	 LEFT AND RIGHT TRIM TABS.				1	L	7	1 	3O				2A13    					 
1996071800236	19960718	00236	SO  	1996	7	18	96ZZZX3543       	1	19960619	G	5513	6358501	TRIM TAB        			PIPER 	PA28  	PA28R200    	7102811	SO  										RT STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	75340					28R7635292				DURING 100-HOUR INSPECTION, THE TRIM TAB WAS DISCONNECTED TO ACCOMMODATE REPLACEMENT OF TRIM BARREL HARDWARE, THE TRIM T	AB WAS FOUND CRACKED; UNDER THE ATTACH BRACKET, AT THE EDGE OF THE ATTACH BRACKET, INTO THE SUPPORTING RIBS, AND ON BOTH	 LEFT AND RIGHT TRIM TABS.				1	L	7	1 	3O				2A13    					 
1996071800237	19960718	00237	CE  	1996	7	18	96ZZZX3544       	1	19960617	G	2434		PULLEY          	FORD        	DOFF10300   	CESSNA	206   	U206        	2073306	CE  										ALTERNATOR	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	8013Z				A85562	U2060413				DRIVE PULLEY FOUND SEPARATED FROM VENT FAN DURING UNSCHEDULED MAINTENANCE.  ALTERNATOR, 386.7 HOURS SINCE OVERHAUL.  PUL	LEY TIME UNKNOWN.  CORROSION EVIDENT ON MATING SURFACES OF DETACHED PIECES.					1	H	7	1 	3O				A4CE    					 
1996071800238	19960718	00238	SW  	1996	7	18	96ZZZX3545       	1	19960610	G	5210	206033636009	HINGE HALF      			BELL  	206   	206L1       	1182107	SW  										PASSENGER DOOR	LOOSE           	B			QEVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	5753T	5837 				45547				UPON DAILY INSPECTION OF AIRCRAFT, RIGHT PASSENGER DOOR LOWER HINGE FOUND LOOSE.  AFT 2 CHERRY LOCK RIVETS PULLED THROUG	H DOOR STRUCTURE WITH INDICATION OF PAINT MISSING AROUND AREA.  SUSPECT CAUSE OF PROBLEM - DOORS NOT SECURED PROPERLY UN	DER WINDY CONDITIONS ALLOWING DOOR TO OVERTRAVEL HINGE CAUSING EXCESSIVE PULL ON REAR RIVETS PULLING THROUGH DOOR STRUCT	URE.  SUBMITTER RECOMMENDED REPLACING RIVETS WITH 2 AN525-1032-R10 STRUCTURAL SCREWS WITH AN960-1032 WASHERS AND NAS 129	1-3 NUTS FOR GREATER STRENGTH AND MORE SURFACE CONTACT WITH DOOR AND SECURE DOOR PROPERLY IN WINDY CONDITIONS.		1	G	7	1 	3U				H2SW    					 
1996071800239	19960718	00239	NE  	1996	7	18	96ZZZX3546       	1	19960614	G	5280	7620902019045	FITTING         			SKRSKY	S76   	S76B        	8143007	NE  										LT MLG DOOR	FAILED          	G		A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			NE	03	9UT	2041 				760379				LEFT MAIN GEAR DOOR LINK ATTACH FITTING FAILED DURING GEAR EXTENSION ON LANDING.  COMPONENT HAS A HISTORY OF FAILURE AND	 MANUFACTURER HAS AN IMPROVED DASH 048 REPLACEMENT.  THE PART HAS BEEN REDESIGNED TO BE STRUCTURALLY LARGER.  THE ARICRA	FT HAS BEEN FITTED WITH THE DASH 048 FITTINGS AND RETURNED TO SERVICE.  SUBMITTER SUGGESTS OPERATORS OF THIS AIRCRAFT WI	TH DASH 045 FITTINGS INSTALLED CONTACT MANUFACTURER FOR AVAILABILITY OF REPLACEMENT PARTS, AT THEIR CONVENIENCE.			1	G	7	2 	4U				H1NE    					 
1996071800415	19960718	00415	EU  	1996	7	18	96ZZZX3547       	1	19960601	G	2720		STOP            			TRNSQP	KR03A 	KR03A       	1130847	EU  										RUDDER STOP	BROKEN          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	210C					0315				EXAMINATION OF THE RUDDER SECTION DISCLOSED THE CASTELLATED NUTS ON THE RUDDER TOP COUNTERWEIGHT WAS STRIKING VERTICAL S	KIN ON THE LEFT SIDE OF THE VERTICAL FIN CREATING SMALL PUNCTURE HOLES IN THE SKIN.  THIS WAS CAUSED BY THE PHENOLIC STO	PS BEING BROKEN DUE TO NOT USING GUSTLOCKS ON RUDDER DURING WINDY CONDITIONS.  THIS ALLOWED THE RUDDER TO TRAVEL AN ADDI	TIONAL .25 INCH CAUSING THE DAMAGE.  SUBMITTER RECOMMENDATION:  USE STRONGER TYPE MATERIAL FOR RUDDER STOP.			1	K	0	0 	0 			NC	G56EU   					 
1996071800417	19960718	00417	CE  	1996	7	18	96ZZZX3549       	1	19960410	G	3213	508100324	TORQUE KNEE     			BEECH 	90    	C90A        	1152911	CE  										MLG	CRACKED         	B	L	A	NN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	476JA					LJ1161				INITIALLY IDENTIFIED A CRACK IN THE UPPER MAIN LANDING GEAR TORQUE KNEE OF ONE BEECHCRAFT C90A TRAINING AIRCRAFT WHILE L	OOKING FOR CRACKS IN THE LOWER KNEE FOLLOWING A LOWER KNEE FAILURE.  ALTHOUGH NO CRACKS OR IRREGULARITIES ON OTHER LOWER	 KNEES WERE FOUND, DETECTED SMALL CRACKS IN VIRTUALLY EVERY OTHER UPPER TORQUE KNEE, AT THE RADIUS OF THE CENTER ATTACH 	POINT IN FLEET OF 18 AIRCRAFT.  ALTHOUGH ONLY ONE MALFUNCTION OR DEFECT REPORT INCLUDED, HAVE REPLACED A TOTAL OF 36 UPP	ER TORQUE KNEES.		1	L	7	2 	3T			RT	3A20    					 
1996071800418	19960718	00418	EU  	1996	7	18	96ZZZX3550       	1	19960327	G	5710		HOLE SEALS      			TRNSQP	KR03A 	KR03A       	1130847	EU  										SPOILER BOX	DETACHED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	101TU	326  				0405KP				COTTON PATCHES GLUED TO THE FLANGED HOLES TO SEAL THE INSIDE OF THE WING AT THE SPOILER/SPEED BRAKE AREA WERE FALLING OU	T.  THE AIRCRAFT AT TIME OF ITS FIRST ANNUAL HAD LOST THREE-FOURTHS OF THE SEALS IN BOTH SPOILER BOXES.  THESE COVERS PR	EVENTED TURBULENT AIR FROM ENTERING THE INSIDE OF THE FABRIC COVERED SECTIONS OF THE WINGS DURING SPOILER DEPLOYMENTS. S	UBMITTER STATED THE CONTINUED OPERATION WITHOUT THE COVERS MAY AT SOME POINT CAUSE THE FABRIC COVERING TO DISBOND FROM T	HE RIBS.  NOTE:  THE MANUFACTURER DOES NOT USE RIB STITCHING ON THIS AEROBATIC CAPABLE AIRCRAFT.		1	K	0	0 	0 			NC	G56EU   					 
1996072200002	19960722	00002	SO  	1996	7	22	96ZZZX3551       	2	19960628	G	7421		SPARK PLUG      	CHAMPION    		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					ENGINE	ELECTRODE LOOSE 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	25	11174					18504435	282968R			NEW SPARK PLUG HAS DEFECT, SIDE ELECTRODE LOOSE.						1	H	7	1 	3O	3	O		3A24    	E5CE				 
1996071800419	19960718	00419		1996	7	18	96ZZZX3552       	4	19960307	G	2562	BP1020	BATTERY PACK    	DORNEMARGLN 	DMELT6      	CESSNA	182   	R182        	2072734	CE  										ELT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	40AT	891  	163  		13482	R18200527				DURING ANNUAL, FOUND ELT INOPERATIVE ON BOTH MANUAL AND AUTOMATIC ACTIVATION TESTS PER 91.207.  ELT REMOVED FOR REPAIRS 	AT THIS TIME.  ELT WAS REPAIRED BY MANUFACTURER IN 1991, 163.2 HOURS AGO.  TESTED BATTERY TO DETERMINE IF THERE WAS SUFF	ICIENT VOLTAGE AND FOUND 1 BATTERY CELL WAS SHORTED.  INSTALLED NEW BATTERY.  OPS CHECK OK.				1	H	7	1 	3O			RT	3A13    					 
1996071800420	19960718	00420	CE  	1996	7	18	96ZZZX3553       	1	19960308	G	5280	22130601	BRACKET         			CESSNA	182   	R182        	2072734	CE  										LT AFT NLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	40AT	891  				R18200527				DURING ANNUAL INSPECTION, FOUND LEFT, CENTER, AFT BRACKET FOR NOSE LANDING GEAR DOOR HINGE CRACKED FROM LOWER RIVET HOLE	 EXTENDING INTO RADIUS OF 90 DEGREE BEND OF BRACKET.  AT LAST ANNUAL, FOUND SAME BRACKET ON RIGHT CRACKED.  SUSPECT CAUS	E WAS VIBRATION/STRESS AT RIVET HOLE.				1	H	7	1 	3O			RT	3A13    					 
1996071800421	19960718	00421	CE  	1996	7	18	96ZZZX3554       	1	19960611	G	5210	3540000812	HINGE           			BEECH 	35    	V35B        	1151548	CE  										MAIN CABIN DOOR	PIN FROZEN      	B			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	400LF	3900 				D9825				MAIN CABIN LOWER DOOR HINGE WAS BINDING CAUSING DIFFICULT DOOR OPERATON.  GAINED ACCESS TO HINGE ASSY.  REMOVED HINGE, F	OUND STEEL HINGE PIN PN MS20392-2C63 FROZEN IN PLACE BY SEVERE CORROSION (INTERGRANULAR).  UPON REMOVAL, HINGE FRACTURED	 AT HINGE PIN RADIUS.  INSPECTION OF AREA DIFFICULT WITHOUT REMOVAL OF DOOR.  LUBRICATION ALSO DIFFICULT.  SUBMITTER STA	TED EVERY 1,000 HOURS REMOVE HINGE PIN AND DOOR, INSPECT AND APPLY ANTI-SEIZE LUBRICATION.			1	L	7	1 	3O				3A15    					 
1996071800422	19960718	00422	CE  	1996	7	18	96ZZZX3555       	1	19960319	G	7430	C12925010105	SWITCH          	GERDES      	A510        	CESSNA	177   	177RG       	2073709	CE  										IGNITION	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1989Q	3799 				177RG0389				DURING PRE-BUY INSPECTION, FOUND IGNITION KEY COULD BE REMOVED FROM SWITCH IN ANY POSITION.  DURING LOG BOOK REVIEW, FOU	ND SWITCH HAD BEEN MODIFIED PER AD 93-05-06 BY INSTALLING ACS/GERDES KIT A-3600.  THIS MODIFICATION WAS DONE AT LAST ANN	UAL (8/95) 58 HOURS PREVIOUSLY.  THIS CREATED A HAZARDOUS SITUATION AS KEY COULD BE REMOVED WITH MAGS STILL HOT.  SUSPEC	T CAUSE WAS HIGH TOTAL TIME.  LACK OF PROPER MAINTENANCE/INSPECTION COULD HAVE CAUSED SERIOUS INJURY.			1	H	7	1 	3O				A20CE   					 
1996071800423	19960718	00423		1996	7	18	96ZZZX3556       	4	19960307	G	2562		CASE            	LEIGH       	SHARC7      	CESSNA	177   	177RG       	2073709	CE  										ELT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1989Q	3800 			17885	177RG0389				DURING PRE-BUY INSPECTION, FOUND ELT INOPERATIVE DURING IMPACT TEST REQUIRED BY 91.207.  CORROSION FOUND ON CIRCUIT BOAR	D.  ELT SENT OUT FOR REPAIRS AND DETERMINED TO BE NON-REPAIRABLE DUE TO CRACKED CASE.					1	H	7	1 	3O				A20CE   					 
1996071800424	19960718	00424	CE  	1996	7	18	96ZZZX3557       	1	19960316	G	3260	S20771	HORN            			CESSNA	177   	177RG       	2073709	CE  										GEAR WARNING	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1989Q	1960 				177RG0389				DURING PRE-BUY INSPECTION, FOUND LANDING GEAR WARNING HORN INOPERATIVE.  TROUBLESHOT SYSTEM AND FOUND GEAR HORN DEFECTIV	E.  OWNER CONFIRMED GEAR HORN HAD BEEN INOPERATIVE, BUT ANNUAL WAS SIGNED OFF 8/95 ANYWAY.  SUSPECT CAUSE, VIBRATION CAU	SED HORN TO COME APART INTERNALLY.				1	H	7	1 	3O				A20CE   					 
1996071800425	19960718	00425	CE  	1996	7	18	96ZZZX3558       	1	19960628	G	2913	878H	RELAY           			CESSNA	210   	T210L       	2073449	CE  										MLG POWER PACK	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	29176	6033 				21059828				GEAR POWER PACK RUNS ALL THE TIME WHEN RELAY IS IN STUCK POSITION.						1	H	7	1 	3O				3A21    					 
1996071800426	19960718	00426	CE  	1996	7	18	96ZZZX3559       	1	19960702	G	5210		LATCH PIN       			BEECH 	99    	99A         	1154003	CE  										CREW DOOR	BINDING         	B			DQFR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	07	326CA					U135				KING CARGO SYSTEMS COCKPIT CREW DOOR, STC SA1438GL.  PILOT HAD DIFFICULTY LATCHING DOOR.  TOOK OFF, DOOR CAME OPEN DURIN	G CLIMB.  AIRCRAFT LANDED WITHOUT INCIDENT.  EXAMINATION FOUND LATCH PINS BINDING IN GUIDES; LUBRICATED AND INSTALLED LI	GHT SPRINGS TO HOLD PINS IN ALIGNMENT.  RECOMMEND STC HOLDER REDESIGN PIN GUIDES TO ALLOW FOR BETTER SUPPORT OF CATCH PI	N.			1	L	7	2 	3T				A14CE   					 
1996071800427	19960718	00427	CE  	1996	7	18	96ZZZX3560       	1	19960705	G	5312	17121541	BULKHEAD        			CESSNA	177   	177B        	2073708	CE  										FUSELAGE	CRACKED         	B			QH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	34994	2752 				17702144				BULKHEAD WAS INSPECTED AFTER GROUND ACCIDENT AND FOUND CRACKED AT LOWER INNER FLANGE.  THIS PART WAS PENETRANT TESTED IA	W MIL-STD-6866 NC/1, DATED OCTOBER 4, 1989.  MECHANIC SAID CRACK WAS NOT CAUSED BY ACCIDENT.  BULKHEAD WAS REPAIRED AND 	REINSTALLED.				1	H	7	1 	3O				A13CE   					 
1996071800428	19960718	00428	NE  	1996	7	18	96ZZZX3561       	2	19960506	G	8530		CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340*      	52016	NE  					NR 1	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	48395		261  			1628	21888			INSPECTION FOUND NR 1 CYLINDER CRACKED HORIZONTALLY THROUGH SPARK PLUG BUSHING ON FORWARD FACE.						1	Q	7	1 	3R	3	R		1A16    	5E2				 
1996071800429	19960718	00429	EA  	1996	7	18	96ZZZX3562       	2	19960612	G	7323	70389	SHAFT           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					RT ENGINE GOV	SHEARED         	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			EA	23	5064C	1889 				277405376	RL2477748A			DURING FLIGHT, OVERSPEED CONDITION OCCURRED ON RT ENGINE.  ENGINE WAS SHUT DOWN AND LANDED.  MECHANIC FOUND GOVERNOR DRI	VESHAFT SHEARED.					1	L	7	2 	3O	3	O		1A10    	1E4				 
1996071800430	19960718	00430	SO  	1996	7	18	96ZZZX3563       	2	19960627	G	7322	63255523	LEVER ARM       			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					AIR THROTTLE	LOOSE           	B			MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	5469X	1864 	491  			P21000507	513515			WHILE C/W CESSNA SEB95-15R1, THROTTLE CONTROL LEVER INSPECTION.  FOUND LEVER LOOSE AT SHAFT ATTACHMENT; ALSO, FOUND METE	RING UNIT LEVER LOOSE ON ITS SHAFT.  CESSNA SB ONLY DEALS WITH AIRFRAME CONTROL ATTACHMENT.  SUSPECT CAUSE, INCORRECT OV	ERHAUL PROCEDURES OR POOR WORKMANSHIP.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996071800431	19960718	00431	CE  	1996	7	18	96ZZZX3564       	1	19960612	G	2410		LINK ARM        			CESSNA	150   	152         	2071835	CE  										START/ALT	BOLT BROKEN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	69082	6000 				15282477				STARTER TO ALTERNATOR LINK ARM BOLT FOUND BROKEN AND HELD IN PLACE BY SAFETY WIRE DURING ROUTINE INSPECTION.						1	H	7	1 	3O			NT	3A19    					 
1996071800432	19960718	00432	EU  	1996	7	18	96ZZZX3565       	1	19960625	G	3222	5322012038	STRUT ASSY      			PILATS	PC12  	PC12        	7090550	EU  										NLG	BINDING         	B		A	FE6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	695WF	160  			IL028	125				PILOTS REPORT ROUGHNESS IN RUDDER PEDALS WHICH GOT WORSE WITH TIME.  INSPECTION REVEALED WHEN TURNING NOSE WHEEL WITH RU	DDER PEDALS, SEVERE BINDING IN NOSE STRUT ASSEMBLY.  CONTACTED PILATUS, THEY SENT A REPLACEMENT NOSE GEAR STRUT.  PROBLE	M SOLVED.  PILATUS WILL DETERMINE WHAT WENT WRONG.  SUSPECT PROBLEM FROM MANUFACTURER.				1	L	7	1 	3T			RT	A78EU   					 
1996071800433	19960718	00433	EA  	1996	7	18	96ZZZX3566       	2	19960313	G	7414		IMPULSE COUPLER 	SLICK       	4371        	CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					MAGNETO	EXCESS WEAR     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	79301	115  			95090178	17258030	L2497227A			DURING ROUTINE MAINTENANCE (COMPRESSION CHECK) ENGINE 'LOCKED UP.'  UPON INVESTIGATION/EXAMINATION, IMPULSE COUPLER PAWL	 AND PAWL AXIS FOUND EXTREMELY WORN ALLOWING IMPULSE COUPLING TO JAM INTERMITTENTLY WITH NO WARNING.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996071800434	19960718	00434	CE  	1996	7	18	96ZZZX3567       	1	19960320	G	3232	521303810	BRACKET ASSY    			CESSNA	441   	441         	2076020	CE  										NLG RT DOOR	BROKEN          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	09	83A	4170 				4410050				NOSE GEAR WOULD NOT EXTEND, CYCLED SEVERAL TIMES.  USED EMERGENCY BLOW-DOWN BOTTLE, NOSE GEAR STILL WOULD NOT EXTEND.  A	IRCRAFT LANDED WITH NOSE GEAR UP.  RIGHT NOSE GEAR DOOR RETREAT BRACKET BROKEN.  NOSE GEAR PULLED RT DOOR UP INTO NOSE G	EAR WELL AND JAMMED GEAR IN WELL.				1	L	7	2 	3T			RT	A28CE   					 
1996071800435	19960718	00435		1996	7	18	96ZZZX3568       	1	19960624	G	2822	1B56	PUMP            	AIRBORNE    																FUEL BOOST	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					3AD18					FUEL PUMP ARMATURE OUT OF BALANCE RESULTING IN PUMP FAILURE.																			 
1996071800436	19960718	00436		1996	7	18	96ZZZX3569       	1	19960702	G	2822	9C52	PUMP            	AIRBORNE    																FUEL BOOST	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13										FUEL PUMP MAY HAVE RUN DRY CAUSING DAMAGE TO THE ARMATURE.																			 
1996071800437	19960718	00437		1996	7	18	96ZZZX3570       	1	19960702	G	2822		PUMP            																	FUEL BOOST	SHAFT WORN      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					9E688					FUEL PUMP ARMATURE SHAFT HAS GROOVE WORN IN IT BY THE SPACERS.																			 
1996071800438	19960718	00438	CE  	1996	7	18	96ZZZX3571       	1	19960709	G	2820		LINE            			CESSNA	182   	182P        	2075816	CE  										FWD RT DOOR POST	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	91389					18261995				DURING WINDSHIELD REPLACEMENT, FOUND AILERON CONTROL CABLE, WHICH TRAVELS UP THE FORWARD RIGHT DOOR POST, WAS CHAFING ON	 THE ADJACENT FUEL LINE.  ORIGINAL WALL THICKNESS IS .030 INCH AND THE DEPTH OF THE CHAFE WAS .020 INCH.					1	H	7	1 	3O			NT	TA13    					 
1996071800439	19960718	00439	NM  	1996	7	18	96ZZZX3572       	1	19960701	G	5711		SPAR            			UNIVAR	415   	415E        	0420308	NM  										LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	94841					4914				INSPECTION REQUIRED IN AD 94-18-04.  FOUND EVIDENCE OF CORROSION BETWEEN PARTS OF REAR SPAR IN LEFT WING.  SAME CONDITIO	N FOUND IN RIGHT WING AS WELL AS A PORTION OF EXFOLIATION FOUND IN BOTTOM SPAR CAP, AFT SIDE, ABOUT A FOOT FROM THE OUTB	OARD END.				1	L	7	1 	3O				A787    					 
1996071800440	19960718	00440	GL  	1996	7	18	96ZZZX3573       	3	19960501	G	6114	D6603	HUB             			CESSNA	210   	210         	2073402	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER	CORRODED        	B			AQYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03								750803		INSPECTION FOUND CORROSION ON EXTERIOR AND INTERIOR OF HUB.  RECOMMEND ROUTINE MAINTENANCE.						1	H	7	1 	3O			RT	3A21    		5	C	P21EA	 
1996071800441	19960718	00441	GL  	1996	7	18	96ZZZX3574       	3	19960501	G	6114	D5897	HUB             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER	CORRODED        	B			AQYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	421SM					42180889		748237		INSPECTION FOUND CORROSION THROUGHOUT HUB.  RECOMMEND ROUTINE MAINTENANCE.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996071800442	19960718	00442	GL  	1996	7	18	96ZZZX3575       	3	19960617	G	6114	D5894	HUB             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER	CRACKED         	B			AQYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	421BB					421B0967		739542		HUB EDDY CURRENT INSPECTION OF RETENTION THREADS REVEALED A CRACK.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996071800443	19960718	00443	GL  	1996	7	18	96ZZZX3576       	3	19960617	G	6114	D5894	HUB             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	RETAIN THREADS	CRACKED         	B			AQYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	421BB					421B0967		751875		HUB EDDY CURRENT INSPECTION OF RETENTION THREADS REVEALED A CRACK.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996012600434	19960126	00434	NM  	1996	1	26	96ZZZX358        	1	19960109	G	2612	80380203	FIRE DET UNIT   			DOUG  	MD11  	MD11        	3023602	NM  										NR 1 ENGINE	FAULTY          	G		A		O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			GL	23	2FOR					48556				ENGINE NR 1 FIRE DURING LANDING ROLL OUT.  ECL PROCEDURE COMPLETED(PAGE 34B).  FIRE OUT AFTER A FEW SECONDS.  MAINTENANC	E VERIFIED ENGINE NR 1 DUCTING CONDITION AND FIRE LOOPS.  ALL OK.  PERFORMED RESISTANCE CHECK AT FDCU AT PINS J AND K PE	R FIM.  ALL READINGS WITHIN NORMAL.  MAINTENANCE CREW REMOVED AND REPLACED FIRE DETECTION CONTROL UNIT.  RAN ENGINE AND 	NO FURTHER INDICATIONS EXPERIENCED.  PART REMOVED AND REPLACED WAS FIRE DETECTION CONTROL UNIT, MFG PN 8038-02-03, AND S	N 796.  MFG DATE, 7-93.  TRIGGERED BOTH LOOPS 'A' AND 'B' AND TESTED OK DURING GROUND CHECK.		2	L	7	3 	4F			RT	A22WE   					 
1996071800669	19960718	00669	SW  	1996	7	18	96ZZZX3602       	1	19960503	G	7714	206070266009	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT N1	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	206MH				355D	45426				INTERNAL LIGHT INOPERATIVE.  LOOSE CONNECTION WHERE WIRE ENTERS INDICATOR.  MOUNTING WIRE BREAKS CONTINUITY.  REMOVED AN	D REPLACED.					1	G	7	1 	3U				H2SW    					 
1996071800674	19960718	00674	EU  	1996	7	18	96ZZZX3607       	1	19960601	G	6730	741C000005	ACTUATOR        			BOLKMS	117   	BK117A4     	5626017	EU  										T/R	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	313LF				00446	7138				ACTUATOR LEAKING.						1	G	7	2 	3U				H13EU   					 
1996071800675	19960718	00675	EU  	1996	7	18	96ZZZX3608       	1	19960503	G	6730	7012409901	ACTUATOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  										DUPLEX PITCH	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				91100172	7505				AP1 WILL NOT COME ON LINE.						1	G	7	2 	3U			NC	H13EU   					 
1996071800676	19960718	00676	EU  	1996	7	18	96ZZZX3609       	1	19960620	G	6730	7012409901	PITCH ACTUATOR  			BOLKMS	BK117 	BK117C1     	5626025	EU  										DUPLEX PITCH	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				91050153	7505				ACTUATOR CAUSING AP1 AND AP2 TO GENERATE ERROR CODES, AP1 AND AP2 WILL NOT COME ON LINE.						1	G	7	2 	3U			NC	H13EU   					 
1996071800677	19960718	00677		1996	7	18	96ZZZX3610       	4	19960503	G	2215	7012693901	SERVO MONITOR   			BOLKMS	BK117 	BK117C1     	5626025	EU  										AUTOPILOT	SHORTED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				90090152	7505				RZ-710 SHORTED, A/P WOULD NOT COME ON LINE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996071800678	19960718	00678	EU  	1996	7	18	96ZZZX3611       	1	19960612	G	3340	099799100	SEARCH LIGHT    			BOLKMS	BK117 	BK117C1     	5626025	EU  										EXTERIOR LIGHT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				441	7505				SEARCH LIGHT WILL NOT TURN OFF.						1	G	7	2 	3U			NC	H13EU   					 
1996071800679	19960718	00679	EU  	1996	7	18	96ZZZX3612       	1	19960510	G	2840	1178978301	DETECTOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  										PUMP FAIL	MALFUNCTION     	B			TI1R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	05	317MC				422	7505				FUEL PUMP FAIL LIGHT ACTIVATES WHEN RADIO IS TRANSMITTING.						1	G	7	2 	3U			NC	H13EU   					 
1996071800680	19960718	00680	EU  	1996	7	18	96ZZZX3613       	1	19960507	G	7714	645383051	INDICATOR       			AEROSP	SA365 	SA365N1     	8680668	EU  										COCKPIT NG	FAILED          	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	365SC				1128	6298				ORDERED EXCHANGE UNIT, BUT UNIT DOES NOT WORK PROPERLY (LIGHT WORKS, BUT DOES NOT ILLUMINATE GAUGE FACE).						1	G	7	2 	3U				H10EU   					 
1996071800681	19960718	00681		1996	7	18	96ZZZX3614       	4	19960522	G	3454	066401000	RECEIVER        			BOLKMS	117   	BK117A3     	5626015	EU  										R NAV	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4493X	4    			3865	S7038				KNOB HARD TO TURN, FREQUENCY DOES NOT ADJUST PROPERLY, SOMETIMES UP, SOMETIMES DOWN.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996071800682	19960718	00682		1996	7	18	96ZZZX3615       	4	19960528	G	2211	11788292	COMPUTER        			BOLKMS	117   	BK117A3     	5626015	EU  										SPAS	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4493X	14   				S7038				COMPUTER CAUSING SPAS NOT TO TEST.  UNIT ONLY HAS 13.90 HOURS, SINCE REPAIR.						1	G	7	2 	3U				H13EU   					 
1996071800683	19960718	00683		1996	7	18	96ZZZX3617       	4	19960529	G	3457	066040310111	GPS             			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTION     	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	495LF				12083	S645				GPS HAD HARDWARE ERROR CODE 0010 ON INITIAL INSTALLATION AND START-UP.  ALTHOUGH SATELLITE SIGNAL STRENGTHS WERE ALL IN 	THE 40'S, EVEN AFTER ALL SATELLITES WERE CAPTURED, UNIT DID NOT SHOW PRESENT POSITION AND MESSAGE CONTINUED TO SHOW ERRO	R CODE, APPROXIMATELY 10 MINUTES.				1	G	7	2 	3U				H3EU    					 
1996071800684	19960718	00684		1996	7	18	96ZZZX3618       	4	19960528	G	3457	066040310111	GPS             			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	495LF				13398	S645				GPS VERY SLOW TO COME ON LINE AT 5 TO 6 MINUTES OR LONGER.  PART WAS JUST SENT IN FOR REPAIR LAST MONTH.  REMOVED AND RE	PLACED.					1	G	7	2 	3U				H3EU    					 
1996071800685	19960718	00685		1996	7	18	96ZZZX3619       	4	19960522	G	3457	066040310111	GPS             			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT DISPLAY	ERRATIC         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LF				13440	S663				COCKPIT GPS DISPLAY ERRATIC.						1	G	7	2 	3U				H3EU    					 
1996071800686	19960718	00686	SW  	1996	7	18	96ZZZX3620       	1	19960617	G	6240	222375071105	INDICATOR       			BELL  	222   	222         	1182122	SW  										TRIPLE TACH	FLUCTUATES      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MK				083	47515				TRANSMISSION TORQUE NEEDLE FLUCTUATES 20 - 30 PERCENT, FALLS TO ZERO, AND THEN RETURNS AND BEGINS TO FLUCTUATE AGAIN.						1	G	7	2 	3U				H9SW    					 
1996071800687	19960718	00687	EU  	1996	7	18	96ZZZX3621       	1	19960508	G	2435	200SGL115Q	STARTER         			BOLKMS	105   	BO105LSA3   	5626020	EU  										DAMPER	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV	2282 			1100	2033				FRICTION DAMPER LOOSE - STARTER BANGS ON START-UP.						1	G	7	2 	3U				H3AU    					 
1996071800739	19960718	00739	EU  	1996	7	18	96ZZZX3625       	1	19960529	G	7830		INTERCOSTAL     		F10A5B20202 	ISRAEL	1124  	1124        	4500102	EU  										LATCH SUPPORT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	269AJ	4400 				276				INSPECTION FOUND RT T/R SECONDARY BRACKET LATCH INTERCOSTAL CRACKED.						2	M	7	2 	4F				A2SW    					 
1996071800740	19960718	00740	SW  	1996	7	18	96ZZZX3626       	1	19960710	G	5751	2734023011	SPAR            		2734000039  	SWRNGN	SA227 	SA227AC     	8780603	SW  										AILERON	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	359AE					AC674				DURING DISASSEMBLY OF AILERON FOR SKIN CHANGE, THE SPAR WAS FOUND CRACKED IN TWO PLACES AROUND OUTBOARD HINGE BRACKET. T	HE CRACKS WERE THE FULL WIDTH OF THE SPAR WEB AND INTO THE RADIUS OF THE FLANGES.  THIS IS THE SECOND SPAR FOUND CRACKED	 LIKE THIS RECENTLY.  SUBMITTER SUGGESTED MANDATORY VISUAL INSPECTION OF THE AILERON SPAR IS STRONGLY RECOMMENDED.				2	L	7	2 	4T			RT	A8SW    					 
1996071800741	19960718	00741	CE  	1996	7	18	96ZZZX3627       	1	19960410	G	3213	6541000200	PISTON          		554100017   	CESSNA	500   	500CESSNA   	2076602	CE  										LT MLG	BROKEN          	B	S		OS5D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	9AX	4127 			021	5000016				WHILE DISASSEMBLYING THE LEFT MAIN LANDING GEAR FOR AN AXLE CHANGE, FOUND ISOLATION PISTON STEM THAT THE DAMPENING SPRIN	G SURROUNDS WAS BROKEN FLUSH AT THE PISTON HOUSING.  SEE CITATION 500 COMPONENT MM, PAGE 32-10-00, FIGURE 1002, SHEET 2,	 ITEMS 110, 113, 114, 115.  THIS STEM HAS BEEN CRACKED BROKEN FOR QUITE SOME TIME.  POSSIBLE CAUSE, AIRCRAFT WAS LANDED 	WITH UNDERSERVICED STRUT OR WAS TAXI/TOWED WITH FLAT STRUTS.			1	L	7	2 	4F				A22CE   					 
1996071800742	19960718	00742	EU  	1996	7	18	96ZZZX3628       	1	19960529	G	7830		INTERCOSTAL     		F10A5B20202 	ISRAEL	1124  	1124        	4500102	EU  										LATCH SUPPORT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	98WW	3057 				398				THRUST REVERSER SECONDARY BRACKET LATCH SUPPORT INTERCOSTAL FOUND CRACKED NUMEROUS PLACES.  MATERIAL IS .032 INCH 2024T6	 ALUMINUM.					2	M	7	2 	4F				A2SW    					 
1996071800743	19960718	00743	SO  	1996	7	18	96ZZZX3629       	1	19960619	G	7732		INDICATOR       			GULSTM	G1159 	G1159       	3953505	SO  										RT ENG TVI	ERRATIC         	B			GJQR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			NM	01	26WP	9107 				24				ON DEPARTURE, RIGHT ENGINE TVI INCREASED TO 2.2 THEN AT ABOUT 10,500 MSL, WENT TO 5. PLUS TVI READING.  AFTER REDUCING P	OWER, TVI VARIED FROM 2. TO 5 PLUS.  THE CREW MADE A PRECAUTIONARY ENGINE SHUT DOWN AND RETURNED FOR INVESTIGATION TO TH	E PROBLEM.  CHECKED AND CLEANED RIGHT TVI AMPLIFIER, TRANSDUCER, OIL SYSTEM CHIP PLUGS, AND OIL FILTERS.  GROUND OPERATI	ONAL CHECK TVI OPERATED NORMALLY.  SUSPECT HIGH RESISTANCE AT TVI TRANSDUCER OR AMPLIFIER CONNECTIONS WHICH CLEANING COR	RECTED.		2	L	7	2 	4F			RT	A12EA   					 
1996071800744	19960718	00744	EU  	1996	7	18	96ZZZX3630       	1	19960313	G	5751	513501504	AILERON SKIN    			ISRAEL	1124  	1124A       	4500103	EU  										RT AILERON	CRACKED         	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	551TP	2473 				419				FOUND RIGHT AILERON TOP SKIN CRACKED AT OUTBOARD END.  CRACK EXTENDED OUT FROM TWO SIDES OF A RIVET HEAD, APPROXIMATELY 	.1875 INCH IN BOTH DIRECTIONS.  AILERON WAS REPAIRED AND WILL BE MONITORED FOR FURTHER CRACKING.					2	M	7	2 	4F				A2SW    					 
1996071800745	19960718	00745	EU  	1996	7	18	96ZZZX3632       	2	19960507	G	7250	3013300650	SHAFT           								CFMINT	CFM56 	CFM563B2    	13802	EU  					LPT ROTOR	CRACKED         	B			RD43	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		28425			FN01136		721108			THE LPT SHAFT HAS 2 EACH CRACKS, ONE IS 5 AND ONE IS 7 INCHES LONG, ONE INCH APART STARTING APPROXIMATELY .50 INCH FROM 	THE AFT END OF THE SPLINES.  INVESTIGATION IS IN PROGRESS BY CFMI.										4	F			E21EU				 
1996071800746	19960718	00746	NE  	1996	7	18	96ZZZX3633       	2	19960607	G	7210	447245	BEARING         								PWA   	JT8   	JT8D217A    	52053	NE  					N2 GEARBOX	FAILED          	B			RD43	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	05							717374			ENGINE EXPERIENCED LOUD BANG AND EPR AND RPM WENT TO ZERO.  ENGINE WAS REMOVED WITH INTERNAL AND EXTERNAL DAMAGE TO THE 	N2 GEARBOX.  DISASSEMBLY OF THE GEARBOX REVEALED A FAILED BEARING.  INVESTIGATION IS STILL UNDER WAY AT AVIALL.										4	F			E9NE				 
1996071800747	19960718	00747	WP  	1996	7	18	96ZZZX3634       	1	19960705	G	5753		CLEVIS          			DOUG  	DC8   	DC8F54      	3021926	WP  										RT INBD FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	426FB					45667				DURING C-CHECK INSPECTION, A CRACK WAS FOUND EMANATING FROM A FASTENER HOLE IN THE LOWER TANG OF THE RIGHT WING INBOARD 	FLAP LOWER CLEVIS.  REPAIRED CLEVIS BY INSTALLING A 2.0 INCH BY 2.0 INCH DOUBLER MADE OF .125 A1S1 301 1/2 H MATERIAL IA	W EO 9606181.  8110-3 ISSUED BY DER SW-713.				2	L	7	4 	4F				4A25    					 
1996071800748	19960718	00748	WP  	1996	7	18	96ZZZX3635       	1	19960705	G	5753		CLEVIS          			DOUG  	DC8   	DC8F54      	3021926	WP  										LT INBD FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	426FB					45667				DURING C-CHECK INSPECTION, A CRACK WAS FOUND EMANATING FROM A FASTENER HOLE IN THE INBOARD FLAP.  REPAIRED CLEVIS BY INS	TALLING A 2.0 INCH BY 2.0 INCH DOUBLER MADE OF .125 A1S1 301 1/2 H MATERIAL IAW EO 960511.  8110-3 ISSUED BY DER SW-713.					2	L	7	4 	4F				4A25    					 
1996071800749	19960718	00749	SW  	1996	7	18	96ZZZX3636       	1	19960619	G	6230	412040101117	MAST            			BELL  	412   	412         	1182202	SW  										M/R	MISOVERHAULED   	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05		117  			N574X					MAST RECEIVED FROM BELL AS SERVICEABLE REPAIRED.  FOLLOWING DISCREPANCIES FOUND ON RECEIVING INSPECTION:  1.  THE WORD '	REWORKED' NEVER WAS ENGRAVED ON FLANGE 'E' AS STATED ON BHT-C. R AND O MANUAL, SECTION 63-00-00, PAGE 62, PARAGRAPH 1, F	IGURE 63-17.  2.  INNER MAST AREA (BORE) WAS NEVER CLEANED AND CORE ON TOP SECTION IS MISSING.  3.  FOUND PITTING CORROS	ION ON SPLINES K-M, AREA 'A', SURFACE 'N', AND SPLINES 'O' AS MARKED ON MAST.			1	G	7	2 	4U				H4SW    					 
1996012600442	19960126	00442	EA  	1996	1	26	96ZZZX366        	2	19960105	G	7322	377	PUG             		MA4SPA      	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					FUEL BOWL	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	98242		290  		CK34507	2826130	L2048027A			CARBURETOR WAS FOUND TO HAVE A PLUG MISSING FROM FUEL BOWL.  THE OPEN HOLE WAS ABOVE THE NORMAL FUEL LEVEL IN THE BOWL; 	HOWEVER, FUEL WAS FREE TO LEAK OUT WHEN THE A/C IS POSITIONED IN A NOSE DOWN PITCH.  FUEL STAINS WERE NOTED.  THIS PLUG 	WAS USED TO PLUG A HOLE MADE DURING THE MANUFACTURE OF THE CARBURETOR.				1	L	7	1 	3O	3	O		2A13    	E274				 
1996072500264	19960725	00264		1996	7	25	96ZZZX3667       	4	19960402	G	3421	4021541671	GYRO            			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT ATTITUDE	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				85101231	7098				ON INSTALLATION, GYRO UNIT WAS SLOW TO SPIN-UP AND GRADE-OFF.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996072500265	19960725	00265	SW  	1996	7	25	96ZZZX3668       	1	19960430	G	6410	206016201103	BLADE           		2060118103  	BELL  	206   	206B        	1181511	SW  										T/R	DELAMINATED     	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	10ED	1516 			TAH2340	1960				BOTH BLADES WERE FOUND DELAMINATED ON THE DOUBLERS AT THE BUTT END.  NOTE:  THE BLADES WERE REPAINTED IN 1991 - 353.7 HO	URS AGO.  REFERENCE:  OPERATOR CONTROL NR CHI1543.  (X)					1	G	7	1 	3U				H2SW    					 
1996072500266	19960725	00266		1996	7	25	96ZZZX3669       	4	19960525	G	2312	40001452500	TRANSCEIVER     		RT138F      	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				1263	7098				VHF-FM HI BAND RADIO WILL NOT TRANSMIT OR RECEIVE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1996072500267	19960725	00267		1996	7	25	96ZZZX3670       	4	19960619	G	3442	07113780D	SENSOR          		RDS008100   	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT RADAR	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				12851	7098				TRANSMITTER FAULT.  RADAR SENSOR.  COLOR RADAR INDICATOR.						1	G	7	2 	3U				H13EU   					 
1996072500268	19960725	00268		1996	7	25	96ZZZX3671       	4	19960619	G	3442	066311400	INDICATOR       		RDS008100   	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT RADAR	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				13644	7098				TRANSMITTER FAULT.  RADAR SENSOR.  COLOR RADAR INDICATOR.						1	G	7	2 	3U				H13EU   					 
1996072500378	19960725	00378	CE  	1996	7	25	96ZZZX3673       	1	19960604	G	7120	075100113	MOUNT           			CESSNA	180   	180         	2072602	CE  										FIREWALL	CRACKED         	B	S		HE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11										UPPER LEFT AND RIGHT FIREWALL ATTACH BUSHINGS WERE FOUND CRACKED HORIZONTALLY.  SUSPECT OVERTORQUING OF FIREWALL BOLTS A	ND VIBRATION.					1	H	7	1 	3O			NC	5A6     					 
1996072500379	19960725	00379	SO  	1996	7	25	96ZZZX3674       	1	19960619	G	2913	41130	ARMATURE        		HYC5005     	PIPER 	PA28  	PA28R200    	7102811	SO  										POWER PACK	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4290T	1048 			ERH2506B	28R7235003				ARMATURE WAS NEW AT POWER PACK OVERHAUL AT 5,055 HOURS.  ARMATURE FAILURE AT 6,103 HOURS.  POWER PACK TT UNKNOWN.						1	L	7	1 	3O				2A13    					 
1996072500380	19960725	00380	CE  	1996	7	25	96ZZZX3675       	1	19960618	G	2720	35660031	CONTROL HORN    			BEECH 	35    	B35         	1151506	CE  										RUDDERVATOR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	5269C					D2663				DURING ANNUAL INSPECTION, CRACK FOUND COMING OUT OF BOLT HOLE WHERE HORN MOUNTS TO RUDDERVATOR.  REPLACED WITH NEW PART.						1	L	7	1 	3O				A777    					 
1996072500381	19960725	00381	CE  	1996	7	25	96ZZZX3676       	1	19960617	G	3230	S24266	ROD END         			CESSNA	177   	177RG       	2073709	CE  										MLG ACTUATOR	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	52945					177RG1316				AT ANNUAL INSPECTION, THIS PART WAS FOUND BROKEN.  SUBMITTER STATED SL SE79-37 OBVIOUSLY WAS NEVER COMPLIED WITH.  SUGGE	ST THAT THIS SERVICE LETTER BE MADE MANDATORY.					1	H	7	1 	3O				A20CE   					 
1996072500382	19960725	00382	SO  	1996	7	25	96ZZZX3677       	1	19960621	G	7922	53E19600	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  										THERMO BYPASS	NUT LOOSE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	35584	887  			18135	318052076				THERMO BYPASS VALVE FAILED LYC SB 518C.  LOCKNUT WAS SO LOOSE ITS REPAIR IAW SB 518C WAS NOT POSSIBLE.  MOST OF THE VALV	ES SUBMITTER REPORTS (APPROXIMATELY 85 TO 90 PERCENT) ARE FAILING THE INSPECTION AND REPAIRED ONLY 3 DUE TO THE EXTREMEL	Y LOOSE LOCKNUTS.  SUBMITTER STATED ANY VALVES WITH A LOOSE LOCKNUT SHOULD BE REPLACED.				1	L	7	2 	3O				A20SO   					 
1996072500383	19960725	00383	SO  	1996	7	25	96ZZZX3678       	2	19960710	G	8530	530341	PISTON          			CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300D       	17022	SO  					NR 1 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3793S		925  			17250993	28332D3D			DURING SCHEDULED OIL CHANGE, OWNER REQUESTED A COMPRESSION CHECK BE DONE.  NR 1 CYLINDER WAS LOW AT 28/80.  FURTHER INVE	STIGATION REVEALED THE FOLLOWING:  PISTON CRACKED FROM SKIRT TO FACE AT 6:00 O'CLOCK POSITION.  TOP COMPRESSION RING BRO	KEN AND CYLINDER WALL SCORED.  THIS ENGINE ONLY HAD 30 HOURS SINCE PREVIOUS COMPRESSION CHECK WHICH WAS WELL WITHIN TCM 	CRITERIA.  SUBMITTER RECOMMENDS COMPRESSION CHECKS BE DONE ON THESE OLDER ENGINES ESPECIALLY IF TOTAL TIME IS UNKNOWN AN	D TSMOH IS MID-POINT OR BEYOND.		1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1996072500384	19960725	00384		1996	7	25	96ZZZX3679       	4	19960705	G	2562		G SWITCH        	DORNEMARGLN 	DMELT6      	CESSNA	182   	182Q        	2072732	CE  										ELT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4743N	2338 			39108	18267332				DURING 100-HOUR INSPECTION, PULLED ELT FOR FUNCTION CHECK, G-SWITCH WOULD NOT TRIGGER ON IMPACT.  ELT WOULD FUNCTION IN 	ON POSITION.  ELT REPLACED.					1	H	7	1 	3O			NT	3A13    					 
1996012600444	19960126	00444	SO  	1996	1	26	96ZZZX368        	2	19960105	G	8530	6529551A	CYLINDER        			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360GB   	17025	SO  					NR 5	HEAD SEPARATED  	D				A				UNSCHED LANDING         				O	E	R	OTHER                     	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	CL	CLIMB          	1			WP	17	8335C		1473 			348333056	309328			NR 5 CYLINDER HEAD SEPARATED FROM TIRE BARREL DURING TAKEOFF AT POWER REDUCTION.  EMERGENCY LANDING MADE.  NO FURTHER DA	MAGE FOUND.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996072500385	19960725	00385	CE  	1996	7	25	96ZZZX3680       	1	19960708	G	2710	040010759	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  										LT AIL BALANCE	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5403H	696  				15284096				LEFT AILERON BALANCE CABLE FOUND FRAYED AT WS 56.87 ON CABLE SUPPORT BLOCK.  THIS AIRCRAFT WAS ON 100-HOUR INSPECTION AN	D ONCE CABLE STARTED FRAYING, CONDITION MUST HAVE ACCELERATED, CABLE WAS 50 PERCENT THROUGH.					1	H	7	1 	3O			NT	3A19    					 
1996072500386	19960725	00386	SO  	1996	7	25	96ZZZX3681       	1	19960703	G	2750	62738000	BRACKET         			PIPER 	PA28  	PA28140     	7102802	SO  										FLAP HANDLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	98334					2826175				WHEN ACCOMPLISHING AD 96-10-03, FOUND FLAP HANDLE BRACKET CRACKED ONE-THIRD OF THE MOUNTING BOLT HEAD RADIUS, AROUND 3 O	F THE 6 ATTACHING BOLTS.  REPLACED BRACKET WITH FACTORY PART.					1	L	7	1 	3O				2A13    					 
1996072500387	19960725	00387	NM  	1996	7	25	96ZZZX3682       	1	19960702	G	7922	53E19600	VALVE           			CHILD 	S2    	S2BPITTS    	0110304	NM  										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	60823	70   			57113	5269				INSPECTION FOUND LOOSE CRIMP NUT ON THERMOSTATIC BYPASS VALVE (EVEN WITH NEW STYLE PART).						1	Q	7	1 	3O				A8SO    					 
1996072500388	19960725	00388	EA  	1996	7	25	96ZZZX3683       	2	19960601	G	8550		TUBE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					OIL RUNBACK	HOLE CHAFED     	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	16	69082					15282477				INSPECTION FOUND WIRING FOR ALTERNATOR MISROUTED, WORE HOLE IN OIL RUNBACK TUBE CAUSING OIL LEAK.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996072500390	19960725	00390		1996	7	25	96ZZZX3685       	4	19960628	G	6122	D20591	DRIVE GEAR      	MCAULY      	C290D4K     															GOVERNOR	EXCESS WEAR     	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					785062					DURING INSPECTION OF PROPELLER GOVERNOR, FOUND EXCESSIVE WEAR ON SPLINE OF DRIVE GEAR.  DRIVE GEAR WAS REPLACED WITH NEW	 D2088 DRIVE GEAR.																		 
1996080600011	19960806	00011	EA  	1996	8	6	96ZZZX3688       	2	19960624	G	7414	10349271	COIL            	BENDIX      	S6LN1227    	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					LT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	4135R	1677 			17297	3240452	L547048			LEFT AND RIGHT MAGNETOS FAILED BECAUSE OF DEFECTIVE COILS WHEN HEATED FOR APPROXIMATELY 30 MINUTES.  AIRCRAFT ON FERRY F	LIGHT TO PERFORM ANNUAL INSPECTION.  AD 94-01-03R2 REQUIRED AT ANNUAL OR 100 HOURS.  AIRCRAFT HAS BEEN OUT OF ANNUAL FOR	 4 YEARS.  SUGGEST AD TO BE PERFORMED BEFORE FURTHER FLIGHT.				1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996072500393	19960725	00393	EA  	1996	7	25	96ZZZX3689       	2	19960624	G	7414	103493101	COIL            	BENDIX      	S6LN1209    	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					RT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	4135R	1677 			17209	3240452	L547048			LEFT AND RIGHT MAGNETOS FAILED BECAUSE OF DEFECTIVE COILS WHEN HEATED FOR APPROXIMATELY 30 MINUTES.  AIRCRAFT ON FERRY F	LIGHT TO PERFORM ANNUAL INSPECTION.  AD 94-01-03R2 REQUIRED AT ANNUAL OR 100 HOURS.  AIRCRAFT HAS BEEN OUT OF ANNUAL FOR	 4 YEARS.  SUGGEST AD TO BE PERFORMED BEFORE FURTHER FLIGHT.				1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996012600445	19960126	00445	SO  	1996	1	26	96ZZZX369        	2	19960110	G	8530	652955A1	CYLINDER        			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  					NR 1	HEAD SEPARATED  	D				A				UNSCHED LANDING         				B	E	R	SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	CL	CLIMB          	1			EA	21	758FF		634  			R1723055	355014			IMMEDIATELY AFTER LIFT OFF HEARD A LOUD BANG FROM ENGINE COMPARTMENT, 3 MORE ENTERED CABIN, ABORTED TAKEOFF AND SHUT DOW	N ENGINE.  REMOVED COWL AND FOUND NR 1 CYLINDER HEAD SEPARATED FROM BARREL.					1	H	7	1 	3O	3	O		3A17    	E1CE				 
1996072500394	19960725	00394	CE  	1996	7	25	96ZZZX3690       	1	19960708	G	2810	17260424	CAP             			CESSNA	177   	177B        	2073708	CE  										FUEL TANK	WATER LEAK      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	34873					17702058				FLUSH FUEL CAPS ALLOWING WATER TO LEAK INTO FUEL TANKS.  BEING A WET WING AIRCRAFT, IT IS VERY DIFFICULT TO BE SURE ALL 	WATER IS REMOVED.  INSTALLING NEW SEALS OR CAPS IS ONLY A TEMPORARY SOLUTION.  PERMANENT FIX IS TO INSTALL STC SA2457CE 	PLATES AND CAPS OR OTHER TYPE RAISED INLET.				1	H	7	1 	3O				A13CE   					 
1996072500395	19960725	00395	CE  	1996	7	25	96ZZZX3691       	1	19960705	G	5753	05239018	SUPPORT ASSY    		0523901     	CESSNA	172   	172A        	2072404	CE  										LT OTBD FLAP	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7558T	4415 				47158				DURING INSPECTION OF FLAPS PER CESSNA SEB95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SEARED.  INSTALLED FLAP SUPPORT 	KIT SK180-44.  NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS.  SUBMITTER RECOMMENDS THIS SB BECOME AN AD.					1	H	7	1 	3O				3A12    					 
1996072500396	19960725	00396	CE  	1996	7	25	96ZZZX3692       	1	19960705	G	5753	05239019	SUPPORT ASSY    		05239011    	CESSNA	172   	172A        	2072404	CE  										RT OTBD FLAP	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7558T	4415 				47158				DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED.  INSTALLED FLAP SUPPORT	 KIT SK180-44.  NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS.  SUBMITTER RECOMMENDS SB BECOME AN AD.					1	H	7	1 	3O				3A12    					 
1996072500397	19960725	00397	CE  	1996	7	25	96ZZZX3693       	1	19960705	G	5753	05239018	SUPPORT ASSY    		0523901     	CESSNA	172   	172A        	2072404	CE  										LT INBD FLAP	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7558T	4415 				45158				DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED.  INSTALLED FLAP SUPPORT	 KIT SK180-44.  NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS.  SUBMITTER RECOMMENDS THIS SB BECOME AN AD.					1	H	7	1 	3O				3A12    					 
1996072500398	19960725	00398	EA  	1996	7	25	96ZZZX3694       	2	19960708	G	8520		CASE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 2 CYL LT SIDE	CRACKED         	B			DPOD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	739PJ		1431 			17270694	L607576T			LEFT CASE CRACKED BELOW NR 2 CYLINDER BASE.  CRACK WAS ABOUT 2.5 INCHES LONG.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996072500400	19960725	00400		1996	7	25	96ZZZX3696       	4	19960628	G	2562	BP1026	BATTERY         	MERL        	CIR11       	PIPER 	PA23  	PA23250     	7102308	SO  										ELT	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	700Y				23437	277754076				OPEN ELT BATTERY TO CHANGE BATTERY AND C/W FAR 91.207.  FOUND BATTERY PACK LEAKING AND ELT ITSELF JUST STARTING TO CORRO	DE.  SUSPECT CAUSE EITHER AGE OF HEAT FROM SUN.  SUBMITTER RECOMMENDS TO KEEP COMPLYING WITH FAR 91-207.					1	L	7	2 	3O				1A10    					 
1996072500401	19960725	00401	EA  	1996	7	25	96ZZZX3697       	2	19960702	G	8530	434011	CYLINDER        			NAMER 	NA260 	T28*        		GL  	WRIGHT	R1820 	R1820*      	67020	EA  					FLANGE	CRACKED         	D				O				OTHER                   				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		NR	NOT REPORTED   	1			SW	99	28YF		400  			137799W				ENGINE SHOWED EVIDENCE OF OIL LEAK.  MECHANIC MUST HAVE THOUGHT HE HAD CURED PROBLEM.  AIRCRAFT CLEARED FOR FLIGHT.  NR 	1 CYLINDER DEPARTED ENGINE SOME TIME AFTER PILOT NOTICED SMOKE IN COCKPIT.  INSTRUMENTS SHOWED NORMAL READINGS.  CYLINDE	R HAD EVIDENCE OF OLD CRACK IN AREA OBSCURED BY COOLING FINS AND PROPELLER GOVERNOR.  FOLLOWING MILITARY MAINTENANCE PRO	GRAM, COULD (MIGHT) HAVE HELPED, BUT CYLINDER CRACKS OCCURRED IN MILITARY USE ALSO.			1	L	7	1 	4R	4	R		1A18    	5E10				 
1996072500402	19960725	00402	CE  	1996	7	25	96ZZZX3698       	1	19960629	G	3211	24411001	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										LT MLG	SHEARED         	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	99	6589V	6461 				172RG0778				LEFT MLG COULD NOT BE FULLY EXTENDED.  EVERY POSSIBLE ATTEMPT FAILED.  DURING LAST ATTEMPT BEFORE GEAR-UP LANDING, PILOT	 PHYSICALLY REACHED OUT AND LOCKED GEAR.  (FLIGHT INSPECTER WAS ALSO ON BOARD.)  SAFE LANDING WAS MADE.  UPON INSPECTION	, PN 24411001 WAS FOUND SHEARED AT ACTUATOR GEAR ATTACH POINT.  NO DEFINITE CAUSE WAS NOTED.  TIME AND FATIGUE ARE SUSPE	CT REASONS FOR PART FAILURE.  THERE IS NO OTHER WAY OF DOWNLOCKING GEAR WITH THS TYPE OF FAILURE.			1	H	7	1 	3O				3A17    					 
1996072500403	19960725	00403	CE  	1996	7	25	96ZZZX3699       	1	19960705	G	5753	052390139	SUPPORT ASSY    		0523901     	CESSNA	172   	172A        	2072404	CE  										RT OTBD FLAP	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7558T	4415 				47158				DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED.  INSTALLED FLAP SUPPORT	 KIT SK180-44.  NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS.  SUBMITTER RECOMMENDS THIS SB BECOME AN AD.					1	H	7	1 	3O				3A12    					 
1996072500404	19960725	00404	EA  	1996	7	25	96ZZZX3700       	2	19960625	G	7414	M3065	ROTOR           	SLICK       	4347        	BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  					MAGNETO	SHAFT FAILED    	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	199Q	205  			94120022	TD581	L655351A			ENGINE NO START.  TROUBLESHOOTING ISOLATED TO MAGNETO.  OPENED MAGNETO HOUSING TO INSPECT.  REMOVED DISTRIBUTOR BLOCK AN	D GEAR ASSEMBLY.  NOTICED ROTOR GEAR APPEARED DETACHED.  REMOVED GEAR AND FOUND SHAFT HAD BROKEN AT AREA BELOW POINT CAM	 SLOT.  SLOTTED PORTION OF SHAFT REMAINED IN ROTOR GEAR.  BREAK AREA APPEARED TO HAVE HAD MATERIAL DEFECT/CORROSION FROM	 DISCOLORED DARK AREA.  SUBMITTER STATED DUE TO LOW TIME, SUSPECT DEFECTIVE MATERIAL.			1	L	7	2 	3O	3	O		3A16    	1E10				 
1996072500405	19960725	00405		1996	7	25	96ZZZX3701       	4	19960601	G	3418	599160	TRANSDUCER      			PIPER 	PA46  	PA46350P    		SO  										LT WING LIFT	FAILED          	B		A	AMYR	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			CE	05	9261Z	10   			394	4636016				STALL WARNING FAIL LIGHT ON BECAUSE OF FAILED PRIMARY COIL OF LIFT TRANSDUCER.  THIS IS THE SECOND ONE FAILED ON THIS AI	RCRAFT.  FIRST TRANSDUCER HAD 140 HOURS TTSN.  THE SECOND LASTED 10.0 HOURS.  BOTH FAILED FOR SAME MECHANICAL FAULT, PRI	MARY COIL OPEN.  AIRCRAFT MANUFACTURER HAS RECORDED SEVERAL OF THESE FAILURES.  SUGGESTIONS ARE TO USE STALL TEST SWITCH	 FOR TESTS, AND TO NEVER TOUCH TRANSDUCER, ESPECIALLY DURING WASHING AIRCRAFT.			1	L	7	1 	3O			RT	A25SO   					 
1996072500406	19960725	00406	SO  	1996	7	25	96ZZZX3702       	2	19960703	G	8550	CH48108	FILTER          	CHAMPION    		BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					ENGINE OIL	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	05	6648K					TJ204	248173R			OIL FILTER CUT OPEN AT OIL CHANGE.  NOTICED INSIDE GASKET WAS CUT AND SLIGHTLY MISALIGNED.  CLOSER LOOK REVEALED METAL P	ORTION WAS CUT APPROXIMATELY ONE INCH AND ONE INCH SLIVER ABOUT .0625 INCH THICK WAS STICKING INTO OIL OUTLET PATH.  HAD	 THIS SLIVER COME LOOSE, IT WOULD HAVE GONE INTO THE ENGINE, POSSIBLY CAUSING A CATASTROPHIC FAILURE.  RECOMMEND STICKIN	G FINGER INTO NEW FILTERS PRIOR TO INSTALLING TO CHECK FOR DEFECTS.			1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1996072500564	19960725	00564	SW  	1996	7	25	96ZZZX3718       	1	19960710	G	5751	2734023011	SPAR            		2734000039  	SWRNGN	SA227 	SA227AC     	8780603	SW  										OTBD HINGE	CRACKED         	G	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	359AE				C096	AC674				DURING DISASSEMBLY OF AILERON FOR SKIN CHANGE, THE SPAR WAS FOUND CRACKED IN TWO PLACES AROUND OUTBOARD HINGE BRACKET. T	HE CRACKS WERE THE FULL WIDTH OF THE SPAR WEB AND INTO THE RADIUS OF THE FLANGES.  THIS IS THE SECOND SPAR FOUND CRACKED	 LIKE THIS RECENTLY.  A MANDATORY VISUAL INSPECTION OF THE AILERON SPAR IS STRONGLY RECOMMENDED.				2	L	7	2 	4T			RT	A8SW    					 
1996072500565	19960725	00565	EA  	1996	7	25	96ZZZX3719       	1	19960627	G	2913	24535	FACE SEAL       	ABEX        	6310806     	CNDAIR	CL600 	CL6002A12   	1900304	EA  										HYDRAULIC PUMP	GOUGED          	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	CFURG				23534B	3063				DISASSEMBLED PUMP, FOUND THE NOSE SEAL AND FACE SEALS GOUGED.  INSPECTED THE NOSE SEAL, FOUND THE COATING IN THE O-RING 	BOSS CRACKED AND LIFTING OFF.  NO OTHER FOREIGN MATERIAL FOUND IN THE PUMP CAVITY.					2	L	7	2 	4F			RT	A21EA   					 
1996072500566	19960725	00566	EA  	1996	7	25	96ZZZX3720       	1	19960627	G	2913	24539	NOSE SEAL       	ABEX        	6310806     	CNDAIR	CL600 	CL6002A12   	1900304	EA  										HYDRAULIC PUMP	GOUGED          	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	CFURG				23534B	3063				DISASSEMBLED PUMP, FOUND THE NOSE SEAL AND FACE SEALS GOUGED.  INSPECTED THE NOSE SEAL, FOUND THE COATING IN THE O-RING 	BOSS CRACKED AND LIFTING OFF.  NO OTHER FOREIGN MATERIAL FOUND IN THE PUMP CAVITY.					2	L	7	2 	4F			RT	A21EA   					 
1996072500567	19960725	00567	SW  	1996	7	25	96ZZZX3721       	1	19960626	G	5330		PANEL           			MTSBSI	MU2   	MU2B20      	5780407	SW  										AFT FUSELAGE	WATER LEAK      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	183MA					217				THE AIRCRAFT HAS HAD A HISTORY OF DIRECTIONAL GYRO FAILURE.  AT INSPECTION, WATER WAS RUN OVER THE AFT FUSELAGE AND IT W	AS DISCOVERED THAT WATER WAS COMING IN AT THE AFT FUSELAGE ATTACH HARDWARE ACCESS PANELS RUNNING DOWN THE STRINGER JUST 	UNDER ATTACHING HARDWARE AND DRIPPING ON TOP OF GYRO.  THE PANEL WAS REMOVED, CLEANED, AND REINSTALLED WITH SEALANT.				1	H	7	2 	3T				A2PC    					 
1996072500568	19960725	00568	EU  	1996	7	25	96ZZZX3722       	1	19960703	G	5522	46302402	ELEVATOR        			ISRAEL	1124  	1124        	4500102	EU  										RT ELEV TE	DELAMINATED     	B			GQFG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	342AJ				4354	342				DELAMINATION ON UPPER AND LOWER SURFACES WITH A CRACK ON UPPER TRAILING EDGE.  AIRCRAFT TT:  4,100 HOURS.  LANDINGS, 3,3	40.					2	M	7	2 	4F				A2SW    					 
1996072500569	19960725	00569	EA  	1996	7	25	96ZZZX3723       	1	19960624	G	3240	601R852001	SENSOR          			CNDAIR	CL600 	CL6002B19   		EA  										BRAKE TEMP	BROKEN          	B			FZ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	15	5100X	2754 				7008				DURING ROUTINE BRAKE CHANGE, NOTICED THE BRAKE TEMPERATURE SENSOR WAS UNSERVICEABLE DUE TO A CRACK GOING ALL THE WAY ARO	UND THE BASE OF THE PROBE.  THE SENSOR WS REPLACED AND THE BRAKE CHANGE WAS COMPLETED.  AIRCRAFT WAS RETURNED TO SERVICE	.  SUBMITTER RECOMMENDATION WOULD BE TO BEEF UP THE PROBE DIAMETER AT THE BASE.				2	L	7	2 	4F			RT	A21EA   					 
1996072500570	19960725	00570	EU  	1996	7	25	96ZZZX3724       	1	19960703	G	7830	2660042505	LONGERON ASSY   	ROHR        	2660003505  	BRAERO	1000  	BAE1251000  	1500287	EU  										LT ENG T/R	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	513QS	2983 			CUM37	NA1004				FOUND CRACK ON LEFT ENGINE THRUST REVERSER UPPER DOOR INBOARD LONGERON ASSEMBLY, ABOUT 2 INCHES FROM BUMPER.  LONGERON A	SSEMBLY IS WEAK IN MACHINED AREA WHICH IS WHERE THE CRACK IS LOCATED.					2	L	7	2 	4F			RT	A3EU    					 
1996072500572	19960725	00572	SW  	1996	7	25	96ZZZX3726       	1	19960621	G	7120	NAS627H46	BOLT            	LORD        	LM600       	SWRNGN	SA227 	SA227TT     		SW  										ENGINE MOUNT	IMPROPER        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25										SECOND OCCURRENCE ON THIS TYPE AIRCRAFT WITH HEAVY TRUSS.  SIDE MOUNT ISOLATOR THROUGH-BOLT DOES NOT ENGAGE LOCKING DEVI	CE IN ENGINE MOUNT TRUSS.  VENDOR (LORD) CALLS FOR NRS627-H46 AND LM427-10 WASHER.  FAIRCHILD CALLS FOR NAS627-50 WITH M	S20002C7 WASHER.  USING VENDOR HARDWARE REDUCES LENGTH OF ENGAGEMENT BY .295 INCH.  SAFETY WIRE HOLE IN HEAD OF BOLT ON 	THIS TYPE AIRCRAFT SHOULD BE REASON ENOUGH TO INSPECT MORE CLOSELY.			2	L	7	2 	4T			RT	A5SW    					 
1996072500573	19960725	00573	SW  	1996	7	25	96ZZZX3727       	1	19960627	G	2910	27810322682	LINE            			FRCHLD	SA227 	SA227DC     	3377521	SW  										RT FIREWALL	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	01	3005W	2441 				DC801M				HYDRAULIC LINE CRACKED IN RADIUS OF 90 DEGREE BEND.  ALL AIRCRAFT HYDRAULIC PRESSURE LOST WITHIN 10 MINUTES.  THIS LINE 	AND OTHERS ARE SPECIFIED FOR REPLACEMENT AND/OR INSPECTION PER FAIRCHILD SB CC7-29-001 WITH NO SPECIFIC TIME REQUIREMENT	.  SUBMITTER RECOMMENDS AN AD TO AVOID CONTINUED USE OR PROLONGED USE BEFORE INSPECTION OR REPLACEMENT.				2	L	7	2 	4T			RT	A18SW   					 
1996072500574	19960725	00574	GL  	1996	7	25	96ZZZX3728       	2	19960607	G	7200		ENGINE          			DOUG  	DC10  	DC1030      	3023501	WP  	GE    	CF6   	CF66D       	30020	GL  					NR 3	FIRE            	B			ZUFY	K				NONE                    				A			FLAME/FIRE                			IN	INSP/MAINT     	1			EA	35	833LA					46937				DURING ENGINE START ON PUSH-BACK, NR 3 ENGINE SUFFERED A JET-PIPE FIRE AT MANCHESTER.  FIRE EXTINGUISHED BY AIRPORT FIRE	 SERVICE.  NO DAMAGE.  AIRCRAFT HISTORY OF FUEL FLOW PROBLEMS.  FIRE OCCURRED ON SECOND ATTEMPT TO START.  NR 3 ENGINE, 	NR 2 FIRE BOTTLE USED, NO EFFECT.  NR 1 FIRED.  OK.  FULL REPORT TO FOLLOW.				2	L	7	3 	4F	4	F		A22WE   	E23EA				 
1996072500575	19960725	00575	SW  	1996	7	25	96ZZZX3729       	1	19960705	G	6310	206040118001	COUPLING        			BELL  	206   	206B        	1181511	SW  										M/R DRIVE	DEFECTIVE       	B			GS1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	144H	18   			A8966	4348				INSPECTION FOUND COUPLING NOT PROPERLY COATED.  REPLACED WITH NEW COUPLING.						1	G	7	1 	3U				H2SW    					 
1996012600449	19960126	00449	SO  	1996	1	26	96ZZZX373        	1	19960103	G	3230	4198301	HOOK ASSY       			PIPER 	PA31  	PA31        	7103102	SO  										RT MLG	STUCK           	B			CS3R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	17	310DS	4278 				31579				RIGHT GEAR WOULD NOT INDICATE DOWN IN THE AIR.  AIRCRAFT MADE EMERGENCY LANDING.  INSPECTED RIGHT GEAR, FOUND DOWNLOCK H	OOK STUCK.  REMOVED PIVOT BOLT AND HOOK.  CLEANED AND LUBED.  REINSTALLED HOOK.  GEAR SWING OK.					1	L	7	2 	3O				A20SO   					 
1996072500576	19960725	00576	SW  	1996	7	25	96ZZZX3730       	1	19960604	G	2150	JBS2201	COMPRESSOR      			BELL  	206   	206B        	1181511	SW  										COOLING  SYSTEM	INTERFERENCE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09										BHT 206, TH-67 IFR AIRCRAFT WITH ENVIRONMENTAL COOLING SYSTEM OPERATING, WHEN THE HSI IS IN 'SLAVE' POSITION, THE HSI NE	EDLE DRIFTS 4 TO 6 DEGREES.  SUSPECT EMI FROM ENVIRONMENTAL COOLING SYSTEM COMPRESSOR CLUTCH ASSEMBLY.  SUBMITTER STATES	 THE INTERFERENCE IS OCCURRING ON ALL 206B SERIES ROTORCRAFT.				1	G	7	1 	3U				H2SW    					 
1996072500577	19960725	00577	GL  	1996	7	25	96ZZZX3731       	2	19960110	G	7323	A1AA1	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					N2 GOVERNOR	SHAFT SEPARATED 	D	P			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	8625F	1338 	327  		13605	470111D	CAE830515			ENGINE RPM DROOPED.  REMOVED N2 GOVERNOR AND FOUND DRIVE SPLINE, SPRING AND WASHERS HAD FALLEN OFF.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996072500579	19960725	00579	EU  	1996	7	25	96ZZZX3733       	1	19960712	G	2742		ACTUATOR        			ISRAEL	1124  	1124        	4500102	EU  										PITCH TRIM	SHAFT SHEARED   	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	317MB		2734 			432				DURING A 600-HOUR ROUTINE INSPECTION, NOTED A PORTION OF THE HORIZONTAL STABILIZER WAS STRIKING THE FUSELAGE AND CAUSING	 PAINT DAMAGE.  AFTER FURTHER INVESTIGATION DETERMINED THE PITCH TRIM ACTUATOR SHAFT HAD SHEARED.  THE PITCH TRIM ACTUAT	OR IS ATTACHED TO THE HORIZONTAL STABILIZER WITH 2 ROD END SHAFTS.  PRESENTLY, THERE IS NO LIFE-LIMIT ON THIS PART.				2	M	7	2 	4F				A2SW    					 
1996080200061	19960802	00061	EU  	1996	8	2	96ZZZX3736       	1	19960620	G	7712	30573136A	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT TORQUE	FAILED          	B			SZTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	911NW				1192	1605				PILOT REPORTED NO TORQUE INDICATION.  REPLACED GAUGE.  STILL NO TORQUE INDICATION.  REPLACED GAUGE.  OPS CHECKED GOOD.						1	G	7	1 	3U				H9EU    					 
1996080200191	19960802	00191	NM  	1996	8	2	96ZZZX3745       	1	19960710	G	8012	2701321	HOUSING         		2730426     	BOEING	737   	737*        		NM  										AIR START	CRACKED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			20280		015L					THE START VALVE HOUSING, PN 2701321, IS CRACKED UNDER THE IDENTIFICATION PLATE CAUSING AIR TO ESCAPE THROUGH THE CRACK A	ND THE VALVE TO MALFUNCTION.  HAVE RECEIVED SEVERAL UNITS WITH THIS DEFECT/DAMAGE.  THE SUSPECTED CAUSE IS THE OVERTORQU	ING OF THE FILTER WHEN THE VALVE IS INSTALLED ON THE AIRCRAFT.  SUBMITTER RECOMMENDS THE MANUFACTURER LOOK AT THE DESIGN	 OF THE HOUSING TO PREVENT AND CORRECT THE PROBLEM OF CRACKING.  THE AREA OF THE HOUSING THAT IS CRACKING IS A THIN CAST	ING AREA.		2	L	7	2 	4F			RT	A16WE   					 
1996080200192	19960802	00192	NM  	1996	8	2	96ZZZX3746       	1	19960710	G	3610	31737772	ROD ASSY        		32895624    	BOEING	737   	737*        		NM  										COOLER VALVE	CHAFED          	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		693  			960C					MUTUAL CONTACT HAS CAUSED SEVERE CHAFING BETWEEN PIVOT ARMS OF ROD ASSY AND FLAT PIVOT AREA OF LEVER.  THIS OCCURRED DUR	ING NORMAL OPERATION.  TOO SOFT STEEL USED IN MANUFACTURE.  SUBMITTER STATED TO PREVENT RECURRENCE, HARDEN STEEL AND ALL	OW PIVOT ARM ROD TO ROTATE.				2	L	7	2 	4F			RT	A16WE   					 
1996080200193	19960802	00193	NM  	1996	8	2	96ZZZX3747       	1	19960710	G	3610	31776561	LEVER           		32895624    	BOEING	737   	737*        		NM  										COOLER VALVE	CHAFED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		693  								MUTUAL CONTACT HAS CAUSED SEVERE CHAFING BETWEEN PIVOT ARMS OF ROD ASSY AND FLAT PIVOT AREA OF LEVER.  THIS OCCURRED DUR	ING NORMAL OPERATION.  TOO SOFT STEEL USED IN MANUFACTURE.  SUBMITTER STATED TO PREVENT RECURRENCE, HARDEN STEEL AND ALL	OW PIVOT ARM ROD TO ROTATE.				2	L	7	2 	4F			RT	A16WE   					 
1996080200194	19960802	00194	CE  	1996	8	2	96ZZZX3748       	1	19960618	G	3233	98820001	ACTUATOR        			CESSNA	210   	P210N       	2073454	CE  										LT MLG	CRACKED         	B	S		BX4R	K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	03	18DP	1125 			2330	P21000086				AFTER A HARD OFF-FIELD LANDING, FOUND LEFT MAIN ACTUATOR HOUSING CRACKED ADJACENT TO AND ALONG THE AFT PART OF THE UPPER	 SEAM OF THE HOUSING.  CRACK RUNS FROM AFT END, FORWARD TO THE BASE OF BOSS FOR 'AN' FITTING.  ENTIRE LENGTH OF CRACK IS	 OPEN APPROXIMATELY .1250 INCH.				1	H	7	1 	3O				3A21    					 
1996080200195	19960802	00195	CE  	1996	8	2	96ZZZX3749       	1	19960418	G	5711	0411131	SPAR            			CESSNA	140   	140         	2071602	CE  										LT DOOR POST	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2408N	288  				12657				THIS IS THE THIRD TIME THIS SPAR HAS BEEN CRACKED.  THIS AIRCRAFT IS ON EDO 88-1650 FLOATS.  IT IS NECESSARY TO REMOVE T	HE FORWARD END OF THE HEADLINER TO INSPECT THIS AREA.  AIRCRAFT TT, 3,042.39 HOURS.					1	H	7	1 	3O			NC	A768    					 
1996080200196	19960802	00196	SO  	1996	8	2	96ZZZX3750       	2	19960701	G	8550	15000793	NIPPLE          			CESSNA	337   	T337C       	2075714	CE  	CONT  	O360  	TSIO360A    	17025	SO  					ACCESSORY CASE	FAILED          	B		A	DJ3R	A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	17	2522S					3370822	197111R			THE RIGID PIPE NIPPLE THAT IS THREADED INTO ACCESSORY CASE BETWEEN MAGNETOS FAILED AT THE BOTTOM OF THE THREAD GROOVE FL	USH WITH THE ACCESSORY CASE.  THIS ALLOWED RETURN OIL FROM THE WASTEGATE CONTROLLERS TO GO OVERBOARD.  THE PILOT SAW THE	 OIL PRESSURE DROPPING.  SHUT DOWN ENGINE AND MADE A SAFE LANDING.  THE PART INSTALLED IN FACTORY REBUILT ENGINE.  ENGIN	E TIME AT FAILURE 172 HOURS.  FAILURE WAS CAUSED BY METAL FATIGUE AND CONCENTRATED STRESS OF A RIGID ARM PROTRUDING 8 IN	CHES SUPPORTING A T-FITTING AND TWO HOSES.  THIS IS A CESSNA PART ALTHOUGH IT CAME FROM CONTINENTAL ON THE ENGINE.		1	H	7	2 	3O	3	O		A6CE    	E9CE				 
1996080200197	19960802	00197	SO  	1996	8	2	96ZZZX3751       	1	19960624	G	2430	454712	BREAKER         			PIPER 	PA31  	PA31350     	7103110	SO  										ALT CIRCUIT	FAILED          	B		A	HX1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	3529N	33   				31792167				SUBMITTER REPORTS THIS IS THE 4TH CIRCUIT BREAKER SWITCH THAT FAILED INTERNALLY.  BREAKERS HAVE ALL FAILED IN THE SAME M	ANNER.  IF HELD IN THE 'ON' POSITION, THEY WILL WORK, BUT AS SOON AS RELEASED, THEY STOP WORKING AND SHUT THE ALTERNATOR	 OFF.  SUBMITTER STATED ALL 4 FAILURES ARE IN SAME AIRCRAFT AND HAVE TAKEN PLACE IN LAST 6 MONTHS.				1	L	7	2 	3O				A20SO   					 
1996080200198	19960802	00198	SO  	1996	8	2	96ZZZX3752       	1	19960501	G	5210	4834800	MOUNT BRACKET   			PIPER 	PA31T 	PA31T       	7103124	SO  										DOOR SNUBBER	FAILED          	B		A	EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	618SW	4244 				31T8166036				CABIN DOOR SNUBBER UPPER MOUNT BRACKET TORE AWAY FROM FORWARD DOOR FRAME BULKHEAD AS PASSENGER WAS EXITING THE AIRCRAFT.	  PASSENGER APPARENTLY DID NOT ALLOW DOOR TO FULLY OPEN BEFORE STEPPING OUT ONTO IT.  FURTHER INVESTIGATION OF BULKHEAD 	SHOWED EVIDENCE OF PRE-EXISITNG CRACKS EMANATING FROM RIVETS IN THE SNUBBER MOUNT AREA.  SUBMITTER RECOMMENDS PUBLISHING	 AN ALERT FOR THESE AIRCRAFT TO BE INSPECTED FOR CRACKS IN THIS AREA.  ALSO, THESE CABIN DOORS SHOULD BE PLACARDED FOR C	REW OPERATION ONLY.		1	L	7	2 	3T				A8EA    					 
1996080200199	19960802	00199		1996	8	2	96ZZZX3753       	4	19960521	G	2564	1021	CYLINDER        	HOOVERIND   	FR46        															LIFE RAFT	RUSTED          	B			OD1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25					A649687					THIS FACILITY RECEIVED A HOOVER IND MODEL FR-46, S/N J47 FOR OVERHAUL.  UPON INSPECTION AND PRIOR TO PERFORMING A HYDROS	TATIC RE-TEST, THE TWO INSTALLED INFLATION CYLINDERS WERE FOUND TO HAVE INTERNAL RUST.   (CAUSE FOR REJECTION.)  BOTH CY	LINDERS HAVE A 521 94 RE-TESTER STAMP ON THE CYLINDERS.  SUSPECT CAUSE FOR INTERNAL RUST COULD BE DUE TO NOT HAVING BEEN	 DRIED THOROUGHLY AFTER LAST HYDROSTATIC RE-TEST.																 
1996080200200	19960802	00200		1996	8	2	96ZZZX3754       	4	19960521	G	2564	1021	CYLINDER        	HOOVERIND   	FR46        															LIFE RAFT	RUSTED          	B			OD1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25					A685062					THIS FACILITY RECEIVED A HOOVER IND MODEL FR-46, S/N J47 FOR OVERHAUL.  UPON INSPECTION AND PRIOR TO PERFORMING A HYDROS	TATIC RE-TEST, THE TWO INSTALLED INFLATION CYLINDERS WERE FOUND TO HAVE INTERNAL RUST.   (CAUSE FOR REJECTION.)  BOTH CY	LINDERS HAVE A 521 94 RE-TESTER STAMP ON THE CYLINDERS.  SUSPECT CAUSE FOR INTERNAL RUST COULD BE DUE TO NOT HAVING BEEN	 DRIED THOROUGHLY AFTER LAST HYDROSTATIC RE-TEST.																 
1996080200201	19960802	00201		1996	8	2	96ZZZX3755       	4	19960521	G	2564	1021	CYLINDER        	HOOVERIND   																LIFE RAFT	RUSTED          	B			OD1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25					D468310					TWO REPLACEMENT CYLINDERS RECEIVED FROM HOOVER IND FOR A MODEL FR-46 LIFE RAFT WERE FOUND TO BE UNACCEPTABLE.  THESE CYL	INDERS WERE MANUFACTURED IN 8/95 AND 1/96.  THESE CYLINDERS WERE TO BE REPLACEMENTS FOR THE TWO INSTALLED ON THE RAFT AN	D WERE FOUND TO HAVE INTERNAL RUST.																	 
1996080200202	19960802	00202		1996	8	2	96ZZZX3756       	4	19960521	G	2561	1021	CYLINDER        	HOOVERIND   																LIFE RAFT	RUSTED          	B			OD1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25					D303107					TWO REPLACEMENT CYLINDERS RECEIVED FROM HOOVER IND FOR A MODEL FR-46 LIFE RAFT WERE FOUND UNACCEPTABLE.  THESE CYLINDERS	 WERE MANUFACTURED IN 8/95 AND 1/96.  THESE CYLINDERS WERE TO BE REPLACEMENTS FOR THE TWO INSTALLED ON THE RAFT AND WERE	 FOUND TO HAVE INTERNAL RUST.																	 
1996080200203	19960802	00203	EA  	1996	8	2	96ZZZX3757       	2	19960318	G	7414	1016301010	MAGNETO         		S6L200      	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					DRIVE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	123CF	550  			J229127EX	278054017				MAGNETO WAS FOUND WITH DRIVE NUT HAVING NO THREADS AND NO THREADS ON DRIVE.						1	L	7	2 	3O	3	O		1A10    	E14EA				 
1996080200204	19960802	00204	SO  	1996	8	2	96ZZZX3758       	1	19960702	G	2752	489428	TRANSMISSION    	DUKES       	121600011190	PIPER 	PA31T 	PA31T       	7103124	SO  										RT FLAP	FAILED          	D				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			WP	19	155CA	6667 			1190	31T7820024				ON APPROACH TO SVE WITH FLAPS FULLY EXTENDED, THE RT FLAP SUDDENTLY RETRACTED CAUSING SEVERE YAW.  LT FLAP WAS RETRACTED	 AND REGAINED CONTROL.  ABORTED LANDING AND RETURNED TO RNO.  TRANSMISSION FAILED INTERNALLY.  DRIVEN GEAR DISINTEGRATED	.  NOTE:  WEAR CHECKS PERFORMED PER AD 82-27-13R2 EACH 100 HOURS.  SUBMITTER RECOMMENDS REPLACING OLDER DUKES TRANSMISSI	ONS AND DECREASING THE INTERNAL INSPECTION INTERVAL.			1	L	7	2 	3T				A8EA    					 
1996080200205	19960802	00205	CE  	1996	8	2	96ZZZX3759       	1	19960711	G	5711		CARRY THROUGH   			BEECH 	33    	F33A        	1151425	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1556A	7942 				CE1318				INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE.  AD 95-04-03 NOT VALID BY SERIAL NUMBER.						1	L	7	1 	3O				3A15    					 
1996080200206	19960802	00206	CE  	1996	8	2	96ZZZX3760       	1	19960711	G	5711		CARRY THROUGH   			BEECH 	33    	F33A        	1151425	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1564A	8241 				CE1321				INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE.  AD 9504-03 NOT VALID BY SERIAL NUMBER.						1	L	7	1 	3O				3A15    					 
1996080200207	19960802	00207	CE  	1996	8	2	96ZZZX3761       	1	19960711	G	5711		CARRY THROUGH   			BEECH 	33    	F33A        	1151425	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1570A	8242 				CE1333				INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE.  AD 95-04-03 NOT VALID BY SERIAL NUMBER.						1	L	7	1 	3O				3A15    					 
1996080200208	19960802	00208		1996	8	2	96ZZZX3762       	4	19960712	G	2562	7J4193	ELT             	LEIGH       		CESSNA	172   	R172K       	2072431	CE  										G-SWITCH	MALFUNCTION     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1609V				302112	R1722205				EMERGENCY LOCATER TRANSMITTER CESSNA P/N C589510-0209, WOULD NOT PASS G-SWITCH OPERATIONAL CHECK PER FAR 91.207(D).  LIG	HT TOO EXCESSIVE FORCE, WOULD NOT SET OFF G-SWITCH.  ELT WOULD PUT OUT SIGNAL WHEN SWITCHED ON MANUALLY.					1	H	7	1 	3O				3A17    					 
1996080200209	19960802	00209	EA  	1996	8	2	96ZZZX3763       	2	19960705	G	8520		CRANKCASE       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					RT CASE NR 1 CYL	CRACKED         	B			DPOD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	181SP		299  			17268171	RL101576			RIGHT CRANKCASE CRACKED BELOW NR 1 CYLINDER BASE.  CRACK WAS APPROXIMATELY 6 INCHES LONG.  CASE WAS NOT REPAIRABLE.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996080200210	19960802	00210	CE  	1996	8	2	96ZZZX3764       	1	19960316	G	3230	20410306	SHELL ASSY      			CESSNA	172   	172RG       	2072438	CE  										RT/LT MLG	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1989Q	3799 				177RG0389				DURING INSPECTION AND GEAR RETRACTION TEST, FOUND MLG TO HAVE EXCESSIVE FREE PLAY WHEN DOWN AND LOCKED.   UPON INVESTIGA	TION, FOUND MLG DOWNLOCK LATCHES WOULD NOT HOLD LANDING GEAR LEGS LATCHED DUE TO EXCESSIVE CLEARANCE BETWEEN LATCH AND P	IN.  THE SHELL ASSYS WERE FOUND WORN AND THE SHELL INSERT WAS MISSING FROM BOTH RIGHT AND LEFT SHELLS.  AFTER INSTALLATI	ON OF NEW SHELLS AND RIGGING OF MLG, SYSTEM WORKED OK.  SUBMITTER STATES THIS CONDITION COULD HAVE CAUSED COLLAPSE OF TH	E MLG AND INJURY.		1	H	7	1 	3O				3A17    					 
1996080200462	19960802	00462	SO  	1996	8	2	96ZZZX3766       	2	19960713	G	8530	627335D13B	NOZZLE          			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					FUEL INJ	THREADS STRIPPED	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2013S					21060981	294685R			WHEN REMOVING FUEL INJECTOR NOZZLE FOR CLEANING AT FIRST 91-HOUR TSMOH, FACTORY REMANUFACTURE, NOZZLE CAME OUT OF CYLIND	ER HEAD WITH ALUMINUM, STRIPPED THREADS IN CLYINDER HEAD.					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996080200463	19960802	00463	CE  	1996	8	2	96ZZZX3767       	1	19960710	G	2823	45920036	FUEL SELECTOR   			BEECH 	35    	V35         	1151538	CE  										RT TANK FEED	O-RING DEFECTIVE	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2011W				EM3065	D7989				FUEL SELECTOR O-RING FOR THE RIGHT TANK FEED WAS RAISED BETWEEN THE SELECTOR BODY AND PLATE ALLOWING CONTINUOUS FEED OF 	FUEL FROM THE RIGHT TANK.  THE FUEL SELECTOR WAS NOT DETERMINED TO BE A FACTOR IN THIS ACCIDENT.					1	L	7	1 	3O				3A15    					 
1996080200464	19960802	00464		1996	8	2	96ZZZX3768       	4	19960712	G	2562	7J4193	ELT             	LEIGH       	SHARC7      	CESSNA	210   	210         	2073402	CE  										G SWITCH	MALFUNCTION     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	210AK				301604	21061627				CESSNA PART NR C589510-0290.  MANUFACTURED TO TSO-C91, WOULD NOT PASS G-SWITCH OPERATIONAL CHECK PER FAR 91.207(D) EVEN 	AFTER SLAMMING ELT INTO GROUND IN DIRECTION OF FLIGHT.  ELT WOULD PUT OUT SIGNAL WHEN MANUALLY SWITCHED TO ON.					1	H	7	1 	3O			RT	3A21    					 
1996080200465	19960802	00465	SO  	1996	8	2	96ZZZX3769       	1	19960710	G	3211	6704213	FITTING         			PIPER 	PA44  	PA44180     	7104402	SO  										AFT TRUNNION	CRACKED         	B	S		YXUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3062H	578  				447995165				PIPER CASTING NR 67043-3 FACF B, CRACKED HORIZONTALLY AT TOP BEARING BOSS.  SUSPECT CAUSE, HARD LANDINGS OR FATIGUED.  I	NSPECTED OTHER STRUCTURES FOR CRACKS.  NONE NOTED AT THIS TIME.					1	L	7	2 	3O				A19S0   					 
1996080200466	19960802	00466	CE  	1996	8	2	96ZZZX3770       	1	19960601	G	3213	0441140	AXLE            			CESSNA	140   	140         	2071602	CE  										RT MLG	BROKE           	G		A		O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			CE	09	3609V	3425 				14877				DURING TAKEOFF FROM PRIVATE TURF STRIP, RT AXLE BROKE AT JUNCTURE OF TUBE AND MOUNTING FLANGE.  RT WHEEL TIRE BRAKE ASSY	 DEPARTED AIRCRAFT.  AIRCRAFT GROUND LOOPED CAUSING SUBSTANTIAL DAMAGE TO AIRCRAFT.  INSPECTION OF AXLE INDICATED A CRAC	K APPROXIMATELY 150 DEGREES OF CIRCUMFERENCE OF TUBE.  CRACKED AREA DISCOLORED INDICATING IN EXISTENCE FOR SOME TIME AND	 WAS LOCATED ON BOTTOM IN THIS INSTALLATION.			1	H	7	1 	3O			NC	A768    					 
1996080200467	19960802	00467	SW  	1996	8	2	96ZZZX3771       	1	19960626	G	2820		FUEL LINE       			SLINDS	100   	100180      	0140208	SW  										DOOR POST	PIERCED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	4078X					5178				DURING ANNUAL, A WET SPOT WAS NOTED ON LT DOOR NEXT TO REAR POST.  ON INVESTIGATION, FOUND IT WAS FUEL FROM A PIN HOLE M	ADE WHEN INSTALLING A RUG WITH STAPLING GUN.  THE STAPLE WENT THROUGH THE FLOOR (PLYWOOD) INTO FUEL LINE.  IT TOOK SEVER	AL YEARS FOR STAPLE TO LOOSEN ENOUGH TO LEAK FUEL.  SUBMITTER STATED STAPLING GUNS SHOULD NOT BE USED FOR INSTALLING RUG	S.  THOSE AIRCRAFT HAVING PLYWOOD FLOORS SHOULD BE CHECKED FOR THIS CONDITION.			1	H	7	1 	3O				1A21    					 
1996080200468	19960802	00468	CE  	1996	8	2	96ZZZX3772       	1	19960503	G	2821	075600514	STRAINER        			CESSNA	210   	210N        	2073453	CE  										FUEL SYSTEM	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	4636U	2400 				21064794				FUEL STRAINER ASSEMBLY FOUND TO HAVE SEVERE CORROSION ON THE INLET TUBE WHERE THE FILTER TOUCHES IT.  THIS CAUSED HOLES 	IN THE TUBE AND ALLOWED UNFILTERED FUEL TO THE ENGINE.  SUBMITTER STATED SAME PART NUMBER IS USED ON ALL 82-84 C210'S. S	USPECT DISSIMILAR METALS.				1	H	7	1 	3O				3A21    					 
1996080200469	19960802	00469	CE  	1996	8	2	96ZZZX3773       	1	19960711	G	5711		CARRY-THROUGH   			BEECH 	33    	F33A        	1151425	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5544P	7592 				CE1336				INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE.  AD 95-04-03 NOT VALID BY SERIAL NUMBER.						1	L	7	1 	3O				3A15    					 
1996080200470	19960802	00470	SO  	1996	8	2	96ZZZX3774       	2	19960711	G	8530	635448CP	CYLINDER        			CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520H    	17040	SO  					NR 3	SEPARATED       	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	07	6308H		1018 			20700476	506728			PILOT REPORTED ROUGH ENGINE AND LARGE RPM DROP ON MAG CHECK.  INSPECTION FOUND NR 3 CYLINDER CRACKED.  WHEN CYLINDER REM	OVED, IT WAS DISCOVERED THE HEAD WAS COMPLETELY SEPARATED.  BOTTOM SPARK PLUG WAS FOULED.					1	H	7	1 	3O	3	O		A16CE   	E8CE				 
1996080200471	19960802	00471	CE  	1996	8	2	96ZZZX3775       	1	19960705	G	5753	0529018	SUPPORT ASSY    		05239011    	CESSNA	172   	172A        	2072404	CE  										FLAP LT OTBD	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	7558T	4415 				47158				DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED.  INSTALLED FLAP SUPPORT	 KIT SK180-44.  NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS.  SUBMITTER RECOMMENDS THIS SB BECOME AN AD.					1	H	7	1 	3O				3A12    					 
1996080200472	19960802	00472	SO  	1996	8	2	96ZZZX3776       	1	19960624	G	3243	214351	CYLINDER ASSY   	BFGOODRICH  		PIPER 	PA31T 	PA31T2      	7103127	SO  										LT MLG BRAKE	SPLIT           	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	774KV	3487 			377	31T8166057				DURING BRAKE TESTING AFTER OVERHAUL, HYDRAULIC PRESSURE EQUAL TO 150 PSI WAS APPLIED TO BRAKE CYLINDER LEAK CHECK.  THE 	ACTUAL TEST PRESSURE IS 180 PSI PER MANUAL.  AT 150 PSI, THE BRAKE CYLINDER ASSY SPLIT FROM ONE END OF BOLT HOLE APPROXI	MATELY ONE-HALF WAY ACROSS CYLINDER ASSY.  THIS PART APPEARS TO BE ORIGINAL PART ON A/C SINCE NEW.				1	L	7	2 	3T			RT	A8EA    					 
1996080200473	19960802	00473	SO  	1996	8	2	96ZZZX3777       	1	19960204	G	3230	837683D	SEQUENCE VALVE  			PIPER 	PA46  	PA46350P    		SO  										NLG	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	09	9167Q	354  			215	4622031				DURING INVESTIGATION OF LANDING GEAR PROBLEMS, THE HYDRAULIC RESERVOIR WAS FOUND NEARLY EMPTY.  FILLED RESERVOIR AND CHE	CKED FOR LEAKS.  FOUND NLG DOOR SEQUENCE VALVE LEAKING PAST THE PLUNGER.  ALSO, FOUND SEVERAL HYDRAULIC LINES LEAKING AT	 MLG ACTUATORS, AND TWO LINES AT SEQUENCE VALVE.				1	L	7	1 	3O			RT	A25SO   					 
1996080200474	19960802	00474	CE  	1996	8	2	96ZZZX3778       	1	19960711	G	5711		CARRY-THROUGH   			BEECH 	33    	F33A        	1151425	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8268T	5390 				CE1547				INSPECTION FOUND CRACKS IN CARRY-THROUGH STRUCTURE.  AD 95-04-03 NOT VALID BY SERIAL NUMBER.						1	L	7	1 	3O				3A15    					 
1996080200475	19960802	00475		1996	8	2	96ZZZX3779       	4	19960626	G	2562	DMELT61	ELT             			MAULE 	M4    	M4220C      	5460114	SO  										G-SWITCH	MALFUNCTION     	D		A		K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	11	986R				4322	2081C				REMOVED DORNE AND MARGOLIN EMERGENCY LOCATOR TRANSMITTER FOR ANNUAL INSPECTION/FUNCTION CHECK AND BATTERY INSPECTION.  F	OUND THAT FUNCTION CHECK WOULD NOT ACTIVATE ELT.  ELT WOULD WORK IN 'ON' POSITION, BUT NOT IN 'ARM'.  RETURN TO D AND F 	OR REPAIRS.  INV NR 158190.				1	H	7	1 	3O				3A23    					 
1996080200476	19960802	00476	GL  	1996	8	2	96ZZZX3780       	1	19960622	G	2820	MILH6000	FUEL LINE       			AMTR  	KITFOX	KITFOX      	05613LZ	GL  										ENGINE FUEL	DETERIORATED    	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	21	90869				98891	S94070040				DURING RUN-UP TEST PRIOR TO TEST FLIGHT, ENGINE DEMONSTRATED SYMPTOMS OF FUEL STARVATION.  REMOVED FUEL LINE AT SUPPLY O	F FUEL FILTER.  SIGNIFICANT AMOUNTS OF BLACKENED FUEL, RUBBER GLOBULES POURED OUT, FILTER FOULED.  UNABLE TO BLOW AIR TH	ROUGH FUEL LINE, USING 93 OCTANE AMECO WHITE GAS.  (NO OXYIDIZATION ADDITIVE, BUT NOT SURE ABOUT THIS.)  REMOVED ALL FUE	L LINES IN AIRCRAFT AND SLIT OPEN.  FOUND ONE TO HAVE DETERIORATED INSIDE.  FURTHER TESTING OF FUEL LINE IN JAR OF GAS S	HOWS SIGNIFICANT AND RAPID DETERIORATION.		1	H	7	1 	3I			NC	EXPA1H71					 
1996080200477	19960802	00477		1996	8	2	96ZZZX3781       	4	19960712	G	2562	7JH193	ELT             	LEIGH       	SHARC7      	CESSNA	140   	140A        	2071604	CE  										G-SWITCH	MALFUNCTION     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9672A					15393				EMERGENCY LOCATOR TRANSMITTER INSTALLED AS AFTER-MARKET EQUIPMENT, WOULD NOT PASS G-SWITCH OPERATIONAL CHECK PER FAR 91.	207(D).  LIGHT OR EXCESSIVE FORCE IN DIRECTION OF FLIGHT WOULD NOT SET OFF ELT.  NOTE:  ELT WOULD PUT OUT SIGNAL WHEN MA	NUALLY SET TO 'ON' POSITION.				1	H	7	1 	3O				5A2     					 
1996080200478	19960802	00478	SW  	1996	8	2	96ZZZX3782       	1	19960701	G	5530		TAILPOST        			BBAVIA	8     	8GCBC       	1220803	SW  										TAILSPRING PAD	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	88352	9630 				11674				TAILPOST DISCOVERED TO BE CRACKED AROUND THE CIRCUMFERENCE JUST ABOVE THE TAILSPRING PAD.   SUBMITTER SUGGESTS CAUSE FOR	 CRACK DUE TO GROUND HANDLING OVER THE YEARS AND HIGH TIME ON THE AIRFRAME.  THIS POINT IS STRESSED WHEN SWIVELLING THE 	TAILWHEEL DURING GROUND HANDLING.				1	H	7	1 	3O				A21CE   					 
1996080200479	19960802	00479		1996	8	2	96ZZZX3783       	1	19960715	G	8120	633358	CLAMP           		6005739000  															ENGINE TURBO	NOT SAFTIED     	B			APCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01					ZE004706					CLAMP NOT SAFETY WIRED PER PIPER SB 884.  THIS CLAMP SECURES THE COMPRESSOR TO THE TURBINE.																			 
1996080200480	19960802	00480	SO  	1996	8	2	96ZZZX3784       	1	19960711	G	2820	6390115	HOSE ASSY       			PIPER 	PA28  	PA28150     	7102804	SO  										FUEL TANK	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	5909W	3500 				283032				FLEXIBLE FUEL LINE TO FUEL TANK IS HIGHLY CORRODED AND BRITTLE.  BROKE IN HALF UPON TANK REMOVAL.  HOST ASSY WAS ORIGINA	L, DATE - 1965.					1	L	7	1 	3O				2A13    					 
1996080800036	19960808	00036	EU  	1996	8	8	96ZZZX3785       	1	19960514	G	3230	Z00N7070110709	COMPENSATOR     			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										NLG EXTEND	FAILED          	G		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	20FF	1959 				1032				ONE OF THE TWO NOSE GEAR EXTEND COMPENSATORS INSTALLED ON THIS AIRCRAFT LOST ITS AIR CHARGE.  THE NOSE GEAR WOULD NOT EX	TEND PROPERLY DURING AN EMERGENCY GEAR EXTENSION RESULTING FROM A FAILURE DURING NORMAL EXTENSION.  THE AIRCRAFT HAD JUS	T RECEIVED AN ANNUAL INSPECTION, BUT THE COMPENSATORS HAD NOT BEEN CHECKED.  SUBMITTER STATED THE CURRENT MANUFACTURER'S	 MM PROCEDURES FOR EXTENSION/RETRACTION DID NOT SPECIFY THE NEED TO CHECK THEM, THOUGH IT WAS ON THEIR CHECKLIST, WHICH 	HAD NOT BEEN USED.		1	L	7	1 	3O			RT	A51EU   					 
1996080800037	19960808	00037	CE  	1996	8	8	96ZZZX3786       	1	19960616	G	3234	363800501	SWITCH          			BEECH 	58    	58          	1152740	CE  										GEAR LEVER	CAM FAILED      	G		A		O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			EA	25	3174B				1341	TH1724				DURING TAKEOFF ROLL AT ROTATION SPEED, AIRCRAFT LANDING GEARS RETRACTED WHILE THE GEAR LEVER WAS IN THE 'DOWN' POSITION.	  PROPELLER TIPS STRUCK PAVEMENT AND PILOT RETARDED THROTTLES CAUSING THE AIRCRAFT TO SKID ON ITS LOWER FUSELAGE UNTIL I	T CAME TO A STOP AT THE END OF THE RUNWAY.  RECOMMEND THAT CAM ASSY ON GEAR LEVER SHAFT BE DRILLED AND A ROLL PIN INSTAL	LED TO PREVENT CAM FROM COMING LOOSE ON SHAFT.  IN THIS CASE, THE CAM CAME LOOSE AND ALLOWED THE MICROSWITCH TO STAY IN 	THE 'UP' POSITION ALLOWING GEARS TO RETRACT.		1	L	7	2 	3O				3A16    					 
1996080800038	19960808	00038	CE  	1996	8	8	96ZZZX3787       	1	19960625	G	5741	08113508	FITTING         			CESSNA	402   	402C        	207590R	CE  										RT WING	CORRODED        	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	821AN	19463				402C0257				OWNER/OPERATOR FOUND RT WING WOULD CREAK AND GROAN WHEN WING WAS FLEXED.  INSPECTION REVEALED THE LOWER FORWARD MAIN SPA	R ATTACH FITTINGS WERE WORN AROUND THE ATTACH BOLT.  THE BOLT WAS FOUND TO BE IN GOOD CONDITION.  AFTER REMOVAL OF THE F	ITTINGS, FOUND THE BOLT HOSE SLIGHTLY ELONGATED AND CORROSION WITH PITTING ON THE MATING SURFACES OF THE WING FITTINGS. 	 SUBMITTER STATED AD 79-10-15/ME79-16AR4 AND CONTINUED AIRWORTHINESS 57-10-01 TOUCH ON THE SUBJECT OF SPAR FITTINGS, HOW	EVER, NONE OF THE AFOREMENTIONED APPLY TO THE 402 'C' SERIES OF AIRCRAFT.		1	L	7	2 	3O				A7CE    					 
1996080800039	19960808	00039	CE  	1996	8	8	96ZZZX3788       	1	19960625	G	5741	082255020	FITTING         			CESSNA	402   	402C        	207590R	CE  										RT WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	821AN	19463				402C0257				OWNER/OPERATOR FOUND RT WING WOULD CREAK AND GROAN WHEN WING WAS FLEXED.  INSPECTION REVEALED THE LOWER FORWARD MAIN SPA	R ATTACH FITTINGS WERE WORN AROUND THE ATTACH BOLT.  THE BOLT WAS FOUND TO BE IN GOOD CONDITION.  AFTER REMOVAL OF THE F	ITTINGS, FOUND THE BOLT HOSE SLIGHTLY ELONGATED AND CORROSION WITH PITTING ON THE MATING SURFACES OF THE WING FITTINGS. 	 SUBMITTER STATED AD 79-10-15/ME79-16AR4 AND CONTINUED AIRWORTHINESS 57-10-01 TOUCH ON THE SUBJECT OF SPAR FITTINGS, HOW	EVER, NONE OF THE AFOREMENTIONED APPLY TO THE 402 'C' SERIES OF AIRCRAFT.		1	L	7	2 	3O				A7CE    					 
1996080800040	19960808	00040	CE  	1996	8	8	96ZZZX3789       	1	19960625	G	5741	082255026	FITTING         			CESSNA	402   	402C        	207590R	CE  										RT WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	821AN	19463				402C0257				OWNER/OPERATOR FOUND RT WING WOULD CREAK AND GROAN WHEN WING WAS FLEXED.  INSPECTION REVEALED THE LOWER FORWARD MAIN SPA	R ATTACH FITTINGS WERE WORN AROUND THE ATTACH BOLT.  THE BOLT WAS FOUND TO BE IN GOOD CONDITION.  AFTER REMOVAL OF THE F	ITTINGS, FOUND THE BOLT HOSE SLIGHTLY ELONGATED AND CORROSION WITH PITTING ON THE MATING SURFACES OF THE WING FITTINGS. 	 SUBMITTER STATED AD 79-10-15/ME79-16AR4 AND CONTINUED AIRWORTHINESS 57-10-01 TOUCH ON THE SUBJECT OF SPAR FITTINGS, HOW	EVER, NONE OF THE AFOREMENTIONED APPLY TO THE 402 'C' SERIES OF AIRCRAFT.		1	L	7	2 	3O				A7CE    					 
1996080800041	19960808	00041	SO  	1996	8	8	96ZZZX3790       	1	19960715	G	3230	025702	FITTING         			PIPER 	PA32  	PA32R301    	7103218	SO  										NLG DRAG LINK	CRACKED         	D	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	3327P					3213013				WHILE INSPECTING THE NOSE GEAR ASSY, FOUND THE SUPPORT ASSY THAT WAS INSTALLED IN PIPER KIT P/N 766-253 WAS CRACKED.  TH	IS KIT WAS INSTALLED TO C/W AD 93-05-10 AND SB 955.  WHEN THE NOSE GEAR IS FULLY RETRACTED, THE DRAG LINK INTERFERES WIT	H FITTING (P/N 02570-2) THAT WAS ALSO INSTALLED WITH THE KIT.  THE FITTING DID NOT HAVE THE AREAS MILLED OUT.  SUBMITTER	 STATED THIS IS THE SECOND TIME THE INCORRECT PARTS INSTALLED CAME WITH THE KIT FROM PIPER.  AFTER CONTACTING PIPER ON T	HE FIRST KIT, WAS TOLD SOME OF THE FIRST KITS DELIVERED MAY HAVE HAD A FITTING THAT WAS INCORRECTLY MILLED.		1	L	7	1 	3O				A3SO    					 
1996080800042	19960808	00042	SO  	1996	8	8	96ZZZX3791       	1	19960618	G	5553	2074908	ANGLE           			PIPER 	PA24  	PA24250     	7102404	SO  										VERT STAB ATTACH	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	6387P	3930 				241497				DURING AN ANNUAL INSPECTION, A 0.300 INCH CRACK WAS FOUND IN THE FORWARD ATTACH SPAR (FUSELAGE) ANGLE AFT OF THE CHANNEL	 (P/N 20749-0).  PIPER AD 75-12-06 REQUIRES INSPECTION OF THE BEND RELIEF HOLE IN THE CHANNEL AND STRAPS (PN 207 9-5 AND	 DASH 6).  NO CRACKS WERE NOTED IN THESE PARTS.  AIRCRAFT HAD NO RECORD OR INDICATIONS OF CRASH DAMAGE/GROUND DAMAGE.  P	ART REPLACED WITH SERVICEABLE ANGLE.			1	L	7	1 	3O				1A15    					 
1996080800043	19960808	00043		1996	8	8	96ZZZX3792       	2	19960626	G	7414	M3529	IMPULSE COUPLING	SLICK       	4374        															MAG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17		140  			93060026					THE FOLLOWING WAS NOTED DURING OVERHAUL OF SUBJECT MAGNETO.  THE IMPULSE COUPLING ASSEMBLY HAD EVIDENCE OF FAILURE.  THE	 PAWLS ROLLED OVER AND THE CAM ASSEMBLY CAME APART.																		 
1996080800044	19960808	00044		1996	8	8	96ZZZX3793       	2	19960626	G	7414	M3827	ROTOR GEAR      	SLICK       	4373        															MAG	LOOSE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17		140  			93060026					THE FOLLOWING WAS NOTED DURING OVERHAUL OF SUBJECT MAGNETO.  THE ROTOR SHAFT GEAR CAME LOOSE AND TRAVELLED ON THE SHAFT 	UNTIL CONTACT WAS MADE ON THE BLOCK.																		 
1996080800045	19960808	00045		1996	8	8	96ZZZX3794       	2	19960626	G	7414	M3485	BEARING CAP     	SLICK       	4373        															MAGNETO	LOOSE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17		140  			93060026					THE FOLLOWING PROBLEM WAS NOTED DURING OVERHAUL OF SUBJECT MAGNETO.  THE BEARING CAP ASSEMBLY WAS LOOSE IN THE HOUSING.																			 
1996080800046	19960808	00046	SO  	1996	8	8	96ZZZX3795       	2	19960712	G	8530	653445	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					ENGINE	CRACKED         	B			LNCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	3695V	1315 				TH1183	282448R			ON INSPECTION, THE CYLINDER WAS FOUND TO HAVE A CRACK FROM THE SPARK PLUG BOSS TO THE FUEL NOZZLE.  THE CRACK TRAVELS AL	ONG THE CASTING MARK ON THE CYLINDER.  THE CYLINDER WAS STILL HOLDING 78/80.  SUBMITTER BELIEVES THAT THIS IS A MANUFACT	URING PROBLEM.				1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996080800047	19960808	00047	SO  	1996	8	8	96ZZZX3796       	1	19960710	G	5700		LIFT STRUT      			PIPER 	PA12  	PA12        	7101202	SO  										WING RT REAR	CORRODED        	B			CO4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3155M					121857				INSPECTION FOUND RIGHT REAR STRUT WITH LARGE AMOUNT OF CORROSION, LOWER 15 INCHES OF STRUT.  DENSITY CHECK:  COMPARITOR 	SHIM = 3.69 H.D., CORROSION = 4.23 H.D.					1	H	7	1 	3O				A780    					 
1996080800048	19960808	00048	NE  	1996	8	8	96ZZZX3797       	2	19960719	G	7322	PD12FS	CARBURETOR      	BENDIX      		DOUG  	DC3   	DC3         	3021401	WP  	PWA   	R1830 	R183090D    	52020	NE  					ENGINE	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	32MS				740817A	4978	CP350411			ENGINE WILL NOT IDLE, DIES/RESTARTS OK.  WILL NOT TAKE THROTTLE.  WANTS TO BACKFIRE THROUGH CARBURETOR.  REMOVED CARBURE	TOR.  REPLACED WITH OVERHAULED UNIT.					2	L	7	2 	4R	4	R		A669    	5E4				 
1996080800049	19960808	00049	EA  	1996	8	8	96ZZZX3798       	2	19960624	G	8520	11B200511SL	CRANKCASE       			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A1A    	41514	EA  					NR 1 CYL AFT	CRACKED         	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			WP	17	3675Q		773  		313296	MA266	L549451A			ENGINE RUN ROUGH DURING FLIGHT.  NR 1 CYLINDER LOOSE, CRANKCASE FOUND CRACKED BETWEEN BOTTOM STUD HOLES.						1	L	7	1 	3O	3	O		A1CE    	1E10				 
1996080800050	19960808	00050	NE  	1996	8	8	96ZZZX3799       	2	19960719	G	8530	333968	VALVE           			BEECH 	18    	E18S        	1151006	CE  	PWA   	R985  	R985AN14B   	52008	NE  					NR 8 EXHAUST	FAILED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			NM	03	5611D	600  				BA316	22664			IN-FLIGHT FAILURE OF NR 8 CYLINDER EXHAUST VALVE.  VALVE HEAD SNAPPED OFF.  SUSPECT CAUSE OVERHEATED VALVE DUE TO REDUCE	D LEAD IN FUEL.					1	L	7	2 	3R	3	R		A765    	5E1				 
1996012600456	19960126	00456	CE  	1996	1	26	96ZZZX380        	1	19960109	G	2440	1093610165	CIRCUIT BOARD   			BEECH 	1900  	1900C       	1154161	CE  										EXTERNAL POWER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	550CJ					UC50				EXTERNAL POWER SYSTEM REPORTED INOPERATIVE.  FOUND PC BOARD SOAKED WITH DEICE FLUID AND RESISTOR SHORTED.  INSTALLED REP	AIRED PC BOARD.  EXTERNAL POWER LIGHT INOPERATIVE.  TROUBLESHOT AND FOUND WIRE BROKEN OFF TERMINAL ON NEW BOARD AND ALL 	OTHER WIRES CORRODED AT TERMINAL.  ALSO, FOUND WIRES FROM EXTERNAL PLUG TO PC BOARD CHAFED THROUGH AT LIGHTING HOLE.  SP	IRAL WRAP STRETCHED AND DID NOT DO ITS JOB.  REPAIRED AND RETURNED TO SERVICE.			2	L	7	2 	4T			RT	A24CE   					 
1996080800051	19960808	00051	GL  	1996	8	8	96ZZZX3800       	3	19960702	G	6114		PROPELLER       			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	DOME	REQUIRED SERVICE	E				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	54808	3359 				277554106		BP1998		ON 7-2-96, PILOT SHUT DOWN LEFT ENGINE IN-FLIGHT TO PREVENT AN OVERSPEED CONDITION.  ENGINE WAS INSPECTED IAW LYCOMING S	B 369H, PART I, NOTE 1.  NO DEFECTS NOTED.  SERVICED PROPELLER DOME, AIRCRAFT WAS TEST FLOWN AND RETURNED TO SERVICE.					1	L	7	2 	3O				1A10    		5	C	P9EA	 
1996080800052	19960808	00052	CE  	1996	8	8	96ZZZX3801       	1	19960429	G	2822	41400039	PUMP            	DUKES       		BEECH 	35    	S35         	1151532	CE  										FUEL SYSTEM	PORT PLUGGED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	8992M	3536 			145	D7315				FUEL PUMP REPLACED TO C/W BEECH SB N2526, REV II.  WORKING WHEN REMOVED.  FOUND OVERFLOW/RELIEF PORT PLUGGED WITH MATERI	AL THAT APPEARS TO BE RUST.					1	L	7	1 	3O				3A15    					 
1996080800053	19960808	00053	CE  	1996	8	8	96ZZZX3802       	1	19960709	G	2430	DOFF10304B	RECTIFIER ASSY  	FORD        	DOFF10300B  	CESSNA	210   	210L        	2073448	CE  										GROUND STUD	FAILED          	B			KC2R	A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	03	59210		100  		A92243	21060161				THE PILOT EXPERIENCED AN ALTERNATOR FAILURE DURING AN IFR FLIGHT.  A SUCCESSFUL EMERGENCY LANDING WAS MADE.  AN INVESTIG	ATION AS TO WHY THE ALTERNATOR FAILED REVEALED THAT ONE NEGATIVE RECTIFIER GROUND STUD HAD FAILED AND THE OTHER GROUND S	TUD WAS LOOSE.  THIS CONDITION CAUSED THE RECTIFIER ASSEMBLY TO LOSE ITS CIRCUIT TO GROUND RESULTING IN ELECTRICAL ARCIN	G DAMAGE TO THE RECTIFIER AND FAILURE OF THE ALTERNATOR.  SUBMITTER STATED THIS FAILURE COULD HAVE BEEN PREVENTED BY PRO	PERLY TORQUING STUD HARDWARE AND FREQUENT INSPECTIONS.		1	H	7	1 	3O				3A21    					 
1996080800054	19960808	00054	NM  	1996	8	8	96ZZZX3803       	1	19960701	G	5541	41523004	SPAR            			UNIVAR	415   	415E        	0420308	NM  										RUDDER	CRACKED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13	94841					4914				PURCHASED NEW SPAR FOR RUDDER FROM UNIVAIR.  FOUND CRACKS DURING PREP FOR INSTALLATION.  INFORMED UNIVAIR AND REQUESTED 	REPLACEMENT.  RECEIVED A TOTAL OF THREE CRACKED SPARS AND HAD THE FAA INVOLVED BEFORE RECEIVING A GOOD PART.  HAD TO SEN	D THAT BACK AND REQUEST A 'BLANK' IN ORDER TO GET ACCEPTABLE EDGE DISTANCES ON ALL HOLES.				1	L	7	1 	3O				A787    					 
1996080800055	19960808	00055	SO  	1996	8	8	96ZZZX3804       	1	19960625	G	3246		WHEEL           	PARKERHANFIN		GULSTM	AA1   	AA1C        	0631214	SO  										MLG	WRONG BOLTS     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	9645U	1930 				AA1C0083				OWNER/PILOT INSTALLED NEW TIRES AS PREVENTATIVE MAINTENANCE.  WHILE INSTALLING NEW TIRES, HE NOTICED THE WHEEL ASSY THRO	UGH-BOLTS WERE BADLY RUSTED .  HE WENT TO LOCAL HARDWARE STORE, PURCHASED COMMON STEEL/GALVANIZED PLATED BOLTS AND REPLA	CED ORIGINAL 'AN' CADMIUM PLATED BOLTS.  DURING SUBSEQUENT ANNUAL INSPECTION, FOUND THESE BOLTS AND REPLACED THEM WITH '	AN' BOLTS OF CORRECT SIZE.  THE ZINC PLATED BOLTS WERE BADLY CORRODED AND THE WHEEL HALVES WERE ALSO CORRODED.  CLEANED 	AND TREATED CORROSION.		1	L	7	1 	3O				A11EA   					 
1996080800056	19960808	00056	CE  	1996	8	8	96ZZZX3805       	1	19960705	G	2430	S15801A	CONTACTOR       			CESSNA	182   	R182        	2072734	CE  										BATTERY	FAILED          	B			EVCR	A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CE	03	3132C	2263 				R18200238				DURING NORMAL FLIGHT, VFR CONDITION,  ALL ELECTRICAL WAS LOST.  IMMEDIATELY, AIRCRAFT LANDED WITHOUT INCIDENT.  FURTHER 	INVESTIGATION SHOWED MAIN BATTERY CONTACTOR FAILED AND SHOWED SIGNS OF BEING HOT.  REPLACED CONTACTOR AND SYSTEM OPERATE	D NORMALLY.				1	H	7	1 	3O			RT	3A13    					 
1996080800057	19960808	00057	SO  	1996	8	8	96ZZZX3806       	1	19960619	G	2910		FITTING         			PIPER 	PA31  	PA31        	7103102	SO  										RT MLG DOOR ACT	BROKE           	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	08	2336V					31135				INSTALLED 'AERO CRAFTERS' CABIN HEATER MOD STC NR SA240CH.  AFTER 42 FLIGHT HOURS, THE RIGHT GEAR DOOR CLOSED.  HYDRAULI	C FITTING BROKE AT ACTUATOR.  FOUND THE SKEET HOSE INSTALLED IN FORWARD PART OF WHEELWELL INTERFERED WITH FREE MOVEMENT 	OF HYDRAULIC HOSE CAUSING STRESS TO FITTING.  USED 90-DEGREE FITTING AND SHORTER HOSE TO CORRECT PROBLEM.  HEATER KIT IN	STALLED TO RIGHT ENGINE ONLY.  RECOMMEND SPECIAL NOTICE BE GIVEN TO HOSE REACTION AFTER KIT INSTALLATION.			1	L	7	2 	3O				A20SO   					 
1996080800058	19960808	00058		1996	8	8	96ZZZX3807       	4	19960712	G	2562	AK450	ELT             	AMERIKING   		PIPER 	PA31T 	PA31T1      	7103126	SO  										G-SWITCH	FAILED          	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	149CC	100  			4501340	31T7904036				G-SWITCH FAILS TO ACTIVATE UNIT IN THE 'ARMED' POSITION.  IF UNIT IS TURNED 'ON' THE LIGHT ON THE ELT SHOWS THE UNIT IS 	TRANSMITTING, BUT, IN FACT, THE UNIT IS NOT TRANSMITTING ON 121.5 MHZ.					1	L	7	2 	3T				A8EA    					 
1996080800059	19960808	00059	EA  	1996	8	8	96ZZZX3808       	2	19960510	G	8500		ENGINE          			SLNSBY	T67   	T67M260     	8323006	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					POWER SECTION	STOPPAGE        	C				O				OTHER                   				Y			ENGINE STOPPAGE           			AB	AEROBATIC      	1			SW	17	3037C					2134	L2524848			ENGINE STOPPED DURING AEROBATIC MANEUVER.  SUCCESSFUL RESTART AND RETURN TO BASE WITHOUT FURTHER INCIDENT.  ALL INDICATI	ONS NORMAL.  PRELIMINARY ASSESSMENT IS THAT AIRCRAFT WAS PUT IN CONDITION KNOWN TO INDUCE ENGINE STOPPAGE.					1	L	7	1 	3O	3	O	NT	A73EU   	1E4				 
1996080800060	19960808	00060	EU  	1996	8	8	96ZZZX3809       	1	19960425	G	7931		SENDER          			SLNSBY	T67   	T67M260     	8323006	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					ENG OIL PRESS	FAILED          	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	17	3037X					2137	L2557048A			PILOT MADE AN EMERGENCY LANDING AT A SMALL AIRSTRIP.  THE PILOT REPORTED LOW OIL PRESSURE AND RAISING OIL TEMPERATURE. A	 DOSS MAINTENANCE TEAM WAS SENT TO THE AIRSTRIP TO RECOVER THE AIRCRAFT.  THE MAINTENANCE PERSONNEL REMOVED AND REPLACED	 THE OIL PRESSURE SENDING UNIT.  GROUND RUN WAS ACCOMPLISHED, OPERATION CHECK GOOD.  THE AIRCRAFT WAS FLOWN BACK TO HOND	O AT APPROXIMATELY 1,500 HOURS, 25 APRIL 1996, WITH NO RETURN FLIGHT PROBLEMS.			1	L	7	1 	3O	3	O	NT	A73EU   	1E4				 
1996080800061	19960808	00061	EA  	1996	8	8	96ZZZX3810       	2	19960625	G	8500		ENGINE          			SLNSBY	T67   	T67M260     	8323006	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					POWERPLANT	STOPPAGE        	C				O				OTHER                   				Y			ENGINE STOPPAGE           			AB	AEROBATIC      	1			SW	17	3192E					2227	L2257048A			ENGINE STOPPED.  DURING TRAFFIC PATTERN STALL MANEUVERS WITH THE ENGINE AT APPROXIMATELY IDLE.  STARTER WAS ENGAGED FOR 	A SUCCESSFUL RESTART.  DURING LANDING THE ENGINE STALLED AGAIN, NO RESTART WAS ATTEMPTED.  AIRCRAFT LANDED WITHOUT INCID	ENT.  ALL OTHER INDICATIONS WERE NORMAL.  NO KNOWN REASON AT THIS TIME.  AIRCRAFT IMPOUND, PUT INTO DEPOT STATUS.  DOSS 	AVIATION IS PERFORMING AN ENGINE STOPPAGE CHECK LIST.  NO DISCREPANCIES FOUND AT THIS TIME.  ENGINE AND AIRFRAME TIME IS	 72.0 HOURS.		1	L	7	1 	3O	3	O	NT	A73EU   	1E4				 
1996080800062	19960808	00062	EA  	1996	8	8	96ZZZX3811       	2	19960515	G	8500		ENGINE          			SLNSBY	T67   	T67M260     	8323006	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					POWERPLANT	STOPPAGE        	C				O				OTHER                   				Y			ENGINE STOPPAGE           			AB	AEROBATIC      	1			SW	17	3193K					2233	L2559748			ENGINE STOPPED AFTER PILOT REDUCED POWER IN SPIN.  SUCCESSFUL RESTART AND RETURN TO BASE WITHOUT FURTHER INCIDENT.  ALL 	INDICATIONS NORMAL.  USAF CONDUCTING INVESTIGATION.  MAINTENANCE IS IN PROCESS OF COMPLETING ENGINE STOPPAGE CHECK LIST.	  AIRCRAFT HAS 101.9 HOURS.				1	L	7	1 	3O	3	O	NT	A73EU   	1E4				 
1996080800063	19960808	00063	SO  	1996	8	8	96ZZZX3812       	1	19960701	G	3234	752629	O-RING          	GARKENYON   	8376702     	PIPER 	PA46  	PA46310P    	7104605	SO  										GEAR SELECTOR	RUPTURED        	D	S			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EU	01	43362					468408025				DURING A CHECK-FLIGHT, THE EMERGENCY GEAR HANDLE WAS PULLED.  THE GEAR EXTENDED, BUT THE HYDRAULIC POWER PUMP KEPT, AFTE	R RETRACTION, PUMPING AND CYCLING.  THE CIRCUIT BREAKER WAS PULLED TO KEEP PUMP/MOTOR FROM OVERHEATING.  ON THE GROUND, 	THE LANDING GEAR RETRACTED, BUT THE PRESSURE WENT DOWN TO 1000-600 PSI.  AFTER REPLACING THE VALVE ASSY, THE SAME THING 	HAPPENED AFTER AN EMERGENCY EXTENSION.  WHEN THE VALVE ASSY LANDING GEAR SELECTOR WAS DISASSEMBLED, FOUND THE O-RING RUP	TURED.  SUBMITTER SUGGESTS TO HAVE THE HOUSING HOLES DEBURRED, A BETTER O-RING, OR EVEN BETTER - A NEW AND BETTER DESIGN	.	1	L	7	1 	3O				A25SO   					 
1996080800064	19960808	00064	NE  	1996	8	8	96ZZZX3813       	2	19960610	G	8530		CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R985  	R985AN1     	52008	NE  					NR 4	HEAD LEAKAGE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	5296					580	24011			OVER LAST 200 HOURS, CYLINDER HEAD SEPARATED ON 3 CYLINDERS IN FLIGHT OR ON TAKEOFF.  THE 4TH CYLINDER HAD STAINS AND LE	AKAGE AND REMOVED BEFORE FAILURES, BUT WAS NOT BETWEEN NR 2 AND NR 3 FIN PER AD 78-08-07.  IT WAS LEAKING BETWEEN TOP ST	EEL FIN AND NR 1 ALUMINUM FIN.  NONE OF FAILED CYLINDERS SHOWED LEAKAGE PRIOR TO FAILURE.				1	Q	7	1 	3R	3	R		1A16    	5E1				 
1996080800065	19960808	00065		1996	8	8	96ZZZX3814       	4	19960710	G	2562	4530150	ELT             	ARTEX       																G-SWITCH	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01		10   			56995					AIRCRAFT WAS PARKED ON THE RAMP AT NIGHT AND SOME TIME DURING THE NIGHT THE ELT STARTED TO TRANSMIT.  THE FOLLOWING MORN	ING, IT WAS RESET AND A NEW BATTERY WAS INSTALLED.  TWO DAYS LATER, THE SAME CONDITION WAS EXPERIENCED.  THE ELT WAS REP	LACED.																	 
1996080800066	19960808	00066	EU  	1996	8	8	96ZZZX3815       	1	19960718	G	5320	25FC7512	ANGLE           			BRAERO	DH125 	HS125700A   	4230170	EU  										MLG WHEEL PAN	CRACKED         	B	S		LEGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	7728					257028				A CRACK WAS FOUND IN ONE FLANGE OF ANGLE P/N 25-FC751-2.  THIS ANGLE GOES OVER THE TOP OF THE MAIN WHEEL PAN.  THE CRACK	 IS LOCATED IN AN AREA OF THE ANGLE WHERE ONE OF THE FLANGES IS GREATLY REDUCED IN WIDTH FOR TERMINATION OF SEAT TRACK R	AIL.  RAYTHEON HAS A REPAIR TO REPLACE THE CRACKED AREA WITH MATERIAL OF THE SAME TYPE AND SIZE AS PRESENTLY INSTALLED. 	 A SUGGESTED REPAIR IS TO REMOVE THE SECTION OF SEAT TRACK IN THE AREA OF THE FLANGE, THUS, ALLOWING THE FLANGE TO MAINT	AIN THE FULL FLANGE WIDTH AND STRENGTH THROUGHOUT THIS SECTION.		2	L	7	2 	4F				A3EU    					 
1996080800067	19960808	00067	NM  	1996	8	8	96ZZZX3816       	1	19960610	G	5541	B62R0132	SPAR            			PROPJT	200   	200D        	0140312	NM  										RUDDER HINGE	CRACKED         	B		A	OW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	2956T	2750 				329				RUDDER SPAR CRACKED AT TOP HINGE LOCATION.  REPLACED SPAR P/N B62013-2, ADDED DOUBLER P/N 62013-23.  CRACK WAS .75 INCH 	LONG FROM RIVET HOLES ON RIGHT SIDE.					1	L	7	1 	3O				3A18    					 
1996080800068	19960808	00068		1996	8	8	96ZZZX3817       	4	19960628	G	6122	3535035	BETA FORK       	WOODWARD    	8210007F    	BEECH 	200   	200BEECH    	1152920	CE  										GOVERNOR	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03					1747452					PROPELLER BETA FORK PLUNGER WAS FOUND COMPLETELY SHEARED AT THE PRESSED JOINT WHERE THE FORK AND PLUNGER MEET.  SUBMITTE	R STATED IF THIS WAS NOT FOUND AND PROPELLER WAS RETORQUED, TO SERVICE IT COULD HAVE CAUSED THE PROPELLER TO NOT RETURN 	FROM REVERSE.				1	L	7	2 	4T				A24CE   					 
1996080800069	19960808	00069	EA  	1996	8	8	96ZZZX3818       	1	19960703	G	2710	272953	PCU LINK        			CNDAIR	CL600 	CL6002B19   		EA  										RT AILERON	DEFECTIVE       	B			EZ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	5100X	842  				700				CREW REPORTED A HIGH PITCH NOISE COMING FROM THE RIGHT AILERON.  INVESTIGATION PROVED THE AILERON PCU TO AILERON LINK WA	S CHATTERING ON THE AILERON BOLT BUSHING.  SPECIFICALLY, THE ANTI-ROTATION TABS OF THE LINK.  THE BUSHINGS WERE REPLACED	 AS WELL AS THE LINK AND ASSOCIATED HARDWARE.  HIGH TORQUE VALVES WERE SAID TO BE POSSIBLE CAUSE OF PROBLEM AS STATED BY	 ENGINEERING IN THE MM.  RECOMMENDATION WOULD BE TO RE-EVALUATE TORQUE VALVES AND TOGGLE LINK DESIGN.			2	L	7	2 	4F			RT	A21EA   					 
1996080800070	19960808	00070	NM  	1996	8	8	96ZZZX3819       	1	19960701	G	5541	B62R0132	SPAR            			PROPJT	200   	200D        	0140312	NM  										RUDDER HINGE	CRACKED         	B			OW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	2980T	2560 				354				RUDDER SPAR CRACKED AT UPPER HINGE LOCATION.  REPLACED SPAR P/N B62013-2, ADDED DOUBLER P/N B62013-23.  WORK DONE IAW ME	YERS AIRCRAFT DRAWINGS AND PROCEDURES.					1	L	7	1 	3O				3A18    					 
1996080800071	19960808	00071	NM  	1996	8	8	96ZZZX3820       	1	19960710	G	5541	B62R0132	SPAR            			PROPJT	200   	200D        	0140312	NM  										RUDDER HINGE	CRACKED         	B			OW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	260M	1600 				298				RUDDER SPAR BROKEN AT TOP HINGE LOCATION.  REPLACED SPAR P/N B62R013-2, ADDED DOUBLER P/N B62R013-23.  THIS DOUBLER ADDI	TION WAS FIRST USED OVER 10 YEARS AGO ON A DIFFERENT MEYERS 200 WHICH HAS ACCUMULATED OVER 1,000 HOURS OF TROUBLE-FREE U	SAGE.  TECUMSEH AIRCRAFT, FORMERLY MEYERS AIRCRAFT.				1	L	7	1 	3O				3A18    					 
1996080800072	19960808	00072		1996	8	8	96ZZZX3821       	4	19960624	G	2562	ELT1104	ELT             	ARTEX       	4530150     	BEECH 	MU300 	400BEECH    		CE  											CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3196N	595  			55916	RK96				DURING ELT SCHEDULED INSPECTION, FOUND BATTERY CASE CRACKED.  DISASSEMBLED ELT AND FOUND BOTH BATTERIES AT HEAD OF ELT L	EAKING.  REPLACED ELT.  SUBMITTER STATED THIS IS SECOND OCCURENCE IN THIS AIRCRAFT AND THIRD OCCURRENCE BY THIS OPERATOR	.				2	H	7	2 	4F			RT	A16SW   					 
1996080800073	19960808	00073	CE  	1996	8	8	96ZZZX3822       	1	19960624	G	2436	62581038	CAPACITOR ASSY  			CESSNA	500   	S550        	2076607	CE  										GENERATOR GCU	EXPLODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	260QS	5575 				S5500060				GENERATOR AND GENERATOR CONTROL UNIT FILTER INSTALLATION, CAPACITOR ASSEMBLY.  CAPACITOR PART NUMBER BLEW A HOLE IN THE 	END, BLEW ONE LEAD OFF ITS CONTACT, AND BURNED THE INSULATION FROM THE WIRE, FOR APPROXIMATELY 1 INCH.					1	L	7	2 	4F			RT	A22CE   					 
1996080800074	19960808	00074	NE  	1996	8	8	96ZZZX3823       	2	19960408	G	7250	566004	TURBINE         			RKWELL	NA265 	NA26540     	6402608	CE  	PWA   	JT12  	JT12A8      	52042	NE  					2ND STAGE	FAILED          	D				E	F	A		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	UNSCHED LANDING         		J			WARNING INDICATION        			CL	CLIMB          	1			SO	09	307NT	1196 				282072	P637801NB			CLIMBING THROUGH 5,000 FEET, THE CREW HEARD AND FELT A LOUD REPORT FOLLOWED IMMEDIATELY BY THE LT ENGINE FIRE WARNING LI	GHT.  THE LT ENGINE SPEED ROLLED BACK TO APPROXIMATELY 12 PERCENT.  PILOT SHUT ENGINE DOWN, DISCHARGED THE FIRE BOTTLE A	ND MADE A SINGLE ENGINE LANDING.  INSPECTION REVEALED NUMEROUS 1ST AND 2ND STAGE TURBINE BLADES MISSING AND EXTENSIVE DA	MAGE TO 2ND STAGE DISK.			2	L	7	2 	4J	4	J		A2WE    	1E9				 
1996080800077	19960808	00077		1996	8	8	96ZZZX3826       	4	19960603	G	3418	556416	CONNECTOR       			PIPER 	PA42  	PA42        	7104202	SO  										PRESS BULKHEAD	BURNT           	B			GBBR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	11	8RY					428001036				PILOT REPORTED ERRONEOUS RIGHT STALL WARNING AND A MOMENTARY 'PUFF' OF SMOKE FROM RT INSTRUMENT PANEL.  INSPECTION REVEA	LED PRESSURE BULKHEAD AREA BURNED.  (CONNECTOR NR E339/439.)  CONNECTOR WAS REPLACED AND GOLD PLATED PINS AND SOCKETS IN	STALLED.				1	L	7	2 	4T				A23SO   					 
1996080800078	19960808	00078	EU  	1996	8	8	96ZZZX3827       	1	19960712	G	2710	5135123	CONTROL SYSTEM  			ISRAEL	1124  	1124        	4500102	EU  										LT/RT AILERON	CORROSION       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	300LH	5950 				312				INSPECTION FOUND AILERON CONTROL SYSTEM, LT AND RT, CORROSION.						2	M	7	2 	4F				A2SW    					 
1996080800079	19960808	00079	EU  	1996	8	8	96ZZZX3828       	1	19960712	G	3230	283023501	CONTROL ROD     			ISRAEL	1124  	1124        	4500102	EU  										NLG FORWARD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	300LH	5950 				312				INSPECTION FOUND NLG CONTROL RODS FORWARD, CORROSION.						2	M	7	2 	4F				A2SW    					 
1996080800080	19960808	00080	EU  	1996	8	8	96ZZZX3829       	1	19960712	G	3230	3900009231243	CONTROL ROD     			ISRAEL	1124  	1124        	4500102	EU  										NLG RT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	300LH	5950 				312				INSPECTION FOUND NLG CONTROL RODS RT, CORROSION.						2	M	7	2 	4F				A2SW    					 
1996080800081	19960808	00081	EU  	1996	8	8	96ZZZX3830       	1	19960712	G	3230	3900009231288	CONTROL ROD     			ISRAEL	1124  	1124        	4500102	EU  										NLG LT/RT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	300LH	5950 				312				INSPECTION FOUND NLG CONTROL RODS LT AND RT, CORROSION.						2	M	7	2 	4F				A2SW    					 
1996080800082	19960808	00082	NM  	1996	8	8	96ZZZX3831       	1	19960429	G	2820	5888D1	CHECK VALVE     			BOEING	727   	72730       	1384008	NM  										AUX FUEL SYS	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	727BE	418  				18933				CHECK VALVE FAILED IN OPEN POSITION.  VALVE WAS INSTALLED IN AUXILIARY FUEL SYSTEM STC NR SA530NE CONFIGURATION NR 3.  I	NSTALLED PER DWG NR 200-1-503 FUEL SYSTEM.  AUXILARY FUEL KIT INSTALLED PER INSTALLATION MDL-200-1-141, REV. 1, DATED MA	Y 16, 1990.				2	L	7	3 	4F				A3WE    					 
1996080800083	19960808	00083	CE  	1996	8	8	96ZZZX3832       	1	19960504	G	2432	24535020	BATTERY         	MARATHON    	MA520       	CESSNA	500   	550         	2076604	CE  										CELLS	OVERHEAT        	H				H				DEACTIVATE SYST/CIRCUITS				M			OVER TEMP                 			CR	CRUISE         	1			GL	17	7ZU	233  			9403362	5500433				BATTERY TEMPERATURE ROSE TO AN OVERHEAT CONDITION WITHIN 30 MINUTES AFTER DEPARTURE.  CORRECTIVE PROCEDURE ISOLATED BATT	ERY FROM GENERATOR CONTINUING TO HEAT BATTERY.  BATTERY EXAMINED BY MAINTENANCE TECH AND DISCOVERED TO HAVE BAD CELLS. B	AD BATTERY REPLACED WITH NEW ONE.				1	L	7	2 	4F				A22CE   					 
1996080800084	19960808	00084	EU  	1996	8	8	96ZZZX3833       	1	19960329	G	7930	41SG107150G14	TRANSDUCER      			BAG   	JETSTM	JETSTM3101  	1500215	EU  										OIL SYSTEM	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	829JS					713				FOUND TRANSDUCER WAS NOT PRODUCING THE CORRECT OUTPUTS UNDER KNOWN OIL QUANTITY AND PRESSURES.						2	L	7	2 	4T			RT	A21EU   					 
1996080800085	19960808	00085	NM  	1996	8	8	96ZZZX3834       	1	19960601	G	5541	B62R0132	SPAR            			PROPJT	200   	200D        	0140312	NM  										RUDDER HINGE	CRACKED         	B			OW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	898LF	2130 				323				RUDDER SPAR CRACKED AT TOP HINGE LOCATION.  REPLACED SPAR P/N B62013-2, ADDED DOUBLER P/N B62013-23.  WORK ACCOMPLISHED 	IAW MEYERS AIRCRAFT DRAWINGS AND PROCEDURES.					1	L	7	1 	3O				3A18    					 
1996080800086	19960808	00086	CE  	1996	8	8	96ZZZX3835       	1	19960711	G	2612	302158	DETECTOR        			BEECH 	200   	B200        	1152922	CE  										LT ENG FIREWALL	MALFUNCTION     	B			LX5R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			GL	19	991LL					BB1234				CREW REPORTED INTERMITTENT FIRE WARNING ON LEFT ENGINE.  FOUND LOWER FIREWALL FIRE DETECTOR BAD.  THIS DETECTOR HAS BEEN	 SUPERCEDED BY A NEW STYLE.					1	L	7	2 	4T				A24CE   					 
1996080800087	19960808	00087	WP  	1996	8	8	96ZZZX3836       	1	19960610	G	6320	369A510923	PINION SHAFT    		369A5100709 	HUGHES	369   	369HS       	4470728	WP  										T/R & ACCY DRIVE	WORN            	B		A	PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	369PF		2127 		1020434	530473S				MAIN ROTOR TRANSMISSION LOCKNUT LOST TORQUE AND ALLOWED BEARINGS TO FRET ON SHAFT WEARING THE SHAFT UNDER THE BEARINGS A	ND ACCESSORY DRIVE GEAR.  THIS ALLOWED THE DRIVE PIN TO SHEAR AND WHENEVER TORQUE WAS BELOW 6 PERCENT ENGINE TORQUE, THE	 OIL PUMP AND ROTOR TACHOMETER WOULD STOP TURNING.  SHAFT IS TO BE REPAIRED, PIN REPLACED, AND TRANSMISSION REASSEMBLED.	  CHECKED AND RETURNED TO SERVICE TO FINISH ITS 273 HOURS TO OVERHAUL.			1	G	7	1 	3U				H3WE    					 
1996080800088	19960808	00088	SW  	1996	8	8	96ZZZX3837       	1	19960611	G	6230	206040036103	BEARING         		206040002007	BELL  	206   	206B3       	1181506	SW  										MAST XMSN	MAKING METAL    	B			FW7D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	16917	8961 	850  		NJF50813	2303				TRANSMISSION CHIP CAUTION LIGHT ILLUMINATED DURING FLIGHT.  FOUND MULTIPLE FLAKES ON MAGNETO PLUGS.  MAST BEARING FOUND 	TO BE CAUSE OF METAL.  CAUSE UNDETERMINED.					1	G	7	1 	3U				H2SW    					 
1996080800089	19960808	00089	SW  	1996	8	8	96ZZZX3838       	1	19960708	G	6420	MS208234	ELBOW           		4762060029  	BELL  	47    	47G5        	1181032	SW  										TRANSMISSION	WRONG PART      	B			OUGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17					J131224					DURING CLEAN-UP AND INSPECTION OF TRANSMISSION PARTS AT OVERHAUL, DISCOVERED TRANSMISSION OIL SUPPLY FITTING PN MS20823-	4 HAD RESTRICTOR ORIFICE SIMILAR TO PN 47-712-035-1 MANIFOLD PRESSURE GAUGE LINE RESTRICTOR.  SUBMITTER STATED COULD CAU	SE TRANSMISSION FAILURE FROM OIL STARVATION.				1	G	7	1 	3O				2H3     					 
1996080800090	19960808	00090	WP  	1996	8	8	96ZZZX3839       	1	19960611	G	6220	369H120331	LINK ASSY       		369A1200501 	HUGHES	369   	369HS       	4470728	WP  										M/R HUB LEAD/LAG	BUSHING LOOSE   	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	42405	174  			3562	920416S				WHILE C/W WITH VISUAL INSPECTION PER AD 93-03-13 (R/D 3-21-95) TWO BLADE ATTACHMENT BUSHINGS WERE FOUND LOOSE IN ONE LEA	D/LAG LINK ASSY.  M/R HUB TO BE RETURNED TO A MDHS SERVICE CENTER FOR REPLACEMENT OF THIS LINK ASSY WITH A SERVICEABLE P	ART.				1	G	7	1 	3U				H3WE    					 
1996080800118	19960808	00118	SW  	1996	8	8	96ZZZX3840       	1	19960517	G	6230	2060104213	BOLT            			BELL  	206   	206L3       	1182108	SW  										PYLON PILLOW BLK	STEPPED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6533Y					51457				PILLOW BLOCK BOLTS (3 EACH) FOUND STEPPED AND SCORED.						1	G	7	1 	3U				H2SW    					 
1996080800119	19960808	00119	GL  	1996	8	8	96ZZZX3841       	2	19960422	G	7320	1564T1005	SERVO           			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8776				1619	S776				SERVO MOTOR FAILED IN-FLIGHT.  MOTOR SHORTED OUT CAUSING CIRCUIT BREAKER TO TRIP.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996080800120	19960808	00120	NE  	1996	8	8	96ZZZX3842       	1	19960624	G	3210	7625002102041	TUBE            			SKRSKY	S76   	S76A        	8143006	NE  										MLG	CORRODED        	B	S	A	ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31211	8015 				760225				DURING INSPECTION, FOUND HI-LOCK FASTENER ON RIGHT SIDE OF TUBE STICKING OUT APPROXIMATELY .0625 INCH ON BOTH ENDS.  THE	 FASTENER HAD CORRODED IN THE CENTER AND BROKE.  PART NUMBER OF THE FASTENER IS 1528-20 AND THE COLLAR IS NAS1080D8.  SU	BMITTER RECOMMENDS A ONE TIME INSPECTION AND REPLACEMENT OF ALL HI-LOCKS AND A 300 HOUR INSPECTION OF THE TUBE ASSY FOR 	CORROSION AND PITTING ON THE INSIDE.			1	G	7	2 	3U				H1NE    					 
1996080800122	19960808	00122	SW  	1996	8	8	96ZZZX3844       	1	19960620	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007F					45186				PLAY IN EXCESS OF .025 INCH AT TWO PLACES.  SEE BELL MM L3, FIGURE 62.21.  AT TEAR DOWN, FOUND BEARING AND SPACERS WORN.	  TOTAL TIMES, LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED.					1	G	7	1 	3U				H2SW    					 
1996080800123	19960808	00123	SW  	1996	8	8	96ZZZX3845       	1	19960620	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2654					45482				PLAY IN EXCESS OF .025 INCH AT TWO PLACES.  SEE BELL MM L3, FIGURE 62.21.  AT TEAR DOWN, FOUND BEARING AND SPACERS WORN.	  TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED.					1	G	7	1 	3U				H2SW    					 
1996080800124	19960808	00124	SW  	1996	8	8	96ZZZX3846       	1	19960620	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3899C					45596				PLAY IN EXCESS OF .025 INCH AT TWO PLACES.  SEE BELL MM L3, FIGURE 62.21.  AT TEAR DOWN, FOUND BEARING AND SPACERS WORN.	  TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED.					1	G	7	1 	3U				H2SW    					 
1996080800126	19960808	00126	SW  	1996	8	8	96ZZZX3848       	1	19960620	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L3       	1182108	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2619					51375				PLAY IN EXCESS OF .025 INCH AT TWO PLACES.  SEE BELL MM L3, FIGURE 62.21.  AT TEAR DOWN, FOUND BEARING AND SPACERS WORN.	  TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED.					1	G	7	1 	3U				H2SW    					 
1996080800724	19960808	00724	WP  	1996	8	8	96ZZZX3858       	1	19960628	G	5210	L3082511AT	DRIVE MOTOR     	CHICAGOPNEU 		DOUG  	DC10  	DC1030F     	3023504	WP  										4L DOOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	10MB		887  		B713614	47907				DOOR 4L FAILED TO OPEN IN EMERGENCY MODE DURING DITCHING DEMONSTRATION.  TROUBLESHOOTING FOUND THE FAILURE OCCURRED IN T	HE PNEU DRIVE MOTOR.  PNEU DRIVE MOTOR IS 'ON CONDITION' WITH OPS CHECK DUE IN 1,000-HOUR INTERVALS.					2	L	7	3 	4F			RT	A22WE   					 
1996080800725	19960808	00725	CE  	1996	8	8	96ZZZX3859       	1	19960617	G	3240	20011610W	FILTER          		38675       	BEECH 	MU300 	400BEECH    		CE  										PWR BRAKE VALVE	BLOCKED         	B		A	AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	203BA	3686 				RJ3				AFTER STARTING ENGINE AND HYDRAULIC SYSTEM, PRESSURE WAS UP AND NORMAL (1,500 PSI), THE BRAKES LOCKED UP AND AIRCRAFT WO	ULD NOT MOVE.  FOUND THE POWER BRAKE VALVE RETURN FILTER BLOCKED.  THESE FILTERS ARE CLEANED EVERY 24 MONTHS.  NO HOUR R	EQUIREMENT.  SUBMITTER STATES THESE FILTERS NEED TO BE CLEANED AT 400-HOUR INTERVALS.				2	H	7	2 	4F			RT	A16SW   					 
1996080800728	19960808	00728	EA  	1996	8	8	96ZZZX3862       	2	19960718	G	8550	AN9151D	ELBOW           			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					HOBBS SWITCH	FAILED          	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	15	2606L					3879A0778	L2236015			ELBOW P/N AN915-1D WAS INSTALLED IN THE OIL PRESSURE/HOBBS SWITCH SYSTEM OFF THE BACK OF THE ACCESSORY CASE.  THE INSTAL	LATION OF THE HOBBS PRESSURE SWITCH WAS NOT DONE IAW THE MANUFACTURERS IPC.  THE SWITCHES WERE NOT INSTALLED AND SUPPORT	ED CORRECTLY.  AFTER TIME AND ENGINE VIBRATION, THE FITTING BROKE CAUSING ALL THE ENGINE OIL TO BE PUMPED OUT.				1	L	7	1 	3O	3	O		A18SO   	E223				 
1996080800730	19960808	00730	EA  	1996	8	8	96ZZZX3865       	1	19960718	G	2720	37350	TORQUE TUBE     			CNDAIR	CL600 	CL6002B16   	1900305	EA  										RUDDER CONTROL	NOT SAFETIED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	309FX					5306				WHILE PERFORMING CANADAIR ALERT SERVICE BULLETIN A604-27-002, FOUND RUDDER CONTROL TORQUE TUBE LOWER ROD END ATTACH HARD	WARE (SAFETY COTTER PIN) NOT INSTALLED AND THE NUT BACKED OFF ALLOWING THE BOLT TO PARTIALLY BACK OUT.  THE NUT WAS TORQ	UED AND COTTER PIN INSERTED.  MANUFACTURER WAS NOTIFED OF DEFECT.				2	L	7	2 	4F			RT	A21EA   					 
1996080800731	19960808	00731	CE  	1996	8	8	96ZZZX3866       	1	19960715	G	2760	25CW904A	BELLCRANK       			RAYTHN	DH125 	HAWKER800XP 		CE  										RT AIRBRAKE	BINDING         	D				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	07	12F	1810 				8182				FLIGHT CREW NOTICED AIRBRAKE HANDLE WAS STIFF AND HAD AN OCCASIONAL BIND.  TWICE THEY COULD NOT GET LIFT DUMP.  INVESTIG	ATION FOUND THE UPPER AND LOWER BEARINGS IN THE RIGHT AIRBRAKE BELLCRANK VERY ROUGH AND BINDING.  THESE BEARINGS ARE SEA	LED AND NO LUBRICATION REQUIRED.  POSSIBLE CAUSE IS TKS SOMEHOW GOT INTO THE BEARINGS CAUSING THEM TO CORRODE.				2	L	7	2 	4F			RT	A3EU    					 
1996080800732	19960808	00732	CE  	1996	8	8	96ZZZX3867       	1	19960715	G	3040	57033	FAN             			CESSNA	500   	550         	2076604	CE  										DEFOG	MOTOR FAILED    	B		A	R3R2	B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	01	6763L				1216	550673				DEFOG FAN FAILED IN-FLIGHT FILLING CABIN WITH SMOKE.  DEFOG AND OVERHEAD FANS ARE ON SAME CIRCUIT WHICH ALLOWS CONTINUED	 POWER TO FAILED UNIT WITHOUT TRIPPING CIRCUIT BREAKER.  EMERGENCY DESCENT INITIATED AND LANDED SAFELY.  RECOMMEND SB TO	 SPLIT CIRCUIT AND INSTALL CIRCUIT BREAKERS THAT WILL TRIP IF UNIT FAILS.  SYSTEM IS CONFIGURED FROM FACTORY.  SAME COND	ITION EXPERIENCED AT LEAST TWICE PREVIOUSLY.  RECOMMEND AIRWORTHINESS DIRECTIVE IF MFG DELAYS.			1	L	7	2 	4F				A22CE   					 
1996080800733	19960808	00733	CE  	1996	8	8	96ZZZX3868       	1	19960606	G	3411	5120P1	DIGITIZER       			CESSNA	182   	182         	2072702	CE  										TOP PLATE	STATIC LEAK     	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	9620E				500452	18268431				ALTITUDE DIGITIZER MADE OF PLASTIC, TOP PLATE AT STATIC INLET CRACKED CAUSING EXCESSIVE STATIC LEAK.  SUBMITTER STATED T	OP PLATE USED TO BE METAL, NOW IT IS GLASS FILLED NYLON.					1	H	7	1 	3O			NT	3A13    					 
1996080800734	19960808	00734	SO  	1996	8	8	96ZZZX3869       	2	19960717	G	8520		CRANKCASE       			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					LT ENG NR 5 CYL	CRACKED         	B	S		APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	36319					347870318	265936R			THE INSPECTION FOUND CRANKCASE HAS A SMALL .3750 INCH CRACK NEXT TO THE UPPER BOLT JUST FORWARD OF CYLINDER NR 5.  THIS 	IS CONSIDERED A NON-CRITICAL AREA PER SB M90-17.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996080800735	19960808	00735	SO  	1996	8	8	96ZZZX3870       	2	19960627	G	8530		PISTON          			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  					NR 6 OIL SCRAPER	RING FAILED     	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	758LR	1400 				R1723185	356264			UPON DISASSEMBLY AFTER LOW COMPRESSION READING, FOUND THE LOWER PORTION BY OIL SCRAPER RING MISSING FROM THE PISTON.  SU	SPECT DUE TO THE OIL SCRAPER RING HANGING UP, THUS, STUCTRURAL MALFUNCTION.					1	H	7	1 	3O	3	O		3A17    	E1CE				 
1996080800736	19960808	00736	GL  	1996	8	8	96ZZZX3871       	1	19960701	G	3240		BRAKE           			AMTR  	EAGLE 	CHRISEAGLE2 		GL  										MLG	LOCK UP         	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	03	109BX	2    				0245				DURING A HIGH SPEED TAXI SYSTEM CHECK OUT, PILOT EXPERIENCED BRAKE LOCK-UP.  THE AMATEUR/EXPERIMENTAL CATEGORY AIRCRAFT 	SLID OFF RUNWAY WITH MINOR DAMAGE AND NO INJURY TO PILOT.  PILOT, WHO ALSO BUILT AIRCRAFT, STATED BRAKE SYSTEM HAD NO DI	SCREPANCIES NOTED DURING INSPECTION AFTER OCCURRENCE.  PILOT ALSO STATED HIGH SPEED TAXIING WAS NOT INTENDED FOR FLIGHT.				1	Q	7	1 	3O				EXPA1Q71					 
1996080800737	19960808	00737	SO  	1996	8	8	96ZZZX3872       	1	19960716	G	7714	PS50048151	TACHOMETER      	BFGOODRICH  	599282      	PIPER 	PA32  	PA32300     	7103212	SO  										NEEDLE STOP	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	15	2969Q				25180	327740056				REMOVED TACHOMETER FROM BOX.  NEEDLE ON WRONG SIDE OF STOP.						1	L	7	1 	3O				A3SO    					 
1996080800738	19960808	00738	CE  	1996	8	8	96ZZZX3873       	1	19960718	G	7810		STACK           			CESSNA	177   	177B        	2073708	CE  										MUFFLER	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	34348	68   				17701775				EXIT STACK OF MUFFLER SEPARATED FROM THE MUFFLER.  APPEARS WELDS MAY NOT HAVE BEEN 'NORMALIZED' CAUSING A BRITTLE AREA A	ROUND THE WELD.  THIS WAS AN FAA/PMA PART.  ENGINE SHOWED NO SIGNS OF VIBRATION.  EXHAUST EXITED THE MUFFLER INTO COWLIN	G, GASCOLATOR, AND CARBURETOR AREA.				1	H	7	1 	3O				A13CE   					 
1996080800739	19960808	00739	CE  	1996	8	8	96ZZZX3874       	1	19960706	G	2436	99101263	REGULATOR       			CESSNA	414   	414A        	2075907	CE  										DC SYSTEM	FAILED          	C				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			WP	13	4573V					414A0300				REGULATOR FAILED IN-FLIGHT.  REGULATOR REPLACED AND ADJUSTMENTS MADE IAW CESSNA SM.						1	L	7	2 	3O				A7CE    					 
1996080800740	19960808	00740	EA  	1996	8	8	96ZZZX3875       	2	19960723	G	8520	11F20022D3	CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 6 CYL	STUDS FAILED    	B			WC7R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			GL	25	585DT	493  				318052117	L172868A			PILOT REPORTED HEARING A 'BOOM' AND A DECREASE IN MANIFOLD PRESSURE DURING FLIGHT.  UPON INSPECTION, NR 6 CYLINDER OF RI	GHT ENGINE WAS FOUND TO BE AWAY FROM CRANKCASE PAD.  FIVE OUT OF EIGHT CYLINDER HOLD-DOWN STUDS HAD BROKEN OFF.  TWO THR	OUGH STUDS, AND ONE SHORT STUD REMAINED TO HOLD CYLINDER ON.  SUSPECT CAUSE, NOT TORQUED PROPERLY.  1,454.3 HOBBS.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996080800741	19960808	00741	EA  	1996	8	8	96ZZZX3876       	2	19960701	G	8530	EC75971	CYLINDER        			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					NR 4	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	63TW		1209 			M1762	L2069136A			INSPECTION FOUND NR 4 CYLINDER CRACKED FROM OUTSIDE RADIUS OF INTAKE VALVE TO OUTSIDE RADIUS OF EXHAUST VALVE.  CYLINDER	 HEAD SPLIT OPEN BLOWING BOTTOM SPARK PLUG FROM CYLINDER.					1	L	7	1 	3O	3	O		A1CE    	E286				 
1996080800742	19960808	00742	EA  	1996	8	8	96ZZZX3877       	2	19960715	G	8530	SL13790A	ROCKER SHAFT    								LYC   	O320  	O320*       	41508	EA  					ENGINE	BENT            	B			CYKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07										ROUTINE CHECK OF O320 SERIES ENGINE ROCKER SHAFTS FROM STOCK, FOUND P/N SL13790A, LOT NR 510924 DATED 4-30-96, 9 OUT OF 	20 WERE FOUND BENT.										3	O			E274				 
1996080800743	19960808	00743		1996	8	8	96ZZZX3878       	1	19960722	G	2150	220470001	ACM             	ALIDSIGNAL  																THRUST BEARING	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					14700					TWO EACH AIR CYCLE MACHINES THRUST BEARING FAILURES WITHIN 6 TO 8 HOURS OF OPERATION.  ALLIED SIGNAL HAS TRACED THIS BAC	K TO A THRUST BEARING FOIL COATING PROCESS PROBLEM IN MID-1994.																		 
1996080800744	19960808	00744		1996	8	8	96ZZZX3879       	1	19960722	G	2150	220470001	ACM             	ALIDSIGNAL  																THRUST BEARING	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					103699					TWO EACH AIR CYCLE MACHINES THRUST BEARING FAILURES WITHIN 6 TO 8 HOURS OF OPERATION.  ALLIED SIGNAL HAS TRACED THIS BAC	K TO A THRUST BEARING FOIL COATING PROCESS PROBLEM IN MID-1994.																		 
1996080800745	19960808	00745		1996	8	8	96ZZZX3880       	1	19960716	G	2822	2B651	PUMP            	AIRBORNE    																ARMATURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					2D100					PUMP ARMATURE OUT OF BALANCE CAUSING PREMATURE FAILURE OF PUMP.																			 
1996080800746	19960808	00746		1996	8	8	96ZZZX3881       	1	19960716	G	2822	10212	PUMP            	AIRBORNE    																ARMATURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					1D114					PUMP ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996080800747	19960808	00747		1996	8	8	96ZZZX3882       	1	19960712	G	2822	1D16	PUMP            	AIRBORNE    																ARMATURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15					6E166					WASHER WORN THROUGH RESULTING IN ARMATURE SHAFT BEING CUT AND SHEARED OFF, RESULTING IN COMPLETE LOSS OF FUEL PRESSURE A	ND FLOW.																		 
1996080800748	19960808	00748		1996	8	8	96ZZZX3883       	1	19960716	G	2822	1B58	PUMP            	AIRBORNE    																ARMATURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15					1A6					PUMP MAY HAVE BEEN RUN DRY, THEN HEATING UP, AND CAUSING DAMAGE TO ARMATURE.																			 
1996080800749	19960808	00749	CE  	1996	8	8	96ZZZX3884       	1	19960717	G	8011	MZ4224ECH	STARTER         	PRESTOLITE  		CESSNA	172   	172N        	2072434	CE  										GEARBOX	SCREWS STRIPPED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	733FU	12   				17268268				THREE OF FOUR FORWARD CAP SCREWS HOLDING STARTER MOTOR TO GEARBOX HOUSING THE BENDIX - STRIPPED.						1	H	7	1 	3O			NT	3A12    					 
1996080800750	19960808	00750	CE  	1996	8	8	96ZZZX3885       	1	19960717	G	2810		FUEL CAP        			CESSNA	182   	182Q        	2072732	CE  										WING	SEAL FAILED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	97077	2930 				18266966				FUEL CAP ASSY HAD TO BE REPLACED WITH MONARCH AIR AND DEVELOPMENT FUEL CAP AND INLET ASSY DUE TO THE UNAVAILABILITY OF R	EPLACEMENT PARTS.  LEAKING SEALS.					1	H	7	1 	3O			NT	3A13    					 
1996080800751	19960808	00751	CE  	1996	8	8	96ZZZX3886       	1	19960717	G	7921	L639171	OIL COOLER      	LORINORDAM  		CESSNA	206   	TU206G      	2073357	CE  										ENGINE OIL	LEAKED          	D				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			WP	07	P2NTM				94J067	U20603580				INSTALLED NEW LORI OIL COOLER, LEAKED IMMEDIATELY AT WELD AT BASE OF COOLER.  SUBMITTER SUGGESTS TO IMPROVE TEST/QUALITY	 CONTROL BEFORE LEAVING FACTORY.					1	H	7	1 	3O				A4CE    					 
1996080800752	19960808	00752		1996	8	8	96ZZZX3887       	1	19960716	G	2822	2B729	PUMP            	AIRBORNE    																BRUSH BLOCK	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					11E2892					PUMP MAY HAVE RUN DRY CAUSING PUMP TO HEAT UP AND DAMAGE BRUSH BLOCK.																			 
1996080800753	19960808	00753	EA  	1996	8	8	96ZZZX3888       	2	19960718	G	8520	SL13884MO6	BEARING         								LYC   	O540  	O540B2C5    	41532	EA  					NR 2 JOURNAL	FAILED          	B			BG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17		2    					L2295640A			AFTER NORMAL TEST CELL RUN, ENGINE OIL WAS DRAINED AND THE OIL FILTER AND SUCTION SCREEN WAS INSPECTED AND A MASSIVE AMO	UNT OF ALUMINUM WAS FOUND.  UPON DISASSEMBLY, FOUND THE FRONT BEARING HAD FAILED AT THE NR 2 JOURNAL.  THE BEARING HAD S	MEARED AND TRANSFERRED TO THE CRANKSHAFT THRUST AREA AND NR 2 JOURNAL.  ALL PARTS WERE INSPECTED TO DETERMINE THE CAUSE 	WITH NO FIRM CONCLUSION.  SUBMITTER RECOMMENDS USING ONLY LYCOMING BEARINGS ON RE-GROUND CRANKSHAFTS.								3	O			E295				 
1996080800754	19960808	00754		1996	8	8	96ZZZX3889       	1	19960717	G	2434	ALX942513	ALTERNATOR      	ELECTROSYS  	0           															DRIVE	DEFECTIVE       	B			APCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01					6042533					ALTERNATOR REPORTED TO BE 'FACTORY NEW' MISSING SHAFT-TO-DRIVE-COUPLING O-RING, P/N AN123864.  MISING DRIVE-END SEAL, P/	N 352068.  ROTOR 'DRAGS' AND BINDS WHEN SPUN BY HAND.  PROBLEMS FOUND DURING ROUTINE NEW PARTS INSPECTION.																		 
1996080800755	19960808	00755	CE  	1996	8	8	96ZZZX3890       	1	19960701	G	3230	6A07116002	CYLINDER        	WIPLINEINC  	4000        	CESSNA	206   	TU206F      	2073353	CE  										FLOAT	CRACKED         	C	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	7485Q					U20602220				HYDRAULIC LEAK.  CRACK INSIDE OF HYDRAULIC CYLINDER.  REPLACED PART WITH NEW.  INSPECTED, FOUND CORROSION, POSSIBLY CAUS	ED BY GEAR INDICATOR LIGHT WIRES AND HYDRAULIC LINE BEING CLAMPED TO CYLINDER.  A RUBBER/PLASTIC PAD HAD BEEN GLUED TO C	YLINDER TO PREVENT CONTACT SO CORROSION OCCURRED AT PERIPHERY OF PAD.				1	H	7	1 	3O				A4CE    					 
1996080800756	19960808	00756		1996	8	8	96ZZZX3891       	4	19960715	G	6122	53914	STUD            		4B21        	DHAV  	DHC3  	DHC3        	2800202	EA  										PROP GOV	BROKEN          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	511BW		202  		1121	35				ENGINE DEVELOPED AN OIL LEAK.  PROBLEM FOUND TO BE A BROKEN BASE-TO-BODY ATTACH STUD ON THE PROPELLER GOVERNOR OF THE FO	UR STUDS.  ONE WAS BROKEN, AND ONE AN31-5 NUT WAS SLIGHTLY LOOSE.  ALL 4 AN310-5 NUTS WERE SAFETIED.					1	H	7	1 	3R				A815    					 
1996080800757	19960808	00757	NM  	1996	8	8	96ZZZX3892       	1	19960701	G	2550	106091129	HEAT BLANKET    			BOEING	727   	727225      	1384077	NM  										AFT BAG FS 950C	BURNT HOLE      	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8882Z				1734	21579				DURING A C-5 CHECK, NOTED THAT AFT BAG PIT HEAT BLANKET, P/N 10-60911-20; (COX P/N 2137-29), HAD A 2 INCH BY .50 INCH BU	RN THROUGH THE BLANKET.  THE INSULATION BEHIND IT ALSO SHOWED SIGNS OF BURNING.					2	L	7	3 	4F				A3WE    					 
1996081500073	19960815	00073	EU  	1996	8	15	96ZZZX3893       	1	19960620	G	2160	7847231	VALVE           			AMD   	FALC50	FALCON900   	2700160	EU  										CABIN COOLING	MISWIRED        	H		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09	5733					39				TURBINE ANTI-ICE VALVE WAS INSTALLED TO CORRECT UNCONTROLLABLE CABIN AND COCKPIT TEMPERATURE DISCREPANCY.  VALVE OPERATE	D BACKWARDS CAUSING CABIN TO BECOME EXTREMELY HOT.  RECOMMENDATIONS BY TECH SERVICES TO CHECK VALVE FOR PROPER WIRING RE	VEALED THAT VALVE DID, IN FACT, OPERATE BACKWARDS DUE TO INTERNAL REVERSED WIRING ON THE VALVE MOTOR.  WERE ADVISED, AT 	THAT TIME, THAT 3 OR 4 OF THESE VALVES HAD BEEN FOUND WITH THE SAME PROBLEM COMING OUT OF OVERHAUL.			2	L	7	3 	4F			RT	A46EU   					 
1996081500074	19960815	00074	CE  	1996	8	15	96ZZZX3894       	1	19960621	G	2721	556544067	PUSH PULL ROD   			CESSNA	500   	500CESSNA   	2076602	CE  										RUDDER TAB	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	52AJ	7506 				5000061				DURING ROUTINE MAINTENANCE, RUDDER TAB PUSH/PULL RODS WERE REMOVED TO LUBRICATE TRIM ACTUATOR SCREWS.  THE ROD WAS SPLIT	 80 PERCENT OF THE LENGTH FROM WHAT APPEARED TO BE WATER FREEZING INSIDE THE TUBE.					1	L	7	2 	4F				A22CE   					 
1996081500075	19960815	00075	CE  	1996	8	15	96ZZZX3895       	1	19960621	G	2731		PUSH PULL ROD   			CESSNA	500   	500CESSNA   	2076602	CE  										ELEVATOR TAB	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	52AJ	7506 				5000061				DURING ROUTINE MAINTENANCE, ELEVATOR TAB PUSH/PULL RODS WERE REMOVED TO LUBRICATE ACTUATOR SCREWS.  THE ROD WAS FOUND TO	 HAVE BRAZE REPAIR OVER A CRACK AND WAS SPLIT OPEN.					1	L	7	2 	4F				A22CE   					 
1996081500076	19960815	00076	CE  	1996	8	15	96ZZZX3896       	1	19960705	G	2430	035A8843421	WIRE            			MTSBSI	MU2   	MU2B40      	5780440	CE  										START/GEN CABLE	BROKEN          	B		A	ACOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	68CL					448SA				LEFT ENGINE STARTER/CABLE COPPER CONNECTION LUG CONNECTED TO THE STARTERS GENERATOR, BROKE IN THE SHARP 90 DEGREE BEND S	EPARATING THE STARTER-CABLE FROM THE STARTER GENERATOR.  STARTER CABLE, AFTER SEPARATING FROM STARTER GENERATOR AND BEIN	G RELEASED FROM STRESS, CAME TO REST ON FUEL CONTROL BELLCRANK.  ELECTRICAL POWER SURGE ON ATTEMPTED ENGINE START DESTRO	YED 3 CONTROL ROD ASSYS AND NECESSITATED FUEL CONTROL UNIT OVERHAUL.  NOTE, THIS OCCURRED ON GROUND.  FURTHER INVESTIGAT	ION REVEALED CRACK IN STARTER GENERATOR GROUND CABLE LUG.  SUBMITTER RECOMMENDS LONGER LENGTH CABLES TO REMOVE STRESS.		1	H	7	2 	3T			RT	A10SW   					 
1996081500077	19960815	00077	NE  	1996	8	15	96ZZZX3897       	2	19960621	G	7310	991202426	HOSE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					MOTIVE FLOW FUEL	CHAFED          	B		A	CNQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	323QS	785  				5600323				FOUND THE LEFT ENGINE THRUST REVERSER CONTROL LINKAGE HAD CUT INTO THE OUTER PROTECTIVE COVER OF THE MOTIVE FLOW FUEL HO	SE.  THE FUEL HOSE ASSY WAS REPLACED AND THE T/R CONTROL LINKAGE SAFETY WIRE REPOSITIONED TO PREVENT IT FROM CHAFING THE	 HOSE.				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
1996081500078	19960815	00078	CE  	1996	8	15	96ZZZX3898       	1	19960715	G	2810	66005004	CELL            			LEAR  	60    	60LEAR      	5170707	CE  										FUSELAGE	LEAKING         	D	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	01	7US	1001 			9270409	014				FUSELAGE FUEL CELL CAVITY DRAIN LEAKING.  FOUND FORWARD FUSELAGE FUEL CELL NIPPLE CRACKED.  THREE EACH FUSELAGE CELL FLA	PPER VALVES DISCONNECTED.   REF:  LEAR SB60-28-5, INSPECTION OF AFT FUSELAGE CELL FLAPPER VALVES.					2	L	7	2 	4F			RT	A10CE   					 
1996081500079	19960815	00079	EU  	1996	8	15	96ZZZX3899       	1	19960719	G	2150	25VF1399AC	DUCT            			HWKSLY	DH125 	BH125400A   	4230138	EU  										RAM AIR	CRACKED         	B	S		RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4QB	9238 				25255				WHILE ACCOMPLISHING AIRFRAME INSPECTION, ONE OF THE INSPECTION REQUIREMENTS CALLED OUT TO INSPECT THE APU.  WHILE CONDUC	TING THE INSPECTION, NOTED A LARGE CRACK ABOVE THE RAM AIR DUCT DOOR.  THE APU WAS REMOVED WHICH REVEALED THE CRACKED RA	M AIR DUCT ASSY.  THE RIGHT SIDE OF THE DUCT CONTAINED A CRACK 7 INCHES - 10 INCHES LONG WITH ADDITIONAL CRACKS THROUGHO	UT THE DUCT ASSY.  THE APU IS NOT NORMALLY REMOVED DURING THIS INSPECTION WHICH COULD GO FOR NUMEROUS INSPECTIONS UNDETE	CTED.  IT IS BELIEVED THE HIGH VIBRATION LEVEL ASSOCIATED WITH THE APU CAUSED THE DUCT ASSY TO CRACK.		2	L	7	2 	4J				A3EU    					 
1996081500080	19960815	00080	CE  	1996	8	15	96ZZZX3900       	1	19960715	G	2435	66085121	GENERATOR       		400SG138Q   	LEAR  	60    	60LEAR      	5170707	CE  										LT START/GEN	DEFECTIVE       	C				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			EA	01	7US	961  			1184XL	014				VIBRATION THROUGH AIRCRAFT.  LEFT GENERATOR LIGHT ILLUMINATED IN-FLIGHT.  INSTALLED OVERHAULED STARTER 5-7-96.						2	L	7	2 	4F			RT	A10CE   					 
1996081500081	19960815	00081	CE  	1996	8	15	96ZZZX3901       	1	19960715	G	2435	60580031	STARTER         		400SG138Q   	LEAR  	60    	60LEAR      	5170707	CE  										LT ENGINE	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	7US		20   		1276XL	014				LEFT ENGINE SLOW TO START.  INSTALLED SERVICEABLE STARTER GENERATOR 6-5-96.						2	L	7	2 	4F			RT	A10CE   					 
1996081500082	19960815	00082	CE  	1996	8	15	96ZZZX3902       	1	19960715	G	2435	6058031	GENERATOR       		400SG138Q   	LEAR  	60    	60LEAR      	5170707	CE  										RT START/GEN	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	7US		9    		1171XL	014				RIGHT STARTER GENERATOR VENT CAUSING SEVERE SOOTING ON LOWER COWL.  FOUND .1875 INCH DIFFERENCE IN BRUSH LENGTH BETWEEN 	BRUSH SETS.					2	L	7	2 	4F			RT	A10CE   					 
1996081500083	19960815	00083	CE  	1996	8	15	96ZZZX3903       	1	19960715	G	2435	60580031	STARTER         		400SG138Q   	LEAR  	60    	60LEAR      	5170707	CE  										RT START/GEN	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	7US		21   		1276XL	014				RIGHT ENGINE SLOW TO START AFTER SHUT DOWN AND RE-START.  ENGINE HANGS AT 4 TO 6 PERCENT N2.  FIRST START NORMAL.						2	L	7	2 	4F			RT	A10CE   					 
1996081500084	19960815	00084	EU  	1996	8	15	96ZZZX3904       	1	19960711	G	2435	03601015	BEARING         	LUCAS       	23080005    	BRAERO	DH125 	BAE125800A  	1500285	EU  										START/GEN DR END	SEAL FAILED     	B			JAVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	208R	868  			2349	NA1003				RECEIVED SEVERAL STARTER/GENERATOR UNITS OF THIS MODEL TYPE WITH DRIVE END BEARING SEALS DISLODGED AND BEARING LUBRICATI	ON LOST.  THIS PROBLEM HAS BEEN ADDRESSED IN THE PAST BY THE O.E.M. WITH P/N UPGRADES, BUT THE PROBLEM STILL SEEMS TO EX	IST.  SUBMITTER RECOMMENDS OVERHAUL BE PERFORMED IN LESS TIME THAN O.E.M. RECOMMENDED HOURS TO PREVENT BEARING FAILURE. 	 THIS COULD COINSIDE WITH NORMAL BRUSH WEAR AT APPROXIMATELY 700 HOURS.			2	L	7	2 	4F			RT	A3EU    					 
1996081500085	19960815	00085	CE  	1996	8	15	96ZZZX3905       	1	19960725	G	2913	MX211919A	PUMP            	VICKERS     		RKWELL	NA265 	NA26540     	6402608	CE  										HYDRAULIC SYS	SEAL FAILED     	D				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			SO	16	303NT		72   			28229				HYDRAULIC PUMP SHAFT SEAL FAILURE IN-FLIGHT 'WITHOUT INCIDENT', BUT ELECTRIC DRIVE MOTOR AND SURROUNDING AFT FUSELAGE AR	EA TO TAIL WAS SATURATED WITH APPROXIMATELY 2 GALLONS OF FLUID WHICH POSED A SEVERE FIRE HAZARD.					2	L	7	2 	4J				A2WE    					 
1996081500086	19960815	00086	NE  	1996	8	15	96ZZZX3906       	2	19960710	G	7230		COMPRESSOR      			RKWELL	NA265 	NA26540     	6402608	CE  	PWA   	JT12  	JT12A8      	52042	NE  					ENGINE	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	309NT	11970	1398 			28261	P638364NB			COMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT.  INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND.  T	HIS IS A MULTI-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PART FAILURE IS VERY DIFFICULT.  NO FOD NOTED 	AND NO DAMAGE OR DEFECTS NOTED IN TURBINE HOT SECTION.  ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL.				2	L	7	2 	4J	4	J		A2WE    	1E9				 
1996081500087	19960815	00087	EU  	1996	8	15	96ZZZX3907       	1	19960624	G	2820	L96Z31201	CHECK VALVE     			AMD   	FALC50	FALCON50MYST	2730106	EU  										PLUNGER	WASHER FAILED   	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	48HB				21442	233				UPON FUELING AIRCRAFT FOR LEAK CHECKS OF FEEDER TANKS, THE CENTER FEEDER TANK OVERFILLED AND VENTED OVERBOARD.  DEFUELED	 ACFT TO TROUBLESHOOT.  AFTER T/S, FOUND PLUNGER WASHER OF A CHECK VALVE LODGED IN THE LT FEEDER TANK FUELING VALVE.  AP	PARENTLY, THE WASHER WAS INITIALLY LODGED IN THE CENTER FEEDER TANK SYSTEM CAUSING THE OVERFILL, THEN MOVED THROUGH THE 	FUELING MANIFOLD TO THE LT FEEDER TANK FUELING VALVE DURING THE DEFUEL, AND SUBSEQUENT TROUBLESHOOTING.  THIS WASHER IS 	HELD ON THE CHECK VALVE PLUNGER BY A POP RIVET.  SUBMITTER RECOMMENDS ANALYSIS OF HOW MANY OF THESE CHECK VALVES HAVE FA	ILED LIKE THIS AND POSSIBLE REPLACMENT WITH NEW STYLE OR IMPROVEMENT OF EXISTING VALVES.	2	L	7	3 	4F				A46EU   					 
1996081500088	19960815	00088	CE  	1996	8	15	96ZZZX3908       	1	19960718	G	2720	1303800033	TRANSDUCER      			BEECH 	B300  	B300        	1159232	CE  										RUDDER BOOST	FAILED          	B		A	GJQR	A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			F			FLT CONT AFFECTED         			CL	CLIMB          	1			NM	01	4S	15   			56305141	FL107				ON DEPARTURE, PILOT REPORTED RUDDER BOOST APPLIED RIGHT RUDDER.  HAD TO USE DISCONNECT BUTTON TO DISCONNECT RUDDER BOOST	 SYSTEM AND RETURNED AND LANDED.  TROUBLESHOOTING REVEALED TRANSDUCER GIVING FALSE SIGNAL.  REPLACED TRANSDUCER AND FUNC	TIONAL TESTS WERE NORMAL.  APPARENTLY, BEECH IS ENCOUNTERING AN EPIDEMIC OF PROBLEMS WITH THESE TRANSDUCERS.  SINCE IT A	FFECTS THE RUDDER FLIGHT CONTROL SYSTEM, SUBMITTER CONSIDERS THIS A FLIGHT SAFETY ISSUE.			2	L	7	2 	4T			RT	A24CE   					 
1996081500089	19960815	00089	CE  	1996	8	15	96ZZZX3909       	1	19960718	G	2720	1303800031	TRANSDUCER      			BEECH 	B300  	B300        	1159232	CE  										RUDDER BOOST	FAILED          	B			GJQR	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NM	01	4S	658  			459	FL107				RUDDER BOOST INOPERABLE.  LEFT SIDE, NO SIGNAL, HARD RIGHT PEDAL ALL THE TIME.  REPLACED RUDDER BOOST TRANSDUCER, SYSTEM	 FUNCTIONAL TESTED NORMALLY.					2	L	7	2 	4T			RT	A24CE   					 
1996081500090	19960815	00090	EA  	1996	8	15	96ZZZX3910       	2	19960613	G	8530	LW16475	SPRING SEAT     			PIPER 	PA44  	PA44180T    	7104404	SO  	LYC   	O360  	LTO360E1A6  	41515	EA  					VALVE	FAILED          	B			PAIR	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	05	8269T		229  			448107022	RL00026674T			THE OPERATOR INCURRED AN IN-FLIGHT FAILURE.  INSPECTION REVEALED VALVE SEAT FAILED.  SUBMITTER STATED THIS UNIT WAS NOT 	REPLACED DURING LAST OVERHAUL BECAUSE LYCOMING SB 447A FAILED TO LIST LTO-360-E1A6D AS AN EFFECTED ENGINE.  SUBMITTER ST	ATED AD 80-14-07 NEGLECTED TO ADDRESS THIS ENGINE MODEL POSSIBLY IN ERROR.				1	L	7	2 	3O	3	O		A19SO   	E26EA				 
1996081500091	19960815	00091	EA  	1996	8	15	96ZZZX3911       	2	19960717	G	7414	10357592	OIL SEAL        		S4LN200     	HUGHES	269   	TH55A       	4471004	WP  	LYC   	O360  	HIO360B1A   	41514	EA  					MAG DRIVE END	FAILED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			WP	07	331SD		450  		00349	291105	L333351A			DURING TRAINING FLIGHT, ENGINE ROUGHNESS 'FELT' IN-FLIGHT; FOUND MAGNETO POINTS SATURATED WITH OIL.  REPLACED MAGNETO WI	TH REBUILT UNIT.					1	G	7	1 	3R	3	O			1E10				 
1996081500092	19960815	00092	SW  	1996	8	15	96ZZZX3912       	1	19960725	G	2910	MS8001F200A	HOSE            		206076056103	BELL  	204   	UH1H        	1181407	SW  										HYD SYSTEM	CHAFED          	B		A	LS1R	A				UNSCHED LANDING         				F	J	K	FLT CONT AFFECTED         	WARNING INDICATION        	FLUID LOSS                	CR	CRUISE         	1			EA	13	51AG	4164 				7120178				DURING STRAIGHT AND LEVEL FLIGHT, PILOT NOTICED FLIGHT CONTROLS STARTING TO FEEL STIFF.  THIS WAS IMMEDIATELY FOLLOWED B	Y A DROP IN HYDRAULIC PRESSURE.  PILOT LANDED ACFT SAFELY IN A FIELD.  MECHANIC WAS DISPATCHED AND FOUND A HYDRAULIC LIN	E HAD RUPTURED DUE TO CHAFING.  IN ADDITION, HYD LINE PN 205-076-201-1 HAD A SMALL CRACK UNDER THE B-NUT AT THE COMPRESS	ION FITTING.  NEW LINES WERE INSTALLED, HYDRAULIC SYSTEM SERVICED, AND AIRCRAFT RETURNED TO SERVICE.			1	G	7	1 	4U				EXPA1G71					 
1996081500093	19960815	00093	SW  	1996	8	15	96ZZZX3913       	1	19960709	G	6730	2140760291	HOUSING         		214076014101	BELL  	214   	214ST       	1182106	SW  										SERVO ACTUATOR	CORRODED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11					7098					CORROSION WAS FOUND DURING FLUORESCENT PENETRANT INSPECTION AND WAS REJECTED PER HR-TEXTRON TD-WP-101-5.						2	G	7	2 	4U				H10SW   					 
1996081500094	19960815	00094	SW  	1996	8	15	96ZZZX3914       	1	19960709	G	6730	2140760291	HOUSING         		2140761461  	BELL  	214   	214ST       	1182106	SW  										SERVO ACTUATOR	CORRODED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11					580B					CORROSION WAS FOUND DURING FLUORESCENT PENETRANT INSPECTION AND WAS REJECTED PER NR-TEXTRON TD-WP-101-5.						2	G	7	2 	4U				H10SW   					 
1996081500095	19960815	00095	SW  	1996	8	15	96ZZZX3915       	1	19960709	G	6730	214060281	RETAINER        		214076146001	BELL  	214   	214ST       	1182106	SW  										SERVO ACUATOR	CORRODED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11					549					CORROSION WAS FOUND DURING FLUORESCENT PENETRANT INSPECTION AND WAS REJECTED PER HR-TEXTRON TD-WP-101-5.						2	G	7	2 	4U				H10SW   					 
1996081500096	19960815	00096	SW  	1996	8	15	96ZZZX3916       	1	19960709	G	6730	2140760291	HOUSING         			BELL  	214   	214ST       	1182106	SW  										SERVO ACTUATOR	CORRODED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11					7057					CORROSION WAS FOUND DURING FLUORESCENT PENETRANT INSPECTION AND WAS REJECTED PER HR-TEXTRON TD-WP-101-5.						2	G	7	2 	4U				H10SW   					 
1996081500097	19960815	00097	CE  	1996	8	15	96ZZZX3917       	1	19960718	G	5520	50350056	FITTING         			CESSNA	402   	402C        	207590R	CE  										RT ELEVATOR	CRACKED         	E		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	305AT	4720 				402C0030				WHILE C/W CESSNA SB MEB 95-10, FOUND RT ELEVATOR FITTING CRACKED AT AREA WHERE THE TAPER PIN COMES THROUGH.  SUBMITTER S	UGGESTS THAT THESE FITTINGS ARE INSPECTED ANYTIME THE TAIL CONE IS REMOVED.					1	L	7	2 	3O				A7CE    					 
1996081500098	19960815	00098	SO  	1996	8	15	96ZZZX3918       	1	19960716	G	5712	708475004	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  										LT WING	CRACKED         	B		A	OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	172ND	5813 				2837007				FOUND RIB IN LEFT WING WHEELWELL CRACKED.  CRACK LOCATED IN RIB FLANGE RADIUS AT FORWARD LOWER CORNER WHERE RIB RIVETS/B	OLTS TO SPAR.  DRAG LINK KNUCKLE ALSO ATTACHES AT THIS POINT.					1	L	7	1 	3O				2A13    					 
1996081500099	19960815	00099	GL  	1996	8	15	96ZZZX3919       	3	19960725	G	6114	DB2248	HUB             			CESSNA	340   	340A        	2076405	CE  						HARTZL	HCC3Y	PHCC3YF2    	GL  	MOUNT BOLTS	CRACKED         	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	8636K	1661 				340A0562		EB2248		PROPELLER WAS INSTALLED 7-25-96 AT HOUR METER 1362.6.  PROPELLER WAS NEW AT TIME OF INSTALL.  PROPELLER REMOVED WITH 166	1.4 HOURS TOTAL TIME.  FIRST INDICATION OF DEFECT WAS GREASE ON FRONT OF ENGINE COWLING.  FOUND APPROXIMATE 4 INCH LONG 	CRACK ON AFT HUB BY MOUNTING BOLTS.				1	L	7	2 	3O				3A25    		5	C	P25EA	 
1996081500100	19960815	00100	SO  	1996	8	15	96ZZZX3920       	1	19960724	G	2730	7105602	SPRING          			PIPER 	PA31  	PA31325     	7103105	SO  										ELEVATOR	FAILED          	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	979SP	3786 				317812015				FAILED ELEVATOR STRING WAS FOUND DURING 100-HOUR INSPECTION.						1	L	7	2 	3O				A20SO   					 
1996081500102	19960815	00102	CE  	1996	8	15	96ZZZX3922       	1	19960626	G	2823	C2915030101	VALVE           			CESSNA	210   	P210N       	2073454	CE  										FUEL SELECTOR	LEAKING         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	4515K		23   		6566	P21000205				FOLLOWING INSTALLATION OF FUEL VALVE, A FUEL SMELL WAS NOTICED IN AIRCAFT CABIN.  INVESTIGATION REVEALED FUEL LEAKING FR	OM THE AFT PLUG ADJACENT TO THE FUEL LINE FITTING PORT WHICH IS AFT WHEN VALVE IS INSTALLED.  THIS PLUG IS APPARENTLY IN	STALLED DURING MANUFACTURE OF THE FUEL VALVE, AND ONLY A CIRCULAR OUTLINE CAN BE DISTINGUISHED.  IT IS DIFICULT TO SEE. 	 THE CAUSE OF THIS LEAKAGE IS UNKNOWN, ALTHOUGH THE PLUG SEEMED TO BE TIGHT.			1	H	7	1 	3O				3A21    					 
1996081500104	19960815	00104	SO  	1996	8	15	96ZZZX3924       	1	19960725	G	7120	6129400	BRACKET         			PIPER 	PA25  	PA25        	7102502	SO  										ENGINE MOUNT	BROKEN          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	6270Z	3815 				25335				TWO OF FOUR ENGINE MOUNT BRACKETS CRACKED AT BOLT HOLES.  ONE MOUNT BRACKET BROKE IN HALF BY HAND WHEN REMOVED.  FATIGUE	 SUSPECT CAUSE.  THESE BRACKETS ALLOW THE ENGINE TO SWING AWAY FROM THE FIRE WALL.  FAILURE IN-FLIGHT WOULD BE CATASTROP	HIC.  SUBMITTER RECOMMENDS GOOD INSPECTION OF MOUNTS.				1	L	7	1 	3O				2A10    					 
1996081500105	19960815	00105	SO  	1996	8	15	96ZZZX3925       	1	19960725	G	3211	AN626A	BOLT            			PIPER 	PA25  	PA25        	7102502	SO  										MLG RT FWD	SHEARED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	6270Z					25335				RIGHT FORWARD LANDING GEAR BOLT WAS FOUND WITH HEAD SHEARED COMPLETELY OFF DURING ANNUAL INSPECTION OF WING ATTACH FITTI	NGS.  RECOMMEND GOOD INSPECTION OF GEAR ATTACH AREA.					1	L	7	1 	3O				2A10    					 
1996081500106	19960815	00106	CE  	1996	8	15	96ZZZX3926       	1	19960607	G	3230	98820201	PIN             			CESSNA	210   	T210N       	2073456	CE  										NLG DOWNLOCK	FAILED          	D	P			O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CE	05	6939N	1993 				21063161				PILOT COULD NOT GEAR DOWN GREEN LIGHT AFTER REPEATED CYCLES AND EMERGENCY EXTENSION.  AFTER FAILURE AND ON LANDING, ACFT	 PLACED ON JACKS AND GEAR CYCLED NORMAL UP AND DOWN OVER 20 TIMES WITH NO APPARENT PROBLEM.  REMOVED NOSE GEAR ACTUATOR 	TO BENCH TEST, FOUND BOTH DOWNLOCK PINS IN NOSE GEAR ACTUATOR BEARING BROKEN AT ROLL PIN LOCATION.  THE BROKEN PINS WOUL	D NOT ALLOW ACTUATOR TO ENGAGE DOWNLOCK HOOKS ONTO PINS.  JAM NUT ON ACTUATOR SHAFT WOULD NOT PASS TO ALLOW ACTUATOR TO 	FULLY RETRACT.  THE ONLY WAY TO CHECK FOR THIS PROBLEM IS TO UNLOCK NOSE GEAR AND STOP IN MID-CYCLE SO AS TO ALLOW ACCES	S TO PINS TO CHECK FOR MOVEMENT.	1	H	7	1 	3O				3A21    					 
1996081500107	19960815	00107	CE  	1996	8	15	96ZZZX3927       	1	19960612	G	3230	0842102497	BELLCRANK       			CESSNA	310   	310N        	2074234	CE  										NLG	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	743JR	4400 				310N0116				NOSE GEAR IDLER BELLCRANK LINKAGE FAILURE.						1	L	7	2 	3O				3A10    					 
1996081500108	19960815	00108	EA  	1996	8	15	96ZZZX3928       	2	19960722	G	7421	REM37BY	SPARK PLUG      			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					NR 4 CYLINDER	FOULED          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	09	2416B	50   				3879A0052	L1758615			WHILE FLYING, PILOT EXPERIENCED PARTIAL LOSS OF ENGINE RPM AND MADE A PRECAUTIONARY LANDING IN A FIELD.  UPON INVESTIGAT	ION, FOUND THE BOTTOM SPARK PLUG IN NR 4 CYLINDER WAS NOT GAPPED PROPERLY.  A PIECE OF CARBON GOT STUCK BETWEEN THE ELEC	TRODES OF THE SPARK PLUG ALLOWING IT TO BECOME OIL FOULED.  THERE WAS NO DAMAGE TO AIRCRAFT OR PERSONS.				1	L	7	1 	3O	3	O		A18SO   	E223				 
1996081500109	19960815	00109	EA  	1996	8	15	96ZZZX3929       	2	19960701	G	7322	105267	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					FINGER SCREEN	BLOCKAGE        	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	05	3281R					15284363	L2106415			PARTIAL POWER LOSS.  FINGER SCREEN WAS FOUND PARTIALLY FILLED WITH A LINT-LIKE SUBSTANCE TO THE POINT THAT FUEL FLOW WAS	 RESTRICTED.  THE FUEL SYSTEM WAS CHECKED BY DRAINING FUEL FROM SUMPS, GASCOLATOR, FUEL LINE, CARBURETOR FLOAT BOWL.  NO	 FURTHER CONTAMINATION WAS FOUND.  GASCOLATOR WAS DISASSEBLED, AND SCREEN WAS FOUND TO BE CLEAN.  THE GASOLATOR HAD FAIL	ED TO TRAP CONTAMINATION.  SYSTEM REASSEMBLED, AIRCRAFT GROUND RUN AND TEST FLOWN.  OPERATION NORMAL, RETURNED TO SERVIC	E.		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996081500110	19960815	00110	SO  	1996	8	15	96ZZZX3930       	1	19960718	G	3210	2082900	STUD            			PIPER 	PA24  	PA24250     	7102404	SO  										MLG SIDE BRACE	CRACKED         	B			R7LR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	6476P					241592				ON C/W AD 95-20-07, BOTH MLG SIDE BRACE STUDS WERE FOUND CRACKED BY MPI.  ONE STUD WAS NEW TYPE 487-596 WITH ZERK GREASE	 FITTING.  CRACKS NOT VISIBLE WITHOUT MPI.  CRACKS AT SHANK RADIUS.					1	L	7	1 	3O				1A15    					 
1996081500112	19960815	00112	NE  	1996	8	15	96ZZZX3932       	2	19960722	G	8530	399354	CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R985  	R985AN14B   	52008	NE  					NR 1 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	8605H	5000 	1157 			1432	13782			ENGINE INSPECTION FOUND NR 1 CYLINDER HEAD HAD CRACKED FROM FORWARD SPARK PLUG BOSS UP OVER CENTER OF CYLINDER HEAD AROU	ND BELOW EXHAUST PORT, FORWARD AT CYLINDER HEAD/BARREL ATTACH AREA, BACK TO LOWER SIDE OF FORWARD SPARK PLUG BOSS.					1	Q	7	1 	3R	3	R		1A16    	5E1				 
1996081500113	19960815	00113		1996	8	15	96ZZZX3933       	4	19960722	G	2562	AK450	ELT             	AMERIKING   		CESSNA	150   	150F        	2071814	CE  										G-SWITCH	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	8749S	5    			4502286	15062049				ELT SYSTEM INSTALLED AND INSPECTION IAW FAR 91.207.0.  ELT SYSTEM CHECKED 60 DAYS LATER BY DEPRESSING TEST SWITCH.  TEST	 LIGHT CAME ON, BUT NO AUDIO HEARD ON 121.5.  ALSO 'G' SWITCH TURNS LIGHT ON, BUT NO AUDIO ON FREQUENCY.					1	H	7	1 	3O				3A19    					 
1996081500114	19960815	00114	GL  	1996	8	15	96ZZZX3934       	1	19960716	G	3221		SUPPORT         			AMTR  	LNCAIR	235LANCAIR  	05612ML	GL  										NLG	BROKEN          	B		A	AW4R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	11	880RS	237  				88				WHEN PILOT WENT TO LOWER GEAR DURING APPROACH, THE HANDLE ON THE GEAR CONTROL SWITCH BROKE OFF PREVENTING GEAR FROM LOWE	RING USING THE NORMAL SYSTEM.  MANUAL GEAR EXTENSION WAS INITIATED, BUT NOSE GEAR FAILED TO EXTEND.  LANDING WAS MADE WI	TH NLG RETRACTED.  TWO PROBLEMS WERE NOTED UPON INITIAL EXAMINATION  WHEN LOWER COWL WAS REMOVED, THE ENGINE MOUNT/NOSE 	GEAR SUPPORT WAS FOUND BROKEN AT LEFT SIDE OF NLG.  IT IS SUSPECTED THIS BROKEN TUBE ALLOWED NLG TO SHIFT POSITION ENOUG	H TO JAM THE WHEELWELL PREVENTING IT FROM MOVING INTO THE DOWN POSITION WHEN MANUAL EXTENSION SYSTEM WAS USED.  CAUSE OF	 CRACKED TUBE HAS NOT BEEN DETERMINED.  LAST CONDITION INSPECTION COMPLETED 10-95 AT 177.6 HOURS.	1	L	7	1 	30			RT	EXPA1L71					 
1996081500115	19960815	00115	GL  	1996	8	15	96ZZZX3935       	1	19960716	G	3230		SWITCH          			AMTR  	LNCAIR	235LANCAIR  	05612ML	GL  										MLG CONTROL	FAILED          	B		A	AW4R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	11	880RS	237  				88				WHEN PILOT WENT TO LOWER GEAR DURING APPROACH, THE HANDLE ON THE GEAR CONTROL SWITCH BROKE OFF PREVENTING GEAR FROM LOWE	RING USING THE NORMAL SYSTEM.  MANUAL GEAR EXTENSION WAS INITIATED, BUT NOSE GEAR FAILED TO EXTEND.  LANDING WAS MADE WI	TH NLG RETRACTED.				1	L	7	1 	30			RT	EXPA1L71					 
1996081500116	19960815	00116		1996	8	15	96ZZZX3936       	1	19960723	G	2822	2B632	PUMP            	AIRBORNE    																FUEL BOOST	ARMATURE FAILED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					12W322					INSPECTION FOUND ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996081500117	19960815	00117		1996	8	15	96ZZZX3937       	1	19960723	G	2822	2B638	PUMP            	AIRBORNE    																FUEL BOOST	ARMATURE FAILED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					12A23					INSPECTION FOUND ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996081500118	19960815	00118		1996	8	15	96ZZZX3938       	1	19960723	G	2822	2B632	PUMP            	AIRBORNE    																FUEL BOOST	ARMATURE FAILED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					12W342					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996081500119	19960815	00119		1996	8	15	96ZZZX3939       	1	19960723	G	2822	2B632	PUMP            	AIRBORNE    																FUEL BOOST	ARMATURE FAILED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					12W355					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996081500120	19960815	00120		1996	8	15	96ZZZX3940       	1	19960723	G	2822	2B632	PUMP            	AIRBORNE    																FUEL BOOST	ARMATURE FAILED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					4A149					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996081500121	19960815	00121		1996	8	15	96ZZZX3941       	1	19960723	G	2822	2B636	PUMP            	AIRBORNE    																FUEL BOOST	ARMATURE FAILED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					5D72					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996081500122	19960815	00122		1996	8	15	96ZZZX3942       	1	19960701	G	2822	2B663	PUMP            	AIRBORNE    																FUEL BOOST	SHAFT DAMAGED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					10AC101					ARMATURE SHAFT DAMAGED BY SPACER.																			 
1996081500123	19960815	00123		1996	8	15	96ZZZX3943       	1	19960701	G	2822	2B663	PUMP            	AIRBORNE    																FUEL BOOST	SHAFT DAMAGED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					10AC114					ARMATURE SHAFT DAMAGED BY SPACER, DEEP GROOVE WORN IN SHAFT.																			 
1996081500239	19960815	00239	GL  	1996	8	15	96ZZZX3944       	2	19960729	G	7230	6898607	BEARING         		6896028     	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C28B     	03013	GL  					NR 1	FAILED          	B			KUVR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	19	165BH	2509 			R1747	45249	CAE860728			AIRCRAFT EXPERIENCED 3 CHIP LIGHTS WITHIN 50 HOURS.  AIRCRAFT GROUNDED PER ALLISON MM.  UPON INVESTIGATION FOUND NR 1 BE	ARING CAGE BROKEN INTO PIECES AND BEARING FELL APART.  SIMPLE MECHANICAL FAILURE THAT COULD HAVE CAUSED ENGINE FLAME-OUT	.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1996081500240	19960815	00240	EA  	1996	8	15	96ZZZX3945       	2	19960718	G	7260	330170501	HOUSING         		330160203   	SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6B36      	52043	EA  					NR 1 ENG AGB	DAMAGED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	22CP	999  				760425	36207			AIRCRAFT TT:  999.1 HOURS.  NR 1 ENGINE TT, 999.1 HOURS.  DURING REPLACEMENT OF NR 1 HMU, FOUND CORROSION DAMAGE IN THE 	BORE ON THE HOUSING WHERE HMU IS INSTALLED.  CORROSION DAMAGE WAS AT THE 6 O'CLOCK POSITION, AND RANGED FROM MINOR TO SO	ME DEEP PITS UP TO .140 INCH DEEP.  ENGINE IS BEING REMOVED AND SENT FOR EVALUATION AND REPAIR.				1	G	7	2 	4U	4	U		H1NE    	E4EA				 
1996081500729	19960815	00729	CE  	1996	8	15	96ZZZX3994       	1	19960717	G	2150	585550273	PULLEY          			BEECH 	58    	58          	1152740	CE  										AIR COND IDLER	BEARING WORN    	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	43240	151  				TH1740				AIR CONDITIONER IDLER PULLEY WAS VERY LOOSE.  FOUND THE PULLEY BOSS THAT FITS INSIDE OF THE BEARING (PN 203SZZ) WAS VERY	 WORN.  BEARING COULD BE TURNED BY HAND, B4UT WAS ROUGH FEELING WHEN ROTATED.  SUBMITTER SUGGESTS POSSIBLY A BETTER QUAL	ITY BE6ARING AND A BETTER FIT BETWEEN THE PULLEY AND THIS BEARING WOULD HELP.				1	L	7	2 	3O				3A16    					 
1996081500730	19960815	00730	EA  	1996	8	15	96ZZZX3995       	2	19960702	G	8520	67204	LOCKWASHER      			BELL  	47    	47G5        	1181032	SW  	LYC   	O435  	VO435B1A    	41516	EA  					CRANKSHAFT	FAILED          	D	L	A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			WP	17	7938J	3550 	1035 			25043	L359731			DURING TROUBLESHOOTING, METAL IN OIL SCREEN PROBLEM, A TANG WAS FOUND IN SUMP SUCTION SCREEN, BUT WAS UNABLE TO POSITIVE	LY IDENTIFY THE SOURCE OF METAL.  TENTATIVELY IDENTIFIED AND HELICOPTER RETURNED TO SERVICE.  6.5 HOURS LATER, THE ENGIN	E QUIT SUDDENLY ON TAKEOFF.  FORTUNATELY, NO DAMAGE TO HELICOPTER.  ON INVESTIGATION OF PROBLEM, FOUND CRANKSHAFT GEAR A	ND PARTS IN ACCESSORY HOUSING.  SUSPECT IMPROPER INSTALLATION AT LAST OVERHAUL.			1	G	7	1 	3O	3	O		2H3     	E279				 
1996081500731	19960815	00731	SO  	1996	8	15	96ZZZX3996       	1	19960710	G	5330	99470001	SKIN            			PIPER 	PA34  	PA34200     	7103405	SO  										FS 215	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	94PG	3240 				347450064				PILOTS PRE-FLIGHT INSPECTION FOUND RT SIDE OF AIRCRAFT AT STA 215 WITH SKIN CRACKED.  FURTHER INVESTIGATION, STRINGER CR	ACKED AT BULKHEAD STA 215.  SUBMITTER STATED THIS AIRCRAFT USED FOR MULTI-ENGINE TRAINING, SUSPECT SINGLE ENGINE FLIGHT 	FATIGUES EMPENNAGE STRUCTURE.				1	L	7	2 	3O				A7SO    					 
1996081500732	19960815	00732	SO  	1996	8	15	96ZZZX3997       	1	19960710	G	5313	78608003	STRINGER        			PIPER 	PA34  	PA34200     	7103405	SO  										BLKHD FS 215	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	94PG	3240 				347450064				PILOTS PRE-FLIGHT INSPECTION FOUND RT SIDE OF AIRCRAFT AT STA 215 WITH SKIN CRACKED.  FURTHER INVESTIGATION, STRINGER CR	ACKED AT BULKHEAD STA 215.  SUBMITTER STATED THIS AIRCRAFT USED FOR MULTI-ENGINE TRAINING, SUSPECT SINGLE ENGINE FLIGHT 	FATIGUES EMPENNAGE STRUCTURE.				1	L	7	2 	3O				A7SO    					 
1996081500733	19960815	00733	SO  	1996	8	15	96ZZZX3998       	1	19960719	G	5260	159AM100573	JACKSHAFT       			GULSTM	G1159 	G1159       	3953505	SO  										MAIN ENTRY DOOR	CRACKED         	B	P	A	RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2MIL	11611				045				WHILE CLOSING ACFT MAIN ENTRY DOOR, NOTED DOOR WOULD NOT PROPERLY CLOSE AND LOCK.  DURING INVESTIGATION AND T/S OF MAIN 	ENTRY DOOR, JACKSHAFT ASSY PN 159AM10057-3 WAS FOUND TO HAVE A FRACTURE CRACK RUNNING THE FULL LENGTH.  OLD JACKSHAFT WA	S REMOVED AND REPLACED WITH P/N 159AM10057-5.  AFTER FURTHER RESEARCH, ASC NR 146 ADDRESSES REWORK OF AIRSTAIR DOOR.  TH	IS ASC PROVIDES INSTRUCTION FOR REMOVAL AND REPLACEMENT OF JACKSHAFT AND ADDITIONAL COMPONENTS REQUIRED FOR REPLACEMENT 	OF NEW JACKSHAFT P/N.  REMOVAL AND REPLACEMENT OF THE JACKSHAFT BY ITSELF COULD CAUSE FURTHER DAMAGE WITHOUT CHANGING AL	 REQUIRED COMPONENTS AS CALLED OUT IN ASC 146.  CAUSE OF FAILURE IS UNKNOWN.	2	L	7	2 	4F			RT	A12EA   					 
1996081500734	19960815	00734	GL  	1996	8	15	96ZZZX3999       	3	19960716	G	6114		HUB             													MCAULY	3AF32C	3AF32C87    	GL  	SOCKET	PLUGS MISSING   	B			F3PR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15								727049		INSPECTION FOUND IN ALL 3 BLADE SOCKETS WHERE BLADE NUT AND HUB SOCKETS MEET, EXPANSION PLUGS WERE NOT INSTALLED.  PROPE	LLER WAS RECENT AD COMPLIANCE BY SHOP IN KANSAS.															5	C	P22EA	 
1996081500735	19960815	00735	GL  	1996	8	15	96ZZZX4000       	3	19960716	G	6114		HUB             													MCAULY	3AF32C	3AF32C87    	GL  	SOCKET	PLUGS MISSING   	B			F3PR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15								722019		INSPECTION FOUND IN ALL 3 BLADE SOCKETS WHERE BLADE NUT AND HUB MEET, EXPANSION PLUGS WERE NOT INSTALLED.  EXAMINATION S	HOWS THAT PREVIOUS HOLES WERE DRILLED TOO CLOSE TOGETHER WHICH REJECTS HUB.  ALSO, REAR HUB ADAPTER USED APPEARS TO BE B	OGUS.  PROPELLER WAS FRESH AD COMPLIANCE FROM SHOP IN KANSAS.														5	C	P22EA	 
1996081500736	19960815	00736	SO  	1996	8	15	96ZZZX4001       	1	19960701	G	3213		BRACE           			PIPER 	PA34  	PA34200T    	7103406	SO  										MLG STRUT	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	38679					347770332				INSPECTION FOUND BINDING ON GEAR STRUT BRACE.  SUBMITTER STATED NEEDS TO BE REAMED TO FREE MOVEMENT.						1	L	7	2 	3O				A7SO    					 
1996081500737	19960815	00737	CE  	1996	8	15	96ZZZX4002       	1	19960725	G	2821	331995	STRAINER        			CESSNA	180   	180         	2072602	CE  										FUEL SYSTEM	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	25	3122C	3000 				30921				PILOT REPORTED AFTER SOME TURBULENCE ON FINAL APPROACH, ENGINE QUIT.  ON INVESTIGATION, DISCOVERED THE FUEL STRAINER BOW	L AND CAP WERE MISSING.  SUBMITTER RECOMMENDATION:  PILOTS BE AWARE THAT FUEL DRAINS NEED TO BE SAFETIED AND CHECKED DUR	ING PRE-FLIGHT.				1	H	7	1 	3O			NC	5A6     					 
1996081500738	19960815	00738	SO  	1996	8	15	96ZZZX4003       	1	19960629	G	3230	9572400	MOUNT ASSY      			PIPER 	PA34  	PA34200     	7103405	SO  										NLG HYD JACK	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	01	4484T	5662 				347250110				NOSE GEAR COLLAPSE UNDER FULL POWER APPLICATON DURING A TOUCH-AND-GO LANDNG.  MOUNT ASSY APPEARS TO HAVE FAILED AT BOLT 	HOLE, INBD SIDE, WHERE IT CONNECTS TO RETRACT LINK PN 9571200.  SUSPECT REPEATED RETRACTION CYCLES CAUSED CRACK TO PROPA	GATE FROM BOLT HOLE (FOR AN 23-25) FORWARD TO EDGE OF PART.  AIRCRAFT WAS SEEN ON PREVIOUS LANDING TO HIT ON NOSE WHEEL 	FIRST.			1	L	7	2 	3O				A7SO    					 
1996081500739	19960815	00739	SO  	1996	8	15	96ZZZX4004       	1	19960716	G	5712	78475005	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  										RT WING	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	170ND	6357 				2837005				INSPECTION FOUND RIB IN WHEELWELL CRACKED.  CRACK LOCATED IN RIB FLANGE RADIUS AT FORWARD LOWER CORNER WHERE RIB RIVETS/	BOLTS TO SPAR.  DRAG LINK KNUCKLE ALSO ATTACHES AT THIS POINT.					1	L	7	1 	3O				2A13    					 
1996081500740	19960815	00740	CE  	1996	8	15	96ZZZX4005       	1	19960724	G	7331	543015	BRACKET         			CESSNA	182   	TR182       	2072735	CE  										TRANSDUCER MOUNT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6323T	147  				R18201480				FUEL FLOW TRANSDUCER MOUNT FAILED AFTER 147 HOURS OF OPERATION.  SUBMITTER STATED LOCATION OF MOUNT SHOULD BE REVISED TO	 STRENGTHEN MOUNTING TO PREVENT BREAKAGE OF THE BRACKET.					1	H	7	1 	3O				3A13    					 
1996081500741	19960815	00741		1996	8	15	96ZZZX4006       	4	19960701	G	3416	3431	CASTING         	UNITEDINST  	5934P1      															ATLIMTER	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15										THIS INSTRUMENT WAS A NEW FACTORY SEALED ALTIMETER.  TWO SHAFT END-SHAKES WERE UNDER THE MINIMUM .0020 INCH CALLED OUT I	N THE OVERHAUL MANUAL.  THEY MEASURED .0006 INCH AND .0010 INCH.  THE MANUFACTURER HAS INDICATED AN END-SHAKE OF .0004 I	NCH OR LESS CAN CAUSE A POINTER HANG-UP DURING A NORMAL SPECIFIED COLD TEST.  END-SHAKE CHANGES OF .0002 INCH TO .0003 I	NCH HAVE BEEN MEASURED DURING DIFFERENT PRESSURE SETTINGS ON THE ALTIMETER.																 
1996081500742	19960815	00742	EA  	1996	8	15	96ZZZX4007       	2	19960719	G	8520	75154	STUD            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 4 BEARING	CORRODED        	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	145ND	3197 	796  			2841226	RL1708539A			DURING ENGINE TEAR DOWN FOLLOWING ACCIDENT, CRANKCASE HALF NUT ON NR 4 BEARING STUDS SEIZED RESULTING IN STUD BACKING OU	T OF CRANKCASE.  UPON REMOVAL, FOUND BOTH NR 4 BEARING CRANKCASE STUDS HEAVILY CORRODED/RUSTED.  ALSO, HAD GLASS BEADS I	N STUD RECEPTACLES.  ENGINE WAS FACTORY OVERHAULED 11-18-94, INSTALLED 1-95.				1	L	7	1 	3O	3	O		2A13    	E274				 
1996081500743	19960815	00743	CE  	1996	8	15	96ZZZX4008       	1	19960729	G	1100		MARKING         			BEECH 	36    	A36         	1151604	CE  										STAB ELEV TRIM	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03	4572S					E744				AIRCRAFT RETURNED HOME AIRPORT AFTER REPAINTING.  WHILE PERFORMING WALK-AROUND, NOTICED REQUIRED MARKINGS (STAB TRIM ACT	UATOR) NOT IN PLACE PER AD 91-17-01.  PAINT SHOP HAD COVERED THESE MARKINGS AND NOT REINSTALLED THEM.					1	L	7	1 	3O				3A15    					 
1996081500744	19960815	00744		1996	8	15	96ZZZX4009       	2	19960530	G	7414	M3975	COIL            	SLICK       	4381        															MAGNETO	FAILED          	B			RL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					92050067					MAGNETO SENT TO ACCESSORY SHOP TO T/S BECAUSE OF POOR RUNNING.  FOUND SECONDARY WINDING OPEN IN COIL.  SUBMITTER STATED 	ONCE AGAIN, SLICK COILS SEEM TO BE WEAKEST PART OF MAGNETO.																		 
1996081500745	19960815	00745	GL  	1996	8	15	96ZZZX4010       	3	19960729	G	6111		PROPELLER       			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE	BEARINGS DRY    	B			B2PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	350SP	6669 	972  			402B0580		776724		PROPELLER WAS EXPERIENCING SERVICE DIFFICULTIES.  UPON REMOVAL, DISASSEMBLY AND INSPECTION, NOTED ALL OIL BATH PARTS HAD	 AN EXCESSIVE CLAY-LIKE SLUDGE BUILD-UP.  ALL BEARING RACES WERE VOID OF GREASE AND SEVERELY RUSTED.  THESE FINDINGS WOU	LD DIRECTLY IMPEDE THE PROPELLERS ABILITY TO CHANGE PITCH.  ROUTINE MAINTENANCE IS RECOMMENDED TO AVOID THIS PROBLEM IN 	THE FUTURE.			1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996081500746	19960815	00746	CE  	1996	8	15	96ZZZX4011       	1	19960725	G	3210		BOLT            			PIPER 	PA24  	PA24180     	7102402	CE  										MLG BRACE STUD	CRACKED         	B			DP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										SURPLUS PARTS INSPECTED IAW AD 95-20-07, 1 OF 3 REJECTED DUE TO CRACK NEAR SHANK TO HEAD.  APPROXIMATELY .25 INCH CIRCUM	FERENCE.					1	L	7	1 	3O			NT	1A15    					 
1996081500747	19960815	00747	CE  	1996	8	15	96ZZZX4012       	1	19960725	G	3210		BOLT            			PIPER 	PA24  	PA24180     	7102402	CE  										MLG BRACE STUD	CRACKED         	B	S		DP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	7214P	3500 				242384				ONE BOLT REJECTED.  INSPECTED IAW AD 95-20-07.  MAGNETIC PARTICLE INSPECTION REVEALED LINEAR CRACK-LIKE INDICATION (CIRC	UMFERENCIAL) NEAR SHANK TO HEAD RADIUS.					1	L	7	1 	3O			NT	1A15    					 
1996081500748	19960815	00748		1996	8	15	96ZZZX4013       	1	19960801	G	7810	62749	GASKET          								CONT  	A65   	A658        	17003	SO  					NR 2/3 CYL EXH	MISMANUFACTURED 	D	P			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										NEW EXHAUST GASKET IS MISMANUFACTURED .032 INCH LARGER THAN ORIGINAL.  IT WILL FIT OK ON CYLINDERS 1 AND 4, BUT DUE TO C	LEARANCE REQUIRED FOR FIT, IT IS TOO LARGE FOR CYLINDERS 2 AND 3.										3	O			E205				 
1996081500749	19960815	00749	CE  	1996	8	15	96ZZZX4014       	1	19960808	G	3230	16001260	BREAKER         			BEECH 	B300  	B300        	1159232	CE  										MLG	TRIPPED         	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NM	01	4S	11   				FL107				AIRCRAFT ARRIVED AT DESTINATION AND REQUIRED LANDING GEAR TO BE PUMPED DOWN.  INVESTIGATION REVEALED 60-AMP CIRCUIT BREA	KER HAD TRIPPED.  THIS IS POTENTIALLY AN ACCIDENT WAITING TO HAPPEN WHEN THE CREW HAS NO INDICATION THAT THIS 60-AMP BRE	AKER LOCATED OUT IN THE WING HAS TRIPPED.				2	L	7	2 	4T			RT	A24CE   					 
1996081500750	19960815	00750	NE  	1996	8	15	96ZZZX4015       	2	19960730	G	7261	31B360801	PUMP            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       		NE  					LT ENG OIL	HOUSING CRACKED 	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	65BL	371  			17A861	054	305218			EXCESSIVE OIL LEAK ON LEFT ENGINE.  FOUND OIL PUMP HOUSING CRACKED AT UPPER LEFT BOLT HOLE AREA.  SUBMITTER STATED THIS 	IS TURNING INTO A FLEET-WIDE CONCERN AS THIS CAN CAUSE AN ENGINE SHUTDOWN IN FLIGHT.  OTHER OPERATORS HAVE EXPERIENCED T	HIS SAME CRACK.  AD RECOMMENDED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
1996081500751	19960815	00751	NE  	1996	8	15	96ZZZX4016       	2	19960606	G	7230	798209	BLADE           								PWA   	JT8   	JT8D17      	52049	NE  					HPC STAGE 9	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99							709688			AFTER DISASSEMBLY OF THE 9TH STAGE COMPRESSOR DISK, FOUND 3 BLADES WITH CRACKS IN THE ROOTS.  THESE CRACKS ARE ON THE CO	NCAVE SIDE OF THE BLADE, BEGINS AT THE TRAILING EDE OF THE ROOTS, AND RUNS ALONG THE PRESSURE SIDE.  ONE OF THESE BLADES	 IS ALMOST TOO LOOSE, NEARLY A THIRD OF THE ROOT.									4	F			E2EA				 
1996081500752	19960815	00752	NE  	1996	8	15	96ZZZX4017       	2	19960515	G	7250	596968	SPACER          								PWA   	JT8   	JT8D15      	52051	NE  					TURB RING SEAL	DISPLACED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99							708355			DURING DISASSEMBLY OF NGV3, FOUND THE RING SPACER AIR SEAL, PN 596968, HAD DEPARTED FROM HOUSING.  THIS RING WAS FOUND B	ETWEEN DISK AND NGV3.  DAMAGE (IMPACTS, CRACS, ETC.) ARE VISIBLE ON STAGE 2 BLADES AND STAGE 3 NGVS.										4	F			E2EA				 
1996082200061	19960822	00061	NM  	1996	8	22	96ZZZX4018       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										SKINS	DELAMINATED     	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					RR2502					ENTIRE HONEYCOMB CORE IS CORRODED.  BEARINGS, BUSHINGS, SEALS, AND ATTACHING HARDWARE SEVERELY WORN.  DELAMINATION ON UP	PER AND LOWER SKINS.					2	L	7	3 	4F				A3WE    					 
1996082200062	19960822	00062	NM  	1996	8	22	96ZZZX4019       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										SKINS	DELAMINATED     	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2402					LEFT AND RIGHT SPOILER STOPS WORN BEYOND ALLOWABLE LIMITS.  UPPER AND LOWER SKINS SEVERELY DELAMINATED.  ENTIRE HONEYCOM	B CORE IS CORRODED.  INTERNAL DOUBLER HAS A PREVIOUS REPAIR THAT IS NOT PER TECHNICAL DATA.  BEARINGS, BUSHINGS, SEALS, 	AND ATTACH HARDWARE ARE WORN BEYOND LIMITS.				2	L	7	3 	4F				A3WE    					 
1996082200063	19960822	00063	NM  	1996	8	22	96ZZZX4020       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										SKINS	CORRODED        	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					RR2503					SEVERAL DELAMINATIONS ON UPPER AND LOWER SKINS.  BOTH SURFACES HAVE NUMEROUS DENTS.						2	L	7	3 	4F				A3WE    					 
1996082200064	19960822	00064	NM  	1996	8	22	96ZZZX4021       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										SKIN	DELAMINATED     	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2348					LOWER SKIN DELAMINATED ALONG ENTIRE LENGTH OF LEADING EDGE.  BUSHINGS, BEARINGS, SEALS, ATTACHING HARDWARE ARE EXCESSIVE	LY WORN.					2	L	7	3 	4F				A3WE    					 
1996082200065	19960822	00065	NM  	1996	8	22	96ZZZX4022       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										DELAMINATED	WORN            	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					R2319					HINGE FITTINGS, BUSHINGS AND BEARINGS ARE EXCESSIVELY WORN.  UPPER AND LOWER SKINS DELAMINATED.  HONEYCOMB CORE CORRODED	 AND FILLED WITH WATER.  CENTER HINGE FITTINGS IS LOOSE.					2	L	7	3 	4F				A3WE    					 
1996082200066	19960822	00066	NM  	1996	8	22	96ZZZX4023       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										HONEYCOMB CORE	CORRODED        	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					R2319					INTERNAL DOUBLERS AT HINGES AND DOWNSTOPS ARE MISSING.  HONEYCOMB CORE IS CORRODED.  UPPER AND LOWER SKINS ARE DELAMINAT	ED.  CENTER HINGE FITTING BEARING WELLS ARE CORRODED.  TRAILING EDGE OF UPPER SKIN DELAMINATED ALONG 85 PERCENT OF ITS S	PAN.				2	L	7	3 	4F				A3WE    					 
1996082200067	19960822	00067	NM  	1996	8	22	96ZZZX4024       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										SKINS	DELAMINATED     	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					TC523					SKIN DELAMINATED AROUND CENTER HINGE FITTING.  SURFACE CORROSION NEAR LAP JOINTS AND RIBS.  OUTBOARD HINGE FITTINGS WORN	 BEYOND ALLOWABLE LIMITS.					2	L	7	3 	4F				A3WE    					 
1996082200068	19960822	00068	NM  	1996	8	22	96ZZZX4025       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										HONEYCOMB CORE	CORRODED        	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					TC525					HONEYCOMB CORE CORRODED WITH WATER DAMAGE NEAR CENTER HINGE FITTING.  BEARINGS EXCESSIVELY WORN.  UPPER AND LOWER SKINS 	DELAMINATED.					2	L	7	3 	4F				A3WE    					 
1996082200069	19960822	00069	NM  	1996	8	22	96ZZZX4026       	1	19960710	G	5755	651734748	SPOILER         			BOEING	727   	727         	1384001	NM  										SKIN	CORRODED        	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					RR1455					DELAMINATION AT CENTER HINGE FITTING.  HONEYCOMB CORE UPPER SKIN, UPPER INTERNAL DOUBLER AND LOWER SKIN ARE CORRODED IN 	OVER 60 PERCENT OF THE TOTAL AREA.					2	L	7	3 	4F				A3WE    					 
1996082200070	19960822	00070	NM  	1996	8	22	96ZZZX4027       	1	19960710	G	5753	652163429	INTERNAL DOUBLER		652163480   	BOEING	727   	727         	1384001	NM  										ATTACH FITTING	CRACKED         	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					BN80					INTERNAL DOUBLER THAT SUPPORTS ATTACH FITTING AND TIES LEADING EDGE SPLICE TOGETHER IS CRACKED AT BOTH LOWER RADII.  BOT	H CRACKS FOLLOW MATERIAL GRAIN REARWARDS APPROXIMATELY .75 INCH EACH.  SUSPECT CAUSE:  MATERIAL FATIGUE DUE TO EXCESSIVE	 LOADS AT LEADING EDGE SPLICE.  DOUBLER MATERIAL GAUGE IS NOT THICK ENOUGH.  NOTE:  DOUBLER HAD PROPER CLEARANCE FROM FI	TTING AND CORNERS WERE PROPERLY RADIUSED.			2	L	7	3 	4F				A3WE    					 
1996082200071	19960822	00071	NM  	1996	8	22	96ZZZX4028       	1	19960710	G	5753	652163429	INTERNAL DOUBLER		652163491   	BOEING	727   	727         	1384001	NM  										CARRIAGE FITTING	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					BN407					INTERNAL DOUBLER THAT SUPPORTS ATTACH FITTING AND TIES LEADING EDGE SPLICE TOGETHER IS CRACKED AT BOTH LOWER RADII.  BOT	H CRACKS FOLLOW MATERIAL GRAIN REARWARDS APPROXIMATELY .75 INCH EACH.  SUSPECT CAUSE:  MATERIAL FATIGUE DUE TO EXCESSIVE	 LOADS AT LEADING EDGE SPLICE.  DOUBLER MATERIAL GAUGE IS NOT THICK ENOUGH.  NOTE:  DOUBLER HAD PROPER CLEARANCE FROM FI	TTING AND CORNERS WERE PROPERLY RADIUSED.			2	L	7	3 	4F				A3WE    					 
1996082200072	19960822	00072	NM  	1996	8	22	96ZZZX4029       	1	19960710	G	5753	652163429	DOUBLER         		6521634149  	BOEING	727   	727         	1384001	NM  										CARRIAGE FITTING	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					BN33					THERE ARE 3 CRACKS .25 INCH, .50 INCH AND 1.0 INCH LONG IN LOWER END OF LEADING EDGE SKIN SPLICE DOUBLER.  TWO CRACKS EX	TEND THROUGH NEAREST FASTENER HOLES.  DOUBLER IS LOCATED AT NR 2 CARRIAGE FITTING.  THE CRACKS RUN PARALLEL TO GRAIN OF 	MATERIAL.  LEADING EDGE SKIN IS SPLICED AT THIS POINT CAUSING A STRESS POINT DURING FLEXING OF FLAP.  SUBMITTER SUGGESTS	 MAKING DOUBLER OUT OF THICKER GAUGE MATERIAL.			2	L	7	3 	4F				A3WE    					 
1996082200073	19960822	00073	NM  	1996	8	22	96ZZZX4030       	1	19960710	G	5753	652163482	SKIN            		652163480   	BOEING	727   	727         	1384001	NM  										FLAP T/E ASSY	DELAMINATED     	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					BN3					DURING TEAR-DOWN INSPECTION, DELAMINATION WAS NOTED ON BOTH UPPER AND LOWER SURFACES.  UPON REMOVAL OF DELAMINATED SKINS	, IT WAS REVEALED THAT BONDING PRIMER HAD NOT BEEN USED AT TIME OF INSTALLATION OF UPPER AND LOWER SKINS.  SEVERE CORROS	ION WAS PRESENT THROUGHOUT T/E BONDED ASSY.  THE T/E BONDED ASSY ITSELF WAS A CONGLOMERATION OF ALUMINUM HONEYCOMB, NOME	X HONEYCOMB, POTTING COMPOUND, FIBERGLASS RESIN, AND FOAM.  SUSPECT CAUSE, THE PREVIOUS REPAIRS DOWN TO T/E BONDED ASSY 	WERE DONE INCORRECTLY.		2	L	7	3 	4F				A3WE    					 
1996082200074	19960822	00074	CE  	1996	8	22	96ZZZX4031       	1	19960716	G	5720	316321	STRUT FITTING   			BBAVIA	8     	8KCAB       	2110612	CE  										LIFT STRUT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	419JR	34   	34   			75995				INSPECTED THE LIFT STRUT FITTINGS (PN 3-1632-1 AND PN 316322) IAW AD 96-03-11 PER AMERICAN CHAMPION SERVICE LETTER NR 40	8.  FOUND TWO OF THE FOUR FITTINGS CRACKED AT THE RADIUS AS SHOWN IN THE ILLUSTRATION.  INSTALLED THE NEW STYLE FITTINGS	 (PN 3-1691) PER AMERICAN CHAMPION.  THESE FITTINGS ONLY HAD A TOTAL TIME OF 33.6 HOURS SINCE NEW WITH NO HARD AEROBATIC	S.  SUBMITTER STATED THE POOR DESIGN OF THE OLD FITTINGS WAS THE MAJOR CONTRIBUTING FACTOR TO THE CRACKING OF THE FITTIN	GS.  THE FITTINGS (PN 3-1632-1 AND PN 3-1632-2) SHOULD BE REMOVED FROM SERVICE IMMEDIATELY.		1	H	7	1 	3O				A21CE   					 
1996082200075	19960822	00075	CE  	1996	8	22	96ZZZX4032       	1	19960716	G	5720	316322	STRUT FITTING   			BBAVIA	8     	8KCAB       	2110612	CE  										LIFT STRUT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	419JR	34   	34   			75995				INSPECTED THE LIFT STRUT FITTINGS (PN 3-1632-1 AND PN 316322) IAW AD 96-03-11 PER AMERICAN CHAMPION SERVICE LETTER NR 40	8.  FOUND TWO OF THE FOUR FITTINGS CRACKED AT THE RADIUS AS SHOWN IN THE ILLUSTRATION.  INSTALLED THE NEW STYLE FITTINGS	 (PN 3-1691) PER AMERICAN CHAMPION.  THESE FITTINGS ONLY HAD A TOTAL TIME OF 33.6 HOURS SINCE NEW WITH NO HARD AEROBATIC	S.  SUBMITTER STATED THE POOR DESIGN OF THE OLD FITTINGS WAS THE MAJOR CONTRIBUTING FACTOR TO THE CRACKING OF THE FITTIN	GS.  THE FITTINGS (PN 3-1632-1 AND PN 3-1632-2) SHOULD BE REMOVED FROM SERVICE IMMEDIATELY.		1	H	7	1 	3O				A21CE   					 
1996082200076	19960822	00076	CE  	1996	8	22	96ZZZX4033       	1	19960717	G	3241	9542039	TRANSDUCER      			RKWELL	NA265 	NA26540     	6402608	CE  										ANTISKID	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	304NT				JUL6560E	2822				UNIT WAS INSTALLED IN THE AIRCRAFT, TESTED, AND FOUND TO BE INOPERATIVE.  UNIT WAS TESTED AGAIN (IN OPPOSITE POSITION ON	 SAME AIRCRAFT) AND WAS STILL INOPERABLE.  UNIT WAS TESTED AND RELEASED BY REPAIR STATION ON 7-9-96.  AIRCRAFT TOTAL TIM	E:  12,813.4 HRS.				2	L	7	2 	4J				A2WE    					 
1996082200077	19960822	00077	NE  	1996	8	22	96ZZZX4034       	2	19960621	G	7230		COMPRESSOR      			RKWELL	NA265 	NA26540     	6402608	CE  	PWA   	JT12  	JT12A8      	52042	NE  					ENGINE	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	312NT	9217 	950  			28232	P637745NB			COMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND.  TH	IS IS A MULTI 9-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT.  NO FOD NOTE	D AND NO DAMAGE OR DEFECTS NOTED IN TURBINE HOT SECTION.  ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL.				2	L	7	2 	4J	4	J		A2WE    	1E9				 
1996082200078	19960822	00078	NE  	1996	8	22	96ZZZX4035       	2	19960614	G	7230		COMPRESSOR      			RKWELL	NA265 	NA26540     	6402608	CE  	PWA   	JT12  	JT12A8      	52042	NE  					ENGINE	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	302NT	6995 	1300 			28281	P672928NB			COMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT.  INTERNAL BINDING COULD BE FELT WHEN ROATING BY HAND.  TH	IS IS A MULTI 9-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT.  NO FOD NOTE	D AND NO DAMAGE OR DEFECTS NOTED IN TURBINE HOT SECTION.  ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL.				2	L	7	2 	4J	4	J		A2WE    	1E9				 
1996082200080	19960822	00080	NE  	1996	8	22	96ZZZX4037       	2	19960725	G	7250	805172	VANE            								PWA   	JT8   	JT8D217A    	52053	NE  					N1 TURBINE	FAILED          	D				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			SW	05							709893			ENGINE WAS REMOVED FROM SERVICE DUE TO A LOUD BANG AND ENGINE EXPERIENCED AN IN-FLIGHT SHUT DOWN.  DISASSEMBLY OF THE EN	GINE REVEALED A SECOND STAGE VANE CLUSTER WAS MISSING AND THE REMAINDER OF THE N1 TURBINE HAD MASSIVE DAMAGE.  THE CAUSE	 FOR THE FAILURE IS STILL UNDER INVESTIGATION.									4	F			E9NE				 
1996082200081	19960822	00081	EU  	1996	8	22	96ZZZX4038       	1	19960718	G	2750	SD345032XA	BRACKET         			STBROS	SD3   	SD360       	8100606	EU  										LT WS 71.25 AFT	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	913SB	17929				SH3403				LEFT CENTER WING REAR SPAR AT STA 71.25, THE INNER FLAP OPERATING ARM LEVER BRACKET WAS FOUND CRACKED.  CRACK CAUSED BY 	CONTACT WITH FLAP OPERATING ARM LEVER DUE TO EXCESSIVE WEAR ON THE BRACKET WHERE THE LEVER ATTACHES.  BEARINGS INSIDE OF	 THE LEVER WERE FOUND FROZEN WHICH CAUSED THE EXCESSIVE WEAR TO THE BRACKET WHICH CAUSED CONTACT BETWEEN THE LEVER AND T	HE BRACKET WHICH CAUSED THE CRACK.  PART TC:  24,254.			2	H	7	2 	4T				A41EU   					 
1996082200082	19960822	00082	CE  	1996	8	22	96ZZZX4039       	1	19960724	G	1100		PLACARD         			CESSNA	210   	210         	2073402	CE  										COCKPIT	IMPROPER        	D		A		A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SW	11	6909					57514				AIRCRAFT MADE AN EMERGENCY RETURN TO AIRPORT LANDING (GEAR UP) DUE TO ENGINE POWER LOSS ON TAKEOFF/CLIMB.  INVESTIGATION	 FOUND INDUCTION AIR FLAPPER IN 'HOT' POSITION.  THIS IS AN INJECTED ENGINE.  AIRCRAFT PLACARD FOR TAKEOFF LANDING CHECK	 LIST IMPROPERLY WORDED VERSUS TC DATA SHEET.  SUBMITTER STATED PROPER CHECK LIST NOT AVAILABLE FROM CESSNA.				1	H	7	1 	3O			RT	3A21    					 
1996082200220	19960822	00220	NE  	1996	8	22	96ZZZX4042       	2	19960701	G	7230		COVER           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					CENTRIFUGAL COMP	FAILED          	B		A	R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	5771C				392	1369	639			UPON DAILY INSPECTION, A METAL PIECE WAS FOUND ON THE ENGINE DECK THAT APPEARED TO BE PART OF THE ENGINE.  VISUAL INSPEC	TION DETERMINED THE OBJECT DID NOT COME FROM THE EXTERNAL PORTION OF THE ENGINE.  THE OBJECT WAS SENT TO THE MFG WHO DET	ERMINED IT WAS A CENTRIFUGAL COMPRESSOR COVER BRIDGE WHICH HAD EXITED THROUGH THE BLEED VALVE.  THE ENGINE WAS INSPECTED	 PER THE MANUFACTURER'S REQUEST AND INSTRUCTIONS AND RETURNED TO SERVICE.  SUGGEST PERIODIC INSPECTION OF CENTRIFUGAL CO	MPRESSOR COVER DURING BORESCOPE INSPECTION.		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1996082900153	19960829	00153	CE  	1996	8	29	96ZZZX4050       	1	19960626	G	2520		SEAT            			CESSNA	421   	421B        	2076014	CE  										CABIN	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	620TQ	2533 				421B0919				WHILE PERFORMING ANNUAL INSPECTION, FOUND A FORWARD FACING SEAT INSTALLED IN AN AFT FACING SEAT POSITION.  THERE IS A ST	RUCTURAL DIFFERENCE BETWEEN AN AFT FACING AND A FORWARD FACING SEAT.  AD 78-13-05 AND MEB 78-17 REFERENCE THIS, HOWEVER,	 AD 78-13-05, IS A ONE-TIME ONLY AD.  SUBMITTER STATED THIS SHOULD BE MADE A RECURRING AD TO APPLY WHENEVER SEATS ARE RE	MOVED.  THIS AD APPLIES TO VARIOUS TWIN ENGINE CESSNA.			1	L	7	2 	3O				A7CE    					 
1996082900154	19960829	00154		1996	8	29	96ZZZX4051       	4	19960329	G	3416	3431	CASTING         	UNITEDINST  	5934P1      	PIPER 	PA28  	PA28140     	7102802	SO  										ALTIMETER	OUT OF SPEC     	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	3489K				1E723	2823582				WHEN RECEIVED, THIS WAS A FACTORY SEALED INSTRUMENT.  WHEN BENCH TESTED, IT HAD STICK AND JUMP FRICTION OF 100 FEET TO 1	50 FEET.  WHEN DISASSEMBLED, 3 DEFECTS WERE FOUND.  THERE WAS A CIRCULAR SCRATCH ON THE BACK OF THE DISC POINTER.  THE M	OLY/KOTE IN THE TOP PLATE HAD COAGULATED.  THE TOP PLATE BREAK-FREE TORQUE WAS 5 TIMES THE PROPER SAFE VALUE.  ONE MECHA	NISM SHAFT END SHAKE MEASURED .0006 INCH, THE OVERHAUL SPEC CALLS FOR .0020 INCH MINIMUM.  ANY ONE OF THESE DEFECTS OR A	 COMBINATION OF THESE DEFECTS COULD CAUSE A POINTER HANG-UP AT A LATER DATE.		1	L	7	1 	3O				2A13    					 
1996082900155	19960829	00155		1996	8	29	96ZZZX4052       	4	19960605	G	3416	3431	CASTING         	UNITEDINST  	593RPA1     	PIPER 	PA28  	PA28140     	7102802	SO  										ALTIMETER	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4569X				7B871	287625057				THE END SHAKES ON ALL 3 OF THE CRITICAL SHAFTS IN THE MECHANISM WERE UNDER THE .0020 INCH CALLED OUT IN THE OVERHAUL MAN	UAL.  THESE MEASURED (.0003 INCH), (.0004 INCH), AND (.0015 INCH).  ACCORDING TO THE MANUFACTURER, ANY END SHAKE BELOW .	0004 INCH WILL CAUSE THE POINTERS TO HANG UP DURING THE LOW SPECIFIED OPERATING TEMPERATURE.				1	L	7	1 	3O				2A13    					 
1996082900156	19960829	00156	GL  	1996	8	29	96ZZZX4053       	1	19960703	G	2430	W23XA1AG2	BREAKER         	AMF         		DIAMON	DA20A1	DA20A1      	05626UX	GL  										GEN CONTROL	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	518SS	366  				10073				DURING THE DAY, THESE PLANES ARE HAVING PROBLEMS WITH CIRCUIT BREAKERS TRIPPING.  THIS USUALLY OCCURS DURING THE HOTTEST	 PART OF THE DAY.  WHEN THE PART COOLS DOWN THEY WILL RESET AND SHOW NO INDICATION OF ANY PROBLEMS WITHIN THE SYSTEM.  S	UBMITTER STATES IT IS SUSPECTED THAT AS THE DAY GETS HOTTER AND THE DASH WARMS UP, THEN THE CIRCUIT BREAKERS LOSE RESIST	ANCE AND FAIL.			1	L	7	1 	3O			NT	TA4CH   					 
1996082900157	19960829	00157	SO  	1996	8	29	96ZZZX4054       	1	19960729	G	2410	6519905	BRACKET         			PIPER 	PA28  	PA28236     	7102815	SO  										ALTERNATOR	CRACKED         	D				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			EA	21	611AJ					287911172				ALTERNATOR FAILED ON TAXI AFTER FUELING.  MAINTENANCE FOUND ALTERNATOR BELT LOOSE.  FURTHER INSPECTION REVEALED ENGINE T	O ALTERNATOR MOUNT BRACKET BROKEN.  EVIDENCE SHOWED BRACKET HAD BEEN CRACKED FOR SOME TIME.  ALTERNATOR CHANGED 20 HOURS	 PREVIOUSLY.  SUBMITTER STATED CAUSE OF BRACKET FAILURE MAY BE ALTERNATOR WAS SECURED IMPROPERLY (NOT PER PA28 IPC).  AL	TERNATOR HAD TO BE REPLACED DUE TO DAMAGED HOLES IN CASE.  CORRECT MOUNT KIT NEEDS TO BE INSTALLED.  CLOSE INSPECTION OF	 BRACKET RECOMMENDED AT ALTERNATOR CHANGE.		1	L	7	1 	3O				2A13    					 
1996082900158	19960829	00158	CE  	1996	8	29	96ZZZX4055       	1	19960723	G	3213		AXLE NUT        			CESSNA	172   	172M        	2072418	CE  										LANDING GEAR	MISINSTALLED    	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	16	64117	6429 				17265033				DURING GROUND TAXI OPERATIONS, THE RT AXLE NUT SEPARATED FROM THE AXLE.  UPON RETURN FROM FLIGHT, THE NUT WAS FOUND MISS	ING BY THE PILOT.  THE AXLE NUT WITH COTTER PIN INSTALLED WAS RECOVERED BY UNKNOWN PERSONS.  THE WHEEL WAS DISASSEMBLED,	 INSPECTED, AND RE-ASSEMBLED WITH NO DEFECTS NOTED.  THE AXLE AND NUT WERE ALSO INSPECTED AND RETURNED TO SERVICE.  UPON	 INSTALLATION OF THE WHEEL ASSY, NOTED THE DIAMETER OF HOLE IN THE AXLE NUT IS SUCH THAT WHEN FULLY INSTALLED, THE END O	F THE AXLE IS EXPOSED IN THE COTTER PIN HOLE PERMITTING INCORRECT INSTALLATION OF THE COTTER PIN THROUGH THE NUT, BUT MI	SSING THE AXLE.	1	H	7	1 	3O			NT	3A12    					 
1996082900159	19960829	00159	GL  	1996	8	29	96ZZZX4056       	3	19960809	G	6111		BLADE           			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	B			UP7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	6497M	7453 				15284757		R776850		PROPELLER WAS REMOVED TO FIX A NICK IN THE LEADING EDGE OF ONE BLADE.  ALL PAINT WAS REMOVED AND UPON INSPECTION, THE EV	IDENCE OF A CRACK APPEARS TO BE SEEN IN ONE BLADE APPROXIMATELY 5 INCHES FROM THE CENTER OF THE HUB HOLE.  SUBMITTER REC	OMMENDATIONS:  INCREASE INSPECTION BOX IN SB 219A AND PUT DIMENSIONS ON BOX.  INSPECT 7 INCHES ON EACH SIDE OF CENTER HO	LE.			1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1996082900160	19960829	00160	CE  	1996	8	29	96ZZZX4057       	1	19960720	G	2810	MDI	DRAIN VALVE     			CESSNA	150   	150H        	2071818	CE  										RT TANK	CORRODED        	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	6520S				S21061	15067320				THE RIGHT SIDE FUEL TANK SUMP DRAIN VALVE DIFFICULT TO CLOSE AFTER SUMPING FUEL TANK.  FINALLY BECAME IMPOSSIBLE TO OPEN	.  REPLACED DRAIN VALVE.  FOUND DRAIN VALVE CORRODED BETWEEN PLUNGER AND VALVE BODY.  DRAIN VALVE NEEDS TO BE MORE CORRO	SION RESISTANT.  THE RIGHT SIDE FUEL TANK ALWAYS IS THE SIDE THAT HAS WATER IN IT.				1	H	7	1 	3O				3A19    					 
1996082900161	19960829	00161	CE  	1996	8	29	96ZZZX4058       	1	19960607	G	5753	24250012	FLAP TRACK      			CESSNA	150   	152         	2071835	CE  										RT INBD	CORRODED        	B			LCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	69219	773  				15285350				DURING 100-HOUR INSPECTION, THE RIGHT INBOARD FLAP TRACK WAS FOUND WITH INTERGRANULAR CORROSION ALONG THE BOTTOM.  PART 	WAS INSTALLED 23 MONTHS EARLIER.					1	H	7	1 	3O			NT	3A19    					 
1996082900162	19960829	00162	EA  	1996	8	29	96ZZZX4059       	2	19960716	G	8520	72877	CAM FOLLOWER    								LYC   	O540  	O540B2C5    	41532	EA  					CYLS 1,3,5	BROKEN          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07							1481540			CAM FOLLOWERS BROKEN ON NR 1 CYLINDER EXHAUST NR 3, EXHAUST AND INTAKE, NR 5 CYLINDER-INTAKE.  REST OF CAM FOLLOWERS PIT	TED OR SPALLED.  NR 2 CYLINDER DROPPED THE EXHAUST VALVE.  OIL SUMP REMOVED FOR INSPECTION AND CLEANING.  FOUND PIECES O	F CAM FOLLOWERS IN SUMP.  ENGINE DISASSEMBLED FOR OVERHAUL.  ALL SIX ROD CAPS DAMAGED.  ALL PIECES RETAINED AND ARE AVAI	LABLE FOR SCRUTINY.								3	O			E295				 
1996082900163	19960829	00163		1996	8	29	96ZZZX4060       	1	19960725	G	3150	6838	LAMP            																	WARNING PANEL	FAILED          	B		A	XEFR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03										INSTALLED LAMPS AS REPLACEMENTS IN ANTI-SKID, PITOT HEAT, AND LT AIR IGNITION ANNUNCIATORS.  WHEN POWER WAS TURNED ON TO	 TEST LAMPS, LAMPS BECAME VERY BRIGHT AND THEN FAILED.  SUSPECT LAMPS WERE MISLABELED AT VENDOR.  CORRECT LAMPS AND F/T 	OK.																	 
1996082900164	19960829	00164	GL  	1996	8	29	96ZZZX4061       	3	19960723	G	6111	C84686R	BLADE           													HARTZL	HCE2Y	HCE2YR2     	GL  	PITCH CHANGE	KNOB BROKEN     	B	P		PS4R	C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			SO	05					B52644			DJ5494		DURING POWER-UP FOR TAKEOFF, THE PILOT REPORTED HEARING A LOUD POP.  HE PULLED POWER OFF AND TAXIED TO THE LOCAL FBO.  A	FTER SHUT DOWN, ONE BLADE WAS IN FEATHER.  THE PROPELLER WAS REMOVED AND BROUGHT TO OUR SHOP.  UPON TEAR DOWN, THE PITCH	 CHANGE KNOB ON THE BLADE HAD BROKEN OFF.  NO OTHER DAMAGE WAS NOTICED.  CAUSE IS UNKNOWN AND THE BLADE HAS BEEN SENT TO	 THE FACTORY.													5	C	P9EA	 
1996082900165	19960829	00165		1996	8	29	96ZZZX4062       	4	19960730	G	6122	D20591	DRIVE GEAR      	MCAULY      	C290D5GT17  															PROP GOVERNOR	CRACKED         	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					91041					DURING INSPECTION OF PROPELLER GOVERNOR, DRIVE GEAR WAS FOUND CRACKED IN SPLINE.  GOVERNOR RETURNED TO CUSTOMER WITHOUT 	REPAIR.																		 
1996082900166	19960829	00166		1996	8	29	96ZZZX4063       	4	19960709	G	2562	E01	ELT             	ACK         																CASE HALF	MISASSEMBLED    	D	P			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	14										PRIOR TO INSTALLATION, AN ELT WAS NOTED TO BE HOT.  INVESTIGATION FOUND 4 OF BATTERIES WERE SHORTED DUE MIS-ASSEMBLY OF 	THE ELT CASE HALVES.  SUBMITTER STATES MIS-ASSEMBLY IS EASY TO DO WHEN BATTERY INSTALLATION INSTRUCTIONS NOT FOLLOWED.																		 
1996082900167	19960829	00167	SW  	1996	8	29	96ZZZX4064       	1	19960723	G	3340	930021507	CONNECTOR       			MOONEY	M20   	M20J        	5870219	SW  										INST PANEL	MELTED          	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	191ER	5055 				243252				DUE TO LARGE AMP DRAW, 34-PIN CONNECTOR IS MELTING.  AT LANDING/TAXI, LIGHT PIN CONTACTS.  SUBMITTER SUGGESTS REWIRING W	IRES OUTSIDE CONNECTOR OR LARGE PINS FOR CONNECTOR.  THIS IS SECOND AIRCRAFT IN FLEET TO HAVE THIS PROBLEM.  M20J MODEL 	ACFT WITH WING MOUNTED TAXI AND LANDING LIGHTS.				1	L	7	1 	3O				2A3     					 
1996082900168	19960829	00168	SW  	1996	8	29	96ZZZX4065       	1	19960723	G	3340	930021508	CONNECTOR       			MOONEY	M20   	M20J        	5870219	SW  										INST PANEL	MELTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	191ER					243252				DUE TO LARGE AMP DRAW, 34-PIN CONNECTOR IS MELTING.  AT LANDING/TAXI, LIGHT PIN CONTACTS.  SUBMITTER SUGGESTS REWIRING W	IRES OUTSIDE CONNECTOR OR LARGER PINS FOR CONNECTOR.  THIS IS SECOND AIRCRAFT IN FLEET TO HAVE THIS PROBLEM.  M20J MODEL	 ACFT WITH WING MOUNTED TAXI AND LANDING LIGHTS.				1	L	7	1 	3O				2A3     					 
1996082900169	19960829	00169	CE  	1996	8	29	96ZZZX4066       	1	19960730	G	7120	643816	BAR             			BEECH 	36    	A36TC       	1151603	CE  										ENGINE STAB	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	3685W	1912 				EA113				DUE TO LOCATION OF ENGINE STABILIZER BAR, CRACK COULD NOT BE SEEN AT FIRST INSPECTION, ONLY FOUND UPON REMOVAL.  LAST PA	RT INSPECTION AT LAST ENGINE OVERHAUL, 387 HOURS.					1	L	7	1 	3O				3A15    					 
1996082900170	19960829	00170	CE  	1996	8	29	96ZZZX4067       	1	19960730	G	7810	642465	WYE PIPE        			BEECH 	36    	A36TC       	1151603	CE  										MT SUPPORT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	3685W	1912 	387  			EA113				CRACKED IN FRONT OF ASSY NEAR CENTER SUPPORT BOSS.  SUBMITTER STATES VERY HARD TO SEE DUE TO LOCATION AND BLACK COATING 	OF PART.  SUGGEST DIFFERENT COLOR AND REDESIGNED PART MADE OUT OF THICKER MATERIAL.					1	L	7	1 	3O				3A15    					 
1996082900171	19960829	00171	CE  	1996	8	29	96ZZZX4068       	1	19960722	G	5712	51220252	RIB             			CESSNA	414   	414A        	2075907	CE  										RT OTBD WING	CRACKED         	B		A	FTKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	543AC	4098 				414A0103				DURING ANNUAL INSPECTION, A CRACK WAS DISCOVERED IN RT OUTBOARD WING RIB WHERE AILERON HINGE BEARING BLOCK ATTACHES.  CR	ACK IS HARD TO DETECT WITH AILERON INSTALLED.  SUSPECT CAUSE IS THOUGHT TO BE FLYING IN TURBULENT AIR ABOVE MANEUVERING 	SPEED.				1	L	7	2 	3O				A7CE    					 
1996082900172	19960829	00172	CE  	1996	8	29	96ZZZX4069       	1	19960722	G	2730	50350054	FITTING         			CESSNA	414   	414A        	2075907	CE  										RT ELEV TORQUE	CRACKED         	B		A	FTKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5431C	4098 	4098 			414A0103				DURING ANNUAL INSPECTION, A CRACK WAS DISCOVERED IN THE RT ELEVATOR TORQUE TUBE ATTACH FITTING.  CRACK RADIATED FROM TAP	ERED HOLE.  NEW FITTING DELIVERED FROM CESSNA WAS OF DIFFERENT DESIGN AND REQUIRED NEW HOLE DRILLED IN TORQUE TUBE FOR T	APERED PIN INSTALLATION.  PART NUMBER STAMPED ON OLD FITTING WAS FOR A MODEL 421B SERIES AIRPLANE.  CRACK POSSIBLY HAPPE	NED DURING INSTALLATION.			1	L	7	2 	3O				A7CE    					 
1996082900173	19960829	00173	CE  	1996	8	29	96ZZZX4070       	1	19960724	G	3246	C1630060103	WHEEL           			CESSNA	210   	210L        	2073448	CE  										MLG ASSY	FAILED          	D		A		K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	15	5489V	7188 				21060961				WHEEL ASSY BLEW APART ON TAXI, DISC SIDE OF WHEEL.  SUSPECT CAUSE, THREADS WEAK ON 12-BOLT, 3-PIECE, MCCAULEY WHEEL ASSY	.  REPLACED WHEEL ASSY, 3-PIECE, WITH 2-PIECE CLEVELAND AFTER 2,500 HOURS TIS.					1	H	7	1 	3O				3A21    					 
1996082900174	19960829	00174	CE  	1996	8	29	96ZZZX4071       	1	19960701	G	3230	AN512A	BOLT            			CESSNA	402   	402B        	207590P	CE  										NLG LINK ATTACH	BROKEN          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	69PB					402B1248				DURING SCHEDULED INSPECTION, THE NOSE LANDING GEAR LOWER ATTACH BOLT FOR DRAG LINK FOUND BROKEN.  INSPECTED OTHER 10 ACF	T IN FLEET, NO OTHERS BROKEN OR DAMAGED.  SUBMITTER STATED IF UNDETECTED, NLG WILL COLLAPSE.					1	L	7	2 	3O				A7CE    					 
1996082900175	19960829	00175	EA  	1996	8	29	96ZZZX4072       	2	19960517	G	8520		CRANKCASE       			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					LT NR 2 CYL FWD	CRACKED         	B			DPOD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	2141T		1058 			28R7135144	L619151A			LEFT CRANKCASE CRACKED BELOW NR 2 CYLINDER, FORWARD LOWER BASE STUD.  CRACK WAS APPROXIMATELY 2 INCHES LONG.  CASE WAS R	EPAIRED.					1	L	7	1 	3O	3	O		2A13    	1E10				 
1996082900176	19960829	00176	CE  	1996	8	29	96ZZZX4073       	1	19960726	G	3246	C1630060103	WHEEL           			CESSNA	210   	210L        	2073448	CE  										MLG ASSY	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	15	2667S	2806 				21061347				WHEEL ASSY BLEW APART ON LANDING.  (DISC SIDE.)  SUSPECT CAUSE, THREADS WEAK ON 12-BOLT, 3-PIECE MCCAULEY WHEEL ASSY.  R	EPLACED 3-PIECE WHEEL ASSY WITH 2-PIECE CLEVELAND AFTER 2,500 HRS TIS.					1	H	7	1 	3O				3A21    					 
1996082900177	19960829	00177	CE  	1996	8	29	96ZZZX4074       	1	19960722	G	8120		CLAMP           			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					TURBO	FAILED          	G				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	09	28SA					4040072	276238R			CLAMP CAME LOOSE AND DUCT BETWEEN TURBO AND INTAKE THROAT LEAKED CAUSING ENGINE TO RUN ROUGH.  PILOT CHOSE TO SHUT DOWN 	ENGINE IN-FLIGHT AND MADE SAFE SINGLE ENGINE LANDING.  NEW CLAMP WAS INSTALLED AND TORQUED TO SPECS.					1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996082900178	19960829	00178	CE  	1996	8	29	96ZZZX4075       	1	19960710	G	3211	MS2446112	BEARING         			CESSNA	310   	310R        	2074245	CE  										LT MLG AFT	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	3420G					310R1229				BEARING BINDING UP CAUSING TWISTING MOVEMENT ON TRUNNION PIN, PN 0841011-1, SHEARING SLOTTED PIN, PN NAS561P4-28, ALLOWI	NG TRUNNION PIN TO SLIDE OUT OF TRUNNION.  SUBMITTER STATED TO PREVENT, REPLACE WITH NEW TRUNNION PINS WITH GREASE FITTI	NGS.				1	L	7	2 	3O				3A10    					 
1996082900179	19960829	00179	EA  	1996	8	29	96ZZZX4076       	2	19960701	G	7414	10682016	GEAR            			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	36201	529  				32R7887027	L697961A			MAGNETO DISTRIBUTOR GEAR FAILED.						1	L	7	1 	3O	3	O		A3SO    	E14EA				 
1996082900180	19960829	00180	CE  	1996	8	29	96ZZZX4077       	1	19960723	G	3213	5041182	BEARING         			CESSNA	340   	340CESSNA   	2076404	CE  										LT/RT STRUT	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	40BA	5102 				3400046				ONE BEARING IN EACH GEAR WAS CRACKED.  INSPECTION PERFORMED PER CESSNA SB ME B88-7 AND AD 90-02-13.  ONE BEARING CRACKED	 IN ONE PLACE.  ONE BEARING CRACKED IN TWO PLACES.  LAST INSPECTION C/W 1,000 HOURS.					1	L	7	2 	3O				3A25    					 
1996082900181	19960829	00181	SO  	1996	8	29	96ZZZX4078       	1	19960718	G	2750	63900174	BUSHING         		6378100     	PIPER 	PA28  	PA28140     	7102802	SO  										FLAP CONTROL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	56678	1574 				287425016				BUSHING WORN OUT AFTER 1,573 HOURS.  SHOULD KEEP 500-HOUR INSPECTION OF BOLT AND BUSHING PER PIPER INSPECTION FORM EVEN 	IF MODIFIED IAW PIPER SB 965.					1	L	7	1 	3O				2A13    					 
1996082900183	19960829	00183	CE  	1996	8	29	96ZZZX4080       	1	19960724	G	3231	08411066	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  										RT MLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	6181C					310R1320				PILOT HEARD LOUD POP WHEN LOWERING THE LANDING GEAR.  HAD 3 GREEN LIGHTS, VERIFIED GEAR DOWN AND LOCKED.  UPON LANDING, 	RT GEAR DOOR WAS NOT CLOSED.  INSPECTION REVEALED BROKEN GEAR DOOR BELLCRANK.  PART HAD INDICATIONS OF A CRACK THAT WAS 	OLD.  SUBMITTER RECOMMENDS MORE FREQUENT INSPECTION OF THIS AREA.				1	L	7	2 	3O				3A10    					 
1996082900184	19960829	00184	EA  	1996	8	29	96ZZZX4081       	2	19960730	G	7414	10682016	GEARTOOTH       		D6LN3000    	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	6339T				E029002GR	R18201986	RL2385940A			DURING C/W AD 96-12-07, DISCOVERED DISTRIBUTOR GEAR MISSING A TOOTH, DID NOT AFFECT ENGINE OPS.  REPLACED BOTH DISTRIBUT	OR GEARS WITH NEW.  REASON FOR FAILURE UNKNOWN, NO OTHER DEFECTS NOTED.					1	H	7	1 	3O	3	O		3A13    	E295				 
1996082900185	19960829	00185	EU  	1996	8	29	96ZZZX4082       	1	19960725	G	3250	GA58122	ROD END         			AMD   	FALC10	FALCON10    	2730101	EU  										STEER ACTUATOR	FAILED          	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	73B	8338 				79				WHILE TAXIING AFTER LANDING, THE FLIGHT CREW HEARD A SNAPPING NOISE AND LOST NORMAL STEERING CONTROL.  FOUND THE STEERIN	G ACTUATOR ROD END SHEARED ON THE STEERING ACTUATOR.  THE THREAD AREA WHERE THE FAILURE OCCURRED CANNOT BE INSPECTED UNL	ESS THE SEALER IS REMOVED.				2	L	7	2 	4F			 	A33EU   					 
1996082900186	19960829	00186	SO  	1996	8	29	96ZZZX4083       	1	19960723	G	2721	63457003	ARM ASSY        			PIPER 	PA32  	PA32301     	7103207	SO  										RUDDER TRIM	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	8309A	2031 				328106026				ATTACH ARM FOR RUDDER TRIM BROKE AWAY FROM ARM ASSY.						1	L	7	1 	3O				A3SO    					 
1996082900187	19960829	00187	CE  	1996	8	29	96ZZZX4084       	1	19960720	G	3246	C1630060103	WHEEL           			CESSNA	210   	210M        	2073450	CE  										MLG ASSY	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	8427M					21062043				WHEEL ASSY BLEW APART ON TAXI ON BRAKE DISC SIDE.  SUSPECT CAUSE, WEAK THREADS ON 12-BOLT, 3-PIECE MCCAULEY WHEEL ASSY. 	 REPLACED WHEEL ASSY WITH 2-PIECE, CLEVLAND.					1	H	7	1 	3O				3A21    					 
1996082900188	19960829	00188	GL  	1996	8	29	96ZZZX4085       	3	19960731	G	6114	D32517	HUB             			CESSNA	340   	340A        	2076405	CE  						HARTZL	HCC3Y	PHCC3YF2    	GL  	NR 1 SOCKET	CRACKED         	B			UF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	8636K				EB2248	340A0562		EB2248		HUB CRACK FOUND BECAUSE OF LEAKING GREASE.  CRACK IS PERMEATING FROM SLINGER RING ATTACHING HOLE IN REAR OF HUB TRANSGRE	SSING 4 INCHES IN HUB SOCKET ON INSIDE OF HUB.					1	L	7	2 	3O				3A25    		5	C	P25EA	 
1996082900189	19960829	00189	CE  	1996	8	29	96ZZZX4086       	1	19960618	G	3246	C1630060103	WHEEL           			CESSNA	210   	210L        	2073448	CE  										MLG ASSY	THREADS FAILED  	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	15	93887					21060445				WHEEL ASSY BLEW APART ON LANDING, RT BRAKE DISC SIDE OF WHEEL.  SUSPECT CAUSE, THREADS WEAK ON 12-BOLT, 3-PIECE MCCAULEY	 WHEEL ASSY.  REPLACED WHEEL ASSY, 3-PIECE, WITH 2-PIECE, CLEVELAND.					1	H	7	1 	3O				3A21    					 
1996082900190	19960829	00190	SO  	1996	8	29	96ZZZX4087       	1	19960430	G	3211	9529900	STUD            			PIPER 	PA34  	PA34200T    	7103406	SO  										MLG SIDE BRACE	CRACKED         	B		A	CTKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9565K					347670209				MAIN LANDING GEAR SIDE BRACE, 2 EACH, STUDS LEFT AND RIGHT FOUND CRACKED AT RADIUS OF HEAD.  REF:  AD 95-20-07 N/R.						1	L	7	2 	3O				A7SO    					 
1996082900191	19960829	00191	CE  	1996	8	29	96ZZZX4088       	1	19960729	G	3230		GEAR HANDLE     			BEECH 	58    	58P         	1152744	CE  										EMERG EXTEND	NOT FUNCTIONAL  	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03	36EB					TJ465				DURING ANNUAL INSPECTION, FOUND EMERGENCY GEAR HANDLE TRAPPED UNDER FORWARD SPAR COVER.  EMERGENCY EXTENSION WOULD HAVE 	BEEN IMPOSSIBLE.  SUBMITTER STATED SPAR COVER INSTALLED INCORRECTLY BY PERSONS UNKNOWN.					1	L	7	2 	3O				A23CE   					 
1996082900192	19960829	00192	SO  	1996	8	29	96ZZZX4089       	1	19960814	G	7160		AIR BOX         			PIPER 	PA32  	PA32260     	7103206	SO  										CARB ATTACH	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	3755W	3500 				32670				DURING SERVICING OF NOSE STRUT, DISCOVERED AIR BOX CRACKED AROUND CARBURETOR ATTACH FLANGE.  CRACK WAS 270 DEGREES (FRON	T, RIGHT, REAR).  THIS ASSY IS QUITE HEAVY AND PUTS A STRAIN ON THIS WELD IN ALUMINUM PART.  PART RE-WELDED AND RE-INSTA	LLED.				1	L	7	1 	3O				A3SO    					 
1996082900193	19960829	00193	CE  	1996	8	29	96ZZZX4090       	1	19960701	G	3246		WHEEL           			BEECH 	58    	58          	1152740	CE  										NLG	BROKEN          	D	P			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	15	4016A	7599 				TH9				INNER HALF OF NOSE WHEEL BROKE WHEN AIRCRAFT LANDED.  STRUCTURAL INSPECTION OF NOSE LANDING GEAR STRUT REVEALED NO DAMAG	E TO AIRCRAFT.  SUBMITTER STATED CAUSE OF FAILURE UNKNOWN, BUT INSPECTION OF NOSE WHEEL REVEALED SOME PITTING CORROSION 	ON INSIDE OF WHEEL.				1	L	7	2 	3O				3A16    					 
1996082900194	19960829	00194	CE  	1996	8	29	96ZZZX4091       	1	19960723	G	7603	C2995050102	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  										THROTTLE	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	64108	4615 				17265024				INSPECTION FOUND THROTTLE OUTER CABLE HOUSING VERY DETERIORATED DUE TO AGE/HEAT EXPOSURE.  INNER HOUSING LOOSE AT FORWAR	D END, ABOUT TO SEPARATE.  SUBMITTER STATED IF NOT CORRECTED, LOSS OF THROTTLE CONTROL AND ENGINE POWER WILL RESULT.  TH	IS IS THE SECOND REPORT SUBMITTER HAS FILED ON THIS PART.  THIS IS THE FOURTH CABLE SUBMITTER HAS FOUND IN BAD CONDITION	 IN APPROXIMATELY ONE AND ONE-HALF YEARS.  SUBMITTER STATED CABLES SHOULD BE REPLACED WITH NEW PARTS WHICH ARE OF DIFFER	ENT CONSTRUCTION.		1	H	7	1 	3O			NT	3A12    					 
1996082900195	19960829	00195	SO  	1996	8	29	96ZZZX4092       	1	19960724	G	2410	757388	BOLT            	PRESTOLITE  	4111810     	PIPER 	PA28  	PA28181     	7102807	SO  										ALTERNATOR MOUNT	SEPARATED       	B			WC7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8444S				2090476	288290025				DURING AN OIL CHANGE, THE MECHANIC NOTICED A BOLT WITH A SECURE NUT PROTRUDING FORWARD FROM THE BASE OF THE ALTERNATOR. 	 A CLOSER LOOK INDICATED THE HEAD OF THE ALTERNATOR MOUNT BOLT HAD SEPARATED FROM THE SHANK ALLOWING THE BOLT TO VIBRATE	 FORWARD TOWARD THE STARTER FLYWHEEL.  REPLACED BOLT WITH NEW PART AND SECURED.  TACHOMETER:  484.8.  HOBBS:  181.8.				1	L	7	1 	3O				2A13    					 
1996082900196	19960829	00196	CE  	1996	8	29	96ZZZX4093       	1	19960729	G	3230	131553FGB17	ROD END         			BEECH 	23    	C24R        	1151254	CE  										LT MLG ACTUATOR	FAILED          	B			AKGR	O	A			OTHER                   	UNSCHED LANDING         			J			WARNING INDICATION        			NR	NOT REPORTED   	1			CE	05	5246M	4844 				MC564				LEFT MAIN GEAR CAME DOWN WHILE IN-FLIGHT.  CYCLED GEAR DOWN AND BACK UP, AND IT STAYED DOWN.  CYCLED GEAR DOWN AND LANDE	D.  WITH AIRCRAFT IN SHOP, FOUND THE ROD END ON THE ACTUATOR BROKEN.  IT APPEARS TO HAVE BEEN CRACKED AT THE GREASE ZERK	 FIRST THEN, IN TIME, FAILED.				1	L	7	1 	3O				A1CE    					 
1996082900197	19960829	00197	CE  	1996	8	29	96ZZZX4094       	1	19960729	G	3710	B904	HOSE            			CESSNA	150   	152         	2071835	CE  										VACUUM SYSTEM	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	93114					15285404				TWO EACH CESSNA 152 FLIGHT SCHOOL AIRCRAFT REPORTED VACUUM INSTRUMENT PROBLEMS.  FOUND VACUUM SYSTEM HOSES WERE CRUMBLIN	G AND IN VERY POOR CONDITION, ALSO, ONE VACUUM PUMP FAILURE DUE TO INJESTION OF RED INNER SLEEVE PARTICLES FROM HOSES. C	ESSNA SEB 96-10 COVERS THE FAILURE ON THIS SERIES OF HOSE.				1	H	7	1 	3O			NT	3A19    					 
1996082900198	19960829	00198	SO  	1996	8	29	96ZZZX4095       	1	19960801	G	8011	MHB4014	STARTER         			PIPER 	PA31  	PA31350     	7103110	SO  										BENDIX DRIVE	BOLTS FAILED    	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	777KT		547  			317552053				RIGHT ENGINE STARTER WOULD NOT ENGAGE.  FOUND MOTOR HOUSING SEPARATED FROM BENDIX DRIVE SECTION DUE TO BROKEN ATTACH BOL	TS.  SECOND UNIT WITH THIS PROBLEM IN OUR FLEET.					1	L	7	2 	3O				A20SO   					 
1996082900199	19960829	00199	SO  	1996	8	29	96ZZZX4096       	1	19960806	G	2820	K2406SAE2	RING NUT        		451103      	PIPER 	PA28  	PA28161     	7102803	SO  										FUEL PRIMER	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	109GP					287816287				FUEL PRIMER LOCKING RING NUT WAS MISSING APPROXIMATELY 180 DEGREES OF MATERIAL.  THIS PREVENTED THE PLUNGER FROM LOCKING	 IN.  THE NORMAL LOCKING AREA IS THE WIDTH OF THE PIN ON THE PLUNGER, THE AMOUNT OF LOCK MISSING WAS APPROXIMATELY 10 TI	MES THE WIDTH OF THE PIN.				1	L	7	1 	3O				2A13    					 
1996082900200	19960829	00200		1996	8	29	96ZZZX4097       	4	19960701	G	3416	3431	CASTING         	UNITEDINST  	5934P1      															ALTIMETER	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					AG131					THIS INSTRUMENT WAS A  NEW FACTORY SEALED ALTIMETER.  TWO SHAFT END SHAKES WERE UNDER THE MINIMUM .0020 INCH CALLED OUT 	IN THE OVERHAUL MANUAL.  THEY MEASURED .0006 INCH AND .0010 INCH.  THE MANUFACTURER HAS INDICATED AN END SHAKE OF .0004 	INCH OR LESS CAN CAUSE A POINTER HANG-UP DURING A NORMAL SPECIFIED COLD TEST.  END SHAKE CHANGES OF .0002 INCH TO .0003 	INCH HAVE BEEN MEASURED DURING DIFFERENT PRESSURE SETTINGS ON THE ALTIMETER.  SUBMITTER STATED THIS INSTRUMENT COULD HAN	G UP DURING NORMAL COLD OPERATION.															 
1996082900201	19960829	00201		1996	8	29	96ZZZX4098       	4	19960626	G	2350	215640026	CAPACITOR       			PIPER 	PA32  	PA32300     	7103212	SO  										AUDIO PANEL	SHORTED         	E				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SO	13	2351M					327840047				AFTER TAKEOFF, PILOT SMELLED SOMETHING ELECTRICAL BURNING AND THEN SMOKE CAME FROM AROUND AUDIO PANEL.  NARCO CP 135 TSO	.  FOUND C9 CAPACITOR COMING OFF OF 9.6 VOLT LINE TO GROUND SHORTED AND SMOKED COCKPIT.					1	L	7	1 	3O				A3SO    					 
1996082900202	19960829	00202		1996	8	29	96ZZZX4099       	4	19960611	G	3416	3431	CASTING         	UNITEDINST  	5934P       	PIPER 	PA28  	PA28140     	7102802	SO  										ALTIMETER	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2385T				72453	287225064				FRICTION IN ALTIMETER REPORTED 200 FEET.  BENCH TEST CONFIRMED 160 FEET OF FRICTION.  THE END SHAKES ON TWO OF THE MECHA	NISM CRITICAL SHAFTS MEASURED .00085 INCH AND ZERO.  THE OVERHAUL MANUAL CALLS OUT .0020 INCH MINIMUM.  THE ZERO END SHA	KE WOULD CLOSE IN UNDER A COLD CONDITION AND LOCK UP THE POINTERS AS PROVEN AND DOCUMENTED BY THE MANUFACTURER'S TESTS.				1	L	7	1 	3O				2A13    					 
1996082900203	19960829	00203	SW  	1996	8	29	96ZZZX4100       	1	19960610	G	5302	206033004045	TAIL BOOM       			BELL  	206   	206L3       	1182108	SW  										DRIVESHAFT COVER	CRACKED         	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	10SP	5822 			01278	51064				WHILE PERFORMING A 300-HOUR INSPECTION, CRACKS WERE FOUND IN THE TAIL BOOM.  THESE CRACKS WERE FOUND ONLY AFTER THE RT F	RONT TAIL ROTOR DRIVESHAFT COVER CLIP WAS DRILLED OFF TO REPLACE A LOOSE RIVET.  THE CRACKS WERE NOT VISIBLE UNTIL THE C	LIP WAS REMOVED.  THE CRACKS WERE VISIBLE FROM THE BACK SIDE.  TOTAL TIME ON THE HELICOPTER IS 5,821.8 HOURS.				1	G	7	1 	3U				H2SW    					 
1996082900204	19960829	00204	SW  	1996	8	29	96ZZZX4101       	1	19960717	G	5302	206033004045	TAIL BOOM       			BELL  	206   	206L3       	1182108	SW  										DRIVESHAFT COVER	CRACKED         	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	3KY		3443 			51113				WHILE PERFORMING A 100-HOUR INSPECTION, 4 CRACKS WERE FOUND IN THE TAIL BOOM PER ASB 206L-8447, REV C.  THESE CRACKS WER	E NOT VISIBLE FROM THE OUTSIDE.  HOWEVER, DUE TO THE PREVIOUS CRACKS, INSPECTED THIS TAIL BOOM FROM THE INSIDE.  THESE C	RACKS WERE FROM THE RIVET HOLES ON THE TWO FRONT TAIL ROTOR DRIVESHAFT COVER CLIPS.				1	G	7	1 	3U				H2SW    					 
1996082900205	19960829	00205	SW  	1996	8	29	96ZZZX4102       	1	19960723	G	6520	206040405101	SHAFT           			BELL  	206   	206BELL     	1181502	SW  										T/R GEARBOX	MISMANUFACTURED 	B			ETRR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09					A2738					NEW SHAFT RECEIVED FROM BELL FOUND TO BE MACHINED IMPROPERLY.						1	G	7	1 	3U				H2SW    					 
1996082900206	19960829	00206	WP  	1996	8	29	96ZZZX4103       	1	19960726	G	6320	369H5656	PULLEY ASSY     		369A5100709 	HUGHES	369   	369HS       	4470728	WP  										XMSN GEARSHAFT	BOTTOM OUT      	C		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09					820413					ON SOME MAIN ROTOR TRANSMISSION ASSEMBLIES, THE SPLINES ON THE PULLEY ASSEMBLY DRIVER BOTTOM OUT ON THE SPLINES OF THE G	EARSHAFT INPUT BEVEL PINION (369A5107-21).  THIS RESULTS IN A GAP BETWEEN THE GUARD (369H5657) AND THE SPACER (369A5165)	.  OPERATING WITH THIS CONDITION WILL DAMAGE THE INPUT PINION AND THE PULLEY ASSEMBLY.  SUBMITTER RECOMMENDATIONS, CHECK	 FOR THIS CONDITION WITH ANY REPLACEMENT TRANSMISSION ASSEMBLY, MAIN ROTOR.			1	G	7	1 	3U				H3WE    					 
1996082900207	19960829	00207	EA  	1996	8	29	96ZZZX4104       	2	19960708	G	8530	68795	ROCKER COVER    			ENSTRM	F28   	F28F        	3300412	GL  	LYC   	O360  	HIO360F1AD  	41514	EA  					ENGINE	GROOVED         	B			NQ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	210PD	547  				805	L25515S1A			ENGINE DISASSEMBLED DUE TO ROTOR BLADE STRIKE.  FOUND SEVERAL DEEP RINGS WORN IN ROCKER COVERS WHERE ROCKER SHAFTS RIDE.	  (NOT CAUSED BY ACCIDENT.)  SUBMITTER STATED THIS PROBLEM HAS BEEN CORRECTED ON OTHER TYPES OF LYCOMINGS BY INSTALLATIO	N OF PLASTIC THRUST BUTTONS, BUT NOT ON THIS TYPE.				1	G	7	1 	3O	3	O		H1CE    	1E10				 
1996082900208	19960829	00208	EU  	1996	8	29	96ZZZX4105       	1	19960123	G	6520	350A5302005	GEARBOX         			SNIAS 	350   	AS350B1     	8680811	EU  										T/R	MAKING METAL    	B			VE3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	216LA	155  			M2041	2251				TAIL ROTOR GEAR BOX RECENTLY OVERHAULED.  MADE METAL AFTER 154.8 HOURS SINCE OVERHAUL.  TAIL ROTOR GEARBOX WAS REPLACED.	  AIRCRAFT TT:  6,253.8 HOURS.					1	G	7	1 	3U				H9EU    					 
1996082900209	19960829	00209	SW  	1996	8	29	96ZZZX4106       	1	19960123	G	5302	206031004115	TAIL BOOM       			BELL  	206   	206B3       	1181506	SW  										T/R GEARBOX	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	2044C	7226 				3363				DURING 100-HOUR INSPECTION, FOUND CRACK APPROXIMATELY 1.5 INCHES AT FORWARD LEFT MOUNTING HOLE OF TAIL ROTOR GEARBOX ON 	TAIL BOOM.  SUSPECT CAUSED BY FATIGUE.  SUBMITTER STATED NO OUT OF BALANCE CONDITION EXISTED OR REPORTED.  NO OTHER DAMA	GE NOTED.				1	G	7	1 	3U				H2SW    					 
1996082900210	19960829	00210	SW  	1996	8	29	96ZZZX4107       	1	19960123	G	6210	206010200133	BLADE           			BELL  	206   	206B        	1181511	SW  										M/R	CORRODED        	B			VE3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	3202X	3200 			A448	3939				DURING A 1,200-HOUR INSPECTION, MAIN ROTOR BLADES WERE REJECTED DUE TO EXFOLIATION ON LEADING EDGE.  TSN:  3,200.  THESE	 BLADES HAVE A LIFE OF 5,000.0 HOURS.  ACFT TT:  13,200.0 HOURS.					1	G	7	1 	3U				H2SW    					 
1996082900211	19960829	00211	SW  	1996	8	29	96ZZZX4108       	1	19960123	G	6210	206010200133	BLADE           			BELL  	206   	206B        	1181511	SW  										M/R	CORRODED        	B			VE3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	3202X	3200 			A440	3939				DURING A 1,200-HOUR INSPECTION, MAIN ROTOR BLADES WERE REJECTED DUE TO EXFOLIATION ON LEADING EDGE.  TSN:  3,200.  THESE	 BLADES HAVE A LIFE OF 5,000.0 HOURS.  ACFT TT:  13,200.0 HOURS.					1	G	7	1 	3U				H2SW    					 
1996082900212	19960829	00212	SW  	1996	8	29	96ZZZX4109       	1	19960725	G	7160	476150041	GASKET          			BELL  	47    	47G5        	1181032	SW  										CARB INLET	MISINSTALLED    	H		A		A	R			UNSCHED LANDING         	AUTOROTATION            			R	W		PARTIAL RPM/PWR LOSS      	INADEQUATE Q C            		NR	NOT REPORTED   	1			WP	17	7885S	190  				7873				DURING INVESTIGATION FOR CAUSE OF POWER LOSS AND AUTOROTATION OF AIRCRAFT, DISCOVERED GASKET BETWEEN AIR FILTER HOUSING 	AND CARBURETOR INLET HAD ONE CORNER FOLDED OVER ALLOWING DIRT TO ENTER AND BLOCK CARBURETOR AIR PASSAGES.  SUBMITTER SUS	PECTS IMPROPER INSTALLATION WHEN CARBURETOR WAS INSTALLED 190.4 HOURS PREVIOUSLY.				1	G	7	1 	3O				2H3     					 
1996082900213	19960829	00213	EU  	1996	8	29	96ZZZX4110       	1	19960718	G	5720	21211151052	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900214	19960829	00214	EU  	1996	8	29	96ZZZX4111       	1	19960718	G	5720	21211151061	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900215	19960829	00215	EU  	1996	8	29	96ZZZX4112       	1	19960718	G	5720	21211151072	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900216	19960829	00216	EU  	1996	8	29	96ZZZX4113       	1	19960718	G	5720	21211151082	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900217	19960829	00217	EU  	1996	8	29	96ZZZX4114       	1	19960718	G	5720	21211151092	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900218	19960829	00218	EU  	1996	8	29	96ZZZX4115       	1	19960718	G	5720	21211151101	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900219	19960829	00219	EU  	1996	8	29	96ZZZX4116       	1	19960718	G	5720	21211151102	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900220	19960829	00220	EU  	1996	8	29	96ZZZX4117       	1	19960718	G	5720	21211151112	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900221	19960829	00221	EU  	1996	8	29	96ZZZX4118       	1	19960718	G	5720	21211151121	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900222	19960829	00222	EU  	1996	8	29	96ZZZX4119       	1	19960718	G	5720	21211151122	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900223	19960829	00223	EU  	1996	8	29	96ZZZX4120       	1	19960718	G	5720	21211151132	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900224	19960829	00224	EU  	1996	8	29	96ZZZX4121       	1	19960718	G	5720	21211151141	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900225	19960829	00225	EU  	1996	8	29	96ZZZX4122       	1	19960718	G	5720	21211151142	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900226	19960829	00226	EU  	1996	8	29	96ZZZX4123       	1	19960718	G	5720	21211151152	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900227	19960829	00227	EU  	1996	8	29	96ZZZX4124       	1	19960718	G	5720	21211151162	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900228	19960829	00228	EU  	1996	8	29	96ZZZX4125       	1	19960718	G	5720	21211151192	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900229	19960829	00229	EU  	1996	8	29	96ZZZX4126       	1	19960718	G	5720	21213201061	STIFFENER       			CASA  	C212  	C212200     	2410304	EU  										LT/RT WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	311ST	9077 				292				INSPECTION OF BOTH RIGHT AND LEFT WINGS PER CASA COM LETTER 212-224, FOUND STIFFENER ANGLES AFT OF FALSE SPAR CRACKED.						2	H	7	2 	4T				A43EU   					 
1996082900231	19960829	00231	WP  	1996	8	29	96ZZZX4128       	1	19960808	G	2921	43645082	DIAPHRAGM       		43442795002 	DOUG  	DC8   	DC871F      	302199D	WP  										HYD ACCUMULATOR	RUPTURED        	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8076U	225  			85319028	45941				INSTALLED NEW DIAPHRAGM AND ACCUMULATOR INSTALLED IN AIRCRAFT 6-5-61.  ACCUMULATOR REMOVED 7-25-96 FOR INTERNAL FAILURE.	  FOUND DIAPHRAGM RUPTURED AFTER 225 HOURS TIME IN SERVICE.					2	L	7	4 	4F			RT	4A25    					 
1996082900232	19960829	00232	SW  	1996	8	29	96ZZZX4129       	1	19960802	G	3230	75006131	ARM ASSY        			GULSTM	690TP 	695A        	7630519	SW  										NLG LINKAGE	CRACKED         	B			IUMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	20GT	3400 				96036				FOUND NLG ARM ASSY CRACKED FROM BOTH BOLT HOLES AND ALONG TUBE PORTION.  TWO CRACKS FROM BOLT HOLES OUTBOARD AND ONE CRA	CK FROM OUTER EDGE .75 INCH INBOARD ON PART.  BOLT HOLE CRACKS FROM THESE BOLTS DO NOT APPEAR TO BE DEBURRS FROM INSTALL	ATION.  FOUND ON 100-HOUR INSPECTION.				1	H	7	2 	4T				2A4     					 
1996082900233	19960829	00233	EU  	1996	8	29	96ZZZX4130       	1	19960715	G	2910	751112	TUBE            			AMD   	FALC50	FALCON50MYST	2730106	EU  										HYDRAULIC PRESS	CHAFE/LEAK      	B			AMCR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	09	254DV	6250 				85				AFTER RETURNING FROM A FLIGHT, GROUND CREW NOTICED HYDRAULIC FLUID ON BOTTOM OF NR 1 PYLON.  INVESTIGATION REVEALED THE 	HYDRAULIC SUPPLY AND PRESSURE LINES WERE CHAFING.  BOTH LINES WERE CHAFED EVENLY, BUT THE PRESSURE LINE JUST STARTED TO 	LEAK.  THE LINES WERE RUBBING AT APPROXIMATELY 3 INCHES FORWARD OF THE AFT BEND WHERE IT COMES OUT OF THE FUSELAGE AND S	TARTS TO GO FORWARD THROUGH THE PYLON.  NOTHING WAS OUT OF PLACE INCLUDING THE LINE CLAMPS.  INSPECTION OF THE RIGHT PYL	ON REVEALED GOOD CLEARANCE.  INSTALLATION OF THE NEW LINES IN THE NR 1 PYLON RENDERED GOOD CLEARANCE.		2	L	7	3 	4F				A46EU   					 
1996082900234	19960829	00234	EU  	1996	8	29	96ZZZX4131       	1	19960715	G	2910	751103	TUBE            			AMD   	FALC50	FALCON50MYST	2730106	EU  										HYDRAULIC SUPPLY	CHAFE/LEAK      	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	254DV	6250 				85				AFTER RETURNING FROM A FLIGHT, GROUND CREW NOTICED HYDRAULIC FLUID ON BOTTOM OF NR 1 PYLON.  INVESTIGATION REVEALED THE 	HYDRAULIC SUPPLY AND PRESSURE LINES WERE CHAFING.  BOTH LINES WERE CHAFED EVENLY, BUT THE PRESSURE LINE JUST STARTED TO 	LEAK.  THE LINES WERE RUBBING AT APPROXIMATELY 3 INCHES FORWARD OF THE AFT BEND WHERE IT COMES OUT OF THE FUSELAGE AND S	TARTS TO GO FORWARD THROUGH THE PYLON.  NOTHING WAS OUT OF PLACE INCLUDING THE LINE CLAMPS.  INSPECTION OF THE RIGHT PYL	ON REVEALED GOOD CLEARANCE.  INSTALLATION OF THE NEW LINES IN THE NR 1 PYLON RENDERED GOOD CLEARANCE.		2	L	7	3 	4F				A46EU   					 
1996082900236	19960829	00236	SW  	1996	8	29	96ZZZX4133       	1	19960729	G	2434	ALV8402	ALTERNATOR      	PRESTOLITE  		GULSTM	500   	500S        	0141107	SW  										CASE MOUNT	LUG BROKEN      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	47RF		700  		8000020	3261				WHILE COMPLETING 100-HOUR FACTORY INSPECTION, FOUND ALTERNATOR MOUNT LUG ON LEFT ALTERNATOR BROKEN, ALTERNATOR SYSTEM WA	S OPERATING.  MOUNTING LUG WAS BROKEN OFF CASE OF ALTERNATOR.  EXCHANGE ALTERNATOR INSTALLED.					1	H	7	2 	3O				6A1     					 
1996082900237	19960829	00237	SO  	1996	8	29	96ZZZX4134       	1	19960727	G	3250	285692	VALVE           			LKHEED	1049  	1049H82     	5262122	SO  										NLG STEERING	DEFECTIVE       	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	15	6937C		5    			4830				DURING LANDING AFTER FLY-BY DEMONSTRATION, ACFT VEERED OFF THE RUNWAY TO THE LEFT AND COMPLETED ROLL-OUT IN THE GRASS. A	IRCRAFT WAS ABLE TO TAXI TO DISPLAY/TIE-DOWN AREA WITHOUT FURTHER INCIDENT.  FIELD INVESTIGATION REVEALED THE NOSE GEAR 	STEERING VALVE PRESENTED A HYDRAULIC CONDITION THAT MADE THE NOSE GEAR DEFLECT HARD OVER TO THE LEFT.  MINOR DAMAGE WAS 	DONE TO THE RIGHT NOSE TIRE AND WHEEL WHEN IT HIT A RUNWAY MARKER LIGHT.  SUBMITTER STATED SINCE THIS UNIT WAS RECENTLY 	OVERHAULED, TESTING PROCEDURES MAY NOT BE ADEQUATE PRIOR TO INSTALLATION.		2	L	7	4 	4R				6A5     					 
1996082900238	19960829	00238	CE  	1996	8	29	96ZZZX4135       	1	19960722	G	3230	711701	VALVE           			RKWELL	NA265 	NA26540     	6402608	CE  										MLG HYDRAULIC	FAILED          	B			EBVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	7KG	3    			1177H	282111				AIRCRAFT WAS INITIALLY EXPERIENCING LANDING GEAR OPERATION PROBLEMS.  PROBLEM WAS TROUBLESHOT TO A BAD LANDING GEAR HYDR	AULIC CONTROL VALVE.  REQUIRED A REPAIRED VALVE AND INSTALLED.  ALL OPS CHECKS WERE GOOD.  ON THE FIRST TRIP, PILOT REPO	RTED HEARING THE HYDRAULIC POWERPACK CYCLING EXCESSIVELY.  FOUND NEWLY INSTALLED REPAIRED VALVE TO BE BYPASSING INTERNAL	LY.  REMOVED AND REPLACED VALVE WITH ANOTHER REPAIRED VALVE.  VALVE OPERATION WAS NORMAL.  AIRCRAFT WAS RETURNED TO SERV	ICE.		2	L	7	2 	4J				A2WE    					 
1996082900239	19960829	00239	NM  	1996	8	29	96ZZZX4136       	1	19960701	G	5320		HAT CHANNEL     			BOEING	727   	727243      	138408D	NM  										FS 1136-1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				RT AFT LAVATORY HAT CHANNEL CORRODED BL 20R, STA 1136 TO STA 1166.  FOUND DURING C10 CHECK ON CPCP INSPECTION.						2	L	7	3 	4F			RT	A3WE    					 
1996082900240	19960829	00240	WP  	1996	8	29	96ZZZX4137       	1	19960716	G	3610	AAM74141	DUCT            			DOUG  	DC10  	DC10*       		WP  										BLEED SYSTEM	FLANGE BROKEN   	B			L4PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01										THE DUCT WAS RECEIVED WITH ONE FLANGE RUPTURED AT A PREVIOUS WELD REPAIR LOCATION.  ALL OTHER HIDDEN DAMAGE INSPECTION T	O THE DUCT ASSEMBLY DID NOT REVEAL ANY SUBSEQUENT DAMAGE AS A RESULT OF THE DUCT FAILURE.  WELD WAS AT A RADIUS OF THE F	LANGE IN AN AREA NOT NORMALLY REPAIRABLE.				2	L	7	3 	4F				A22WE   					 
1996082900241	19960829	00241	WP  	1996	8	29	96ZZZX4138       	1	19960801	G	3320	BR9708001	POWER LAMPHOLDER	BRUCE       	BR9702931NW 	DOUG  	DC9   	DC931       	3022065	WP  										LIGHT SYSTEM	BURN DAMAGE     	B			ZZBR	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			WP	11										STC NR ST00092LA.  TWO ITEMS RETURNED, BOTH WITH DATE CODE 9521.  BOTH WITH SIMILAR DAMAGE.  BURN DAMAGE RESTRICTED TO T	HE LAMPHOLDER CONTACTS AND SURROUNDING AREA WITH AN 0.1 INCH AT THE LAMP CONTACT LOCATION.  SUSPECT CAUSE IS ON INTERMIT	TENT CONNECTION BETWEEN THE LAMP AND LAMPHOLDER.				2	L	7	2 	4F				A6WE    					 
1996082900242	19960829	00242	WP  	1996	8	29	96ZZZX4139       	1	19960801	G	3320	BR9708001	POWER LAMPHOLDER	BRUCE       	BR9702931NW 	DOUG  	DC9   	DC931       	3022065	WP  										LIGHT SYSTEM	BURN DAMAGE     	B			ZZBR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	11										STC NR ST00092LA.  BURN DAMAGE INCLUDED THE LAMPHOLDER FACEPLATE AND THE PRINTED CIRCUIT BOARD.  THE FACEPLATE WAS DAMAG	ED IN THE AREA BETWEEN BOTH CONTACTS AND EXTENDED TO ONE EDGE.  THE CIRCUIT BOARD WAS BURNED THROUGH.  THE HEAT GENERATI	ON POINT APPEARS TO HAVE BEEN THE ELECTRICAL CONTACT BETWEEN THE LAMPHOLDER AND THE LAMP.  SUSPECT CAUSE IS AN INTERMITT	ENT CONNECTION BETWEEN THE COMPONENTS.  DAMAGE TO THE CIRCUIT BOARD MAY INDICATE A SECONDARY FAILURE.			2	L	7	2 	4F				A6WE    					 
1996082900333	19960829	00333		1996	8	29	96ZZZX4140       	4	19960812	G	6122	D20594	DRIVE GEAR      	MCAULY      	DCFTS290D10 															PROPELLER	WORN            	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					820155					DURING INSPECTION OF GOVERNOR, SPLINE IN DRIVE GEAR WAS FOUND WORN.  GOVERNOR WAS RETURNED TO CUSTOMER.																			 
1996082900334	19960829	00334	CE  	1996	8	29	96ZZZX4141       	1	19960802	G	3220	074214610	BRACKET         			CESSNA	185   	A185F       	2072821	CE  										TAIL STINGER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	1047F					18502704				FREE-PLAY WAS OBSERVED IN TAIL WHEEL STINGER DURING SERVICING OF TAIL WHEEL.  TAIL CONE WAS REMOVED AND BRACKET FOUND CR	ACKED AROUND BOLT HOLE UNDER NUT.  PART WAS REPLACED WITH NEW FROM FACTORY.					1	H	7	1 	3O				3A24    					 
1996082900335	19960829	00335	EA  	1996	8	29	96ZZZX4142       	2	19960418	G	8530	LW14115	CYLINDER        			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 1 CYL SLEEVE	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	17PS	321  				31P7630008	RL62362			HOBBS - 3,213.6 HOURS.  OIL APPEARED AROUND NR 1 CYLINDER PUSH ROD TUBES.  SEALS REPLACED, GROUND CHECK OPS GOOD.  AFTER	 FLIGHT, OIL APPEARED AGAIN.  REMOVED NR 1 CYLINDER, FOUND CYLINDER SLEEVE CRACKED APPROXIMATELY THREE-FOURTHS OF CIRCUM	FERENCE.  LOG REVEALED THIS TO BE THE 3RD CYLINDER ON NR 1 IN 4 YEARS.  PISTON P/N LW 10545 SHOWED SIGNS OF BEING HOT. S	USPECT OIL NOZZLE FOR PISTON COOLING INOPERATIVE.  REPLACED NOZZLE, P/N 73772.  REPLACED CYLINDER KIT, P/N 05K21116-3, A	ND ASSOCIATED SEALS AND GASKETS.  PISTON SKIRT WAS OIL COKED AND DISCOLORED.		1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
1996082900336	19960829	00336	SO  	1996	8	29	96ZZZX4143       	1	19960703	G	3230	6703102	FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  										GEAR RETRACT	BROKEN          	B			MN3R	O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			WP	11	2191Z	3677 				347970212				DURING APPROACH TO LANDING AND GEAR EXTENSION, LEFT MLG FAILED TO INDICATE DOWN AND LOCKED (NO GREEN LIGHT).  LANDING GE	AR UNSAFE LIGHT AND GEAR PUMP BOTH REMAINED ON.  UNEVENTFUL LANDING MADE, MAINTENANCE FOUND GEAR UNLOCKED AND FITTINGS H	OLES BROKEN OUT (LOCK TURNBUCKLE HOLES).  ONE SIDE SHOWED INTERGRANULAR CORROSION ALONG CRACK, OTHER SIDE HAD CLEAN BREA	K.			1	L	7	2 	3O				A7SO    					 
1996082900337	19960829	00337	SO  	1996	8	29	96ZZZX4144       	1	19960521	G	3230	5541602	CONTROL CABLE   			PIPER 	PA31  	PA31325     	7103105	SO  										MLG CONTROL	BROKEN          	H		A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	25	732WC	7629 				317512049				WHEN PILOT SELECTED GEAR DOWN POSITION, HE HEARD A SNAP AND HANDLE FELL LOOSELY TO DOWN POSITION.  UNABLE TO LOWER GEAR.	  GEAR 'UP' LANDING WAS PERFORMED.  FOUND LANDING GEAR CONTROL CABLE BROKEN INSIDE THE OUTER HOUSING NEAR GEAR HANDLE EN	D.  SUSPECT CABLE FAILED DUE TO FATIGUE DUE TO AGE AND NUMBER OF CYCLES.  NO EVIDENCE OF CORROSION OR OTHER DAMAGE WERE 	FOUND.			1	L	7	2 	3O			 	A20SO   					 
1996082900339	19960829	00339	EA  	1996	8	29	96ZZZX4146       	2	19960410	G	7420		P-LEAD          			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					FIREWALL	SHORTING        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	376AA					32R7885094	L1803048A			TROUBLESHOOTING FOR INTERMITTENT INOPERATIVE CONDITION ON RT MAGNETO FOUND P-LEAD SHORTING WHERE IT EXITS THROUGH FIREWA	LL.  REPLACED P-LEADS AND INSTALLED PLASTIC SLEEVING.					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996082900340	19960829	00340	SO  	1996	8	29	96ZZZX4147       	1	19960718	G	2140	B3040	HEATER          	JANITROL    		PIPER 	PA31  	PA31325     	7103105	SO  										AIR INLET	BIRD NEST       	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	4074K					318112019				PILOT REPORTED GRASS BLOWING OUT OF DEFROSTER.  FOUND BIRD NEST INSIDE OF HEATER INLET, IN BLOWER FAN, AND INSIDE HEATER	 AROUND BURNER CAN.  SUGGEST SCREEN INSTALLED IN INLET TO HEATER AND MORE THOROUGH PRE-FLIGHT.					1	L	7	2 	3O				A20SO   					 
1996082900341	19960829	00341	EA  	1996	8	29	96ZZZX4148       	2	19960812	G	7414	1035110	BEARING         		D4RN1021    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAG REAR	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4949G		822  		4083837	17273496	L537776			MAGNETO POINTS WERE NOT OPENING DUE TO EXCESSIVE WEAR ON THE POINTS' CAM FOLLOWER.  THIS WEAR WAS ACCELERATED BY A HEAT 	BUILD-UP ON THE MAGNETO SHAFT GENERATED BY A FAILED REAR BEARING.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996082900342	19960829	00342	SO  	1996	8	29	96ZZZX4149       	1	19960718	G	2750	6378100	FLAP HANDLE     			PIPER 	PA28  	PA28140     	7102802	SO  										CABLE ATTACH	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	56678	5055 				287425016				C/W PIPER SB 965 ON 10-29-93 AT 3,481.3 HOURS.  C/W AD 96-10-03 ON 7-18-96 AT 5,054.8 HOURS.  FOUND FLAP HANDLE, BUSHING	 INSTALLED IAW SB 965 AND BOLT AT CABLE ATTACH WORN ALMOST THROUGH.  PART LASTED 3,481 HOURS WITH NO PROBLEM.  C/W SB 96	5 AND PART WAS WORN OUT IN 1,753 HOURS.  SUBMITTER SUGGESTS ADDING 500-HOUR INSPECTION INTERVALS TO AD 96-10-03.				1	L	7	1 	3O				2A13    					 
1996082900343	19960829	00343	CE  	1996	8	29	96ZZZX4150       	1	19960726	G	5520	59343001	ELEVATOR        			CESSNA	425   	425         	2076018	CE  										LT SIDE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	6773L					4250073				RECEIVED 'NEW' PART, DROP SHIPPED FROM CESSNA AIRCRAFT.  PREPPED AND PAINTED TO MATCH AIRCRAFT.  PLACED CONTROL SURFACE 	ON BALANCING JIG.  PART REQUIRED 6 OUNCES OF ADDITIONAL COUNTERWEIGHT TO BRING WITHIN PRESCRIBED LIMITS.  REMOVED EXISTI	NG LT ELEVATOR DUE TO MINOR HANGAR DAMAGE.  ATTEMPTED TO INSTALL 'NEW' PART ON ACFT.  HINGE BOLTS WERE INSTALLED AND IT 	WAS DETERMINED THERE WAS INSUFFICIENT CLEARANCE BETWEEN THE WEIGHT RIB AND HORIZONTAL STABILIZER.  ALSO, THE TORQUE TUBE	 FLANGE WAS NOT PROPERLY INDEXED AND COULD NOT BE CORRECTED BY NORMAL RIGGINGS.		1	L	7	2 	3T			RT	A7CE    					 
1996082900344	19960829	00344	SO  	1996	8	29	96ZZZX4151       	2	19960807	G	7310	6410321147	VALVE           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					FUEL MANIFOLD	LEAKING         	B			APCR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	666HL	54   			ED89606CK	347770235	809072R			FUEL MANIFOLD VALVE HAS FUEL LEAKING FROM TOP OF UNIT.  INCREASE TORQUE VALUE FOR SCREWS.						1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996082900345	19960829	00345	SO  	1996	8	29	96ZZZX4152       	1	19960729	G	2750	480715	PIN             			PIPER 	PA28  	PA28140     	7102802	SO  										FLAP CONTROL	SHEARED         	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	8159N					2825354				THE RECENT AD 96-10-03 ADDRESSES THE ATTACHMENT OF THE FLAP CONTROL CABLE TO THE FLAP HANDLE ON THE PA28 SERIES AIRCRAFT	.  WHILE COMPLYING WITH THIS AD, FOUND THE PIN (WHICH FORMS PART OF THE RATCHETING MECHANISM TO SELECT FLAPS DOWN) SHEAR	ED INTO TWO PARTS.  SUBMITTER STATED THIS IS 3RD TIME TO FIND A SHEARED PIN ON THIS MODEL OF PIPER.				1	L	7	1 	3O				2A13    					 
1996082900346	19960829	00346	CE  	1996	8	29	96ZZZX4153       	1	19960701	G	2810	369200152	FUEL TANK       	USRUBBER    		BEECH 	58    	58          	1152740	CE  										ANTI-SLOSH	DETERIORATED    	B	P	A	DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	9737S					TH671				THE SPONGE-LIKE MATERIAL USED IN THIS TANK BEGAN TO DETERIORATE/DISENTEGRATE.  THIS BECAME APPARENT WHEN PILOT BEGAN NOT	ICING SMALL DARK PARTICLES IN FUEL SAMPLE OF RT INBOARD QUICK DRAIN ON PRE-FLIGHT INSPECTION.  PARTICLE QUANTITY INCREAS	ED AND RAN SAMPLE THROUGH A FILTER AND DETERMINED WHAT PARTICLES WERE.  UPON REMOVAL, FOUND MOST OF SPONGE MATERIAL LOOS	E IN TANK.  SUBMITTER FEELS THIS CAME ABOUT AS A RESULT OF AGE ON TANK (24 YEARS) AND 100LL GAS ACTING ON PLASTIC-LIKE S	PONGE MATERIAL.		1	L	7	2 	3O				3A16    					 
1996082900347	19960829	00347	CE  	1996	8	29	96ZZZX4154       	1	19960710	G	2750	2111031001	FLAP FOLLOW-UP  	STEC        	602         	BEECH 	35    	S35         	1151532	CE  										LT WING FLAP	SEIZED          	D				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	17	5826K					D7842				FLAPS FAILED TO EXTEND.  FOUND AUTOPILOT FOLLOW-UP IN LEFT WING SEIZED IN THE AFT POSITION ALLOWING THE ACTUATING WIRE T	O MOVE OVER FLAP MICROSWITCH AND NOT ALLOWING FLAP TO EXTEND.  LUBRICATED SHAFT OF FOLLOW-UP AND SYSTEM OPERATES CORRECT	LY.  NEW SERVO FOLLOW-UP ON ORDER.				1	L	7	1 	3O				3A15    					 
1996082900348	19960829	00348		1996	8	29	96ZZZX4155       	4	19960808	G	2562	BP1025	BATTERY         	COMMUNCOMP  	CIR10       	BEECH 	95    	95B55       	1152729	CE  										ELT	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	712BP				4155	TC1520				REPLACED BATTERY (ELT) BP-1025 PURCHASED FROM TRIM-CRAFT, JUNE, 1994.  ELT TESTED OK; THEN, JUNE, 1995 WAS OK AT THAT AN	NUAL TIME.  AT THIS YEAR'S ANNUAL, TESTED ELT.  SIGNAL OK, BUT FOUND CASE AND AREA OF ELT MOUNTING LOCATION FULL OF CORR	OSION.  CALLED COMMUNICATION CORP AND WAS TOLD THEY NEVER HEARD OF THAT.  UNIT WAS SENT TO THEM FOR ANALYSIS OF UNIT.				1	L	7	2 	3O			RT	3A16    					 
1996082900349	19960829	00349	EA  	1996	8	29	96ZZZX4156       	2	19960728	G	7414	M3081	CONTACT POINTS  	SLICK       	4373        	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					MAGNETO	SPRING DEFECT   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	73785	239  			94090132	17267677				AIRCRAFT LANDED AFTER CROSS-COUNTRY.  WHEN THE PILOT ATTEMPTED TO DEPART, ENGINE WOULD NOT START.  TROUBLESHOOTING DETER	MINED THE POINTS IN THE LEFT MAGNETO WOULD NOT CLOSE COMPLETELY.  GAP WAS WITHIN TOLERANCE.  RETURN SPRING APPEARED TO B	E BOWED, NOT SUPPLYING ENOUGH TENSION.  INSTALLED NEW CONTACT KIT.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996082900350	19960829	00350	SO  	1996	8	29	96ZZZX4157       	1	19960806	G	8120	3AT6EE10J2	TURBOCHARGER    	GARRTT      		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					RT ENGINE	LOCKED UP       	E				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	11	98HD	1258 				347870461				PILOT APPLIED POWER TO RIGHT ENGINE FOR PRE-FLIGHT CHECK.  ENGINE WOULD ONLY TURN UP TO 26 INCHES MAN/PRESSURE.  FOUND T	URBO HAD LOCKED UP.  INSTALLED OVERHAULED TURBO, ENGINE GROUND RAN, CHECKED NORMAL.  AIRCRAFT TEST FLOWN, ALL CONDITIONS	 NORMAL.				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996082900351	19960829	00351		1996	8	29	96ZZZX4158       	4	19960530	G	3416	3431	CASTING         	UNITEDINST  	593RPA56    	MOONEY	M22   	M22         	5870402	SW  										ALTIMETER	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					E54					THE END SHAKE ON THE THREE CRITICAL MECHANISM SHAFTS WERE MEASURED.  TWO OF THE SHAFTS HAD END SHAKES OF .0003 INCH.  AN	 ALERT SERVICE BULLETIN PUT OUT BY THE MANUFACTURER INDICATED THAT AN END SHAKE OF .0004 INCH OR LESS WOULD CAUSE POINTE	R HANG-UP AT THE LOW OPER TEMPERTURE.				1	L	7	1 	3O				A6SW    					 
1996082900352	19960829	00352	NM  	1996	8	29	96ZZZX4159       	1	19960701	G	5711		SPAR            			UNIVAR	415   	415E        	0420308	NM  										LT/RT WING AFT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99						4914				REPORTING FINDINGS OF INSPECTION REQUIRED IN AD 94-18-04.  EVIDENCE FOUND OF CORROSION BETWEEN PARTS OF REAR SPAR IN LEF	T WING.  SAME CONDITION FOUND IN RIGHT WING AS WELL AS A PORTION OF EXFOLIATION FOUND IN BOTTOM SPAR CAP, AFT SIDE, ABOU	T A FOOT FROM THE OUTBOARD END.				1	L	7	1 	3O				A787    					 
1996082900353	19960829	00353	WP  	1996	8	29	96ZZZX4160       	1	19960804	G	3246	9560892	BOLT            		GY189       	DOUG  	DC9   	DC9*        		WP  										WHEEL TIE BOLT	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	17										DEFECT:  WHEEL TIE BOLT FAILURE.  SUSPECT CAUSE:  FATIGUE.						2	L	7	2 	4F				A6WE    					 
1996082900354	19960829	00354	NM  	1996	8	29	96ZZZX4161       	1	19960807	G	5753	6521758	FITTING         		652163475   	BOEING	707   	727100      	1384036	NM  										INBD AFT FLAP	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13					BN77					AFT PORTION OF ONE CARRIAGE SUPPORT FITTING FOUND EXFOLIATION ONCE THE LEADING EDGE CAP WAS REMOVED FROM SPAR.  FND CORR	OSION ON MATING SURFACES OF L/E CAP AND SPAR.  FLAP IN SHOP FOR COMPLETE HONEYCOMB/SKIN REPLACMENT AND OVERHAUL.  DUE TO	 DESIGN, AFT PORTION OF FITTING AND FWD FACE OF SPAR FITTING CANNOT BE INSPECTED DUE TO INACCESSABILITY.  OHM HAS NOTHIN	G ON INSP OF THESE FITTINGS AND FWD FACE OF SPAR IN AREAS THAT ARE INACCESSIBLE, AND NOTHING ABOUT SEPARATING L/E FROM S	PAR FOR INSP.  SUBMITTER RECOMMENDS OHM BE AMENDED TO INCLUDE SEPARATION OF L/E CAP FROM SPAR FOR FURTHER INSP ON ALL FL	APS OF THIS DESIGN.	2	L	7	3 	4F			RT	A3WE    					 
1996082900355	19960829	00355	NM  	1996	8	29	96ZZZX4162       	1	19960801	G	5320		SHEAR WEB       			BOEING	727   	727243      	138408D	NM  										FS 1136-1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				RIGHT AFT LAVATORY SHEAR WEB CORRODED FROM STA 1136 TO STA 1166, BL 20R TO BL 45R.  FOUND ON CPCP INSPECTION UNDER C10 C	HECK.					2	L	7	3 	4F			RT	A3WE    					 
1996082900356	19960829	00356	CE  	1996	8	29	96ZZZX4163       	1	19960802	G	2435	1545924	BAND            	ALIDSIGNAL  	30B10719A   	LEAR  	55    	55LEAR      	5170702	CE  										GENERATOR ROTOR	SEPARATED       	B			PW2R	K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CE	07	127GT		122  		1333	067				BAND SEPARATED FROM ROTOR CAUSING CATASTROPHIC FAILURE OF ROTOR AND STATOR.  BAND IS NOT AS SPECIFIED OR SUPPLIED ON THE	 GENERATOR BY ALLIED SIGNAL.  PART DOES NOT CONFORM TO DESIGN DATA.  APPEARS UNAUTHORIZED REPAIR MADE TO ROTOR USING UNA	UTHORIZED PARTS.  REPAIR OF ROTOR NOT AUTHORIZED BY REPAIR MANUAL.				2	L	7	2 	4F				A10CE   					 
1996082900357	19960829	00357	NM  	1996	8	29	96ZZZX4164       	1	19960809	G	2121	13B63352	BEARING         	SUNDSTRANDEM	5007024620  	BOEING	737   	737210C     	1384459	NM  										GASPER FAN	FAILED          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		290  			AA51542					BEARING COMPLETELY DESTROYED.  BEARING INSTALLED NEW AND FAILED AFTER 289.80 HOURS OF OPERATION.  FAN TRIPPED CIRCUIT BR	EAKER, IMPELLER OF FAN RUBS ON FAN HOUSING.					2	L	7	2 	4F				A16WE   					 
1996082900358	19960829	00358	WP  	1996	8	29	96ZZZX4165       	1	19960726	G	3320	BR9708001	POWER LAMPHOLDER	BRUCE       	BR9702931NW 	DOUG  	DC9   	DC931       	3022065	WP  										LIGHT SYSTEM	BURNED          	B	L		ZZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11										MAIN HOUSING HAS A BURN HOLE APPROX 1 INCH BY 0.5 INCH ON RT HAND SIDE WHICH EXPOSED INTERNAL CIRCUITRY.  REMAINING MAJO	RITY OF PLASTIC HOUSING DISTORTED WITH BULGING OF CONTOUR SURFACE IN A FEW LOCATIONS, AND DISCOLORATION FROM OVERHEATING	.  INDUCTOR AND OVERCURRENT FUSE ARE VISIBLE THROUGH BURN HOLE.  FUSE METAL END CAP AND ITS ASSOC AXIAL LEAD HAVE MELTED	.  THERE ARE 2 DISTINCT FAILURE MODES IN EVIDENCE; CAPACITOR FAILURE AND A SHORT CIRCUIT BETWEEN THE OVERCURRENT FUSE AN	D INDUCTOR.  DEGREE OF FAILURE IS UNPRECEDENTED DUE TO COMBINED FAILURE MODES.  WHEN OVERCURRENT FUSE SHORTED TO THE IND	UCTOR, IT ALSO SHORTED OUT THERMOSTAT AND THERMAL FUSE LEAVING CIRCUIT UNPROTECTED FROM CAPACITOR FAILING.  THERE IS INS	2	L	7	2 	4F				A6WE    					 
1996082900359	19960829	00359	CE  	1996	8	29	96ZZZX4166       	1	19960628	G	2842	EA8182069	SENSOR          			RKWELL	NA265 	NA26540     	6402608	CE  										NR 7 TANK	INOPERATIVE     	B			OPER	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09					B1919141					RECEIVING INSPECTION CONDUCTED BY RAYTHON AEROSPACE.  THERE IS 'NO WAY' THAT THIS NR 7 FUEL QUANTITY TANK UNIT COULD HAV	E BEEN BENCH CHECKED/FUNCTIONAL TESTED.  RECEIVING INSPECTION READINGS WERE 35MMF'S AND WOULD NOT 'NULL' READINGS SUGGES	T THAT THE UNIT IS WIRED IN REVERSE.				2	L	7	2 	4J				A2WE    					 
1996082900360	19960829	00360	EA  	1996	8	29	96ZZZX4167       	2	19960608	G	7313	3035228	FUEL NOZZLE     								PWA   	PT6   	PT6A65B     	52043	EA  					RT ENGINE	DEFECTIVE       	B			MASR	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			SW	01	2FOR				1195		97169			AT CLIMB-OUT THE CREW NOTICED THE RT ITT CLIMBING PAST RED LINE.  POWER LEVER WAS PULLED BACK UNTIL ITT WAS RED LINE.  T	HERE WAS ONLY 1,200 POUNDS OF TORQUE NOTED.  WHEN THE ENGINE HOT SECTION WAS REMOVED, THE CT VANE RING HAD ONE VANE WITH	 99 PERCENT OF THE VANE AREA MELTED OR BURNED AWAY.  THE CT BLADES WERE DISCOLORED DUE TO HIGH TEMP.  AT THIS POINT OF T	HE INVESTIGATION, THE FUEL NOZZLE SET IS THE SUSPECTED CAUSE FOR FOR THE HOT SECTION DAMAGE.								4	T			E4EA				 
1996082900364	19960829	00364	CE  	1996	8	29	96ZZZX4168       	1	19960630	G	2710	656501620	CONTROL CABLE   			CESSNA	500   	S550        	2076607	CE  										INBD AILERON	FRAYED          	B		A	CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	157QS	4402 				S5500157				DURING PHASE 12 INSPECTION, FOUND LOWER INBOARD AILERON CABLE WITH BROKEN WIRES.  THIS WEAR/DAMAGE OCCURS AT FAIRLEADS P	/N S338-1.  INSPECTION FOUND TEFLON FAIRLEAD DAMAGES THIS CABLE ABOUT 75 PERCENT OF THE TIME.  SUBMITTER STATED SOMETHIN	G NEEDS TO BE DONE ABOUT THE WEAR/DAMAGE CAUSED BY THIS FAIRLEAD.				1	L	7	2 	4F			RT	A22CE   					 
1996082900365	19960829	00365	SO  	1996	8	29	96ZZZX4169       	1	19960729	G	3222	6705403	TRUNNION        		6710008     	PIPER 	PA44  	PA44180     	7104402	SO  										NLG	FAILED          	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	15	22390	5031 				447995066				AFTER VARIOUS ATTEMPTS TO GET A LOCKED INDICATION (GREEN LIGHT) FOR THE NOSE GEAR, A GREEN INDICATION WAS NOTED AND A NO	RMAL LANDING WAS ACCOMPLISHED.  AIRCRAFT MAINTENANCE FOUND THE ALUMINUM CASTING FOR THE NLG TRUNNION ASSY HAD FAILED WHE	RE THE CENTERING SPRING ASSY, PN 86636-02, ATTACH BRACKET ASSY, PN 67114-00, BOLTS TO THE NLG TRUNNION.  THIS ALLOWED TH	E CENTERING SPRING TO ROTATE AND JAM THE NOSE GEAR IN WHEELWELL.  SUBMITTER SUGGESTS INSPECTION OF THIS AREA AT 100-HOUR	 INTERVALS.		1	L	7	2 	3O				A19S0   					 
1996082900366	19960829	00366	EU  	1996	8	29	96ZZZX4170       	1	19960809	G	5553	3301028709	ATTACH FITTING  			FOKKER	F27   	F27MK200    	4990620	EU  										VERTICAL STAB	CRACKED         	B	S		MJ7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	279MA					10297				WHILE PERFORMING A C-CHECK ON THIS AIRCRAFT, DISCOVERED THROUGH AN EDDY CURRENT INSPECTION THAT A VERTICAL CRACK EMITTIN	G FROM THE ATTACH BOLT TO OUTER EDGE, TYPE 'A' AS DEFINED IN SB F27/55-48, LOCATED IN RIGHT REAR FORWARD ATTACH FITTING 	LUG.  UPON CONFERENCING WITH EAGLE AIR, THE DETERMINATION WAS MADE TO REPLACE THE ENTIRE RIGHT REAR ATTACH FITTING.				2	H	7	2 	4T				A817    					 
1996082900367	19960829	00367	CE  	1996	8	29	96ZZZX4171       	1	19960812	G	3830	17000382	PUMP            			CESSNA	500   	S550        	2076607	CE  										TOILET FLUSH	MOTOR SEIZED    	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	299QS	7773 			1949	S5500099				CREW REPORTED TOILET WOULD NOT FLUSH.  FOUND MOTOR/PUMP ASSEMBLY LOCKED UP TIGHT.  THIS IS A COMMON OCCURRENCE AS THE PU	MP IMPELLER SWELLS AND JAMS IN THE PUMP HOUSING.  NEED TO USE A MOTOR/PUMP ASSEMBLY THAT IS RESISTANT TO 'BLUE WATER'.					1	L	7	2 	4F			RT	A22CE   					 
1996082900368	19960829	00368	CE  	1996	8	29	96ZZZX4172       	1	19960806	G	2430	M22759749	WIRE            			BEECH 	100   	B100        	1152919	CE  										LT/RT START/GEN	CRACKED         	B		A	VO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	300R	4793 				BE110				THE STARTER/GENERATOR 4-GAUGE WIRES THAT RUN FROM FIREWALL POWER CONNECTOR AND GENERATOR GROUND TO THE STARTER/GENERATOR	, WERE FOUND WITH CRACKED INSULATION.  THE CRACKS RUN PARALLEL WITH THE WIRE.  SOME OF THE CRACKS ARE OVER 3 INCHES IN L	ENGTH EXPOSING THE CENTER CONDUCTOR.  THE CRACKS ARE ON THE OUTSIDE OF BENDS AND IN STRAIGHT SECTIONS.  ON THE LEFT AND 	RIGHT ENGINES THE WIRE NUMBERS OF THE DEFECTIVE WIRES ARE K2D4, K2F4, P10A4, P10C4, P10E4, K17A4N, K17B4N, AND K17C4N.			1	L	7	2 	4T			 	A14CE   					 
1996082900369	19960829	00369	NM  	1996	8	29	96ZZZX4173       	1	19960814	G	5314	65564417	KEELBEAM        			BOEING	727   	727230      	1384080	NM  										BS 950	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	360PA					20676				WHILE PERFORMING A KEELBEAM INSPECTION DURING A C-CHECK, THE LT KEELBEAM WAS FOUND WITH SEVERE CORROSION OVER THE ENTIRE	 LENGTH OF THE BEAM MAINLY ON THE LT MOUNTING FLANGE AREA AND THE VERTICAL LEG.  AT ONE POINT BETWEEN BS 950F AND BS 970	, CORROSION HAD EATEN COMPLETELY THROUGH THE VERTICAL LEG OF THE BEAM CREATING A HOLE 5 INCHES IN LENGTH WITH CRACKS EXT	ENDING FROM THE ENDS OF THE HOLE.  NUMEROUS CRACKS WERE NOTED IN THE LOWER RADIUS OF THE VERTICAL LEG.  TYPES OF CORORSI	ON NOTED EXFOLIATION, INTERGRANULAR, SURFACE, AND SEVERE PITTING.  KEELBEAM WAS REMOVED AND REPLACED.		2	L	7	3 	4F				A3WE    					 
1996082900370	19960829	00370	SO  	1996	8	29	96ZZZX4174       	1	19960809	G	5755	400502	SPOILER         			GULSTM	G1159 	GIV         	3980115	SO  										LT INBOARD	SCRAPED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	399CC	3560 			063398897	1051				UPON COMPLETION OF MAJOR REFURBISH AND EXTERIOR PAINT, ACFT RETURNED TO EWR.  AFTER SEVERAL FLIGHTS, BOTH LEFT AND RIGHT	 INBOARD FLIGHT SPOILERS DAMAGED DUE TO INSUFFICIENT CLEARANCE BETWEEN SPOILER LEADING EDGE AND WING SKIN.  SUSPECT EXCE	SSIVE PAINT BUILD-UP ABSORBING REQUIRED CLEARANCE.				2	L	7	2 	4F			RT	A12EA   					 
1996082900371	19960829	00371	SO  	1996	8	29	96ZZZX4175       	1	19960809	G	5755	400502	SPOILER         			GULSTM	G1159 	GIV         	3980115	SO  										RT INBOARD	SCRAPED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	399CC	3560 			03598897	1051				UPON COMPLETION OF MAJOR REFURBISH AND EXTERIOR PAINT, ACFT RETURNED TO EWR.  AFTER SEVERAL FLIGHTS, BOTH LEFT AND RIGHT	 INBOARD FLIGHT SPOILERS DAMAGED DUE TO INSUFFICIENT CLEARANCE BETWEEN SPOILER LEADING EDGE AND WING SKIN.  SUSPECT EXCE	SSIVE PAINT BUILD-UP ABSORBING REQUIRED CLEARANCE.				2	L	7	2 	4F			RT	A12EA   					 
1996082900372	19960829	00372	SW  	1996	8	29	96ZZZX4176       	1	19960729	G	2720	53006515	BRACKET         			GULSTM	500   	500S        	0141107	SW  										RUDDER PULLEY	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	47RF	11068				3261				WHILE COMPLETING 200-HOUR FACTORY INSPECTION OF NOSE AREA, FOUND BOTH PULLEY BRACKETS CRACKED AT BEND RADIUS.  PULLEY IS	 FOR RUDDER CABLE AND IS SUPPORTED BY THESE TWO BRACKETS.  REPLACED CRACKED BRACKETS WITH SUPERCEDING PART NUMBERS FROM 	MANUFACTURER.  SUBMITTER SUGGESTS CLOSE INSPECTION OF BRACKETS AND REPLACMENT IF CRACKS ARE FOUND.  NO SERVICE BULLETIN 	EXISTS ON THESE BRACKETS.			1	H	7	2 	3O				6A1     					 
1996082900373	19960829	00373	SW  	1996	8	29	96ZZZX4177       	1	19960729	G	2720	53006516	BRACKET         			GULSTM	500   	500S        	0141107	SW  										RUDDER PULLEY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	47RF	11068				3261				WHILE COMPLETING 200-HOUR FACTORY INSPECTION OF NOSE AREA, FOUND BOTH PULLEY BRACKETS CRACKED AT BEND RADIUS.  PULLEY IS	 FOR RUDDER CABLE AND IS SUPPORTED BY THESE TWO BRACKETS.  REPLACED CRACKED BRACKETS WITH SUPERCEDING PART NUMBERS FROM 	MANUFACTURER.  SUBMITTER SUGGESTS CLOSE INSPECTION OF BRACKETS AND REPLACMENT IF CRACKS ARE FOUND.  NO SERVICE BULLETIN 	EXISTS ON THESE BRACKETS.			1	H	7	2 	3O				6A1     					 
1996082900375	19960829	00375	CE  	1996	8	29	96ZZZX4178       	1	19960724	G	7830	650161	SWITCH          	ROHR        	225012509   	BEECH 	MU300 	400A        	1155402	CE  										T/R DEPLOY	FAILED          	B			KI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	85CR	1220 				RK22				THRUST REVERSER CONTROL CIRCUIT BREAKER ON LEFT SIDE 'POPPED' WHEN REVERSERS WERE ACTUATED.  TROUBLESHOOTING DETERMINED 	THRUST REVERSER CONTROL BOX, P/N 45A5888656-5, HAD BURNT RESISTOR AND TRANSISTOR IN THE THROTTLE T/R LOCK HOLDING SOLENO	ID CIRCUITS.  T/R THROTTLE LOCK SOLENOID MEASURED AND FOUND RESISTANCE TO BE EXTREMELY LOW.  (P/N 18578-01.)  FURTHER TR	OUBLESHOOTING DETERMINED REVERSER DEPLOY LIMIT SWITCH TO HAVE STUCK CONTACTS THAT, CONSEQUENTLY, KEPT LOCK SOLENOID ACTU	ATED.		2	H	7	2 	4F			RT	A16SW   					 
1996082900604	19960829	00604	SW  	1996	8	29	96ZZZX4183       	1	19960413	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5000G					45163				PLAY IN EXCESS OF .025 INCH AT TWO PLACES.  SEE BELL MM L3, FIGURE 62.21.  AT TEAR DOWN FOUND BEARINGS AND SPACERS WORN.	  TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED.					1	G	7	1 	3U				H2SW    					 
1996082900605	19960829	00605	EU  	1996	8	29	96ZZZX4184       	1	19960701	G	7714	65201008	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	MALFUNCTION     	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5366Y	7655 			104	S782				TACHOMETER GAVE A FALSE READING OF 105 PERCENT PERCENT DURING FLIGHT.  REPLACED TACHOMETER.						1	G	7	2 	3U				H3EU    					 
1996090500127	19960905	00127	CE  	1996	9	5	96ZZZX4219       	1	19960807	G	2730	05130631	BRACKET         			CESSNA	172   	172F        	2072414	CE  										ELEV BELLCRANK	RIVETS PULLED   	B	S	A	B5XR	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			WP	07	8831U					17252740				INVESTIGATION FOR A SAGGING ELEVATOR WITH GUST LOCK IN PLACE, FOUND BRACKET ASSY MOUNTING RIVETS PULLED.  BRACKET ASSY I	S MOUNT POINT FOR ELEVATOR BELLCRANK.  WITH BELLCRANK BRACKET LOOSE, ELEVATOR CABLE GAINS SLACK.  LOSS OF EFFECTIVE ELEV	ATOR CONTROL HAD BEEN NOTED ON A PREVIOUS FLIGHT WHEN WIND SHEAR OCCURRED DURING LANDING.  REPLACEMENT PART IS SUPERCEDE	D BY A HEAVIER DASH 3 PART.  SUBMITTER RECOMMENDS AD CONSIDERATION.			1	H	7	1 	3O			NT	3A12    					 
1996090500128	19960905	00128	EA  	1996	9	5	96ZZZX4220       	1	19960723	G	5412	60137003162	FIREWALL        			CNDAIR	CL600 	CL6002B16   	1900305	EA  										PYLON RT LOWER	CHAFE/BURNED    	B		A	B5XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	309FX					5306				WHILE PERFORMING SB A604-27-002, THE RT LOWER PYLON PANEL HEAT SHIELD HAD EVIDENCE OF ELECTRICAL SHORT DAMAGE.  UPON FUR	THER INVESTIGATION, RT ENGINE GENERATOR WIRE HARNESS WAS FOUND NEARLY SEVERED FROM CHAFING ON THE HEAT SHIELD.  THE CLAM	P SECURING THE WIRE HARNESS WAS ROTATED FORCING THE HARNESS INTO THE EDGE OF THE HEAT SHIELD.  THE WIRE HARNESS AND HEAT	 SHIELD WERE REPLACED AND THE SECURING CLAMP WAS ROTATED 45 DEGREES TO CLEAR THE HEAT SHIELD.			2	L	7	2 	4F			RT	A21EA   					 
1996090500129	19960905	00129		1996	9	5	96ZZZX4221       	4	19960412	G	6122	3020166	SHAFT ASSY      	WOODWARD    	8210176     															PROP GOVERNOR	CRACKED         	B	S		OL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27			9025 		2346724C					FOUND CRACK ON GEROTOR FACE GOING OUT FROM KEYWAY CORNER.  CRACK EXTENDED THROUGH GEAR.																			 
1996090500130	19960905	00130	CE  	1996	9	5	96ZZZX4222       	1	19960731	G	5553	04310093	ATTACH FITITNG  			CESSNA	150   	152         	2071835	CE  										VERT STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	64971	4511 				15281505				WHILE C/W WITH AD 80-11-04 NUTPLATES, INSPECTION FOUND A .8750 INCH LONG CRACK ON THE LEFT FIN ATTACH FITTING (LOWER OUT	BOARD SIDE.)  BROKE IN HALF UPON REMOVAL.					1	H	7	1 	3O			NT	3A19    					 
1996090500131	19960905	00131	SO  	1996	9	5	96ZZZX4223       	1	19960804	G	2410	69113	BRACKET         			PIPER 	PA22  	PA22135     	7102206	SO  										ALTERNATOR	BROKEN          	C	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	1213C	3390 				221021				DURING ANNUAL INSPECTION, GENERATOR FELT LOOSE.  FURTHER INVESTIGATION REVEALED THE GENERATOR BRACKET HAD BROKEN.						1	H	7	1 	3O				1A6     					 
1996090500132	19960905	00132	EA  	1996	9	5	96ZZZX4224       	2	19960804	G	8510	69340	SUPPORT         			PIPER 	PA22  	PA22135     	7102206	SO  	LYC   	O290  	O290D2      	41506	EA  					START RING GEAR	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	1213C	3390 				221021	495821			DURING AN ANNUAL INSPECTION, A CRACK WAS NOTICED ON THE FACE OF THE STARTER RING SUPPORT ASSY.  A DYE PENETRANT TEST WAS	 DONE.  THE TEST REVEALED THE CRACK WAS HALF-WAY AROUND THE STARTER RING GEAR SUPPORT, BUT NOT THROUGH THE RING GEAR ITS	ELF.				1	H	7	1 	3O	3	O		1A6     	E229				 
1996090500133	19960905	00133	EU  	1996	9	5	96ZZZX4225       	1	19960701	G	7603	AN4864	CONTROL FORK    			WSK   	M18   	M18DROMADER 	9810102	EU  										THROTTLE	STRIPPED        	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	2047S					1200509				THROTTLE CONTROL THREADS STRIPPED OUT OF TERMINAL END (FORK).  THREAD DAMAGE INDICATED THE MALE END OF THROTTLE CONTROL 	WAS NOT TURNED INTO THREADED PORTION OF FORK TO THE INDICATOR HOLES.					1	L	7	1 	3O				A47EU   					 
1996090500135	19960905	00135		1996	9	5	96ZZZX4227       	4	19960808	G	6113	22501215	BACKPLATE       			CESSNA	182   	R182        	2072734	CE  										SPINNER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	6347T					R18201990				INSPECTION FOUND PROPELLER SPINNER BULKHEAD CRACKED.  SUBMITTER STATED REPLACING THESE BULKHEADS IS AN ANNUAL OCCURRENCE	.  BOTH HALVES EACH TIME.  SUSPECT POOR DESIGN, SPINNER FLEXES FORE AND AFT, NEED A RIGID FRONT PLATE OR .25 INCH BACKPL	ATE.  TT AIRFRAME:  2,450 HOURS.  TT THIS PART:  100 HOURS.				1	H	7	1 	3O			RT	3A13    					 
1996090500136	19960905	00136	GL  	1996	9	5	96ZZZX4228       	1	19960804	G	3250	1945330	COLLAR          		194391      	BLANCA	17    	1731A       	1220435	GL  										NLG	WELD CRACKED    	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	4205B	1997 				7532146				WHILE PUTTING A HAND TOW BAR ON THE NOSE FORK, NOTICED PAINT FLAKING OFF THE FRONT STEERING COLLAR.  REMOVED ALL THE PAI	NT OFF THE COLLAR AND NOTICED THE WELD WAS CRACKED FROM SIDE TO SIDE.  P/N 19453-30. TT:  1,996.6 HOURS.					1	L	7	1 	3O				A18CE   					 
1996090500137	19960905	00137	CE  	1996	9	5	96ZZZX4229       	1	19960701	G	5540	AG752001	HORN            			BOEING	75    	A75N1       	1380134	CE  										RUDDER	FAILED          	G	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	58712					75341				RUDDER HORN FAILURE.  CORROSION HAD DETERIORATED THE WALL THICKNESS OF THE RUDDER HORN.  ALSO, RUST INDICATED THE HORN W	AS CRACKED PRIOR TO FAILURE.					1	Q	7	1 	3R				A743    					 
1996090500138	19960905	00138	CE  	1996	9	5	96ZZZX4230       	1	19960821	G	5320	00244000029	DOUBLER         			BEECH 	36    	A36         	1151604	CE  										FS 272	CRACKED         	B	L		NN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	8165Q	2484 				E5292				DURING INSPECTION OF EMPENNAGE, CRACK WAS DISCOVERED IN THE DOUBLER LOCATED JUST FORWARD OF STA 272, BULKHEAD.  THE CRAC	K WAS IN THE RADIUS OF CUT-OUT AREA OF DOUBLER ON THE LEFT SIDE.  INSPECTION OF OTHER AIRCRAFT IN THE FLEET FOUND 5 OTHE	RS WITH THE SAME DEFECTS, SERIAL NUMBERS RANGED FROM E2592 TO E2667, TOTAL TIME FROM 2,300 - 2,600 HOURS.				1	L	7	1 	3O				3A15    					 
1996090500139	19960905	00139		1996	9	5	96ZZZX4231       	4	19960802	G	3410	B904	HOSE            			CESSNA	150   	A152        	2071836	CE  										INSTRUMENTS	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	152J					A1520963				1981 - 1,425 HOURS TT.  TOTAL DETERIORATION OF OUTER LAYER, REINFORCING THREADS, AND INNER LAYER.  HOSE IS OF A PLASTIC 	TYPE, APPEARS TO BE ORIGINAL.  REPLACED WITH AEROQUIP 306 INSTRUMENT HOSE.					1	H	7	1 	3O				3A19    					 
1996090500140	19960905	00140	EA  	1996	9	5	96ZZZX4232       	2	19960821	G	8520	LW17060	CRANKSHAFT      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					FLANGE	CRACKED         	D	S			A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	03	84652	6047 				288216062	L947639A			THE AIRCRAFT COMPLETED AN UNSCHEUDLED ON AIRPORT EMERGENCY LANDING DUE TO OIL SPRAYING ON THE WINDSHIELD.  THE CRANKSHAF	T WAS FOUND CRACKED AT THE RADIUS BY THE PROPELLER FLANGE.  (APPROXIMATELY 1.75 INCH VISIBLE.)					1	L	7	1 	3O	3	O		2A13    	E274				 
1996090500141	19960905	00141		1996	9	5	96ZZZX4233       	4	19960805	G	3416	D120P2T	DIGITIZER       	TRANSCAL    		SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										ALTIMETER	STATIC LEAK     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	5546A				70279	1241				ALTITUDE DIGITIZER HAS PLASTIC GLASS FILLED NYLON HEADER.  THE STATIC INLET PORT CRACKED CAUSING LEAK.  SUBMITTER STATED	 THIS IS A RECURRING PROBLEM WITH THIS ITEM WHICH WAS ORIGINALLY METAL.					1	L	7	1 	3O			RT	A51EU   					 
1996090500142	19960905	00142	CE  	1996	9	5	96ZZZX4234       	1	19960801	G	2820		LINES           			CESSNA	180   	180H        	2072618	CE  										DOOR POST	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	2461F					18051663				IN LT DOOR POST, THE AILERON CABLE WAS RUBBING ON THE FUEL LINE.  UNDER THE FLOOR, THE FUEL LINES WERE CHAFING ON THE BU	LKHEADS WHERE THEY PENETRATED.  SUBMITTER RECOMMENDS CLOSE INSPECTION OF THESE AREAS WITH A MIRROR AND LIGHT.  INTERIOR 	PANELS MUST BE MOVED TO PROPERLY INSPECT DOOR POST AREAS. RECOMMENDED SOLUTION IS INSTALLATION OF RUBBER GROMMETS OR CHA	FE SEAL AND/OR SECURING THE LINES TO PREVENT MOVEMENT AGAINST AIRFRAME.			1	H	7	1 	3O				5A6     					 
1996090500143	19960905	00143	CE  	1996	9	5	96ZZZX4235       	1	19960625	G	2750	51152532	CAM ASSY        			CESSNA	402   	402C        	207590R	CE  										FLAP ACTUATOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	2717B					402C0221				CAM WAS LOOSE ON SHAFT.  FAILED TO LIMIT FLAP TRAVEL TO THE DOWN SIDE AND BROKE DRIVE CHAIN TO FLAP CABLE.  TAT:  12,176	.3 HOURS.  LAST INSPECTED ON 12,020.5 HRS, CHECK NR 2.  PROGRESSIVE CARE ITEM NR 16.  CAM ITSELF NOT SPECIFICALLY CALLED	 OUT IN INSPECTION.				1	L	7	2 	3O				A7CE    					 
1996090500144	19960905	00144	SO  	1996	9	5	96ZZZX4236       	1	19960724	G	2510	510232827	BRACKET         	GRUMAN      	5102349501  	GULSTM	AA5   	AA5B        	3960105	SO  										PILOT SEAT	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	28618	3400 				AA5B0707				DURING GROUND RUN-UP, THE SEAT BRACKETS FAILED ALMOST SIMULTANEOUSLY ALLOWING THE PILOT'S SEAT BACK TO FALL INTO THE REA	R SEAT AREA.  FAILURE APPEARS TO BE BENDING FATIGUE, A FLEXURE OF THESE ALUMINUM BRACKETS IS NOTED WHEN THE TOP OF THE S	EAT IS PULLED AFT (PASSENGER EXITING THE AIRCRAFT).  THE LATER MODEL, AG5-B, HAS STEEL BRACKETS.  THERE WAS NO EVIDENCE 	OF A PREVIOUS CRACK PRIOR TO FAILURE.			1	L	7	1 	3O				A16EA   					 
1996090500145	19960905	00145	SO  	1996	9	5	96ZZZX4237       	1	19960724	G	2510	510232828	BRACKET         	GRUMAN      	5102349501  	GULSTM	AA5   	AA5B        	3960105	SO  										PILOT SEAT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	28618	3400 				AA5B0707				DURING GROUND RUN-UP, THE SEAT BRACKETS FAILED ALMOST SIMULTANEOUSLY ALLOWING THE PILOT'S SEAT BACK TO FALL INTO THE REA	R SEAT AREA.  FAILURE APPEARS TO BE BENDING FATIGUE, A FLEXURE OF THESE ALUMINUM BRACKETS IS NOTED WHEN THE TOP OF THE S	EAT IS PULLED AFT (PASSENGER EXITING THE AIRCRAFT).  THE LATER MODEL, AG5-B, HAS STEEL BRACKETS.  THERE WAS NO EVIDENCE 	OF A PREVIOUS CRACK PRIOR TO FAILURE.			1	L	7	1 	3O				A16EA   					 
1996090500149	19960905	00149		1996	9	5	96ZZZX4241       	4	19960122	G	2210	P2110311	SWITCH          		STD9891     	BEECH 	B300  	B300        	1159232	CE  										AUTOPILOT	FROZEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4S					FL107				ON PRE-FLIGHT, FOUND AUTOPILOT DISCONNECT SWITCH FROZEN.  THE SPRING LOADED PUSH BUTTON IS FIXED OR FROZEN SOLID.  SUBMI	TTER STATED EVEN BEFORE IT FROZE, IT FELT CATCHY OR SCRATCHY WHEN BUTTON WAS DEPRESSED.					2	L	7	2 	4T			RT	A24CE   					 
1996090500150	19960905	00150	GL  	1996	9	5	96ZZZX4242       	3	19960723	G	6114		CYLINDER        													HARTZL	HCB3R	HCB3R304    	GL  	PROP PISTON	DENTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03			200  					EMA054		PROPELLER WAS BROUGHT BACK TO SHOP AFTER OVERHAUL BECAUSE HIGH RPM COULD NOT BE ESTABLISHED UNTIL TAKEOFF ROLL AND TAIL 	WAS LIFTED.  AT DISASSEMBLY, THE CYLINDER WAS FOUND TO HAVE A DENT WHICH CAUSED THE PISTON TO HANG UP AND NOT ALLOW THE 	PROP TO GO TO LOW PITCH POSITION.  WHEN CENTRIFIGAL TWISTING MOMENT WAS HIGH ENOUGH, PISTON WOULD GO PAST THE DENT BY FO	RCE.  DURING INSTALLATION, THE MOUNTING NUT HAD BEEN DAMAGED BECAUSE OF USE OF IMPROPER INSTALLATION TOOLS.  THIS CAUSED	 THE DENT ON THE CYLINDER AND ALSO DESTROYED THE MOUNTING NUT.												5	C	P28EA	 
1996090500351	19960905	00351	NE  	1996	9	5	96ZZZX4273       	1	19960709	G	6210	7615009100051	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R LE STRIP	DEFECTIVE       	B		A	ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31211	2487 			A08601079	760225				FOUND APPROXIMATELY 8.50 INCH SECTION OF MAIN ROTOR BLADE NICKLE LEADING EDGE STRIP MISSING APPROXIMATELY 48 INCHES FROM	 THE TIP CAP.  THIS AREA HAD A CRACK IN THE LEADING EDGE AND IT WAS REPAIRED PER THE COMPOSITE REPAIR MANUAL.  SUSPECT D	ISBONDING UNDER THE STRIP FROM CRACK.  RECOMMEND A BETTER PROCEDURE FOR SEALING CRACKS IN LEADING EDGE ABRASION STRIPS.				1	G	7	2 	3U				H1NE    					 
1996090500352	19960905	00352	SW  	1996	9	5	96ZZZX4274       	1	19960730	G	6230	206010443001	DUPLEX BEARING  			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	FAILED          	B		A	ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2654	546  			18490	45482				SWASHPLATE REMOVED DUE TO BINDING AND ROUGHNESS.  ON DISASSEMBLY, FOUND DUPLEX BEARING FLAKING AND CHIPPING.  BEARING CA	GE HAS SEPARATED AND CAUSED DAMAGE TO INNER RING OF SWASHPLATE.  SUBMITTER STATED THIS IS THE THIRD BEARING IN LAST 12 M	ONTHS WITH LESS THAN 1,000 HOURS.				1	G	7	1 	3U				H2SW    					 
1996090500353	19960905	00353	SW  	1996	9	5	96ZZZX4275       	1	19960716	G	6320	206040032011	DUPLEX BEARING  			BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	FAILED          	B			ZV1R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	5759M	703  			50980	45555				TRANSMISSION MAKING METAL AT 702.5 TSO.  FOUND DEFECTIVE LOWER DUPLEX BEARING.  BEARING HAD 702.5 HOURS SINCE NEW.						1	G	7	1 	3U				H2SW    					 
1996090500664	19960905	00664	EU  	1996	9	5	96ZZZX4276       	1	19960513	G	2432	16061	BATTERY         	SAFT        		SNIAS 	350   	AS350B2     	8680813	EU  										RT BAG COMPT	SHORTED         	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	07	6103X	900  				2723				A BATTERY TEMP LIGHT ILLUMINATED DURING FLIGHT.  EMERGENCY PROCEDURES INITIATED.  FOUND ACFT BATTERY SHORTED.  A SECONDA	RY LEAD IS ATTACHED TO ACFT BATTERY USING A METAL TAB LUG WHICH IS CONNECTED TO THE WIRE END CONNECTOR USING A NUT AND B	OLT WHICH IS PROTECTED BY HEAT SHRINK INSULATOR.  THIS NUT AND BOLT CONNECTING THE WIRE END CONNECTOR AND TAB LUG WEARS 	THROUGH THE INSULATION AND CONTACTS THE NICAD BATTERY'S CASE SHORTING THE BATTERY AND OVERHEATING IT.  REPLACED THE WIRE	 TERMINAL CONNECTOR AND TAB LUG WITH A SINGLE APPROPRIATE SIZE WIRE AND TERMINAL.  REPAIRED 2 OTHER ACFT WITH SAME PROBL	EM.	1	G	7	1 	3U				H9EU    					 
1996090500665	19960905	00665	WP  	1996	9	5	96ZZZX4277       	1	19960729	G	6710	10064603	SWITCH          			HUGHES	369   	369E        	4470707	WP  										CYCLIC TRIM	DEFECTIVE       	D				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	503MP					0414E				PILOT'S CYCLIC TRIM SWITCH FREQUENTLY BECOMES INTERMITTENT.  PILOT FIRST REPORTS A STIFF CYCLIC.  SOMETIMES TRIM RUNS AW	AY IN ANY ONE OF FOUR DIRECTIONS.  THIS CAUSES MUCH STICK FORCE.  FLIGHT MUST BE TERMINATED DUE TO FATIGUE.  RETURN TO H	OME BASE.  AVERAGE LIFE OF SWITCH IS 150 TO 250 HOURS.  TEN SWITCHES HAVE BEEN CHANGED IN LAST SIX MONTHS.				1	G	7	1 	3U				H3WE    					 
1996090500666	19960905	00666	WP  	1996	9	5	96ZZZX4278       	1	19960813	G	6710	A21810064603	SWITCH          			HUGHES	369   	369E        	4470707	WP  										CYCLIC TRIM	FAILED          	D				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	504MP	388  				0523E				PILOT REPORTED NO TRIM IN FORE/AFT DIRECTION.  DURATION OF FLIGHT HAD TO FIGHT HIGH FORE/AFT STICK FORCES.  SUBMITTER ST	ATED A COMMON PROBLEM, SWITCH IS TOO LIGHT-DUTY FOR APPLICATION.					1	G	7	1 	3U				H3WE    					 
1996090500667	19960905	00667	SW  	1996	9	5	96ZZZX4279       	1	19960810	G	6520	476452691	SHAFT VENY      		476400751   	BELL  	47    	47G5        	1181032	SW  										T/R GEARBOX	PLUGGED         	B		A	OUGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17	7885S				A133111	7873				RECEIVED NEW REPLACMENT PART FROM BELL.  DURING RECEIVING INSPECTION, NOTICED .1250 INCH HOLE DRILLED IN SHAFT TO VENT G	EARBOX WAS PLUGGED SOLID WITH GRAY COATING THAT WAS APPLIED TO INTERIOR OF SHAFT FOR CORROSION PROTECTION.  SUBMITTER ST	ATED THIS COULD POSSIBLY CAUSE OIL LEAKS IN SERVICE.				1	G	7	1 	3O				2H3     					 
1996090500668	19960905	00668	EU  	1996	9	5	96ZZZX4280       	1	19960717	G	6322	1090401211	BOLT            		A090600109  	AGUSTA	A109  	A109A2      	0260120	EU  										OIL COOLER SHAFT	SHEARED         	B			KUVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	169BH	1705 				6290				ON DAILY INSPECTION, MECHANIC NOTICED EXCESSIVE MOVEMENT OF OIL COOLER DRIVESHAFT UNDER ENGINE.  FOUND BOLT TYING FORWAR	D OUTPUT COUPLING TO AFT COUPLING THROUGH ENGINE.  PTO GEARSHAFT SHEARED FLUSH WITH BOTTOM OF RETENTION NUT.  COTTER PIN	 WAS STILL INSTALLED IN BOLT END THROUGH-NUT.  OIL COOLER SHAFT CONTAINED AFT ADAPTER IN GEARBOX, SO DID NOT FAIL COMPLE	TELY.  SUBMITTER SUGGESTS BOLT AGE AND/OR IMPROPER INSTALLATION CAUSED BOLT TO FAIL.			1	G	7	2 	3U				H7EU    					 
1996090500669	19960905	00669	SW  	1996	9	5	96ZZZX4281       	1	19960805	G	6710	A21810064603	SWITCH          	GUARDIAN    		HUGHES	500N  	500N        	3027374	SW  										CYCLIC TRIM	STICKING        	D				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	527FB	286  				LN007				SWITCH STICKS IN ALL POSITIONS AFTER 1 HOUR OF FLIGHT.  IN-FLIGHT CAUSES TRIM TO RUN AWAY OR BURN UP TRIM MOTOR.  SWITCH	 PLATING COMES OFF AND BINDS TRIGGER.					1	G	7	1 	3U			NC	H3WE    					 
1996090500670	19960905	00670	WP  	1996	9	5	96ZZZX4282       	1	19960729	G	6320	369D25100901	TRANSMISSION    			HUGHES	369   	369E        	4470707	WP  										TACHOMETER DRIVE	SEAL LEAK       	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	503MP	271  				0414E				ROTOR TACHOMETER GEN SEAL LEAKS INTO OIL COOLER BLOWER INLET, AIR/OIL MIX TURE GETS DISTRIBUTED OVER HOT 250C20R ENGINE.	  REMAINDER OF AIR OIL MIXTURE ENTERS HEATER DUCTS.  WHEN PILOT SELECTS HEATER, HAZARDOUS AIR/OIL MIXTURE FILLS COCKPIT.	  THIS PAD SHOULD HAVE A SCUPPER DRAIN LINE OVERBOARD LIKE THE 2 OTHER SEALS IN SAME PROXIMITY.				1	G	7	1 	3U				H3WE    					 
1996090500672	19960905	00672	SW  	1996	9	5	96ZZZX4284       	1	19960821	G	3340	A469B	LAMP            	WHELEN      	A470        	BELL  	206   	206L1       	1182107	SW  										STROBE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	911SA	20   				45383				ANTI-COLLISION LIGHT FAILED, FOUND LAMP ASSY, A469B, INOPERATIVE.  THIS IS FOURTH LAMP TO FAIL, ALL WITH LESS THAN 20-30	 FLIGHT HOURS.					1	G	7	1 	3U				H2SW    					 
1996090500673	19960905	00673		1996	9	5	96ZZZX4285       	1	19960730	G	2822	2B69	PUMP            	AIRBORNE    																FUEL BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					10E8					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996090500674	19960905	00674		1996	9	5	96ZZZX4286       	1	19960810	G	2822	2B663	PUMP            	AIRBORNE    																ARMATURE	OUT OF BALANCE  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23					6AD96					INSPECTION FOUND PUMP ARMATURE OUT OF BALANCE.																			 
1996090500675	19960905	00675	EA  	1996	9	5	96ZZZX4287       	2	19960814	G	8530	LW11634	VALVE           		LW11633     	PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 CYL EXH	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	33BA		200  		511561	3879A0021	L1598715			EXHAUST VALVE FAILURE, 200 HOURS AFTER CYLINDER OVERHAUL.  YELLOW TAG INDICATES CYLINDER WAS REBUILT USING SERVICEABLE P	ARTS.  REBUILDER WAS CONTACTED, BUT COULD NOT DETERMINE TOTAL NUMBER OF HOURS ON VALVE WHEN INSTALLED. LYC SB NR 301B ST	ATES EXHAUST VALVES SHOULD NOT BE RE-USED UNLESS THEY HAVE BEEN RECENTLY INSTALLED AND MEET INSPECTION CRITERIA.				1	L	7	1 	3O	3	O		A18SO   	E223				 
1996090500676	19960905	00676	SO  	1996	9	5	96ZZZX4288       	1	19960520	G	3211	452368	BEARING         			PIPER 	PA28  	PA28R200    	7102811	SO  										RT/LT MLG	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	33075	4888 				28R7535116				FOUND BOTH MLG'S COULD BE MOVED SIDE TO SIDE BECAUSE OF PLAY IN THE TRUSS BEARING (ROD END).  SUSPECT LACK OF REGULAR LU	BRICATION AND HIGH TOTAL TIME.					1	L	7	1 	3O				2A13    					 
1996090500678	19960905	00678	SO  	1996	9	5	96ZZZX4290       	2	19960730	G	8530	22250	GASKET          			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					INDUCTION ELBOW	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	3707R	391  				17255507	025665R			ENGINE REPORTED TO RUN ROUGH AT LOW RPM'S AND HAVE POPPING SOUND.  TROUBLESHOOTING FOUND THAT CYLINDERS', NR 1, NR 3, AN	D NR 5, INDUCTION ELBOW GASKETS HAD BEEN SUCKED IN.  ENGINE HAS 391.0 HOURS SINCE FACTORY REMANUFACTURE.  ATTACHING HARD	WARE WAS FOUND TO BE PROPERLY TORQUED.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1996090500679	19960905	00679	SO  	1996	9	5	96ZZZX4291       	1	19960719	G	2810	1609700	FUEL CAP        			PIPER 	PA23  	PA23250     	7102308	SO  										RT OTBD	NOT SECURE      	H				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			NE	05	40571					277405313				DURING TAKEOFF, THE RIGHT FUEL CAP COVER OPENED AND FUEL STARTED COMING OUT.  PILOT RETURNED TO SECURE THE FUEL CAP, AND	 ADD APPROXIMATELY 10 GALLONS OF FUEL.					1	L	7	2 	3O				1A10    					 
1996090500680	19960905	00680	SO  	1996	9	5	96ZZZX4292       	2	19960201	G	8530	646100A1	CYLINDER        			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					SPARK PLUG HOLE	CRACKED         	B	S		APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	41SA	1449 				4040023	276274R			DURING A ROUTINE ENGINE COMPRESSION TEST, CYLINDER NR 1 SHOWED 10/80.  A VISUAL INSPECTION CONFIRMED A CRACK EMANATING F	ROM THE LOWER SPARK PLUG HOLE TO THE COOLING FINS, APPROXIMATELY 1.50 INCHES LONG.  THIS IS A RECURRING ITEM, OPERATOR K	NOWS OF AT LEAST 12 OCCURRENCES OVER THE LAST 2 YEARS.				1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996090500682	19960905	00682	CE  	1996	9	5	96ZZZX4294       	1	19960808	G	2820	51001107	LINE            			CESSNA	421   	421C        	2076016	CE  										RT TANK	HOLE CHAFED     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	421RL		3437 			421C1081				WHILE C/W AD 95-09-13, THE FUEL LINE GOING TO THE FORWARD RIGHT WING INLET VALVE WAS FOUND NOT CENTERED GOING THROUGH A 	BULKHEAD THROUGH-HOLE.  REMOVING THE LINE, A HOLE WAS FOUND CHAFED THROUGH.  IF THE FUEL LEVEL HAD GONE BELOW THIS LINE,	 A FUEL STARVATION WOULD HAVE DEVELOPED.  A NEW LINE WAS INSTALLED AND PROPER CLEARANNCE WAS ESTABLISHED.  THIS AREA SHO	ULD BE CHECKED ANY TIME THE FUEL TANKS ARE OPENED.			1	L	7	2 	3O				A7CE    					 
1996090500683	19960905	00683	SW  	1996	9	5	96ZZZX4295       	1	19960729	G	5410	26002024	FRAME           			GULSTM	500   	500S        	0141107	SW  										RT NACELLE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	47RF	11068				3261				WHILE COMPLETING 100-HOUR FACTORY INSPECTION, NOTED CORROSION BUILD-UP AFT OF EXHAUST ON TOP OF RT NACELLE.  REMOVED COR	ROSION AND FOUND 1 INCH HOLE.  BOTH SKIN AND FRAME HAD BEEN EATEN THROUGH.  REPLACED FRAME WITH NEW AND C/W RIVETED PATC	H REPAIR ON NACELLE SKIN.  SUGGEST PEROXIDE CLEANING INSPECTION AND PAINTING OF THIS AREA.				1	H	7	2 	3O				6A1     					 
1996090500684	19960905	00684	NM  	1996	9	5	96ZZZX4296       	1	19960810	G	7160		HINGE           			PIPER 	PA60  	PA60600     	7106001	NM  										ALTERNATE AIR	SEPARATED       	D		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			EA	13	600VF					600757806122				IN-FLIGHT, THE THROTTLE COULD NOT BE REDUCED BELOW 22 INCHES OF MANIFOLD PRESSURE DUE TO A RESTRICTION IN THE FUEL INJEC	TOR SERVO BUTTERFLY.  THE BLOCKAGE WAS THE ALTERNATE AIR DOOR THAT HAD SEPARATED FROM THE HINGE AND WENT DOWN LINE IN TH	E INDUCTION SYSTEM TO BLOCK THROTTLE.  FURTHER INVESTIGATION SHOWS THE AEROSTARS OWNERS GROUP HAD IDENTIFIED THIS AS AN 	ONGOING PROBLEM IN THE 600 NON-TURBO MODELS ONLY.  RECOMMEND A 50-HOUR INSPECTION OF ALTERNATE AIR DOORS.			1	M	7	2 	3O			RT	A17WE   					 
1996090500685	19960905	00685	CE  	1996	9	5	96ZZZX4297       	1	19960808	G	3340	08701321	LANDING LIGHT   	GRIMES      	G3600A1     	CESSNA	310   	310R        	2074245	CE  										LT WING	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	6181C	1    			94902	310R1320				PART FAILED AFTER 2 CYCLES.  LIGHT WOULD NOT RETRACT.  FOUND INTERNAL SWITCH LINKAGE LOOSE.  SUSPECT MICROSWITCHES INOPE	RABLE DUE TO POOR WORKMANSHIP AND PARTS MISALIGNED.					1	L	7	2 	3O				3A10    					 
1996090500686	19960905	00686	EU  	1996	9	5	96ZZZX4298       	1	19960815	G	7603	T67G150525	PUSH ROD        			SLNSBY	T67   	T67M260     	8323006	EU  										LT SIDE COCKPIT	BROKEN          	B		A	UNER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	3104L	580  				2164				THE AIRCREW DECLARED AN IN-FLIGHT EMERGENCY AFTER ACFT ENGINE WOULD NOT RESPOND TO THROTTLE APPLICATION FROM IP'S REMOTE	 THROTTLE HANDLE AND LINKAGE LOCATED ON LT SIDE OF COCKPIT.  REMOTE THROTTLE LEVER/HANDLE IS ATTACHED TO LT SIDE OF AIRF	RAME.  IT IS ATTACHED TO THE THROTTLE PUSH ROD, PN T67G-150-525.  THIS PUSH ROD IS A STEEL TUBE WHICH HAS A M5 THREAD SC	REW WELDED TO THE STEEL ROD.  A FORK-END TRAVELS ON THE THREAD FOR ADJUSTMENT.  THE THREAD BREAKS NEAR OR AT THE WELD AS	 OPPOSING FORCES ARE PLACED ON THE TWO THROTTLE LEVERS AND LINKAGE.  THIS IS THE SECOND OCCURRENCE.  A ONE-TIME INSPECTI	ON REVEALED SEVEN BENT THREADED ROD ENDS.  THE THROTTLE LINKAGE MAY NEED A STOP INSTALLED ON THE REMOTE THROTTLE LEVER.	1	L	7	1 	3O			NT	A73EU   					 
1996090500687	19960905	00687	EU  	1996	9	5	96ZZZX4299       	1	19960710	G	7603	T67G150525	PUSH ROD        			SLNSBY	T67   	T67M260     	8323006	EU  										LT SIDE COCKPIT	BROKEN          	B			UNER	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	3172R	314  				2193				THE AIRCREW DECLARED AN IN-FLIGHT EMERGENCY AFTER ACFT ENGINE WOULD NOT RESPOND TO THROTTLE APPLICATION FROM IP'S REMOTE	 THROTTLE HANDLE AND LINKAGE LOCATED ON LT SIDE OF COCKPIT.  REMOTE THROTTLE LEVER/HANDLE IS ATTACHED TO LT SIDE OF AIRF	RAME.  IT IS ATTACHED TO THE THROTTLE PUSH ROD, PN T67G-150-525.  THIS PUSH ROD IS A STEEL TUBE WHICH HAS A M5 THREAD SC	REW WELDED TO THE STEEL ROD.  A FORK-END TRAVELS ON THE THREAD FOR ADJUSTMENT.  THE THREAD BREAKS NEAR OR AT THE WELD AS	 OPPOSING FORCES ARE PLACED ON THE TWO THROTTLE LEVERS AND LINKAGE.  THIS IS THE SECOND OCCURRENCE.  A ONE-TIME INSPECTI	ON REVEALED SEVEN BENT THREADED ROD ENDS.  THE THROTTLE LINKAGE MAY NEED A STOP INSTALLED ON THE REMOTE THROTTLE LEVER.	1	L	7	1 	3O			NT	A73EU   					 
1996090500688	19960905	00688		1996	9	5	96ZZZX4300       	1	19960807	G	2822	1D217	ARMATURE        	AIRBORNE    																FUEL BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					1AA35					ARMATAURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996090500689	19960905	00689		1996	9	5	96ZZZX4301       	1	19960820	G	2822	2B738	ARMATURE        	AIRBORNE    																FUEL BOOST	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					1AD44					PUMP MAY HAVE BEEN RUN DRY CAUSING SEVERE DAMAGE TO ARMATURE.																			 
1996090500690	19960905	00690		1996	9	5	96ZZZX4302       	1	19960820	G	2822	2B738	PUMP            	AIRBORNE    																FUEL BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					1AD71					PUMP FAILURE.  PUMP WAS POSSIBLY RUN DRY CAUSING DAMAGE TO ARMATURE.																			 
1996090500691	19960905	00691		1996	9	5	96ZZZX4303       	1	19960807	G	2822	1D217	ARMATURE        	AIRBORNE    																FUEL PUMP	FAILURE         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					3AH31					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996090500692	19960905	00692		1996	9	5	96ZZZX4304       	1	19960820	G	2822	1B58	ARMATURE        	AIRBORNE    																FUEL SYSTEM	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					5C32					PUMP OVERHEATED, MAY HAVE BEEN RUN DRY CAUSING DAMAGE TO ARMATURE																			 
1996090500693	19960905	00693		1996	9	5	96ZZZX4305       	1	19960820	G	2822	2B664	ARMATURE        	AIRBORNE    																FUEL PUMP	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					2AK61					ARMATURE SHAFT HAS DAMAGE TO IT.  GROOVE WORN IN BY SPACER AND OTHER WEAR MARKS ON SHAFT.																			 
1996090500694	19960905	00694		1996	9	5	96ZZZX4306       	1	19960807	G	2822	1D217	ARMATURE        	AIRBORNE    																FUEL PUMP	OUT OF BLAANCE  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					11AH66					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996090500695	19960905	00695		1996	9	5	96ZZZX4307       	1	19960820	G	2822	2B738	BRUSH BLOCK     	AIRBORNE    																FUEL PUMP	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					1AD44					OVERHEATING OF THE PUMP CAUSED DAMAGE TO THE BRUSH BLOCK.																			 
1996090500696	19960905	00696		1996	9	5	96ZZZX4308       	1	19960808	G	2822	2B663	ARMATURE        	AIRBORNE    																FUEL PUMP	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					9E517					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996090500697	19960905	00697	CE  	1996	9	5	96ZZZX4309       	1	19960806	G	2730	05130631	BRACKET         			CESSNA	172   	172G        	2072420	CE  										CENTER FUSELAGE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	1130F					17254725				ELEVATOR BELLCRANK BRACKET LOCATED UNDER FLOOR AT CENTER FUSELAGE FS 27, BROKEN AT ATTACHMENT BULKHEAD.  REPLACEMENT PAR	T IS CONSTRUCTED OF HEAVIER MATERIAL AND IS A DASH 3 PART NUMBER.					1	H	7	1 	3O			NT	3A12    					 
1996090500698	19960905	00698	SO  	1996	9	5	96ZZZX4310       	1	19960814	G	3340	3012905	LIGHT           	GRIMES      		PIPER 	PA31  	PA31350     	7103110	SO  										RECOG LIGHT	CONTACT BURNS   	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3582X					318052105				ELECTRICAL CONTACT BUTTON FOR LAMP CENTER ELECTRODE IS INADEQUATE TO SUPPORT HIGH HEAT GENERATED BY HIGH AMPERAGE FLOW T	HROUGH LAMP.  CONTACT BUTTON BURNS AWAY REQUIRING REPLACEMENT OF (EXPENSIVE) LIGHT BASE ASSEMBLY.  MULTIPLE FLEET FAILUR	ES.				1	L	7	2 	3O				A20SO   					 
1996090500700	19960905	00700	CE  	1996	9	5	96ZZZX4312       	1	19960807	G	7602		VERNIER CONTROL 			CESSNA	172   	R172E       	2072413	CE  										MIXTURE	FAILED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	01	7898N					R1720289				WHILE IN CRUISE FLIGHT, AN ATTEMPT TO LEAN THE MIXTURE WAS MADE.  AFTER ABOUT THREE TURNS OF THE VERNIER CONTROL KNOB, A	 PUSH WAS FELT AND CONTROL WENT TO IDLE CUT-OFF.  ATTEMPTS TO PUSH THE CONTROL IN FAILED.  AN AIRPORT LANDING WAS MADE W	ITH PARTIAL POWER OBTAINED.  AFTER LANDING, THE CONTROL WAS CYCLED, A CLICKING WAS HEARD, AND NORMAL OPERATION HAD RETUR	NED.  THE CONTROL WAS REPLACED WITH A NEW PART.  THE FAILED CONTROL WAS SENT TO CESSNA FOR EVALUATION.  THE CONTROL HAD 	FAILED INTERNALLY.  ANY BINDING OF AN ENGINE CONTROL SHOULD BE INVESTIGATED AND CORRECTED PRIOR TO FURTHER FLIGHT.  **S/	D** CESSNA'S EVALUATION DETERMINED THAT THE CONTROL WAS NOT P/N S1818-1, NOR WAS THE VENDOR A CESSNA APROVED SUPPLIER.	1	H	7	1 	3O				3A17    					 
1996090500701	19960905	00701	EA  	1996	9	5	96ZZZX4313       	2	19960812	G	8550	CH48111	FILTER          	CHAMPION    		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE OIL	LEAKING         	D	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	15	99604	63   			F11F181	172766477				WHEN OIL FILTER WAS REMOVED, MECHANIC NOTICED THE CAN AREA OF THE FILTER TURNED, BUT THE ATTACH MOUNTING (CRIMPED FLANGE	 END BRACKET) STAYED STATIONARY.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996090500702	19960905	00702	SO  	1996	9	5	96ZZZX4314       	2	19960809	G	8550		ADAPTER         			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					OIL FILTER	NUT LOOSE       	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	35945	201  				U20602819	553686			DURING COMPLIANCE OF AD 96-12-22, OIL FILTER ADAPTER INSPECTION, FOUND RETAINING NUT TORQUE LOOSE.  REMOVAL OF OIL FILTE	R ADAPTER ASSY REVEALED BOTTOM THREAD OF ADAPTER ASSY CRACKED.  THIS PART WAS INSTALLED NEW ON 6-6-95 DUE TO CRACKED THR	EADS DURING C/W CESSNA SEB 93-1R, PARAGRAPH B2 (600 HRS INSP).				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996090500703	19960905	00703	EA  	1996	9	5	96ZZZX4315       	2	19960703	G	8520	78027	CONNECTIING ROD 			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					NR 1 CYLINDER	BOLT FAILED     	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			SO	11	1493V	1301 				17263623	L4160927A			ENGINE FAILED IN-FLIGHT WITH LOUD BANG.  AIRPLANE FORCE LANDED ON ROAD.  INSPECTION REVEALED NR 1 CYLINDER ROD HAD COME 	LOOSE FROM CRANK AND PUNCHED HOLE IN BOTTOM OF CASE.  INSPECTION OF ENGINE FOUND CONNECTING ROD BOLTS, P/N 78027, ON NR 	1 AND NR 4 CYLINDERS' CONNECTING RODS HAD BROKEN IN HALF.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996091200048	19960912	00048	SO  	1996	9	12	96ZZZX4316       	2	19960731	G	7310	60100040234	HOSE            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	TSIO520C    	17040	SO  					FUEL SYSTEM	LEAKING         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	2316U					U20602360				HOSE ASSY FAILED AFTER 2 YEARS AND LESS THAN 200 HOURS OF OPERATION.  HOSE TSO:  C531, MFG DATE A1094, LOT NR 06827.						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1996091200049	19960912	00049	SO  	1996	9	12	96ZZZX4317       	2	19960731	G	7310	60100040286	HOSE ASSY       	AEROQUIP    		CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	TSIO520C    	17040	SO  					FUEL SYSTEM	LEAKING         	D	L			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	2316U					U20602360				HOSE ASSY FAILED AFTER 2 YEARS AND LESS THAN 200 HOURS OF OPERATION.  HOSE IS TSO C53A, MFG DATE A1094, LOT NR 06827.						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1996091200050	19960912	00050	CE  	1996	9	12	96ZZZX4318       	1	19960710	G	5700	NAS679AW	NUT             			CESSNA	206   	U206F       	2073333	CE  										LIFT STRUT	FRACTURED       	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	50939	3065 				U20601954				LIFT STRUT HAS 5 BOLTS, AN5, THROUGH TOP AND BOTTOM.  TOTAL OF '5' NUTS HAD FAILED (FIFTY PERCENT).  RIGHT LIFT STRUT AL	L NORMAL.  CAUSE UNKNOWN, NUT P/N NAS679AW.					1	H	7	1 	3O				A4CE    					 
1996091200051	19960912	00051	SO  	1996	9	12	96ZZZX4319       	1	19960624	G	3211	AN510A	TRUNNION ATTACH 			PIPER 	PA34  	PA34200T    	7103406	SO  										MLG	BOLTS LOOSE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	47611	6090 				347770418				PIPER SB 956, PART II, WAS C/W AT 4,914 HOURS TT ON 5-92.  PART II IS PERMANENT COMPLIANCE AND BOLTS USED WERE LOOSE ON 	ATTACH FITTINGS.  THESE ARE A LARGER BOLT THAN ORIGINAL WITH AIRCRAFT.  RETORQUED ALL BOLTS PER SB 956, PART II.					1	L	7	2 	3O				A7SO    					 
1996020200066	19960202	00066	GL  	1996	2	2	96ZZZX432        	2	19960109	G	7510	6856983	VALVE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE ANTI-ICE	LEAKING         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D	CAE830750			ANTI-ICE VALVE WAS LEAKING.  FOUND THE PLUNGER WAS WORN ON ONE SIDE ALLOWING THE VALVE TO BE COCKED OFF ITS SEAT.  REPLA	CED PART.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996091200052	19960912	00052	WP  	1996	9	12	96ZZZX4320       	1	19960813	G	5320	738080	PLATFORM        	HAMSTD      		LKHEED	1011  	1011*       		WP  										APU	DAMAGED         	B	S		SI3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	GBBAF				ED55196					RIVET INSTALLATION TOOL MARKS EVIDENT ON REAR PANEL OF APU PLATFORM (SURGE SYSTEM SIDE).  SUSPECT RIVET INSTALLATION TOO	L RUBBED AGAINST PLATFORM DURING INSTALLATION OF RIVETS.  REF:  OHM 49-00-01, PAGE 1138B, FIGURE 9B.					2	L	7	3 	4F				A23WE   					 
1996091200053	19960912	00053	NE  	1996	9	12	96ZZZX4321       	2	19960819	G	7210	77577511	HOUSING         	HAMSTD      	77580010    	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GEARCASE	HOLE            	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		8439 			143		GEE785328			DURING PERFORMANCE OF AN AS RECEIVED TEST, OIL WAS NOTED COMING FROM THE ATMOSPHERIC VENT.  THE DISASSEMBLY OF THE GEAR 	CASE REVEALED THE AFT HOUSING TRANSFER TUBE BORE AREA SHOWED A HOLE IN THE HOUSING ALLOWING OIL TO ENTER THE ADS AREA OF	 THE GEARBOX.  EXAMINATION OF THE AREA WHERE THE HOLE IS SHOWS THAT LOCAL HAND BLENDING HAD BEEN PERFORMED ON THE CASTIN	G RESULTING IN A THIN WALL.  THE BLENDED AREA APPEARED TO HAVE BEEN ANODIZED DURING THE ORIGINAL MANUFACTURING PROCESS.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1996091200054	19960912	00054	EU  	1996	9	12	96ZZZX4322       	1	19960731	G	3230	258UN4871A	BRIDGE CASTING  		258UN3143A  	BRAERO	DH125 	BAE125800A  	1500285	EU  										NLG DRAG LINK	BEARING DAMAGED 	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	CGCIB				SAM2402	258048				NOSE LANDING GEAR DRAG LINK, ALL 3 ROLLER BEARINGS IN NEW STEEL CASTING WERE DAMAGED WHEN INSTALLED BY FACTORY.  THIS CA	USED BINDING OF THE PIVOT SHAFT.					2	L	7	2 	4F			RT	A3EU    					 
1996091200055	19960912	00055	NE  	1996	9	12	96ZZZX4323       	2	19960701	G	7230	536210	LOCK            								PWA   	JT12  	JT12A8      	52042	NE  					3RD STAGE DISK	MISSING         	B			JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03		322  					P637622NB			INTERNAL BLADE RUBBING, BINDING, AND LOCKING UP.  AN INDUCTION TEST RUN WAS PEFORMED ON 6-20-96.  DURING THE TEST, VIBRA	TION OF 3.8 MIL AT 75 PERCENT WAS NOTED.  (3.2 MIL IS MAXIMUM ALLOWABLE).   ENGINE WAS DISASSEMBLED AS NECESSARY TO ACCE	SS COMPRESSOR ASSY.  COMPRESSOR WAS DISASSEMBLED TO ELEVATE RUBBING CONDITION.  P/N 536203, 3RD STAGE COMPRESSOR BLADE W	AS FOUND LOOSE IN THE BLADE SLOT OF 3RD STAGE DISK.  BLADE HAD MOVED AFT MAKING CONTACT WITH COMPRESSOR STATOR, P/N 3855	03, DAMAGING EVERY VANE.  BLADE LOCK COULD NOT BE FOUND AND SUSPECT IT MAY HAVE FAILED AND EXITED ENGINE ALLOWING BLADE 	TO WORK LOOSE.  NO OBVIOUS DAMAGE FROM LOCK WAS NOTED.  CAUSE OF LOCK FAILURE IS UNKNOWN AT THIS TIME.  ONE EACH P/N 536						4	J			1E9				 
1996091200057	19960912	00057	CE  	1996	9	12	96ZZZX4325       	1	19960725	G	3230	12805201	LOCK VALVE      			CESSNA	177   	177RG       	2073709	CE  										MLG	MALFUNCTION     	B	L		CGFR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	03	1566H					177RG0740				PILOT WAS UNABLE TO EXTEND LANDING GEAR EITHER BY THE NORMAL OR THE EMERGENCY HYDRAULIC SYSTEM.  A GEAR UP LANDING WAS M	ADE AND MINOR DAMAGE.  WHEN ACFT WAS JACKED UP PRIOR TO REMOVING IT, NOTED THE LANDING GEAR COULD NOT BE PUSHED INTO LOC	KS.  WHEN MAIN GEAR WAS MOVED TO DOWN AND LOCK POSITION, NOSE GEAR WOULD RETRACT, AND WHEN MAINS WERE MOVED TO WHEELWELL	S, NOSE WOULD GO INTO ITS DOWN AND LOCKED POSITION.  HYDRAULIC PRESSURE WAS TRAPPED IN RETRACT 'SIDE' OF HYD SYS.  A B-N	UT ON THE RETRACT PORT OF NOSE GEAR HYD ACTUATOR WAS LOOSENED TO ALLOW FLUID TO ESCAPE AND THE HAND PUMP WAS THEN USED T	O PUMP LANDING GEAR TO A 'DOWN AND LOCKED' POSITION ALLOWING ACFT TO BE TOWED FROM RUNWAY.	1	H	7	1 	3O				A20CE   					 
1996091200059	19960912	00059	EU  	1996	9	12	96ZZZX4327       	1	19960725	G	2751		LEVER ARM       			AMD   	FALC20	FALCON20FS  	2730105	EU  										WING FLAP SWITCH	WORN            	B		A	JGVR	K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			CE	09	148MC	6470 				428				AIRCRAFT FLYING IN A CLEAN CONFIGURATION WITH G-LOADS WOULD GET A GEAR WARNING HORN THAT COULD NOT BE CANCELLED.  PROBLE	M COULD NOT BE DUPLICATED ON JACKS IN THE HANGAR, BUT HAPPENED ON EVERY FLIGHT.  FINALLY, THE 24G 280 DEGREE FLAP SWITCH	ES, MOUNTED ON THE WING, PIVOT ARM LEVER AND THE FLAP MOUNTED SWITCH ACTUATION RAMP, WERE FOUND AT MAXIMUM ADJUSTMENT. I	NSPECTION REVEALED PIVOT LEVER ROLLER WAS FLAT SPOTTED AND CENTER HOLE WORN OVERSIZE.			2	L	7	2 	4F			RT	A7EU    					 
1996091200060	19960912	00060	GL  	1996	9	12	96ZZZX4328       	3	19960812	G	6111		BLADE           			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	TIP FLUTTER     	D		A		K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SO	07	1660W		620  			BB390		RBU15955		BOTH PROPELLERS GO INTO TIP FLUTTER AT ENGINE POWER SETTINGS AT AND ABOVE 1,800 FEET/POUNDS OF TORQUE.  HIGH FREQUENCY V	IBRATION CAN BE FELT THROUGHOUT THE ENTIRE AIRCRAFT.  BLADE TIPS TOO THIN AT TIPS.  MANUFACTURER HAS NO STANDARDS FOR MI	NIMUM THICKNESS AT THIS BLADE STATION.				1	L	7	2 	4T				A24CE   		6	C	P15EA	 
1996091200061	19960912	00061	EU  	1996	9	12	96ZZZX4329       	1	19960819	G	5753		BEARING         			FOKKER	F27   	F27MK200    	4990620	EU  										FLAP HINGE	WRONG PART      	A	S	A	MJ4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19	279MA					10297				DURING A C-CHECK INSPECTION, NOTED THAT AN INCORRECT BEARING WAS INSTALLED IN THE LEFT FLAP CENTER HINGE.  THE PART WAS 	UNIDENTIFIABLE AND NO PART OR SERIAL NUMBERS WERE PRESENT.  PART APPEARED TO COME FROM A NON-AIRCRAFT PARTS SOURCE.					2	H	7	2 	4T				A817    					 
1996020200067	19960202	00067	GL  	1996	2	2	96ZZZX433        	2	19960102	G	7321	23033917	FUEL CONTROL    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	DEFECTIVE       	A			EJYA	O				OTHER                   				J			WARNING INDICATION        			IN	INSP/MAINT     	1			WP	07	90328		1935 		335870	1853	830842			PILOT ABORTED START WHEN TOT WENT PAST 850 DEGREES RAPIDLY DURING START ATTEMPT.  TROUBLESHOOTING REVEALED FAULTY FUEL C	ONTROL.  REPLACED FUEL CONTROL IAW ALLISON AND BELL MM.  LEAK AND FUNCTIONAL CHECKS GOOD.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996091200062	19960912	00062	CE  	1996	9	12	96ZZZX4330       	1	19960807	G	2821	306051	FILTER ASSY     			BEECH 	36    	A36         	1151604	CE  										FUEL SYSTEM	BOWL LOOSE      	B			CB5Y	K				NONE                    				X			ENGINE FLAMEOUT           			IN	INSP/MAINT     	1			EA	35	250TP	208  				E2408				ENGINE FLAME-OUT ON POWER CHECK.  FUEL FILTER BOWL FOUND LOOSE, SUFFICIENT TO ALLOW ENGINE FUEL STARVATION.  FUEL BOWL I	S TORQUED TO 25 INCH/POUND (THE LOWER TORQUE VALUE) AS HAD EXPERIENCED A CRACKED FILTER HOUSING WHEN TORQUED TO THE HIGH	 LIMITS.  FILTER LOCKING WIRE FRACTURED RESULTING IN THE BOWL VIBRATING LOOSE.  SUSPECT TOO MANY TWISTS TO THE INCH AT T	HE TOP END OF THE LOCKING WIRE.			1	L	7	1 	3O				3A15    					 
1996091200063	19960912	00063	NE  	1996	9	12	96ZZZX4331       	2	19960808	G	7230		COMPRESSOR      			RKWELL	NA265 	NA26540     	6402608	CE  	PWA   	JT12  	JT12A8      	52042	NE  					ENGINE	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	302NT	5836 	420  			28281	P672953NB			COMPRESSOR VERY DIFFICULT TO ROTATE, IINTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND WITH SHORT SPOOL DOWN TIME. N	O FOD NOTED, NO DAMAGE OR VISUAL DEFECTS NOTED IN TURBINE HOT SECTION.  ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL.	  ENGINE WAS REMOVED FROM SERVICE AND RETURNED TO SABERLINER FOR TEAR DOWN INSPECTION.				2	L	7	2 	4J	4	J		A2WE    	1E9				 
1996091200064	19960912	00064	CE  	1996	9	12	96ZZZX4332       	1	19960807	G	3233	265580125	ACTUATOR        			RKWELL	NA265 	NA26540     	6402608	CE  										NLG	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	09	301NT					2829				ACTUATOR WAS INSTALLED ON THE AIRCRAFT, OPERATIONALLY CHECKED, AND REMOVED DUE TO LEAKAGE THROUGH A HOLE (OR CRACK) IN T	HE ACTUATOR CYLINDER (BARREL) WALL.  THE ACTUATOR WAS OVERHAULED 9-7-95.  ACTUATOR TIME SINCE OVERHAUL WHEN REMOVED:  ZE	RO HOURS.  AIRCRAFT TOTAL TIME:  14,208.5 HOURS.				2	L	7	2 	4J				A2WE    					 
1996091200065	19960912	00065	SW  	1996	9	12	96ZZZX4333       	1	19960801	G	2435	23046007	GENERATOR       	LEARSIEGLER 		GULSTM	680TP 	680W        	0141716	SW  										START/GEN	BEARING FAILED  	B			ESMR	A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SO	11	54163		10   		2097	177412				GENERATOR STOPPED OPERATING IN-FLIGHT.  AFTER LANDING, CHECKED STARTER/GENERATOR AND FOUND LOCKED UP.						1	H	7	2 	3T				2A4     					 
1996091200066	19960912	00066	EU  	1996	9	12	96ZZZX4334       	1	19960808	G	3244	DR6385T	TIRE            	DUNLOP      		HWKSLY	DH125 	BH125400A   	4230138	EU  										SIDEWALL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	68CB	206  			95206281	NA765				TIRE LOST 25 POUNDS PRESSURE OVERNIGHT.  FOUND HOLE IN SIDEWALL.  REPLACED TIRE WHICH HAD 199 LANDINGS.  NORMAL USAGE GI	VES 500 LANDINGS.  TIRE SENT TO DUNLOP FOR EXAMINATION.					2	L	7	2 	4J				A3EU    					 
1996091200068	19960912	00068	NE  	1996	9	12	96ZZZX4336       	2	19960719	G	7230	3021436	BYPASS DUCT     			MTSBSI	MU300 	MU300       	5780602	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT ENGINE	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	83BG		452  			A018SA	PCE70623			A CRACK DEVELOPED AT THE FORWARD FLANGE OF THE AFT INNER BYPASS DUCT AT THE 6 O'CLOCK POSITION ALLOWING IT TO COME OUT O	F THE MATING FLANGE AND ENTER THE AIR FLOW, THEREBY CAUSING A 3 INCH (APPROX) SECTION TO PEEL BACK AND CAUSE A 2 INCH (A	PPROX) TEAR ALONG THE RADIUS OF THE BEND.  THE PILOT NOTICED THE PIECE HANGING DOWN DURING PRE-FLIGHT INSPECTION AND ASS	Y WAS REPLACED BEFORE FURTHER FLIGHT.			2	H	7	2 	4F	4	F	RT	A14SW   	E1NE				 
1996091200069	19960912	00069	NE  	1996	9	12	96ZZZX4337       	3	19960801	G	6114		PROPELLER       	HAMSTD      		AIRTRC	AT300 	AT301       	0390103	SW  						HAMSTD	12D	12D40       	NE  	COUNTERWEIGHT	BOLT BROKE      	H				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	8883S					3010226		728749		COUNTERWEIGHT BOLT BROKE CAUSING AIRCRAFT TO PERFORM AN EMERGENCY LANDING AND NOSING OVER ON ITS BACK CAUSING EXTENSIVE 	DAMAGE TO THE AIRCRAFT.					1	L	7	1 	3R				A9SW    		5	C	P257	 
1996091200070	19960912	00070	CE  	1996	9	12	96ZZZX4338       	1	19960729	G	7830	202SR00113	BUMPER PAD      	ROHR        	65550291    	CESSNA	500   	550         	2076604	CE  										THRUST REV	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	87SF	320  			0218	5500096				PILOTS REPORTED LT REVERSER WOULD INTERMITTENTLY 'HANG UP' WHILE OPENING, BUT CLOSE AND LOCKING WERE NORMAL.  319.7 HRS,	 490 CYCLES PRIOR TO THIS OCCURRENCE, ROHR SB CIT 78-8R1 WAS C/W WHICH INSTALLS NEW DOOR BUMPERS OVER OLD BUMPERS.  THIS	 DECREASES CLEARANCE BETWEEN INBD UPPER STANG FAIRING SUPPORT AND DOOR BUMPER.  OVER TIME, NEW BUMPER MUSHROOMED SLIGHTL	Y ALLOWING DOOR TO CATCH ON SUPPORT SKIN.  INSPECTION OF RT SIDE SHOWED SIGNS OF SAME PROBLEM BEGINNING TO OCCUR.  ROUTI	NG OUT FORWARD SKIN OF BOTH SUPPORTS FOR EXTRA CLEARANCE RECTIFIED PROBLEM.  SUBMITTER SUGGESTS SB BE REVISED TO INSPECT	 THIS AREA AND ALLOW A MINIMUM OF .25 INCH CLEARANCE.	1	L	7	2 	4F				A22CE   					 
1996091200071	19960912	00071	CE  	1996	9	12	96ZZZX4339       	1	19960729	G	7830	202SR00114	BUMPER PAD      	ROHR        	65550291    	CESSNA	500   	550         	2076604	CE  										THRUST REV	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	87SF	320  			0218	5500096				PILOTS REPORTED LT REVERSER WOULD INTERMITTENTLY 'HANG UP' WHILE OPENING, BUT CLOSE AND LOCKING WERE NORMAL.  319.7 HRS,	 490 CYCLES PRIOR TO THIS OCCURRENCE, ROHR SB CIT 78-8R1 WAS C/W WHICH INSTALLS NEW DOOR BUMPERS OVER OLD BUMPERS.  THIS	 DECREASES CLEARANCE BETWEEN INBD UPPER STANG FAIRING SUPPORT AND DOOR BUMPER.  OVER TIME, NEW BUMPER MUSHROOMED SLIGHTL	Y ALLOWING DOOR TO CATCH ON SUPPORT SKIN.  INSPECTION OF RT SIDE SHOWED SIGNS OF SAME PROBLEM BEGINNING TO OCCUR.  ROUTI	NG OUT FORWARD SKIN OF BOTH SUPPORTS FOR EXTRA CLEARANCE RECTIFIED PROBLEM.  SUBMITTER SUGGESTS SB BE REVISED TO INSPECT	 THIS AREA AND ALLOW A MINIMUM OF .25 INCH CLEARANCE.	1	L	7	2 	4F				A22CE   					 
1996091200072	19960912	00072	NM  	1996	9	12	96ZZZX4340       	1	19960813	G	2810	25W357450003	DRAIN LINE      			ISRAEL	1125  	1125        		NM  										REFUEL PORT	CRACKED         	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	91FD	2109 				045				DURING OTHER MAINTENANCE,THE DRAIN LINE FOR THE GRAVITY REFUEL PORT WAS FOUND CRACKED IN 4 PLACES.   THIS COULD ALLOW FU	EL TO LEAK INTO THE TAILCONE/BAGGAGE AREA.  DEBRIS WAS FOUND NEAR OUTLET.  LINE WAS REPLACED AND A LOW SPOT WAS ELIMINAT	ED.  THE GRAVITY FUEL CAP IS ALSO A RELIEF VALVE IN CASE OF FUEL EXPANSION.  THE EXPANDED FUEL WOULD DRAIN INTO THE AFFE	CTED DRAIN TUBE.			2	L	7	2 	4F			RT	A16NM   					 
1996091200073	19960912	00073		1996	9	12	96ZZZX4341       	4	19960815	G	2562	AK450	ELT             	AMERIKING   																WIRING	DEFECTIVE       	C	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	13										INSPECTION FOUND WIRING EMPLOYED BETWEEN THE CIRCUIT BOARD AND THE BATTERY CASE DEFECTIVE.  THE SLIP-ON CONNECTOR WAS AS	SEMBLED WITH APPROXIMATELY 2MM OF THE CONTACT LUGS PROTRUDING FROM THE PLASTIC HOUSING LEAVING THESE METAL ENDS VERY CLO	SE AND IN DANGER OF SHORTING.  SINGLE STRAND WIRE IS USED.  THIS IS INAPPROPRIATE FOR THE TYPE OF CRIMP CONNECTOR USED, 	AND WOULD ALSO BE OF CONCERN FOR FATIGUE LIFE.  THE CRIMP ON ONE OF THE CONNECTORS IS LOOSE.  THE OTHER ENDS OF THE WIRE	S WERE LOOPED AROUND THE BATTERY SPRING ENDS, THE WIRES BEING SOLDERED.  BOTH WIRES WERE EASILY SLIPPED OFF THE SPRINGS 	WITHOUT UNSOLDERING THEM, OBVIOUSLY THE TYPE OF PLATING ON THE SPRINGS IS INAPPROPRIATE FOR RELIABLE SOLDER ADHESION.														 
1996091200074	19960912	00074	NE  	1996	9	12	96ZZZX4342       	2	19960711	G	7230	536211	LOCK            								PWA   	JT12  	JT12A8      	52042	NE  					4TH STAGE DISK	MISSING         	B	L		JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03		1300 					P672928NB			METAL-TO-METAL CONTACT, BIND, BLADE RUB.  INVESTIGATION FINDINGS:  AN INDUCTION TEST RUN COULD NOT BE ACCOMPLISHED DUE T	O RUBBING CONDITION. THE ENGINE AND COMRPESSOR ASSEMBLY WERE DISASSEMBLED TO IDENTIFY CAUSE OF DISCREPANCY.   INVESTIGAT	ION REVELAED THAT P/N 536204, FOURTH STAGE COMPRESSOR BLADE, WAS FOUND LOOSE IN THE BLADE SLOT OF THE FOURTH STAGE DISK.	  THE BLADE HAD MOVED AFT MAKING CONTACT WITH THE INNER SEAL AREA OF THE FOURTH STAGE COMPRESSOR STATOR, P/N 542274.  P/	N 536211, BLADE LOCK, COULD NOT BE FOUND AND SUSPECT IT MAY HAVE FAILED AND LEFT THE ENGINE ALLOWING THE BLADE TO WORK L	OOSE.  NO OBVIOUS DAMAGE FROM THE LOCK WAS NOTED.						4	J			1E9				 
1996091200075	19960912	00075	CE  	1996	9	12	96ZZZX4343       	1	19960624	G	7714	22A667	TACH GENERATOR  			BEECH 	58    	58          	1152740	CE  										STATOR WINDING	INOPERATIVE     	B	L		FFKR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	11HW		65   		8060	TH271				THE TACHOMETER GENERATOR FAILED DURING NORMAL OPERATING CONDITIONS.  THE SUSPECT CAUSE IS PHASE 'A' OPEN CIRCUIT, WITHIN	 STATOR WINDING.					1	L	7	2 	3O				3A16    					 
1996091200076	19960912	00076	CE  	1996	9	12	96ZZZX4344       	1	19960808	G	2820		TRANSFER PUMP   			CESSNA	206   	U206F       	2073333	CE  										TIP TANK	CORRODED        	G	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	CGVQG					U20602082				MALFUNCTION AND DEFECT REPORT RECEIVED FROM TRANSPORT CANADA ON A CESSNA U206 IN WHICH CHECK VALVES, FUEL LEVEL TRANSMIT	TERS, AND TRANSFER PUMPS WERE FOUND CORRODED IN THE AUXILIARY FUEL TIP TANKS INSTALLED IAW STC SA4368WE.  HAVE DETERMINE	D THE CORROSION RESULTED FROM CONDENSATION WITHIN THE TANKS DUE TO LOW FUEL LEVELS OVER AN EXTENDED PERIOD OF TIME.  NOT	E THAT THIS PHENOMENON IS NOT UNIQUE TO THE FLINT AUXILIARY FUEL TIP TANK INSTALLATION.			1	H	7	1 	3O				A4CE    					 
1996091200077	19960912	00077	CE  	1996	9	12	96ZZZX4345       	1	19960624	G	7714	H60050	TACH GENERATOR  			BEECH 	58    	58          	1152740	CE  										TACH DRIVE	SHAFT SHEARED   	B	L		FFKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05	11HW		1    		239102	TH271				THE TACHOMETER GENERATOR FAILED UNDER NORMAL OPERATING CONDITIONS.  THE SUSPECT CAUSE IS A SMALL O-RING FITTED ON THE DR	IVESHAFT AND INSIDE THE ROTOR SHAFT IS AN UNSPECIFIED PART.  (DOES NOT APPEAR IN PARTS BREAKDOWN.)  THIS O-RING RESTRICT	ED THE SELF-CENTERING ACTION OF THE DRIVESHAFT WITH MATING DRIVE ON THE AIRCRAFT.  THIS CAUSED THE DRIVESHAFT TO FAIL.				1	L	7	2 	3O				3A16    					 
1996091200122	19960912	00122	SW  	1996	9	12	96ZZZX4348       	1	19960621	G	6210	47110250023	BLADE           			BELL  	47    	OH13H       	1180820	SW  										M/R	DEFECTIVE       	B	L	A	WG3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	27	67154	253  			A1149	585377				RECEIVED THE NEW BLADES AND REINSTALLED.  WERE UNABLE TO TRACK AND BALANCE THE M/R SYSTEM TO AN ACCEPTABLE LEVEL DUE TO 	ONE BLADE BEING OUT OF TRACK AND WAS UNABLE TO CONTROL THIS PROBLEM WITH STANDARD ADJUSTMENTS.					1	G	7	1 	3O				H1      					 
1996091200188	19960912	00188	SW  	1996	9	12	96ZZZX4367       	1	19960717	G	6310	28952017	SEAL            			BELL  	206   	206B        	1181511	SW  										FREEWHEEL	LEAKING         	B			WG3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	27	82HH	212  				4337				PILOT REPORTED FREEWHEELING ASSY LEAKING OIL.  FOUND INPUT SEAL LEAKING.  REMOVED SEAL, P/N 28905-2017, AND INSTALLED NE	W SEAL, P/N 206-340-204-101, WITH O-RINGS MB3248/1-237 AND MB248/1-215.					1	G	7	1 	3U				H2SW    					 
1996091200189	19960912	00189	SW  	1996	9	12	96ZZZX4368       	1	19960717	G	7110	50007A26	STUD            			BELL  	206   	206B        	1181511	SW  										COWLING	LOOSE           	B			WG3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	27	82HH	212  				4337				PILOT REPORTED THAT COWLING STUDS WERE LOOSE WHEN FASTENED.  INSPECTED AND FOUND ENGINE COWL STUDS TO BE TOO LONG.  REMO	VED AND INSTALLED NEW STUDS, P/N 50-007-15, AND GROMMET, P/N 50-009-2 ( 5 EACH).  TWO EACH  P /N 50007A26 AND P/N 50007A	22.				1	G	7	1 	3U				H2SW    					 
1996091200190	19960912	00190		1996	9	12	96ZZZX4369       	4	19960717	G	2312	90367	SWITCH          			BELL  	206   	206B        	1181511	SW  										PILOT TRANSMIT	DEFECTIVE       	B			WG3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	82HH	212  				4337				PILOT REPORTED  THE PILOT'S TRANSMIT SWITCH WAS INOPERATIVE, INTERMITTENT.  INSPECTED TRANSMIT SWITCH AND FOUND CONTACT 	BENT.  INSTALLED NEW SWITCH, P/N 90-367, AND OPS TESTED.					1	G	7	1 	3U				H2SW    					 
1996091200529	19960912	00529	CE  	1996	9	12	96ZZZX4370       	1	19960425	G	3233	9910002RX	ACTUATOR        			CESSNA	310   	310L        	2074230	CE  										MLG	PIN SHEARED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	3315X	149  			1776	310L0165				THE GEAR ACTUATOR STOP PIN WAS FOUND SHEARED.  THE SUSPECT CAUSE WAS FROM THE GEAR MOTOR NOT STOPPING AND SHEARING THE S	TOP PIN.  THE COAST TIME IN THE CW DIRECTION WAS EXCESSIVE.					1	L	7	2 	3O				3A10    					 
1996091900001	19960919	00001	EA  	1996	9	19	96ZZZX4371       	2	19960824	G	8530		CYLINDER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					SPARK PLUG HOLE	CRACKED         	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SO	16	30230					287990088	L2558336A			CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND SIDE TO BOTTOM SPARK PLUG HOLE.  AIRCRAFT LANDED SAFELY WITHOUT FURTHER	 PROBLEMS (LOSS OF RPM).  ENGINE TT, 2,601.4 HOURS.  TSMOH:  607.7 HOURS.  SUBMITTER STATED THIS IS THE THIRD CRACKED CY	LINDER ON THIS AIRCRAFT SINCE OVERHAUL.				1	L	7	1 	3O	3	O		2A13    	E286				 
1996091900002	19960919	00002	CE  	1996	9	19	96ZZZX4372       	1	19960823	G	2434	ALV9510	ALTERNATOR      	PRESTOLITE  		CESSNA	421   	421B        	2076014	CE  										AUXILIARY CIRC	WIRE BROKEN     	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	13	41055	63   			5100914	421B0576				RIGHT ALTERNATOR 'FAIL' LIGHT FLICKERED AND CAME ON IN-FLIGHT, ALTERNATOR SHOWED TO HAVE CORRECT OUTPUT.  REMOVED SAME W	ITH ANOTHER.  AFTER 38 HOURS, THE REPLACEMENT ALTERNATOR HAD THE SAME PROBLEM.  CALLED ELECTRO SYSTEMS AND CONVEYED PROB	LEM TO SERVICE REP.  HE CHECKED THE PROBLEM ON FIRST ALTERNATOR AND FOUND WIRE TO AUXILILARY TERMINAL BROKEN.  HE GAVE P	ERMISSION TO DISASSEMBLE PRESENT ALTERNATOR.  FOUND THE SAME PROBLEM.  AFTER RE-SOLDER OF AUXILIARY WIRE AND REASSEMBLY,	 RAN A/C.  THE PROBLEM WAS CURED.		1	L	7	2 	3O				A7CE    					 
1996091200530	19960912	00530	SO  	1996	9	12	96ZZZX4373       	2	19960813	G	8530	635448CP	CYLINDER        			CESSNA	188   	A188B       	2073005	CE  	CONT  	O520  	IO520D      	17032	SO  					NR 4	FAILED          	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			SW	17	9370R		450  		5538AA620	18802262T	563670			NR 4 CYLINDER HEAD SEPARATED FROM BARREL CAUSING ENGINE FAILURE IN-FLIGHT RESULTING IN FORCED LANDING (I-35 SOUTH, SAN A	NTONIO).  R2 CYLINDER ASSY OPS CHECK OK.					1	L	7	1 	3O	3	O		A9CE    	E5CE				 
1996091200531	19960912	00531	CE  	1996	9	12	96ZZZX4374       	1	19960822	G	3710	3P194FA	PUMP            	PESCO       		CESSNA	182   	182J        	2072722	CE  	CONT  	O470  	O470N       	17026	SO  					VACUUM SYSTEM	DRIVE SHEARED   	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	2714F				PE09124FDG	18256814	1319985R			VACUUM PUMP DRIVESHAFT SHEARED AND SPLINES EXTREMELY WORN.  IT STILL MADE VACUUM PRESSURE.  SUBMITTER RECOMMENDS MORE FR	EQUENT INSPECTIONS OF DRIVE SPLINE ASSY (NOTE:  WET DRIVE VACUUM PUMP).					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996091200532	19960912	00532	GL  	1996	9	12	96ZZZX4375       	3	19960731	G	6111	1301	CLAMP           			PIPER 	PA31T 	PA31T1      	7103126	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	BLADE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03								BU12340		PROPELLERS WERE IN FOR TIME OVERHAUL.  THREE OF THE BLADE CLAMPS WERE REJECTED FOR CORROSION INSIDE THE CLAMP WHERE CONT	ACT IS MADE WITH THE BLADE THRUST BEARING.  ONE CLAMP WAS REJECTED FOR A CRACK THAT RAN PARALLEL TO THE CLAMP HAD SPLIT.	  IT WAS ALSO FOUND THAT THE WRONG SPRING ASSY WAS INSTALLED IN BOTH PROPELLERS.  THE WRONG SPRING ASSY HAS HIGHER SPRIN	G TENSION THAN THE ONE THAT SHOULD HAVE BEEN INSTALLED.  THE SPRING ASSYS WERE CHANGED AND THE FOUR CLAMP ASSYS WERE REP	LACED ALONG WITH OVERHAUL OF THE PROPS AND RETURNED TO SERVICE.		1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1996091200533	19960912	00533	CE  	1996	9	12	96ZZZX4376       	1	19960801	G	3250	59420011	BRACKET         			CESSNA	310   	T310P       	2074240	CE  										NLG STRUT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08										AFTER FINDING A CRACKED STEERING BRACKET ON A CESSNA 401, INSPECTED A CE310 AND FOUND BRACKET CRACKED IN RADIUS.  BRACKE	T LOCATED ON TOP OF NOSE STRUT.  TTAF:  3,826.					1	L	7	2 	3O				3A10    					 
1996091200534	19960912	00534		1996	9	12	96ZZZX4377       	2	19960709	G	7322	CF131520	SHAFT           	FACET       	MA3PA       															THROTTLE	MISDRILLED      	D	P			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23										PURCHASED CARBURETOR THROTTLE SHAFT KIT, P/N CF 778-1006, NEW FROM AVSCO. ON INSPECTION OF PART BEFORE INSTALLATION, FOU	ND PART ASSEMBLED IMPROPERLY, P/N CF13-1520.  THE HOLE IN THE THROTTLE STOP WAS DRILLED CROOKED AND STILL ASSEMBLED ONTO	 THE SHAFT.  BECAUSE OF THIS, THE SERRATED THROTTLE LEVER WOULD NOT FIT SQUARELY, AND THE SERRATED PARTS DID NOT LINE UP	 AND ENGAGE EACH OTHER PROPERLY.  THROTTLE LEVER, P/N 12-B57.  SUBMITTER STATED PROPER QUALITY CONTROL WOULD SOLVE THIS 	PROBLEM.															 
1996091200535	19960912	00535	EA  	1996	9	12	96ZZZX4378       	3	19960801	G	6110		PROPELLER       			PIPER 	PA28  	PA28161     	7102803	SO  						SNSNCH	74D	74DM        	EA  	FLANGE	MISINSTALLED    	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										SUBMITTER REPORTS FINDING PIPER PA 28-161 PROPELLERS INCORRECTLY INSTALLED PER SERVICE MANUAL  INSTRUCTIONS.  SHOULD BE 	INDEXED WITH PROPELLER BLADES AT 2 AND 8 O'CLOCK POSITIONS AS VIEWED FROM COCKPIT.					1	L	7	1 	3O				2A13    		5	N	P88614	 
1996091200536	19960912	00536	CE  	1996	9	12	96ZZZX4379       	1	19960718	G	2820	MS28775111	O-RING          		CCA3400     	BEECH 	36    	A36         	1151604	CE  										DRAIN VALVE	WRONG PART      	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	3122U	95   				E2431				THE FUEL DRAIN VALVES MANUFACTURED BY CURTIS USE SPECIAL SEALS THAT ARE COMPOUNDED OF MATERIALS SPECIFICALLY DESIGNED TO	 RESIST AVIATION FUEL.  MORE IMPORTANTLY, THE SEALS ARE SPECIALLY SHAPED (MOST LOOK LIKE A SMALL PANCAKE WITH A HOLE IN 	THE MIDDLE) TO FIT CURTIS VALVES.  THE CORRECT REPLACEMENT SEAL FOR THIS VALVE IS P/N CCA1319.  GENERIC O-RINGS MAY NOT 	PROVIDE ADEQUATE SEALING OR PROTECTION AGAINST CHEMICAL ATTACK BY AVIATION FUEL.  IN-FLIGHT LEAKAGE COULD RESULT IN A RE	DUCTION OF AN AIRCRAFT'S RANGE OR ENDURANCE, OR CREATE FIRE HAZARD.		1	L	7	1 	3O				3A15    					 
1996091200537	19960912	00537	NE  	1996	9	12	96ZZZX4380       	2	19960814	G	7313	231009801	NOZZLE          		216362036   	BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R     	41580	NE  					FUEL MANIFOLD	CRACKED         	B	S	A	PGLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13					82F001					OVERTORQUED CONDITION RESULTING IN CRACKED FLANGE AREA.  RECOMMEND USE OF PROPER TORQUE DURING INSTALLATION OF NOZZLE IN	TO MANIFOLD ASSY.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996091200538	19960912	00538	SO  	1996	9	12	96ZZZX4381       	1	19960524	G	2720		TORQUE TUBE     			PIPER 	PA31T 	PA31T       	7103124	SO  										RUDDER BAR	BEARING DETACHED	C	L	A		O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			EA	25	809SW					31T8020082				SPARKS AROUND THE PILOT'S FEET WHEN HE WAS USING THE RUDDER PEDALS TO TURN THE ACFT FOR BACK-TRACKING DOWN THE RUNWAY TO	 EXIT POINT.  REMOVED PILOT'S SEAT AND CARPET, FOUND RUDDER TORQUE TUBE BEARING ADRIFT FROM THE FLOOR LETTING THE RUDDER	 BAR ASSEMBLY LIFT AND SHORT OUT ONTO THE AVIONICS BUSS BAR.				1	L	7	2 	3T				A8EA    					 
1996091200539	19960912	00539	EA  	1996	9	12	96ZZZX4382       	2	19960820	G	8530		CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 2	CRACKED         	D				C				ABORTED TAKEOFF         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			NM	01	46758					15283101	L1612315			TAKEOFF ABORTED FOR LOSS OF POWER/ROUGH RUNNING ENGINE.  POST-FLIGHT MAINTENANCE INSPECTION REVEALED 3 INCH HAIR LINE CR	ACK RUNNING CIRCUMFERENTIALLY, BETWEEN NR 14 AND NR 15 FIN (COUNTING DOWN FROM TOP) OF NR 2 CYLINDER.  SMALL BURN AREA O	BSERVED ON NR 4 CYLINDER INTAKE PUSH ROD TUBE.  REPLACED ENGINE.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996091200540	19960912	00540	SO  	1996	9	12	96ZZZX4383       	2	19960801	G	8520	6436511	STUD            			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					CYLINDER BASE	STRETCH         	B	P	A	YYBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	2847J					28R7931221	24809612			ENGINE WAS BEING REPAIRED FOR SEVERAL BROKEN CYLINDERS, BASE STUDS, AND LOOSE NUTS.  MECHANIC RECEIVED 36 BRAND NEW STUD	S FROM THREE DIFFERENT VENDORS IN TCM PACKAGING.  UPON TORQUING TO THE REQUIRED MINIMUM TORQUE VALVE, A TOTAL OF 12 STRE	TCHED.  THEY WERE ALL REMOVED.  TWO WERE SUBMITTED TO TCM FOR ANALYSIS.				1	L	7	1 	3O	3	O		2A13    	E9CE				 
1996091200542	19960912	00542	CE  	1996	9	12	96ZZZX4385       	1	19960806	G	3340	612008	POWER SUPPLY    			RKWELL	NA265 	NA26540     	6402608	CE  										STROBE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	303NT		25   		12381C	28229				STROBE POWER SUPPLY WAS INSTALLED IN THE AIRCRAFT, OPERATED FOR 25 HOURS, AND WAS REMOVED FOR INTERNAL FAILURE WITH NO P	OWER OUTPUT.  UNIT WAS OVERHAULED ON 10-18-95.  RELIABILITY OF OVERHAULED UNITS FROM THIS REPAIR STATION HAS BEEN POOR. 	 AIRCRAFT TT:  10,625.8 HRS.				2	L	7	2 	4J				A2WE    					 
1996091200543	19960912	00543		1996	9	12	96ZZZX4386       	4	19960817	G	3414	2014001210	INDICATOR       	AEROSONIC   		BEECH 	200   	B200        	1152922	CE  										PILOT AIRSPEED	GASKET FAILED   	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	44NL	209  			W20644	BB1492				BEZEL GASKET ROLLED FROM SEAT ALLOWING PRESSURIZATION TO ENTER AIRSPEED INDICATOR.  THIS CUASED LARGE ERROR IN AIRSPEED,	 ALTIMETER, AND V.S.I. DURING FLIGHT.  UNIT HAD BEEN REPAIRED PRIOR TO FLIGHT.  RECOMMEND A POST-ASSEMBLY INSPECTION TO 	DESIGN PRESSURE LIMITS TO DETECT SIGNS OF INTERNAL LEAKS.				1	L	7	2 	4T				A24CE   					 
1996091200544	19960912	00544	EU  	1996	9	12	96ZZZX4387       	1	19960815	G	7830	2660042505	LONGERON        	ROHR        	26600021M   	BRAERO	1000  	BAE1251000  	1500287	EU  										T/R DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	514QS	2854 			CUM101001	NA1005				FOUND CRACK ON LEFT ENGINE THRUST REVERSER UPPER DOOR INBOARD LONGERON ASSEMBLY ABOUT TWO INCHES FROM BUMPER.  LONGERON 	ASSY IS WEAK IN MACHINED AREA WHICH IS WHERE THE CRACK IS LOCATED.  SUBMITTER STATED IF THE BUMPER IS MODIFIED TO EXTEND	 PAST THE WEAK AREA, THE PROBLEM WILL PROBABLY GO AWAY.				2	L	7	2 	4F			RT	A3EU    					 
1996091200546	19960912	00546	GL  	1996	9	12	96ZZZX4389       	1	19960806	G	7810		EXHAUST         			AMTR  	VECITY	VELOCITY    	05612DU	GL  										CYLINDERS 1-3	BROKEN          	G	S			K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			SO	11	637KM					DMO63				EXHAUST FROM NR 1 CYLINDER AND NR 3 CYLINDER BROKE OFF AT FLANGE CAUSING HIGH HEAT INSIDE COWL CAUSING IGNITION TO HEAT 	UP, OIL TEMPERATURE TO BE EXCESSIVELY HIGH, PLUS LOOSE EXHAUST ASSY JAMMED AILERON CONTROLS.  ERRATIC EGT ALSO NOTED.					1	M	7	1 	3O			NT	EXPA1M71					 
1996091200547	19960912	00547	CE  	1996	9	12	96ZZZX4390       	1	19960624	G	2434	30B10719A	GENERATOR       	BENDIX      		LEAR  	35    	35A         	5170602	CE  										RT ENGINE	FAILED          	A		A	GQVR	O				OTHER                   				E	H		VIBRATION/BUFFET          	ELECT. POWER LOSS-50 PC   		NR	NOT REPORTED   	1			SW	05	1AH		128  		2319	398				THE AIRCRAFT EXPERIENCED VIBRATION THEN GENERAL FAILURE ON THE RIGHT SIDE.  BEARING FAILURE WAS THE CAUSE OF THE PROBLEM	S.  THIS WAS THE SECOND TIME IN 130 FLIGHT HOURS SINCE GENERATOR OVERHAUL.					2	L	7	2 	4F				A10CE   					 
1996091200548	19960912	00548	CE  	1996	9	12	96ZZZX4391       	1	19960722	G	2434	30B1077F	GENERATOR       	BENDIX      		LEAR  	35    	36A         	5170603	CE  										RT ENGINE	FAILED          	A		A	GQVR	K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	05	53JA		201  		912	043				THE AIRCRAFT EXPERIENCED VIBRATIONS AND AMP FLUCTUATIONS.  THE PROBLEM WAS ISOLATED TO THE RIGHT GENERATOR.  GENERATOR R	EMOVAL REVEALED BEARING FAILURE.  THIS WAS THE SECOND FAILURE WITHIN 200 FLIGHT HOURS OF OVERHAUL.  THE LEFT GENERATOR, 	S/N 2400, HAD THE IDENTICAL PROBLEM TWICE WITHIN 600 FLIGHT HOURS OF OVERHAUL.				2	L	7	2 	4F				A10CE   					 
1996091200549	19960912	00549	CE  	1996	9	12	96ZZZX4392       	1	19960807	G	3240		BRAKE DISC      			BEECH 	55    	D55         	1152730	CE  										RT MLG	CHAFE SCISSORS  	B			BVMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	25JK					TE533				FOUND RIGHT BRAKE DISC RUBBING GEAR SCISSORS.  SUSPECT DISC ORDERED UNDER WRONG SERIAL NUMBERED AIRCRAFT.  BRAKE DISC OF	FSET .1250 INCH FROM PROPER P/N 164-27 DISC.  AXLE SPACER AND SHIMS NOT PROPERLY INSTALLED TO MAKE UP CLEARANCE.  FOUND 	DURING ANNUAL INSPECTION.				1	L	7	2 	3O				3A16    					 
1996091200550	19960912	00550	CE  	1996	9	12	96ZZZX4393       	1	19960807	G	3040		RESERVOIR       			BEECH 	55    	D55         	1152730	CE  										DE-ICE TANK	AV GAS FILLED   	B		A	BVMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	25JK					TE533				ANNUAL INSPECTION FOUND PROPELLER AND WINDSHIELD ALCOHOL RESERVOIRS FILLED WITH 100LL AV GAS.  SUSPSECT TANK MISTAKEN FO	R HEATER FUEL TANK.  FIRE HAZARD IF SYSTEM USED WITH ENGINES RUNNING.  TANK IS PROPERLY MARKED FOR DE-ICER FLUID.					1	L	7	2 	3O				3A16    					 
1996091200551	19960912	00551		1996	9	12	96ZZZX4394       	4	19960124	G	3416		JEWEL ASSY      	UNITEDINST  	5934        															ALTIMETER	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01					N2035					INACCURATE READINGS PLUS OR MINUS 60 FEET CAUSED BY INCORRECT JEWEL ASSY MISSING A CAP JEWEL.  THIS ALLOWED PIVOT SHOULD	ER TO RIDE AGAINST JEWEL FACE.  SUBMITTER STATED FROM THE LOOKS OF WORK DONE, IT INDICATES POOR WORKMANSHIP AND LACK OF 	TRAINING.  RECOMMEND THAT ONLY QUALIFIED PERSONNEL WORK ON CRITICAL DEVICES.																	 
1996091200553	19960912	00553	CE  	1996	9	12	96ZZZX4396       	1	19960731	G	5720	041332511	CHANNEL         			CESSNA	150   	152         	2071835	CE  										LT WING FWD SPAR	CORRODED        	B			LCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	5521H	7966 				15284111				WHEN LEFT DOORPOST TRIM WAS REMOVED FOR WINDSHIELD CHANGE, CORROSION WAS FOUND AT LEFT WING FORWARD SPAR CARRY-THROUGH A	REA.  WING WAS REMOVED.  BRACE AND CHANNEL WERE REPLACED.					1	H	7	1 	3O			NT	3A19    					 
1996091200554	19960912	00554	CE  	1996	9	12	96ZZZX4397       	1	19960731	G	5720	0411132	CHANNEL         			CESSNA	150   	152         	2071835	CE  										LT WG CARRY THRU	CORRODED        	B			LCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	5521H	7966 				15284111				WHEN LEFT DOORPOST TRIM WAS REMOVED FOR WINDSHIELD CHANGE, CORROSION WAS FOUND AT LEFT WING FORWARD SPAR CARRY-THROUGH A	REA.  WING WAS REMOVED.  BRACE AND CHANNEL WERE REPLACED.					1	H	7	1 	3O			NT	3A19    					 
1996091200555	19960912	00555	EA  	1996	9	12	96ZZZX4398       	2	19960722	G	7414	103493576	IMPULSE CAM     		1038255511  	CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B    	41514	EA  					MAGNETO	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	52073	426  				177RG1161	L1696551A			INSPECTED MAGNETO RIVETED CAM ASSY AND FOUND WORN BEYOND 'X' PLUS .014 INCH.  SUBMITTER STATES THESE EARLY RIVETED UNITS	 SHOULD BE CHANGED OUT TO THE SNAP RING STYLE AT 500 HOURS.  NEW STYLE FOR THIS APPLICATION IS 10-400167-9.					1	H	7	1 	3O	3	O		A20CE   	1E10				 
1996091200556	19960912	00556	SO  	1996	9	12	96ZZZX4399       	2	19960725	G	8530	625393	SPRING RETAINER 			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520U    	17040	SO  					EXH VALVE NR 3	FAILED          	B			QL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	112Z	1336 				TJ371	274153R			WHILE CHANGING VALVE COVER GASKET ON NR 3 CYLINDER, MECHANIC FOUND TWO SMALL PIECES OF METAL IN VALVE COVER.  INVESTIGAT	ED AND DETERMINED PIECES CAME FROM THE EXHAUST VALVE INNER VALVE SPRING RETAINER TCM.  PERFORMED HIDDEN DAMAGE INSPECTIO	N.  INSPECTED AND CHECKED OK.  INSTALLED NEW SPRING RETAINER.  ENGINE IS A TCM FACTORY REMANUFACTURED WITH 1,336 HOURS T	SMOH.			1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1996091200557	19960912	00557	EU  	1996	9	12	96ZZZX4400       	2	19960627	G	8530		PISTON          			AMTR  	500   	MINI500     	13015HW	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					SKIRT	UNDERSIZE       	F	L	A		K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CE	05	500ZZ					0000	4655214			THE ENGINE BACKFIRED AND MOMENTARILY HAD A LOSS OF POWER.  THE PISTONS WERE FOUND UNDERSIZED AT THE SKIRT END.  THIS COU	LD HAVE POSSIBLY BEEN CAUSED BY IMPROPER BREAK IN PROCEDURES.					1	G	7	1 	3I	3	I	NC	EXPA1G71	EXPE3I				 
1996091200558	19960912	00558	EA  	1996	9	12	96ZZZX4401       	2	19960807	G	7414	1038255514	MAGNETO         			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	IO360A1G6   	41514	EA  					RT ENGINE	SEPARATED       	D				O				OTHER                   				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			WP	27	66291					ME224				MAGNETO SEPARATED FROM ENGINE ON TAKEOFF CAUSING ENGINE TO STOP.  THIS IS A DUAL MAGNETO ON A SINGLE DRIVE.  IT WAS DETE	RMINED THE NUTS HAD LOOSENED AND ALLOWED MAG TO COME OFF.  THERE IS NO TORQUE LISTED FOR THIS MAGNETO EXCEPT STANDARD TO	RQUE.  RECOMMEND THAT MAGNETO ATTACHMENTS BE CHECKED AT 50-HOUR INTERVALS.  ALSO, MAG NEEDS TO BE CHECKED FOR NEW STYLE 	HOLD-DOWN BRACKETS.  TIME SINCE LAST CHECK OF HOLD-DOWN NUTS WAS APPROXIMATELY 80 HOURS.			1	L	7	2 	3O	3	O		A29CE   	1E10				 
1996091200559	19960912	00559	EA  	1996	9	12	96ZZZX4402       	2	19960729	G	8520		CRANKSHAFT      			BOEING	75    	A75N1       	1380134	CE  	WRIGHT	R975  	R975*       	67012	EA  					HUB SOCKET	SCREWS FAILED   	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			WP	27	68251		700  			757976	78224			AFTER TAKEOFF, ENGINE STOPPED.  AIRCRAFT CRASH LANDED IN A FIELD.  AIRCRAFT DESTROYED BY POST-FIRE.  INVESTIGATION FOUND	 CRANKSHAFT GEAR ASSEMBLY HUB SOCKET SCREWS SHEARED.  P/N 401337.  TSO:  700 HOURS.  TT:  UNKNOWN.					1	Q	7	1 	3R	3	R		A743    	ATC21				 
1996091200560	19960912	00560	EA  	1996	9	12	96ZZZX4403       	2	19960801	G	8550	68759	LINE            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					NR 1 CYL OIL	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	738WK					R18200969	L2099840A			WHILE TROUBLESHOOTING AN ALTERNATOR PROBLEM, FOUND THE OIL RETURN LINE ON NR 1 CYLINDER HAD ALTERNATOR WIRE HARNESS TY-W	RAP TO IT.  REMOVED TY-WRAP TO INSPECT THE WIRE HARNESS, AND THE LINE WAS FOUND CHAFED MORE THAN 75 PERCENT THROUGH THE 	WALL THICKNESS.  SUBMITTER STATED TY-WRAPPING WIRES DIRECTLY TO THESE ALUMINUM LINES IS COMMON, BUT SHOULD HAVE SOME KIN	D OF PROTECTION FROM CHAFING.			1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1996091200561	19960912	00561	CE  	1996	9	12	96ZZZX4404       	1	19960809	G	5712	95110014191	RIB             			BEECH 	60    	B60         	1153605	CE  										LT-RT WS 64	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	75RL					P390				WHILE PERFORMING ANNUAL INSPECTION, THE WING TRAILING EDGE RIBS AND ATTACHING CLIPS AT STA'S 64, 74, AND 89 WERE FOUND C	RACKED ON LEFT AND RIGHT WINGS.  SUBMITTER STATED IT APPEARED DURING REMOVAL THE RIBS WERE STRESSED TO OBTAIN PROPER ALI	GNMENT.  THIS AREA IS DIFFICULT TO SEE WITH FLAPS INSTALLED, BUT NOT IMPOSSIBLE.  MOST CRACKS WERE AT THE NOTCH-OUT AREA	 FOR THE SKIN STIFFENER.			1	L	7	2 	3O				A12CE   					 
1996091200562	19960912	00562	CE  	1996	9	12	96ZZZX4405       	1	19960809	G	5712	95110014129	RIB             			BEECH 	60    	B60         	1153605	CE  										LT-RT WS 74	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	75RL					P390				WHILE PERFORMING ANNUAL INSPECTION, THE WING TRAILING EDGE RIBS AND ATTACHING CLIPS AT STA'S 64, 74, AND 89 WERE FOUND C	RACKED ON LEFT AND RIGHT WINGS.  SUBMITTER STATED IT APPEARED DURING REMOVAL THE RIBS WERE STRESSED TO OBTAIN PROPER ALI	GNMENT.  THIS AREA IS DIFFICULT TO SEE WITH FLAPS INSTALLED, BUT NOT IMPOSSIBLE.  MOST CRACKS WERE AT THE NOTCH-OUT AREA	 FOR THE SKIN STIFFENER.			1	L	7	2 	3O				A12CE   					 
1996091200563	19960912	00563	CE  	1996	9	12	96ZZZX4406       	1	19960809	G	5712	95110014153	RIB             			BEECH 	60    	B60         	1153605	CE  										LT-RT WS 89	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	75RL					P390				WHILE PERFORMING ANNUAL INSPECTION, THE WING TRAILING EDGE RIBS AND ATTACHING CLIPS AT STA'S 64, 74, AND 89 WERE FOUND C	RACKED ON LEFT AND RIGHT WINGS.  SUBMITTER STATED IT APPEARED DURING REMOVAL THE RIBS WERE STRESSED TO OBTAIN PROPER ALI	GNMENT.  THIS AREA IS DIFFICULT TO SEE WITH FLAPS INSTALLED, BUT NOT IMPOSSIBLE.  MOST CRACKS WERE AT THE NOTCH-OUT AREA	 FOR THE SKIN STIFFENER.			1	L	7	2 	3O				A12CE   					 
1996091200564	19960912	00564	CE  	1996	9	12	96ZZZX4407       	1	19960805	G	2752	C3010020103	MOTOR           			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					FLAP	SHORTED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	7513G	4089 				15074679	242709R			FLAPS EXCEEDED THE LIMIT SWITCH, STOPS, AND BROKE THE DOWN-LIMIT SWITCH AND FUSE BLEW.  PROBLEM WAS CAUSED BY FLAP MOTOR	 DEVELOPED AN INTERNAL SHORT WHICH PROVIDED THE GROUND NORMALLY WHICH IS PROVIDED THROUGH THE LIMIT SWITCH CIRCUIT.  THI	S MOTOR IS A REVERSING 12V DC MOTOR WHICH CHANGES POWER AND GROUND CIRCUIT THROUGH THE SWITCH AND LIMIT SWITCHES NORMALL	Y.  NO LOG ENTRY SHOWS MOTOR CHANGED PREVIOUSLY.			1	H	7	1 	3O	3	O		3A19    	E252				 
1996091200565	19960912	00565	SO  	1996	9	12	96ZZZX4408       	2	19960625	G	8550	CH48109	FILTER          	CHAMPION    		PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					ENGINE OIL	BROKEN          	B			JAVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	94MA	23   			F11E111	468608056	273793R			AFTER CUTTING OIL FILTER OPEN, THE MANUFACTURER'S ANTI-DRAIN BACK VALVE ROLLED EDGE WAS FOUND CRACKED APPROXIMATELY ONE-	HALF WAY AROUND AND A PIECE, APPROXIMATELY 1 INCH LONG, HAD BROKEN OFF.  BROKEN PIECES WERE FOUND AFTER OIL COOLER WAS R	EMOVED AND BACK-FLUSHED.				1	L	7	1 	3O	3	O		A25SO   	E8CE				 
1996091200566	19960912	00566	CE  	1996	9	12	96ZZZX4409       	1	19960613	G	3211	05411212	SUPPORT         			CESSNA	172   	172G        	2072420	CE  										MLG OTBD RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	173DA	4500 				17253664				WHILE CHANGING A BROKEN U-BOLT, NOTICED POSSIBLE CRACK ON MLG OUTBOARD SUPPORT AT FORWARD HOLE WHERE U-BOLT ATTACHES.  C	RACK CONFIRMED BY NDT.  SUSPECT CAUSE WAS BROKEN U-BOLT CONCENTRATING STRESSES AT FORWARD HOLE.					1	H	7	1 	3O			NT	3A12    					 
1996091200567	19960912	00567	CE  	1996	9	12	96ZZZX4410       	1	19960613	G	3211	0541153	U-BOLT          			CESSNA	172   	172G        	2072420	CE  										RT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	173DA	4500 				17253664				DURING 100-HOUR INSPECTION, FOUND RIGHT MLG U-BOLT BROKEN.  UPON INSPECTION OF BOLT, SUBMITTER STATED IT APPEARS A CRACK	 HAD BEEN EVIDENT AND HAD FINALLY FAILED POSSIBLY DUE TO A HARD LANDING.					1	H	7	1 	3O			NT	3A12    					 
1996091200568	19960912	00568	CE  	1996	9	12	96ZZZX4411       	1	19960713	G	7160		HEAT VALVE      			CESSNA	150   	150L        	2071826	CE  										CARBURETOR INLET	LOOSE           	B		A	PN9R	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			GL	13	18071					15073773				ENGINE WAS NOT DEVELOPING POWER.  UPON INSPECTION, FOUND THE CARBURETOR HEAT DOOR HAD BECOME LOOSE ON THE SHAFT GIVING N	O CONTROL TO THE CARBURETOR HEAT.  SUBMITTER STATED THIS WAS CAUSED BY CORROSION UNDER THE WELD THAT ATTACHES THE DOOR T	O THE SHAFT.  TO PREVENT THIS, THE DOOR SHOULD BE RIVETED TO THE SHAFT.				1	H	7	1 	3O				3A19    					 
1996091200569	19960912	00569	SO  	1996	9	12	96ZZZX4412       	1	19960813	G	2810		FUEL CAP        			PIPER 	PA38  	PA38112     	7103812	SO  										LT WING	WATER LEAK      	G	L	A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CE	05	2466D					3879A0324				WATER IN LEFT WING FUEL TANK RESULTED IN AN EMERGENCY LANDING WITH THE LEFT WING TIP RECEIVING MINOR DAMAGE.    SUSPECT 	DUE TO FUEL CAP NOT PROPERLY INSTALLED.					1	L	7	1 	3O				A18SO   					 
1996091200570	19960912	00570	SO  	1996	9	12	96ZZZX4413       	1	19960802	G	5280	4205907	HINGE           			PIPER 	PA31T 	PA31T       	7103124	SO  										RT OTBD GR DOOR	FAILED          	B			AU3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	6080A	2275 				31T7820077				PILOT REPORTED FINDING OUTBOARD GEAR DOOD HINGE FAILED DURING PRE-FLIGHT.  IT IS ASSUMED HINGE FAILED ON LAST FLIGHT.  F	AILED AREA SHOWED SIGNS OF BEING CRACKED PREVIOUSLY.  OTHER 3 REMAINING HINGES INSPECTED, NO DEFECTS NOTED.					1	L	7	2 	3T				A8EA    					 
1996091200571	19960912	00571	SW  	1996	9	12	96ZZZX4414       	1	19960802	G	2436	800331721	ADAPTER         	ELECTRODELTA	VR415F      	MOONEY	M20   	M20C        	5870208	SW  										DC SYSTEM	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	6980V					201195				QEM REGULATOR, P/N 20082, WAS NOT AVAILABLE SO A ELECTRODELTA REGULATOR, P/N VR415F, THAT HAS A DIFFERENT CONNECTOR WAS 	INSTALLED WITH ADAPTER CABLE, P/N 800331-721.  THE QEM REGULATOR INTERNAL GROUND ORIGINALLY ATTACHED TO SHELL OF ALUMINU	M MS TYPE CANNON PLUG, ADAPTER ELIMINATES GROUND PATH.  AFTER INSTALLATION, MS PORTION OF PLUG WAS LAYING AGAINST REGULA	TOR MAKING HIGH RESISTANCE CONTACT CAUSING ERRATIC OPERATION OF CHARGING SYSTEM.  RE-LOCATING GROUND CORRECTED CONDITION	.  MANUFACTURER OF REGULATOR SHOULD CAUTION ABOUT THIS.		1	L	7	1 	3O				2A3     					 
1996091200572	19960912	00572	SO  	1996	9	12	96ZZZX4415       	2	19960117	G	8530	538283	CYLINDER        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					CYLS 1,3,4, EXH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1321G					310R0701	565272			FOUND SMALL CRACKS LEADING FROM SPARK PLUG HOLES AROUND TO THE EXHAUST PORTS ON NR 1, NR 3, AND NR 4 CYLINDERS.  A BRIGH	T FLASHLIGHT AND MAGNIFING GLASS WERE USED TO FIND THE CRACKS DURING A 100-HOUR INSPECTION.  DYE CHECK WOULD NOT PICK UP	 ONE CRACK.				1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996091200574	19960912	00574	CE  	1996	9	12	96ZZZX4417       	1	19960717	G	3242	16432505	DISC            	PARKERHANFIN		BEECH 	36    	A36         	1151604	CE  										RT BRAKE	FAILED          	D	S			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21VR	1755 				E2468				DISC TORN OFF WHEEL LEAVING METAL UNDER BOLTS INTACT ON WHEEL.  THIS IS THE SECOND DISC TO FAIL ON THIS AIRCRAFT.  ON 12	-26-95, THE LEFT BRAKE DISC FAILED UNDER SIMILAR CONDITIONS (1,617 TIS).  SUBMITTER STATED COULD BE CAUSED BY IMPROPER A	LLOY CASTINGS OR BY CRACKS AROUND BOLT HOLE.				1	L	7	1 	3O				3A15    					 
1996091200575	19960912	00575	SO  	1996	9	12	96ZZZX4418       	1	19960312	G	2810	461722	CELL            			PIPER 	PA31T 	PA31T2      	7103127	SO  										LT INBOARD	LEAKING         	B			ESMR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	11	2501Y				74231	31T8166013				LEFT INBOARD FUEL CELL LEAKING AT PUMP MOUNTING PAD.  3-12-96- REMOVED.						1	L	7	2 	3T			RT	A8EA    					 
1996091200576	19960912	00576	SO  	1996	9	12	96ZZZX4419       	1	19960313	G	2810	527784	FUEL CELL       			PIPER 	PA31T 	PA31T2      	7103127	SO  										PUMP PAD	MOUNT SEPARATED 	B			ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	2501Y				7616399	31T8166013				AFT FUEL PUMP  MOUNTING PAD SEPARATED FROM FUEL CELL, LOWER LEFT CORNER.  3-13-96 INSTALLED.						1	L	7	2 	3T			RT	A8EA    					 
1996091200578	19960912	00578	SO  	1996	9	12	96ZZZX4421       	2	19960616	G	7314	LW15473	PUMP            			MOONEY	M20   	M20J        	5870219	SW  	CONT  	O360  	IO360A      	17025	SO  					ENGINE FUEL	FAILED          	D		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SO	09	5774J	98   			154739510	241509	L223909			AIRCRAFT FORCED LANDING DUE TO FUEL STARVATION TO ENGINE.  INVESTIGATION REVEALED THAT NO FUEL COULD BE PUMPED THROUGH T	HE ENGINE DRIVEN PUMP.  APPEARED TO BE BLOCKED INTERNALLY.  NO OTHER DEFECTS WERE FOUND IN THE FUEL SYSTEM.  ALL SCREENS	 WERE FOUND TO BE CLEAN.  BOOST PUMP OPERATION OK AS WELL.				1	L	7	1 	3O	3	O		2A3     	E1CE				 
1996091200579	19960912	00579	CE  	1996	9	12	96ZZZX4422       	1	19960816	G	2510		HARNESS         			CESSNA	188   	T188C       	2073012	CE  										PILOT	FAILED          	G		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	2081J					T18803371T				PILOT'S SHOULDER HARNESS WEBBING BROKE.  WAS NOTED DURING ACCIDENT INVESTIGATION.  SUBMITTER STATED COULD BE A RESULT OF	 FORCES DURING IMPACT.  WEBBING MAY HAVE BEEN 'SUN' DETERIORATED.					1	L	7	1 	3O				A9CE    					 
1996091200580	19960912	00580	GL  	1996	9	12	96ZZZX4423       	1	19960716	G	7603	2076000113	CONTROL CABLE   			DIAMON	DA20A1	DA20A1      	05626UX	GL  										THROTTLE	WIRE BROKEN     	B			TV3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	614P	1203 				10014				THROTTLE CONTROL PIANO WIRE BROKE WHERE HOUSING PASSES THROUGH FIREWALL.  WIRE APPEARS TO BE WORK HARDENED AND BRITTLE. 	 HOUSING TAKES HARD BEND AFTER PASSING THROUGH FIREWALL.					1	L	7	1 	3O			NT	TA4CH   					 
1996091200582	19960912	00582	SO  	1996	9	12	96ZZZX4425       	2	19960801	G	7414	10400309	IMPULSE COUPLER 			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE MAG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	255EM					TC1552				WHILE C/W AD 78-09-07R3, AN IMPULSE COUPLER WAS FOUND TO NEED REPLACEMENT.  A NEW PART WAS INSTALLED ON MAG.  WHILE TIGH	TENING NUT ON COUPLER TO 240 INCH/POUNDS, THE COUPLER CRACKED WHERE IT SLIDES ON THE TAPERED SHAFT.  SUBMITTER FOUND THA	T IMPULSE COUPLERS THAT ARE CHECKED ARE ONLY LASTING FOR ONE CYCLE (500 HOURS) OF AD INSPECTION, WHERE IN THE PAST, AN I	MPULSE COUPLER WOULD OFTEN LAST FOR 1,000 HOURS OR MORE.  SUBMITTER SUSPECTS THE MATERIAL USED FOR NEW UNITS IS NOT AS G	OOD A MATERIAL AS WAS USED IN THE PAST.		1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
1996091200583	19960912	00583		1996	9	12	96ZZZX4426       	1	19960410	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.  REPORTED OPERATOR:  SKYWEST.																			 
1996091200584	19960912	00584		1996	9	12	96ZZZX4427       	1	19960419	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.  REPORTED OPERATOR:  WESTAIR.																			 
1996091200585	19960912	00585		1996	9	12	96ZZZX4428       	1	19960419	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.  REPORTED OPERATOR:  WESTAIR.																			 
1996091200586	19960912	00586		1996	9	12	96ZZZX4429       	1	19960426	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.  REPORTED OPERATOR:  SKYWEST.																			 
1996091200587	19960912	00587		1996	9	12	96ZZZX4430       	1	19960507	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.  REPORTED OPERATOR:  SKYWEST.																			 
1996091200588	19960912	00588		1996	9	12	96ZZZX4431       	1	19960509	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.  REPORTED OPERATOR:  SKYWEST.																			 
1996091200589	19960912	00589		1996	9	12	96ZZZX4432       	1	19960501	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.  REPORTED OPERATOR:  SKYWEST.  SIX UNITS FAIL	ED OR WERE DEFECTIVE.																		 
1996091200590	19960912	00590		1996	9	12	96ZZZX4433       	1	19960509	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.  REPORTED OPERATOR:  WESTAIR.																			 
1996091200591	19960912	00591		1996	9	12	96ZZZX4434       	1	19960514	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.  REPORTED OPERATOR:  SKYWEST.																			 
1996091200592	19960912	00592		1996	9	12	96ZZZX4435       	1	19960514	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.  REPORTED OPERATOR:  SKYWEST.																			 
1996091200593	19960912	00593		1996	9	12	96ZZZX4436       	1	19960419	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.  REPORTED OPERATOR:  WESTAIR.																			 
1996091200594	19960912	00594		1996	9	12	96ZZZX4437       	1	19960520	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.  REPORTED OPERATOR:  WESTAIR.																			 
1996091200595	19960912	00595		1996	9	12	96ZZZX4438       	1	19960528	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.  REPORTED OPERATOR:  DELTA.																			 
1996091200596	19960912	00596		1996	9	12	96ZZZX4439       	1	19960612	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.  REPORTED OPERATOR:  SKYWEST.																			 
1996091200597	19960912	00597		1996	9	12	96ZZZX4440       	1	19960620	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.  REPORTED OPERATOR:  SKYWEST.																			 
1996091200598	19960912	00598		1996	9	12	96ZZZX4441       	1	19960621	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.  REPORTED OPERATOR:  WESTAIR.																			 
1996091200599	19960912	00599		1996	9	12	96ZZZX4442       	1	19960514	G	3320	BR6303102	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.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200600	19960912	00600		1996	9	12	96ZZZX4443       	1	19960620	G	3320	BR6303102	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.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200601	19960912	00601		1996	9	12	96ZZZX4444       	1	19960620	G	3320	BR6303102	LAMP HOLDER     	BRUCE       																CABIN LIGHTS	BUTTON MISSING  	B			ZZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200602	19960912	00602		1996	9	12	96ZZZX4445       	1	19960507	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.  REPORTED OPERATOR:  PANOR.																			 
1996091200603	19960912	00603		1996	9	12	96ZZZX4446       	1	19960507	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.  REPORTED OPERATOR:  PANOR.																			 
1996091200604	19960912	00604		1996	9	12	96ZZZX4447       	1	19960507	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.  REPORTED OPERATOR:  PANOR.																			 
1996091200605	19960912	00605		1996	9	12	96ZZZX4448       	1	19960509	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.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200606	19960912	00606		1996	9	12	96ZZZX4449       	1	19960514	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.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200607	19960912	00607		1996	9	12	96ZZZX4450       	1	19960507	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.  REPORTED OPERATOR:  PANOR.																			 
1996091200608	19960912	00608		1996	9	12	96ZZZX4451       	1	19960426	G	3320	BR63031023	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.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200609	19960912	00609		1996	9	12	96ZZZX4452       	1	19960628	G	3320	BR63031023	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.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200610	19960912	00610		1996	9	12	96ZZZX4453       	1	19960509	G	3320	BR63031023	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.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200611	19960912	00611		1996	9	12	96ZZZX4454       	1	19960509	G	3320	BR63031023	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.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200612	19960912	00612		1996	9	12	96ZZZX4455       	1	19960617	G	3320	BR63031023	LAMP HOLDER     	BRUCE       																CABIN LIGHTS	WILL NOT LOCK   	B			ZZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11										CABIN LIGHTING LAMP HOLDER RETURNED TO REPAIR STATION FOR BEING DEFECTIVE.  REPORTED OPERATOR:  PIEDMONT.																			 
1996091200727	19960912	00727		1996	9	12	96ZZZX4471       	1	19960104	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.																			 
1996091200728	19960912	00728		1996	9	12	96ZZZX4472       	1	19960112	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.																			 
1996091200729	19960912	00729		1996	9	12	96ZZZX4473       	1	19960111	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.																			 
1996091200730	19960912	00730		1996	9	12	96ZZZX4474       	1	19960123	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.																			 
1996091200731	19960912	00731		1996	9	12	96ZZZX4475       	1	19960123	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.																			 
1996091200732	19960912	00732		1996	9	12	96ZZZX4476       	1	19960126	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.																			 
1996091200733	19960912	00733		1996	9	12	96ZZZX4477       	1	19960201	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.																			 
1996091200734	19960912	00734		1996	9	12	96ZZZX4478       	1	19960207	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.																			 
1996091200735	19960912	00735		1996	9	12	96ZZZX4479       	1	19960207	G	3320	BC10047005	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:  SKYWEST.																			 
1996091200736	19960912	00736		1996	9	12	96ZZZX4480       	1	19960215	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.																			 
1996091200737	19960912	00737		1996	9	12	96ZZZX4481       	1	19960318	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.																			 
1996091200738	19960912	00738		1996	9	12	96ZZZX4482       	1	19960315	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.																			 
1996091200739	19960912	00739		1996	9	12	96ZZZX4483       	1	19960102	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:  AGES GROUP.																			 
1996091200740	19960912	00740		1996	9	12	96ZZZX4484       	1	19960103	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.																			 
1996091200741	19960912	00741		1996	9	12	96ZZZX4485       	1	19960103	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.																			 
1996091200742	19960912	00742		1996	9	12	96ZZZX4486       	1	19960122	G	3320	BR63031021	LAMP TAB        	BRUCE       																CABIN LIGHTS	MISSING         	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.																			 
1996091200743	19960912	00743		1996	9	12	96ZZZX4487       	1	19960122	G	3320	BR63031021	LAMP TAB        	BRUCE       																CABIN LIGHTS	MISSING         	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.																			 
1996091200744	19960912	00744		1996	9	12	96ZZZX4488       	1	19960201	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:  AGES GROUP.																			 
1996091200745	19960912	00745		1996	9	12	96ZZZX4489       	1	19960212	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.																			 
1996091200746	19960912	00746		1996	9	12	96ZZZX4490       	1	19960213	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.																			 
1996091200747	19960912	00747		1996	9	12	96ZZZX4491       	1	19960214	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.																			 
1996091200748	19960912	00748		1996	9	12	96ZZZX4492       	1	19960223	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.																			 
1996091200749	19960912	00749		1996	9	12	96ZZZX4493       	1	19960223	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.																			 
1996091200750	19960912	00750		1996	9	12	96ZZZX4494       	1	19960311	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.																			 
1996091200751	19960912	00751		1996	9	12	96ZZZX4495       	1	19960313	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.																			 
1996091200752	19960912	00752		1996	9	12	96ZZZX4496       	1	19960313	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.																			 
1996091200753	19960912	00753		1996	9	12	96ZZZX4497       	1	19960313	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.																			 
1996091200754	19960912	00754		1996	9	12	96ZZZX4498       	1	19960318	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.																			 
1996091200755	19960912	00755		1996	9	12	96ZZZX4499       	1	19960318	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.																			 
1996091200807	19960912	00807		1996	9	12	96ZZZX4551       	1	19960222	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.																			 
1996091900236	19960919	00236	WP  	1996	9	19	96ZZZX4607       	1	19960730	G	3246	2601483	BOLT            		2608871     	DOUG  	DC9   	DC9*        		WP  										WHEEL	FAILED          	B			LU5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17										FATIGUE RELATED FAILURE OF MD80 WHEEL TIE BOLTS.  INSUFFICIENT TIE BOLT PRELOAD TORQUE.  SUBMITTER SUGGESTS PREVENTIVE A	CTION, USE SNUG ANGLE TORQUE METHOD.					2	L	7	2 	4F				A6WE    					 
1996091900238	19960919	00238	NM  	1996	9	19	96ZZZX4609       	1	19960719	G	2761	654494711	HOUSING         		65448517    	BOEING	737   	737300      	1384610	NM  										SPOILER	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4475					HOUSING IS CRACKED IN THE BEARING RECESS AREA EXTENDING LATERALLY FROM THE RETRACT PRESSURE PORT.  THIS MAY BE CAUSED BY	 A LACK OF PISTON SNUBBING ACTION DURING GROUND NO-LOAD CONDITIONS.  SUBMITTER RECOMMENDS A RE-DESIGN OF THE HOUSING ASS	EMBLY BY STRENGTHENING THE BEARING RECESS AREA AND RESTRICTING SPOILER MOVEMENT DURING NO-LOAD GROUND OPERATIONS.				2	L	7	2 	4F			RT	A16WE   					 
1996091900239	19960919	00239	NM  	1996	9	19	96ZZZX4610       	1	19960719	G	2782	69358861	RESTRICTOR PLUG 		65446517    	BOEING	737   	737*        		NM  										LE SLAT ACTUATOR	DEBRIS PLUGGED  	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					448					RETRICTOR PLUGS (8) WERE PLUGGED UP WITH DEBRIS.						2	L	7	2 	4F			RT	A16WE   					 
1996091900240	19960919	00240	NM  	1996	9	19	96ZZZX4611       	1	19960719	G	2782	71001291	ACTUATOR        			BOEING	727   	727         	1384001	NM  										TRUNNION	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					0043					SLAT ACTUATOR CRACKED INSIDE TRUNNION.  SUBMITTER RECOMMENDS MANUFACTURING PROCESS TO SMOOTH OUT SHARP EDGES OF PORT.						2	L	7	3 	4F				A3WE    					 
1996020200275	19960202	00275	SW  	1996	2	2	96ZZZX462        	1	19960109	G	7160	600118015	DOOR            			MOONEY	M20   	M20J        	5870219	SW  										ALT AIR DOOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	4566H	2626 				240848				DURING C/W AD 95-26-16, RIVETS HOLDING NUTPLATE TO ALTERNATE AIR DOOR WERE FOUND LOOSE ALLOWING NUTPLATE TO WEAR THROUGH	 APPROXIMATELY ONE-HALF OF THICKNESS AT THE DOOR.  MOONEY SB M20-250B AND SB M20-253A AND AD 95-26-16R1, ADDRESS THIS PR	OBLEM.				1	L	7	1 	3O				2A3     					 
1996091900249	19960919	00249		1996	9	19	96ZZZX4620       	1	19960801	G	2822	1B58	PUMP            	AIRBORNE    																ARMATURE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					8M43					BOOST PUMP POSSIBLY WAS RUN DRY, CAUSING SEVERE DAMAGE TO ARMATURE.																			 
1996091900251	19960919	00251	CE  	1996	9	19	96ZZZX4622       	1	19960803	G	2910		LINE            			CESSNA	206   	206CESSNA   	2073302	CE  										HYD PUMP	CHAFE/LEAK      	D		A		O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	99										HYDRAULIC LINE CHAFED ON HYDRAULIC PUMP WITH LOSS OF FLUID.  AIRCRAFT GEAR-UP LANDING WITH ONLY NOSE WHEEL EXTENDED.  DA	MAGE TO GEAR DOORS AND RIGHT HORIZONTAL STABILIZER.  ALSO, AFT BULKHEAD DAMAGED.					1	H	7	1 	3O				A4CE    					 
1996091900252	19960919	00252	SO  	1996	9	19	96ZZZX4623       	2	19960801	G	7322	39077	NEEDLE VALVE    	BENDIX      	NAS3A1      	CESSNA	140   	140         	2071602	CE  	CONT  	C90   	C9012F      	17009	SO  					FLOAT CHAMBER	SWELLED UP      	G				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			NM	06										CARBURETOR FLOAT CHAMBER NEEDLE VALVE TIP SWELLED UP, PROBABLY DUE TO 100 LL OR AUTOGAS.  ENGINE FALTERED AT HIGH POWER 	SETTINGS.  TAKEOFF ABORTED.					1	H	7	1 	3O	3	O	NC	A768    	E252				 
1996091900253	19960919	00253		1996	9	19	96ZZZX4624       	1	19960807	G	2822	1D217	PUMP            	AIRBORNE    																FUEL BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					11AE106					FUEL PUMP ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996091900254	19960919	00254	NM  	1996	9	19	96ZZZX4625       	1	19960720	G	6320	A0061	TRANSMISSION    			ROBSIN	R22   	R22BETA     		NM  										M/R	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	11	22640	2120 	120  			0502				DURING PRE-FLIGHT INSPECTION, PILOT NOTICED A PUDDLE OF OIL (BLUE IN COLOR) ON THE GROUND BENEATH THE HELICOPTER.  INSPE	CTION OF THE HELICOPTER BY A MAINTENANCE TECHNICIAN REVEALED TRANSMISSION OIL WAS  LEAKING FROM THE LOWER TRANSMISSION H	OUSING COVER PARTING SURFACE.  INSPECTION OF TRANSMISSION COVER AFTER DISASSEMBLY REVEALED POROSITY IN AREA OF O-RING SE	ALING SURFACE OF THE COVER.  THE O-RING SHOWS INDICATION OF POROSITY TRANSFER MARKS IN O-RING.			1	G	7	1 	3O				H10WE   					 
1996091900255	19960919	00255	NM  	1996	9	19	96ZZZX4626       	1	19960821	G	6310	A0511	CLUTCH ACTUATOR 			ROBSIN	R22   	R22BETA     		NM  										M/R DRIVE	BLOWS FUSES     	D		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	23	8338Q	21   			3273	2614				THE NEW AIRCRAFT WAS BEING FERRIED FROM CALIFORNIA TO NEBRASKA.  DURING A FUEL STOP, THE 1.5 AMP FUSE FOR THE CLUTCH ACT	UATOR WAS FOUND 'BLOWN'.  THE FUSE WAS REPLACED BY THE PILOT WITH A 1 AMP.  DURING A LATER FUEL STOP, THE FUSE WAS FOUND	 BLOWN AGAIN AND THE PILOT NOTICED THE A190-2 V-BELTS WERE SEVERELY DAMAGED.  FURTHER INSPECTION SHOWED THE CLUTCH ACTUA	TOR SPRINGS POPPED WEAKLY WHEN THE BOLTS WERE TENSIONED, BUT CONTINUED TO INCREASE THE TENSION UNTIL THE FUSE BLEW.  THE	 V-BELTS AND CLUTCH ACTUATOR WERE REPLACED WITH NEW, AND THE FLIGHT WAS COMPLETED.		1	G	7	1 	3O				H10WE   					 
1996091900256	19960919	00256	NM  	1996	9	19	96ZZZX4627       	1	19960821	G	6310	A1902	BELT            			ROBSIN	R22   	R22BETA     		NM  										M/R DRIVE	DAMAGED         	D		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	23	8338Q	21   				2614				THE NEW AIRCRAFT WAS BEING FERRIED FROM CALIFORNIA TO NEBRASKA.  DURING A FUEL STOP, THE 1.5 AMP FUSE FOR THE CLUTCH ACT	UATOR WAS FOUND 'BLOWN'.  THE FUSE WAS REPLACED BY THE PILOT WITH A 1 AMP.  DURING A LATER FUEL STOP, THE FUSE WAS FOUND	 BLOWN AGAIN AND THE PILOT NOTICED THE A190-2 V-BELTS WERE SEVERELY DAMAGED.  FURTHER INSPECTION SHOWED THE CLUTCH ACTUA	TOR SPRINGS POPPED WEAKLY WHEN THE BOLTS WERE TENSIONED, BUT CONTINUED TO INCREASE THE TENSION UNTIL THE FUSE BLEW.  THE	 V-BELTS AND CLUTCH ACTUATOR WERE REPLACED WITH NEW, AND THE FLIGHT WAS COMPLETED.		1	G	7	1 	3O				H10WE   					 
1996091900258	19960919	00258	SO  	1996	9	19	96ZZZX4629       	1	19960809	G	3320	BR9800005	LAMP            	BRUCE       	BCI0047005  	EMB   	120   	EMB120RT    		SO  										CABIN LIGHT	BURN DAMAGE     	B			ZZBR	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			WP	11										FOUND LAMP UNIT WITH BURN DAMAGE.  REFER TO BRUCE INDUSTRIES, INC., DOCUMENT NR 350-149.  A DESIGN CHANGE WAS INCORPORAT	ED ON BRUCE IND. INC., DRAWING BR9800 TO REDUCE THE LENGTH AT THE STARTING AID BY .9 INCH (11-13-95).					2	L	7	2 	4T			RT	A31SO   					 
1996091900259	19960919	00259	EU  	1996	9	19	96ZZZX4630       	1	19960809	G	3320	BV501258	LAMP HOLDER     	BRUCE       	BCI0004001  	BAC   	146   	AVRO146RJ100	1500096	EU  										CABIN	BURN DAMAGE     	B			ZZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11										FOUND LAMP HOLDER WITH BURN DAMAGE.  APPARENTLY EXTERNAL HEAT SOURCE.						2	H	7	4 	4F			RT	A49EU   					 
1996091900260	19960919	00260	NM  	1996	9	19	96ZZZX4631       	1	19960827	G	2121	71912	END BELL        	SUNDSTRANDEM	65771       	BOEING	727   	727         	1384001	NM  										BEARING BORE	WORN            	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		546  			888					FAN END BELL BEARING BORE WORN OVERSIZE AFTER 545.5 HOURS OF OPERATION.						2	L	7	3 	4F				A3WE    					 
1996091900261	19960919	00261	NE  	1996	9	19	96ZZZX4632       	2	19960812	G	7230	771706	BLADE           								PWA   	JT8   	JT8D219     	52053	NE  					LOW COMP C6	FAILED          	B			VV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19			60   				725425			THE ENGINE WAS INSPECTED FOR CUSTOMER WHO REPORTED 'SURGE DURING CRUISE', AND C6, 7 AND 13 STAGE BLADE DAMAGE.  DISASSEM	BLY FINDINGS REVEALED 2 EACH LIBERATED C6 BLADES AND EXTENSIVE DAMAGE TO HPC.  THE FAILED BLADES ARE UNDER INVESTIGATION	 AT GREENWICH-TEXAS.									4	F			E9NE				 
1996091900478	19960919	00478	SW  	1996	9	19	96ZZZX4642       	1	19960720	G	6330	206033506101	RESTRAINT SPRING		LK0104      	BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	BEARING WORN    	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2616		550  			51418				RESTRAINT SPRING BEARINGS WORN BEYOND LIMITS.  REPLACED BEARINGS, 2 EACH, P/N 206-033-509-003.						1	G	7	1 	3U				H2SW    					 
1996091900479	19960919	00479	SW  	1996	9	19	96ZZZX4643       	1	19960705	G	6330	206033506101	RESTRAINT SPRING			BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	BEARING WORN    	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759M	729  			LK3115	45555				RESTRAINT SPRING BEARINGS WORN BEYOND LIMITS.  REPLACED BEARINGS, P/N 206-033-509-003.						1	G	7	1 	3U				H2SW    					 
1996091900480	19960919	00480	SW  	1996	9	19	96ZZZX4644       	1	19960705	G	6320	206040032011	BEARING         		206040004111	BELL  	206   	206L1       	1182107	SW  										M/R XMSN	FAILED          	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759M	12948			J0980	45555				LOWER DUPLEX BEARING BAD.  CONTAMINATED TRANSMISSION, DAMAGING OIL PUMP, AND GEARSHAFT ROLLER BEARING.  TRANSMISSION COM	PLETELY TORN DOWN, INSPECTED, CLEANED, AND REASSEMBLED.  TSO:   702.5 HOURS TOTAL TIME OF DEFECTIVE DUPLEX BEARING.  702	.5 HOURS AND 9 MONTHS SINCE NEW.				1	G	7	1 	3U				H2SW    					 
1996091900481	19960919	00481	SW  	1996	9	19	96ZZZX4645       	1	19960717	G	3213		AXEL            			BELL  	206   	206B        	1181511	SW  										PIN HOLE	MISMANUFACTURED 	B			WG3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	27	82HH					4337				OWNER REPORTED THAT GROUND HANDLING WHEELS WERE UNABLE TO LOCK BECAUSE MISALIGNMENT AT AXEL PIN HOLE.  RESHIMMED TO CORR	ECT PROBLEM.					1	G	7	1 	3U				H2SW    					 
1996091900482	19960919	00482	EU  	1996	9	19	96ZZZX4646       	1	19960715	G	6720	741C000005	ACTUATOR        			BOLKMS	117   	BK117A1     	5626010	EU  										TAIL ROTOR	LEAKS           	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117LF				00248	7013				ACTUATOR LEAKS.						1	G	7	2 	3U				H13EU   					 
1996091900483	19960919	00483	EU  	1996	9	19	96ZZZX4647       	1	19960606	G	6410	11731742	BLADE           			BOLKMS	117   	BK117B1     	5626012	EU  										TAIL ROTOR	PAINT PEEL      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	217MC	4251 			286	7195				TAIL ROTOR BLADE PAINT PEELING OFF LESS THAN 90 DAYS INSTALLED.  107.8 ACFT HRS.						1	G	7	2 	3U				H13EU   					 
1996091900484	19960919	00484	EU  	1996	9	19	96ZZZX4648       	1	19960606	G	6410	11731742	BLADE           			BOLKMS	117   	BK117B1     	5626012	EU  										TAIL ROTOR	PAINT PEEL      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	217MC	3779 			509	7195				TAIL ROTOR BLADE PAINT PEELING OFF LESS THAN 90 DAYS INSTALLED.  107.8 ACFT HRS.						1	G	7	2 	3U				H13EU   					 
1996091900485	19960919	00485		1996	9	19	96ZZZX4649       	4	19960731	G	3450	066303402	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT NAV	ERRORS          	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	213AE				50271	7219				IINDICATOR 50 DEGREES OFF.  NAVIGATOR WILL NOT RETRACT.						1	G	7	2 	3U				H13EU   					 
1996091900486	19960919	00486		1996	9	19	96ZZZX4650       	4	19960731	G	3421	5050031904	GYRO            			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	213AE				959	7219				GYRO PRECESSES - RECALIBRATE.						1	G	7	2 	3U				H13EU   					 
1996091900487	19960919	00487	EU  	1996	9	19	96ZZZX4651       	1	19960801	G	6240	117945641	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										MAST MOMENT	FAULTY          	B			TI1R	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	05	213AE				E030585	7219				MAST MOMENT LIMIT LIGHT DOES NOT ILLUMINATE WHEN POWER IS APPLIED.						1	G	7	2 	3U				H13EU   					 
1996091900488	19960919	00488	EU  	1996	9	19	96ZZZX4652       	1	19960801	G	2822	1176415103	PUMP            			BOLKMS	117   	BK117B1     	5626012	EU  										FUEL BOOST	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	213AE				172203	7219				BOOST PUMP LEAKING FROM SEAL DRAIN.						1	G	7	2 	3U				H13EU   					 
1996091900489	19960919	00489	EU  	1996	9	19	96ZZZX4653       	1	19960720	G	3310	1179203903	POWER SUPPLY    			BOLKMS	117   	BK117B1     	5626012	EU  										LIGHTS	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	213AE				1069	7219				COCKPIT LIGHTING POWER SUPPLY INOPERATIVE.						1	G	7	2 	3U				H13EU   					 
1996091900490	19960919	00490	SW  	1996	9	19	96ZZZX4654       	1	19960626	G	2435	23032048	STARTER         			BELL  	222   	222U        	1182140	SW  										START/GEN	VIBRATION       	B			TI1R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	05	219HM		205  		23014	47573				STARTER HAS 0.24 IPS VIBRATION.						1	G	7	2 	3U				H9SW    					 
1996091900491	19960919	00491	SW  	1996	9	19	96ZZZX4655       	1	19960729	G	6310	222044672101S	COUPLING        			BELL  	222   	222U        	1182140	SW  										ENGINE/XMSN	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM	296  			A000877	47573				CORROSION ON INSIDE DIAMETER OF OUTER COUPLING.						1	G	7	2 	3U				H9SW    					 
1996091900492	19960919	00492	SW  	1996	9	19	96ZZZX4656       	1	19960730	G	6410	2220167001111	BLADE           			BELL  	230   	230         	1182149	SW  										TAIL ROTOR	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	230JP	310  			A532	23019				BLADE S/N A532 HAD FILLER COMING OFF OF BLADE AND S/N A528 WAS REMOVED PER ASB 23595-8.						1	G	7	2 	3U			NC	H9SW    					 
1996091900493	19960919	00493		1996	9	19	96ZZZX4657       	4	19960711	G	2210	741C000005	ACTUATOR        			BOLKMS	117   	BK117A3     	5626015	EU  										YAW	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	312LF				00305	7083				ACTUATOR MAKES COMPUTER CLATTER INSIDE.						1	G	7	2 	3U				H13EU   					 
1996091900494	19960919	00494		1996	9	19	96ZZZX4658       	4	19960710	G	2211	117884141	COMPUTER        			BOLKMS	117   	BK117A3     	5626015	EU  										YAW/CSAS	INOPERATIVE     	B			TI1R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	05	312LF				018609010	7083				COMPUTER INOPERATIVE, UNIT SMOKING.						1	G	7	2 	3U				H13EU   					 
1996091900495	19960919	00495		1996	9	19	96ZZZX4659       	4	19960706	G	2211	117884141	COMPUTER        			BOLKMS	117   	BK117A3     	5626015	EU  										YAW/CSAS	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	312LF				018609001	7083				YAW KICKS IN-FLIGHT.						1	G	7	2 	3U				H13EU   					 
1996020200279	19960202	00279	SO  	1996	2	2	96ZZZX466        	2	19960115	G	7421	RHB32S	SPARK PLUG      			CESSNA	185   	185F        	2072820	CE  	CONT  	O520  	IO520D      	17032	SO  					ELECTRODE	SPLIT           	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	11174	1401 			1M92	18504435	282968R			FOUND 2 SPARK PLUGS WITH ROUND ELECTRODES SPLIT.  SUBMITTER STATED MORE THAN 20 OF THE PART NUMBERS HAVE BEEN FOUND.						1	H	7	1 	3O	3	O		3A24    	E5CE				 
1996091900496	19960919	00496	EU  	1996	9	19	96ZZZX4660       	1	19960708	G	6520	4639311043	BEVEL GEAR TOOTH			BOLKMS	BK117 	BK117C1     	5626025	EU  										TAIL ROTOR	PITTED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1318 			784	7505				PITTING ON TOOTH FACE IS REASON FOR REJECTION.						1	G	7	2 	3U			NC	H13EU   					 
1996091900497	19960919	00497	EU  	1996	9	19	96ZZZX4661       	1	19960708	G	6520	4639310012	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										TAIL ROTOR	SCORED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1318 			1519	7505				BEARING ROLLERS ARE SCORED.						1	G	7	2 	3U			NC	H13EU   					 
1996091900498	19960919	00498	EU  	1996	9	19	96ZZZX4662       	1	19960708	G	6520	4639311003	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										TAIL ROTOR	SCORED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1318 			751	7505				BEARING ROLLERS ARE SCORED.						1	G	7	2 	3U			NC	H13EU   					 
1996091900499	19960919	00499	EU  	1996	9	19	96ZZZX4663       	1	19960802	G	7120	117601091	FORK            			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE MOUNT	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				UPON REMOVAL OF NR 1 ENGINE, FOUND TRANSIT ENGINE MOUNT FORK WORN BEYOND LIMITS.						1	G	7	2 	3U			NC	H13EU   					 
1996091900500	19960919	00500	EU  	1996	9	19	96ZZZX4664       	1	19960729	G	6520	4639311005	SHAFT           			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R OUTPUT	PLATING MISSING 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	317MC				1088	7505				TAIL ROTOR GEARBOX OUTPUT SHAFT, SILVER PLATING IS MISSING ON ONE SPOT ON INSIDE DIAMETER OF SHAFT.  NOT ACCEPTABLE IAW 	CURRENT REM 305 MANUAL.  PART IS NO GOOD AS IS.					1	G	7	2 	3U			NC	H13EU   					 
1996091900501	19960919	00501	EU  	1996	9	19	96ZZZX4665       	1	19960521	G	5210	T6301107	HANDLE          			BOLKMS	BK117 	BK117C1     	5626025	EU  										DOOR	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	317MC					7505				HANDLE ASSY NOT MAKING POSITIVE CONTACT AND SOMETIMES VIBRATES OPEN.						1	G	7	2 	3U			NC	H13EU   					 
1996091900502	19960919	00502	EU  	1996	9	19	96ZZZX4666       	1	19960607	G	6720	11731821	PITCH LINK      			BOLKMS	BK117 	BK117C1     	5626025	EU  										TAIL ROTOR	BEARING PLAY    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				TAIL ROTOR CONTROL PLAY IN BEARINGS (2 EACH).						1	G	7	2 	3U			NC	H13EU   					 
1996091900503	19960919	00503		1996	9	19	96ZZZX4667       	4	19960805	G	2211	117884141	COMPUTER        			BOLKMS	117   	BK117A4     	5626017	EU  										YAW/CSAS	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	313LF	68   			5034	7138				YAW/CSAS OSCILLATES LEFT TO RIGHT ON GROUND AND IN-FLIGHT.						1	G	7	2 	3U				H13EU   					 
1996091900504	19960919	00504	EU  	1996	9	19	96ZZZX4668       	1	19960729	G	6520	4639311005	SHAFT           			BOLKMS	117   	BK117A3     	5626015	EU  										T/R GEARBOX	PLATING MISSING 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	4493X				1179	S7038				TAIL ROTOR GEARBOX OUTPUT SHAFT SILVER PLATING MISSING ON THREE SPOTS ON INSIDE DIAMETER OF SHAFT.  NOT ACCEPTABLE IAW C	URRENT REM 305 MANUAL.  PART IS NO GOOD AS IS.					1	G	7	2 	3U				H13EU   					 
1996091900505	19960919	00505	SW  	1996	9	19	96ZZZX4669       	1	19960709	G	3510	IDP5	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										OXYGEN SYSTEM	READS LOW       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	519EH				6160833	45429				OXYGEN INDICATOR READS 150 TO 200 PSI LOW.  WILL NOT WORK ON INTERNAL CALIBRATION MODE.						1	G	7	1 	3U				H2SW    					 
1996020200280	19960202	00280	EA  	1996	2	2	96ZZZX467        	2	19960102	G	7322	2271683	THROTTLE BODY   		MA45        						LYC   	O360  	O360*       	41514	EA  					CARBURETOR	CRACKED         	F				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					75049602		L3475436A			INSPECTION FOUND THROTTLE BODY IS CRACKED ABOVE P/N 43-648 IDLE MIXTURE ADJUSTING NEEDLE.  THE CRACK EXTENDS FROM THE MO	UNTING FACE DOWN TO THE IDLE MIXTURE BOSS AND BACK TO THE MOUNTING FACE.										3	O			E286				 
1996091900506	19960919	00506	EU  	1996	9	19	96ZZZX4670       	1	19960617	G	2435	23032022	GENERATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										START/GEN	ARMATURE SCORED 	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	527MB	324  			21976	7103				START/GENERATOR ARMATURE SCORED DUE TO BRUSH HOLDER BENT.						1	G	7	2 	3U				H13EU   					 
1996091900507	19960919	00507	CE  	1996	9	19	96ZZZX4671       	1	19960602	G	3244	22X675108TL	TIRE            			BEECH 	200   	B200        	1152922	CE  										GEAR	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	75LV				31172342	BB1075				TIRE DEVEOPED BUMP.  SUPSECT CORD SEPARATION.						1	L	7	2 	4T				A24CE   					 
1996091900508	19960919	00508		1996	9	19	96ZZZX4672       	4	19960704	G	2312	4000103001	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LF				613	S663				TRANSCEIVER WILL NOT TRANSMIT WHEN UNIT GETS HOT.						1	G	7	2 	3U				H3EU    					 
1996091900509	19960919	00509		1996	9	19	96ZZZX4673       	4	19960621	G	2312	3130001010111	CONTROL UNIT    			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT VHF	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LF				176	S663				ENTER KNOB INOPERATIVE.						1	G	7	2 	3U				H3EU    					 
1996091900510	19960919	00510		1996	9	19	96ZZZX4674       	4	19960627	G	2312	40001452500	TRANSCEIVER     			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT VHF	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				269	7098				TRANSCEIVER WILL NOT TRANSMIT CLEAR, BUT RECEIVES OK.  PART WAS JUST IN FOR REPAIR 5-14-96.						1	G	7	2 	3U				H13EU   					 
1996091900511	19960919	00511	EU  	1996	9	19	96ZZZX4675       	1	19960701	G	7120	1176272102	LINK            			BOLKMS	117   	BK117A3     	5626015	EU  										MOUNT	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	950MB				0059	7061				FOUND ENGINE MOUNT EAR CRACKED INTO TWO PIECES.						1	G	7	2 	3U				H13EU   					 
1996020200281	19960202	00281	EA  	1996	2	2	96ZZZX468        	2	19960108	G	7322	2271683	THROTTLE BODY   		MA45        						LYC   	O360  	O360*       	41514	EA  					CARBURETOR	CRACKED         	F				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					75049615		L3478536A			INSPECTION FOUND THROTTLE BODY IS CRACKED ABOVE P/N 43-648 IDLE MIXTURE ADJUSTING NEEDLE.  THE CRACK EXTENDS FROM THE MO	UNTING FACE DOWN TO THE IDLE MIXTURE BOSS AND BACK TO THE MOUNTING FACE.  THIS IS THE SECOND OCCURRENCE THIS MONTH.										3	O			E286				 
1996091900519	19960919	00519	EU  	1996	9	19	96ZZZX4683       	1	19960821	G	3320	350A64518205	PC BOARD        			AEROSP	AS355 	AS355F1     	8680810	EU  										CABIN LIGHTS	FAILED          	B			SZTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5789X	40   				5100				INTERIOR LIGHTS INOPERATIVE.  REPLACED P.C. BOARD.  LIGHTS OPS CHECKED GOOD.						1	G	7	2 	3U				H11EU   					 
1996091900520	19960919	00520	WP  	1996	9	19	96ZZZX4684       	1	19960821	G	6320	369D25149	BEARING         		369D25100505	HUGHES	369   	369D        	4470706	WP  										M/R XMSN	DEFECTIVE       	B			EOOR	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			AL	03	5074R				9102	1151D				DURING INSPECTION OF MAIN ROTOR TRANSMISSION AFTER CHIP LIGHT, FOUND 369D25149 OUTPUT SHAFT BALL BEARING TO BE SEVERELY 	ETCHED ON ONE BALL.					1	G	7	1 	3U				H3WE    					 
1996091900521	19960919	00521	WP  	1996	9	19	96ZZZX4685       	1	19960820	G	6320	369D2514C	BEARING         		369D25100505	HUGHES	369   	369D        	4470706	WP  										MR GRBOX	CRACKED         	B	S	A	EOOR	K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		IN	INSP/MAINT     	1			AL	03	5074R				1190	1151D				DISASSEMBLED MAIN ROTOR TRANSMISSION AFTER CHIP LIGHT.  FOUND THE FORWARD SUPPORT BEARING FOR THE TAIL ROTOR O/P SHAFT H	AD A CRACKED INNER RACE AND THAT IT HAD FORCED THE SNAP RING OFF OF THE END OF THE SHAFT AND THEN THE INNER RACE GOUGED 	INTO THE COVER ASSEMBLY ABOUT .125 INCH DEEP.				1	G	7	1 	3U				H3WE    					 
1996091900523	19960919	00523		1996	9	19	96ZZZX4687       	4	19960514	G	3422	40205773	GYRO            			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT DIR	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				92015145	7505				COCKPIT DIRECTIONAL GYRO, INTERMITTENT FAILURES.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1996091900576	19960919	00576	EU  	1996	9	19	96ZZZX4688       	1	19960316	G	2612		CONNECTOR       			BRAERO	DH125 	HS125700A   	4230170	EU  										LT ENG FIRE WARN	CONTAMINATED    	D				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			CR	CRUISE         	1			EA	01	193RC	9660 				NA0258				FIRE BELL RANG WITH NO OTHER INDICATIONS.  THROUGH ISOLATION SWITCH MOVEMENT, CONDITION WAS DETERMINED TO BE ON LEFT ENG	INE.  ENGINE AND FIRE DETECTION SYSTEM EXAMINED.  NO DEFECTS NOTED.  LT ENG FIRE SYS LIGHTS AND BELL CAME ON.  ENGINE SE	CURED AND NR 1 FIRE BOTTLE FIRED.  LIGHTS AND BELL EVENTUALLY WENT OUT.  FOUND SMALL AMT OF SEMI-CONDUCTIVE BLK GREASE I	N CONNECTOR PLUG IN LT ENG PLYON.  CLEANED PLUG, SYS NOW NORMAL.  PROBLEM OCCURRED APPROX 45 HRS AFTER ENG CHANGE AND TH	IS PLUG WAS DISCONNECTED AT THAT TIME.		2	L	7	2 	4F				A3EU    					 
1996020200282	19960202	00282	SO  	1996	2	2	96ZZZX469        	2	19960109	G	7322	390077	SEAT VALVE      			BBAVIA	7     	7AC         	2110102	SW  	CONT  	C85   	C858        	17008	SO  					CARBURETOR	LOOSE           	D				C				ABORTED TAKEOFF         				Y	W		ENGINE STOPPAGE           	INADEQUATE Q C            		TO	TAKEOFF        	1			GL	27	83975		5    			2661	3070788			ENGINE QUIT ON TAKEOFF.  DISASSEMBLED CARBURETOR AND INSPECTION FOUND SEAT VALVE HAD NOT BEEN PROPERLY TORQUED.  SEAT WO	RKED LOOSE AND LOWERED FLOAT LEVEL TO WHERE ENGINE COULD NOT DEVELOP FULL POWER.  CARBURETOR OVERHAULED 10-95.					1	H	7	1 	3O	3	O		A759    	E233				 
1996091900578	19960919	00578	EU  	1996	9	19	96ZZZX4690       	1	19960828	G	3320	6900080	LIGHT           			SAAB  	SF340 	SF340A      	7850100	EU  										LAVATORY	OVERHEATED      	B			PJ2R	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CE	07	39MB	3000 			PW3888	340A022				P/N 6900080, 28V, FOR FLUORESCENT LIGHTS.  SUBMITTER STATED THE LIGHTS ARE A PROBLEM IN THAT THEY DO NOT LAST BEFORE FAI	LURE OR BECOMING INOPERABLE.  ONE SPECIFIC OCCURRENCE IN THAT UNIT OVERHEATED, BURNED WITH BAD ODOR AND DISCOLORATION AR	OUND INSTALLATION, INTERNAL FAILURE.				2	L	7	2 	4T			RT	A52EU   					 
1996091900579	19960919	00579	EU  	1996	9	19	96ZZZX4691       	1	19960729	G	5753	25WS21AD	FLAP VANE       			HWKSLY	DH125 	BH125400A   	4230138	EU  										RT FLAP	CRACKED         	A	S	A	FE6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	456WH	6348 				NA760				THE LT AND RT OTBD FLAP VANE SKINS AND VANE SPARS HAVE BEEN ALTERED FROM THE ORIGINAL.  A RADIUS APPROX 1 INCH WIDE AND 	.6250 INCH DEEP HAS BEEN GROUND INTO THE FLAP VANES IN THE AREA OF THE OTBD FLAP  HINGE.  ONE RIVET HAS BEEN REMOVED.  I	T IS BELIEVED THIS 'MODIFICATION' HAS BEEN INCORPORATED TO ALLOW REMOVAL OF THE OTBD FLAP HINGE RETAINING PIN WITHOUT TI	LTING VANE.  CRACKS ARE NOTED IN THE LEFT VANE, IN THE AREA OF THE ALTERATION POSSIBLY DUE TO DECREASED SPAR WEB STRENGT	H.  THE MANUFACTURER IS PRESENTLY EVALUATING THE SITUATION FOR A POSSIBLE REPAIR.  REPLACEMENT OF BOTH OTBD FLAP VANES I	S ALSO BEING CONSIDERED.	2	L	7	2 	4J				A3EU    					 
1996091900580	19960919	00580	EU  	1996	9	19	96ZZZX4692       	1	19960729	G	5753	25WS22AD	FLAP VANE       			HWKSLY	DH125 	BH125400A   	4230138	EU  										LT FLAP	CRACKED         	A		A	FE6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	456WH	6348 				NA760				THE LT AND RT OTBD FLAP VANE SKINS AND VANE SPARS HAVE BEEN ALTERED FROM THE ORIGINAL.  A RADIUS APPROX 1 INCH WIDE AND 	.6250 INCH DEEP HAS BEEN GROUND INTO THE FLAP VANES IN THE AREA OF THE OTBD FLAP  HINGE.  ONE RIVET HAS BEEN REMOVED.  I	T IS BELIEVED THIS 'MODIFICATION' HAS BEEN INCORPORATED TO ALLOW REMOVAL OF THE OTBD FLAP HINGE RETAINING PIN WITHOUT TI	LTING VANE,.  CRACKS ARE NOTED IN THE LEFT VANE, IN THE AREA OF THE ALTERATION POSSIBLY DUE TO DECREASED SPAR WEB STRENG	TH.  THE MANUFACTURER IS PRESENTLY EVALUATING THE SITUATION FOR A POSSIBLE REPAIR.  REPLACEMENT OF BOTH OTBD FLAP VANES 	IS ALSO BEING CONSIDERED.	2	L	7	2 	4J				A3EU    					 
1996091900581	19960919	00581	EU  	1996	9	19	96ZZZX4693       	1	19960227	G	2422	ASH6641PF	STATIC INVERTER 			BRAERO	DH125 	BAE125800A  	1500285	EU  										TAIL COMPARTMENT	WATER SOAKED    	B			MJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	60PM	2445 			DK905	NA0453				AIRCRAFT SAT ON GROUND OVERNIGHT IN RAIN STORM.  INVERTER WAS SATURATED WITH WATER.  UNIT WOULD NOT OPERATE.						2	L	7	2 	4F			RT	A3EU    					 
1996091900582	19960919	00582	EU  	1996	9	19	96ZZZX4694       	1	19960227	G	2450	LDA150A8C	CONTACTOR       			BRAERO	DH125 	BAE125800A  	1500285	EU  										BUS TIE	FAILED          	B			MJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	60PM	3155 			7930	NA0453				INTERMITTENT TRIPPING OF CIRCUIT BREAKER (B85).  BUS TIE OPEN.  REPLACED BUS TIE CONTACTOR.  PROBLEM WENT AWAY.						2	L	7	2 	4F			RT	A3EU    					 
1996091900584	19960919	00584	CE  	1996	9	19	96ZZZX4696       	1	19960820	G	5730	26513008	SKIN            			RKWELL	NA265 	NA26580     	7630108	CE  										LT L/E WS 236.9	CRACKED         	C	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	7148J	12563				38033				WHILE PERFORMING PRE-FLIGHT INSP, MECH NOTICED PAINT CRACKED AND CHIPPED ON L/E OF WING ABOUT SS 236.9.  UPON FURTHER IN	SP FOUND A CRACK, ABOUT 8.5 INCHES, THROUGH FIRST STIFFENER AND 4.0 INCHES AND 5.0 INCHES THROUGH SECOND STIFFENER ON BO	TTOM OF L/E UNDER DE-ICE BOOT OTBD TO ABOUT WS 264.  THIS AREA CLOSED OUT BY RIBS ONE EACH SIDE OF SLAT TRACKS.  CRACK A	REA COULD NOT BE FELT THROUGH DE-ICE BOOT.  AFTER REMOVING CRACKED PORTION OF L/E FROM WING, FOUND 4 EACH STIFFENERS AND	 RIB CRACKED BEYOND REPAIR.  ALSO, FOUND SLAT ATTACH FITTING IN NR 2 SLAT, P/N FITTING 246-17050-5, LOOSE IN SLAT.  A CR	ACK ALSO RADIATED OUT FROM ATTACH BOLT HOLE THROUGH ATTACH RIB.	2	L	7	2 	4F				A2WE    					 
1996091900585	19960919	00585	EU  	1996	9	19	96ZZZX4697       	1	19960729	G	5755	258W851A	AIR BRAKE       			BRAERO	DH125 	BAE125800A  	1500285	EU  										PANEL LT T/E	CRACKED         	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	85DW	3917 			DHP59	258034				THE LEFT HAND UPPER AIR BRAKE PANEL FOUND WITH A 5.5 INCH CRACK IN THE CENTER OF THE AIR BRAKE AT THE TRAILING EDGE OF T	HE LOWER SKIN, AT THE JOGGLE BEND.  FACTORY NEW PART NOT READILY AVAILABLE.  REPAIRED PER BAE 800 SRM, P/N SRM 125-800, 	REV 25, DATED APRIL 30, 1995, CHAPTER 51-10-03, AND OTHERS, AS APPLICABLE.				2	L	7	2 	4F			RT	A3EU    					 
1996091900586	19960919	00586	EU  	1996	9	19	96ZZZX4698       	1	19960729	G	5730	S258WS50022A	SKIN            			BRAERO	DH125 	BAE125800A  	1500285	EU  										LE TKS REBATE	CORRODED        	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	85DW	1121 			AST93B062	258034				ALL WING LEADING EDGES WERE REPLACED WITH FACTORY NEW ON 7-10-93, PER MANDATORY SB 57-77, DUE TO CORROSION.  UNTIL THIS 	TIME, SUBSEQUENT INSPECTIONS REQUIRED BY AD 95-15-04, AMDT 39-9307, DATED 8-23-95, AND MANDATORY SB 57-77, REV 1, DATED 	10-28-93, HAVE SHOWN NO CORROSION.  THESE INSPECTIONS ARE NO LONGER REQUIRED.  AT THIS TIME, THE WING LEADING EDGES ARE 	INSPECTED PER THE STRUCTURAL INSPECTIONS, ITEMS 570019/570021, APPROX 3 YEARS PRIOR TO REQUIREMENT, FOR SCHEDULING PURPO	SES.  MINOR CORROSION IS NOTED, AT THE TKS REBATES.  CORROSION IS BLENDED AND REMOVED PER MFG REPAIR INSTRUCTION LETTER,	 RIL 25W AND 279, REV 3, DATED 4-30-93.	2	L	7	2 	4F			RT	A3EU    					 
1996091900587	19960919	00587	EU  	1996	9	19	96ZZZX4699       	1	19960729	G	5730	S25BWS50026AX	SKIN            			BRAERO	DH125 	BAE125800A  	1500285	EU  										LE TKS REBATE	CORRODED        	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	85DW	1121 			DHB081	258034				ALL WING LEADING EDGES WERE REPLACED WITH FACTORY NEW ON 7-10-93, PER MANDATORY SB 57-77, DUE TO CORROSION.  UNTIL THIS 	TIME, SUBSEQUENT INSPECTIONS REQUIRED BY AD 95-15-04, AMDT 39-9307, DATED 8-23-95, AND MANDATORY SB 57-77, REV 1, DATED 	10-28-93, HAVE SHOWN NO CORROSION.  THESE INSPECTIONS ARE NO LONGER REQUIRED.  AT THIS TIME, THE WING LEADING EDGES ARE 	INSPECTED PER THE STRUCTURAL INSPECTIONS, ITEMS 570019/570021, APPROX 3 YEARS PRIOR TO REQUIREMENT, FOR SCHEDULING PURPO	SES.  MINOR CORROSION IS NOTED, AT THE TKS REBATES.  CORROSION IS BLENDED AND REMOVED PER MFG REPAIR INSTRUCTION LETTER,	 RIL 25W AND 279, REV 3, DATED 4-30-93.	2	L	7	2 	4F			RT	A3EU    					 
1996091900588	19960919	00588	EU  	1996	9	19	96ZZZX4700       	1	19960729	G	5730	S258WS50041A	SKIN            			BRAERO	DH125 	BAE125800A  	1500285	EU  										LE TKS REBATE	CORRODED        	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	85DW	1121 			AST93E180	258034				ALL WING LEADING EDGES WERE REPLACED WITH FACTORY NEW ON 7-10-93, PER MANDATORY SB 57-77, DUE TO CORROSION.  UNTIL THIS 	TIME, SUBSEQUENT INSPECTIONS REQUIRED BY AD 95-15-04, AMDT 39-9307, DATED 8-23-95, AND MANDATORY SB 57-77, REV 1, DATED 	10-28-93, HAVE SHOWN NO CORROSION.  THESE INSPECTIONS ARE NO LONGER REQUIRED.  AT THIS TIME, THE WING LEADING EDGES ARE 	INSPECTED PER THE STRUCTURAL INSPECTIONS, ITEMS 570019/570021, APPROX 3 YEARS PRIOR TO REQUIREMENT, FOR SCHEDULING PURPO	SES.  MINOR CORROSION IS NOTED, AT THE TKS REBATES.  CORROSION IS BLENDED AND REMOVED PER MFG REPAIR INSTRUCTION LETTER,	 RIL 25W AND 279, REV 3, DATED 4-30-93.	2	L	7	2 	4F			RT	A3EU    					 
1996091900589	19960919	00589	EU  	1996	9	19	96ZZZX4701       	1	19960729	G	5730	S258WS50045A	SKIN            			BRAERO	DH125 	BAE125800A  	1500285	EU  										LE TKS REBATE	CORRODED        	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	85DW	1121 			AST93E178	258034				ALL WING LEADING EDGES WERE REPLACED WITH FACTORY NEW ON 7-10-93, PER MANDATORY SB 57-77, DUE TO CORROSION.  UNTIL THIS 	TIME, SUBSEQUENT INSPECTIONS REQUIRED BY AD 95-15-04, AMDT 39-9307, DATED 8-23-95, AND MANDATORY SB 57-77, REV 1, DATED 	10-28-93, HAVE SHOWN NO CORROSION.  THESE INSPECTIONS ARE NO LONGER REQUIRED.  AT THIS TIME, THE WING LEADING EDGES ARE 	INSPECTED PER THE STRUCTURAL INSPECTIONS, ITEMS 570019/570021, APPROX 3 YEARS PRIOR TO REQUIREMENT, FOR SCHEDULING PURPO	SES.  MINOR CORROSION IS NOTED, AT THE TKS REBATES.  CORROSION IS BLENDED AND REMOVED PER MFG REPAIR INSTRUCTION LETTER,	 RIL 25W AND 279, REV 3, DATED 4-30-93.	2	L	7	2 	4F			RT	A3EU    					 
1996091900590	19960919	00590	EU  	1996	9	19	96ZZZX4702       	1	19960817	G	7921	5711012334	INLET FENCE     			PILATS	PC12  	PC12        	7090550	EU  										OIL COOLER	CRACKED         	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	117WF	328  				117				DURING SCHEDULED INSPECTION, FOUND OIL COOLER INLET FENCE CRACKED ON BOTTOM NOSE COWLING.  POSSIBLE TURBULENT AREA CAUSI	NG VIBRATION AND CRACKING.  SUBMITTER RECOMMENDS CLOSE INSPECTION DURING PRE-FLIGHT AND DURING SCHEDULED MAINTENANCE.					1	L	7	1 	3T			RT	A78EU   					 
1996091900591	19960919	00591	SO  	1996	9	19	96ZZZX4703       	1	19960801	G	5412		WEB             			PIPER 	PA42  	PA42        	7104202	SO  										ENGINE FIREWALL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	123AG	6410 				428001031				INSPECTION FOUND A CRACKED WEB AT BOTH ENGINE FIREWALLS AT ENGINE MOUNT AREA.						1	L	7	2 	4T				A23SO   					 
1996091900592	19960919	00592	GL  	1996	9	19	96ZZZX4704       	2	19960322	G	7210	23035178	GEARBOX         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					MOUNT PAD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	722H	3546 			CAG95568	51452				PITTED CORROSION ON RT GEARBOX BOSS OCCURRED DURING NORMAL OPERATION.  FOUND DURING ROUTINE INSPECTION.  RECOMMENDED SUP	PLIER CHECK MATERIALS FOR DEFECTS.  SIMILAR PROBLEM FOUND ON THREE GEARBOXES.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1996091900593	19960919	00593	EU  	1996	9	19	96ZZZX4705       	1	19960820	G	6320	4638001004	CHAFE TAPE      			BOLKMS	105   	BO105C      	5626005	EU  										M/R XMSN	DETACHED        	D		A		A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			EA	27	60EG	158  			1038	S556				DURING CRUISE FLIGHT, ACFT EXPERIENCED A SUDDEN RIGHT YAW, A RAPID RISE IN TURBINE OUTLET TEMPERATURE (TOT), AND A TORQU	E REDUCTION IN THE NR 1 ENGINE.  REDUCING THE POWER LEVER TO IDLE ARRESTED THE RISE IN TOT AND AN UNEVENTFUL EMERGENCY L	ANDING WAS MADE.  NO LIMITS WERE EXCEEDED.  INSPECTION DETERMINED THE NR 1 ENGINE AIR INLET WAS 25 TO 50 PERCENT BLOCKED	 BY AN 11 INCH BY 3 INCH PIECE OF ANTI-CHAFE TAPE.  THE MANUFACTURER INSTALLED TAPE  HAD COME LOOSE FROM THE TRANSMISSIO	N BY THE INLET DEFLECTOR SHIELD HOUSING AND WAS ALMOST INGESTED INTO THE COMPRESSOR.  RECOMMEND CLOSELY CHECKING THE ANT	I-CHAFE TAPE DURING THE DAILY, PRE-FLIGHT, AND 50-HOUR INSPECTIONS.	1	G	7	2 	3U				H3EU    					 
1996091900594	19960919	00594	NM  	1996	9	19	96ZZZX4706       	1	19960812	G	2133	7786863	VALVE           	HAMSTD      		DHAV  	DHC8  	DHC8201     	2809001	NM  										HI PRESS SOV	STUD BROKEN     	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	986HA	66   			960115	421				SHUT-OFF VALVE STUD FOUND BROKEN DURING POST-FLIGHT INSPECTION.  NO IN-FLIGHT INDICATIONS WERE OBSERVED.  CAUSE UNKNOWN.	  VALVE ASSY WAS REPLACED AND ALL SYSTEMS FUNCTIONED NORMALLY.					2	H	7	2 	4T			RT	A13NM   					 
1996091900595	19960919	00595	CE  	1996	9	19	96ZZZX4707       	1	19960826	G	2810	10038000015	FUEL CELL       			BEECH 	90    	F90         	1152909	CE  										PROBE MOUNT	MISMANUFACTURED 	B			ESMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	600WM				R504	LA75				FUEL CELL PROBE MOUNTING PORTS WERE .75 INCH TOO CLOSE TOGETHER.  FUEL CELL SUPPOSEDLY NEW FROM MANUFACTURER.						1	L	7	2 	4T				A31CE   					 
1996091900597	19960919	00597	SO  	1996	9	19	96ZZZX4709       	2	19960807	G	8520		CRANKCASE       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520BB     	17032	SO  					NR 2 CYLINDER	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	2636Y	2181 	367  			310R1652	573827			CRANKCASE CRACKED IN ON-CRITICAL AREA AS DEFINED BY M90-17.  CRACK IN EXCESS OF 2 INCHES EXTENDING FROM NR 2 CYLINDER ST	UD UP THROUGH TOP OF CRANKCASE TOWARD MAGNETOS.  ENGINE REMOVED FOR REPAIRS TO CRANKCASE BY OVERHAUL SHOP.					1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996091900598	19960919	00598	NM  	1996	9	19	96ZZZX4710       	1	19960822	G	2782		FITTING         			BOEING	737   	737284      	138448R	NM  										SLAT ACT SUPPORT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	310VA					21501				DURING SB INSPECTION OF NR 1 AND NR 5 LEADING EDGE SLAT ACTUATOR SUPPORT FITTINGS, FITTINGS WERE REMOVED TO REPLACE ATTA	CH HARDWARE.  CORROSION WAS FOUND AT BOTH POSITIONS SEVERE ENOUGH TO REQUIRE REPAIR.  SUBSEQUENT INSPECTION UNDER REMAIN	ING FITTINGS REVEALED CORROSION AT NR 3 POSITION NOT SERIOUS ENOUGH TO REQUIRE REPAIR.  SUGGEST SPECIAL ATTENTION TO SEA	LING PRIMING AND CORROSION PREVENTION IN ACTUATOR SUPPORT FITTINGS.			2	L	7	2 	4F				A16WE   					 
1996092300001	19960923	00001	CE  	1996	9	23	96ZZZX4711       	1	19960827	G	2437	MS915872	SHUNT           			BEECH 	90    	B90         	1152912	CE  										AMMETER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	40CK	8415 				LJ358				MOUNTING BASE OF AMMETER SHUNT BROKE UP AROUND THE 2 MOUNTING SCREWS ALLOWING THE SHUNT TO MOVE ABOUT.  THE BASE OF THE 	MOUNT IS HOLLOW EXPOSING THE SCREWS THAT HOLD THE TERMINAL BLOCKS TO THE BASE.  THESE SCREWS CONTACTED THE BASE MOUNTING	 SCREWS ARCING TO GROUND.  THE REPLACEMENT SHUNT HAS A SOLID BASE MAKING IT STRONGER.  THERE ARE NO EXPOSED SCREWS ON TH	E BOTTOM OF THE BASE OF THE NEW UNIT.  BOTH SHUNTS HAVE THE SAME PART NUMBER.			1	L	7	2 	3T				3A20    					 
1996091900601	19960919	00601	WP  	1996	9	19	96ZZZX4714       	1	19960826	G	2700	34856	BODY            		428007      	LKHEED	1011  	1011*       		WP  										CONTROL DAMPER	CORROSION       	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					2435					CONTROL SURFACE DAMPER'S ALUMINUM BODY HAS EXCESSIVE CORROSION IN THE INSIDE DIAMETER.						2	L	7	3 	4F				A23WE   					 
1996091900602	19960919	00602	CE  	1996	9	19	96ZZZX4715       	1	19960809	G	2931	PT50018LMBE	INDICATOR       			BEECH 	200   	B200        	1152922	CE  										MLG ACCUM PRESS	FAILED          	B			LX5R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	961LL	304  				BB1139				LANDING GEAR ACCUMULATOR PRESSURE GAUGE WAS PEGGED OUT ON THE HIGH SIDE.  THE ABOVE PRESSURE GAUGE IS PART OF THE 'AVIAD	ESIGN HYDRUALIC LANDING GEAR' MODIFICATION FOR BEECH 200 SERIES AIRCRAFT.  STC SA4378WP.					1	L	7	2 	4T				A24CE   					 
1996091900603	19960919	00603	CE  	1996	9	19	96ZZZX4716       	1	19960831	G	2910	25057014939	LINE            			LEAR  	24    	24D         	5170311	CE  										HYDRAULIC TEE	FAILED          	D		A		K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	27	98WJ	6675 				268				FAILED ALUMINUM HYDRAULIC LINE IS LOCATED BETWEEN THE AUXILIARY HYDRUALIC PUMP PRESSURE SWITCH TEE FITTING AND THE THRUS	T REVERSER ACCUMULATOR.  THE LINE FAILED AT THE FLARE UNDER THE B-NUT ON THE PRESSURE SWITCH FITTING, WHICH RESULTED IN 	A SUBSEQUENT HYDRAULIC SYSTEM FLUID LOSS.  SUBMITTER SUGGESTS REPLACING THIS LINE WITH A STAINLESS STEEL BRAIDED FLEX LI	NE DUE TO THE HYDRAULIC PANEL VIBRATION DURING THRUST REVERSER ACTUATION.			2	L	7	2 	4J				A10CE   					 
1996091900604	19960919	00604	WP  	1996	9	19	96ZZZX4717       	2	19960821	G	7250	30733543	AIR SEAL        		30727262    						GARRTT	TFE731	TFE73122B   	01518	WP  					TRANSITION DUCT	DEFECTIVE       	B	L		IY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		4225 	463  		1013453990		P74146			DURING AN UNSCHEDULED MAINTENANCE EVENT, FOUND AN P/N 3073354-3, AIR SEAL WAS INSTALLED IN THE TRANSITION DUCT, P/N 3072	726-2, S/N 1-01345-3990.  SB TFE731-72-3577, REV ZERO, ADDRESSES THIS SUBJECT.										4	F			E6WE				 
1996091900605	19960919	00605	SW  	1996	9	19	96ZZZX4718       	1	19960806	G	6710	A21810064603	SWITCH          	GUARDIAN    		HUGHES	500N  	500N        	3027374	SW  										CYCLIC TRIM	STICKS          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB	811  				LN001				SWITCH STICKS IN LEFT POSITION.  RESULTS IN BURNT TRIM MOTOR (ELECTRICALLY) INOPERATIVE.  SWITCH PLATING COMES OFF AND B	ONDS TRIGGER.					1	G	7	1 	3U			NC	H3WE    					 
1996091900606	19960919	00606		1996	9	19	96ZZZX4719       	1	19960815	G	3710	D9181	FILTER          	PARKER      																VACUUM SYSTEM	DETERIORATED    	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01										VACUUM SYSTEM FILTER UPPER BLACK RUBBER CAP WILL CRUMBLE IN YOUR FINGERS.  NOT CURED.  BOTTOM APPEARS OK.  SUBMITTER STA	TED VERY DANGEROUS, WILL BLOCK DOWN STREAM INSTRUMENTS.  LABEL ON BOX HAD DATE 8/94 ON IT.																		 
1996020200285	19960202	00285	SO  	1996	2	2	96ZZZX472        	2	19960108	G	8550	58551761	OIL SEPARATOR   			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					ENGINE OIL	FROZE           	D				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			NM	11	409EX					4040436	241003R			AIR/OIL SEPARATOR OUTLET FROZE SHUT.  ENGINE PUMPED OIL OVERBOARD.  ENGINE FAILED, THREW ROD THROUGH CASE.						1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996091900607	19960919	00607		1996	9	19	96ZZZX4720       	1	19960830	G	3710	441CC7	PUMP            	AIRBORNE    																PNEU SYSTEM	SHAFT SEIZED    	B			APCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01					4AM103					DRIVE SHAFT IS SEIZED SOLID.  UNDERSTAND THIS MAY OR MAY NOT BE NORMAL.  SOME AIRBORNE REPS SAY IT IS OK.  HOWEVER, MOST	 NEW PUMPS TURN FREELY.  TECHNICIANS HAVE NO WAY TO IDENTIFY A GOOD/BAD NEW PUMP UNLESS TORQUE CRITERIA SUPPLIED.  ALL A	PPEARANCES INDICATE SEIZED/UNAIRWORTHY UNIT.																	 
1996091900608	19960919	00608	GL  	1996	9	19	96ZZZX4721       	3	19960522	G	6114	C4716C98	HUB             			CESSNA	188   	188B        	2073007	CE  						MCAULY	2A34C	D2A34C98    	GL  	BLADE RETAIN	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		1220 						890754		INSPECTION FOUND BLADE RETENTION THREADS IN HUB SOCKET ARE CRACKED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1996091900610	19960919	00610	CE  	1996	9	19	96ZZZX4723       	1	19960124	G	3230	HMX5FG	ROD END         			BEECH 	58    	58P         	1152744	CE  										NLG RETRACT	FRACTURED       	B			FC6R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	11	121Z					TJ285				ROD END FAILED (FRACTURED) WHILE RETRACTING LANDING GEAR.  PILOT HAD AN UNSAFE NOSE GEAR LIGHT, PILOT REPOSITIONED GEAR 	HANDLE TO THE DOWN POSITION.  PUSH ROD TRAVELLED FORWARD PUSHING AGAINST NOSE GEAR EXTENDING AND LOCKING GEAR IN THE DOW	N POSITION.  CAUSE OF FAILURE WAS A CRACK IN THE NECK OF THE BEARING HOUSING.  SUBMITTER RECOMMENDATION NDI TESTING OR T	IME CHANGE ROD END ON AS SCHEDULED BASIS.			1	L	7	2 	3O				A23CE   					 
1996091900613	19960919	00613	SO  	1996	9	19	96ZZZX4726       	1	19960625	G	5712	6206102	WING WALK RIB   		6659501     	PIPER 	PA28  	PA28R200    	7102811	SO  										RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	33075	4900 				28R7535116				DURING INSPECTION, FOUND WING WALK DOUBLER RIBS CRACKED.  THREE OF THE RIBS WERE CRACKED AT OUTBOARD EDGE.  SUSPECT CAUS	E WAS HIGH TOTAL TIME AND POSSIBLY STRESS INDUCED DURING FORMING OF STIFFENER RIBS.  SUBMITTER STATED THIS SEEMS TO BE A	 COMMON OCCURRENCE ON PIPER PA28 SERIES WITH AT LEAST 4,000 HOURS.				1	L	7	1 	3O				2A13    					 
1996091900614	19960919	00614	CE  	1996	9	19	96ZZZX4727       	1	19960814	G	7714	22A667	TACH GENERATOR  			CESSNA	340   	340A        	2076405	CE  										ENGINE RPM	INOPERATIVE     	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	340FP		10   			340A0298				TACHOMETER GENERATOR FAILED 10 HOURS AFTER OVERHAUL.						1	L	7	2 	3O				3A25    					 
1996091900615	19960919	00615	CE  	1996	9	19	96ZZZX4728       	1	19960325	G	3230	35825094	RETRACT ROD     			BEECH 	35    	35BEECH     	1151502	CE  										MLG	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	3941N	5200 				D1257				INVESTIGATION OF INCIDENT SHOWS THE ROD END HAD BROKEN AT THE BOLT HOLE.  THE ROD END SHOWED SIGNS OF COLD WORKING.  SUB	MITTER RECOMMENDS A NDI TEST BE PERFORMED ON THIS PART OR A TIME LIFE BE PLACED ON THE PART.					1	L	7	1 	3O				A777    					 
1996091900616	19960919	00616	SO  	1996	9	19	96ZZZX4729       	2	19960819	G	7310		HOSE            			CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520A      	17032	SO  					ENGINE FUEL	DETERIORATED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	4931U					21058631	1108644A			FUEL HOSES NON-OPERATONAL FOR 3 YEARS ALLOWING NON-PRESSURE SIDE OF FUEL HOSES TO DRY OUT AND INSIDE OF HOSE TO DETERIOR	ATE.  SMALL PIECES OF RUBBER HOSE BROKE OFF AND CLOGGED FUEL LINES IN FUEL INJECTION SYSTEM.					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996091900617	19960919	00617	CE  	1996	9	19	96ZZZX4730       	1	19960811	G	3230	52435181	FORK BOLT       			CESSNA	310   	310P        	2074238	CE  										RT MLG	BROKEN          	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	5741M					310P0041				BOLT BROKE AND CAUSED AFT ROD ASSY (P/N 0840125-13) TO JAM AND RT MLG WOULD NOT EXTEND FULLY.  FORK BOLT WAS PREVIOUSLY 	CRACKED FOR SOME TIME, BUT CRACK WAS HIDDEN BY TORQUE TUBE AND NOT DETECTABLE BY VISUAL INSPECTION.					1	L	7	2 	3O				3A10    					 
1996091900620	19960919	00620	CE  	1996	9	19	96ZZZX4733       	1	19960829	G	7810	K1250860104	EXHAUST SYSTEM  			CESSNA	210   	T210L       	2073449	CE  										TURBO INLET	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	613CW	274  				21059920				NEW EXHAUST SYSTEM WAS INSTALLED AT ENGINE CHANGE.  274 HOURS LATER DURING 100-HOUR INSPECTION, NUMEROUS CRACKS WERE FOU	ND ON RIGHT SIDE OF EXHAUST, BY TURBO INLET AND FRONT RISER.					1	H	7	1 	3O				3A21    					 
1996091900622	19960919	00622	CE  	1996	9	19	96ZZZX4735       	1	19960831	G	2436	VR500	REGULATOR       	AUXILEC     		CESSNA	210   	T210M       	2073451	CE  										DC SYSTEM	FAILED          	B	L		YWYR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	732TG	1700 				21061757				REGULATOR FIELD LINE WENT TO FULL VOLTAGE CONDITION CAUSING OVERVOLTAGE PROTECTION TO DISABLE SYSTEM.  REPLACED VOLTAGE 	REGULATOR TO SOLVE PROBLEM.					1	H	7	1 	3O				3A21    					 
1996020200287	19960202	00287		1996	2	2	96ZZZX474        	4	19960104	G	2564	1021	CYLINDER        	HOOVERIND   	4600107     															LIFE RAFT	FAIL TEST       	B			OD1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25					A649700					INFLATION CYLINDER FAILED HYDROSTATIC RETEST DUE TO EXCESSIVE ELASTIC EXPANSION.  HOOVER IND. P/N 102-1 (165 CUBIC INCHE	S), S/N A649700.  CAUSE WOULD BE IN MANUFACTURING.  RECOMMEND MANUFACTURER BE CONTACTED.  DATE OF MFG IS 7-93, THIS WAS 	ITS FIRST RETEST.																	 
1996091900927	19960919	00927	SO  	1996	9	19	96ZZZX4742       	2	19960806	G	8530		ROCKER BOSS     			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					NR 3 CYL EXH	FAILED          	D				K				NONE                    				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			AL	01	105AK					40400833	243227R			ROCKER BOSS FAILED (CRACKED) ON EXHAUST SIDE ON CYLINDER NR 3.  ROCKER SHAFT PUNCHED THROUGH VALVE COVER.  INSPECTED MAG	NETO DRIVE COUPLING PER SB M90-11, FOUND OK.					1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996091900930	19960919	00930	GL  	1996	9	19	96ZZZX4745       	3	19960521	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	220BR		832  		774447	310R0973		774447		BLADE RETENTION THREADS IN ALL THREE SOCKETS ARE CRACKED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1996020200288	19960202	00288	CE  	1996	2	2	96ZZZX475        	1	19960105	G	5753	0523920	ROLLER ASSY     		052390138   	CESSNA	172   	172RG       	2072438	CE  										RT FLAP INBOARD	FROZEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	9627B	369  				172RG0928				DURING 100-HOUR INSPECTION, NOTICED THE RT FLAP VIBRATING AS IT WAS LOWERED.  INSPECTION FOUND THE AFT INBOARD ROLLER WA	S FROZEN.  UPON REMOVAL OF THE ROLLER, FOUND THE OUTER BRASS (?) RING HAD PARTIALLY SLID OFF OF THE INNER BEARING ASSY C	AUSING THE ROLLER TO CUT INTO THE ADJOINING PLASTIC SPACER (PN S1450-5N12-050).  FRICTION EVENTUALLY CAUSED THE ROLLER T	O STOP TURNING.  SUBMITTER STATED THIS IS THE THIRD SUCH OCCURRENCE ON DIFFERENT AIRCRAFT.  PART TOTAL TIME:  368.5 HOUR	S.  INSTALLED WITH SERVICE KIT SK180-44.		1	H	7	1 	3O				3A17    					 
1996091900935	19960919	00935	CE  	1996	9	19	96ZZZX4750       	1	19960508	G	8011	MHB4016	STARTER         	PRESTOLITE  		CESSNA	172   	172N        	2072434	CE  										DRIVE END	ARMATURE OPEN   	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	05	2212W				2L000488	17271516				STARTER REMOVED DUE TO OPEN IN ARMATURE.  FOUND WIRE WINDINGS OF ARMATURE ON DRIVE END WERE POTTED WITH MATERIAL RESEMBL	ING BODY PUTTY TO INSULATE THE WIRES.  ALSO, A PIECE OF A CARDBOARD BOX WAS INSERTED BETWEEN THE COPPER FIELD LEAD AND T	HE CASE FOR INSULATION.				1	H	7	1 	3O			NT	3A12    					 
1996091900936	19960919	00936	EA  	1996	9	19	96ZZZX4751       	2	19960821	G	8520	AS16507A01	CAMSHAFT        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					LT ENGINE	BROKE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2110F		1897 		WB1122M182	447995152	L45377T			ENGINE WAS REMOVED FOR CAM FAILURE AT 299.20 TSMOH.  A  RE-GROUND CAM WAS INSTALLED BY CRS.  AT 2,195.50 TSMOH, ENGINE W	AS REMOVED FOR OVERHAUL AND DISASSEMBLY REVEALED CAM HAD BROKEN IN 2 PIECES WHERE THE PROP GOVERNOR GEAR P/N LW-15274 IS	 INSTALLED AND CRACKED WHERE THE WOODRUFF KEY P/N STD-96 IS INSTALLED TO SECURE THE PROP GOVERNOR DRIVE GEAR.  THE ORIGI	NAL PART NUMBER FOR THIS CAM BEFORE IT WAS RE-GROUND AND INSTALLED BY THE CRS WAS AS16508.  NOTE:  THIS ENGINE NEVER GAV	E AN INDICATION OF FAILURE/METAL IN OIL.		1	L	7	2 	3O	3	O		A19S0   	E286				 
1996091900937	19960919	00937	CE  	1996	9	19	96ZZZX4752       	1	19960821	G	3246	D30256	HUB ASSY        	MCAULY      	C1630030101 	CESSNA	172   	172M        	2072418	CE  										MLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	23470	5000 			743933	17264090				FOUND ON TIRE CHANGE, HUB ASSY HAS 4 CRACKS ON ONE SIDE AND TWO CRACKS ON THE BACK SIDE.  ALL CRACKS ARE AT BOLT HOLES.						1	H	7	1 	3O			NT	3A12    					 
1996091900938	19960919	00938	CE  	1996	9	19	96ZZZX4753       	1	19960827	G	3230	57412026	UPLOCK HOOK     			CESSNA	414   	414A        	2075907	CE  										LT MLG	CRACKED         	H		A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	13	26635	4552 				414A0531				UPLOCK HOOK FOUND CRACKED AFTER GEAR WOULD NOT RETRACT AND REMAIN IN UPLOCK.  ALSO, FOUND P/N 5141204-3, CRACKED AT FORW	ARD BLOCK ATTACH HOLE.  HOOK CRACKED AT RADIUS OF MLG RETAINING CUT OUT.  UNABLE TO DETERMINE IF DAMAGE OCCURRED UPON LA	ST EXTENSION OR RETRACTION.  SUBMITTER SUSPECTS WEAK HOOK DESIGN AND INADEQUATE MATERIAL THICKNESS ON SUPPORT COMPOUNDED	 BY AGE.			1	L	7	2 	3O				A7CE    					 
1996091900940	19960919	00940	CE  	1996	9	19	96ZZZX4755       	1	19960821	G	3222	108820010653	NOSE GEAR       			BEECH 	77    	77          	1153007	CE  										PISTON CLAMP	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	23	3868J	4403 				WA258				AIRCRAFT LANDED, BOUNDED HARD, THEN HIT NOSE GEAR FIRST.  NOSE GEAR SHEARED OFF.  NO INJURIES.  AIRCRAFT DAMAGE TO NOSE 	GEAR, PROPELLER STRIKE, AND ENGINE SUDDEN STOPPAGE.					1	L	7	1 	3O				A30CE   					 
1996091900941	19960919	00941	SO  	1996	9	19	96ZZZX4756       	2	19960811	G	8530		BALANCE TUBE    			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470R       	17026	SO  					COWL MOUNT	CHAFED          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	414SC					18266352				BOTTOM COWL SHOCK MOUNT WAS FOUND CHAFING AGAINST INTAKE BALANCE TUBE ON THE ENGINE.  THIS WOULD CAUSE AN INDUCTION LEAK	.  SAME CONDITION NOTICED ON SEVERAL 182'S.  ACTT:  1,281 HOURS.  SHOCK MOUNT, P/N S1115-29.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996091900942	19960919	00942	CE  	1996	9	19	96ZZZX4757       	1	19960814	G	2434	649304	ALTERNATOR      			CESSNA	421   	421C        	2076016	CE  										DC SYSTEM	INOPERATIVE     	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	421CW		39   		E030305360	421C0137				ALTERNATOR FAILED WITHIN 40 HOURS OF OVERHAUL.  A/E SN:  A-80319.  ARSNV2R045L.						1	L	7	2 	3O				A7CE    					 
1996091900943	19960919	00943	SO  	1996	9	19	96ZZZX4758       	1	19960820	G	2822	2B664	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										LT FUEL INLINE	LOW PRESSURE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	59987					317552081				RIGHT FUEL IN-LINE PUMP, FOUND TO OPERATE INTERMITTENTLY.  LEFT FUEL IN-LINE PUMP, FUEL PRESSURE WAS VERY LOW.						1	L	7	2 	3O				A20SO   					 
1996091900944	19960919	00944	SO  	1996	9	19	96ZZZX4759       	1	19960820	G	2822	2B650	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										RT FUEL INLINE	INTERMITTENT    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	59987					317552081				RIGHT FUEL IN-LINE PUMP, P/N 2B6-50, FOUND TO OPERATE INTERMITTENTLY.  LEFT FUEL IN-LINE PUMP, P/N 2B6-64, FUEL PRESSURE	 WAS VERY LOW.					1	L	7	2 	3O				A20SO   					 
1996091900945	19960919	00945		1996	9	19	96ZZZX4760       	3	19960822	G	6112	660712268	DEICE BOOT      			PIPER 	PA42  	PA421000    	7104225	SO  										LT PROPELLER	SHORTED         	B		A	GFER	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NM	09	431MC		1600 			425527031				WHILE IN-FLIGHT, THE CREW NOTICED A SUDDEN SHOWER OF SPARKS FROM THE LEFT PROPELLER.  A QUICK CHECK OF THE AMMETER SHOWE	D NO UNUSUAL CURRENT DRAW.  THE PROPELLER DEICE SYSTEM SHUT ITSELF OFF BEFORE THE CREW COULD TURN IT OFF.  AFTER LANDING	, THE PROPELLER WAS INSPECTED, A DEICE BOOT HAD SHORTED AND BURNED A HOLE APPROXIMATELY .25 INCH DEEP AND 1.50 INCH LONG	 ON THE LEADING EDGE APPROXIMATELY 9 INCHES FROM THE BLADE ROOT AND INTO THE COMPOSITE STRUCTURE OF THE BLADE.  THE BLAD	E WAS REMOVED AND SHIPPED TO AN OEM APPROVED REPAIR FACILITY FOR EVALUATION AND/OR REPAIR.  IT WAS LIKELY THE SHORT WAS 	THE RESULT OF A SMALL FOD STRIKE.	1	L	7	2 	4T			RT	A23SO   					 
1996091900946	19960919	00946	CE  	1996	9	19	96ZZZX4761       	1	19960816	G	5541	04330106	SPAR            			CESSNA	150   	150M        	2071830	CE  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	63651	4158 				15077456				WHILE INSPECTING RUDDER SPAR IAW SEB94-3, 3 CRACKS WERE FOUND AROUND THE EDGE OF THE 1 INCH HOLE AT THE TOP OF THE SPAR.	  REPLACED SPAR IAW CESSNA SB SEB94-3.  THE NEW SPAR DOES NOT HAVE THE HOLE INSTALLED.					1	H	7	1 	3O				3A19    					 
1996091900947	19960919	00947	CE  	1996	9	19	96ZZZX4762       	1	19960820	G	2720	081309032	BRACKET         			CESSNA	310   	310R        	2074245	CE  										RUDDER CONTROL	FAILED          	B		A	SBVR	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			GL	17	677WC					310R0100				PILOT REPORTED LOSS OF RUDDER CONTROL IN-FLIGHT.  THE AIRCRAFT WAS LANDED SAFELY AND DELIVERED TO MAINTENANCE.  INSPECTI	ON REVEALED THE RUDDER PULLEY BRACKET L OCATED AT STA 1.67 HAD PULLED FREE FROM THE FORWARD BULKHEAD.  THIS ALLOWED MISA	LIGNMENT OF THE CABLES ON THE PULLEYS AND ONE PULLEY , P/N MS20220-2, FAILED CAUSING LOSS OF RUDDER CONTROL.  CAUSE OF T	HIS WAS UNDETERMINED.  AS ACCESS TO THIS AREA IS VERY LIMITED, RECOMMEND INSTALLATION OF AN ACCESS PANEL BELOW THE AREA 	TO FACILITATE FUTURE INSPECTION.		1	L	7	2 	3O				3A10    					 
1996091900948	19960919	00948	CE  	1996	9	19	96ZZZX4763       	1	19960726	G	7921	AN9121D	FITTING         		635996      	BEECH 	36    	A36         	1151604	CE  										OIL COOLER	CRACKED         	D	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	11	7214Y					E2169				UPON RETURN OF FLIGHT, MECHANIC NOTICED SUBSTANTIAL AMOUNT OF OIL ON THE BELLY OF ACFT.  UPON INVESTIGATION, FOUND A FIT	TING (AN912-1D) THAT EXITS THE OIL COOLER WAS CRACKED IN HALF.  THIS ENGINE HAS BEEN RECONFIGURED TO A FLIGHTCRAFT TURBO	, TURBO NORMALIZED SYSTEM.  IT IS RECOMMENDED THIS FITTING SHOULD BE REPLACED WITH ONE MANUFACTURED FROM STEEL.				1	L	7	1 	3O				3A15    					 
1996091900949	19960919	00949	CE  	1996	9	19	96ZZZX4764       	1	19960724	G	7160	12503005	AIR BOX         			CESSNA	210   	210         	2073402	CE  										FLAPPER VALVE	DEFECTIVE       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	11	6909	2192 				57514				FLAPPER VALVE IN AIR BOX WAS IN CLOSED POSITION CAUSING INDUCTION HEAT TO BE SUPPLIED TO ENGINE WITH CONTROL IN THE INDU	CTION HEAT OFF POSITION.  SUSPECT CAUSE, CONTROL CABLE SLIPPAGE ALLOWING INDUCTION AIR TO BE CLOSED OFF AND INDUCTION HE	A T TO BE SUPPLIED TO ENGINE.  SUBMITTER RECOMMENDATION, REMOVE INDUCTION HEAT SYSTEM FROM AIRCRAFT.  INDUCTION AIR IS T	AKEN FROM BACK OF ENGINE ANYWAY AND THIS IS A FUEL INJECTED ENGINE NOT REQUIRING INDUCTION HEAT FOR ICING CONDITIONS.			1	H	7	1 	3O			RT	3A21    					 
1996091900950	19960919	00950	SO  	1996	9	19	96ZZZX4765       	2	19960826	G	8520		LIFTER          			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					VALVES	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	7466Q	215  				18261106	288361R			CYLINDER REMOVED FOR LOW COMPRESSION.  FOUND BOTH LIFTERS STARTING TO SPALL.  CHECKED ALL LIFTERS, 9 OF 12 LIFTERS SHOWE	D EVIDENCE OF SPALLING.  FACTORY NEW LIFTERS (ALL 12) INSTALLED.  CAM APPEARS OK.  THIS ENGINE FACTORY REMANUFACTURED, 6	/95.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1996091900979	19960919	00979		1996	9	19	96ZZZX4768       	4	19960801	G	2312	064101905	TRANSCEIVER     		KY196       	BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG				16305	7083				TRANSCEIVER INTERMITTENTLY SCRATCHY AND WILL NOT PICK UP STATIONS.  NO CHARGE WARRANTY REPAIR.						1	G	7	2 	3U				H13EU   					 
1996091900980	19960919	00980		1996	9	19	96ZZZX4769       	4	19960716	G	2312	40001452500	TRANSCEIVER     		RT138F      	BOLKMS	117   	BK117A1     	5626010	EU  										COCKPIT VHF	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117M				297	S7023				INSTALLED UNIT, TURNED ON POWER, CONTROL HEAD GUARD INDICATOR LIGHTS ILLUMINATED, AND STAYED LIT EVEN WITH NO GUARD MODU	LE INSTALLED.					1	G	7	2 	3U				H13EU   					 
1996092600120	19960926	00120	SO  	1996	9	26	96ZZZX4783       	2	19960826	G	8530		VALVE GUIDE     			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					NR 1 CYLINDER	OVERSIZE        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	7466Q	215  				18261106	288361R			CYLINDER REMOVED FOR LOW COMPRESSION.  FOUND EXT VALVE GUIDE .012 INCH OVERSIZE AT ONE END ALLOWING EXT VALVE EXCESS MOV	EMENT CAUSING IMPROPER VALVE SEATING.  FACTORY NEW CYLINDER INSTALLED.  THIS ENGINE FACTORY REMANUFACTURED 6/95.					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1996092600122	19960926	00122	EA  	1996	9	26	96ZZZX4785       	2	19960705	G	7414	1051324	SPRING          			CESSNA	172   	172         	2072402	CE  	LYC   	O320  	O320H2AD    	41508	EA  					IMPULSE COUPLING	BROKEN          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	75814	578  				17267971				CHECKED IGNITION TIMING.  FOUND APROXIMATELY 90 DEGREES OFF.  REMOVED MAGNETO, FOUND IMPULSE COUPLING SPRING BROKEN.  CH	ECKED I-C PER AD 78-09-07R3/AD 96-12-0-7 AND FOUND SATISFACTORY.  REVIEWED MAG O/H DATE FAXED BY INS.  ADJ.  FOUND I-C S	PRING, INSP AND REUSED, CONTRARY TO MANUFACTURER'S DATA TO "REPLACE AT EACH DIS ASSEMBLY WITH NEW PARTS."				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996092600124	19960926	00124	SO  	1996	9	26	96ZZZX4787       	1	19960820	G	5751	88639803	RIB             			PIPER 	PA32  	PA32R301    	7103218	SO  										AILERON	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	886JH	3167 				32R8213006				RIB WAS FOUND CRACKED FROM NUTPLATE RIVET.  AFTER REMOVING HINGE FITTING 86392-02, A 1.25 INCH CRACK WAS FOUND RUNNING A	LONG THE BOTTOM OF THE NUTPLATE.  USING A BORESCOPE, THE INBOARD NOSE RIB WAS ALSO FOUND TO HAVE A 1 INCH CRACK RUNNING 	THROUGH THE LOWER BOLT HOLE.  ALTHOUGH NOT AS BAD, THE OTHER AILERON WAS IN THE SAME CONDITION.				1	L	7	1 	3O				A3SO    					 
1996092600126	19960926	00126	CE  	1996	9	26	96ZZZX4789       	1	19960813	G	5511	07326117	RIB             			CESSNA	185   	A185F       	2072821	CE  										HORIZ STAB	CRACKED         	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	93055	5122 				18503173				WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN.  THIS IS A PUBLIC AIRCRAFT AND IS	 SUBJECTED TO MANY HOURS OF LOW LEVEL FLYING.					1	H	7	1 	3O				3A24    					 
1996092600127	19960926	00127	CE  	1996	9	26	96ZZZX4790       	1	19960813	G	5511	07326118	RIB             			CESSNA	185   	A185F       	2072821	CE  										HORIZ STAB	CRACKED         	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	93055	5122 				18503173				WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN.  THIS AIRCRAFT IS SUBJECTED TO MA	NY HOURS OF LOW LEVEL FLYING.					1	H	7	1 	3O				3A24    					 
1996092600128	19960926	00128	CE  	1996	9	26	96ZZZX4791       	1	19960813	G	5511	073261111	RIB             			CESSNA	185   	A185F       	2072821	CE  										HORIZ STAB	CRACKED         	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	93055	5122 				18503173				WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN.  THIS IS A PUBLIC AIRCRAFT AND IS	 SUBJECTED TO MANY HOURS OF LOW LEVEL FLYING.					1	H	7	1 	3O				3A24    					 
1996092600129	19960926	00129	CE  	1996	9	26	96ZZZX4792       	1	19960813	G	5511	07326119	RIB             			CESSNA	185   	A185F       	2072821	CE  										HORIZ STAB	CRACKED         	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	93055	5122 				18503173				WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN.  THIS IS A PUBLIC AIRCRAFT AND IS	 SUBJECTED TO MANY HOURS OF LOW LEVEL FLYING.					1	H	7	1 	3O				3A24    					 
1996092600130	19960926	00130	CE  	1996	9	26	96ZZZX4793       	1	19960813	G	5511	073261110	RIB             			CESSNA	185   	A185F       	2072821	CE  										HORIZ STAB	CRACKED         	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	93055	5122 				18503173				WHILE DOING THE CESSNA CONTINUAL AIRWORTHINESS PROGRAM, FOUND LEADING EDGE RIB BROKEN.  THIS IS A PUBLIC AIRCRAFT AND IS	 SUBJECTED TO MANY HOURS OF LOW LEVEL FLYING.					1	H	7	1 	3O				3A24    					 
1996092600133	19960926	00133		1996	9	26	96ZZZX4796       	4	19960824	G	6113	0550321	BULKHEAD        			CESSNA	172   	172Q        	2072437	CE  										SPINNER	WRONG HOLES     	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	918AT					17275933				SPINNER BULKHEAD FOR THE 172Q IS THE SAME PART NUMBER AS FOR THE OTHER MODELS, 172.  THE 172Q USES LARGER DIAMETER BOLTS	 TO ATTACH THE PROPELLER.  THE BOLT HOLES IN THE SPINNER BULKHEAD ARE FOR THE SMALLER BOLTS.  THE LARGER BOLTS CAN BE FO	RCED INTO POSITION, DEFORMING THE BULKHEAD.				1	H	7	1 	3O			NT	3A12    					 
1996092600134	19960926	00134		1996	9	26	96ZZZX4797       	1	19960904	G	2822	2B664	PUMP            	AIRBORNE    																BOOST	SHAFT DAMAGE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					2F198					PUMP SHAFT HAD DAMAGE TO IT.  PUMP MAY HAVE BEEN RUN DRY.																			 
1996092600136	19960926	00136	SW  	1996	9	26	96ZZZX4799       	1	19960830	G	7810	649263	EXHAUST TUBE    			MOONEY	M20   	M20K        	5870220	SW  										NR 3 CYLINDER	FLANGE FAILED   	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	CGLEE	113  				251042				APPROXIMATELY ONE-HALF OF INTAKE PIPE TO CYLINDER FLANGE BROKE OFF.  FOUND ON INSPECTION BY FUEL STAINS AT FLANGE.  THIS	 IS THE 8TH NR 3 INTAKE TUBE ON THIS ENGINE.  TT:  1,037.0 HOURS.  TUBES WERE CHANGED AT THE FOLLOWING TIMES/HOURS:  30.	0, 77.5, 156.0, 197.1, 225.0, 306.5, 794.3, 924.0, AND AT 1,037.2.  A  PREVIOUS MDR SUBMITTED BY THIS SHOP DETAILED 17 N	R 3 INTAKE TUBES REPLACED ON 3 OTHER MB-1 ENGINES,  IN ALL CASES DUE TO A BROKEN FLANGE, ALL IN THE SAME PLACE.  RECOMME	ND THAT TCM SHORTEN THE OPPOSITE END OF THE TUBE WHERE IT SLIDES IN THE COUPLING.  FOUND NO CLEARANCE BETWEEN THE TUBE E	ND AND THE THROTTLE BODY.  ALL TCM SB/S C/W.	1	L	7	1 	3O				2A3     					 
1996092600137	19960926	00137	CE  	1996	9	26	96ZZZX4800       	1	19960723	G	3244	650X108PLY	TIRE            			CESSNA	414   	414A        	2075907	CE  										MLG	RUBS PLATE      	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	116HA					414A0501				DURING INSPECTION, BOTH GOODYEAR 6:50 X 10 8-PLY FLT CUSTOMER II TUBE TYPE TIRES FOUND DAMAGED BY BRAKE ASSY BACK PLATES	.  AFTER WORN PARTS OF BRAKE ASSY WERE REPLACED, NEW TIRES WERE INSTALLED.  (SAME MAKE, GOODYEAR.)  TIRES STILL RUBBED. 	 INSPECTED TWO OTHER 400 SERIES AIRCRAFT ON FIELD WITH SAME TYPE GOODYEAR TIRES AND ALL WERE FOUND TO RUB ON BACK PLATES	.  ONE OTHER AIRCRAFT WAS CHECKED ON ANOTHER AIR FIELD WITH NO PROBLEM.  NEW CONDOR BRAND TIRES WERE INSTALLED ON AIRCRA	FT AND FOUND TO HAVE PLENTY OF CLEARANCE FROM BACK PLATE ASSYS.		1	L	7	2 	3O				A7CE    					 
1996092600138	19960926	00138	EA  	1996	9	26	96ZZZX4801       	1	19960502	G	3213		FORK            			FRCHLD	M62   	M62C        	3374004	EA  										LOWER LT MLG	FAILED          	C				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			CE	07	67481					T434341				LOWER LEFT LANDING GEAR FORK FAILED APPARENTLY DUE TO 'INTERNAL' CORROSION.  DURING TAKEOFF ROLL (TIME OF FAILURE), THE 	LEFT TIRE WAS CAUSED TO WEDGE AGAINST UPPER STRUT.  THIS EFFECTED SEVERE LEFT BRAKING AND CAUSING ACFT TO DEPART RUNWAY 	TO LEFT.				1	L	7	1 	3R				A724    					 
1996092600139	19960926	00139		1996	9	26	96ZZZX4802       	1	19960911	G	2810	CCA1550	DRAIN VALVE     																	FUEL SUMP	FAILED          	G	S	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	17										RETRAINING FEATURE ON END OF VALVE FAILED CAUSING PLUNGER TO DROP OUT.																			 
1996092600140	19960926	00140	SO  	1996	9	26	96ZZZX4803       	2	19960910	G	7414	1015828Y	MAGNET          	BENDIX      	SFS4RNR     						CONT  	A75   	A75*        	17005	SO  					ENGINE MAG	SHAFT FAILED    	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	07					80998					MAGNETO FAILED IN-FLIGHT.  MAGNET, P/N 10-15828Y, SHAFT FAILED.  BROKE IN TWO PIECES AT THE INNER WOODRUFF KEY SLOT AT T	HE OUTER EDGE OF THE SLOT.  THIS FAILURE WAS INSIDE THE MAGNETO SO THE GEAR AND OUTWARD END OF THE SHAFT CONTINUED TO RO	TATE.  THE ENGINE CONTINUED RUNNING UNTIL A SUCCESSFUL LANDING WAS MADE.  THE MAGNETO DRIVE GEAR TILTED PARTIALLY GRINDI	NG ALUMINUM FROM THE ACCESSORY CASE CONTAMINATING THE OIL AND RESULTING IN SUBSEQUENT ENGINE OVERHAUL.  THERE IS NO EVID	ENCE OF A LOCK-UP OF THE MAGNETO CAUSING THE SHAFT TO SHEAR THE WAY IT DID.  THE BEARINGS WERE VERY ROUGH, BUT INTACT. M	AGNETO MAINTENANCE HISTORY IS UNKNOWN AND TOTAL TIME IS UNKNOWN.  THE MAGNETO WAS USED ON A HOMEBUILT.  ENGINE, CONTINE						3	O			E213				 
1996092600141	19960926	00141	GL  	1996	9	26	96ZZZX4804       	1	19960904	G	2810	V0064	FUEL SYSTEM     			AMTR  	FALCXP	FALCONXP    	05658MR	GL  										CAP VENT	MALFUNCTION     	F				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	647AA	200  				600137				AIRCRAFT ENGINE LOST POWER ON LANDING AND COLLIDED WITH TREE DUE TO FUEL STARVATION OF ENGINE CAUSED BY LOSS OF FUEL SYS	TEM VENTING.  FUEL CAP LOOSES VENT FUNCTION WHEN TIGHTENED (SCREWED IN) TO FUEL TANK FILLER NECK.  CAP IS THERMOS TYPE T	HAT EXPANDS AS IT IS TIGHTENED.  WHEN CAP IS UNSCREWED FROM FILLER NECK, VENT FUNCTION RETURNS.				1	H	7	1 	3I			NT	EXPA1H71					 
1996092600142	19960926	00142		1996	9	26	96ZZZX4805       	1	19960816	G	2560	B79229	BATTERY         		BE369       															NEG LEAD	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EU	01					21428					DURING OVERHAUL OF RESCUE BEACON, FOUND FAILURE WAS DUE TO BATTERY NEG LEAD FAILURE.  REMAINING STOCK CHECKED AND FOUND 	OTHERS DEFECTIVE.  BATTERIES RETURNED TO MFG AND FOUND THOSE UNITS, S/N 21425 THROUGH S/N 21527, WERE SUSPECT TO FAILURE	 DUE TO A PRODUCTION PROBLEM.																	 
1996092600143	19960926	00143	CE  	1996	9	26	96ZZZX4806       	1	19960905	G	5330	07107005	SKIN            			CESSNA	182   	182P        	2075816	CE  										CENTER SECTION	CORRODED        	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	21150					18261448				BOTH CENTER SECTION SKIN AND CENTER SECTION DOUBLER BADLY CORRODED (WITH HOLES).  CORROSION IS APPARENTLY DUE TO 'DRIZ-A	IR' DESICCANT SPILLING ONTO CARPET, AND THEN FLOWING BETWEEN SKINS INTO GEARBOX.					1	H	7	1 	3O			NT	TA13    					 
1996092600144	19960926	00144	EA  	1996	9	26	96ZZZX4807       	2	19960528	G	8530	05K21120	CYLINDER        			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					NRS 1-2/3-4	WORN            	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	377LC	4950 	110  			28R7918120	L1501751A			COMPRESSION CHECK INDICATES ALL 4 CYLINDERS NOT SERVICEABLE DUE TO LOW COMPRESSION AT 110 HOURS TSO. TT:  4,950 HOURS.						1	L	7	1 	3O	3	O		2A13    	1E10				 
1996092600145	19960926	00145	EA  	1996	9	26	96ZZZX4808       	2	19960528	G	8530	05K21120	CYLINDER        			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					NRS 1/2-3/4	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	377LC	4544 	689  			28R7918120	L277151A			COMPRESSION CHECK INDICATES ALL 4 CYLINDERS NOT SERVICEABLE DUE TO LOW COMPRESSION.  TSO:  689 HOURS.  TT:  4,544 HOURS.						1	L	7	1 	3O	3	O		2A13    	1E10				 
1996092600146	19960926	00146	SO  	1996	9	26	96ZZZX4809       	1	19960801	G	8120	46C19839	TURBO           			PIPER 	PA46  	PA46350P    		SO  										RT ENGINE	WORN BEARINGS   	B			MZER	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	15	463WP	955  			XFL30850	4622173				MANIFIOLD PRESSURE LOSS AT 13,000 FEET.  FOUND TURBO BLADES MACHINING INTO HOUSING.  (BEARING FAILURE.)  THIS IS THE THI	RD FAILURE OF THIS PART SUBMITTER IS AWARE OF.  OTHERS RESULTED IN DEPLETION OF OIL SUPPLY TO THE POINT OF ENGINE FAILUR	E.				1	L	7	1 	3O			RT	A25SO   					 
1996092600147	19960926	00147	EU  	1996	9	26	96ZZZX4810       	1	19960801	G	7921	5711012334	INLET FENCE     			PILATS	PC12  	PC12        	7090550	EU  										OIL COOLER	BROKEN          	B			S5YR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	62JT	677  				107				PILOT PRODUCED BROKEN PART WHEN ARRIVING FOR INSPECTION.  POSSIBLE TURBULENT AREA CAUSING VIBRATION AND FAILURE OF PART.	  SUBMITTER RECOMMENDS INSPECTING THIS AREA DURING PRE-FLIGHT AND PAY CLOSE ATTENTION DURING INSPECTION TIMES.					1	L	7	1 	3T			RT	A78EU   					 
1996092600148	19960926	00148	CE  	1996	9	26	96ZZZX4811       	1	19960830	G	2140	RE65G3R00	RESISTOR        			BEECH 	95    	E95         	1153410	CE  										CABIN HEAT	BURNED          	G				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	01	729EM					TD713				A RESISTOR IN CABIN HEATER OVERHEAT WARNING SYSTEM FAILED AND BURNED CAUSING SMOKE IN THE CABIN						1	L	7	2 	3O				3A16    					 
1996092600149	19960926	00149	SW  	1996	9	26	96ZZZX4812       	1	19960813	G	2810	630183	FUEL SUMP       			GULSTM	500   	500S        	0141107	SW  										BAG COMP	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	800CB	1100 				17847				HOLE CORRODED THROUGH FUSELAGE FUEL SUMP.  THE DRAIN VALVE WAS REPLACED TO CORRECT A FUEL LEAK, BUT FUEL CONTINUED TO LE	AK FROM THE SUMP BY THE DRAIN VALVE.  WHILE WIPING FUEL OFF OF THE SUMP, THE MECHANICS FINGER POKED THROUGH THE SUMP BY 	THE DRAIN VALVE.  THE CORROSION HAD WORKED THROUGH FROM THE INSIDE TO THE POINT THAT THE PAINT WAS ALL THERE WAS LEFT AT	 THAT AREA HOLDING THE FUEL IN.			1	H	7	2 	3O				6A1     					 
1996092600150	19960926	00150	SO  	1996	9	26	96ZZZX4813       	2	19960514	G	7322	30764	FLOAT ASSY      	FACET       	MA45        	CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					CARBURETOR	DETACHED        	B			YECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	88MA	850  			3997983	34691				CARBURETOR WAS REMOVED AT ANNUAL INSPECTION FOR EXCESSIVE WEAR ON THROTTLE SHAFT.  UPON DISASSEMBLY, ONE OF THE FLOATS W	AS FOUND BROKEN FROM THE ACTUATING ARM.  IT WAS NOT RUPTURED OR WORN THROUGH.  FLOAT WAS DATE CODED 4-84.  SUSPECT A ROU	GH RUNNING ENGINE AND/OR A BAD SOLDER POINT ON THE FLOAT TO BRACKET.  NOTE:  THE ENGINE WAS 'OVERHAULED' 77 HOURS AGO. T	HE CARBURETOR WAS NOT.			1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996092600151	19960926	00151	SO  	1996	9	26	96ZZZX4814       	1	19960826	G	7921	455192	COOLER          			PIPER 	PA32  	PA32301     	7103207	SO  										ENGINE OIL	SPLIT           	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	09	8442H	1465 			81E871	328106098				OIL COOLER SPLIT AND ALLOWED A VERY LARGE AMOUNT OF ENGINE OIL TO EXIT THE LOWER COWLING WITHOUT ANY VISUAL INFORMATION 	TO THE PILOT.					1	L	7	1 	3O				A3SO    					 
1996092600152	19960926	00152	EA  	1996	9	26	96ZZZX4815       	2	19960720	G	7230	3108301	CT BLADE        			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					GAS GEN	FAILED          	A		A	MASR	E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			SW	07	156YV	3059 				UC156	32460GG			AN IN-FLIGHT SHUT DOWN OF THE RIGHT ENGINE DUE TO THE FAILURE OF THE HOT SECTION CT BLADE.  AT THE ENGINE TEAR DOWN, NOT	ED ONE CT BLADE HAD LIBERATED AT THE ROOT AND ALL THE OTHER CT BLADES WERE SEVERELY DAMAGED DUE TO THE CONTACT WITH THE 	LIBERATED BLADE.  THE CT BLADE REMAINING ROOT SECTION WAS SENT TO PRATT AND WHITNEY FOR FURTHER INVESTIGATION				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1996092600153	19960926	00153	EA  	1996	9	26	96ZZZX4816       	2	19960507	G	7210	310076701	SUN GEAR        			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					POWER SECTION	FAILED          	A		A	MASR	E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	157YV	13550	13550		55C036	UC157	32512PS			AN IN-FLIGHT SHUT DOWN OF THE LT ENGINE DUE TO THE FAILURE OF THE POWER SECTION.  AT THE ENGINE TEAR DOWN, THE INVESTIGA	TION REVEALED THE 1ST STAGE SUN GEAR HAD FAILED AND IS BEING CONSIDERED THE CAUSE OF THE SHUT DOWN.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1996092600154	19960926	00154	NM  	1996	9	26	96ZZZX4817       	1	19960824	G	3232	400089002	BELLCRANK       			PIPER 	PA60  	PA60601     	7106010	NM  										GEAR DOOR	FAILED          	B			TRKR	A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CL	CLIMB          	1			SO	15	42WH	3969 				610533131				AFTER TAKEOFF, PILOT RETRACTED GEAR AND GOT NO UP LIGHT.  COULD SEE INBOARD DOOR TRAILING.  PILOT LOWERED AND LANDED.  B	ELLCRANK WAS FOUND IN SEVERAL PIECES.  OUTBOARD ROD, 400006-11, WAS BENT AND INBOARD GEAR DOOR WAS OPEN ON LANDING, SCRA	PED RUNWAY, AND HAD TO BE REPLACED.  NO OTHER DAMAGE FOUND AND NO MIS-RIGGING WAS FOUND.				1	M	7	2 	3O			RT	A17WE   					 
1996092600155	19960926	00155	CE  	1996	9	26	96ZZZX4818       	1	19960730	G	3710	S250016	HOSE            			CESSNA	182   	182R        	2072731	CE  										VACUUM FILTER	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	1481E	1676 				18268180				VACUUM HOSE FROM CENTER VACUUM FILTER TO ATTITUDE INDICATOR HAS CRUMBLED, FALLING APART.  NAME ON WHAT IS LEFT OF HOSES 	IS REDI-SEAL OR IMPERIAL EAST MAT.					1	L	7	1 	3O			NT	3A13    					 
1996092600156	19960926	00156	EA  	1996	9	26	96ZZZX4819       	2	19960801	G	8530		VALVE           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE EXHAUST	FAILED          	B			BXPR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			EA	09	32490	1709 				287515169	L3989027A			ENGINE LOST POWER ON TAKEOFF.  PILOT ABLE TO  MAINTAIN ALTITUDE AND RETURN TO AIRPORT.  VALVE APPEARS TO BE P/N 75068 WH	ICH IS PRONE TO BREAKAGE WHEN USING FUEL HIGHER THAN 80/87 (REF:  LYCOMING SB 404).  ANY VALVES STILL IN SERVICE SHOULD 	BE REPLACED.				1	L	7	1 	3O	3	O		2A13    	E274				 
1996020200295	19960202	00295	CE  	1996	2	2	96ZZZX482        	1	19960109	G	2750	0512129	BRACKET         			CESSNA	185   	A185F       	2072821	CE  										FS 65.33 RT FLAP	BROKEN          	D		A		A	O			UNSCHED LANDING         	OTHER                   			F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	15	105NR	6106 				18503956				CESSNA 185 WITH ROBERTSON STOL KIT INSTALLED WAS AIRBORNE WHEN PILOT APPLIED FLAPS AND THE AIRCRAFT STARTED TO ROLL TO T	HE RIGHT.  A PASSENGER REPORTED HEARING A SOUND COMING FROM THE FLOOR OF THE AIRCRAFT.  PILOT PUT FLAPS BACK UP AND LAND	ED AT NEAREST AIRPORT.  A MECHANIC INVESTIGATED THE PROBLEM AND FOUND THE PULLEY BRACKET FOR THE RIGHT FLAP HAD COMPLETE	LY BROKEN OFF, ALSO, THE PULLEY BRACKET FOR THE LEFT FLAP WAS STARTING TO CRACK.  THE LOCATION OF THE PULLEY BRACKETS IS	 IN THE BELLY UNDER THE MIDDLE PASSENGER SEAT MOUNTED IN CENTER OF THE FUSELAGE BULKHEAD STATION 65.33.		1	H	7	1 	3O				3A24    					 
1996092600157	19960926	00157	SO  	1996	9	26	96ZZZX4820       	1	19960820	G	7120		MOUNT           			PIPER 	PA28  	PA28R180    	7102809	SO  										ENGINE LOWER LT	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	4598J	2271 				28R30475				ENGINE MOUNT WAS CRACKED AT THE CROSS-OVER TUBE AT THE LOWER LEFT SIDE OF MOUNT.  MOUNT HAD BEEN PREVIOUSLY REPAIRED IN 	A DIFFERENT LOCATION.					1	L	7	1 	3O				2A13    					 
1996092600158	19960926	00158	GL  	1996	9	26	96ZZZX4821       	1	19960918	G	3230		RETRACT CYLINDER			YAKLEV	YAK983	YAK50       	9830220	GL  										LT MLG	MALFUNCTION     	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	01	50RK	381  				812001				LEFT MLG COLLAPSED AFTER LANDING ON ROLL-OUT.  LANDING GEAR WAS INSPECTED FOR DAMAGE, LUBED LT GEAR AT HINGE POINTS AND 	CYCLED.  VERIFIED GEAR WAS DOWN AND LOCKED.  SAFTIED GEAR HANDLE IN DOWN POSITION FOR FERRY FLIGHT.  AIRCRAFT TOTAL TIME	 381.4 HOURS.  ACFT IS CERTIFIED EXPERIMENTAL, EXHIBITION.  IT APPEARS THE INTERNAL DOWNLOCKS IN THE LANDING GEAR RETRAC	T CYLINDER DID NOT POSITIVELY ENGAGE AS GEAR WORKED PROPERLY ON JACKS.  ONLY THE LEFT GEAR RETRACTED ON ROLL-OUT.			1	L	7	1 	3R			RT	EXPA1L71					 
1996092600159	19960926	00159	SO  	1996	9	26	96ZZZX4822       	1	19960801	G	3234	752303	SELECTOR        			PIPER 	PA23  	PA23250     	7102308	SO  										MLG LEVER	FAILED          	H	L	A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			EA	23	5064C					277405376				AIRCRAFT WAS MAKING AN APPROACH TO LANDING WHEN THE PILOT SELECTED THE LANDING GEAR DOWN POSITION.  WHEN OPERATING THE L	ANDING GEAR SELECTOR LEVER THE COMPONENT BROKE AWAY INTO THE PILOT'S HAND AND AS A RESULT BECAME DISCONNECTED FROM THE R	EST OF THE LANDING GEAR SYSTEM.  UNABLE TO LOWER THE GEAR, THE PILOT CRAWLED UNDER THE PANEL AND MANUALLY SELECTED THE G	EAR DOWN POSITION FROM THE REMAINING PORTION OF THE LEVER UTILIZING A FUEL TESTER.  THE GEAR WAS LOWERED AND THE AIRCRAF	T LANDED WITHOUT INCIDENT.  THE FAILED LANDING GEAR SELECTOR LEVER, PIPER P/N 752303, WAS THE SUBJECT OF SB NR 635, DATE	D 1-3-79, AND A SUBSEQUENT AD NR 79-11-06.	1	L	7	2 	3O				1A10    					 
1996092600160	19960926	00160	GL  	1996	9	26	96ZZZX4823       	3	19960827	G	6111	S84B2	BLADE           			BEECH 	35    	V35A        	1151544	CE  						MCAULY	2A36C	2A36C82     	GL  	RETAIN THREAD	CRACKED         	B			ZJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	7917R				C70591YS	D8940		685951		PROPELLER SUBMITTED FOR OVERHAUL/COMPLIANCE WITH AD 89-26-08, OIL FILL MODIFICATION TO DETECT BLADE/HUB CRACKS.  UPON PE	NETRANT INSPECTION OF BLADE, A 1.25 INCH LONG CRACK WAS DISCOVERED IN THE SECOND RETENTION THREAD.   ALSO, THE PROPELLER	 HUB, S/N 685951, WAS FOUND WITH SEVERE EXTERNAL CORROSION.  SUBMITTER STATED CAUSE OF CRACK UNKNOWN.  RECOMMEND OPERATO	RS CHECK C/W AD 89-26-08.			1	L	7	1 	3O				3A15    		5	C	P880	 
1996092600161	19960926	00161	SO  	1996	9	26	96ZZZX4824       	1	19960813	G	3211	2082900	SIDE BRACE      			PIPER 	PA24  	PA24250     	7102404	SO  										LT/RT MLG	STUD CRACKED    	B			CTKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8300P					243549				SIDE BRACE STUD INSPECTED IAW AD 95-20-07.  BOTH LEFT AND RIGHT STUDS CRACKED AT RADIUS OF HEAD.						1	L	7	1 	3O				1A15    					 
1996092600162	19960926	00162	EA  	1996	9	26	96ZZZX4825       	2	19960504	G	7414	1068255511	MAGNETO         		D4KB3999    	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					DIST BLOCK	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	91307				K20882G	243201	L2556651A			INSPECTED MAG IAW 500-HOUR INSPECTION AT 1,057 HRS TTSN AND FOUND DISTRIBUTOR BLOCK DRIVEN GEAR BEARING BROKEN LOOSE FRO	M BLOCK (BROWN BLOCK). REPLACED WITH 10-682054 BLOCK.  ENGINE STILL HAD ACCEPTABLE MAG DROP.  APPROXIMATELY 500 HRS SINC	E LAST 500-HOUR COMPLYING INSPECTION.  NO 500-HOUR INSPECTION LISTED FOR MAGNETO IN LOG BOOKS.				1	L	7	1 	3O	3	O		2A3     	1E10				 
1996092600163	19960926	00163	EA  	1996	9	26	96ZZZX4826       	2	19960809	G	8530		CYLINDER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					NR 2	PISTON FAILED   	G				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			D	E	K	INFLIGHT SEPARATION       	VIBRATION/BUFFET          	FLUID LOSS                	CR	CRUISE         	1			EA	13	2343Z	4191 	20   			278054018	L1195648A			AIRCRAFT MADE EMERGENCY LANDING.  RIGHT ENGINE FAILED DUE TO NR 2 CYLINDER AND PISTON DEPARTING AIRCRAFT IN-FLIGHT.  CYL	INDER PARTS AND SIDE COWL NEVER RECOVERED.  TEAR-DOWN INSPECTION REVEALED NO APPARENT REASON FOR FAILURE.					1	L	7	2 	3O	3	O		1A10    	1E4				 
1996092600164	19960926	00164		1996	9	26	96ZZZX4827       	4	19960801	G	3457	TNL2101IO	GPS SYSTEM      	TRBNAV      		CESSNA	650   	650         	2076802	CE  										ACFT NAV	ERRORS          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	334H					650071				UNIT DOES NOT CONFORM TO ARINC 419 DATABUS STANDARDS.  WHEN UNIT WAS PROPERLY INSTALLED AND CONFIGURED TO SUPPLY NAVIGAT	ION INFO TO THE EFIS SYSTEM, SOME UNITS OF INFORMATION WERE ERRONEOUS.					2	L	7	2 	4F				A9NM    					 
1996092600165	19960926	00165		1996	9	26	96ZZZX4828       	4	19960801	G	3457	TNL2101IO	GPS SYSTEM      	TRBNAV      		CESSNA	650   	650         	2076802	CE  										ACFT NAV	ERRORS          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	434H					6500123				UNIT DOES NOT CONFORM TO ARINC 419 STANDARDS WHEN THE UNIT WAS PROPERLY INSTALLED AND CONFIGURED TO SUPPLY NAVIGATION IN	FO TO THE EFIS SYSTEM, SOME BITS OF INFORMATION WERE ERRONEOUS.					2	L	7	2 	4F				A9NM    					 
1996092600166	19960926	00166	GL  	1996	9	26	96ZZZX4829       	2	19960202	G	7250	6877736	LABYRINTH SEAL  		6898735     						ALLSN 	250C  	250C20B     	03013	GL  					GP TURBINE	FRACTURED       	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17										TURBINE WAS REMOVED DUE TO RUB.  UPON DISASSEMBLY, FOUND THE GP STATOR SEAL HAD FRACTURED AT THE FORWARD END OF THE BEAR	ING BORE.  THIS TURBINE HAD THE NEW NR 8 BEARING AND RETAINING PLATE INCORPORATED PER CEB 1326.  CAUSE OF FAILURE UNKNOW	N.									3	U			E4CE				 
1996020200296	19960202	00296	CE  	1996	2	2	96ZZZX483        	1	19960108	G	2910	MS2951207	PLUG SEAL       		51170111    	CESSNA	414   	414A        	2075907	CE  										HYD FILLER	FAILED          	B		A	DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	25SC					414A114				HYDRAULIC FILLER PLUG SEAL LEAKED WATER WHILE ACFT PARKED OUTSIDE.  WATER WAS CIRCULATED THROUGH HYD SYSTEM DURING NORMA	L OPERATION.  ACFT REPOSITIONED FROM WARM HANGAR TO FREEZING TEMP.  UPON PRE-FLIGHT, 1 MLG DOWNLOCK LIGHT WAS OUT AND GE	AR UNSAFE LIGHT WAS LIT.  UPON TROUBLESHOOTING, WATER FOUND IN ALL LANDING GEAR ACTUATORS.  WHEN WATER FROZE, IT ACTUATE	D DOWNLOCK SWITCH AND GAVE FALSE GEAR UNSAFE INDICATION.  THIS IS SECOND OCCURRENCE ON THIS ACFT.  HYD SYS CLEANED AND R	EPAIRED.  FILLER PLUG SEAL REPLACED.  ACFT RETURNED TO SERVICE.  SUBMITTER SUGGESTS REGULAR INSP OF FILLER PLUG SEAL ON 	ALL 400 SERIES CESSNA ACFT.	1	L	7	2 	3O				A7CE    					 
1996092600167	19960926	00167	CE  	1996	9	26	96ZZZX4830       	1	19960830	G	2435		SWITCH WIRE     	LEARSIEGLER 	23080002    	RKWELL	NA265 	NA26565     	7630107	CE  										GEN HOT LIGHT	LOOSE           	G				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	13	265A	1024 	272  		1609	46547				GENERATOR 'HOT LIGHT' CAME ON THE ANNUNCIATOR PANEL.  REDUCING ENGINE POWER, LIGHT WENT OUT.  CAME BACK IN WITH POWER, L	IGHT CAME BACK ON.  ENGINE WAS SHUT DOWN IAW FLIGHT MANUAL.  STARTER/GENERATOR WAS SENT TO OVERHAUL FACILITY FOR REPAIR 	AND TEAR-DOWN REPORT.  IT WAS NOTED THAT THERMAL SWITCH WIRE WAS LOOSE INSIDE STARTER/GENERATOR.  REPAIR WAS MADE AND UN	IT TESTED GOOD.			2	L	7	2 	4J				A2WE    					 
1996092600168	19960926	00168	SW  	1996	9	26	96ZZZX4831       	1	19960904	G	2435	300SG119Q	STARTER         			GULSTM	690TP 	695A        	7630519	SW  										START/GEN	WRONG PART      	B			GFER	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	695NC	893  			1463	96032				DURING INSPECTION, NOTED ONE OF THE STARTER/GENERATORS HAD A DATA TAG ISSUED BY AIRCRAFT PARTS CORPORATION AND IDENTIFIE	D WITH P/N 300.S.G.119Q, NOT THE LEAR SIEGLER (LUCAS) P/N 23079-000-1 REQUIRED BY THE IPC.  APC CONTACTED TO INQUIRE IF 	EVER AN STC OR A PAH LETTER OF EQUIVALENCY HAD BEEN ISSUED AGAINST STARTER/GENERATORS FOR INSTALLATION ON COMMANDER MODE	L 695A, NONE HAD.  P/N 300.S.G.119Q IS SIMILAR IN MOST RESPECTS TO OTHER LEAR SIEGLER STARTER/GENERATORS INSTALLED ON ME	TROLINERS AND JETSTREAM 31'S, AND APPROVALS FOR THEIR USE ON ACFT HAVE BEEN SECURED, BUT NOT FOR THE 695A.  UNAPPROVED P	ART INSTALLED IN AUSTRIALIA 10-92 AND WENT UNDETECTED DURING IMPORT IN 1-95, AT 1ST 100-HR INSP AFTER IMPORT AND AT FAA	1	H	7	2 	4T				2A4     					 
1996092600211	19960926	00211	EU  	1996	9	26	96ZZZX4833       	1	19960709	G	3243	T67G73231	MASTER CYLINDERS			SLNSBY	T67   	T67M260     	8323006	EU  										BRAKE	FAILED          	B			UNER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	3102J	802  				2162				AIR CREWS HAVE REPORTED AIRCRAFT BRAKE PEDALS WERE SPONGY OR HAVE FADED/FAILED DURING BRAKING APPLICATIONS.  AFTER 20,00	0 HOURS OF OPERATION AT THE USAFA, BRAKE SYSTEMS STARTED TO DEVELOP PROBLEMS.  REVISED BRAKE BLEEDING PROCEDURES WERE DE	VELOPED, OPERATOR BRAKING APPLICATION TECHNIQUE IMPROVED AND AIRCRAFT KEPT FLYING WHILE MORE EMERGENCIES WERE DELCARED F	OR BRAKE FAILURES.  FINALLY, THE MASTER BRAKE CYLINDER WAS MODIFIED UNDER SAL MOD 726 (P/N T67G73213).  THE ENTIRE FLEET	 IS BEING UPGRADED TO THE MODIFIED MASTER CYLINDER WHILE ACCUMULATING 50,000 FLYING HOURS.  SAL AND PARKER/CLEVELAND HAV	E BEEN TASKED TO IMPROVE THE CURRENT BRAKING SYSTEM.	1	L	7	1 	3O			NT	A73EU   					 
1996092600212	19960926	00212	EU  	1996	9	26	96ZZZX4834       	1	19960829	G	2822	2B66	FUEL PUMP       			SLNSBY	T67   	T67M260     	8323006	EU  										FUEL BOOST	FAILED          	B			UNER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	30723	802  				2154				THE AIR CREW REPORTED LOW OR NO FUEL PRESSURE INDICATION/RISE DURING PRE-FLIGHT CHECK.  FURTHER INSPECTION BY UNC MAINTE	NANCE TECHNICIANS REVEALED THE FUEL PUMP DID NOT PRODUCE ANY NOISE WHEN THE FUEL PUMP BOOST SWITCH WAS TURNED ON.  THERE	 HAVE BEEN 6 AIRBORNE ELECTRIC FUEL BOOST PUMPS (P/N 2B6-6, SAL P/N 12634036) FAILURES AT THE USAFA.  AIRBORNE HAS REPOR	TED THE PUMPS ARE CONTAMINATED AND HAVE FAILED.  AFTER 2 YEARS AND 30,000 FLYING HOURS AT THE USAFA, ONLY 6 AIRBORNE ELE	CTRIC FUEL PUMPS (P/N 2B6-6) HAVE FAILED ON 55 AIRCRAFT.  THE T-3A FUEL TANK ARE FABRICATED FROM GRP (FIBERGLASS) AND SE	ALED WITH FUEL RESISTANCE SEALANT.	1	L	7	1 	3O			NT	A73EU   					 
1996092600213	19960926	00213	EU  	1996	9	26	96ZZZX4835       	1	19960829	G	3242	16402000	BRAKE DISC      		16402000    	SLNSBY	T67   	T67M260     	8323006	EU  										MLG	WARPED          	B			UNER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	3102J	704  				2162				THE AIR CREW REPORTED THE ACFT BRAKES WERE SPONGY DURING BRAKING APPLICATION.  THERE HAVE BEEN MANY REPORTS BY USAF PILO	TS IN THE T-3A PROGRAM PERTAINING TO SPONGY OR DEFECTIVE BRAKES.  A DETAILED INSPECTION OF THIS AIRCRAFT'S BRAKING SYSTE	M REVEALED A WARPED BRAKE DISC.  AFTER 2 YEARS AND 30,000 FLYING HOURS AT THE USAFA, ONLY 5 CLEVELAND BRAKE DISCS (P/N 1	64-02000) HAVE WARPED ON 54 AIRCRAFT.  THERE HAVE BEEN PROLBLEMS WITH THE T-3A BRAKING SYSTEM AND THE SLINGSBY MANUFACTU	RED MASTER CYLINDERS (P/N T67G73231 NOW REVISED TO P/N T67G73213 LATEST REVISION).  THIS OCCURRENCE DID NOT APPEAR TO IN	VOLVE THE MASTER CYLINDERS AS THE DEFECTIVE COMPONENT IN THE BRAKING SYSTEM.	1	L	7	1 	3O			NT	A73EU   					 
1996092600214	19960926	00214	EU  	1996	9	26	96ZZZX4836       	1	19960829	G	3242	16402000	BRAKE DISC      			SLNSBY	T67   	T67M260     	8323006	EU  										MLG	WARPED          	B			UNER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	31398	537  				2176				THE AIR CREW REPORTED THE AIRCRAFT BRAKES WERE SPONGY DURING BRAKING APPLICATION.  THERE HAVE BEEN MANY REPORTS BY USAF 	PILOTS IN THE T-3A PROGRAM PERTAINING TO SPONGY OR DEFECTIVE BRAKES.  A DETAILED INSPECTION OF THIS AIRCRAFT'S BRAKING S	YSTEM REVEALED A WARPED BRAKE DISC.  AFTER 2 YEARS AND 30,000 FLYING HOURS AT THE USAFA, ONLY 5 CLEVELAND BRAKE DISCS (P	/N 164-02000) HAVE WARPED ON 54 AIRCRAFT.  THERE HAVE BEEN PROBLEMS WITH THE T-3A BRAKING SYSTEM AND THE SLINGSBY MANUFA	CTURED MASTER CYLINDERS (P/N T67G73231 NOW REVISED TO P/N T67G73213 LATEST REVISION).  THIS IS SECOND OCCURRENCE AND DID	 NOT APPEAR TO INVOLVE THE MASTER CYLINDERS AS THE DEFECTIVE COMPONENT IN THE BRAKING SYSTEM.	1	L	7	1 	3O			NT	A73EU   					 
1996092600216	19960926	00216	GL  	1996	9	26	96ZZZX4838       	2	19960729	G	7412	6899093	EXCITER         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE IGNITION	FAILED          	B			JSNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	204PC	648  				S895	836679			START CIRCUIT BREAKER OPENED 1-2 SECONDS AFTER START INITIATED.  TROUBLESHOT AND FOUND HIGH TENSION SIDE OF IGNITION EXC	ITER SHORTED OUT.  REPLACED EXCITER.  THIS AIRCRAFT HAS CONTINUOUS IGNITION SYSTEM WHICH MUST BE OPERATED WHEN FLYING IN	 FALLING SNOW.  THIS SYSTEM OPERATES APPROXIMATELY 25 OF LAST 30 FLIGHT HOURS.  PERHAPS TOO MUCH FOR EXCITER UNIT.  AIRC	RAFT SHOULD INCORPORATE AUTO-RELIGHT INSTEAD.			1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996092600217	19960926	00217	EU  	1996	9	26	96ZZZX4839       	1	19960729	G	6710	D133145401E	GUIDE ASSY      			BOLKMS	105   	BO105S      	5626006	EU  										M/R	FAILED          	B			JSNR	A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	09	204PC	644  				S895				PILOT EXPERIENCED SWITCH OVER TO SYSTEM 2 HYDRAULICS DURING FLIGHT.  AIRCRAFT LANDED.  RESET TO SYSTEM 1.  SYSTEM SWITCH	ED TO NR 2.  TROUBLESHOT AND FOUND SWITCH IN 10DB4 GUIDE ASSY SHORTED.  GUIDE ASSY HAD LOTS OF MOISTURE UNDER COVER.  GU	IDE ASSY REPLACED.  AIRCRAFT HAD BEEN OPERATING IN HIGH HUMIDITY, RAIN, AND SNOW.				1	G	7	2 	3U				H3EU    					 
1996020200297	19960202	00297	SO  	1996	2	2	96ZZZX484        	1	19960102	G	2810	710282LH	TANK            			PIPER 	PA31  	PA31350     	7103110	SO  										LT WING INBD	CHAFED          	B		A	WC7R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	711LH				8111762	318152174				PILOT REPORTED 'FUEL LEAK, LEFT WING'.  SEAM TAPE ON FUEL TANK BED WAS FOUND MISSING.  BLADDER TANK HAD CHAFED THROUGH O	N ROUGH EDGES (2 PLACES).  REMOVED BLADDER AND REPLACED WITH NEW BLADDER.  SUBMITTER STATED TO MAKE SURE ALL SEAMS ARE T	APED TO PREVENT CHAFING.  HOBBS, 2,766.8.				1	L	7	2 	3O				A20SO   					 
1996092600219	19960926	00219	GL  	1996	9	26	96ZZZX4841       	2	19960725	G	7230	6871259	TIE BOLT        		6890550     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMP ROTOR	UNDERSIZE       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107AL				59038	S772	821484			DISCOVERED DEFECT DURING TOLERANCE INSPECTION.  THE TIE BOLT SHOULDER UNDER SIZE BY .002 INCH, .440 INCH, BPS .4420 INCH	 TO .4425 INCH.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996092600220	19960926	00220	GL  	1996	9	26	96ZZZX4842       	2	19960719	G	7314	216002	DRIVE SHAFT     		6896822     	BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUEL PUMP	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	170AL	2991 	1186 			52063				DURING DISASSEMBLY FOR OVERHAUL, FOUND WORN DRIVESHAFT SPLINES (SMALL END) AND WORN INTERNAL GEAR SPLINE.  (PARTS SCRAPP	ED).  SUSPECT IMPROPER LUBRICATION.					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
1996092600221	19960926	00221	EU  	1996	9	26	96ZZZX4843       	1	19960719	G	6330	10510156	SUPPORT         			BOLKMS	105   	BO105C      	5626005	EU  										TRANSMISSION	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	205BB				603	S58				SCHEDULED INSPECTION FOUND TRANSMISSION SUPPORT WITH MECHANICAL DAMAGE BEYOND LIMITS, CAUSED BY VIBRO-ETCHING IN TOP FLA	NGE AREA.					1	G	7	2 	3U				H3EU    					 
1996092600222	19960926	00222	EU  	1996	9	26	96ZZZX4844       	1	19960719	G	6330	10510155	SUPPORT         			BOLKMS	105   	BO105C      	5626005	EU  										TRANSMISSION	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	205BB				590	S58				SCHEDULED INSPECTION FOUND TRANSMISSION SUPPORT WITH MECHANICAL DAMAGE BEYOND LIMITS - CAUSED BY VIBRO-ECTHING IN TOP FL	ANGE AREA.					1	G	7	2 	3U				H3EU    					 
1996092600223	19960926	00223	EU  	1996	9	26	96ZZZX4845       	1	19960719	G	6330	10510155	SUPPORT         			BOLKMS	105   	BO105C      	5626005	EU  										TRANSMISSION	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	352TT	2519 	1450 		633	S59				SCHEDULED INSPECTION FOUND TRANSMISSION SUPPORT WITH MECHANICAL DAMAGE BEYOND LIMITS CAUSED BY VIBRO-ETCHING IN TOP FLAN	GE AREA.					1	G	7	2 	3U				H3EU    					 
1996092600224	19960926	00224	EU  	1996	9	26	96ZZZX4846       	1	19960719	G	6330	10510156	SUPPORT         			BOLKMS	105   	BO105C      	5626005	EU  										TRANSMISSION	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	352TT	3368 	1450 		617	S59				INSPECTION FOUND TRANSMISSION SUPPORT WITH MECHANICAL DAMAGE BEYOND LIMITS CAUSED BY VIBRO-ETCHING IN TO FLANGE AREA.						1	G	7	2 	3U				H3EU    					 
1996092600225	19960926	00225	EU  	1996	9	26	96ZZZX4847       	1	19960719	G	7120	10560371	LT BIPOD        			BOLKMS	105   	BO105C      	5626005	EU  										ENGINE MOUNTS	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	352TT				10489	S59				SHOP INSPECTION (MAJOR AIRFRAME), FOUND ENGINE LT BIPOD CRACKED.						1	G	7	2 	3U				H3EU    					 
1996092600226	19960926	00226	SW  	1996	9	26	96ZZZX4848       	1	19960625	G	6210	206010200133	BLADE           			BELL  	206   	206B        	1181511	SW  										MAIN ROTOR	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42AL	2827 			A954	918				DAILY SERVICE CHECK FOUND M/R BLADE CRACKED ABOUT 2.50 INCHES TO ABOUT 3 INCHES RUNNING SPAN-WISE JUST OUTBOARD OF FINGE	RS.					1	G	7	1 	3U				H2SW    					 
1996092600227	19960926	00227	GL  	1996	9	26	96ZZZX4849       	2	19960719	G	7261	23030994	SCAVENGE TUBE   		23035179    	SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GEARBOX	BRACKET BROKEN  	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	702AL	4117 				760243	CAE890588S			UPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY AND SCAVENGE TUBE.  FOUND ALIGNMENT BRACKET ON SCAVENGE BROKEN.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996020200298	19960202	00298	CE  	1996	2	2	96ZZZX485        	1	19960101	G	2820	070009916	FUEL LINE       			CESSNA	182   	182         	2072702	CE  										RT SIDE	CHAFED          	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	3393Y					18254393				FOUND RIGHT SIDE FUEL LINE CHAFED FROM ELEVATOR CABLE.  THE LINE IS BEFORE FUEL SELECTOR AND IF IT LEAKED, WOULD BE IMPO	SSIBLE TO STOP DURING FLIGHT.  DAMAGE OCCURRED DUE TO IMPROPER CABLE ROUTING WHILE REPAIRING EXTENSIVE FIRE WALL DAMAGE.	  SUBMITTER RECOMMENDS CHECKING ALL ASSOCIATED SYSTEMS WHENEVER EXTENSIVE DISASSEMBLY AND REASSEMBLY HAVE BEEN ACCOMPLIS	HED.			1	H	7	1 	3O			NT	3A13    					 
1996092600228	19960926	00228	NE  	1996	9	26	96ZZZX4850       	1	19960725	G	5510	7620205002103	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										STABILIZER	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	709AL	12969				760278				DURING SCHEDULED MAINTENANCE, FOUND STABILIZER INSTALLATION WITH EXCESSIVE CORROSION.						1	G	7	2 	3U				H1NE    					 
1996092600229	19960926	00229	NE  	1996	9	26	96ZZZX4851       	1	19960725	G	5510	7620105001107	DOUBLER         			SKRSKY	S76   	S76A        	8143006	NE  										STABILIZER	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	709AL	12969				760278				DURING SCHEDULED MAINTENANCE, FOUND STABILIZER DOUBLER WITH EXCESSIVE CORROSION.  COMPONENT P/N 7600006003011.						1	G	7	2 	3U				H1NE    					 
1996092600230	19960926	00230	NE  	1996	9	26	96ZZZX4852       	1	19960725	G	5510	7620204001147	LONGERON        			SKRSKY	S76   	S76A        	8143006	NE  										LT STABILIZER	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	709AL	12969				760278				DURING SCHEDULED MAINTENANCE, FOUND LT STABLIZER LONGERON WITH EXCESSIVE CORROSION.						1	G	7	2 	3U				H1NE    					 
1996092600231	19960926	00231	NE  	1996	9	26	96ZZZX4853       	1	19960725	G	5511	762010500118	SPAR RIB        			SKRSKY	S76   	S76A        	8143006	NE  										STABILIZER	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	709AL	12969				760278				DURING SCHEDULED MAINTENANCE, FOUND STABILIZER SPAR RIB WITH EXCESSIVE CORROSION.  COMPONENAT P/N 7600006003011.						1	G	7	2 	3U				H1NE    					 
1996092600232	19960926	00232	NE  	1996	9	26	96ZZZX4854       	1	19960725	G	5511	7620205001109	RIB             			SKRSKY	S76   	S76A        	8143006	NE  										STABILIZER	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	709AL	12969				760278				DURING SCHEDULED MAINTENANCE, FOUND STABILIZER RIB WITH EXCESSIVE CORROSION.  COMPONENT P/N 7600006003011.						1	G	7	2 	3U				H1NE    					 
1996092600233	19960926	00233	NE  	1996	9	26	96ZZZX4855       	1	19960725	G	2520	806131	SEAT BACK ASSY  			SKRSKY	S76   	S76         	8143010	NE  										CABIN	CORRODED        	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	769AL	6131 				760048				DURING ROUTINE MAINTENANCE, FOUND SEAT BACK FRAME CORRODED THROUGH.						1	G	7	2 	3U				H1NE    					 
1996092600234	19960926	00234	EU  	1996	9	26	96ZZZX4856       	1	19960719	G	6330	10510156	SUPPORT         			BOLKMS	105   	BO105C      	5626005	EU  										TRANS AREA	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1818X	4106 	985  		440	S103				A/C TRANSMISSION WAS REMOVED FOR INSPECTION.  AT THIS TIME, BOTH A-FRAME STRUTS WERE REMOVED.  UPON REINSTALLATION, THE 	STRUTS WERE INSPECTED AND PROBLEM WAS FOUND.  PART AND SERIAL NUMBERS WERE ETCHED INTO TOP OF A-FRAME STRUT.  THIS IS CO	NSIDERED MECHANICAL DAMAGE AND IS BEYOND DAMAGE LIMITS SET IN THE BO-105 MM.				1	G	7	2 	3U				H3EU    					 
1996092600235	19960926	00235	SW  	1996	9	26	96ZZZX4857       	1	19960817	G	6330	206033506101	RESTRAINT SPRING			BELL  	206   	206L1       	1182107	SW  										M/R XMSN	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2654	184  			LK1533	45482				RESTRAINT SPRING BEARINGS WORN BEYOND LIMITS.  REPLACED 2 EACH BEARINGS, P/N 206-033-509-003.						1	G	7	1 	3U				H2SW    					 
1996092600236	19960926	00236	SW  	1996	9	26	96ZZZX4858       	1	19960727	G	6230	206010443001	DUPLEX BEARING  			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	FAILED          	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2654	547  			1849D	45482				SWASHPLATE REMOVED DUE TO BEARING ROUGHNESS.  FOUND DUPLEX BEARING BAD.  BEARING PARTS DAMAGE INNER RING.  INNER RING RE	PLACED.  SUBMITTER STATES THE THIRD BEARING FAILURE IN PAST 12 MONTHS WITH LESS THAN 1,000 HOURS TT.					1	G	7	1 	3U				H2SW    					 
1996092600237	19960926	00237	SW  	1996	9	26	96ZZZX4859       	1	19960722	G	6330	206033506101	RESTRAINT SPRING			BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007F	820  			LK3183	45186				RESTRAINT SPRING BEARINGS WORN BEYOND LIMITS.  REPLACED BEARINGS, P/N 206-033-509-003.						1	G	7	1 	3U				H2SW    					 
1996020200299	19960202	00299	CE  	1996	2	2	96ZZZX486        	1	19960105	G	3230	AN425A	BOLT            		08412259    	CESSNA	310   	310         	2074202	CE  										LT MLG BELLCRANK	FAILED          	G		A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	17	8199M	4500 				3100199				UPON LANDING, LEFT MLG COLLAPSED.  AN INSPECTION OF LANDING GEAR REVEALED THE BOLT THAT ATTACHES THE BELLCRANK ASSY TO M	LG HAD FAILED.  CLOSER INSPECTION OF THE BOLT REVEALED THE SHANK HAD CORROSION AND PITTING.  SUBMITTER SUGGESTS TO HAVE 	BOLT REMOVED AT EVERY THIRD ANNUAL AND INSPECTED.				1	L	7	2 	3O			RT	3A10    					 
1996092600238	19960926	00238	EU  	1996	9	26	96ZZZX4860       	1	19960728	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	PAINT PEEL      	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8775	133  			527	S775				THESE TWO BLADES WERE REPAIRED BY EUROCOPTERS ONLY 35.8 HOURS AGO FOR THE SAME PROBLEM.  PAINT PEELING OFF EXCESSIVELY. 	 SUBMITTER SUGGESTION:  USE SUPER KOROPON AS BASE PRIMER.					1	G	7	2 	3U				H3EU    					 
1996092600239	19960926	00239	EU  	1996	9	26	96ZZZX4861       	1	19960728	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	PAINT PEEL      	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8775	133  			528	S775				THESE TWO BLADES WERE REPAIRED BY EUROCOPTERS ONLY 35.8 HOURS AGO FOR THE SAME PROBLEM.  PAINT PEELING OFF EXCESSIVELY. 	 SUBMITTER SUGGESTION:  USE SUPER KOROPON AS BASE PRIMER.					1	G	7	2 	3U				H3EU    					 
1996092600240	19960926	00240	EU  	1996	9	26	96ZZZX4862       	1	19960508	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	PAINT PEEL      	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8776	97   			527	S776				PAINT PEELING OFF IN SHEETS.  SENDING BACK FOR WARRANTY REPAIR.						1	G	7	2 	3U				H3EU    					 
1996092600241	19960926	00241	EU  	1996	9	26	96ZZZX4863       	1	19960508	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	PAINT PEEL      	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8776	97   			528	S776				PAINT PEELING OFF IN SHEETS.  SENDING BACK FOR WARRANTY REPAIR.						1	G	7	2 	3U				H3EU    					 
1996092600252	19960926	00252	EU  	1996	9	26	96ZZZX4867       	1	19960905	G	7931	30600018	SENDER          			SLNSBY	T67   	T67M260     	8323006	EU  										ENGINE OIL	FAILED          	B			UNER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	3064Q	602  				2151				AIRCREWS REPORT ENGINE OIL PRESSURE TOO LOW OR TOO  HIGH DURING GROUND AND FLIGHT OPERATIONS.  ERRONEOUS OIL PRESSURE GA	UGE NEEDLE INDICATIONS HAVE CAUSED EMERGENCY LANDINGS.  THE OIL PRESSURE SENDER/TRANSDUCER IS MANUFACTURED BY VDO IN GER	MANY AND DISTRIBUTED/TESTED BY B. F. GOODRICH AND INSTRUMENT TECH (P/N 3060-0018, SAL P/N 12634096BFG AND 12634041IT). T	HE USAFA CO AND HONDO, TX HAVE REPLACED 210 SENDER UNITS.  THE SENDER IS CONNECTED TO A ROCHESTER INSTRUMENT CLUSTER. TH	E SENDING UNIT AND OIL PRESSSURE GAUGE MAY HAVE AN ELECTRICAL RESISTANCE MISMATCH.  THE CIRCUIT MAY BE UNBALANCED.  IT I	S POSSIBLE A 1050 OHM RESISTOR ADDED TO THE CIRCUIT MAY PROVIDE BETTER LASTING RESULTS.  TWO YEARS AND 50,00 FLYING HO	1	L	7	1 	3O			NT	A73EU   					 
1996092600253	19960926	00253	GL  	1996	9	26	96ZZZX4868       	2	19960910	G	7323	23057869	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	MALFUNCTION     	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NE	05	221GP	863  			BR40733	4309	CAE270674			ENGINE RPM BLEEDS OFF.  UNABLE TO ADJUST, DROOPS IN-FLIGHT.  REPLACED GOVERNOR.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996092600254	19960926	00254	EU  	1996	9	26	96ZZZX4869       	1	19960911	G	6420	109013305101	BEARING         		109013305101	AGUSTA	A109  	A109K2      	0260502	EU  										T/R SWASHPLATE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	911RX	888  				10017				DURING THE PRE-FLIGHT INSPECTION, THE SEAL OF THE DUPLEX BEARING WAS OBSERVED TO BE DETACHED FROM THE BEARING.  DISASSEM	BLY SHOWED A TOTAL LOSS OF LUBRICANT AND SEVERAL BALLS MISSING FROM THE OUTER DUPLEX BEARING.					1	G	7	2 	3U			RT	H7EU    					 
1996092600256	19960926	00256	WP  	1996	9	26	96ZZZX4871       	1	19960822	G	6710	A21810064603	SWITCH          	GUARDIAN    		HUGHES	369   	369E        	4470707	WP  										CYCLIC TRIM	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	503MP	201  				0414E				TRIM SWITCH IS INTERMITTENT.  PILOT REPORTS CYCLIC WAS VERY STIFF IN THE FORE/AFT DIRECTION.  REPLACED SWITCH, STICK FOR	CE IS GONE, WORKS AS IT SHOULD.  THIS SWITCH IS A CHRONIC PROBLEM, TOO LIGHT DUTY FOR THIS APPLICATION.					1	G	7	1 	3U				H3WE    					 
1996092600257	19960926	00257		1996	9	26	96ZZZX4872       	4	19960729	G	2210	391110002	ACTUATOR        																	SPAS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		161  			109					UNIT FAILED AFTER 161.1 HOURS.  SPAS IS INTERMITTENT TO TEST, LIGHT COMES ON AS SOON AS SWITCH IS PUT IN TEST POSITION.																			 
1996092600258	19960926	00258	SW  	1996	9	26	96ZZZX4873       	1	19960713	G	6230	206010336005	LINK ASSY       			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PLAY IN EXCESS OF .025 INCH AT TWO PLACES.  SEE BELL MM L3, FIG 62.21.  AT TEAR DOWN FOUND BEARING AND SPACERS WORN.  TO	TAL TIME LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED.  REPLACED 5 EACH.					1	G	7	1 	3U				H2SW    					 
1996092600259	19960926	00259		1996	9	26	96ZZZX4874       	4	19960809	G	2562	0025004	BATTERY         	MARTECH     	EB2BCD      	CESSNA	182   	182A        	2072704	CE  										ELT	SPLIT           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	3959D				4482	34659				REMOVED BATTERY FOR REPLACEMENT DURING SCHEDULED MAINTENANCE AND FOUND BATTERY PACK HAD SPLIT AND EMITTING ACID.  SPLIT 	WAS ALONG NARROW SIDE, RUNNING APPROXIMATELY 1.50 INCH.  SUSPECT CAUSE APPEARED TO BE POOR EPOXY SURROUNDING BATTERY PAC	K.				1	H	7	1 	3O			NT	3A13    					 
1996092600260	19960926	00260	EU  	1996	9	26	96ZZZX4875       	1	19960821	G	3020	AC1192	LIP HEATER      			STBROS	SD3   	SD360       	8100606	EU  										AIR INTAKE	WIRE CHAFED     	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09										UPON TEAR DOWN OF SHORTS 360 AIRCRAFT FOR CONVERSION TO C-23B+, IT HAS BEEN OBSERVED ON ALL MOD AIRCRAFT THAT WIRING TO 	THE ENGINE INTAKE LIP HEATER IS CHAFED TO BARE WIRE CONDITION AS IT EXITS THE CONDUIT TO THE HEATER IN THE LOWER ENGINE 	COWLS.  ALSO, WIRING AFTER THE CONDUIT IS CHAFING ON THE COWL FLOOR BEFORE IT CONNECTS TO AIR INTAKE TERMINAL BOARDS NR 	1 AND NR 2.  SUSPECT CAUSE:  WIRE HARNESS INADEQUATELY SECURED.  SUBMITTER RECOMMENDS MORE FREQUENT INSPECTION.			2	H	7	2 	4T				A41EU   					 
1996092600261	19960926	00261	EA  	1996	9	26	96ZZZX4876       	2	19960904	G	7230		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RT ENG COMP	FAILED          	H				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	07	200FV					BB299	80637			WHILE IN-FLIGHT, THE RIGHT PROPELLER STOPPED TURNING SUDDENLY.  INITIAL INSPECTION REVEALED A FAILURE OF THE COMPRESSOR 	SECTION OF THE RIGHT ENGINE CAUSING COMPLETE STOPPAGE.  ENGINE WAS REMOVED AND SENT TO PRATT AND WHITNEY, CANADA, FOR EV	ALUATION.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996092600262	19960926	00262	NM  	1996	9	26	96ZZZX4877       	1	19960904	G	2822	1C552	PUMP            	AIRBORNE    		ISRAEL	1125  	1125        		NM  										FUEL BOOST	SCREEN LOOSE    	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	232S	3961 			5AB6	032				REMOVED FUEL BOOST PUMPS FOR 2,000 HOUR JET PUMP INSPECTION.  FOUND INLET SCREEN ON BOOST PUMP COMING APART.  LOOSE INLE	T SCREEN WIRES COULD ENTER INLET OF BOOST PUMP.  IAI, P/N V25W652003-503.  HAVE SEEN THIS PROBLEM ON ANOTHER ASTRA.  OPP	OSITE BOOST PUMP INLET SCREEN IS STARTING TO FALL APART ALSO.				2	L	7	2 	4F			RT	A16NM   					 
1996092600263	19960926	00263	SW  	1996	9	26	96ZZZX4878       	1	19960826	G	3250	7500801	SPACER ASSY     			GULSTM	690TP 	695         	7630518	SW  										STUD	STUD MISSING    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3U	3428 				95041				NOSE WHEEL STEERING CYLINDER ACTUATOR ROD END ATTACHES TO A STUD THAT IS HELD IN PLACE BY A COLLAR ASSEMBLY USED FOR SHI	MMY DAMPENING.  THE STUD WAS FOUND MISSING FROM THE SPACER ASSEMBLY.  SUSPECT CAUSE UNCERTAIN, POSSIBLY FAILURE OF STUD 	ROLL PIN BREAKAGE.  STEERING CYLINDER ROD IS CLEAR OF ANY MECHANICAL LINES, ETC.  DID NOT CAUSE ANY OTHER FAILURES OR BR	EAKAGE.  FAILURE WAS DISCOVERED ON AIRCRAFT POST-FLIGHT INSPECTION.			1	H	7	2 	3T				2A4     					 
1996092600264	19960926	00264	SO  	1996	9	26	96ZZZX4879       	1	19960807	G	3610	DE25479	CLAMP           			GULSTM	G1159 	G1159       	3953505	SO  										BLEED DUCT	FAILED          	D	P			O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	03	420JM					094				WHILE IN-FLIGHT, A VEE JOINT CLAMP FAILED ON THE BLEED AIR DUCT FROM THE LEFT ENGINE PYLON.  THE DUCT SHIFTED, BLEED AIR	 LEAKED INTO THE AFT COMPARTMENT.  UPON EXAMINATION, NOTICED THE EXPANSION LIMITER HAD BROKEN.  WHILE REPLACING VEE CLAM	P, NOTICED THE DUCTING WAS PRE-LOADED AND NEEDED TO BE LOOSENED UP CONSIDERABLY FOR THE DUCT TO LINE UP.				2	L	7	2 	4F			RT	A12EA   					 
1996092600265	19960926	00265	CE  	1996	9	26	96ZZZX4880       	1	19960710	G	4960	2T29941	RELAY           			CESSNA	425   	425         	2076018	CE  										APU CUT OUT	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			WP	15	425BZ					4251040				RELAY CONTROLS THE APU CUT-OUT RELAY TO PREVENT USE OF WINDSHIELD HEAT WITHOUT THE GENERATOR OR APU ON-LINE.  THIS RELAY	 SHORTED INTERNALLY WHICH POSSIBLY SENT A FALSE SIGNAL TO THE GCU WHICH CAUSED THE GENERATORS* TO GO OFF LINE IN-FLIGHT.	  AFTER EXTENSIVE TROUBLESHOOTING WITH CESSNA TECH SUPPORT, COULD NOT EXPLAIN WHY THIS HAPPENED IN-FLIGHT NOR COULD FIND	 ANY OTHER REPEATABLE CAUSE.  ALL OTHER SYSTEMS OPERATE PROPERLY.  *BOTH GENERATORS WENT OFF-LINE AND COULD NOT BE RESET	.		1	L	7	2 	3T			RT	A7CE    					 
1996092600266	19960926	00266	EU  	1996	9	26	96ZZZX4881       	1	19960906	G	3010		LINE            			BAG   	JETSTM	JETSTM3101  	1500215	EU  										DEICE	CORRODED        	B			IUMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	618JX					618				FOUND ALL DEICE LINES FROM TAIL TO DISTRIBUTER VALVE CORRODED FROM INSIDE.  APPROXIMATELY 20 EACH HOLES FOUND.  .25 INCH	 - .020 INCH DIAMETER IN THE TOTAL RUN OF TUBING.					2	L	7	2 	4T			RT	A21EU   					 
1996092600267	19960926	00267	CE  	1996	9	26	96ZZZX4882       	1	19960828	G	2810		ELBOW           			CESSNA	441   	441         	2076020	CE  										LT WING VENT	PLUGGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	832AD	2894 				4410311				INSPECTING LEFT WING FUEL VENT SYSTEM FOR OBSTRUCTION, FOUND MUD NEST IN ELBOW OF LINE, P/N 5700113-28,  ABOUT 2.50 FEET	 IN FROM INLET.  ALSO, FOUND OUTBOARD RIB COLLAPSED.					1	L	7	2 	3T			RT	A28CE   					 
1996092600268	19960926	00268	CE  	1996	9	26	96ZZZX4883       	1	19960828	G	3010	3D235306	FLOW CONTROL VLV			CESSNA	441   	441         	2076020	CE  										RT WING DEICE	PLUGGED         	D		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	832AD	2894 				4410311				WING BOOTS INFLATED AND REMAINED INFLATED UNTIL ENGINE SHUT-DOWN.  THEY WOULD NOT RESET.  REMOVED FLOW CONTROL EJECTOR V	ALVE AND FOUND OVERBOARD PORT PLUGGED WITH MUD AND INSECT EGG SACKS.					1	L	7	2 	3T			RT	A28CE   					 
1996092600269	19960926	00269	CE  	1996	9	26	96ZZZX4884       	1	19960828	G	2810	570011327	LINE            			CESSNA	441   	441         	2076020	CE  										RT WING VENT	PLUGGED         	D		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	07	832AD	2894 				4410311				PILOT REPORTED LOUD BANG IN-FLIGHT AND NOTED RT OUTBOARD WING WAS CAVED IN AND AILERONS WERE VERY HARD TO MOVE.  SAFE LA	NDING WAS MADE.  BOTH TOP AND BOTTOM OF RT OUTBOARD WING PANEL WERE COLLAPSED WITH RIBS COMPRESSED FROM OUTBOARD RIB OF 	FUEL BAY, INBOARD 8.50 FEET, AND FROM FORWARD SPAR TO AFT SPAR.  FOUND A MUD NEST IN VENT LINE 3 FEET INSIDE OF RT VENT 	SYSTEM.			1	L	7	2 	3T			RT	A28CE   					 
1996092600270	19960926	00270	WP  	1996	9	26	96ZZZX4885       	1	19960801	G	7710	96641754G06	PROBE           			DOUG  	DC10  	DC1030      	3023501	WP  										NR 1 ENG PT 5.4	PLUG MISSING    	B			AY54	K				NONE                    				M	W		OVER TEMP                 	INADEQUATE Q C            		IN	INSP/MAINT     	1			EA	35	832LA					46931				NR 1 ENGINE PT 5.4 PROBE WAS FOUND INSTALLED WITHOUT BLANK.  AS EPR INDICATION SYSTEM IS NOT INSTALLED ON THIS AIRCRAFT,	 THE OPEN PORT ALLOWED HPT OUTLET GASSES TO IMPINGE ON THE CORE COWL (TITANIUM).  SLIGHT LOCAL HEAT DISCOLORATION AND SO	OT DEPOSITS FOUND.  IT APPEARS THIS ENGINE WAS CONFIGURED FOR A/C WITH EPR SYSTEM.  (BORESCOPE PLUG IS NORMALLY INSTALLE	D).			2	L	7	3 	4F				A22WE   					 
1996092600271	19960926	00271	CE  	1996	9	26	96ZZZX4886       	1	19960828	G	7830	202000331	SUPPORT FORMER  		2250007     	BEECH 	MU300 	400A        	1155402	CE  										THRUST REV	CRACKED         	B			KI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	85CR	1270 			2380	RK22				IN  PROCESS OF ROUTINE INSPECTION, NOTICED THE STANG FAIRING SUPPORT FORMERS, OUTBOARD SIDE OF EACH ENGINE, WERE CRACKED	 WHERE THEY ATTACH TO STANG.  BEECH SB NR 2674 APPLIES TO THIS SUBJECT, HOWEVER, NOT TO THIS SPECIFIC REVERSER PART NUMB	ER.  RECOMMEND REVISING SB AND REQUIRING MANDATORY INSPECTION NOT TO EXCEED 200-HOUR INTERVALS UNTIL MODIFICATION KIT IS	 INSTALLED.			2	H	7	2 	4F			RT	A16SW   					 
1996020200302	19960202	00302	NE  	1996	2	2	96ZZZX489        	2	19960117	G	7250	34A0062	BOLT            								IAE   	V2500 	V2500A1     		NE  					LPT ROTOR	FAILED          	D				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	05		14279					50XV0014			ENGINE WAS REMOVED FROM SERVICE DUE TO VIBRATION, DISASSEMBLY OF THE ENGINE REVEALED LPT GAS PATH DAMAGE.  INVESTIGATION	 DETERMINED SEVEN OF THIRTY-SIX, 6TH TO 7TH STAGE DISK BOLTS HAD FAILED.  PRELIMINARY ANALYSIS INDICATE THE BOLTS FAILED	 WITH THE CHARACTERISTICS OF A STRESS CORROSION MECHANISM.									4	F			E311NE				 
1996020200305	19960202	00305	NE  	1996	2	2	96ZZZX492        	2	19960105	G	7321	105970	NOZZLE          	HAMSTD      	JFC3123     	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R     	41580	NE  					PUMP	FRACTURED       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	05			8822 		F9341		2082			ENGINE ROLL-BACK IN FLIGHT.  FUEL CONTROL PUMP NOZZLE IS FRACTURED CAUSING SEVERE CONTAMINATION.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996100300413	19961003	00413	CE  	1996	10	3	96ZZZX4924       	1	19960815	G	3230	12802091	DOWNLOCK PIN    		123805149   	CESSNA	182   	R182        	2072734	CE  										NLG ACTUATOR	FAILED          	D		A		K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	01	7362X	4890 				R18200087				BOTH DOWNLOCK PINS BROKE AND KEPT NOSE GEAR FROM LOCKING.  GEAR COLLAPSED DURING TAXI.  CESSNA SEB 95-20 WAS C/W BY INSP	ECTION 80 HOURS PRIOR.  SUBMITTER SUGGES TS BAGGING THE INSPECTIONS AND MODIFYING WITH NEW DESIGN PINS AS SOON AS POSSIB	LE.  THESE INSPECTIONS ARE TO RECUR EACH 200 HOURS.				1	H	7	1 	3O			RT	3A13    					 
1996100300414	19961003	00414	GL  	1996	10	3	96ZZZX4925       	3	19960913	G	6114	D5892C87	HUB             													MCAULY	3AF32C	3AF32C87    	GL  	NR 1 SOCKET	CRACKED         	B		A	ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								795594		DISASSEMBLED MCCAULEY PROPELLER FOR OVERHAUL - C/W AD 95-24-05R1.  AFTER STRIPPING HUB, A CRACK DISCOVERED IN NR 1 BLADE	 SOCKET, 3 THREADS IN, 2 INCHES LONG AT THE 7 O'CLOCK POSITION.  CRACK DISCOVERED USING A VISUAL 10X POWER MICROSCOPE.															5	C	P22EA	 
1996100300415	19961003	00415		1996	10	3	96ZZZX4926       	1	19960816	G	2435	03601015	BEARING         	LUCAS       	230650181   															BRUSH DRIVE END	FAILED          	B			ED2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09			500  							STARTER/GENERATOR DRIVE END BEARING FAILURE.  TWO UNITS HAD BEARING FAIL AND ONE UNIT BEARING COVER DEFECTIVE.																			 
1996100300416	19961003	00416		1996	10	3	96ZZZX4927       	1	19960816	G	2435	03601015	BEARING         	LUCAS       	230650181   															BRUSH DRIVE END	FAILED          	B			ED2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09			500  		3670					STARTER/GENERATOR DRIVE END BEARING FAILURE.  TWO UNITS HAD BEARING FAIL AND ONE UNIT BEARING COVER DEFECTIVE.																			 
1996100300417	19961003	00417		1996	10	3	96ZZZX4928       	1	19960816	G	2435	03601015	BEARING         	LUCAS       	230650181   															DRIVE END	LOST COVER      	B			ED2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09			500  							STARTER/GENERATOR DRIVE END BEARING FAILURE.  TWO UNITS HAD BEARING FAIL AND ONE UNIT BEARING COVER DEFECTIVE.																			 
1996100300418	19961003	00418		1996	10	3	96ZZZX4929       	1	19960909	G	2822	2B664	PUMP            	AIRBORNE    																FUEL BOOST	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					UPTR00139					INSPECTION FOUND PUMP WAS POSSIBLY RUN DRY CAUSING DAMAGE TO ARMATURE.  SHAFT IS ALSO BADLY WORN.																			 
1996100300419	19961003	00419	EA  	1996	10	3	96ZZZX4930       	2	19960909	G	8530	LW11775	PIN PLUG        			PIPER 	PA28  	PA28*       		SO  	LYC   	O360  	IO360C1C    	41514	EA  					ENGINE CYLINDERS	FAILED          	B			PB2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23		450  								CYLINDER REMOVED FROM ENGINE DUE TO ALUMINUM IN OIL SCREEN.  FOUND PIN PLUG SHAVED COMPLETELY OFF ON NR 3 CYLINDER ALLOW	ING PIN TO RUB AGAINST CYLINDER WALL.  THESE TYPES OF PIN PLUGS ARE A LOOSE FIT UNLIKE SUPERIOR AIR PARTS, INC., STYLE A	ND WERE INSTALLED WITH CORRECT LYCOMING PART NUMBER AND FIT.  REMAINING PIN PLUGS SHAVED ALSO.				1	L	7	1 	3O	3	O		2A13    	1E10				 
1996100300420	19961003	00420	GL  	1996	10	3	96ZZZX4931       	3	19960905	G	6114	C4716C98	HUB             			CESSNA	188   	A188        	2073004	CE  						MCAULY	2A34C	D2A34C98    	GL  	BLADE RETAIN	CRACKED         	B			B2PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					783528			783528		UPON CHEMICAL STRIPPING AND VISUAL INSPECTION, A CRACK WAS DISCOVERED IN THE BLADE RETENTION THREADS.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1996100300421	19961003	00421	NE  	1996	10	3	96ZZZX4932       	2	19960911	G	8520	AT90114	CRANKSHAFT      								PWA   	R1340 	R1340AN1    	52016	NE  					AFT CNTRWEIGHT	CRACKED         	B		A	EJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11		1800 	900  		RE56		18171			ENGINE RECEIVED FOR OVERHAUL DUE TO CRACK IN REAR COUNTERWEIGHT.  UPON INSPECTION, FOUND THE REAR COUNTERWEIGHT CRACKED 	IN THE 4-1/2 ORDER FLYWEIGHT LINER AREA OF CRANKSHAFT. THIS SAME CRANKSHAFT WAS FOUND CRACKED IN THE SAME AREA AT THE PR	EVIOUS OVERHAUL, 900 HOURS.  AT THAT TIME, CRANKSHAFT WAS RETURNED TO AIR TRACTOR TO HAVE SNOW ENGINEERING CO. SL NR 134	 C/W.  AD NOTE 96-15-02 DID NOT APPLY TO THIS CRANKSHAFT AS IT ALREADY HAD THE LATE PART NUMBERED COUNTERWEIGHTS INSTALL	ED (AT 90133-1 AND AT 90134-1).							3	R			5E2				 
1996100300422	19961003	00422	EA  	1996	10	3	96ZZZX4933       	2	19960224	G	8520	LW17676	CRANKSHAFT      			BNORM 	BN2   	BN2         	1520202	EU  	LYC   	O540  	O540E4C5    	41532	EA  					FRONT MAIN	CORROSION PITS  	B	P		YECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	XCDUT						L2223640A			ENGINE DISASSEMBLED AT O/H, CRANKSHAFT INSPECTED.  FRONT MAIN ID FND WITH NUMEROUS CORROSION PITS, APPROX 2.0 INCHES AFT	 OF FRONT EDGE OF FLANGE PILOT.  CRANK ASSY LW 17676, SN V721 (CRANK AND BUSHING SUBASSY LW17622) HAS ALWAYS OPERATED WI	TH  CONSTANT-SPEED PROP AND IS NOT INCLUDED BY MDL OR DESIGN IN INSP REQUIREMENTS OF LYC SB 505A.  THIS REPAIR STATION I	NSPECTS ALL CRANKS FOR INTERNAL CORROSION REGARDLESS OF MDLS AND THIS IS 2ND CONSTANT-SPEED PROP CRANK SUBMITTER HAS SEE	N IN PAST MONTH WITH SERIOUS INTERNAL CORROSION.  CRANKSHAFT SUGGESTS ENVIRONMENT AND OPERATION ARE KEY FACTORS IN AFFEC	TING CORROSION AS WELL AS CONSTANT-SPEED/FIXED PITCH APPLICATION.  SUBJECT ACFT OPERATED IN MEXICO AND HAWAII.	1	H	7	2 	3O	3	O		A17EU   	E295				 
1996100300423	19961003	00423	GL  	1996	10	3	96ZZZX4934       	1	19960901	G	7602		CONTROL CABLE   			AMTR  	VAREZE	VARIEZE     	       	GL  										MIXTURE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3LV	627  				1				MIXTURE CABLE HOUSING FAILED AT BRACKET ASSY WHERE CABLE IS SECURED TO THE CARBURETOR.  CABLE COULD PULL LEVER TO 'LEAN'	, BUT COULD NOT PUSH TO 'RICH'.  CABLE ALSO APPEARED TO BE TOO SHORT AS IT ENTERED THE BRACKET AT AN ACUTE ANGLE.  THIS 	PREVENTED THE RETURN SPRING FROM OVERRIDING THE FRICTION OF THE CABLE HOUSING ON THE CABLE.				1	M	7	1 	3O			 	EXPA1M71					 
1996100300424	19961003	00424	CE  	1996	10	3	96ZZZX4935       	1	19960807	G	8011	36E141C	STARTER         	BENDIX      		BEECH 	35    	C35BEECH    	1151508	CE  										ENGINE	FAILED          	B			CKYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	5931C				A113452	D3292				STARTER RECEIVED FROM OVERHAUL REPAIR STATION.  INSTALLED AND MADE ONE START AND UNIT FAILED.  STARTER SPINS, BUT WILL N	OT ENGAGE.  REMOVED, RETURNED TO REPAIR STATION FOR REWORK.  RECOMMEND THAT REPAIR STATION CHECK OUT QUALITY OF REPAIRS/	OVERHAUL.				1	L	7	1 	3O				A777    					 
1996100300425	19961003	00425	CE  	1996	10	3	96ZZZX4936       	1	19960806	G	3230	50452112	FORK BOLT       			CESSNA	402   	402B        	207590P	CE  										NLG	BROKEN          	E	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	106GP	10509				402B1235				DURING PRE-FLIGHT AWAY FROM HOME STATION, PILOT FOUND THE NOSE LANDING GEAR FORK BOLT BROKEN AND PULLED AWAY FROM BELLCR	ANK, PN 0842104-3.  THE AREA WHERE THE BREAK WAS FOUND CANNOT BE INSPECTED WITHOUT REMOVING IT FROM THE BELLCRANK.					1	L	7	2 	3O				A7CE    					 
1996100300426	19961003	00426	CE  	1996	10	3	96ZZZX4937       	1	19960911	G	5280	082210045	BRACKET         			CESSNA	310   	310R        	2074245	CE  										RT INB GEAR DOOR	CRACKED         	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	05	181A	11482				310R0014				WHEN PILOT SELECTED GEAR DOWN, HAD A RIGHT GEAR UNSAFE LIGHT.  CYCLING AND CRANKING GEAR DID NOT HELP.  LANDING WAS MADE	 WITHOUT INCIDENT.  THE SIDE BRACE WAS OVER CENTER, BUT THE DOWNLOCK WAS NOT MADE.  THE CAUSE WAS THE INBOARD GEAR DOOR 	FORWARD HINGE BRACKET WAS CRACKED AND PULLED OFF OF BOTTOM ATTACHING SCREWS ALLOWING DOOR TO PIVOT FORWARD AND HANG-UP O	N LOWER SKIN PREVENTING THE RIGHT GEAR FROM FULLY LOCKING.			1	L	7	2 	3O				3A10    					 
1996100300427	19961003	00427	SO  	1996	10	3	96ZZZX4938       	1	19960813	G	2810		FUEL SYSTEM     			PIPER 	PA38  	PA38112     	7103812	SO  										LT WING	WATER CONTAM    	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CE	05	2466D	3063 				3879A0324				DURING TAKEOFF AND CLIMB, ENGINE SUFFERED A LOSS OF POWER AND STOPPAGE CAUSING AN EMERGENCY LANDING.  ENGINE REGAINED PO	WER AS TOUCH DOWN WAS MADE.  FOUND EVIDENCE OF WATER IN LEFT FUEL TANK.  PILOT STATED TANKS HAD BEEN SAMPLED PRIOR TO TA	KEOFF.  HIGH HUMIDITY HAD BEEN IN THE AREA FOR SEVERAL DAYS.				1	L	7	1 	3O				A18SO   					 
1996100300428	19961003	00428	SO  	1996	10	3	96ZZZX4939       	1	19960829	G	2730	7784402	BRACKET         			PIPER 	PA38  	PA38112     	7103812	SO  										FS 134 ELEV CTL	BROKEN          	B		A	EDER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2321D	10617				3879A0272				FOUND EXCESSIVE PLAY IN ELEVATOR CONTROL SYSTEM.  FOUND BOTH PULLEY BRACKETS BROKE WHERE BOLT GOES THROUGH FIVE PULLEYS.	  (TRIM, RUDDER, ELEVATOR, CABLES) AT FS 134.  SUBMITTER SUGGESTED DYE CHECK FOR CRACKS IMMEDIATELY.					1	L	7	1 	3O				A18SO   					 
1996100300429	19961003	00429	SO  	1996	10	3	96ZZZX4940       	1	19960829	G	2730	7784403	BRACKET         			PIPER 	PA38  	PA38112     	7103812	SO  										FS 134 ELEV CTL	BROKEN          	B		A	EDER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2321D	10617				3879A0272				FOUND EXCESSIVE PLAY IN ELEVATOR CONTROL SYSTEM.  FOUND BOTH PULLEY BRACKETS BROKE WHERE BOLT GOES THROUGH FIVE PULLEYS.	  (TRIM, RUDDER, ELEVATOR, CABLES) AT FS 134.  SUBMITTER SUGGESTED DYE CHECK FOR CRACKS IMMEDIATELY.					1	L	7	1 	3O				A18SO   					 
1996100300430	19961003	00430	SO  	1996	10	3	96ZZZX4941       	1	19960826	G	3246	0313A1	WHEEL           	BFGOODRICH  		PIPER 	J5    	J5A         	7100702	SO  										HUB GROOVE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	26946	2875 				516				DURING ANNUAL INSPECTION, A 2.50 INCH CRACK WAS FOUND IN GROOVE FOR THE SNAP RING WHICH RETAINS THE OUTBOARD WHEEL FLANG	E.  THE WHEEL WAS REPLACED.					1	H	7	1 	3O				A725    					 
1996100300431	19961003	00431		1996	10	3	96ZZZX4942       	4	19960918	G	3416	3431	CASTING         	UNITEDINST  	5934P1      	CESSNA	210   	210L        	2073448	CE  										END SHAKE	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	218SG				1031	21061225				THIS WAS A FACTORY SEALED INSTRUMENT.  THE NORMAL MFG NAME TAG WAS NOT ON THE INST.  A FABRICATED NAME TAG WAS ON THE TO	P SURFACE OF THE INST.  (A DATE OF 3-12-85 WAS STAMPED ON THE CASE).  TWO CRITICAL END SHAKES MEASURED ).0005 INCH AND .	0010 INCH).  SPEC CALLS FOR .0020 INCH TO .0030 INCH END SHAKE.  THIS UNDER MINIMUM END SHAKE CONDITION COULD POSSIBLY C	AUSE A POINTER HANG UP, (ESPECIALLY UNDER COLD OPERATING CONDITIONS).  THIS INSTRUMENT ALSO HAD A CIRCULAR SCRATCH MARK 	ON THE BACK OF THE DISC POINTER WHICH WAS CAUSED BY THE BINDER HEAD SCREWS THAT SECURE THE DIAL OF THE INST.		1	H	7	1 	3O				3A21    					 
1996100300432	19961003	00432		1996	10	3	96ZZZX4943       	4	19960918	G	3416	3431	CASTING         	UNITEDINST  	5934P1      	CESSNA	206   	P206A       	2073308	CE  										END SHAKE	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4654F				R4957	P2060254				THIS ALTIMETER WAS RECEIVED IN A PARTICULARLY HAZARDOUS CONDITOIN.  ALL THREE END SHAKES ON THE CRITICAL ROTATING SHAFTS	 WERE UNDER THE MINIMUM TOLERANCE.  THEY MEASURED .0000 INCH, .0006 INCH, AND .0008 INCH.  THE HAIR SPRING WHEEL SHAFT I	S THE ONE THAT MEASURED .0000 INCH.  THE FACTORY RAN COLD TESTS ON THIS PARTICULAR TYPE ATLIMETER, AND FOUND IF THE END 	SHAKE WAS .0004 INCH OR LESS, THE INSTRUMENTS WOULD HANG UP.  FROM THIS FACTORY TEST INFORMATION, THIS INSTRUMENT WOULD 	DEFINITELY HANG UP UNDER A COLD ENVIRONMENT.		1	H	7	1 	3O				A4CE    					 
1996100300433	19961003	00433	CE  	1996	10	3	96ZZZX4944       	1	19960830	G	3710		HOSE            			CESSNA	182   	TR182       	2072735	CE  										VACUUM	DETERIORATED    	B			LN7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	4952T					R18201802				VACUUM HOSES NEEDED TO BE REMOVED FROM THE AIRCRAFT INSTRUMENT GYROS FOR INSTRUMENT REPLACEMENT.  UPON REMOVAL, THE HOSE	 INNER AND OUTER CASINGS CRUMBLED.  SUGGEST REPLACEMENT OF IMPERIAL EASTMAN HOSE WITH AEROQUIP '306' LOW PRESSURE HOSE. 	 CONDITION IS NOT READILY DETECTABLE EXTERNALLY. THE HOSE CAN BE IDENTIFIED BY A RED INNERTUBE COVERED WITH FABRIC AND A	 BLACK OUTER CASING.			1	H	7	1 	3O				3A13    					 
1996100300435	19961003	00435	SO  	1996	10	3	96ZZZX4946       	1	19960828	G	2820	492052	BUSHING         	SCOTT       	4600        	PIPER 	PA23  	PA23250     	7102308	SO  										CROSSFEED VALVE	CRACKED         	D	S			K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	25	40510	5214 				277405241				CROSSFEED VALVE FITTING HAD NOT BEEN DISTURBED FOR AT LEAST 6 YEARS PRIOR TO A SUDDEN FAILURE WITH A BAD FUEL LEAK (ONTO	 STROBE POWER SUPPLY) DURING BOOST PUMP USE DURING LANDING.  COULD NOT OBTAIN REPLACEMENT FITTING FROM PIPER, HAD TO REP	LACE ENTIRE CROSSFEED VALVE.				1	L	7	2 	3O				1A10    					 
1996100300436	19961003	00436	CE  	1996	10	3	96ZZZX4947       	1	19960903	G	5540	043100127	RUDDER ASSY     			CESSNA	150   	150         	2071802	CE  										RUDDER SPAR	ATTACH CRACKED  	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	5802E	1784 				17302				BOTTOM RUDDER SPAR ATTACHMENT TO RUDDER HORN HAS SMALL HAIR LINE CRACK DUE TO IMPROPER FIT AT SPAR AND RIB ASSEMBLY AT R	IVETS.					1	H	7	1 	3O			NT	3A19    					 
1996100300437	19961003	00437	CE  	1996	10	3	96ZZZX4948       	1	19960903	G	5540	043100117	RUDDER ASSY     			CESSNA	150   	150         	2071802	CE  										RUDDER HORN	ATTACH CRACKED  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	5802E	1784 				17302				BOTTOM RUDDER SPAR ATTACHMENT TO RUDDER HORN HAS SMALL HAIR LINE CRACK DUE TO IMPROPER FIT AT SPAR AND RIB ASSEMBLY AT R	IVETS.					1	H	7	1 	3O			NT	3A19    					 
1996100300438	19961003	00438	EA  	1996	10	3	96ZZZX4949       	2	19960806	G	8530	75413	PISTON          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CYLINDERS	WRONG PART      	B			PB2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	52219	250  				17274443	L1227539A			CUSTOMER COMPLAINED OF LOW STATIC RPM AND SLUGGISH PERFORMANACE OF AIRCRAFT.  THIS CORRESPONDED WITH APPROXIMATE TIME OF	 A TOP OVERHAUL.  PROPELLER AND TACHOMETER WERE CHECKED AND WITHIN SPECIFICATIONS.  LOG BOOK ENTRIES STATING WORK DONE W	AS VERY VAGUE AND NO PARTS LIST PROVIDED.  ONE CYLINDER WAS REMOVED TO EXAMINE INTERNAL ENGINE CONDITION AND PARTS INSTA	LLED.  LOW COMPRESSION (150 HP) PISTON P/N LW75413 WERE INSTALLED INSTEAD OF HIGH COMPRESSION (160 HP) PISTON PN 75089.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996100300439	19961003	00439	CE  	1996	10	3	96ZZZX4950       	1	19960610	G	5720	0823400109	BULKHEAD        			CESSNA	402   	402B        	207590P	CE  										TIP TANK MOUNT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	6387X	3450 				402B1350				DURING SCHEDULED INSPECTION, BULKHEAD WAS FOUND CRACKED AND BUCKLED AT UPPER INBD ATTACHMENT TO FUEL TANK.  INITIAL CRAC	K APPEARS TO HAVE STARTED AT RIVET HOLE ON FLANGE ATTACHING TANK SKIN TO BULKHEAD.  THIS RIVET HOLE HAD INSUFFICIENT EDG	E DISTANCE.  CRACK PROGRESSED TO NUTPLATE FOR BONDING STRAP ATTACHMENT AND BEYOND.  THE WEAKNESS CAUSED TWO MORE CRACKS 	AT UPPER ATTACHMENT OF BULKHEAD TO TANK & SUBSEQUENT BUCKLING.  THE AFT TIP TANK ATTACHMENT HAD LOST 50 PERCENT OF ITS I	NTEGRITY AND WAS IN DANGER OF FAILURE.  BULKHEAD WAS REPLACED.		1	L	7	2 	3O				A7CE    					 
1996100300440	19961003	00440	NM  	1996	10	3	96ZZZX4951       	1	19960819	G	2820	50520	LINE            			UNIVAR	415   	A2ALON      	0540102	NM  										TANK DRAIN	CORRODED        	H		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	09	6567Q	2785 				A67				FUEL SMELL IN CABIN.  ALUMINUM TUBING FOR FUSELAGE TANK DRAIN LINE IN CONTACT WITH FRESH AIR LINE HOSE.  CORROSIVE ACTIO	N BETWEEN LINE AND HOSE ALLOWED FUEL TO LEAK FROM DRAIN LINE.					1	L	7	1 	3O				A787    					 
1996100300441	19961003	00441	CE  	1996	10	3	96ZZZX4952       	1	19960810	G	5543	3566004323	HORN            			BEECH 	35    	S35         	1151532	CE  										LT RUD TRIM TAB	BROKEN          	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			SW	99	6851Q	3485 				D7500				SHORTLY AFTER TAKEOFF, PLANE STARTED TO SHUDDER VIOLENTLY.  PILOT THOUGHT PROPELLER TIP BROKE.  AN IMMEDIATE EMRGENCY LA	NDING WAS MADE ON AN INTERSECTING RUNWAY.  UPON INSPECTION, LEFT TRIM TAB HORN FOUND BROKEN AND TRIM WIRE LOOSE PART BRO	KE MIDWAY BETWEEN RVET AND BOLT HOLE.				1	L	7	1 	3O				3A15    					 
1996100300442	19961003	00442	SO  	1996	10	3	96ZZZX4953       	2	19960610	G	8540	643259AD	ADAPTER         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520D   	17032	SO  					STARTER DRIVE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	65AE		857  			421B0953	219417R			DURING SCHEDULED OIL CHANGE, A LARGE QUANTITY OF FERROUS PARTICLES WERE FOUND IN OIL FILTER AND ON DRAIN PLUG.  INVESTIG	ATION REVEALED BEARING FAILURE OF STARTER DRIVE ADAPTER.  FORWARD PILOT BEARING WAS COMPLETELY GONE AND CASE BORE DAMAGE	D.  AFT BEARING SUPPORTING COUNTERWEIGHT WAS WORN AND SLOPPY.  COMPLETE ENGINE SENT FOR REPAIR.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996100300443	19961003	00443	EA  	1996	10	3	96ZZZX4954       	2	19960619	G	7414	K3822	DISTRIBUTOR BLK 	SLICK       	4250        	BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					RT MAGNETO	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	66343		1188 		4040022	M2206	L12681936A			DISASSEMBLED RT MAGNETO.  FOUND EXCESSIVE CARBON RESIDUE IN COIL AREA.  FURTHER INVESTIGATION REVEALED THE ROTOR ARM ON 	GEAR ASSY HAD BECOME LOOSE ALLOWING APPROXIMATELY 30 DEGREE MOVEMENT SIDE TO SIDE.  SUBMITTER RECOMMENDS 500-HOUR INSPEC	TION OF BLOCK AND GEAR ASSY IN FAA SAFETY RECOMMENDATION.				1	L	7	1 	3O	3	O		A1CE    	E286				 
1996100300444	19961003	00444	CE  	1996	10	3	96ZZZX4955       	1	19960831	G	3246	D302529	HUB             			CESSNA	172   	172M        	2072418	CE  										WHEEL	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	6814H	2734 				17265594				INSPECTION FOUND HUB CRACKED 2 PLACES.						1	H	7	1 	3O			NT	3A12    					 
1996100300445	19961003	00445	SO  	1996	10	3	96ZZZX4956       	1	19960809	G	5540	54030987	HINGE           			AYRES 	S2    	S2RNORMAL   	7630202	SO  										RUDDER TOP	FAILED          	G	P			A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			EA	23	5521X	857  				1721R				THE TOP HALF OF THE RUDDER SEPARATED AND DEPARTED ACFT LANDING ON NEW YORK THRUWAY.  UNEVENTFUL LANDING MADE.  INVESTIGA	TION FOUND THE TOP RUDDER HINGE ('NEW' TYPE TRIPLE DESIGN) FAILED FIRST FOLLOWED BY STRUCTURAL OVERLOAD OF RUDDER TUBULA	R SPAR, AND SUBSEQUENT RUDDER SEPARATION APPROXIMATELY 6 INCHES BELOW TOP HINGE.  'NEW' TYPE TRIPLE HINGE INSTALLED PER 	AD 79-10-10 ON 6-15-91. TRIPLE HINGE TT:  857 HOURS.  TOTAL ACFT TIME:  5,420.7 HOURS.			1	L	7	1 	3R			NC	A3SW    					 
1996100300447	19961003	00447	SO  	1996	10	3	96ZZZX4958       	2	19960705	G	8520	631716	CRANKSHAFT      			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520H    	17040	SO  					PROPELLER	FLANGE FAILED   	B			MW2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	7398M					21062018	506302			PROPELLER AND CRANKSHAFT PROPELLER FLANGE SEPARATED FROM ENGINE.						1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996100300669	19961003	00669	GL  	1996	10	3	96ZZZX4959       	3	19960819	G	6110	AN6H34A	BOLT            			UNIVAR	415   	A2ALON      	0540102	NM  						MCAULY	1A105	1A105SCM    	GL  	PROPELLER	FAILED          	H		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	6567Q	2785 				A67				WHEN BOLT WAS REINSTALLED AND PROPELLER TORQUE APPLIED, THE BOLT BROKE.  FURTHER INSPECTION OF THE BOLT REVEALED A MANUF	ACTURER'S DEFECT.  THE BOLT CHANGES FROM COARSE THREAD TO FINE THREAD.  THERE ARE NO LOG BOOK ENTRIES SHOWING THE BOLT E	VER BEING CHANGED OUT.  THE CHANGE OVER FROM COARSE TO FINE THREAD ALSO NARROWS THE DIAMETER OF THE BOLT.				1	L	7	1 	3O				A787    		5	N	P918	 
1996100300670	19961003	00670	CE  	1996	10	3	96ZZZX4960       	1	19960705	G	5753	05239018	SUPPORT ASSY    		05239011    	CESSNA	172   	172A        	2072404	CE  										RT FLAP ASSY	EXCESS WEAR     	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7558T	4415 				47158				DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED.  INSTALLED FLAP SUPPORT	 KIT SK180-44.  NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS.  SUBMITTER RECOMMENDS THIS SB BECOME AN AD.					1	H	7	1 	3O				3A12    					 
1996100300671	19961003	00671	CE  	1996	10	3	96ZZZX4961       	1	19960705	G	5753	05239019	SUPPORT ASSY    		0523901     	CESSNA	172   	172A        	2072404	CE  										LT FLAP ASSY	EXCESS WEAR     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7558T	4415 				47158				DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED.  INSTALLED FLAP SUPPORT	 KIT SK 180-44.  NEW SUPPORTS ARE HEAVIER AND ARE FLANGED FOR STIFFNESS.  SUBMITTER RECOMMENDS THIS SB BECOME AN AD.					1	H	7	1 	3O				3A12    					 
1996100300672	19961003	00672	CE  	1996	10	3	96ZZZX4962       	1	19960705	G	5753	05239019	SUPPORT ASSY    		05239011    	CESSNA	172   	172A        	2072404	CE  										RT FLAP ASSY	EXCESS WEAR     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7558T	4415 				47158				DURING INSPECTION OF FLAPS PER CESSNA SEB 95-3, FOUND ALL FLAP SUPPORTS HEAVILY WORN AND SCORED.  INSTALLED FLAP SUPPORT	 KIT SK 180-44.  NEW SUPPORTS ARE HEAVIER AND FLANGED FOR STIFFNESS.  SUBMITTER RECOMMENDS THIS SB BECOME AN AD.					1	H	7	1 	3O				3A12    					 
1996100300673	19961003	00673	CE  	1996	10	3	96ZZZX4963       	1	19960903	G	5511	043200117	SPAR            			CESSNA	150   	150         	2071802	CE  										HORIZ STAB	CRACKED         	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7734E	5817 				17534				CRACK FOUND IN LT FRONT SPAR OF HORIZONTAL STABILIZER JUST INBOARD OF LT ATTACH RIB.  CRACK APPEARED TO STOP UNDER SIDE 	AT FUSELAGE CONTACT POINT 2 INCHES FROM FRONT SPAR.  SUSPECT CAUSE WAS WEAR INTO STABILIZER SKIN FROM FUSELAGE SKIN EDGE	 CONTACT.  FUSELAGE SKIN RELIEVED TO PREVENT CONTACT.  SEE FIGURE 8, CESSNA IPC MODEL 150.				1	H	7	1 	3O			NT	3A19    					 
1996100300674	19961003	00674	CE  	1996	10	3	96ZZZX4964       	1	19960903	G	5512	043200146	SKIN            			CESSNA	150   	150         	2071802	CE  										HORIZ STAB	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7734E	5817 				17534				CRACK FOUND IN LT FRONT SPAR OF HORIZONTAL STABILIZER JUST INBOARD OF LT ATTACH RIB.  CRACK APPEARED TO STOP UNDER SIDE 	AT FUSELAGE CONTACT POINT 2 INCHES FROM FRONT SPAR.  SUSPECT CAUSE WAS WEAR INTO STABILIZER SKIN FROM FUSELAGE SKIN EDGE	 CONTACT.  FUSELAGE SKIN RELIEVED TO PREVENT CONTACT.  SEE FIGURE 8, CESSNA IPC MODEL 150.				1	H	7	1 	3O			NT	3A19    					 
1996100300675	19961003	00675	SO  	1996	10	3	96ZZZX4965       	1	19960906	G	3246		HORN            		2400        	MAULE 	M7    	M7235       	5460170	SO  										WATER RUDDER	ATTACH FAILED   	D	S			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	77627	876  			1155	4104C				THIS PART IS THE EXTEND/RETRACT HORN ON THE WATER RUDDER OF CAPRE, INC., STRAIGHT FLOATS, MODEL 2400, SN'S 1155, 1156, I	NSTALLED ON THIS MAULE.  THE SPRING ATTACH POINT FAILED AS A RESULT OF MATERIAL LOSS DUE TO RUST/CORROSION.  SUBMITTER W	OULD SUGGEST MORE MATERIAL IN THE PART, GREATER HOLE TO EDGE DISTANCE.  THE AIRCRAFT HAD SEEN SALT WATER SERVICE, BUT IS	 CURRENTLY IN A FRESH WATER LAKE.			1	H	7	1 	3O			NC	3A23    					 
1996100300676	19961003	00676	SO  	1996	10	3	96ZZZX4966       	1	19960706	G	2410	9907200	PULLEY          			PIPER 	PA32  	PA32R301    	7103218	SO  										ALTERNATOR BELT	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			SO	03		1334 								IDLER PULLEY FAILED CAUSING ELECTRICAL FAILURE.						1	L	7	1 	3O				A3SO    					 
1996100300677	19961003	00677		1996	10	3	96ZZZX4967       	1	19960910	G	2437	3E13898	AMMETER         	BFGOODRICH  																PROP DEICE	MISMARKED       	B			APCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01					5260713					AMMETER FOR PROPELLER DEICE SYSTEM, PIPER PN 548-084, APPEARS MIS-MARKED.  OLD UNIT GREEN ARC IS FROM 20-24 AMPS.  NEW U	NIT MARKED 17-24 AMPS.  NORMAL DRAW ON SYSTEM IS 17-18 AMPS.  OLD METER SHOWS 17 AMPS, BUT THAT IS BELOW GREEN ARC, WHIC	H CAUSES PILOTS TO SQUAWK SYSTEM, EVEN THOUGH IT WORKS PROPERLY.																	 
1996100300678	19961003	00678	CE  	1996	10	3	96ZZZX4968       	1	19960912	G	7160	12507024	AIR BOX         	CESSNA      		CESSNA	207   	207         	2073602	CE  										CARB INLET	DOOR LOOSE      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01										INSPECTION OF AIR BOX FOUND ALTERNATE AIR DOOR LOOSE ON SHAFT WITH NUTS AND SCREWS TIGHT, AND AT OTHER END OF DOOR, DOES	 NOT SEAL ALLOWING UNFILTERED AIR INJESTED.  CONFIRMED ALTERNATE AIR DOOR SHOULD BE TIGHT ON SHAFT, WITH CESSNA TECH SER	VICES.  SUSPECT HOLES IN SHAFT FOR DOOR ELONGATED TO FIT SCREWS WHICH REDUCES NEEDED MATERIAL ON THE SHAFT.  IF SHAFT BR	EAKS, PIECES OF MATERIAL WILL BE INJESTED CAUSING A LACK OF POWER OR LOSS OF POWER.			1	H	7	1 	3O				A16CE   					 
1996100300679	19961003	00679	SO  	1996	10	3	96ZZZX4969       	1	19960822	G	5320	86444802	SPAR            		86444800    	PIPER 	PA44  	PA44180     	7104402	SO  										NOSE CONE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2153B	5900 				447995099				DURING 100-HOUR INSPECTION, BOTH SPARS WERE DETERMINED TO HAVE CRACKS IN THE 'S' ANGLE REINFORCEMENT AT LOWER AFT BOLT H	OLE FOR DRAG LINK MOUNTING BRACKET.  CRACKS RAN LENTGHWISE AND EXTENDED PAST BOLT HOLE IN BOTH DIRECTIONS APPROXIMATELY 	ONE INCH.  THIS IS THE SECOND SEMINOLE FOUND WITH THIS ON, AND IT IS A VERY DIFFICULT AREA TO ACCESS AND INSPECT.				1	L	7	2 	3O				A19S0   					 
1996020200310	19960202	00310	SO  	1996	2	2	96ZZZX497        	1	19960118	G	3246	GYS187C35	BOLT            			GULSTM	G1159 	G1159       	3953505	SO  										WHEEL HALF	BROKEN          	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	26WP					24				AFTER WHEEL CHANGE WHEN REMOVING NUTS FROM WHEEL HALF RETAINER BOLTS, 1 BOLT WAS FOUND BROKEN.  WAS STILL IN BOLT HOLE, 	BUT BECAME 2 PIECES WHEN PUTTING WRENCH ON NUT TO REMOVE.  THIS BOLT HAD 281.5 HOURS AND 228 LANDINGS SINCE LAST MAGNAFL	UXED.  INSPECTION AND ESTIMATED TOTAL TIME OF 840 HOURS AND 660 LANDINGS.				2	L	7	2 	4F			RT	A12EA   					 
1996100300681	19961003	00681	WP  	1996	10	3	96ZZZX4971       	2	19960906	G	7230	3101375	BEARING         			MTSBSI	MU2   	MU2B20      	5780407	SW  	GARRTT	TPE331	TPE3311     	01514	WP  					COMPRESSOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	89CR	1246 				233	34008			89CR FAILURE.  ENGINE S/N 34008.  THE DATE OF THE FAILURE WAS 6-28-96.  THE ENGINE TOTAL TIME SINCE OVERHAUL WAS 2,603.5	 HOURS AND THE AIRCRAFT TOTAL TIME WAS 5,554.1 HOURS.  THE TOTAL CYCLES SINCE OVERHAUL ON THE ENGINE WERE 3,315.1 HOURS.	  TORE THE ENGINE DOWN AND DISCOVERED THE COMPRESSOR BEARING HAD FAILED.  COMPRESSOR BEARING HAD 246.5 HOURS SINCE NEW W	HEN IT WAS INSTALLED ON THIS ENGINE AT TOTAL TIME SINCE OVERHAUL 1,604.4 HOURS ON 8-24-94.  THE COMPRESSOR BEARING HAD1,	245.6 HOURS IN IT AT THE TIME OF THE FAILURE.		1	H	7	2 	3T	3	T		A2PC    	E3WE				 
1996100300683	19961003	00683		1996	10	3	96ZZZX4973       	1	19960913	G	2822	2B664	PUMP            	AIRBORNE    																FUEL BOOST	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					6E415					INSPECTION FOUND ARMATURE SHAFT DAMAGE BY SPACERS WEARING A GROOVE IN SHAFT.																			 
1996100300684	19961003	00684		1996	10	3	96ZZZX4974       	1	19960913	G	2822	2B729	PUMP            	AIRBORNE    																FUEL BOOST	SHAFT WORN      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					7E1240					INSPECTION FOUND HIGH WEAR ON ARMATURE SHAFT.  PUMP MAY HAVE BEEN RUN DRY.																			 
1996100300685	19961003	00685		1996	10	3	96ZZZX4975       	1	19960913	G	2822	2B633	PUMP            	AIRBORNE    																FUEL BOOST	DAMAGE          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					8W132					INSPECTION FOUND ARMATURE SHAFT SHOWS CONSIDERABLE AMOUNT OF DAMAGE.																			 
1996100300686	19961003	00686		1996	10	3	96ZZZX4976       	1	19960913	G	2822	2B729	PUMP            	AIRBORNE    																FUEL BOOST	SHAFT DAMAGE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					2J116					INSPECTION FOUND PUMP MAY HAVE BEEN RUN DRY.  DAMAGE TO ARMATRUE SHAFT RESULTED.																			 
1996100300687	19961003	00687		1996	10	3	96ZZZX4977       	1	19960913	G	2822	2B664	PUMP            	AIRBORNE    																FUEL BOOST	SHAFT DAMAGE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					7AC53					INSPECTION FOUND DAMAGE TO THE PUMP ARMATURE SHAFT.  A GROOVE WORN BY SPACERS.																			 
1996100300688	19961003	00688		1996	10	3	96ZZZX4978       	1	19960913	G	2822	2B664	PUMP            	AIRBORNE    																FUEL BOOST	SHAFT WORN      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					6E415					INSPECTION FOUND ARMATURE SHAFT BADLY WORN.  PUMP MAY HAVE BEEN RUN DRY.																			 
1996100300689	19961003	00689	EU  	1996	10	3	96ZZZX4979       	1	19960919	G	7110	5711012278	COWL            		5711012002  	PILATS	PC12  	PC12        	7090550	EU  										DEICE LIP	LOOSE RIVETS    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	124BW	207  				124				OWNER REQUESTED THAT LOOSE RIVETS IN COWLING ASSEMBLY BE ADDRESSED AND FIXED DURING THE ANNUAL INSPECTION.  INVESTIGATIO	N REVEALED THE RIVETS HAD BEEN INSUFFICIENTLY DRIVEN AT TIME OF MANUFACTURE.					1	L	7	1 	3T			RT	A78EU   					 
1996020200311	19960202	00311	CE  	1996	2	2	96ZZZX498        	1	19960109	G	2810		FUEL CELL       			CESSNA	650   	650         	2076802	CE  										WINGS	CONTAMINATED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	9KL					6500068				WHILE PERFORMING A PHASE 5 INSPECTION WHERE ALL THE FUEL PANELS ARE OPENED UP, THERE WERE APPROXIMATELY 8 FUEL IDENTIFIC	ATION LABELS LOCATED LOOSELY INSIDE WING.  IN THE SUMP AREA THERE WERE 2 LABELS STUCK IN A FLAPPER VALVE.  THE LABELS AR	E APPROXIMATELY 1 INCH BY 6 INCHES.				2	L	7	2 	4F				A9NM    					 
1996100300690	19961003	00690	EU  	1996	10	3	96ZZZX4980       	1	19960919	G	3020	5302412082	DEICE LIP       		5711012278  	PILATS	PC12  	PC12        	7090550	EU  										COWL FWD	WELD CRACKED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	124BW	207  				124				UPON INVESTIGATION OF A LOOSE RIVET, AN EXHAUST GAS STREAK WAS NOTED ON THE INNER DEICE LIP.  FURTHER DISASSEMBLY REVEAL	ED A CRACKED WELDED JOINT.  SUBMITTER STATED CLOSE INSPECTION OF THE PART IS RECOMMENDED AT EACH SCHEDULED INSPECTION.					1	L	7	1 	3T			RT	A78EU   					 
1996100300691	19961003	00691	SO  	1996	10	3	96ZZZX4981       	1	19960820	G	3250	9539400	CHANNEL         			PIPER 	PA34  	PA34200     	7103405	SO  										NLG STEERING	BOLT BROKEN     	D		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	15445					347350065				NOSE GEAR DID NOT FULLY EXTEND.  AIRCRAFT LANDED, DAMAGING NOSE.  THE FORWARD BOLT (AN4-7A) WAS FOUND BROKEN, AFT BOLT (	AN4-7A) WAS BENT.  THESE BOLTS ATTACH THE STEERING CHANNEL.  THE FORWARD BOLT BROKE ALLOWING THE STEERING CHANNEL TO TUR	N APPROXIMATELY 90 DEGREES AND PREVENTING THE NOSE GEAR TO GO FULL DOWN AND LOCK.  AIRCRAFT TOTAL TIME:  7,051.2 HOURS.				1	L	7	2 	3O				A7SO    					 
1996100300692	19961003	00692	CE  	1996	10	3	96ZZZX4982       	1	19960917	G	2810	50260141	GASKET          			CESSNA	421   	421B        	2076014	CE  										AUXILIARY FUEL	CRACKED         	B			QY5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	1950G	10   				421B0849				AUXILIARY TANK GASKET REPLACED AT FUEL TANK CHANGE.  RADIAL CRACKS DEVELOPED CAUSING FUEL LEAK.  GASKET REPLACED WITH NE	W.  NEW GASKET FAILED IN SAME MANNER.  CRACKS STARTED AT ALL SCREW HOLES IN GASKETS.  REPLACEMENT GASKETS WERE WHAT APPE	ARED TO BE NEOPRENE.  ORIGINAL GASKET WAS CORK.				1	L	7	2 	3O				A7CE    					 
1996100300693	19961003	00693	CE  	1996	10	3	96ZZZX4983       	1	19960814	G	5520		HINGE           			BEECH 	58    	58          	1152740	CE  										ELEV LT INBD	BUSHING WORN    	D		A		O				OTHER                   				F	E		FLT CONT AFFECTED         	VIBRATION/BUFFET          		IN	INSP/MAINT     	1			WP	01	23704	3487 				TH900				DURING AN ANNUAL INSPECTION, THE LT INBD ELEVATOR HINGE BUSHING WAS FOUND TO HAVE ITS INNER RACE WORN TO THE POINT THAT 	IT ALLOWED THE ELEVATOR ADDITIONAL MOVEMENT PAST THE NORMAL TRAVEL.  BUSHING WAS REPLACED WITH NEW.  WHEN QUESTIONING TH	E PILOT ABOUT THE AIRCRAFT'S FLIGHT CHARACTERISTICS, IT WAS INDICATED THE EMPENNAGE WOULD SHUDDER ON LANDINGS.  THE SHUD	DER CEASED AFTER THE REPLACEMENT OF THE BUSHING.			1	L	7	2 	3O				3A16    					 
1996100300694	19961003	00694	CE  	1996	10	3	96ZZZX4984       	1	19960906	G	2820	070009924	LINE            			CESSNA	182   	182G        	2072716	CE  										DOOR POST FWD	CHAFING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	2444R	5076 				18255544				INSPECTION FOUND THE PINS ON THE JUMP DOOR THAT EXTEND INTO THE DOOR POSTS WERE HITTING THE FUEL LINES THAT RUN PARALLEL	 WITH THE DOOR POST, BOTH FORWARD AND AFT, ON THE RIGHT SIDE.  SPLICED IN A NEW SECTION OF TUBING AND ROUTED THE LINES O	UT AND AROUND THE PINS.  USED UNIONS AND TUBING NUTS TO SPLICE IN THE NEW TUBING.				1	H	7	1 	3O			NT	3A13    					 
1996100300695	19961003	00695	CE  	1996	10	3	96ZZZX4985       	1	19960906	G	2820	070009919	LINE            			CESSNA	182   	182G        	2072716	CE  										DOOR POST AFT	CHAFING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	2444R	5076 				18255544				INSPECTION FOUND THE PINS ON THE JUMP DOOR THAT EXTEND INTO THE DOOR POSTS WERE HITTING THE FUEL LINES THAT RUN PARALLEL	 WITH THE DOOR POST, BOTH FORWARD AND AFT, ON THE RIGHT SIDE.  SPLICED IN A NEW SECTION OF TUBING AND ROUTED THE LINES O	UT AND AROUND THE PINS.  USED UNIONS AND TUBING NUTS TO SPLICE IN THE NEW TUBING.				1	H	7	1 	3O			NT	3A13    					 
1996100300696	19961003	00696	CE  	1996	10	3	96ZZZX4986       	1	19960919	G	5320	121141426	TUNNEL ASSY     			CESSNA	210   	210J        	2073439	CE  										OTBD LT SIDE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	3356S	1293 				21059156				DURING ANNUAL INSPECTION AND GEAR SADDLE INSPECTION PER AD 76-14-7R2, THE OUTBOARD LT TUNNEL ASSEMBLY WAS FOUND CRACKED 	OUT FROM AN INSPECTION HOLE TO THE OUTER SKIN.  THE CRACK STARTED JUST AFT OF A FACTORY INSTALLED DOUBLER PLATE.  THE GE	AR SADDLE ON THIS SIDE WAS ALSO FOUND TO HAVE A CRACK, REPLACEMENT OF BOTH PANEL AND SADDLE WERE ACCOMPLISHED.  SUBMITTE	R STATED CAREFUL INSPECTION AT ANNUAL OR 100-HOUR INTERVALS WOULD DETECT THIS TYPE CRACK BELIEVED TO BE CAUSED BY A HARD	 L ANDING.  NO DAMAGE NOTED ON RT SIDE.  EXTENSION OF THE DOUBLER WOULD POSSIBLY ELIMINATE THE STRESS CONCENTRATION IN T	HIS AREA.	1	H	7	1 	3O				3A21    					 
1996100300697	19961003	00697	CE  	1996	10	3	96ZZZX4987       	1	19960919	G	3213		SADDLE          			CESSNA	210   	210J        	2073439	CE  										LT GEAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	3356S	1293 				21059156				DURING ANNUAL INSPECTION AND GEAR SADDLE INSPECTION PER AD 76-14-7R2, THE OUTBOARD LT TUNNEL ASSEMBLY WAS FOUND CRACKED 	OUT FROM AN INSPECTION HOLE TO THE OUTER SKIN.  THE CRACK STARTED JUST AFT OF A FACTORY INSTALLED DOUBLER PLATE.  THE GE	AR SADDLE ON THIS SIDE WAS ALSO FOUND TO HAVE A CRACK, REPLACEMENT OF BOTH PANEL AND SADDLE WERE ACCOMPLISHED.  SUBMITTE	R STATED CAREFUL INSPECTION AT ANNUAL OR 100-HOUR INTERVALS WOULD DETECT THIS TYPE CRACK BELIEVED TO BE CAUSED BY A HARD	 L ANDING.  NO DAMAGE NOTED ON RT SIDE.  EXTENSION OF THE DOUBLER WOULD POSSIBLY ELIMINATE THE STRESS CONCENTRATION IN T	HIS AREA.	1	H	7	1 	3O				3A21    					 
1996100300698	19961003	00698	EA  	1996	10	3	96ZZZX4988       	2	19960911	G	7414	ES1068291012	MAGNETO         		D6LN3200    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MOUNT FLANGE	CHAFED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3587P		112  		5032447	318052120	RL263261A			LEFT ENGINE WITH LESS THAN 100 HOURS SINCE OVERHAUL HAD NAGGING SMALL LEAK AT MAGNETO, WAS THOUGHT TO BE IMPROPER INSTAL	LATION, MAG GASKET GETTING DAMAGED.  UPON FURTHER INVESTIGATION, FOUND MOUNTING FLANGE WORN AT SPOT WHERE CLAMP GOES.  O	RDERED NEW BENDIX SHELL PN 10-682001-1, AND FOUND FLANGE TO BE MUCH THICKER.  ALSO, BEFORE MAG WAS REMOVED, IT SHOWED SI	GNS OF BEING LOOSE.  ALSO, FOUND ONE OTHER MAG OF SAME TYPE STARTING TO WEAR AT SAME SPOT PN ES10-382910-12.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996100300699	19961003	00699	EA  	1996	10	3	96ZZZX4989       	2	19960911	G	7414	ES10398291012	MAGNETO         		D6LN3200    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MOUNT FLANGE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3587P		112  		R011355010	318052120	RL263261A			LEFT ENGINE WITH LESS THAN 100 HOURS SINCE OVERHAUL HAD NAGGING SMALL LEAK AT MAGNETO, WAS THOUGHT TO BE IMPROPER INSTAL	LATION, MAG GASKET GETTING DAMAGED.  UPON FURTHER INVESTIGATION, FOUND MOUNTING FLANGE WORN AT SPOT WHERE CLAMP GOES.  O	RDERED NEW BENDIX SHELL PN 10-682001-1, AND FOUND FLANGE TO BE MUCH THICKER.  ALSO, BEFORE MAG WAS REMOVED, IT SHOWED SI	GNS OF BEING LOOSE.  ALSO, FOUND ONE OTHER MAG OF SAME TYPE STARTING TO WEAR AT SAME SPOT PN ES10-382910-12.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996100300700	19961003	00700	CE  	1996	10	3	96ZZZX4990       	1	19960918	G	5510	07321014	BRACKET         			CESSNA	182   	R182        	2072734	CE  										H STAB REINFORC	CRACKED         	B		A	VIB3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	37G	4505 				R18202024				A CRACK WAS FOUND IN A BEND RADIUS OF THE LEFT HAND REAR SPAR ATTACHMENT REINFORCEMENT BRACKET ADJACENT TO THE BEND RADI	US HOLE.  SUBMITTER RECOMMENDS THE MFG TO MAKE LARGER BRACKET EXTENDING PAST THE LIGHTNING HOLE.					1	H	7	1 	3O			RT	3A13    					 
1996100300701	19961003	00701	SO  	1996	10	3	96ZZZX4991       	1	19960910	G	3231		DOOR            			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	OUT OF ADJUST   	B			APCR	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			NM	01	40ST					317405183				RIGHT MAIN GEAR FAILED TO RETRACT FULLY AND FELL OUT OF UP POSITION DUE TO BINDING/MISADJUSTMENT OF OUTER DOOR.						1	L	7	2 	3O				A20SO   					 
1996100300702	19961003	00702	SO  	1996	10	3	96ZZZX4992       	1	19960622	G	3260	565288	HORN            	PAC         		PIPER 	PA28  	PA28R201T   	7102813	SO  										GEAR WARNING	INOPERATIVE     	G				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			GL	25	47230	3092 				28R7703355				DURING LANDING GEAR-UP INCIDENT INVESTIGATION, THE GEAR WARNING HORN WAS FOUND INOPERATIVE.  WARNING LIGHT FUNCTIONED, B	UT NOT HORN.					1	L	7	1 	3O				2A13    					 
1996100300703	19961003	00703	SO  	1996	10	3	96ZZZX4993       	1	19960909	G	3250	AN47A	BOLT            		9539400     	PIPER 	PA34  	PA34200T    	7103406	SO  										STEERING CHANNEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	53BD	2923 				347970114				THE BOLTS ATTACHING THE STEERING CHANNEL WERE REMOVED FOR INSPECTION.  THE FORWARD BOLT WAS FOUND BENT AND CRACKED 75 PE	RCENT OF THE WAY THROUGH, THE AFT BOLT BENT.  INSTALLED 2 EACH NEW 'AN' 4-7A BOLTS AND RETURNED TO SERVICE.  AIRCRAFT TO	TAL TIME:  2,922.8 HOURS.				1	L	7	2 	3O				A7SO    					 
1996101000094	19961010	00094	CE  	1996	10	10	96ZZZX4994       	1	19960814	G	2510	04140071	SEAT ASSY       			CESSNA	150   	150K        	2071822	CE  										PILOT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	5852G	5203 				15071352				DURING A 100-HOUR INSPECTION, FOUND PILOT AND COPILOT SEATS TO HAVE NUMEROUS CRACKS STARTING AT SEAT BACK TO BOTTOM SUPP	ORTS AND AT THE RECLINING MECHANISM SUPPORTS.  ALSO, ON THE COPILOT'S SEAT, FOUND RECLINE ADJUSTER SHAFT WORN OUT.  THIS	 SHAFT ALSO WORE OUT ITS CORRESPONDING SUPPORT BRACKETS.  ALL PARTS REPAIRED IAW CESSNA MM AND AC 43.13.				1	H	7	1 	3O				3A19    					 
1996101000095	19961010	00095	CE  	1996	10	10	96ZZZX4995       	1	19960814	G	2510	0414072	SEAT ASSY       			CESSNA	150   	150K        	2071822	CE  										COPILOT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	5852G	5203 				15071352				DURING A 100-HOUR INSPECTION, FOUND PILOT AND COPILOT SEATS TO HAVE NUMEROUS CRACKS STARTING AT SEAT BACK TO BOTTOM SUPP	ORTS AND AT THE RECLINING MECHANISM SUPPORTS.  ALSO, ON THE COPILOT'S SEAT, FOUND RECLINE ADJUSTER SHAFT WORN OUT.  THIS	 SHAFT ALSO WORE OUT ITS CORRESPONDING SUPPORT BRACKETS.  ALL PARTS REPAIRED IAW CESSNA MM AND AC 43.13.				1	H	7	1 	3O				3A19    					 
1996101000096	19961010	00096	CE  	1996	10	10	96ZZZX4996       	1	19960814	G	2510	04111051	ADJUSTER SHAFT  			CESSNA	150   	150K        	2071822	CE  										COPILOT RECLINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	5852G	5203 				15071352				DURING A 100-HOUR INSPECTION, FOUND PILOT AND COPILOT SEATS TO HAVE NUMEROUS CRACKS STARTING AT SEAT BACK TO BOTTOM SUPP	ORTS AND AT THE RECLINING MECHANISM SUPPORTS.  ALSO, ON THE COPILOT'S SEAT, FOUND RECLINE ADJUSTER SHAFT WORN OUT.  THIS	 SHAFT ALSO WORE OUT ITS CORRESPONDING SUPPORT BRACKETS.  ALL PARTS REPAIRED IAW CESSNA MM AND AC 43.13.				1	H	7	1 	3O				3A19    					 
1996101000097	19961010	00097	CE  	1996	10	10	96ZZZX4997       	1	19960917	G	3246	95301078	WHEEL HALF      			BEECH 	18    	E18S        	1151006	CE  										NO BRAKE SIDE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5867					BA333				CRACK IN WHEEL HALF NO BRAKE SIDE.  FOUND ON PRE-FLIGHT.						1	L	7	2 	3R				A765    					 
1996101000098	19961010	00098	SO  	1996	10	10	96ZZZX4998       	1	19960803	G	8120	4091709001	TURBOCHARGER    	GARRTT      		PIPER 	PA31  	PA31350     	7103110	SO  										BEARING	FAILED          	D				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			WP	01	59826		1936 		VHL0177	317652077				PILOT REPORTS A DROP IN MANIFOLD PRESSURE AFTER TAKEOFF TO 18 INCHES AND THE LEFT ENGINE WAS FEATHERED.  UPON INSPECTION	, THE TURBOCHARGER SHAFT, BEARING/HOUSING HAD FAILED.  NO OIL RESTRICTION IN THE SUPPLY HOSE WAS FOUND.					1	L	7	2 	3O				A20SO   					 
1996101000099	19961010	00099	SO  	1996	10	10	96ZZZX4999       	2	19960911	G	8530	646678	SEAL            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360KB  	17025	SO  					INT VALVE STEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	64TP	129  				3447003	320270			DURING AN ANNUAL INSPECTION, THE ENGINE OIL SUCTION SCREEN WAS FOUND TO CONTAIN A SPRING AND FRAGMENTS OF A RUBBER COMPO	UND.  TELEDYNE CONTINENTAL SB CSB 95-4 PERTAINS TO THIS SUBJECT, BUT IS NOT SUBJECT TO MODELS AFFECTED BY SERIAL NUMBER.	  THE SB WAS C/W ON BOTH ENGINES, AND EACH SEAL WAS FOUND DEFECTIVE IN EACH ENGINE.  SUGGEST REVISING SERIAL NUMBER APPL	ICABILITY OF SB.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996102300004	19961023	00004	SO  	1996	10	23	96ZZZX5000       	2	19960911	G	8530	646678	SEAL            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360KB  	17025	SO  					INT VALVE STEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	64TP	129  				3447003	319279			DURING AN ANNUAL INSPECTION, THE ENGINE OIL SUCTION SCREEN WAS FOUND TO CONTAIN A SPRING AND FRAGMENTS OF A RUBBER COMPO	UND.  TELEDYNE CONTINENTAL SB CSB 95-4 PERTAINS TO THIS SUBJECT, BUT IS NOT SUBJECT TO MODELS AFFECTED BY SERIAL NUMBER.	  THE SB WAS C/W ON BOTH ENGINES, AND EACH SEAL WAS FOUND DEFECTIVE IN EACH ENGINE.  SUGGEST REVISING SERIAL NUMBER APPL	ICABILITY OF SB.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996101000100	19961010	00100	CE  	1996	10	10	96ZZZX5001       	1	19960807	G	3230	504501018	TORQUE TUBE     			CESSNA	310   	310Q        	2074242	CE  										RT MLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	7743Q	3470 				310Q0243				DURING 100-HOUR INSPECTION, FOUND BOTH LT AND RT TORQUE TUBES CRACKED (SMALL CRACKS) AT THE AREA WHERE THE FORK BOLT BOS	S IS WELDED TO THE TUBE.  HAVE SEEN THIS PROBLEM IN THE AIRWORTHINESS ALERTS BEFORE AND PAID CLOSE ATTENTION TO THIS ARE	A.  THE PROBLEM WAS NOT DISCOVERED DURING A PRE-BUY BECAUSE THE AREA WAS NOT CLEANED WELL ENOUGH.  RECOMMEND CLEANING AN	D INSPECTING THIS AREA WELL DURING INSPECTIONS.  ALSO, NEW TORQUE TUBES DASH 32 AND DASH 33 ARE REINFORCED IN THIS AREA.			1	L	7	2 	3O				3A10    					 
1996101000101	19961010	00101	CE  	1996	10	10	96ZZZX5002       	1	19960807	G	3230	504501019	TORQUE TUBE     			CESSNA	310   	310Q        	2074242	CE  										LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	7743Q	3470 				310Q0243				DURING 100-HOUR INSPECTION, FOUND BOTH LT AND RT TORQUE TUBES CRACKED (SMALL CRACKS) AT THE AREA WHERE THE FORK BOLT BOS	S IS WELDED TO THE TUBE.  HAVE SEEN THIS PROBLEM IN THE AIRWORTHINESS ALERTS BEFORE AND PAID CLOSE ATTENTION TO THIS ARE	A.  THE PROBLEM WAS NOT DISCOVERED DURING A PRE-BUY BECAUSE THE AREA WAS NOT CLEANED WELL ENOUGH.  RECOMMEND CLEANING AN	D INSPECTING THIS AREA WELL DURING INSPECTIONS.  ALSO, NEW TORQUE TUBES DASH 32 AND DASH 33 ARE REINFORCED IN THIS AREA.			1	L	7	2 	3O				3A10    					 
1996101000102	19961010	00102	SO  	1996	10	10	96ZZZX5003       	2	19960916	G	8550	CH48109	FILTER          			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE OIL	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	782B	84   				TE247	240532R			DURING A ROUTINE OIL CHANGE, EXAMINATION OF THE OIL FILTER REVEALED THE RUBBER GASKET BETWEEN THE FILTER ELEMENT AND THE	 FILTER END HOUSING HAD SHIFTED, APPARENTLY DURING MANUFACTURE, AND COVERED APPROXIMATELY 75 PERCENT OF THE OIL IN HOLE 	AND 100 PERCENT OF TWO OIL OUT HOLES.  PART REMOVED FROM SERVICE.  SUBMITTER STATED STIFFER QA GUIDELINES ARE NEEDED TO 	PREVENT RECURRENCE.			1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996101000103	19961010	00103	CE  	1996	10	10	96ZZZX5004       	1	19960901	G	3211	08221804	SUPPORT         			CESSNA	310   	310Q        	2074242	CE  										MLG	DEFORMED        	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	85DS					310Q0080				DURING INSTALLATION OF LANDING GEAR KIT SK-414, FOUND SUPPORT DEFORMED AND STRUCTURE AT POINT OF ATTACH CRACKED.  SUBMIT	TER URGENTLY RECOMMENDS THIS MODIFICATION BE MADE AN AIRWORTHINESS DIRECTIVE FOR ALL CESSNA 300 AND CESSNA 400 SERIES AI	RCRAFT USING ELECTRIC MECHANICAL LANDING GEAR REGARDLESS OF AIRCRAFT TIME OR AGE.				1	L	7	2 	3O				3A10    					 
1996101000104	19961010	00104	CE  	1996	10	10	96ZZZX5005       	1	19960731	G	5741	AN824A	BOLT            			CESSNA	150   	152         	2071835	CE  										FWD WING ATTACH	RUSTED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	89969	7006 				15282934				WHILE REMOVING BOTH WINGS FROM ACFT, FOUND FORWARD WING ATTACH BOLT EXTREMELY DIFFICULT TO TURN.  AFTER LUBRICATION, BOL	T STILL HARD TO TURN.  AFTER BOLT WAS REMOVED, PLATING WAS OBSERVED TO BE GONE, THE BOLT WAS BENT, AND IT HAD SEVERE PIT	TING FROM RUST, WITH A POSSIBLE CRACK.  AT LEAST ONE OTHER WING ATTACH BOLT FROM THE SAME ACFT HAS THIS SITUATION.  SUBM	ITTER RECOMMENDS WING ATTACHMENT BOLT INSPECTION AT PERIODIC INTERVALS.  LUBRICATING BOLTS UPON INSTALLATION SHOULD BE A	CCOMPLISHED.  NOTE:  THIS CONDITION COULD ONLY BE OBSERVED BY REMOVAL OF THE BOLT.  THIS PARTICULAR AIRCRAFT SHOWED NO E	XTERNAL SIGNS OF THIS DETERIORATION.	1	H	7	1 	3O			NT	3A19    					 
1996101000105	19961010	00105	CE  	1996	10	10	96ZZZX5006       	1	19960904	G	3310	XR7200B	RHEOSTAT        			BEECH 	35    	K35         	1151524	CE  										INST PNL LIGHTS	OVERHEATED      	D		A		K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			EA	21	9538R					D6094				ALL FOUR LIGHTING DIMMER RHEOSTAT/TRANSISTOR ASSEMBLIES WERE SUBJECTED TO EXCESSIVE HEAT DURING NORMAL OPERATION.  THERE	 WAS NOT A SHORTED WIRE CONDITION CAUSING THIS HEAT.  THE POTTING COMPOUND FORMING THE UNIT MELTED (DRIPPING DOWN ONTO T	HE FLOOR) EVENTUALLY CAUSING THE FAILURE OF THE RHEOSTAT.  SUBMITTER STATED THIS ASSEMBLY POSES A SAFETY HAZARD AND SHOU	LD BE REPLACED WITH ONE THAT CAN HANDLE THE LOAD AND DISSIPATE THE HEAT EFFECTIVELY.			1	L	7	1 	3O				3A15    					 
1996101000106	19961010	00106	SO  	1996	10	10	96ZZZX5007       	2	19960918	G	7322	643085	BRACKET         			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					THROTTLE BODY	SEPARATED       	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9489M	157  				21062081	294714R			THROTTLE BODY SUPPORT BRACKET FOUND SEPARATED AT ANNUAL INSPECTION.  TIS:  156.5 HOURS, SEPARATED AT SPOT WELDS.						1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996101000107	19961010	00107	SO  	1996	10	10	96ZZZX5008       	1	19960910	G	2434	DOFF103005	ALTERNATOR      	FORD        		GULSTM	AA5   	AA5A        	3960106	SO  										DC SYSTEM	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			NE	01	9860U					AA5A0260				ALTERNATOR FAILED ON TAKEOFF.  IFR ALTERNATOR HAD OVER 1,000 HOURS SINCE REBUILD.  AVERAGE TIME FOR ACCESSORIES IS ABOUT	 1,000 HOURS.  IFR AIRCRAFT ESPECIALLY SHOULD BE CAREFULLY LOOKED AT IN REGARDS TO ACCESSORY TIMES.					1	L	7	1 	3O				A16EA   					 
1996101000109	19961010	00109		1996	10	10	96ZZZX5010       	4	19960621	G	3442	ART2100	ART SENSOR      	BENDIX      	07101550101 	BEECH 	200   	B200        	1152922	CE  										RADAR ANT STAB	DEFECTIVE       	B			FR2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	38V				P1009	BB1412				ANTENNA STABLIZATION WORKS ONLY IN LEVEL FLIGHT AUTOTILT STILL DROPS ANTENNA.  S/W-01/12 SOFTWARE LEVEL DID NOT FIX PROB	LEMS OF THE ORIGINAL RADAR UNIT.  INSTALLED REPLACEMENT ART 2100, SN 1036, WITH THIRD BENDIX/KING SOFTWARE UPGRADE S/W-0	1/03 AND MOD STATUS 2.				1	L	7	2 	4T				A24CE   					 
1996101000110	19961010	00110		1996	10	10	96ZZZX5011       	4	19960130	G	3442	ART2100	ART SENSOR      	BENDIX      	07101550101 	BEECH 	200   	B200        	1152922	CE  										ARDAR ANT STAB	MALFUNCTION     	B			FR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	38V				1016	BB1412				ANTENNA STABILIATION TOO SENSITIVE.  RADAR PAINTS HEAVY LEFT AND RIGHT.  AUTOTILT DROPS ANTENNA.						1	L	7	2 	4T				A24CE   					 
1996101000111	19961010	00111		1996	10	10	96ZZZX5012       	4	19960819	G	3442	ART2100	ART SENSOR      	BENDIX      	07101550101 	BEECH 	200   	B200        	1152922	CE  										RADAR ANT STAB	MALFUNCTION     	B			FR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	38V				1036	BB1412				TEN MONTHS AFTER CHANGING ART 2100'S, BENDIX/KING STILL HAS NOT COME OUT WITH A GOOD FIX.  BASIC PROBLEM IS THE SOFTWARE	 WHICH CANNOT KEEP UP WITH 'GYRO PRECESSION'.  FAULT LABEL:  'ANT FLT'.					1	L	7	2 	4T				A24CE   					 
1996101000112	19961010	00112		1996	10	10	96ZZZX5013       	4	19960918	G	3442	ART2100	ART SENSOR      	BENDIX      	07101550101 	BEECH 	200   	B200        	1152922	CE  										RADAR ANT STAB	MALFUNCTION     	B			FR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	38V				1044	BB1412				STABILIZATION TOO SENSITIVE.  AUTOTILT DROPS ANTENNA.  STAB OFF AND INFLIGHT 6.						1	L	7	2 	4T				A24CE   					 
1996101000114	19961010	00114	CE  	1996	10	10	96ZZZX5015       	1	19960902	G	7120	9401120	MOUNT           			CESSNA	172   	172N        	2072434	CE  										ENGINE	DEFECTIVE       	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	1558E					17271046				AFTER ORDERING LORD MOUNTS J-9613-49 FOR REPLACMENT OF CESSNA 172N ENGINE, BARRY MOUNTS WERE AUTOMATICALLY SUBSTITUTED B	Y THE SUPPLIER.  SUBMITTER STATED ALTHOUGH THESE ARE APPROVED BY FAA, THEY DO LACK THE CENTER (DAMPER BAG) AND CESSNA RE	COMMENDS NOT DOING WITHOUT.  LORD CLAIMS THE NEED DURING START-UP AND SHUT DOWN.				1	H	7	1 	3O			NT	3A12    					 
1996101000115	19961010	00115	SO  	1996	10	10	96ZZZX5016       	1	19960901	G	7120		MOUNT           			GULSTM	AA5   	AA5B        	3960105	SO  										ENGINE	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1562R					AA5B0062				ENGINE MOUNT WAS DISCOVERED CRACKED ON THE CROSS-OVER SUPPORT BRACE JUST INBOARD OF THE WELD JOINT.  NO SIGNIFICANT INBO	ARD CORROSION WAS DISCOVERED.  IT APPEARS THE CRACK WAS CAUSED BY METAL FATIGUE.					1	L	7	1 	3O				A16EA   					 
1996101000116	19961010	00116	GL  	1996	10	10	96ZZZX5017       	3	19960901	G	6111		BLADE           			BEECH 	35    	V35B        	1151548	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER	BEARING FAILED  	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3161W		445  			D9572		781089		MAINTENANCE REMOVED THE PROPELLER FOR INSPECTION AND FOUND ALL THE BEARINGS, BEARING RACE FOR THE BLADES, WERE TOTALLY C	ORRODED AND THE PISTON AND SPRING AND THE DOME WERE TOTALLY UNSERVICEABLE.					1	L	7	1 	3O				3A15    		5	C	P21EA	 
1996101000118	19961010	00118	GL  	1996	10	10	96ZZZX5019       	1	19960812	G	2720	2027200100	CONTROL CABLE   			DIAMON	DA20  	DA20A1      	2990000	GL  										RUDDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	402KT	766  				10039				PILOT'S LEFT OUTBOARD RUDDER CABLE BROKE AT NICO PRESSURE FITTING.  WITH RUDDER PEDALS ADJUSTED FULL FORWARD POSITION, S	-TUBE MAKES CONTACT WITH NICO-PRESSURE FITTING.  S-TUBE WORE THROUGH THE CABLE.  AIRCRAFT WAS ON THE GROUND.					1	L	7	1 	3O			NT	TA4CH   					 
1996101000119	19961010	00119	CE  	1996	10	10	96ZZZX5020       	1	19960901	G	3110		INSTRUMENT PANEL			BEECH 	35    	G35         	1151516	CE  										COCKPIT	POOR SUPPORT    	B			UQ2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	4645D					D4840				A PORTION OF TOP FUSELAGE SKIN EXTENDING FROM WINDSHIELD LINE AFT TO INSTRUMENT PANEL WAS REMOVED.  SUBMITTER SUSPECTS T	HIS SECTION OF SKIN REMOVED TO MAKE IT EASIER TO INSTALL A NEW 1-PIECE SPEED SLOPE WINDSHIELD.  THIS SECTION PROVIDES ST	RUCT  STRENGTH AND SUPPORT FOR INSTR PANEL AND SHOCK MOUNTED SUB-PANEL.  THE TOP OF INSTR PANEL HAD LITTLE FORE AND AFT 	SUPPORT AND ENTIRE PANEL WEAKLY SUPPORTED BY CHANNEL THAT RUNS ALONG BOTTOM OF PANEL ATTACHED TO LT AND RT SIDEWALLS.  B	Y MOVING CONTROL COLUMN UP AND DOWN, ENTIRE INSTR  PANEL WOULD FLEX AT LEAST .50 INCH.  SUBMITTER RECOMMENDS WHEN OLDER 	BONANZA'S HAVE WINDSHIELD MODS DONE, TAKE PRECAUTIONS NOT TO LOSE INSTRUMENT PANEL STRUCTURAL STRENGTH.	1	L	7	1 	3O				A777    					 
1996101000122	19961010	00122	EA  	1996	10	10	96ZZZX5023       	2	19960820	G	8530		PISTON          			PIPER 	PA14  	PA14        	7101402	SO  	LYC   	O290  	O290D       	41506	EA  					NR 3 CYLINDER	FAILED          	D	P			A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	11	5196H	2286 				14493	188521			DURING FLIGHT, THE PILOT REPORTED HEARING A SLIGHT KNOCKING IN THE ENGINE AND NOTED A 20 PSI DROP IN OIL PRESSURE.  A PR	ECAUTIONARY LANDING WAS MADE WITHOUT INCIDENT.  COMPRESSION CHECK REVEALED NR 3 CYLINDER LOW AT 50/80.  CYLINDER REMOVAL	 REVEALED NR 3 PISTON SKIRT BROKE WITH 2 INCH BY 3 INCH PIECE LOCATED IN OIL SUMP OF ENGINE.				1	H	7	1 	3O	3	O		A797    	E229				 
1996101000123	19961010	00123	EU  	1996	10	10	96ZZZX5024       	1	19960711	G	2460	727727	BREAKER         			HWKSLY	DH125 	HS125600A   	4230158	EU  										COMM NR 2	FAILED          	G		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	03	600G					256066				COMM 2 CIRCUIT BREAKER OPENED DURING FLIGHT AND WOULD NOT RESET.  CIRCUIT BREAKER WAS REPLACED WITH NEW BREAKER.						2	L	7	2 	4J				A3EU    					 
1996101000125	19961010	00125	CE  	1996	10	10	96ZZZX5026       	1	19960819	G	2842	169380066	TRANSMITTER     			BEECH 	23    	C23         	1151242	CE  										FUEL QUANTITY	LEAKING         	H	P			K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CE	09	6519R	2432 				M1542				FUEL SMELL IN CABIN. LEFT AND RIGHT FUEL QUANTITY TRANSMITTERS LEAKING FUEL FROM CENTER POST OF TRANSMITTER.  FUEL APPEA	RS TO BE LEAKING FROM INTERNAL SEALS.  PARTS TO BE REMOVED AND REPLACED.					1	L	7	1 	3O				A1CE    					 
1996101000126	19961010	00126	CE  	1996	10	10	96ZZZX5027       	1	19960918	G	2760	0148	WORM GEAR       			CESSNA	210   	P210N       	2073454	CE  										SPEED BRAKE	SCREW LOOSE     	D		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	731MV				4455	P21000512				STC SA2602NM.  SPEED BRAKES FAILED TO DEPLOY.  SET SCREW PART NUMBER UNKNOWN USED TO SECURE WORM GEAR TO GEAR MOTOR SHAF	T.  HAD ALLOWED WORM GEAR TO SLIP OFF OF SHAFT.  SHAFT HAD SMALL DRILL SPOT ON OUTSIDE DIAMETER AS DETENT FOR SET SCREW 	.  SET SCREW IS LARGER IN DIAMETER THAN DRILL SPOT.  SET SCREW DID NOT PENETRA TE INTO SHAFT AREA ALLOWING WORM GEAR TO 	WORK OFF OF SHAFT.  SUBMITTER STATED THIS CONDITION, BECAUSE ONE MOTOR IS INSTALLED IN EACH SPEED BRAKE, COULD ALLOW ASY	MMETRICAL LIFT CONDITION TO EXIST.		1	H	7	1 	3O				3A21    					 
1996101000127	19961010	00127	NE  	1996	10	10	96ZZZX5028       	2	19960902	G	8520	20506	LINK ROD        			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183090B    	52020	NE  					NR 7 CYLINDER	BROKEN          	E				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	05	8187E	6179 	181  			25285	BP307288			IN CRUISE POWER, LT ENGINE STARTED RUNNING ROUGH. FOUND NR 7 CYLINDER LINK ROD BROKEN.						2	L	7	2 	4R	4	R		A669    	5E4				 
1996101000180	19961010	00180	SO  	1996	10	10	96ZZZX5029       	1	19960902	G	7160	MS202531	HINGE PIN       			PIPER 	PA28  	PA28R200    	7102811	SO  										ALT AIR DOOR	FAILED          	D		A		K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	21	75340	600  				28R7635292				DURING PRE-FLIGHT RUN UP, POWER WAS LIMITED TO 1,900 RPM.  THE ALTERNATE AIR DOOR WAS FOUND IN THE FUEL METERING UNIT, T	HE HINGE PIN HAD WORN COMPLETELY THROUGH IN 600 HOURS OF OPERATION.  (ONE YEAR AT FLIGHT SCHOOL).  SUBMITTER RECOMMENDAT	ION, A TAB ON THE ALTERNATE AIR DOOR COULD PROVIDE BOTH A PUSH/PULL TEST OF THE HINGE AND AN ATTACH POINT FOR A COUPE LE	ASH.			1	L	7	1 	3O				2A13    					 
1996101000181	19961010	00181	SO  	1996	10	10	96ZZZX5030       	1	19960701	G	5523	6358501	TRIM TAB        		6358500     	PIPER 	PA28  	PA28R200    	7102811	SO  										STABILATOR	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	75340	6100 				28R7635292				DURING 100-HOUR INSPECTION, THE TRIM TAB WAS DISCONNECTED TO ACCOMODATE REPLACEMENT OF TRIM BARREL HARDWARE, THE TRIM TA	B WAS FOUND TO BE CRACKED:  UNDER THE ATTACH BRACKET, AT THE EDGE OF THE ATTACH BRACKET,  INTO THE SUPPORTING RIBS., ON 	BOTH LT AND RT TRIM TAB.				1	L	7	1 	3O				2A13    					 
1996101000183	19961010	00183	CE  	1996	10	10	96ZZZX5032       	1	19960827	G	3230	504501019	TORQUE TUBE     			CESSNA	310   	310Q        	2074242	CE  										LT MLG	CRACKED         	B	L		CSLR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	01	7872Q	5000 				310Q0653				DURING FLIGHT, PILOT NOTED THE ACFT SEEMED SLOWER AND YAWING TO THE LEFT.  FLYBY INDICATED THE LEFT MAIN LANDING GEAR WA	S DOWN WHILE THE RT AND NOSE WERE RETRACTED GEAR.  SELECTED DOWN, ALL THREE INDICATED DOWN AND LOCKED.  ACFT LANDED AT M	AINTENANCE BASE WITHOUT INCIDENT.  INVESTIGATION REVEALED THE LEFT MAIN GEAR TORQUE TUBE HAD CRACKED AT THE FORK BOLT BO	SS AND THE CRACK HAD PROGRESSED AROUND THE TORQUE TUBE IN A SPIRAL MANNER.			1	L	7	2 	3O				3A10    					 
1996101000184	19961010	00184	SO  	1996	10	10	96ZZZX5033       	1	19960820	G	3297		WIRE            			PIPER 	PA24  	PA24250     	7102404	SO  										NLG SWITCH	BURNED          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	8230P					243483				WIRES LEADING TO NOSE GEAR SWITCHES WERE FOUND CHARRED BARE WHERE THEY WERE SECURED BEHIND MUFFLER.  WIRES WERE ROUTED T	O OUTBOARD SIDE OF ENGINE COMPARTMENT TO REMOVE THEM FROM HOT AREA.					1	L	7	1 	3O			 	1A15    					 
1996101000185	19961010	00185	CE  	1996	10	10	96ZZZX5034       	1	19960917	G	2710	2300003142	CONTROL CABLE   			LEAR  	24    	24B         	5170306	CE  										AILERON	FRAYED          	E				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	83HC					193				CABLE WAS INSTALLED TO AIRCRAFT.  PRE-TENSIONED TO 200 FEET/POUNDS (PER MM) WHILE AILERON CONTROLS WERE RUN THROUGH WHIL	E CABLE WAS UNDER TENSION AT 200 POUNDS, A SMALL 'BULGE' WAS NOTED AT APPROIXMATELY MID-CABLE LENGTH.  AN INTERNAL CABLE	 STRAND HAD BROKEN (APPARENTLY) UNDER THE PRE-TENSION LOAD.  ANOTHER NEW CABLE WAS INSTALLED.  LEARJET FIELD SERVICE WAS	 INFORMED.			2	L	7	2 	4J			 	A10CE   					 
1996101000186	19961010	00186		1996	10	10	96ZZZX5035       	4	19960901	G	2562	4530150	ELT             	ARTEX       	52770       	PIPER 	PA46  	PA46350P    		SO  										CASE	BATTERY FAULTY  	B	P		SJ7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	9250B	500  				4622161				ELT BATTERY, ONE BATTERY SHOWED EVIDENCE OF HIGH HEAT, AND EXCESS CORROSION CRACKING BATTERY CASE.  ELT MANUFACTURED '94	.					1	L	7	1 	3O			RT	A25SO   					 
1996101000187	19961010	00187	SO  	1996	10	10	96ZZZX5036       	1	19960905	G	7810	1245712	STACK           			PIPER 	PA18  	PA18A150    	7101837	SO  										NR 2 CYL EXH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9295D	201  				186602				THE NR 2 EXHAUST PORT STACK CRACKED AT MOUNTING FLANGE.  THIS PART WAS NEW FROM UNIVAIR.  THE EXHAUST STACK ONLY HAD 200	 HOURS SINCE NEW.  SUBMITTER STATED UNIVAIR STATES THEY HAVE HAD CRACKING PROBLEMS BEFORE.  THIS PART IS MANUFACUTRED BY	 A SUB-CONTRACTOR TO UNIVAIR.				1	H	7	1 	3O				1A2     					 
1996101000188	19961010	00188	SO  	1996	10	10	96ZZZX5037       	1	19960818	G	2750	6270600	LEVER ASSY      			PIPER 	PA28  	PA28140     	7102802	SO  										FLAP CONTROL	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	9851W	5000 				2823364				WHILE C/W AD 96-10-03 FLAP ATTACH BOLT, DISCOVERED THE BRACKET THE FLAP HANDLE ATTACHES TO HAD 4 CRACKS IN IT, ONE AT EA	CH CORNER.					1	L	7	1 	3O				2A13    					 
1996101000189	19961010	00189	EA  	1996	10	10	96ZZZX5038       	2	19960618	G	8540	76327	DRIVE GEAR      			BELL  	47    	47G5        	1181032	SW  	LYC   	O435  	VO435B1A    	41516	EA  					ACCY DRIVE	BOLTS SHEARED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	1449W		530  			7931	2345331			GEAR AND SHAFT ASSEMBLY IS A TWO-PART GEAR HELD TOGETHER BY SIX .25 INCH BOLTS AND THREE .25 INCH PILOT PINS.  IT APPEAR	S THE SIX .25 INCH BOLTS WERE NOT PROPERLY TORQUED AT OVERHAUL AND THEY SHEARED OFF AT 529.6 HOURS SMOH.					1	G	7	1 	3O	3	O		2H3     	E279				 
1996101000190	19961010	00190	NE  	1996	10	10	96ZZZX5039       	2	19960829	G	7261		ENGINE          			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					N1 GEARBOX	OIL VENTING     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	311KA	409  				A940017	LE81016			ENGINE WAS VENTING OIL OVERBOARD FROM LARGE VENT LINE CONNECTED TO N1 GEARBOX.  ALL POSSIBLE STEPS TO CORRECT WERE NOT S	UCCESSFUL.  ENGINE WAS REPLACED AUGUST 29, 1996.					1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
1996101000191	19961010	00191	SW  	1996	10	10	96ZZZX5040       	1	19960829	G	6220	K913014001	DROOP STOP      		K913001004  	KAMAN 	K1200 	K1200       	05625F6	SW  										RT HUB ASSY	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	311KA	409  			8BM	A940017				DROOP STOP ON RT SIDE HUB WAS BENT BY PILOT WHEN ATTEMPTING TO INSTALL TEETER LOCKS DURING ACFT TY-DOWN PROCEDURE.  CREW	 CHIEF HAD REPAIRED STOP, BUT STOP WAS TWEAKED FORE AND AFT AS WELL AS UP AND DOWN.  STOP HUNG UP DURING COAST DOWN AND 	R/S ROTOR BLADES CHAFED OPPOSING HUB.  AFTER THOROUGH INSPECTION, ONLY R/S ROTOR BLADES (TWO EACH) WERE REPLACED.				1	G	7	1 	4F			NT	TR7BO   					 
1996101000192	19961010	00192	SW  	1996	10	10	96ZZZX5041       	1	19960904	G	6520	2060404103	DUPLEX BEARING  		206040400013	BELL  	206   	206B3       	1181506	SW  										T/R TRANSMISSION	ROUGH           	B			PN5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	11CQ	4678 	1677 		A49	3778				COULD NOT BALANCE T/R DUE TO ROUGH BEARING GIVING FALSE SIGNALS TO BALANCE EQUIPMENT.  REPLACED BEARING AND REINSTALLED 	GEARBOX ON AIRCRAFT AND BALANCED T/R IN NORMAL MANNER WITH GOOD RESULTS.					1	G	7	1 	3U				H2SW    					 
1996101000193	19961010	00193	SW  	1996	10	10	96ZZZX5042       	1	19960917	G	5302	206031329103	FITTING         		206033410001	BELL  	206   	206L1       	1182107	SW  										TAILBOOM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	613					45287				ACFT TT:  7,745.2 HOURS.  DURING 300-HOUR INSPECTION, FOUND CRACK IN T/B FITTING.  AIRCRAFT HAS BEEN DOING SLING WORK. S	UBMITTER RECOMMENDATION WOULD BE TO INSPECT MORE FREQUENTLY UNTIL A STRONGER FITTING IS MADE.					1	G	7	1 	3U				H2SW    					 
1996101000194	19961010	00194	NE  	1996	10	10	96ZZZX5043       	2	19960912	G	7250	834401	BLADE           								PWA   	JT8   	JT8D9A      	52048	NE  					N2 TURBO T1	FAILURE         	B			SQ5R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			NE	03							P674220			ENGINE EXHIBITED HIGH VIBRATION IN SERVICE.  DISASSEMBLY INSPECTION REVEALED T-2 BLADE FAILURE AND CONSEQUENTIAL DAMAGE 	TO THE 2ND, 3RD, AND 4TH AIRFOILS. THE CAUSE OF FAILURE IS UNDER INVESTIGATION.										4	F			E2EA				 
1996101000195	19961010	00195	NE  	1996	10	10	96ZZZX5044       	2	19960912	G	7240	628748001	T-DUCT          								PWA   	JT8   	JT8D9A      	52048	NE  					COMB CHAMBER	FAILURE         	B			SQ5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							P674220			DISASSEMBLY INSPECTION OF ENGINE AFTER HPT BLADE FAILURE REVEALED FAILURE OF THE COMBUSTION CHAMBER SUPPORT/INNER C.C. C	ASE ATTACHMENT FINGERS.  SUSPECT CAUSE OF FAILURE WAS RELATED TO SHORT TERM OPERATION OF MALFUNCTIONING ENGINE AFTER HPT	 BLADE FAILURE.									4	F			E2EA				 
1996101000196	19961010	00196	CE  	1996	10	10	96ZZZX5045       	1	19960819	G	3260	MS243311	SWITCH          			BEECH 	MU300 	400A        	1155402	CE  										LT MLG DOWNLOCK	INTERMITTENT    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3196N	349  				RK96				LEFT GEAR DOWN INDICATION INTERMITTENT.  PROBLEM TRACED TO DOWN SWITCH ON GEAR.  THIS IS 3RD OCCURRENCE ON THIS AIRCRAFT	 IN 14 MONTHS.  ANOTHER B-400A IN FLEET HAS HAD 3 SWITCHES FAIL ALSO.  IN MOST CASES, DOWN AND LOCKED LIGHT WOULD COME O	N WHEN SWITCH WAS LIGHTLY TAPPED.  RIGGING WAS WITHIN SPECS ON ALL OCCURRENCES.				2	H	7	2 	4F			RT	A16SW   					 
1996101000197	19961010	00197	NE  	1996	10	10	96ZZZX5046       	2	19960902	G	7250	3115154	NOZZLE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					PT HOUSING OIL	PLUGGED         	A		A	MASR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	35YV	9267 	1156 			UE35	114031			AT DISASSEMBLY, THE NR 3 BEARING WAS FOUND COMPLETELY DESTROYED.  IT APPEARS TO BE OIL STARVATION DUE TO THE NR 3 AND NR	 4 BEARING OIL NOZZLE BEING PLUGGED.  WHEN THE NOZZLE WAS FLOW CHECKED, IT REVEALED 3 OF THE 4 OIL PORTS WERE PLUGGED. T	HE BLOCKAGE APPEARS TO BE CARBON BUILD-UP INSIDE THE NOZZLE.  THE OIL NOZZLE WAS SENT TO PRATT AND WHITNEY FOR INVESTIGA	TION ALONG WITH THE FAILED NR 3 BEARING REMAINS.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1996101000198	19961010	00198	NM  	1996	10	10	96ZZZX5047       	1	19960901	G	5311		FRAME           			BOEING	727   	727224      	1384076	NM  										FS 219.8	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS FOUND ON FRAME 219.8, LT SIDE OF LOWER NOSE COMPARTMENT DOOR CUT-OUT.						2	L	7	3 	4F				A3WE    					 
1996101000199	19961010	00199	CE  	1996	10	10	96ZZZX5048       	1	19960725	G	3244	301393190	TIRE            			BEECH 	300   	300BEECH    	1152930	CE  										NLG	DEFECTIVE       	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			NM	09	488GA					FA125				PILOT REPORTED VIBRATION ON TAKEOFF ROLL.  LANDED WITHOUT INCIDENT.  INSPECTION REVEALED NOSE TIRE INTERNAL BALANCE PATC	H HAD COME LOOSE.  SUSPECT HIGH OAT AS CAUSE.					2	L	7	2 	4T				A24CE   					 
1996101000200	19961010	00200	NE  	1996	10	10	96ZZZX5049       	2	19960913	G	8530		CYLINDER        			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183092     	52020	NE  					RT ENG NR 2	CRACKED         	E				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SW	11	59316		950  			18986	359283			RIGHT ENGINE STARTED TO RUN ROUGH AND BACKFIRE IN-FLIGHT.  ENGINE SHUT DOWN AND AN UNEVENTFUL LANDING WAS MADE.  INVESTI	GATION FOUND NR 2 CYLINDER CRACKED.  CYLINDER WAS REMOVED AND REPLACED WITH A YELLOW TAGGED UNIT.  ENGINE GROUND RAN, CH	ECKED SATISFACTORY.  AIRCRAFT RETURNED TO SERVICE.  SUSPECT FATIGUE AS CAUSE OF CRACK.				2	L	7	2 	4R	4	R		A669    	5E4				 
1996101000201	19961010	00201	CE  	1996	10	10	96ZZZX5050       	1	19960828	G	3010	3D235306	FLOW CONTROL    			CESSNA	441   	441         	2076020	CE  										LT WING DEICE	PLUGGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	832AD	2894 				4410311				WING BOOTS INFLATED AND STAYED INFLATED UNTIL ENGINE SHUT DOWN.  THEY WOULD NOT RESET.  REMOVED FLOW CONTROL EJECTOR VAL	VE AND FOUND OVERBOARD PORT PLUGGED WITH MUD AND INSECT EGG SACKS.					1	L	7	2 	3T			RT	A28CE   					 
1996101000202	19961010	00202	CE  	1996	10	10	96ZZZX5051       	1	19960820	G	3240	G51710917	LINE            			CESSNA	500   	S550        	2076607	CE  										LT BRAKE	CHAFE/FAIL      	B		A	EB1R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	13	91ML					S550132				BRAKE PRESSURE LOST ON LANDING.  INVESTIGATION OF PROBLEM REVEALED THE BRAKE LINE GOING TO THE LT BRAKE HAD BEEN CHAFED 	THROUGH BY AN ELEVATOR CONTROL CABLE.  THE LINE WAS REMOVED AND REPLACED.  THE NEW LINE WAS INSTALLED WITH ADEQUATE CLEA	RANCE BETWEEN THE BRAKE LINE AND CABLE TO PREVENT RECURRENCE.  THE CABLE WAS NOT DAMAGED.  THE LOCATION OF THE PROBLEM W	AS UNDER THE FLOOR JUST INSIDE THE MAIN ENTRANCE DOOR.			1	L	7	2 	4F			RT	A22CE   					 
1996101000203	19961010	00203	NE  	1996	10	10	96ZZZX5052       	2	19960820	G	7250		ENGINE          								PWA   	JT8   	JT8D219     	52053	NE  					TURBINE	FAILURE         	B			RH2R	E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			SO	19		11588					725447			IN-FLIGHT SHUTDOWN AND ENGINE WAS REMOVED FROM AIRCRAFT DUE TO TURBINE FAILURE.  1ST, 2ND, 3RD, AND 4TH TURBINE BLADES A	ND 2ND, 3RD, AND 4TH NOZZLE GUIDE VANES SUSTAINED EXTENSIVE DAMAGE.  EXACT CAUSE HAS NOT BEEN DETERMINED AT THIS TIME. I	T IS SUSPECTED THE 2ND NGV'S MADE CONTACT WITH THE T-2 BLADES CAUSING FAILURE.  SB'S 5830, 5840, AND 5891 HAD BEEN PREVI	OUSLY C/W AND ASB 5782 WAS CURRENT.								4	F			E9NE				 
1996101000204	19961010	00204	NM  	1996	10	10	96ZZZX5053       	1	19960725	G	3610	797839	VALVE SHAFT     	HAMSTD      	77385618    	BOEING	747   	747*        		NM  										PRESS CHECK	WORN            	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					DL22					ANTI-ROTATION SLOTS ARE WORN AWAY ON VALVE SHAFT CAUSING SHAFT TO ROTATE AND SHAFT SHOULDER TO WEAR EXCESSIVELY.  REF: O	HM 36-12-06, PAGE 606, FIGURE 603.					2	L	7	4 	4F			RT	A20WE   					 
1996101000363	19961010	00363	CE  	1996	10	10	96ZZZX5055       	1	19960913	G	2150	75065912	SWITCH          			CESSNA	650   	650         	2076802	CE  										PAC OVERHEAT	FAILED          	D				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			GL	09	2UP	1780 				6500227				FLIGHT CREW REPORTED COCKPIT PAC OVERHEAT LIGHT ON AT FL 410.  LIGHT STAYED ON AFTER LANDING.  INVESTIGATION FOUND FAULT	Y PAC OVERHEAT SWITCH.  REPLACEMENT SWITCH CLEARED PROBLEM.					2	L	7	2 	4F				A9NM    					 
1996101000364	19961010	00364	SO  	1996	10	10	96ZZZX5056       	1	19960918	G	3500	8RC1500HT	CYLINDER        		FR149A2114  	GULSTM	G1159 	G1159       	3953505	SO  										OXYGEN SYSTEM	MISMARKED       	B			LC2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	125JJ				961751P	15				SECTIONS 173.34(3) (13) (1V).  MARKING D.O. T3HT SPECIFICATION CYLINDERS WITH A  HIGH STRESS  MARKING STAMP.  CYLINDERS 	ARE REQUIRED TO BE MARKED WITH A LOW STRESS MARKING STAMP.  EX:  8-16-96 TEST NRS. 7 AND 8.					2	L	7	2 	4F			RT	A12EA   					 
1996101000365	19961010	00365	SO  	1996	10	10	96ZZZX5057       	1	19960918	G	3500	8RC1500HT	CYLINDER        		FR149A2114  	GULSTM	G1159 	G1159       	3953505	SO  										OXYGEN SYSTEM	MISMARKED       	B			LC2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	125JJ				961700P	15				SECTIONS 173.34(3) (13) (1V).  MARKING D.O. T3HT SPECIFICATION CYLINDERS WITH A  HIGH STRESS  MARKING STAMP.  CYLINDERS 	ARE REQUIRED TO BE MARKED WITH A LOW STRESS MARKING STAMP.  EX:  8-16-96 TEST NRS. 7 AND 8.					2	L	7	2 	4F			RT	A12EA   					 
1996101000366	19961010	00366	CE  	1996	10	10	96ZZZX5058       	1	19960913	G	2612	99140921	FIRE LOOP       			CESSNA	650   	650         	2076802	CE  										LT ENG DETECTOR	FAULTY          	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			GL	09	1UP	1836 				6500224				FLIGHT CREW REPORTED LEFT FIRE DETECTOR FAIL ANNUNCIATOR LIGHT ON.  FIRE TEST NORMAL.  INVESTIGATION REVEALED FIRE DETEC	TOR LOOP RUBBED THROUGH INBOARD SIDE UNDER AFT ENGINE SHROUD.  REPLACEMENT LOOP CLEARED PROBLEM.					2	L	7	2 	4F				A9NM    					 
1996101000367	19961010	00367	CE  	1996	10	10	96ZZZX5059       	1	19960913	G	3040	99141242	VALVE           			CESSNA	650   	650         	2076802	CE  										ANTI-ICE MASTER	FAULTY          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1UP	1787 				6500224				FLIHGT CREW REPORTED LEFT EMERGENCY PRESSURIZATION WOULD NOT WORK UNLESS WINDSHIELD AIR SELECTOR ON. INVESTIGATION REVEA	LED FAULTY ANTI-ICE MASTER VALVE.  REPLACEMENT VALVE CLEARED PROBLEM.					2	L	7	2 	4F				A9NM    					 
1996101000368	19961010	00368	CE  	1996	10	10	96ZZZX5060       	1	19960730	G	5210	10143014253	DOOR            			BEECH 	200   	200CBEECH   	1152926	CE  										CABIN DR HINGE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	111NS	5877 				BL36				FLIGHT CREW REPORTED SEEING LIGHT THROUGH CABIN DOOR AROUND HINGE AREA. ON INSPECTION, FOUND DOOR CRACKED OVER 10 INCHES	 LONG ABOVE HINGE ATTACHMENT.  THE DOOR WAS REPLACED.					1	L	7	2 	4T				A24CE   					 
1996101000369	19961010	00369		1996	10	10	96ZZZX5061       	4	19960522	G	3442	ART2100	SENSOR          	BENDIX      	07101550101 	BEECH 	200   	B200        	1152922	CE  										RADAR ANT STAB	MALFUNCTIONED   	B			FR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	128V				1016	BB1442				ART-2100, SN 1016, SAME OLD PROBLEMS.  STABILIZATION TOO SENSITIVE.  PAINT HEAVY IN ROLL LEFT OR RIGHT.  AUTOTILT DROPS 	ANTENNA.  BENDIX/KING RECOMMENDED FACTORY EXCHANGE ART-2100, SN 1016.  INSTALLED ART-2100, SN 1044.					1	L	7	2 	4T				A24CE   					 
1996101000371	19961010	00371		1996	10	10	96ZZZX5063       	4	19960625	G	3442	ART2100	SENSOR          	BENDIX      	07101550101 	BEECH 	200   	B200        	1152922	CE  										RADAR ANT STAB	MALFUNCTIONED   	B			FR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	128V				1044	BB1442				ART-2100, SN 1044, SAME OLD STAB PROBLEMS.  ALSO, PAINTS SQUIGGLES BEYOND 40 MILE RANGE IN 'HEAVY THUNDERSTORMS'.  BENDI	X/KING RECOMMENDED STC MOD.  EXCHANGED ART-2100 WITH NEW SOFTWARE LEVEL 01/03 AND MOD 2 FOR STC COMPENSATION.  INSTALLED	 ART-2100, SN 1026.				1	L	7	2 	4T				A24CE   					 
1996101000372	19961010	00372		1996	10	10	96ZZZX5064       	4	19960405	G	3442	ART2100	SENSOR          	BENDIX      	07101550101 	BEECH 	200   	B200        	1152922	CE  										RADAR ANT STAB	MALFUNCTIONED   	B			FR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	128V				1018	BB1442				ART-2100, SN 1018, SAME PROBLEMS AFTER PREVIOUS SOFTWARE CHANGE.  STABLIZATION TOO SENSISTIVE.  PAINTS HEAVY LEFT OR RIG	HT.  AUTOTILT DROPS ANTENNA.  INSTALLED ART-2100, SN 1016, SN DASH 01/02 MOD DASH 1.					1	L	7	2 	4T				A24CE   					 
1996101000373	19961010	00373		1996	10	10	96ZZZX5065       	4	19960130	G	3442	ART2100	SENSOR          	BENDIX      	07101550101 	BEECH 	200   	B200        	1152922	CE  										RADAR ANT STAB	MALFUNCTIONED   	B			FR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	128V				1018	BB1442				ART-2100, SN 1018 SOFTWARE S/W DASH 01/01,  MOD 1.  STABILIZATION TOO SENSITIVE.  PAINTS HEAVY LEFT/RIGHT.  AUTOTILT DRO	PS ANTENNA.  BENDIX/KING RECOMMENDED SOFTWARE CHANGE.  INSTALLED ART-2100.  NEW SOFTWARE LEVEL S/W DASH 01/02, MOD 1.  N	O ATTEMPT WAS MADE TO FIX 'AUTOTILT'.				1	L	7	2 	4T				A24CE   					 
1996101000375	19961010	00375	WP  	1996	10	10	96ZZZX5067       	2	19960901	G	7310	300297719	MANIFOLD        			AMD   	FALC20	FALCON200   	2730150	EU  	GARRTT	ATF3  	ATF36A4     	29002	WP  					LT ENGINE	CRACKED         	B			GQRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	200WY				P426C	P21122	509			FUEL MANIFOLD SHROUD WAS FOUND CRACKED.  REPLACED WITH SERVICEABLE UNIT.  UNKNOWN IF FUEL WAS LEAKING FROM MANIFOLD.  AF	TT:  3,358 HOURS.  LE TT:  3,653 HOURS.  TC LE:  2,655.					2	L	7	2 	4F	4	F	RT	A7EU    	E7WE				 
1996101000376	19961010	00376	WP  	1996	10	10	96ZZZX5068       	2	19960901	G	7240	300174517	LINER           			AMD   	FALC20	FALCON200   	2730150	EU  	GARRTT	ATF3  	ATF36A4     	29002	WP  					COMB LINER	CRACKED         	B			GQRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	200WY					509	P21122			DURING ROUTINE 600 HOUR INSPECTION, DISCOVERED SEVERAL COMBUSTION LINER CRACKS OUTSIDE OF MM LIMITATIONS.  REMOVED AND R	EPLACED LINER.  AFTT:  3,358 HOURS.  LE TT:  3,653 HOURS.  TC:  2,655.					2	L	7	2 	4F	4	F	RT	A7EU    	E7WE				 
1996101000377	19961010	00377	WP  	1996	10	10	96ZZZX5069       	2	19960901	G	7250	30031522	MID FRAME       			AMD   	FALC20	FALCON200   	2730150	EU  	GARRTT	ATF3  	ATF36A4     	29002	WP  					LT ENGINE	CERAMIC FLAKING 	B			GQRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	200WY				5P3930	509	P21122			BLADE TIP SEALING CERAMIC FLAKED OFF 30 TO 40 PERCENT OF AREA.  NO DETECTABLE RESULTING DISCREPANCY.  DISCOVERED DURING 	SCHEDULED 600 HOUR INSPECTION BORESCOPE INSPECTION.  NEW INNER MID-FRAME ASSY INSTALLED TO CORRECT PROBLEM.  AFTT:  3,35	8 HOURS.  LE TT:  3,653 HOURS.  TC:  2,655.				2	L	7	2 	4F	4	F	RT	A7EU    	E7WE				 
1996101000378	19961010	00378	CE  	1996	10	10	96ZZZX5070       	1	19960913	G	3240	07515500	TORQUE PLATE    	PARKERHANFIN	19990       	BEECH 	90    	C90A        	1152911	CE  										WHEEL BRAKE	CRACKED         	B	S		DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	301ER	1767 				LJ1286				DURING A ROUTINE PHASE INSPECTION, A WHEEL BRAKE GUIDE PIN BUSHING WAS FOUND LOOSE.  CLEANING AND INSPECTION REVEALED A 	CRACK WITH A WIDE GAP IN THE CASTING.  STC NR SA619GL.					1	L	7	2 	3T			RT	3A20    					 
1996101000379	19961010	00379	NM  	1996	10	10	96ZZZX5071       	1	19960807	G	2612		FIRE WARNING    			BOEING	747   	747SP09     	1384903	NM  										AFT CARGO	ACTIVATED       	D				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			CR	CRUISE         	1			SW	99	4522V					22805				SIN/JNB - FLT CI-091 - 8-7-96, AFTER FLIGHT OF 9 HOURS 20 MINUTES, FL 4,300 FEET, AFT CARGO FIRE WARNING LIGHT ILLUMINAT	ED.  BOTH FIRED BOTTLES DISCHARGED.  BOTH FIRE BOTTLES CHANGED.  NR 3 AND NR 4 SMOKE DETECTOR CHANGED.  FIRE WARNING AMP	LIFIER CHANGED.  ALL FUNCTIONAL TESTS PASSED IAW MM 26-16-00.				2	L	7	4 	4F				A20WE   					 
1996101000380	19961010	00380	CE  	1996	10	10	96ZZZX5072       	1	19960918	G	3230	42000118	RELIEF VALVE    		2129402     	CESSNA	500   	550         	2076604	CE  										EMERG GEAR BOTL	LEAKING         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	602AT				626	5500606				UPON ACTIVATION OF GEAR BLOW-DOWN TO TEST NEWLY INSTALLED BOTTLE, AFTER 3 GREENS WERE OBTAINED THE BODY OF THE RELIEF VA	LVE WAS LEAKING AROUND SEAM QUICKLY DEPLETING SUPPLY OF NITROGEN. THIS OCCURRED ON 3 BOTTLES IN A ROW FROM SAME VENDOR.					1	L	7	2 	4F				A22CE   					 
1996101000381	19961010	00381	SO  	1996	10	10	96ZZZX5073       	1	19960920	G	2421	28B13512GA	ALTERNATOR      			GULSTM	G1159 	G1159B      	3953535	SO  										LT GENERATOR	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NM	01	812RS		15   		243M	098				LEFT AC GENERATOR SUSPECT FAILED.  DROPPED OFF LINE IN-FLIGHT.  TVI FROM .5 TO 2.0 IPS.  NOTED DEBRIS AROUND MOUNTING FL	ANGE UPON INSPECTION.  REPLACED ALTERNATOR.  THIS IS THE 3RD AC GENERATOR FAILURE WITH A REAL LOW TSO IN THE LAST 6 MONT	HS, BEARINGS FAILED.				2	L	7	2 	4F			RT	A12EA   					 
1996101000382	19961010	00382	EA  	1996	10	10	96ZZZX5074       	2	19960913	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RT ENGINE	FAILED          	B	L		PIQR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			EA	21	859CC					BB389	80383			ACFT HAD IN-FLT FAILURE OF RT ENG, AS ACFT REACHED CRUISE ALTITUDE.  ENG HAS TTSN 7,559.4, TSHSI 120.9, TSO1605.3.  A PR	ELIM INSP OF ENG FND LARGE OIL STAIN ACROSS TOP OF NACELLE AND OIL DRIPPING FROM COWLING.  PROP WOULD NOT ROTATE IN NORM	AL DIRECTION OF ROTATION, BUT WOULD ROTATE COUNTERCLOCKWISE WITH GRINDING SOUND.  INTERIOR OF EXH STACKS FND TO CONTAIN 	MANY SMALL CHUNKS OF METAL.  UPON OPENING COWLING, COMP HOUSING FND DISTORTED AND ALL INLET SUPPORT STRUTS HAD FAILED. C	OMP MAIN SHAFT OFF CENTER AND ALL  BLADES DESTROYED.  AFT SECT OF COMP HOUSING AND ACCY GRBX SHIFTED 3 INCHES AFT.  APPE	ARS MOST OF OIL LOSS OCCURRED WHEN ACCY GRBX SHIFTED, DISCONNECTING EXT OIL PRESS AND RETURN TUBES.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996101000383	19961010	00383	SO  	1996	10	10	96ZZZX5075       	1	19960918	G	3230	WTC22171	SHUTTLE VALVE   			PIPER 	PA42  	PA42        	7104202	SO  										RT MLG ACTUATOR	DAMAGED         	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	15	930CA					428001030				NIPPLE OF VALVE TO MAIN GEAR ACTUATOR BROKE OFF CAUSING LOSS OF FLUID AND FAILURE OF RIGHT GEAR TO DOWNLOCK.						1	L	7	2 	4T				A23SO   					 
1996101000384	19961010	00384	CE  	1996	10	10	96ZZZX5076       	1	19960911	G	2612	302158	FLAME DETECTOR  	PYROTECTOR  		BEECH 	200   	B200        	1152922	CE  										LT ENGINE	MALFUNCTIONED   	B			LX5R	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	19	991LL	6546 			79373	BB1234				LEFT ENGINE FIRE LIGHT CAME ON, SIGNAL VOLTAGE TOO HIGH.  BEECH HAS NEW STYLE FLAME DETECTOR FOR BETTER RELIABILITY.						1	L	7	2 	4T				A24CE   					 
1996101000385	19961010	00385		1996	10	10	96ZZZX5077       	4	19960907	G	2565	60322103	ASPIRATOR       	AIRCRUISERS 		AIRBUS	320   	A320231     	3930325	EU  										EVAC SLIDE	DAMAGED         	A		A	ET3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21					45114					EVACUATION SLIDE DEFECTIVE.  NO MALFUNCTION OCCURRED.  DAMAGE WAS DISCOVERED DURING ROUTINE OVERHAUL.  SUSPECT CAUSE:  I	MPROPER PACKING PROCEDURES CAUSING BOTH ASPIRATOR BODIES TO BE DEFORMED. ONE SO BADILY STRESSED, A WELD WAS BROKEN.  REC	OMMENDATION:  ENSURE PROPER PACKING PROCEDURES ARE FOLLOWED.  VISUALLY INSPECT ASPIRATORS AFTER PACKING.  DISTORTION CAN	 BE FOUND BY LOOKING INSIDE WITH LIGHT.			2	L	7	2 	4F			RT	A28NM   					 
1996101000386	19961010	00386	NM  	1996	10	10	96ZZZX5078       	1	19960916	G	2782	1103044	BODY ASSY       		1U11032     	BOEING	727   	727         	1384001	NM  										SLAT ACTUATOR	CHROME FLAKE    	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			175  							ACTUATOR CHROME FLAKING FROM INSIDE MAIN CYLINDER BORE/POOR ADHESION UPON RECHROME.						2	L	7	3 	4F				A3WE    					 
1996101000387	19961010	00387	NE  	1996	10	10	96ZZZX5079       	2	19960827	G	7210	7757582	BEARING         	HAMSTD      	7757582     	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GEARCASE	SPALLED         	B	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		11502			8137		GEE785540			DISASSEMBLY OF GEARCASE REVEALED THE AFT ROLLER BEARING ASSEMBLY SHOWED HEAVY SPALLING OF ALL BEARING COMPONENTS (775758	-2) (ITEM 10, FIG 7, AND ITEM 110, FIG 8 IPL).					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1996101000388	19961010	00388	NE  	1996	10	10	96ZZZX5080       	2	19960916	G	7210	7757651	ROLLER BEARING  	HAMSTD      	7758001     	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GEARCASE	CAGE BROKEN     	A		A	SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13095			5237		GEE367358			DISASSEMBLY OF GEARCASE REVEALED THE FORWARD INPUT ROLLER BEARING CAGE WAS BROKEN (775765-1, FIG 5, ITEM 180 OF 72-11-02	 PARTS LIST).  ALSO,THE INPUT PINION GEAR HAS STARTED TO HAVE SEVERE TOOTH BREAK DOWN (775755-3, FIG 3, ITEM 1558).  BOT	H IDLER GEARS ALSO HAD TOOTH WEAR.  LT IDLER SN 1C6411358A (775753-5, FIG 8-40B).  RT IDLER SN 1C64411268A (775754-5, FI	G 8-75B).`			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1996101000389	19961010	00389	NM  	1996	10	10	96ZZZX5081       	1	19960725	G	3610	797839	VALVE SHAFT     	HAMSTD      	77385618    	BOEING	747   	747*        		NM  										PRESS CK VLV	WORN            	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					830716					ANTI-ROTATION SLOTS ARE WORN AWAY ON VALVE SHAFT CAUSING SHAFT TO ROTATE AND SHAFT SHOULDER TO WEAR EXCESSIVELY.  REF: O	HM 36-12-06, PAGE 606, FIGURE 603.					2	L	7	4 	4F			RT	A20WE   					 
1996101000390	19961010	00390	NM  	1996	10	10	96ZZZX5082       	1	19960725	G	3610	797839	VALVE SHAFT     	HAMSTD      	77385618    	BOEING	747   	747*        		NM  										PRESS CHK VLV	WORN            	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					830913					ANTI-ROTATION SLOTS ARE WORN AWAY ON VALVE SHAFT CAUSING SHAFT TO ROTATE AND SHAFT SHOULDER TO WEAR EXCESSIVELY.  REF: O	HM 36-12-06, PAGE 606, FIGURE 603.					2	L	7	4 	4F			RT	A20WE   					 
1996101000391	19961010	00391	SO  	1996	10	10	96ZZZX5083       	1	19960916	G	3710	MILH6000	HOSE            			PIPER 	PA34  	PA34200T    	7103406	SO  										LOW PRESS PNEU	DEFECTIVE       	B			APCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01										PURSUANT TO BEECHCRAFT SAFETY COMMUNIQUE DATED 8, 1996,AIRCRAFT AND PARTS INVENTORY ARE BEING INSPECTED FOR BAD HOSE STO	CK WITH DATE CODE AS  LISTED IN COMMUNIQUE.  TEN FEET OF THIS HOSE FOUND IN STOCK INVENTORY.  SUGGEST AD NOTE ON HOSE. A	S MANY AIRCRAFT OTHER THAN BEECH/RAYTHEON MAY BE AFFECTED DUE TO COMMON HOSE USAGE.				1	L	7	2 	3O				A7SO    					 
1996101000392	19961010	00392	GL  	1996	10	10	96ZZZX5084       	2	19960911	G	7313	5233414	FILTER ASSY     		6890917     	HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL NOZZLE	CRUSHED         	E				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	23	577DB		296  		AG45257	0381E	CAE836296			PILOT EXPERIENCED N2 DROOP ON TAKEOFF WITH SLOW RECOVERY.  CONDITION WORSENED DURING TROUBLESHOOTING UNTIL ENGINE WOULD 	NOT ACHIEVE IDLE SPEED.  FUEL NOZZLE REMOVED AND DISASSEMBLED.  FILTER ELEMENT FOUND CRUSHED AND TWISTED, RESTRICTING FU	EL FLOW AT SPEEDS ABOVE IDLE SPEED.  NO FUEL CONTAMINATION EVIDENT IN AIRFRAME FILTER OR FCU FILTER.  IT IS POSSIBLE FIL	TER ELEMENT WAS CRUSHED AT TIME OF OVERHAUL AND IS NOT A REGULAR INSP ITEM EXCEPT FOR CLEANING.  SUBMITTER RECOMMENDS FI	LTER BE INSP AT 100-HOUR INTERVALS PAYING ATTN TO SEATING FILTER ELEMENT BEFORE FURTHER ASSY IAW MDHC/ACT MM AND INSPECT	 ANY NOZZELS IN STOCK OR UPON RECEIVING FROM O/H FOR THIS CONDITION.	1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996101000395	19961010	00395		1996	10	10	96ZZZX5087       	4	19960901	G	3421	KG258	GYRO            	KING        																COCKPIT HORIZ	MISMODIFIED     	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99					9437					GYRO MODIFIED FORM ZERO DEGREES TILT PANEL TO 8 DEGREES TILT PANEL.  TALKED TO KING.  THIS IS NOT AN AUTHORIZED MOD PART	 NUMBER AND DECAL CHANGED.  INDICATOR OUT OF TOLERANCE.																		 
1996101000396	19961010	00396	CE  	1996	10	10	96ZZZX5088       	1	19960706	G	2612	302158	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  										RT ENGINE	MOISTURE CONTAM 	E				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			WP	23	12NG	7086 				BB581				AIRCRAFT DEPARTED WARNER ROBBINS AFB IN LIGHT RAIN SHOWERS.  AS ACFT BROKE THREW OVERCAST LAYER, RT ENG FIRE WARNING LIG	HT ILLUMINATED.  FLIGHT CREW MONITORED ENG PARAMETERS AND ENG COWLING.  NO ABNORMAL CONDITIONS NOTED.  CHECK LIST REVIEW	ED AND ACFT RETURNED TO WARNER ROBBINS AFB, UNEVENFUL LANDING MADE.  ACFT TURNED OVER TO MAINTENANCE.  INSP FOUND MOISTU	RE CONTAMINATION OF THE UPPER AFT.  FIRE DETECTOR, PIN 30-215-8.  NECESSARY REPAIRS MADE AND ACFT RETURNED FOR SERVICE. 	 SUBMITTER SUGGESTS MFG IMPROVE SEALING METHOD OF WIRING TO DETECTOR.		1	L	7	2 	4T				A24CE   					 
1996101000456	19961010	00456	CE  	1996	10	10	96ZZZX5099       	1	19960910	G	3260	1SE13	SWITCH          			CESSNA	340   	340A        	2076405	CE  										RT MLG DOWNLOCK	FAILED          	D				L				ABORTED APPROACH        				P			NO WARNING INDICATION     			AP	APPROACH       	1			EA	03	1232K	4015 				340A1815				UPON LANDING, THE GEAR WAS EXTENDED AND NO RIGHT MAIN INDICATION WAS NOTED THAT IT WAS DOWN AND LOCKED.  AFTER A FLY-BY 	THE TOWER, THE GEAR WAS DETERMINED TO BE DOWN.  THE AIRCRAFT WAS LANDED SAFELY.  PART FAILED DUE TO AGE.					1	L	7	2 	3O				3A25    					 
1996101000457	19961010	00457	CE  	1996	10	10	96ZZZX5100       	1	19960917	G	3231	35815125602	RETRACT ROD     			BEECH 	35    	V35B        	1151548	CE  										LT MLG	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	2021E	1586 				D10158				BEARING SUPPORT IN INBOARD END OF RETRACT ROD FOUND LOOSE.  ROD REPLACED WITH NEW PART FROM BEECH.  SUBMITTER STATED THI	S IS THE SECOND AIRCRAFT OF THIS TYPE TO HAVE THE SAME DEFECT IN TWO MONTHS.					1	L	7	1 	3O				3A15    					 
1996101000458	19961010	00458	CE  	1996	10	10	96ZZZX5101       	1	19960917	G	3251		STEERING CAP    			BEECH 	35    	V35B        	1151548	CE  										NLG	BOLTS LOOSE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	2021E	1586 				D10158				BOLTS IN NOSE GAR STEERING CAP FOUND LOOSE.  SUBMITTER STATED THIS IS THE SECOND AIRCRAFT OF THIS TYPE TO HAVE THIS DEFE	CT IN TWO MONTHS.					1	L	7	1 	3O				3A15    					 
1996101000459	19961010	00459	CE  	1996	10	10	96ZZZX5102       	1	19960923	G	5510	17320312	BRACKET         			CESSNA	177   	177RG       	2073709	CE  										STAB AFT WT ARM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	2023Q	3417 				177RG0423				DURING ANNUAL INSPECTION, CRACKS WERE NOTED ON (3 OF THE 4) STABILATOR WEIGHT ARM MOUNT BRACKETS.  CAUSE, NORMAL WEAR AN	D VIBRATION.  SUBMITTER RECOMMMENDS CLOSER INSPECTION AND DYE CHECK.  ALSO INCLUDES FORWARD MOUNT P/N 1732010-1 AND DASH	 2.				1	H	7	1 	3O				A20CE   					 
1996101000460	19961010	00460	CE  	1996	10	10	96ZZZX5103       	1	19960923	G	5510	17320311	BRACKET         			CESSNA	177   	177RG       	2073709	CE  										STAB AFT WT ARM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	2023Q	3417 				177RG0423				DURING ANNUAL INSPECTION, CRACKS WERE NOTED ON (3 OF THE 4) STABILATOR WEIGHT ARM MOUNT BRACKETS.  CAUSE, NORMAL WEAR AN	D VIBRATION.  SUBMITTER RECOMMMENDS CLOSER INSPECTION AND DYE CHECK.  ALSO INCLUDES FORWARD MOUNT P/N 1732010-1 AND DASH	 2.				1	H	7	1 	3O				A20CE   					 
1996101000461	19961010	00461	SO  	1996	10	10	96ZZZX5104       	1	19960604	G	5751	86396803	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										RT AILERON LE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2199Z	5100 				447995297				DURING A ROUTINE INSPECTION (100 HOUR), EXCESSIVE LATERIAL PLAY WAS DISCOVERED AT RT AILERON TO THE POINT OF CONTACTING 	WING TIP.  FURTHER INVESIGATION FOUND ALL 3 LEADING EDGE RIBS WHICH SUPPORT THE HINGES CRACKED.  THESE RIBS ARE DIFFICUL	T TO INSPECT DUE TO THE LEADING EDGE SKIN COVERING THE AREA AND NO INSPECTION PANELS ARE AVAILABLE.  ALL 5,100 HOURS IN 	SERVICE WERE FLIGHT TRAINING.			1	L	7	2 	3O				A19S0   					 
1996101000462	19961010	00462	SO  	1996	10	10	96ZZZX5105       	1	19960604	G	5751	86398803	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										RT AILERON LE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2199Z	5100 				447995297				DURING A ROUTINE INSPECTION (100 HOUR), EXCESSIVE LATERIAL PLAY WAS DISCOVERED AT RT AILERON TO THE POINT OF CONTACTING 	WING TIP.  FURTHER INVESIGATION FOUND ALL 3 LEADING EDGE RIBS WHICH SUPPORT THE HINGES CRACKED.  THESE RIBS ARE DIFFICUL	T TO INSPECT DUE TO THE LEADING EDGE SKIN COVERING THE AREA AND NO INSPECTION PANELS ARE AVAILABLE.  ALL 5,100 HOURS IN 	SERVICE WERE FLIGHT TRAINING.			1	L	7	2 	3O				A19S0   					 
1996101000463	19961010	00463	SO  	1996	10	10	96ZZZX5106       	1	19960604	G	5751	86399803	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										RT AILERON LE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2199Z	5100 				447995297				DURING A ROUTINE INSPECTION (100 HOUR), EXCESSIVE LATERIAL PLAY WAS DISCOVERED AT RT AILERON TO THE POINT OF CONTACTING 	WING TIP.  FURTHER INVESIGATION FOUND ALL 3 LEADING EDGE RIBS WHICH SUPPORT THE HINGES CRACKED.  THESE RIBS ARE DIFFICUL	T TO INSPECT DUE TO THE LEADING EDGE SKIN COVERING THE AREA AND NO INSPECTION PANELS ARE AVAILABLE.  ALL 5,100 HOURS IN 	SERVICE WERE FLIGHT TRAINING.			1	L	7	2 	3O				A19S0   					 
1996101000464	19961010	00464	EU  	1996	10	10	96ZZZX5107       	1	19960719	G	2701	TB1023012100	SUPPORT         			SOCATA	TB9   	TB9         	8680694	EU  										YOKE LT/RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	28216	2885 				1063				DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT 	FLANGE OF SUPPORT.  THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE	 TO SEVERED.  THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL.  CORRECTIVE ACTION CONSISTS	 OF REPLACING LT AND RT SUPPORTS WITH NEW UNITS.  IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRIN	G OF LOADS FROM THE CONTROL LOCK ASSEMBLY.		1	L	7	1 	3O			NT	AS1EU   					 
1996101000465	19961010	00465	EU  	1996	10	10	96ZZZX5108       	1	19960719	G	2701	TB1023012101	SUPPORT         			SOCATA	TB9   	TB9         	8680694	EU  										YOKE LT/RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	28216	2885 				1063				DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT 	FLANGE OF SUPPORT.  THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE	 TO SEVERED.  THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL.  CORRECTIVE ACTION CONSISTS	 OF REPLACING LT AND RT SUPPORTS WITH NEW UNITS.  IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRIN	G OF LOADS FROM THE CONTROL LOCK ASSEMBLY.		1	L	7	1 	3O			NT	AS1EU   					 
1996101000466	19961010	00466	EU  	1996	10	10	96ZZZX5109       	1	19960919	G	2701	TB1023012100	SUPPORT         			SOCATA	TB9   	TB9         	8680694	EU  										YOKE LT/RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	28199	2970 				1062				DURING ROUTINE 100-HOUR INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE 	OF SUPPORT.  THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO SEV	ERED.  THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL.  CORRECTION ACTION CONSISTS OF REP	LACING LT AND RT SUPPORTS WITH NEW UNITS.  IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF LO	ADS FROM THE CONTROL LOCK ASSEMBLY.		1	L	7	1 	3O			NT	AS1EU   					 
1996101000467	19961010	00467	EU  	1996	10	10	96ZZZX5110       	1	19960919	G	2701	TB1023012101	SUPPORT         			SOCATA	TB9   	TB9         	8680694	EU  										YOKE LT/RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	28199	2970 				1062				DURING ROUTINE 100-HOUR INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT FLANGE 	OF SUPPORT.  THE CRACKS WERE QUITE SEVERE, ONE SIDE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO SEV	ERED.  THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL.  CORRECTION ACTION CONSISTS OF REP	LACING LT AND RT SUPPORTS WITH NEW UNITS.  IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF LO	ADS FROM THE CONTROL LOCK ASSEMBLY.		1	L	7	1 	3O			NT	AS1EU   					 
1996101000468	19961010	00468	CE  	1996	10	10	96ZZZX5111       	1	19960810	G	3244	650X10	TIRE            			CESSNA	402   	402C        	207590R	CE  										LT MLG	FLAT            	I				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3249M	196  			B3M6274	402C0296				AFTER COMPLETION OF FLIGHT AT THE GATE, FLIGHT CREW NOTICED LT MAIN TIRE FLAT.  UPON TEAR-DOWN INSPECTION, NOTED WIRE FR	OM SIDE WALL DAMAGED THE TUBE.  TOTAL TIME ON TIRE, 196 HOURS.  MCCRARY 6.50X10, 8-PLY RECAP.					1	L	7	2 	3O				A7CE    					 
1996101000469	19961010	00469	EA  	1996	10	10	96ZZZX5112       	2	19960920	G	8520		LIFTER          			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  					CYL NR 4 LOBE	FAILED          	B			CB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	43125	2243 				287415430	L3796827A			LIFTER FAILED AT NR 4 CYLINDER CAM LOBE.  LOBE DAMAGED AND PEENED ON CAMSHAFT.  CRANKSHAFT PILOT END, BENT OVER LIMITS. 	 FLANGE ON CRANKSHAFT OUT OF LIMITS ON RUN-OUT.  FINDINGS RESULT OF ENGINE, TIME EXPIRED INSPECTION.					1	L	7	1 	3O	3	O		2A13    	E274				 
1996101000470	19961010	00470	CE  	1996	10	10	96ZZZX5113       	1	19960923	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										RT WING CANTED	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	441LL	5923 				4410139				DURING PHASE INSPECTION, FOUND 1.5 INCH CRACK IN RT WING CANTED RIB TOP CAP.  CRACK STARTS AT AFT SIDE OF FORWARD SPAR A	ND RUNS AFT PARALLEL TO THE BEND RADIUS.  STOP DRILL CRACK PER CESSNA INSTRUCTIONS.					1	L	7	2 	3T			RT	A28CE   					 
1996101000471	19961010	00471	SO  	1996	10	10	96ZZZX5114       	2	19960916	G	8530		ROCKER          			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					NR 2 CYL EXH	FAILED          	B			GNER	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SW	01	4930K	333  				P21000372	513389			WHEN AIRCRAFT WAS FLYING, A LOUD BANG WAS HEARD.  MAP WENT FROM 27 INCHES TO 20 INCHES WITH NOTICEABLE LOSS OF POWER AND	 INCREASED VIBRATION.  AIRCRAFT WAS LANDED WITHOUT DAMAGE.  NR 2 ROCKER COVER REMOVED AND BALL JOINT OF EXHAUST ROCKER F	OUND LAYING IN COVER.  LOOKED LIKE PART HAD CRACK IN IT FOR A WHILE AND FINALLY LET GO UNDER STRESS.  SUBMITTER RECOMMEN	DS MAGNAFLUXING PART BEFORE INSTALLATION.			1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996101000472	19961010	00472	EA  	1996	10	10	96ZZZX5115       	2	19960903	G	7310	S1236C30420	HOSE            			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					FLOW DIVIDER	DEFECTIVE       	D		A		A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CL	CLIMB          	1			EA	07	520	299  				177RG1164				PILOT REPORTED A TOTAL DROP IN FUEL PRESSURE DURING CLIMB-OUT LANDING WITHOUT INCIDENT.  UPON INSPECTION, FOUND FUEL PRE	SSURE HOSE FROM FIREWALL TO FLOW DIVIDER LEAKING PROFUSELY WHERE THE RE-USABLE SOCKET THREADS TO HOSE.  THIS HOSE WAS PU	RCHASED FROM CESSNA ON 8-93 AND INSTALLED.  THE METAL IDENTIFICATION BAND HAD AN ASSEMBLY DATE OF 4-85.  RECOMMEND CESSN	A REVIEW THEIR POLICY ON SHELF LIFE OF HOSES WHICH AT PRESENT IS CONTRARY TO THE HOSE MANUFACTURER. SUBMITTER STATED THI	S SITUATION COULD HAVE BEEN CATASTROPHIC.		1	H	7	1 	3O	3	O		A20CE   	1E10				 
1996101000473	19961010	00473	CE  	1996	10	10	96ZZZX5116       	1	19960828	G	3246	D306601	WHEEL           	MCAULY      	AN441A      	CESSNA	150   	A150L       	2071828	CE  										MLG	BOLT SEPARATED  	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	16	6005J	4000 				A1500305				WHEEL BOLT AND NUT SEPARATED POSSIBLY DUE TO WORN THREADS.  BOLT WAS INSERTED FROM BRAKE ROTOR SIDE.  WHEN NUT LEFT BOLT	, BOLT HIT TORQUE LINK AND DEFORMED TORQUE LINK.  IF INSTALLED FROM OUTSIDE OF WHEEL, THIS WOULD NOT OCCUR.  MFG'S DRAWI	NG SHOWS BOLT INSERTED FROM OUTSIDE WITH NUT ON ROTOR SIDE OF WHEEL.				1	H	7	1 	3O				3A19    					 
1996101000475	19961010	00475	CE  	1996	10	10	96ZZZX5118       	1	19960909	G	3230	51412044	SUPPORT         			CESSNA	414   	414A        	2075907	CE  										RT MLG UPLOCK	CRACKED         	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	711HN	2520 				414A0108				SUPPORT CRACKED/SPLIT FROM THE AFT BOLT HOLE TO FORWARD BOLT HOLE AND OUT THE FRONT.  LANDING GEAR UPLOCK HAS MOVED UPWA	RD ALLOWING LANDING GEAR STRUT TO CONTACT UPPER WING SKIN.  WING SKIN DENTED SLIGHTLY OVER MAIN WHEEL AXLE.  SUPPORT IS 	LATE STYLE WITH LARGER BOLTS THAN ORIGINAL.  SUBMITTER STATED HAS SEEN MANY EARLY SUPPORTS FAIL, BUT THIS IS THE FIRST H	EAVY SUPPORT FOUND.			1	L	7	2 	3O				A7CE    					 
1996101000476	19961010	00476	CE  	1996	10	10	96ZZZX5119       	1	19960524	G	2434	DOFF10300B	ALTERNATOR      			CESSNA	206   	U206G       	2073356	CE  										DC SYSTEM	MALFUNCTION     	D				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			WP	07	756HQ		124  			U20604107				PILOT ATTEMPTED START, START SOLENOID CLICKING.  LOW BATTERY OUTPUT TO LOW TO CLOSE SOLENOID.  ALTERNATOR CHECKED FOR CH	ARGING.  ALTERNATOR OUTPUT APPROXIMATELY 19.3 VDC FOR 24 VDC SYSTEM.  ALTERNATOR REPLACED WITH OVERHAULED UNIT.					1	H	7	1 	3O				A4CE    					 
1996101000479	19961010	00479	SO  	1996	10	10	96ZZZX5122       	1	19960829	G	5542		SKIN            			PIPER 	PA32  	PA32R301    	7103218	SO  										TE RUDDER	CRACKED         	B	S		DFKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	8147B	6913 	6913 			32R8013048				THREE CRACKS WERE NOTICED IN SKIN OF RUDDER POSSIBLY DUE TO FATIGUE OVER TIME.  REMOVED SKIN, NO INTERNAL DAMAGE FOUND. 	 NEW SKIN INSTALLED.  CRACK LENGTHS APPROXIMATELY 1 INCH.					1	L	7	1 	3O				A3SO    					 
1996101000480	19961010	00480	SO  	1996	10	10	96ZZZX5123       	1	19960909	G	5751	8639202	FITTING         			PIPER 	PA32  	PA32R301    	7103218	SO  										LT AIL OUTBOARD	LOOSE           	B		A	AMYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	9259V	218  				3246011				DURING A 100-HOUR INSPECTION, NOTICED THE LEFT AILERON WOULD STILL MOVE AFTER STOPS WERE CONTACTED.  THE OUTBOARD ATTACH	 FITTING WAS FOUND LOOSE AND WORKING.  BOTH BOLTS THAT ATTACH THE FITTING TO THE AILERON WERE FOUND LOOSE.  NO TORQUE SE	AL FOUND ON ANY OF THE 4 ATTACH FITTING BOLTS ON EITHER AILERON.  THE OTHER 3 FITTING BOLTS WERE CHECKED AND FOUND PROPE	RLY TORQUED.  TORQUING THE 2 LOOSE BOLTS SOLVED THE PROBLEM.  TORQUE SEAL WAS APPLIED TO ALL 8 BOLT HEADS.  SUBMITTER RE	COMMENDS ALL NEW PIPER AILERON ATTACHMENT FITTINGS BE CHECKED AT THE FIRST SCHEDULED INSPECTION.		1	L	7	1 	3O				A3SO    					 
1996101000844	19961010	00844	SO  	1996	10	10	96ZZZX5124       	1	19960916	G	7120		MOUNT           			PIPER 	PA12  	PA12        	7101202	SO  										LT BOTTOM TUBE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	98922	3485 				12275				AT ANNUAL INSPECTION, BOTTOM LEFT ENGINE MOUNT TUBE WAS FOUND CRACKED AT ENGINE MOUNTING FLANGE.  ENGINE PREVIOUSLY CHAN	GED TO LYC 0320 IN C/W STC SA-4-456.  REINFORCEMENT TUBING HAD NOT BEEN EXTENDED FULL LENGTH ON BOTTOM TUBE.  WELDED LEN	GTH OF .8750 INCH TUBING IN PLACE TO C/W STC DRAWING.				1	H	7	1 	3O				A780    					 
1996101000845	19961010	00845	SW  	1996	10	10	96ZZZX5125       	1	19960917	G	3340		LANDING LIGHT   			MOONEY	M20   	M20J        	5870219	SW  										NR 1 CYL EXH	WIRE CHAFED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	991CC	1745 				241054				AN INSPECTION OF THE LANDING LIGHT CIRCUIT REVEALED THE WIRE FROM THE ENGINE COWL TO THE LIGHT CAME IN CONTACT WITH NR 1	 CYLINDER EXHAUST STACK.  THIS IS A RECURRING PROBLEM.  THERE HAD BEEN A PREVIOUS REPAIR.  THE PROBLEM AREA CAN BE VIEWE	D THROUGH THE RIGHT COWL FLAP OPENING TO OBSERVE EXHAUST PIPE/WIRE CLEARANCE.				1	L	7	1 	3O				2A3     					 
1996101000846	19961010	00846	EA  	1996	10	10	96ZZZX5126       	2	19961002	G	7322	666915	FLOAT           			PIPER 	PA18  	PA18135     	7101820	SO  	LYC   	O290  	O290D2      	41506	EA  					CARBURETOR	FAILED          	D		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	99		261  								AN AIRCRAFT EXPERIENCED TOTAL POWER LOSS DURING A PERSONAL FLIGHT.  AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LANDED WI	THOUT INCIDENT.  INVESTIGATION OF THE ENGINE INCIDENT REVEALED THE FAILURE WAS CAUSED BY A FAULTY METAL FLOAT ON CARBURE	TOR.  THE METAL FLOAT WAS FOUND FULL OF FUEL WHICH CAUSED FLOAT SINKING.  THE METAL FLOAT PN 666-915 HAD BEEN REPLACED F	ROM COMPOSITE TYPE FLOAT ACCORDING TO MANUFACTURE SB MSA-1 AND IT WAS NOT AFFECTED BY THE AD 93-19-04 SB CF 1 92 DUE TO 	DIFFERENT CODE STAMP.		1	H	7	1 	3O	3	O		1A2     	E229				 
1996101000847	19961010	00847	CE  	1996	10	10	96ZZZX5127       	1	19960923	G	2510		CHEST BELT      			CESSNA	150   	152         	2071835	CE  										COCKPIT	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13										SUBMITTER STATED IF THE CHEST BELT IS MANDATORY, IT SHOULD BE FUNCTIONAL AND RELIABLE.  IT IS NOT.  SOMEONE EVEN PUT A T	IE WRAP ON THE SEAT BELT CLIP POST.  IT KEEPS THE CHEST BELT ATTACHED A WHILE LONGER, BUT IT IS NOT A RELIABLE CLIP.					1	H	7	1 	3O			NT	3A19    					 
1996101000848	19961010	00848	CE  	1996	10	10	96ZZZX5128       	1	19960913	G	5520	04320031	BUSHING         			CESSNA	150   	150L        	2071826	CE  										ELEV RT OTBD	FAILED          	G	P	A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CE	07	18132	7706 				15073810				ELEVATOR BROKE LOOSE FROM THE OUTBOARD HINGE BOLT.  THE REMAINING INBOARD BRACKET BROKE OUT OF THE SPAR.						1	H	7	1 	3O				3A19    					 
1996101000849	19961010	00849	CE  	1996	10	10	96ZZZX5129       	1	19960913	G	5520	043200124	HINGE HALF      		043200152   	CESSNA	150   	150L        	2071826	CE  										ELEV RT OTBD	FAILED          	G		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CE	07	18132	7706 				15073810				ELEVATOR BROKE LOOSE FROM THE OUTBOARD HINGE BOLT.  THE REMAINING INBOARD BRACKET BROKE OUT OF THE SPAR.						1	H	7	1 	3O				3A19    					 
1996101000850	19961010	00850	EA  	1996	10	10	96ZZZX5130       	2	19960828	G	7310	LW120980100	LINE            			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					NR 3 FUEL INJ	FAILED          	D	L			K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			GL	21	39603	1767 				32R7887119	1554961A			AIRCRAFT OPERATOR REPORTED ROUGH RUNNING ENGINE.  OWNER REMOVED TOP COWL AND FOUND NR 3 FUEL INJECTION LINE COMPLETELY B	ROKEN OFF AT AND JUST BEHIND WHERE NUT AND FITTING ARE WELDED TO LINE.  FURTHER INSPECTION REVEALED NR 4 CYLINDER OIL RE	TURN TUBE CHAFED THROUGH BY FUEL INJECTION LINE AT THIS AREA (VIBRATING).  OIL RETURN LINE AND FUEL INJECTION LINE BOTH 	REPLACED WITH NEW PARTS.  FUEL INJECTION T-FITTING ON 2ND, 4TH, AND 6TH BANK OF CYLINDERS WAS FOUND LOOSE AT THIS TIME A	ND RESECURED.		1	L	7	1 	3O	3	O		A3SO    	E14EA				 
1996101000851	19961010	00851	SO  	1996	10	10	96ZZZX5131       	1	19960923	G	5711		SPAR            			PIPER 	PA28  	PA28180     	7102808	SO  										LT/RT WING	CORRODED        	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5349L					284652				DURING FUEL TANK REMOVAL FOR DETERIORATED HOSE REPLACEMENT, FOUND CORROSION ON WING SPAR.						1	L	7	1 	3O				2A13    					 
1996101000852	19961010	00852	EU  	1996	10	10	96ZZZX5132       	1	19960719	G	2701	TB1023012100	SUPPORT         			SOCATA	TB9   	TB9         	8680694	EU  										YOKE LT/RT	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	55372	3470 				1188				DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FORMS AFT 	FLANGE OF SUPPORT.  THE CRACKS WERE QUITE SEVERE, ONE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO S	EVERED.  THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL.  CORRECTIVE ACTION CONSISTS OF R	EPLACING LT AND RT SUPPORTS WITH NEW UNITS.  IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF 	LOADS FROM THE CONTROL LOCK ASSEMBLY.		1	L	7	1 	3O			NT	AS1EU   					 
1996101000853	19961010	00853	EU  	1996	10	10	96ZZZX5133       	1	19960719	G	2701	TB1023012101	SUPPORT         			SOCATA	TB9   	TB9         	8680694	EU  										YOKE LT/RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	55372	3470 				1188				DURING ROUTINE 100-HOUR ANNUAL INSPECTION, FOUND BOTH RT AND LT YOKE SUPPORTS CRACKED IN RADIUS OF BEND WHICH FROMS AFT 	FLANGE OF SUPPORT.  THE CRACKS WERE QUITE SEVERE, ONE BEING COMPLETELY SEVERED, AND THE OTHER SIDE BEING VERY CLOSE TO S	EVERED.  THE CRACKS ARE IMPOSSIBLE TO SEE WITHOUT TILTING THE PILOT'S INSTRUMENT PANEL.  CORRECTIVE ACTION CONSISTS OF R	EPLACING LT AND RT SUPPORTS WITH NEW UNITS.  IT IS THE SUBMITTER'S OPINION THIS DAMAGE IS CAUSED BY THE TRANSFERRING OF 	LOADS FROM THE CONTROL LOCK ASSEMBLY.		1	L	7	1 	3O			NT	AS1EU   					 
1996101000854	19961010	00854	CE  	1996	10	10	96ZZZX5134       	1	19960911	G	7820	125025116R	MUFFLER         			CESSNA	206   	U206G       	2073356	CE  										BAFFLE	CONE MISSING    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	05	206PB	230  				U20603781				ON AN ANNUAL INSPECTION, FOUND CONE BAFFLE 'INTERNAL PART MISSING' ON LT MUFFLER.  THIS UNIT WAS OVERHAULED AT 230 HOURS	 PREVIOUSLY AND WAS INSTALLATED 2 YEARS PREV ANNUAL.					1	H	7	1 	3O				A4CE    					 
1996101000855	19961010	00855	GL  	1996	10	10	96ZZZX5135       	1	19960924	G	5540		RUDDER          			AMTR  	GAIR  	GLASAIRIII  	05691HK	GL  										TRAILING EDGE	CONCAVE         	D				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			GL	13	231YE	26   				5192				AT APPROXIMATELY 120 MPH, THE RUDDER WOULD 'WALK' BECOMING MORE VIOLENT AS THE SPEED INCREASED.  AN INSPECTION OF THE RU	DDER FOUND THE RUDDER SKIN WAS SLIGHTLY CONCAVE.  THE RUDDER WAS REMOVED AND THE TRAILING EDGE WAS 'SQUEEZED' IN A PRESS	URE BRAKE.  THIS ELIMINATED THE CONCAVE SHAPE.  A FLIGHT TEST UP TO 150 MPH DETERMINED THE PROBLEM NO LONGER EXISTS.  NO	TE:  THE CONSTRUCTION MANUAL CALLS FOR INSPECTING FOR THIS CONDITION AND DETAILS THE CORRECTIVE PROCEDURE.			1	L	7	1 	3O			RT	EXPA1L71					 
1996101000856	19961010	00856	SW  	1996	10	10	96ZZZX5136       	1	19960903	G	3230	102053	CLUTCH SPRING   		1020001     	MOONEY	M20   	M20K        	5870220	SW  										LT MLG ACTUATOR	FAILED          	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	16	32DG	1426 				251126				NO-BACK CLUTCH SPRING TANG BROKE OFF AND JAMMED EMERGENCY EXTENSION SYSTEM COMPLETELY.  THIS PART IS SUBJECT OF MOONEY S	I M20-52A DATED 10-25-94, RECOMMENDING CHANGE AT 1,000 HOURS.  SUBMITTER STATED THIS SHOULD BE AN AD.  OPERATOR SUCCESSF	ULLY EXTENDED GEAR AFTER CIRCUIT BREAKER TRIPPED BY RESETTING BREAKER SEVERAL TIMES.  (DISCOVERED DURING INSPECTION AFTE	R SWITCH REPAIR).			1	L	7	1 	3O				2A3     					 
1996101000859	19961010	00859	SO  	1996	10	10	96ZZZX5139       	2	19960910	G	8530	649543A3	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					EXH VALVE GUIDE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	704LY	547  				15078707	255111A48			TCM CYLINDER KITS (2) PN 649543A3, 547 HOURS SINCE NEW, EXHAUST VALVE GUIDES WORE OUT (VALVE SWIMS IN GUIDES).  SUSPECT 	CAUSE - GUIDES MADE OF POOR MATERIAL.  RECOMMENDATION - BETTER QUALITY CONTROL BY TCM.					1	H	7	1 	3O	3	O		3A19    	E252				 
1996101000860	19961010	00860	EU  	1996	10	10	96ZZZX5140       	2	19960913	G	8530	924540	EQUALIZER TUBE  			DIAMON	DA20A1	DA20A1      	05626UX	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					MANIFOLD PRESS	BLOCKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	854DF	17   				10181	4412618			FOUND EQUALIZER TUBE BLOCKAGE AT SMALL HOLE WHERE MANIFOLD PRESSURE LINE CONNECTS.  BLOCKED BY CONTAMINATES PERHAPS DUE 	TO MANUFACTURING.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
1996101000861	19961010	00861	NE  	1996	10	10	96ZZZX5141       	2	19960923	G	7240	97861798P02	SCREW           								GE    	CFM56 	CFM563B1    	13802	NE  					COMBUSTION SECT	FAILED          	B	L		LY2R	C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CE	07		10390					724982			ABORTED TAKEOFF DUE TO HIGH EGT.  INVESIGATION FOUND DAMAGE TO HPTR BLADES.  FOUND COMBUSTION SECTION SCREWS HAD BEEN RE	USED AND FAILED.  MANUAL CALLS FOR CENTER PUNCHING SCREW LEAKS TO AID IN REMOVAL OF THE SCREW.  MANUAL CALLS FOR SCREWS 	TO BE DISCARDED AFTER REMOVAL.  IN THIS CASE TWO SCREWS WERE REINSTALLED.									4	F			E2GL				 
1996101000862	19961010	00862	CE  	1996	10	10	96ZZZX5142       	1	19960923	G	2730	265522077	CONTROL CABLE   			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV CONT	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	305NT	13237				28266				LOWER AFT ELEVATOR CONTROL CABLE, FS 388 TO FS 457, SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF THE FI	BERGLASS PROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390.  CABLES ARE VISUALLY INSPECTED AT 150-HOUR INTERVAL	S.  CABLES ARE MANUFACTURED OF CARBON STEEL .3125 INCH IN DIAMETER WITH 10 STRANDS PRIOR TO REMOVAL.  'NO' BROKEN WIRES 	OR STRANDS WERE NOTED 'SMOOTH' SURFACE.  REMOVED CABLE FOR FURTHER INSPECTION, FLEXED CABLE IN A MILD 'U' AND 15 WIRES I	N DIFFERENT STRANDS IN A 1 INCH AREA BROKE WITH SEVERE INNER CORROSION.  NOTE:  CORROSION COULD BE OVERLOOKED DUE TO SMA	LL SURFACE AREA EFFECTED.  REMOVED CABLE FROM SERVICE.	2	L	7	2 	4J			 	A2WE    					 
1996101000863	19961010	00863	EA  	1996	10	10	96ZZZX5143       	1	19960912	G	3231	600861165	UNLOCK LEVER    			CNDAIR	CL600 	CL6002B16   	1900305	EA  										NLG DOOR	STUCK           	B	L		QU2R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	17	307FX	600  	600  			5179				ACFT DEPARTED AFTER A 300 HR/600 HR INSPECTION .  CREW SELECTED 'GEAR UP' AND HAD A RED LIGHT.  CREW SELECTED 'GEAR DOWN	'.  HAD 3 GREEN ON MAIN GEAR.  ACFT LANDED WITHOUT INCIDENT.  JACKED ACFT, FOUND NLG DOOR UNLO CK LEVER STUCK IN AN 'INT	ERMEDIATE' UP POSITION CAUSING RT NLG DOOR TO NOT GO FULLY CLOSED.  CHECKED RIGGING OF MANUAL RELEASE CABLE TO NLG DOOR 	UNLOCK LEVER.  FOUND LEVER WOULD NOT RETURN TO FULL DOWN POSITION WHICH IS SLIGHTLY OFF A STOP.  LUBED NLG DOOR UNLOCK L	EVER PIVOT POINT AND 'FREED UP' LEVER.  SPRINGS ATTACHED TO LEVER RETURNED IT TO PROPER POSITION.  PERFORMED GEAR RETRAC	T AND EXT CKS.  ACFT RETURNED TO SERVICE.	2	L	7	2 	4F			RT	A21EA   					 
1996101000864	19961010	00864	CE  	1996	10	10	96ZZZX5144       	1	19960924	G	2730	265522077	CONTROL CABLE   			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV CONT	BROKEN          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	312NT	10001				28232				LOWER AFT ELEVATOR CONTROL CABLE FS 388 TO FS 457, SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF FIBERGL	ASS PROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390.  CABLES ARE VISUALLY INSPECTED AT 150-HR INTERVALS.  CAB	LES ARE MANUFACTURED OF CARBON STEEL .3125 INCH IN DIAMETER WITH 10 STRANDS.  PRIOR TO REMOVAL 'NO' BROKEN WIRES OR STRA	NDS NOTED 'SMOOTH' SURFACE.  REMOVED CABLE FOR FURTHER INSPECTION.  FLEXED CABLE IN A MILD 'U' AND 13 BROKEN WIRES IN DI	FFERENT STRANDS BROKE IN A  1 INCH AREA WITH SEVERE INNER CORROSION.  NOTE:  CORROSION COULD BE OVERLOOKED DUE TO SMALL 	SURFACE AREA EFFECTED.  REMOVED CABLE FROM SERVICE.	2	L	7	2 	4J			 	A2WE    					 
1996101000865	19961010	00865	CE  	1996	10	10	96ZZZX5145       	1	19960923	G	2730	265522077	CONTROL CABLE   			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV CONT	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	316NT					28260				LOWER AFT ELEVATOR CONTROL CABLE FS 388 TO FS 457, SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF FIBERGL	ASS PROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390.  CABLES ARE VISUALLY INSPECTED AT 150-HR INTERVALS.  CAB	LES ARE MANUFACTURED OF CARBON STEEL .3125 INCH IN DIAMETER WITH 10 STRANDS.  PRIOR TO REMOVAL 'NO' BROKEN WIRES OR STRA	NDS NOTED 'SMOOTH' SURFACE.  REMOVED CABLE FOR FURTHER INSPECTION.  FLEXED CABLE IN A MILD 'U' AND 1 COMPLETE BROKEN STR	AND AND 10 DIFFERENT WIRES IN DIFFERENT STRANDS IN A 1 INCH AREA BROKE WITH SEVERE INNER CORROSION.  NOTE:  CORROSION CO	ULD BE OVERLOOKED DUE TO SMALL SURFACE AREA EFFECTED.  REMOVED CABLE FROM SERVICE.	2	L	7	2 	4J			 	A2WE    					 
1996101000867	19961010	00867	CE  	1996	10	10	96ZZZX5147       	1	19960829	G	3222		PISTON TUBE     		62420106    	CESSNA	650   	650         	2076802	CE  										NLG STRUT	DISCONNECTED    	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	11	40N	1036 			039	6507031				NOSE GEAR PISTON-TUBE DISCONNECTED FROM UPPER BARREL.  LOCKING ASSY, PN 6242124-1, BACKED OFF FROM PISTON TUBE, PN 62421	22-2.  THE AFT TORQUE LINK WAS THE ONLY THING WHICH PREVENTED THE PISTON TUBE, WHEEL FORK, AND NOSE WHEEL FROM SEPARATIN	G FROM AIRCRAFT.  LOCKING ASSY, PN 6242124-1, IS SECURED TO PISTON ASSY, PN 6242122-2, WITH 150 INCH/POUNDS OF TORQUE AN	D LOCTITE 609.  NO  MEANS OF SAFETYING.  TORQUE LINKS WERE ALSO BENT AND HAD TO BE REPLACED.			2	L	7	2 	4F				A9NM    					 
1996101000868	19961010	00868	CE  	1996	10	10	96ZZZX5148       	1	19960904	G	3240	244537	CARRIER         		99141362    	CESSNA	650   	650         	2076802	CE  										NR 1 BRAKE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	40N	1036 				6507031				NR 1 BRAKE MAKES NOISES WHILE TOWING AIRCRAFT. FOUND FIRST CARRIER AND LINING ASSY BROKEN IN THREE PIECES.  BRAKE ASSY P	N 2-15-02 B. F. GOODRICH.  AIRCRAFT TOTAL TIME:  1,036.9 HOURS.  753 LANDINGS.					2	L	7	2 	4F				A9NM    					 
1996101000869	19961010	00869	CE  	1996	10	10	96ZZZX5149       	1	19960911	G	3230	12838002117	CONTROL CABLE   			BEECH 	MU300 	400A        	1155402	CE  										RT MLG EMERG	FRAYED          	B			ERYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	401EE	731  				RK6				RIGHT LANDING GEAR UPLOCK EMERGENCY RELEASE CABLE FOUND KINKED AND FRAYED AT UPLOCK RELEASE MECHANISM.  EXCESS SLACK IN 	CABLE MAY ALLOW CABLE END TO BEND IN EXCESS OF 90 DEGREES KINKING CABLE AND CREATING 'MEMORY' TO CAUSE CABLE TO REPEAT T	HIS MOTION EVERY TIME LANDING GEAR IS CYCLED.  FAILURE OF CABLE WILL PREVENT RIGHT MAIN GEAR FROM EXTENDING USING EMERGE	NCY PROCEDURES.  SUBMITTER STATED A THICKER CABLE OR A 360 DEGREE CABLE GUIDE MAY PREVENT RECURRENCE.  FOUND DEFECT DURI	NG A/B INSPECTION.  IN THIS SHOP, HAVE FOUND AT LEAST 2 COMPLETE FAILURES (CABLE BROKEN) PREVIOUSLY.  REF:  400A ILLUST 	PARTS CAT. 32-30-32, ITEM NR 95.	2	H	7	2 	4F			RT	A16SW   					 
1996101000870	19961010	00870	CE  	1996	10	10	96ZZZX5150       	1	19960920	G	2150	24540200	COUPLING        	HAMSTD      		CESSNA	500   	550         	2076604	CE  										ACM	OVERTORQUE      	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5314J	2339 	2339 			5500663				WHILE PERFORMING MAINTENANCE TO ACM, COUPLING (V-BAND CLAMP) WAS FOUND SEVERELY OVERTORQUED ALMOST TO THE POINT OF FAILU	RE.  CLAMP WAS REPLACED USING CORRECT TORQUE, OPS CHECK GOOD.  SUBMITTER RECOMMENDS MAINTENANCE PERSONNEL ADHERE TO PROP	ER CLAMP TORQUE PROCEDURES ESPECIALLY CLAMPS USED ON EXHAUST SYSTEMS.  THIS CLAMP WAS USED ON A PRESSURIZATION DUCT AND 	COULD HAVE CAUSED PRESSURE LOSS HAD IT FAILED.			1	L	7	2 	4F				A22CE   					 
1996101000871	19961010	00871	EU  	1996	10	10	96ZZZX5151       	1	19960807	G	2720		ACTUATOR        			AIRBUS	300   	A300B4622R  		EU  										RUDDER	MALFUNCTIONED   	D				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	99	88881					743				HKG/TPE - FLT CI-618 - AUGUST 7, 1996, RUDDER TRAVEL SYSTEMS 1 AND 2 FAULT.  RUDDER TRAVEL ACTUATOR CHANGED.  ARTF FEEL 	LIMITING COMPUTER CHANGE.  309CY1 AND 309CY2 RELAY CHANGE.  FUNCTIONAL TEST OK PER A300-600R AMM 27-23-00.					2	L	7	2 	4F			RT	A35EU   					 
1996101000872	19961010	00872	EU  	1996	10	10	96ZZZX5152       	1	19960910	G	3244	181K632	TIRE            	GOODYEARAERO		BRAERO	DH125 	BAE125800A  	1500285	EU  										TIRE BALANCE	PATCH LOOSE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	195KC				61020501	NA0455				BALANCE PATCH CAME OPFF AFTER 97 LANDINGS.   THIS IS SECOND TIME HAVE HAD PROBLEMS WITH THIS PART NUMBERED TIRE IN 6 MON	THS.  LAST TIRE HAD EXCESSIVE SIDE WALL VENTING (ALSO AT 97 LANDINGS).					2	L	7	2 	4F			RT	A3EU    					 
1996101000873	19961010	00873	NM  	1996	10	10	96ZZZX5153       	1	19960905	G	2742		BEARING         		12970008    	BOEING	727   	727         	1384001	NM  										CLUTCH	LEAKING GREASE  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										STAB ACTUATOR CLUTCH BEARINGS MIGRATE SMALL AMOUNT OF GREASE THAT COATS THE SLIP RING AND BRUSHES REDUCING D.C. CURRENT 	TO THE CLUTCHES EFFECTING THE UNITS OUTPUT TORQUE.					2	L	7	3 	4F				A3WE    					 
1996101000874	19961010	00874	WP  	1996	10	10	96ZZZX5154       	1	19960912	G	5320	6224415	BALLAST WEIGHT  			HILLER	UH12  	UH12E       	4360122	WP  										TAIL BOOM	DISLODGED       	B	L	A	BHHR	A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	156HA	6068 	6068 			HA3056				ON SEPTEMBER 12, 1996, A HILLER MODEL UH-12 ET OPERATED BY SUMMIT HELICOPTERS CRASHED, COMPLETELY DESTROYING THE HELICOP	TER AND SERIOUSLY INJURING THE PILOT.  THE CAUSE OF THE CRASH WAS BALLAST WEIGHT P/N 62244-15 MADE CONTACT WITH TAIL ROT	OR BLADES CAUSING LOSS OF TAIL ROTOR ASSEMBLY AND TAIL ROTOR GEARBOX.  INVESTIGATION DETERMINED ONE OF THE QUICK RELEASE	 PINS PART NUMBER NAS 1334A2825 THAT HOLD THE BALLAST WEIGHT IN PLACE DISLODGED FROM BALLAST MOUNTING STUD CAUSING STUD 	TO TURN IN TAIL BOOM AND BALLAST WEIGHT TO CONTACT TAIL ROTOR SYSTEM CAUSING LOSS OF DIRECTIONAL CONTROL WHICH RESULTED 	IN THE HELICOPTER CRASHING INTO THE TREES.	1	G	7	1 	3O				4H11    					 
1996101000879	19961010	00879	WP  	1996	10	10	96ZZZX5159       	1	19960926	G	6320	369F5100503	TRANSMISSION    			HUGHES	369   	369E        	4470707	WP  										M/R	NOISE/LEAK      	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	21	911RP	100  			0055700001	526E				DURING 3,000-HOUR OVERHAUL TIME, FOUND NOISE AND WHINE IN TRANSMISSION AND LEAK ING INPUT SEAL.  COMPLETE REPLACEMENT OF	 TRANSMISSION.					1	G	7	1 	3U				H3WE    					 
1996101000880	19961010	00880	WP  	1996	10	10	96ZZZX5160       	1	19960926	G	6310	369F54501	HOUSING         			HUGHES	369   	369E        	4470707	WP  										OVERRUN CLUTCH	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	911RP	93   			0099990011	526E				FACTORY RECALL OF OVERRUN CLUTCH, P/N 369F5453-1.  SUSPECT CRACK IN P/N 369F5450-1.  PART FOUND CRACKED.  SUSPECT REASON	 OF FAILURE DUE TO IMPROPER HEAT TREATING.  1,800-HOUR OVERHAUL REQUIREMENTS, NEW CLUTCH MODEL 'F' TYPE.					1	G	7	1 	3U				H3WE    					 
1996101000881	19961010	00881	NE  	1996	10	10	96ZZZX5161       	2	19960925	G	7320		CONTROL CABLE   			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ANTICIPATOR	BINDING         	D				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SO	17	54EW					1936	949			ON FINAL APPROACH, COLLECTIVE WAS LOWERED TO START A DESCENT, ROTOR RPM OBSERVED HIGHER THAN NORMAL.  THE COLLECTIVE WAS	 RAISED TO RESTORE ROTOR RPM TO NORMAL, BUT NO CHANGE WAS OBSERVED.  PER THE MANUFACTURER'S FLIGHT MANUAL, THE FUEL FLOW	 CONTROL LEVER WAS USED TO SLOW RPM.  THIS RESULTED IN AN OPPOSITE PROBLEM IN SLOWING THE RPM TOO MUCH.  UPON LANDING, A	IRCRAFT WAS GROUNDED UNTIL MAINTENANCE COULD LOOK AT THE AIRCRAFT, THEY DISCOVERED THE CABLE THAT ATTACHES TO THE FFC WA	S BINDING, AND REPLACED THE CABLE.		1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
1996101700246	19961017	00246	NE  	1996	10	17	96ZZZX5162       	1	19960913	G	6210	7615009100051A	BLADE           			SKRSKY	S76   	S76B        	8143007	NE  										M/R	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5NJ	4289 			A08601121	760346				BLADE WAS BEING INSPECTED AFTER BEING USED AS A RENTAL UNIT. WHILE INSPECTING M/R BLADE ROOT END IAW SIKORSKY COMPOSITE 	MANUAL, SA 4047-76-5, PARAGRAPHS 2-7, A CRACK WAS FOUND COMING OUT FROM UNDERNEATH THE PHOENLIC BLOCK.  BLADE REMOVED FR	OM SERVICE.				1	G	7	2 	4U				H1NE    					 
1996101700247	19961017	00247	NE  	1996	10	17	96ZZZX5163       	1	19960913	G	6210	7615009100041A	BLADE           			SKRSKY	S76   	S76B        	8143007	NE  										MAIN ROTOR	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5NJ	4802 			A08600513	760346				BLADE BEING INSPECTED AFTER BEING USED AS RENTAL UNIT.  WHILE INSPECTING M/R BLADE ROOT END IAW SIKORSKY COMPOSITE MANUA	L, SA 4047-76-5, PARAGRAPHS 2-7, A CRACK WAS FOUND COMING OUT FROM UNDERNEATH THE PHOENLIC BLOCK.  BLADE REMOVED FROM SE	RVICE.				1	G	7	2 	4U				H1NE    					 
1996101700248	19961017	00248	EU  	1996	10	17	96ZZZX5164       	1	19960901	G	5320		DECK            			AEROSP	SA365 	SA365N1     	8680668	EU  										LT TRANSMISSION	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	365UC	1919 				6329				250 MM CRACK FOUND LT SIDE TRANSMISSION DECK AT STA 3826.7.  REPAIR MADE PER EUROCOPTER REPAIR DATA SHEET.  MANUFACTURER	 ISSUED AIRFRAME SB 05.00.36.  OPERATOR RECOMMENDS THAT SB 05.00.36 CHANGE FROM A RECOMMENDED TO A MANDATORY SB AND HOUR	S BE DECREASED FROM 2,000 TO SOMETHING LESS.				1	G	7	2 	3U				H10EU   					 
1996101700260	19961017	00260	SW  	1996	10	17	96ZZZX5173       	1	19960909	G	6730	206076062003	CYLINDER        			BELL  	206   	206L1       	1182107	SW  										COLLECTIVE SERVO	DEFECTIVE       	B			GCHR	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	19	2072M	3088 	388  		RH301	45720				PILOT REPORTED LOSS OF COLLECTIVE CONTROL ON AIRCRAFT.  ARRIVED AT SCENE AND INSPECTED AND FOUND COLLECTIVE SERVO PISTON	 UNSCREWS FROM ROD END BEARING.  CAUSE OF INCIDENT WAS NO SAFETY WAS FOUND ON FWD SERVO PISTON.  INSPECTED COLLECTIVE SE	RVO FOR DAMAGE AND PISTON FOR STRAIGHTNESS, AND DAMAGE.  NO DEFECTS FOUND.  INSPECTED CONTROL TUBES FOR CRACKS, NICKS, A	ND STRAIGHTNESS, OPENED VERTICAL TUNNEL, INSPECTED CONTROL TUBES FOR CRACKS AND DAMAGE.  NO DEFECT FOUND.			1	G	7	1 	3U				H2SW    					 
1996101700262	19961017	00262	WP  	1996	10	17	96ZZZX5174       	1	19960823	G	6320	369D25143	BEARING         		369D25100505	HUGHES	369   	369D        	4470706	WP  										M/R XMSN	FAILED          	B			EOOR	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			AL	03	5074R				82	1151D				DURING INSPECTION OF M/R TRANSMISSION AFTER CHIP LIGHT, THE FORWARD INPUT PINION BEARING WAS FOUND CONTAMINATED WITH IMP	REGNATED METAL.					1	G	7	1 	3U				H3WE    					 
1996101700264	19961017	00264	GL  	1996	10	17	96ZZZX5176       	1	19960521	G	6710	KUP14D5524	RELAY           			ENSTRM	F28   	F28F        	3300412	GL  										CYCLIC TRIM	STUCK CONTACTS  	C			PP0M	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	01	8626S	1057 				786				POINTS IN RELAY FUSE TOGETHER CAUSING RUNAWAY TRIM ACTION RESULTING IN UNCONTROLLED ATTITUDES OF AIRCRAFT.  REQUIRES BOT	H PILOTS ON CYCLIC TO OVERRIDE.  RELAY MFG HAS INDICATED THIS IS NOT THE CORRECT RELAY FOR THIS APPLICATION.  INSTALLED 	NEW RELAY PER MM.				1	G	7	1 	3O				H1CE    					 
1996101700272	19961017	00272	SW  	1996	10	17	96ZZZX5178       	1	19960719	G	5311	212030367004S	FRAME           			BELL  	212   	212         	1181420	SW  										RT ROOF	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	68AL	15619				30934				MAJOR INSPECTION, FOUND FRAME WAS CRACKED ACROSS UPPER FLANGE AND 3.2 INCHES DOWN VERTICAL FLANGE R.H.F.S. 118.  DURING 	REMOVAL OF DAMAGE, 6 MS20470ADS RIVETS WERE FOUND LOOSE whICH PERMITTED UPPER FLANGE TO CHAFE.  CRACK DID NOT START OR C	ROSS CHAFED AREA.  CAUSE UNKNOWN.				1	G	7	1 	4U				H4SW    					 
1996101700273	19961017	00273	SW  	1996	10	17	96ZZZX5179       	1	19960710	G	6230	206040032101	DUPLEX BEARING  			BELL  	206   	206B        	1181511	SW  										SWASHPLATE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3181B	466  			MB742	3770				DUPLEX BEARING BREAKING DOWN WITH ONLY 465.9 HOURS.						1	G	7	1 	3U				H2SW    					 
1996101700274	19961017	00274	SW  	1996	10	17	96ZZZX5180       	1	19960710	G	6320	206040002029	TRANSMISSION    			BELL  	206   	206B        	1181511	SW  										M/R	MAKING METAL    	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3181B	13795			BKW11485	3770				INSTALLED DUPLEX BEARING 206-040-032-101, SN MB472, INTO ABOVE TRANSMISSION WHEN BEARING WAS NEW.  AIRCRAFT FLEW 465.9 H	OURS AND BEARING MAKING METAL.					1	G	7	1 	3U				H2SW    					 
1996101700275	19961017	00275	NE  	1996	10	17	96ZZZX5181       	2	19960329	G	7230	536210	TABLOCK         			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					3RD STAGE DISK	MISSING         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	154AC	575  				64037	672566			TABLOCK MISSING AT POST-FLT INSP ON 3-29-96.  LAST O/H PERFORMED BY EAC ON 3-23-95.  WHEN INSP COMP THRU INLET, CONTACT 	OF 3RD STG BLD NOTED ON FACE OF 4TH STG STATOR NEAR CENTERLINE OF ENG (ROOT END OF BLD).  BLD MOVED AFT CONTACTING FRONT	 OF STATOR DUE TO TABLOCK FAILURE.  ERICKSON ALSO DOCUMENTED DIMENSIONAL VARIANCES FND ON TABLOCKS SUPPLIED BY TP&M,  SE	NT A PIECE OF FRACTURED TABLOCK TO P&W FOR LAB ANALYSIS.  WHEN CORRECTIVE ACTION WAS NOT FORTHCOMING FROM P&W, REMAINING	 PIECE OF TABLOCK SENT TO OUTSIDE LAB FOR METALLURGICAL ANALYSIS.  RESULTS SHOWED MICRO CRACKING ON EDGES OF TABLOCKS WH	ICH ARE A MFG DEFECT.	2	G	7	2 	4U	4	U		H4EA    	E15EA				 
1996101700506	19961017	00506	NE  	1996	10	17	96ZZZX5187       	1	19960723	G	6410	73676HA78	BLADE BOLT      			SKRSKY	S64   	S64F        		NE  										RED T/R BLADE	FRACTURED       	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	158AC					64081				DURING INSPECTION OF TAIL ROTOR ASSY DURING POST-FLIGHT INSPECTION, TWO BOLTS FOUND FRACTURED.  THE RED T/R BLADE AND AL	L EIGHT BOLTS WERE REPLACED.  THERE WAS NO DAMAGE TO THE AIRCRAFT EXCEPT AS NOTED HEREIN.					2	G	7	2 	4U				H6EA    					 
1996101700507	19961017	00507	NE  	1996	10	17	96ZZZX5188       	1	19960726	G	6410	73676HA78	BLADE BOLT      			SKRSKY	S64   	S64F        		NE  										RED T/R BLADE	FRACTURED       	B	L		JYDR	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			NM	09	178AC	76   				64097				CLIMB, 50-60 KTS IAS ABOUT 1K FPM RATE , PILOT  NOTED VIBRATION IN T/R.  RETURNED ORIG TAKEOFF POINT, LANDED.  VIBRATION	 BECAME STRONGER DURING DESCENT.  FOUND 8 BOLTS RETAINING T/R BLADE, 1 EA BOLT HEAD  MISSING AND NEVER FOUND.  3 EA BOLT	 HEADS BROKEN ABOUT 3RD THREAD OTBD FROM SHANK, AND 2 BOLTS HAD NO TORQUE REMAINING.    RED T/R BLADE REPLACED AND ACFT 	INSPECTED FOR  PROBLEMS, NONE FOUND.   THIS IS UPDATED MDR.			2	G	7	2 	4U				H6EA    					 
1996101700508	19961017	00508	NE  	1996	10	17	96ZZZX5189       	1	19960723	G	6410	7376HA78	BLADE BOLT      			SKRSKY	S64   	S64F        		NE  										YELLOW T/R BLADE	FRACTURED       	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	178AC					64097				TWO BOLTS WERE FOUND FRACTURED ON THE YELLOW T/R BLADE AT THE PITCH CHANGE ATTACH LOCATION WHEN THE T/R WAS INSPECTED AT	 THE NOON SHUT-DOWN.  THIS IS A GENERAL INSPECTION INTERVAL FOR THE T/R.  THE BLADE WAS CHANGED OUT AND ALL 8 BOLTS REPL	ACED ON THE YELLOW BLADE.  ADDITIONALLY, ALL OTHER BOLTS ON THE OTHER 3 T/R BLADES WERE ALSO REPLACED.  THERE WAS NO DAM	AGE TO ANY OTHER PART OF THE A/C.			2	G	7	2 	4U				H6EA    					 
1996101700509	19961017	00509	NE  	1996	10	17	96ZZZX5190       	2	19960625	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	423  				64097	677799			TABLOCK FOUND MISSING AT POST-FLIGHT INSPECTION ON 6-25-96.  THE LAST OVERHAUL WAS PERFORMED BY SABRELINER.  WHEN INSPEC	TING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF E	NGINE (ROOT END OF BLADE).  THE BLADE MOVED AFT CONTACTING FRONT OF STATOR DUE TO TABLOCK FAILURE.  THIS IS THE 7TH OCCU	RRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1994.  ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACTURER.			2	G	7	2 	4U	4	U		H6EA    	E15EA				 
1996101700510	19961017	00510	NE  	1996	10	17	96ZZZX5191       	2	19960426	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	581  				64097	677770			TABLOCK FOUND MISSING AT PRE-FLIGHT INSPECTION CONDUCTED ON 4-26-96.  THE LAST OVERHAUL PERFORMED BY EAC ON 8-4-94.  WHE	N INSPECTING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3RD STAGE BLADE WAS NOTED ON FACE OF 4TH STAGE STATOR NEAR CEN	TERLINE OF ENGINE (ROOT END OF BLADE).  THE BLADE MOVED AFT CONTACTING FRONT OF STATOR DUE TO TABLOCK FAILURE.  THIS IS 	THE 6TH OCCURRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1994.  ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACTURER	.		2	G	7	2 	4U	4	U		H6EA    	E15EA				 
1996101700513	19961017	00513	NE  	1996	10	17	96ZZZX5194       	2	19960704	G	7230	536210	TABLOCK         			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					3RD STAGE DISK	MISSING         	B	L		JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	194AC	2203 				64017	676463			TABLOCK FOUND MISSING AT POST-FLIGHT INSPECTION ON 7-4-96 DUE TO NOISE FROM STATOR RUBBING.  LAST OVERHAUL PERFORMED BY 	SABRELINER.  WHEN INSPECTING COMPRESSOR THROUGH INLET, CONTACT 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 THE 8TH OCCURRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1994.  ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACT	URER.		2	G	7	2 	4U	4	U		H4EA    	E15EA				 
1996101700858	19961017	00858		1996	10	17	96ZZZX5205       	1	19960927	G	2822	2B729	PUMP            	AIRBORNE    																FUEL BOOST	ARMATURE DAMAGE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					7H587					FOUND DAMAGE TO SHAFT.  PUMP MAY HAVE BEEN DRY.																			 
1996101700859	19961017	00859		1996	10	17	96ZZZX5206       	1	19960930	G	2822	2B616	PUMP            	AIRBORNE    																ARMATUARE	SHAFT BENT      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					10AG3					FOUND PUMP KEYED END OF SHAFT IS BENT.																			 
1996101700860	19961017	00860	CE  	1996	10	17	96ZZZX5207       	1	19960918	G	7120	26510264	MOUNT BOLT      			LEAR  	35    	35LEAR      	5170600	CE  										ENGINE	HEAD CRACKED    	H			GQFG	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09										FOUND CRACKED HEAD ON NEW ENGINE MOUNT BOLT PURCHASED FROM LEAR IN KIT NR 2695006-1 FOR SB 35/36-71-5, REV 2, 6-18-93. B	ATCH NR SPS18.					2	L	7	2 	4F				A10CE   					 
1996101700861	19961017	00861	EA  	1996	10	17	96ZZZX5208       	2	19960903	G	7322	MA45	CARBURETOR      	PRECISION   							LYC   	O360  	O360A4A     	41514	EA  					BOWL DRAIN	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11		100  			K33508					FOUND LEAK IN BOWL DRAIN WHEN REBUILT CARBURETOR INSTALLED.  REMOVED DRAIN, RESEAL.											3	O			E286				 
1996101700862	19961017	00862	SO  	1996	10	17	96ZZZX5209       	2	19960906	G	7322	MA45	CARBURETOR      								CONT  	O470  	O470U       	17026	SO  					BOWL DRAIN	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11					C00308					FOUND LEAK IN BOWL DRAIN.  REMOVED PLUG, SEAL, AND REINSTALLED.											3	O			E273				 
1996101700864	19961017	00864	CE  	1996	10	17	96ZZZX5211       	1	19960808	G	7120	075100331	MOUNT           			CESSNA	185   	A185E       	2072818	CE  										ENGINE	BROKE           	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	1950U					18501659				IO550 INSTALLED IAW STC SA2933S0.  INSTALLATION INSTRUCTIONS UTILIZE MCAULEY D3A34C401 THREE-BLADE PROPELLER WITH EXISIT	NG ENGINE MOUNT.  AIRCRAFT WITH TWO-BLADE ENGINE MOUNTS ARE APPLICABLE.  CESSNA SL SE79-62 REQUIRES ENGINE MOUNT BE CHAN	GED TO A 0751007-16 MOUNT.  N1950U WAS EQUIPPED WITH 0751003-31 MOUNT.  MOUNT WAS CRACKED.  FUEL HEADER TANK WAS CRACKED	, EXHAUST WAS CRACKED.  IO550 AND THREE-BLADE PROP WERE INSTALLED 205 HOURS PREVIOUSLY.  ACFT TT WAS 2,701.9 HRS.			1	H	7	1 	3O				3A24    					 
1996101700865	19961017	00865	CE  	1996	10	17	96ZZZX5212       	1	19960901	G	8120	4066109025	TURBOCHARGER    			CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  					NR 1 ENGINE	FAILED          	D				A				UNSCHED LANDING         				D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			WP	19	82TA		454  		SHR1829	4020156	22356872E			WHILE IN-FLIGHT, NR 1 TURBOCHARGER FAILED.  THE AIRCRAFT LANDED WITHOUT DAMAGE.  UPON INSPECTION BY MAINTENANCE, DISCOVE	RED TURBO MAIN SHAFT HAD BROKEN AND WHEEL ON THE EXHAUST SIDE WAS MISSING.  IT APPEARS TO HAVE GONE OUT THE OVERBOARD ST	ACK.  THE OTHER WHEEL WAS STILL IN THE TURBO.  CAUSE:  UNKNOWN.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996101700866	19961017	00866	SO  	1996	10	17	96ZZZX5213       	2	19960808	G	8530		CYLINDER        			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  					1 THRU 6	SCORED          	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	1950U		203  			18501659	284035R			AT ANNUAL INSPECTION ENGINE COMPRESSION READINGS SHOWED THE FOLLOWING:  NR 1, 70/80, NR 2, 58/80, NR 3, 72/80, NR 4, 56/	80, NR 5, 64/80, AND NR 6, 70/80.  ALL LEAKAGE WAS PAST PISTON RINGS.  BORESCOPE INSPECTION REVEALED SCORING ON ALL CYLI	NDERS.  AN INSPECTION ON 7-21-95 AT 159 TSOH REVEALED THE FOLLOWING NR 1, 70/80, NR 2, 72/80, NR 3, 76/80, NR 4, 72/80, 	NR 5, 72/80, AND NR 6, 72/80.			1	H	7	1 	3O	3	O		3A24    	E5CE				 
1996101700867	19961017	00867	CE  	1996	10	17	96ZZZX5214       	1	19960906	G	2810	3540002	BLADDER         			BEECH 	35    	S35         	1151532	CE  										RT TANK	BAFFFLE CRUMBLE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	3MG				383	07856				FUEL BLADDER INNER BAFFLING DISENTEGRATING INTO SAND-SIZE PARTICLES.  PARTICLES FOUND AT SUMP AND STRAINER.  COULD CAUSE	 FUEL STARVATION.  DETERMINED TO BE INNER BAFFLE FOAM.					1	L	7	1 	3O				3A15    					 
1996101700868	19961017	00868	NM  	1996	10	17	96ZZZX5215       	1	19960910	G	5102	C16151J	TANK            			RAVEN 	S50   	S50A        	05604XW	NM  										GONDOLA	CHAFE DOOR      	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	1235R	166  				S50A275				UPON INSPECTION OF FLOOR ASSY, VISUAL CHAFING OF STRUCTURAL ALUMINUM U-TUBING WAS OCCURRING DUE TO ABRASION BY PROPANE F	UEL TANK.  WICKER WAS ALREADY BROKEN.  SUGGEST THOROUGH INSPECTION AT ANNUALS AND APPLICATION OF ANTI-CHAFE MATERIAL (SP	LIT HOSE) TO TANK BASE.				1	B	0	0 					A15CE   					 
1996101700869	19961017	00869	CE  	1996	10	17	96ZZZX5216       	1	19960805	G	2810	S14958	HOSE            			CESSNA	182   	182J        	2072722	CE  										LT TANK VENT	SPLIT           	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	3119F	2509 				18257219				AFTER EACH FLIGHT, PILOT REPORTED HAD TO WIPE FUEL STAIN FROM TRAILING EDGE OF LT WING.  INSPECTION OF LT FUEL BLADDER M	ADE AND FOUND HOSE CONNECTING TANK VENT LINE TO THE LT FUEL TANK WAS SPLIT AND ALLOWING FUEL TO VENT INTO THE WING BAY O	UTBOARD OF LT TANK.  THE AGE OF THE RUBBER HOSE WAS DETERMINED TO BE THE CAUSE OF FAILURE.				1	H	7	1 	3O			NT	3A13    					 
1996101700870	19961017	00870	CE  	1996	10	17	96ZZZX5217       	1	19960723	G	3230	1315531F66M	ROD END         			BEECH 	33    	F33A        	1151425	CE  										RT MLG ACTUATOR	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	09	3133W					CE465				WHILE MAKING NORMAL LANDING, PILOT LOWERED GEAR AND HEARD A LOUD 'POP' FROM RT MAIN GEAR.  WHEN GEAR WAS RETRACTED, GEAR	 INTRANSIT LIGHT WOULD NOT GO OFF.  GEAR SELECTOR PLACED BACK IN DOWN POSITION AND AIRCRAFT WAS FLOWN TO HOME AIRFIELD W	ITH GEAR DOWN.  AFTER LANDING, INSPECTION FOUND RT MAIN OUTBOARD ACTUATOR ROD END BROKEN.  THE ROD END WAS DRY AND LACKE	D LUBE (WAS RUSTED IN BEARING SURFACE).  SUBMITTER SUGGESTS LUBE AT 100-HOUR INTERVALS.  NEW PART HAS GREASE FITTING INS	TALLED.		1	L	7	1 	3O				3A15    					 
1996101700871	19961017	00871	SO  	1996	10	17	96ZZZX5218       	1	19960925	G	2140	A23D0475	REGULATOR       	JANITROL    		PIPER 	PA31  	PA31350     	7103110	SO  										HEATER PRESSURE	GASKET LEAK     	B			APCR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	36PB	20   				317405128				JANITROL HEATER FUEL PRESSURE REGULATOR WAS INSTALLED NEW 8-22-96.  ON 9-19-96 WITH 20.1 HRS TIME IN SERVICE, UNIT FAILE	D CAUSING FLUCTUATION OF RT FUEL SYSTEM PRESSURE.  WHEN REMOVED, FOUND FUEL LEAKING AROUND GASKET.					1	L	7	2 	3O				A20SO   					 
1996101700872	19961017	00872	SO  	1996	10	17	96ZZZX5219       	1	19960924	G	2140	A23D0475	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  										HEATER PRESSURE	LEAKING         	B			APCR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	36PB					317405128				FUEL PRESSURE REGULATOR FOR COMBUSTION HEATER CAUSED FUEL PRESSURE GAUGE FLUCTUATIONS.  EXAMINATION FOUND REGULATOR LEAK	ING EXTERNALLY.  OPERATOR HAS RECORDS OF MULTIPLE FAILURES OF THESE UNITS.					1	L	7	2 	3O				A20SO   					 
1996101700873	19961017	00873	SO  	1996	10	17	96ZZZX5220       	1	19960926	G	3260	67411008	SWITCH          			PIPER 	PA34  	PA34200T    	7103406	SO  										LT MLG	OUT OF ADJUST   	B			APCR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	01	36319					347870318				AIRCRAFT TOOK OFF, PILOT SELECTED 'GEAR UP', GEAR DID NOT MOVE.  WARNING HORN AND LIGHT CAME ON.  AIRCRAFT LANDED WITHOU	T INCIDENT.  MAINTENANCE FOUND GEAR SAFETY 'SQUAT' SWITCH OUT OF ADJUSTMENT.  RE-ADJUSTMENT CURED PROBLEM.					1	L	7	2 	3O				A7SO    					 
1996101700875	19961017	00875	CE  	1996	10	17	96ZZZX5222       	1	19960901	G	5510		STABILIZER      			CESSNA	210   	P210N       	2073454	CE  										HORZ STAB LE	LOOSE RIVETS    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4752K	1850 				P21000283				FOUND LOOSE RIVETS ON LEADING EDGE OF HORIZONTAL STABILIZER ON THE FIRST TWO RIBS OUT FORM THE FUSELAGE.  REMOVED AND RE	PLACED RIVETS WITH NEW.  AIRCRAFT EQUIPPPED WITH DE-ICE BOOTS.					1	H	7	1 	3O				3A21    					 
1996101700876	19961017	00876	CE  	1996	10	17	96ZZZX5223       	1	19960924	G	2571	07120591	SUPPORT         		07120741    	CESSNA	182   	182Q        	2072732	CE  										BATTERY BOX	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	501AC	1208 				18266922				INSPECTION FOUND BATTERY SUPPORT CRACKED.  SUSPECT CAUSE IS TIME IN SERVICE.  SHOULD BE THICKER MATERIAL.						1	H	7	1 	3O			NT	3A13    					 
1996101700877	19961017	00877	CE  	1996	10	17	96ZZZX5224       	1	19960930	G	2820	040034321	PRIMER ASSY     			CESSNA	150   	152         	2071835	CE  										CYLINDER NR 2	SEPARATED       	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			EA	09	5297M	5554 				15284518				STUDENT PILOT ON SOLO CROSS-COUNTRY EXPERIENCED ROUGH ENGINE OPERATION.  AIRCRAFT RETURNED TO AIRPORT.  INSPECTION REVEA	LED PRIMER LINE ASSY AT NR 2 AND NR 4 CYLINDERS SEPARATED AT SOLDER JOINT OF THREADED CONNECTOR OF CYLINDER.  FRACTURES 	ARE CONSISTENT WITH CYCLIC FATIGUE.  SUBMITTER RECOMMENDS SECURITY INSPECTION ANY TIME COWLING REMOVED.  TOTAL ACFT TIS:	  5,554.0 HOURS ESTIMATED.			1	H	7	1 	3O			NT	3A19    					 
1996101700878	19961017	00878	CE  	1996	10	17	96ZZZX5225       	1	19960930	G	2820	040034322	PRIMER ASSY     			CESSNA	150   	152         	2071835	CE  										CYLINDER NR 4	SEPARATED       	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			EA	09	5297M	5554 				15284518				STUDENT PILOT ON SOLO CROSS-COUNTRY EXPERIENCED ROUGH ENGINE OPERATION.  AIRCRAFT RETURNED TO AIRPORT.  INSPECTION REVEA	LED PRIMER LINE ASSY AT NR 2 AND NR 4 CYLINDERS SEPARATED AT SOLDER JOINT OF THREADED CONNECTOR OF CYLINDER.  FRACTURES 	ARE CONSISTENT WITH CYCLIC FATIGUE.  SUBMITTER RECOMMENDS SECURITY INSPECTION ANY TIME COWLING REMOVED.  TOTAL ACFT TIS:	  5,554.0 HOURS ESTIMATED.			1	H	7	1 	3O			NT	3A19    					 
1996101700879	19961017	00879	EA  	1996	10	17	96ZZZX5226       	2	19960926	G	8530	74541	VALVE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 3 CYL EXH	STEM FAILED     	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	09	737FP	1855 				17269385	L220576			PRECAUTIONARY LANDING MADE DUE TO POWER LOSS AND FLUCTUATING OIL PRESSURE.  ENGINE WOULD MAINTAIN 1,800 RPM, AT FULL THR	OTTLE.  NR 3 CYLINDER EXHAUST VALVE FAILED JUST ABOVE HEAD/STEM RADIUS.  SECONDARY CYLINDER AND PISTON DAMAGE REMNENTS O	F VALVE FOUND IN MUFFLER.  STEM REMAINED FROZEN IN VALVE GUIDE.  RECOMMENDATIONS:  LYC SI 1425.  SL L197.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996101700880	19961017	00880	EA  	1996	10	17	96ZZZX5227       	2	19960802	G	7310		HOSE            			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					FIREWALL	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	738FH	3025 			4Q78	R18200920	L2106640A			AIRCRAFT IS 1979 MODEL.  ALL HOSES FORWARD OF FIREWALL, DATED 4Q78.  REPLACED HOSES.  SUBMITTER STATED MECHANICS MUST CH	ECK HOSE CONDITION AND DATES ON A REGULAR BASIS TO AVOID BURST HOSES.					1	H	7	1 	3O	3	O		3A13    	E295				 
1996101700881	19961017	00881	EA  	1996	10	17	96ZZZX5228       	2	19960802	G	8530	LW15605	VALVE           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					ENG EXHAUST	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	738FH	3025 	1082 			R18200920	L2106640A			PEFORMED SB 388B ON ALL 6 CYLINDERS AT ANNUAL INSPECTION, 4 OF 6 CYLINDER EXHAUST VALVE AND GUIDES WORN BEYOND SPECS.  R	EMOVED CYLINDERS, FOUND 2 CYLINDERS WITH BROKEN RINGS, AND 6 CYLINDERS WERE CRACKED. REPLACED CYLINDER ASSY.  SUBMITTER 	STATED SB 88B IS A GOOD TOOL TO PREVENT ENGINE FAILURE.				1	H	7	1 	3O	3	O		3A13    	E295				 
1996101700882	19961017	00882	CE  	1996	10	17	96ZZZX5229       	1	19960802	G	5330		SKIN            			CESSNA	182   	TR182       	2072735	CE  										FWD FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	738FH	3025 				R18200920				AT ANNUAL INSPECTION, FOUND SEVERE CORROSION UNDER SOUND DEADENER SHEETS IN FORWARD FUSELAGE SIDE PANELS.  REMOVED DEADE	NER SHEETS, TREATED AND PAINTED WITH CHROMATE PAINT.  CESSNA ADDRESSES THIS PROBLEM IN SERVICE NEWS LETTER SNL 93-3, DAT	ED JUNE, 1993.  IF NOT CAUGHT, THIS CORROSION WOULD HAVE REQUIRED REPLACEMENT OF FORWARD FUSELAGE SKINS.				1	H	7	1 	3O				3A13    					 
1996101700883	19961017	00883	CE  	1996	10	17	96ZZZX5230       	1	19960802	G	5511	0700099101	RIB             			CESSNA	182   	TR182       	2072735	CE  										RT H STAB NR 2	CRUSHED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	738FH	3025 				R18200920				RIGHT STABILIZER'S 2ND NOSE RIB CRUSHED BY USING TAIL TO GROUND HANDLE AIRCRAFT.  SUBMITTER STATED THIS IS RECURRING PRO	BLEM.  HERE IS ANOTHER REMINDER.					1	H	7	1 	3O				3A13    					 
1996101700885	19961017	00885	EA  	1996	10	17	96ZZZX5232       	3	19960920	G	6111		BLADE           			BEECH 	23    	A23         	1151204	CE  						SNSNCH	74DC	M74DC       	EA  	PROPELLER	FAILED          	G		A		A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			SO	05	8879M	1851 				M626		B920		WITH AIRCRAFT AT CRUISE, 2,500 RPM., ONE BLADE FAILED AT 14.6250 INCHES FORM CENTER OF HUB.  IT WAS A CLEAN BREAK WITH N	O SIGN OF NICK OR SCRATCH ANYWHERE ON THE BLADE.  ENGINE VIBRATION BROKE ALL 4 ENGINE MOUNTS.  ENGINE DROPPED INTO BOTTO	M OF COWLING AND SHUT-DOWN.  PILOT DEAD STICKED AIRCRAFT TO AIRPORT AND MADE AN UNEVENTFUL LANDING.  NO INJURIES.  NTSB 	IS INVESTIGATING BLADE FAILURE.			1	L	7	1 	3O				A1CE    		5	N	P88614	 
1996101700887	19961017	00887	SW  	1996	10	17	96ZZZX5233       	1	19960118	G	7160	600355507	PLATE ASSY      			MOONEY	M20   	M20J        	5870219	SW  										ALT AIR DOOR	RIVETS FAULTY   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	9138Z					243219				WHILE C/W AD 95-26-16R1, FOUND 2 OF THE 4 RIVETS SECURING PLATE ASSY 600355-507 MISSING HEAD.  APPARENTLY WORN AWAY BY C	HAFING AGAINST RIVETS THAT SECURE DOUBLER TO AIR BOX.  RECOMMEND ANTI-CHAFE MATERIAL OR REPLACING RIVETS WITH FLUSH HEAD	S.				1	L	7	1 	3O				2A3     					 
1996101700888	19961017	00888	SO  	1996	10	17	96ZZZX5234       	1	19961001	G	2720	9621200	TUBE ASSY       			PIPER 	PA34  	PA34220T    	7103420	SO  										RUDDER	ELONGATED HOLES 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9249N					3448048				AIRCRAFT TOTAL TIME:  470.2 HOURS, 1995 SENECA IV.  FOUND DURING ANNUAL INSPECTION, RUDDER HAD 3 TO 4 DEGREE MOVEMENT WI	THIN THE MOUNT FITTING, PN 96319-802.  FURTHER INSPECTION (RUDDER REMOVED) TORQUE TUBE ASSY HAD WORN, ELONGATED BOLT HOL	ES (4).  CAUSE - VIBRATION, WINDLOAD, WEAK TUBE CONSTRUCTION.  SUBMITTER RECOMMENDS RE-ISSUE PIPER SB 899, DATED 2-10-89	, TO COVER SENECA IV MAKING THIS AREA A 50-HOUR INSPECTION ITEM.			1	L	7	2 	3O				A7SO    					 
1996101700889	19961017	00889	CE  	1996	10	17	96ZZZX5235       	1	19960731	G	2842	C6680020301	TRANSMITTER     	STWARNER    		CESSNA	150   	152         	2071835	CE  										FUEL QUANTITY	FLOAT DETACHED  	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	93114	5700 				15285404				DISCREPANCY WAS FOUND ON PRE-FLIGHT THAT LEFT HAND FUEL GAUGE READING WAS ZERO WHEN TANK WAS FULL OF FUEL.  REMOVED TANK	 TRANSMITTER AND FOUND FLOAT MISSING FROM ARM OF TRANSMITTER.  RETRIEVED FLOAT FROM TANK, FOUND CONDITION OF FLOAT OK. R	E-ATTACHED WITH EXISTING WASHERS, INSTALLED, AND SYSTEM CHECKED OK.				1	H	7	1 	3O			NT	3A19    					 
1996101700890	19961017	00890	SO  	1996	10	17	96ZZZX5236       	1	19961004	G	5311	226667	TUBULAR FRAME   			PIPER 	PA22  	PA22160     	7102214	SO  										DOOR POST	FATIGUE HOLE    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	9753D	3438 				226667				MANUFACTURER USED A SMALL WELD DOT TO SNUB VIBRATION IN THE TOP OF THE LOWER FRONT DOOR CHANNEL.  VIBRATION IN THE COWL 	WRAPPER/DOOR CHANNEL FATIGUED A .1250 INCH BY .25 INCH HOLE IN THE DOOR TUBE.  THIS TUBE CONNECTS THE FRONT WING FITTING	 TO THE LOWER LONGERON.  FOUND ON TEAR DOWN FOR REBUILD.  WOULD NOT NORMALLY BE INSPECTED.				1	H	7	1 	3O				1A6     					 
1996101700891	19961017	00891	SO  	1996	10	17	96ZZZX5237       	1	19961004	G	5311	226667	FRAME           			PIPER 	PA22  	PA22160     	7102214	SO  										LOWER RT LONG	PITTED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	9753D	3438 				226667				A COMBINATION OF AN UNCORRECTED WATER LEAK AT A WINDOW AND DIRT HELD BETWEEN THE LONGERON/INTERIOR FABRIC RESULTED IN A 	BADLY PITTED LONGERON.  SUBMITTER STATED SHOULD FIX LEAKS AND CLEAN.					1	H	7	1 	3O				1A6     					 
1996101700892	19961017	00892	SO  	1996	10	17	96ZZZX5238       	1	19961004	G	5311	226667	TUBE FRAME      			PIPER 	PA22  	PA22160     	7102214	SO  										INST PANEL	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	9753D	3438 				226667				INSTRUMENT PANEL CROSS-TUBE CRACKED AT BRAKE LEVER MOUNTING BRACKET WELD (MORE THAN ONE-FOURTH OF CIRCUMFERENCE).  THE B	RAKE LEVER PUTS A HIGH STRESS ON THE MOUNTING BRACKET WHEN THE BRAKES ARE APPLIED.  THE CRACK IS LOCATED UNDER THE INSTR	UMENT PANEL AND VERY DIFFICULT TO SEE.				1	H	7	1 	3O				1A6     					 
1996101700894	19961017	00894	SO  	1996	10	17	96ZZZX5240       	1	19960225	G	2437	3733700	AMMETER         			PIPER 	PA34  	PA34200T    	7103406	SO  										DC SYSTEM	WRONG PART      	B		A	LC1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	33156					347570096				PIPER PARTS CATALOG HAS NOT YET BEEN UPDATED TO REFLECT AMMETER REPLACEMENT IAW AD 86-17-01.  PARTS SUPPLIERS ARE USING 	OLD FICHE TO SEND OUT OLD STYLE AMMETERS WHICH DO NOT COMPLY WITH PREVIOUSLY STATED AD.  IN THE EVENT ONE OF THESE OLD S	TYLE AMMETERS IS INSTALLED, IT COULD CAUSE A POSSIBLE SHORT CIRCUIT AND/OR SMOKE AND FIRE IN THE COCKPIT.  OLD STYLE PAR	T NR 37337-00.			1	L	7	2 	3O				A7SO    					 
1996101700895	19961017	00895	EA  	1996	10	17	96ZZZX5241       	1	19960921	G	5700	AN677AC16300	FLYING WIRE     			SCWZER	G164  	G164B       	3952802	EA  										WING LT AFT	BROKE           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	3629K					748B				WIRE BROKE 10 INCHES FROM WING ATTACH (BROKE FROM TOP TO BOTTOM).  PART APPEARS TO HAVE BEEN CRACKED ONE-HALF THROUGH FO	R SOME TIME PRIOR TO FAILURE.					1	Q	7	1 	3R				1A16    					 
1996101700896	19961017	00896	CE  	1996	10	17	96ZZZX5242       	1	19960909	G	3234	A4503M95	GEAR CONTROL    			BEECH 	200   	A200        	1152921	CE  										MLG	MISWIRED        	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	05	2MIL				660	BJ24				UPON INSPECTION OF REPAIRED PART PRIOR TO INSTALLATION, DISCOVERED THE LANDING GEAR CONTROL WAS WIRED INCORRECTLY.  PART	 HAD BEEN REPAIRED BY REPAIR STATION PRZR073K.  ANOTHER CONTROL REMOVED FROM SUPPLY WAS ALSO WIRED INCORRECTLY.					1	L	7	2 	4T				A24CE   					 
1996101700897	19961017	00897	EA  	1996	10	17	96ZZZX5243       	2	19960629	G	8520	LW13809	CRANKCASE       			AMTR  	ACROSP	ACROSPORT   		GL  	LYC   	O360  	IO360B1F    	41514	EA  					OIL SUMP	BROKEN          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	09	4362D	1346 				780	L619836C			NOTED OIL  LEAK ON LT SIDE OF OIL SUMP.  FOUND THE CRANKCASE HAD MISSING PIECES AT LT REAR OIL SUMP MOUNTING STUD.  ENGI	NE WAS CONVERTED TO IO-360 APPROXIMATELY 100 HOURS PREVIOUSLY.  A NEW OIL SUMP WAS INSTALLED AT THAT TIME.  SUSPECT OIL 	SUMP TO CASE BOLTS WERE OVERTORQUED CAUSING A CRACK AND EVENTAULLY VIBRATION CAUSED PIECE TO DEPART CASE.				1	Q	7	1 	3O	3	O	NC	EXPA1Q71	1E10				 
1996102400011	19961024	00011	CE  	1996	10	24	96ZZZX5254       	1	19960821	G	2130	26195009	VALVE           			LEAR  	35    	35A         	5170602	CE  										LT PRESS SYS	MALFUNCTIONED   	E				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			SW	99	21NG	4251 				343				DUDRING TAKEOFF FROM BINGHAMTON REGIONAL AIRPORT, LEFT EMERGENCY PRESSURIZATION 3-WAY VALVE WENT TO EMERGENCY POSITION. 	 PROBLEM INTRODUCED HOT AIR AND SMOKE INTO CABIN.  VALVE WOULD NOT SHUT OFF.  EMERGENCY DECLARED AND ACFT RETURNED AND A	N UNEVENTFUL LANDING  MADE.  AIRCRAFT TURNED OVER TO MAINTENANCE.  THE LT EMERGENCY PRESSURIZATION 3-WAY VALVE WAS REPLA	CED.			2	L	7	2 	4F				A10CE   					 
1996102400012	19961024	00012	NE  	1996	10	24	96ZZZX5255       	2	19960830	G	7412	3033378	EXCITER         	LUCAS       		CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	INOPERATIVE     	B			CWQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	111QS	9769 			K7837	S5500111				DURING OPERATIONAL CHECK OF NEW ENGINE IGNITER, IGNITION EXCITER FAILED TO FIRE IGNITER.  PROPER VOLTAGE OBSERVED AT CAN	NON PLUG.  INTERNAL PROBLEM WITH EXCITER BOX.					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
1996102400013	19961024	00013	CE  	1996	10	24	96ZZZX5256       	1	19960823	G	3010	P067L015	SWITCH          			CESSNA	500   	S550        	2076607	CE  										TKS DEICE	CORRODED        	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	112QS	9613 			B16286	S5500112				DURING PHASE 5 INSPECTION, FOUND LT WING CUFF TKS PANEL PRESSURES SWITCH BADLY CORRODED AND METAL EXFOLIATED ON THE SURF	ACE OF THE SWITCH.  SUBMITTER STATED POOR QUALITY OF METAL USED IN MAKING SWITCH BODY WITH POSSIBLE TKS FLUID LEAKAGE LI	KELY CAUSE.				1	L	7	2 	4F			RT	A22CE   					 
1996102400014	19961024	00014	NM  	1996	10	24	96ZZZX5257       	1	19960830	G	3397		WIRE            			ISRAEL	1125  	1125        	       	NM  										CABIN LIGHTS	WRONG PART      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	121GV	32   				082				PER AD 95-22-01, HI-VOLTAGE WIRE MUST MEET A CERTAIN SPEC.  THIS AIRCRAFT APPEARS TO HAVE STANDARD 20-GAUGE TEFLON WIRE 	INSTALLED WHICH DOES NOT MEET THAT STANDARD.					2	L	7	2 	4F			RT	A16NM   					 
1996102400015	19961024	00015	CE  	1996	10	24	96ZZZX5258       	1	19960807	G	2910		LINE            			CESSNA	650   	650         	2076802	CE  										AFT BAG COMP	CRACKED         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	05	17TE					6500011				RIGHT STAINLESS STEEL HYDRAULIC LINE COMPRESSED FITTING CRACKED, SOME HYDRAULIC FLUID WAS LOST AND SYSTEM PRESSURE DROPP	ED.  REASON FITTING CRACKED IS UNKNOWN.  LINE WAS REPAIRED BY CESSNA AIRCRAFT PERSONNEL AND DISPATCHED BY THEM.					2	L	7	2 	4F				A9NM    					 
1996102400016	19961024	00016	SW  	1996	10	24	96ZZZX5259       	1	19960828	G	3245	600X6	TUBE            	MCCREARY    	7500681     	GULSTM	690TP 	690B        	7630516	SW  										NLG	FAILED          	G				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			GL	05	177EM	270  			772015	11471				AIRCRAFT ABORTED TAKEOFF DUE TO NOSE WHEEL SHIMMY.  FULL REVERSE AND BRAKES APPLIED.  NOSE GEAR COLLAPSED.  MCCREARY 6.0	0 X 6 TUBE APPEARS TO HAVE FAILED ALONG A MOLD LINE.  TUBE IS MARKED 77-2-015 AND 120 113 09E.  THE OPERATOR WILL SEND T	HE TUBE OUT FOR EVALUATION.				1	H	7	2 	3T				2A4     					 
1996102400017	19961024	00017	CE  	1996	10	24	96ZZZX5260       	1	19960917	G	2720		BOLT            			CESSNA	500   	550         	2076604	CE  										RUD TORQUE TUBE	WRONG PART      	B			CWQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	6862Q					5500265				DURING PHASE 5 INSPECTION, FOUND INCORRECT BOLT AND NUTS INSTALLED IN RUDDER TORQUE TUBE WHERE IT ATTACHED TO BELLCRANK.	  THREE DIFFERENT TYPES OF LOCKING NUTS USED IN PLACE OF CASTLE NUTS THAT ARE REQUIRED.  MOST LIKELY INSTALLED BY PAINT 	SHOP WHEN AIRCRAFT WAS REPAINTED.				1	L	7	2 	4F				A22CE   					 
1996102400019	19961024	00019	SO  	1996	10	24	96ZZZX5262       	1	19960901	G	3244	706C861	TIRE            	GOODYEARAERO		PIPER 	PA23  	PA23250     	7102308	SO  										MLG	CHAFE GROOVE    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	888RJ					277305139				THE MAIN LANDING GEAR TIRE HAS 2 EACH GROOVES WORN IN SIDEWALLS, 1.3750 INCH AND 7.8750 INCH FROM INNER EDGE OF BEAD OUT	WARD ON SIDEWALL APPROXIMATELY .1250 INCH DEEP IN AREAS.  THE TIRES HAVE TOO MUCH ROUNDNESS AT SIDEWALLS.  NOTE:  CONDOR	 TIRES INSTALLED AND CLEARANCE BETWEEN BRAKE PAD ABOUT .50 INCH.  TIRE WOULD RUB ON SIDEWALL, COULD NOT TURN WHEEL BY HA	ND.  APPROXIMATELY 10 LANDINGS.			1	L	7	2 	3O				1A10    					 
1996102400020	19961024	00020	SO  	1996	10	24	96ZZZX5263       	2	19960927	G	7414	10357426	DISTRIBUTOR BLOC		S6RN25      	PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					MAG	OVERHEAT        	B			SMTR	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			EA	17	91284	1    			A233618	347970111	306764			DISTRIBUTOR BLOCK AND DISTRIBUTOR GEAR HAD EXCESSIVE HEAT BUILD-UP AND MELTING OF GEAR POSSIBLY DUE TO LACK OF SUFFICIEN	T CLEARANCE DURING MANUFACTURE OR IMPROPER OIL IMPREGNATION DURING MANUFACTURE.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996102400025	19961024	00025	CE  	1996	10	24	96ZZZX5268       	1	19960910	G	2770	65652752	SLIDE ASSY      			CESSNA	500   	550         	2076604	CE  										GUST LOCK	SPLIT           	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1886G	1348 				5500722				WHILE ACCOMPLISHING A PHASE INSPECTION, FLIGHT CONTROL GUST LOCK WAS ENGAGED AND FOUND SLOPPY AND OUT OF RIG.  FURTHER I	NVESTIGATION FOUND THE GUST LOCK SLIDE ASSY HAD SPLIT IN HALF WHERE THE RT ELEVATOR CABLE PASSES THROUGH.  ONLY THE FORW	ARD SIDE OF THE SLIDE ASSY WAS HOLDING IT TOGETHER.  THE APPEARANCE OF THE FAILURE INDICATED AN EXCESSIVE ELEVATOR DOWN 	FORCE WAS APPLIED WHILE THE GUST LOCK WAS ENGAGED.  SUBMITTER STATED SYSTEM SHOWED NO SIGNS OF BEING RIGGED IMPROPERLY. 	 ALL FLIGHT CONTROL SYSTEMS WERE CHECKED FOR DAMAGE.  FAILED SLIDE ASSY WAS REPLACED WITH NEW FLIGHT CONTROL AND GUST LO	CK SYSTEMS WERE ALL RIGGED.	1	L	7	2 	4F				A22CE   					 
1996102400026	19961024	00026	CE  	1996	10	24	96ZZZX5269       	1	19961001	G	3260	J3A	CONNECTOR       			CESSNA	500   	550         	2076604	CE  										GEAR INDICATOR	MISWIRED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	2734K	3497 				5500595				PILOT REPORTED 'GEAR UNSAFE' LIGHT REMAINS 'DIMLY' LIT AFTER GEAR UP WITH PANEL  LIGHTS ON.  FOUND WIRE 'D41' FROM GEAR 	UNSAFE LIGHT ASSY PINNED INTO 'F2' INSTEAD OF 'A2' OF CONNECTOR J3A AS SCHEMATIC SHOWS ON P3A SIDE, WIRE IDENTIFIED AS F	2P3APP4 WAS PINNED IN COMING FROM 5VDC COPILOT INST LIGHT DIMMER SOURCE.  COULD NOT FIND THIS WIRE IN ANY DRAWINGS, BUT 	SINCE GEAR POSITION LIGHTS ARE 28VDC, THE 5VDC INPUT EXPLAINS THE DIMLY ILLUMINATED CONDITION.  WIRING CORRECTED AND LIG	HTS FUNCTIONED NORMALLY.		1	L	7	2 	4F				A22CE   					 
1996102400027	19961024	00027	CE  	1996	10	24	96ZZZX5270       	1	19960930	G	2730	2655221303	BELLCRANK       			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV STAB	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	301NT	14458	14458			28229				SEVERELY CORRODED MAGNESIUM BELLCRANK WHICH OPERATES THE BIAS BUNGEE FOR ELEVATOR TO STABILIZER LONGITUDINAL CONTROL.  T	HIS UNIT IS LOCATED IN THE AFT LOWER LEFT SIDE OF FS 457. VISUAL INSPECTION IS VERY DIFFICULT DUE TO LOCATION AND POSITI	ON OF ROD END ATTACHMENT POINTS.  SUBMITTER SUGGESTS THIS ITEM BE REMOVED AND INSPECTED AT NEXT SCHEDULED INSPECTION.  B	ELLCRANKS FAILURE WOULD CAUSE LIMITED ELEVATOR TRAVEL AND LOSS OF ELEVATOR TO STABILIZER CONTROL FOR TRIMMING.			2	L	7	2 	4J				A2WE    					 
1996102400028	19961024	00028	CE  	1996	10	24	96ZZZX5271       	1	19960924	G	2730	265522007	CONTROL CABLE   			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV CONTROL	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	303NT	10833				28229				LOWER AFT ELEV CONTROL CABLE FS 388 TO FS 457 SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF FIBERGLASS P	ROTECTIVE CABLE SHROUD PN 265-540425-37 FS 368 TO FS 390.  CABLES ARE VISUALLY INSPECTED AT 150 HR INTERVALS.  CABLES AR	E MANUFACTURED OF CARBON STEEL .1562 INCH DIAMETER WITH 10 STRANDS.  PRIOR TO REMOVAL, 'NO' BROKEN WIRES OR STRANDS WERE	 NOTED 'SMOOTH' SURFACE.  REMOVED CABLE FOR FURTHER INSPECTION, FLEXED CABLE IN A MILD 'U' AND 12 BROKEN WIRES IN DIFFER	ENT STRANDS BROKE IN A 1 INCH AREA WITH SEVERE INNER CORROSION.  NOTE:  CORROSION COULD BE OVERLOOKED DUE TO SMALL SURFA	CE AREA EFFECTED.  REMOVED CABLE FROM SERVICE.	2	L	7	2 	4J			 	A2WE    					 
1996102400029	19961024	00029	CE  	1996	10	24	96ZZZX5272       	1	19960927	G	2730	265522007	CONTROL CABLE   			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV CONT	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	309NT	10508				28261				LOWER AFT ELEV CONTROL CABLE FS 388 TO FS 457 SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF THE FIBERGLA	SS PROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390.  CABLES ARE VISUALLY INSPECTED AT 150-HOUR INTERVALS.  CA	BLES ARE MANUFACTURED OF CARBON STEEL .1562 INCH DIAMETER WITH 10 STRANDS PRIOR TO REMOVAL.  'NO' BROKEN WIRES OR STRAND	S WERE NOTED, 'SMOOTH' SURFACE.  REMOVED CABLE FOR FURTHER INSPECTION, FLEXED CABLE IN A MILD 'U' AND 1 COMPLETE BROKEN 	STRAND AND 15 DIFFERENT WIRES IN DIFFERENT STRANDS IN A 1 INCH AREA BROKE, WITH  SEVERE INNER CORROSION.  NOTE:  CORROSI	ON COULD BE OVERLOOKED DUE TO SMALL SURFACE AREA EFFECTED.  REMOVED CABLE FROM SERVICE.	2	L	7	2 	4J			 	A2WE    					 
1996102400030	19961024	00030	CE  	1996	10	24	96ZZZX5273       	1	19960925	G	2730	2655221303	BELLCRANK       			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV STAB	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	314NT	14458	14458			28228				SEVERELY CORRODED MAGNESIUM BELLCRANK WHICH OPERATES THE BIAS BUNGEE FOR ELEVATOR TO STABILIZER LOCATED IN AFT LOWER LEF	T SIDE OF FS 457.  VISUAL INSPECTION IS VERY DIFFFICULT DUE TO LOCATION AND POSITION OF ROD END ATTACHMENT POINTS.  SUBM	ITTER SUGGESTS THIS ITEM BE REMOVED AND INSPECTED AT NEXT SCHEDULED INSPECTION.  BELLCRANKS FAILURE WOULD CAUSE LIMITED 	ELEV TRAVEL AND LOSS OF ELEV TO STABILIZER CONTROL FOR TRIMMING PURPOSES.  BELLCRANK REMOVED FROM SERVICE.			2	L	7	2 	4J				A2WE    					 
1996102400031	19961024	00031	CE  	1996	10	24	96ZZZX5274       	1	19960926	G	2730	265522007	CONTROL CABLE   			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV CONT	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	314NT	14458				28228				LOWER AFT ELEV CONTROL CABLE FS 388 TO FS 457 SHOWED SIGNS OF CORROSION ON UPPER SURFACE 'ONLY' JUST AFT OF FIBERGLASS P	ROTECTIVE CABLE SHROUD PN 265-540425-37, FS 368 TO FS 390.  CABLES ARE VISUALLY INSPECTED AT 150-HOUR INTERVALS.  CABLES	 ARE MANUFACTURED OF CARBON STEEL .1562 INCH DIAMETER WITH 10 STRANDS.  PRIOR TO REMOVAL 'NO' BROKEN WIRES OR STRANDS NO	TED, SMOOTH SURFACE.  REMOVED CABLE FOR FURTHER INSPECTION.  FLEXED CABLE IN A MILD 'U' AND 14 BROKEN WIRES IN DIFFERENT	 STRANDS BROKE IN A 1 INCH AREA, WITH SEVERE INNER CORROSION.  NOTE:  CORROSION COULD BE OVERLOOKED DUE TO SMALL SURFACE	 AREA EFFECTED.  REMOVED CABLE FROM SERVICE.	2	L	7	2 	4J			 	A2WE    					 
1996102400032	19961024	00032	CE  	1996	10	24	96ZZZX5275       	1	19960916	G	2910	1303800033	SWITCH          			BEECH 	B300  	B300        	1159232	CE  										LT PRESS	FAILED          	D		A		K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			NM	01	4S	22   				FL207				PILOT REPORTED INTERMITTENT RUDDER BOOST ACTIVATION.  BOOST WAS ON FOR TAKEOFF AND INTO 10 MINUTES OF FLIGHT.  YAW DAMP 	WAS INOP THIS TIME.  RECYCLING RUDDER BOOST SWITCH TURN THE BOOST OFF AND THEN BACK ON.  AUTOPILOT WORKED, BUT WITHOUT R	UDDER BOOST.  AFTER ABOUT 10 MINUTES, RUDDER BOOST STARTED WORKING AGAIN PROPERLY AS WELL AS THE YAW DAMPENER.  DETERMIN	ED LEFT PRESSURE SWITCH FAULTY.  REPLACED PRESSURE SWITCH AND FUNCTIONALLY TESTED NORMAL.			2	L	7	2 	4T			RT	A24CE   					 
1996102400034	19961024	00034	EU  	1996	10	24	96ZZZX5276       	1	19961003	G	2150	25VF1399AB	DUCT            			HWKSLY	DH125 	BH125400A   	4230138	EU  										RAM AIR	CRACKED         	B	L	A	K5SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	89SR	7034 				NA778				AIR CONDITIONING RAM AIR INTAKE TO REFRIGERATION UNIT INLET DUCT SEVERELY CRACKED ON LT AND RT SIDES LOWER AREA.  RT SID	E LOWER CONNECTION PORT (CAPPED FOR THIS INSTALLATION) COMPLETELY SEPARATED FROM DUCT AND FOUND LAYING ON ELEVATOR FLIGH	T CONTROL CABLES DURING A PRE-FLIGHT INSPECTION.  BAE 125 1-600 AIRCRAFT MAINTENANCE SCHEDULE MAKES NO SPECIFIC INSPECTI	ON NOTES TO THIS DUCT, ONLY GENERAL - 'INSPECT AIR CONDITIONING PIPES, DUCTS, ETC.'  DUE TO DUCT LOCATION, A DETAILED IN	SPECTION IS NOT POSSIBLE WITHOUT DISASSMEBLY AND REMOVAL OF OTHER AIR CONDITIONING SYSTEM COMPONENTS.		2	L	7	2 	4J				A3EU    					 
1996102400085	19961024	00085		1996	10	24	96ZZZX5277       	2	19960913	G	7314	5006485	DRIVE SHAFT     	LUCAS       	5009986     															FUEL PUMP	FAILED          	H				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			WP	27					1836					FUEL PUMP FAILED ON TAKEOFF ROLL.  FOUND THERE IS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR.  DRIVE SHAFT TURNS EASILY	 BY HAND.																		 
1996102400086	19961024	00086		1996	10	24	96ZZZX5278       	2	19960913	G	7314	5006484	DRIVE GEAR      	LUCAS       																FUEL PUMP	FAILED          	H				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			WP	27					1836					FUEL PUMP FAILED ON TAKEOFF ROLL.  FOUND THERE IS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR.  DRIVE SHAFT TURNS EASILY	 BY HAND.																		 
1996102400087	19961024	00087		1996	10	24	96ZZZX5279       	2	19960923	G	7314	5006485	DRIVE SHAFT     	LUCAS       	5009986     															FUEL PUMP	FAILED          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	27					1601					FUEL PUMP HAS NO FUEL FLOW.  FOUND THERE WAS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR.  DRIVE SHAFT EASILY TURNS BY H	AND.  SUBMITTER STATED C/W P & W SB NR 21087R6 COULD HAVE PREVENTED EXCESSIVE WEAR ON DRIVE SHAFT INTERNAL SPLINE.																		 
1996102400088	19961024	00088		1996	10	24	96ZZZX5280       	2	19960923	G	7314	5006484	DRIVE GEAR      	LUCAS       	5009986     															FUEL PUMP	FAILED          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	27					1601					FUEL PUMP HAS NO FUEL FLOW.  FOUND THERE WAS NO SPLINE LEFT ON DRIVE SHAFT OR DRIVE GEAR.  DRIVE SHAFT EASILY TURNS BY H	AND.  SUBMITTER STATED C/W P & W SB NR 21087R6 COULD HAVE PREVENTED EXCESSIVE WEAR ON DRIVE SHAFT INTERNAL SPLINE.																		 
1996102400089	19961024	00089		1996	10	24	96ZZZX5281       	1	19960901	G	2822	2B761	PUMP            	AIRBORNE    																FUEL BOOST	SHAFT DAMAGED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					6AA17					BOOST PUMP ARMATURE SHAFT DAMAGED, SPACER WORE GROOVE IN SHAFT.																			 
1996102400090	19961024	00090		1996	10	24	96ZZZX5282       	1	19961009	G	2822	2B729	PUMP            	AIRBORNE    																FUEL BOOST	SHAFT DAMAGED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					1AH6					BOOST PUMP ARMATURE SHAFT DAMAGED BY SPACER.																			 
1996102400091	19961024	00091		1996	10	24	96ZZZX5283       	1	19961007	G	2822	2B673	PUMP            	AIRBORNE    																FUEL BOOST	OUT OF BALANCE  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					11F7					FOUND ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996102400092	19961024	00092		1996	10	24	96ZZZX5284       	1	19961009	G	2822	2B729	PUMP            																	FUEL BOOST	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					6AG94					FOUND BOOST PUMP HAS DAMAGE TO ARMATURE SHAFT.																			 
1996102400093	19961024	00093		1996	10	24	96ZZZX5285       	1	19961009	G	2822	2B729	PUMP            																	FUEL BOOST	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					7AC292					BOOST PUMP HAS DAMAGE TO ARMATURE SHAFT.																			 
1996102400094	19961024	00094	CE  	1996	10	24	96ZZZX5286       	1	19960901	G	7603		CABLE           			BEECH 	18    	H18         	1151012	CE  										POWER LEVER	SLIPPED         	D				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	508FS					BA688				PILOT COULD NOT REDUCE POWER TO RT ENGINE DURING FLIGHT,  RT ENGINE WAS FEATHERED FOR LANDING.  INSPECTION REVEALED POWE	R CABLE ATTACH POINT AT FUEL CONTROL UNIT JAM NUT BACKED OFF ALLOWING THE CABLE TO SLIP.  TIGHTENED JAM NUT.  CHECKED RI	GGING, OPS CHECK GOOD.				1	L	7	2 	3R				A765    					 
1996102400095	19961024	00095	EA  	1996	10	24	96ZZZX5287       	2	19960127	G	7314	LW15473	PUMP            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					ENGINE FUEL	PORT BLOCKED    	G				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	13	2FOR	7    	7    			347350236	L1054451A			AN AUSTRALIAN BASED PA-34 PILOT REPORTED ENGINE FAILURE DUE TO FUEL STARVATION.  CAUSE WAS A RUBBER WASHER BLOCKING THE 	FUEL OUTLET PORT OF A NEW TEXTRON FUEL PUMP.  TEXTRON SB 525 ADDRESSES THE PROBLEM.  NO AIRWORTHINESS DIRECTIVE HAS BEEN	 ISSUED TO DATE.  SUBMITTER STATED THERE ARE 4 KNOWN FAILURES FROM SAME CAUSE.  NOTE:  SAME PROBLEM AS MOONEY M20J IN OC	T '96 ALERTS.			1	L	7	2 	3O	3	O		A7SO    	1E10				 
1996102400096	19961024	00096	SO  	1996	10	24	96ZZZX5288       	1	19960805	G	3231	8626203	TUBE            			PIPER 	PA44  	PA44180     	7104402	SO  										GEAR DOOR	ARM BROKE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	144RJ					447995323				THE ARM THAT HOLDS THE ROD FOR THE GEAR DOOR BROKE.  THIS JAMMED THE GEAR DOOR IN THE UP POSITION NOT LETTING THE GEAR G	O DOWN.					1	L	7	2 	3O				A19S0   					 
1996102400097	19961024	00097	SO  	1996	10	24	96ZZZX5289       	2	19961001	G	7414	107902010	IMPULSE COUPLING		S6RN2510    	CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  					RT MAGNETO	SPRING BROKEN   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	2700X	125  			I059114DR	18051500	1311175R5			FOUND IMPULSE COUPLING, SPRING BROKEN DUE TO CORROSION.						1	H	7	1 	3O	3	O		5A6     	E273				 
1996102400098	19961024	00098	SO  	1996	10	24	96ZZZX5290       	2	19961001	G	7414	107902010	IMPULSE COUPLING		S6RN2510    	CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  					LT MAGNETO	SPRING BROKEN   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	2700X	125  			H089109DR	18051500	1311175R5			FOUND IMPULSE COUPLING, SPRING BROKEN DUE TO CORROSION.						1	H	7	1 	3O	3	O		5A6     	E273				 
1996102400099	19961024	00099	SO  	1996	10	24	96ZZZX5291       	2	19960928	G	8530		CYLINDER        								CONT  	O520  	IO520*      	17032	SO  					NR 4 CYL EXH	SEAT WORN       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2FOR	422  					291369R			THE AIRCRAFT ARRIVED FOR 100-HOUR INSPECTION.  COMPRESSION CHECK SHOWED NR 4 CYLINDER 55/80.  ALL OTHER CYLINDERS WERE I	N THE MID 70'S.  THE CYLINDER WAS REMOVED. EXHAUST VALVE AND SEAT WERE WORN EXCESSIVELY.  THIS IS A FACTORY RE-MANUFACTU	RED ENGINE.  ALSO, FOUND, EXHAUST GUIDE WORN EXCESSIVELY, CYLINDER CHOKE AT MINIMUM SERVICE  LIMIT, AND CYLINDER .0015 I	NCH OUT OF ROUND.  ALL OTHER CYLINDERS APPEAR TO BE NORMAL.								3	O			E5CE				 
1996102400100	19961024	00100	EA  	1996	10	24	96ZZZX5292       	2	19960814	G	7314	LW154731095	PUMP            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE FUEL	PORT BLOCKED    	G				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	13	29145	30   				327940128	L1932048A			PILOT REPORTED ENGINE FAILURE DUE TO FUEL STARVATION.  CAUSE WAS A RUBBER WASHER BLOCKING THE FUEL OUTLET PORT OF A NEW 	TEXTRON FUEL PUMP.  TEXTRON SB 525 ADDRESSES THE PROBLEM.  NO AIRWORTHINESS DIRECTIVE HAS BEEN ISSUED TO DATE.  SUBMITTE	R STATED THERE ARE 4 KNOWN FAILURES FROM SAME CAUSE.  NOTE:  SAME PROBLEM AS MOONEY M20J IN OCT '96 ALERTS.				1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996102400101	19961024	00101	EU  	1996	10	24	96ZZZX5293       	1	19961003	G	2720	T67M45209	CRANK           			SLNSBY	T67   	T67M260     	8323006	EU  										RUDDER BAR	CHAFING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	3189N	289  				2213				WHILE PERFORMING AN ANNUAL INSPECTION, NOTICED LT RUDDER BAR CRANK WAS CHAFING ON RUDDER BAR WHEN BRAKE WAS APPLIED.  SU	SPECT RUDDER BAR CRANK WAS IMPROPERLY INSTALLED IN PRODUCTION.  SLINGSBY IPC CHAPTER 19, PAGES 19, 20, ITEMS 5 AND 2.					1	L	7	1 	3O			NT	A73EU   					 
1996102400102	19961024	00102	EU  	1996	10	24	96ZZZX5294       	1	19960907	G	3242	30305500	BRAKE CALIPER   	PARKERHANFIN		SLNSBY	T67   	T67M260     	8323006	EU  										RT MLG	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	17	3192X	197  				2231				DURING 100-HOUR INSPECTION, RT BRAKE CALIPER FOUND LEAKING THROUGH CASE, WHEN BRAKE WAS APPLIED.  HYDRAULIC FLUID WAS SE	EN LEAKING FROM CASE.  SUBMITTER SUSPECTS POSSIBLE IMPURITIES IN MOLD WHEN BEING MADE.  THIS IS THE SECOND OCCURRENCE.					1	L	7	1 	3O			NT	A73EU   					 
1996102400103	19961024	00103	CE  	1996	10	24	96ZZZX5295       	1	19961002	G	3230	12414231	SADDLE ASSY     			CESSNA	210   	210D        	2073414	CE  										LT MLG ACT	BROKEN          	G		A		A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			NM	11	3815Y	3008 				21058315				LEFT LANDING GEAR WOULD NOT EXTEND OR RETRACT AFTER TAKEOFF.  AN EMERGENCY LANDING WAS MADE WITH THE GEAR IN THE UP POSI	TION.  MINOR DAMAGE TO BELLY OF AIRCRAFT AND BENT PROPELLER BLADES.  FOUND BROKEN GEAR SADDLE THAT ATTACHES TO GEAR ACTU	ATOR.				1	H	7	1 	3O				3A21    					 
1996102400104	19961024	00104	SO  	1996	10	24	96ZZZX5296       	1	19960921	G	2510	AF35	HARNESS         			PIPER 	J3    	J3L         	7100542	SO  										COCKPIT	IMPROPER        	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	38345					6953				WHEN SHOULDER HARNESS IS INSTALLED PER STC NR SA 1581 GL, IT PREVENTS THE SOLO PILOT, SITTING IN THE AFT SEAT, FROM OPER	ATING EITHER THE FUEL SHUT-OFF VALVE OR THE CARBURETOR HEAT VALVE.  ONLY AN INERTIA REEL TYPE HARNESS WOULD ALLOW THIS T	YPE OF INSTALLATION TO MEET THE AIRWORTHINESS (CONTROL ACCESSIBILITY) REQUIREMENTS OF C.A.R.4A.  SUBMITTER BELIEVES THIS	 STC SHOULD BE REVIEWED ON THIS BASIS.  P/N AF35 OR AF36.			1	H	7	1 	3O				A698    					 
1996102400105	19961024	00105	CE  	1996	10	24	96ZZZX5297       	1	19960912	G	8120		TURBOCHARGER    			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  					WASTEGATE	FAILED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	19	401LF					40180018				PILOT COMPLAINED OF LOOSING POWER IN BOTH ENGINES ALTHOUGH NOT SIMULTANEOUSLY.  DURING GROUND RUN BOTH WASTEGATES WERE F	OUND STUCK IN THE OPEN POSITION.  AFTER LUBRICATING WASTEGATE SHAFTS AND MOVING THEM BY HAND, SUBSEQUENT GROUND RUNS SHO	WED NORMAL OPERATION.  FAILURE INITIALLY OCCURRED EN ROUTE AT 19,000 FEET.  MOUSE MILK WAS USED TO LUBE.  RECOMMEND REGU	LAR LUBRICATION.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996102400106	19961024	00106	SO  	1996	10	24	96ZZZX5298       	1	19960501	G	7430	A1502	SWITCH          	GERDES      		PIPER 	PA38  	PA38112     	7103812	SO  										IGNITION	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	4276E	3454 			2317F	3878A0522				IN THE OFF POSITION, ENGINE WOULD CONTINUE TO RUN ON RIGHT MAGNETO.  PROPER MAGNETO DROP OCCURRED ON EITHER LEFT OR RIGH	T MAGNETO.					1	L	7	1 	3O				A18SO   					 
1996102400107	19961024	00107	SO  	1996	10	24	96ZZZX5299       	1	19960626	G	5712	6206102	RIB             			PIPER 	PA28  	PA28151     	7102805	SO  										RT WINGWALK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	43456	4940 				287415499				DURING 100-HOUR INSPECTION, FOUND WING-WALK DOUBLER RIBS CRACKED.  FIVE OF THE RIBS WERE CRACKED AT OUTBOARD EDGE.  SUBM	ITTER SUSPECTS CAUSE WAS TOTAL TIME AND POSSIBLY STRESS INDUCED DURING FORMING OF RIBS.					1	L	7	1 	3O				2A13    					 
1996102400108	19961024	00108	CE  	1996	10	24	96ZZZX5300       	1	19960614	G	3222	AN547A	BOLT            			CESSNA	172   	172M        	2072418	CE  										NLG FORK	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	4468R	4428 				17263210				DURING ANNUAL INSPECTION AND INSTALLATION OF WHEEL PANTS, FOUND AN5-47A BOLT BENT AFTER REMOVAL.  THIS BOLT RETAINS THE 	FORK TO THE LOWER BARREL AND SECURES THE PIN BASE PLUG IN PLACE.  SUBMITTER SUSPECTS CAUSE IS HIGH TOTAL TIME WITH POSSI	BLY HARD LANDINGS				1	H	7	1 	3O			NT	3A12    					 
1996102400109	19961024	00109	CE  	1996	10	24	96ZZZX5301       	1	19960621	G	7810	15550142	CLAMP           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					EXHAUST SYSTEM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5249P	5047 				15284901	L1451415			DURING INSPECTION, FOUND SIX EXHAUST CLAMP HALVES CRACKED.  SUBMITTER SUSPECTS HIGH TOTAL TIME AND CORROSION OF EXHAUST 	PARTS.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996102400110	19961024	00110	SO  	1996	10	24	96ZZZX5302       	1	19960805	G	7810	7846310	TAILPIPE        			PIPER 	PA34  	PA34200     	7103405	SO  										LT ENGINE	BAFFLE DETACHED 	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			GL	09	56676	5945 				347450020				WHILE TROUBLESHOOTING INTERMITTENT LOSS OF POWER, FOUND BAFFLE INSIDE OF TAILPIPE HAD BROKEN LOOSE AND WEDGED NEAR OUTLE	T OF TAILPIPE.  THIS CAUSED AN INCREASE I N BACK PRESSURE WHICH CAUSED THE ENGINE TO NOT DEVELOP RATED POWER.  SUBMITTER	 SUSPECTS CAUSE, HIGH TOTAL TIME, VIBRATION, HEAT.				1	L	7	2 	3O				A7SO    					 
1996102400111	19961024	00111	SO  	1996	10	24	96ZZZX5303       	2	19960910	G	8530	642410CN	CYLINDER        			CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470R       	17026	SO  					INT RKR SHAFT	OUT OF SPEC     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	71136				28	18259509	1949268R			CYLINDER CLASS 68-1 RECEIVED WITH INTAKE ROCKER SHAFT END-PLAY IN EXCESS OF (SIDE CLEARANCE). .040 INCH RECEIVED FROM EC	 SW, 8-13-96.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996102400112	19961024	00112	EA  	1996	10	24	96ZZZX5304       	2	19960501	G	7314	LW15473	PUMP            			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  					ENGINE FUEL	PORT BLOCKED    	G		A		O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	13	7567J	12   				28R30946	L556251			PILOT REPORTED ENGINE FAILURE DUE TO FUEL STARVATION.  CAUSE WAS A RUBBER WASHER BLOCKING FUEL OUTLET PORT OF A NEW TEXT	RON FUEL PUMP.  TEXTRON SB 525 ADDRESSES THE PROBLEM.  NO AIRWORTHINESS DIRECTIVE HAS BEEN ISSUED TO DATE.  SUBMITTER ST	ATES THERE ARE 4 KNOWN FAILURES FROM SAME CAUSE.  NOTE:  SAME PROBLEM AS MOONEY M20J IN OCT '96 ALERTS.				1	L	7	1 	3O	3	O		2A13    	1E10				 
1996102400113	19961024	00113	SO  	1996	10	24	96ZZZX5305       	1	19960920	G	7921	8529245	COOLER          			PIPER 	PA28  	PA28236     	7102815	SO  										ENGINE OIL	WELD SPLIT      	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	07	8181H				791462	288011073				AIRCRAFT LOST OIL PRESSURE IN-FLIGHT.  RETURNED TO AIRPORT FOR A SAFE LANDING.  INVESTIGATION FOUND OLD WELD REPAIR ON O	IL COOLER LET GO.  METAL FOUND IN OIL FILTER.  ENGINE BEING DISASSEMBLED FOR INSPECTION.					1	L	7	1 	3O				2A13    					 
1996102400114	19961024	00114	CE  	1996	10	24	96ZZZX5306       	1	19961002	G	3260	YZ2RN7T	SWITCH          			CESSNA	182   	R182        	2072734	CE  										MLG DOWNLOCK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	7571W	1261 				R18200062				DURING ANNUAL INSPECTION, FOUND BOTH MAIN LANDING GEAR DOWNLOCK INDICATOR SWITCHES CRACKED.  BY APPLYING VERY SLIGHT SID	E PRESSURE TO SWITCHES, THEY BOTH BROKE APART.  SUSPECT CAUSE:  BOTH LEFT AND RIGHT DOWNLOCK PADS, CESSNA P/N 2241105-5,	 WERE FOUND WORN.  THIS CONDITION CAUSED THE MAIN LANDING GEAR TO STRIKE THE SWITCHES WITH TOO MUCH FORCE CAUSING THE SU	BSEQUENT CRACKS TO THE SWITCHES.  SUBMITTER RECOMMENDS REPLACEMENT OF WORN DOWNLOCK PADS OR INSTALLING CESSNA SK P/N SK1	82-8014, TO UPGRADE THE DOWNLOCK SWITCHES AND DOWNLOCK PADS, IF NOT PREVIOUSLY INSTALLED.		1	H	7	1 	3O			RT	3A13    					 
1996102400116	19961024	00116	SO  	1996	10	24	96ZZZX5308       	1	19960916	G	7713	6333	INDICATOR       			MAULE 	M7    	M7235       	5460170	SO  										ENG MAN PRESS	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	9234N	259  			175369	4119C				INDICATOR M.P. NEEDLE BECAME SLOW TO MOVE, THEN STUCK AT 25 INCHES.  DATE STAMPED 1091.  IN USE SINCE 1993.						1	H	7	1 	3O			NC	3A23    					 
1996102400117	19961024	00117	SO  	1996	10	24	96ZZZX5309       	1	19960901	G	3250	3519200	HORN ASSY       			PIPER 	PA28  	PA28151     	7102805	SO  										NLG STEERING	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	9217K	4500 				287615183				DURING ANNUAL INSPECTION OF AIRCRAFT, NOSE WHEEL STEERING HORN ASSEMBLY PIPER P/N 35 192-00, WAS FOUND TO HAVE A CRACK W	HERE IT ATTACHES TO THE OLEO STRUT.  SUSPECT CAUSE, PILOT APPLYING PRESSURE TO RUDDER PEDAL WITHOUT MOVING AIRCRAFT					1	L	7	1 	3O				2A13    					 
1996102400118	19961024	00118	NM  	1996	10	24	96ZZZX5310       	1	19960605	G	7920		HOSE            	AEROQUIP    		CHILD 	S2    	S2APITTS    	0110201	NM  										ENGINE	STIFF           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	80032	457  				2054				REMOVED VERY RIGID/STIFF OIL AND FUEL HOSES, REPLACED WITH NEW ASSEMBLIES.  HOSES WERE DATED 1971 AND 1972.  THE AIRPLAN	E IS A 1973 MODEL.  SUBMITTER CONTINUES TO FIND OLD STIFF/BRITTLE HOSES ON ANNUAL INSPECTIONS.  (THIS AIRCRAFT HAS 2 OIL	 COOLERS).				1	Q	7	1 	3O				A8SO    					 
1996102400119	19961024	00119	EA  	1996	10	24	96ZZZX5311       	2	19960902	G	7414		MAGNETO         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CAM FOLLOWER	FAILED          	D	L			A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	08	4696G		304  		67119	17273322	RL18276T			DURING CRUISE FLIGHT, ENGINE STOPPED PRODUCING POWER.  AN OFF-AIRPORT LANDING MADE WITHOUT INCIDENT.  MAINTENANCE INSPEC	TION REVEALED BOTH SETS OF POINTS IN THE DUAL 2000 SERIES MAGNETO HAD CLOSED CAUSING ENG TO STOP.  POINTS WERE RESET AND	 ENG RAN AND PRODUCED NORMAL POWER.  2.1 HRS LATER, WHILE FLYING ACFT HOME FROM THIS INCIDENT, ENG AGAIN STOPPED PRODUCI	NG POWER AND ANOTHER OFF-AIRPORT LANDING MADE WITHOUT INCIDENT.  MAINTENANCE INVEST REVEALED ONCE AGAIN POINTS HAD CLOSE	D CAUSING ENG TO STOP.  NYLON CAM FOLLOWER ON BOTH SETS OF POINTS WERE WORN COMPLETELY OFF.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996102400120	19961024	00120	EA  	1996	10	24	96ZZZX5312       	2	19960927	G	7414		MAGNETO         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CAM FOLLOWER	EXCESS WEAR     	D	L			O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SO	08	4696G		27   		H019606GR	17273322	RL18276T			AFTER INSTALLING A FACTORY REBUILT 3000 SERIES, MAGNETO AIRCRAFT WAS PLACED BACK ON RENTAL STATUS ON 9-27-96, A FLIGHT I	NSTRUCTOR NOTICED TAKEOFF POWER WAS DOWN BY APPROXIMATELY 200 RPM AT FULL THROTTLE.  MAINTENANCE INVESTIGATION REVEALED 	BOTH SETS OF MAGNETO POINTS HAD CLOSED TO APPROXIMATELY .005 INCH TO .006 INCH.  CAM FOLLOWERS ON BOTH POINTS SHOWED AN 	ABNORMAL AMOUNT OF WEAR AND THE CAM SURFACE APPEARED ROUGH AND GRAINEY.  ANOTHER REBUILT MAGNETO WAS SUPPLIED BY TCM WHI	CH HAD AN EVEN ROUGHER CAM.  BOTH MAGNETOS WERE RETURNED.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996102400364	19961024	00364	NE  	1996	10	24	96ZZZX5313       	2	19960126	G	7230	536210	TABLOCK         			SKRSKY	S64   	S64F        		NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					THIRD STAGE DISK	MISSING         	B	L		JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	159AC	1100 				64084	677815			TABLOCK FOUND MISSING AT HIDDEN DAMAGE INSPECTION CONDUCTED ON COMPRESSOR BEING PROCESSED INTO THE REPAIR STATION ON 1-2	6-96.  THE LAST OVERHAUL WAS PERFORMED BY EAC ON 8-4-94.  WHEN INSPECTING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3	RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF ENGINE (ROOT END OF BLADE).  THE BLADE MOVED AFT CON	TACTING FRONT OF STATOR DUE TO TABLOCK FAILURE.  THIS IS THE 4TH OCCURRENCE OF TABLOCK FAILURE NOTED BY ERICKSON SINCE 1	994.  ALL PROBLEMS HAVE BEEN REPORTED TO THE MANUFACTURER.		2	G	7	2 	4U	4	U		H6EA    	E15EA				 
1996102400373	19961024	00373	NE  	1996	10	24	96ZZZX5316       	3	19961010	G	6111	7826761	BEARING RACE    		RFC11M16A   	EMB   	120   	EMB120RT    		SO  						HAMSTD	14RF	14RF9       	NE  	PROPELLER BLADE	CRACKED         	B	S		NQ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	503AS				854349	120275				CRACK INDICATION IN BLADE FILLET AND BUTT AREA OF SHANK ON BOTH SIDES OF GOUGE LINE IN FILLET AREA FROM EDGE OF SPLIT RA	CES.					2	L	7	2 	4T			RT	A31SO   		6	C	P11NE	 
1996102400741	19961024	00741	CE  	1996	10	24	96ZZZX5318       	1	19961008	G	2731	07612059	SHAFT           			CESSNA	185   	A185F       	2072821	CE  										ELEV TRIM WHEEL	PIN SHEARED     	D	L			A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			SO	11	1206F	2575 				18502769				AIRCRAFT LOST ELEVATOR TRIM FUNCTION IN-FLIGHT AFTER TAKEOFF TRIMMED FOR CLIMB.  THE AIRCRAFT WAS VERY DIFFICULT TO FLY 	LEVEL AT ANYTHING LESS THAN LOW POWER.  INVESTIGATION OF THE ELEVATOR TRIM WHEEL SYS SHOWED ROLL PIN, CNAS 561-3-8, HOLD	ING THE SHAFT TO THE TRIM CHAIN SPROCKET, WAS SHEARED ALLOWING SHAFT TO ROTATE INSIDE THE SPROCKET.  REMOVAL OF THE SHAF	T FOUND THE HOLE HOLDING ROLL PIN WAS ELONGATED, LARGER THAN THE HOLE IN THE SPROCKET.  THIS IS DIFFICULT TO INSPECT, BU	T ROCKING THE TRIM WHEEL BACK AND FORTH INDICATES IF THE ROLL PIN IS LOOSE (IT SHOULD BE A TIGHT FIT).  ANY BINDING OF S	TAB JACK SCREWS PUTS A LOT OF STRAIN ON THESE ROLL PINS.  SUBMITTER STATED THIS IS A POTENTIALLY DANGEROUS SITUATION.	1	H	7	1 	3O				3A24    					 
1996102400742	19961024	00742	WP  	1996	10	24	96ZZZX5319       	2	19960928	G	7313	8682421	NOZZLE          								GARRTT	TPE331	TPE331*     	01514	WP  					ENG FUEL	THREADS CRACKED 	B			IUMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11										DEFECT - CRACKS IN THE NOZZLE THREADS.  THESE ARE VERY NOTICEABLE UPON ASSEMBLY WHEN BEING TORQUED, THEY TWIST OFF.  THE	SE TIPS COULD HAVE SEVERAL THOUSAND HOURS AND PREVIOUSLY OVERTORQUED.  A LOT OF ENGINE DAMAGE CAN BE DONE IF THESE SEPAR	ATE IN-FLIGHT.  SUBMITTER RECOMMENDATION:  CLOSE INSPECTGION OF THREAD AREA AFTER CLEANING, BEFORE ASSEMBLY.  NOTE:  OTH	ER ACCESSORY SHOPS ARE ALSO FINDING THIS PROBLEM WITH CRACKING.								3	T			E2WE				 
1996102400743	19961024	00743	WP  	1996	10	24	96ZZZX5320       	2	19960928	G	7313	8687521	NOZZLE          								GARRTT	TPE331	TPE331*     	01514	WP  					ENG FUEL	THREADS CRACKED 	B			IUMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11										DEFECT - CRACKS IN THE NOZZLE THREADS.  THESE ARE VERY NOTICEABLE UPON ASSEMBLY WHEN BEING TORQUED, THEY TWIST OFF.  THE	SE TIPS COULD HAVE SEVERAL THOUSAND HOURS AND PREVIOUSLY OVERTORQUED.  A LOT OF ENGINE DAMAGE CAN BE DONE IF THESE SEPAR	ATE IN-FLIGHT.  SUBMITTER RECOMMENDATION:  CLOSE INSPECTION OF THREAD AREA AFTER CLEANING, BEFORE ASSEMBLY.  NOTE:  OTHE	R ACCESSORY SHOPS ARE ALSO FINDING THIS PROBLEM WITH CRACKING.								3	T			E2WE				 
1996102400744	19961024	00744	NM  	1996	10	24	96ZZZX5321       	1	19961007	G	2823	9785AR	INPUT GEAR      		107796A110  	BOEING	737   	737*        		NM  										FUEL SOV	BINDING         	B			DM4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19					1073					FUEL SHUTOFF ACTUATOR ASSY WOULD STALL WITH A SLIGHT INWARD PRESSURE ON OUTPUT SHAFT.  RECENTLY OVERHAULED BY ANOTHER RE	PAIR STATION (6-20-96).  IMPROPER SHIMMING OF ARMATURE ASSY CAUSED INPUT GEAR TO RUB AGAINST ARMATURE SHAFT, ALSO, EXCES	SIVE PLAY AT OUTPUT SHAFT ALLOWED GEAR TRAIN TO MOVE AGAINST INPUT GEAR.  INCORRECT GREASE AND PACKINGS WERE USED, LOCK 	SCREWS ARE NOT HOLDING.  NOT ALL PACKINGS REPLACED.			2	L	7	2 	4F			RT	A16WE   					 
1996102400745	19961024	00745	NE  	1996	10	24	96ZZZX5322       	2	19960802	G	7313	814358	NOZZLE          								PWA   	JT8   	JT8D217     	52053	NE  					FUEL NOZZLE	NUT DETACHED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09			5195 							THE FUEL NOZZLE AS RECEIVED CONDITION FOR OVERHAUL TO CMM73-13-02 BY FST REPAIR  STATION - IUR 948M WITH THE NUT COMPLET	ELY DETACHED FROM THE NOZZLE ASSY.  THE NUT HAD LOOSENED AND MANY AREAS OF THE NUT, NOZZLE, AND SUPPORT SHOW AREAS OF SE	VERE WEAR.  SOME OF THESE AREAS ARE OVER FUEL PASSAGES, INTERNAL TO THE NOZZLE ASSY, AD 94-14-16 WAS C/W IN '95.  P AND 	W SB 6240 WAS ISSUED SUBSEQUENT TO THE LAST OVERHAUL.								4	F			E9NE				 
1996102400746	19961024	00746	SW  	1996	10	24	96ZZZX5323       	1	19961007	G	2820	AN82112	ELBOW           			GULSTM	560   	560         	0141402	SW  										FUEL DIST	LOOSE           	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	183AJ	1008 				5600276				DURING REPAIR OF FUEL PANEL, PN 611BB, RT CENTER STUB WING, THE STATED ELBOW WAS FOUND LOOSE AT BOTH B-NUTS, ONE ONLY EN	GAGED BY HALF OF A TURN.  NUTS WERE TIGHTENED AND TORQUED IAW MAINTENCE.  THIS AREA IS NOT INSPECTED UNTIL THE PHASE 5 1	,200-HOUR INSPECTION.  SUBMITTER SUSPECTS LOOSE NUTS WERE NEVER TIGHTENED AT FACTORY.				1	H	7	2 	3O				6A1     					 
1996102400747	19961024	00747	CE  	1996	10	24	96ZZZX5324       	1	19961004	G	3233	B543	BEARING         		99810057603 	BEECH 	200   	B200        	1152922	CE  										RT MLG INBD	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	113GW	2195 				BB541				DURING MAINTENANCE AND LUBRICATION OF MAIN LANDING GEAR ACTUATORS AND INSPECTION, BEARING FELL APART ON REMOVAL.  RACE, 	OUTER PORTION OF BEARING WAS BROKEN IN HALF.  BEARING SCORED.  PLATE, PN 115-811046-1, AND PLATE HAD TO BE REPLACED.					1	L	7	2 	4T				A24CE   					 
1996102400748	19961024	00748	EA  	1996	10	24	96ZZZX5325       	2	19961003	G	7261	3026889	RETAIN RING     			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENG OIL VALVE	DETACHED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3263C	30   				LJ1432	PCE25909			ON ENGINE START-UP TO IDLE, ENGINE OIL PRESSURE GAUGE SHOWED NO OIL PRESSURE.  FOUND OIL PRESSURE RELIEF VALVE RETAINING	 RING WAS NOT SEATED IN HOUSING AND RELIEF VALVE HAD FALLEN PART WAY OUT OF HOUSING.  SUBMITTER STATED WHEN INSTALLING P	RESSURE RELIEF VALVE CHECK FOR PROPER ENGAGEMENT OF RETAINING RING WITH SMALL MIRROR AND FLASHLIGHT.				1	L	7	2 	3T	4	T		3A20    	E4EA				 
1996102400749	19961024	00749	CE  	1996	10	24	96ZZZX5326       	1	19961004	G	2730	2655221303	BELLCRANK       			RKWELL	NA265 	NA26540     	6402608	CE  										ELEVATOR CONTROL	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	307NT	13742				28272				SEVERELY CORRODED MAGNESIUM BELLCRANK, PN 265-522130-3, WHICH OPERATES THE BIAS BUNGEE FOR ELEVATOR TO STABILIZER LONGIT	UDINAL CONTROL.  THIS UNIT IS LCOATED IN THE AFT LOWER LEFT SIDE OF FS 457. VISUAL INSPECTION IS VERY DIFFICULT DUE TO L	OCATION AND POSITION OF ROD END ATTACHMENT POINTS.  SUBMITTER SUGGESTS THIS ITEM BE REMOVED AND INSPECTED AT THE NEXT SC	HEDULED INSPECTION.  BELLCRANKS FAILURE WOULD CAUSE LIMITED ELEVATOR TRAVEL AND LOSS OF ELEVTOR TO STABILIZER CONTROL FO	R TRIMMING PURPOSES.  BELLCRANK REMOVED FROM SERVICE.		2	L	7	2 	4J				A2WE    					 
1996102400750	19961024	00750	CE  	1996	10	24	96ZZZX5327       	1	19961004	G	2730	2655221303	BELLCRANK       			RKWELL	NA265 	NA26540     	6402608	CE  										ELEV CONTROL	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	317NT	8024 				282100				SEVERELY CORRODED MAGNESIUM BELLCRANK PN 265-522130-3 WHICH OPERATES THE BIAS BUNGEE ELEVATOR TO STABILIZER LONGITUDINAL	 CONTROL.  THIS UNIT IS LOCATED IN THE AFT LOWER LEFT SIDE OF FS 457.  VISUAL INSPECTION IS VERY DIFFICULT DUE TO LOCATI	ON AND POSITION OF ROD END ATTACHMENT POINTS.  SUBMITTER SUGGESTS THIS ITEM BE REMOVED AND INSPECTED AT THE NEXT SCHEUDL	ED INSPECTION.  BELLCRANKS FAILURE WOULD CAUSE LIMITED ELEVATOR TRAVEL AND LOSS OF ELEVATOR TO STABILIZER CONTROL FOR TR	IMMING PURPOSES.  BELLCRANK REMOVED FROM SERVICE.		2	L	7	2 	4J				A2WE    					 
1996102400751	19961024	00751	CE  	1996	10	24	96ZZZX5328       	1	19960923	G	2150	1179100609	PIVOT PLATE     			BEECH 	B300  	B300        	1159232	CE  										LT ENG ACCY BOX	EAR BROKEN      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	550TP	1224 				FL35				AIR CONDITIONER COMPRESSOR PIVOT PLATE HAD EAR BROKEN OFF THAT MOUNTS THE COMPRESSOR ONTO THE ENGINE ACCESSORY AREA.  TH	IS IS THE THIRD SUCH DEFECT FOUND ON THIS PART,  ALSO, FOUND COMPRESSOR DRIVE BELT BROKEN AND DRIVE BELT PULLEY DESTROYE	D BY OVERHEATED BEARING.  BEARING PIN IS 206S22C AND MADE BY (MRC BEARINGS INC.)  BEARING ONLY HAD 200 HOURS TOTAL ON IT	.  SUBMITTER SUGGESTS ALL FAILURES ARE RELATED TO ONE ANOTHER.			2	L	7	2 	4T			RT	A24CE   					 
1996102400752	19961024	00752	CE  	1996	10	24	96ZZZX5329       	1	19960922	G	3213	508100324	TORQUE KNEE     			BEECH 	90    	E90         	1152914	CE  										RT MLG	BROKE           	D		A		C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			NM	03	5911P	7522 				LW70				RT UPPER TORQUE KNEE BROKE AT PIVOT POINT WHERE THE LOWER TORQUE KNEE ATTACHES TO IT.  THE PILOT WAS ON TAKEOFF ROLL WHE	N HE THOUGHT HE HAD A RT MAIN TIRE BLOW.  HE THEN BROUGHT THE ACFT TO A STOP.  WHEN THE TORQUE KNEE BROKE, THE TIRE SPUN	 AROUND AND RIPPED HALF THE TREAD OFF THE TIRE.  AIRCRAFT TOTAL LANDINGS, 8,499.				1	L	7	2 	3T				3A20    					 
1996102400755	19961024	00755	SW  	1996	10	24	96ZZZX5331       	1	19960223	G	5320	4715011713	SLEEVE ASSY     			BELL  	47    	47G2A       	1181012	SW  										FUSELAGE	WELD FAILED     	B			MT1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	8522F	4768 				7800				BRACKET WELDS EXHIBIT FAILURE AT TOE OF WELD AT SLEEVE.  FAILURE OBSERVED VIA FLUORESCENT MAGNETIC PARTICLE INSPECTION.						1	G	7	1 	3O				2H3     					 
1996102400756	19961024	00756	SO  	1996	10	24	96ZZZX5332       	1	19960910	G	5741	404532V	NUTS            			PIPER 	PA34  	PA34200T    	7103406	SO  										LT WING SPAR	CRACKED         	H			AY8V	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	68KS					347770252				FOUND 2 NUTS SPLIT ON LT LOWER WING SPAR ATTACH POINT OUTSIDE CABIN.  NUTS WERE CRACKED WHEN A/C WAS PAINTED 3 YEARS AGO	.  PIPER SB 602 COVERS INSPECTION OF THESE NUTS, NO RECORD OF COMPLIANCE.					1	L	7	2 	3O				A7SO    					 
1996102400757	19961024	00757		1996	10	24	96ZZZX5333       	1	19961009	G	6123	D5012	HOUSING         																	FEATHER SPRING	CRACKED         	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15										UPON TEAR-DOWN AND INSPECTION OF PROPELLER, FEATHER SPRING HOUSING WAS FOUND CRACKED.  PART HAS BEEN SCRAPPED.																			 
1996102400760	19961024	00760	CE  	1996	10	24	96ZZZX5336       	1	19960826	G	2810		GASKET          			CESSNA	180   	180F        	2072614	CE  										FUEL CAP	FAILED          	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21	2125Z					18051225				UMBRELLA-TYPE FUEL CAP GASKET WAS WEATHERED AND CRACKED AROUND RADIUS.  ONE CRACK WAS COMPLETELY THROUGH THE GASKET CAUS	ING FUEL SYPHONING.  SUBMITTER STATED INSPECT GASKET DURING PRE-FLIGHT INSPECTIONS.  REPLACE AS NECESSARY.					1	H	7	1 	3O				5A6     					 
1996102400761	19961024	00761	SO  	1996	10	24	96ZZZX5337       	2	19961002	G	8520		CRANKCASE       			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  					NR 5 CYL STUD	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	1096W	417  				CE436	S69112			ON 10-2-96 MAINTENANCE WAS NOTIFIED OF AN OIL LEAK ON THE ENGINE.  UPON FURTHER INVESTIGATION, A CRACK WAS NOTED ABOVE T	HE TOP FORWARD CYLINDER HOLD DOWN STUD OF THE NR 5 CYLINDER.  SUSPECT CAUSE OVERTORQUEING OR TORQUEING SEQUENCE.  SUBMIM	TTER STATED CLOSE INSPECTION OF THESE AREAS WILL PREVENT FURTHER DAMAGE.				1	L	7	1 	3O	3	O		3A15    	E5CE				 
1996102400762	19961024	00762	SO  	1996	10	24	96ZZZX5338       	1	19960715	G	3211	402960	BOLT            			PIPER 	PA28  	PA28R200    	7102811	SO  										MLG TRUNNION	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	33075					28R7535116				WHILE REPAIRING MLG, ORDERED 2 BOLTS, PIPER PN 402-960 (NAS 464P8A-44) THAT ATTACHES THE MAIN GEAR TRUSS ASSY (452-368) 	TO THE MLG TRUNNION.  WHEN INSTALLED, THESE BOLTS INTERFERE WITH GEAR RETRACTION BECAUSE THE HEX HEAD CONTACTS THE GEAR 	DOOR RETRACTION ROD.  FURTHER INVESTIGATION DISCOVERED THE OLD P/N 400-810 (AN28-50A) AS THE ONLY BOLT THAT WILL WORK DU	E TO CLEVIS HEAD BEING A SMALLER DIMENSION THAN THE HEX HEAD NAS BOLT.  BOTH PART NUMBERS WERE STILL VALID WITH PIPER.			1	L	7	1 	3O				2A13    					 
1996102400763	19961024	00763	CE  	1996	10	24	96ZZZX5339       	1	19960913	G	3260		SWITCH          			CESSNA	310   	310R        	2074245	CE  										RT MLG	WIRE DETACHED   	D				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	07	3700G					310R0899				(OMA) RT MAIN GEAR HAS NO DOWN AND LOCK INDICATIONS.  RT GEAR SWITCH GROUND WIRE PULLED FROM LUG.  REPAIRED GROUND WIRE,	 PERFORMED RETRACTION, CHECK OK.					1	L	7	2 	3O				3A10    					 
1996102400764	19961024	00764	SO  	1996	10	24	96ZZZX5340       	1	19960930	G	3231		DOOR            			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			GL	07	3547C					318052018				(CMH) GEAR DOORS DID NOT COME UP ON GEAR RETRACTION.  CYCLED GEAR WORKED NORMALLY.						1	L	7	2 	3O				A20SO   					 
1996102400765	19961024	00765	SO  	1996	10	24	96ZZZX5341       	2	19960907	G	8530	646657A2	CYLINDER        			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					NR 5	HEAD SEPARATED  	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	03	44C					P21000311	513319			DURING CRUISE ENGINE BECAME ROUGH RUNNING.  EMERGENCY LANDING WAS MADE.  INVESTIGATION REVEALED HEAD SEPARATION OF CYLIN	DER.					1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996102400767	19961024	00767	GL  	1996	10	24	96ZZZX5343       	1	19961011	G	3710	EGB03003	FILTER          			BLANCA	17    	1730        	1220432	GL  										VACUUM INLET	BLOCKED YOKE    	H		A		K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	03	6667V					30018				FILTER PREVENTED YOKE FROM FORWARD MOVEMENT.  WHEN FILTER WAS INSTALLED IT WAS NOT HARD MOUNTED.  HOSES WERE HOLDING FIL	TER.  HOSE CLAMP LOOSENED ALLOWING FILTER TO MOVE.  HARD MOUNTED FILTER TO AIRCRAFT FRAME USING LOCKNUT AND ADEL CLAMP. 	 REPLACED HOSES.  SUBMITTER STATED NO LOCATION FOUND IN AIRCRAFT MANUALS FOR FILTER INSTALL.				1	L	7	1 	3O				1A3     					 
1996102400768	19961024	00768	NM  	1996	10	24	96ZZZX5344       	1	19960918	G	3260	588244	SWITCH          			PIPER 	PA60  	PA60600     	7106001	NM  										NLG WOW	WIRE BROKEN     	D				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			GL	07	6896B					600919816126				NO GEAR DOWN AND LOCK INDICATION.  FOUND BROKEN WIRE ON NOSE GEAR SQUAT SWITCH.  REMOVED AND REPLACED SWITCH.  OPS CHECK	S GOOD.					1	M	7	2 	3O			RT	A17WE   					 
1996102400769	19961024	00769	CE  	1996	10	24	96ZZZX5345       	1	19961011	G	2841	SK172118A	GAUGE           	ROCHSTRGAUGE	C669562019  	CESSNA	172   	172N        	2072434	CE  										LT FUEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	739TX				394	17270803				OUT OF BOX FAILURE OF LT FUEL GAUGE.  NEED SOME QUALITY CONTROL.  ROCHESTER, P/N 6247-00133.						1	H	7	1 	3O			NT	3A12    					 
1996102400770	19961024	00770	CE  	1996	10	24	96ZZZX5346       	1	19961011	G	2841	SK172118A	GAUGE           	ROCHSTRGAUGE	C669562019  	CESSNA	172   	172N        	2072434	CE  										LT FUEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	739TX				398	17270803				THE FUEL GAUGE FAILED OUT OF THE BOX.  THE GAUGE FAILED BEFORE INSTALLATION.  RECOMMEND BETTER QUALITY CONTROL.  ROCHEST	ER, P/N 6247-00133.					1	H	7	1 	3O			NT	3A12    					 
1996102400771	19961024	00771	CE  	1996	10	24	96ZZZX5347       	1	19961011	G	2841	SK172118A	GAUGE           	ROCHSTRGAUGE	C669562019  	CESSNA	172   	172N        	2072434	CE  										RT FUEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	739TX				403	17270803				THIRD OUT OF BOX FAILURE FOR THIS TYPE GAUGE IN THREE DIFFERENT FUEL GAUGE KITS.  ROCHESTER, P/N 6247-00133.						1	H	7	1 	3O			NT	3A12    					 
1996102400772	19961024	00772	GL  	1996	10	24	96ZZZX5348       	3	19961003	G	6111	V84337	BLADE           		U84337      	PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CRACKED         	B		A	W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	7662P		665  			242875		1556		PROPELLER WAS SUBMITTED FOR OVERHAUL BY OWNER AND FBO DUE TO AGE. PROPELLER HAD BEEN OVERHAULED 5 YEARS AGO AND 665.26 H	RS AND THE OWNER AND MECHANICS FELT AN INSP WAS IN ORDER.  UPON DISASSEMBLY AND INSPECTION OF BLADE SHANKS PER AD 68-19-	04, THE SHANKS WERE FOUND CRACKED IN RADII REFERENCED IN AD AND IN SERVICE DOCUMENTS LISTED IN AD.  EDDY CURRENT INSP CO	NFIRMED PENETRANT INSP RESULTS.  SUBMITTER'S OPINION THAT HAD THE OWNER DECIDED TO FLY UNTIL REACHING THE HOUR LIMIT OF 	1000 HRS ALLOWED BY AD 68-19-04, ONE OR MORE OF THE BLADES WOULD HAVE SEPARATED, AS THE SHANKS ARE CRACKED APPROX ONE-HA	LF THE CIRCUMFERENCE OF THE SHANK.	1	L	7	1 	3O				1A15    		5	C	P23EA	 
1996102400773	19961024	00773	GL  	1996	10	24	96ZZZX5349       	3	19961003	G	6111	V84337	BLADE           		U84337      	PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CRACKED         	B		A	W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	7662P		665  			242875		1556		PROPELLER WAS SUBMITTED FOR OVERHAUL BY OWNER AND FBO DUE TO AGE. PROPELLER HAD BEEN OVERHAULED 5 YEARS AGO AND 665.26 H	RS AND THE OWNER AND MECHANICS FELT AN INSP WAS IN ORDER.  UPON DISASSEMBLY AND INSPECTION OF BLADE SHANKS PER AD 68-19-	04, THE SHANKS WERE FOUND CRACKED IN RADII REFERENCED IN AD AND IN SERVICE DOCUMENTS LISTED IN AD.  EDDY CURRENT INSP CO	NFIRMED PENETRANT INSP RESULTS.  SUBMITTER'S OPINION THAT HAD THE OWNER DECIDED TO FLY UNTIL REACHING THE HOUR LIMIT OF 	1000 HRS ALLOWED BY AD 68-19-04, ONE OR MORE OF THE BLADES WOULD HAVE SEPARATED, AS THE SHANKS ARE CRACKED APPROX ONE-HA	LF THE CIRCUMFERENCE OF THE SHANK.	1	L	7	1 	3O				1A15    		5	C	P23EA	 
1996102400774	19961024	00774	SW  	1996	10	24	96ZZZX5350       	1	19961003	G	2752	240014025	BRACKET         			MOONEY	M20   	M20C        	5870208	SW  										FLAP ACTUATOR	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	7150V	4345 				200037				INSPECTION FOUND BOTH FLAP ACTUATOR BRACKETS WITH INNER GRANULAR CORROSION.						1	L	7	1 	3O				2A3     					 
1996102400775	19961024	00775	SW  	1996	10	24	96ZZZX5351       	1	19961003	G	2752	240014026	BRACKET         			MOONEY	M20   	M20C        	5870208	SW  										FLAP ACTUATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	7150V	4345 				200037				INSPECTION FOUND BOTH FLAP ACTUATOR BRACKETS WITH INNER GRANULAR CORROSION.						1	L	7	1 	3O				2A3     					 
1998042300054	19980423	00054	WP  	1998	4	23	96ZZZX5352       	2	19960905	G	7230		BLADE           			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					RT ENGINE	FOD             	H				O				OTHER                   				C			F.O.D.                    			TO	TAKEOFF        	1			GL	07	130F					044	874216			RT ENGINE BIRD FOD ON TAKEOFF.  BENT 7-8 FAN BLADES.  HAD GARRETT IN LONG ISLAND REMOVE AND REPLACE BLADES AND C/W BALAN	CE.					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1998042300056	19980423	00056	NM  	1998	4	23	96ZZZX5354       	1	19960920	G	5320		FLANGE          			BOEING	727   	72722C      	138400F	NM  										FS 940 RT	CRACKED         	B			XE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	427EX					19090				INSPECTION FOUND 1.50 INCH CRACK AT BS 940, RT SIDE FWD FLANGE.  FLOOR LEVEL.  SUSPECT CAUSE FATIGUE.						2	L	7	3 	4F				A3WE    					 
1998042300057	19980423	00057	NM  	1998	4	23	96ZZZX5355       	1	19960918	G	5320		INTEGRAL RIB    			BOEING	727   	72722C      	138400F	NM  										FS 950 LT	CRACKED         	B			XE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	427EX					19090				INSPECTION FOUND 3 INCH CRACK AT BS 950 LT/INTEGRAL RIB, STR 13L.  SUSPECT CAUSE:  FATIGUE.						2	L	7	3 	4F				A3WE    					 
1998042300058	19980423	00058	NM  	1998	4	23	96ZZZX5356       	1	19960918	G	5320		INTEGRAL RIB    			BOEING	727   	72722C      	138400F	NM  										FS 870 RT	CRACKED         	B			XE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	427EX					19090				INSPECTION FOUND 1.50 INCH CRACK AT BS 870 RT, INTEGRAL RIB STR 13R.  SUSPECT CAUSE:  FATIGUE.						2	L	7	3 	4F				A3WE    					 
1998042300059	19980423	00059	NM  	1998	4	23	96ZZZX5357       	1	19960920	G	5320		FLANGE          			BOEING	727   	72722C      	138400F	NM  										FS 940 LT	CRACKED         	B			XE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	427EX					19090				INSPECTION FOUND .50 INCH CRACK AT BS 940 LT SIDE AFT FLANGE AT FLOOR BEAM LEVEL.  SUSPECT CAUSE:  FATIGUE.						2	L	7	3 	4F				A3WE    					 
1998042300060	19980423	00060	SW  	1998	4	23	96ZZZX5358       	1	19961002	G	5541	5533110148	RIB             			GULSTM	560   	560         	0141402	SW  										RUD INTERSPAR	CRACKED         	B			PAZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	560GL	1658 				5600079				DURING PHASE INSPECTION, FOUND RUDDER TO HAVE UNUSUAL NOISE WHEN MOVED.  NO EXTERNAL DEFECTS NOTED.  INSPECTED WITH BORE	SCOPE AND FOUND RIB WITH APPROXIMATELY 2.3750 INCH CRACK ORIGINATING AT FORWARD LIGHTENING HOLE.  NEW RIB INSTALLED AND 	RUDDER BALANCED.				1	H	7	2 	3O				6A1     					 
1998042300061	19980423	00061	NE  	1998	4	23	96ZZZX5359       	2	19960913	G	7310	AN62353A	FILTER          			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					FUEL DISCHARGE	MISINSTALLED    	H	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	79TE	2    				FA67	PCE95140			FILTER PACKING WAS INSTALLED AT 150-HOUR NR 2 INTERIM INSP.  O-RING HAD BEEN ROLLED DURING INSTALLATION 1.8 HRS.  TOO SM	ALL OF SAFETY WIRE USED ON RT ENGINE ON FUEL FILTER BOWL ALSO.					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998042300062	19980423	00062	NM  	1998	4	23	96ZZZX5360       	1	19960903	G	2751	S508315	SUPPORT         			BOEING	707   	707*        		NM  										AILERON	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					19295					WHILE REPLACING L/E WEBS IN  HINGE AREA, NOTED FITTING (SUPPORT WAS CRACKED IN AREAS OF FASTENER HOLES.  POSSIBLE CAUSE,	 SHOOTING 'D' RIVETS IN MAGNESIUM SUPPORT.  RECOMMEND USING 'B' RIVETS.					2	L	7	4 	4J			RT	4A21    					 
1998042300063	19980423	00063	NM  	1998	4	23	96ZZZX5361       	1	19960920	G	2620		HOSE            			ISRAEL	1125  	1125        	       	NM  										APU FIRE EXT	BLOCKED         	B	L	A	JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09										THE BLOCKAGE WAS DISCOVERED DURING THE MODIFICATION PROCESS.  THE TECHNICIAN HAD CUT THE HOSE ON A BAND SAW, INSTALLED T	HE SOCKET PORTION OF THE FITTING AND STARTED TO INSTALL THE B-NUT, ONLY 1 OR 2 TURNS.  TECH DECIDED TO CHAMFER INSIDE OF	 HOSE TO ALLOW EASIER INSTALLATION OF FITTING.  TECH REMOVED FITTNG AND INSERTED A SMALL ROUND FILE INTO OPEN END OF HOS	E.  THE FILE WOULD NOT PASS THROUGH THE HOSE.  AT THIS TIME,  NOTED THE INNER HOSE HAD RETRACTED ABOUT .50 INCH FROM THI	S CUT-OFF.  THE HOSE WAS CUT LENGTHWISE TO EXPOSE THE BLOCKAGE.  IT APPEARS THE INNER HOSE WAS TWISTED 90-DEGREES DURING	 MFG PROCESS CAUSING IT TO KINK AND CLOSE INTERNALLY.	2	L	7	2 	4F			RT	A16NM   					 
1998042300064	19980423	00064	GL  	1998	4	23	96ZZZX5362       	2	19960516	G	7250	6870832	COUPLING        								ALLSN 	250C  	250C20      	03013	GL  					POWER TURBINE	DAMAGED SPLINES 	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17					26903					THE DEFECT WAS DISCOVERED DURING INSPECTION OF THE PART ON RECEIPT FROM A 3RD PARTY VENDOR.  THE ALLISON GAS TURBINE 250	-C20 SERIES OVERHAUL MANUAL PROVIDES IN TABLE VI-19 INSPECTION CRITERIA FOR POWER TURBINE COUPLINGS.  ITEM 58 OF THIS TA	BLE, ON PAGE 6-119 ALLOWS NO DAMAGE SUCH AS 'NICK, CHIPS, GROOVES' IN THE SPLINE TEETH.  THE DAMAGED TOOTH CLEARLY RENDE	RS THIS SHAFT UNSERVICEABLE.								3	U			E4CE				 
1998042300065	19980423	00065	GL  	1998	4	23	96ZZZX5363       	2	19960516	G	7250	23037403	INNER SHAFT     								ALLSN 	250C  	250C20B     	03013	GL  					POWER TURBINE	PITTED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17					74872					THE DEFECT DESCRIBED BELOW WAS DISCOVERED DURING INSPECTION OF THE PART ON RECEIPT FROM A 3RD PARTY VENDOR.  THE ALLISON	 GAS TURBINE 250-C20 SERIES OVERHAUL MANUAL, TABLE VI-19, PAGE 6-114, PROVIDES INSPECTION CRITERIA FOR POWER TURBINE INN	ER SHAFTS.  ITEM 27A PROVIDES THE BEARING RACE PITTING SERVICEABLE LIMITS.  'NO PIT LARGER THAN 0.006 INCH WHICH CAN DEF	INITELY BE FELT WITH A 0.030 INCH RADIUS SCRIBER' IS ALLOWED.  SEVERAL PITS CAN BE DETECTED WITH A 0.030 INCH SCRIBER, T	HEREFORE, THIS SHAFT IS NOT SERVICEABLE.							3	U			E4CE				 
1998042300066	19980423	00066	CE  	1998	4	23	96ZZZX5364       	1	19960925	G	3211	9012006092	SUPPORT         		901200602   	BEECH 	90    	C90A        	1152911	CE  										RT MLG OTBD	CRACKED         	B	S	A	DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	301ER	2833 				LJ1286				DURING A ROUTINE PHASE INSPECTION, RT MLG RETRACT CLYINDER SUPPORT BRACKETS (ONE INBOARD, ONE OUTBOARD) WERE FOUND CRACK	ED 50 PERCENT OF THEIR LENGTH.  DURING LANDING GEAR RETRACT TEST ON JACKS, CRACKS WERE OBSERVED OPENING WIDE.  AIRCRAFT 	SENT TO DEALERSHIP MAINTENANCE SHOP FOR REPAIR.				1	L	7	2 	3T			RT	3A20    					 
1998042300067	19980423	00067	CE  	1998	4	23	96ZZZX5365       	1	19960925	G	3211	9012006094	SUPPORT         		901200602   	BEECH 	90    	C90A        	1152911	CE  										RT MLG INBD	CRACKED         	B		A	DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	301ER	2833 				LJ1286				DURING A ROUTINE PHASE INSPECTION, RT MLG RETRACT CLYINDER SUPPORT BRACKETS (ONE INBOARD, ONE OUTBOARD) WERE FOUND CRACK	ED 50 PERCENT OF THEIR LENGTH.  DURING LANDING GEAR RETRACT TEST ON JACKS, CRACKS WERE OBSERVED OPENING WIDE.  AIRCRAFT 	SENT TO DEALERSHIP MAINTENANCE SHOP FOR REPAIR.				1	L	7	2 	3T			RT	3A20    					 
1998042300068	19980423	00068	CE  	1998	4	23	96ZZZX5366       	1	19961004	G	5210	1313232C15	PIN             		1014300301  	BEECH 	200   	200BEECH    	1152920	CE  										CABIN DOOR HOOK	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	113GW	5802 				BB541				MAINTENANCE FOUND FORWARD CABIN DOOR HOOK-PIN MOVING.  DISASSEMBLED, PIN WORN ABOUT HALF WAY INTO AND BROKEN IN HALF, FA	ILED.  SUBMITTER SUGGESTS CAUSE MAY BE POOR LUBRICATION OR NOT DONE AT PROPER INTERVALS, AND NEEDS TO BE INSPECTED AT PR	OPER HOURS.				1	L	7	2 	4T				A24CE   					 
1996110100367	19961101	00367	CE  	1996	11	1	96ZZZX5400       	1	19961007	G	2810	10132006121	VALVE           			BEECH 	200   	200BEECH    	1152920	CE  										FUEL ANTISIPHON	DAMAGED         	B		A	HBKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	6HU					BB319				DURING INSP BOTH ANTI-SIPHON VALVES AT THE LT AND RT FUEL FILLER PORTS WERE FOUND DAMAGED.  FLAPPER-TYPE VALVES ARE INTE	NDED TO PREVENT FUEL LOSS AND FUEL CELL DAMAGE IF THE FUEL CAPS ARE LEFT OFF PRIOR OR LEAK DURING FLIGHT.  DIFFICULT TO 	INSERT STANDARD SIZE JET FUEL NOZZLE INTO THE CELL WITHOUT DAMAGING THE ANTI-SIPHON VALVE.  THE NOZZLE MUST BE INSERTED 	AT AN ANGLE AND WEDGED INTO THE VALVE ASSEMBLY TO PREVENT FUEL FROM SPRAYING BACK ON THE FUELLER.  THE VALVES SOON BECOM	E DAMAGED TO THE POINT THEY NO LONGER SEAL AFTER THE NOZZLE HAS BEEN REMOVED.  SUBMITTER STATED MUST INSTALL NEW VALVES 	AT NEARLY EVERY KING-AIR 200 INSPECTION.	1	L	7	2 	4T				A24CE   					 
1996110100368	19961101	00368	SO  	1996	11	1	96ZZZX5401       	1	19960901	G	7197		WIRE            			PIPER 	PA31T 	PA31T       	7103124	SO  										ENGINE COMP	SHORTED         	B			XZJR	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SO	17	737WB					31T7620052				WIRES IN THE ENGINE COMPARTMENTS RUNNING BY EXHAUST DUCTS ARE MELTING AND SHORTING OUT DUE TO LONG TERM EXPOSURE TO HEAT	.  SUBMITTER RECOMMENDS INSULATED WIRES WITH FIRE SLEEVE BE INSTALLED TO PREVENT RECURRENCE.					1	L	7	2 	3T			 	A8EA    					 
1996110100369	19961101	00369	SO  	1996	11	1	96ZZZX5402       	1	19961001	G	5280	6709304	DOOR ASSY       			PIPER 	PA32  	PA32R301    	7103218	SO  										LT MLG DOOR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	226DT					3246006				LEFT MLG DOOR CRACKED JUST ABOVE ROD END ATTACH POINT.  EXCESSIVE VIBRATION FROM SLIP STREAM, SUSPECT CAUSE OF THE CRACK	.  NOTE:  SUBMITTER STATED THIS DEFECT HAS BEEN OBSERVED BEFORE.  RECOMMEND REINFORCING AFFECTED AREAS OF THE DOOR OR RE	PLACE WITH AN ALUMINUM DOOR.  PART TOTAL TIME IN SERVICE 187.2 HOURS.				1	L	7	1 	3O				A3SO    					 
1996110100370	19961101	00370	GL  	1996	11	1	96ZZZX5403       	3	19960901	G	6111	517	BLADE           			PIPER 	PA32  	PA32300     	7103212	SO  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER	TIP LOST        	D				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			SW	99	32139	517  				327540017		CH20126		LOST APPROXIMATELY 6.5 INCHES OF PROPELLER TIP JUST PRIOR TO LANDING AFTER A 30-MINUTE FLIGHT.  NO OTHER DAMAGE FOUND TO	 AIRCRAFT AFTER COMPLETE INSPECTION.					1	L	7	1 	3O				A3SO    		5	C	P920	 
1996110100371	19961101	00371	SO  	1996	11	1	96ZZZX5404       	2	19961009	G	8520	643207	CRANKCASE       			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 2 MAIN	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	37U	1379 				414A0010	276971R			AFTER REMOVAL OF CYLINDER NR 4 DUE TO A LEAKING EXHAUST VALVE, A 4 INCH CRACK WAS FOUND STARTING AT THE NR 2 MAIN JOURNA	L.  THIS CRACK STARTED AT THE BEARING SURFACE AND PROGRESSED TO THE INSIDE OF THE CASE BETWEEN CYLINDERS NR 2 AND 4.  NO	 EVIDENCE OF A CRACK WAS FOUND ON THE OUTSIDE OF THE CASE.  SUBMITTER STATED THIS IS THE 3RD CRACK FOUND IN THIS AREA ON	 3 DIFFERENT ENGINES.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996110100372	19961101	00372	CE  	1996	11	1	96ZZZX5405       	1	19961016	G	7160	165201338	DUCT ADAPTER    			CESSNA	182   	182Q        	2072732	CE  										ALTERNATE AIR	DOOR BROKEN     	B		A	P3NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5144N	587  				18267543				DURING AN INVESTIGATION FOR DAMAGE FROM AN INTAKE FIRE, THE ALTERNATE AIR DOOR WAS FOUND BROKEN LOOSE FROM THE FIBERGLAS	S AIR DUCT.  THIS AIRCRAFT HAS BEEN MODIFIED IAW A PETERSON 260 SE/STOL CONVERSION.  THIS DOOR COULD BLOCK THE AIR FLOW 	TO THE INTAKE SYSTEM.  SUBMITTER RECOMMENDS PERIODIC INSPECTION OF THE ALTERNATE AIR DOOR MOUNTING SECURITY.  ALSO, RECO	MMEND A DRAIN SYSTEM TO PREVENT FIRE HAZARD DURING STARTING.			1	H	7	1 	3O			NT	3A13    					 
1996110100374	19961101	00374	CE  	1996	11	1	96ZZZX5407       	1	19960927	G	3244	800X6X6	TIRE            	MCCREARY    		CESSNA	172   	172M        	2072418	CE  										LT MLG	RUBS CALIPER    	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	20109					17261017				BRAKE CALIPER DRAGS WHEN TIRE INSTALLED ON AIRCRAFT.  MEASURED LEFT AND RIGHT HAND TIRE SIDEWALL WHEN PRESSURED TO 28 PS	I.  LEFT TIRE SIDEWALL 1.25 INCH WIDER THAN RIGHT TIRE.					1	H	7	1 	3O			NT	3A12    					 
1996110100375	19961101	00375	CE  	1996	11	1	96ZZZX5408       	1	19961004	G	3211	2411001	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  										LT MLG	SHAFT SHEARED   	H		A	OQDV	O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CE	07	5204U	6790 				172RG0282				LEFT MAIN GEAR WOULD NOT INDICATE DOWN AND LOCK WHEN THE GEAR WAS SELECTED DOWN.  THE PILOT LANDED WITH GEAR UP.  THE LT	 MAIN GEAR ASSY WAS REMOVED FROM THE AIRCRAFT AND IT WAS DISCOVERED THE PIVOT SHAFT OF THE PIVOT ASSY HAD SHEARED FROM T	HE MAIN BODY OF THE PIVOT ASSY.				1	H	7	1 	3O				3A17    					 
1996110100376	19961101	00376	EA  	1996	11	1	96ZZZX5409       	2	19961006	G	8520	LW11750	CONNECT ROD     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540J4A5   	41532	EA  					NR 6 CYL	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	6730Y		991  			274062	L647748			ROD FOR CYLINDER NR 6 FAILED AT CRANKSHAFT END.  UNABLE TO TELL IF ROD OR ROD BOLTS FAILED BECAUSE OF DAMAGE.						1	L	7	2 	3O	3	O		1A10    	1E4				 
1996110100377	19961101	00377	GL  	1996	11	1	96ZZZX5410       	3	19961009	G	6114	D32512	HUB             			PIPER 	PA44  	PA44180T    	7104404	SO  						HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	838PC	2000 				448107056		CK2593		AFTER CLEANING OF HUB AND NDT, HUB WAS CORRODED BADLY ON THE INSIDE OF THE HUB ONLY.  THE CAUSE OF THIS IS THE USE OF NO	N-APPROVED AUTO GREASE.  SUBMITTER STATED IF THIS WAS NOT FOUND, IT IS POSSIBLE A CRACK AND FAILURE OF THE HUB WOULD OCC	UR.				1	L	7	2 	3O				A19SO   		5	C	P25EA	 
1996110100379	19961101	00379	CE  	1996	11	1	96ZZZX5412       	1	19961001	G	5320		STRUCTURE       			CESSNA	414   	414A        	2075907	CE  										NOSE WHEELWELL	CORRODED        	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	414JK					414A0626				CORROSION FOUND AROUND THE HOLES (WHEELWELL-NOSE) AREA WHERE THE BLACK HEAT DUCT TUBING THAT RUNS THROUGH STRUCTURE MAKE	S CONTACT WITH THE ALUMINUM.  FOUND THIS ON  A 1981 CESSNA 414A WITH A TOTAL TIME OF 4900 HRS AND ALSO 1981 CESSNA 425 W	ITH 6203 HRS.				1	L	7	2 	3O				A7CE    					 
1996110100380	19961101	00380	CE  	1996	11	1	96ZZZX5413       	1	19961004	G	3230	51001116	NITROGEN LINE   			CESSNA	414   	414A        	2075907	CE  										BLOW DOWN BOTTLE	RUPTURED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	414JK	4900 				414A0626				FOUND CORROSION ON THE NITROGEN LINE FROM THE EMERGENCY GEAR BLOW DOWN BOTTLE WHERE IT WAS IN CONTACT WITH BLACK HEAT DU	CT.  THERE WAS NO CORROSION FOUND ON THE LINE EXCEPT WHERE IT MADE CONTACT WITH THE HEAT DUCT.  WHEN THE EMERGENCY GEAR 	DOWN BOTTLE ACTIVATED, THIS NITROGEN LINE RUPTURED AT THE CORRODED AREA. THIS WAS ON A 1981 CESSNA 414A WITH TOTAL TIME 	OF 4900 HRS.			1	L	7	2 	3O				A7CE    					 
1996110100381	19961101	00381	NE  	1996	11	1	96ZZZX5414       	2	19960906	G	7322	2523973	SPOOL BEARING   	BENDIX      	430124803   						LYC   	LTS101	LTS101750B2 	41560	NE  					FUEL CONTROL	NOT LUBED       	B		A	ESER	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11					86010299					USCG FUEL CONTROL RECEIVED FROM BENDIX WEST COAST AS ZERO HOURS TSO REQUIRED UPGRADE IAW GT 264 AND GT 279.  IN THE PROC	ESS OF DISASSEMBLY DISCOVERED THE BLUE GREASE RESERVOIR IN THE SPOOL BEARING CAP HAD NEVER BEEN FILLED.  THIS CONDITION 	HAS BEEN CITIED IN THE PAST AS BEING A CAUSE OF SPOOL BEARING FAILURE.									3	U			E5NE				 
1996110100382	19961101	00382	CE  	1996	11	1	96ZZZX5415       	1	19960830	G	3213	6041100018	MAIN GEAR       			LEAR  	60    	60LEAR      	5170707	CE  										RT MLG	MALFUNCTION     	D		A		O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SW	05	63BL	532  			014	051				LANDING GEAR OVER EXTENDED, CONTACTED MAIN FUEL LINES IN WHEELWELL WHICH PREVENTED COMPLETE RETRACTION.  THIS CAUSED THE	 STRUT TO DEFLATE ALONG WITH LOSS OF FLUID WHICH, IN TURN, CAUSED A COLLAPSED STRUT ON LANDING.  IT WAS ALSO NOTED THAT 	THE MAIN FUEL LINE WAS CROSSED LT RT, RT LT. REMOVED AND REPLACED GEAR AND FUEL LINES.				2	L	7	2 	4F			RT	A10CE   					 
1996110100525	19961101	00525	EU  	1996	11	1	96ZZZX5417       	1	19960913	G	2720	F10A755401	LINE            			AMD   	FALC10	FALCON10    	2730101	EU  										V STAB RUD SERVO	PIN HOLE        	B	L		GFER	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	163AV	5033 				163				UPON LANDING, THE FLT CREW NOTICED HYD FLUID IN THE AREA OF THE VERT STAB. INVEST REVEALED THE RUD SERVO HYD RETURN LINE	 HAD BEEN CHAFED BY THE BRAIDED STEEL RUD SERVO LINE PN 000AE90-4-0232 WHERE A PIN HOLE HAD DEVELOPED.  LINE WAS REPLACE	D AND PROTECTED WITH A STRIP OF 'SPIRAL WRAP', ALSO, THE FLEX LINE WAS FOUND TO HAVE A SLIGHT TWIST FROM INSTALLATION WH	ICH ALLOWED THE LINE TO RUB HARD IN CERTAIN RUD POSITIONS, THIS DEFECT WAS FIXED.  THE PIN HOLE DEVELOPED IN AN AREA NOT	 ACCESSIBLE TO VISUAL INSP EVEN WITH THE LEAD EDGE OF THE V STAB ACCESS PANEL REMOVED.  REF ALSO  FALCON 10 IPC 27-23-05	 PG 1-0, ITEMS 144 AND 140.	2	L	7	2 	4F				A33EU   					 
1996110100526	19961101	00526	NM  	1996	11	1	96ZZZX5418       	1	19961012	G	5711		SPAR CAP        			UNIVAR	415   	415C        	0420302	NM  										RT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	2576H	1938 				3201				UPON PREPPING WINGS FOR RE-COVER, EXFOLIATION DISCOVERED IN STBD WING MAIN SPAR CAP UPPER.  SEVERAL LAYERS OF VARIOUS TY	PES OF TAPE HID THE CORROSION UNTIL REMOVED FOR INSPECTION.  EXFOLIATION RUNS FULL LENGTH OF SPAR CAP, VARYING IN DEPTH 	TO .0625 INCH.				1	L	7	1 	3O				A718    					 
1996110100527	19961101	00527	EU  	1996	11	1	96ZZZX5419       	1	19961009	G	3020	5302412082	DEICE LIP       			PILATS	PC12  	PC12        	7090550	EU  										DEICE LIP COWL	BROKEN JOINTS   	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	121RF	357  				114				DISCOLORATION AND EXHAUST STREAKS LED TO FURTHER INVESTIGATION OF THE DE-ICE LIP ASSEMBLY.  INVESTIGATION REVEALED BROKE	N SLIP JOINTS AT THE DE-ICE LIP JOINT, LT SIDE.  SUBMITTER STATES IMMEDIATE INSPECTION RECOMMENDED ON ALL PC12'S.					1	L	7	1 	3T			RT	A78EU   					 
1996110100528	19961101	00528	EU  	1996	11	1	96ZZZX5420       	1	19961008	G	5220	5222012036	EMERGENCY EXIT  			PILATS	PC12  	PC12        	7090550	EU  										CABIN	SEAL LEAKS      	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	121RF	357  				114				INVESTIGATION OF MOISTURE REPORT REVEALED THAT ALL INSULATION FROM THE EMERGENCY EXIT TO THE AFT PRESSURE BULKHEAD IN TH	E BELLY OF THE AIRCRAFT WAS DETERIORATED AND SOAKED IN WATER.  LEAKY EMERGENCY EXIT, FAULTY SEALING SUSPECTED.  SUBMITTE	R STATED INSPECTION RECOMMENDED.  PILATUS ACFT ADVISED.				1	L	7	1 	3T			RT	A78EU   					 
1996110100529	19961101	00529	EU  	1996	11	1	96ZZZX5421       	1	19961008	G	5220	5522012036	EMERGENCY EXIT  			PILATS	PC12  	PC12        	7090550	EU  										CABIN	SEAL LEAKS      	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	124BW	207  			124	124				INVESTIGATION OF MOISTURE REPORT REVEALED ALL INSULATION FROM EMERGENCY EXIT TO AFT PRESSURE BULKHEAD DETERIORATED AND S	OAKING IN WATER.  SUBMITTER STATED IMMEDIATE INSPECTION RECOMMENDED; FAULTY SEAL.					1	L	7	1 	3T			RT	A78EU   					 
1996110100530	19961101	00530	SO  	1996	11	1	96ZZZX5422       	2	19961017	G	8520		CRANKCASE       			ARONCA	15    	15AC        	0191202	EA  	CONT  	O300  	O300*       	17022	SO  					ENGINE	FAILURE         	G				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			AL	03	1132H					15AC145				PUSH ROD FAILURE RESULTED IN ENGINE STOPPING AND SUBSEQUENT CRANKCASE FAILURE.  (ROD THROUGH CASE.)  SUBMITTER SUSPECTS 	OIL PUMP FAILURE, ENGINE OVERHEAT.					1	H	7	1 	3O	3	O		A802    	E253				 
1996110100531	19961101	00531	CE  	1996	11	1	96ZZZX5423       	1	19961016	G	3246	201302591	WHEEL           			CESSNA	182   	182P        	2075816	CE  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	1307S	3887 				18264872				DURING TIRE CHANGE ON RT MAIN, 3 CRACKS FOUND AT VARIOUS BOLT HOLES IN THE CENTER WHEEL BODY SECTION OF THE 3-PIECE WHEE	L ASSY.  POSSIBLE CAUSES INCLUDE OVERTORQUING DURING INSTALLATION COMBINED WITH HARD LANDINGS.  THIS SHOP EXPECTS TO SEE	 1 TO 2 CRACKED WHEEL BODIES A YEAR AND INSPECTS THESE WHEEL SECTIONS CAREFULLY DURING WHEEL/TIRE MAINTENANCE.  SUBMITTE	R RECOMMENDS CAREFUL ADHERENCE TO PROPER WHEEL ASSY TORQUES UPON INSTALLATION OF TIRES.  ALSO SUGGEST THE APPROVAL OF A 	2-PIECE RATHER THAN A 3-PIECE WHEEL ASSY FOR THIS INSTALLATION.		1	H	7	1 	3O			NT	TA13    					 
1996110100532	19961101	00532	EA  	1996	11	1	96ZZZX5424       	2	19961017	G	8530	73806	PUSH ROD        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 CYL EXH	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	25813	6000 				15280797	L1416215			UNDER NORMAL OPERATING CONDITIONS, REMOVED NR 1 CYLINDER EXHAUST SIDE PUSH ROD AND NOTICED SHINEY CHAFE MARK.  THE CAUSE	 IS UNKNOWN.  THERE WAS NO DENT IN THE PUSH ROD TUBE.  SUBMITTER STATED THIS IS THE THIRD OCCURRENCE ON THE O-235 ENGINE	 AT THE NR 1 CYLINDER LOCATION.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996110100533	19961101	00533	CE  	1996	11	1	96ZZZX5425       	1	19960907	G	5312	05121083	BULKHEAD        			CESSNA	170   	170B        	2072306	CE  										FS 228.687	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2269D	3050 				20421				REAR BULKHEAD WAS FOUND CRACKED AT THE TAIL WHEEL MOUNTING SHEAR BRACKET.  THE SKIN ON BOTH SIDES OF THE TAIL WHEEL MOUN	TING BRACKET WERE FOUND CRACKED UPON DISASSEMBLY WITH CORROSION BETWEEN THE BRACKET AND SKIN.  SUSPECT CAUSE WAS THE WEA	RING OF THE SKIN BY THE CORROSION.  THE OLD STYLE TAIL WHEEL BRACKET IS STEEL, THE NEW ONE IS ALUMINUM.  THIS SHOULD PRE	VENT THE DISSIMILAR METAL CORROSION WHICH MAY HAVE CAUSED THE PROBLEM.  NOTE:  THE PART WAS 44 YEARS OLD.			1	H	7	1 	3O				A799    					 
1996110100534	19961101	00534	CE  	1996	11	1	96ZZZX5426       	1	19960907	G	5330	051200080	SKIN            			CESSNA	170   	170B        	2072306	CE  										FS 205-228	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2269D	3050 				20421				REAR BULKHEAD WAS FOUND CRACKED AT THE TAIL WHEEL MOUNTING SHEAR BRACKET.  THE SKIN ON BOTH SIDES OF THE TAIL WHEEL MOUN	TING BRACKET WERE FOUND CRACKED UPON DISASSEMBLY WITH CORROSION BETWEEN THE BRACKET AND SKIN.  SUSPECT CAUSE WAS THE WEA	RING OF THE SKIN BY THE CORROSION.  THE OLD STYLE TAIL WHEEL BRACKET IS STEEL, THE NEW ONE IS ALUMINUM.  THIS SHOULD PRE	VENT THE DISSIMILAR METAL CORROSION WHICH MAY HAVE CAUSED THE PROBLEM.  NOTE:  THE PART WAS 44 YEARS OLD.			1	H	7	1 	3O				A799    					 
1996110100535	19961101	00535	CE  	1996	11	1	96ZZZX5427       	1	19961001	G	8011	639153	DRIVE           		MZ4214      	CESSNA	150   	150M        	2071830	CE  										STARTER	CLUTCH SEIZED   	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	9440U					15078388				STARTER CLUTCH WAS FOUND LOCKED UP SOLID CAUSING STARTER TO ROTATE ALL THE TIME THE ENGINE WAS RUNNING.						1	H	7	1 	3O				3A19    					 
1996110100536	19961101	00536	CE  	1996	11	1	96ZZZX5428       	1	19961010	G	5310		TRUSS           			BEECH 	35    	35BEECH     	1151502	CE  										LT FWD UPPER	WELD CRACKED    	B	L		QISR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	3079V					D494				A CRACKED WELD WAS DISCOVERED ON THE PORT SIDE UPPER WELD JOINT OF THE FORWARD TRUSS AND A CRACKED WELD ON THE LOWER STA	RBOARD REAR TRUSS CLIP.  SUBMITTER STATED THIS AIRCRAFT IS OUT-OF-SERVICE AND HAS BEEN FOR APPROXIMATELY 15 YEARS.  OWNE	R IS INTERESTED IN RESTORING THIS AIRCRAFT.  INSPECTION WAS PERFORMED AS REQUIRED BY SB NR 24 AND AD 63-25-01.				1	L	7	1 	3O				A777    					 
1996110100537	19961101	00537	CE  	1996	11	1	96ZZZX5429       	1	19961010	G	5310		TRUSS CLIP      			BEECH 	35    	35BEECH     	1151502	CE  										RT AFT CLIP	WELD CRACKED    	B			QISR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	3079V					D494				A CRACKED WELD WAS DISCOVERED ON THE PORT SIDE UPPER WELD JOINT OF THE FORWARD TRUSS AND A CRACKED WELD ON THE LOWER STA	RBOARD REAR TRUSS CLIP.  SUBMITTER STATED THIS AIRCRAFT IS OUT-OF-SERVICE AND HAS BEEN FOR APPROXIMATELY 15 YEARS.  OWNE	R IS INTERESTED IN RESTORING THIS AIRCRAFT.  INSPECTION WAS PERFORMED AS REQUIRED BY SB NR 24 AND AD 63-25-01.				1	L	7	1 	3O				A777    					 
1996110100538	19961101	00538		1996	11	1	96ZZZX5430       	4	19961008	G	6122		CONTROL ARM     		V54         	PIPER 	PA32  	PA32R301    	7103218	SO  										PROP GOVERNOR	CHAFE BAFFLE    	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	32WF	127  			A952JPC10	3246026				CONTROL ARM OF PROPELLER GOVERNOR RUBBING THROUGH BAFFLING.  AIR FLOW PUSHES BAFFLING INTO STUD ON CONTROL ARM AND IS WE	ARING THROUGH.  SUBMITTER STATED MAKE BRACKET TO HOLD BAFFLES BACK.					1	L	7	1 	3O				A3SO    					 
1996110100539	19961101	00539		1996	11	1	96ZZZX5431       	4	19960813	G	6113	3532312	SPINNER         			PIPER 	PA28  	PA28151     	7102805	SO  										FWD BULKHEAD	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	43456	1700 				287415499				DURING ANNUAL INSPECTION, FOUND FRONT SPINNER BULKHEAD CRACKED.  A CRACK HAD PREVIOUSLY BEEN STOP DRILLED.						1	L	7	1 	3O				2A13    					 
1996110100540	19961101	00540	SO  	1996	11	1	96ZZZX5432       	1	19961001	G	7921	89082003	CLIP            			PIPER 	PA46  	PA46350P    		SO  										LT INTERCOOLER	SEPARATED       	B	S		LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	46PM					4622081				NOTED DURING ANNUAL, LT INTERCOOLER 'CLIP' SEPARATED LEAVING ONLY SCREW AND WELD BUSHING.  SUBMITTER STATED THIS IS A RE	CURRING PROBLEM.  A FIX WOULD BE TO BOND CLIP TO SIDE OF INTERCOOLER UPON INSTALLATION WITH HIGH TEMP RED SILICONE ADHES	IVE.				1	L	7	1 	3O			RT	A25SO   					 
1996110100541	19961101	00541	SO  	1996	11	1	96ZZZX5433       	1	19960930	G	3250	AN47A	BOLT            			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG STEERING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	53BD	2923 				347970114				DURING AN ANNUAL INSPECTION, NOSE GEAR STEERING BOLTS (2 EACH) SECURING THE STEERING CHANNEL WERE REMOVED FOR INSPECTION	 AND FOUND 1 BOLT CRACKED APPROXIMATELY 75 PERCENT THROUGH SHANK, OTHER BOLT WAS FOUND BENT.  INSTALLED NEW BOLTS.  SUBM	ITTER IS OF THE OPINION THESE BOLTS WERE OVERSTRESSED FROM TOWING LIMITS BEING EXCEEDED.				1	L	7	2 	3O				A7SO    					 
1996110100542	19961101	00542	SO  	1996	11	1	96ZZZX5434       	1	19960919	G	5711		SPAR            			PIPER 	PA28  	PA28180     	7102808	SO  										FUEL TANK ATTACH	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5349L					284652				FOUND SEVERE SPAR DELAMINATION ON UPPER OUTBOARD FUEL TANK ATTACH POINTS.  SUBMITTER STATED APPEARS TO BE RESULT OF EXPO	SURE TO SALT AIR NEAR SEACOAST IN FLORIDA.  SUBMITTER SUGGESTS TANK REMOVAL AND INSPECTION OF AREA EVERY 5 YEARS.  AIRCR	AFT WAS BASED IN SALT ENVIRONMENT 22 OF 28 YEARS.  PART TOTAL TIME APPROXIMATELY 2,200 HRS.				1	L	7	1 	3O				2A13    					 
1996110100543	19961101	00543	SO  	1996	11	1	96ZZZX5435       	1	19960824	G	7110	96506000	HINGE ASSY      			PIPER 	PA34  	PA34200     	7103405	SO  										LT ENG OTBD COWL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	56676	5990 				347450020				UPON INVESTIGATION AS TO WHY COWLING WAS CHAFING AND WEARING THROUGH THE ALUMINUM, FOUND HINGE ASSY CRACKED WHICH ALLOWE	D THE SIDE COWL ASSY TO MOVE AND CHAFE AGAINST UPPER COWL ASSY.  THIS P/N HINGE ASSY IS LOCATED AT FWD OTBD ON LT ENGINE	.  SUBMITTER STATES THE HINGE APPEARED TO HAVE BEEN CRACKED AND BROKEN FOR QUITE SOME TIME.				1	L	7	2 	3O				A7SO    					 
1996110100544	19961101	00544	SO  	1996	11	1	96ZZZX5436       	1	19960824	G	7110	96506001	HINGE ASSY      			PIPER 	PA34  	PA34200     	7103405	SO  										LT ENG INBD COWL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	56676	5990 				347450020				UPON INVESTIGATION AS TO WHY COWLING WAS CHAFING AND WEARING THROUGH THE ALUMINUM, FOUND HINGE ASSYS CRACKED WHICH ALLOW	ED THE SIDE COWL ASSY TO MOVE AND CHAFE AGAINST UPPER COWL ASSY.  THIS P/N HINGE ASSY IS LOCATED AT FWD INBD ON LT ENGIN	E AND FWD OTBD ON RT ENGINE.  THE HINGES APPEARED TO HAVE BEEN CRACKED AND BROKEN FOR QUITE SOME TIME.				1	L	7	2 	3O				A7SO    					 
1996110100920	19961101	00920	CE  	1996	11	1	96ZZZX5437       	1	19960621	G	7160	04500705	BUTTERFLY VALVE 		04500523    	CESSNA	150   	152         	2071835	CE  										AIR BOX	SCREWS WORN     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	5249P	5047 				15284901				DURING INSPECTION, FOUND THE TWO SCREWS WHICH SECURE THE CARBURETOR HEAT BUTTERFLY VALVE TO THE SHAFT WERE LOOSE.  UPON 	REMOVAL, FOUND SCREWS WORN APPROXIMATELY 80 PERCENT THROUGH.  SUBMITTER STATED APPEARS THEY HAD BEEN LOOSE FOR SOME TIME	.  FAILURE OF SCREWS COULD CAUSE LOSS OF POWER DUE TO RESTRICTION OF AIR FLOW AND INJESTION OF SCREWS INTO ENGINE.				1	H	7	1 	3O			NT	3A19    					 
1996110100921	19961101	00921	CE  	1996	11	1	96ZZZX5438       	1	19960926	G	5553	04320049	BRACKET         		04320019    	CESSNA	150   	152         	2071835	CE  										V STAB ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	49158	7297 	7297 			15281171				WHILE INSPECTING HORIZONTAL STABILIZER TO VERTICAL FIN ATTACH NUTPLATES PER AD 80-11-4 FOR CRACKS, NUTPLATES WERE FOUND 	OK, BUT THE BRACKET THE NUTPLATES ARE RIVETED TO WAS CRACKED IN TWO SPOTS, RADIATING FROM THE BOLT HOLE.					1	H	7	1 	3O			NT	3A19    					 
1996110100922	19961101	00922	CE  	1996	11	1	96ZZZX5439       	1	19960926	G	5210	504300431207	BRAZE ASSY      			BEECH 	90    	C90         	1152913	CE  										CABIN DOOR	BOLT FAILED     	B	S	A	IA4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	438SP					LJ1108				PILOT LOCKED CABIN DOOR AND SECURED AIRCRAFT.  THE NEXT MORNING THE CABIN DOOR COULD NOT BE OPENED.  THE UPPER FORWARD H	OOK AND ROD LINK WAS NOT MOVING WHEN THE HANDLE WAS TURNED.  AFTER 3 HOURS OF TRYING TO GET THE DOOR OPEN, A DECISION WA	S MADE TO CUT THE RT AFT CABIN WINDOW TO GAIN ACCESS TO THE EMERGENCY EXIT RELEASE HANDLE.  ENTERED THE CABIN THROUGH TH	E EMERGENCY EXIT AND REMOVED DOOR PANELS.  FOUND THE UPPER BRAZE ASSY ATTACHMENT HOLE FOR THE UPPER LINK SEVERELY ELONGA	TED AND BOLT HAD FAILED.  PART TOTAL TIME APPROXIMATELY 4,900 HRS.  SUBMITTER RECOMMENDATION:  PANELS SHOULD BE REMOVED 	DURING INSPECTION AND ATTACHMENT BOLTS INSPECTED AND LUBED.	1	L	7	2 	3T				3A20    					 
1996110100923	19961101	00923	CE  	1996	11	1	96ZZZX5440       	1	19960913	G	3230		DOWNLOCK        			BEECH 	76    	76          	1153005	CE  										NLG	MALFUNCTION     	D		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	03	6017U					ME159				NOSE GEAR COLLAPSED DURING A TOUCH-AND-GO WHEN POWER WAS APPLIED FOR A TAKEOFF.  INVEST REVEALED:  LT FWD DRAG BRACE ATT	ACH BOLT LOOSE (COTTER PIN WAS INSTALLED), INCORRECT WASHERS WERE INSTALLED (BASED ON PARTS MANUAL).  DOWNLOCK HOOK PIVO	T BOLT WAS PARTIALLY SEIZED (HOOK VERY SLOW TO LOCK EVEN WITH ACTUATOR DISCONNECTED).  THE PIVOT BOLT AND BUSHINGS BETWE	EN THE UPPER AND LOWER DRAG BRACE WERE VERY WORN AT DOWNLOCK ASSY.  NOSE GEAR DOWNLOCK SWITCH WAS NOT ADJUSTED PER THE M	M.  ALL THE PARTS STATED ABOVE ARE TO BE REPLACED AND/OR LUBRICATED AND REINSTALLED IAW MM.		1	L	7	2 	3O				A29CE   					 
1996110100924	19961101	00924	CE  	1996	11	1	96ZZZX5441       	1	19960920	G	3710	442CW4	PUMP            	AIRBORNE    		BEECH 	58    	58P         	1152744	CE  										VACUUM SYSTEM	FAILED          	B			CGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	6371V	490  			07AH000102	TJ417				VACUUM SYSTEM FAILED PER PILOT REPORT.  GAINED ACCESS TO VACUUM PUMPS, FOUND DRIVE SHAFTS SHEARED.  REPLACED BOTH PUMPS,	 FILTERS, AND EVACUATED LINES AS REQUIRED.  (NOTE:  IT WOULD BE POSSIBLE THAT ONE PUMP HAD BEEN INOPERABLE FOR SOME TIME	.)				1	L	7	2 	3O				A23CE   					 
1996110100925	19961101	00925	CE  	1996	11	1	96ZZZX5442       	1	19960920	G	3710	442CW4	PUMP            	AIRBORNE    		BEECH 	58    	58P         	1152744	CE  										VACUUM SYSTEM	FAILED          	B			CGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	6371V	490  			07AH000099	TJ417				VACUUM SYSTEM FAILED PER PILOT REPORT.  GAINED ACCESS TO VACUUM PUMPS, FOUND DRIVE SHAFTS SHEARED.  REPLACED BOTH PUMPS,	 FILTERS, AND EVACUATED LINES AS REQUIRED.  (NOTE:  IT WOULD BE POSSIBLE THAT ONE PUMP HAD BEEN INOPERABLE FOR SOME TIME	.)				1	L	7	2 	3O				A23CE   					 
1996110100926	19961101	00926	CE  	1996	11	1	96ZZZX5443       	1	19960928	G	3230	1CH16	SWITCH          		99101393    	CESSNA	414   	414A        	2075907	CE  										NLG ACTUATOR	WIRE TORN LOOSE 	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	13	6604C				CE271	414A0030				LANDING GEAR FAILED TO RETRACT.  AIRCRAFT LANDED WITHOUT INCIDENT.  IT WAS DISCOVERED THE WIRING HARNESS HAD TORN LOOSE 	FROM THE MICROSWITCH.  HYD ACTUATOR WAS REPLACED.  OPERATIONAL CHECK PERFORMED AND IS OKAY.					1	L	7	2 	3O				A7CE    					 
1996110100927	19961101	00927	SO  	1996	11	1	96ZZZX5444       	1	19961015	G	7603	555815	CONTROL CABLE   			PIPER 	PA32  	PA32R300    	7103213	SO  										THROTTLE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	7236U	4930 				32R7780298				THROTTLE CABLE BROKE AT QUADRANT END WHERE CABLE MEETS END.  CABLE BROKE ON FIRST COLD MORNING OF FALL.  WAS NOT EXCESSI	VELY STIFF AT NORMAL TEMPS.					1	L	7	1 	3O			 	A3SO    					 
1996110100928	19961101	00928	CE  	1996	11	1	96ZZZX5445       	1	19960627	G	2750		FUSE            			CESSNA	150   	150H        	2071818	CE  										FLAP CONT	BLOWN           	G				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			WP	15	7260S					15067960				DURING A GO-AROUND, THE FLAPS WERE STUCK IN THE 40 DEGREE POSITION.  THIS MALFUNCTION CAUSED THE PILOT TO MAKE AN EMERGE	NCY LANDING WHICH RESULTED IN AN ACCIDENT.  AN INSPECTION OF THE FUSE FOR THE FLAP SYSTEM REVEALED CORROSION ON THE FUSE	 WHICH HAD CORRODED ITSELF TO THE FUSE CAP AND THE FUSE WAS BLOWN.  IT WAS ALSO NOTED THE FUSE WAS THE WRONG AMPERAGE.				1	H	7	1 	3O				3A19    					 
1996110100929	19961101	00929	SO  	1996	11	1	96ZZZX5446       	1	19961015	G	5210	8732910	LOCK ASSY       		9691700     	PIPER 	PA34  	PA34200T    	7103406	SO  										DOOR ASSY	FAILS TEST      	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8107D				PK565	348070010				KEY CAN BE REMOVED FROM DOOR LOCK WHEN LOCK IS IN OPEN POSITION REGARDLESS OF DOOR LATCH POSTION.  FAILS TESTS PER AD 88	-04-05.  SUBMITTER STATED THE AD SHOULD BE A 100-HOUR RECURRING MAINTENANCE REQUIREMENT.  MOST PILOTS UNAWARE OF NEED FO	R PRE/POST-FLIGHT CHECKS PER PAPER SB 633B.				1	L	7	2 	3O				A7SO    					 
1996110100930	19961101	00930	SO  	1996	11	1	96ZZZX5447       	1	19960927	G	2842	548671	SENSOR          			PIPER 	PA28  	PA28151     	7102805	SO  										FUEL QUANTITY	FLOAT DETACHED  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8403C	1466 				287615102				ZERO FUEL QUANTITY INDICATED WITH FULL TANK PROMPTED INSPECTION OF FUEL QUANTITY SENDING UNIT.  FLOAT WAS FOUND COMPLETE	LY DETACHED FROM WIRE LEVER ARM AND FLOATING IN TANK.  HOLE THROUGH WHICH WIRE PASSED IS WORN SUFFICIENTLY TO ALLOW RETA	INING WASHER TO PASS THROUGH ALSO.				1	L	7	1 	3O				2A13    					 
1996110100931	19961101	00931	SO  	1996	11	1	96ZZZX5448       	2	19961008	G	8520		CRANKSHAFT      			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					NR 2 CON ROD	BROKEN          	B			CR1R	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	25	99TM					28R7703073	248145R			ENGINE LOST POWER IN-FLIGHT.  ACFT ABLE TO LAND AND TAXIED IN UNDER ITS OWN POWER.  ENG INSP REVEALED PROP COULD BE MOVE	D 15 TO 20 DEGREES WITHOUT RESISTANCE.  WITH PLUGS REMOVED, FND THE FRONT 4 PISTONS WOULD MOVE IN THAT 15 TO 20 DEGREES,	 BUT NR 1 AND NR 2 CYL PISTON WOULD NOT.  REMOVED TIMING PLUG AND FND CRANKSHAFT HAD A ROCKING MOTION WHILE MOVING PROP 	IN THAT FREE-PLAY AREA.  THE ENGINE NOT TORN DOWN AT TIME OF REPORT, BUT IT APPEARS THE CRANKSHAFT BROKE JUST FWD OF WHE	RE THE NR 2 CONNECTING ROD ATTACHES.		1	L	7	1 	3O	3	O		2A13    	E9CE				 
1996110100932	19961101	00932	GL  	1996	11	1	96ZZZX5449       	2	19960923	G	7250	6892832	NOZZLE SHIELD   								ALLSN 	250C  	250C30P     	03013	GL  					3RD STAGE	ELONGATED HOLES 	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17							CAE895208			UPON DISASSEMBLY OF THE TURBINE FOR REPLACEMENT OF THE FIRST STAGE NOZZLE, FOUND FRETTING WEAR ON THE SHEATHS OF THE TOT	 HARNESS PROBES, AND ELONGATED HOLES IN THE THIRD STAGE NOZZLE SHIELD WHERE THE PROBES PASS THROUGH.  TOT HARNESS REQUIR	ED REPLACEMENT.									3	U			E1GL				 
1996110100933	19961101	00933		1996	11	1	96ZZZX5450       	1	19960923	G	7722	6893072	HARNESS         								ALLSN 	250C  	250C30P     	03013	GL  					ENG TOT PROBE	FRETTED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17					FF4311E		CAE895208			UPON DISASSEMBLY OF THE TURBINE FOR REPLACEMENT OF THE FIRST STAGE NOZZLE, FOUND FRETTING WEAR ON THE SHEATHS OF THE TOT	 HARNESS PROBES, AND ELONGATED HOLES IN THE THIRD STAGE NOZZLE SHIELD WHERE THE PROBES PASS THROUGH.  TOT HARNESS REQUIR	ED REPLACEMENT.									3	U			E1GL				 
1996110100934	19961101	00934	WP  	1996	11	1	96ZZZX5451       	1	19961021	G	2750	37741723	BELLCRANK       		5772691     	DOUG  	DC8   	DC8*        		WP  										FLAP ACTUATOR	BROKEN          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					H058594					BELLCRANK ARRIVED BROKEN.  SUSPECT CAUSE WAS STRESS AND CORROSION.						2	L	7	4 	4J			F	4A25    					 
1996110100935	19961101	00935	CE  	1996	11	1	96ZZZX5452       	1	19961015	G	3411	D37C15	SWITCH          			CESSNA	500   	560CESSNA   	2076750	CE  										PITOT DIFF PRESS	DEFECTIVE       	D				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	05	277RC	1277 			0751	5600210				LANDING GEAR WARNING HORN FAILED PRE-FLIGHT CHECK.  HORN WOULD SOUND WHEN EACH THROTTLE WAS RETARDED SEPARATELY, BUT FAI	LED TO SOUND WHEN BOTH THROTTLES WERE RETARDED TOGETHER.  TROUBLESHOOTING FOUND PITOT/STATIC DIFFERENTIAL PRESSURE SWITC	H (150 KNOT AIRSPEED SWITCH) WITH HIGHER THAN NORMAL INTERNAL RESISTANCE.   INSTALLED NEW SWITCH.  ALL GROUND OPS AND LE	AK CHECKS WERE NORMAL PER CITATION 560 MM, CHAPTERS 32-60-00 AND 34-11-00.			2	L	7	2 	4F			RT	A22CE   					 
1996110100936	19961101	00936	EU  	1996	11	1	96ZZZX5453       	1	19960913	G	3242	5003340	ROTATING DISC   		50028053    	ISRAEL	1124  	1124        	4500102	EU  										BRAKE ASSY	BROKEN          	B			XZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	38AE		140  		5626	318				ON PRE-FLIGHT, FOUND ROTATING DISC BROKEN, WHICH, IN TURN, BROKE THE WHEEL HALF.  LANDINGS, 72.						2	M	7	2 	4F				A2SW    					 
1996110100937	19961101	00937	NM  	1996	11	1	96ZZZX5454       	1	19961010	G	3230	F6137	UPLOCK          			AMD   	FALC50	FALCON2000  	2730170	NM  										MLG	MALFUNCTION     	B			YL1R	K				NONE                    				O			OTHER                     			CL	CLIMB          	1			SW	11	790M	10   			U402	19				LANDING GEAR DOORS WOULD NOT RETRACT AFTER GEAR UP SELECTED.  RED LIGHTS ON GEAR PANEL WERE ON, GEAR HANDLE LIGHT FLASHI	NG.  THE CREW INDICATED THEY HAVE HAD SIMILAR PROBLEMS WITH THE LANDING GEAR ON THIS AIRCRAFT BEFORE.  THEY REPLACED THE	 GEAR UPLOCK.  UNABLE TO DUPLICATE PROBLEM ON THE GROUND.  ALL TESTS INDICATE NO PROBLEM WITH SYSTEM.  3 EACH GEAR UPLOC	KS CHANGED OUT AS BEFORE.			2	K	7	3 	4F			RT	A50NM   					 
1996110100938	19961101	00938	NM  	1996	11	1	96ZZZX5455       	1	19961010	G	3230	F6137	UPLOCK          			AMD   	FALC50	FALCON2000  	2730170	NM  										MLG	MALFUNCTION     	B			YL1R	K				NONE                    				O			OTHER                     			CL	CLIMB          	1			SW	11	790M	10   			U249	19				LANDING GEAR DOORS WOULD NOT RETRACT AFTER GEAR UP SELECTED.  RED LIGHTS ON GEAR PANEL WERE ON, GEAR HANDLE LIGHT FLASHI	NG.  THE CREW INDICATED THEY HAVE HAD SIMILAR PROBLEMS WITH THE LANDING GEAR ON THIS AIRCRAFT BEFORE.  THEY REPLACED THE	 GEAR UPLOCK.  UNABLE TO DUPLICATE PROBLEM ON THE GROUND.  ALL TESTS INDICATE NO PROBLEM WITH SYSTEM.  3 EACH GEAR UPLOC	KS CHANGED OUT AS BEFORE.			2	K	7	3 	4F			RT	A50NM   					 
1996110100939	19961101	00939	NM  	1996	11	1	96ZZZX5456       	1	19961010	G	3230	F6137	UPLOCK          			AMD   	FALC50	FALCON2000  	2730170	NM  										MLG	MALFUNCTION     	B			YL1R	K				NONE                    				O			OTHER                     			CL	CLIMB          	1			SW	11	790M		10   		U673	19				LANDING GEAR DOORS WOULD NOT RETRACT AFTER GEAR UP SELECTED.  RED LIGHTS ON GEAR PANEL WERE ON, GEAR HANDLE LIGHT FLASHI	NG.  THE CREW INDICATED THEY HAVE HAD SIMILAR PROBLEMS WITH THE LANDING GEAR ON THIS AIRCRAFT BEFORE.  THEY REPLACED THE	 GEAR UPLOCK.  UNABLE TO DUPLICATE PROBLEM ON THE GROUND.  ALL TESTS INDICATE NO PROBLEM WITH SYSTEM.  3 EACH GEAR UPLOC	KS CHANGED OUT AS BEFORE.			2	K	7	3 	4F			RT	A50NM   					 
1996110100940	19961101	00940	CE  	1996	11	1	96ZZZX5457       	1	19961011	G	2430	P41K16	WIRE            			BEECH 	200   	200BEECH    	1152920	CE  										RT GEN GCU	BURNED          	B			FGQR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	01	93ME	2509 				BB1345				RIGHT GEAR FAILED.  TROUBLESHOOTING FOUND ALL COMPONENTS OPERATIONAL.  HIGH RESISTANCE FOUND FROM PIN 33 ON RELAY PANEL 	A123 AND PIN B AT GCU.  CAUSE FOUND IN WIRE P41R16 WITHIN THE BUNDLE RUNNING FROM RELAY PANEL A123 WHERE WIRE HAD BEEN S	TAMPED BY LABELING MACHINE CAUSING AN INDENTATION IN SHIELDED WIRE WHICH APPARENTLY ALLOWED ARCING TO OCCUR AND EVENTUAL	LY BURNED THROUGH THE CONDUCTOR.  WIRE WAS SPLICED AND SYSTEM OPERATED NORMALLY.			1	L	7	2 	4T			 	A24CE   					 
1996110100941	19961101	00941	SO  	1996	11	1	96ZZZX5458       	1	19960620	G	2435	230801971	BRUSH           	LUCAS       	23080013    	EMB   	120   	EMB120RT    		SO  										START/GEN	EXCESS WORN     	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	261CA	660  			3852	120254				BRUSHES FAILED PREMATURELY.  BRUSHES WORN 85 PERCENT, BRUSH SHUNTS BROKEN OFF BRUSHES. BRUSHES BURNED, ARMATURE OVERHEAT	ED,  SUBMITTER STATED POOR DESIGN OF BRUSH.  RECOMMENDED RE-DESIGN OF BRUSH.					2	L	7	2 	4T			RT	A31SO   					 
1996110700105	19961107	00105	NM  	1996	11	7	96ZZZX5466       	1	19961017	G	2121	X11374	BEARING         	SUNDSTRANDEM	215201      	BOEING	727   	727         	1384001	NM  										COOL FAN	FAILED          	B		A	DM4R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	19		1571 								AVIONIC COOLING FAN BEARING FAILED AFTER 1,571.22 HRS OF OPERATION.  INNER BALL RACE DISTORTED AND BALLS MISSING.  FLIGH	T ATTENDANTS REPORTED SMOKE IN CABIN DUE TO FAN FAILURE.					2	L	7	3 	4F				A3WE    					 
1996110700107	19961107	00107	GL  	1996	11	7	96ZZZX5468       	3	19961017	G	6114	D4344	HUB             													MCAULY	3AF32C	3AF32C87    	GL  	NR 3 SOCKET	CRACKED         	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23					800240			800240		DURING C/W AD 95-24-05, SL 93-11A OIL FILL.  HUB FOUND CRACKED IN NR 3 BLADE SOCKET.																5	C	P22EA	 
1996110700109	19961107	00109		1996	11	7	96ZZZX5469       	4	19960905	G	6122	D20271	GOVERNOR BODY   	MCAULY      	C290D3T22   															PROPELLER	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					820303					PROPELLER GOVERNOR BODY WORN IN GEAR POCKET.  SUSPECT CAUSE, IDLER GEAR STUD WORN ALLOWED GEAR TO RUN OFFSET.																			 
1996110700110	19961107	00110	SO  	1996	11	7	96ZZZX5470       	2	19960910	G	8530	501867	LOCK TAB        			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  					RKR SHAFT BOLT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CYLINDERS WERE SENT OUT FOR CHROMING AND OVERHAUL.  CYLINDERS WERE RECEIVED BACK READY TO INSTALL.  NEW SUPERIOR AIR PAR	TS ROCKER ARM SHAFT BOLT LOCK TABS WERE INSTALLED.  UPON BENDING TANGS OVER BOLT HEADS, ALL TANGS EITHER CRACKED OR BROK	E OFF COMPLETELY.  SUBMITTER STATES, APPARENTLY, A STOCK METAL WAS TEMPERED WRONG AND WAS TOO BRITTLE.  CONTINENTAL LOCK	 TABS WERE INSTALLED AND OPERATED FINE.			1	L	7	1 	3O	3	O		2A13    	E9CE				 
1996110700111	19961107	00111	GL  	1996	11	7	96ZZZX5471       	3	19961015	G	6114	C4850	GASKET          			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP CYL DOME	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	07										RED DYE LEAKAGE FROM THE PROP CYLINDER 'DOME' GASKETS.  SPECIFICALLY WHERE THE DOWL PINS ARE.  HAS BEEN A RECURRING PROB	LEM JUST AFTER OVERHAUL.  SUBMITTER STATES THIS SHOP HAS SEEN 7 PROPS LEAK AFTER THE OIL-FILL MOD.  THESE OVERHAULS WERE	 PERFORMED BY 4 DIFFERENT PROPELLER REPAIR STATIONS.  AFTER RESEAL, 2 OF THE 7 HAVE SHOWN SUBSEQUENT LEAKAGE AND NEED FO	R RESEAL.  SUGGEST MCCAULEY HAVE AN O-RING INCORPORATED WITH OIL-FILL MOD.			1	L	7	2 	3O				3A10    		5	C	P22EA	 
1996110700112	19961107	00112	GL  	1996	11	7	96ZZZX5472       	1	19961001	G	5541		RIB             			AMTR  	BEDE4 	BEDEBD4     		GL  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	2831W					692				RUDDER TOP RIB CRACKED, DISCOVERED DURING INSPECTION.  RUDDER BALANCE WEIGHT IS RIVETED TO RIB.  RIB WAS BUILT BY OWNER 	IAW INSTRUCTIONS.  RIB BUILT FROM .025 INCH 2024.  APPEARS NOT TO BE STRONG ENOUGH TO HOLD BALANCE WEIGHT.  NEW RIB FABR	ICATED FROM .032 INCH WITH DOUBLERS.				1	H	7	1 	3O				EXPA1H71					 
1996110700113	19961107	00113	EA  	1996	11	7	96ZZZX5473       	1	19961008	G	2910	MS219266D	ELBOW           			CNDAIR	CL600 	CL6001A11   	1900302	EA  										LT WELL HYD	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	100LR					1064				50 HRS AFTER MAJOR INSP, DEVELOPED LEAK IN LT WHEELWELL.  FOUND NR 6 ELBOW CRACKED AND LEAKING.  NEXT DAY FOUND HYD FLUI	D LEAKING OUT OF LT WHEELWELL AGAIN.  FOUND NR 6 TEE FITTING CRACKED AND LEAKING.  REPLACED BOTH.  PRE-FLIGHTED A/C ON T	HIRD DAY FOR TRIP AND NOTICED FLUID LEAKING FROM RT WHEELWELL AFTER PREFLIGHT.  FOUND NR 4 TEE FITTING CRACKED AND LEAKI	NG.  CANCELLED TRIP.  REPLACED NR 4 TEE FITTING.  NO MORE PROBLEMS.  SUSPECT CAUSE WAS NR 3 HYD RES IN WHEELWELL WAS REM	OVED TO PERFORM SB AND ALL THE FITTINGS WERE REMOVED TO GAIN ACCESS TO RES.  ALL FITTINGS ARE ALUM AND HYD LINES ARE STA	INLESS STEEL.  SUGGEST REPLACEMENT OF ALUM FITTINGS AROUND HYD RES ANYTIME IT IS REMOVED.	2	L	7	2 	4F			RT	A21EA   					 
1996110700114	19961107	00114	EA  	1996	11	7	96ZZZX5474       	1	19961008	G	2910	MS21905D	TEE FITTING     			CNDAIR	CL600 	CL6001A11   	1900302	EA  										LT WELL HYD	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	100LR					1064				50 HRS AFTER MAJOR INSP, DEVELOPED LEAK IN LT WHEELWELL.  FOUND NR 6 ELBOW CRACKED AND LEAKING.  NEXT DAY FOUND HYD FLUI	D LEAKING OUT OF LT WHEELWELL AGAIN.  FOUND NR 6 TEE FITTING CRACKED AND LEAKING.  REPLACED BOTH.  PRE-FLIGHTED A/C ON T	HIRD DAY FOR TRIP AND NOTICED FLUID LEAKING FROM RT WHEELWELL AFTER PREFLIGHT.  FOUND NR 4 TEE FITTING CRACKED AND LEAKI	NG.  CANCELLED TRIP.  REPLACED NR 4 TEE FITTING.  NO MORE PROBLEMS.  SUSPECT CAUSE WAS NR 3 HYD RES IN WHEELWELL WAS REM	OVED TO PERFORM SB AND ALL THE FITTINGS WERE REMOVED TO GAIN ACCESS TO RES.  ALL FITTINGS ARE ALUM AND HYD LINES ARE STA	INLESS STEEL.  SUGGEST REPLACEMENT OF ALUM FITTINGS AROUND HYD RES ANYTIME IT IS REMOVED.	2	L	7	2 	4F			RT	A21EA   					 
1996110700115	19961107	00115	EA  	1996	11	7	96ZZZX5475       	1	19961008	G	2910	MS21909D	TEE FITTING     			CNDAIR	CL600 	CL6001A11   	1900302	EA  										RT WELL HYD	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	100LR					1064				50 HRS AFTER MAJOR INSP, DEVELOPED LEAK IN LT WHEELWELL.  FOUND NR 6 ELBOW CRACKED AND LEAKING.  NEXT DAY FOUND HYD FLUI	D LEAKING OUT OF LT WHEELWELL AGAIN.  FOUND NR 6 TEE FITTING CRACKED AND LEAKING.  REPLACED BOTH.  PRE-FLIGHTED A/C ON T	HIRD DAY FOR TRIP AND NOTICED FLUID LEAKING FROM RT WHEELWELL AFTER PREFLIGHT.  FOUND NR 4 TEE FITTING CRACKED AND LEAKI	NG.  CANCELLED TRIP.  REPLACED NR 4 TEE FITTING.  NO MORE PROBLEMS.  SUSPECT CAUSE WAS NR 3 HYD RES IN WHEELWELL WAS REM	OVED TO PERFORM SB AND ALL THE FITTINGS WERE REMOVED TO GAIN ACCESS TO RES.  ALL FITTINGS ARE ALUM AND HYD LINES ARE STA	INLESS STEEL.  SUGGEST REPLACEMENT OF ALUM FITTINGS AROUND HYD RES ANYTIME IT IS REMOVED.	2	L	7	2 	4F			RT	A21EA   					 
1996120300039	19961203	00039	CE  	1996	12	3	96ZZZX5476       	1	19961001	G	3610	66002552	CHECK VALVE     			LEAR  	24    	24D         	5170311	CE  										ENG BLEED SYS	FLAP BROKEN     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	101VS	6941 				218				THERE ARE 2 EACH PN 6600255-2 HOT AIR CHECK VALVES INSTALLED AS PARTS OF KIT PN 2881701-1 FOR AMR 79-8 FOR LEAR 28229 AI	RCRAFT.  BOTH CHECK VALVES HAD FAILURES OF THE RETENTION SPRING AND MOUNT PIN OF THE HINGED PORTION OF THE FLAPPER IN TH	E CHECK VALVE.  THIS ALLOWED THE FLAPPER TO MOVE AROUND RANDOMLY WITHIN THE CHECK VALVE HOUSING.  THE PIN AND SPRING WER	E MISSING.  SUBMITTER STATES THIS IS A POSSIBLE ENGINE FOD PROBLEM.			2	L	7	2 	4J				A10CE   					 
1996110700116	19961107	00116	SO  	1996	11	7	96ZZZX5477       	1	19961017	G	3213	083114	FORK END        			LUSCOM	8     	8A          	8190104	SO  										LT MLG JACK STRU	SHEARED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1294M	8800 				4021				LT GEAR JACK STRUT LOOSE WHEN USING ENTRY STEP.  FOUND FORK END SHEARED OFF (IN THREADED AREA) WHERE JACK STRUT ATTACHES	 TO MAIN GEAR LEG.					1	H	7	1 	3O				A694    					 
1996110700117	19961107	00117	SO  	1996	11	7	96ZZZX5478       	1	19961009	G	2913	HYC5005	PUMP            	PRESTOLITE  		PIPER 	PA44  	PA44180     	7104402	SO  										HYD PACK	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	25PE		317  		AH1318	447995184				POWER PACK PUMP LASTED ONLY 317.13 HRS.  SUBMITTER STATED PUMP SHOULD HAVE LASTED LONGER.						1	L	7	2 	3O				A19S0   					 
1996110700118	19961107	00118	SO  	1996	11	7	96ZZZX5479       	1	19960905	G	5751	6071417	SPAR ASSY       		6071403     	PIPER 	PA18  	PA18150     	7101828	SO  										RT AIL	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2561N	3314 				188009038				FOUND THE SPAR CRACKED ON RT AILERON PN 60 714-03 AT CENTER HORN AND HINGE ASSY AT THE SPAR ATTACH.  SUSPECT FAULT LIES 	IN DESIGN AS THE AILERON SPAR WAS CUT OUT BY FACTORY ON THE OTBD EDGES OF THE 'U' CHANNGEL SPAR TO ACCOMMODATE THE AILER	ON HORN ASSY.  THIS WEAKENS SPAR AND CONTRIBUTES TO CRACKS.  CAN ONLY BE DETECTED IN EARLY STAGES BY DRILLING OFF THE HI	NGE ASSY PN 41891-00 AND INSPECTING THE SPAR.			1	H	7	1 	3O				1A2     					 
1996110700119	19961107	00119	SO  	1996	11	7	96ZZZX5480       	1	19960905	G	5751	6071416	SPAR ASSY       		6071402     	PIPER 	PA18  	PA18150     	7101828	SO  										LT AIL	CRACKED         	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2561N	3314 				188009038				FOUND THE SPAR CRACKED ON LT AILERON AT CENTER HORN AND HINGE ASSY AT THE SPAR ATTACH.  SUSPECT FAULT LIES IN DESIGN AS 	THE AILERON SPAR WAS CUT OUT ON THE OTBD EDGES OF THE 'U' CHANNEL SPAR TO ACCOMODATE THE AILERON ASSY.  THIS WEAKENS THE	 SPAR AND CONTRIBUTES TO THE CRACKS.  CAN ONLY BE DETECTED IN EARLY STAGES BY DRILLING OFF THE HINGE ASSY PN 41891-00 AN	D SUSPECT THE SPAR.			1	H	7	1 	3O				1A2     					 
1996110700120	19961107	00120	SO  	1996	11	7	96ZZZX5481       	1	19961008	G	2912	28110H	FILTER          	FACET       		PIPER 	PA31  	PA31350     	7103110	SO  										HYD SYS	THREADS BROKEN  	D				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			AL	01	3582P	17561				318052103				LANDING GEAR WOULD NOT EXTEND WITHOUT USING EMERGENCY HAND PUMP.  FOUND HYD LEAK AT LT HYD FILTER ASSY.  O-RING WAS BLOW	N AND UPON REMOVING FILTER BOWL, THREADS ON FILTER BOWL WERE FOUND BROKEN.  SUSPECT CAUSE THREADS SEPARATED FROM METAL F	ATIGUE OR OVERTORQUING.				1	L	7	2 	3O				A20SO   					 
1996110700121	19961107	00121	SO  	1996	11	7	96ZZZX5482       	1	19961015	G	8120	LW315531	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  										TURBO MOUNT	BROKEN          	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	36PB	900  				317405128				TURBO SUPPORT BOLT FOUND BROKEN 3 INCHES FROM HEAD.  BROKEN IN SHEAR.  SUBMITTER STATED THIS IS RECURRING PROBLEM WITH U	PPER LT MOUNT BOLT FOR TURBO SUPPORT ASSY.  SUBMITTER SUGGESTS BOLT WITH MORE STRENGTH.					1	L	7	2 	3O			 	A20SO   					 
1996110700122	19961107	00122	SO  	1996	11	7	96ZZZX5483       	2	19961022	G	7310	111F4174S	HOSE            	STRATOFLEX  		CESSNA	188   	T188C       	2073012	CE  	CONT  	O520  	TSIO520T    	17040	SO  					FUEL MANIFOLD	LEAKING         	G		A		A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	07	3619J					T18803655T				THE ENGINE LOST POWER, AN EMERGENCY LANDING ACCOMPLISHED WITH SMOKE COMING FROM THE ENGINE.  AN EXAMINATION OF THE ENGIN	E FOUND THE FUEL HOSE BETWEEN THE THROTTLE AND CONTROL ASSY AND THE FUEL MANIFOLD LEAKING AT A 20 PSI CHECK.  THE BAND O	N THE HOSE INDICATED A 1Q8R DATE.				1	L	7	1 	3O	3	O		A9CE    	E8CE				 
1996110700123	19961107	00123	SO  	1996	11	7	96ZZZX5484       	1	19961017	G	2436	B002881	REGULATOR       			PIPER 	PA34  	PA34200T    	7103406	SO  										DC SYS	ERRATIC         	B			APCR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			NM	01	36319	1700 	475  		AR5761	347870318				VOLTAGE REGULATOR BECAME UNSTABLE ALLOWING ALTERNATOR TO DROP OFF-LINE.  REGULATOR WOULD NOT ADJUST, REQUIRED REPLACEMEN	T.  UNIT LAST OVERHAULED BY NV2R045L.					1	L	7	2 	3O				A7SO    					 
1996110700124	19961107	00124	EA  	1996	11	7	96ZZZX5485       	2	19961015	G	8550	78619	PUMP            			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  					ENG OIL	FAILED          	B			PB2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	4232T	1700 				287210005	L1475740			DURING OVERHAUL DISASSEMBLY OF OIL PUMP, DISCOVERED WOODRUFF KEY DRIVE SHAFT AND SINTERED IRON GEARS.  AD 75-08-09 REQUI	RES REMOVAL OF THIS STYLE, BUT THIS SERIAL NUMBER IS OUTSIDE OF THOSE SPECIFIED BY LYCOMING.  AD 81-18-04 CALLS FOR REPL	ACEMENT AT 2,000 HRS OR AT ACCY CASE DISASSEMBLY FOR SINTERED IRON OIL PUMP IMPELLERS.  CURRENT AD 96-09-10 DOES SPECIFI	CY THIS ENGINE AS HAVING SINTERED IRON, BUT THIS STYLE OF DRIVE SHOULD HAVE BEEN REPLACED PER 75-08-09.			1	L	7	1 	3O	3	O		2A13    	E295				 
1996110700126	19961107	00126	CE  	1996	11	7	96ZZZX5486       	1	19960509	G	5751	122005211	HINGE           			CESSNA	206   	206CESSNA   	2073302	CE  										AIL LT WING	CRACKED         	B	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5065U	2913 				2060065				INSPECTION FOUND CRACKS AT LOWER OTBD AILERON HINGE ANGLES, CRACKS RADIATE UPWARD.  RIGHT WING HAS 2 CRACKS, LEFT WING H	AS 1 CRACK ON SIDE.					1	H	7	1 	3O			 	A4CE    					 
1996110700127	19961107	00127	CE  	1996	11	7	96ZZZX5487       	1	19960509	G	5751	122005212	HINGE ASSY      			CESSNA	206   	206CESSNA   	2073302	CE  										AIL RT WING	CRACKED         	B			T4OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5065U	2913 				2060065				INSPECTION FOUND CRACKS AT LOWER OTBD AILERON HINGE ANGLES, CRACKS RADIATE UPWARD.  RIGHT WING HAS 2 CRACKS, LEFT WING H	AS 1 CRACK ON SIDE.					1	H	7	1 	3O				A4CE    					 
1996110700128	19961107	00128	SO  	1996	11	7	96ZZZX5488       	1	19960920	G	2434	1965276	BRUSH           		110077      	PIPER 	PA23  	PA23250     	7102308	SO  										RT ENG ALT	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SO	11	6039Y		278  		A98864	273224				RIGHT ENGINE ALTERNATOR FAILED DURING FLIGHT.  WHEN ALTERNATOR FAILED, IT ALSO DAMAGED MAIN VOLTAGE REGULATOR.  THE ALTE	RNATOR  WAS OVERHAULED BY AERO ELECTRIC, INC., ON 11-17-94, AND INSTALLED ON 11-28-94.  IT APPEARS ONE BRUSH FAILED AND 	GOUGED THE ROTOR.				1	L	7	2 	3O				1A10    					 
1996110700129	19961107	00129	CE  	1996	11	7	96ZZZX5489       	1	19961004	G	3211	24411001	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  										LT MLG	BROKEN          	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CE	07	5204U	6790 			1009	172RG0282				LT GEAR WOULD NOT RETRACT OR EXTEND.  AIRCRAFT LANDED GEAR UP.  SOME DAMAGE TO PROP AND BELLY.  AFTER RECOVERY, REMOVED 	LEFT MAIN GEAR.  THE GEAR PIVOT ASSY WAS SHEARED AT THE SPLINES TO THE MAIN BODY.  BEFORE THE FLIGHT, THE BRAKES WERE NO	T SPONGY.  AFTER FAILURE, THERE WERE NO BRAKES.  THIS PROBLEM IS ADDRESSED BY CESSNA SB SEB 90-1.				1	H	7	1 	3O				3A17    					 
1996110700130	19961107	00130	CE  	1996	11	7	96ZZZX5490       	1	19961014	G	3211	22411027	PIVOT ASSY      			CESSNA	182   	R182        	2072734	CE  										LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	6110T	4240 				R18201906				PIVOT ASSY CRACKED UNDER INBOARD PRESSED-ON BEARING.  BRAKE HYD FLUID LEAKS FROM CRACK INTO SECTOR GEAR HOUSING.  SYMPTO	MS ARE A RECURRING SPONGY BRAKE.  SECOND TIME THIS CRACK HAS OCCURRED ON ONE OF THESE PIVOT ASSYS.  BOTH IN SAME PLACE. 	 THIS FORM WAS SUBMITTED ON PREVIOUS OCCASION.				1	H	7	1 	3O			RT	3A13    					 
1996110700131	19961107	00131		1996	11	7	96ZZZX5491       	4	19961014	G	6113	C5046	ATTACH PLATE    			CESSNA	182   	R182        	2072734	CE  										SPINNER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	6110T					R12801906				PROP SPINNER BULKHEAD CRACKED.  SUBMITTER STATES ON FLEET OF R182'S, THIS PART IS CRACKING WITH GREAT FREQUENCY.  THIS I	S THE 4TH TIME IN 2 YEARS.  MUST BE MADE FROM DIFFERENT MATERIAL.					1	H	7	1 	3O			RT	3A13    					 
1996110700132	19961107	00132	CE  	1996	11	7	96ZZZX5492       	1	19961017	G	2434	E3FF10300AA	ALTERNATOR      	FORD        		CESSNA	210   	T210M       	2073451	CE  										DC SYS	FAILED          	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NM	01	6161N				5090432	21062932				FAILURE DURING IFR CONDITIONS.  OPS CHECK AFTER LANDING SHOWED NORMAL VOLTAGE AND CHARGING RATE.  SECOND FAILURE IN IFR 	AND A/C LANDED.  OPS CHECK SHOWED ERRATIC VOLTAGE AND HIGH CHARGE RATE.  A/C FERRIED IFR TO REPAIR FACILITY 10 MINUTES A	WAY WITH ALT ON LINE IT FAILED AFTER TAKEOFF.  OPS CHECK SHOWED ALT TOTALLY INOP.  SUBMITTER SUSPECTS ALT BRUSH NOT INST	ALLED PROPERLY.  NEW OVHL UNIT INSTALLED.  OPS CHECK NORMAL.			1	H	7	1 	3O				3A21    					 
1996110700133	19961107	00133	CE  	1996	11	7	96ZZZX5493       	1	19961002	G	7120	051313211	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENG MOUNT	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	6624E	3969 				56124				ENG MOUNT BRACKET LOCATED AT UPPER RT SIDE FUSELAGE IMMEDIATELY AFT OF FIREWALL.  NUT AND WASHER OF ENGINE MOUNT BOLT PU	LLED THROUGH BRACKET, BOWED FIREWALL, AND PRODUCED CRACKS IN FIREWALL DOUBLER PN 0513109-29.  NOTED LACK OF TACHOMETER M	ARKINGS REQUIRED BY STC SA777CE DENOTING LIMITED OPERATION 2000-2350 RPM.				1	H	7	1 	3O			NT	3A17    					 
1996110700134	19961107	00134	CE  	1996	11	7	96ZZZX5494       	1	19960903	G	5540		SPAR ATTACH     			CESSNA	150   	150         	2071802	CE  										RUD SPAR	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7734E	5827 				17534				RUDDER BOTTOM SPAR ATTACHMENT TO RUDDER HORN, HAIR LINE CRACKED AT RIVETS DUE TO IMPROPER FIT AT SPAR AND RIB ASSY.  (RE	PAIR REINFORCMENT PREVIOUSLY INSTALLED) AND IT CRACKED ALSO.					1	H	7	1 	3O			NT	3A19    					 
1996110700135	19961107	00135	SO  	1996	11	7	96ZZZX5495       	1	19961008	G	3610	2H2216	REGULATOR VALVE 			PIPER 	PA34  	PA34200T    	7103406	SO  										2 STAGE PNEU	FAILED          	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8107D				9E336	3480170010				THE SHUT-OFF FUNCTION IS INOP ON THE LOW PRESSURE REGULATOR OF THE 2-STAGE PNEUMATIC REGULATOR VALVE ASSY.  WHEN ACTIVAT	ED VALVE DOES NOT ALLOW SUFFICIENT PNEUMATIC PRESSURE FOR OPERATION OF THE SURFACE DEICE BOOTS.					1	L	7	2 	3O				A7SO    					 
1996110700136	19961107	00136	SO  	1996	11	7	96ZZZX5496       	1	19961015	G	5230	9694300	LATCH ASSY      			PIPER 	PA34  	PA34200T    	7103406	SO  										FWD-BAG DOOR	DEFECTIVE       	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8107D					348070010				LOWER LATCH ASSY IS ELONGATING HOLE IN LOWER SILL OF FWD BAGGAGE DOOR ASSY.  FAILS TESTS PER AD 88-04-05 EVEN THOUGH AD 	PREVIOUSLY C/W.  SUBMITTER STATES INSPECTIONS REQUIRED BY AD SHOULD BE 100-HR MAINTENANCE REQUIREMENTS.  MOST PILOTS UNA	WARE OF NEED FOR PRE/POST-FLIGHT CHECK PER PIPER SB 633B.				1	L	7	2 	3O				A7SO    					 
1996110700137	19961107	00137	SO  	1996	11	7	96ZZZX5497       	1	19961011	G	3310		LIGHTING        			PIPER 	PA28  	PA28161     	7102803	SO  										COCKPIT OVERHEAD	SHORTING        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	9089N	5150 				2816003				REPORT BY PILOT THAT OVERHEAD LIGHT INOP.  REPAIR/SIGN OFF - BY MECHANIC STATED 'DID NOT HAVE SWITCH TURNED ON.  WORKS F	INE'.  AFTER SEEING THIS AND BEING FAMILIAR WITH CESSNA SEB 92-33, REV 2, TOOK ANOTHER LOOK AT OVERHEAD PANEL AND FOUND 	THAT YOU HAD TO HIT THE PANEL TO GET THE LIGHT TO COME ON AND THE RHEOSTAT ASSY WAS ROTATING FREELY EXCEPT FOR THE TANGL	ED WIRES.			1	L	7	1 	3O				2A13    					 
1996110700138	19961107	00138	EA  	1996	11	7	96ZZZX5498       	2	19961016	G	8530		ENGINE          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					PIN BUSHING	MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	93772	2403 	800  			15285549	L231015			DURING OIL CHANGE, REMOVED AND CUT OPEN OIL FILTER, FOUND COMPLETELY CONTAMINATED WITH NONFERROUS MATERIAL.  APPEARED TO	 BE ALUMINUM.  LYCOMING NOTIFIED, INFORMED OUR SHOP THAT MATERIAL PROBABLY WAS PISTON WRIST PIN OUTER BUSHINGS.  AIRCRAF	T GROUNDED, WAITING ON REPLACEMENT ENGINE.  NOTE:  CONDITION DID NOT DEGRADE-PREVIOUS OIL CHANGE (50 HRS) DID NOT SHOW M	ATERIAL OF ANY SORT.  LYC SB 525 AND SB 527 A AND B ARE SIMILAR.  (FACTORY REBUILT/OVERHAULED ENGINE.)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996110700271	19961107	00271	WP  	1996	11	7	96ZZZX5499       	1	19961015	G	6320	369A51893	SEAL            			HUGHES	369   	369D        	4470706	WP  										MR XMSN TACH GEN	LEAKING         	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	5074R	236  				1151D				M/R TRANSMISSION WAS LEAKING AND SUBSEQUENT INSPECTION FOUND THE TACHOMETER GENERATOR SEAL WAS LEAKING.  THE SEAL EDGE S	EEMED TO BE ROUGH AND BURNT LOOKING.  REPLACED SEAL.					1	G	7	1 	3U				H3WE    					 
1996110700274	19961107	00274	GL  	1996	11	7	96ZZZX5502       	2	19960705	G	7240	23031260	COMBUSTION CASE 			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ARM PIT	CRACKED         	B			EOPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	493HL					S809				ENGINE COMBUSTION CASE CRACKED AT 'ARMPIT' THROUGH WIRE MESH REINFORCEMENT.  ENGINE SHOWED A CONTINUING TREND OF LOW POW	ER.  REPLACED CASE.					1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
1996110700275	19961107	00275	GL  	1996	11	7	96ZZZX5503       	2	19961001	G	7230	6870992	CAN             		6890550     	BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CRACKED         	B			EOPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	493HL	4917 			41732	S809				TURBINE 'CAN' PN 6870992 WAS FOUND CRACKED TWO TIMES IN APPROXIMATELY 100 HOURS.  VIBRATION ANALYSIS SHOWED HIGH VIBRATI	ON LEVELS, .8IPS AT 48,000 RPM (N-1 SPEED) ON THE COMPRESSOR.  REPLACED COMPRESSOR AND HAVE HAD NO MORE CRACKING.  NOTE:	  TURBINE VIBRATION LEVEL NORMAL.  REPLACED COMPRESSOR FOR REPAIR.				1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
1996110700276	19961107	00276	SW  	1996	11	7	96ZZZX5504       	1	19960911	G	2430	SM20ACD200A21	RELAY           			BELL  	206   	206L1       	1182107	SW  										DC SYS	INOPERATIVE     	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2618	115  				45503				REMOVED RELAY FOR INOPERATIVE DC SYS.						1	G	7	1 	3U				H2SW    					 
1996110700277	19961107	00277	SW  	1996	11	7	96ZZZX5505       	1	19960829	G	6330	206033509003	BEARING         		206033506101	BELL  	206   	206L3       	1182108	SW  										XMSN RESTRAINT	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2619	460  			LK2004	51375				RESTRAINT BEARINGS WORN BEYOND LIMITS.  REPLACED 2 EACH BEARINGS, PN 206-033-509-003.						1	G	7	1 	3U				H2SW    					 
1996110700278	19961107	00278	SW  	1996	11	7	96ZZZX5506       	1	19960918	G	3340	A402AR	STROBE          			BELL  	206   	206L3       	1182108	SW  										LIGHT	LENS CRACKED    	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7159J	5473 				51408				LENS CRACKED IN HALF.  THE REFLECTOR FELL OUT.						1	G	7	1 	3U				H2SW    					 
1996110700280	19961107	00280	SW  	1996	11	7	96ZZZX5507       	1	19960815	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	1078N		241  			45389				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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 241.0.				1	G	7	1 	3U				H2SW    					 
1996110700281	19961107	00281	SW  	1996	11	7	96ZZZX5508       	1	19960815	G	6230	206010336005	LEVER IDLER     		206010350021	BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078N		241  			45389				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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 241.0.				1	G	7	1 	3U				H2SW    					 
1996110700282	19961107	00282	SW  	1996	11	7	96ZZZX5509       	1	19960903	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					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 206-010-470-10	1 BEARING.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 655.1.				1	G	7	1 	3U				H2SW    					 
1996110700283	19961107	00283	SW  	1996	11	7	96ZZZX5510       	1	19960903	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					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 206-010-470-10	1 BEARING.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 655.1.				1	G	7	1 	3U				H2SW    					 
1996110700284	19961107	00284	SW  	1996	11	7	96ZZZX5511       	1	19960815	G	6230	206010335001	LEVER ASSY      		206020350021	BELL  	206   	206L4       	1182110	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	175AL		323  			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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 322.7				1	G	7	1 	3U			NC	H2SW    					 
1996110700285	19961107	00285	SW  	1996	11	7	96ZZZX5512       	1	19960815	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		323  			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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 322.7.				1	G	7	1 	3U			NC	H2SW    					 
1996110700286	19961107	00286	SW  	1996	11	7	96ZZZX5513       	1	19960917	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	177AL		296  			52157				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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 296.2.				1	G	7	1 	3U			NC	H2SW    					 
1996110700287	19961107	00287	SW  	1996	11	7	96ZZZX5514       	1	19960903	G	6230	2106010335001	LEVER ASSY      		206010350021	BELL  	206   	206L3       	1182108	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	187AL		364  			51135				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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 363.9.				1	G	7	1 	3U				H2SW    					 
1996110700288	19961107	00288	SW  	1996	11	7	96ZZZX5515       	1	19960903	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	27554		400  			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 NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 399.7.				1	G	7	1 	3U				H2SW    					 
1996110700289	19961107	00289	SW  	1996	11	7	96ZZZX5516       	1	19960903	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		791  			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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 790.7				1	G	7	1 	3U				H2SW    					 
1996110700290	19961107	00290	SW  	1996	11	7	96ZZZX5517       	1	19960917	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		430  			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 206-010-470-10	1 BEARING.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 429.5.				1	G	7	1 	3U				H2SW    					 
1996110700291	19961107	00291	SW  	1996	11	7	96ZZZX5518       	1	19960815	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		462  			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 206-010-470-10	1 BEARING.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 461.9.				1	G	7	1 	3U				H2SW    					 
1996110700292	19961107	00292	SW  	1996	11	7	96ZZZX5519       	1	19960815	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		462  			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 206-010-470-10	1 BEARING.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 461.9				1	G	7	1 	3U				H2SW    					 
1996110700293	19961107	00293	SW  	1996	11	7	96ZZZX5520       	1	19960917	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	351AL		593  			51431				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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 593.3.				1	G	7	1 	3U				H2SW    					 
1996110700294	19961107	00294	SW  	1996	11	7	96ZZZX5521       	1	19960903	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	367AL		452  			51443				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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 451.7.				1	G	7	1 	3U				H2SW    					 
1996110700295	19961107	00295	NE  	1996	11	7	96ZZZX5522       	1	19960815	G	5531	7620205002108	RIB             			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, VERTICAL PYLON RIB CORRODED INNER GRANULAR, CRACKED, NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996110700296	19961107	00296	NE  	1996	11	7	96ZZZX5523       	1	19960815	G	5530	7620204002101	SHEAR DECK      			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERTICAL PYLON SHEAR DECK CRACKED, NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996110700297	19961107	00297	NE  	1996	11	7	96ZZZX5524       	1	19960815	G	5530	7620204011120	FITTING         			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	DEFECTIVE       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, VERT PYLON FITTING BOLT HOLE DIAMETER BEYOND LIMITS.  NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996110700298	19961107	00298	NE  	1996	11	7	96ZZZX5525       	1	19960815	G	5530	7608020046102	ANGLE           			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR IN SPECTION, FOUND VERT PYLON ANGLE CORRODED BEYOND LIMITS, IMPROPER CORROSION PREVENTION, INNER GRANULAR CORROSIO	N, NORMAL WEAR AND TEAR.					1	G	7	2 	3U				H1NE    					 
1996110700299	19961107	00299	NE  	1996	11	7	96ZZZX5526       	1	19960815	G	5530	7608020046101	ANGLE           			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERT PYLON LT ANGLE CORRODED BEYOND LIMITS, INNER GRANULAR CORROSION, NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996110700300	19961107	00300	NE  	1996	11	7	96ZZZX5527       	1	19960815	G	5531	7620205002109	RIB             			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERT PYLON RIB CRACKED, NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996110700301	19961107	00301	NE  	1996	11	7	96ZZZX5528       	1	19960815	G	5530	7620124010101	BULKHEAD        			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERT PYLON BULKHEAD CRACKED, NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996110700302	19961107	00302	NE  	1996	11	7	96ZZZX5529       	1	19960815	G	5530	7620105002105	DOUBLER         			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERT PYLON DOUBLER CRACKED, NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996020900018	19960209	00018	CE  	1996	2	9	96ZZZX553        	1	19960101	G	7110	55521106	SEAL            		555211077   	CESSNA	500   	560CESSNA   	2076750	CE  										LT INBD COWL	CORROSION       	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	500UB	1613 				5600052				OUTSIDE OF COWLING SHOWED THREE SMALL SPOTS OF CORROSION.  FOUND THE SEAL ON THE INSIDE OF THE COWLING WAS HOLDING MOIST	URE AND HAD CAUSED CORROSION TO PENETRATE ALL THE WAY THROUGH.					2	L	7	2 	4F			RT	A22CE   					 
1996110700303	19961107	00303	NE  	1996	11	7	96ZZZX5530       	1	19960815	G	5530	7620124009101	BULKHEAD        			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERT PYLON BULKHEAD CORRODED BEYOND LIMITS, INNER GRANULAR CORROSION, NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996110700304	19961107	00304	NE  	1996	11	7	96ZZZX5531       	1	19960815	G	5530	7620105001112	WEB DOUBLER     			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERT PYLON WEB DOUBLER CORRODED AND CRACKED, NORMAL WEAR AND TEAR.						1	G	7	2 	3U				H1NE    					 
1996110700305	19961107	00305	NE  	1996	11	7	96ZZZX5532       	1	19960815	G	5530	620105001101	WEB             			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERT PYLON WEB CORRODED AND CRACKED, NORMAL WEAR AND TEAR						1	G	7	2 	3U				H1NE    					 
1996110700306	19961107	00306	NE  	1996	11	7	96ZZZX5533       	1	19960815	G	5530	7620105001104	CAP ANGLE       			SKRSKY	S76   	S76A        	8143006	NE  										VERT PYLON	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				MAJOR INSPECTION, FOUND VERT PYLON CAP ANGLE CORRODED BEYOND LIMITS, INNER GRANULAR CORROSION, IMPROPER CORROSION PREVEN	TION, NORMAL WEAR AND TEAR.					1	G	7	2 	3U				H1NE    					 
1996110700307	19961107	00307	EU  	1996	11	7	96ZZZX5534       	1	19960815	G	6230	350A37100206	STAR            			AEROSP	AS355 	AS355F1     	8680810	EU  										SWASHPLATE	BROKEN          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376E	1732 			M2257	5213				REPAIR IN OVERHAUL SHOP FOUND SWASHPLATE NON-ROTATING STAR BRIDGES (PN 350A37-1 515-20) WORN THROUGH AND BROKEN.						1	G	7	2 	3U				H11EU   					 
1996110700308	19961107	00308	SW  	1996	11	7	96ZZZX5535       	1	19960917	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	42AL		707  			918				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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 706.7.				1	G	7	1 	3U				H2SW    					 
1996110700309	19961107	00309	SW  	1996	11	7	96ZZZX5536       	1	19960917	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	42AL		707  			918				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.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 706.7.				1	G	7	1 	3U				H2SW    					 
1996110700310	19961107	00310	SW  	1996	11	7	96ZZZX5537       	1	19960815	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		506  			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 NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 505.9.				1	G	7	1 	3U				H2SW    					 
1996110700311	19961107	00311	SW  	1996	11	7	96ZZZX5538       	1	19960815	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		506  			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 NAS6605D64 BOLTS, 1 EACH 206-010-470-10	1 BEARING.  SUBMITTER STATED NORMAL USE CAUSED PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 505.9.				1	G	7	1 	3U				H2SW    					 
1996110700312	19961107	00312	GL  	1996	11	7	96ZZZX5539       	2	19960909	G	7250	23032264	NOZZLE          		23035128    	SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30S     	03013	GL  					OUTER BAND/WEB	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	702AL	4667 	1448 		X59426	760243	CAE890287S			UPON MAJOR REPAIR OF TURBINE, FOUND WEB OF OUTER BAND SEEMS TO HAVE BEEN MACHINED BELOW SPECS AND REPLATED.  THIS CAUSED	 A WEAK SPOT IN FLANGE OF NOZZLE THAT CRACKED AND WENT INTO BOTH BLADE TIP PATHS.  NOZZLE IS TO BE SCRAPPED.  ASSURE THA	T PARENT METAL IS MACHINED BELOW SPECS.				1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996020900019	19960209	00019	CE  	1996	2	9	96ZZZX554        	1	19960105	G	3230	51410521	FORK BOLT       			CESSNA	402   	402B        	207590P	CE  										LT MLG RETRACT	ELONGATED HOLE  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	3131K	1650 				402B0248				DURING A ROUTINE INSPECTION, THE LEFT LANDING GEAR RETRACT LINKAGE HAD EXCESSIVE PLAY.  INVESTIGATION REVEALED THE LEFT 	MAIN GEAR TORQUE TUBE FORK BOLT HOLE WAS SEVERELY ELONGATED.  FORK BOLT IS COVERED UNDER AD 76-13-07 WHICH REQUIRES REPL	ACEMENT AT 5,000 HOUR INTERVALS.  THIS PART HAD BEEN REPLACED 1,650 HOURS PREVIOUSLY.  SUSPECT ATTACH HOLE DRILLED OVERS	IZE DURING MANUFACTURE.  IMPROPER HEAT TREATMENT.  SUBMITTER SUGGESTS MORE FREQUENT REPLACEMENT AND INSPECTION INTERVALS	.		1	L	7	2 	3O				A7CE    					 
1996110700313	19961107	00313	GL  	1996	11	7	96ZZZX5540       	1	19960607	G	6230	2816119	YOKE            			ENSTRM	F28   	F28F        	3300412	GL  										SWASHPLATE	CRACKED         	C	L	A	PP0M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	890JR	4393 			1189488H	764				CRACKS FOUND BETWEEN CONTROL ROD AND UNIVERSAL YOKES.  CRACK RUNS DOWN THE WEB BETWEEN BOTH AT 2 LOCATIONS.  SUBMITTER S	TATED THIS IS SECOND FOUND THIS MONTH.  THE OTHER CRACKED SWASHPLATE IS S/N 11-897-88H WITH SIMILAR TIME IN SERVICE.  CR	ACKED SWASHPLATE YOKE REMOVED FROM SERVICE.  NEW YOKE PURCHASED AND INSTALLED.				1	G	7	1 	3O				H1CE    					 
1996110700466	19961107	00466	CE  	1996	11	7	96ZZZX5544       	1	19960905	G	3610	10138001313	VALVE           			BEECH 	200   	200BEECH    	1152920	CE  										LT ENG FLOW CONT	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30PH		250  			BB635				PILOT REPORTS WARM AIR INFLOW TO CABIN AT FLOOR VENTS AND AT EYEBALL VENTS AT GLARESHIELD.  SHUTTING OFF LEFT SOURCE OF 	BLEED AIR, AIR FLOW RETURNS TO NORMAL TEMPERATURE.  RIGHT SIDE TURNED OFF, AIR TEMP BECOMES EXCESSIVELY WARM.  CHANGED P	NEUMOSTAT, AIR-TO-AIR COOLER, ETC.  CHECKED ENTIRE BLEED AIR SYSTEM, COULD NOT LOCATE DEFECT.  DECIDED TO CHANGE LT FLOW	 CONTROL VALVE FOR TROUBLESHOOTING PURPOSES.  PROBLEM WENT AWAY.  ALSO NOTED LT ENGINE PARAMETERS MATCHED RT ENGINE MORE	 CLOSELY AFTER FLOW CONTROL VALVE WAS CHANGED.  VALVE IN QUESTION WAS OPERATING NORMALLY EXCEPT FOR TEMP OF AIR GOING IN	TO CABIN.	1	L	7	2 	4T				A24CE   					 
1996110700467	19961107	00467	CE  	1996	11	7	96ZZZX5545       	1	19960711	G	5320	504300431183	INTERCOSTAL     			BEECH 	100   	A100        	1152915	CE  										CABIN DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	4475W	9858 				B208				THIS PART SUPPORTS THE AFT CABIN DOOR CABLE POST BRACKET (PN 50-430043-1259).  OVERLOADING OF DOOR IS THE SUSPECT CAUSE.	  SUBMITTER SUGGESTS MANUFACTURING INTERCOSTAL FROM STRONGER MATERIAL.					1	L	7	2 	3T				A14CE   					 
1996110700469	19961107	00469		1996	11	7	96ZZZX5547       	1	19960917	G	6230	206010336005	DRIVE LINK      																	M/R	BEARINGS WORN   	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PLAY IN EXCESS OF .025 INCH AT TWO PLACES.  SEE BELL MM L3 FIG 62.21.  AT TEAR DOWN FOUND BEARINGS AND SPACES WORN.  TOT	AL TIME OF BEARINGS AND SPACERS LESS THAN 100 HOURS AND 1 YEAR SINCE REPLACED.  REPLACED 4 EACH.																		 
1996110700470	19961107	00470	GL  	1996	11	7	96ZZZX5548       	2	19961009	G	7230	23050833	MODULE          			AGUSTA	A109  	A109C       	0260118	EU  	ALLSN 	250C  	250C20      	03013	GL  					AXIAL COMP	FOD DAMAGE      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	109TW	683  			15299	7650	CAE295180			DURING A ROUTINE 100-HOUR INSPECTION, FOD DAMAGE FOUND TO RT ENGINE AXIAL COMPRESSOR ROTORS AND STATOR VANES.  UNABLE TO	 ESTABLISH EXACT SOURCE OF FOD.  OPERATOR TO REVIEW CURRENTLY USED LANDING SITES.					1	G	7	2 	3U	3	U		H7EU    	E4CE				 
1996110700471	19961107	00471	NE  	1996	11	7	96ZZZX5549       	1	19960926	G	5302	7610205004110	PRESSURE PAD    			SKRSKY	S76   	S76A        	8143006	NE  										T/R	WRONG SIZE      	B			EGRR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	274TC					760274				PAD NORMAL THICKNESS IS .122 INCH.  DEFECTIVE ONE MEASURES .135 INCH CAUSING INCORRECT CLAMP UPON T/R SPAR.						1	G	7	2 	3U				H1NE    					 
1996110700473	19961107	00473	SO  	1996	11	7	96ZZZX5551       	1	19961001	G	5730	83127002	SKIN            			PIPER 	PA46  	PA46310P    	7104605	SO  										LT WING ROOT	CRACKED         	B	S	A	MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	286CM	1530 				468608043				INSP OF LT AND RT WING FOUND SKIN CRACKED AT THE POINT WHERE BONDED STRINGER DOES NOT ATTACH TO INBOARD RIB.  SKIN CRACK	S AT THE .1875 INCH GAP BETWEEN STRINGER AND RIB.					1	L	7	1 	3O				A25SO   					 
1996110700474	19961107	00474	SO  	1996	11	7	96ZZZX5552       	1	19961001	G	5730	83127003	SKIN            			PIPER 	PA46  	PA46310P    	7104605	SO  										RT WING ROOT	CRACKED         	B			MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	286CM	1530 				468608043				INSP OF LT AND RT WING FOUND SKIN CRACKED AT THE POINT WHERE BONDED STRINGER DOES NOT ATTACH TO INBOARD RIB.  SKIN CRACK	S AT THE .1875 INCH GAP BETWEEN STRINGER AND RIB.					1	L	7	1 	3O				A25SO   					 
1996110700475	19961107	00475		1996	11	7	96ZZZX5553       	1	19961024	G	2140	45C40	COMBUSTION TUBE 	JANITROL    	D83A28      															HEATER	BLOWN OUT       	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09					7650194					COMBUSTION TUBE REMOVED FROM D83A28 JANITROL HEATER, MODEL NR S-50.  OUTSIDE SKIN OF COMBUSTION TUBE BLOWN THROUGH AT CR	OSS-OVER PORT LOCATIONS.  SUSPECT CAUSE IS DUE TO LACK OF MAINTENANCE AND NOT BEING OVERHAULED AT RECOMMENDED INTERVALS.	  THESE TUBES ARE INSTALLED IN BEECHCRAFT A55, B55, 56TC AIRCRAFT.  SUBMITTER STATED TO PREVENT THESE OCCURRENCES, AN AD	 WOULD BE REQUIRED.  THESE HEATERS ARE NOT BEING TAKEN CARE OF PER THE JANITROL AND BEECHCRAFT SM'S.  PRESSURE DECAY TES	TING WOULD FIND THE BAD TUBES.															 
1996110700476	19961107	00476	CE  	1996	11	7	96ZZZX5554       	1	19961023	G	3213	51411036	TRUNNION ASSY   			CESSNA	421   	421C        	2076016	CE  										RT MLG	CRACKED         	B	S		HLFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	148MA	5129 				421C0078				INSP FOUND RT MLG TRUNNION ASSY UPPER BARREL CRACKED.						1	L	7	2 	3O				A7CE    					 
1996110700477	19961107	00477		1996	11	7	96ZZZX5555       	4	19961014	G	6113	15573005	BULKHEAD        			CESSNA	337   	337G        	2075730	CE  										SPINNER	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	11	31ME					33701524				SPINNER BULKHEAD RECEIVED FORM CESSNA WITH HEAVY TOOL MARKS IN THE RADIUS OF THE INNER FLANGE.  THE MOUNTING BOLT HOLES 	DO NOT LINE UP BETWEEN THE FLANGE AND FLANGE DOUBLER.  ALSO, DEEP SANDING MARKS AT BOLT HOLE AREA AND UNDER AND AROUND R	IVET BUCK TAILS OF FLANGE DOUBLER.				1	H	7	2 	3O				A6CE    					 
1996110700478	19961107	00478	SO  	1996	11	7	96ZZZX5556       	2	19961025	G	8530	631521	SPRING          			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					INT VALVE	BROKEN          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	33NC					402B0825	271359R			DURING A ROUTINE COMP CHECK, NR 6 CYL WAS NOTED TO HAVE LOW COMP.  THE ROCKER COVER WAS REMOVED TO STACK VALVE.  AT THAT	 POINT, IT WAS NOTED THAT THE INT VALVE SPRING WAS BROKEN.  THE ADJACENT ROCKER WAS THEN REMOVED AND ANOTHER SPRING WAS 	FOUND TO BE BROKEN AS WELL. AT THIS POINT, THE REMAINING COVERS WERE REMOVED AND SPRINGS WERE FOUND TO BE BROKEN ON ALL 	REMAINING CYLINDERS.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996110700479	19961107	00479	CE  	1996	11	7	96ZZZX5557       	1	19961010	G	2750		LIMIT SWITCH    			CESSNA	402   	402C        	207590R	CE  										FLAP GEARBOX	ARMS LOOSE      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	402MQ					402C095				FLAPS FOUND HANGING DOWN APROXIMATELY 1 INCH AT INSPECTION.  DISCOVERED FLAP GEARBOX LIMIT SWITCH ACTUATING ARM LOOSE ON	 SHAFT.  FLAP PRE-SELECT SWITCH FAILED AND FLAPS DID NOT STOP.  REPLACED BENT PUSH/PULL TUBES AND GEARBOX RIGGED AND OPS	 CHECKED SYSTEM.				1	L	7	2 	3O				A7CE    					 
1996110700480	19961107	00480	CE  	1996	11	7	96ZZZX5558       	1	19961001	G	3230	368200113	RETRACT TUBE    			BEECH 	36    	A36         	1151604	CE  										NLG RETRACT	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	11	47KA	5341 				E530				DURING ROLL-OUT AFTER NORMAL LANDING, THE NLG COLLAPSED.  FURTHER INVESTIGATION REVEALED THE AFT NOSE GEAR RETRACT ROD H	AD FAILED AT A POINT APPROXIMATELY 1 INCH ONTO THE THREADED PORTION OF THE ROD WHERE P/N ARHT5ECR ROD END THREADS ENDED 	IN THE ROD.				1	L	7	1 	3O				3A15    					 
1996110700481	19961107	00481	SO  	1996	11	7	96ZZZX5559       	2	19961022	G	8530	653446A11	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					NR 2	BROKEN          	D				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			NM	11	4856U		1470 			21064825	517396			AFTER DEPARTURE, THE PILOT RETURNED AND LANDED DUE TO AN UNUSUAL NOISE FROM THE ENGINE.  HE STATED THAT HE BELIEVED THE 	EXHAUST SYSTEM HAD PROBABLY BROKEN.  UPON INVESTIGATION OF THE ENGINE, DISCOVERED THE NR 2 CYL HAD CRACKED 3/4 OF THE WA	Y AROUND THE CIRCUMFERENCE OF THE COMBUSTION CHAMBER.  COMBUSTION PRESSURE AND EXH GAS BURNED A HOLE THROUGH THE COOLING	 FINS OF THE NR 4 CYL.  COMBUSTION GAS EXITING THE BROKEN CYL WAS DIRECTED ON TO THE STAINLESS STEEL FUEL INJECTION NOZZ	LE LINE.  CONTINUED FLIGHT AND WOULD MOST PROBABLY HAVE RESULTED IN AN ENGINE FIRE.		1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996110700482	19961107	00482	SO  	1996	11	7	96ZZZX5560       	2	19961004	G	7313	633723019A	INJECTOR        			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NR 3 CYLINDER	MISDRILLED      	B	S		EVCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03	915DW		846  			421B0914	634835R			WHILE PERFORMING REPAIR IN ADJACENT AREA, FUEL STAINS WERE NOTED AT NR 3 CYLINDER INJECTOR WHERE IT THREADS INTO CYLINDE	R HEAD. WHILE REMOVING THE INJECTOR, IT BROKE OFF AT THREADS.  FURTHER INSP OF INJECTOR REVEALED THE ORIFICE IN THE OUTL	ET OF THE INJECTOR IS DRILLED OFF-CENTER.  SUBMITTER STATED FAILURE OF INJECTOR IN THIS AREA IS POTENTIALLY CATASTROPHIC	 DUE TO RAW FUEL LEAKING OVER THE TOP OF THE ENGINE. INJECTORS SHOULD BE INSP CLOSELY WHEN CLEANED OR AFTER RECEIVING FR	OM OVERHAUL FACILITY.		1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996110700483	19961107	00483	SO  	1996	11	7	96ZZZX5561       	2	19961001	G	8530	537750	BOLT            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 4 CYL EXH RKR	FAILED          	D				E				ENGINE SHUTDOWN         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			WP	17	98PJ					421C0824	272345R			NR 4 CYLINDER ROCKER SHAFT BOLTS BROKE. LOOSE ROCKER PUNCHED A HOLE THROUGH VALVE COVER.  ROUGH RUNNING AND SMOKE IS REA	SON FOR IN-FLIGHT SHUT DOWN.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996110700485	19961107	00485		1996	11	7	96ZZZX5562       	4	19961001	G	3457	GPS90	YOKE MOUNT      	GARMIN INTL 		PIPER 	PA24  	PA24260     	7102406	SO  										POWER WIRE	FOULS YOKE      	D	P	A		O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	15	9137P					244618				YOKE MOUNT CLAMP INSTALLED BY OWNER GOT FOULED IN THE POWER WIRE TO PORTABLE GPS.  RESTRICTED YOKE MOVEMENT.  PILOT MAKE	 HARD LANDING.  WIRE FINALLY BROKE IN TWO ALLOWING A/C TO BE 'FLARED'.  PILOTS SHOULD BE MADE AWARE TO CHECK YOKE MOVEME	NT ON PRE-FLIGHT.  YOKE MODIFIED WITH CURLEY CORD TO PREVENT RECURRENCE.				1	L	7	1 	3O				1A15    					 
1996110700486	19961107	00486	GL  	1996	11	7	96ZZZX5563       	2	19960831	G	7230	9380M28P05	SPOOL           								GE    	CF6   	CF680C      		GL  					3-9 HPC	CRACKED         	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01		16197			VOLO3872		31X95154			THE HPC 3-9 SPOOL IS REJECTED DUE TO CRACK INDICATION PER SB 72-812.  INDICATION IS LOCATED ON STAGE 9 FORWARD FACE APPR	OXIMATELY 0.170 INCH FROM OUTSIDE DIAMETER AND APPROX 220 DEGREES FROM SERIAL NUMBER.  INDICATION HAS A DEPTH OF 0.030 I	NCH AND DISPLAYS AN AMPLITUDE OF 50 PERCENT FSII AT 2416 DB.  THE SURFACED AREA AROUND THE INDICATION EXHIBITED A RIPPLE	 EFFECT ON INITIAL INSPECTION.  THE SURFACE WAS BLENDED TO A SMOOTH FINISH AND RE-INSPECTED WITH NO CHANGE TO THE INDICA	TION AMPLITUDE.							4	F			E23EA				 
1996110700487	19961107	00487	WP  	1996	11	7	96ZZZX5564       	1	19961001	G	2410	696747B	SUPPORT         	SUNDSTRANDEM	696233B     	DOUG  	DC9   	DC9         	3022002	WP  										CSD	MISINSTALLED    	B			KQ4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17					D529					5 EA BOLTS USED TO MOUNT THE GOVERNOR SUPPORT ASSY TO THE OUTPUT HOUSING WERE SAFETY WIRED TOGETHER.  THIS PRACTICE IS N	OT SPECIFIED IN THE OEM MANUAL.					2	L	7	2 	4F				A6WE    					 
1996110700488	19961107	00488	SO  	1996	11	7	96ZZZX5565       	1	19961010	G	3230	400235	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  										NLG DRAG LINK	BROKEN          	D	L			O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			EA	23	2556Z	8500 				278054048				ACFT IS USED IN A PART 135 CHARTER OPERATION.  THE ACFT WAS RETURNING WITH ONE PILOT AND ONE PAX ABOARD.  THE ACFT MADE 	A NORMAL LANDING AND ROLL-OUT, HOWEVER, WHILE TAXIING TO PARKING THE LANDING GEAR UNSAFE HORN BECAME AUDIBLE AND THE PIL	OT NOTICED THE NLG (DOWN AND LOCKED) GREEN LIGHT INDICATOR WAS NOT LIGHTED.  THE ACFT WAS STOPPED IMMEDIATELY AND SHUT-D	OWN.  AN INITIAL INSP BY A MECH REVEALED THAT THE BOLT SECURING THE UPPER DRAG LINK TO THE AIRFRAME WAS CRACKED AND PART	IALLY SHIFTED FROM ITS ORIGINAL LOCATION.  THE ATTACH FITTINGS WHICH CONNECT THE UPPER DRAG LINK TO THE AIRFRAME WERE CR	ACKED AND PARTIALLY TWISTED FROM ORIGINAL POSITION.	1	L	7	2 	3O				1A10    					 
1996110700489	19961107	00489	WP  	1996	11	7	96ZZZX5566       	1	19961001	G	2410	695855	DISCONNECT CLAMP	SUNDSTRANDEM	696233B     	DOUG  	DC9   	DC9         	3022002	WP  										CSD	WRONG PART      	B			KQ4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17					1526					BOLT USED TO CONNECT CLAMP ON DISCONNECT PLUNGER SHAFT PROTRUDES .5 INCH INTO CAVITY. OEM MANUAL SPECIFIES NAS1352-3-8, 	FOUND DASH 12 TO BE INSTALLED IN UNIT.					2	L	7	2 	4F				A6WE    					 
1996110700490	19961107	00490	SW  	1996	11	7	96ZZZX5567       	1	19961023	G	7922	53E19600	VALVE           			MOONEY	M20   	M20J        	5870219	SW  										THERMO BYPASS	FAILED          	D	L			A				UNSCHED LANDING         				M			OVER TEMP                 			CR	CRUISE         	1			WP	25	1148N	340  				241208				20 MINUTES INTO A FLT, THE OIL TEMP WENT FULL HOT.  A CROSS CHECK OF INSTRUMENTS REVEALED ALL CYL TEMPERATURES NORMAL. T	HERE WAS NO LOSS OF ENG POWER, HOWEVER, OIL PRESS WAS LOWER THAN NORMAL.  THE ONLY WAY TO LOWER THE OIL TEMP WAS TO REDU	CE POWER AND PUT THE AIRCRAFT INTO A GLIDE.  RETURN TO THE AIRPORT WAS MADE.  THE VERNATHERM VLV WAS REMOVED AND UPON CH	ECKING IT IN HOT WATER, FOUND TO BE DEFECTIVE.			1	L	7	1 	3O				2A3     					 
1996110700491	19961107	00491	CE  	1996	11	7	96ZZZX5568       	1	19960402	G	3020	10191012323	ICE VANE DOOR   		10191011215 	BEECH 	300   	300BEECH    	1152930	CE  										LT COWL	BROKEN          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	250PD					FA33				UPON INSPECTION OF AIRCRAFT (150 HR 2ND INTERIM) LEFT COWL FWD LOWER ICE VANE DOOR OUTER EDGE (4 INCH BY 8 INCH) FOUND M	ISSING FROM ASSEMBLY.  LEFT ENGINE 1ST STAGE COMPRESSOR INSPECTED FOR FOD.  ONE BLADE FOUND LEADING EDGE BENT AND TORN R	EQUIRING ENGINE TEAR DOWN AND REPAIR OF FOD PER P & W MM 3034342.  ON FURTHER INSPECTION, ICE VANE DOOR ON RT COWL FOUND	 CRACKING IN SAME AREA.  ICE VANE AFT BLOCKER DOOR (PN 101-910124-51).  ALSO FOUND CRACKING ON LT/RT COWLS.  RECOMMEND D	OOR 'BOND ASSEMBLY' MADE THICKER WHERE ACTUATOR BRACKETS ARE ATTACHED.		2	L	7	2 	4T				A24CE   					 
1996110700492	19961107	00492	CE  	1996	11	7	96ZZZX5569       	1	19961010	G	2750		CONTROL CABLE   			CESSNA	402   	402C        	207590R	CE  										RT FLAP RETURN	FRAYED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5820C					402C0047				DURING INSPECTION RIGHT HAND FLAP RETURN CABLE WAS FOUND FRAYED.  SEVERAL STRANDS BROKEN AT A PULLEY.  REPLACED CABLE, R	IGGED PER MM.  SUGGEST CLOSE INSPECTION OF CABLES AT PULLEYS.					1	L	7	2 	3O			 	A7CE    					 
1996110700493	19961107	00493	EU  	1996	11	7	96ZZZX5570       	1	19961001	G	2422	ASH6641PF	INVERTER        			BRAERO	DH125 	BAE125800A  	1500285	EU  										INST AC SYS	FAILED          	C		A		K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	17	600J	1267 			MJ870M	NA0470				INVERTER OUTPUT RAN UNDER VOLTAGE AND UNDER FREQ AND SUBSEQUENTLY THE UNIT BURNED, CAUSING DUAL ALTIMETER FAILURES.  SUB	MITTER STATED THIS FAILURE TOOK PLACE ON FEBRUARY 24, 1996 AND AS OF OCTOBER 14, 1996 NO CORRECTIVE ACTION FROM THE COMP	ONENT MANUFACTURER OR THE ARIFRAME MANUFACTURER HAS BEEN BROUGHT FWD.  THIS IS THE SECOND FAILURE OF THIS TYPE ON A 125-	800.			2	L	7	2 	4F			RT	A3EU    					 
1996110700494	19961107	00494	SO  	1996	11	7	96ZZZX5571       	1	19961022	G	3213	452838	BUSHING         		8360503     	PIPER 	PA46  	PA46350P    		SO  										RT MLG	WORN            	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	711BL	322  				4622175				DURING AN ANNUAL INSPECTION, VERTICAL FREE PLAY OF THE RIGHT MAIN LANDING GEAR TRUNNION PIN TO BUSHING TO PIN CLEARANCE 	MEASURED .025 INCH GREATER THAN THE LEFT MAIN LANDING GEAR.  NO TOLERANCE FOR VERTICAL MOVEMENT COULD BE FOUND IN THE AI	RCRAFT MANUFACTURERS SM.  A NEW FORWARD AND AFT BUSHING WERE ORDERED AND RECEIVED FROM THE MANUFACTURER.  WHEN THE SM WA	S AGAIN PERUSED FOR A BUSHING REPLACEMENT PROCEDURE, NONE WAS FOUND.  THE AIRCRAFT MANUFACTURER'S ENGINEERING DEPARTMENT	 WAS CONSULTED FOR A PROCEDURE.  ENGINEERING INFORMED US THAT THEY HAD NOT ANTICIPATED THAT REPLACEMENT OF THE BUSHING W	OULD EVER BE REQUIRED, AND THEREFORE HAD NO PROCEDURE AVAILABLE.	1	L	7	1 	3O			RT	A25SO   					 
1996110700495	19961107	00495	CE  	1996	11	7	96ZZZX5572       	1	19961010	G	3010	2H598	FLOW VALVE      			CESSNA	402   	402C        	207590R	CE  										LT WING DEICE	STICKING        	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	747WS					402C0080				WING DEICE BOOTS DID NOT FULLY DEFLATE AFTER NORMAL CYCLE.  LEFT FLOW VALVE STUCK PARTIALLY OPEN.  INSTALLED NEW VALVE. 	 OPS CHECKED NORMAL.					1	L	7	2 	3O				A7CE    					 
1996020900023	19960209	00023		1996	2	9	96ZZZX558        	4	19960117	G	3452	6221270001	TRANSPONDER     	COLLINS     		CESSNA	650   	650         	2076802	CE  										NR 2	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	39WP				511	6500039				REINSTALLED ADC AFTER MOD STATUS UPGRADE AND CERTIFICATION.  WHILE COMPLYING WITH CFR SECTION 91.411/91.413 FUNCTION TES	T, NOTED NR 2 TRANSPONDER ALTITUDE READ-OUT WAS INVALID FROM 500 FEET TO 1,000 FEET AND AT EACH ASCENDING 500 FOOT INCRE	MENT TO THE NEXT THOUSAND.  IN DESCENDING ALTITUDE TESTS, THE NR 2 TRANSPONDER READ INVALID FROM EACH 1,000 FOOT ALTITUD	E READING THROUGH EACH 500 FOOT ALTITUDE LEVEL.  REMOVED AND REPLACED TRANSPONDER AND REQUESTED SHOP BENCH REPORT ON FIN	DINGS.		2	L	7	2 	4F				A9NM    					 
1996110700704	19961107	00704	SW  	1996	11	7	96ZZZX5582       	1	19960917	G	6230	206010335001	LEVER ASSY      		206010350021	BELL  	206   	206L1       	1182107	SW  										SPACERS/BUSHINGS	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1075W		296  			45377				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL WEAR CAUSES PARTS TO WEAR OUT TOO SOON.  WORN P	ARTS TT 296.2.				1	G	7	1 	3U				H2SW    					 
1996111400298	19961114	00298	CE  	1996	11	14	96ZZZX5584       	1	19961008	G	3240	61706917	CONTROL CABLE   			CESSNA	501   	501         	2076603	CE  										PARK BRAKE	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	101RR	4186 				5010241				WHEN THE PILOT ATTEMPTED TO SET THE PARK BRAKE, THE ATTEMPT PULLED THE KNOB AN D APPROXIMATELY 18 INCHES OF CABLE FROM T	HE HOUSING.					1	L	7	2 	4F			 	A27CE   					 
1996111400299	19961114	00299	EA  	1996	11	14	96ZZZX5585       	1	19961027	G	3411	601A51631	MANIFOLD        			CNDAIR	CL600 	CL6002B16   	1900305	EA  										STATIC SYSTEM	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	612CC					5186				CREW COMPLAINED OF EXCESSIVE ALTIMETER SPLITS AT ALTITUDE.  FOUND STATIC MANIFOLD (TIE POINT OF ALL 3 STATIC SYSTEMS) MO	UNTED BACKWARDS.  FOUND THE ARROW INDICATING FWD 180 DEGREES OUT.					2	L	7	2 	4F			RT	A21EA   					 
1996111400300	19961114	00300		1996	11	14	96ZZZX5586       	4	19961025	G	2562	DMU1581	BATTERY PACK    	DORNEMARGLN 	ELT1411     	LEAR  	60    	60LEAR      	5170707	CE  										ELT	FAULTY          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	618R	656  			1053A	044				DURING A SCHEDULED ELT FUNCTIONAL CHECK, THERE WAS NO DOWNWARD SWEEPING TONE.  DURING THE TROUBLESHOOTING OF THE ELT, IT	 WAS FOUND THAT THE BATTERY PACK WAS AT 6.8 VOLTS.  (SUPPOSED TO BE 9 VOLTS).  THE REPLACE ON/OR BEFORE DATE IS FEB '97.	  DATE OF INSTALL WAS JAN '95.				2	L	7	2 	4F			RT	A10CE   					 
1996111400301	19961114	00301	CE  	1996	11	14	96ZZZX5587       	1	19961025	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										RT WING	CRACK           	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	81WS	4724 				4410181				DURING A PHASE INSPECTION, FOUND A 1.5 INCH CRACK IN RT WING CANTED RIB TOP CAP.  CRACK STARTS AT AFT SIDE OF FWD WING S	PAR AND RUNS AFT PARALLEL TO THE BEND RADIUS.  STOP DRILLED CRACK PER CESSNA INSTRUCTIONS.					1	L	7	2 	3T			RT	A28CE   					 
1996111400302	19961114	00302	GL  	1996	11	14	96ZZZX5588       	2	19961025	G	7320	23033400	FILTER ELEMENT  			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FCU PC FILTER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	937S	3271 				51258	CAE895318			FILTER ELEMENT CRACKED WHERE END CAP IS ATTACHED TO ELEMENT.  SOME PIN HOLES AND CORROSION AROUND FILTER TO END CAP BOND	.  ELEMENT MAY HAVE BEEN FROM ENGINE OPERATED IN SALT LADEN ATMOSPHERE AND INSTALLED WHEN ENGINE WAS TORN DOWN FOR INSPE	CTION BY OUTSIDE VENDOR.  RECOMMEND INSP WITH 10X MAGNIFYING GLASS EACH INSP INTERVAL.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1996111400303	19961114	00303	CE  	1996	11	14	96ZZZX5589       	1	19961017	G	5347	870106	SAF T STOP      			CESSNA	172   	172M        	2072418	CE  										SEAT RAIL STOP	MISUSE          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07										THE SAF-T-STOP ITSELF IS NOT THE PROBLEM.  IT IS THE WAY IT IS INSTALLED ON SEAT RAILS.  OWNERS AND OPERATORS ARE USING 	THE SAF-T-STOP FOR PRIMARY SEAT STOPS EVEN THOUGH INSTRUCTIONS STATE OTHERWISE.  SUBMITTER STATES ONLY FIX IS TO REMOVE 	PRODUCT FROM SERVICE.				1	H	7	1 	3O			NT	3A12    					 
1996111400304	19961114	00304	CE  	1996	11	14	96ZZZX5590       	1	19961008	G	2121	BC61A9012	BLOWER          			CESSNA	501   	501         	2076603	CE  										CABIN	FAILED          	D				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CE	09	101RR		1    			5010241				THE CABIN BLOWER ASSY WAS INSTALLED AND CHECKED FOR OPERATION.  LESS THAN AN HOUR INTO THE NEXT FLIGHT, THE BLOWER FAILE	D.  WHEN THE BLOWER WAS EXAMINED, THE ELECTRICAL LEADS COULD BE FELT CONTACTING THE ARMATURE WHEN THE BLOWER WAS TURNED.	  THE ASSY WAS NOT DISASSEMBLED DUE TO WARRANTY CONSIDERATIONS.				1	L	7	2 	4F				A27CE   					 
1996111400305	19961114	00305		1996	11	14	96ZZZX5591       	1	19961021	G	7100	4914	FITTING         	AEROQUIP    																HOSE	BROKE           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11										PART OF FITTING THAT GOES INSIDE 303 HOSE BROKE BEFORE IT WAS SCREWED ALL THE WAY IN.  IT WAS NOT CROSS-THREADED.  IT BR	OKE AT THE END OF THE THREADS.  THREE FITTINGS BROKE IN A ROW.  ALL AEROQUIP FITTING TAGS WERE HAND WRITTEN 491-4.  DIAM	ETER OF BREAK .253 INCH.  FITTINGS WERE PURCHASED FROM AUSCO COLLEGE PARK, GA.																	 
1996111400306	19961114	00306	EA  	1996	11	14	96ZZZX5592       	2	19961025	G	7310	883410000600094	HOSE            	DEUTSCH     		CESSNA	177   	177         	2073704	CE  	LYC   	O360  	O360A1F6    	41514	EA  					PUMP TO CARB	LEAK            	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	19974	30   				17702617				NOTICED FUEL STAIN ON STEEL BRAID HOSE.  REMOVED AND TESTED.  FOUND SEEP HOLE.  NOTIFIED SUPPLIER AND SENT FOR FACTORY I	NSPECTION.  (SEEP WAS DETECTABLE WITH SHOP AIR AND SOAPY WATER.)					1	H	7	1 	3O	3	O	NT	A13CE   	E286				 
1996111400307	19961114	00307	NE  	1996	11	14	96ZZZX5593       	2	19960718	G	8520		VALVE           			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R985  	R985AN14B   	52008	NE  					NR 4 EXH	STRETCHED       	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	AG	AGRICULTURE    	1			NM	04	5291	624  				572	JP205327			DURING SPRAY APPLICATION, CYLINDER HOLD-DOWN STUDS SHEARED 8 OF 10.  THE CYLINDER CAME LOOSE RESULTING IN LOSS OF POWER 	AND FORCED PRECAUTIONARY LANDING.  NO RECOMMENDATION.					1	Q	7	1 	3R	3	R		1A16    	5E1				 
1996111400308	19961114	00308	GL  	1996	11	14	96ZZZX5594       	3	19961015	G	6111	S84B	BLADE           													MCAULY	2A36C	2A36C23     	GL  	THREADS	CRACKED         	B			DJFR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23								676355		FOUND RED DYED OIL LEAK NR 2 BLADE.  DISASSEMBLED PROP, REMOVED FERRULE, FOUND CRACK IN BLADE THREADS.																5	C	P880	 
1996111400309	19961114	00309	CE  	1996	11	14	96ZZZX5595       	1	19960628	G	3213	NAS50200	SNAP RING       			BEECH 	35    	J35         	1151522	CE  										LT MLG STRUT	DISENGAGED      	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	3029C	3187 				D5694				THE SNAP RING DISENGAGED FROM THE GROOVE IN THE LT MLG STRUT WHICH ALLOWED THE END PLUG P/N 45-815224 TO BE EXPELLED WIT	H GREAT FORCE THROUGH THE TOP OF THE WING WHILE THE AIRCRAFT WAS PARKED ON THE RAMP.  MANUFACTURER'S TECH SUPPORT INDICA	TES 3 POSSIBLE REASONS THE SNAP RING CAN BE DISLOGED.  1.  THE WRONG PART NUMBER SNAP RING.  2.  THE SNAP RING WAS INSTA	LLED UPSIDE DOWN, I.E., THE BEVELED SIDE UP.  3.  THE SNAP RING WAS DISTORTED WHEN IT WAS INSTALLED, ALL OF WHICH CAN BE	 LAID AT THE FAULT OF THE MAINTENANCE FACILITY THAT LAST INSTALLED THE SNAP RING.  ACCORDING TO THE AIRCRAFT RECORDS THE	 STRUT WAS SERVICED 49.6 HOURS.	1	L	7	1 	3O				3A15    					 
1996111400310	19961114	00310	CE  	1996	11	14	96ZZZX5596       	1	19961001	G	5311	12124139	FRAME           			CESSNA	210   	P210N       	2073454	CE  										FS 166.40	CRACKED         	B			JZRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	40RC	6995 				P21000261				REMOVED ANTENNA FROM TOP OF TAILCONE, FOUND CRACKS IN SKINS P/N 1210504-4 AND P/N 1210504-6.  FURTHER INVESTIGATION REVE	ALED REPAIRED BULKHEAD.  PREVIOUSLY INSTALLED REPAIR AND SKIN DOUBLER FOUND CRACKED AS WELL.  POOR LOCATION FOR ANTENNA 	INSTALLATION DUE TO LIGHT STRUCTURE.  CONTRIBUTING WAS POOR QUALITY OF REPAIR TO BULKHEAD AND SKIN DOUBLER.				1	H	7	1 	3O				3A21    					 
1996111400311	19961114	00311	NM  	1996	11	14	96ZZZX5597       	1	19961001	G	5711	11121460	SPAR            			UNIVAR	108   	1083        	9230408	NM  										LT WING FORE	CORRODED        	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	6093M					1084093				INSPECTION OF LT WING AFTER INCIDENCE OF STORM DAMAGE TO TIP BOW, FOUND HEAVY CORROSION TO BOTH SPARS.  RT WING WAS THEN	 INSPECTED AND SPAR CORROSION WAS ALSO FOUND.  LT WING CORROSION WAS ACCELERATED BY A LARGE BIRD NEST INSIDE.  REPLACED 	SPARS WITH NEW.				1	H	7	1 	3O				A767    					 
1996111400312	19961114	00312	NM  	1996	11	14	96ZZZX5598       	1	19961001	G	5711	11121470	SPAR            			UNIVAR	108   	1083        	9230408	NM  										LT WING AFT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	6093M					1084093				INSPECTION OF LT WING AFTER INCIDENCE OF STORM DAMAGE TO TIP BOW, FOUND HEAVY CORROSION TO BOTH SPARS.  RT WING WAS THEN	 INSPECTED AND SPAR CORROSION WAS ALSO FOUND.  LT WING CORROSION WAS ACCELERATED BY A LARGE BIRD NEST INSIDE.  REPLACED 	SPARS WITH NEW.				1	H	7	1 	3O				A767    					 
1996111400313	19961114	00313	CE  	1996	11	14	96ZZZX5599       	1	19961024	G	2740	NAS314251411	CONTROL CABLE   			BEECH 	23    	C23         	1151242	CE  										STABILATOR	FRAYED          	B	S	A	AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6711C	5572 				M2116				DURING ANNUAL INSPECTION, STABILATOR DOWN CABLE WAS FOUND FRAYED AT FORWARD PULLEY BEHIND FIRE WALL UNDER CONTROL COLUMN	.  SEVERAL STRANDS WERE BROKEN.  REPLACED CABLE.  SUGGEST CLOSE INSPECTION AT EACH ANNUAL INSPECTION.					1	L	7	1 	3O			 	A1CE    					 
1996111400314	19961114	00314	CE  	1996	11	14	96ZZZX5600       	1	19961029	G	3245	15X6006	TUBE            	PARKERHANFIN	4090B       	CESSNA	414   	414A        	2075907	CE  										NLG	STEM FAILED     	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	13	4573V					414A0300				ON LANDING ROLL-OUT, NOSE TIRE DEFLATED.  FENDER P/N 5042022-9 WAS TORN FROM THE NOSE GEAR ASSEMBLY.  IT WAS DISCOVERED 	THE VALVE STEM WAS MISSING FROM THE NOSE TIRE.  NOSE TIRE P/N 600-6-8-330 HAD BEEN REPLACED 8-10-95.  THE TOTAL TIME ON 	THE TIRE SINCE REPLACEMENT 715.5 HRS.				1	L	7	2 	3O				A7CE    					 
1996111400315	19961114	00315	CE  	1996	11	14	96ZZZX5601       	1	19961008	G	3231	12838002143	CONTROL CABLE   			MTSBSI	MU300 	MU300       	5780602	CE  										MLG DR EMERG EXT	FAILED          	B		A	PIQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	75BL	1988 	1988 			A017SA				DURING ROUTINE A-CHECK INSPECTION WHILE PERFORMING EMERGENCY GEAR EXTENSION CHECK, RIGHT HAND GEAR DOOR WOULD NOT OPEN. 	 INVESTIGATED DISCREPANCY AND FOUND SWAGED TERMINAL END ON DOOR CABLE BROKEN OFF.  IN AN ACTUAL IN-FLIGHT EMERGENCY, THE	 RT MAIN LANDING GEAR WOULD NEVER EXTEND.				2	H	7	2 	4F			RT	A14SW   					 
1996111400317	19961114	00317	CE  	1996	11	14	96ZZZX5603       	1	19961101	G	8011	66082686	STARTER         			LEAR  	35    	35A         	5170602	CE  										RT ENGINE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	815L		71   		468U	142				STARTER VERY SLOW IN BRINGING ENGINE UP TO START SPEED.						2	L	7	2 	4F				A10CE   					 
1996111400318	19961114	00318	CE  	1996	11	14	96ZZZX5604       	1	19961023	G	7620	MS924529	COTTER PIN      		310281201   	CESSNA	500   	550         	2076604	CE  										RT ENG NR 4 BRG	WORN            	D		A		E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			EA	23	6846T		286  			5500625				ON CLIMB-OUT AFTER TAKEOFF, RT ENGINE OIL TEMPERATURE BEGAN TO RISE AND PRESSURE BEGAN TO FALL.  PILOT IMMEDIATELY SHUT 	DOWN RT ENGINE AND RETURNED TO AIRPORT WHERE AN UNEVENTFUL LANDING WAS MADE.  LOSS OF ENGINE OIL WAS DISCOVERED TO BE CO	MING FROM THE NR 4 BEARING HOUSING AREA.  THE COTTER PINS HOLDING THE PIN FOR THE EMERGENCY FUEL SHUT-OFF LEVER ON THE N	R 4 BEARING HOUSING HAD FAILED (WORN) ALLOWING THE LEVER PIN, LEVER, AND ACTUATOR ROD TO FALL OUT, WHICH ALLOWED OIL TO 	ESCAPE THROUGH THE ACTUATOR ROD HOLE.  C/W SB7384R3 TO RECTIFY PROBLEM.  SUBMITTER SUGGESTS THIS SB BE C/W AT EARLIEST O	PPORTUNITY.	1	L	7	2 	4F				A22CE   					 
1996111400319	19961114	00319	NM  	1996	11	14	96ZZZX5605       	1	19961001	G	3244	6053P00139	TIRE            	BFGOODRICH  		BOEING	757   	757*        		NM  										MLG	LEAK            	B			UQER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2FOR				Q5124					DUNLOP EQUIPPED BOEING 757 MAIN WHEEL ASSEMBLIES LEAKING.  SUSPECT CAUSE WAS MICHELIN TIRE HAS A SMALL PROCESS CONTROL S	TICKER INSTALLED ON THE INSIDE TIRE WALL TO ENSURE PROPER CURE MOLD.  THIS STICKER HAS DETERIORATED ONCE IN SERVICE AND 	MAY LODGE IN VALVE CORE SEAT WHEN TIRE PRESSURE IS CHECKED CAUSING SLOW LEAKAGE.  TIRE IS MANUFACTURED BY MICHELIN FOR B	FG.			2	L	7	2 	4F			RT	A2NM    					 
1996111400320	19961114	00320	CE  	1996	11	14	96ZZZX5606       	1	19961030	G	2750	58651053	BELLCRANK       			CESSNA	441   	441         	2076020	CE  										LT/RT FLAP IDLER	WORN            	B	P	A	FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	2722Y	3944 				4410173				THE LT AND RT FLAP IDLER BELLCRANKS, BOTH P/N 5865105-3, ARE FOUND TO BE WORKING BETWEEN THE CAST ARM AND THE TUBULAR BE	ARING SUPPORT COLUMN.  THE 4 SECURING RIVETS ALSO APPEAR TO BE LOOSE, BUT NOT SHEARED.  IT IS BELIEVED THAT RIVET FAILUR	E WOULD RESULT IN FLAP BINDING.  THESE WERE FOUND ON A RELATIVELY LOW TIME AIRCRAFT (UNDER 4,000 HRS).  SERVICEABLE BELL	CRANKS ARE INSTALLED.			1	L	7	2 	3T			RT	A28CE   					 
1996111400321	19961114	00321	EA  	1996	11	14	96ZZZX5607       	2	19961023	G	8530		VALVE           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					NR 4 EXH	STRETCHED       	B			FSER	O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			NE	05	6344V	624  				172RG0635	L2881936A			PILOT REPORTED THAT THE ENGINE RAN ROUGH AT FULL POWER.  REMOVED VALVE COVERS AND FOUND NR 4 CYLINDER EXHAUST VALVE HAD 	NO CLEARANCE BETWEEN THE VALVE AND ROCKER ARM.  THE VALVE HEAD WAS STRETCHED.					1	H	7	1 	3O	3	O		3A17    	E286				 
1996111400484	19961114	00484	WP  	1996	11	14	96ZZZX5608       	1	19960930	G	6320	369D251253	SHAFT           			HUGHES	369   	369D        	4470706	WP  										T/R O/P	DAMAGED         	B	S		EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	778  	715  			1151D				DURING OVERHAUL INSPECTION OF M/R TRANS, THE T/R OUTPUT PINION SHAFT WAS FOUND DAMAGED BEYOND LIMITS FROM A BROKEN BEARI	NG RACE GOUGING THE BEARING LAND AND RETAINING RING LIP.					1	G	7	1 	3U				H3WE    					 
1996111400485	19961114	00485	GL  	1996	11	14	96ZZZX5609       	2	19960930	G	7321	23057344	FCU             			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		440  		329147	1151D	CAE832750			FCU CAUSED DELAYED LIGHT-OFF WHEN AT AMBIENT TEMP.  UNITS REPLACED, STARTS NORMAL.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996111400486	19961114	00486	WP  	1996	11	14	96ZZZX5610       	1	19960930	G	6320	369D251141	HOUSING         			HUGHES	369   	369D        	4470706	WP  										M/R XMSN	DAMAGED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	8534 	2433 			1151D				DURING OVERHAUL INSPECTION OF M/R TRANSMISSION, A DEEP GOUGE .137 INCH WAS FOUND IN THE HOUSING COVER IN THE FWD T/R O/P	 PINION BEARING BOX CAUSED BY THE BEARING FAILURE.					1	G	7	1 	3U				H3WE    					 
1996111400487	19961114	00487	GL  	1996	11	14	96ZZZX5611       	2	19960930	G	7323	23057869	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	ERRATIC         	B			EOOR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	5074R		1100 		27963	1151D	CAE832750			PILOT COMPLAINED OF ERRATIC OPERATION AND CONSTANT BEEP ADJUSTMENT.  UNIT IS 344.6 HOURS SINCE REPAIR.  THIS IS ANOTHER 	OF NUMEROUS GOVERNOR PROBLEMS.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996111400488	19961114	00488	WP  	1996	11	14	96ZZZX5612       	1	19961008	G	6320	B3148A	DRAIN VALVE     			HUGHES	369   	369D        	4470706	WP  										M/R XMSN	CRACKED         	B	S	A	EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		2433 			1151D				DURING OVERHAUL, FOUND THE M/R TRANS DRAIN PLUGS CRACKED AT THE FLANGE COMPLETELY AROUND, BUT NOT YET ALL THE WAY THROUG	H THE WALL.  REPLACED PART.					1	G	7	1 	3U				H3WE    					 
1996111400489	19961114	00489		1996	11	14	96ZZZX5613       	4	19961029	G	3451	KI572	CONTROL HEAD    	KING        		SNIAS 	350   	AS350B2     	8680813	EU  										DME	MISWIRED        	B			EOOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	4035W	56   				2912				DME WOULD NOT WORK ON SEVERAL CHANNELS.  THE AIRCRAFT WAS RECENTLY DELIVERED FROM MANUFACTURING AND WAS MISSING JUMPER I	N CONTROL HEAD K1572 BETWEEN PINS 30 AND 47.  THIS APPEARS TO BE A REVISION THAT WAS NOT INCORPORATED BY THE INSTALLER. 	 THE OLD INSTALL MANUAL DOES NOT INDICATE THIS JUMPER.				1	G	7	1 	3U				H9EU    					 
1996111400490	19961114	00490	WP  	1996	11	14	96ZZZX5614       	1	19961001	G	6710	A218100646	TRIM SWITCH     			HUGHES	369   	369E        	4470707	WP  										PILOT CYCLIC	INTERMITTENT    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	503MP	295  				0414E				WHEN TRIM SWITCH WAS RELEASED FROM AFT POSITION, FORWARD TRIM STARTED TO RUN AWAY, SWITCH INTERMITTENT.						1	G	7	1 	3U				H3WE    					 
1996111400491	19961114	00491	WP  	1996	11	14	96ZZZX5615       	1	19960909	G	6220	369H120351	LEAD LAG LINK   		369D21200501	HUGHES	369   	369D        	4470706	WP  										M/R HUB	LOOSE BUSHING   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	911FT	1958 				811036D				DURING REMOVAL OF M/R BLADES, FOUND ONE OF THE LEAD LAG/LINK BUSHINGS LOOSENED FROM LINK. PART REJECTED BY MDHS FIELD SE	RVICE REP.  REPLACED DEFECTIVE LINK ASSY W/SERVICEABLE UNIT.					1	G	7	1 	3U				H3WE    					 
1996111400492	19961114	00492	SW  	1996	11	14	96ZZZX5616       	1	19960925	G	6420	206011811009	YOKE            		206011810015	BELL  	206   	206B        	1181511	SW  										T/R	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	777CP	4559 	1233 		GDLG11652	3429				DURING DAILY CLEANING OF HELICOPTER, PILOT NOTICED WHAT APPEARED TO BE A CRACK IN TH E T/R YOKE.  AFTER REMOVING PAINT A	ND INSPECTING WITH A MAGNIFYING GLASS, A CRACK WAS DEFINITELY VISIBLE.  CRACK STARTED AT CENTER LINE OF OUTBOARD BOLT HO	LE, EXTENDIING TO OUTER END OF YOKE AND STARTING TO TRAVEL TO OTHER SIDE OF YOKE.				1	G	7	1 	3U				H2SW    					 
1996111400493	19961114	00493	WP  	1996	11	14	96ZZZX5617       	1	19961001	G	2424	369A4652H	REGULATOR       		VR214       	HUGHES	369   	OH6A        		WP  										STATIC VOLTS	FAILED          	H				A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			WP	07	446SD				42942	6716286				SHORTLY AFTER TAKEOFF, VOLTAGE REGULATOR FAILURE CONTRIBUTED TO SLIGHT SMOKE EMITTING FROM COMPONENT.  PRECAUTIONARY LAN	DING MADE, W/H CONNECTOR DISCONNECTED FROM VRS.  A/C FLOWN TO HOME BASE, 5-MINUTE FLIGHT, A/C BATTERY UTILIZED.  AT THIS	 TIME VOLTAGE REGULATOR FAILURE UNKNOWN.				1	G	7	1 	3U				H3WE    					 
1996111400494	19961114	00494	NE  	1996	11	14	96ZZZX5618       	1	19961009	G	3213	S61255030411	CYLINDER        			SKRSKY	S61   	S61N        	8142104	NE  										LT MLG LEG	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	05	7011M		4730 			61216				DURING A POST-FLIGHT INSPECTION, HYDRAULIC FLUID WAS NOTICED SEEPING OUT FROM THE LT MAIN OLEO, JUST BELOW THE LOWER ATT	ACHMENT LUG.  A CLOSE VISUAL INSPECTION REVEALED A .50 INCH LONG CRACK IN THE CYLINDER.					2	G	7	2 	4U				1H15    					 
1996111400495	19961114	00495	CE  	1996	11	14	96ZZZX5619       	1	19961015	G	2750	035A961001003	CONTROL CABLE   			MTSBSI	MU2   	MU2B35      	5780411	CE  										FLAP FLEX DRIVE	FAILED          	B			IZ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	6569L	1588 			390	645				DURING ROUTINE 500-HOUR INSPECTION, FLAPS WERE OPERATED TO VERIFY PROPER FUNCTION.  DURING OPERATION, A 'POP' WAS HEARD 	AND THE LEFT OUTBOARD FLAP WAS NO LONGER MOVING.  INSPECTION REVEALED THE FLEX CABLE INNER SHAFT HAD FAILED.  CABLE WAS 	INSTALLED 2-8-88, AD 87-04-03, PERFORMED AT 4,113.0 HRS.  BOTH LEFT AND RIGHT CABLES REPLACED WITH NEW AT THIS TIME.				1	H	7	2 	3T			RT	A10SW   					 
1996111400496	19961114	00496	CE  	1996	11	14	96ZZZX5620       	1	19961025	G	2430	M22759749	WIRE            			BEECH 	100   	B100        	1152919	CE  										START/GEN	CRACKED         	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	1807H	5464 				BE119				THE STARTER/GENERATOR 4 GAUGE WIRES THAT RUN FROM THE FIREWALL POWER CONNECTOR AND GENERATOR GROUND TO THE STARTER/GENER	ATOR WERE FOUND WITH CRACKED INSULATION.  THE CRACKS RUN PARALLEL WITH THE WIRE.  SOME OF THE CRACKS ARE OVER 3 INCHES I	N LENGTH EXPOSING THE CENTER CONDUCTOR.  ON THE LT AND RT ENGINES, THE WIRE NUMBERS OF THE DEFECTIVE WIRES ARE K2D4, K2F	4, P10A4, P10C4, P10E4, K17A4N, K17B4N, AND K17C4N.  THIS IS THE SECOND B100 FOUND LIKE THIS.			1	L	7	2 	4T			 	A14CE   					 
1996111400497	19961114	00497	EU  	1996	11	14	96ZZZX5621       	1	19961017	G	3020		HEATED LIP      			PILATS	PC12  	PC12        	7090550	EU  										COWLING	EXH LEAKS       	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	62JT					107				EXHAUST LEAKS SHOWING AROUND LOWER COWLING HEATED LIP.  REMOVED LIP INNER PANEL.  LEAKING EXHAUST PAST THE RIVETS AND IN	SULATION.  FOIL HEAT SHIELD AND INSULATION BURNED.  SUBMITTER RECOMMENDS 50-HOUR INSPECTION BE MANDATORY.  ACFT TOTAL TI	ME, 827.1 HRS.				1	L	7	1 	3T			RT	A78EU   					 
1996111400498	19961114	00498		1996	11	14	96ZZZX5622       	4	19961031	G	3414	C6610630103	INDICATOR       	AEROSONIC   	202401189   															AIR SPEED	BENT SHAFT      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25										RECENTLY HAVED RECEIVED FROM THE VENDOR, SEVERAL AIRSPEED INDICATORS WITH BENT SHAFTS ON FLT INDEX KNOB ASSY.  SUBMITTER	 SUGGESTS TO PAY CLOSE ATTENTION TO THIS UPON RECEIPT FROM VENDOR BEFORE INSTALLING UNIT.  CREDIT IS NOT GIVEN ONCE INST	ALLED.																	 
1996111400499	19961114	00499		1996	11	14	96ZZZX5623       	4	19961031	G	3414	202401189	INDICATOR       	AEROSONIC   																AIR SPEED	BENT SHAFT      	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25										RECENTLY SUBMITTER HAS RECEIVED FROM THE VENDOR SEVERAL AIRSPEED INDICATORS WITH BENT SHAFTS ON SET INDEX KNOB ASSY.  SU	BMITTER SUGGESTS TO PAY CLOSE ATTENTION TO THIS UPON RECEIPT FROM VENDOR BEFORE INSTALLING UNIT.  CREDIT IS NOT GIVEN ON	CE INSTALLED.																	 
1996111400500	19961114	00500	SO  	1996	11	14	96ZZZX5624       	2	19960829	G	8520	6419441048	THROUGH-BOLT    			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360C    	17025	SO  					NR 2 CYL BASE	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	8CE		198  			P3370144	224343R			INSPECTION FOUND LOWER THROUGH-BOLT IN NR 2 CYLINDER BASE BROKEN.						1	H	7	2 	3O	3	O		A6CE    	E9CE				 
1996112700247	19961127	00247	NE  	1996	11	27	96ZZZX5625       	3	19961015	G	6111		EROSION STRIP   			SAAB  	2000  	2000SAAB    	7860200	EU  						ROTOL	R381	R3816123F5  	NE  	LT PROP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	5124	697  				2000027		DAP0063		DURING A POST-FLIGHT INSPECTION, A LEFT PROP BLADE EROSION STRIP WAS FOUND CRACKED.  THE CRACK WAS APPROXIMATELY 4.1 INC	HES LONG AND PARALLEL TO THE LEADING EDGE.  REPLACED THE PROPELLER PER SAAB 2000 MM AND PERFORMED GROUND CHECKS.					2	L	7	2 	4T			RT	A47NM   		6	C	P6BO	 
1996112700248	19961127	00248	EU  	1996	11	27	96ZZZX5626       	1	19961024	G	5520		ELEVATOR        			GROB  	ASTIR 	G102IIIB    		EU  										EMPENNAGE	FLUTTER         	D				O				OTHER                   				F	E		FLT CONT AFFECTED         	VIBRATION/BUFFET          		CR	CRUISE         	1			WP	11	851BG	1842 				5639CB				ELEVATOR FLUTTER CAUSED MULTIPLE FRACTURES AND DELAMINATIONS IN ELEVATOR SKINS INCLUDING SEPARATION OF INBOARD HINGES ON	 HORIZONTAL STABILIZER.  PILOT REPORTED A VIBRATION AT 120 KTS AND 10,000 FEET IN SMOOTH AIR.  REDLINE AT 10,000 FEET IS	 128 KTS.  POST-INSPECTION OF ELEVATOR BALANCE SUGGESTS THAT SPECIFICATIONS IN MM TO BE INACCURATE AND/OR INADEQUATE.  E	LEVATOR BY DESIGN HAS NO COUNTERWEIGHTS INSTALLED.  OTHER CASES OF FLUTTER ON THIS MODEL GROB HAVE BEEN REPORTED.			1	K	0	0 	0 			0	G33EU   					 
1996112700249	19961127	00249	WP  	1996	11	27	96ZZZX5627       	1	19961008	G	5400	58950815	SPAR            			DOUG  	DC8   	DC8F54      	3021926	WP  										NR 1 PYLON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	57FB					45669				DURING C-CHECK INSPECTION, FOUND NR 1 PYLON UPPER OUTBOARD SPAR CRACKED.  REMOVED AND REPLACED NR 1 PYLON UPPER OTBD SPA	R IAW DOUGLAS DRAWING 5895081.					2	L	7	4 	4F				4A25    					 
1996112700250	19961127	00250	SO  	1996	11	27	96ZZZX5628       	2	19961028	G	8530	653453	VALVE SEAT      								CONT  	O520  	GTSIO520*   	17032	SO  					INT VALVE	MISINSTALLED    	B			VA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19							613067			CYLINDER INTAKE SEAT NOT SEATED INTO MACHINED PORTION OF CYLINDER HEAD ALL THE WAY IN.  UPON INSTALLATION AT FACTORY, NO	T TAPPED IN COMPLETELY OR SEATED TO MACHINED HOLE.  SUBMITTER STATES ALWAYS INSPECT NEW CYLINDERS FOR CORRECT SEATING OF	 VALVE SEAT INTO CYLINDERS.									3	O			E7CE				 
1996112700251	19961127	00251	SO  	1996	11	27	96ZZZX5629       	2	19961028	G	8530	653445	VALVE SEAT      								CONT  	O520  	TSIO520*    	17040	SO  					EXH VALVE	MISINSTALLED    	B			VA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19							519648			CYLINDER EXHAUST SEAT NOT SEATED INTO MACHINED PORTION OF CYLINDER HEAD ALL THE WAY IN.  SUSPECT CAUSE:  UPON INSTALLATI	ON AT FACTORY, SEATS ARE NOT TAPPED IN, BUT DROPPED IN ASSUMING INSTALLED.  SUBMITTER STATED ALWAYS INSPECT NEW CYLINDER	S FOR GOOD SEATING OF SEAT INTO CYLINDER.									3	O			E8CE				 
1996112700252	19961127	00252	SO  	1996	11	27	96ZZZX5630       	1	19961004	G	2710	520235501	AILERON         			GULSTM	AA5   	AA5B        	3960105	SO  										TORQ TUBE LT	RIVETS LOOSE    	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	28519	5307 				AA5B0658				DURING ANNUAL INSPECTION, FOUND BOTH AILERONS TO HAVE CONTROL LOOSENESS INTERNALLY.  REMOVED AILERON ASSYS AND FOUND BOT	H TO HAVE LOOSE RIVETS AT TORQUE TUBE TO AILERON ATTACHMENT.  SUSPECT AIRCRAFT EXPERIENCED HIGH WINDS FROM REAR WHILE PA	RKED.  GUST LOCKS ON AILERONS PROPER, WOULD PREVENT THIS.				1	L	7	1 	3O				A16EA   					 
1996112700253	19961127	00253	SO  	1996	11	27	96ZZZX5631       	1	19961004	G	2710	5202035502	AILERON         			GULSTM	AA5   	AA5B        	3960105	SO  										TORQ TUBE RT	RIVETS LOOSE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	28519	5307 				AA5B0658				DURING ANNUAL INSPECTION, FOUND BOTH AILERONS TO HAVE CONTROL LOOSENESS INTERNALLY.  REMOVED AILERON ASSYS AND FOUND BOT	H TO HAVE LOOSE RIVETS AT TORQUE TUBE TO AILERON ATTACHMENT.  SUSPECT AIRCRAFT EXPERIENCED HIGH WINDS FROM REAR WHILE PA	RKED.  GUST LOCKS ON AILERONS PROPER, WOULD PREVENT THIS.				1	L	7	1 	3O				A16EA   					 
1996112700254	19961127	00254	SO  	1996	11	27	96ZZZX5632       	1	19961004	G	2752	56040091	BRACKET         			GULSTM	AA5   	AA5B        	3960105	SO  										FLAP ACTUATOR	BROKEN          	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	28519	5307 				AA5B0658				FLAP ACTUATOR TRANSMISSION SUPPORT MOUNT AFT ATTACH POINT TAB FOUND BROKEN OFF AND HAD BEEN FOR SOME TIME.  FLAPS HAD EX	CESSIVE UP AND DOWN FREE TRAVEL.  SUSPECT EXPOSURE TO TAIL WINDS ON THE PARKING AREA.					1	L	7	1 	3O				A16EA   					 
1996112700256	19961127	00256	CE  	1996	11	27	96ZZZX5634       	1	19961021	G	2422	KGSSPC38B	INVERTER        			CESSNA	500   	550         	2076604	CE  										NR 1 POS	FAILED          	B	L	A	VXWR	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			EA	21	24E				1737	5500651				INVESTIGATION FOR A DOUBLE INVERTER FAILURE FOUND OPTIC COUPLER IN PHASE LOCK CIRCUIT FALIED.  WITH COUPLER FAILED FREQ 	OUTPUT UNREGULATED, CAUSING PHASE LINK TO DISCONNECT THE OTHER INVERTER.  PHASE LINK NOT PROTECTED BY FAULT MONITOR AND 	CAN FAIL BOTH INVERTERS.  SUBMITTER SUGGESTS REDESIGN FAULT CKT TO PROTECT UNIT FROM DUAL FAILURE.				1	L	7	2 	4F				A22CE   					 
1996112700257	19961127	00257	EA  	1996	11	27	96ZZZX5635       	2	19960914	G	7414	M3548	ROTOR           	SLICK       	4270        	CHILD 	S1    	S1SPITTS    	0110301	NM  	LYC   	O360  	IO360B4A    	41514	EA  					ENGINE MAGNETO	BROKEN          	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			WP	15		205  			90030130					INVESTIGATION FOR ROUGH RUNNING ENGINE FOUND MAGNETO OUT OF TIME DUE TO BROKEN ROTOR.						1	Q	7	1 	3O	3	O		A8SO    	1E10				 
1996112700258	19961127	00258	GL  	1996	11	27	96ZZZX5636       	3	19961107	G	6111	C4503	FORK            													HARTZL	HCC4Y	HCC4YR2     	GL  	PITCH CONT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		1735 			901N			FH516		DURING OVERHAUL OF THE PROPELLER, MAGNETIC PARTICLE INSPECTION REVEALED TWO INDICATIONS RADIATING FROM THE PITCH ROD BOR	E ACROSS THE FORWARD SURFACE OF THE FORK.  THE INDICATIONS WERE LOCATED IN THE FORGED SURFACE AND DID NOT PROTRUDE INTO 	THE PITCH ROD BORE.  THE FORK WAS FORWARDED TO THE MANUFACTURER FOR EVALUATION.														5	C	P52GL	 
1996112700259	19961127	00259	CE  	1996	11	27	96ZZZX5637       	1	19961101	G	7603	16991001723	BRACKET SUPPORT 			BEECH 	23    	B24R        	1151253	CE  										THROTTLE CABLE	FAILED          	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	15	1957L	1501 				MC423				THROTTLE SUPPORT BRACKET THAT BOLTS TO OIL SUMP FAILED AND ALSO GROOVED AT POINT OF CABLE CLAMP ATTACH.  SUBMITTER STATE	S LOOSE BOLT AND INCORRECT PART AS CONTRIBUTING FACTOR.  CORRECT P/N 169-910017-45.					1	L	7	1 	3O				A1CE    					 
1996112700260	19961127	00260	CE  	1996	11	27	96ZZZX5638       	1	19961008	G	3310	05701661	DIMMING ASSY    			CESSNA	172   	172RG       	2072438	CE  										PANEL LIGHT	OVERHEATED      	B			AQHD	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			WP	11	111HP	5583 				172RG1153				SMOKE IN COCKPIT DURING FLIGHT.  OVERHEATED TRANSISTORIZED DIMMING ASSY LIKELY CAUSED BY ADDED ELECTRICAL LOAD DUE TO RE	CENTLY ADDED RADIO EQUIPMENT.  SUBMITTER STATED AN EVALUATION NEEDED OF CURRENT DRAW ON SUBJECT SYSTEM.  THAT DETERMINAT	ION HAS NOT YET BEEN MADE ON THIS AIRCRAFT.  THIS AIRCRAFT DELIVERED NEW IN 1984 WITHOUT RADIO.  THE AVIONICS AND RADIO 	GEAR HAVE BEEN ADDED TO OVER THE YEARS WITHOUT BENEFIT OF ENGINEERING REQUIREMENTS OF SUBJECT CIRCUIT.			1	H	7	1 	3O				3A17    					 
1996112700262	19961127	00262	SO  	1996	11	27	96ZZZX5640       	1	19961001	G	7931	486440	TRANSDUCER      			PIPER 	PA38  	PA38112     	7103812	SO  										ENG OIL PRESS	FAILED          	D				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	99	2489P					3879A1003				OIL PRESSURE TRANSDUCER APPEARS TO HAVE GROUNDED ITSELF INTERNALLY CAUSING AN INDICATION OF NO OIL PRESSURE WHILE IN-FLI	GHT.					1	L	7	1 	3O				A18SO   					 
1996112700263	19961127	00263	CE  	1996	11	27	96ZZZX5641       	1	19961104	G	2750	500000861CR	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										FLAP	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	247CB	7765 				421C0299				UPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED.  ALSO NOTE THAT LOCATION OF DAMAGE A	REAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL.  BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERN	AL VISUAL INSPECTION OF CABLES.				1	L	7	2 	3O			 	A7CE    					 
1996112700264	19961127	00264	CE  	1996	11	27	96ZZZX5642       	1	19961104	G	2750	500000862	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										FLAP	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	247CB	7765 				421C0299				UPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED.  ALSO NOTE THAT LOCATION OF DAMAGE A	REAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL.  BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERN	AL VISUAL INSPECTION OF CABLES.				1	L	7	2 	3O			 	A7CE    					 
1996112700265	19961127	00265	CE  	1996	11	27	96ZZZX5643       	1	19961104	G	2750	500000863CR	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										FLAP	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	247CB	7765 				421C0299				UPON INSPECTION OF FLAP CABLES AFTER REMOVAL, SEVERAL BROKEN WIRES WERE DISCOVERED.  ALSO NOTE THAT LOCATION OF DAMAGE A	REAS WERE UNDETECTABLE WITHOUT CABLE REMOVAL.  BENDING OF CABLES REVEALED SEVERITY OF BROKEN WIRES NOT EVIDENT BY EXTERN	AL VISUAL INSPECTION OF CABLES.				1	L	7	2 	3O			 	A7CE    					 
1996112700266	19961127	00266	CE  	1996	11	27	96ZZZX5644       	1	19961029	G	2750	500000862	CABLE ASSY      			CESSNA	414   	414A        	2075907	CE  										PRESELECT CLAMP	BROKE           	D				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			EA	03	2688D	6775 				414A0332				A SPLIT FLAP CONDITION OCCURRED ON FINAL APPROACH.  FLAP EXTEND CABLE WAS FOUND BROKEN ON INBOARD SIDE OF PRE-SELECT CON	TROL ATTACH CLAMP.  PRE-SELECT CABLE IS NOT RUNNING PARALLEL TO FLAP CABLE.  THIS EXTEND CABLE WAS ALSO FOUND TO HAVE IN	TERNAL WEAR AT PULLEY LOCATIONS.				1	L	7	2 	3O				A7CE    					 
1996112700267	19961127	00267	CE  	1996	11	27	96ZZZX5645       	1	19961029	G	2750	500000863	CABLE ASSY      			CESSNA	414   	414A        	2075907	CE  										FLAP PULLEYS	FRAYED          	D				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			EA	03	2688D	6775 				414A0332				A SPLIT FLAP CONDITION OCCURRED ON FINAL APPROACH.  AFTER CHECKING SYSTEM, ALL CABLES WERE REMOVED FROM AIRCRAFT FOR REP	LACEMENT.  INTERNAL CABLE WEAR WAS FOUND AT ALL PULLEY LOCATIONS.  HIGH CABLE SYSTEM TENSION IS REQUIRED ON THESE CABLES	.  SUBMITTER SUGGESTS LIFE LIMIT.				1	L	7	2 	3O				A7CE    					 
1996112700268	19961127	00268	CE  	1996	11	27	96ZZZX5646       	1	19961029	G	2750	51152242	CONTROL         			CESSNA	414   	414A        	2075907	CE  										FS 166	WORN            	D				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			EA	03	2688D					414A0332				A SPLIT FLAP CONDITION OCCURRED ON FINAL APPROACH.  THE OUTER HOUSING OF THE PRE-SELECT CONTROL IS BADLY WORN WHERE IT M	OUNTS TO BULKHEAD AT STA 166.  FLAP CABLE AND PRE-SELECT ARE NOT RUNNING PARALLEL WITH EACH OTHER.  SUBMITTER STATED A S	TRONGER MOUNTING MIGHT HELP AT BULKHEAD.				1	L	7	2 	3O				A7CE    					 
1996112700269	19961127	00269	SO  	1996	11	27	96ZZZX5647       	1	19961023	G	7922	53E19600	VERNATHERM      			PIPER 	PA31  	PA31350     	7103110	SO  										THERMO BYPASS	CONE WORN       	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	40ST	454  			63888	317405183				DURING VALVE INSPECTION IAW LYCOMING SB 518C, EXCESSIVE WEAR ON THE CONE AREA WAS NOTED WHERE CONE CONTACTS SEAT.  WEAR 	MEASURED FROM .06 INCH TO .1 INCH AROUND CIRCUMFERENCE OF THE CONE.  THE SEAT AREA INSIDE THE ACCESSORY CASE ALSO SHOWED	 EXCESSIVE WEAR AND 'SLOPE' CAUSED BY CONTACT WITH THE CONE.  SUBMITTER SUGGESTS SOME THROUGHT BE GIVEN TO SOME TYPE OF 	NEW SEAT SINCE THIS SEEMS TO BE THE ROOT OF ALL THE VERNATHERM PROBLEMS.			1	L	7	2 	3O				A20SO   					 
1996112700270	19961127	00270		1996	11	27	96ZZZX5648       	4	19961004	G	6113	4393308	BULKHEAD        			PIPER 	PA31  	PA31310     	7103103	SO  										RT PROP	FAILED          	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			EA	07	4081F	85   				318112036				SPINNER BULKHEAD FAILED RIGHT AFTER TAKEOFF DAMAGING THE PROPELLER AND THE FUSELAGE.  THE BULKHEAD SHOWED SIGNS OF STRES	S CRACKS.  THERE WAS NO SIGN OF OVERTORQUEING OR MIS-ALIGNMENT.					1	L	7	1 	3O			RT	A20SO   					 
1996112700271	19961127	00271	SW  	1996	11	27	96ZZZX5649       	1	19961024	G	3233	EA1165	CYLINDER        			GULSTM	680   	680E        	0141604	SW  										RT MLG	FAILED          	B		A	MV1R	O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			EA	17	50	7    			628	680E81862				INTERNAL FAILURE OF RT MLG ACTUATOR CAUSED TOTAL HYDRAULIC FLUID DEPLETION WITH SUBSEQUENT EMERGENCY EXTENSION OF LANDIN	G GEAR WITHOUT INCIDENT.  ACTUATOR WAS RECEIVED NEW.  ASSEMBLY DATE IS 1/90.  INSTALLED 10-9-96.  TSN IS 7.4 AND 3 LANDI	NGS.  OZONE INDUSTRIES, INC.				1	H	7	2 	3O				2A4     					 
1996112700272	19961127	00272	EA  	1996	11	27	96ZZZX5650       	2	19961029	G	8530	LW12416	VALVE           			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 3 CYL EXH	STUCK           	H				K				NONE                    				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			SO	17	52276	5091 	602  			17274476	L1376139A			NR 3 CYLINDER EXHAUST VALVE STUCK, AND BENT PUSH ROD AND PUSH ROD HOUSING.  THIS CAUSED ROUGH ENGINE AND AN OIL LEAK.  C	YLINDER WAS REPLACED WITH OVERHAULED UNIT.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996112700274	19961127	00274	CE  	1996	11	27	96ZZZX5652       	1	19961101	G	3230	582212715	ANGLE           			CESSNA	441   	441         	2076020	CE  										RT UPLOCK HOOK	CRACKED         	B	S		WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	555WA	8283 				4410219				DURING A PHASE INSPECTION, FOUND A CRACK IN THE OUTBOARD END OF THE RT AND LT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE THAT A	TTACHES TO THE FORWARD WING SPAR WEB.  CRACK ORIGINATES AT THE OUTBOARD HILOCK HOLE AND EXTENDS FOR A TOTAL LENGTH OF 1.	25 INCHES.  INSTALLED NEW ANGLES.				1	L	7	2 	3T			RT	A28CE   					 
1996112700275	19961127	00275	CE  	1996	11	27	96ZZZX5653       	1	19961101	G	3230	582212716	ANGLE           			CESSNA	441   	441         	2076020	CE  										LT UPLOCK HOOK	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	555WA	8283 				4410219				DURING A PHASE INSPECTION, FOUND A CRACK IN THE OUTBOARD END OF THE RT AND LT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE THAT A	TTACHES TO THE FORWARD WING SPAR WEB.  CRACK ORIGINATES AT THE OUTBOARD HILOCK HOLE AND EXTENDS FOR A TOTAL LENGTH OF 1.	25 INCHES.  INSTALLED NEW ANGLES.				1	L	7	2 	3T			RT	A28CE   					 
1996112700276	19961127	00276	CE  	1996	11	27	96ZZZX5654       	1	19961101	G	5712	57222061	CANTED RIB      			CESSNA	441   	441         	2076020	CE  										RT WING TOP CAP	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	555WA	8283 				4410219				DURING A PHASE INSPECTION FOUND BOTH RT AND LT WING CANTED RIB TOP CAP CRACKED.  CRACK STARTS AT AFT SIDE OF FWD WING SP	AR AND RUNS AFT PARALLEL TO THE BEND RADIUS.  STOP-DRILLED ENDS OF CRACKS PER CESSNA INSTRUCTIONS.					1	L	7	2 	3T			RT	A28CE   					 
1996112700277	19961127	00277	CE  	1996	11	27	96ZZZX5655       	1	19961101	G	5712	57222062	CANTED RIB      			CESSNA	441   	441         	2076020	CE  										LT WING TOP CAP	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	555WA	8283 				4410219				DURING A PHASE INSPECTION FOUND BOTH RT AND LT WING CANTED RIB TOP CAP CRACKED.  CRACK STARTS AT AFT SIDE OF FWD WING SP	AR AND RUNS AFT PARALLEL TO THE BEND RADIUS.  STOP-DRILLED ENDS OF CRACKS PER CESSNA INSTRUCTIONS.					1	L	7	2 	3T			RT	A28CE   					 
1996112700278	19961127	00278	CE  	1996	11	27	96ZZZX5656       	1	19961023	G	2730	115610010325	TORQUE TUBE     		115610010368	BEECH 	99    	C99         	1154006	CE  										RT ELEV	CASTING CRACKED 	B			EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6656N	5729 				U213				WHILE COMPLYING WITH BEECH MANDATORY SB 2145, RT ELEVATOR TORQUE TUBE OUTBOARD CASTING WAS FOUND CRACKED FROM ONE OF THE	 TAPER PIN HOLES.					1	L	7	2 	3T				A14CE   					 
1996112700281	19961127	00281	SO  	1996	11	27	96ZZZX5659       	2	19961101	G	8550	646253	ADAPTER ASSY    			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  					OIL FILTER	WORN            	B	S		G9NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	758RV		365  			R1723308	288547R			BYPASS PLUG CAME OUT OF HOUSING.  FOUND WORN PLUG AND DAMAGED HOUSING.  PLUG IS STAKED IN IF BYPASS VALVE IS NOT USED. F	OUND METAL IN OIL FILTER AT PREVIOUS OIL CHANGE 10 HRS PRIOR AND AT THIS OIL CHANGE.  SUBMITTER STATED MFG NEEDS BETTER 	WAY TO SECURE PLUG.				1	H	7	1 	3O	3	O		3A17    	E1CE				 
1996112700316	19961127	00316	EU  	1996	11	27	96ZZZX5691       	1	19960616	G	3340	11159851	LAMP            			BOLKMS	105   	BO105S      	5626006	EU  										STROBE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	105NG	15   			G5280	S632				LIGHT INOPERATIVE.  THIS LAMP WAS A NO COST WARRANTY REPLACMENT LAMP AND IT ONLY LASTED 14.8 HRS AFTER INSTALLED.						1	G	7	2 	3U				H3EU    					 
1996112700317	19961127	00317	EU  	1996	11	27	96ZZZX5692       	1	19960913	G	6410	11731747	BLADE           			BOLKMS	117   	BK117A3     	5626015	EU  										T/R	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1140H	536  			1118	7078				SUSPECT BLADE IS CRACKED AT BOLT HOLE.						1	G	7	2 	3U				H13EU   					 
1996112700318	19961127	00318	EU  	1996	11	27	96ZZZX5693       	1	19960913	G	6410	11731747	BLADE           			BOLKMS	117   	BK117A3     	5626015	EU  										T/R	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1140H	536  			1116	7078				REMOVED AS MATCHED SET WITH BLADE S/N 1118, REF MMIR 78798.						1	G	7	2 	3U				H13EU   					 
1996112700319	19961127	00319	EU  	1996	11	27	96ZZZX5694       	1	19960920	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	117M				00212	S7023				ACTUATOR EXCESSIVE LEAKAGE.						1	G	7	2 	3U				H13EU   					 
1996112700320	19961127	00320	EU  	1996	11	27	96ZZZX5695       	1	19960927	G	6520	4639310062	BEVEL GEAR      			BOLKMS	117   	BK117A1     	5626010	EU  										T/R GRBOX	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117M				821	S7023				UNABLE TO GET CORRECT CONTACT PATTERN.  ONLY A SPLIT PATTERN.						1	G	7	2 	3U				H13EU   					 
1996112700321	19961127	00321	EU  	1996	11	27	96ZZZX5696       	1	19960927	G	6520	46393100	BEVEL GEARSHAFT 			BOLKMS	117   	BK117A1     	5626010	EU  										TR GRBOX	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117M				842	S7023				UNABLE TO GET CORRECT CONTACT PATTERN.  ONLY A SPLIT CONTACT PATTERN.						1	G	7	2 	3U				H13EU   					 
1996112700322	19961127	00322		1996	11	27	96ZZZX5697       	4	19961022	G	3160	066040211111	SYMBOL GENERATOR		SG465       	BELL  	230   	230         	1182149	SW  										COCKPIT	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	230JP	94   			1945	23019				SYMBOL GENERATOR CHECK CONFIG MESSAGE COMES ON INTERMITTENTLY.						1	G	7	2 	3U			NC	H9SW    					 
1996112700323	19961127	00323	SW  	1996	11	27	96ZZZX5698       	1	19960805	G	6200	222310503101	BEARING PAD     			BELL  	230   	230         	1182149	SW  										M/R	DEBONDED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	230JP	310  			LK0007	23019				BEARING PAD DEBONDED.						1	G	7	2 	3U			NC	H9SW    					 
1996112700324	19961127	00324	SW  	1996	11	27	96ZZZX5699       	1	19960831	G	2150	2730502	VALVE           			BELL  	230   	230         	1182149	SW  										BLEED	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	230JP	391  			1384	23019				VALVE CAUSING ECU BREAKER TO P0P.						1	G	7	2 	3U			NC	H9SW    					 
1996112700325	19961127	00325	SW  	1996	11	27	96ZZZX5700       	1	19960816	G	3350	214175140101	POWER SUPPLY    			BELL  	230   	230         	1182149	SW  										CABIN EEL	DEFECTIVE       	B			TI1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	05	230JP				1069	23019				EMERGENCY CABIN LIGHTING DIM.						1	G	7	2 	3U			NC	H9SW    					 
1996112700326	19961127	00326		1996	11	27	96ZZZX5701       	4	19961104	G	3452	071015071301	TRANSPONDER     			BELL  	230   	230         	1182149	SW  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	230JP	488  			1388	23019				TRANSPONDER NUMBERS WILL NOT CHANGE.						1	G	7	2 	3U			NC	H9SW    					 
1996112700327	19961127	00327		1996	11	27	96ZZZX5702       	4	19960906	G	2211	117884141	COMPUTER        			BOLKMS	117   	BK117A4     	5626017	EU  										YAW CSAS	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	313LF	6    			018609010	7138				YAW/CSAS OSCILLATES LEFT AND RIGHT ON GROUND.  ONLY LASTED 5.8 HRS SINCE INSTALLED IN A/C.						1	G	7	2 	3U				H13EU   					 
1996112700328	19961127	00328		1996	11	27	96ZZZX5703       	4	19960905	G	2211	117884141	COMPUTER        			BOLKMS	117   	BK117A4     	5626017	EU  										YAW CSAS	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	313LF				018609001	7138				YAW CSAS OSCILLATES LEFT AND RIGHT ON THE GROUND.  DID NOT WORK CORRECTLY UPON INSTALLATION.						1	G	7	2 	3U				H13EU   					 
1996112700329	19961127	00329		1996	11	27	96ZZZX5704       	4	19960905	G	3421	5040017926	GYRO            			BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT ATTITUDE	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG	90   			3428	7083				ATTITUDE GYRO INOPERATIVE.  ONLY 89.9 HRS SINCE INSTALLED IN A/C.						1	G	7	2 	3U				H13EU   					 
1996112700330	19961127	00330	EU  	1996	11	27	96ZZZX5705       	1	19960809	G	3310	1179203103	CONTROL UNIT    			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	170MC	5    			0141	7217				LIGHTS WILL NOT TURN 'ON'.  NO OUTPUT VOLTAGE.  INSTALLED ONLY 4.5 HRS BEFORE FAILURE.  LOOSE PARTS INSIDE UNIT.						1	G	7	2 	3U				H13EU   					 
1996112700331	19961127	00331	EU  	1996	11	27	96ZZZX5706       	1	19960815	G	3310	1179203103	CONTROL UNIT    			BOLKMS	117   	BK117A3     	5626015	EU  										LIGHTS	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	118LL				0106	7097				INOP WORKED LESS THAN TWO MINUTES AFTER INSTALLED.						1	G	7	2 	3U				H13EU   					 
1996112700514	19961127	00514	CE  	1996	11	27	96ZZZX5707       	1	19961030	G	2750	50000063	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										FLAP PULLEY	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	782LC	7193 				421C0486				ALL FLAP SYSTEM CABLES WERE REMOVED AS A PRECAUTIONARY MEASURE FOR A VISUAL INSPECTION.  BOTH FLAP EXTEND CABLES WERE FO	UND TO HAVE A GREAT DEAL OF INTERNAL WEAR AT PULLEY LOCATIONS.  SUBMITTER SUGGESTS LIFE LIMIT ON CABLES.					1	L	7	2 	3O			 	A7CE    					 
1996112700515	19961127	00515	CE  	1996	11	27	96ZZZX5708       	1	19961030	G	2750	50000062	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										FLAP PULLEY	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	782LC	7193 				421C0486				ALL FLAP SYSTEM CABLES WERE REMOVED AS A PRECAUTIONARY MEASURE FOR A VISUAL INSPECTION.  BOTH FLAP EXTEND CABLES WERE FO	UND TO HAVE A GREAT DEAL OF INTERNAL WEAR AT PULLEY LOCATIONS.  SUBMITTER SUGGESTS LIFE LIMIT ON CABLES.					1	L	7	2 	3O			 	A7CE    					 
1996112700516	19961127	00516	SO  	1996	11	27	96ZZZX5709       	1	19961104	G	7810	LW15806	ELBOW           			PIPER 	PA32  	PA32R301T   	7103220	SO  										TURBO INLET	CRACKED         	B			BONR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	8314B	1676 				32R8129021				DURING ROUTINE OIL CHANGE, NOTICED EXHAUST RESIDUE AROUND WASTEGATE ASSEMBLY.  FOUND INLET ELBOW FROM CYLINDERS NR 1, NR	 3, AND NR 5 CRACKED.  THIS PART IS NOT PART OF AD REQUIRING COMPONENT CHANGE.  SUBMITTER RECOMMENDS MAKING REPLACMENT P	ART OF THICKER MATERIAL.				1	L	7	1 	3O				A3SO    					 
1996112700517	19961127	00517		1996	11	27	96ZZZX5710       	4	19961015	G	3425	52D1371120	HSI             	CENTURY     	NSD360      	PIPER 	PA34  	PA34200T    	7103406	SO  										COCKPIT HEADING	FAILED          	B			APCR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	8407C		966  		I1234C	347670137				HEADING FUNCTION OF HSI FAILED JUST PRIOR TO ENTERING IMC.  MOTOR INSIDE INSTRUMENT BURNED OUT.  SUBMITTER STATED OPERAT	OR'S FLEET HAS MANY, MANY FAILURES OF NSD-360 TYPE UNITS.  VIRTUALLY ALL INTERNAL SYSTEM FAIL AT DIFFERENT TIMES.					1	L	7	2 	3O				A7SO    					 
1996112700518	19961127	00518	SO  	1996	11	27	96ZZZX5711       	1	19961015	G	3210	9652200	CENTERING SPRING			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG	SHAFT BROKEN    	B	S		APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8407C					347670167				CENTER SHAFT OF NOSE GEAR CENTERING SPRING FOUND SHEARED AT ROD END FITTING.  VISUAL INSPECTION  INDICATED SHAFT HAD BEE	N CRACKED VERTICALLY ON BOTH SIDES OF CENTER FOR SOME TIME PRIOR TO FINALLY BREAKING.  SUSPECT THIS WAS CAUSED BY UTILIZ	ATION OF A TOWING TUG AND TURNING NOSE GEAR TOO FAR SIDE TO SIDE.  RECOMMEND FREQUENT INSPECTION.				1	L	7	2 	3O				A7SO    					 
1996112700519	19961127	00519	SO  	1996	11	27	96ZZZX5712       	1	19961024	G	3260		BRACKET         			PIPER 	PA34  	PA34200T    	7103406	SO  										RT MLG UP SWITCH	CRACKED         	B			APCR	A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			NM	01	8407C	15400				347670137				RIGHT MAIN GEAR 'UP' LIGHT SWITCH MOUNTING BRACKET CRACKED ALLOWING SWITCH TO FLEX AWAY FROM TRUNNION ON RETRACTION.  TH	IS CAUSED RED 'UNSAFE' LIGHT TO STAY 'ON'.  AIRCRAFT RETURNED TO AIRPORT WITHOUT INCIDENT.  GEAR EXTENDED AND LOCKED NOR	MALLY.				1	L	7	2 	3O				A7SO    					 
1996112700520	19961127	00520	SO  	1996	11	27	96ZZZX5713       	2	19961030	G	7314	6493682	PUMP            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					ENG FUEL	FAILED          	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8407C		443  		K139506BR	347670137	265901R			ENGINE DRIVEN FUEL PUMP DEVELOPED EXCESSIVE OUTPUT.  (HIGH PRESSURE) FOUND FUEL IN DECK REFERENCE LINE, INDICATING INTER	NAL LEAKAGE.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996112700521	19961127	00521	CE  	1996	11	27	96ZZZX5714       	1	19961018	G	5312	07136172	BULKHEAD        			CESSNA	182   	182P        	2075816	CE  										FS 17 RT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	8431Q					18263546				AT FUSELAGE STA 17.00 RT SIDE WHERE BULKHEAD AND SUPPORT CONNECT TOGETHER BENEATH FLOORBOARD, IT WAS FOUND TO BE BADLY C	ORRODED IN AN AREA OF ABOUT 4 INCHES IN DIA AND LIGHTER CORROSION FOR ABOUT A 12 INCH DIAMETER.  SUBMITTER STATED THAT S	OMETHING WAS SPILLED IN THIS AREA.  THE AIRFRAME HAS NO OTHER CORROSION.				1	H	7	1 	3O			NT	TA13    					 
1996112700522	19961127	00522	CE  	1996	11	27	96ZZZX5715       	1	19961018	G	5320	07137875	SUPPORT         			CESSNA	182   	182P        	2075816	CE  										FS 17 RT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	8431Q					18263546				AT FUSELAGE STA 17.00 RT SIDE WHERE BULKHEAD AND SUPPORT CONNECT TOGETHER BENEATH FLOORBOARD, IT WAS FOUND TO BE BADLY C	ORRODED IN AN AREA OF ABOUT 4 INCHES IN DIA AND LIGHTER CORROSION FOR ABOUT A 12 INCH DIAMETER.  SUBMITTER STATED THAT S	OMETHING WAS SPILLED IN THIS AREA.  THE AIRFRAME HAS NO OTHER CORROSION.				1	H	7	1 	3O			NT	TA13    					 
1996112700523	19961127	00523	SW  	1996	11	27	96ZZZX5716       	1	19961002	G	5522	430026001	ELEVATOR        			MOONEY	M20   	M20J        	5870219	SW  										LT ELEV	LOOSE SKIN      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	88EY	925  				243128				BOTH ELEVATORS ON THIS 1989 AIRCRAFT WITH ONLY 925 HRS HAVE LOOSE SKINS.  THE RT ELEVATOR TOP SKIN IS LOOSE AT THE ROW O	F RIVETS ALONG THE SPAR; THE LT ELEVATOR IS THE SAME EXCEPT THE BOTTOM SKIN IS LOOSE.  THE BALANCE WEIGHTS AT THE ELEVAT	OR TIPS CAN BE FLEXED UP AND DOWN AT LEAST AN INCH IN EACH DIRECTION.  SUBMITTER STATES THE ELEVATORS HAVE LOST ALL RIGI	DITY WHICH COULD EASILY CONTRIBUTE TO OR PRECIPITATE A FLUTTER.  NO APPARENT CAUSE CAN BE DETERMINED.			1	L	7	1 	3O				2A3     					 
1996112700524	19961127	00524	SW  	1996	11	27	96ZZZX5717       	1	19961002	G	5522	430026002	ELEVATOR        			MOONEY	M20   	M20J        	5870219	SW  										RT ELEV	LOOSE SKIN      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	88EY	925  				243128				BOTH ELEVATORS ON THIS 1989 AIRCRAFT WITH ONLY 925 HRS HAVE LOOSE SKINS.  THE RT ELEVATOR TOP SKIN IS LOOSE AT THE ROW O	F RIVETS ALONG THE SPAR; THE LT ELEVATOR IS THE SAME EXCEPT THE BOTTOM SKIN IS LOOSE.  THE BALANCE WEIGHTS AT THE ELEVAT	OR TIPS CAN BE FLEXED UP AND DOWN AT LEAST AN INCH IN EACH DIRECTION.  SUBMITTER STATES THE ELEVATORS HAVE LOST ALL RIGI	DITY WHICH COULD EASILY CONTRIBUTE TO OR PRECIPITATE A FLUTTER.  NO APPARENT CAUSE CAN BE DETERMINED.			1	L	7	1 	3O				2A3     					 
1996112700525	19961127	00525	CE  	1996	11	27	96ZZZX5718       	1	19961008	G	5712	95110026603	RIB             			BEECH 	58    	58          	1152740	CE  										WS 45 LT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4494A					TH30				DURING A 100-HOUR INSPECTION, FOUND LT WING STA 45 RIB ASSY HAS 3 CRACKS ALONG UPPER SKIN RIVET ROW ON RIB, 1 PULLED RIV	ET AT FORWARD LOWER CORNER ATTACH TO SPAR.  RIB IS DEFORMED IN THE CENTER AREA AT RIB.  AILERON TRIM CABLES WEARING HOLE	S IN RIB.  SUSPECT CAUSE POSSIBLE HARD LANDING.  SUBMITTER STATED CLOSER INSP OF THESE AREAS.				1	L	7	2 	3O				3A16    					 
1996112700526	19961127	00526	CE  	1996	11	27	96ZZZX5719       	1	19961008	G	5751	451350309	SKIN            			BEECH 	58    	58          	1152740	CE  										LT AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4494A	8311 				TH30				DURING 100-HOUR INSPECTION, FOUND .25 INCH CRACK IN OUTBOARD UPPER TRAILING EDGE OF SKIN OF THE LT AILERON.  SUSPECT CAU	SE DUE TO VIBRATION.  SUBMITTER RECOMMENDATION IS CLOSE INSPECTION OF THE AILERONS.					1	L	7	2 	3O				3A16    					 
1996020900282	19960209	00282	CE  	1996	2	9	96ZZZX572        	1	19960112	G	2933	P50018LMBE	GAUGE           			BEECH 	200   	B200        	1152922	CE  										HYD PRESSURE	STUCK           	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	961LL	222  				BB1139				THIS GAUGE IS PART OF STC-SA4378-WP, HYDRAULIC LANDING GEAR RETRACTION SYSTEM.  GAUGE FOUND STUCK AT 500 P.S.I. DURING A	IRCRAFT INSPECTION.  SUBMITTER RECOMMENDS A BETTER QUALITY GAUGE BE USED IN SYSTEM.					1	L	7	2 	4T				A24CE   					 
1996112700527	19961127	00527	CE  	1996	11	27	96ZZZX5720       	1	19961008	G	5712	95110014167	RIB             			BEECH 	58    	58          	1152740	CE  										LT WS 136.188	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4494A	8311 				TH30				DURING A 100-HOUR INSPECTION, FOUND CRACK IN RIB/FORMER AT LOCATION LT WING STA 136.188.  SUSPECT CAUSE DUE TO VIBRATION	.  REPLACE RIB/FORMER.					1	L	7	2 	3O				3A16    					 
1996112700528	19961127	00528	CE  	1996	11	27	96ZZZX5721       	1	19961105	G	2913	99101372	PUMP            			CESSNA	414   	414A        	2075907	CE  										RT HYD PUMP	SEAL FAILED     	H				O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			WP	13	5614C	386  				414A0203				LT AND RT HYD LOW FLOW LITES CAME ON IN FLIGHT.  LANDING GEAR HAD TO BE EXTENDED USING THE LANDING GEAR EMERGENCY PROCED	URE.  ACFT LANDED WITHOUT INCIDENT.  RIGHT HYD PUMP NOSE SEAL LEAKED HYDRAULIC FLUID OVERBOARD THROUGH THE NOSE CASE DRA	IN.  PUMP REPLACED.  AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3O				A7CE    					 
1996112700529	19961127	00529	SO  	1996	11	27	96ZZZX5722       	2	19961107	G	8530	653426A13	CYLINDER        			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  					EXH GUIDE	EXCESS WEAR     	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99			14   							THIS FACILITY INSTALLED SIX CYL ASSEMBLIES PREASSEMBLED BY TCM ON AN O300A ENGINE (CESSNA 172).  ENGINE WAS OPERATED ON 	80/87 AVIATION FUEL AND AEROSHELL 80 MINERAL OIL.  AFTER 14 HOURS TOTAL TIME IN SERVICE (TWO MONTHS ELAPSED TIME) LOW CO	MPRESSION WAS EXPERIENCED ON THREE CYLINDERS.  FURTHER EXAMINATION REVEALED EXHAUST GUIDES WORN BEYOND LIMITS IN ALL SIX	 CYLINDERS.  .007L TO APPROXIMATELY .014L AT THE COMBUSTION END.			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1996112700530	19961127	00530	GL  	1996	11	27	96ZZZX5723       	3	19961018	G	6111	SCM7154	BLADE           			GULSTM	AA1   	AA1B        	0631206	SO  						MCAULY	1A105	1A105SCM    	GL  	NR 1 BLADE	TIP SEPARATED   	D	S			A				UNSCHED LANDING         				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CR	CRUISE         	1			EA	17	1447R		193  			AA1B0547		G19493		DURING FLIGHT, THE AIRCRAFT BEGAN TO SHAKE VIOLENTLY.  AFTER A PRECAUTIONARY LANDING IT WAS FOUND THAT APPROXIMATELY 4.5	 INCHES OF THE NR 1 BLADE TIP HAD SEPARATED.  A 1.1250 INCH CIRCUMFERENCE BY .0156 INCH DEPTH/NICK WAS LOCATED AT THE PO	INT OF SEPARATION.  PROPAGATION WAS PROBABLY CAUSED BY EITHER EXCESSIVE STRESS DURING OVERHAUL OR FATIGUE.  RECOMMENDATI	ON:  CLOSER EXAMINATION DURING OVERHAUL TO IDENTIFY STRESS RISERS OR FRACTURES.			1	L	7	1 	3O				A11EA   		5	N	P918	 
1996112700531	19961127	00531	SO  	1996	11	27	96ZZZX5724       	1	19961104	G	2720	6342002	BAR ASSY        		6345905     	PIPER 	PA32  	PA32260     	7103206	SO  										RUDDER PEDAL	CRACKED         	D		A		O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SO	19	3927W	4061 	4061 			32874				PILOT REPORTS EXCESSIVE RT RUDDER APPLICATION WITH LITTLE CONTROL.  CLOSE INSPECTION REVEALED RUDDER CONTROL BAR ASSY WA	S CRACKED AT LEFT WELD AREA OF CROSS-OVER BAR.  SUSPECT CAUSE OF FAILURE MAY HAVE BEEN THE RESULT OF OVER TOW-LIMITS DUR	ING GROUND HANDLING OR LACK OF LUBRICATION BETWEEN ROTATING BARS.  SUBMITTER RECOMMENDS PERIODIC LUBRICATION AND INSPECT	ION OF WELD AREAS.			1	L	7	1 	3O				A3SO    					 
1996112700532	19961127	00532	CE  	1996	11	27	96ZZZX5725       	1	19961104	G	2820	040034317	FUEL LINE       			CESSNA	150   	152         	2071835	CE  										LT HAND	LEAKING         	D		A		K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	25	6529B					15283944				FUEL FUMES IN CABIN.  INSPECTION FOUND FUEL LINE CORROSION PIN HOLE IN LT FUEL LINE.  CARPET SATURATED WITH FUEL.  REPLA	CEMENT OF FUEL LINE REQUIRED.  SCHOOL AIRPLANE - ON TIE DOWN OUTSIDE, TRAPPED MOISTURE BEHIND CARPET.					1	H	7	1 	3O			NT	3A19    					 
1996112700533	19961127	00533	GL  	1996	11	27	96ZZZX5726       	3	19961114	G	6114	E3943	HUB             			CESSNA	210   	T210K       	2073447	CE  						MCAULY	3A32C	D3A32C88    	GL  	MOUNT STUD	CRACKED         	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8237M		40   			T21059237		740765		THE PROPELLER HUB WAS FOUND CRACKED AT 5 OF THE 6 MOUNTING STUDS.  THE PROPELLER HAD ACCUMULATED APPROXIMATELY 40 HOURS 	OF OPERATING TIME SINCE THE LAST OVERHAUL PERFORMED ON 1-10-96.  THE CRACKS WERE DISCOVERED BY AN IA WHILE PERFORMING TH	E ANNUAL INSPECTION.  THE TOTAL TIME OF THE PROPELLER HUB WAS NOT DETERMINED DUE TO INCOMPLETE RECORDS.				1	H	7	1 	3O				3A21    		5	C	P21EA	 
1996112700534	19961127	00534	SO  	1996	11	27	96ZZZX5727       	1	19961014	G	2430	6661602	TERMINAL STRAP  			PIPER 	PA34  	PA34200T    	7103406	SO  										BATTERY	BURNED          	B	S		APCR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	8407C					347670137				BRAIDED-WIRE-TYPE BATTERY TERMINAL STRAP BECAME LOOSE AT NEGATIVE TERMINAL CAUSING HIGH RESISTANCE, HEAT, AND ARCING, AN	D TOTAL ELECTRICAL SYSTEM FAILURE (INTERMITTENT).  SUBMITTER STATED CONCERNS:  POSSIBLE EXPLOSION DUE TO BATTERY GASSES.	  RECURRING PROBLEMS WITH BRAIDED BATTERY TERMINAL STRAP - NUT TORQUE CAUSES DEFORMATION - SHOULD BE CHANGED TO SOLID-TY	PE WIRING.  SAME FAILURE OCCURRED ON PA31-350 AIRCRAFT.			1	L	7	2 	3O				A7SO    					 
1996112700535	19961127	00535	EA  	1996	11	27	96ZZZX5728       	2	19961025	G	7414	10382585	CONTACT POINTS  	ELECTROSYS  	LW685124    	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					MAG	FAILED          	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CE	05	1163Z	2361 			3012013	241285	L1412151A			ENGINE QUIT DURING ROUTINE FLIGHT.  REMOVED MAGNETO AFTER FORCED LANDING.  FOUND CONTACT POINTS PITTED AN CAM FOLLOWERS 	WORN OUT TO THE POINT THAT THEY WOULD NO LONGER OPEN THE CONTACTS.  SUBMITTER STATED MAGNETOS SHOULD BE INSPECTED ON 500	-HOUR INTERVALS AND POINTS SHOULD BE REPLACED ON CONDITION DURING THESE INSPECTIONS.  THE POINTS IN THIS MAG HAD A T.I.S	. OF 2361.0 HRS.			1	L	7	1 	3O	3	O		2A3     	1E10				 
1996112700536	19961127	00536	SW  	1996	11	27	96ZZZX5729       	1	19961009	G	6420	212011702001	YOKE            			BELL  	412   	412         	1182202	SW  										T/R	REQ REPLACEMENT 	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		3187 			A100062					COMPLY WITH ASB412-96-89 INSPECTION OF T/R YOKE.  YOKE REPLACED.						1	G	7	2 	4U				H4SW    					 
1996020900283	19960209	00283	CE  	1996	2	9	96ZZZX573        	1	19960117	G	3010	45AS66010005	HORN TIP        			BEECH 	MU300 	400BEECH    		CE  										LT ELEV HEAT	ELEMENT FAILED  	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3038V	572  			9583237	RK93				LEFT HEATED HORN ON ELEVATOR FAILED.  INSTALLED NEW HEATED TIP.  KIT NR 128-4015-5 PREVIOUSLY INSTALLED.  (HORIZONTAL ST	ABILIZER LEADING EDGE KIT).					2	H	7	2 	4F			RT	A16SW   					 
1996112700537	19961127	00537	NM  	1996	11	27	96ZZZX5730       	1	19961029	G	2720	596005003	HYD SOLENOID    		65C370529   	BOEING	737   	7372A6      	138448B	NM  										RUDDER PCU	CONTAMINATED    	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2181A					RUDDER PCU INVESTIGATION, FLUID FOUND IN SOLENOID COIL CAUSING FAILURE.						2	L	7	2 	4F				A16WE   					 
1996112700538	19961127	00538	NM  	1996	11	27	96ZZZX5731       	1	19961028	G	2710	3170286	FWD MANIFOLD    	BENDIX      	31701203    	BOEING	747   	747*        		NM  										FILTER PORT	CRACKED         	B		A	IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					7950898					AS DETERMINED BY NDI, AILERON PCU MANIFOLD IS CRACKED IN FILTER PORT ADJACENT CHECK VALVE AND INLET PORTS.  SUBMITTER ST	ATES THIS IS A CONTINUING DEFECT WITH THIS PART.					2	L	7	4 	4F			RT	A20WE   					 
1996112700539	19961127	00539	NM  	1996	11	27	96ZZZX5732       	1	19961028	G	2710	3170317	AFT MANIFOLD    	BENDIX      	31701203    	BOEING	747   	747*        		NM  										FILTER PORT	CRACKED         	B		A	IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					7950898					AS DETERMINED BY NDI, AILERON PCU MANIFOLD IS CRACKED IN FILTER PORT ADJACENT CHECK VALVE AND INLET PORTS.  SUBMITTER ST	ATED THIS IS A CONTINUING DEFECT WITH THIS PART.					2	L	7	4 	4F			RT	A20WE   					 
1996112700540	19961127	00540	NE  	1996	11	27	96ZZZX5733       	2	19961011	G	7250	775404	BLADE           								PWA   	JT8   	JT8D217A    	52053	NE  					TURBINE T4	FAILED          	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	05							708485			ENGINE WAS REMOVED FROM SERVICE DUE TO LOST POWER, LOW SPEED AND TURBINE DAMAGE.  THE ENGINE WAS DISASSEMBLED TO DETERMI	NE CAUSE OF THE TURBINE DAMAGE.  ONE T4 BLADE HAD FRACTURED IN HIGH CYCLE FATIGUE CAUSING MASSIVE TURBINE DAMAGE.  THE F	AILURE IS STILL UNDER INVESTIGATION AT GREENWICH, TX.									4	F			E9NE				 
1996112700541	19961127	00541	SO  	1996	11	27	96ZZZX5734       	1	19961021	G	7120	553344	BOLT            		74888002    	PIPER 	PA42  	PA42        	7104202	SO  										LT ENG LT MT	FRACTURED       	B	L	A	GW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	29TF	5338 				425501003				DURING ROUTINE INSPECTION THE LEFT ENGINE, LEFT OUTBOARD UPPER ENGINE MOUNT TO FIREWALL RETENTION BOLT, P/N 553-344 WAS 	FOUND FRACTURED.  PART TOTAL TIME WAS 5338.1 HRS.  LIFE LIMIT FOR THE PART PER PIPER MTC. MANUAL (P/N 761.523 CHAPTER 5 	IS 7,500 HRS.  IT WAS DECIDED TO REPLACE ALL ENGINE MOUNT TO FIREWALL BOLTS (P/N 553-344) AT THIS TIME.)				1	L	7	2 	4T				A23SO   					 
1996112700542	19961127	00542	EU  	1996	11	27	96ZZZX5735       	1	19961106	G	3320	61213	BALLAST         		BAC106075213	HWKSLY	DH125 	DH125400A   	4230140	EU  										CABIN LIGHTS	FAILED          	D		A		K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	05	45NQ	11522			3501	NA749				DURING PRE-FLIGHT INSPECTION, CABIN FILLED WITH SMOKE.  BALLAST CASE WAS CRACKED AND MATERIAL RUNNING OUT.  SUBMITTER SU	GGESTS DISABLING THE INTERIOR LIGHTING SYSTEM.  NOTE: REF AD 95-22-01.					2	L	7	2 	4J				A3EU    					 
1996112700544	19961127	00544	EU  	1996	11	27	96ZZZX5737       	1	19960901	G	3213	350A41108601	CROSS TUBE      			SNIAS 	350   	AS350B1     	8680811	EU  										LANDING GEAR	CORRODED        	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31	2FOR	1948 				2233				SEVERE CORROSIONS FOUND UNDER THE CHAFING STRIPS OF THE LANDING GEAR CROSS TUBES.						1	G	7	1 	3U				H9EU    					 
1996112700545	19961127	00545	EU  	1996	11	27	96ZZZX5738       	1	19960901	G	3213	350A41108700	CROSS TUBE      			SNIAS 	350   	AS350B1     	8680811	EU  										LANDING GEAR	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31	2FOR	1948 				2233				SEVERE CORROSIONS FOUND UNDER THE CHAFING STRIPS OF THE LANDING GEAR CROSS TUBES.						1	G	7	1 	3U				H9EU    					 
1996112700546	19961127	00546	NE  	1996	11	27	96ZZZX5739       	2	19961017	G	7320	5225742	VALVE           	WOODWARD    	8061531     						GE    	CFM56 	CFM565A     	13802	NE  					HMU	MISMANUFACTURED 	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03		1119 								WOODWARD HMU WAS RECENTLY RETURNED FROM SINGAPORE AIRLINES DUE TO A REPORTED COMPLAINT OF 'HP FUEL VALVE DID NOT OPEN DU	RING ENG START'.  THE SUBSEQUENT INVESTIGATION REVEALED THAT THE FUNCTIONAL OBSERVATION WAS THE RESULT OF AN IMPROPERLY 	MACHINED PART.  P/N 5225-742 FEATURES A THRUST BEARING DIAMETER WHICH EXTENDS TO AN ADJACENT SHOULDER (RELIEF GROOVE). T	HE SHOULDER POSITIONS THE BEARING AND WITHSTANDS THE OPERATING THRUST LOADS.  IN THE CASE OF THE IMPROPERLY MACHINED PAR	T, THE BEARING DIAMETER WAS THE PROPER SIZE BUT DID NOT FULLY EXTEND INTO A GRINDING RELIEF GROOVE.							4	F			E29NE				 
1996112700547	19961127	00547	EU  	1996	11	27	96ZZZX5740       	1	19961004	G	3411		PITOT TYS       			AIRBUS	300   	A300B4203   	3930306	EU  										CAPT AIRSPEED	OBSTRUCTED      	D				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			SW	99	225KW					093				ABORTED TAKEOFF DUE NO AIRSPEED IND ON CAPT AND F/O AIRSPEED IND.  BLEW OUT DEBRIS (BUG DEBRIS) FROM CAPTS AND F/O'S PIT	OT LINES AND TUBES.  FUNCTIONAL CHECK OF AIRSPEED INDICATORS OK.  LEAK CHECK OK.					2	L	7	2 	4F				A35EU   					 
1996112700548	19961127	00548	CE  	1996	11	27	96ZZZX5741       	1	19961105	G	2121	BWT141100121B	SILENCER        			BEECH 	60    	60          	1153602	CE  										BLEED AIR	RUPTURED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	211FX	315  				076				WHILE PERFORMING FINAL ENGINE RUNS AND AIRFRAME SYSTEMS CHECK OUT FOLLOWING INITIAL 300/600 HOUR INSPECTIONS, BOTH ENGIN	E BLEED AIR SOURCES WERE TURNED ON TO CHECK AIR DISTRIBUTION SYSTEM.  CABIN AND COCKPIT WERE SHOWERED WITH FIBERGLASS FR	OM AIR DUCTS.  FOUND LT BLEED DUCT AIR SILENCER, LT SIDE OF AFT CABIN BAGGAGE COMPARTMENT, HAD RUPTURED.  CLEANED AIRCRA	FT AND DUCTS.  INSTALLED NEW SILENCER.  OPS CHECKS NORMAL.  RECOMMENDATION:  NEED TO ADD VISUAL INSPECTION OF THESE DUCT	S TO 300 OR 600 HOUR INSPECTION GUIDE.		1	L	7	2 	3O				A12CE   					 
1996112700549	19961127	00549	CE  	1996	11	27	96ZZZX5742       	1	19961023	G	5313		STRINGER        			BEECH 	200   	200BEECH    	1152920	CE  										AFT FUSELAGE	CRACKED         	B		A	BDTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	607KW	5918 				BB977				AD 93-25-07.  SB 2472RII.  VISUAL INSPECTION C/W 8-28-96 AT 5845.3 HOURS.  AT TIME OF 5918.1 AND 10-22-96, THE NR 9 AND 	NR 10 STRINGERS WERE FOUND CRACKED UNDER THE SEALER (RIGHT SIDE).  SUBMITTER STATED NOTIFIED BEECH TECH REP ABOUT THIS P	ROBLEM AND DO BELIEVE THAT THE AD AND SB MUST BE CHANGED TO REFLECT THE CRACKS BEING CONCEALED UNDER THE SEALER.  NEITHE	R AD OR SB ARE REQUESTING THAT THE SEALER BE REMOVED FOR THE USUAL INSPECTION.			1	L	7	2 	4T				A24CE   					 
1996112700551	19961127	00551	EA  	1996	11	27	96ZZZX5744       	2	19961122	G	8530		PISTON P IN     			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  					ENG CYL	FAILED          	B		A	KM5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	55425	215  				347350213	L70461A			PISTON PIN BROKE IN 2 PIECES CAUSING A CATASTROPHIC ENGINE FAILURE.  OCTOBER 8, 1996, LYCOMING ISSUED A MANDATORY SB NR 	527B PERTAINING TO THIS SUBJECT.  THE PISTON PIN THAT FAILED HAD THE SAME CODE MARKED ON IT (17328) THAT THE SERVICE BUL	LETIN STATED MUST BE REPLACED.  SUBMITTER RECOMMENDS SB 527B BE REPLACED WITH AN AD.  MAINTENANCE RECORD REPORT NR 96-01	1-8520.			1	L	7	2 	3O	3	O		A7SO    	1E10				 
1996112700552	19961127	00552	SO  	1996	11	27	96ZZZX5745       	1	19961112	G	2740	481640	PULLEY          			PIPER 	PA32  	PA32300     	7103212	SO  										STABILATOR TRIM	WORN            	B	S	A	AJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	4272R	3509 				3240647				AT THE ANNUAL INSPECTION WHILE CHECKING AND LUBING TRIM CABLE PULLEY FOR STABILATOR, FOUND RIGHT PULLEY WORN IN HALF.  B	EARING CHECKED GOOD.  CABLE CHECKED GOOD.  PART TOTAL TIME 3509 HRS.					1	L	7	1 	3O				A3SO    					 
1996112700553	19961127	00553	SO  	1996	11	27	96ZZZX5746       	1	19961111	G	3411	5631903	GAUGE           			PIPER 	PA31T 	PA31T       	7103124	SO  										PNEU PRESS	CRACKED         	B	S		DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	47CA	3195 				31T7920043				PILOT REPORTED THAT THE PRESSURIZATION WOULD NOT REACH 5.5 DIFFERENTIAL PRESSURE, BUT THE CABIN ALTITUDE WAS CORRECT FOR	 THE AIRCRAFT ALTITUDE.  FOUND THE INSTRUMENT PRESSURE GAUGE CRACKED BEHIND THE BEZEL.  THIS IS CONNECTED INTO THE ALTIM	ATIC STATIC SYSTEM AND IS INSIDE THE CABIN PRESSURE VESSEL AND WAS LEAKING CABIN AIR INTO THE SYSTEM.				1	L	7	2 	3T				A8EA    					 
1996120500001	19961205	00001	EU  	1996	12	5	96ZZZX5747       	1	19960812	G	3310	1179203103	CONTROL UNIT    			BOLKMS	117   	BK117A3     	5626015	EU  										LIGHTS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	118LL	5    			0858	7097				INTERNAL ELECTRICAL DAMAGE.  POPS CIRCUIT BREAKER.  INSTALLED ONLY 4.9 HRS BEFORE FAILURE.						1	G	7	2 	3U				H13EU   					 
1996120500002	19961205	00002	EU  	1996	12	5	96ZZZX5748       	1	19960816	G	2150	JBS141161	COMPRESSOR      			BOLKMS	BK117 	BK117C1     	5626025	EU  										CABIN	SEIZED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				0151304100	7505				COMPRESSOR WILL NOT TURN - LOCKED UP - CLUTCH.						1	G	7	2 	3U			NC	H13EU   					 
1996120500003	19961205	00003	EU  	1996	12	5	96ZZZX5749       	1	19960708	G	6520	4639310006	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	SCORED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1318 			2224	7505				BEARING ROLLERS ARE SCORED.						1	G	7	2 	3U			NC	H13EU   					 
1996120500004	19961205	00004	EU  	1996	12	5	96ZZZX5750       	1	19960817	G	6520	4639310005	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	DAMAGED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				1452	7505				DAMAGE TO OUTER RACE FROM METAL CONTAMINATION.						1	G	7	2 	3U			NC	H13EU   					 
1996120500005	19961205	00005	EU  	1996	12	5	96ZZZX5751       	1	19960708	G	6520	4639306006	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	SCORED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1318 			1729	7505				BEARING ROLLERS ARE SCORED.						1	G	7	2 	3U			NC	H13EU   					 
1996120500006	19961205	00006	EU  	1996	12	5	96ZZZX5752       	1	19960708	G	6520	4639311005	SHAFT           			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R OUTPUT	DAMAGED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1318 			350	7505				HEAVY SCRAPE MARK ON I.D. OF SHAFT GOES THROUGH SILVER PLATING INTO THE BARE METAL AND THIS IS REASON FOR REJECTION IAW 	CORRECT REM 3095 MANUAL.					1	G	7	2 	3U			NC	H13EU   					 
1996120500007	19961205	00007	EU  	1996	12	5	96ZZZX5753       	1	19960802	G	5412	1176625502	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				FIREWALL CRACKED.						1	G	7	2 	3U			NC	H13EU   					 
1996120500008	19961205	00008	EU  	1996	12	5	96ZZZX5754       	1	19960802	G	5412	1176625501	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				FIREWALL CRACKED.						1	G	7	2 	3U			NC	H13EU   					 
1996120500009	19961205	00009	EU  	1996	12	5	96ZZZX5755       	1	19961007	G	6720	117317171	BELLCRANK       			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	BEARING WORN    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				T/R BELLCRANK BEARINGS WORN.						1	G	7	2 	3U			NC	H13EU   					 
1996120500010	19961205	00010	EU  	1996	12	5	96ZZZX5756       	1	19960614	G	6320	4639305011	SPACER TUBE     			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R GRBOX	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1355 				7505				SPACER TUBE WORN BEYOND LIMITS.						1	G	7	2 	3U			NC	H13EU   					 
1996120500011	19961205	00011	EU  	1996	12	5	96ZZZX5757       	1	19960614	G	6210	10514101111	BLADE BOLT      			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				BLADE BOLT WORN BEYOND LIMITS.  SCRAPED PARTS ON SITE.  REPLACED 2 EA.						1	G	7	2 	3U			NC	H13EU   					 
1996120500012	19961205	00012	EU  	1996	12	5	96ZZZX5758       	1	19960614	G	6220	1051418206	RING            			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R	GROOVED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1355 				7505				GROOVED RING.  REPLACED 4 EA.						1	G	7	2 	3U			NC	H13EU   					 
1996120500013	19961205	00013	EU  	1996	12	5	96ZZZX5759       	1	19960810	G	6730	7012693901	SERVO           			BOLKMS	BK117 	BK117C1     	5626025	EU  										SERVO SYS	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				90100154	7505				SERVO MOTOR CAUSES ERROR CODES.						1	G	7	2 	3U			NC	H13EU   					 
1996120500014	19961205	00014	EU  	1996	12	5	96ZZZX5760       	1	19961007	G	6720	11731822	PITCH LINK      			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R CONT	BEARING PLAY    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				PLAY IN BEARINGS, 2 EA PITCH LINK ASSY.						1	G	7	2 	3U			NC	H13EU   					 
1996120500015	19961205	00015	EU  	1996	12	5	96ZZZX5761       	1	19961010	G	6320	1179586901	WIRE            			BOLKMS	BK117 	BK117C1     	5626025	EU  										NR 1 TRANS	SHORTED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1637 				7505				NR 1 TRANS PRESSURE PLUG SHORTING OUT CAUSING FLUCTUATION IN GAUGE.						1	G	7	2 	3U			NC	H13EU   					 
1996120500016	19961205	00016	EU  	1996	12	5	96ZZZX5762       	1	19960825	G	7714	1179405303	TRIPLE TACH     			BOLKMS	117   	BK117A3     	5626015	EU  										NR 2 ENG	NEEDLE STICKS   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4493X	390  			170	S7038				NR 2 ENGINE NEEDLE STICKS - SUBMITTER STATES UNIT WAS REPAIRED FOR SAME DISCREPANCY LAST REPAIR.						1	G	7	2 	3U				H13EU   					 
1996120500017	19961205	00017		1996	12	5	96ZZZX5763       	4	19960813	G	3421	40205773	GYRO            			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4493X	375  			80031622	S7038				RMI AND HSI CARDS WANDER.						1	G	7	2 	3U				H13EU   					 
1996121800001	19961218	00001	EU  	1996	12	18	96ZZZX5764       	1	19960901	G	7714	32005008	TACH GENERATOR  			BOLKMS	105   	BO105S      	5626006	EU  										ENG	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	495LF	2    			164718	S645				TACH GEN DRIVE SHAFT DISENGAGED FROM INTERNAL DRIVE PIN.						1	G	7	2 	3U				H3EU    					 
1996120500018	19961205	00018	SW  	1996	12	5	96ZZZX5765       	1	19961011	G	7810	206064300005	EXHAUST         			BELL  	206   	206L1       	1182107	SW  										FLANGE WELD	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	721SP					45486				EXHAUST CRACKED AT FLANGE ALONG WELD.						1	G	7	1 	3U				H2SW    					 
1996120500019	19961205	00019	CE  	1996	12	5	96ZZZX5766       	1	19960817	G	2422	PC17A	INVERTER        			BEECH 	200   	B200        	1152922	CE  										AC SYS	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	75LV	86   			7407A	BB1075				INVERTER INOP.  NO AC OUTPUT.						1	L	7	2 	4T				A24CE   					 
1996120500020	19961205	00020		1996	12	5	96ZZZX5767       	4	19960819	G	3421	222375033101	INDICATOR       			BELL  	222   	222         	1182122	SW  										COCKPIT ATTITUDE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW	1    			0143	47520				INDICATOR WILL NOT DROP 'OFF' FLAG.  PRECESSES AFTER 4-5 MINUTES.						1	G	7	2 	3U				H9SW    					 
1996120500021	19961205	00021		1996	12	5	96ZZZX5768       	4	19960817	G	3421	222375033101	INDICATOR       			BELL  	222   	222         	1182122	SW  										COCKPIT ATTITUD	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW	3    			0188	47520				PRECESSES 8 TO 10 DEGREES NOSE DOWN IN 3 TO 4 MINUTES.  DOES NOT FULLY RECOVER FROM NOSE DOWN ATTITUDE.						1	G	7	2 	3U				H9SW    					 
1996120500022	19961205	00022	SW  	1996	12	5	96ZZZX5769       	1	19960823	G	7331	912042T38D	METER           			BELL  	222   	222         	1182122	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					FUEL FLOW	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW	78   			1252	47520				FUEL FLOW METER WILL NOT COMPLETE SELF-TEST.  FAILED AFTER ONLY 77.8 HRS INSTALLED.						1	G	7	2 	3U	3	U		H9SW    	E5NE				 
1996020900287	19960209	00287	SO  	1996	2	9	96ZZZX577        	2	19960110	G	8530	646101CN	CYLINDER        			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					CYLINDERS 1-6	COATING FAILED  	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	707SP		49   			421B0411	267057R			INSPECTION FOUND CERMINIL CYLINDER PROCESS HAS FAILED.  PARTICLES COMING LOOSE IN SMALL PIECES.  CONTAMINATION IS PASSIN	G THROUGH ENTIRE OIL SYSTEM.  BEARINGS ARE DAMAGED BEYOND FURTHER USE.  CAMSHAFT AND LIFTERS ARE DAMAGED.  SUBMITTER STA	TED ALL ACCESSORIES THROUGH WHICH OIL HAS PASSED MUST BE INSPECTED AND/OR REPAIRED.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996120500023	19961205	00023		1996	12	5	96ZZZX5770       	4	19960922	G	2312	40001452500	TRANSCEIVER     			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				294	7098				INOP WHEN INSTALLED IN A/C - WILL NOT TRANSMIT.						1	G	7	2 	3U				H13EU   					 
1996120500024	19961205	00024	EU  	1996	12	5	96ZZZX5771       	1	19960720	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105LSA3   	5626020	EU  										MAST MOMENT	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV	172  			1881	2033				SYSTEM OPERATES INTERMITTENTLY.  UNIT LASTED LESS THAN 4 MO. IN OPERATION.						1	G	7	2 	3U				H3AU    					 
1996120500025	19961205	00025	EU  	1996	12	5	96ZZZX5772       	1	19960720	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105LSA3   	5626020	EU  										MAST MOMENT	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV	172  			1881	2033				SYSTEM OPERATES INTERMITTENTLY.  UNIT LASTED LESS THAN 4 MO. IN OPERATION.						1	G	7	2 	3U				H3AU    					 
1996020900288	19960209	00288	SO  	1996	2	9	96ZZZX578        	1	19960104	G	3213	75215004	HOUSING         			PIPER 	PA42  	PA421000    	7104225	SO  										LT MLG STRUT	FAILED          	B		A	AU3R	O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			WP	15	42MD	2284 				425527015				AIRCRAFT WAS MODIFIED WITH LONG RANGE FUEL TANKS FOR FLIGHT TO AUKLAND, NEW ZEALAND FROM OAKLAND, CALIFORNIA.  AIRCRAFT 	WAS APPROVED FOR OVERWEIGHT TAKEOFF.  DURING TAKEOFF ROLL, LEFT MLG COLLAPSED CAUSING EXTENSIVE DAMAGE TO AIRCRAFT.  MLG	 HOUSING WAS INSPECTED APPROXIMATELY 10 HOURS EARLIER IAW PIPER SB 929A.  METALLURGICAL EXAM REVEALED FAILURE OF HOUSING	 BEGAN AT THE AREA ADDRESSED BY SB 929A.  SUBMITTER RECOMMENDS EITHER INCREASING THE INSPECTION INTERVAL OF SB 929A, OR 	REPLACING HOUSINGS WITH NEW IMPROVED STYLE, DASH 006 HOUSING OR MORE THOROUGH INSPECTION PROCESS.		1	L	7	2 	4T			RT	A23SO   					 
1996020900289	19960209	00289	SO  	1996	2	9	96ZZZX579        	1	19960104	G	3230	40336000	LINK            			PIPER 	PA42  	PA42        	7104202	SO  										NLG RT DRAG LINK	CRACKED         	B		A	AU3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	700VF	3763 				428001053				DURING A SCHEDULED INSPECTION, THE RIGHT NLG DRAG LINK WAS FOUND CRACKED ON THE FORWARD SIDE OF THE INBOARD LUG THAT THE	 NLG ACTUATOR ATTACHES TO.  SUBMITTER RECOMMENDS SCHEDULED INSPECTIONS OF THIS AREA.  THIS IS THE SECOND OCCURRENCE.					1	L	7	2 	4T				A23SO   					 
1996020900290	19960209	00290	SO  	1996	2	9	96ZZZX580        	1	19960122	G	3222	9572300	TRUNNION        			PIPER 	PA34  	PA34200     	7103405	SO  										NLG	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	16LL	5633 				347250050				DURING ANNUAL INSPECTION, THE NLG TRUNNION WAS FOUND CRACKED .25 INCH AT THE RIGHT STAY ARM WELD JOINT.						1	L	7	2 	3O				A7SO    					 
1996120500134	19961205	00134	NE  	1996	12	5	96ZZZX5800       	2	19960729	G	7250	414129001	PT ROTOR        			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENG	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	311LF	1890 			SC12211	7070	LE45121			C/W SB 0153 R1.  PT ROTOR REPLACED.						1	G	7	2 	3U	3	U		H13EU   	E5NE				 
1996120500318	19961205	00318		1996	12	5	96ZZZX5801       	1	19961016	G	2822	2B6540	PUMP            	AIRBORNE    																FUEL SYS	FAILURE         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	13					7B166					FUEL PUMP ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE PUMP.																			 
1996120500319	19961205	00319	EU  	1996	12	5	96ZZZX5802       	1	19961105	G	7160	115C6602	AIR BOX         			GROB  	G115  	G115C       	1660303	EU  										INDUCTION AIR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	115AK	72   				82054C2				DURING ACCEPTANCE INSPECTION ON NEW GROB AIRCRAFT WITH 72.2 HOURS SINCE NEW, FOUND INDUCTION AIR BOX CRACKED IN NUMEROUS	 LOCATIONS.  LT AND RT FWD SIDES CRACKED, TOP L SIDE DOUBLER FWD OF CARBURETOR ADAPTOR CRACKED.  CRACKS ARE ATTRIBUTED T	O PROPELLER/ENGINE VIBRATION.  BOTH ENGINE AND PROPELLER HAVE 72.2 HOURS SINCE NEW.  DYNAMIC BALANCE TO BE ACCOMPLISHED 	TO REMEDY CRACKING.			1	L	7	1 	3O			NT	A57EU   					 
1996120500320	19961205	00320	SO  	1996	12	5	96ZZZX5803       	2	19961018	G	8550	538937	TUBE            			BEECH 	35    	K35         	1151524	CE  	CONT  	O470  	IO470C      	17026	SO  					OIL SUMP	BROKEN          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	192AA	4306 				D5964	716589C			DISASSEMBLING ENG FOR OVERHAUL FOUND THE OIL SUCTION TUBE WAS BROKEN IN 2 PLACES.  TUBE WAS BROKE OFF FROM SCREEN AND ON	E OF THE ATTACHING ANGLES WAS BROKEN BY BOLT HOLE. TT ENG 4306.44.  SMOH 1448.84.					1	L	7	1 	3O	3	O		3A15    	E273				 
1996120500321	19961205	00321	CE  	1996	12	5	96ZZZX5804       	1	19961030	G	2750	58651053	BELLCRANK       			CESSNA	441   	441         	2076020	CE  										LT-RT FLAP IDLER	LOOSE           	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	2722Y	3944 				4410173				THE LEFT AND RIGHT FLAP IDLER BELLCRANKS, BOTH P/N 5865105-3, ARE FOUND TO BE WORKING BETWEEN THE CAST ARM AND THE TUBUL	AR BEARING SUPPORT COLUMN.  THE 4 SECURING RIVETS ALSO APPEAR TO BE LOOSE BUT NOT SHEARED.  SUBMITTED STATED IT IS BELIE	VED THAT RIVET FAILURE WOULD RESULT IN FLAP BINDING.  THESE WERE FOUND ON A RELATIVELY LOW TIME AIRCRAFT (UNDER 4000 HRS	).  SERVICEABLE BELLCRANKS WERE INSTALLED.			1	L	7	2 	3T			RT	A28CE   					 
1996120500322	19961205	00322	SO  	1996	12	5	96ZZZX5805       	1	19961028	G	3260	1CH214	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	DEFECTIVE       	D				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	23	35871					313052123				RIGHT MAIN GEAR FAILED TO SHOW GEAR DOWN AND LOCKED UPON LANDING.  RETRACTION TEST ON GROUND FOUND SWITCH PIPER PN 487-8	62 DEFECTIVE.  REMOVED AND REPLACED WITH NEW PART.  SYSTEM CHKS NORMAL.					1	L	7	2 	3O				A20SO   					 
1996120500323	19961205	00323	SO  	1996	12	5	96ZZZX5806       	2	19961106	G	8530	630046	PISTON PIN      			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					NR 4 CYL	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	37VM	1779 				468508002	273577R			REMOVED NR 4 CYLINDER FOR MAINTENANCE.  FOUND PISTON PIN INTERNAL PIN BROKEN.  INSTALLED NEW P/N 630046 PIN ASSY WITH EX	CHANGE CYLINDER ASSY.					1	L	7	1 	3O	3	O		A25SO   	E8CE				 
1996120500324	19961205	00324	EA  	1996	12	5	96ZZZX5807       	2	19961024	G	7310	60100030092	HOSE            			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  					ENG FUEL	LEAKING         	B			BXSR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	09	34933					17702099				PILOT REPORTED A FUEL LEAK FROM THE ENGINE COMPARTMENT.  FOUND THE FUEL PRESSURE HOSE LEAKING.  THIS PROBLEM HAS BEEN AD	DRESSED BY AEROQUIP SB AA135.  THIS HOSE WAS DATED 2Q86.  ALTERNATE P/N FROM CESSNA:  S1236-3-0092.					1	H	7	1 	3O	3	O		A13CE   	E286				 
1996120500325	19961205	00325	EA  	1996	12	5	96ZZZX5808       	2	19961004	G	7414	M3215	CARBON BRUSH    	SLICK       	6393        	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENG MAG	EXCESS WORN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	415CC	336  			91110003	273908	RL1063248			OWNER REPORTED EXCESSVIE MAG DROP INTERMITTENTLY RIGHT ENG LEFT MAG. NOTICED EXCESSIVE CARBON DUST AROUND MAG VENT.  PUL	LED MAG AND OPENED UP EVERYTHING COATED WITH CARBON DUST.  SUBMITTER STATED BRUSH WORN TOO QUICKLY.  MANUFACTURE BRUSH F	ROM HARDER SUBSTANCE.				1	L	7	2 	3O	3	O		1A10    	1E4				 
1996120500326	19961205	00326	SO  	1996	12	5	96ZZZX5809       	2	19961106	G	7310	646425	LINE            			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					NR 5 CYL INJ	BROKE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4323D	3475 	1884 			468408018	528375			NR 5 CYLINDER FUEL INJECTOR LINE BROKE.  SUBMITTER RECOMMENDS DIFFERENT TYPE CLAMPING SYSTEM BE USED ON THESE FUEL INJEC	TION LINES.  CURRENT SYSTEM ALLOWS FOR ALOT OF VIBRATION.					1	L	7	1 	3O	3	O		A25SO   	E8CE				 
1996020900291	19960209	00291	CE  	1996	2	9	96ZZZX581        	1	19960104	G	3233	3A0540201	BARREL          		3A0500002   	CESSNA	185   	185         	2072802	CE  										LT MLG ACTUATOR	CRACKED         	B			OG5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21	185ND	2030 				18504369				HYDRAULIC FLUID WAS OBSERVED DRIPPING FROM LEFT GEAR WELL DURING 100-HOUR ANNUAL INSPECTION.  OPERATIONAL CHECK OF GEAR 	FOUND MAIN GEAR ACTUATOR BARREL CRACKED.  BARREL PART NUMBER IS 3A05402-01.  CRACK LOCATED AT MIDDLE AREA AND EXTENDS LE	NGTHWISE APPROXIMATELY 1 INCH.  THERE DOES NOT APPEAR TO BE ANY MARKS IN THIS AREA TO CAUSE CRACK.				1	H	7	1 	3O			NC	3A24    					 
1996120500327	19961205	00327	SO  	1996	12	5	96ZZZX5810       	1	19961104	G	2913	HYC5005	POWER PACK      			PIPER 	PA34  	PA34200T    	7103406	SO  										MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	47611		268  		1803	347770418				LANDING GEAR POWER RACK WOULD NOT PUT GEAR IN EXTENDED POSITION - UPON DISASSEMBLY - COMMUTATOR ARMATURE SEEMED TO BE 'O	UT OF ROUND DUE TO THE BRUSH MARKS.  THE BRUSHES WERE NOT WORN EXCESSIVE.					1	L	7	2 	3O				A7SO    					 
1996120500328	19961205	00328	EA  	1996	12	5	96ZZZX5811       	2	19961101	G	7322	105135	CARBURETOR      	FACET       		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2D     	41508	EA  					GASKET	MISOVERHAULED   	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	5AU		289  		CK35802	287725339				CARBURETOR RUNNING OVER RICH.  AFTER DISASSEMBLY, FOUND STICKY MATERIAL (PROBABLY FUEL LUBE TM) ON PARTING SURFACE GASKE	T COVERING ENTIRE GASKET.  THIS CARB HAS HAD OTHER WORK DONE SINCE GASKET WAS INSTALLED.  SUBMITTER STATED MECHANIC ERRO	R?				1	L	7	1 	3O	3	O		2A13    	E274				 
1996120500329	19961205	00329	SW  	1996	12	5	96ZZZX5812       	1	19961017	G	3233	EA1165	ACTUATOR        	OZONE       	631         	GULSTM	680   	680E        	0141604	SW  										RT MLG	FAILED          	H				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			EA	17	50	9    				680E81862				INTERNAL FAILURE OF RT MLG ACTUATOR CAUSED TOTAL HYDRAULIC FLUID DEPLETION WITH SUBSEQUENT EMERGENCY EXTENSION OF LANDIN	G GEAR WITHOUT INCIDENT.  ACTUATOR WAS RECEIVED NEW.  ASSEMBLY DATE IS 1/90 AND WAS INSTALLED 6/96.  TSN IS 8.6 HRS AND 	6 LANDINGS.				1	H	7	2 	3O				2A4     					 
1996120500330	19961205	00330	GL  	1996	12	5	96ZZZX5813       	3	19961111	G	6111	7666A	BLADE           			PIPER 	PA28  	PA28R180    	7102809	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	SHANK	CRACKED         	B			QV9R	O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	13	7527J	1994 				28R30898		CH11993		PROPELLER EXPERIENCED VIBRATION DURING FLIGHT.  PROPELLER REMOVED FOR INSPECTION FOR CAUSE OF VIBRATION.  FOUND BLADE SH	ANK FAILURE AS DESCRIBED IN AD 77-12-06.					1	L	7	1 	3O				2A13    		5	C	P920	 
1996120500331	19961205	00331	SW  	1996	12	5	96ZZZX5814       	1	19961106	G	3243	35202	PISTON          	PARKERHANFIN	305         	MOONEY	M20   	M20B        	5870206	SW  										LT MLG BRAKE	STUCK           	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	09	74796					1796				DURING LANDING, THE LEFT BRAKE LOCKED AT FIRST APPLICATION.  THE LEFT TIRE SKIDDED AND THE AIRCRAFT LEFT THE RUNWAY.  LA	TER, THE BRAKE RELEASED AND THE AIRCRAFT WAS TAXIED TO MAINT.  A MECH DETERMINED THAT HYD FLUID SEEPAGE HAD CONGEALED AR	OUND THE PISTON, PREVENTING ITS RETRACTION.				1	L	7	1 	3O				2A3     					 
1996120500332	19961205	00332	SO  	1996	12	5	96ZZZX5815       	1	19961112	G	7603	3092902	CONTROL CABLE   			PIPER 	PA25  	PA25235     	7102504	SO  										THROTTLE	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	77852					253989				WHILE RUNNING UP ENGINE AFTER ANNUAL, THROTTLE CABLE BROKE INSIDE THE HOUSING BECAUSE OF EXCESSIVE WEAR.  BECAUSE OF THE	 INCIDENT, INSPECTED 2ND ACFT AND FOUND CABLE WORN THROUGH IN THE SAME SPOT, CABLE IS NEARLY IMPOSSIBLE TO INSPECT.  SUB	MITTER RECOMMENDS THROTTLE CABLES BE REPLACED ON AIRCRAFT WITH 300 HRS OR MORE.				1	L	7	1 	3O			 	2A10    					 
1996120500333	19961205	00333	CE  	1996	12	5	96ZZZX5816       	1	19961111	G	3213	508100324	TORQUE KNEE     			BEECH 	90    	E90         	1152914	CE  										RT MLG UPPER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	87CH	10078				LW20				AFTER AN INCIDENT CAUSED BY AN UPPER TORQUE KNEE FAILURE, OTHER AIRCRAFT IN THE FLEET ARE BEING INSPECTED.  DURING THIS 	INSPECTION THE UPPER TORQUE KNEE ON THE RIGHT GEAR WAS VISUALLY FOUND TO BE CRACKED.  A NEW UNIT WAS INSTALLED.  BOTH TH	E NEW UNIT AND THE OLD UNIT ARE OF THE SAME P/N BUT THE NEW UNIT IS DIFFERENT THAN THE OLD.				1	L	7	2 	3T				3A20    					 
1996120500334	19961205	00334	EA  	1996	12	5	96ZZZX5817       	2	19961104	G	7314	LW15473	PUMP            			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENG FUEL	SEAL FAILED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	80426	1670 				328306028	L2213948A			TROUBLESHOOTING REASON  FOR SPORADIC/INTERMITTENT FUEL FLOW INDICATIONS.  FOUND FLOW WAS LOW AND WAS CHANGING - FOUND ME	CHANICAL FUEL PUMP SEAL FAILED ALLOWING ENGINE OIL TO FILL MOST BOTTOM CHAMBER OF PUMP BELOW LOWEST DIAPHRAGM.  SUSPECT 	THAT THIS WAS NOT ALLOWING DIAPHRAGM FULL MOVEMENT AND THUS RESTRICTING FUEL FLOW.				1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996120500335	19961205	00335	SO  	1996	12	5	96ZZZX5818       	1	19961101	G	2140	A08D49	BLOWER MOTOR    			PIPER 	PA34  	PA34200T    	7103406	SO  										COMBUSTION AIR	FAILED          	D				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			GL	21	812JA	440  			1025931	347970422				COMBUSTION AIR BLOWER MOTOR QUIT DURING FLIGHT.  BRUSHES WERE OK.  REPLACMENT WAS ACCOMPLISHED.  HEATER OPERATION NORMAL	.					1	L	7	2 	3O				A7SO    					 
1996120500336	19961205	00336	SO  	1996	12	5	96ZZZX5819       	2	19961105	G	8530	630046	PISTON PIN      			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					NR 4 CYL	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	9133G	808  				4608111	528427			REMOVED NR 4 CYLINDER FOR MAINTENANCE FOUND PISTON PIN INTERNAL PIN BROKEN.  INSTALLED NEW P/N 630046 PIN ASSY WITH EXCH	ANGE CYLINDER ASSY.					1	L	7	1 	3O	3	O		A25SO   	E8CE				 
1996020900292	19960209	00292	SO  	1996	2	9	96ZZZX582        	1	19960120	G	2820		HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  										WING FUEL BAY	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	4347T	3134 				287125510				INSPECTION FOUND ALL HOSES EXCEPT BRAKE AND OIL COOLER HOSES WERE ORIGINAL EQUIPMENT PARTS AT LEAST 25 YEARS OLD.  WITH 	3,134 HOURS TT, THE HOSES WERE ALL IN A STATE OF DETERIORATION.  THE WING BAY FUEL HOSES AT TANKS WERE CORRODED AT SOCKE	TS.  SERVICE MANUAL CHECK LIST RECOMMENDS HOSE REPLACEMENT AT 1,000 HOURS OR 5 YEARS CALENDAR LIFE.				1	L	7	1 	3O				2A13    					 
1996120500337	19961205	00337	CE  	1996	12	5	96ZZZX5820       	1	19961105	G	2910	26070144	LINE ASSY       			LEAR  	35    	35A         	5170602	CE  										HYD	WORN            	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	425AS	8394 				281				UPON INSPECTION DISCOVERED LINE CHAFED UNDER ADEL CLAMP.  REMOVAL DISCLOSED RUBBER FROM CLAMP PARTIALLY MISSING AND LINE	 WORN 50 PERCENT OF WALL THICKNESS.  RUBBER ON OUTSIDE OF CLAMP STILL IN PLACE MAKING IT HARD TO NOTICE.					2	L	7	2 	4F				A10CE   					 
1996120500338	19961205	00338	CE  	1996	12	5	96ZZZX5821       	1	19961104	G	5102		SUSPENSION CABLE			HEAD  	AX888 	AX888HEAD   	05637T7	CE  										ENVELOPE	DEFECTIVE       	B	S		RG1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	8307M	104  				218				THE SERVING AROUND THE KEVLAR SUSPENSION CABLE WHICH FORMS THE EYE AT THE BASE OF THE CABLE HAS COME APART.  THE MANUFAC	TURER HAS REFUSED TO SUPPLY INFORMATION ON THE REPAIR OF THIS ITEM.  THIS ITEM IS NOT MENTIONED IN THE MAINTENANCE MANUA	L.				1	B	0	0 					A29SO2  					 
1996120500339	19961205	00339	CE  	1996	12	5	96ZZZX5822       	1	19961107	G	3230	504501019	TORQUE TUBE     			CESSNA	340   	340CESSNA   	2076404	CE  										MLG	CORRODED        	B	L	A	DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	100HJ	2659 				3400334				DURING ANNUAL INSPECTION AND INSTALLATION OF KIT SK 414-8E FOUND MLG TORQUE TUBE HAD INTERNAL RUST/CORROSION WITH WALL P	ITTING IN EXCESS OF 10 PERCENT.					1	L	7	2 	3O				3A25    					 
1996120500340	19961205	00340	GL  	1996	12	5	96ZZZX5823       	2	19961023	G	7210	A6887772	BEARING         								ALLSN 	250C  	250C20B     	03013	GL  					PTO GEARSHAFT	MAKING METAL    	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17					033		832429			ENGINE WAS REPORTEDLY MAKING METAL.  FOUND THE CAUSE TO BE THE PTO GEARSHAFT FORWARD BEARING WHICH HAD A SEVERELY SPALLE	D INNER RACE. THE BEARING IS AN FAA-PMA PART, MANUFACTURED BY SUPERIOR.										3	U			E4CE				 
1996120500341	19961205	00341	GL  	1996	12	5	96ZZZX5824       	2	19961104	G	7230	6898607	BEARING         								ALLSN 	250C  	250C30P     	03013	GL  					COMPRESSOR	FAILED          	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17							CAE895060			ENGINE WAS RECEIVED FOR METAL GENERATION.  FOUND THE NR 1 BEARING HAD FAILED (SPALLING ON BALLS AND RACES; SEPARATOR IN 	PIECES).										3	U			E1GL				 
1996120500342	19961205	00342	NM  	1996	12	5	96ZZZX5825       	1	19961025	G	2711	65255467	PULLEY          		65742841    	BOEING	727   	727227      	1384078	NM  										LT INBD AIL	BEARING FAILED  	B		A	YN4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	76753					21249				DURING MID-D CHECK INSPECTION, LT INBD AIL TAB CONTROL CABLE TURNAROUND PULLEY WAS FOUND TO HAVE A RUSTED AND FAILED BEA	RING.  SUSPECT CAUSES ARE WATER INTRUSTION OR INSUFFICIENT LUBRICATION DURING BEARING MANUFACTURE.  SUBMITTER STATED SPE	CIAL ATTENTION SHOULD BE GIVEN TO THIS PULLEY BEARING DURING INSPECTION TO DETECT EARLY SIGNS OF RUSTING OR WEAR.  REF I	PC 27-10-0-24.			2	L	7	3 	4F				A3WE    					 
1996120500343	19961205	00343	NM  	1996	12	5	96ZZZX5826       	1	19961025	G	2711	65255467	PULLEY          		65742842    	BOEING	727   	727227      	1384078	NM  										RT INB AIL	BEARING FAILED  	B		A	YN4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	76753					21249				DURING MID-D CHECK INSPECTION, RT INBD AILERON TAB CONTROL CABLE TURNAROUND PULLEY WAS FOUND TO HAVE A RUSTED AND FROZEN	 BEARING.  SUSPECT CAUSES ARE WATER INTRUSION OR INSUFFICIENT LUBRICATION DURING MANUFACTURE.  SUBMITTER STATED SPECIAL 	ATTENTION SHOULD BE GIVEN TO THIS PULLEY BEARING DURING INSPECTION TO DETECT EARLY SIGNS OF RUSTING OR WEAR.  REF IPC 27	-10-0-24.  AC TT 50080.  AC CYC 32554.			2	L	7	3 	4F				A3WE    					 
1996120500344	19961205	00344	NM  	1996	12	5	96ZZZX5827       	1	19961025	G	2711	65742842	BRACKET ASSY    			BOEING	727   	727227      	1384078	NM  										RT INBD AIL	WORN BOLT HOLE  	B		A	VN4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	76753					21249				DURING MID-D CHECK INSPECTION, RT INBD AILERON TAB CONTROL CABLE TURNAROUND PULLEY MOUNTING BRACKET WAS FOUND WITH ELONG	ATED PULLEY MOUNT BOLT HOLES.  CAUSE WAS A RUSTED AND FROZEN BEARING IN P/N 65-25546-7 PULLEY.  SPECIAL ATTENTION SHOULD	 BE GIVEN TO THE PULLEY TO DETECT EARLY SIGNS OF RUST AND FAILURE OF THE BEARING.  REF IPC 27-10-0-24.  AC TT 50080.  AC	 CYC 32554.			2	L	7	3 	4F				A3WE    					 
1996120500345	19961205	00345	GL  	1996	12	5	96ZZZX5828       	2	19960925	G	7200		ENGINE          			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					M50 BEARING	MAKING METAL    	B			MUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	525FS					5250026	1022			ROUTINE OIL ANALYSIS REVEALED SMALL SHINY PLATELETS OF M-50 BEARING MATERIAL.  ENGINE MANUFACTURER ADVISES ENGINE IS TO 	BE REMOVED FOR TEAR DOWN EVALUATION.					1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
1996120500346	19961205	00346	WP  	1996	12	5	96ZZZX5829       	1	19961030	G	5312		TEE CAP         			DOUG  	DC8   	DC861       	3021952	WP  										AFT PRESS LKHD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	30UA					45888				DURING INSPECTION OF AFT PRESSURE BULKHEAD AT STA Y=1766 IAW PSI 53.08.009/010C AND NDI 53-10-18, FOUND TWO CRACKS AT CO	RNER RADIUS OF THE TEE CAP AT LONGERON 10 RT AND LONGERON 10 LEFT.  REPAIRED CRACKS BY INSTALLING A REPAIR ANGLE IAW SRM	 53-2-5, PAGES 15 AND 16.				2	L	7	4 	4F				4A25    					 
1996020900293	19960209	00293	SO  	1996	2	9	96ZZZX583        	2	19960110	G	8530	530658	BUSHING         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NR 6 CYL PIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	707SP		49   			421B0411	267057R			UPON REMOVAL OF NR 6 CYLINDER, THE CONNECTING ROD PISTON PIN BUSHING WAS FOUND CRACKED.						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996120500347	19961205	00347	CE  	1996	12	5	96ZZZX5830       	1	19961108	G	2130	261950010	VALVE           			LEAR  	35    	36A         	5170603	CE  										EMERG PRESS	LOOSE CONNECTOR 	E				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	71CK					O35				EMERGENCY PRESSURIZATION KICKED ON AT 14,500.  TIGHTENED AND RE-SAFTIED CONNECTOR ON RT EMERGENCY BLEED VALVE.  GROUND A	ND TEST FLIGHT CHECK NORMAL.					2	L	7	2 	4F				A10CE   					 
1996120500348	19961205	00348	NE  	1996	12	5	96ZZZX5831       	3	19961105	G	6111	RFC11T10C	BLADE PIN       	HAMSTD      	8022581     	SAAB  	SF340 	340B        	7860101	EU  						HAMSTD	14RF	14RF19      	NE  	SHANK	CRACKED         	B		A	H2SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13		11238	5788 		864231					BLADE WAS RECEIVED FOR MAJOR INSPECTION. DURING DYE PENETRANT CHECK OF THE SHANK, TWO INDICATIONS APPEARED, ONE WAS APPR	OXIMATELY 180 DEGREES FROM THE BLADE PIN AND THE OTHER WAS APPROXIMATELY 120 DEGREES FROM THE PIN.  EACH INDICATION HAD 	THE FOLLOWING CHARACTERISTICS:  TWO PARALLEL LINES, ONE IN THE RACE FILLET RADIUS, AND ONE ON THE SHANK BUTT O.D., EACH 	END OF THE INDICATIONS WERE CONNECTED BY LINES RUNNING FROM THE FILLET RADIUS OVER THE 90 DEGREE TRANSITION, AND INTO TH	E SHANK BUTT O.D.		2	L	7	2 	4T			RT	A52EU   		6	C	P11NE	 
1996120500351	19961205	00351		1996	12	5	96ZZZX5834       	4	19961031	G	2562	SHARC7	ELT             	LEIGH       																G SWITCH	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05										IN C/W FAR 91-207 AT ANNUAL INSPECTIONS, 9 ELT'S HAVE FAILED THIS PAST YEAR DUE TO G-SWITCH FAILURE TO OPERATE WHEN TEST	ED.  ALL HAVE BEEN LEIGH SHARC 7 ELTS.  RECOMMEND CLOSE ATTENTION BE GIVEN TO TESTING OF G-SWITCH TO MAKE SURE THEY WILL	 ACTIVATE WHEN PROPERLY TESTED.																	 
1996120500352	19961205	00352		1996	12	5	96ZZZX5835       	4	19961106	G	2350	M64151	MIC JACKS       			CESSNA	172   	172N        	2072434	CE  										HEADPHONE MIC	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	1558E					17271046				THE HEADPHONE AND MICROPHONE JACKS HAVE BEEN 'VIBRATING LOOSE'. CIRCUIT BREAKERS OF THE SAME ATTACHMENT NUT SIZE POSSESS	 A THIN WALLED LOCK WASHER WHICH PREVENT THIS LOOSENING TREND.					1	H	7	1 	3O			NT	3A12    					 
1996120500353	19961205	00353	CE  	1996	12	5	96ZZZX5836       	1	19961106	G	2120	1570401	PLENUM ASSY     			CESSNA	172   	172N        	2072434	CE  										RADIO COOLING	JAMMED YOKE     	D	S	A		K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			EA	21	1558E	3133 				17271046				DURING PRE-FLIGHT 'CONTROL FREEDOM CHECK', THE FLIGHT CONTROLS BECAME JAMMED IN THE NOSE DOWN POSITION!  THE RADIO RACK 	COOLING PLENUM HAD FALLEN INTO THE YOKE PATH.  UPON FURTHER INVESTIGATION, ONLY ONE OF THE FOUR RETAINING CLAMPS/SPRINGS	 WAS FOUND AND IT WAS NOT ATTACHED PROPERLY.  SUBMITTER STATED INSPECTION AND ADHERANCE TO CESSNA'S AVIONICS INSTALLATIO	N MANUAL IS RECOMMENDED.			1	H	7	1 	3O			NT	3A12    					 
1996120500354	19961205	00354	SO  	1996	12	5	96ZZZX5837       	1	19961030	G	3710	842CW	PUMP            	AIRBORNE    		PIPER 	PA31  	PA31P       	7103120	SO  										VAC SYS	SHAFT SHEARED   	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	110SK	370  			04AK000053	31P7630006				PUMP WAS INSTALLED ON FRESH O/H ENG 9-15-95, PUMP NEW FROM AIRBORNE, FAILED AT 369.6 HRS 10-30-96.  SEIZED AND SHEARED S	HAFT.  FAILURE RATE ON THESE PUMPS FROM SUBMITTERS EXPERIENCE IS QUITE HIGH.  ABOUT 50 PERCENT FAIL JUST PAST THIS WARRA	NTY TIME OF 1 YR OR 400 HRS.				1	L	7	2 	3O				A8EA    					 
1996120500355	19961205	00355	EA  	1996	12	5	96ZZZX5838       	2	19961111	G	8520	78290	PLUNGER ASSY    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 1 CYL EXH	LIFTER BROKEN   	B			P3NR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	13	27236	1097 				317752111	L249268A			PILOT NOTICED OIL COMING FROM COWLING.  INVESTIGATION REVEALED NR 1 CYLINDER EXHAUST VALVE TRAIN FAILURE, PUSH ROD BENT,	 AND HYDRAULIC LIFTER BROKEN.  CAUSE UNKNOWN.  EXHAUST VALVE TO GUIDE CLEARANCE OKAY.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996120500356	19961205	00356	GL  	1996	12	5	96ZZZX5839       	2	19961113	G	7210	6705924	OIL PLUG        		6854702     	CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					COMP DRV ASSY	DETACHED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	49		866  			479	501422			AS PART OF TROUBLESHOOTING FOR AN ENGINE OIL QUANTITY PROBLEM, OIL PLUG, WAS FOUND MISSING FROM THE ENGINE DRIVEN COMPRE	SSOR DRIVE ASSEMBLY.  ALLISON P/N 6854702.  OIL PLUG WAS RETRIEVED FROM THE REDUCTION GEARBOX LOW POINT DRAIN.  OIL PLUG	 IS PRESS-FIT INTO DRIVE ASSEMBLY SHAFT AT MANUFACTURE, AND SEPARATED FROM SHAFT FOR UNKOWN REASONS.  REDUCTION GEARBOX 	SPLIT, INSPECTED, REPAIRED AND RETURNED TO SERVICE.  ENGINE TSO 865.8.			2	L	7	2 	4R	4	T		6A6     	E282				 
1996020900294	19960209	00294	SO  	1996	2	9	96ZZZX584        	2	19960119	G	8530		CYLINDER ASSY   			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					NR 5 EXH ROCKER	BOSS BROKE      	C			HNXG	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	91130		875  			18261955	451117			FOUND NR 5 CYLINDER ROCKER ARM BOSSES BROKEN OFF ON EXHAUST VALVE.						1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1996120500357	19961205	00357	CE  	1996	12	5	96ZZZX5840       	1	19961104	G	2721	043213822	CHAIN ASSY      		12606732    	CESSNA	206   	U206G       	2073356	CE  										RUDDER TRIM	LOCK MISSING    	D				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	756HQ	3947 				420604107				PILOT REPORTED RUDDER TRIM INOPERATIVE, BUT WOULD TURN WHEEL.  MASTER LINK LOCK MISSING, INSTALLED NEW MASTER LINK ASSY.	  (ADJUSTED CHAIN TENSION).					1	H	7	1 	3O				A4CE    					 
1996120500640	19961205	00640	EU  	1996	12	5	96ZZZX5842       	1	19960824	G	7714	1179405303	TRIPLE TACH     			BOLKMS	117   	BK117A3     	5626015	EU  										ENG N2	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ	24   			282	7098				INTERMITTENT N2 - NR 2 DROP OF 2 PERCENT AT 100 PERCENT.						1	G	7	2 	3U				H13EU   					 
1996020900297	19960209	00297	SO  	1996	2	9	96ZZZX587        	2	19960116	G	8520		CRANKSHAFT      			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	BROKE           	G				A				UNSCHED LANDING         				J	R		WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SW	99	70076	2643 	950  			20700547	286336R			PERFORMED EMERGENCY LANDING ON FROZEN LAKE.  DURING THE LANDING ROLL, THE RIGHT WING TIP STRUCK A SPRUCE TREE.  THE AIRC	RAFT RECEIVED DAMAGE TO THE RIGHT WING AND AILERON.  THE ENGINE WAS REPLACED WITH THE AIRCRAFT ON THE FROZEN LAKE.  THE 	EMERGENCY LANDING WAS FORCED DUE TO LOSS OF OIL PRESSURE AND ENGINE RPM AT THE SAME TIME.  THIS WAS THE RESULT OF THE CR	ANKSHAFT BEING BROKEN IN TWO.  NOTE:  VAR CRANKSHAFT INSTALLED IN THIS IO-520 ENGINE.			1	H	7	1 	3O	3	O		A16CE   	E5CE				 
1996121200069	19961212	00069	GL  	1996	12	12	96ZZZX5874       	2	19961017	G	7250	68777362	STATOR SEAL     								ALLSN 	250B  	250B17      	03012	GL  					GAS PROD AFT	CRACKED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17							CAE870101			DURING PARTIAL DISASSEMBLY OF TURBINE TO REPLACE THE FIRST STAGE NOZZLE, FOUND CRACKS IN BEARING BORE AREA OF SEAL.  UPO	N REMOVAL OF SEAL, NOTICED FRETTING ON OUTER DIAMETER.  SUSPECT IMPROPER FIT OF SEAL IN SUPPORT.										3	T			E10CE				 
1996121200070	19961212	00070	EA  	1996	12	12	96ZZZX5875       	2	19961113	G	8540	75288	DRIVE ASSY      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ASSORY CASE	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	19956					17260886	L3181427A			WHILE C/W AD 960910C, IT WAS DISCOVERED AD 75-8-9R3 HAD NOT BEEN C/W.  (REQUIRED REPLACEMENT OF DRIVE ASSY 75288 WITH DR	IVE ASSY PN 61174) A CHECK OF AD 75-8-9R3 AND RELATED SB.  ENG S/N WAS NOT LISTED.  AD APPLICABLE TO S/N 33229-27A TO 41	054-27A.  NO RECORD OF ENG OVH OR ANY MAINT ON OIL PUMP GEARS.  ENG TOTAL TIME 625.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996121200071	19961212	00071	EA  	1996	12	12	96ZZZX5876       	2	19961112	G	8550	06B21326	GASKET          		06B21326    	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					OIL SUMP	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	3626C	431  				R18200284	L1983640A			OIL SUMP GASKET DETERIORATED AND TURNED TO MUSH LIKE SUBSTANCE CAUSIING GASKET INGESTION AND LOSS OF GASKET SEAL AT OIL 	PICK UP GALLEY CAUSING LOW OIL PRESSURE.  OIL PUMP CAVITATED AND SUCKED AIR INSTEAD OF OIL.					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1996121200072	19961212	00072	CE  	1996	12	12	96ZZZX5877       	1	19961101	G	7120	40043	MOUNT           			CESSNA	172   	172G        	2072420	CE  										ENG FWD RT	CORRODED        	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3918L	1628 				17254087				INSPECTION FOUND MOTOR MOUNT THROUGH-BOLTS HOLES WERE CORRODED.  FWD RIGHT MOUNT AND LEFT AFT MOUNT.						1	H	7	1 	3O			NT	3A12    					 
1996121200073	19961212	00073	CE  	1996	12	12	96ZZZX5878       	1	19961101	G	7120	40044	MOUNT           			CESSNA	172   	172G        	2072420	CE  										ENG LT AFT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3918L	1628 				17254087				INSPECTION FOUND MOTOR MOUNT THROUGH-BOLTS HOLES WERE CORRODED.  FWD RIGHT MOUNT AND LEFT AFT MOUNT.						1	H	7	1 	3O			NT	3A12    					 
1996121200074	19961212	00074	SO  	1996	12	12	96ZZZX5879       	1	19961114	G	3240		BRAKE SYS       			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	WATER CONTAM    	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	515RM					317405159				INSP FOR BRAKE PEDALS LOCKED AND BRAKE DRAG, IT WAS DISCOVERED THAT THE ENTIRE BRAKE SYSTEM, EXCEPT FOR ABOUT A QUARTER 	OF A PINT, WAS FULL OF WATER WHICH HAD FROZEN THE NIGHT BEFORE WHEN THE TEMPERATURE HAD DROPPED BELOW FREEZING.  HEAT WA	S APPLIED TO THE ACCESSIBLE AREAS OF BRAKE LINES AND THE RESERVOIR TO THAW THEM.  THE SYSTEM WAS THEN FLUSHED OUT AND SE	RVICED WITH THE CORRECT FLUID AND CHECKED FOR LEAKS.  ALL TOGETHER ABOUT A QUART OF WATER WAS DRAINED FROM THE SYSTEM.			1	L	7	2 	3O				A20SO   					 
1996020900298	19960209	00298	CE  	1996	2	9	96ZZZX588        	1	19960105	G	5312	511201144	BULKHEAD        			CESSNA	421   	421C        	2076016	CE  										FS 373.56	CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	685GF	5579 				421C0680				WHILE PERFORMING INSPECTION REQUIRED BY CESSNA SB 95-10A, FOUND CRACK IN TAIL BULKHEAD AT STA 373.56.  NEW BULKHEAD INST	ALLED AND AREA REINFORCED WITH SK 421-143 KIT INSTALLATION.  SUBMITTER SUGGESTS INSPECTION PER SB 95-10A AND KIT INSTALL	ATION ON 400 SERIES CESSNAS.				1	L	7	2 	3O				A7CE    					 
1996121200075	19961212	00075	SO  	1996	12	12	96ZZZX5880       	1	19960129	G	2823	236405	SELECTOR O-RING 	SCOTT       		PIPER 	PA34  	PA34200T    	7103406	SO  										LT & RT WING	FAILED          	B			CEKR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	2119C					347970015				FUEL DRAINED FROM ONE SIDE TO OTHER CAUSING LOW TANK TO FLOOD.  UNABLE TO MOVE FUEL SELECTORS TO OFF POSITION.  REMOVED 	SELECTOR AND FOUND BOTH LEFT AND RIGHT SELECTOR O-RINGS IN A MELTED STATE, PARTS OF O-RINGS IN SELECT OR RACK GEAR.  ONE	 SET OF O-RINGS HAVE DISINTEGRATED.  APPEARS THE LACK OF USE AND TIME WERE A CONTRIBUTING FACTOR.  (REFERENCE AD 80-18-1	0 AND PIPER SB 648A.  (THESE ARE ON A PA31).  THE VALVE IS SIMILAR AND THE PROBLEM THE SAME).			1	L	7	2 	3O				A7SO    					 
1996121200076	19961212	00076	SW  	1996	12	12	96ZZZX5881       	1	19960724	G	3340	93235140	CIRCUIT BOARD   		930500251   	BELL  	206   	206B        	1181511	SW  										SEARCH LIGHT	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	67172	456  			1964	5118				THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP--THE BULB WOULD NOT ILLUMINATE.  INVESTIGATION REVEALED THAT THE PRO	BLEM WAS IN THE PRINTED CIRCUIT BOARD.  THE PRINTED CIRCUIT TRACK WAS FOUND TO BE BURNED IN TWO BETWEEN THE RELAY 30 AND	 POINT 13.				1	G	7	1 	3U				H2SW    					 
1996121200077	19961212	00077	SW  	1996	12	12	96ZZZX5882       	1	19960804	G	3340	93235140	CIRCUIT BOARD   		930500151   	BELL  	206   	206B        	1181511	SW  										SEARCH LIGHT	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	67476	187  			1982	5158				THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP--THE BULB WOULD NOT ILLUMINATE.  INVESTIGATION REVEALED THAT THE PRO	BLEM WAS IN THE PRINTED CIRCUIT BOARD.  THE PRINTED CIRCUIT TRACK WAS FOUND TO BE BURNED IN TWO BETWEEN THE RELAY 30 AND	 POINT 13.				1	G	7	1 	3U				H2SW    					 
1996121200078	19961212	00078	SW  	1996	12	12	96ZZZX5883       	1	19960417	G	3340	930500251	SEARCH LIGHT    			BELL  	206   	206B        	1181511	SW  										EXT LIGHT	CONTACT BURNED  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	67118	768  			1914	5112				THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP.  INVESTIGATION REVEALED THAT THE SEARCHLIGHT CONTACT WAS BURNED AND	 OPEN.					1	G	7	1 	3U				H2SW    					 
1996121200079	19961212	00079	SW  	1996	12	12	96ZZZX5884       	1	19960227	G	3340	930500251	SEARCH LIGHT    			BELL  	206   	206B        	1181511	SW  										EXT LIGHT	CONTACT BURNED  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	67176	457  			1909	5119				THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP.  INVESTIGATION REVEALED THAT THE SEARCHLIGHT CONTACT WAS BURNED AND	 OPEN.					1	G	7	1 	3U				H2SW    					 
1996121200080	19961212	00080	SW  	1996	12	12	96ZZZX5885       	1	19960729	G	3340	93235140	CIRCUIT BOARD   		930500151   	BELL  	206   	206B        	1181511	SW  										SEARCH LIGHT	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	67301	888  			1029	5135				THE AIRCRAFT SEARCHLIGHT WAS REPORTED AS BEING INOP--THE BULB WOULD NOT ILLUMINATE.  INVESTIGATION REVEALED THAT THE PRO	BLEM WAS IN THE PRINTED CIRCUIT BOARD.  THE PRINTED CIRCUIT TRACK WAS FOUND TO BE BURNED IN TWO BETWEEN THE RELAY 30 AND	 POINT 13.				1	G	7	1 	3U				H2SW    					 
1996121200081	19961212	00081	WP  	1996	12	12	96ZZZX5886       	1	19960826	G	6310	369F54531	SHAFT           		369F54501   	HUGHES	369   	369E        	4470707	WP  										OVERUN CLUTCH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	911RP	93   			0099990088	526E				REMOVED OVERUNNING CLUTCH SUB-ASSEMBLY PER MDHC, FOUND OUTER RACE SHAFT CRACKED AT SPLINE RADIUS.						1	G	7	1 	3U				H3WE    					 
1996121200082	19961212	00082	GL  	1996	12	12	96ZZZX5887       	2	19961001	G	7260	6854424	SEAL            		6886442     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					START/GEN MT PAD	FAILED          	D				A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			WP	09	268ST	2    			AG35540	470122D	CAE830599			DURING NORMAL CRUISE FLIGHT, PILOT NOTICED A LOW TORQUE PRESSURE INDICATION, FURTHER EXAMINATION OF ENGINE INSTRUMENTS R	EVEALED ENGINE OIL PRESSURE STEADILY DROPPING.  PILOT PROCEEDED TO IMMEDIATELY LAND HELICOPTER.  AFTER AIRCRAFT WAS SHUT	 DOWN PILOT FOUND OIL LEAK IN ENGINE AREA AT THE ENGINE GEARBOX STARTER GENERATOR MOUNT PAD.  WHEN STARTER GENERATOR WAS	 REMOVED, THE P/N 6854424 SEAL WAS LAYING ON THE STARTER GENERATOR SPLINED SHAFT.  FURTHER INVESTIGATION OF THE FAILED S	EAL REVEALED THAT THE OUTER DIAMETER OF SEAL WAS SMALLER THAN THREE OTHER SAME P/N SEALS INCLUDING ANOTHER PREVIOUSLY IN	STALLED SEAL.  SEAL TOTAL TIME WAS 1.5 HOURS.	1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996121200083	19961212	00083	SO  	1996	12	12	96ZZZX5888       	1	19961122	G	5720		ABRASION STRIP  			PIPER 	PA28  	PA28140     	7102802	SO  										WING-STAB LE	DETERIORATED    	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	4170J					2822505				DEFECTIVE/UNAPPROVED DUCT TAPE ABRASION STRIPS FOUND ON LEADING EDGES OF WINGS AND STABILATOR.  STRIPS DEBONDED AND BADL	Y DETERIORATED.					1	L	7	1 	3O				2A13    					 
1996121200084	19961212	00084	SO  	1996	12	12	96ZZZX5889       	2	19961125	G	8530	539467	PISTON PIN      								CONT  	O470  	IO470D      	17026	SO  					ENG CYL	MISMFG          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01										BOUGHT 6 EACH 539467 PISTON PINS.  4 OF THEM WERE WAY TOO LONG.  2 OF THEM WERE CORRECT.  RETURNED AND FOUND OUT ALL OF 	THEM IN STOCK THAT WERE LONG HAD HG CODE ON THE BOX.  THE ONES WITH DG AND JG CODES WERE THE CORRECT LENGTH.										3	O			3E1				 
1996121200085	19961212	00085	CE  	1996	12	12	96ZZZX5890       	1	19961101	G	5510	07321014	REINFORCEMENT   		12320008    	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					HORIZ STAB	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	9F	4283 				18502855	282576R			AT 50 HR INSP, NOTICED REINFORCEMENT CRACKED AT BOTTOM FLANGE WHERE HINGE BOLTS TO STABILIZER.  INSTALLED NEW REINFORCEM	ENT FROM CESSNA.  SUBMITTER STATED HINGE BOLTS WERE NOT LOOSE, SO CRACK MUST HAVE OCCURRED DUE TO FATIGUE.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
1996121200086	19961212	00086	SO  	1996	12	12	96ZZZX5891       	1	19961122	G	7160	3563104	HEAT MUFF       		3563100     	PIPER 	PA28  	PA28161     	7102803	SO  										CARB HEAT	SCREEN FAILED   	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	3024S	3886 				287916297				CARB HEAT MUFF SCREEN BROKEN AND INJESTED.  DURING ANNUAL INSPECTION, SCREEN LOCATED IN MUFFLER HEAT EXCHANGER FOUND TO 	BE DETERIORATED.  SUSPECT CAUSE IS HEAT AND AGE.  SUGGEST INSPECTION OF SCREEN EACH TIME MUFFLER SHROUD IS REMOVED.					1	L	7	1 	3O				2A13    					 
1996121200087	19961212	00087	CE  	1996	12	12	96ZZZX5892       	1	19961031	G	3252	04425121	DAMPENER        			CESSNA	150   	150G        	2071816	CE  										NLG	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	03	2951J					15065751				AIRCRAFT LANDED, RAN OFF RUNWAY PUSHING NOSE GEAR UNDER FUSELAGE.  OWNER SAID PLANE DEVELOPED SHIMMY AND HE COULDN'T KEE	P ON RUNWAY.  CHECKED SHIMMY DAMPENER AND FOUND ONE-HALF AIR IN IT.  SUBMITTER STATED SHOULD MAYBE CHECK SHIMMY DAMPENER	 MORE OFTEN FOR FLUID LEVEL.				1	H	7	1 	3O				3A19    					 
1996121200088	19961212	00088	CE  	1996	12	12	96ZZZX5893       	1	19961101	G	7810	265401818	EXHAUST DUCT    			CESSNA	208   	208B        	2073701	CE  										SECONDARY EXH	CRACKED         	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1040W	2285 				208B0336				AN EXHAUST STAIN WAS OBSERVED ON ENGINE COWLING DURING A PRE-FLIGHT WALK-AROUND.  CLOSER INSPECTION BY MAINT PERSONNEL D	ISCOVERED A LARGE CRACK IN THE UPPER SURFACE OF THE EXHAUST DUCT.  PART WAS REMOVED FOR REPAIR AND REPLACED WITH A SERVI	CEABLE UNIT.				1	H	7	1 	3T				A37CE   					 
1996121200089	19961212	00089	GL  	1996	12	12	96ZZZX5894       	1	19961013	G	2510		BELT ATTACH     			AMTR  	TAILWD	TAILWINDW8  		GL  										COCKPIT SEAT	FAILED          	G	P	A		A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	91323	83   				001				AIRPLANE CRASHED BECAUSE OF ENGINE FAILURE BUT THE SEAT BELTS FAILED BECAUSE OF POOR WELDS.  ATTACHMENT LUGS BROKE LOOSE	 FROM STRUCTURE, ALLOWING PILOT TO BE EJECTED INTO INSTRUMENT PANEL.  SUBMITTER RECOMMENDS THAT AMATEUR AIRCRAFT BUILDER	S MAKE GOOD WELDS.				1	H	7	1 	3O				EXPA1H71					 
1996121200090	19961212	00090	GL  	1996	12	12	96ZZZX5895       	3	19961122	G	6114	C4716C58	HUB             													MCAULY	2A34C	D2A34C58    	GL  	NR 1 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			1439 					701466		PROPELLER RECEIVED FOR OVERHAUL.  DURING INSPECTION, HUB DISCOVERED CRACKED IN NR 1 BLADE SOCKET, NR 1 THROUGH NR 5 THRE	ADS ABOUT 5 TO 7 O'CLOCK POSITION.  NOTE:  OIL FILL AD'S 78020-0 AND 91-15-04 WERE C/W.  NO OIL NOTED LEAKING FROM THE P	ROPELLER BEFORE DISASSEMBLY.														5	C	P3EA	 
1996121200091	19961212	00091		1996	12	12	96ZZZX5896       	4	19961104	G	3457	071015530200	ANTENNA         	KING        																COCKPIT GPS	DEFECTIVE       	B			AMVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05					08885					GPS KA92 L1 ACTIVE ANTENNA IS FOR THE KLN 90B IFR APPROACH GPS.  IT WAS INSTALLED ACCORDING TO THE KLN 90B INSTALL MANUA	L P/N 006-10521-0002 REV 2 FEB. 1995.  UPON TESTING THE INSTALLED EQUIPMENT, THE ANTENNA WAS FOUND TO BE DEFECTIVE NEW O	UT OF THE BOX.  IT WOULD RECEIVE NO SATELLITES.																	 
1996121200092	19961212	00092	CE  	1996	12	12	96ZZZX5897       	1	19961101	G	7120	9691000575	MOUNT           			BEECH 	95    	95B55       	1152729	CE  										ENGINE	CHAFE DAMAGE    	B	S		UWDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	18388					TC2081				INSPECTION FOUND ENG MOUNT WITH HEAVY CHAFE DAMAGE AT LOWER RT FIREWALL ATTACH.						1	L	7	2 	3O			RT	3A16    					 
1996121200093	19961212	00093		1996	12	12	96ZZZX5898       	4	19961104	G	3457	071015530200	ANTENNA         	KING        	KA92        															COCKPIT GPS	DEFECTIVE       	B			AMVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05					08381					GPS KA92 L1 ACTIVE ANTENNA IS FOR THE KLN 90B IFR APPROACH GPS.  IT WAS INSTALLED ACCORDING TO THE KLN 90B INSTALL MANUA	L P/N 006-10521-0002 REV 2, FEB, 1995.  UPON TESTING THE INSTALLED EQUIPMENT, THE ANTENNA WAS FOUND TO BE DEFECTIVE NEW 	OUT OF THE BOX.  IT WOULD RECEIVE NO SATELLITES.																	 
1996121200094	19961212	00094	SO  	1996	12	12	96ZZZX5899       	2	19961120	G	8530	625432A2	CYLINDER        			BEECH 	45    	D45         	1152012	CE  	CONT  	O470  	O4704       	17026	SO  					NR 4 RKR BOSS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	111JH				237	BG392	116049			INSP FOUND ALL FOUR ROCKER BOSSES CRACKED OFF CYLINDER.						1	L	7	1 	3O	3	O		5A3     	E269				 
1996020900300	19960209	00300	SW  	1996	2	9	96ZZZX590        	1	19960112	G	3230	540002020	TRUSS           			MOONEY	M20   	M20C        	5870208	SW  										NLG RIGHT	BROKE           	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17	6604U	3970 				M20C2391				AIRCRAFT WAS BEING TAXIED OUT FOR A POST-ANNUAL TEST FLIGHT WHEN THE NOSE GEAR FOLLOWED BY THE RIGHT THEN LEFT MAIN GEAR	 COLLAPSED.  FOUND NOSE GEAR RETRACTION TRUSS HAD FAILED (BROKE) AT THE RIGHT RETRACT ROD.  THE ASSY TUBE THAT CANTS INW	ARD SHOWS SIGNS OF INTERNAL CORROSION AND THE ONLY EVIDENCE OF CORROSION ON THE OUTSIDE IS A SMALL AREA OF DISCOLORATION	 AT A PLACE WHERE IT CANNOT BE SEEN BECAUSE OF THE TIGHTNESS OF THE AREA.			1	L	7	1 	3O				2A3     					 
1996121200095	19961212	00095		1996	12	12	96ZZZX5900       	4	19961029	G	2562	569950102	BATTERY         	NARCO       	910         	PIPER 	PA28  	PA28R200    	7102811	SO  										ELT	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	15919				11288	28R7335106				AFTER INSTALLING A NEW NARCO ELT BATTERY, THE ELT COULD NOT BE RESET AFTER ACTIVATING THE ELT.  REPLACEMENT DATE OF BATT	ERY WAS 10-1-98.  BATTERIES HAVE A COMPUTER CHIP IN THEM SO ONLY NARCO BATTERIES CAN BE UTILIZED.  APPARENTLY FAULT WAS 	IN THIS CHIP.  AFTER INSTALLING ANOTHER NEW NARCO BATTERY, OPERATION WAS SATISFACTORY.				1	L	7	1 	3O				2A13    					 
1996121200096	19961212	00096	EA  	1996	12	12	96ZZZX5901       	2	19961119	G	8520	75359	DOWEL           		75670       	PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					CRANKSHAFT	LOOSE           	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	18MC	3235 	99   			31P7300143	2L48862			FOUND DOWEL FOR CRANKSHAFT SPLINE BUSHING IN SUMP AT OIL SCREEN.  UPON TEAR DOWN FOUND ONLY 1 OF 3 DOWELS STILL IN CRANK	SHAFT.  BUSHING WAS STARTING TO TWIST IN BETWEEN CRANKSHAFT AND SPLINE BUSHING.  NO OTHER INDICATION OF PROBLEMS.  ENGIN	E RAN GOOD, FILTER WAS CLEAR.				1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1996121200097	19961212	00097	CE  	1996	12	12	96ZZZX5902       	1	19961025	G	7920	6010008018	HOSE ASSY       			BEECH 	95    	B95         	1153404	CE  										OIL COOLER	CHAFE LEAK      	E				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			SW	11	2012C					TD430				WHILE EN ROUTE ON A ROUTINE FLIGHT, THE PILOT NOTICED OIL LEAKING FROM THE RIGHT ENGINE.  THE AIRCRAFT DIVERTED TO AWN W	HERE UPON INSPECTION IT WAS DISCOVERED THAT THE OIL COOLER OUTLET LINE P/N (AEROQUIP 950012-4-0090) HAD A SMALL HOLE DUE	 TO CHAFING WHICH WAS POSSIBLY CAUSED BY A BROKEN CLAMP P/N MS 21919DG10 WHICH ALLOWED THE LINE TO CHAFE AGAINST THE INT	AKE TUBE.  A NEW LINE WAS INSTALLED, OIL FILTER WAS INSPECTED FOR METAL, ENGINE WAS RUN AND LEAK CHECKED.  NO LEAKS WERE	 NOTED.  AIRCRAFT WAS THEN RELEASED FOR FURTHER FLIGHT.  (IT SHOULD BE NOTED THAT THE OIL LEVEL WAS ONLY DOWN BY 2.5 QUA	RTS).	1	L	7	2 	3O				3A16    					 
1996121200098	19961212	00098	GL  	1996	12	12	96ZZZX5903       	3	19961029	G	6114	D7015C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	23NC	6552 	330  		734266	402B0419		734266		PROP INSP FOUND HUB CRACKED IN THREAD AREA.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996121800006	19961218	00006	EU  	1996	12	18	96ZZZX5906       	1	19961107	G	7810	12634912	MUFFLER         	WALLCOLMNY  		SLNSBY	T67   	T67M260     	8323006	EU  										FIREWALL FRAME	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	3004H	790  				2126				ON ANNUAL INSPECTION THE MUFFLER TAILPIPE WAS FOUND CHAFING ON FRAME NR 1 (FIREWALL).  THE HEAT EXPANDS THE TAILPIPE WHI	CH CAUSED IT TO HIT THE BOTTOM OF FRAME NR 1.					1	L	7	1 	3O			NT	A73EU   					 
1996121200101	19961212	00101	EU  	1996	12	12	96ZZZX5907       	1	19961107	G	2720	T67M45245	SUPPORT BRACKET 			SLNSBY	T67   	T67M260     	8323006	EU  										RUDDER BAR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	31917	158  				2224				ON ANNUAL INSPECTION THE INBD STBD RUDDER BAR SUPPORT BRACKET WAS FOUND CRACKED.  PRESSURE APPLIED TO RUDDER PEDAL PUTS 	PRESSURE ON BRACKET CAUSING IT TO CRACK.  SUBMITTER RECOMMENDS A HEAVIER DUTY BRACKET.					1	L	7	1 	3O			NT	A73EU   					 
1996121200102	19961212	00102	CE  	1996	12	12	96ZZZX5908       	1	19961109	G	2720	35524106	CONTROL ROD     			BEECH 	35    	E35         	1151512	CE  										RUDDERVATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	3247C	3233 				D3912				DURING AN ANNUAL INSP THE TWO CONTROL RODS THAT CONNECT TO THE RUDDERVATORS WERE REMOVED TO C/W SB NR 2668.  HEAT HAD TO	 BE APPLIED TO REMOVE THE ROD ENDS.  THREADS WERE CORRODED AND INSIDE OF TUBES PITTED CORROSION WAS FOUND.  BOTH CONTROL	 ROD ASSEMBLIES WERE REPLACED WITH NEW PARTS FROM BEECH.  THIS AIRCRAFT HAS ALWAYS BEEN HANGARED.  RECOMMEND SB 2668 BEC	OME AN AD.  THIS BRINGS UP A QUESTION ABOUT OTHER AIRCRAFT THAT USE CONTROL TUBES.			1	L	7	1 	3O				A777    					 
1996020900301	19960209	00301	SO  	1996	2	9	96ZZZX591        	1	19960104	G	3230	40336000	LINK            			PIPER 	PA31T 	PA31T       	7103124	SO  										RT NLG DRAG LINK	CRACKED         	B		A	AU3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	44HT	5407 				31T7920061				DURING A SCHEDULED INSPECTION, THE RIGHT NLG DRAG LINK WAS FOUND CRACKED ON THE INBOARD LUG FORWARD SIDE WHERE THE NLG A	CTUATOR ATTACHES.  SUBMITTER RECOMMENDS SCHEDULED INSPECTIONS OF THIS AREA.  THIS IS THE SECOND OCCURRENCE.					1	L	7	2 	3T				A8EA    					 
1996121200104	19961212	00104	SO  	1996	12	12	96ZZZX5910       	1	19961029	G	3230		LINKAGE         			PIPER 	PA31  	PA31350     	7103110	SO  										MLG DOWNLOCK	REQ LUBE        	B			BSYR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	07	35871					318052123				GEAR HANDLE DID NOT RETURN TO NEUTRAL, GEAR HORN BLEW, INBD GEAR DOORS DID NOT CLOSE.  FOUND DOWN AND LOCK LINKAGE STIFF	, LUBED AND SWUNG GEAR.  OPS CHECKED GOOD.					1	L	7	2 	3O				A20SO   					 
1996121200105	19961212	00105	SO  	1996	12	12	96ZZZX5911       	1	19961028	G	3260	487862	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	FAILED          	B			BSYR	O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			GL	07	35871					318052123				NO RT MAIN DOWN AND LOCK.  INBD GEAR DOORS WILL NOT CLOSE.  FOUND RT MAIN DOWN AND LOCK SWITCH BAD, ALSO, CORRODED SPLIC	ES IN WHEELWELL.  SWITCH MFG P/N 1CH21-4.					1	L	7	2 	3O				A20SO   					 
1996121200106	19961212	00106	CE  	1996	12	12	96ZZZX5912       	1	19961101	G	7120	9691000575	MOUNT           			BEECH 	95    	95B55       	1152729	CE  										ENG	DAMAGED         	B	S		UWDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	42P					TC2244				INSP FOUND ENGINE MOUNT WITH HEAVY CHAFE DAMAGE AT LOWER RT FIREWALL ATTACH POINT.						1	L	7	2 	3O			RT	3A16    					 
1996121200107	19961212	00107	CE  	1996	12	12	96ZZZX5913       	1	19961105	G	7120	07516001	MOUNT           			CESSNA	182   	182L        	2072726	CE  										BRACE TUBES	CORRODED        	B			AJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	42036	4217 				18258822				DURING ANNUAL INSPECTION, FOUND HEAVY CORROSION AT FORWARD END OF ENGINE MOUNT MAIN BEAMS AND DIAGONAL BRACE TUBES ON BO	TH SIDES.  CAUSE OF CORROSION-PROXIMITY OF EXHAUST COLLECTORS TO MOUNT.  CORRECTIVE ACTION-INSTALL HEAT SHIELDS AFTER PA	INTING WITH HEATPROOF PAINT.				1	H	7	1 	3O			NT	3A13    					 
1996020900303	19960209	00303	SO  	1996	2	9	96ZZZX593        	1	19960116	G	2750	95504000	BRACKET         			PIPER 	PA34  	PA34200T    	7103406	SO  										FLAP LEVER	CRACK           	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4377X	16429				347670035				THE FLAP LEVER ATTACH BRACKET IS CRACKED AT THE FORWARD LOWER BEND RADIUS, ADJACENT TO THE ATTACH POINT TO THE FLOOR.						1	L	7	2 	3O				A7SO    					 
1996020900304	19960209	00304	EA  	1996	2	9	96ZZZX594        	2	19960118	G	7310	6390156	HOSE            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					ENGINE	OVER AGE        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21					1989					NEW ENGINE HOSES RECEIVED FROM PIPER WERE FOUND TO BE 6 YEARS OLD.  THE DISTRIBUTOR AGREED THIS WAS UNSATISFACTORY SAYIN	G AT FIRST THAT 5 YEARS WAS THE MAXIMUM SHELF LIFE; BUT, AFTER CONTACTING PIPER, FAX'ED A STATEMENT THAT PIPER'S PROPRIE	TARY INFORMATION ALLOWED AN 8-YEAR SHELF LIFE.  NO WONDER PIPER'S SERVICE MANUALS LIMIT THE SERVICE LIFE TO 3 YEARS.				1	L	7	1 	3O	3	O		2A13    	E286				 
1996121200155	19961212	00155	WP  	1996	12	12	96ZZZX5940       	1	19961109	G	5302	AN517A	BOLT            			HILLER	UH12  	UH12E       	4360122	WP  										TAIL BOOM ATTACH	FAILED          	B			CHIR	A				UNSCHED LANDING         				O			OTHER                     			EX	EXTERNAL LOAD  	1			NM	09	9749C		33   			2146				IN CLIMB-OUT FROM LOG LANDING WITH EXT LOAD AT AN ALT OF APPROX 400 FEET AND 69.5 PSI TORQ, PILOT HEARD A 'BANG' FOLLOWE	D BY A HIGH FREQ VIBR.  AFTER CHECKING ALL INST (NORMAL) PILOT JETTISONED EXT LOAD AND LONG LINE.  PILOT EXECUTED A PREC	AUTIONARY LANDING TO THE LOG LANDING WITHOUT INCIDENT.  HELICOPTER INSP AFTER SHUT DOWN DISCOVERED BOTH UPPER LT HAND TA	IL BOOM TO FUSELAGE ATTACH BOLTS BROKEN.  REPLACED ALL TAIL BOOM ATTACHMENT BOLTS (6 EA), 5 INCH DRIVE SHAFT, SLIDER COU	PLING AND ENG TO TRANSMISSION DRIVE SHAFT.  NOTE - THOROUGH INSP OF ACFT AND DYE PENETRANT INSP OF ATTACHMENT FITTINGS D	ID NOT TURN UP ANY DAMAGE TO THE AIRFRAME OR ENG MOUNTS.  A/C TEST FLIGHT CHECKED GOOD.	1	G	7	1 	3O				4H11    					 
1996121200156	19961212	00156	WP  	1996	12	12	96ZZZX5941       	1	19961109	G	5302	AN520A	BOLT            			HILLER	UH12  	UH12E       	4360122	WP  										TAIL BOOM ATTACH	FAILED          	B			CHIR	A				UNSCHED LANDING         				O			OTHER                     			EX	EXTERNAL LOAD  	1			NM	09	9749C		33   			2146				IN CLIMB-OUT FROM LOG LANDING WITH EXT LOAD AT AN ALT OF APPROX 400 FEET AND 69.5 PSI TORQ, PILOT HEARD A 'BANG' FOLLOWE	D BY A HIGH FREQ VIBR.  AFTER CHECKING ALL INST (NORMAL) PILOT JETTISONED EXT LOAD AND LONG LINE.  PILOT EXECUTED A PREC	AUTIONARY LANDING TO THE LOG LANDING WITHOUT INCIDENT.  HELICOPTER INSP AFTER SHUT DOWN DISCOVERED BOTH UPPER LT HAND TA	IL BOOM TO FUSELAGE ATTACH BOLTS BROKEN.  REPLACED ALL TAIL BOOM ATTACHMENT BOLTS (6 EA), 5 INCH DRIVE SHAFT, SLIDER COU	PLING AND ENG TO TRANSMISSION DRIVE SHAFT.  NOTE - THOROUGH INSP OF ACFT AND DYE PENETRANT INSP OF ATTACHMENT FITTINGS D	ID NOT TURN UP ANY DAMAGE TO THE AIRFRAME OR ENG MOUNTS.  A/C TEST FLIGHT CHECKED GOOD.	1	G	7	1 	3O				4H11    					 
1996121200157	19961212	00157	WP  	1996	12	12	96ZZZX5942       	1	19961113	G	6220	5143711	HUB             			HILLER	UH12  	UH12E       	4360122	WP  										M/R HEAD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	180HA	823  			346	HA3080				CRACK FOUND INSIDE CONICAL SURFACE DURING PRE-FLIGHT INSPECTION.  CRACKING IN THIS AREA IS COMMON.						1	G	7	1 	3O				4H11    					 
1996121200158	19961212	00158	CE  	1996	12	12	96ZZZX5943       	1	19961119	G	2437	MTA206R	SWITCH          			CESSNA	425   	425         	2076018	CE  										BAT/GEN	MALFUNCTION     	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	35TK	3337 				4250088				LEFT HAND GENERATOR APPEARED TO CARRY ONLY 60 AMP LOAD.  TROUBLESHOT TO AN INDICATION ERROR.  FOUND BAT/GEN SWITCH TO CA	USE LEFT GENERATOR AMMETER INDICATION ERROR.  INSTALLED NEW SWITCH OPERATIONAL TEST GOOD.  THIS IS THE SECOND TIME THIS 	FACILITY HAS FOUND THIS PROBLEM.				1	L	7	2 	3T			RT	A7CE    					 
1996121200349	19961212	00349	SO  	1996	12	12	96ZZZX5945       	1	19960717	G	3340	6537200	RETAIN ASSY     			PIPER 	PA28  	PA28151     	7102805	SO  										LANDING LIGHT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	43456					287415499				WHILE CHANGING LANDING LIGHT, FOUND LAMP RETAINER CRACKED AROUND UPPER STUD AND AROUND SCREW  HOLE.  THIS CONDITION CAUS	ED LANDING LIGHT TO VIBRATE EXCESSIVELY, PREMATURELY BURNING OUT BULB.  SUBMITTER STATED THIS RETAINER SHOULD BE CHECKED	 AT EVERY INSPECTION, INCLUDING PRE-FLIGHT.  IF RETAINER BROKE LOOSE, IT AND THE LANDING LIGHT COULD POSSIBLY BECOME ENT	ANGLED IN THE PROP.			1	L	7	1 	3O				2A13    					 
1996121200350	19961212	00350	SO  	1996	12	12	96ZZZX5946       	2	19961119	G	7310	646432	PRIMER LINE     			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					TOP OF ENG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	4323B					468408009				AIRCRAFT ENGINE HARD TO START AND RUNNING LEAN WITH HIGH TIT READING WHEN FLYING.  INSPECTED ENGINE AND FOUND CLAMP P/N 	24609 (CONTINENTAL) WAS BROKEN THROUGH AND PRIMER VALVE WAS MOVING AROUND UNSUPPORTED.  THIS CAUSED THE PRIMER LINE TO W	ORK-HARDEN AND AT THE B-NUT CONNECTION.  SUBMITTER STATED THIS CAN CAUSE ENGINE FIRE AT A HOT START CONDITION.				1	L	7	1 	3O	3	O		A25SO   	E8CE				 
1996121200351	19961212	00351	SO  	1996	12	12	96ZZZX5947       	2	19961120	G	8540		GEAR SHAFT      			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					LT START ADAPTER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	511LC		310  			421B0423	1881017A			STARTER ADAPTER SHAFT GEAR WAS REMOVED FOR INSPECTION AND FOUND TO BE WORN BEYOND ACCEPTABLE LIMITS IAW CSB94-4A.						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996121200352	19961212	00352	EA  	1996	12	12	96ZZZX5948       	2	19960621	G	8530	73806	PUSHROD         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENG CYL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	5249P	4284 				15284901	L1451415			DURING 100-HOUR INSPECTION, NOTICED FOUR PUSHROD TUBES WERE DENTED.  UPON FURTHER INVESTIGATION, FOUND THAT THREE OF THE	 FOUR PUSHRODS WERE WORN DUE TO RUBBING ON THE PUSHROD SHROUD.  THE THREE PUSHRODS WERE WORN FROM 25 PERCENT TO 80 PERCE	NT THROUGH WALL THICKNESS.  SUSPECT CAUSE OF BENT PUSHROD SHROUDS WAS MECHANICS LAYING TOOLS AND EQUIPMENT ON ENGINE DUR	ING MAINTENANCE.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996121200353	19961212	00353	CE  	1996	12	12	96ZZZX5949       	1	19961023	G	2820	0403434	LINE            			CESSNA	150   	152         	2071835	CE  										CABIN LT FWD	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	6101Q	8174 				15285126				FUEL LEAK IN CABIN.  LT FORWARD LOWER FUEL LINE FOUND LEAKING DUE TO CORROSION CAUSED BY MOISTURE UNDER LOOSE FITTING PL	ASTIC SLEEVE.  RT ALSO CORRODED.  REPLACED BOTH FUEL LINES AND REMOVED PLASTIC SLEEVE.  PROTECTED LINE WITH SPIRAL WRAP.					1	H	7	1 	3O			NT	3A19    					 
1996121200354	19961212	00354	CE  	1996	12	12	96ZZZX5950       	1	19961023	G	2820	0403433	LINE            			CESSNA	150   	152         	2071835	CE  										CABIN RT FWD	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	6101Q	8174 				15285126				FUEL LEAK IN CABIN.  LT FORWARD LOWER FUEL LINE FOUND LEAKING DUE TO CORROSION CAUSED BY MOISTURE UNDER LOOSE FITTING PL	ASTIC SLEEVE.  RT ALSO CORRODED.  REPLACED BOTH FUEL LINES AND REMOVED PLASTIC SLEEVE.  PROTECTED LINE WITH SPIRAL WRAP.					1	H	7	1 	3O			NT	3A19    					 
1996121200356	19961212	00356	CE  	1996	12	12	96ZZZX5952       	1	19961115	G	5753	3516505084	RIB             			BEECH 	35    	V35         	1151538	CE  										FLAP	CRACKED         	B			BX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	6238V	2638 				D8588				DURING RE-SKIN OF HAIL DAMAGED FLAP, FOUND NOSE RIB AT ACTUATOR ATTACH POINT CRACKED.  CRACK IS IN WEB OF RIB AT THE REL	IEF OF THE CAP FORMATION, LOWER FORWARD.  SUBMITTER STATED THIS IS NOT AN UNCOMMON FIND.  THIS CAN ONLY BE DETECTED IF T	HE SKIN IS REMOVED.				1	L	7	1 	3O				3A15    					 
1996121200357	19961212	00357	EA  	1996	12	12	96ZZZX5953       	2	19961111	G	8530	SL134441	PISTON PIN      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 3 CYL	BROKEN          	B			PP4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	65665		1055 			17275810	L1336139A			NR 3 CYL HAS BROKEN PISTON PIN.  SUSPECT CAUSE - MANUFACTURER'S DEFECT.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996121200358	19961212	00358	EA  	1996	12	12	96ZZZX5954       	2	19961023	G	8550	RJ10251	PUMP            			PIPER 	PA60  	PA60700P    	7106023	NM  	LYC   	O540  	LTIO540U2A  	41533	EA  					OIL SCAV	WASHER WORN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	6905A				3268	608423001	L271568A			IN  C/W AEROSTAR SB600-131 INSPECTION OF TURBO OIL SCAVENGE PUMP, FOUND WASHER UNDER RETAINING RING OF SCAVENGE PUMP EMP	ELLER WORN AWAY LEAVING RING TO FLOAT IN COUPLING AREA.  SUBMITTER STATED THIS CONDITION APPARENTLY SHOULD NOT HAPPEN IF	 PROPER GARLOCK SEAL IS INSTALLED IN ENGINE ADAPTER WHICH, ON THIS PARTICULAR APPLICATION, THE PROPER SEAL IS INSTALLED.	  PART TOTAL TIME 784.1 HRS.			1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
1996121200359	19961212	00359	SO  	1996	12	12	96ZZZX5955       	2	19961107	G	8540		GEAR SHAFT      			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					LT START ADAPTER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	707DM		550  			421B0145	218419R			STARTER ON THE RIGHT ENGINE BEGAN TO WORK INTERMITTENTLY.  THE PILOT SAID THE STARTER HAD BEEN TURNING SLOW AND MAKING N	OISE.  WHEN THE STARTER WAS REMOVED AND TESTED, IT WORKED FINE.  THE STARTER ADAPTER SHAFT GEAR WAS REMOVED AND FOUND TO	 BE WORN BEYOND ACCEPTABLE LIMITS, IT ALSO DAMAGED THE REST OF THE ENGINE.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996121200360	19961212	00360	SO  	1996	12	12	96ZZZX5956       	2	19961112	G	8530	653446	VALVE           			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					NR 1 CYL EXH	LEAKAGE         	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	717CM	40   				U20604988	230184R			ENGINE HAS 40.0 HRS SINCE MAJOR OVERHAUL AT WHICH TIME NEW TCM CYLINDERS WERE INSTALLED.  COMPRESSION CHECK SHOWS NR 1 C	YLINDER AT 40/80 LEAKING THROUGH EXHAUST VALVE AND CYLINDERS NR 2, 3, 5, AND 6 TO BE AT 70/80 WITH SLIGHT EXHAUST VALVE 	LEAKAGE.  BORESCOPE INSPECTION SHOWS NR 1 CYLINDER TO HAVE A VERY NARROW EXHAUST VALVE SEAT WITH LIGHT CONTACT.  COMPRES	SION READINGS ON THE ABOVE CYLINDERS ARE OUTSIDE THE LIMITS SPECIFIED IN TCM SB M84-15, DATED DEC 21, 1984.			1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1996121200361	19961212	00361	SW  	1996	12	12	96ZZZX5957       	1	19961114	G	5730	STITSHS90X	FABRIC          			BBAVIA	7     	7AC         	2110102	SW  										RT INB WING	LOOSE           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	72468		450  			7AC5450				DURING FLIGHT, UNUSUAL NOISE WAS HEARD.  IT WAS FOUND THAT FABRIC WAS LOOSE ON 1ST AND 2ND RIBS ON RT WING, AND NR 4 AND	 NR 8 SCREWS HAD PULLED OUT OF RIBS.  SUBMITTER STATED IT IS BELIEVED THAT SCREW HOLES WERE SLIGHTLY OVERSIZE AND FABRIC	 WEAVE WAS FORCED INTO HOLES DURING INSTALLATION GIVING FALSE SENSE OF TIGHTNESS.				1	H	7	1 	3O				A759    					 
1996121800017	19961218	00017	EA  	1996	12	18	96ZZZX5959       	2	19961113	G	7322	24A56	SPRING          	FACET       	MA4SPA      	CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					CARB IDLE ADJ	WEAK            	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SW	13	7624G	4043 	10   		BL224699	17259324	L2833127A			INSTALLED OVERHAULED CARBURETOR AND RIGGED.  WITHIN 10 HOURS, OWNER REPORTED ENGINE VERY ROUGH AT LOW POWER SETTINGS OR 	WOULD NOT EVEN IDLE.  FOUND IDLE MIXTURE ADJUST SCREW GONE.  NOTIFIED OVERHAULER WHO SENT NEW CARB.  UPON INSTALLATION O	F NEW UNIT, SPRING TENSION ON AJUST SCREW FOUND TO BE WEAK OR NON-EXISTANT AT CORRECT SETTING.  OVERHAULER RECOMMENDED S	TRETCHING SPRING.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996121200363	19961212	00363	CE  	1996	12	12	96ZZZX5960       	1	19961016	G	3230	08421042	BELLCRANK       			CESSNA	310   	310Q        	2074242	CE  										NLG	FAILED          	D		A		O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			SW	07	7935Q	6484 				310Q0667				PILOT HEARD A POP DURING GEAR EXTENSION.  PILOT RETRACTED AND EXTENDED GEAR AND NOSE GEAR WAS NOT DOWN AND LOCKED.  NO G	REEN LIGHT, GEAR TRAILING AT A 45 DEGREE ANGLE.  UPON LANDING, THE NOSE GEAR FOLDED AFT.  INVESTIGATION REVEALED THAT TH	E BELLCRANK NEAR THE AFT END OF THE NOSE GEAR WELL HAD FAILED AT THE FORK BOLT.  NO EVIDENCE OF PRIOR CRACK ON THE BELLC	RANK.  THIS AIRCRAFT HAD EXPERIENCED A BELLY LANDING WHERE IT APPEARED THAT THE GEAR WAS BEGINNING TO EXTEND WHEN THE RU	NWAY WAS CONTACTED.  THAT BELLY-IN WAS JUST HOURS PRIOR TO THIS FAILURE.  THE ABOVE BELLCRANK WAS INSPECTED VISUALLY, AN	D NOT REPLACED DURING REPAIRS.  SUSPECT STRESS OF BELLY-IN CAUSED FAILURE.  SUGGEST BETTER INSPECTION.	1	L	7	2 	3O				3A10    					 
1996121200364	19961212	00364	SO  	1996	12	12	96ZZZX5961       	1	19961118	G	2820	MIL6000	HOSE            			PIPER 	PA18  	PA18150     	7101828	SO  										HEADER TANK	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	9798P	1350 				187609031				THE ENGINE WOULD STARVE FOR FUEL WHEN THE RIGHT TANK WAS SELECTED.  THE RIGHT FUEL HEADER TANK (REAR) WAS REMOVED.  BOTH	 LINES INTO THE HEADER TANK WERE PLUGGED WITH MIL-6000 HOSE COUPLING MATERIAL.  THE EXPOSED HOSE INTERIOR WAS NOTICEABLY	 DETERIORATED.  IF HOSES WERE ORIGINAL, THEY COULD BE 20 YEARS OLD.  THE A/C WAS APPROVED FOR AUTO GAS.  IT HAD ALSO USE	D 100LL.			1	H	7	1 	3O				1A2     					 
1996121200365	19961212	00365	CE  	1996	12	12	96ZZZX5962       	1	19961105	G	3211	63411121	PIN             			CESSNA	525   	525         	2076601	CE  										MLG ATTACH	DEFECTIVE       	B			EBVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09										DURING COMPLETION OF CESSNA SB SB 525-32-08, THE REQUIRED KIT WAS ORDERED AND RECEIVED.  UPON INSPECTION OF THE KIT PART	S, ALL FOUR MAIN LANDING GEAR PINS WERE FOUND UNSERVICEABLE.  3 PINS (PN 6341112-1) WERE FOUND WITH LABELING IDENTIFYING	 THEM AS BAD FROM STOCK AND THE FOURTH WAS SCRATCHED AND NICKED.  A REPLACMENT KIT WAS ORDERED FROM CESSNA, INSPECTED, A	ND THE BULLETIN COMPLETED.			1	L	7	2 	4F			RT	A1WI    					 
1996121200367	19961212	00367	CE  	1996	12	12	96ZZZX5964       	1	19960927	G	2150	4573150	CLAMP           			CESSNA	525   	525         	2076601	CE  										RAM AIR PRECOOL	BROKEN          	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	195ME					5250110				AIRCRAFT WAS HAVING A HEATING PROBLEM.  (COULD NOT GET HEAT INTO CABIN) WHILE TROUBLESHOOTING.  MAINTENANCE FOUND A CLAM	P LAYING ON THE REAR COMPARTMENT FLOOR BROKEN.  THE CLAMP CAME FROM THE FWD SIDE OF THE RAM-AIR PRECOOLER, HOWEVER, THE 	HEATING PROBLEM WAS NOT CAUSED BY THE BROKEN CLAMP.  MAINTENANCE FOUND A BAD RAM AIR MODULATING VALVE.				1	L	7	2 	4F			RT	A1WI    					 
1996121200368	19961212	00368	CE  	1996	12	12	96ZZZX5965       	1	19960927	G	2150		VALVE           			CESSNA	525   	525         	2076601	CE  										RAM AIR MOD	FAILED          	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	195ME					5250110				AIRCRAFT WAS HAVING A HEATING PROBLEM.  (COULD NOT GET HEAT INTO CABIN) WHILE TROUBLESHOOTING.  MAINTENANCE FOUND A CLAM	P LAYING ON THE REAR COMPARTMENT FLOOR BROKEN.  THE CLAMP CAME FROM THE FWD SIDE OF THE RAM-AIR PRECOOLER, HOWEVER, THE 	HEATING PROBLEM WAS NOT CAUSED BY THE BROKEN CLAMP.  MAINTENANCE FOUND A BAD RAM AIR MODULATING VALVE.				1	L	7	2 	4F			RT	A1WI    					 
1996121200369	19961212	00369	SW  	1996	12	12	96ZZZX5966       	1	19960821	G	7160	65525062	DUCT            			GULSTM	560   	560         	0141402	SW  										LT/RT ENG	CRACKED         	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	444GG	1300 				5600262				DURING A PHASE INSPECTION, BOTH THE LT AND RT ENGINE INLET OUTER DUCT SKINS WERE FOUND TO HAVE SEVERAL CRACKS EMANATING 	FROM THE RIVET HOLES TO THE SKIN EDGES WHERE THE DUCT IS RIVETED TO THE INLET LIP.  DISCUSSION WITH MANUFACTURER DETERMI	NED THE SUSPECT CAUSE OF CRACKING WAS DUE TO IMPROPER ASSEMBLY AT THE TIME THE AIRCRAFT WAS BUILT.  SUBMITTER RECOMMENDS	 OWNER/OPERATOR INSPECT FOR THIS CONDITION AT FIRST AVAILABLE OPPORTUNITY.			1	H	7	2 	3O				6A1     					 
1996121200370	19961212	00370	NE  	1996	12	12	96ZZZX5967       	2	19961025	G	7200		ENGINE          			LEAR  	25    	25          	5170506	CE  	GE    	CJ610 	CJ6106      	30006	NE  					PWR SECT	MALFUNCTION     	E				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	09	345MC					046	251164			DURING CRUISE, ENGINE ROLL BACK AT FL 380.  INSPECTED ENGINE BLADES T-GUIDE VANES AND FUEL CONTROL FOR CAUSE.  NO DEFECT	S NOTED.  FLIGHT TEST A/C TO FL 410, NO DEFECTS NOTED.					2	L	7	2 	4J	4	J		A10CE   	1E16				 
1996121200371	19961212	00371	CE  	1996	12	12	96ZZZX5968       	1	19960917	G	3211	63411121	PIN             		6322000801S 	CESSNA	525   	525         	2076601	CE  										RT MLG ATTACH	RUSTED          	B			EBVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	525KA					5250019				AFT PIN IN RT MAIN LANDING GEAR WAS RUSTED AND PITTED.  THIS IS FROM A NEW WING ASSY WITH ZERO TIME SINCE NEW.  SUBMITTE	R RECOMMENDS RUST INHIBITOR APPLICATION DURING ASSEMBLY.					1	L	7	2 	4F			RT	A1WI    					 
1996121200372	19961212	00372	CE  	1996	12	12	96ZZZX5969       	1	19961123	G	3040		WARN LIGHT      			BEECH 	60    	60          	1153602	CE  										DEICER LOW LEVEL	STAYS ARMED     	D		A		O				OTHER                   				N			FALSE WARNING             			TO	TAKEOFF        	1			NM	03	164PA					030				THE DE-ICE ALCOHOL LOW LEVEL WARNING LIGHT ILLUMINATES ON THE MASTER WARNING PANEL AT AIRCRAFT ROTATION DURING TAKEOFF. 	 ONCE ACTIVATED, THE LIGHT STAYS ILLUMINATED UNTIL POWER IS REMOVED FROM THE AIRCRAFT.  LEARJET ISSUED OPTIONAL SERVICE 	BULLETIN 60-30-1 TO ADDRESS THE PROBLEM.  SINCE THE ILLUMINATION OF A CAUTION LIGHT OCCURS AT SUCH A CRITICAL POINT IN T	HE FLIGHT, SUBMITTER'S OPINION IS THIS IS A SAFETY OF FLIGHT ISSUE.  SUBMITTER RECOMMENDS THAT LEARJET RE-CLASSIFY THE B	ULLETIN TO MANDATORY, OR THE FAA SHOULD CONSIDER ISSUING AN AD.		1	L	7	2 	3O				A12CE   					 
1996020900307	19960209	00307	CE  	1996	2	9	96ZZZX597        	1	19960115	G	2434	1101900	GENERATOR       	DELCO       		BEECH 	23    	23          	1151202	CE  										REAR HOUSING	BRUSHES FAILED  	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			EA	05	8722M					M511				GENERATOR WENT 'OFF LINE'.  DISASSEMBLY FOUND BRUSH LEADS CUT AND FRAYED BY BRUSH HOLDERS.  REAR BEARING FOUND LOOSE IN 	REAR HOUSING CAUSING ROTATIONAL VIBRATION WHICH CAUSED BRUSH LEADS TO HIT BRUSH HOLDERS.					1	L	7	1 	3O				A1CE    					 
1996121200373	19961212	00373	CE  	1996	12	12	96ZZZX5970       	1	19961119	G	2430	M22759749	WIRE            			BEECH 	100   	B100        	1152919	CE  										START/GEN	CRACKED         	B		A	UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	87NW	5675 				BE42				THE STARTER/GENERATOR 4 GAUGE WIRES THAT RUN FROM THE FIREWALL POWER CONNECTOR TO THE STARTER/GENERATOR WERE FOUND WITH 	CRACKED INSULATION.  THE CRACKS ARE 2 INCHES TO 4 INCHES IN LENGTH, EXPOSING THE CENTER CONDUCTOR.  ON THE LT AND RT ENG	INE, THE DEFECTIVE WIRE IS LABELED P10C4.  SOME OF THE WIRING ON THIS AND OTHER B100'S IS M22759/8 OR /16.  THESE 2 SHOW	 NO SIGNS OF SPLITTING OR CRACKING.  ONLY THE TYPE M22759/7 HAS BEEN FOUND WITH CRACKS.  TEMP RATING ON THESE WIRE TYPES	 ARE PLUS 150 DEGRESS CELSIUS FOR THE /16, PLUS 200 DEGREES CELSIUS FOR THE /7 AND PLUS 260 DEGREES CELSIUS FOR THE /8. 	 THIS IS THE FOURTH B100 FOUND WITH THIS PROBLEM.	1	L	7	2 	4T			 	A14CE   					 
1996121200374	19961212	00374	CE  	1996	12	12	96ZZZX5971       	1	19961110	G	5712	5522620	RIB STRAP       			CESSNA	500   	550         	2076604	CE  										LT WS 91	MISINSTALLED    	H	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	101KK					5500209				LEFT WING RIB AT WS 91 UPPER STRAP IS JOGGLED TO FIT BETWEEN SPAR AND RIB.  ASSEMBLY AT FACTORY PUT STRAP ABOVE SPAR, CR	EATING A 0.050 INCH BUMP IN WING.  SUBMITTER STATES CESSNA RESEARCHED AIRCRAFT BUILD RECORDS AND COULD NOT FIND ANYTHING	 SHOWING WHY THIS WAS ASSEMBLED THAT WAY.  RECOMMEND ALL 500 OPERATORS CHECK FOR THIS CONDITION.				1	L	7	2 	4F				A22CE   					 
1996121200375	19961212	00375	NE  	1996	12	12	96ZZZX5972       	2	19961120	G	7200		ENGINE          			AEROSP	601   	SN601       	8680661	EU  	PWA   	JT15  	JT15D4      	52112	NE  					RT ENG	FAILED          	G		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	05	200MT	2040 	606  			40	PCE70080			PILOT EXPERIENCED SUDDEN RT ENGINE FAILURE AT 27,000 FEET ALTITUDE WITH NO WARNING OR PREVIOUS INDICATIONS.  PRELIMINARY	 INSPECTION BY CREW AFTER LANDING DISCLOSED DAMAGED PARTS COMING OUT ENGINE TAIL SECTION.					2	L	7	2 	4F	4	F		A37EU   	E1NE				 
1996121200376	19961212	00376	SO  	1996	12	12	96ZZZX5973       	1	19960720	G	7332	320283	SWITCH          			GULSTM	G159  	G159        	3952202	SO  										FUEL PRESS	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	09	3NA					92				FUEL DIFFERENTIAL PRESSURE SWITCH CRACKED 1/2 WAY AROUND AT POINT OF CONNECTOR PLUG ATTACH, THIS ALLOWED FUEL TO LEAK ON	 TO TOP OF ENGINE.					2	L	7	2 	4T				1A17    					 
1996121200378	19961212	00378	CE  	1996	12	12	96ZZZX5975       	1	19961106	G	5311		FRAME           			MTSBSI	MU2   	MU2B60      	5780460	CE  										RT FS 4850	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	33EW	3264 				1519SA				AFTER REMOVING THE RT SIDE WALL OF CABIN INTERIOR, CRACKS WERE FOUND IN FS 4850.  MUII SB 073/53-002A, FUSELAGE FRAME IN	SP AND REPAIR ADDRESSES THIS PROBLEM.  THE SB WAS C/W AT 2606.0 AFTT.  REINSPECTION IS DUE AT 4606.0 HRS.  ACFT ONLY HAS	 3264.0 HRS.  SUBMITTER STATED THIS IS THE SECOND ACFT WITH CRACKS FOUND AT THIS STATION THAT HAVE HAD SB P/C/W AND BEFO	RE REINSPECTION WAS DUE.			1	H	7	2 	3T			RT	A10SW   					 
1996121200379	19961212	00379	GL  	1996	12	12	96ZZZX5976       	3	19961126	G	6111		BEARING         			MTSBSI	MU2   	MU2B60      	5780460	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP BLADE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	429WM					1520SA		CDA3351		HUB TT 486.7 BLADES, 946.0 TT.  ONE BLADE STICKS IN ONE POSITION AND 2 BLADES ROUGH, HARTZELLS REPLY WAS A FLAT SPOT ON 	BEARINGS OR BEARINGS STEPPING ACROSS SPLIT IN RACE, OR MISMATCHED SET OF RACES.  BEARING AND RACES TT IS UNKNOWN DUE TO 	NO ENTRY IN LOG BOOK OR WORK ORDER.  PROBLEM FOUND DURING 100 HOUR INSPECTION.  PROP SENT TO HARTZELL NOV 26, 1996.				1	H	7	2 	3T			RT	A10SW   		6	C	P40EA	 
1996121200380	19961212	00380	NM  	1996	12	12	96ZZZX5977       	1	19961115	G	3210	65195173	SIDE BRACE      		65195177    	BOEING	727   	72761       	1384017	NM  										LT MLG	BROKEN          	B		A	VN4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	530KF					19176				AFTER LANDING, LEFT MLG DOOR STARTED CYCLING OPEN AND CLOSED.  DURING TROUBLESHOOTING OF DOOR PROBLEM, LEFT MLG UPPER SI	DE BRACE SEGMENT WAS FOUND BROKEN AT THE FWD TRUNNION.  REF IPC 32-10-1, FIGURE 4, ITEM 310.  A/C HOURS 31,889.  A/C CYC	LES 71,297.				2	L	7	3 	4F				A3WE    					 
1996121200381	19961212	00381	CE  	1996	12	12	96ZZZX5978       	1	19961031	G	2430	M22759749	WIRE            			BEECH 	100   	B100        	1152919	CE  										LT ENG START/GEN	CRACKED         	B		A	UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	6241P					BE130				THE STARTER/GENERATOR 4 GAUGE WIRES, THAT RUN FROM THE FIREWALL POWER CONNECTOR TO THE STARTER/GENERATOR, WERE FOUND WIT	H CRACKED INSULATION.  THE CRACKS RUN PARALLEL WITH THE WIRE.  SOME OF THE CRACKS ARE OVER 3 INCHES IN LENGTH EXPOSING T	HE CENTER CONDUCTOR.  ON THE LEFT ENGINE, THE WIRE NUMBERS OF THE DEFECTIVE WIRES ARE K2D4, K2F4, P10A4, P10C4, AND P10E	4.  THIS IS THE THIRD B100 FOUND WITH THIS DEFECT.			1	L	7	2 	4T			 	A14CE   					 
1996121200382	19961212	00382	CE  	1996	12	12	96ZZZX5979       	1	19961025	G	5512	23320007	SKIN            			LEAR  	25    	25D         	5170514	CE  										HORIZ STAB	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	70JF	7096 				278				FOUND CORROSION ON LEADING EDGE SKIN WHEN STAB BOOTS WERE BEING REPLACED.  COULD HAVE BEEN CAUSED BY METAL NOT BEING PRO	PERLY TREATED WHEN MANUFACTURED OR BOOTS GOT HOLES IN THEM LETTING MOISTURE IN.  SUBMITTER STATES PROPER TREATMENT OF ME	TAL AND/OR GOOD BOOTS INSTALLED AT ALL TIMES.				2	L	7	2 	4J				A10CE   					 
1996020900308	19960209	00308	CE  	1996	2	9	96ZZZX598        	1	19960118	G	7430	C2925010106	SWITCH          	GERDES      		CESSNA	150   	152         	2071835	CE  										MAG IGNITION	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4847B	5574 				15283670				DURING RUN-UP/MAG CHECK, THE IGNITION KEY COULD BE EASILY REMOVED (IN ANY POSITION).  CESSNA SEB 92-29 AND TCM SB 636 CL	EARLY CITES THIS AS A MANDATORY INSPECTION, AND A 'HOT MAG' IS NOT SAFE.  YET, AD 93-05-06 'GERDES SWITCH INSPECTION', H	AD BEEN SIGNED OFF.				1	H	7	1 	3O			NT	3A19    					 
1996121200384	19961212	00384	NM  	1996	12	12	96ZZZX5981       	1	19961024	G	5311		FRAME           			BOEING	727   	727276      	138408R	NM  										FS 227.8	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FUSELAGE FRAME 227.8 FROM WL 208 TO WL 225.						2	L	7	3 	4F			RT	A3WE    					 
1996121200385	19961212	00385	NM  	1996	12	12	96ZZZX5982       	1	19961024	G	5311		FRAME           			BOEING	727   	727276      	138408R	NM  										FS 219.8	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				DURING C-CHECK INSPECTION, LEVEL 2 CORORSION WAS NOTED ON FUSELAGE FRAME 219.8, AT WL 220.						2	L	7	3 	4F			RT	A3WE    					 
1996020900309	19960209	00309	CE  	1996	2	9	96ZZZX599        	1	19960109	G	2913	24343RAB	PUMP            			CESSNA	421   	421C        	2076016	CE  										HYD/AIR COND	SHAFT RUSTED    	B			R2JR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	940WP	4037 				421C0228				NR 2 ENGINE AIR CONDITIONER HYDRAULIC PUMP FOUND LEAKING OUT CASE DRAIN.  WHILE ATTEMPTING TO REMOVE PUMP, FOUND SHAFT R	USTED ONTO AIRCRAFT HYDRAULIC PUMP AND AIRCRAFT HYDRAULIC SHAFT RUSTED SOLID ONTO ENGINE DRIVE ADAPTER.  DRIVE SHAFT HAD	 TO BE FORCIBLY REMOVED FROM ENGINE AND ADAPTER BEARING REPLACED.  THESE TWO HYDRAULIC PUMPS ARE 'PIGGY-BACKED' ONTO THE	 SAME ENGINE DRIVE PAD.  MANUFACTURER REQUIRES NO INSPECTION OR LUBE OF THESE DRIVE SHAFT SPLINES.  SUBMITTER SUGGESTS C	ESSNA REVISE INSPECTION PROGRAM TO PERIODICALLY REMOVE, INSPECT, AND LUBE THESE SPLINES.		1	L	7	2 	3O				A7CE    					 
1996121200492	19961212	00492		1996	12	12	96ZZZX5991       	4	19961018	G	2312	4000103000	TRANSCEIVER     		RT450       	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT VHF	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				202	7061				TRANSCEIVER WILL NOT TRANSMIT.  IN A/C ONLY 3.5 HRS BEFORE FAILURE.						1	G	7	2 	3U				H13EU   					 
1996121200493	19961212	00493		1996	12	12	96ZZZX5992       	4	19961016	G	2312	4000103000	TRANSCEIVER     		RT450       	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT VHF	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				778	7061				TRANSCEIVER WILL NOT TRANSMIT.						1	G	7	2 	3U				H13EU   					 
1996121200495	19961212	00495	NM  	1996	12	12	96ZZZX5993       	1	19960823	G	5530	6516829	FITTING         			BOEING	727   	727251      	138408H	NM  										VERT STAB	CORROSION       	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	280US					21159				VERTICAL STABILIZER HINGE FITTINGS HAVE CORROSION DAMAGE AT THE BEARING HOLES.  REPAIRED FITTINGS PER DALFORT AVIATION X	EA NR X1-55-130.					2	L	7	3 	4F				A3WE    					 
1996121200496	19961212	00496	NM  	1996	12	12	96ZZZX5994       	1	19960823	G	5530	6516873	FITTING         			BOEING	727   	727251      	138408H	NM  										VERT STAB	CORROSION       	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	280US					21159				VERTICAL STABILIZER HINGE FITTINGS HAVE CORROSION DAMAGE AT THE BEARING HOLES.  REPAIRED FITTINGS PER DALFORT AVIATION X	EA NR X1-55-130.					2	L	7	3 	4F				A3WE    					 
1996121200497	19961212	00497	NM  	1996	12	12	96ZZZX5995       	1	19960823	G	5320	65C290802	ANGLE           			BOEING	727   	727251      	138408H	NM  										BS 1183	CRACK           	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	280US					21159				BS 1183 BULKHEAD FORWARD SIDE VERTICAL SUPORT ANGLE HAS .3750 INCH LONG CRACK ON RBL 10 AS SEEN FROM AFT BAG BIN.  REPAI	RED ANGLE PER BOEING SB 727-53-0175.					2	L	7	3 	4F				A3WE    					 
1996121200649	19961212	00649	CE  	1996	12	12	96ZZZX5996       	1	19961127	G	7160	1211282	AIR FILTER      	AIRMAZE     		BEECH 	58    	58P         	1152744	CE  										ELEMENT FRAME	RIVETS PULLED   	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	25										NEW ENGINE AIR FILTERS WERE ORDERED FROM BEECH.  WHILE INSTALLING A FILTER, IT WAS DISCOVERED THAT THE FRAME WAS ASSEMBL	ED WITH A PULLED 'POP' RIVET.  THE RIVET STEM WAS NOT REMOVED FROM THE RIVET AFTER IT WAS PULLED.  ONE STEM FELL TO THE 	FLOOR.  FURTHER INVESTIGATION FOUND ONE STEM LODGED TO THE FILTER ELEMENT 'FINS' AND 2 OTHERS STILL IN RIVETS, BUT LOOSE	.			1	L	7	2 	3O				A23CE   					 
1996121200650	19961212	00650	SO  	1996	12	12	96ZZZX5997       	1	19961112	G	3213	2001	STRUT FORK      			MAULE 	M7    	M7235       	5460170	SO  										MLG	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03										INSP OF NEW STRUT FORK FOUND UNUSEABLE DUE TO THREADS FILLED WITH CAD PLATING.  ALSO FORK PORTION WAS POORLY MACHINED AN	D WAS GROOVED.					1	H	7	1 	3O			NC	3A23    					 
1996121200651	19961212	00651		1996	12	12	96ZZZX5998       	1	19961111	G	2822	1B56	PUMP            	AIRBORNE    																ENG FUEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					1C55					ARMATURE OUT OF DYNAMIC BALANCE CAUSING PREMATURE FAILURE OF THE FUEL PUMP.																			 
1996121200652	19961212	00652	SO  	1996	12	12	96ZZZX5999       	1	19960927	G	5610	54901006	WINDOW          			PIPER 	PA31T 	PA31T1      	7103126	SO  										PILOT SIDE	BLEW OUT        	B		A	ATZR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	09	2552Y	4200 				31T8104061				PILOT'S SIDE WINDOW BLEW OUT AT 19,000 FEET ON CLIMB.  STORM WINDOW AND SOME PARTS OF SIDE WINDOW DID NOT LEAVE AIRCRAFT	.  ALL SYSTEMS SEEMED TO BE FUNCTIONING NORMAL AND NO WARNING JUST BLEW OUT.  AC AND PART TT:  4200.0.					1	L	7	2 	3T				A8EA    					 
1996121200653	19961212	00653	CE  	1996	12	12	96ZZZX6000       	1	19961117	G	3222	DC630C	VALVE           			RAYTHN	DH125 	HAWKER800XP 		CE  										NLG STRUT	LEAKING         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	11	291XP	270  				258291				ON 11-17-96 DURING ROLL-OUT, NOSE STRUT COLLAPSED.  AFTER A/C RETURNED, INSP FOUND SCHRADER VALVE LEAKING.  REPLACED VAL	VE AND LEAK CHECKED FOR 24 HRS.  CYCLES, 156.					2	L	7	2 	4F			RT	A3EU    					 
1996121200654	19961212	00654	GL  	1996	12	12	96ZZZX6001       	3	19961111	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	2717B	4021 	1379 			402C0221		796457		PROPELLER RECEIVED FOR OVERHAUL.  AFTER DISASSEMBLY, DISCOVERED HUB CRACK IN NR 2 BLADE SOCKET, 2 THREADS IN 3 DEGREE TO	 5 DEGREE POSITION.  ALSO, BLADE RACES AND BALLS CORRODED.  (WATER IN THE HUB).					1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996121200655	19961212	00655	CE  	1996	12	12	96ZZZX6002       	1	19961122	G	8011	641500	CLUTCH ASSY     			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					STARTER	FAILED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	21968					15074576	250816A48			ENGINE WAS INSTALLED IN TEST CELL AFTER OVERHAUL AND RUN FOR OVER 1 HR WITH AT LEAST 4 STARTS.  CUSTOMER THEN INSTALLED 	ON AIRCRAFT, STARTED IT TO TAXI, PILOT SAID IT SEEMED ROUGH.  ENGINE WAS SHUT DOWN.  VISUAL CHECKS REVEALED NOTHING.  TI	MING WAS OK.  HARNESS WAS ROUTED CORRECTLY.  PILOT AGAIN ATTEMPTED TO START ENGINE.  AFTER SEVERAL REVOLUTIONS PROP STOP	PED AND HE SAID IT BRACKED UP BUT STARTER MOTOR CONTINUED TO TURN FREELY NOW WITHOUT TURNING CRANKSHAFT.  STARTER WAS RE	MOVED AND CLUTCH WAS FOUND WITH THE PILOT CENTER SHAFT BROKEN OFF AND ALL GEAR TEETH BROKEN OFF AND THE GEAR BODY SPLIT 	AT FRONT BUSHING HOLE LOCATION.	1	H	7	1 	3O	3	O		3A19    	E252				 
1996121200656	19961212	00656	EU  	1996	12	12	96ZZZX6003       	1	19961112	G	3210	TB1041033000	SCISSORS        			SOCATA	TB9   	TB9         	8680694	EU  										LT MLG	FAILED          	G	L	A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	05	3040X					1503				THE LOWER SCISSORS ON THE LEFT MAIN GEAR CRACKED UPON TOUCH-DOWN, AND THE WHEEL TURNED CAUSING THE A/C TO SLIDE TO A STO	P.  INSPECTION REVEALED THE OUTBOARD SIDE OF THE LOWER SCISSORS WHERE IT ATTACHED TO THE STRUT HAD BEEN CRACKED FOR SOME	 TIME. THE ATTACHMENT PINS THAT HOLD THE SCISSORS WERE CORRODED DUE TO LACK OF GREASE.  THIS CAUSED UNDUE STRESS ON THE 	SCISSORS WHICH WERE VERY HARD TO MOVE.  THE GREASE FITTING IN THE SCISSORS WOULD NOT TAKE GREASE AT TIME OF INSPECTION.			1	L	7	1 	3O			NT	AS1EU   					 
1996121200657	19961212	00657	EA  	1996	12	12	96ZZZX6004       	2	19961015	G	7414	M3056	DISTRIBUTOR GEAR	SLICK       	631         	MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540AF1A  	41532	EA  					LT MAG	DETERIORATED    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	530JP	631  			92080001	270114	L928361A			INVESTIGATION FOR DETERIORATED LT MAG FOUND LEFT MAG WAS (PRESSURIZED) FROM SAME 'T' FITTING AS RIGHT MAG BUT HAS MORE H	EAT.  LEFT MAG HAS B AND D TACHOMETER PICK UP WITH LARGER ORIFICE WHICH ALLOWS ALMOST TWICE THE AIRFLOW ALLOWING MORE HE	AT INTO MAG.  SUBMITTER STATED SLICK REPORTED OVER 1 YR AGO THEY WERE AWARE OF PROBLEM AND IT WOULD BE CORRECTED.  THIS 	IS THE 2ND TIME HAVE HAD THIS PROBLEM WHICH IS SHARED BY MANY MOONEY OWNERS.			1	L	7	1 	30	3	O	RT	2A3     	E14EA				 
1996121200658	19961212	00658	SO  	1996	12	12	96ZZZX6005       	2	19961115	G	7414	10349237	GEAR TOOTH      		103493505   	CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					RT MAG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6506G	1330 			653290R	21064406	269905R			DURING INSP OF MAG FOR POINT WEAR AND CONDITION, A TOOTH WAS FOUND BROKEN FROM THE DIST GEAR.  A NEW GEAR, CONDENSOR, AN	D POINT WAS INSTALLED.  THE MAG WAS RUN ON A TEST BENCH WITH NORMAL OPERATION.  A POSSIBLE FLAW IN MATERIAL OR A GEAR HO	LDING TOOL NOT BEING USED PROPERLY IS SUSPECT CAUSE OF THIS DEFECT.  SUBMITTER STATED IF YOU USE A HOLDING TOOL, PAY CLO	SE ATTENTION NOT TO TWIST THE MAG.  ON REINSTALLATION!			1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996121200659	19961212	00659	CE  	1996	12	12	96ZZZX6006       	1	19960731	G	2150	8820K16	SWITCH          			CESSNA	404   	404CESSNA   	2075901	CE  										AIR COND	BURNED          	D				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			GL	17	37167	1352 				4040129				PRIOR TO LANDING, THE PILOT NOTICED SMOKE IN THE COCKPIT COMING FROM THE PILOT'S SWITCH PANEL.  THE PILOT THEN TURNED TH	E MASTER OFF AND MADE A SAFE LANDING.  INVESTIGATION FOUND THAT THE AIR COND TOGGLE SWITCH HAD FAILED AND BURNT.  REPLAC	EMENT OF THE SWITCH ALLOWED THE SYSTEM TO OPERATE NORMALLY.  NOTED THAT THE SWITCH USED IS A 20-AMP SWITCH WHICH IS PROT	ECTED BY A 20 AMP CIRCUIT BREAKER.			1	L	7	2 	3O				A25CE   					 
1996121200660	19961212	00660	CE  	1996	12	12	96ZZZX6007       	1	19961107	G	2750	31B1642	TORQUE TUBE     			CESSNA	340   	340A        	2076405	CE  										FLAP ACTUATOR	DAMAGE BY SEAL  	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	6341X	3371 				340A0510				CESSNA 340A, WITH ROBERTSON STOL KIT, NOW OWNED BY SIERRA INDUSTRIES, STC SA474NW.  ALUMINUM FLAP ACTUATOR TORQUE TUBE F	OUND NEARLY SEVERED BY A WORN PRESSURIZATION SEAL.  DEFECT WAS ONLY FOUND BECAUSE OWNER REPORTED POOR PRESSURIZATION DIF	FERENTIAL AND ALL FUSELAGE LEAKS WERE BEING CORRECTED.  IT IS NOT VISIBLE WITHOUT DISASSEMBLY OF PARTS.  FAILURE OF PART	 WOULD CERTAINLY RESULT IN ASYMMETRICAL FLAPS.  SUBMITTER STATED TORQUE TUBE SHOULD HAVE A STAINLESS STEEL SLEEVE AS THE	 SOFT ALUMINUM TUBE WAS CUT BY STEEL IN THE SEAL.		1	L	7	2 	3O				3A25    					 
1996121200661	19961212	00661	SO  	1996	12	12	96ZZZX6008       	2	19961111	G	8520	646778	CONNECT ROD     			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENG	FAILED          	G				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			WP	17	732LR	1633 				21061601	512467			ENGINE OPERATED 233 HOURS OVER MFG RECOMMENDED OVERHAUL TIME OF 1400 HRS.  REF SB NR M91-8, 10JULY91.  CONNECTING ROD FA	ILED IN NORMAL CRUISE AT 8,000 FEET ALTITUDE.  ENGINE HAD A 100 HR INSPECTION WITHIN PREVIOUS 25 HRS OF OPERATION.  COMP	RESSION REPORTED 72/80 ALL CYLINDERS.  NOTE:  ENGINE HAD A PROP STRIKE IN EARLY LIFE.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
1996121200662	19961212	00662	CE  	1996	12	12	96ZZZX6009       	1	19961107	G	5320		STRUCTURE       			CESSNA	340   	340A        	2076405	CE  										RT ENG SUPPORT	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	6341X	4574 				340A0510				INSP FOUND 1.5 INCH CRACK ON AIRFRAME STRUCTURE SUPPORTING RIGHT ENGINE AND TURBOCHARGER.  CESSNA REPORTS THAT THEY HAVE	 NOT SEEN THIS PROBLEM ON 340'S, BUT THEY HAVE SEEN IT ON 400 SERIES.  THIS AIRCRAFT HAS RAM ENGINES OF INCREASED HP/STR	ESS.				1	L	7	2 	3O				3A25    					 
1996121200663	19961212	00663	SO  	1996	12	12	96ZZZX6010       	1	19961105	G	5730	6206102	SKIN            			PIPER 	PA28  	PA28181     	7102807	SO  										WING WALK PANEL	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8285Y	6248 				288190023				ROUTINE 100 HR INSPECTION REVEALED MULTIPLE CRACKS ON THE BOTTOM OF THE FWD WING WALK PANEL.  THESE CRACKS ARE FOUND AT 	THE INBD AND OTBD ENDS OF THE CORRUGATIONS STAMPED IN THE PANEL.  THESE ARE QUITE DIFFICULT TO INSPECT VISUALLY, HOWEVER	, USING YOUR HANDS, THE CRACKS CAN USUALLY BE FELT BY YOUR FINGERNAILS CATCHING ON THE EDGE OF THE CRACKS.  SUBMITTER ST	ATED THIS IS THE 6TH SUCH AIRCRAFT FOUND WITH THIS PROBLEM.  ALL AIRCRAFT WERE USED IN FLIGHT TRAINING AND HAD APPROX 5,	000 HRS TTIS.  SIMILAR CRACKS WERE ALSO FOUND IN THE AFT WING WALK PANEL.		1	L	7	1 	3O				2A13    					 
1996121200664	19961212	00664	SO  	1996	12	12	96ZZZX6011       	1	19961105	G	5730	6206104	SKIN            			PIPER 	PA28  	PA28181     	7102807	SO  										WING WALK PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8285Y	6248 				288190023				ROUTINE 100 HR INSPECTION REVEALED MULTIPLE CRACKS ON THE BOTTOM OF THE FWD WING WALK PANEL.  THESE CRACKS ARE FOUND AT 	THE INBD AND OTBD ENDS OF THE CORRUGATIONS STAMPED IN THE PANEL.  THESE ARE QUITE DIFFICULT TO INSPECT VISUALLY, HOWEVER	, USING YOUR HANDS, THE CRACKS CAN USUALLY BE FELT BY YOUR FINGERNAILS CATCHING ON THE EDGE OF THE CRACKS.  SUBMITTER ST	ATED THIS IS THE 6TH SUCH AIRCRAFT FOUND WITH THIS PROBLEM.  ALL AIRCRAFT WERE USED IN FLIGHT TRAINING AND HAD APPROX 5,	000 HRS TTIS.  SIMILAR CRACKS WERE ALSO FOUND IN THE AFT WING WALK PANEL.		1	L	7	1 	3O				2A13    					 
1996121200665	19961212	00665	CE  	1996	12	12	96ZZZX6012       	1	19960901	G	3230	08421022	BELLCRANK IDLER 			CESSNA	320   	320B        	2074508	CE  										NLG	FAILED          	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	99	99004	3677 				320B0013				UPON LOWERING LANDING GEAR, BELLCRANK IDLER FAILED NOT ALLOWING NOSE GEAR TO EXTEND FULLY AND LOCK IN POSITION.  SUSPECT	 CAUSE DUE TO METAL FATIGUE.					1	L	7	2 	3O				3A25    					 
1996121200666	19961212	00666	CE  	1996	12	12	96ZZZX6013       	1	19960919	G	3211	24411001	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										RT MLG SPLINE	CRACKED         	D		A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	09	9365D	2200 				172RG1138				RIGHT LANDING GEAR FAILED TO EXTEND TO THE DOWN AND LOCKED POSITION.  AFTER ATTEMPTS TO SECURE/ACTUATE TO SAFE DOWNLOCK 	POSITION FAILED, A SUCCESSFUL GEAR UP BELLY LANDING WAS MADE.  PROPELLER AND BELLY SKIN DAMAGE RESULTED, NO INJURY TO FL	IGHT CREW.  INSPECTION REVEALED THE RT LANDING GEAR PIVOT ASSY HAD CRACKED IN THE SPLINE AREA NEXT TO THE INNER BEARING 	RACE RESULTING IN FAILURE OF THE RT GEAR TO ACTUATE TO THE DOWNLOCK POSITION.  981 HRS SINCE PART INSPECTED PER CESSNA S	B SEB90-1.		1	H	7	1 	3O				3A17    					 
1996121200667	19961212	00667	SO  	1996	12	12	96ZZZX6014       	1	19961122	G	7160	BA6110	AIR FILTER      	BRACKETT    		MAULE 	M5    	M5235C      	5460135	SO  										INTAKE	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	01	402X	99   				7035C				DURING ANNUAL INSPECTION, FOUND BRACKETT AIR FILTER WITH ALUMINUM SCREEN.  AD 81-15-03 (EFFECTIVE 7-20-81) REQUIRED REPL	ACEMENT OF ALUMINUM SCREEN.  THIS ASSEMBLY WAS INSTALLED 5-6-87 (NEARLY 6 YEARS LATER).  ACCORDING TO AD, NO ALUMINUM SC	REENS WERE MADE AFTER AUGUST OF '78.  SUBMITTER RECOMENDATION:  REVISE AD TO INCLUDE ALL AIRCRAFT THIS FILITER ASSEMBLY 	IS NOW APPROVED FOR.  1984 CATALOG DOES NOT LIST IT AS APPROVED ON MAULE.  ROTATE STOCK AND CHECK SHELF STOCK FOR AD COM	PLIANCE.		1	H	7	1 	3O				3A23    					 
1996121200668	19961212	00668	SO  	1996	12	12	96ZZZX6015       	1	19961127	G	5751	6237201	BRACKET         			PIPER 	PA32  	PA32300     	7103212	SO  										LT AIL OB HINGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	2205U	3586 				327940064				DURING ANNUAL INSPECTION, FOUND LEFT OUTER AILERON HINGE 'SPAR SIDE' BRACKET COMPLETELY CRACKED IN RADIUS AREA WHERE ATT	ACHMENTS SCREWS ARE LOCATED.					1	L	7	1 	3O				A3SO    					 
1996121800021	19961218	00021	SO  	1996	12	18	96ZZZX6016       	1	19961023	G	2730	2020302	TORQUE TUBE     			PIPER 	PA24  	PA24250     	7102404	SO  										ELEV	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	6996P					242139				REMOVED ELEV FROM STABILATOR TUBE FOR PAINTING AIRCRAFT.  HAD TO REMOVE INSIDE BLOCK ASSY FIRST DUE TO ELEV WOULD NOT SL	IDE OFF.  ELEV WOULD NOT SLIDE OFF DUE TO RUST BUILD-UP ON STAB TUBE.  SUSPECT CAUSE OF RUST BUILD-UP IS MOISTURE IN ELE	V.  SUBMITTER RECOMMENDS REMOVAL OF ELEV ONCE EVERY 2 YEARS FOR INSP AND CLEANING OF TUBES.				1	L	7	1 	3O				1A15    					 
1996121200669	19961212	00669	SO  	1996	12	12	96ZZZX6017       	1	19961127	G	7810	6366602	PIPE            			PIPER 	PA28  	PA28140     	7102802	SO  										NR 1 CYL EXH	CRACKED         	G	S			O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	19	5677U	2346 				2826474				PILOT HEARD NOISE DURING FLIGHT.  AIRCRAFT LANDED WITHOUT INCIDENT.  FOUND NR 1 CYLINDER EXHAUST PIPE CRACKED AROUND REI	NFORCEMENT.					1	L	7	1 	3O				2A13    					 
1996121200670	19961212	00670	SO  	1996	12	12	96ZZZX6018       	1	19961115	G	5510	MS210694	NUTPLATE        		5302042501  	GULSTM	AA5   	AA5B        	3960105	SO  										HORIZ STAB	CRACKED         	B	S	A	SL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	74420	3388 				AA5B0222				DURING REPAIR OF HORIZ STAB, FOUND STRUCTURAL NUTPLATES CRACKED THROUGH THREADS.  NUTPLATES ARE USED TO ATTACH ELEVATOR 	HINGE BRACKETS AND FORWARD STAB SPAR TO FUSELAGE.  THESE PARTS CANNOT BE SEEN DURING ROUTINE INSPECTIONS.  ATTEMPTED TO 	REUSE ONE PREVIOUSLY UNCRACKED NUTPLATE WHICH CRACKED WHEN STANDARD TORQUE WAS APPLIED TO BOLT.  INSTALLED ALL NEW NUTPL	ATES AND TORQUES TO STANDARD TORQUE.  SUBMITTER STATED FAILURE OF THESE NUTPLATES COULD LEAD TO LOSS OF ELEVATOR AND/OR 	HORIZ STABILIZER.		1	L	7	1 	3O				A16EA   					 
1996121200671	19961212	00671	CE  	1996	12	12	96ZZZX6019       	1	19961121	G	3221	07436062	FORGING         			CESSNA	182   	182P        	2075816	CE  										NLG ATTACH	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	8431Q	1547 				18263546				DURING ANNUAL INSPECTION, CRACK WAS DISCOVERED IN LOWER NOSE FORGING OF NOSE GEAR.  NO OTHER DEFECTS WERE FOUND IN LANDI	NG GEAR.  TTAF 1547.					1	H	7	1 	3O			NT	TA13    					 
1996020900312	19960209	00312	CE  	1996	2	9	96ZZZX602        	1	19960113	G	2810	07213032	CAP             			CESSNA	182   	182C        	2072708	CE  										FUEL TANK	WATER LEAK      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8561T					52461				FUEL CAP LEAKED RAIN WATER THROUGH CAP WHICH HAS A BUILT-IN WATER TRAP.  SUBMITTER RECOMMENDS REPLACEMENT OF CAP AND ADA	PTER WITH DESIGN WHICH DOES NOT TRAP RAIN WATER.					1	H	7	1 	3O			NT	3A13    					 
1996121200672	19961212	00672	EA  	1996	12	12	96ZZZX6020       	2	19961120	G	8530		PISTON          			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					NR 2 CYL	HOLE IN SIDE    	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	03	771LB					61P059979632	L2086348A			DURING TEST FLIGHT, A LARGE STREAM OF OIL, FROM OIL DOOR OF RIGHT ENGINE WAS NOTICED.  SUBSEQUENTLY, ENGINE SHUT DOWN WA	S PERFORMED AND AN UNEVENTFUL LANDING WAS MADE.  TROUBLESHOOTING REVEALED A DIME SIZE HOLE IN NR 2 CYLINDER PISTON AND S	IGNS OF SEVER DETONATION.  CAUSE UNKNOWN.  ENGINE WAS REMOVED FOR REPAIR/OVERHAUL.				1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1996121200673	19961212	00673		1996	12	12	96ZZZX6021       	1	19961127	G	3320	BAO80061	BALLAST         	BRUCE       																CABIN LIGHTS	CABIN ODOR      	B	L		ZZBR	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	11										LIGHTING BALLAST RETURNED TO MFG'R FOR INSPECTION FOLLOWING A REPORTED IN FLIGHT EMERGENCY LANDING DUE TO BURNING SMELL 	IN CABIN.  AIR ONTARIO 303 REF BFM-96-11040.																		 
1996121200674	19961212	00674	NE  	1996	12	12	96ZZZX6022       	3	19961017	G	6111	RFC11N16A	BLADE PIN       	HAMSTD      		EMB   	120   	EMB120      	3260201	SO  						HAMSTD	14RF	14RF9       	NE  	PIN BOSS	CRACKED         	B			H2SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13		17344			857677					BLADE WAS RECEIVED FROM THE OPERATOR WITH A REPORT OF CRACK INDICATED AT BLADE PIN BOSS.  VISUAL EXAMINATION CONFIRMED A	 LINEAR INDICATION LOCATED AT THE RADIUS OF THE PIN BOSS-TO-BUTT AREA, APPROXIMATELY 1.300 INCHES IN LENGTH.  THE INDICA	TION ALSO EXTENDED SLIGHTLY INTO THE PLUG SEAL AREA, TO THE SNAP RING GLAND.				2	L	7	2 	4T			RT	A31SO   		6	C	P11NE	 
1996121200675	19961212	00675	CE  	1996	12	12	96ZZZX6023       	1	19961119	G	3230	MS3567514	ROLL PIN        			CESSNA	500   	500CESSNA   	2076602	CE  										EMERG EXTENSION	SHEARED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	153JP	5617 				5000153				DURING PHASE INSPECTION LANDING GEAR EMERGENCY EXTENSION CHECK - BOTTLE WOULD NOT ACTUATE AND HANDLE WOULD NOT LOCK OUT.	  FOUND GROOVED PIN INSIDE EMERG GEAR HANDLE MECHANISM BROKEN.  REPLACED PIN - SYSTEM RETESTED OK.  SUBMITTER STATED FAI	LURE WAS BELIEVED TO BE CAUSED BY IMPROPER RESET OF THE SYSTEM DURING MAINT AFTER SYSTEM ACTIVATION SEVERAL MONTHS EARLI	ER.  MM SHOULD BE CONSULTED.			1	L	7	2 	4F				A22CE   					 
1996121200676	19961212	00676	CE  	1996	12	12	96ZZZX6024       	1	19961119	G	2721	556544067	TAB ROD         			CESSNA	500   	500CESSNA   	2076602	CE  										RUD TRIM	CORRODED        	B		A	R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	153JP	5617 				500153				FOUND RUDDER TRIM TAB ACTUATOR ROD CORRODED THROUGH DUE TO CORROSION.  TUBE IS HOLLOW AND MAY HAVE CORRODED FROM THE INS	IDE OUT.  FOUND DURING LUBE REQUIREMENT OF PHASE 1 THROUGH 4 AIRFRAME INSPECTION.  REPLACED WITH NEW PART.  CLOSE INSPEC	TION OF THIS AREA SUGGESTED.				1	L	7	2 	4F				A22CE   					 
1996121200677	19961212	00677	CE  	1996	12	12	96ZZZX6025       	1	19961119	G	5711	552211210	SPAR CAP        			CESSNA	500   	500CESSNA   	2076602	CE  										RT WING	CORRODED        	B		A	R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	153JP	5617 				5000153				FOUND CORROSION ON RT WING SPAR FITTING INSIDE RT FUEL TANK WHILE C/W PHASE 50H INSPECTION AND SB 28-10 FOAM REMOVAL.  C	LEANED CORROSION TO .040 INCH DEPTH.  REMOVED ALL PITTING.  CONTRACTED FACTORY.  MAJOR REPAIR REQUIRED EVEN THOUGH AREA 	OF CORROSION WAS LESS THAN 1 SQUARE INCH.  STRAP HAD TO BE INSTALLED ON FORWARD FLANGE TO REINFORCE CORRODED AREA.  SUBM	ITTER STATED CAUSE OF CORROSION WAS DUE TO WATER CONTAINED AND TRAPPED IN FOAM COVERING THIS AREA.  SUGGEST REMOVING FOA	M AND CLOSE INSPECTION OF AREA FOR POWDERY CORROSION.		1	L	7	2 	4F				A22CE   					 
1996121200678	19961212	00678	CE  	1996	12	12	96ZZZX6026       	1	19961117	G	2730	26315041	DRAW BOLT       			LEAR  	35    	35A         	5170602	CE  										ELEV DOWN SPRING	MISMFG          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	388PD					630				ELEVATOR DRAW BOLT NEW FROM STOCK.  FWD ATTACH HOLE WAS MEASURED .323 INCH PER DRAWING NR 2631504.  THIS FWD HOLE SHOULD	 BE .316 (PLUS .004 INCH/MINUS .000 INCH).  PART NOT MADE PER SPECS.  COULD NOT USE THIS NEW PART.					2	L	7	2 	4F				A10CE   					 
1996121200679	19961212	00679	CE  	1996	12	12	96ZZZX6027       	1	19961119	G	5754	55251411	SLAT            			CESSNA	501   	501         	2076603	CE  										LT WING	CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	888MJ	7358 				5010446				DURING PHASE 1 INSPECTION FOUND LT FLAP SLAT 552S141-1 CRACKED AT WELDS AT SEVERAL PLACES.  NO SPARES AVAILABLE, HAD TO 	BE REMOVED FOR REPAIR BY MANUFACTURER DUE TO BEING MADE FROM MAGNESIUM ALLOY.  SPECIAL ATTENTION NEEDS TO BE PAID TO THI	S UNIT DURING PHASE 1 AND 2 INSPECTIONS.  SLAT REPAIRED BY WELDING.				1	L	7	2 	4F				A27CE   					 
1996121200680	19961212	00680	SW  	1996	12	12	96ZZZX6028       	1	19961112	G	2422	412075101103	INVERTER        			BELL  	412   	412EP       	1182205	SW  										STATIC AC	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6267J	10   				36130				STATIC INVERTER FAILED.  REPLACED WITH NEW STATIC INVERTER.						1	G	7	2 	4U				H4SW    					 
1996121200681	19961212	00681	SW  	1996	12	12	96ZZZX6029       	1	19961112	G	6730	212076005105	CYLINDER        			BELL  	412   	412EP       	1182205	SW  										SERVO SYS	LEAKING         	B			GS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	6267J	14   			HR9043	36130				SERVO LEAKING.  REPLACED WITH NEW CYLINDER.						1	G	7	2 	4U				H4SW    					 
1996121200682	19961212	00682		1996	12	12	96ZZZX6030       	4	19961112	G	3410	7002353913	SENSOR          			BELL  	412   	412EP       	1182205	SW  										AIR DATA	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6266T	13   			95111255	36124				AIR DATA SENSOR FAILED.  REPLACED WITH NEW AIR DATA SENSOR.						1	G	7	2 	4U				H4SW    					 
1996121200683	19961212	00683		1996	12	12	96ZZZX6031       	4	19961112	G	3421	1113034	INDICATOR       			BELL  	412   	412EP       	1182205	SW  										COCKPIT ATT	STICKS          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6266T	13   			91871	36124				ATTITUDE INDICATOR STICKS IN PITCH.  REPLACED WITH NEW ATTITUDE INDICATOR.						1	G	7	2 	4U				H4SW    					 
1996121200686	19961212	00686	SW  	1996	12	12	96ZZZX6034       	1	19961112	G	7714	407365008103	INDICATOR       			BELL  	407   	407         		SW  										DUAL TACH	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407NA	55   			0012	53012				INDICATOR FAILED.  REPLACED WITH NEW DUAL TACH IND.						1	G	7	1 	3U			O	H2SW    					 
1996121200687	19961212	00687	SW  	1996	12	12	96ZZZX6035       	1	19961112	G	2844	407375007101	INDICATOR       			BELL  	407   	407         		SW  										FUEL PRESS	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6198V	13   			0026	53020				INDICATOR FAILED.  REPLACED WITH NEW FUEL PRESSURE IND.						1	G	7	1 	3U			O	H2SW    					 
1996121200688	19961212	00688	SW  	1996	12	12	96ZZZX6036       	1	19961112	G	6220	206011005015	COLLAR SET      			BELL  	206   	206L4       	1182110	SW  										M/R	MIS MFG         	B			GS1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	62673	17   	17   			52176				INSP FOUND M/R COLLAR SET DEFECTIVE.  REPLACED WITH NEW COLLAR SET.						1	G	7	1 	3U			NC	H2SW    					 
1996121200690	19961212	00690	SW  	1996	12	12	96ZZZX6038       	1	19961112	G	6220	222031662105	ROD END BEARING 			BELL  	222   	222U        	1182140	SW  										M/R	DEFECTIVE       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	911EC	256  			0843	47505				INSP FOUND ROD END BEARING DEFECTIVE.  REPLACED WITH NEW ROD END BEARING.						1	G	7	2 	3U				H9SW    					 
1996020900314	19960209	00314	CE  	1996	2	9	96ZZZX604        	1	19960105	G	2710		CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  										RIGHT AILERON	FAILED          	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	21258	2220 				17263917				ON NOVEMBER 11, 1995, AIRCRAFT EXPERIENCED WIND GUSTS AS HIGH AS 70 MPH FROM THE SOUTHEAST.  THE AIRPLANE WAS TIED DOWN 	HEADING 330 DEGREES AND BOTH THE RUDDER GUST LOCK AND THE PIN IN THE YOKE WERE IN PLACE.  THE NEXT DAY, THE RIGHT AILERO	N WAS DROOPING SLIGHTLY AND UPON GRASPING IT, THERE WAS NO QUESTION OF A SERIOUS PROBLEM.  UPON DISASSEMBLY, THE SHOP FO	UND THE RIGHT AILERON CABLE BROKEN COMPLETELY.  THERE WAS EVIDENCE OF CONSIDERABLE RUST WHERE THE CABLE RUNS OVER THE OV	ERHEAD PULLEY AND IT IS PROBABLE SOME STRANDS OF THE CABLE WERE ALREADY BROKEN.  IT ALSO APPEARED THE PULLEY ITSELF WAS 	FROZEN OR TURNED VERY HARD.  EVERYTHING ON THE LEFT SIDE WAS OKAY.	1	H	7	1 	3O			NT	3A12    					 
1996020900315	19960209	00315	NE  	1996	2	9	96ZZZX605        	2	19960115	G	7261	65B90115176	OIL TUBE        			BOEING	747   	7472B4B     	138481B	NM  	PWA   	JT9   	JT9D7J      	52054	NE  					NR 1 ENG PRESS	CRACKED         	H	L	A		A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			K			FLUID LOSS                			CR	CRUISE         	1			SW	99	202AE					21097	689476			AIRCRAFT EXPERIENCED HEAVY OIL LOSS ON NR 1 ENGINE 40 MINUTES AFTER TAKEOFF WHICH RESULTED IN NR 1 ENGINE IFSD AND ACFT 	AIR TURN BACK.  UPON ACFT ARRIVAL, BEY GROUND INVESTIGATION REVEALED CRACKED NR 1 ENGINE DELTA PRESSURE SWITCH OIL TUBE.	  ITEM 150 REF:  IPC 79 - 31 - 02 - 01, PAGE 1, NO EVIDENCE OF CHAFING OR INTERFERING.  PIPE ASSY REPLACED AND ACFT RETU	RNED TO SERVICE.			2	L	7	4 	4F	4	F	RT	A20WE   	E20EA				 
1996020900316	19960209	00316		1996	2	9	96ZZZX606        	4	19960108	G	3160	EFD871	MFD             	COLLINS     		BEECH 	MU300 	400BEECH    		CE  										COCKPIT	FAILED          	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	440DS	1152 			369	RK8				FOUND MULTI-FUNCTION DISPLAY (MFD) FOR A 3-TUBE COLLINS SYSTEM, ON THE LEFT SIDE OF THE MFD, THE AIR INLET FOR COOLING I	S 75 PERCENT OR MORE COVERED WITH LINT, DIRT, AND CARPET FIBERS.  THE COOLING FANS OR EACH CRT IN THE COCKPIT DO NOT HAV	E ANY KIND OF FILTER TO PREVENT THIS PROBLEM BEFORE REACHING THE UNITS.  SUBMITTER STATED OPERATORS SHOULD CHECK THIS TO	 PREVENT OVERHEAT FAILURES.			2	H	7	2 	4F			RT	A16SW   					 
1996020900317	19960209	00317	CE  	1996	2	9	96ZZZX607        	1	19960122	G	2430	BD161	CONNECTOR       	ELCON       		CESSNA	500   	S550        	2076607	CE  										BATTERY	CORRODED        	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	98QS	8667 				S5500098				CREW REPORTED THEY COULD NOT BATTERY START ENGINE.  FOUND BATTERY CONNECTOR CORRODED AND BURNED.  REMOVED AND REPLACED E	LCON CONNECTOR AND REPLACED BATTERY.  CONNECTOR FAILED GO, NO-GO CHECK.  LOOSE CONNECTOR CAUSED ARCING AND CORROSION.					1	L	7	2 	4F			RT	A22CE   					 
1996121900272	19961219	00272	CE  	1996	12	19	96ZZZX6072       	1	19961011	G	7160	1019100207	DOOR SEAL       			BEECH 	200   	B200        	1152922	CE  										ICE VANE DOOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	200PU	1117 				BB1477				BRISTLE MATERIAL ON SIDE OF INLET COWLING THAT SEALS ICE DEFLECTOR DOOR CAME LOOSE FROM ITS RETAINER STRIP SENDING NYLON	 HAIRS TOWARD ENGINE INLET SCREEN.  A LARGE VOLUME OF THE HAIRS WERE INJESTED BY THE ENGINE AND ENGINE WAS SPLIT AT THE 	'C' FLANGE FOR INSPECTION AFTER THE OCCURRENCE.  MELTED NYLON MATERIAL WAS FOUND IN ENGINE, BUT NO OTHER DAMAGE.				1	L	7	2 	4T				A24CE   					 
1996121900274	19961219	00274	CE  	1996	12	19	96ZZZX6074       	1	19961121	G	5610	5042006930	WINDSHIELD      	PPG         		BEECH 	90    	C90         	1152913	CE  										OUTER PANE	CRACKED         	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	01	660GW	5005 			84H10209	LJ673				WINDSHIELD OUTER HEATED PANE CRACKED.  CAUSE:  ICE BUILD-UP, PILOT SELECTED ELECT. HEAT ON, AND FULL WINDSHIELD DEFROST.	  OUTER PANE CRACKED FROM POSSIBLE OLD AGE, PRESSURE CYCLES, AND HEAT SHOCK DUE TO DIFFERENTIAL IN OAT AND HEAT APPLIED 	TO INSIDE.				1	L	7	2 	3T				3A20    					 
1996121900275	19961219	00275	NM  	1996	12	19	96ZZZX6075       	1	19961114	G	5313		STRINGER        			BOEING	727   	727225      	1384077	NM  										BS 940 18A LT	CRACKED         	B			XE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	806MA					22437				FOUND 1.25 INCH CRACK IN STR 18A LT AT AFT LOWER ATTACH BOLT HOLE TO BS 940 FITTING.						2	L	7	3 	4F				A3WE    					 
1996121900276	19961219	00276	NM  	1996	12	19	96ZZZX6076       	1	19961114	G	2782	69734941	SEAL PLATE      		65447607    	BOEING	737   	7373B7      	1384580	NM  										SLAT ACTUATOR	DETERIORATED    	B			IU6R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01					0240					SLAT ACTUATOR HAS BEEN IN REPAIR TWICE ON WARRANTY.  BOTH TIMES SEAL PLATES WERE CA USING UNIT TO LEAK.						2	L	7	2 	4F			RT	A16WE   					 
1996121900277	19961219	00277	NM  	1996	12	19	96ZZZX6077       	1	19961114	G	2782	69734961	SEAL PLATE      			BOEING	737   	7373B7      	1384580	NM  										SLAT ACTUATOR	DETERIORATED    	B			IU6R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01										SLAT ACTUATOR HAS BEEN IN REPAIR TWICE ON WARRANTY.  BOTH TIMES SEAL PLATES WERE CAUSING UNIT TO LEAK.						2	L	7	2 	4F			RT	A16WE   					 
1996121900278	19961219	00278	NM  	1996	12	19	96ZZZX6078       	1	19961112	G	2720	65448671	PISTON          		65448617    	BOEING	737   	7372A6      	138448B	NM  										RUDDER PCU	CHROME CHIPPED  	B	L		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					777A					THE CHROME PLATING ON THE CHAMFER IS CHIPPED OFF CAUSING CHROME PARTICLES TO FLOW THROUGHOUT THE INSIDE OF THE UNIT.  TH	IS WAS CAUSED WHEN THE FWD PISTON (FIG 1103 IT. 14) WAS TORQUED ONTO THE AFT PISTON AND THE CHROME ON THE CHAMFER CHIPPE	D OFF DUE TO PRESSURE.  RECOMMENDATION:  HAVE ZERO CHROME RUN OUT ON CHAMFER WHEN RECHROMED.				2	L	7	2 	4F				A16WE   					 
1996121900279	19961219	00279	GL  	1996	12	19	96ZZZX6079       	3	19961129	G	6114	C2835C23	HUB             													MCAULY	2A36C	2A36C23     	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			238  					671575		PROPELLER RECEIVED FOR INSPECTION DUE TO RED DYE OIL LEAK.  AD NOTE 89-26-08 WAS C/W.  AFTER DISASSEMBLY, HUB WAS STRIPP	ED AND A CRACK DISCOVERED IN NR 2 BLADE SOCKET, THREE THREADS IN 6 TO 7 O'CLOCK POSITION ABOUT .50 INCH LONG CRACK DISCO	VERED USING A 10X POWER MICROSCOPE.														5	C	P880	 
1996020900318	19960209	00318	NE  	1996	2	9	96ZZZX608        	2	19960122	G	7412	3033378A	EXCITER         	LUCAS       		CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LEFT IGNITION	SHORTED         	B			CWQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	98QS	8667 			K8951	S5500098				FLIGHT CREW REPORTED LEFT IGNITION CIRCUIT BREAKER TRIPS.  DISCONNECTED UPPER IGNITION EXCITER BOX.  CIRCUIT BREAKER STA	YED IN AND OTHER EXCITER BOX CHECKED SATISFACTORY.  REMOVED AND REPLACED.  INTERNAL SHORT IN IGNITION EXCITER BOX.					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
1996121900280	19961219	00280	EA  	1996	12	19	96ZZZX6080       	2	19961202	G	7414	ES10382681	CAPACITOR       		D3000       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT MAG	FAILED          	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SO	01	135JP					7952034				LT MAG CAPACITOR P/N ES10-382681, FAILED.  FOUND CENTER THREADED PORTION LOOSE FROM OUTER PART.  MAG DROP WAS 400 PLUS. 	 NEW TCM 10-382681 FIXED IT.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996121900281	19961219	00281	SO  	1996	12	19	96ZZZX6081       	1	19961127	G	7120	6871000	MOUNT           			PIPER 	PA32  	PA32300     	7103212	SO  										LOW LT MT BRACE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	2205U	3586 				327940064				DURING ANNUAL INSPECTION FOUND LOWER LEFT ENGINE MOUNT BRACE CRACKED AT NOSE GEAR STRUT HOUSING WELD.						1	L	7	1 	3O				A3SO    					 
1996121900282	19961219	00282	EA  	1996	12	19	96ZZZX6082       	2	19961122	G	8530	71894	VALVE SEAT      			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 5 CYL EXH	LOOSE           	B			EKIR	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	07	252MA					31P33	L52162			ENGINE RUN-UP AND ROUGH.  CHECKED COMPRESSION, FOUND NR 5 CYLINDER 0/80.  REMOVED CYLINDER, FOUND EXHAUST VALVE SEAT LOO	SE IN HEAD FOLLOWING VALVE DURING VALVE MOVEMENT.					1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1996121900283	19961219	00283	SO  	1996	12	19	96ZZZX6083       	1	19961122	G	3211	6704213	TRUNNION FITTING			PIPER 	PA44  	PA44180     	7104402	SO  										MLG RT AFT	CRACKED         	B	S		YXUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3062H	5861 				447995165				FOUND CRACK ON 100-HR INSPECTION.						1	L	7	2 	3O				A19S0   					 
1996121900284	19961219	00284	SO  	1996	12	19	96ZZZX6084       	1	19961116	G	2460		POWER BUSS      			PIPER 	PA34  	PA34200T    	7103406	SO  										AVIONICS MASTER	LOOSE CONNECTION	B			HBKR	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	11	33809					347570165				AVIONICS FAILED IN-FLIGHT.  TROUBLESHOT AND FOUND SEVERAL BAD CONNECTIONS IN AVIONICS MASTER POWER BUSS.  REPAIRED ALL O	PEN CONNECTIONS.  CHECKED GOOD.  APPARENT PROBLEM WAS CORROSION ON CONNECTOR.					1	L	7	2 	3O				A7SO    					 
1996121900285	19961219	00285	SO  	1996	12	19	96ZZZX6085       	1	19961106	G	3230	4179300	FORK ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG DOWNLOCK	BROKE           	D		A		A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	01	3535F					317952200				UPON PILOT CYCLING GEAR UP, RT GEAR STAYED EXTENDED AND DOWN, GREEN LIGHT REMAINED ON.  PILOT RETURNED AND LANDED WITH N	O INCIDENT.  UPON MAINT INSPECTION, RT GEAR DOWNLOCK ROD FORK WAS FOUND BROKEN.  ROD FORK BOLT WAS NOT WORN AS IS A USUA	L FINDING.  MAINT. REMOVED THESE AT DETAILED GEAR INSPECTIONS TO CHECK WEAR.  THIS SUMITTER BELIEVES FORK BOLT WAS OVERT	ORQUED DURING INSTALLATION AND CRACKED AT THAT TIME.  SUBMITTER RECOMMENDS ENSURING PROPER AMOUNT OF WASHERS ARE USED TO	 KEEP NUT FROM BOTTOMING OUT, AS WELL AS ENSURING THAT FORK WILL TURN FREELY WHEN INSTALLED.		1	L	7	2 	3O				A20SO   					 
1996121900286	19961219	00286	SO  	1996	12	19	96ZZZX6086       	1	19961121	G	2822	2B663	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										FUEL BOOST	FAILED          	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	36PB				2E79	317405128				BOOST PUMP INOPERATIVE.  ELECTRIC MOTOR DOES NOT RUN.						1	L	7	2 	3O				A20SO   					 
1996121900287	19961219	00287	SO  	1996	12	19	96ZZZX6087       	1	19961120	G	3710	442CW6	PUMP            	AIRBORNE    		PIPER 	PA34  	PA34200T    	7103406	SO  										PNEU SYS	SEIZED          	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	36319	540  			8AK501	347870318				PUMP SEIZED AND DRIVE SHAFT BROKEN.						1	L	7	2 	3O				A7SO    					 
1996121900288	19961219	00288		1996	12	19	96ZZZX6088       	4	19961125	G	2350		COIL CORD       			PIPER 	PA31  	PA31350     	7103110	SO  										PILOT YOKE	SET PARK BRAKE  	B		A	APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	36PB					317405128				AIRCRAFT STUCK ON RUNWAY DUE TO 'LOCKED BRAKES' ON TWO FLIGHTS.  MAINTENANCE FOUND NO DEFECTS IN BRAKE SYSTEMS.  FOUND P	USH TO TALK COIL CORD FROM PILOT'S YOKE WOULD WRAP AROUND PARKING BRAKE 'T' HANDLE AND ENGAGE PARKING BRAKE WHEN YOKE PU	LLED AFT.				1	L	7	2 	3O				A20SO   					 
1996121900289	19961219	00289	EA  	1996	12	19	96ZZZX6089       	2	19961109	G	8530	73806	PUSH ROD        			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 CYL INT	BENT            	D	P			A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SW	15	38PT	3616 				3878A0042	L1533715			PILOT NOTED A SUDDEN ROUGHNESS IN THE ENGINE FOLLOWED BY A 200-300 RPM LOSS.  MADE A SAFE EMERGENCY LANDING.  DISPATCHED	 A MECHANIC TO DETERMINE CAUSE.  THE INTAKE PUSHROD AND TUBE WERE SEVERELY BENT.  THE LOWER SPARK PLUG WAS BADLY LEAD FO	ULED.  SUSPECT CAUSE WAS DETERMINED TO BE EITHER DETONATION OR THE INTAKE VALVE STICKING MOMENTARILY.  THE ENGINE WAS RE	MOVED FOR OVERHAUL.			1	L	7	1 	3O	3	O		A18SO   	E223				 
1996121900290	19961219	00290	SO  	1996	12	19	96ZZZX6090       	1	19961120	G	3710	2H2211	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  										PNEU SYS	LEAKING         	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	40ST				7E911	317405183				PNEUMATIC REGULATOR LEAKS BADLY AT LOW PRESSURE SIDE.  KEEPS PNEUMATIC SYSTEM FROM DEVELOPING PRESSURE.						1	L	7	2 	3O				A20SO   					 
1996121900291	19961219	00291	SO  	1996	12	19	96ZZZX6091       	1	19961120	G	3710	441CC7	PUMP            			PIPER 	PA34  	PA34200T    	7103406	SO  										LT ENG PNEU	SEIZED          	B			APCR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	01	4490F	571  			10AK759	347670339				LEFT ENGINE PNEUMATIC PUMP SEIZED AND FAILED DURING PNEUMATIC DE-ICE OPERATION DURING IFR/ICING CONDITIONS.						1	L	7	2 	3O				A7SO    					 
1996121900292	19961219	00292		1996	12	19	96ZZZX6092       	3	19961204	G	6112	RA12884	DEICE BOOT      	RAPCO       		BEECH 	80    	65A80       	1152808	CE  										PROP	WIRES BREAK     	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	55SA					LD243				PROP DE-ICE BOOT OTB, INB, AND GRD WIRES BREAK 12 INCHES FROM THE TERMINALS.  THE LEAD IS REQUIRED TO BEND IN THIS AREA.	  THIS IS THE 8TH BOOT WHICH HAS FAILED IN THIS AREA IN THE LAST TWO WEEKS.					1	L	7	2 	3O				3A20    					 
1996121900293	19961219	00293	CE  	1996	12	19	96ZZZX6093       	1	19961120	G	3230	20430156	BOLT            			CESSNA	177   	177RG       	2073709	CE  										DRAG LINK	BROKEN          	B	S		MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	53257					177RG1363				INSP FOUND DRAG LINK ASSY BOLT BROKEN.						1	H	7	1 	3O				A20CE   					 
1996121900294	19961219	00294	SO  	1996	12	19	96ZZZX6094       	1	19960831	G	3230	2572000	GEAR EXTENSION  			PIPER 	PA24  	PA24250     	7102404	SO  										MLG	MOTOR FAILED    	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NM	11	5909P					24995				THE LANDING GEAR WOULD NOT FULLY EXTEND OR RETRACT WITH THE ELECTRICAL SYSTEM.  THE EMERGENCY SYSTEM WAS ACTUATED AND DI	D NOT EXTEND THE GEAR.  IT WAS DETERMINED THE LANDING GEAR MOTOR FAILED TO FUNCTION UNDER THE LOAD REQUIRED TO ACTUATE T	HE GEAR.  AFTER EXTENSIVE INSP AND OPERATION OF THE EMERGENCY GEAR SYSTEM, IT WAS UNDETERMINED AS TO WHY THE GEAR FAILED	 TO EXTEND.  IT IS SPECULATED EMERGENCY GEAR EXT WAS ACTUATED WITH THE GEAR PARTIALLY EXTENDED.  THIS IS BASED ON THE FA	CT WHEN THE AIRCRAFT WAS JACKED FOR RECOVERY, THE LINKAGE WAS RELEASED BY THE MECHANIC AND THE GEAR EXTENDED FULLY.		1	L	7	1 	3O				1A15    					 
1996121900295	19961219	00295	EA  	1996	12	19	96ZZZX6095       	1	19961202	G	3230	555402	SELECTOR VALVE  			CNDAIR	CL600 	CL6002A12   	1900304	EA  										NLG	MALFUNCTION     	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	601TX				303	3005				THE NOSE GEAR SELECTOR VALVE FAILS ON THE RETRACT MODE.  IF IT FAILS AFTER THE GEAR HAS ALREADY EXT., THE ONLY SYMPTOM I	S A LOSS OF NOSE STEERING.  NOSE STEERI NG CAN BE MEL'D.  IF THE AIRCRAFT DISPATCHES PER THE MEL, THE NOSE GEAR WILL RET	RACT, BUT WILL NOT EXTEND NORMALLY.  A MANUAL FREE FALL WOULD HAVE TO BE PERFORMED.				2	L	7	2 	4F			RT	A21EA   					 
1996121900296	19961219	00296	CE  	1996	12	19	96ZZZX6096       	1	19961113	G	3211	24411001	FITTING         			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	6352V					172RG0640				DURING 100 HR INSPECTION, MECHANIC NOTICED PAINT MISSING FROM AROUND AREA THAT ALUMINUM CASTING (FITTING, AXLE) ATTACHES	 TO MAIN GEAR LEG - CLOSER INSPECTION OF THIS AREA REVEALED CRACK RUNNING FROM TOP OF CASTING DOWN TO ATTACH BOLT HOLE. 	 ZYGLO FOUND DEFINITE CRACK COMPLETELY THROUGH CASTING.  AIRCRAFT IS TRAINING AIRCRAFT AND PART AFFECTED IS BELIEVED TO 	BE ORIGINAL PART.			1	H	7	1 	3O				3A17    					 
1996121900297	19961219	00297	SO  	1996	12	19	96ZZZX6097       	2	19961126	G	7314	6462108	PUMP            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					RT ENG FUEL	FAILED          	B		A	FE6R	O				OTHER                   				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			NM	11	7011X				J20902513	402C0255	L290329R			ON TAKEOFF ROLL, THE RIGHT ENGINE QUIT. THE PILOT MADE REJECTED TAKEOFF PROCEDURES.  NO DAMAGE TO A/C OR PERSONAL.  INVE	STIGATION SHOWED THE ENG DRIVEN PUMP FAILED.  A TEAR DOWN INSPECTION REVEALED SOME WEAR AND TWO BROKEN BLADES.  NO CONCL	USIONS WERE DRAWN ON THE CAUSE FOR FAILURE.  THERE WERE NO INDICATIONS PRIOR TO FAILURE.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996121900298	19961219	00298	EA  	1996	12	19	96ZZZX6098       	2	19961024	G	8520	74644	ROD BOLT        			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2B5    	41532	EA  					NR 4 CYL	STRIPPED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	7545Z		51   			253591	L988640			ROD BOLT APPEARS TO BE TOO SOFT.  THREADS STRIPPED CAUSING NR 4 CONNECTING ROD CAP TO COME LOOSE MAKING CONTACT WITH CAS	E AND NR 3 PISTON.  THIS CAUSED MAJOR DAMAGE TO ENGINE.					1	L	7	1 	3O	3	O		2A10    	E295				 
1996121900299	19961219	00299	EA  	1996	12	19	96ZZZX6099       	2	19961122	G	8520	75637	COUNTER WEIGHT  			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 5 CYL	CRACKED         	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	252MA		641  		75670	31P33	L52162			PULLED SUCTION SCREEN FOLLOWING OIL CHANGE, FOUND BROKEN PIECE OF SNAP RING, P/N 71906.  REMOVED SUMP, FOUND COUNTER WT 	NR 5 SNAP RING AFT SIDE INBOARD BROKE AND COUNTER WT CRACKED AT BUSHING HOLE.  SCREEN WAS PULLED FOLLOWING FAILURE OF NR	 5 CYL (DROPPED EXHAUST VALVE SEAT).				1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1996121900300	19961219	00300	SO  	1996	12	19	96ZZZX6100       	2	19961121	G	7322	63357310	FUEL CONTROL    			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					RT ENG MIX	DEFECTIVE       	B			APCR	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			NM	01	48SA		706  		G119402AR	4040417	276387R			PILOT REPORTED ENGINE STUMBLE ON TAKEOFF AND AT CLIMB POWER SETTING.  EXTENSIVE TROUBLESHOOTING FOUND LOOSE BUSHING AT R	IGHT ENGINE.  MIXTURE CONTROL SHAFT INSTALLED USED SERVICEABLE FUEL CONTROL ASSY.  TEST FLOWN OK.					1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996121900301	19961219	00301	CE  	1996	12	19	96ZZZX6101       	1	19961023	G	5320	521304029	TEE STRUCTURE   			CESSNA	441   	441         	2076020	CE  										NLG TUNNEL	CRACKED         	B		A	DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	489CE	4902 				4410027				NOSE GEAR TUNNEL FORWARD SUPPORT 'TEE' WAS FOUND CRACKED IN THE RADIUS OF THE 'TEE' STRUCTURE.  THIS IS THE THIRD CRACKE	D 'TEE' THAT HAS BEEN FOUND ON THIS TYPE OF AIRCRAFT.  SUSPECT GROUND HANDLING MAY CONTRIBUTE TO CAUSE.  INSPECT ANYTIME	 NOSE BAY FLOORS ARE REMOVED.				1	L	7	2 	3T			RT	A28CE   					 
1996121900302	19961219	00302	SO  	1996	12	19	96ZZZX6102       	2	19961202	G	7310	6343264	MANIFOLD        			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENG FUEL	CLOGGED         	B			AM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	69520		20   		A167532C	3400353	311659			FUEL MANIFOLD WAS ONLY ABLE TO SUPPLY FUEL TO 3 OF THE ENGINES CYLINDER.  THREE OF THE FUEL LINES WERE CLOGGED.  THE MAN	IFOLD HAD LESS THAN 20 HRS SINCE OVERHAUL.					1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996121900303	19961219	00303		1996	12	19	96ZZZX6103       	4	19961121	G	3418	C522074	LIFT DETECTOR   	SAFEFLIGHT  		PIPER 	PA31  	PA31350     	7103110	SO  										RT WING SWITCH	WATER CONTAM    	B			APCR	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			NM	01	777KT				330937	317552053				STALL VANE/LIFT DETECTOR GAVE COUNTINUOUS STALL WARNING DUE TO WATER ENTRY INTO SWITCH.  2ND FAILURE.  OPERATOR HAS NUME	ROUS FAILURES OF SAME TYPE VANES WHENEVER AIRCRAFT FLY IN RAIN.  SUBMITTER STATED UNITS NEED TO BE WATERPROOFED.  VERY D	ANGEROUS FAILURE MODE, AS PILOT'S MUST PULL CIRCUIT BREAKER TO SHUT OFF STALL HORN, WHICH LEAVES THEM NO STALL WARNING A	T ALL.			1	L	7	2 	3O				A20SO   					 
1996121900304	19961219	00304		1996	12	19	96ZZZX6104       	4	19961120	G	3418	C522074	LIFT DETECTOR   	SAFEFLIGHT  		PIPER 	PA31  	PA31350     	7103110	SO  										RT WING SWITCH	WATER CONTAM    	B			APCR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	777KT					317552053				STALL VANE/LIFT DETECTOR GAVE CONTINUOUS STALL WARNING DUE TO WATER ENTRY INTO SWITCH.  SUBMITTER STATED OPERATOR HAS NU	MEROUS FAILURES OF SAME TYPE UNITS WHENEVER IT RAINS.  UNITS NEED TO BE WATERPROOFED.  1ST FAILURE.					1	L	7	2 	3O				A20SO   					 
1996121900305	19961219	00305	SO  	1996	12	19	96ZZZX6105       	1	19961119	G	3230		NOSE GEAR       			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG WELL	FROZEN          	B		A	APCR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	8407C	15429				347670137				AIRCRAFT DEPARTED BOEING FIELD WITH SNOW ON TAXIWAY AND RUNWAY.  SNOW SLUSH ENTERED NOSE WHEEL WELL AND FROZE GEAR IN 'U	P' POSITION.  AIRCRAFT LANDED ON RUNWAY WITH MAINS DOWN AND NOSE GEAR UP.  MODERATE DAMAGE TO NOSE CONE FROM RUNWAY CONT	ACT.				1	L	7	2 	3O				A7SO    					 
1996121900306	19961219	00306	SO  	1996	12	19	96ZZZX6106       	1	19961120	G	2434	ALX9425	ALTERNATOR      	PRESTOLITE  		PIPER 	PA34  	PA34200T    	7103406	SO  										DRIVE END	CASE CRACKED    	B	S		APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8407C		49   		A112746	347670137				ALTERNATOR REMOVED DUE TO DEFECTIVE DIODES, BUT ALSO FOUND CRACK IN CASE AT DRIVE END.						1	L	7	2 	3O				A7SO    					 
1996121900307	19961219	00307	SO  	1996	12	19	96ZZZX6107       	2	19961112	G	8520		CONNECT ROD     			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470VO     	17026	SO  					NR 5-6 CYL	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			SO	03	7700Q		1180 			310Q0410	L149140VO			AFTER DEPARTURE, OIL PRESSURE ON RIGHT ENGINE DROPPED.  ENGINE BEGAN TO SMOKE POSSIBLE BLEED OIL FIRE AND SMOKE WERE NOT	ED.  ENGINE WAS SHUT DOWN AND FEATHERED.  NORMAL LANDING WAS MADE.  DAMAGE TO AIRCRAFT RESTRICTED TO ENGINE AND PROP.  F	IRST INSPECTION REVEALED NR 6 AND NR 5 RODS BROKEN WITH A PORTION OF BOTH CASE HALVES EJECTED FROM THE TOP OF THE MOTOR.	  PROP HAS SEVERAL NICKS POSSIBLY CAUSED BY EJECTED MATERIAL.			1	L	7	2 	3O	3	O		3A10    	3E1				 
1996121900308	19961219	00308	CE  	1996	12	19	96ZZZX6108       	1	19961119	G	7120	255100317	MOUNT           			CESSNA	303   	T303        	2073820	CE  										RT ENG	CORRODED        	B		A	FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	727RT	1413 				T30300090				FOUND SEVERE CORROSION ON THE ENGINE MOUNT, BELOW THE ENGINE SUPERCHARGER, ON THE RIGHT ENGINE.  THE ENGINE MOUNT HAS BE	EN PREVIOUSLY REPAIRED, WITH A FISHMOUTH REINFORCEMENT, FOR PRESUMABLY THE SAME PROBLEM.  THE LEFT ENGINE MOUNT HAS THE 	SAME PROBLEM BUT IS NOT AS SEVERE.  CORROSION AND RUST HAVE PENETRATED THE REPAIR.  THE ENGINE MOUNT IS AGAIN REPAIRED B	UT BY REPLACEMENT OF ENTIRE TUBE SECTIONS.  MOST INSTALLATIONS OF THIS TYPE HAVE A HEAT SHIELD INSTALLED.			1	L	7	2 	3O				A34CE   					 
1996121900341	19961219	00341	NM  	1996	12	19	96ZZZX6109       	1	19961202	G	3320	BR63031021	LUMINAIRE       	BRUCE       		DHAV  	DHC8  	DHC8102     	2809003	NM  										CABIN	BURN DAMAGE     	B			ZZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	934HA					139				PIEDMONT AIRLINES RETURNED LIGHTING UNIT FOR ARCING AND BURN DAMAGE AT LAMP HOLDER.						2	H	7	2 	4T			RT	A13NM   					 
1996020900627	19960209	00627	WP  	1996	2	9	96ZZZX611        	1	19960119	G	6220	369H120321	LEAD LAG LINK   			HUGHES	369   	369D        	4470706	WP  										M/R	CRACKED         	B			MMZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	88SE	2027 			1888	800775D				INSPECTION FOUND BUSHING LOOSE AND CRACK IN LEAD LAG LINK ORIGINATING FROM BUSHING.						1	G	7	1 	3U				H3WE    					 
1996121900744	19961219	00744	EU  	1996	12	19	96ZZZX6110       	1	19960819	G	5720	21211151102	STIFFENER       			CASA  	C212  	C212CC      	2410204	EU  										WING FALSE SPAR	CRACKED         	B			ST9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	349TA	3244 				349				INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED.  REFERENCE CASA COM LETTER 212-224.						2	H	7	2 	4T				A43EU   					 
1996121900745	19961219	00745	EU  	1996	12	19	96ZZZX6111       	1	19960819	G	5720	21211151142	STIFFENER       			CASA  	C212  	C212CC      	2410204	EU  										WING FALSE SPAR	CRACKED         	B			ST9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	349TA	3244 				349				INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED.  REFERENCE CASA COM LETTER 212-224.						2	H	7	2 	4T				A43EU   					 
1996121900746	19961219	00746	EU  	1996	12	19	96ZZZX6112       	1	19960819	G	5720	21211151122	STIFFENER       			CASA  	C212  	C212CC      	2410204	EU  										WING FALSE SPAR	CRACKED         	B			ST9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	349TA	3244 				349				INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED.  REFERENCE CASA COM LETTER 212-224.						2	H	7	2 	4T				A43EU   					 
1996121900747	19961219	00747	EU  	1996	12	19	96ZZZX6113       	1	19960819	G	5720	21211151112	STIFFENER       			CASA  	C212  	C212CC      	2410204	EU  										WING FALSE SPAR	CRACKED         	B			ST9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	349TA	3244 				349				INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED.  REFERENCE CASA COM LETTER 212-224.						2	H	7	2 	4T				A43EU   					 
1996121900748	19961219	00748	EU  	1996	12	19	96ZZZX6114       	1	19960819	G	5720	21211151062	STIFFENER       			CASA  	C212  	C212CC      	2410204	EU  										WING FALSE SPAR	CRACKED         	B			ST9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	349TA	3244 				349				INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED.  REFERENCE CASA COM LETTER 212-224.						2	H	7	2 	4T				A43EU   					 
1996121900749	19961219	00749	EU  	1996	12	19	96ZZZX6115       	1	19960819	G	5720	21211151072	STIFFENER       			CASA  	C212  	C212CC      	2410204	EU  										WING FALSE SPAR	CRACKED         	B			ST9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	349TA	3244 				349				INSP FOUND STIFFENERS LOCATED ON REAR FALSE SPAR CRACKED.  REFERENCE CASA COM LETTER 212-224.						2	H	7	2 	4T				A43EU   					 
1996121900750	19961219	00750	SW  	1996	12	19	96ZZZX6116       	1	19961112	G	7712	430375009101	INDICATOR       			BELL  	430   	430         	1182150	SW  										TRIPLE TORQ	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6283T	21   			E006	49007				INDICATOR FAILED.  REPLACED WITH NEW TRIPLE TORQUE IND.						1	G	7	2 	3U			RT	H9SW    					 
1996121900752	19961219	00752	EA  	1996	12	19	96ZZZX6118       	1	19961114	G	3320	2927300	CAPACITOR       	BRUCE       	BR95005     	CNDAIR	CL600 	CL6002B19   		EA  										CABIN	FAILED          	B	L		ZZBR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			WP	11	411SW					7067				BALLAST UNIT RECEIVED FOR INSP FOLLOWING REPORT OF CABIN SMOKE.  FOUND CAPACITOR C1 FAILED.						2	L	7	2 	4F			RT	A21EA   					 
1996121900753	19961219	00753	SO  	1996	12	19	96ZZZX6119       	1	19961202	G	3320	BC10047005	LUMINAIRE       	BRUCE       	BR99002     	EMB   	120   	EMB120ER    	3260203	SO  										LAMP HOLDER	BURN DAMAGE     	B			ZZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	214SW					120280				ULTRALIGHT LIGHTING SYSTEM FROM SKYWEST RETURNED FOR 'BROKEN END'.  BURN DAMAGE AT LAMP HOLDER NOTED AT INITIAL INSP.						2	L	7	2 	4T			RT	A31SO   					 
1996020900628	19960209	00628	WP  	1996	2	9	96ZZZX612        	1	19960117	G	6210	369D21100516	BLADE           			HUGHES	369   	369D        	4470706	WP  										M/R	DELAMINATED     	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5313Y	596  			2022226095	490496D				DURING ANNUAL INSPECTION, FOUND M/R BLADE WAS DELAMINATED UNDER THE ABRASION STRIP ON THE UPPER SURFACE OF THE BLADE FOR	 ABOUT 6 SQUARE INCHES.  BLADE REMOVED AND SENT IN FOR REPAIR.					1	G	7	1 	3U				H3WE    					 
1996121900754	19961219	00754	SW  	1996	12	19	96ZZZX6120       	1	19961101	G	7120	2762114083	MOUNT           			SWRNGN	SA227 	SA227AC     	8780603	SW  										ENG TRUSS	CRACKED         	B		A	H7NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17					407012					CRACK IN THE TUBE P/N 27-62114-021 WHERE IT IS MATED TO TUBES P/N 27-62114-019 AND 27-62114-023.  THIS IS WHERE PLATE 27	-62114-073/074 IS ATTACHED.  THE TUBES UNDER THE PLATE ATTACH POINT ARE NOT WELDED.  SUBMITTER BELIEVES THESE TUBES NOT 	BEING WELDED ALLOW FLEX THAT LEADS TO CRACKS.				2	L	7	2 	4T			RT	A8SW    					 
1996121900755	19961219	00755	SW  	1996	12	19	96ZZZX6121       	1	19961211	G	5753	652513020	FLAP            			GULSTM	560   	560         	0141402	SW  										RT INBD	SKIN SEPARATED  	D		A		A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SO	06	1217V	38160				5600001				ON FIRST FLIGHT AFTER AIRCRAFT WAS REPAINTED, AT AN ALTITUDE OF 15,000 FEET, RIGHT INBOARD FLAP SKIN SEPARATED INTERNALL	Y FROM THE FLAP RIBS.  AIRCRAFT MADE EMERGENCY LANDING AT RIC.  INVESTIGATION REVEALED VENT HOLES IN FLAP WERE CLOGGED W	ITH FOREIGN MATTER WHICH WOULD HAVE PREVENTED THE FLAP FROM VENTING EXCESS PRESSURE.  CESSNA M/M 56MM064F SECTION 20-330	0, PAGE 704, ADDRESS THIS SUBJECT.			1	H	7	2 	3O				6A1     					 
1996121900756	19961219	00756	NE  	1996	12	19	96ZZZX6122       	2	19961211	G	7270	5757513501	DUCT            			DOUG  	DC8   	DC862       	3021970	WP  	PWA   	JT3D  	JT3D7       	52039	NE  					FAN BYPASS	FAILED          	B			UMXR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	1808E				130	46105				FAILURE OF DUCT, P/N 5757513-501, CAUSED BY COMPRESSOR STALL/SURGE.  REPORT ON FILE AT REPAIR STATION UMXR629L.						2	L	7	4 	4F	4	F		4A25    	1E8				 
1996121900757	19961219	00757	CE  	1996	12	19	96ZZZX6123       	1	19961203	G	2910	2607003453	LINE            			LEAR  	35    	35A         	5170602	CE  										LT HYD PUMP	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	510SG	4806 				268				LT PUMP HYD LINE WAS WORN THROUGH BY SCREW IN ELECTRICAL WIRE BUNDLE ON ENGINE BEAM.  SUSPECT CAUSE, WIRING WAS PROBABLY	 UNCLAMPED FOR ACCESS TO EITHER FIRE BOTTLE OR 3-WAY VALVE AND UPON INSTALLATION, WIRING WAS ROUTED TOO CLOSE TO HYD PIP	E.  SUBMITTER STATED TO PREVENT:  CLOSER INSPECTION SHOULD BE MADE ON INSTALLATION OF WIRING AFTER WIRE MOVEMENT.				2	L	7	2 	4F				A10CE   					 
1996121900758	19961219	00758	CE  	1996	12	19	96ZZZX6124       	1	19961202	G	5712	017A12054	RIB             			MTSBSI	MU2   	MU2B60      	5780460	CE  										RT WING OUTER	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	941S					738SA				DISCOVERED BY CREW DURING POST-FLIGHT INSP, CAUSE AT THIS TIME IS UNDETERMINED.  BOTH OUTER RIBS CRACKED, ON RT WING.						1	H	7	2 	3T			RT	A10SW   					 
1996121900759	19961219	00759	CE  	1996	12	19	96ZZZX6125       	1	19961202	G	5712	017A127046	RIB             			MTSBSI	MU2   	MU2B60      	5780460	CE  										RT WING OUTER	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	941S					738SA				DISCOVERED BY CREW DURING POST-FLIGHT INSP, CAUSE AT THIS TIME IS UNDETERMINED.  BOTH OUTER RIBS CRACKED, ON RT WING.						1	H	7	2 	3T			RT	A10SW   					 
1996121900760	19961219	00760	NE  	1996	12	19	96ZZZX6126       	2	19961111	G	7230	793015	DISC            			BOEING	747   	747136      	1384883	NM  	PWA   	JT9   	JT9D7       	52054	NE  					STAGE 15 HPC	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		79240			B85733		685824			DISC HAS .1875 INCH LONG CIRCUMFERENTIAL CRACK IN FRONT SNAP DIAMETER (I.E. IN AN UNUSUAL LOCATION NOT PREDICTED BY ASB 	4908).  PART CYCLES, 9,092.					2	L	7	4 	4F	4	F		A20WE   	E20EA				 
1996121900761	19961219	00761	NE  	1996	12	19	96ZZZX6127       	2	19961013	G	7510	7958591503	DUCT            		13277503    	DOUG  	MD88  	MD88        	3023688	NM  	PWA   	JT8   	JT8D219     	52053	NE  					NR 2 ENG AI	B NUT LOOSE     	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	12FQ	15021				49766	718244			AFTER TAKEOFF, PILOT REPORTED NR 2 ENGINE OVERHEAT LIGHTS CAME ON ONE AFTER THE OTHER.  AIRCRAFT LEVELED OFF.  NR 2 THRO	TTLE RETARDED AND OVERHEAT CONDITION DISAPPEARED.  AIRCRAFT RETURNED TO DEPARTING AIRPORT AND NORMAL LANDING PERFORMED. 	 INSPECTION REVEALED THAT NOSE COWL ANTI-ICE DUCT'S FORWARD ATTACH B-NUT DESINTEGRATED CAUSING 13TH STAGE BLEED AIR TO H	EAT UP THE 'A' AND 'B' LOOPS.  MDC S/N 3061 NOT C/W AT THE TIME OF INCIDENT.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
1996121900763	19961219	00763	EU  	1996	12	19	96ZZZX6128       	1	19961030	G	7700		CONNECTOR       			BAC   	146   	AVRO146RJ100	1500096	EU  										ENG 1,2,3,4	DIRTY           	W			ANCF	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	23	504MM					E3221				45 MIN AFTER T/O FROM SKBO AT FL 280.  VIBRATION FOR ENG NR 3 SHOWED 2.0 WITH MWS CALL OUT.  SOON AFTER ENG 1 SHOWED 1.3	 VIBR, ENG 2 AND 4 SHOWED 1.4.  ALSO, ALL ENG TEMP SHOWED ZERO, AND ALL ENG OIL PRESS IND SHOWED FULL SCALE.  INDICATION	 PROBLEM SUSPECTED.  DIVERTED TO AND LANDED AT SKBO.  INSPECTED OIL SYSTEM PER SB 19-5.  FLUSHED OIL SYSTEM ALL ENGINES.	  CHANGED OIL FILTER ALL ENGINES.  TEST ON GROUND OK.  CHANGED VIBRATION UNIT, NO HELP.  CLEANED CONNECTORS OF ENG AND C	HECKED WIRING IAW AMM.  ENGINES RUN-UP IN T/O POWER, WITH PUMPS AND GENERATOR ON, ALL PARAMETERS OK AND IN LIMITS.		2	H	7	4 	4F			RT	A49EU   					 
1996121900764	19961219	00764	EU  	1996	12	19	96ZZZX6129       	1	19961116	G	3234		LANDING GEAR    			BAC   	146   	AVRO146RJ100	1500096	EU  	LYC   	LF507 	LF5071F     	 	NE  					MLG	LACK OF LUBE    	W			ANCF	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SO	23	504MM					E3221	LF07320			AFTER TAKEOFF, LANDING GEAR LEVER DIDN'T COME UP AND SPOILER LIGHT ON MWS CAME ON.  RETURNED TO AIRPORT.  LUBRICATED LAN	DING GEAR LEVER MECHANISM.  CHECKED SPOILER AND FOUND NORMAL.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996020900629	19960209	00629	EU  	1996	2	9	96ZZZX613        	1	19960122	G	5311	1052050172RE	FRAME           			BOLKMS	105   	BO105CBS    	5626008	EU  										RT SHELL 9V	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5366Y	7024 				S782				DURING A ROUTINE INSPECTION, A CRACK WAS FOUND IN THE UPPER END OF FRAME 9V IN THE RIGHT SIDE SHELL.  THE CRACK WAS APPR	OXIMATELY 2.5 INCHES LONG.  THE CRACK EXTENDED UNDER THE ATTACHMENT OF THE INBOARD WEB ATTACHED TO THE RIGHT AFT MAIN GE	ARBOX ATTACHMENT FITTING IN THE AIRFRAME.  REPAIRED PER FIELD APPROVED 337 AND BOLKOW SB SI-BO105-142.				1	G	7	2 	3U			NC	H3EU    					 
1996121900765	19961219	00765	NE  	1996	12	19	96ZZZX6130       	2	19961117	G	7200		ENGINE          			BAC   	146   	AVRO146RJ100	1500096	EU  	LYC   	LF507 	LF5071F     	 	NE  					NR 2	VIBRATION       	W			ANCF	C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			SO	23	508MM					E3247	LF73062			DURING TAKEOFF ROLL, ENGINE VIBRATION WARNING LIGHT CAME ON.  ENGINE NR 2 REACHED 2.2.  TAKEOFF WAS REJECTED.  ENGINE NR	 2 WAS CHANGED.  TEST WAS PERFORMED ACCORDING TO AMM 72-00-00.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996121900766	19961219	00766	NE  	1996	12	19	96ZZZX6131       	2	19961110	G	7200		ENGINE          			BAC   	146   	AVRO146RJ100	1500096	EU  	LYC   	LF507 	LF5071F     	 	NE  					NR 3	BIRD STRIKE     	W			ANCF	K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			SO	23	508MM	4014 	222  			E3247	LF07320			PERFORMING WALK-AROUND IN SAN JOSE, A BIRD WAS FOUND INGESTED IN ENG NR 3.  ACCOMPLISHED ENGINE BORESCOPIC INSPECTION DU	E TO BIRD STRIKE, NO DAMAGE FOUND ON THE ENGINE.  ENGINE RUN-UP.  ALL PARAMETERS WITHIN LIMITS.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996121900767	19961219	00767	EU  	1996	12	19	96ZZZX6132       	1	19961114	G	5270		WARNING LIGHT   			BAC   	146   	AVRO146RJ100	1500096	EU  										LOWER DOOR	ILLUMINATED     	W			ANCF	C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			SO	23	504MM					E3221				DURING TAKEOFF ROLL, THE LOWER DOOR NOT SHUT LIGHT CAME ON.  TAKEOFF WAS REJECTED.  ALL LOWER DOORS HYDRAULIC, ELECTRICA	L AND CARGO WERE CHECKED AND FOUND OK.  RESET THE CONTACTORS ON ALL DOORS.					2	H	7	4 	4F			RT	A49EU   					 
1996121900768	19961219	00768	WP  	1996	12	19	96ZZZX6133       	1	19961204	G	6220	369H120351	LINK            			HUGHES	369   	369E        	4470707	WP  										M/R HUB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	440TJ	4982 				0442E				CRACKED LINK DISCOVERED ON PRE-FLIGHT INSP.						1	G	7	1 	3U				H3WE    					 
1996121900769	19961219	00769	SW  	1996	12	19	96ZZZX6134       	1	19961111	G	6510	L	NUT             		2060403709  	BELL  	206   	206L1       	1182107	SW  										DRIVE SHAFT	DETACHED        	B			KBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	5746N					45461				DURING RUN-UP, NUT CAME OFF AND DRIVE SHAFT SEGMENT CAME OFF.  NUT APPEARS TO HAVE LOST TARE TORQUE.  CHECK FOR ADEQUATE	 TARE TORQUE PRIOR TO INSTALLING SELF LOCKING NUTS.					1	G	7	1 	3U				H2SW    					 
1996122600001	19961226	00001		1996	12	26	96ZZZX6135       	1	19961210	G	2911	1456613267	END CAP         	PARKERHANFIN	26604725    															ACCUMULATOR	BLEW OFF        	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					107					GAS END CAP BLEW OFF THE ASSY.  DURING TEST, ON INSPECTION, FOUND PREVIOUS INTERNAL CRACK IN THE CIRCUMFERENCE ON THE I/	D OF CAP.  TEST BEING PERFORMED WAS PRELIMINARY BEFORE DISASSEMBLY.																		 
1996122600002	19961226	00002	GL  	1996	12	26	96ZZZX6136       	3	19961207	G	6114	D3944C88	HUB             													MCAULY	3A32C	D3A32C88    	GL  	NR 2 BLD SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			512  					692219		PROPELLER RECEIVED FOR OVERHAUL.  AFTER DISASSEMBLY, THE FOLLOWING PARTS WERE CONDEMNED DUE TO CORROSION.  RACES, BALLS,	 CYLINDER, BLADE PINS, AND BLADE NUTS.  1 EACH FERRULE CONDEMNED DUE TO CRACK IN BLADE PIN HOLE, RACE SIDE.  HUB CRACKED	 IN NR 2 BLADE SOCKET, 5 THREADS IN, 2 INCHES LONG.  CRACK DISCOVERED USING A 10X DOWEL MICROSCOPE.														5	C	P21EA	 
1996122600003	19961226	00003	GL  	1996	12	26	96ZZZX6137       	3	19961209	G	6114	C4716C98	HUB             													MCAULY	2A34C	D2A34C98    	GL  	NR 1 BLD SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								789111		PROP RECEIVED FROM OVERSEAS CUSTOMER FOR 5 YEAR OVERHAUL.  AFTER DISASSEMBLY, HUB WAS STRIPPED AND INSPECTED.  A CRACK W	AS DISCOVERED IN NR 1 BLADE SOCKET, NR 1 TO NR 2 THREAD AT THE 7 O'CLOCK POSITION ABOUT 1 INCH LONG.  NO LOG BOOK AVAILA	BLE FOR FURTHER INFORMATION.														5	C	P3EA	 
1996122600004	19961226	00004	GL  	1996	12	26	96ZZZX6138       	3	19961210	G	6114	D5892C93	HUB             													MCAULY	3AF32C	3AF32C93    	GL  	NR 3 BLD SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								794515		PROPELLER RECEIVED FOR OVERHAUL.  DURING HUB MICROSCOPIC INSPECTION (10X POWER), HUB DISCOVERED CRACKED IN NR 3 BLADE SO	CKET, NR 3 THREAD IN 7 O'CLOCK POSITION ABOUT 1 INCH LONG.  NO PROPELLER LOG BOOK PROVIDED FOR FURTHER INFORMATION.															5	C	P22EA	 
1996122600005	19961226	00005	SO  	1996	12	26	96ZZZX6139       	1	19961205	G	3710	842CW	PUMP            	AIRBORNE    		PIPER 	PA31  	PA31P       	7103120	SO  										VAC SYS	FAILED          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	18MC	315  			12AK000076	31P7300143				VAC PUMP REMOVED FOR ENGINE REPAIR.  SHAFT VERY HARD TO TURN AND UNIT SQUEALED.						1	L	7	2 	3O				A8EA    					 
1996122600006	19961226	00006	EA  	1996	12	26	96ZZZX6140       	2	19961205	G	8510	75562	GEAR TOOTH      			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					PROP SHAFT	BROKEN          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	18MC	4117 	50   		246	31P7300143	L38662			ENGINE SOUNDED ROUGH ON SHUT DOWN.  FOUND EXCESSIVE PLAY IN PROPELLER.  DRAINED OIL, PULLED SUCTION SCREEN, FOUND PIECE 	OF TOOTH IN SCREEN.  ENGINE TORN DOWN, FOUND BROKEN TEETH ON PROP SHAFT DRIVE GEAR, ALSO, DRIVE GEAR DAMAGED.  SUBMITTER	 SUSPECTS PREVIOUS CRACK CAUSED TOOTH TO BREAK OFF.				1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1996122600007	19961226	00007	EA  	1996	12	26	96ZZZX6141       	2	19961212	G	7322	15B395	RETAIN SCREW    	FACET       	HA6         	GULSTM	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					MIX CONTROL	LOOSE           	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			SW	07	28794	1014 			CH101834	AA5B0819	L249536A			PILOT REPORTED ENIGNE HAD STARTED RUNNING ROUGH AND EGT AT PEAK WITH MIXTURE FULL RICH.  INVESTIGATION REVEALED MIXTURE 	CONTROL VALVE END PLAY OF APPROX  .0625 INCH.  PRECISION AIRMOTIVE SB MSA-6 HAD NOT BEEN C/W.  RETENTION SCREW P/N 15-B3	95 WAS FOUND TO HAVE PIN SEPARATED FROM END AND FLOATING IN HOLE.  PIN AND SCREW APPEAR TO HAVE BEEN WELDED IN MANUFACTU	RE AND SEPARATED AT WELD.  INSTALLATION OF RETENTION KIT PER MSA-6 RETURNED NORMAL OPERATION.			1	L	7	1 	3O	3	O		A16EA   	E286				 
1996122600008	19961226	00008	SO  	1996	12	26	96ZZZX6142       	1	19961116	G	2913		POWER PAC       			PIPER 	PA23  	PA23250     	7102308	SO  										NLG	FAILED          	C				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	99	329SD					273512				NOSE GEAR WOULD NOT COME DOWN.  EMERGENCY BOTTLE USED TO LOCK GEAR.  HYD POWER PAC FAILURE.						1	L	7	2 	3O				1A10    					 
1996122600009	19961226	00009		1996	12	26	96ZZZX6143       	4	19961203	G	2562	7B1115	G SWITCH        	LEIGH       	SHARC7      	CESSNA	182   	182K        	2072724	CE  										ELT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3047Q	2000 			4254	18258047				DURING ANNUAL INSPECTION, G-SWITCH WAS FOUND TO BE INOPERATIVE.  1 COVER SCREW BOSS CRACKED, O-RING BROKEN.						1	H	7	1 	3O			NT	3A13    					 
1996122600010	19961226	00010	SO  	1996	12	26	96ZZZX6144       	1	19961128	G	2821	CCA1550	DRAIN VALVE     	CURTIS      		PIPER 	PA28  	PA28R200    	7102811	SO  										FUEL GASCOLATOR	STEM FAILED     	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	55177	5800 				28R7335190				ON PRE-FLIGHT THIS VALVE WHICH IS ATTACHED TO AN ELBOW ATTACHED TO GASCOLATOR; WAS DIFFICULT TO PUSH IN TO DRAIN.  A SLI	GHT PULL WAS MADE AND THE STEM CAME OUT IN HAND.  FUEL BEGAN TO DRAIN AND THE FUEL SELECTOR HAD TO BE SHUT OFF.  VALVE W	AS REMOVED AND THE RETAINING COLLAR WAS FOUND SEPARATED FROM STEM END.  SUBMITTER STATED IF STEM FELL OUT IN-FLIGHT - TH	E ENGINE WOULD STOP.  THE VALVE WAS REPLACED.			1	L	7	1 	3O				2A13    					 
1996122600011	19961226	00011	SO  	1996	12	26	96ZZZX6145       	1	19961206	G	5751	4020043	SPAR            			PIPER 	PA31  	PA31310     	7103103	SO  										RT AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	578F	9037 				317712004				DURING C/W AD 96-21-03, A CRACK WAS DETECTED IN THE AILERON SPAR AND REINFORCEM ENT DOUBLER IN BOTTOM BRACKET ATTACH HOL	E.					1	L	7	1 	3O			RT	A20SO   					 
1996020900631	19960209	00631	GL  	1996	2	9	96ZZZX615        	1	19960124	G	8120	28125523	WASTEGATE       			ENSTRM	F28   	F28F        	3300412	GL  										TUBRO	WARPED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	8626S	900  				786				BUTTERFLY IN WASTEGATE FOUND WARPED AT EACH 100-HOUR INSPECTION.  WARPED WASTEGATE AND WORN BUTTERFLY AND SHAFT CAUSE TH	ROTTLE BINDING.  BUTTERFLY MUST BE STRAIGHTENED FOR PROPER RIGGING.  ON SOME AIRCRAFT, BUTTERFLIES COME OFF OF SHAFT AND	 BIND THROTTLE.  COMMON TO ALL 'F' AND 'FX' MODELS.  SUBMITTER STATED WASTEGATES NEED TO BE REPLACED AT 900 HOURS MAXIMU	M TIME IN SERVICE.			1	G	7	1 	3O				H1CE    					 
1996122600404	19961226	00404	CE  	1996	12	26	96ZZZX6153       	1	19961121	G	3211	SK4148	REINFORCEMENT   			CESSNA	402   	402A        	207590M	CE  										LT/RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	186BA					402A0110				CESSNA SERVICE KIT SK414-8 WAS INSTALLED ON THIS AIRCRAFT IN 1982.  DURING A 100-HOUR INSPECTION, CRACKS WERE DISCOVERED	 IN THE DOUBLER ON THE LEFT AND RIGHT MAIN GEAR SIDE BRACE BRACKETS.					1	L	7	2 	3O				A7CE    					 
1996122600405	19961226	00405	CE  	1996	12	26	96ZZZX6154       	1	19960926	G	7120	10291002638	TRUSS           			BEECH 	58    	58P         	1152744	CE  										LT ENG MOUNT	LOOSE           	B			JA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2056N	2823 				TJ156				ON ANNUAL INSPECTION, RIGHT TRUSS WAS FOUND LOOSE AT FORWARD END ATTACHMENT TO MOUNT.  NUT ON HILOCK WAS FINGER TIGHT ON	LY AND REMOVED BY HAND.  REMOVAL OF HILOCK REVEALED .031 INCH DEEP SLOT WORN IN SHANK.  WEAR IS IN AREA THAT CONTACTS MO	UNTS.  NO WEAR IN AREA THAT CONTACTS TRUSS FORK OR IN TRUSS.  SUBMITTER RECOMMENDS INSPECTION FOR MOVEMENT OF TRUSS TO M	OUNT ATTACHMENT EACH 100 HOURS.			1	L	7	2 	3O				A23CE   					 
1996122600406	19961226	00406	EA  	1996	12	26	96ZZZX6155       	2	19961120	G	7322	25244919	INJECTOR SERVO  	BENDIX      	RSA10ED1    	PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					ENGINE	FAILED          	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			NE	03	3646N	1768 	63   		64435	61P085881634	L2051648A			INJECTOR SERVO 'SHUT DOWN' DURING ACTUAL FUEL FLOW TEST', ALLOWING ONLY A DRIBBLE OF FUEL THROUGH WITH FULL THROTTLE AND	 FULL MIXTURE AND FUEL PUMP ON.  HAD THIS HAPPENED IN-FLIGHT, ENGINE WOULD HAVE STOPPED.					1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1996122600407	19961226	00407	EA  	1996	12	26	96ZZZX6156       	2	19961101	G	7322		VALVE TANG      	FACET       	HA6         	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					FUEL CUT OFF	WORN            	B	S		ATZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	5099U	4986 	1015 		DL0414	172RG0223	L2782536A			TANG OF FUEL CUT OFF VALVE ASSY WORE DEEPLY INTO FULL RICH STOP AREA ALLOWING APPROX ONE-QUARTER TURN MORE THAN NORMAL. 	 ENGINE WENT EXTREMELY LEAN.  TAKEOFF ABORTED.					1	H	7	1 	3O	3	O		3A17    	E286				 
1996122600408	19961226	00408		1996	12	26	96ZZZX6157       	4	19961122	G	2562	DMELT83	WIRE            	DORNEMARGLN 	DMELT81     	CESSNA	210   	P210R       	2073455	CE  										ELT ANTENNA	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	5522A					P21000860				WHEN CHECKING ELT OUTPUT PER FAR 91.207(D)(4), UNIT COULD NOT BE HEARD ON NEARBY AM RADIO, BUT COULD BE RECEIVED ON AIRC	RAFT'S VHF RADIO.  FOUND ANTENNA CABLE CENTER CONDUCTOR INTERNALLY SHORTED TO GROUND.  PROPERLY OPERATING ELT SHOULD BLE	ED OVER ON AN AM RADIO.				1	H	7	1 	3O			RT	3A21    					 
1996122600410	19961226	00410	CE  	1996	12	26	96ZZZX6159       	1	19961209	G	5711		SPAR            			BEECH 	58    	58          	1152740	CE  										CARRY THRU WEB	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7234K	2886 				TH1479				INSP SPAR CARRY-THROUGH WEB STRUCTURE.  FOUND LT FWD AND AFT RT FWD CORNERS CRACKED.  THIS AIRCRAFT IS 4 SERIAL NUMBERS 	NEWER THAN BEECH AD 90-18-14 APPLIES TO.  SUBMITTER STATED AD 90-18-14 NEEDS REVISING TO INCLUDE NEW AIRCRAFT.					1	L	7	2 	3O				3A16    					 
1996122600412	19961226	00412	SO  	1996	12	26	96ZZZX6160       	2	19961116	G	8540	643259AZ	DRIVE ADAPTER   			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					STARTER DRV END	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	749CA	3707 	724  			421C1239	608257			STARTER DRIVE GEAR WEAR UNACCEPTABLE IAW TELEDYNE CONTINENTAL CSB 94-4 EVEN THOUGH THE SERVICE KIT REQUIRED BY TCM CSB 9	4-4 HAD BEEN PREVIOUSLY INSTALLED AT THE ENGINE OVERHAUL.  SUSPECT CAUSE:  CSB 94-4 MAY NOT BE SUFFICIENT.  SUBMITTER RE	COMMENDS FLEET DATA BE EXAMINED TO DETERMINE NUMBER OF OCCURRENCES.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996122600413	19961226	00413	EA  	1996	12	26	96ZZZX6161       	2	19961115	G	7322		DISCHARGE TUBE  			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					CARB HEAT BOX	BROKEN          	B		A	M6MR	A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	7916G					17259616	L2213727A			THROTTLE JAMMED IN-FLIGHT.  SAFE LANDING MADE.  FOUND CARB DISCHARGE TUBE BENT AND BROKEN IN CARB HEAT BOX.  FOUND THROT	TLE SHAFT BUSHINGS EXCESSIVELY WORN AND LEAKING.  AIRCRAFT 4.6 HOURS SINCE 'OWNER ASISTED ANNUAL'  WAS COMPLETED.  THESE	 ITEMS ARE PART OF ANNUAL CHECK LIST AND SHOULD HAVE BEEN FOUND AT ANNUAL AS AD 93-18-03 WAS SIGNED OFF, THE AREA WAS SU	PPOSED TO BE INSPECTED.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996122600414	19961226	00414	CE  	1996	12	26	96ZZZX6162       	1	19961115	G	2720	031019612	SPRING          			CESSNA	172   	172L        	2072432	CE  										RUDDER CONTROL	BROKEN          	B		A	M6MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	7916G					17259616				OPERATOR COMPLAINED OF HEAVY RUDDER AND OUT OF TRIM.  UPON INSPECTION, FOUND RT RUDDER CENTERING SPRING BROKEN AT AFT AT	TACHMENT.  AIRCRAFT 4.6 HOURS SINCE 'OWNER ASSISTED ANNUAL INSPECTION' WAS COMPLETED.  AREA IS AWKWARD TO INSPECT UNLESS	 AREA PANELS ARE REMOVED INCLUDING CENTER PANEL FORWARD OF CENTER PEDESTAL.  SPRING EXHIBITS WEAR IN AREA WHERE IT BROKE	.  AREA SHOULD BE INSPECTED AT 100 HR AND ANNUAL INSPECTIONS.  THIS WAS THE SECOND 'SAFETY OF FLIGHT' CONDITION FOUND TH	IS DATE.		1	H	7	1 	3O			NT	3A12    					 
1996122600415	19961226	00415	CE  	1996	12	26	96ZZZX6163       	1	19961213	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	13	9310D	3569 				172RG1116				RIGHT MAIN GEAR ACTUATOR HOUSING CRACK AT SMALL END WHERE GEAR ATTACHES TO ACTUATOR.  ACTUATOR CRACKED IN THREE DIRECTIO	NS ALLOWING PINION TO DISENGAGE FROM ACUTATOR.  GEAR FAILED TO EXTEND FOR LANDING.					1	H	7	1 	3O				3A17    					 
1996122600416	19961226	00416	CE  	1996	12	26	96ZZZX6164       	1	19961120	G	3230		PAD             			CESSNA	172   	172RG       	2072438	CE  										NLG UPSTOP	WORN            	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	99	9574B	6128 				172RG0891				GEAR WAS RETRACTED AND EXTENDED SEVERAL TIMES DURING FLIGHT.  AFTER RETRACTION, GEAR WOULD NOT INDICATE GREEN LIGHT ON D	OWN AND LOCKED POSITION.  FOUND THE UPSTOP PAD WORN TO APPROX .25 INCH THICK, ALLOWED GEAR TO GO BEYOND NORMAL UP POSITI	ON.  NOSE WHEEL FORK BOUND ITSELF IN WHEELWELL AREA.  MANUFACTURER MM DOES NOT LIST MIN THICKNESS OR ANY INFO ON CONDITI	ON OR INSPECTION OF THE UPSTOP PADS OR BUMPERS.  IT IS SUGGESTED THAT THESE COMPONENTS ARE INSPECTED FOR THICKNESS AND C	ONDITION EACH 100 HRS.		1	H	7	1 	3O				3A17    					 
1996122600417	19961226	00417	EA  	1996	12	26	96ZZZX6165       	1	19961122	G	3350	5521981	BATERY PACK     	GRIMES      	6013211     	CNDAIR	CL601 	CL6013A     	8070802	EA  										CABIN	SHORTED         	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	2FOR				18115	5092				THE NEW BATTERY PACKS USED BY GRIMES WHICH ARE MFG'D BY E.A.C., USE A METAL STRAP BETWEEN POSITIVE AND NEGATIVE TERMINAL	S WITH A SMALL PIECE OF HEAT SHRINK ON THEM.  THE PROBLEM IS THE HEAT SHRINK SHRINKS AT TEMPERATURE AND THE STRAPS CUT T	HE HEAT SHRINK AND SHORT THE TERMINALS TO THE BATTERY CAUSING SHORTS AND THE PACKS OVERHEAT.				2	L	7	2 	4F			RT	A21EA   					 
1996122600418	19961226	00418	CE  	1996	12	26	96ZZZX6166       	1	19961108	G	3213	010A38371012	YOKE            			MTSBSI	MU2   	MU2B26A     	5780414	CE  										RT MLG	FAILED          	D		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	09	333WF	5700 				387				YOKE ASSY FAILED DURING LANDING ALLOWING THE RIGHT MAIN WHEEL ASSY TO ROTATE APPROXIMATELY 90 DEGREES.  THIS GROUND THE 	TIRE, WHEEL ASSY, AND BRAKE DISC TO THE POINT OF RENDERING THESE PARTS UNSERVICEABLE.  SUBMITTER RECOMMENDATION:  ESTABL	ISH AN INSPECTION TIME LIMIT ON THE ABOVE PART AFTER SO MANY LANDINGS OR HOURS WHICHEVER COMES FIRST AND TO MAGNAFLUX TH	E RESPECTIVE PART.			1	H	7	2 	3T				A10SW   					 
1996122600421	19961226	00421	CE  	1996	12	26	96ZZZX6168       	1	19961204	G	7810	1019500171	STACK           			BEECH 	300   	300BEECH    	1152930	CE  										RT ENG INB	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	195AL	78   				FA102				THE RIGHT ENGINE INBOARD EXHAUST STACK WAS FOUND TO HAVE A CRACK 10 INCHES LONG PARALLEL WITH THE HORIZONTAL WELD ON THE	 FORWARD SIDE.  THIS IS THE SECOND NEW EXHAUST STACK THAT HAS CRACKED AND ONLY AFTER 78.1 HRS OF OPERATION.					2	L	7	2 	4T				A24CE   					 
1996122600422	19961226	00422	CE  	1996	12	26	96ZZZX6169       	1	19961101	G	2910	1145800501	LINE ASSY       			BEECH 	1900  	1900D       	1154162	CE  										PWR PACK FILL	CRACKED         	B	S		ATZR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CE	09	225GL					UE225				FILL LINE TUBES ASSY CRACKED AT FLARE.  LOSS OF FLUID IN HYDRAULIC SYSTEM SUFFICIENT TO ILLUMINATE LOW FLUID LIGHT.  GEA	R EXTENDED NORMALLY.					2	L	7	2 	4T			RT	A24CE   					 
1996020900633	19960209	00633	EA  	1996	2	9	96ZZZX617        	2	19960116	G	8530	77160	VALVE GUIDE     			GULSTM	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					CYLINDERS 1-3	EXCESS WEAR     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	74608	413  				AA5B0282	3295236A			NR 1 AND NR 3 CYLINDERS FAILED LYC SB 388B TEST FOR EXCESS WEAR (.035 INCH AND .043 INCH RESPECTIVELY).  THESE EXACT SAM	E TWO GUIDES AND CORRESPONDING VALVES HAD BEEN PREVIOUSLY REPLACED AT 408 HOURS SINCE NEW ENGINE.  FOUR-PROBE EGT/CHT SH	OWED ALL TEMPS NORMAL AND BAFFLE SEALS WERE GOOD.  GROUND RUN ENGINE AND COLLECTED OIL FROM ROCKER BOXES OF THE 4 CYLIND	ERS.  FOUND NR 1 AND NR 3 CYLINDERS GETTING MUCH LESS THAN NR 2 AND NR 4.  NR 2 AND NR 4 GUIDES PASSES SB 388B TESTS AND	 THEY HAVE 821 HOURS TTSN.  IN THAT TIME, 2 SETS OF NR 1 AND NR 3 EXHAUST VALVES/GUIDES HAVE FAILED THE TEST IN SB 388B.	  SUBMITTER SUSPECTS POSSIBLE DESIGN PROBLEM THAT PROVIDES INSUFFICIENT OIL TO NR 1 AND NR 3 CYLINDERS.	1	L	7	1 	3O	3	O		A16EA   	E286				 
1996122600423	19961226	00423	CE  	1996	12	26	96ZZZX6170       	1	19961203	G	5542	553300013	SKIN            		553300095   	CESSNA	500   	560CESSNA   	2076750	CE  										RUD LT SIDE LE	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	327QS	1383 				5600327				LT SIDE OF BOTTOM L/E SKIN HAS A CRACK ALONG THE RIVET LINE THAT IS 2.25 INCHES LONG.  THIS IS THE 7TH OCCURRENCE OF THI	S PROBLEM.					2	L	7	2 	4F			RT	A22CE   					 
1996122600424	19961226	00424	CE  	1996	12	26	96ZZZX6171       	1	19961030	G	5542	553300095	RUDDER SKIN     			CESSNA	500   	560CESSNA   	2076750	CE  										LT BELOW TAB	CRACKED         	B		A	DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	330QS	1277 				5600329				LT RUDDER SKIN HAS 2 INCH CRACK APPROX 3 INCHES BELOW TRIM TAB FWD OF HINGE LINE.  THIS IS THE SECOND DISCOVERED VERTICA	L CRACK, AND THE SIXTH RUDDER SKIN CRACK OVERALL.  CESSNA WAS NOTIFIED BY SERVICE CONDITION REPORT.					2	L	7	2 	4F			RT	A22CE   					 
1996122600425	19961226	00425	CE  	1996	12	26	96ZZZX6172       	1	19961209	G	5542	553300013	SKIN            		553300095   	CESSNA	500   	560CESSNA   	2076750	CE  										RUD LT SIDE LE	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	348QS	1035 				5600348				LT SIDE OF BOTTOM L/E SKIN HAS A 1 INCH HORIZONTAL CRACK ALONG THE RIVET LINE.  THIS IS THE SAME AREA OF MANY OTHER RUDD	ERS, AND IS THE EIGHTH (8) OCCURRENCE OF THIS PROBLEM.					2	L	7	2 	4F			RT	A22CE   					 
1996122600426	19961226	00426	CE  	1996	12	26	96ZZZX6173       	1	19961112	G	7810		TAILPIPE        			LEAR  	24    	24          	5170302	CE  										LT ENG	CRACKED         	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	555LB					177				LT FIRE LIGHT ILLUMINATED AT ALTITUDE.  REPLACED CRACKED TAIL PIPE WITH SERVICEABLE UNIT.						2	L	7	2 	4J				A10CE   					 
1996122600527	19961226	00527	WP  	1996	12	26	96ZZZX6174       	2	19961211	G	7210	3072178	GEAR ASSY       			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					RT ENG PLANETARY	DAMAGED         	E	L	A		O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CE	07	112FX	347  	347  			116	P99348			DURING DESCENT INTO ICT, PILOT REPORTED UNUSUAL NOISE FROM RT ENGINE.  AFTER LANDING AND SHUT DOWN, ROTATION OF FAN BY L	EAR JET MECHANIC CONFIRMED NOISE.  INSP FOUND A BAYONET FROM A STUD IN THE TEETH OF THE FAN SUPPORT RING GEAR FOR GEARBO	X.  INSPECTION FOUND THE STUD THAT WAS MISSING THE BAYONET, THE STUD WAS REPLACED AND NO OTHER DAMAGE WAS NOTED.				2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
1996122600529	19961226	00529		1996	12	26	96ZZZX6175       	4	19961101	G	3441	5H120	CELL            	MARATHON    	CA54        	GULSTM	G1159 	G1159A      	3970109	SO  										INS STDBY BAT	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	93CX	1285 				314				BATTERY CELL LIFE IS TOO SHORT.  THIS BATTERY WAS RECELLED 10/96, 1/95, 5/94.  SUBMITTER STATED POSSIBLY REDUCING CHARGE	 RATE TO THIS BATTERY OR INSTALL A STRONGER CELL (SUPER POWER).  POSSIBLY A 20 CELL MODIFICATION WOULD HELP, PRESENTLY 1	9 CELL.				2	L	7	2 	4F				A12EA   					 
1996122600530	19961226	00530	CE  	1996	12	26	96ZZZX6176       	1	19961028	G	5542	553300095	RUDDER SKIN     			CESSNA	500   	560CESSNA   	2076750	CE  										LT BELOW TAB	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	341QS					5600341				FOUND 4 INCH VERTICAL CRACK ON LT SKIN OF RUDDER APPROXIMATELY 3 INCHES BELOW HINGE LINE OF TRIM TAB.  SKIN REMOVED AND 	REPLACED.  THIS IS THE 5TH INCIDENT OF A LT RUDDER SKIN CRACK.					2	L	7	2 	4F			RT	A22CE   					 
1996122600531	19961226	00531	CE  	1996	12	26	96ZZZX6177       	1	19961028	G	5542	553300095	RUDDER SKIN     			CESSNA	500   	560CESSNA   	2076750	CE  										LT BELOW TAB	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	ES7QS					5600307				A LT RUDDER SKIN CRACK HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB.						2	L	7	2 	4F			RT	A22CE   					 
1996122600532	19961226	00532	CE  	1996	12	26	96ZZZX6178       	1	19961028	G	5542	553300095	RUDDER SKIN     			CESSNA	500   	560CESSNA   	2076750	CE  										LT BELOW TAB	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	317QS					5600317				A LT RUDDER SKIN CRACK HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB.						2	L	7	2 	4F			RT	A22CE   					 
1996122600533	19961226	00533	CE  	1996	12	26	96ZZZX6179       	1	19961028	G	5542	553300095	RUDDER SKIN     			CESSNA	500   	560CESSNA   	2076750	CE  										LT BELOW TAB	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	344QS					5600344				A LT RUDDER SKIN CRACK.  HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB.						2	L	7	2 	4F			RT	A22CE   					 
1996020900634	19960209	00634	CE  	1996	2	9	96ZZZX618        	1	19960106	G	2710	NAS304220255	CABLE ASSY      			BEECH 	33    	3533        	1151402	CE  										AILERON	MISINSTALLED    	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	915T					CD115				DURING ANNUAL INSPECTION, FOUND AILERON TRAVEL TO BE 14 DEGREES UP AND DOWN WHILE SPEC IS 20 DEGREES.  STOPS ON AILERON 	BELLCRANK WERE NOT CONTACTING.  UPON CLOSER INSPECTION, FOUND AILERON CABLE WEDGED BETWEEN 2 PULLEYS AT STA 51.5.  THE P	ARTS CATALOG CALLS FOR 2 AN392-35 CLEVIS PINS TO BE INSTALLED FORWARD AND BELOW THE PULLEYS TO PREVENT THE CABLE FROM CO	MING OFF PULLEYS.  THE PINS WERE MISSING AND IT APPEARED THEY HAD BEEN MISSING FOR SOME TIME.  INSTALLED CABLE AND WAS A	BLE TO GET FULL AILERON TRAVEL.		1	L	7	1 	3O				3A15    					 
1996122600534	19961226	00534	CE  	1996	12	26	96ZZZX6180       	1	19961028	G	5542	553300095	RUDDER SKIN     			CESSNA	500   	560CESSNA   	2076750	CE  										LT BELOW TAB	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	375QS					5600375				A LT RUDDER SKIN CRACK.  HORIZONTAL, ABOUT 2 INCHES LONG, AND ALONG THE RIB LINE OF THE RUDDER RIB BELOW THE TRIM TAB.						2	L	7	2 	4F			RT	A22CE   					 
1997010200343	19970102	00343	SW  	1997	1	2	96ZZZX6182       	1	19961007	G	6410	206016201131	BLADE           			BELL  	206   	206L1       	1182107	SW  										T/R	BEARING WORN    	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2611	1081 			CS452	45417				T/R BLADES REMOVED DUE TO FEATHERING BEARINGS WORN AND EXCESSIVE AXIAL MOVEMENT OF THE BLADES.  INSPECTED BLADE FEATHERI	NG BEARINGS PER BELL 206L MM, CH 65-30-00, PG 65-49 PARA 65-62 ITEM 6 AXIAL LOOSENESS EXCEEDED .190 INCHES AT BLADE TIP.	  BEARINGS REPLACED.  TOTAL TIME OF OLD BEARINGS 537.7.				1	G	7	1 	3U				H2SW    					 
1997010200344	19970102	00344	SW  	1997	1	2	96ZZZX6183       	1	19961007	G	6410	206016201131	BLADE           			BELL  	206   	206L1       	1182107	SW  										T/R	BEARING WORN    	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2611	538  			CS446	45417				T/R BLADES REMOVED DUE TO FEATHERING BEARINGS WORN AND EXCESSIVE AXIAL MOVEMENT OF THE BLADES.  INSPECTED BLADE FEATHERI	NG BEARINGS PER BELL 206L MM, CH 65-30-00, PG 65-49 PARA 65-62 ITEM 6 AXIAL LOOSENESS EXCEEDED .190 INCHES AT BLADE TIP.	  BEARINGS REPLACED.  TOTAL TIME OF OLD BEARINGS 537.7.				1	G	7	1 	3U				H2SW    					 
1997010200345	19970102	00345	SW  	1997	1	2	96ZZZX6184       	1	19961107	G	2430	SM20ACD200A21	RELAY           			BELL  	206   	206L1       	1182107	SW  										DC SYS	CORRODED        	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2618				MFD9624	45503				RELAY COMING APART.  CORROSION ON INSIDE.						1	G	7	1 	3U				H2SW    					 
1997010200346	19970102	00346	NE  	1997	1	2	96ZZZX6185       	1	19960925	G	2910	0711311005	MODULE          			SKRSKY	S76   	S76         	8143010	NE  										HYD	LEAKING         	B			AC2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5401G				0447B	760137				HYDRAULIC MODULE ASSEMBLY PN 76650-09801-104 WAS REPORTED LEAKING AT CYLINDER OF MODULE.  REMOVED CYLINDER PN 0711311-20	2 O-RING PN 0711311-237 AND INSTALLED ANOTHER SERVICEABLE CYLINDER AND O-RING.  C/W LEAK CHECK OF MODULE ASSY.  FOUND TO	 BE SERVICEABLE.				1	G	7	2 	3U				H1NE    					 
1997010200347	19970102	00347	SW  	1997	1	2	96ZZZX6186       	1	19961009	G	6330	206033509203	BEARING         		206033506101	BELL  	206   	206L1       	1182107	SW  										XMSN RESTRAINT	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3899C		332  		LK3115	45596				TRANSMISSION RESTRAINT BEARINGS WORN BEYOND LIMITS.  REPLACED 2 EACH BEARINGS.						1	G	7	1 	3U				H2SW    					 
1996020900635	19960209	00635	CE  	1996	2	9	96ZZZX619        	1	19960102	G	3246	101028	WHEEL HALF      	BFGOODRICH  	31255       	BEECH 	18    	E18S        	1151006	CE  										LT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AL	03	700WA					BA28				INNER WHEEL HALF FAILED DURING TAXI.  TIME SINCE LAST INSPECTION, 25.9 HOURS.  SUBMITTER SUGGESTED CHECKING WHEELS AND W	HEEL BOLTS FOR CONDITION AND SECURITY.					1	L	7	2 	3R				A765    					 
1996020900636	19960209	00636	SO  	1996	2	9	96ZZZX620        	1	19960120	G	3213		STRUT HEAD      			PIPER 	PA28  	PA28140     	7102802	SO  										MLG	RUSTED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	4347T					287125510				THE CYLINDER HEADS WHICH ARE THE CAPS TO THE MLG STRUTS WERE FOUND SEVERELY RUSTED.  THE ATTACHING BOLTS WERE RUSTED BAD	LY ALSO.  THIS AREA HAS A BUILT-IN WELL AREA WHICH ALLOWS WATER TO ACCUMULATE AND JUST SIT THERE.  THERE IS A METAL PLUG	 BUTTON USED TO COVER THIS AREA AND FILL THE HOLE IN THE WING OVER THE FILL VALVE.				1	L	7	1 	3O				2A13    					 
1996020900638	19960209	00638		1996	2	9	96ZZZX622        	4	19960116	G	2312	466920000	SWITCH          	SIGMATEK    	RT385A      															NAV/COM	DEFECTIVE       	B	L	A	JA3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21					17996					WHILE REPAIRING CESSNA RT385 AIRCRAFT RADIOS, FOUND SIGMATEK CORP IS SHIPPING DEFECTIVE SWITCHES FOR THE CESSNA RT385 NA	V COM THAT POSE AN ONGOING HAZARD TO FLIGHT SAFETY.  THE SIGMATEK PART NUMBERS ARE 46692-0000, 46659-0000, 46693-0000, A	ND 46481-0000.  THE DANGER IS SEPARATE SECTIONS OF EACH SWITCH CONTROL SEPARATE FUNCTIONS OF THE RADIO.  ONE PART OF THE	 SWITCH CONTROLS FREQUENCY DISPLAY AND THE OTHER PART CONTROLS ACTUAL FREQUENCY OF THE RADIO.  IT HAS HAPPENED THAT ONE 	NAVIGATION FACILITY CAN BE DISPLAYED AND ANOTHER RECEIVED.  IN OTHER WORDS, THE RADIO WILL BE RELAYING INFO FOR WHAT THE	 PILOT WOULD ASSUME TO REPRESENT A SOUTHERN APPROACH, BUT IN REALITY, IS RELAYING INFO FOR AN EASTERN APPROACH.														 
1996021600001	19960216	00001	WP  	1996	2	16	96ZZZX626        	1	19960115	G	7160	369A8448	PULLEY          			HUGHES	369   	369D        	4470706	WP  										ALT AIR DOOR	SEIZED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING DAILY INSPECTION, ONE OF THE PULLEYS FOR THE ALTERNATE AIR DOOR CABLE WAS FOUND SEIZED.  REPLACED THE PULLEY.						1	G	7	1 	3U				H3WE    					 
1996021600002	19960216	00002	WP  	1996	2	16	96ZZZX627        	1	19960115	G	7933	369A4533	SENSOR          			HUGHES	369   	369D        	4470706	WP  										ENG OIL	OUT OF CALIB    	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				PILOT COMPLAINED THE ENGINE OIL TEMP WAS TOO LOW.  SUBSEQUENT INSPECTION FOUND TEMP BULB RESISTANCE TOO HIGH AND IT READ	 LOW ON FUNCTIONAL BENCH CHECK.  REPLACED TEMP BULB.					1	G	7	1 	3U				H3WE    					 
1996021600003	19960216	00003	WP  	1996	2	16	96ZZZX628        	1	19960110	G	6320	369D25100505	TRANSMISSION    			HUGHES	369   	369D        	4470706	WP  										M/R	LEAKING         	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	5074R				40893	1151D				DURING INSPECTION, A LEAKY SEAL WAS DISCOVERED ON THE INPUT SHAFT OF THE TRANSMISSION.  REPLACED TRANSMISSION.						1	G	7	1 	3U				H3WE    					 
1996021600004	19960216	00004	WP  	1996	2	16	96ZZZX629        	1	19960116	G	6210	369D51321100	BLADE           			HUGHES	369   	369D        	4470706	WP  										MR OTBD LE STRIP	ERODED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	911FT	2016 			B786	811036D				MAIN ROTOR BLADE L/E ABRASION STRIP ERODED AT THE OUTBOARD END OF M/R BLADE NEAR THE TIP.  CAUSE OF EROSION - OPERATING 	IN AND AROUND SAND AND DIRT DURING OFF-AIRPORT LANDINGS.  REPAIR MADE TO AREA PER APPROVED ENG. DATA - 8110-3.  M/R BLAD	E RETURNED TO SERVICE.				1	G	7	1 	3U				H3WE    					 
1996021600005	19960216	00005	GL  	1996	2	16	96ZZZX630        	2	19960108	G	7261	1740364	OUTLET STRAINER 		174000103   	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					LUBE FILTER	MISSING         	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	911FT				2856	811036D	CAE836410			DURING ROUTINE/RECOMMENDED 1,000-HOUR INSPECTION OF THE OUTLET STRAINER ASSEMBLY, THE SCREEN WAS NOT INSTALLED, RATHER A	N INLET FITTING, PN 1740235, WAS INSTALLED.  THIS UNIT IS APPROXIMATELY 980 HOURS TSN.  SUBMITTER RECOMMENDS COMPLETE IN	SPECTION OF ASSY (FILTER, SCREEN, PACKINGS, ETC.) PRIOR TO INSTALLATION.  STC NR SH401GL.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996021600657	19960216	00657	SO  	1996	2	16	96ZZZX670        	1	19960105	G	7922	53E19600	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					THERMO BYPASS	CRIMP NUT DETACH	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4093W				62939	318152176	L291068A			PILOT REPORTS TO MAINTENANCE THE RT ENGINE WAS VERY SLOW TO WARM UP TO NORMAL OIL TEMP RANGE, AND OIL PRESSURE STAYED IN	 HIGH RANGE.  ALSO WHILE IN A DESCENT, THE OIL TEMP WOULD INDICATE BELOW OPERATING TEMP.  REMOVED THERMOSTATIC BYPASS VA	LVE FOR INSPECTION.  UPON REMOVAL, THIS ASSY CAME OUT OF ENG CAVITY IN SEVERAL PIECES.  THE CRIMP NUT WAS MISSING.  AT T	HIS POINT WE CONTACTED TEXTRON LYC & SPOKE WITH A TECH/REP.  HE SAID TO REMOVE OIL FILTER & FILTER ATTACHMENT BACKPLATE.	  ALSO, TO CHECK OIL COOLER LINES IN THE EFFORT TO LOCATE CRIMPED NUT.  WE DID LOCATE CRIMPED NUT IN THE OIL LINE TO OIL	 COOLER.	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996021600658	19960216	00658	EA  	1996	2	16	96ZZZX671        	2	19960101	G	8530		ENGINE          			FRCHLD	M62   	PT26        	3371622	EA  	FCD   	6440  	6440C5      	26003	EA  					CYLINDERS	MISOVERHAULED   	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17										WHILE DISASSEMBLING THE ENGINE, THE CAM, ROCKER ARM SUPPORTS, AND CAM HOUSING WERE FOUND EXCESSIVELY WORN, METAL TRANSFE	R FROM THE CASE TO THE CAM, GALLING OF JOURNALS, ALL SEVEN BEARING SUPPORTS WERE DAMAGED.  IT WAS ALSO NOTED THE ROCKER 	SUPPORTS THAT FORM A PART OF THE CAM BEARING, WERE INSTALLED IN REVERSE ORDER.  ACTT 1,680 HRS.				1	L	7	1 	3I	3	I		A724    	E216				 
1996021600661	19960216	00661	CE  	1996	2	16	96ZZZX674        	1	19960129	G	3242	16402706	DISC            	PARKERHANFIN		BEECH 	55    	95C55       	1152708	CE  										MLG	CHAFE WHEELS    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	153NL					TE5				CLEVELAND BRAKE DISCS WERE REMOVED DUE TO WEAR.  AFTER VERIFYING PART NUMBER AND INSTALLING NEW DISCS, AIRCRAFT WAS TAXI	-TESTED.  PILOT COMPLAINED THAT BRAKING WAS INADEQUATE.  INSPECTION SHOWED MODERATE TO SEVERE CHAFE DAMAGE TO BOTH WHEEL	S AND TIRES FROM BRAKE ASSY.  AVAILL AND CLEVELAND VERIFIED BRAKE DISC PART NUMBER.  MEASUREMENTS SHOW THAT NEW DISC IS 	MORE SHALLOW THAN OLD DISC WHICH PLACES THE FLANGE TOO CLOSE TO THE WHEEL AND TIRE ASSY.			1	L	7	2 	3O				3A16    					 
1996021600662	19960216	00662	SO  	1996	2	16	96ZZZX675        	1	19960113	G	5751	4244100	HINGE FITTING   		4255500     	PIPER 	PA12  	PA12        	7101202	SO  										AILERON CENTER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7561H	2380 				12430				DURING INSPECTION, CRACKS WERE NOTED IN RADIUS OF FITTING ATTACHED TO AILERON SPAR.  SUBMITTER SUSPECT CAUSE IS POOR ALI	GNMENT OF AILERON ATTACH FITTINGS THROUGH FALSE SPAR AFTER C/W AD 51-21-02 OR, SIMPLY, WEAK AREA IN DESIGN OF AILERON FI	TTING.				1	H	7	1 	3O				A780    					 
1996021600663	19960216	00663	SO  	1996	2	16	96ZZZX676        	1	19960113	G	5751	4188100	HINGE FITTING   		4255501     	PIPER 	PA12  	PA12        	7101202	SO  										AILERON INB/OTBD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7561H	2380 				12430				DURING INSPECTION, CRACKS WERE NOTED IN RADIUS OF FITTING ATTACHED TO AILERON SPAR.  SUBMITTER SUSPECTS CAUSE IS POOR AL	IGNMENT OF AILERON ATTACH FITTINGS THROUGH FALSE SPAR AFTER C/W AD 51-21-02 OR, SIMPLY, WEAK AREA IN DESIGN OF AILERON F	ITTING.				1	H	7	1 	3O				A780    					 
1996021600664	19960216	00664	CE  	1996	2	16	96ZZZX677        	1	19960124	G	5753		FLAP            			CESSNA	180   	180J        	2072622	CE  										RT/LT TE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	9798G					18052298				DURING ANNUAL INSPECTION, SEVERAL CRACKS AT FLAP TRAILING EDGE RIVETS WERE FOUND.  CRACKS WERE FROM .0625 INCH TO .75 IN	CH LONG.  AIR LOADS FROM PROP WASH AND OPERATION ABOVE STATED FLAP SPEEDS ARE SUSPECT.  SUBMITTER STATED THIS AREA SHOUL	D BE CLOSELY CHECKED FOR CRACKS.  PART TOTAL TIME 2,150.0 HOURS.				1	H	7	1 	3O				5A6     					 
1996021600666	19960216	00666	GL  	1996	2	16	96ZZZX679        	3	19960124	G	6110		PROPELLER       													HARTZL	HCC3Y	HCC3YR      	GL  	HUB/BLADES	MISOVERHAULED   	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03								CK4332A		FBO PURCHASED 2 EACH ZERO TSO PROPELLERS FROM A PROPELLER SHOP AND SENT TO LOCAL PROP SHOP TO HAVE THE CORRECT HUB BOLTS	 INSTALLED.  AFTER RECEIPT BY PROP SHOP, THE FOLLOWING DISCREPANCIES WERE NOTED.  HUB BOLTS INSTALLED WERE WRONG PART NU	MBER.  THE WRONG BOOT PART NUMBER WAS INSTALLED.  THE HUB MODEL WAS INCORRECTLY STAMPED.  ANGLES BETWEEN BLADES WERE OUT	 OF TOLERANCE (MEASURED 6/10THS OF A DEGREE, 2/10THS ALLOWED).  PROPELLER WAS RETURNED TO FBO.													5	C	P25EA	 
1996021600668	19960216	00668	SO  	1996	2	16	96ZZZX681        	2	19960110	G	8540	642087	STARTER ADAPTER 			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					LT ENGINE	FAILED          	D				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			SO	13	18FF		1365 			TJ218	237585P			LOST OIL PRESSURE ON LT ENGINE DUE TO LOSS OF OIL VIA BROKEN STARTER ADAPTER.  AIR CONDITIONER DRIVEN PULLEY AND DRIVE S	HAFT HAD BROKEN LOOSE FROM STARTER/ADAPTER ALLOWING OIL TO ESCAPE OUT DRIVE AREA.  WRONG TYPE BELT INSTALLED FOR THE TYP	E DRIVE PULLEYS USED.  SUBMITTER RECOMMENDS ALL MAINTENANCE PERSONNEL BECOME FAMILIAR WITH CURRENT SB'S AND AD'S IN THIS	 AREA.			1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1996021600672	19960216	00672	EA  	1996	2	16	96ZZZX685        	2	19960115	G	7414	LW12707	ADAPTER         			CONAER	LA4   	LA4250      	5110320	NE  	LYC   	O540  	IO540C4B5   	41532	EA  					LT ENG MAG	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	8435H	900  				102	L2417648A			THE MAG ADAPTER INSTALLED WAS THE WRONG P/N LW-12706 WHICH IS THINNER.  WHEN A NEW MAG WAS INSTALLED TO REPLACE THE OLD 	MAG (WHICH WAS REMOVED DUE TO A BAD BEARING AND RACE), THE NEW MAG BEARINGS LASTED ABOUT 2 MINUTES.  INVESTIGATION FOUND	 THE WRONG PART NUMBERED ADAPTER.  THE MAGS HAD NEVER BEEN REMOVED FROM THE ENGINE SINCE FACTORY NEW.  SUBMITTER STATED 	THIS LEADS ONE TO BELIEVE THE WRONG PART NUMBER WAS ORIGINALLY INSTALLED AT THE FACTORY ON THIS LEFT SIDE.  THE RT SIDE 	HAD THE CORRECT PART.  ALSO, THIS BRINGS TO ATTENTION THE LACK OF MAINTENANCE TO THE MAGS, I.E., 500-HOUR INSPECTION.		1	H	7	1 	3O	3	O		1A13    	1E4				 
1996021600673	19960216	00673		1996	2	16	96ZZZX686        	2	19960101	G	7322	8211	COTTER PIN      	PREAIR      	MA45        															FLOAT SHAFT	MISSING         	B			NE2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07					75041009					RECEIVED CARBURETOR FROM CUSTOMER WITH THE FOLLOWING SQUAWK:  'AIRCRAFT WON'T IDLE, CAN'T SHUT DOWN WITH FUEL MIXTURE. S	EEMS TO RUN AT HIGH RPM.  WHEN SHUT OFF WITH SWITCH, FUEL RUNS OUT OF CARBURETOR.  6.0 HOURS SINCE INSTALLED ON AIRCRAFT	'.  TESTED CARBURETOR FOR FLOAT VALVE LEAKAGE, CARBURETOR OVERFLOWED.  DISASSEMBLY REVEALED COTTER PIN MISSING FLOAT SHA	FT ALLOWING SHAFT TO SLIDE OUT OF BRACKET.																 
1996021600677	19960216	00677	NM  	1996	2	16	96ZZZX690        	1	19960115	G	2710		CONTROL CABLE   			UNIVAR	108   	1081        	9230404	NM  										AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8893K	2458 				1081893				DURING REPLACEMENT OF ORIGINAL CABLES, PARTS (CABLES) UNDER BALL ATTACHMENT WERE FOUND BROKEN AND FRAYED.  CABLE WAS SEV	ERELY KINKED DURING ORIGINAL INSTALLATION AND EVENTUALLY BROKEN.  NORMAL INSPECTION WOULD NOT SHOW DAMAGE.  SUBMITTER SU	GGESTS REMOVAL OF COTTER PINS, 4 EACH, LEFT AND RIGHT.  LIFT OUT CABLE TO INSPECT, THEN, REINSTALL IF CABLES ARE FOUND A	CCEPTABLE.			1	H	7	1 	3O			 	A767    					 
1996021600680	19960216	00680		1996	2	16	96ZZZX693        	4	19960112	G	2562	MN1300	BATTERY         	ACK         	E01         															ELT	LEAK            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										WHILE PERFORMING NEW FAR 91.207(D) ELT CHECKS ON FLEET, DISCOVERED NEARLY ONE-HALF OF ACK E-01 ELT'S HAVE LEAKY BATTERIE	S.  ACK CALLS FOR THE USE OF DURACELL MN 1300 1.5 VOLT D-CELL BATTERIES.  SUBMITTER SUGGESTS, APPARENTLY, THESE BATTERIE	S CANNOT WITHSTAND ALASKA'S WINTER CLIMATE, AND COULD CAUSE CORROSION PROBLEMS INSIDE OF THE ELT.  ELT BATTERY REQUIREME	NTS FOR ALASKA SHOULD BE COMPATIBLE WITH OUR ENVIRONMENT INCLUDING TEMPERATURES TO MINUS 50 DEGREES.  BATTERY REPLACEMEN	T IS YEARLY.															 
1996021600682	19960216	00682	SO  	1996	2	16	96ZZZX695        	1	19960110	G	8120	07A19870	BRACKET         			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					LT TURBO	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	1818W	401  				4622151	L946761A			INSPECTION FOUND LEFT TURBOCHARGER SUPPORT BRACKET BROKEN JUST BELOW TOP MOUNT LUG ALLOWING WEIGHT OF TURBOCHARGER TO ON	LY BE CARRIED BY LOWER ATTACHMENT.  BRAKE APPEARS TO HAVE ORIGINATED FROM FACTORY WELD.  SUGGEST CLOSE INSPECTIONS UNTIL	 FACTORY STRENGTHENS PART.				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
1996021600683	19960216	00683	CE  	1996	2	16	96ZZZX696        	1	19960101	G	2750		BRACKET         			CESSNA	185   	185         	2072802	CE  										FLAP FWD PULLEY	FAILED          	D		A		O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	15	105NR					18503956				RIGHT FORWARD PULLEY BRACKET ON ROBERTSON EQUIPMENT FLAP CABLE ASSEMBLY FAILED RESULTING IN ASYMMETRICAL FLAP POSITION D	URING FLAP EXTENSION.  TOTAL TIME, 6,000 HOURS.					1	H	7	1 	3O			NC	3A24    					 
1996021600684	19960216	00684	CE  	1996	2	16	96ZZZX697        	1	19960104	G	2910	AE1005816G0166	HOSE            			CESSNA	414   	414A        	2075907	CE  										RT ENGINE HYD	RUPTURED        	H		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	13	6604C	1289 				414A0030				HOSE ASSEMBLY P/N AE1005816G0166 LOCATED BETWEEN THE RT HYDRAULIC PUMP P/N 9910137-2 AND HYDRAULIC FILTER ASSEMBLY P/N A	N6234-2 RUPTURED APPROXIMATELY 3 INCHES FROM THE HYDRAULIC PUMP.  IT APPEARED THE TOP ENGINE COWLING HAD CHAFED THROUGH 	THE FIRE SHIELD AND STEEL BRAIDS OF THE NOSE ASSY.  SUBMITTER RECOMMENDS PROPER CLEARANCE BETWEEN HOSE ASSY AND ENGINE C	OWL BE CHECKED AND MAINTAINED.			1	L	7	2 	3O				A7CE    					 
1996021600687	19960216	00687	SO  	1996	2	16	96ZZZX700        	2	19960130	G	8530	652960	VALVE GUIDE     			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360CB   	17025	SO  					EXHAUST	EXCESS WEAR     	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	777NB	808  				P3370180	26122R			FREQUENT FINDING OF LOW COMPRESSION ON EITHER FRONT OR REAR ENGINE WITH ONLY 808 HOURS TT.  EACH TIME REPAIR WAS ACCOMPL	ISHED DUE TO THIS HISTORY, COMPLETE CYLINDER TEAR DOWN REVEALED EXCESS WEAR TO EXHAUST VALVES AND EXHAUST VALVE GUIDES. 	 SUBMITTER SUSPECTS MFG DEFECT OR A MATERIAL INCOMPATIBILITY CAUSING ACCELERATED WEAR.				1	H	7	2 	3O	3	O		A6CE    	E9CE				 
1996021600688	19960216	00688	SO  	1996	2	16	96ZZZX701        	2	19960130	G	8530	646460	VALVE           			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360CB   	17025	SO  					EXHAUST	EXCESS WEAR     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	777NB	808  				P3370180	26122R			FREQUENT FINDING OF LOW COMPRESSION ON EITHER FRONT OR REAR ENGINE WITH ONLY 808 HOURS TT.  EACH TIME REPAIR WAS ACCOMPL	ISHED DUE TO THIS HISTORY, COMPLETE CYLINDER TEAR DOWN REVEALED EXCESS WEAR TO EXHAUST VALVES AND EXHAUST VALVE GUIDES. 	 SUBMITTER SUSPECTS MFG DEFECT OR A MATERIAL INCOMPATIBILITY CAUSING ACCELERATED WEAR.				1	H	7	2 	3O	3	O		A6CE    	E9CE				 
1996022300001	19960223	00001	EA  	1996	2	23	96ZZZX708        	2	19960109	G	8520	LW11754	CAMSHAFT        			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					NR 3 INTAKE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	54BA	1145 				1888	L1690239A			DURING REMOVAL OF NR 1 AND NR 3 CYLINDERS FOR MAINTENANCE, INTERNAL INSPECTION OF THE CAMSHAFT AND TAPPET BODIES REVEALE	D EXCESSIVELY WORN CAMSHAFT LOBE AT THE NR 3 INTAKE POSITION.  THE TAPPET BODY WHICH CONTACTS AND RIDES ON THE CAMSHAFT 	LOBE WAS HEAVILY SPALLED ON THE FACE OF THE TAPPET BODY AS WELL.				1	G	7	1 	3O	3	O		H10WE   	E274				 
1996022300003	19960223	00003	SO  	1996	2	23	96ZZZX710        	1	19960116	G	2810	2379901	CELL            			PIPER 	PA24  	PA24260     	7102406	SO  										RT INBD TANK	FUEL WEEP       	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	99	8632P					244074				PILOT REPORTED FUEL SMELL.  INSPECTION FOUND RT INBOARD TANK WEEPING THROUGH FABRIC OF FUEL CELL ENOUGH TO GENERATE SMEL	L, BUT NOT ENOUGH TO LEAK OR CAUSE EXCESSIVE FUEL STAINS.					1	L	7	1 	3O				1A15    					 
1996022300011	19960223	00011	EA  	1996	2	23	96ZZZX718        	2	19960126	G	8530	7380685	PUSH ROD        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 2 CYL EXH VLV	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	68919	2400 				15282402	L1764515			ON INSPECTION OF AD 95-03-10, PUSH ROD OF ACCEPTABLE PART NUMBER PER AD WAS FOUND TO HAVE A LOOSE BALL END AND TUBE WAS 	MUSHROOMED.  THIS ENGINE WAS DUE FOR OVERHAUL IN 42 HOURS AT NEXT 100-HOUR INSPECTION, AND THE HIGH TIS WAS SUSPECT CAUS	E OF DEFECT.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996022300012	19960223	00012	CE  	1996	2	23	96ZZZX719        	1	19960101	G	3213	50411081	BEARING         			CESSNA	421   	421C        	2076016	CE  										LT MLG LEG	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	146TJ	1858 				421C0500				AIRCRAFT OWNER REPORTED HOUR METER RUNNING CONSTANTLY.  FOUND LEFT MLG EXTENDED FULLY, ALLOWING SQUAT SWITCH TO BE UNACT	UATED AND HOUR METER TO RUN CONSTANTLY.  REMOVED LOWER LEG AND FOUND INNER, UPPER BEARING WORN/GALLED AND BINDING IN BAR	REL.  THE AIRCRAFT HAS 1,857.8 HOURS TOTAL TIME AND AD 90-02-13 IS DUE AT 2,128.0 HOURS.  SUBMITTER RECOMMENDATION IS TO	 DECREASE NUMBER OF HOURS AT INITIAL INSPECTION OR TO MAKE REPLACEMENT MANDITORY.			1	L	7	2 	3O				A7CE    					 
1996022300013	19960223	00013	CE  	1996	2	23	96ZZZX720        	1	19960101	G	3213	50411082	BEARING         			CESSNA	421   	421C        	2076016	CE  										LT MLG LEG	GALLED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	146TJ	1858 				421C0500				AIRCRAFT OWNER REPORTED HOUR METER RUNNING CONSTANTLY.  FOUND LEFT MLG EXTENDED FULLY, ALLOWING SQUAT SWITCH TO BE UNACT	UATED AND HOUR METER TO RUN CONSTANTLY.  REMOVED LOWER LEG AND FOUND INNER, UPPER BEARING WORN/GALLED AND BINDING IN BAR	REL.  THE AIRCRAFT HAS 1,857.8 HOURS TOTAL TIME AND AD 90-02-13 IS DUE AT 2,128.0 HOURS.  SUBMITTER RECOMMENDATION IS TO	 DECREASE NUMBER OF HOURS AT INITIAL INSPECTION OR TO MAKE REPLACEMENT MANDITORY.			1	L	7	2 	3O				A7CE    					 
1996022300019	19960223	00019	CE  	1996	2	23	96ZZZX726        	1	19960201	G	2460	6041H144	RELAY           	CUTLERHAM   		CESSNA	208   	208B        	2073701	CE  										STANDBY POWER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	958FE					208B0071				STANDBY POWER REPORTED INOPERATIVE.  NO POWER OUTPUT TO BUS FROM ALTERNATOR.  FOUND DEFECTIVE STANDBY POWER RELAY.  THE 	RELAY SOLENOID SHAFT HAD DISCONNECTED FROM THE CONTACTOR BAR.  SUBMITTER STATED THIS IS THE 4TH OCCURRENCE ON DIFFERENT 	SERIAL NUMBERED AIRCRAFT.				1	H	7	1 	3T				A37CE   					 
1996022300021	19960223	00021	CE  	1996	2	23	96ZZZX728        	1	19960125	G	5521	043200121	SPAR            			CESSNA	150   	150L        	2071826	CE  										OTBD ELEV HINGE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	18519	4838 				15073909				AIRCRAFT USED AS A TRAINER.  ELEVATOR HINGE (RIB) FOR BOLT HOLE BECAME WORN.  BUSHING AND BEARING BECAME WORN.  BOLT WAS	 FOUND WORN.  BRACKET BECAME WORN.  BOLT HOLE IN RIB WAS WORN EXCESSIVELY (.25 INCH OR BETTER).   WITH OUTBOARD RIB WORN	, THIS PUT MORE SUPPORT ON BRACKET WHICH PUT MORE STRESS ON THE SPAR WHICH CAUSED SPAR TO CRACK.  SUBMITTER RECOMMENDS O	PEN ELEVATOR EVERY 1,000 HOURS TO INSPECT SPAR.			1	H	7	1 	3O				3A19    					 
1996022300116	19960223	00116	SW  	1996	2	23	96ZZZX732        	1	19960108	G	6410	206016201127	BLADE           			BELL  	206   	206L1       	1182107	SW  										T/R	BEARING CRACKED 	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2618	1761 			CS4768	45503				TAIL ROTOR BLADES, 2 EACH, HAVE BEARINGS CRACKED.  TSI, 739.1 HOURS.						1	G	7	1 	3U				H2SW    					 
1996022300117	19960223	00117	SW  	1996	2	23	96ZZZX733        	1	19960108	G	6410	206016201127	BLADE           			BELL  	206   	206L1       	1182107	SW  										T/R	BEARING CRACKED 	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2618	1761 			CS4769	45503				TAIL ROTOR BLADES, 2 EACH, HAVE BEARINGS CRACKED.  TSI, 739.1 HOURS.						1	G	7	1 	3U				H2SW    					 
1996022300118	19960223	00118	SW  	1996	2	23	96ZZZX734        	1	19960113	G	6230	206010335001	LINK ASSY       			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007F		268  		3126	45186				DRIVE LINK ASSY HAS PLAY IN EXCESS OF .25 INCH AT TWO PLACES.  SEE BELL MM L3, FIGURE 62.21.  WORN BEARINGS AND SPACERS.						1	G	7	1 	3U				H2SW    					 
1996022300119	19960223	00119	SW  	1996	2	23	96ZZZX735        	1	19960111	G	6230	206040576103	BEARING         			BELL  	206   	206L3       	1182108	SW  										MAST	FAILED          	B			WG3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	6516K	1991 			ZV1401	51391				REMOVED MAST BEARING DUE TO MAST BEARING OUTER RACE FAILURE.  INSTALLED NEW BEARING, PN 206-040-576-105, SN MB349.  FAIL	ED BEARING, TSN 1991.1 HOURS.					1	G	7	1 	3U				H2SW    					 
1996022300123	19960223	00123	NE  	1996	2	23	96ZZZX739        	1	19960109	G	7120	7630907017044	MOUNT           			SKRSKY	S76   	S76A        	8143006	NE  										FWD RT ENG COMP	HOLES WORN      	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N					760088				DURING SCHEDULED INSPECTION, FOUND THE ATTACHMENT HOLE IN OUTSIDE RT FWD TRIPOD SUPPORT TUBES WORN BEYOND LIMITS.						1	G	7	2 	3U				H1NE    					 
1996022300124	19960223	00124	NE  	1996	2	23	96ZZZX740        	1	19960109	G	7120	7630907017043	MOUNT           			SKRSKY	S76   	S76A        	8143006	NE  										FWD LT ENG COMP	HOLES WORN      	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N					760088				DURING SCHEDULED INSPECTION FOUND ATTACHMENT HOLES IN OUTSIDE LT FWD TRIPOD SUPPORT TUBES WORN BEYOND LIMITS.						1	G	7	2 	3U				H1NE    					 
1996022300130	19960223	00130	GL  	1996	2	23	96ZZZX746        	2	19960104	G	7321	25490923	FUEL CONTROL    		23005290    	SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30      	03013	GL  					NR 1 ENGINE	WATER CONTAM    	B			ALGR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			HO	HOVERING       	1			SW	03	701AL	5992 			331729	760238	890101S			DURING FLIGHT CHECK/HOVER, COMPRESSOR STALLED.  REMOVED FROM ENGINE, INSPECTED PX-AIR CIRCUIT ON FUEL CONTROL, FOUND EXC	ESSIVE AMOUNT OF WATER.					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996022300384	19960223	00384	EU  	1996	2	23	96ZZZX748        	1	19960125	G	3230	C23554104	ACTUATOR        			AMD   	FALC10	FALCON10    	2730101	EU  										RT MLG	DEFECTIVE       	D	L			O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	23	191MC	9828 	23   		45	30				UNABLE TO OBTAIN RT MLG GREEN LIGHT.  FLYBY INDICATED GEAR DOWN - UNABLE TO VERIFY LOCKED.  RT MLG FOLDED ON LANDING.  I	NVESTIGATION REVEALED RT MLG DOWNLOCK WAS NOT LOCKING.  RT MLG ACTUATOR DEFECTIVE.					2	L	7	2 	4F				A33EU   					 
1996022300385	19960223	00385	NE  	1996	2	23	96ZZZX749        	2	19960117	G	7210	7757964	TAB WASHER      	HAMSTD      	GC49        	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  					DRV GR RET NUT	BROKEN          	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	95MQ				UDAG0356	340A095				GEARBOX RETURNED FOR:  PROP SHAFT SEAL RUNNER HAS CADMIUM PLATING MISSING.  AT DISASSEMBLY, DISCOVERED TABBED WASHER WAS	 BROKEN INTO 3 PIECES.  DRIVE GEAR RETENTION NUT WAS REMOVED WITH NO TORQUE APPLIED.  THE TABBED WASHER HAS BEEN SUPERSE	DED BY 7895922.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1996022300390	19960223	00390	SO  	1996	2	23	96ZZZX754        	1	19960128	G	5610	1159SCB31023	WINDSHIELD      		PPG         	GULSTM	G1159 	G1159A      	3970109	SO  										COPILOT	CRACKED         	E				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			SW	05	300WY	3633 			85H616058	427				AT CRUISE, FL 410, WITH WINDSHIELD HEAT ON, OUTER PANE OF COPILOT'S WINDSHIELD SPIDER-CRACKED.  THE CREW BEGAN A DESCENT	 AND LANDED AT THE NEAREST AIRPORT, INSPECTED THE WINDOW AND WITH FLIGHT MANUAL PROVISO, FLEW TO HOME BASE.  NO PRIOR WA	RNING OR INDICATION OF FAILURE WAS PRESENT.				2	L	7	2 	4F				A12EA   					 
1996022300391	19960223	00391	CE  	1996	2	23	96ZZZX755        	1	19960105	G	2434	15838162	ROTOR ASSY      		30B10719A   	LEAR  	35    	35A         	5170602	CE  										DC GENERATOR	FAILED          	B			BHKR	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	21	190DA		49   		1691	156				DC GENERATOR SOLD AS OVERHAULED EXCHANGE UNIT.  FAILED IN-FLIGHT.  BEARINGS DID NOT FAIL.  SUSPECT THE ROTOR ASSY RETAIN	ING BAND/BANDS SEPARATED CAUSING SEVERE DAMAGE TO THE GENERATOR SUB-ASSEMBLIES.  FUTURE OVERHAULS/REPAIRS WILL REQUIRE 1	0X MAG AND PROBE INSPECTION TO ENSURE INTEGRITY OF SPOT WELDS.				2	L	7	2 	4F				A10CE   					 
1996022300394	19960223	00394	SW  	1996	2	23	96ZZZX758        	1	19960123	G	3230	750069501	SHAFT           			GULSTM	690TP 	690A        	0141722	SW  										NLG DRAG BRACE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	53RF					11153				REMOVED SHAFT DURING 5-YEAR GEAR INSPECTION.  FOUND CRACKED AT ATTACH BOLT HOLES FOR DRAG BRACE ON NOSE LANDING GEAR.  T	HIS SHAFT IS NOT PART OF GEAR INSPECTION, BUT SHOULD BE.  SUSPECT IMPROPER DRAG BRACE PRELOAD AND/OR HARD NOSE LANDINGS 	OVER A PERIOD OF TIME.  SUBMITTER SUGGESTED PART SHOULD BE REMOVED AND INSPECTED DURING ANY NOSE GEAR REPAIR AND DURING 	5-YEAR GEAR INSPECTION.			1	H	7	2 	3T				2A4     					 
1996022300396	19960223	00396	EU  	1996	2	23	96ZZZX760        	1	19960117	G	5400	HC361C0043000	BRACKET         			BAG   	BAE146	BAE146200A  	1500266	EU  										NR 4 PYLON	BROKEN          	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION, FOUND BOTH LEFT SIDE BRACKETS SUPPORTING PRESSURE REGULATING/ISOLATION VALVE BROKEN IN NR 4	 PYLON.  REPLACED BRACKETS.  REFERENCE:  OPERATOR CONTROL NR A6WR95059.					2	H	7	4 	4F			RT	A49EU   					 
1996022300397	19960223	00397	EU  	1996	2	23	96ZZZX761        	1	19960117	G	2710	HC270H0135006	CONTROL CABLE   			BAG   	BAE146	BAE146200A  	1500266	EU  										AILERON	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION FOUND AILERON INTERCONNECT CABLES CORRODED AT WING ROOT PULLEYS.  REPLACED CABLES.  REFERENC	E:  OPERATOR CONTROL NR A6WR95063.					2	H	7	4 	4F			RT	A49EU   					 
1996022300398	19960223	00398	SW  	1996	2	23	96ZZZX762        	1	19960201	G	3260		WIRE            			GULSTM	560   	560         	0141402	SW  										RT WS 54.07	CHAFED          	B			CNQR	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CE	07	502T	3166 				5600153				FLIGHT CREW REPORTED A GEAR UNSAFE LIGHT WITH GEAR DOWN AND THREE GREEN (NO HYDRAULIC POWER ON LIGHT), ANTI-SKID INOPERA	TIVE LIGHT ON AND GEAR HORN SOUNDING.  FOUND WIRING CHAFED/DAMAGED AT RT WS 54.07 RIB FEED-THROUGH IN THE TRAILING EDGE.	  REPAIRED WIRING, SECURED AND PROTECTED IAW CESSNA SB 560-24-15, REVISION 1.				1	H	7	2 	3O				6A1     					 
1996022300402	19960223	00402	WP  	1996	2	23	96ZZZX766        	2	19960108	G	7250	31038391	ROTATING SEAL   		31070852    						GARRTT	TPE331	TPE33112UAR 	01514	WP  					1ST STAGE TURB	FLANGE CRACKED  	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25		9888 			9233151431		P70015			DURING SCHEDULED HOT SECTION INSPECTION, FOUND PART CRACKED AT SEAL FLANGE.  NO SIGNS OF ABNORMAL OPERATION WERE EVIDENT	.  SUBMITTER STATED THIS IS A CRITICAL LIFE-LIMITED COMPONENT.  LIMIT IS 10,000 CYCLES.  THIS IS THE 25TH MALFUNCTION/DE	FECT REPORT SUBMITTED BY THIS REPAIR STATION ON THIS PROBLEM.  CYCLES, 10,291.									4	T			E4WE				 
1996022300403	19960223	00403	WP  	1996	2	23	96ZZZX767        	1	19960126	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  	DC9   	DC982       	3022082	WP  										WHEEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09										FATIGUE RELATED FAILURE OF MD80 WHEEL TIE BOLTS.  INSUFFICIENT TIE BOLT PRELOAD TORQUE.  SUBMITTER STATED TO USE SNUG AN	GLE TORQUE METHOD.					2	L	7	2 	4F				A6WE    					 
1996022300404	19960223	00404	WP  	1996	2	23	96ZZZX768        	1	19960123	G	2612	355900575	FIRE LOOP       			CVAC  	440   	440         	2422902	WP  										NR 1 ENG NACELLE	CHAFED          	C			OGCB	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			GL	23	171FL					318				FIRE LOOP HAD 3 CHAFE MARKS CAUSING A FALSE FIRE WARNING, LIGHT AND BELL TO SOUND.  FOUND LOOSE MOUNTING CLAMP ON FIRE L	OOP, LETTING LOOP CHAFE ON SCAT TUBING.  FOUND WEAK MOUNTING CLAMP.  REPLACED WITH A NEW CLAMP.  REFERENCE:  OPER CONTRO	L NR DJSA95.				2	L	7	2 	4R				6A6     					 
1996022300406	19960223	00406	CE  	1996	2	23	96ZZZX770        	1	19960123	G	5610	1013840258	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  										COPILOT	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	84				88H0403469	FF19				COPILOT'S WINDSHIELD CRACKED IN CENTER OF WINDOW - TOP-TO-BOTTOM (OUTSIDE PLY ONLY).  SUBMITTER STATED IT LOOKS LIKE A B	UILD-UP OF STATIC ELECTRICITY.					2	L	7	2 	4T				A24CE   					 
1996022300408	19960223	00408	SO  	1996	2	23	96ZZZX772        	2	19960101	G	8530	5397402	SHAFT           			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ROCKER SHAFT	WORN            	B			ADKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	6824Z	1286 				340A1202	276659R			DURING REMOVAL OF A CYLINDER FOR REPAIR, THE ROCKER ARM SHAFTS WERE FOUND WORN DOWN .035 INCH ON ONE SIDE OF THE SHAFT. 	 THIS CONDITION WAS FOUND ON ALL 12 SHAFTS FOR THIS ENGINE.					1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996022300679	19960223	00679	CE  	1996	2	23	96ZZZX773        	1	19960130	G	2520	521912514	SEAT            			CESSNA	402   	402C        	207590R	CE  										PASSENGER	SEPARATED       	E		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	2610Z	107  				402C0068				WHILE LOADING PASSENGERS FOR A ROUTINE FLIGHT, ONE PASSENGER (WEIGHT, APPROX 200 POUNDS) PUSHED HIMSELF BACK AGAINST THE	 SEAT BACK AND THE SEAT SEPARATED FROM ITS BASE.  SEATS INSTALLED IN THIS AIRCRAFT ARE THE 'ENVIROFORM' SEATS THAT HAVE 	BEEN STC'D TO ELIMINATE CESSNA MEB 87-9, REVISION 2, DATED 12-16-88.  UPON INSPECTION OF THIS SEAT, DETERMINED THAT APPR	OXIMATELY 75 PERCENT OF THE MATERIAL USED TO BOND THE SEAT TO ITS BASE WAS STUCK TO THE SEAT BUCKET.  VERY LITTLE BONDIN	G MATERIAL WAS FOUND ON THE SEAT BASE.  STRONGLY RECOMMEND FREQUENT INSPECTION OF THESE SEATS AND IF ANY CRACKS OR OTHER	 ABNORMALITIES ARE FOUND, THAT CESSNA SERVICE KIT 421-135A BE INSTALLED AS SOON A POSSIBLE.	1	L	7	2 	3O				A7CE    					 
1996022300680	19960223	00680	CE  	1996	2	23	96ZZZX774        	1	19960108	G	2820	05160161	LINE            			CESSNA	172   	172P        	2072436	CE  										LT AFT TANK FEED	CLOGGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	52119	6800 				17274418				TWO SEPARATE OCCURRENCES OF THE ENGINE 'SURGING' AT FULL POWER WITH LESS THAN 16 GALLONS TOTAL FUEL ON BOARD.  COULD NOT	 DUPLICATE ON THE GROUND.  WITH FULL TANKS, COULD NOT DUPLICATE AT NORMAL FLIGHT ATTITUDES.  ENTIRE FUEL SYSTEM DISASSEM	BLED AND CLEANED, FOUND INSECT NEST AT AFT LEFT FUEL TANK FEED LINE.  RESEARCHED LOGS, WINGS WERE REMOVED DUE TO ACCIDEN	T (5-88), AIRCRAFT WAS REPAIRED AND RETURNED TO SERVICE (1-89).  SUSPECT INSECT NEST HAS BEEN THERE SINCE '89.  (AIRCRAF	T TT AT WING REMOVAL, 3,814.0 HOURS.  CURRENT AIRCRAFT TT, 6,800.0 HOURS.		1	H	7	1 	3O			NT	3A12    					 
1996022300681	19960223	00681	EA  	1996	2	23	96ZZZX775        	2	19960201	G	8530	7380685	PUSHROD         								LYC   	O235  	O235L2C     	41505	EA  					CYLINDER	BALL SEPARATION 	D		A		K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	11							L1840015			370 HOURS AFTER OVERHAUL, ENGINE VIBRATION WAS DETERMINED TO BE CAUSED BY BALL END SEPARATION FROM PN 73806-85 PUSHROD. 	 PUSHROD WAS REPLACED AND ENGINE VIBRATION WAS BACK TO NORMAL.  AD'S 80-25-02R2 AND 95-03-10 DO NOT PERTAIN TO THESE PUS	HRODS.									3	O			E223				 
1996022300682	19960223	00682	SO  	1996	2	23	96ZZZX776        	1	19960129	G	7110	9856212	COWL SEAL       		9856202     	PIPER 	PA32  	PA32301T    	7103209	SO  										ENG TOP COWL	CHAFE PROP LEAD 	B	S	A	EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	8210H	2100 				32R8229064				AS AIRCRAFT ACCUMULATES HOURS, THE LONG HEAVY ENGINE SAGS ALLOWING TOP COWL PROP SHAFT SEAL TO RUB PROP SHAFT.  THIS RUB	 HAS REMOVED ALL INSULATION FROM PROP DEICE LEADS RUNNING ALONG PROP SHAFT EXPOSING THE BARE WIRES.  TRIED PUSHING UP ON	 NOSE OF COWL AND THEN TIGHTENING COWL TO FUSELAGE SCREWS.  THIS IS A TEMPORARY FIX FOR THE ATTACH SCREW HOLES ARE ELONG	ATED WHICH ALLOWS THE COWL TO AGAIN SAG OVER A SHORT PERIOD OF TIME.  SUBMITTER STATED EITHER THE SEAL SHOULD BE REMOVED	 OR THE LOWER COWL HAVE A SUPPORT ADDED.		1	L	7	1 	3O				A3SO    					 
1996022300684	19960223	00684	SO  	1996	2	23	96ZZZX778        	2	19960101	G	7322		CARBURETOR      			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300A       	17022	SO  					CARB THROAT	MOUSE FOD       	D		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			NE	05	2754L					17255954				INVESTIGATION AFTER ENGINE FAILURE DISCOVERED A MOUSE LODGED IN THE CARBURETOR THROAT.  THE DESIGN OF THE CABIN/CARBURET	OR HEAT SYSTEM LEAVES AN OPEN PATH FROM THE CARBURETOR AIR BOX TO THE CABIN HEAT CONTROL VALVE ASSEMBLY.  MICE CAN ENTER	 VIA THE CABIN OR THE ENGINE COMPARTMENT.  SUBMITTER STATED SOME TYPE OF SCREEN COULD PREVENT THIS.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1996022300685	19960223	00685	EA  	1996	2	23	96ZZZX779        	2	19960123	G	7322	13662	FLOAT BRACKET   		MA45        	CESSNA	177   	177         	2073704	CE  	LYC   	O360  	O360A1F6    	41514	EA  					CARBURETOR	BROKEN          	B	S		SL5R	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NE	03	34102		500  		75020609	17701642	L1573636A			ENGINE LOST POWER IN CRUISE FLIGHT.   AFTER SAFE LANDING AT NEARBY AIRPORT, REMOVED CARBURETOR AND DISASSEMBLED.  FOUND 	FLOAT BRACKET BROKEN IN BEND RADIUS ALLOWING EXCESS FUEL TO ENTER CARBURETOR WHEN FLOAT VALVE COULD NOT SEAT.  BEND RADI	US OF FLOAT BRACKET APPEARED TO BE 90 DEGREES.  SUBMITTER STATED LARGER BEND RADIUS MIGHT PREVENT UNUSUAL STRESSES IN TH	E METAL REDUCING THE POSSIBILITY OF BREAKAGE.			1	H	7	1 	3O	3	O	NT	A13CE   	E286				 
1996022300686	19960223	00686	EA  	1996	2	23	96ZZZX780        	2	19960125	G	7210		BEARING         			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6A20      	52043	EA  					RED GEAR 1ST STG	FAILED          	D				K				NONE                    				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CE	01	5WG					LJ289	PCE21824			FIRST STAGE REDUCTION GEAR BEARING FAILED CAUSING GEAR TO BIND OR SEIZE CAUSING POWER TURBINE SHAFT TO SHEAR CAUSING ENG	INE TO STOP.  CAUSE OF BEARING FAILURE UNKNOWN.					1	L	7	2 	3T	3	T		3A20    	E4EA				 
1996022300689	19960223	00689	SO  	1996	2	23	96ZZZX783        	1	19960124	G	3260	487869	SWITCH          			PIPER 	PA23  	PA23250     	7102308	SO  										NLG	OUT OF ADJUST   	E				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			GL	03	54231					277554025				PILOT COULD NOT GET DOWN AND LOCKED INDICATION OF THE NOSE GEAR.  UPON SUCCESSFUL LANDING (GEAR WAS, IN FACT, DOWN AND L	OCKED), IT WAS NOTED THE SWITCH AND BRACKET ASSEMBLY WERE NOT MAKING CONTACT.  SWITCH IS ADJUSTABLE AND SUBMITTER SUGGES	TS CAREFUL INSPECTION BE MADE AT SCHEDULED INSPECTIONS TO VERIFY SWITCH IS MAKING POSITIVE CONTACT.				1	L	7	2 	3O				1A10    					 
1996022300691	19960223	00691	SO  	1996	2	23	96ZZZX785        	1	19960125	G	3231	91929	SWITCH          		LSM100297   	PIPER 	PA24  	PA24260     	7102406	SO  										NLG DOOR	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	25	8665P	138  				244112				PILOT REPORTED SELECTING GEAR UP AND HAVING GEAR SOLENOID AND LIGHTS' CIRCUIT BREAKER TRIP.  AIRCRAFT HAS A WHOLLY COWL 	CONVERSION FROM LOPRESTI.  PILOT EXPERIENCED REDUCED RUDDER CONTROL, BUT WAS ABLE TO MAKE AN UNEVENTFUL LANDING.  AIRCRA	FT WAS FOUND TO HAVE HAD THE NOSE GEAR DOORS CLOSE ON THE EXTENDED NOSE GEAR CAUSING THE CIRCUIT BREAKER TO OVERLOAD AND	 REDUCING RUDDER CONTROL THROUGH NOSE GEAR INTERCONNECT.  FOUND THE UP-LIMIT SWITCH ON NOSE GEAR DOOR MOTOR HAD FAILED G	IVING A FALSE READING TO THE RELAY BOX ALLOWING THE DOORS TO GO OUT OF SEQUENCE.		1	L	7	1 	3O				1A15    					 
1996022300692	19960223	00692	EA  	1996	2	23	96ZZZX786        	2	19960201	G	8530	73806V	PUSHROD         								LYC   	O235  	O235L2C     	41505	EA  					CYLINDER	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11							L1610415			ENGINE WAS OVERHAULED BY FACTORY 2-20-95.  DURING STC'D CONVERSION PRIOR TO INSTALLATION IN AIRCRAFT, ALL EIGHT PUSHRODS	 WERE FOUND TO BE P/N 73806 'V' PUSHRODS.  SUBMITTER STATED AD 95-03-10 DOES NOT COVER THIS ENGINE (BUT SHOULD).  FACTOR	Y WAS NOTIFIED AND REPLACEMENT PUSHRODS INSTALLED.									3	O			E223				 
1996022300693	19960223	00693	SO  	1996	2	23	96ZZZX787        	1	19960131	G	6120	554070	CONTROL CABLE   			PIPER 	PA31  	PA31P       	7103120	SO  										RT PROP CONTROL	BROKEN          	B			EKIR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	110SK	4742 				31P7630006				RIGHT PROPELLER CONTROL CABLE BROKE ABOUT 12 INCHES AFT OF GOVERNOR ATTACHMENT.  NO PRIOR INDICATION OF CABLE FAILURE. P	ROPELLER CONTROL OPERATED SMOOTHLY.					1	L	7	2 	3O			 	A8EA    					 
1996022300694	19960223	00694	CE  	1996	2	23	96ZZZX788        	1	19960201	G	2731	1695240871	ROD             			BEECH 	23    	C23         	1151242	CE  										TAB PUSH/PULL	END DETACHED    	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	5167M	6932 				M2043				DURING PRE-FLIGHT, THE ELEVATOR TRIM TAB TO TRIM ACTUATOR PUSH/PULL ROD FOUND WITH AFT CLEVIS PUSHED OUT OF ROD SHEARING	 2 RIVETS.  ROD WAS ICE FILLED DUE TO NO DRAIN HOLES TO PERMIT WATER TO DRAIN.  SUBMITTER SUGGESTS PUSH/PULL ROD ASSY BE	 MODIFIED TO LET WATER DRAIN OUT.				1	L	7	1 	3O				A1CE    					 
1996022300695	19960223	00695	EA  	1996	2	23	96ZZZX789        	2	19960111	G	8520	LW16514	CAMSHAFT        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					GOV DRV END	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2199Z	1020 				447995297	L52672T			AT AN ANNUAL INSPECTION, THE GOVERNOR DRIVE COVER PLATE WAS REMOVED IN AN ATTEMPT TO STOP AN OIL LEAK.  THIS EXPOSES THE	 FWD END OF THE CAM AND A CRACK WAS DISCOVERED EXTENDING FROM A SHARP CORNER IN THE KEYWAY.  RECOMMEND A MODIFIED KEYWAY	 WITH A RADIUS IN THE CORNERS TO RELIEVE STRESS AREA.  ALSO, RECOMMEND PERIODIC INSPECTION OF AREA.				1	L	7	2 	3O	3	O		A19S0   	E286				 
1996022300703	19960223	00703	CE  	1996	2	23	96ZZZX797        	1	19960129	G	5740	50110241	FITTING         			CESSNA	402   	402C        	207590R	CE  										RT REAR WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6838A	4047 				402C0470				AT ANNUAL INSPECTION, CORROSION WAS FOUND ON THE BOTTOM RIGHT REAR WING SPAR ATTACH FITTING.  THE FITTING WAS REPLACED.						1	L	7	2 	3O				A7CE    					 
1996022300704	19960223	00704	SO  	1996	2	23	96ZZZX798        	2	19960126	G	8540	63217H	QUILL SHAFT     			CESSNA	421   	421A        	2076012	CE  	CONT  	O520  	GTSIO520D   	17032	SO  					LT ENG DRV GEAR	FAILED          	B			EKIR	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			WP	07	200CH	1320 	481  			421A0102	219168R			LEFT ENGINE QUIT ON CLIMB-OUT.  PROP FEATHERED AIRCRAFT, MADE SAFE LANDING.  FOUND HOLE IN CASE UNDER INTERCOOLER FROM F	AILED CONNECTING ROD.  PROP TURNS FREELY.  ENGINE NOT TORN DOWN AT THIS DATE.  SUBMITTER SUSPECTS QUILL SHAFT FAILED ALL	OWING ENGINE TO OVERSPEED.  WILL SUBMIT FOLLOW-UP M OR D WHEN ENGINE IS TORN DOWN.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996022300709	19960223	00709	SO  	1996	2	23	96ZZZX803        	1	19960122	G	3320		BULB            			GULSTM	G1159 	G1159B      	3953535	SO  										CABIN	BURNING END     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	48EC					009				AEROSPACE LIGHTING AD'S HAVE BEEN ISSUED, BUT THIS HAS NOT CORRECTED THE PROBLEM.  FLUORESCENT BULB ENDS ARE STILL BURNI	NG OFF.  SUBMITTER SUGGESTS POSSIBLE CABIN FIRE COULD RESULT.					2	L	7	2 	4F			RT	A12EA   					 
1996022300710	19960223	00710	EU  	1996	2	23	96ZZZX804        	1	19960118	G	2435	23080005	STARTER/GEN     			BRAERO	DH125 	BAE125800A  	1500285	EU  										LT START/GEN	BEARING FAILED  	H				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			GL	07	600LS		607  		3031	NA0411				AIRCRAFT INCURRED VIBRATION IN-FLIGHT CAUSING DEVIATION TO NEAREST AIRPORT.  UPON INVESTIGATION, FOUND LEFT STARTER/GENE	RATOR BEARING DETERIORATED.  STARTER/GENERATOR HAD LATEST BEARING INSTALLED SB 23080-XXX-24-01.  REPLACED STARTER/GENERA	TOR WITH OVERHAULED UNIT.  OPS CHECK GOOD.				2	L	7	2 	4F			RT	A3EU    					 
1996022300711	19960223	00711	SO  	1996	2	23	96ZZZX805        	1	19960123	G	2820	6010026D0150	HOSE            			GULSTM	G1159 	GIV         	3980115	SO  										FUEL PUMP	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	11	971L	3431 				1116				PERFORMED A 72-MONTH INSPECTION.  DURING DOWN TIME, AIRCRAFT WAS DEFUELED AFTER COMPLETION OF INSPECTION.  WHEN THE AIRC	RAFT WAS REFUELED, ALL 4 FUEL BOOST PUMP VAPOR HOSES WERE NOTED LEAKING UNDER STATIC PRESSURE.  CUSTOMER BULLETIN NR 15 	IS ASSOCIATED WITH THESE NOSES, BUT DOES NOT INCLUDE THIS PRODUCTION NR 1116.				2	L	7	2 	4F			RT	A12EA   					 
1996022300712	19960223	00712	EU  	1996	2	23	96ZZZX806        	1	19960113	G	3231	283002401	CONTROL ROD     			ISRAEL	1124  	1124A       	4500103	EU  										NLG DOOR	BROKE           	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	730CA	5100 				295				LEFT NOSE GEAR DOOR VERTICAL CONTROL ROD - ROD END BROKE OFF WHEN GEAR LOWERED.  ROD END CRACKED IN THREAD LINE WHERE SC	REWED INTO ACTUAL ROD END.  DARK LINE ON CROSS SECTION INDICATED CRACK NOT NEW.  SUBMITTER STATED STRESS POSSIBLE FROM D	OORS BEING ADJUSTED TOO TIGHT.   REPLACED ROD WITH NEW PART AND ADJUSTED IAW MM 32-20-00, PAGE 217.				2	M	7	2 	4F				A2SW    					 
1996022300713	19960223	00713	CE  	1996	2	23	96ZZZX807        	1	19960104	G	5312	551104013	BOX             			CESSNA	500   	500CESSNA   	2076602	CE  										INST PANEL	CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	891CA	6541 	6541 			5000168				WHILE PERFORMING PHASE 1-5 INSPECTION, FOUND CRACK ON FORWARD PRESSURE BULKHEAD BOX.  CRACK WAS AT RIVET WHICH CONNECTS 	INSTRUMENT PANEL ANGLE TO BULKHEAD.  FACTORY HAD NO APPROVED REPAIR.  DER FORM 8110 OBTAINED FOR REPAIR.  SUBMITTER STAT	ED THIS IS THE SECOND AIRCRAFT FOUND BY THIS STATION WITH THE SAME EXACT CRACKED PRESSURE BULKHEAD WITHIN THE LAST YEAR.				1	L	7	2 	4F				A22CE   					 
1996022300714	19960223	00714	SO  	1996	2	23	96ZZZX808        	1	19960104	G	5620	56676002	WINDOW          			PIPER 	PA42  	PA42        	7104202	SO  										FUSELAGE SIDE	CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	18AF	3608 				428001063				WHILE PERFORMING PIPER SB 984, INSPECTION OF FUSELAGE SIDE WINDOWS, FOUND ALL WINDOWS HAD CRACKS IDENTIFIED IN SB 984. A	LL BUT 3 WERE BEYOND LIMITS.  ALL COCKPIT AND SIDE WINDOWS WERE REPLACED WHEN PARTS BECAME AVAIILABLE.  SUBMITTER SUGGES	TS C/W MANDATORY SB 984 AS SOON AS POSSIBLE.  CRACKS ARE NOT VISIBLE WITHOUT PROPER INSPECTION TOOL CALLED OUT IN SERVIC	E BULLETIN.			1	L	7	2 	4T				A23SO   					 
1996022300715	19960223	00715	GL  	1996	2	23	96ZZZX809        	3	19960124	G	6114		HUB             													HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	WRONG BOLTS     	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03								CK4333A		FBO PURCHASED 2 ZERO TSO PROPELLERS FROM A PROPELLER SHOP AND SENT TO LOCAL PROP SHOP TO HAVE THE CORRECT HUB BOLTS INST	ALLED.  AFTER RECEIPT BY PROP SHOP, THE FOLLOWING DISCREPANCIES WERE NOTED.  HUB BOLTS INSTALLED WERE WRONG PART NUMBER.	  THE WRONG BOOT PART NUMBER WAS INSTALLED.  THE HUB MODEL WAS INCORRECTLY STAMPED.  THE TRACK BETWEEN BLADES WAS MEASUR	ED AT .2812 INCH, .0625 INCH IS ALLOWED.  PROPELLER WAS RED TAGGED AND RETURNED TO FBO.													5	C	P25EA	 
1996022300718	19960223	00718	CE  	1996	2	23	96ZZZX812        	1	19960124	G	2434	66082019	GENERATOR       	BENDIX      	30310719A   	LEAR  	35    	35A         	5170602	CE  										LT ENGINE	FAILED          	B			GW4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	190DA				1691	156				CATASTROPHIC FAILURE OF NR 1 DC GENERATOR.  LOG BOOKS WERE NOT AVAILABLE, BUT ESTIMATED TSO TO BE 45-50 HOURS.  CAUSE UN	KNOWN DUE TO SEVERE DAMAGE OF THE GENERATOR.					2	L	7	2 	4F				A10CE   					 
1996022300719	19960223	00719	WP  	1996	2	23	96ZZZX813        	2	19960103	G	7250	31038393	ROTATING SEAL   								GARRTT	TPE331	TPE33112UAR 	01514	WP  					1ST STAGE TURB	FLANGE CRACKED  	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25		7218 					P70104			DURING INSPECTION FOR METAL CONTAMINATION, FOUND PART CRACKED AT SEALING FLANGE.  THIS IS A CRITICAL LIFE-LIMITED COMPON	ENT.  LIFE-LIMIT IS 20,000 CYCLES.  SUBMITTER STATED THIS IS THE 24TH MALFUNCTION/DEFECT REPORT SUBMITTED ON THIS PART B	Y THIS REPAIR STATION.									4	T			E4WE				 
1996022300724	19960223	00724	EU  	1996	2	23	96ZZZX818        	1	19960123	G	5542	S5547000001600	SKIN            			AEROSP	ATR42 	ATR42300    	8680920	EU  										RUD LT/RT WL7058	CRACKED         	B			FI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	4211G	12903				178				RUDDER SKIN HAS CRACKS COMING FROM THE LEFT AND RIGHT SPRING TAB WEIGHT CUT OUTS.  THE CRACKS ARE APPROXIMATELY 1.2 INCH	ES TO 1.5 INCHES AND ARE EMITTING FROM THE AFT SIDE OF CUT OUTS.  SUSPECT CAUSE IS THE WEIGHT SUPPORT ROD IS HITTING THE	 RUDDER SKIN.  RECOMMEND PERIODIC INSPECTION OF RUDDER SKIN AREA UNDER FAIRING.				2	H	7	2 	4T			RT	A53EU   					 
1996030100218	19960301	00218	EU  	1996	3	1	96ZZZX819        	1	19960115	G	7921	TB1053015101	BAFFLE          			SOCATA	TB9   	TB9         	8680694	EU  										OIL COOLER	CRACKED         	B			DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	144ER	591  				1339				BAFFLE OIL COOLER IS CRACKING AROUND OIL COOLER MOUNT POINT.  SUBMITTER STATED BAFFLE NEEDS TO BE MADE FROM THICKER MATE	RIAL.  THIS PROBLEM IS A COMMON OCCURRENCE.  (SEE PREVIOUS M OR D REPORTS).					1	L	7	1 	3O			NT	AS1EU   					 
1996030100219	19960301	00219		1996	3	1	96ZZZX820        	4	19960117	G	2210	065504601	TRIM MONITOR    	KING        	KTA435      	LEAR  	35    	31A         	5170531	CE  										AUTOPILOT	FAILED          	C		A		O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CE	07	92UG	610  			1319	050				ON THREE SEPARATE OCCASIONS, AIRCRAFT HAS BEEN DEICED.  ON ALL THREE OCCASIONS, THE AUTOPILOT QUIT SHORTLY AFTER TAKEOFF	.  INVESTIGATION REVEALED THE TRIM MONITOR BOX MOUNTED AT THE BASE OF VERTICAL FIN SPAR (AFT SIDE) WAS SATURATED WITH DE	ICING FLUID.  KING RADIO AND LEARJET WERE CONTACTED ABOUT THE PROBLEM.  SUBMITTER RECOMMENDS 1)  SHIELD THE MONITOR BOX 	WITH A MOISTURE GUARD, OR, 2)  RELOCATE MONITOR BOX INTO THE AFT EQUIPMENT BAY WHERE IT IS DRY.  AFTER THE ACFT SAT IN T	HE HANGAR OVERNIGHT AND DRIED OUT, THE AUTOPILOT FUNCTIONED NORMALLY.		2	L	7	2 	4F			RT	A10CE   					 
1996030100220	19960301	00220	EU  	1996	3	1	96ZZZX821        	2	19960125	G	7230		BUSHING         			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					HP COMPRESSOR	SHIFTED         	B	L		GJQR	O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			NM	01	26WP	8630 	1920 			024	8576			ENGINE HAD INTERMTTENT HIGH VIBRATION READINGS.  CREW REPORTED A BUZZ ON DESCENT AT 79 PERCENT HI PRESS ROTOR SPEED.  IN	-FLT VIB SURVEY SHOWED VIB PEAK OF 1.3 MILS CORRESPONDING TO HP ROTATIONAL FREQ AT THAT POWER SETTING.  SECONDARY SMALLE	R PEAK CORRESPONDING TO LP ROTOR NOTED.  ENG DISASSEMBLED.  SEVERAL 1ST STG HI PRESS COMPR BLADES WERE BOUND UP.  ROTOR 	DISASSEMBLED, MTNG BUSHINGS FND BACKED OUT OF PIN HOLES.  BUSHINGS SHOWED EVIDENCE OF CONTACT WITH ROTOR HUB.  LOW PRESS	 COMPR BLADE PINS CONTAMINATED WITH DIRT & RUST.  1ST STAGE HAD HEAVIEST ACCUMULATION.  2 BRACKETS HOLD OUTER DUCT TO EN	G BROKEN.  BRACKETS NEAR MNT LOC FOR AFT VIB PICK-UP.  LOCALIZED THERMAL DISTRESS TO NOZZLE GUIDE VANES & COMB CANS.	2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
1996030100223	19960301	00223	EU  	1996	3	1	96ZZZX824        	1	19960117	G	5320	HC536B1427000	PLATE           			BAG   	BAE146	BAE146200A  	1500266	EU  										FR 15-18	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING STRUCTURAL INSPECTION, FOUND TWO SUPPORT PLATES AT 3RD INTERCOSTAL INBOARD FROM LT FORWARD PASSENGER DOOR BETWEEN	 FUSELAGE FRAMES 15 AND 18 CORRODED.  REPLACED BOTH PLATES.  REFERENCE:  OPERATOR CONTROL NR A6WR95065.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996030100224	19960301	00224		1996	3	1	96ZZZX825        	1	19960208	G	2421	952B9561	WEDGE           	SUNDSTRANDEM	915F7181    															ARMATURE ROTOR	MISSING         	B			MG4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										ARMATURE ROTOR HAS BEEN REWOUND BY PERSONS UNKNOWN, WITHOUT 8 EACH BOTTOM WEDGES AS CALLED OUT IN THE SUNDSTRAND DRAWING	.  ARMATURE ROTOR WAS RECEIVD FROM NORTHWEST AIRLINES UNDER WORK ORDER NR 63336400 (R542).																		 
1996030100225	19960301	00225	SW  	1996	3	1	96ZZZX826        	1	19960114	G	6240	222375013103	TORQUE SENSOR   			BELL  	222   	222U        	1182140	SW  										MAST	FAILED          	B		A	EFLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	415MA	604  			9402R005	47658				MAST TORQUE METER FAILED AFTER 604.9 HOURS IN SERVICE.  SUBMITTER STATES EXPERIENCING FREQUENT SENSOR FAILURES.						1	G	7	2 	3U				H9SW    					 
1996030100470	19960301	00470	NE  	1996	3	1	96ZZZX829        	2	19960116	G	7250		BLADE           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE HPT	FAILURE         	B	L		DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	120JP					550468	71331			ENGINE SOUNDED STRANGE AFTER START.  TROUBLESHOT TO ENGINE INTERNAL.  SENT OUT FOR OVERHAUL.  FOUND 3 HT BLADES FAILED.						1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1996030100471	19960301	00471	CE  	1996	3	1	96ZZZX830        	1	19960105	G	2510	59711	SEAT ASSY       		59739       	RKWELL	NA265 	NA26540     	6402608	CE  										PILOT SEAT	WELD BROKEN     	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	314NT					282028				PILOT'S SEAT WOULD NOT ADJUST FORWARD AND AFT OR VERTICALLY, AND SEAT WOULD NOT SIT LEVEL.  INSPECTION FOUND SEAT STRUCT	URAL MEMBERS (WELD ASSYS) BROKEN AT WELDED AREAS.  SEPARATION OF THESE SUPPORT MEMBERS ALLOWS THE SEAT TO PARTIALLY COLL	APSE AND PREVENTS THE SEAT FROM SUPPORTING THE FULL WEIGHT OF THE PILOT.  ALSO, ANY PRESSURE APPLIED TO THE RUDDER OR BR	AKE PEDALS BY THE PILOT CAUSES THE SEAT TO SEPARATE AND MOVE.  ALL DEFECTIVE PARTS ARE TO BE REPLACED.  RECOMMEND INSPEC	TION OF PILOT'S AND COPILOT'S SEAT STRUCTURES AT NEXT SCHEDULED INSPECTION OF SABRELINER AIRCRAFT EQUIPPED WITH THIS MOD	EL SEAT.	2	L	7	2 	4J				A2WE    					 
1996030100472	19960301	00472	CE  	1996	3	1	96ZZZX831        	1	19960105	G	2510	59701	SEAT ASSY       		59731       	RKWELL	NA265 	NA26540     	6402608	CE  										PILOT SEAT	WELD BROKEN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	314NT					282028				PILOT'S SEAT WOULD NOT ADJUST FORWARD AND AFT OR VERTICALLY, AND SEAT WOULD NOT SIT LEVEL.  INSPECTION FOUND SEAT STRUCT	URAL MEMBERS (WELD ASSYS) BROKEN AT WELDED AREAS.  SEPARATION OF THESE SUPPORT MEMBERS ALLOWS THE SEAT TO PARTIALLY COLL	APSE AND PREVENTS THE SEAT FROM SUPPORTING THE FULL WEIGHT OF THE PILOT.  ALSO, ANY PRESSURE APPLIED TO THE RUDDER OR BR	AKE PEDALS BY THE PILOT CAUSES THE SEAT TO SEPARATE AND MOVE.  ALL DEFECTIVE PARTS ARE TO BE REPLACED.  RECOMMEND INSPEC	TION OF PILOT'S AND COPILOT'S SEAT STRUCTURES AT NEXT SCHEDULED INSPECTION OF SABRELINER AIRCRAFT EQUIPPED WITH THIS MOD	EL SEAT.	2	L	7	2 	4J				A2WE    					 
1996030100473	19960301	00473	SO  	1996	3	1	96ZZZX832        	1	19960130	G	2911	1356593105	ACCUMULATOR     	PARKERHANFIN		LKHEED	1329  	132925      	5263125	SO  										LT WING INBD	LEAK            	B			FGQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	01	701JH		58   		544	5230				WHEN SECURING THE AIRCRAFT, THE AUXILIARY HYDRAULIC SYSTEM WAS PRESSURIZED TO RETRACT THE SPEED BRAKE.  WHEN EXITING THE	 PLANE, A PUDDLE OF HYDRAULIC FLUID WAS NOTICED UNDER THE LT WING INBOARD OF THE MLG.  THE LEAK WAS TRACED TO THE UPLOCK	 ACCUMULATORS RELIEF HOLE INDICATING INTERNAL SEAL FAILURE.  THIS ACCUMULATOR HAD BEEN OVERHAULED 1/94 AND BOUGHT ON EXC	HANGE BASIS AND INSTALLED 9/95.			2	L	7	4 	4F				2A1SO   					 
1996030100474	19960301	00474	CE  	1996	3	1	96ZZZX833        	1	19960118	G	5412	251921617	GASKET          			LEAR  	25    	25B         	5170511	CE  										FIREWALL	WRONG PART      	B			IY2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	911JG					147				INTERNAL GASKET, PN 2519216-17, WAS INSTALLED ON THE EXTERNAL SIDE OF THE LT PYLON FIREWALL.  EXTERNAL GASKET, PN 245201	2-1, SHOULD HAVE BEEN INSTALLED.  DUE TO THIS INSTALLATION AND THE NATURAL DETERIORATION OF THESE GASKETS, SEVERE FIREWA	LL DAMAGE OCCURRED.  SUBMITTER RECOMMENDS A TIME CHANGE FOR THE GASKETS AND PARTICULAR INSPECTION IN THIS AREA DURING EN	GINE INSPECTIONS.  AFTT:  5,190.8 HOURS.  LANDINGS, 5,145.			2	L	7	2 	4J				A10CE   					 
1996030100475	19960301	00475	CE  	1996	3	1	96ZZZX834        	1	19960202	G	3230	NAS538816075	BUSHINGS        			MTSBSI	MU300 	MU300       	5780602	CE  										TORQUE KNEE	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	399RP	3562 				A020SA				UPPER TORQUE KNEE PIVOT BUSHINGS WOULD NOT ACCEPT GREASE.  DISASSEMBLED TORQUE KNEE FROM AIRCRAFT AND FOUND GREASE HOLE 	IN BUSHING NOT ALIGNED WITH GALLERY IN CASTING.  BUSHINGS SHOW NO EVIDENCE OF SPINNING IN CASTINGS.  THIS CONDITION FOUN	D ON BOTH MAIN GEAR TORQUE LINKS.				2	H	7	2 	4F			RT	A14SW   					 
1996030100476	19960301	00476	SW  	1996	3	1	96ZZZX835        	1	19960206	G	3610	2481048	DIAPHRAGM       	BENDIX      	38E852B     	GULSTM	690TP 	690A        	0141722	SW  										BLEED AIR REG	RUPTURED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	66GW					11174				DURING THE COURSE OF A 100-HOUR INSPECTION, FOUND BLEED AIR REGULATOR TO HAVE A BLOWN DIAPHRAGM.  THIS IS THE REGULATOR 	LOCATED IN AFT BAGGAGE AREA THAT REDUCES THE BLEED AIR FROM THE ENGINE DOWN TO 18 PSI TO INFLATE THE DOOR SEAL AND DEICE	 BOOTS.  SUBMITTER STATED THEY HAVE FOUND MANY REGULATORS IN THIS CONDITION.  INSTALLED AND OPS CHECKED AN OVERHAULED RE	GULATOR.  SUGGEST THE MANUFACTURER PROVIDE IMPROVED DIAPHRAGM TO BETTER HANDLE THE HEAT, AS THIS MAY BE THE CAUSE OF THE	 NUMEROUS FAILURES.		1	H	7	2 	3T				2A4     					 
1996030100477	19960301	00477	CE  	1996	3	1	96ZZZX836        	1	19960207	G	6123		AUTOFEATHER     			BEECH 	200   	200BEECH    	1152920	CE  										LT ENGNE	MALFUNCTION     	E				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	87BP					BB34				PILOT REPORTED DURING TRAINING, LEFT ENGINE WAS SHUT DOWN USING AUTOFEATHER.  ON ENGINE RESTART, LEFT PROP WOULD NOT COM	E OUT OF FEATHER.  ACFT LANDED WITHOUT INCIDENT.  NOTE:  AUTOFEATHER CHECKED OK PRE-FLIGHT RUNUP CHECK.  MAINTENANCE TRO	UBLESHOT AUTOFEATHER SYSTEM.  CHECKED DUMP SOLENOID, PRESSURE SWITCHES, RELAYS, AND WIRING.  NO DISCREPANCIES FOUND.  GR	OUND CHECKED SYSTEM - SYSTEM CHECK NORMAL PER CHAPTER 61 OF MM.  SWAPPED K2 AND K3 RELAYS FROM LEFT TO RIGHT SIDE FOR FU	RTHER TROUBLESHOOTING.		1	L	7	2 	4T				A24CE   					 
1996030100478	19960301	00478	CE  	1996	3	1	96ZZZX837        	1	19960212	G	3320	6900026	POWER SUPPLY    			BEECH 	200   	B200        	1152922	CE  										CABIN LT NR 5	FAILED          	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			EA	25	8049H	812  				BB1395				CABIN FLUORESCENT LIGHTS WERE TURNED ON FOR AN OPERATIONAL CHECK DURING A POST-FLIGHT INSPECTION.  THE LIGHTS CAME ON, B	LINKED SEVERAL TIMES, AND THE CIRCUIT BREAKER TRIPPED.  SMOKE WAS NOTED AT THE REAR OF THE CABIN.  POWER WAS IMMEDIATELY	 REMOVED FROM THE ACFT AND PROBLEM WAS TRACED TO FLUORESCENT LIGHT ASSY AT THE NR 5 LT PASSENGER WINDOW.  POWER SUPPLY W	AS FOUND BURNED AND WINDOW TRIM BURNED NEXT TO POWER SUPPLY.  THE REPLACEMENT PART SUPERSEDED TO P/N 6900080.  INSTALLED	 NEW LIGHT ASSY.  NO FURTHER DEFECTS NOTED.		1	L	7	2 	4T				A24CE   					 
1996030100481	19960301	00481	NM  	1996	3	1	96ZZZX840        	1	19960122	G	3310	761272	LIGHT ASSY      		579458      	PIPER 	PA60  	PA60601P    	7106012	NM  										ANUN PANEL	SHORTED         	B			P3NR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	13	3638T	2001 				61P080180634				PILOT NOTICED AN ELECTRICAL ARCING WHEN PUSHING ON ANNUNCIATOR PANEL DURING A NIGHT FLIGHT.  FOUND A LIGHT ASSY MOUNTED 	BEHIND ANNUNCIATOR PANEL, HAD INSUFFICIENT CLEARANCE TO THE SOLDER JOINT ON THE UPPER LEFT ANNUNCIATOR LIGHT.  RECOMMEND	 AN INSPECTION IN THIS AREA AND REMOVAL OF THE SPACER ON THE LIGHT ASSY SHAFT AND/OR SHIMMING WITH WASHERS OF THE ANNUNC	IATOR PANEL AT THE TWO MOUNTING POINTS TO ACHIEVE SOME CLEARANCE.			1	M	7	2 	3O			RT	A17WE   					 
1996030100482	19960301	00482	CE  	1996	3	1	96ZZZX841        	1	19960205	G	2130	66002073	VALVE           			LEAR  	35    	35LEAR      	5170600	CE  										CABIN PRESS	DEFECTIVE       	B			BSYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	813AS	10416			47319	167				PRESSURIZATION SAFETY VALVE WILL NOT SEAT PROPERLY.  SUSPECT CAUSE IS INTERNAL DAMAGE.  FOUND DURING SCHEDULED 600-HOUR 	OR 1200-HOUR INSPECTION CYCLE.  AD 94-26-01 IS APPLICABLE.					2	L	7	2 	4F				A10CE   					 
1996030100483	19960301	00483	NE  	1996	3	1	96ZZZX842        	2	19960116	G	7230	310463301	ANTIROTATE RING 			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	FAILED          	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	511AB					550299	70350			AFTER ENGINE START, ENGINE SOUNDED STRANGE (LIKE VACUUM CLEANER).  TROUBLESHOT AND SUSPECTED INTERNAL DAMAGE.  ENGINE RE	MOVED AND SENT FOR OVERHAUL.  FOUND THE ANTI-ROTATION RING HAD FAILED.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1996030100484	19960301	00484	EU  	1996	3	1	96ZZZX843        	1	19960129	G	3010	T700A3013002100	DEICE PIPE      			SOCATA	TBM   	TBM700      	8682000	EU  										ELEVATOR HORN	CHAFE THROUGH   	B		A	LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	700GJ	230  				102				REMOVED ELEVATOR FOR C/W SOCATA SB 70-053.  UPON REMOVAL, FOUND LT DEICE PIPE FOR ELEVATOR HORN WORN THROUGH AT ENTRANCE	 TO HORN.  THIS INSTALLATION WAS DONE AT FACTORY.  WEAR CAUSED BY LACK OF CLEARANCE AT PASS-THROUGH.  SUBMITTER STATED T	BM NEEDS TO ISSUE A SL OR SB TO IMPROVE CLEARANCE.  ALSO, REPLACED RT DEICE PIPE.				1	L	7	1 	3T			RT	A60EU   					 
1996030100486	19960301	00486	EU  	1996	3	1	96ZZZX845        	1	19960106	G	5400	F50B258700A2AAA	S-DUCT          			AMD   	FALC50	FALCON50MYST	2730106	EU  										INTAKE LT SIDE	CRACKED         	B	S		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	16R	5766 				141				DURING 2C INSPECTION, NOTICED CRACKED SPOT WELDS ON THE FORWARD S-DUCT OUTER SKIN.  SUBMITTED FINDINGS TO FALCON JET.  D	OOR '350A' MUST BE REMOVED TO VIEW THIS AREA. THIS PROBLEM IS NOT CURRENTLY ADDRESSED IN AN AD OR SB.					2	L	7	3 	4F				A46EU   					 
1996030100487	19960301	00487	NE  	1996	3	1	96ZZZX846        	2	19960206	G	7210	7895922	TAB WASHER      	HAMSTD      	775800      	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					GC49 GEARBOX	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	3903G	11548				340A0227	GEE785278			GEARBOX RETURNED TO HAMILTON STANDARD FOR FAILED BORESCOPE REPAIR.  AT DISASSEMBLY OF THE DRIVE (BULL) GEAR, HAMILTON ST	ANDARD DISCOVERED THE TABBED WASHER WAS CRACKED.  THE CRACK IS ADJACENT TO A TAB AND EXTENDS THROUGH TO THE INSIDE DIAME	TER TAB.  THE DRIVE GEAR RETENTION NUT REQUIRED 1,600 FEET/POUNDS OF TORQUE TO REMOVE.  THIS PART SUPERSEDED P/N 775796-	4.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6				 
1996030100488	19960301	00488	CE  	1996	3	1	96ZZZX847        	1	19960112	G	2120	355505242	SHUT OFF DOOR   			LEAR  	35    	35LEAR      	5170600	CE  										FIREWALL	INOPERATIVE     	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	3818N	2700 				D1047				ON ANNUAL INSPECTION, EMERGENCY AIR SHUT-OFF TO COCKPIT WAS DETERMINED NOT TO BE OPERATIVE.  FURTHER INSPECTION FOUND BE	LLCRANK LOOSE FROM 'DOOR' BY RIVETS IN BELLCRANK HAVING COME OUT OF BELLCRANK.  WHEN REMOVING UNIT FOR REPLACEMENT OF RI	VETS, HINGE HOLDING DOOR IN PLACE HAD RIVETS, ALSO PULLED OUT, LEAVING DOOR AND ONE-HALF HINGE LOOSE.  OTHER ONE-HALF OF	 HINGE ON DUCT FOUND CORRECTLY ATTACHED.  MADE REPAIRS PER 43.13 AND RETURNED TO SERVICE.  SYSTEM OPERATES NORMALLY.			2	L	7	2 	4F				A10CE   					 
1996030100489	19960301	00489	WP  	1996	3	1	96ZZZX848        	2	19960117	G	7250	8683793	STATOR          			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315     	01514	WP  					HOT SECTION	DEFECTIVE       	B	L		DJFR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23	690HF					11298	P06541C			DURING C/W WITH AD 95-16-08, FOUND HOT SECTION 3RD STATOR WAS IMPROPER DUE TO NOT BEING STAMPED OR SIGNED AND SERIAL NUM	BER OF PART NOT ENTERED.					1	H	7	2 	3T	4	T		2A4     	E4WE				 
1996030100492	19960301	00492	SO  	1996	3	1	96ZZZX851        	2	19960117	G	8520		CRANKCASE       			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NR 3 CYLINDER	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	06	7560Q					421B0346	600641			UPON INSPECTION IAW AD 77-13-22 CRANKCASE CRACKS, CRACK FOUND AT NR 3 CYLINDER UPWARDS UNDER ENGINE DATA PLATE, LENGTH U	NDETERMINED, BUT LEAKING OIL MAKES UNAIRWORTHY.  ENGINE REMOVED FROM LEFT POSITION.  ENT TT, 3,334.2 HOURS.  ENG TSMOH, 	916.3 HOURS.  NOTE:  RIGHT ENGINE HAS HEAVY CASE INSTALLED.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996030100493	19960301	00493	EA  	1996	3	1	96ZZZX852        	2	19960126	G	7414	1052947	SHAFT           		S6LN200     	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MAGNET	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	5729Y		312  		3080084	272853	L122448			REMOVED MAGNETO DURING ANNUAL INSPECTION AND NOTICED SHAFT NUT WAS COMPLETELY STRIPPED AND HELD IN PLACE ONLY BY BROKEN 	COTTER PIN.  REMOVED COTTER PIN AND NUT, FOUND SHAFT COMPLETELY STRIPPED AND BUSHING VERY LOOSE AND SLOPPY ON SHAFT.  RE	MOVED BUSHING AND FOUND SHAFT UNDER BUSHING WORN APPROXIMATELY HALF-WAY THROUGH AND WOODRUFF KEY SEVERELY DEFORMED.  DRI	VE PLATE AND SHAFT AREA UNDER DRIVE PLATE APPEAR NORMAL.			1	L	7	2 	3O	3	O		1A10    	1E4				 
1996030100494	19960301	00494	EA  	1996	3	1	96ZZZX853        	2	19960210	G	7414	66M21195	CLAMP NUT       	SLICK       	4370        	CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					RT MAG ATTACH	MISSING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	734FH				95040291	17268817	L2821736A			RIGHT MAGNETO TOP ATTACHMENT MISSING.  CLAMP, 66M21195.  WASHER, STD-475.  WASHER, STD-1727.  NUT, STD-1410.  RIGHT MAGN	ETO INSTALLED 10-12-95.  TOTAL TIME 168 HOURS.  ACFT TT 4,328.5 HOURS.					1	H	7	1 	3O	3	O	NT	3A12    	E286				 
1996030100495	19960301	00495	SO  	1996	3	1	96ZZZX854        	1	19960104	G	8011	MHB4014	STARTER         	PRESTOLITE  		PIPER 	PA31  	PA31350     	7103110	SO  										ENGINE	BURNED          	B	L		APCR	A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			NM	01	3582X					318052105				ADDENDUM TO SDR DATED 1-4-96.  RT ENGINE STARTER MOTOR FIELD WINDINGS FAILED, APPARENTLY WHILE STARTER ENGAGED TO CRANK 	THE ENG RESULTING IN A SHORT-TO-GROUND OF STARTER POWER CIRCUIT.  PILOT HAD NO INDICATIONS OF TROUBLE, AND ENG STARTED N	ORMALLY AND CONTINUED TO RUN NORMALLY DURING PRE-FLT RUN-UP.  HEAT IN STARTER CIRCUIT CAUSED STARTER SOLENOID CONTACTS T	O STICK CAUSING POWER TO CONTINUE TO FLOW TO STARTER MOTOR EVEN THOUGH STARTER SWITCH HAD BEEN RELEASED.  THE SHORT-TO-G	ROUND INSIDE THE STARTER MOTOR DELETED ACFT BATTERY AND ALTERNATORS COULD NOT KEEP UP WITH THE LOAD AND ALL ACFT SYSTEMS	 DROPPED OFF-LINE.  OCCURRED AT ROTATION ON T/O, & PILOT RETURNED TO AIRPORT.  LANDED WITHOUT RADIO COMM.	1	L	7	2 	3O				A20SO   					 
1996030100496	19960301	00496	SO  	1996	3	1	96ZZZX855        	1	19960209	G	3210	2082900	BRACE STUD      			PIPER 	PA24  	PA24250     	7102404	SO  										RT/LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	6498P	5093 				241618				REMOVED SIDE BRACE STUDS TO C/W AD 95-20-07 AND FOUND BOTH OF THEM CRACKED IN THE AREA DEPICTED IN THE AD.						1	L	7	1 	3O				1A15    					 
1996030100497	19960301	00497	EA  	1996	3	1	96ZZZX856        	2	19960206	G	8520		CRANKSHAFT      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	PITTED          	B			LK1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4333C	1679 				288416039	L1319839A			DURING 100-HOUR ENGINE INSPECTION FOR AIRCRAFT ANNUAL INSPECTION, LYC SB 505A WAS C/W AND THE CRANKSHAFT FOUND PITTED IN	 THE AREA NOTED IN SB 505A.  ENGINE WAS REMOVED AND REPLACED WITH A LYC FACTORY OVERHAULED.  AFTER REMOVAL OF THE CRANKS	HAFT PLUG, THE INTERIOR OF THE CRANKSHAFT WAS FOUND COMPLETELY PLUGGED WITH SLUDGE (1.25 POUNDS).  GENERAL CONDITION AND	 RECORDS INDICATE A WELL MAINTAINED AIRCRAFT WITH MULTI-VISCOSITY OIL CHANGES AS REQUIRED.			1	L	7	1 	3O	3	O		2A13    	E274				 
1996030100498	19960301	00498	CE  	1996	3	1	96ZZZX857        	1	19960201	G	2750	0512128	BRACKET         			CESSNA	185   	A185F       	2072821	CE  										RT FLAP PULLEY	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	205NR					3910				FLAP PULLEY BRACKET FOUND BROKEN ON RIGHT FORWARD SIDE OF FUSELAGE AT STATION 65.33.  TANGS WERE BROKEN OFF OF BRACKET. 	 AIRCRAFT HOURS, 7,000.					1	H	7	1 	3O				3A24    					 
1996030100499	19960301	00499	SO  	1996	3	1	96ZZZX858        	1	19960209	G	3231	9850602	DOOR            			PIPER 	PA32  	PA32RT300T  	7103216	SO  										LT NLG	MISADJ          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11	39526					32R7887102				LEFT NOSE LANDING GEAR DOOR ADJUSTED TOO TIGHT AGAINST AFT TOP PLATE IN WHEELWELL.  AFTER SEVERAL RETRACTIONS, DOOR PULL	ED OVER STOP PLATE AND WEDGED INTO WHEELWELL PREVENTING NLG EXTENSION.  RECOMMENDATION:  IMPROVE INSTRUCTIONS TO PIPER M	M.				1	L	7	1 	3O				A3SO    					 
1996030100501	19960301	00501	CE  	1996	3	1	96ZZZX860        	1	19960130	G	3250	508201883	BRACKET         			BEECH 	200   	200BEECH    	1152920	CE  										STEERING SUPPORT	BROKEN          	B	S	A	VE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	74GS	3006 				BB429				CUSTOMER REPORTED AIRCRAFT YAWS TO THE RIGHT WHEN LANDING GEAR IS SELECTED DOWN.  DURING TROUBLESHOOTING, FOUND STEERING	 LINKAGE SUPPORT BRACKET BROKEN AT FORWARD ATTACH POINT.					1	L	7	2 	4T				A24CE   					 
1996030100504	19960301	00504	CE  	1996	3	1	96ZZZX863        	1	19960206	G	2820	36700	VALVE           			CESSNA	340   	340CESSNA   	2076404	CE  										VAPOR RETURN	LEAKING         	B		A	DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	100HJ	2503 				3400334				WHILE PERFORMING AN ANNUAL INSPECTION ON A TWIN CESSNA, NOTED THAT FUEL WAS LEAKING FROM THE VAPOR RETURN LINE ON THE LT	 ENGINE.  UPON INVESTIGATION, DISCOVERED THE VAPOR RETURN CHECK VALVE SEAL WAS DETERIORATED ALLOWING FUEL FROM THE FULL 	MAIN FUEL TANK TO LEAK BACK DOWN THE LINE.  WHEN THE RT VALVE WAS CHECKED, IT WAS FOUND IN THE SAME CONDITION.  IT WAS F	URTHER NOTED WHEN THE FUEL QUANTITY IN THE FUEL TANKS IS LOW, FUEL WILL NOT LEAK BACK DOWN THE LINE EVEN THOUGH THE VALV	E SEAL IS FAULTY.		1	L	7	2 	3O				3A25    					 
1996030100505	19960301	00505	CE  	1996	3	1	96ZZZX864        	1	19960101	G	3297		WIRE            			BEECH 	55    	95C55       	1152708	CE  										DOWN LIMIT SW	SHORTED         	D		A		A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			WP	01	12DK					TE290				PILOT MADE UNEVENTFUL LANDING AFTER REPORTING SMOKE IN COCKPIT.  INVESTIGATION REVEALED A WIRE SHORTED AS IT PASSED THRO	UGH LIGHTNING HOLE BEHIND BATTERY SWITCH.  ONE SIDE OF WIRE WAS CONNECTED TO COMMON TERMINAL OF LANDING GEAR DOWN LIMIT 	SWITCH AND OTHER SIDE OF WIRE FOUND HANGING FREE WITH TERMINAL LUG STILL ATTACHED.  IT IS SPECULATED THE WIRE WAS DISCON	NECTED FROM THE POSITIVE UNPROTECTED (NO CIRCUIT BREAKER) SIDE OF BUSS PRIOR TO ENTERING REPAIR STATION.  THE NON-FACTOR	Y WIRE DID NOT CONFORM TO BEECHCRAFT WIRING DIAGRAM.  REPAIRS MADE TO BRING ACFT BACK INTO CONFORMITY.		1	L	7	2 	3O			 	3A16    					 
1996030100508	19960301	00508	CE  	1996	3	1	96ZZZX867        	1	19960130	G	2410	5395473000	BELT            			BEECH 	55    	95B55       	1152706	CE  										ALTERNATOR	BROKEN          	B			EIYR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			WP	07	812D	5    				TC1839				PILOT REPORTED LEFT ALTERNATOR OUT.  INSPECTION REVEALED THAT NEW CONTINENTAL ALTERNATOR BELT HAD FAILED.						1	L	7	2 	3O				3A16    					 
1996030100510	19960301	00510	SO  	1996	3	1	96ZZZX869        	2	19960208	G	8530	646279	PISTON          			CESSNA	175   	175A        	2072504	CE  	CONT  	O300  	GO300C      	17022	SO  					CYL BORE	MISMFG          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11	6950E					56450	53078C			PURCHASED 6 EACH CYLINDER POWER PACKS FROM SUPERIOR AIR PARTS.  P/N SA10200A23P.  CONTINENTAL PISTONS WERE SUPPLIED WITH	 THE POWER PACKS.  PISTONS ARE TOO LARGE FOR CYLINDER BORE AND CANNOT GET PROPER PISTON CYLINDER CLEARANCE BELOW 3RD RIN	G.  CONTINENTAL OVERHAUL MANUAL CALLS FOR 4.0476 INCH TO 4.0486 INCH BELOW THIRD RING.  NEW PISTON DIMENSIONS ARE 4.051 	INCH.  OVERHAUL MANUAL CALLS FOR .0134 INCH - .0164 INCH CLEARANCE.  ONLY HAVE .0128 INCH.			1	H	7	1 	3O	3	O		3A17    	E298				 
1996030100511	19960301	00511	SW  	1996	3	1	96ZZZX870        	1	19960126	G	3210	52352	BOLT            			SLINDS	100   	100ACMDR    	0140202	SW  										MLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	631PF	742  	742  			189				INSPECTION FOUND (CORROSION) FERROUS OXIDE DAMAGE TO BOLT ASSEMBLIES (BOTH MAIN LANDING GEAR) TO THE EXTENT THAT STRUCTU	RAL INTEGRITY HAS BEEN SERIOUSLY COMPROMISED.  P/N 52352, P/N 55450, AND P/N 58792.					1	H	7	1 	3O				1A21    					 
1996030100514	19960301	00514	SO  	1996	3	1	96ZZZX873        	2	19960123	G	8550	CH48108	FILTER          	CHAMPION    		CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE OIL	RING BROKEN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3LN	49   			F04C211	3400301				DURING INSPECTION OF OIL FILTER, THE METAL RETAINING RING BETWEEN FILTER AND RUBBER GASKET (ALL PARTS INTERNAL) WAS FOUN	D BROKEN WITH ONE-THIRD OF THE RING MISSING.  THE REMAINING PARTS OF THE RING WERE FOUND IN FILTER, ALL PIECES.  FOUND O	N TWO FILTERS.				1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996030100515	19960301	00515	SO  	1996	3	1	96ZZZX874        	1	19960115	G	5700		LIFT STRUT      			MAULE 	M5    	M5180C      	5460204	SO  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	66VJ					8077C				WHILE PERFORMING MAULE SB NR 11 (WING LIFT STRUT ASSY INSP/REPL), THREE OF THE FOUR LIFT STRUTS FAILED THE INSPECTION, B	OTH FRONT AND RIGHT REAR FAILED.  THERE WAS NO EXTERNAL VISIBILITY OF THIS PROBLEM.  THE AIRCRAFT HAS ALSO BEEN HANGARED	 SINCE NEW.  THE TOTAL TIME IN SERVICE OF THE AIRCRAFT IS 700.9 HOURS.				1	H	7	1 	3O				3A23    					 
1996030100516	19960301	00516	CE  	1996	3	1	96ZZZX875        	1	19960201	G	2730	05130633	BRACKET         			CESSNA	172   	172F        	2072414	CE  										ELEV BELLCRANK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5648R	4000 				17253275				ELEVATOR BELLCRANK ASSY BRACKET FOUND CRACKED.  REPLACEMENT PART IS MUCH HEAVIER.						1	H	7	1 	3O			NT	3A12    					 
1996030100517	19960301	00517	CE  	1996	3	1	96ZZZX876        	1	19960205	G	5511	053200150	RIB             		2432000201  	CESSNA	172   	172M        	2072418	CE  										LT HORIZ STAB	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	92747	5855 				17261613				LEFT HORIZONTAL STABILIZER HAD DAMAGE TO THE RIB AND THE LEADING EDGE.  THE RIB HAD BEEN CRUSHED AND THE SKIN AT THE RIB	 HAD A SMALL CRACK.  SUBMITTER STATED THIS DAMAGE DEVELOPED FROM THE IMPROPER HANDLING OF THE AIRCRAFT ON THE GROUND.  A	LL OTHER AREAS OF TAIL WERE INSPECTED FOR DAMAGE AND NONE WERE DETECTED.				1	H	7	1 	3O			NT	3A12    					 
1996030100518	19960301	00518	CE  	1996	3	1	96ZZZX877        	1	19960205	G	5512	053200176	SKIN            			CESSNA	172   	172M        	2072418	CE  										LT HORIZ STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	92747	5855 				17261613				LEFT HORIZONTAL STABILIZER HAD DAMAGE TO THE RIB AND THE LEADING EDGE.  THE RIB HAD BEEN CRUSHED AND THE SKIN AT THE RIB	 HAD A SMALL CRACK.  SUBMITTER STATED THIS DAMAGE DEVELOPED FROM THE IMPROPER HANDLING OF THE AIRCRAFT ON THE GROUND.  A	LL OTHER AREAS OF TAIL WERE INSPECTED FOR DAMAGE AND NONE WERE DETECTED.				1	H	7	1 	3O			NT	3A12    					 
1996030100519	19960301	00519		1996	3	1	96ZZZX878        	4	19960207	G	3441	7884604021	AMPLIFIER       	DELCO       	7890860511  															INU STAB AMP	DEFECTIVE       	B			CW7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25					0402423					INERTIAL NAV SYSTEM DEVELOPS 100 KNOT GROUND SPEED WITHIN 10 MINUTES WHILE AIRCRAFT IS STATIONARY.  STAB AMP-AZ FOUND AS	 FAULT.  STAB AMP REPLACED, SYSTEM RECALIBRATED AND TESTED TO SPECS.  UNIT HAD 3.6 HOURS SINCE LAST SERVICE AT MFG.																		 
1996030100521	19960301	00521	EA  	1996	3	1	96ZZZX880        	2	19960123	G	8520	SL78027	ROD BOLT        			PIPER 	PA44  	PA44180T    	7104404	SO  	LYC   	O360  	TO360E1A6   	41514	EA  					CONNECT ROD	NOT MARKED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	8264F					448107027	L13673			UPON INSPECTION OF NEW ROD BOLTS BEFORE INSTALLATION, DISCOVERED ONE OF EIGHT ROD BOLTS, SL78027, HAD NO HEAD MARKINGS I	DENTIFYING THE PART.					1	L	7	2 	3O	3	O		A19SO   	E26EA				 
1996030100522	19960301	00522	SO  	1996	3	1	96ZZZX881        	1	19960131	G	5312	380082	BULKHEAD        			LUSCOM	8     	8A          	8190104	SO  										FS 2.5	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	28916					1679				DURING ANNUAL INSPECTION, CRACKS WERE FOUND ON BULKHEAD AT FS 2.5 WHERE JACK STRUT ATTACHES.  JACK STRUT FITTINGS WERE A	LSO FOUND CORRODED AND WORN.  SUSPECT ROUGH OPERATION ON SKIS CAUSED CRACKS.					1	H	7	1 	3O				A694    					 
1996030100523	19960301	00523	CE  	1996	3	1	96ZZZX882        	1	19960201	G	5343	05430131	FITTING         			CESSNA	172   	172P        	2072436	CE  										NLG UPPER	LOOSE           	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	5453K	7199 				17274119				NLG FITTING IS ATTACHED BY RIVETS AND 2 NAS BOLTS.  ALL THE RIVETS WERE LOOSE AND FRETTING.						1	H	7	1 	3O			NT	3A12    					 
1996030100524	19960301	00524		1996	3	1	96ZZZX883        	4	19960207	G	2562	4520130D	BATTERY PACK    	ARTEX       	ELT1104     	PIPER 	PA46  	PA46350P    		SO  										ELT	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9275D	118  			54555	4636002				INSPECTION OF ELT CONDITION REVEALED BATTERY PACK LEAKING ELECTROLYTES FROM BATTERY CELLS.  ELT MFG DATE 1-3-95.  ELT WA	S STILL FUNCTIONAL.					1	L	7	1 	3O			RT	A25SO   					 
1996030100525	19960301	00525	CE  	1996	3	1	96ZZZX884        	1	19960125	G	5342	53120252	ATTACH PAN      			CESSNA	340   	340CESSNA   	2076404	CE  										HORIZ AFT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	4515Q	4500 				3400097				ROUTINE INSPECTION FOUND HORIZONTAL AFT ATTACH BRACE (FORWARD OF BULKHEAD) WITH 2 CRACKS IN CORNERS.						1	L	7	2 	3O				3A25    					 
1996030100526	19960301	00526	CE  	1996	3	1	96ZZZX885        	1	19960131	G	6120	C299506B0104	CONTROL CABLE   			CESSNA	172   	R172K       	2072431	CE  										GOVERNOR	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	7585X	2    				R1723334				INSTALL NEW CONTROL CABLE ASSY AS SUPPLIED BY CESSNA AIRCRAFT.  INSTALLED AND RIGGED PER CESSNA R172K SM.  ALL OPS CHECK	 OK ON GROUND.  RUN-UP OPS CHECK OK.  FLOWN FOR 2.0 HOURS, NO ATTEMPT TO MOVE CONTROL WHILE IN-FLIGHT.  UPON RETURN TO G	ROUND, GOVERNOR CONTROL CABLE ASSY FROZEN SOLID.  CABLE REMOVED AND INSPECTED.  NO DAMAGE, NO MARKS OF ANY KIND, NO KINK	S.  SUSPECT HEAT AFFECTING INTERNAL COMPONENTS.  RETURNED TO CESSNA FOR EVALUATION.			1	H	7	1 	3O				3A17    					 
1996030100527	19960301	00527	EA  	1996	3	1	96ZZZX886        	2	19960130	G	8530	73413	PUSHROD         			PIPER 	PA22  	PA22        	7102202	SO  	LYC   	O320  	O320A1A     	41508	EA  					CYLINDER NR 2	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	5788D					224464	4850			FOUND PUSHROD HOLDING VALVE OPEN.  CLEARANCE .000 INCH, CYLINDER NR 2 CLEARANCE .013 INCH SHOULD BE .028 INCH.  SEVEN HO	URS SINCE SUDDEN STOPPAGE.					1	H	7	1 	3O	3	O		1A6     	E274				 
1996030100528	19960301	00528	EU  	1996	3	1	96ZZZX887        	1	19960115	G	5522		SKIN            			BNORM 	BN2   	BN2A26      	1520226	EU  										ELEVATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	9995A	4000 				897				INSPECTED ELEVATOR AND TABS IAW SB 190 AND SB 142.  STRIPPED PAINT ON ALL HORIZONTAL TAIL FEATHERS.  FOUND NUMEROUS POIN	TS OF CORROSION.  IT EXTENDED INSIDE WHERE NOT VISIBLE FOR NORMAL INSPECTION PROCEDURES.  RIBS, REAR STRINGER, SKIN PIEC	ES.  ALL HAD CORROSION HIDDEN UNDER APPLIED PREVENTATIVE PRIMER.  INSPECTION CAN ONLY BE ACCOMPLISHED BY DISASSEMBLY.  V	ERTICAL INSPECTED PREVIOUSLY, NO CORROSION.			1	H	7	2 	3O				A17EU   					 
1996030100529	19960301	00529	SO  	1996	3	1	96ZZZX888        	1	19960124	G	2434		BRUSH HOLDER    	DELCO       	1101915     	PIPER 	PA30  	PA30        	7103002	SO  										RT ENG GEN	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	8383Y				10255	301538				RIGHT ENGINE GENERATOR INOPERATIVE.  FOUND BRUSH HOLDER BROKEN AND PIECES HAD SHORTED OUT ARMATURE.  INSTALLED REBUILT U	NIT.					1	L	7	2 	3O				A1EA    					 
1996030100531	19960301	00531	NE  	1996	3	1	96ZZZX890        	2	19960115	G	7210	310835601	SUN GEAR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					POWER SECTION	DEFECTIVE       	B			MASR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5YV	6668 			21C611	UE05	114046			ALTHOUGH ALL INDICATIONS POINT TO AN ELECTRICAL DISCHARGE, THE POSSIBILITY OF A SUN GEAR FAILURE IS NOT BEING RULED OUT.	  THE NR 6 BEARING AND THE SUN GEAR WILL BE SHIPPED FOR FURTEHR INVESTIGATION.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1996030800141	19960308	00141	WP  	1996	3	8	96ZZZX920        	1	19960109	G	5320		PANEL           			DOUG  	DC10  	DC1030      	3023501	WP  										FS 1420	CRACKED         	B			ZJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	229NW	88344	23313			46551				DURING L-CHECK, FOUND RIGHT MLG WHEELWELL OUTBOARD PANEL IN SCW 118, FS 1420, HAS A .50 INCH CRACK IN LEFT CORNER.  FABR	ICATED DOUBLER, STOP DRILLED CRACK, SEALED AND INSTALLED DOUBLER IAW SRM 53-00-01.					2	L	7	3 	4F				A22WE   					 
1996030800543	19960308	00543	CE  	1996	3	8	96ZZZX931        	1	19960118	G	7900	58551761	SEPARATOR       			CESSNA	404   	404CESSNA   	2075901	CE  										ENG AIR/OIL	FROZE           	H		A		O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	03	409EX					4040436				THE AIR OUTLETS OF THE AIR/OIL SEPARATORS FROZE OVER, APPARENTLY, FROM INTERNAL MOISTURE CAUSING ALL ENGINE OIL TO BE PU	MPED OVERBOARD ON THE LEFT ENGINE AND ALL BUT 3 QUARTS ON RIGHT ENGINE.  LEFT ENGINE FAILED DUE TO OIL STARVATION.					1	L	7	2 	3O				A25CE   					 
1996030800544	19960308	00544	CE  	1996	3	8	96ZZZX932        	1	19960209	G	5711		SPAR            			BEECH 	33    	F33A        	1151425	CE  										WING CARRY-THRU	CRACKED         	B		A	VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8253C	5583 				CE1546				FOUND CRACKS IN WING SPAR CARRY-THROUGH STRUCTURE.  AD 95-04-03, NOT APPLICABLE BY SERIAL NUMBER OF AIRCRAFT.						1	L	7	1 	3O				3A15    					 
1996030800548	19960308	00548	CE  	1996	3	8	96ZZZX937        	1	19960131	G	3213	51411035	BARREL ASSY     		51411011    	CESSNA	402   	402C        	207590R	CE  										LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	6878L	11549				402C0607				TRUNNION BARREL ASSY CRACKED AT THE TORQUE LINKS/LUGS AND IS COVERED BY CESSNA SB MEB 89-2.  SUSPECT WORN OUT OF ROUND T	ORQUE LINKS/LUGS AND TORQUE LINK BUSHINGS CAUSING SEVERE MLG SHIMMY.					1	L	7	2 	3O				A7CE    					 
1996030800549	19960308	00549	SO  	1996	3	8	96ZZZX938        	2	19960130	G	7324		LINE            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  					NR 6 NOZ B-NUT	BROKE           	H				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			SO	01	999CC					347570159	303156			FUEL LINE FROM FLOW DIVIDER TO NR 6 NOZZLE BROKE AT B-NUT NOZZLE AND SPRAYED RAW FUEL ON ENGINE.  ENGINE ROUGH, BUT NOT 	SHUT DOWN AND LANDED OK WITH NO FIRE.  VERY LUCKY!					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1996030800551	19960308	00551	CE  	1996	3	8	96ZZZX940        	1	19960209	G	5711		SPAR            			BEECH 	33    	F33A        	1151425	CE  										WING CARRY-THRU	CRACKS          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8251C	5840 				CE1543				FOUND CRACKS IN WING SPAR CARRY-THROUGH STRUCTURE, AD 95-04-03.  NOT APPLICABLE BY SERIAL NUMBER OF AIRCRAFT.						1	L	7	1 	3O				3A15    					 
1996030800552	19960308	00552	EA  	1996	3	8	96ZZZX941        	2	19960220	G	8530	73806	PUSHROD         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 4 CYL EXH	FAILED          	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SW	99	6110Q					15285135	L1545415			AIRCRAFT CRASHED AFTER TAKEOFF.  POST-CRASH INSPECTION REVEALED NR 4 CYLINDER EXHAUST PUSHROD BROKEN AT VALVE END.  NR 4	 EXHAUST VALVE NOT IN OPERATION DUE TO BREAK OF PUSHROD.  AD 80-25-02 AND AD 95-03-10 WERE ISSUED PERTAINING O-235 PUSHR	ODS.  TWO OTHER PUSHROD INCIDENTS WERE NOTED FROM CESSNA OWNER'S ORGANIZATION MAGAZINE, MARCH '96 ISSUE.  SUBJECT PUSHRO	D IAW OF AD 80-25-02 AND AD 95-03-10.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996030800553	19960308	00553	CE  	1996	3	8	96ZZZX942        	1	19960222	G	5347	05112408	TRACK           			CESSNA	172   	172K        	2072430	CE  										RT PAX SIDE	CORRODED        	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	7381G					17259081				INTERGRANULAR CORROSION FOUND 8 INCHES AFT OF LEADING EDGE ON SEAT TRACK, RT PASSENGER SIDE.						1	H	7	1 	3O			NT	3A12    					 
1996030800554	19960308	00554	CE  	1996	3	8	96ZZZX943        	1	19960222	G	2731	051010545	CONTROL CABLE   			CESSNA	172   	172K        	2072430	CE  										RIM AFT PULLEY	BROKEN          	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	7381G					1725081				TRIM CABLE FOUND RUSTED AND PULLEY 'FROZEN'.  THE CABLE BROKE WHEN THE TRIM WAS ACTUATED.						1	H	7	1 	3O			NT	3A12    					 
1996030800556	19960308	00556	SO  	1996	3	8	96ZZZX945        	2	19960131	G	8520		BOLT            								CONT  	O520  	IO520L      	17032	SO  					CRANK GEAR	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11		4591 	1105 				567254			THIS ENGINE WAS RECEIVED FOR A CASE CHANGE.  THE CRANKSHAFT WAS A NON VAR.  REMOVED THE 6 BOLTS THAT ATTACH THE CRANK GE	AR AND BOLTS FOUND APROXIMATELY .25 INCH SHORTER THAN REQUIRED.  SUBMITTER STATES WHOEVER ASSEMBLED THIS ENGINE PUT ROCK	ER SHAFT BOLTS, PN 537019, INSTEAD OF PN 536379, AS REQUIRED.  LOG BOOKS WERE NOT SENT.									3	O			E5CE				 
1996030800557	19960308	00557		1996	3	8	96ZZZX946        	4	19960213	G	3416	3431	CASTING         	UNITEDINST  	5934P1      	BEECH 	33    	3533        	1151402	CE  										END SHAKE	OUT OF TOLERANCE	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	316Z				J1083	CD213				THE CRITICAL SHAFT END SHAKES WERE CHECKED ON THIS INSTRUMENT.  OVERHAUL MANUAL CALLS OUT .002 INCH TO .003 INCH.  THESE	 END SHAKES MEASURED .0010 INCH, .0012 INCH, AND .0003 INCH.  THE .0003 INCH END SHAKE COULD CAUSE THE POINTERS TO HANG 	UP IN THE LOWER TEMP.  SUBMITTER STATES ACCORDING TO A FACTORY ALERT SERVICE BULLETIN, A FIX WAS IMPLEMENTED (FAA APPROV	ED), AND THIS ELIMINATED THE UNDER TOLERANCE CONDITION.			1	L	7	1 	3O				3A15    					 
1996030800558	19960308	00558	SO  	1996	3	8	96ZZZX947        	1	19960106	G	5542	6339600	SKIN            			PIPER 	PA28  	PA28R200    	7102811	SO  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4524X					287635069				RUDDER SKIN CRACKED AT AFT END OF SKIN DIMPLES.  SUBMITTER SUSPECTS FAILURE CAUSED BY PILOTS GRIPPING SKIN TO CHECK RUDD	ER ON PRE-FLIGHT.					1	L	7	1 	3O				2A13    					 
1996030800559	19960308	00559	SO  	1996	3	8	96ZZZX948        	2	19960213	G	8530	653445STL	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					SPARK PLUG BOSS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	3695V					TH1183	282448R			CYLINDER CRACKED IN SPARK PLUG BOSS.  CRACK WAS HEADING TO FUEL INJECTOR BOSS.  ENGINE ONLY HAD 1,078.7 HOURS TOTAL TIME	.					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996030800560	19960308	00560	SO  	1996	3	8	96ZZZX949        	1	19960106	G	2510	9809300	FRAME ASSY      			PIPER 	PA28  	PA28R200    	7102811	SO  										COPILOT SEAT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4524X	6603 				28R7635069				CO-PILOT'S SEAT BACK FRAME CRACKED AND BROKEN ABOVE HINGE POINTS.  LEFT SIDE COMPLETELY SEPARATED.  RIGHT SIDE CRACKED T	HREE-FOURTHS WAY AROUND FRAME MEMBER.  DISCOVERED DURING ANNUAL INSPECTION.  SUBMITTER SUSPECTS STRESS AND FATIGUE FROM 	EXIT AND ENTRANCE.				1	L	7	1 	3O				2A13    					 
1996030800563	19960308	00563	CE  	1996	3	8	96ZZZX952        	1	19960215	G	5312	12134072	BULKHEAD        			CESSNA	206   	U206B       	2073322	CE  										STRUT ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3870G	3845 				U2060870				ANNUAL INSPECTION REVEALED BOTH LEFT AND RIGHT SIDES OF LOWER FORWARD DOORPOST BULKHEAD (PN 1213407-2) CRACKED AS SHOWN 	IN CESSNA SEB 93-5R1.  ALTHOUGH ACFT IS BELOW THE 4,000-HOUR TOTAL TIME SHOWN IN SERVICE BULLETIN, EXTENSIVE FLOAT OPERA	TION AND PRIOR DAMAGE HISTORY CONTRIBUTED TO EARLY CRACKING.  THIS INSPECTION IS EASILY ACCOMPLISHED DURING ANNUAL INSPE	CTION AND SHOULD BE ACCOMPLISHED ON ALL AIRCRAFT OPERATED ON FLOATS.			1	H	7	1 	3O				A4CE    					 
1996030800564	19960308	00564	CE  	1996	3	8	96ZZZX953        	1	19960201	G	2912	30018	FILTER HOUSING  			LEAR  	25    	25          	5170506	CE  										HYDRAULIC SYSTEM	FAILED          	C				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	17	155AG					037				AFTER GEAR EXTENSION, ALL HYDRAULIC PRESSURE WAS LOST.  EMERGENCY PROCEDURES WERE CARRIED OUT PER THE AFM AND LANDING WA	S ACCOMPLISHED WITHOUT INCIDENT USING EMERGENCY AIR PRESSURE FOR BRAKING.  FOUND HYDRAULIC PRESSURE WAS LOST DUE TO HYDR	AULIC FILTER HOUSING FAILING.				2	L	7	2 	4J				A10CE   					 
1996030800565	19960308	00565	CE  	1996	3	8	96ZZZX954        	1	19960218	G	2752	99120071	ACTUATOR        			CESSNA	500   	S550        	2076607	CE  										RT FLAP	DEFECTIVE       	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	274QS	3899 				S5500074				DURING PHASE 12 INSPECTION, RIGHT FLAP ACTUATOR FAILED INTERNAL LEAKAGE CHECK.  REPLACED ACTUATOR.  ACTUATOR INTERNAL O-	RING FAILURE SUSPECTED CAUSE.  THIS IS THE FIRST TIME AN ACTUATOR HAS FAILED THIS TEST ON A PHASE 12 INSPECTION HERE.					1	L	7	2 	4F			RT	A22CE   					 
1996030800566	19960308	00566	CE  	1996	3	8	96ZZZX955        	1	19960218	G	2430	BD161	CONNECTOR       			CESSNA	500   	S550        	2076607	CE  										BATTERY	DEFECTIVE       	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	112QS	9105 				S5500112				DURING INSPECTION, FOUND BATTERY ELCON CONNECTOR NOT LOCKING PROPERLY.  FOUND WEAR ON CONNECTOR LOCKING LUGS.  THIS IS T	HE THIRD TIME THIS HAS BEEN FOUND IN THE LAST 3 MONTHS.					1	L	7	2 	4F			RT	A22CE   					 
1996030800570	19960308	00570	EU  	1996	3	8	96ZZZX959        	1	19960216	G	2750	MS21027F271	SWITCH          			ISRAEL	1124  	1124        	4500102	EU  										FLAP TEST	FAILED          	B			WC7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	516AC	33   				187				WRITE UP:  'FLAPS UNBALANCED'.  WILL NOT TEST.  TROUBLESHOOTING REVEALED THE FLAP UNBALANCED TEST SWITCH HAD FAILED INTE	RNALLY.					2	M	7	2 	4F				A2SW    					 
1996030800572	19960308	00572	CE  	1996	3	8	96ZZZX961        	1	19960209	G	2841	4413041	GAUGE           	STWARNER    		CESSNA	206   	206CESSNA   	2073302	CE  										LT FUEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	2070K		821  		813192	2060196				LEFT FUEL GAUGE SHOWED FULL DEFLECTION WHENEVER POWER WAS ON.  JUMPER WIRE CONNECTION TO RT TRANSMITTER WITH AN EMPTY TA	NK AND TO A NEW TRANSMITTER GOT SAME RESULT, GAUGE WAS EXCHANGED FOR NEW SURPLUS AND OPS CHECK OK FOR FULL RANGE OF TRAN	SMISSION FLOAT TRAVEL.				1	H	7	1 	3O				A4CE    					 
1996030800574	19960308	00574	CE  	1996	3	8	96ZZZX963        	1	19960209	G	2750	031212325Y004	FLEX DRIVE      			BEECH 	90    	6590        	1152904	CE  										RT OTBD FLAP	NUT CRACKED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	5245F					LJ92				B-NUT SECURING RIGHT OUTBOARD FLAP FLEXIBLE DRIVE TO FLAP ACTUATOR FOUND CRACKED DURING SCHEDULED INSPECTION.  DEFECTIVE	 PART REPLACED WITH NEW.					1	L	7	2 	3T				3A20    					 
1996030800575	19960308	00575	CE  	1996	3	8	96ZZZX964        	1	19960205	G	7830		REVERSER        			LEAR  	55    	55LEAR      	5170702	CE  										LT ENG T/R	MALFUNCTION     	B			CW1R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	25	725K	6959 			5131	093				UPON LANDING, THRUST REVERSER FAILED TO STOW ALL THE WAY, PILOT TRIED TO CYCLE T/R SEVERAL TIMES WITH NO SUCCESS, CAUSIN	G MORE DAMAGE.  APPEARS BLOCKER DOORS DID NOT GET CLOSED ALL THE WAY BEFORE STOWING AND CAUGHT ON LIP OF THE T/R STRUCTU	RE.				2	L	7	2 	4F				A10CE   					 
1996030800576	19960308	00576	CE  	1996	3	8	96ZZZX965        	1	19960220	G	3230		UPLOCK SYSTEM   			CESSNA	525   	525         	2076601	CE  										MLG	MALFUNCTIONED   	B			CNQR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CE	07	70KW					5250050				BOTH MAIN LANDING GEAR DROPPED FROM THE WHEELWELLS AT FL 350 WITH THE GEAR UNLOCK LIGHT AND HYDRAULIC PRESSURE ON LIGHT 	ILLUMINATED.  CHECKED ALL LANDING GEAR WIRING AND SWITCHES.  REPLACED THE LANDING GEAR CONTROL VALVE AND HYDRAULIC PRESS	URE RELIEF VALVE.  PERFORMED A SATISFACTORY OPERATIONAL CHECK OF THE LANDING GEAR SYSTEM.  AIRCRAFT TOTAL TIME, 440.9 HO	URS AND 365 LANDINGS.			1	L	7	2 	4F			RT	A1WI    					 
1996030800577	19960308	00577	CE  	1996	3	8	96ZZZX966        	1	19960214	G	2720	717	SOLENOID        			BEECH 	200   	B200        	1152922	CE  										LT RUD BOOST	FAILED          	B			FGQR	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SO	01	700WP	2132 			5616	BB1313				AIRCRAFT YAWS TO LEFT IN-FLIGHT AND VEERS LEFT ON GROUND.  FOUND LEFT RUDDER BOOST CONTROL SOLENOID FAILED IN OPEN POSIT	ION ALLOWING BLEED AIR TO THE BOOST ACTUATOR.  REGARDLESS OF RUDDER BOOST SWITCH ON OR OFF, RIGHT RUDDER BOOST SOLENOID 	PREVIOUSLY HAD SAME PROBLEM.  TOTAL TIME, 2,066.1 HOURS.  SUSPECT CAUSE - MOISTURE CONTAMINATION.  SUBMITTER STATES TO M	AKE SURE, PN 101-524009-91, RUDDER BOOST AIR FILTER IS INSTALLED.  FILTER HAS A MOISTURE DRAIN BEECH SERVICE COMMUNIQUE,	 NR 60 REFERENCES THIS.		1	L	7	2 	4T				A24CE   					 
1996030800579	19960308	00579	EU  	1996	3	8	96ZZZX968        	1	19960126	G	2810	9870019B	RELIEF VALVE    			BRAERO	1000  	BAE1251000  	1500287	EU  										FUEL TANK	LEAKING         	D				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	11	533QS					259033				THE AIRCRAFT WAS DETERMINED TO HAVE LEAKING THERMAL RELIEF VALVE.  ORDERED REPLACEMENT PART.  RECEIVED 4 EACH NEW RELIEF	 VALVES.  ALL 4 EACH LEAKED.  SUBMITTER SUSPECTS SPRING IS WEAK OR POOR FIT OF PISTON.					2	L	7	2 	4F			RT	A3EU    					 
1996030800580	19960308	00580	NM  	1996	3	8	96ZZZX969        	1	19960110	G	5320		CHORD           			BOEING	737   	737247      	138448D	NM  										BS 727 STR 20L	CRACKED         	B			S5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	302VA					20126				BS 727 CHORD CRACKED STR 29L - STR 21L.  REPAIRED IAW VISCOUNT AIR SERV. E.O. 53-10-03.  REF SB 737-53-1088.						2	L	7	2 	4F				A16WE   					 
1996030800584	19960308	00584	CE  	1996	3	8	96ZZZX973        	1	19960215	G	3240	07515500	TORQUE PLATE    	PARKERHANFIN	03014400    	BEECH 	90    	E90         	1152914	CE  										RT BRAKE	CRACKED         	C	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	228RA	1128 			2346	LW197				OUTER PORTION OF UPPER FORWARD BUSHING BOSS OF BRAKE IS CRACKED CLEAN THROUGH.  SUSPECT EXCESSIVELY HARD BRAKING WHILE B	RAKE IS HOT.  INFORMATION RETRIEVED FROM CLEVELAND INSTALLATION MANUAL FOR CONVERSION KIT NR 199-90/199-90A.					1	L	7	2 	3T				3A20    					 
1996031500077	19960315	00077	WP  	1996	3	15	96ZZZX974        	1	19960213	G	6210	369D21100517	BLADE           			HUGHES	369   	369E        	4470707	WP  										M/R	DEFECTIVE       	G	L		CHIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07	1611W	198  			H992	0319E				ABRASION STRIPS ON 3 BLADES WERE NOT INSTALLED CORRECTLY.  THEY DO NOT GO ALL THE  WAY TO THE EDGE.  BLADES ARE BEING SE	NT TO RBI FOR REPAIR.  SERIAL NUMBERS, H992, H991, AND H990.  REFERENCE:  OPERATOR CONTROL NR MLTA960213.					1	G	7	1 	3U				H3WE    					 
1996031500078	19960315	00078	WP  	1996	3	15	96ZZZX975        	1	19960205	G	6210	369D21100517	BLADE           			HUGHES	369   	369E        	4470707	WP  										M/R	DEBONDED        	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1611W	198  				0319E				ABRASION STRIP WAS FOUND DEBONDED, BOTTOM AREA OF 1 INCH BY 19 INCHES.  BLADE SENT TO RBI FOR REPAIR.  REFERENCE:  OPERA	TOR CONTROL NR MLTA960205.					1	G	7	1 	3U				H3WE    					 
1996031500079	19960315	00079	WP  	1996	3	15	96ZZZX976        	1	19960206	G	6410	369A16197	ARM             			HUGHES	369   	369E        	4470707	WP  										TAIL ROTOR	CRACKED         	B	S		CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1611W	3394 			22221331	0319E				TAIL ROTOR GRIP ARM, PN 369A1619-7, FOUND CRACKED AT ONE OF THE RIVET HOLES.  PART SENT TO MANUFACTURER FOR INVESTIGATIO	N.  NOTE:  THIS IS THE 4 BLADE INSTALLATION.  REFERENCE:  OPERATOR CONTROL NR MLTA960206.					1	G	7	1 	3U				H3WE    					 
1996031500097	19960315	00097	GL  	1996	3	15	96ZZZX994        	2	19960209	G	7323	23007505	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAIL            	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5059C	1499 			86090389	S779				GOVERNOR SHAFT FAILED.  REPLACED GOVERNOR.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996031500098	19960315	00098	NE  	1996	3	15	96ZZZX995        	1	19960129	G	3340	A402AR	LIGHT           			SKRSKY	S76   	S76A        	8143006	NE  										ANTI COLLISION	LENS CRACKED    	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7266K	398  				760283				ANTI-COLLISION LIGHT LENS CAME UNGLUED AT SEAMS.  REPLACED LENS.						1	G	7	2 	3U				H1NE    					 
1997010900094	19970109	00094	EA  	1997	1	9	97ZZZX1          	2	19961021	G	7420	M6083	HARNESS         	SLICK       	6351        	AMTR  	540   	EDGE540     	056020M	GL  	LYC   	O540  	IO540*      	41532	EA  					TERMINAL CAP NU	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	42GP	130  			95060063					ALTHOUGH THIS PROBLEM OCCURRED ON AN EXPERIMENTAL ACROBATIC AIRCRAFT, IT IS BELIEVED IT COULD OCCUR ON ANY NEW ENGINE AP	PLICATION.  THE SPARK PLUG NUT IS SEIZED TO THE DRIVE FERRULE MAKING REMOVAL FROM THE SPARK PLUG IMPOSSIBLE WITHOUT HOLD	ING THE DRIVE FERRULE.  IT APPEARS THE SPARK PLUG NUT IS PLATED TOO HEAVILY RESULTING IN GALLING OF THE NUT TO THE DRIVE	 FERRULE.  THE PLATING ALSO FORMS SLIVERS OF METAL WHICH DROP INTO THE SPARK PLUG CERAMIC.  AFTER REMOVAL, THE DRIVE FER	RULE IS COATED WITH AN ANTI-SEIZE COMPOUND.  SUBSEQUENT OPERATION NORMAL.		1	M	7	1 	3O	3	O	NC	EXPA1M71	1E4				 
1997010900103	19970109	00103	SO  	1997	1	9	97ZZZX10         	2	19961105	G	8530	641066	O-RING          		649358A2    	BEECH 	36    	36BEECH     	1151602	CE  	CONT  	O550  	IO550B      		SO  					CYL BASES	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	69277	683  				E2148	675571			FOUND CYLINDER BASE O-RING MISSING ON NR 5 CYLINDER.  REMOVED NR 2 CYL.  ALSO, NO O-RING ON CYL BASE.  CHECK REMAINING C	YLINDERS AFTER TALKING TO CONTINENTAL AND FOUND NO O-RINGS ON 3 CYLINDERS, NR 3 NR 4, AND NR 6.					1	L	7	1 	3O	3	O		3A15    	E3SO				 
1997010900435	19970109	00435	SW  	1997	1	9	97ZZZX100        	1	19961125	G	6330	LB61010161V	LINK            	LORD        	206033500006	BELL  	206   	206L1       	1182107	SW  										XMSN MOUNT	BEARING FAILED  	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			SW	99	911SA		867  		LK8423	45383				BACK SEAT CREW MEMBERS REPORTED VIBRATION IN AIRFRAME DURING TAKEOFF AND LANDING.  INSPECTION OF PYLON MOUNT REVEALED LT	 AFT LINK HAD PLAY AND RUBBER EXTRUDING FROM UPPER BEARING.  REPLACED LINK AND OPERATIONAL CHECK SHOWS VIBRATIONS FROM P	REVIOUS FLIGHT MISSING.  SUBMITTER STATED THIS IS A COMMON AND TYPICAL PROBLEM THAT ONLY REQUIRES GOOD VISUAL INSPECTION	.			1	G	7	1 	3U				H2SW    					 
1997010900436	19970109	00436	SW  	1997	1	9	97ZZZX101        	1	19961203	G	3310	2060755581	PANEL           			BELL  	206   	206B        	1181511	SW  										COCKPIT	SHORTED         	B		A	GJOR	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NM	01	1076G	2495 				2831				WHILE IN-FLIGHT, THE PILOT NOTICED SMOKE AT THE CABIN OVERHEAD.  AFTER MAKING PRECAUTIONARY LANDING, IT WAS NOTED THAT T	HE INSTRUMENT CIRCUIT BREAKER HAD POPPED.  INVESTIGATION BY MAINT. REVEALED THAT THE LIGHTED PANEL HAD INTERNALLY SHORTE	D.  THE PANEL WAS REPLACED AND NO FURTHER DISCREPANCIES WERE FOUND.				1	G	7	1 	3U				H2SW    					 
1997031300152	19970313	00152	NE  	1997	3	13	97ZZZX1014       	2	19960229	G	7322		CONTROL ROD     			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LT ENG FCU	HUNG UP         	D		A		E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	05	107Z					BL124				LEFT ENGINE CRUISE POWER REMAINED STEADY AFTER PILOT PULLED BACK POWER LEVER TO BEGIN DESCENT.  ENGINE REACHED HIGH TORQ	UE LIMIT AND HAD TO BE SHUT DOWN IN-FLIGHT.  MAINTENANCE INSPECTED ENGINE AND FOUND THE COTTER PIN ON THE CASTELLATED NU	T RETAINING THE FCU CONTROL ROD TO THE FUEL CONTROL ACTUATING LEVER ON THE CAM BOX HAD CAUGHT AND HUNG UP IN THE ENGINE 	COWLING.  INSTALLED NEW COTTER PIN AND CORRECTLY SET SAME SO IT COULD NOT SNAG COWLING.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997031300154	19970313	00154	NE  	1997	3	13	97ZZZX1016       	2	19961212	G	7250	50L195	AIR SEAL        								PWA   	4158  	PW4158      		NE  					2ND STAGE HPTR	CRACKED         	B			DLAZ	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	PKGAN	11265	4726 		T44897		724812			INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9	61114XFR.  MFG RECOMMENDATIONS SEE ASB PW4 ENGA72-628.										4	F			E24NE				 
1997031300155	19970313	00155	NE  	1997	3	13	97ZZZX1017       	2	19961212	G	7250	50L195	AIR SEAL        								PWA   	4158  	PW4158      		NE  					2ND STAGE HPTR	CRACKED         	B			DLAZ	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	PKGAS	10370	4331 		C332AA0166		724840			INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9	61114XFR.  MFG RECOMMENDATIONS SEE ASB PW4 ENGA72-628.										4	F			E24NE				 
1997031300156	19970313	00156	NE  	1997	3	13	97ZZZX1018       	2	19961212	G	7250	50L195	AIR SEAL        								PWA   	4158  	PW4158      		NE  					2ND STAGE HPTR	CRACKED         	B			DLAZ	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	PKGAT	9313 	3612 		S72690		724088			INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9	61114XFR.  MFG RECOMMENDATIONS SEE ASB PW4 ENGA72-628.										4	F			E24NE				 
1997031300157	19970313	00157	NE  	1997	3	13	97ZZZX1019       	2	19961212	G	7250	50L195	AIR SEAL        								PWA   	4158  	PW4158      		NE  					2ND STAGE HPTR	CRACKED         	B			DLAZ	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	PKGAN	12278	5015 		T44846		724811			INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9	61114XFR.  MFG RECOMMENDATIONS SEE ASB PW4ENG172-628.										4	F			E24NE				 
1997031300158	19970313	00158	NE  	1997	3	13	97ZZZX1020       	2	19961212	G	7250	50L195	AIR SEAL        								PWA   	4158  	PW4158      		NE  					2ND STAGE HPTR	CRACKED         	B			DLAZ	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	PKGAS	10774	4402 		C332AA0128		724839			INSPECTED 2ND STAGE HPTR AIR SEAL AND FOUND CRACK INDICATION AS DESCRIBED IN PW4000 ALL OPER WIRE NOV 14, 1996 NR C301G9	61114XFR.  MFG RECOMMENDATIONS SEE ASB PW4 ENGA72-628.										4	F			E24NE				 
1997031300225	19970313	00225		1997	3	13	97ZZZX1045       	1	19960203	G	4940	473682	HOUSING         	ALIDSIGNAL  	5198022     															APU STARTER	DEFECTIVE       	B			KQ4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17					107269					INSIDE DIAMETER OF END BELL WHICH RECEIVES THE INSERT IS OVERSIZED BY .1245 INCH.  A BUSHING FABRICATED FROM WHAT APPEAR	S TO BE STEEL WAS FOUND INSTALLED IN PLACE OF THE REQUIRED OEM INSERT.  THIS IS CONTRARY TO THE OEM MANUAL.  ATA 49-20-0	8, PAGE 626, FIGURE 607.  HOUSING HAS BEEN REJECTED ALONG WITH FABRICATED BUSHINGS AT THIS FACILITY.																	 
1997010900441	19970109	00441	NE  	1997	1	9	97ZZZX106        	2	19961104	G	7250	783319	LPT SHAFT       								PWA   	JT8   	JT8D217A    	52053	NE  					N1 TURBINE	DISTORTED       	D				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	05		20159	3206 		R69021		708414			ENGINE WAS REMOVED FROM SERVICE DUE TO VIBRATION.  DISASSEMBLY OF THE ENGINE REVEALED THAT AN OIL FIRE HAD OCCURRED IN T	HE N2 COMPRESSOR CENTER TUBE CAUSING THE LPT SHAFT TO DISTORT AND RUB WHICH RESULTED IN ENGINE VIBRATION.  THE FAILURE I	S STILL UNDER INVESTIGATION.									4	F			E9NE				 
1997031300246	19970313	00246	NE  	1997	3	13	97ZZZX1064       	2	19960915	G	8530		CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R985  	R985AN14B   	52008	NE  					NR 4	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	8866H		361  			1553	21433			INSPECTION FOUND NR 4 CYLINDER CRACKED AROUND HEAD OF CYLINDER JUST ABOVE THE TOP OF THE CYLINDER BARREL.						1	Q	7	1 	3R	3	R		1A16    	5E1				 
1997010900442	19970109	00442	NE  	1997	1	9	97ZZZX107        	2	19961108	G	7230	500588701	STATOR VANE     								PWA   	JT8   	JT8D219     	52053	NE  					C7 STATOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					TV9031		716792			ENGINE WAS REMOVED FROM SERVICE DUE TO COMRPESSOR STALLS, IN-FLIGHT SHUT DOWN AND HEAVY TURBINE DAMAGE.  DISASSEMBLY OF 	THE ENGINE REVEALED THAT THE C7 STATOR HAD LIBERATED A VANE CAUSING HEAVY N2 COMPRESSOR DAMAGE WHICH RESULTED IN STALLS 	AND N1 AND N2 TURBINE DAMAGE.  THE FAILURE IS UNDER INVESTIGATION.									4	F			E9NE				 
1997010900443	19970109	00443	NE  	1997	1	9	97ZZZX108        	2	19961121	G	7313	5004308032	NOZZLE SUPPORT  								PWA   	JT8   	JT8D219     	52053	NE  					NR 3 POS NOZZLE	NUT LOOSE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03			5494 		BV5444		709702			INSPECTION OF THE NR 3 POSITION FUEL NOZZLE AND SUPPORT ASSEMBLY REVEALED THAT THE NUT WAS LOOSE.  THE INSPECTOR WAS ABL	E TO REMOVE THE NUT FROM THE SUPPORT BY HAND.  THREADS WERE BADLY WORN.  CONDITION IS UNDER INVESTIGATION BY P AND W.										4	F			E9NE				 
1997011400007	19970114	00007	SW  	1997	1	14	97ZZZX109        	1	19961101	G	5741	NAS15033	BOLT            			SWRNGN	SA226 	SA226AT     	8780405	SW  										WING ATTACH	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1YC					T26131				AIRCRAFT HAS IN EXCESS OF 5,000 HRS.  REMOVED WING ATTACH BOLTS AT CUSTOMER'S REQUEST AND FOUND SEVERE CORROSION AND PIT	TING.  REPLACED BOLTS WITH NEW.  RECOMMEND INSPECTING BOLTS ANNUALLY.					2	L	7	2 	4T			RT	A5SW    					 
1997010900104	19970109	00104	SO  	1997	1	9	97ZZZX11         	1	19961201	G	2436	X16300B	REGULATOR       			PIPER 	PA32  	PA32260     	7103206	SO  										DC SYS	INOPERATIVE     	B			GOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	7731J					321134				TROUBLESHOT ELECTRICAL SYSTEM AND FOUND VOLTAGE REGULATOR TO BE INOPERATIVE.						1	L	7	1 	3O				A3SO    					 
1997010900444	19970109	00444	NM  	1997	1	9	97ZZZX110        	1	19961218	G	3240	211473	BRAKE ASSY      	BFGOODRICH  		BOEING	727   	727         	1384001	NM  										MLG	LOCK UP         	B			QVIR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	2FOR				7472					BRAKE LOCKED UP.  HIGH TEMPERATURE.						2	L	7	3 	4F				A3WE    					 
1997010900445	19970109	00445	NM  	1997	1	9	97ZZZX111        	1	19961219	G	3230	65800519	DRAG BRACE      			BOEING	737   	737297      	1384480	NM  										NLG	DAMAGED         	B			B4GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	147AW				339	22630				DRAG BRACE SENT TO BFG FOR REPAIR.  FOUND BEARING MIGRATED FROM LOCATION CAUSING DAMAGE TO BRACE DURING GEAR ACTUATION. 	 BEARING INSTALLATION RECORDS NOT AVAILABLE TO BFG AT THIS TIME.  CAUSE UNKNOWN.  (REP STA NR B4GR448J).					2	L	7	2 	4F				A16WE   					 
1997010900446	19970109	00446	NM  	1997	1	9	97ZZZX112        	1	19961219	G	3230	658005118	DRAG BRACE      			BOEING	737   	73733A      	1384673	NM  										NLG	DAMAGED         	B			B4GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	173AW				588728	23632				SENT FOR REPAIR.  BEARING MIGRATED FROM LOCATION CAUSING DAMAGE TO BRACE DURING ACTUATION.  BEARING INSTALLED AND TESTED	 PER BAC 0HM 32-10-03.  CAUSE OF MIGRATION IS UNKNOWN. ( REP STA NR B4GR448J).					2	L	7	2 	4F			RT	A16WE   					 
1997032000701	19970320	00701	GL  	1997	3	20	97ZZZX1129       	1	19961016	G	7910		DRAIN EXTENSION 			AMTR  	MINEAR	PIETENPOL   	7040220	GL  										OIL SUMP	FAILED          	H	P	A		A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	99	63SB	120  								FORCED LANDING (ENG FAILED).  INVESTIGATION REVEALED THAT THE OIL DRAIN EXTENSION, WHICH WAS MADE OF COPPER TUBING, HAD 	BROKEN OFF AT THE ADAPTER ON THE BOTTOM OF THE OIL SUMP CAUSING THE TOTAL LOSS OF LUBRICATING OIL.  A REVIEW OF THE AIRC	RAFT PLANS SHOWED NO EXTENSION, BUT THE ORIGINAL DRAIN PLUG ONLY.				1	H	7	1 	3O			NC	EXPA1H71					 
1997010900447	19970109	00447	NM  	1997	1	9	97ZZZX113        	1	19961219	G	3230	658005118	DRAG BRACE      			BOEING	737   	7373S3      	1384711	NM  										NLG	DAMAGED         	B			B4GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	313AW					23712				DRAG BRACE SENT FOR REPAIR.  BEARING MIGRATED FROM LOCATION CAUSING DAMAGE TO BRACE DURING GEAR ACTUATION.  BEARING INST	ALLED AND TESTED PER BAC OHM 32-01-03.  CAUSE OF MIGRATION IS UNKNOWN.					2	L	7	2 	4F			RT	A16WE   					 
1997010900448	19970109	00448	CE  	1997	1	9	97ZZZX114        	1	19961125	G	7830	66082313	SLIDE TRACK     			LEAR  	35    	35A         	5170602	CE  										LT ENG TR	REQUIRED LUBE   	G				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	03	500HG					238				DURING TAXI TO TAKEOFF, FLIGHT CREW NOTICED T/R LIGHT ON, P.I.C. ABORTED TAKEOFF.  MAINTENANCE PERSONNEL DISCOVERED T/R 	SLIDE TRACKS AND INDICATING SWITCHES WERE IN NEED OF LUBRICATION.  MAINTENANCE CREW LUBE T/R SYSTEM.  OPERATIONAL CHECK 	GOOD.				2	L	7	2 	4F				A10CE   					 
1997010900449	19970109	00449	CE  	1997	1	9	97ZZZX115        	1	19961125	G	7830	66082314	SLIDE TRACK     			LEAR  	35    	35A         	5170602	CE  										RT ENG TR	REQUIRED LUBE   	G				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	03	500HG					238				DURING TAXI TO TAKEOFF, FLIGHT CREW NOTICED T/R LIGHT ON, P.I.C. ABORTED TAKEOFF.  MAINTENANCE PERSONNEL DISCOVERED T/R 	SLIDE TRACKS AND INDICATING SWITCHES WERE IN NEED OF LUBRICATION.  MAINTENANCE CREW LUBE T/R SYSTEM.  OPERATIONAL CHECK 	GOOD.				2	L	7	2 	4F				A10CE   					 
1997010900450	19970109	00450	GL  	1997	1	9	97ZZZX116        	3	19961209	G	6110		BEARING         			MTSBSI	MU2   	MU2B60      	5780460	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP BLADE	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	802SM	1622 				1515SA		CDA3194		DURING A ROUTINE 100 HR INSPECTION, IT WAS DISCOVERED THAT 2 OF THE 4 BLADES ON EACH OF THE 2 HARTZELL PROPELLERS HAD A 	ROUGH MOVEMENT WHEN ROTATED FROM REVERSE PITCH TO FEATHER POSITION AND BACK AGAIN.  SENT BOTH PROPS TO A PROPELLER O/H F	ACILITY AND FOUND THE BEARINGS ON THE ROUGH BLADES WERE WORN TO THE LIMITS.  THIS IS THE SECOND TIME DISCOVERED THIS PRO	BLEM ON THE 4 BLADED HARTZELL PROPELLERS INSTALLED ON THE MU-2 AIRCRAFT.			1	H	7	2 	3T			RT	A10SW   		6	C	P40EA	 
1997032700238	19970327	00238	CE  	1997	3	27	97ZZZX1168       	1	19960730	G	2133	13035615	CONTROLLER      	GARRTT      		CESSNA	500   	550         	2076604	CE  										OUTFLOW VLV	MISOVERHAULED   	H		A		A				UNSCHED LANDING         				W			INADEQUATE Q C            			CL	CLIMB          	1			SW	09	26621		193  		79323	5500593				ACFT CLLIMBED TO FL 260.  CREW NOTICED A DISCREPANCY IN THE CABIN PRESSURE DIFFERENTIAL, ALTITUDE AND CONTROLLER INDICAT	ION.  AFTER INVESTIGATION AND COMPARISON WITH ANOTHER ACFT, IT WAS FOUND DURING OVERHAUL THE INCORRECT FACE HAD BEEN INS	TALLED ON THE RATE CONTROLLER.				1	L	7	2 	4F				A22CE   					 
1997032700239	19970327	00239	CE  	1997	3	27	97ZZZX1169       	1	19960613	G	3230	S13771	SWITCH          			CESSNA	210   	210M        	2073450	CE  										RT MLG UPLOCK	FAILED          	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	09	6265B		92   			21062727				LANDING GEAR WOULD NOT EXTEND WHEN SELECTOR SWITCH WAS PLACED IN THE DOWN POSITION.  AIRCRAFT PLACED ON JACKS TO TROUBLE	SHOOT GEAR SYSTEM.  RIGHT MAIN GEAR UPLOCK MICROSWITCH FOUND DEFECTIVE.  REPLACED S1377-1 MICROSWITCH, AND RIGGED.  OPER	ATIONAL CHECK, GOOD.				1	H	7	1 	3O				3A21    					 
1997011400008	19970114	00008	SW  	1997	1	14	97ZZZX117        	1	19961110	G	5741	NAS15033	BOLT            			SWRNGN	SA226 	SA226AT     	8780405	SW  										WING ATTACH	CORROSION       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	345T					T26105				AIRCRAFT HAS IN EXCESS OF 5,000 HRS.  REMOVED WING ATTACH BOLTS AT CUSTOMER'S REQUEST AND FOUND SEVERE CORROSION AND PIT	TINGS.  REPLACED BOLTS WITH NEW.  RECOMMEND INSPECTING BOLTS ANNUALLY.					2	L	7	2 	4T			RT	A5SW    					 
1997010900451	19970109	00451	GL  	1997	1	9	97ZZZX118        	2	19961115	G	7250	23008020	TIE BOLT        								ALLSN 	250C  	250C20B     	03013	GL  					GAS PROD	FAILED          	B	L		HEER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		1306 					CAT36754			IN PROCESS OF REPAIRING A C20B TURBINE, FOR UNUSUAL NOISE AND CHIP LIGHT, FOUND GP TIE BOLT SN DJ 59 BROKEN APPROXIMATEL	Y .6250 INCH BELOW SPANNER NUT ON NR 1 WHEEL SIDE.  CANNOT READ THE COMPLETE SERIAL NUMBER AS IT IS COVERED WITH CARBON.	  CROSS SECTION OF THE BOLT IS HALF DARK, ONE-QUARTER LIGHTER AND REMAINING SECTION VERY LIGHT COLOR.  NO BEARING FAILUR	E OR WHEELS DISINTEGRATION HAD OCCURRED.  NO OTHER DAMAGE TO ENGINE OR HELICOPTER WAS EXPERIENCED.  THE INCIDENT HAPPENE	D ON THE COAST DOWN WHEN UNUSUAL 'CLUNKING' NOISE WAS HEARD.  TURBINE S/N IS CAT 36754.							3	U			E4CE				 
1997010900456	19970109	00456	EU  	1997	1	9	97ZZZX119        	1	19961217	G	5320	25FN4735	WINDOW PAN      			HWKSLY	DH125 	DH1251A     	4230106	EU  										LT DV WINDOW	CRACKED         	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	125JR					25052				DURING A REPETITIVE 4-YEAR INSPECTION OF THE LEFT AND RIGHT DIRECT VISION WINDOW PANS (PN 25FN4735 AND 25FN4736) A 22 IN	CH CRACK IS NOTED IN THE RIGHT PAN ALONG THE LOWER RADIUS.  AN 8 INCH CRACK IS NOTED IN THE SAME LOCATION ON THE LEFT SI	DE.  SOME EXFOLIATION CORROSION IS NOTED ON THE FRAMES.  AIRCRAFT WAS MANUFACTURED IN 1965 AND IS REPORTED TO HAVE 8658.	5 HRS AND APPROX 8300 AIRFRAME CYCLES, WHICH IS CERTAINLY NOT EXCESSIVE FOR ITS AGE AND PURPOSE.  IT IS DIFFICULT TO IMA	GINE THE RIGHT WINDOW CRACK PROGRESSING TO THIS LENGTH IN 4 YEARS.  THE MANUFACTURER OF THE AIRCRAFT HAD TO RETOOL TO PR	ODUCE THE REPLACEMENT PARTS.	2	L	7	2 	4J				A3EU    					 
1997010900457	19970109	00457	EU  	1997	1	9	97ZZZX120        	1	19961217	G	5320	25FN4736	WINDOW PAN      			HWKSLY	DH125 	DH1251A     	4230106	EU  										RT DV WINDOW	CRACKED         	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	125JR					25052				DURING A REPETITIVE 4- YEAR INSPECTION OF THE LEFT AND RIGHT DIRECT VISION WINDOW PANS (PN 25FN4735 AND 25FN4736) A 22 I	NCH CRACK IS NOTED IN THE RIGHT PAN ALONG THE LOWER RADIUS.  AN 8 INCH CRACK IS NOTED IN THE SAME LOCATION ON THE LEFT S	IDE.  SOME EXFOLIATION CORROSION IS NOTED ON THE FRAMES.  AIRCRAFT WAS MANUFACTURED IN 1965 AND IS REPORTED TO HAVE 8658	.5 HRS AND APPROX 8300 AIRFRAME CYCLES, WHICH IS CERTAINLY NOT EXCESSIVE FOR ITS AGE AND PURPOSE.  IT IS DIFFICULT TO IM	AGINE THE NIGHT WINDOW CRACK PROGRESSING TO THIS LENGTH IN 4 YEARS.  THE MANUFACTURER OF THE AIRCRAFT HAD TO RETOOL TO P	RODUCE THE REPLACEMENT PARTS.	2	L	7	2 	4J				A3EU    					 
1997011400011	19970114	00011	SW  	1997	1	14	97ZZZX122        	1	19961125	G	2910	70053H000A100	HOSE ASSY       			BELL  	206   	206L3       	1182108	SW  										HYD PUMP	LEAKING         	H	L		N1UM	A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			EA	11	608PD	2739 				51270				DURING RETURN TO BASE, COMPLETE HYD SYS LOSS.  AFTER LANDING, SEVERE HYD LEAK NOTED, BUT NO CAUSE FOUND PRIOR TO CLEAN U	P.  AFTER SERVICE AND RUN-UP, FOUND LINE TO HYD PUMP RUPTURED.  SUBMITTER BELIEVES LINE DAMAGED DURING 300 HR SPLINE CHE	CK INSP WHERE PUMP IS SEPARATED FROM TACH GEN.  METHOD FLEXES LINE.				1	G	7	1 	3U				H2SW    					 
1997010900767	19970109	00767	GL  	1997	1	9	97ZZZX123        	3	19961105	G	6111	C2987	BEARING         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	BLADE	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		INSPECTION FOUND BLADE BEARING RACE CORROSION.  P/N C2987.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997010900768	19970109	00768	GL  	1997	1	9	97ZZZX124        	3	19961105	G	6111	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	BLADE	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		INSPECTION FOUND FERRULE CORRODED.  P/N C4451.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997040300306	19970403	00306	EU  	1997	4	3	97ZZZX1249       	1	19960915	G	7830	54535111	ACTUATOR        			AMD   	FALC20	FALCON20F5  	2730105	EU  										T REV FAN FLAP	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	17	305AR		66   			378				9-15-96 FOUND FAN FLAP ACTUATOR LEAKING BADLY ON T/R DEPLOY.  ACTUATOR WAS REPAIRED 6-21-96.  P/N AND S/N LISTED.  6-29-	96.  APPROX 66 HOURS AND 74 CYLCES PRIOR TO CURRENT TIME, FOUND SAME P/N AND POSITION, ACTUATOR LEAKING.  THIS ACTUATOR 	S/N 735 HAD APPROX 123 HRS, 130 CYCLES ON IT AND WAS INSTALLED ON 1-10-96.  PRIOR TO THIS ACTUATOR, INSTALLED A LIKE ACT	UATOR WHICH WAS JUST REPAIRED.  THIS ACTUATOR LEAKED STRAIGHT OUT OF THE BOX, WORSE THAN THE ONE BEING REPLACED.			2	L	7	2 	4F			RT	A7EU    					 
1997010900769	19970109	00769	GL  	1997	1	9	97ZZZX125        	3	19961105	G	6114	D7015C93	HUB             													MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		INSPECTION FOUND HUB DEFECTIVE.  BUSHING HOLE OVERSIZE.																5	C	P22EA	 
1997010900770	19970109	00770	GL  	1997	1	9	97ZZZX126        	3	19961105	G	6111	82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					K82853YS			795369		INSPECTION FOUND BLADE CORROSION.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997040300641	19970403	00641	WP  	1997	4	3	97ZZZX1265       	1	19961215	G	5320		T ANGLE         			DOUG  	DC10  	DC1010      	3022110	WP  										CTR CARGO DOOR	CORRODED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1837U					47969				DURING MPV MAINTENANCE CHECK, FOUND CENTER CARGO DOOR FRAME LOWER T-ANGLE EXFOLIATED, STA 1681, STR 44R.  SUSPECT CAUSE 	WAS STRESS RELATED.  APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE.					2	L	7	3 	4F				A22WE   					 
1997040300642	19970403	00642	WP  	1997	4	3	97ZZZX1266       	1	19961215	G	5313		LONGERON        			DOUG  	DC10  	DC1010      	3022110	WP  										FS 1506	CORRODED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1837U					47969				DURING MPV MAINTENANCE CHECK, FOUND CENTER W/W TUNNEL LONGERON 48L LOWER FLANGE BADLY CORRODED, STA 1506.  SUSPECT CAUSE	 WAS MOISTURE.  PROPER APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE.					2	L	7	3 	4F				A22WE   					 
1997040300643	19970403	00643	WP  	1997	4	3	97ZZZX1267       	1	19961215	G	5313		LONGERON        			DOUG  	DC10  	DC1010      	3022110	WP  										FS 1521	CORRODED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1837U					47969				DURING MPV MAINTENANCE CHECK, FOUND CENTER W/W TUNNEL, LONGERON 50L END FITTINGS CORRODED ALONG OTBD FLANGE, STA 1521. S	USPECT CAUSE WAS MOISTURE.  PROPER APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE.					2	L	7	3 	4F				A22WE   					 
1997040300644	19970403	00644	WP  	1997	4	3	97ZZZX1268       	1	19961215	G	5313		LONGERON        			DOUG  	DC10  	DC1010      	3022110	WP  										FS 1521 48L	CORRODED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1837U					47969				DURING MPV MAINTENANCE CHECK, FOUND CENTER W/W TUNNEL, 48L END FITTING AT STA 1521 BADLY PITTED ALONG OTBD FLANGE.  SUSP	ECT CAUSE WAS MOISTURE.  PROPER APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE.					2	L	7	3 	4F				A22WE   					 
1997040300645	19970403	00645	WP  	1997	4	3	97ZZZX1269       	1	19961215	G	5330		SKIN            			DOUG  	DC10  	DC1010      	3022110	WP  										FS 1519 L49R	CORRODED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1837U					47969				DURING MPV MAINTENANCE CHECK, FOUND CENTER W/W TUNNEL SKIN CORRODED OTBD SIDE OF LONGERON 49R, STA 1519. SUSPECT CAUSE W	AS MOISTURE.  PROPER APPLICATION OF CORROSION PREVENTIVE COULD PREVENT RECURRENCE.					2	L	7	3 	4F				A22WE   					 
1997010900771	19970109	00771	GL  	1997	1	9	97ZZZX127        	3	19961105	G	6111	82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					K82928YS			795369		INSPECTION FOUND BLADE CORROSION.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997010900772	19970109	00772	GL  	1997	1	9	97ZZZX128        	3	19961105	G	6110	A1896	PROP ASSY       			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		INSPECTION FOUND P/N A1896 PROP ASSY CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997010900773	19970109	00773	GL  	1997	1	9	97ZZZX129        	3	19961105	G	6110	A4191	PROP ASSY       			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		INSPECTION FOUND PROP ASSY P/N A4191 CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997010900106	19970109	00106	EA  	1997	1	9	97ZZZX13         	2	19961218	G	8550	LW14492	SUMP            			PIPER 	PA32  	PA32301T    	7103209	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					OIL SYS	CRACKED         	D				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	13	8339Z		114  			328124013	L202761A			THIS SUMP WAS INSTALLED ON AN ENGINE THAT CAME FROM LYCOMING AS A FACTORY OVERHAUL.  THERE WOULD BE A SMALL PUDDLE OF OI	L UNDER THE ACFT AFTER IT SAT IDLE FOR A FEW DAYS, BUT DURING OPERATION, NO APPRECIABLE AMOUNT WOULD SHOW UP ON IT.  CRA	CK WAS LOCATED WITH PENETRANT DEVELOPER.  AFTER REMOVAL, IT WAS NOTED THAT THIS CRACK WAS IN AN AREA WHERE IT HAD BEEN G	ROUND (ON THE INSIDE) DURING MANUFACTURE OR REPAIR.			1	L	7	1 	3O	3	O		A3SO    	E14EA				 
1997010900774	19970109	00774	GL  	1997	1	9	97ZZZX130        	3	19961105	G	6111	C2987	BEARING         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	BLADE	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		INSPECTION FOUND BEARING RACE CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997010900775	19970109	00775	GL  	1997	1	9	97ZZZX131        	3	19961105	G	6110	B3490	PROP ASSY       			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		INSPECTION FOUND PROP ASSY P/N B3490 CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997040300833	19970403	00833	SO  	1997	4	3	97ZZZX1314       	1	19961231	G	2410	LW18129	BELT            			PIPER 	PA31  	PA31350     	7103110	SO  										RT ALTERNATOR	FAILED          	B			DQFR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	27354					317752180				LEFT AND RIGHT ALTERNATOR BELTS WERE REPLACED WITH NEW BELTS AT PROPELLER OVERHAUL.  WITHIN APPROXIMATELY 3 HRS, THE RT 	BELT FAILED DUE TO UNKNOWN REASONS AND LT BELT WAS SLIPPING DUE TO METEROLOGICAL CONDITIONS WHICH RESULTED IN LOSS OF EL	ECTRICAL POWER.  RE-ADJUSTED TENSION ON LT BELT AND INSTALLED NEW BELT ON RT SIDE AND ADJUSTED TENSION.  PERFORMED ABOUT	 A 15-MINUTE RUN-UP AND RE-CHECKED TENSIONS.  RECOMMEND CHECKING BELT ALIGNMENT AND RE-CHECKING BELT TENSION AFTER A GOO	D GROUND RUN.		1	L	7	2 	3O				A20SO   					 
1997040300835	19970403	00835	SO  	1997	4	3	97ZZZX1316       	2	19961005	G	8540	22532	BOLT            			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  					ASSORY GRBOX	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	13	6741S	2450 	356  			15067541	674327A			THE ENGINE QUIT SUDDENLY IN CRUISE FLIGHT WITHOUT WARNING AND WOULD NOT RESPOND TO RESTART ATTEMPTS.  A NORMAL LANDING W	AS MADE IN A FARM FIELD.  DISASSEMBLY INSPECTION INDICATED THE FOUR BOLTS (22532) USED TO SECURE THE CRANKSHAFT CLUSTER 	GEAR (35016) BROKE OFF ALLOWING THE GEAR TO ROTATE INDEPENDENTLY OF THE CRANKSHAFT.  PROPER ASSEMBLY WAS INDICATED BY RE	MAINING SAFETY WIRE ON BOLT HEADS.  FATIGUE FAILURE INDICATIONS WERE NOTED ON ONE BOLT IN THE THREADED AREA.  REMAINING 	BOLT FRACTURE FACES WERE SMEARED.  THE ENGINE MAY HAVE HAD A PREVIOUS SUDDEN STOPPAGE.  REUSE OF THE BOLTS IS NOT CONTRA	RY TO THE OVERHAUL MANUAL.  RECOMMEND REPLACEMENT OF THESE BOLTS EACH ENGINE OVERHAUL OR PROPELLER STRIKE.	1	H	7	1 	3O	3	O		3A19    	E252				 
1997010900776	19970109	00776	GL  	1997	1	9	97ZZZX132        	3	19961105	G	6110	D3474	PROP ASSY       			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		INSPECTION FOUND PROPELLER ASSEMBLY P/N D3474 DEFECTIVE.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997010900777	19970109	00777	GL  	1997	1	9	97ZZZX133        	3	19961105	G	6111	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		INSPECTION FOUND BLADE FERRULE CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997041000041	19970410	00041	EU  	1997	4	10	97ZZZX1334       	1	19961023	G	3150	1179405201	ANNUNCIATOR     			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	214AE	48   			0104	7206				ONE SEGMENT DOES NOT LIGHT UP.  SOME SEGMENT ROWS WILL NOT LOCK IN PLACE.  ONLY INSTALLED FOR 47.9 HOURS BEFORE FAILED.						1	G	7	2 	3U				H13EU   					 
1997041000042	19970410	00042	EU  	1997	4	10	97ZZZX1335       	1	19961223	G	6720	741C000005	ACTUATOR        			BOLKMS	117   	BK117B1     	5626012	EU  										T/R	DEFECTIVE       	B			TI1R	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	05	214AE				00248	7206				ON TEST FLIGHT AFTER INSTALLATION OF ACTUATOR, THE T/R PEDAL WAS STIFF IN LEFT FORWARD QUADRANT.						1	G	7	2 	3U				H13EU   					 
1997041000043	19970410	00043	EU  	1997	4	10	97ZZZX1336       	1	19960927	G	6710	1174123101	STRAP ASSY      			BOLKMS	BK117 	BK117C1     	5626025	EU  										CYCLIC	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1600 				7505				CYCLIC CENTERING STRAP ASSY CRACKED.						1	G	7	2 	3U			NC	H13EU   					 
1997041000044	19970410	00044	EU  	1997	4	10	97ZZZX1337       	1	19961212	G	6720	741C000005	ACTUATOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	317MC				00506	7505				LEAKING ACTUATOR.						1	G	7	2 	3U			NC	H13EU   					 
1997041000045	19970410	00045		1997	4	10	97ZZZX1338       	4	19961031	G	2312	069102525	DISPLAY         		KX165       	BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT VHF	WEAK            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				DISPLAY WEAK, SEGMENTS OUT.						1	G	7	2 	3U			NC	H13EU   					 
1997010900778	19970109	00778	GL  	1997	1	9	97ZZZX134        	3	19961105	G	6110	66070924017	PROP ASSY       			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROPELLER	DAMAGED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		15075	5209 					DRG60686		INSPECTION FOUND PROPELLER ASSY DAMAGED.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1997041000048	19970410	00048	EU  	1997	4	10	97ZZZX1341       	1	19961213	G	6240	117945641	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										MAST MOMENT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				E200830	7098				INDICATOR TESTS PASSED THE CALIBRATION LINE.						1	G	7	2 	3U				H13EU   					 
1997041000051	19970410	00051	EU  	1997	4	10	97ZZZX1344       	1	19960929	G	6320	DK040	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										OIL PRESSURE	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	105NG	151  			7598	S632				OIL PRESSURE TRANSMITTER CAUSING OIL PRESSURE TO SPIKE INTERMITTENTLY.						1	G	7	2 	3U				H3EU    					 
1997041000052	19970410	00052		1997	4	10	97ZZZX1345       	4	19961125	G	2312	4000103000	TRANSCEIVER     			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT VHF	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				236	7061				TRANSCEIVER WILL NOT TRANSMIT.						1	G	7	2 	3U				H13EU   					 
1997041000053	19970410	00053		1997	4	10	97ZZZX1346       	4	19961112	G	2312	4000103001	TRANSCEIVER     		RT450       	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				613	7061				TRANSCEIVER WILL NOT RECEIVE.  DID NOT WORK WHEN INSTALLED.						1	G	7	2 	3U				H13EU   					 
1997041000054	19970410	00054		1997	4	10	97ZZZX1347       	4	19961125	G	2312	4000103000	TRANSCEIVER     		RT450       	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT VHF	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				642	7061				INOPERABLE COCKPIT VHF.						1	G	7	2 	3U				H13EU   					 
1997041000056	19970410	00056	EU  	1997	4	10	97ZZZX1349       	1	19960813	G	2432	RG390E	BATTERY         			BOLKMS	117   	BK117A1     	5626010	EU  										DC SYSTEM	FAILED          	B			LI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	117LF	108  			CBC261076	7013				BATTERY FAILED.  BUSS TIE TRIPS.  WILL NOT START A/C.  VOTLAGE DROPS TO ZERO.						1	G	7	2 	3U				H13EU   					 
1997010900779	19970109	00779	GL  	1997	1	9	97ZZZX135        	3	19961105	G	6110	660709612	PROP ASSY       			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PEOPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		21893	5973 					DRG936282		INSPECTION FOUND PROPELLER ASSY DEFECTIVE.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1997041000058	19970410	00058	EU  	1997	4	10	97ZZZX1351       	1	19961212	G	2822	1176415103	PUMP            			BOLKMS	117   	BK117B1     	5626012	EU  										FUEL	INTERMITTENT    	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	170MC				140700	7217				PUMP INTERMITTENT WHEN A/C RUNNING.  ZERO TIME SINCE OVERHAUL.						1	G	7	2 	3U				H13EU   					 
1997041000059	19970410	00059	EU  	1997	4	10	97ZZZX1352       	1	19961212	G	3310	117923103	CONTROL         			BOLKMS	117   	BK117B1     	5626012	EU  										LIGHTS	SMOKES          	B			TI1R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	05	170MC	15   			0858	7217				LIGHT CONTROL UNIT SMOKES WHEN TURNED ON.  CIRCUIT BREAKER TRIPS.						1	G	7	2 	3U				H13EU   					 
1997041000060	19970410	00060	EU  	1997	4	10	97ZZZX1353       	1	19961214	G	2435	23032022	STARTER         			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	118LL	442  			23946	7097				STARTER/GENERATOR MALFUNCTION.  ENGINE SLOW TO START.						1	G	7	2 	3U				H13EU   					 
1997041000061	19970410	00061	NE  	1997	4	10	97ZZZX1354       	2	19961120	G	7321	430128307	FUEL CONTROL    			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	217MC	585  			51638	7195	LE45602			FUEL CONTROL LEAK UNDER PX PY CAP.						1	G	7	2 	3U	3	U		H13EU   	E5NE10				 
1997041000062	19970410	00062		1997	4	10	97ZZZX1355       	4	19961103	G	3421	222375033101	INDICATOR       			BELL  	222   	222U        	1182140	SW  										COCKPIT ATTITUDE	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM				0143	47573				ATTITUDE INDICTOR 'OFF' WARNING FLAG WILL NOT PULL.						1	G	7	2 	3U				H9SW    					 
1997010900780	19970109	00780	GL  	1997	1	9	97ZZZX136        	3	19961105	G	6110	860014002	PROP ASSY       			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		21893	5973 					DRG936282		INSPECTION FOUND PROPELLER ASSY DEFECTIVE.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1997010900781	19970109	00781	GL  	1997	1	9	97ZZZX137        	3	19961105	G	6110	860013002	PROP ASSY       			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		21893	5973 					DRG936282		INSPECTION FOUND PROPELLER ASSY DEFECTIVE.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1997041000078	19970410	00078	CE  	1997	4	10	97ZZZX1371       	1	19960731	G	3230	20430156	BOLT            			CESSNA	177   	177RG       	2073709	CE  										NLG DRAG LINK	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	33224	3800 				177RG0928				BOLT WHICH CONNECTS THE FORWARD AND AFT NOSE LANDING GEAR DRAG LINKS WAS FOUND LOOSE.  FURTHER INSPECTION SHOWED BOLT HA	D BROKEN THROUGH THE CENTER OF LUBRICATION PORT WHICH IS A HOLE DRILLED INTO THE DIAMETER OF THE BOLT WHICH MEETS A HOLE	 DRILLED IN THE AXIS OF THE BOLT.  NLG FAILURE WAS IMMINENT.				1	H	7	1 	3O				A20CE   					 
1997041000081	19970410	00081	GL  	1997	4	10	97ZZZX1374       	2	19960829	G	7313	23008054	NOZZLE          								ALLSN 	250C  	250C28B     	03013	GL  					NR 1	MELTED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		1    			MK169833					NR 1 NOZZLE BRAZE JOINTS MELTED.  ONLY RAN .6 HOURS ON TEST CELL RUN.											3	U			E1GL				 
1997041000082	19970410	00082	EU  	1997	4	10	97ZZZX1375       	1	19961216	G	6520	463900300	GEARBOX         			BOLKMS	117   	BK117A3     	5626015	EU  										T/R GEARBOX	WRONG PART      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		910  			478					GEARBOX WAS REMOVED FROM BK117, S/N 7146, AND ASB BK117-10-109 WAS NOT C/W DURING OVERHAUL.  THIS GEARBOX WAS TO BE USED	 ON A BO105S, S/N 2033, AND IS NOT ALLOWED TO BE IAW THIS ASB.					1	G	7	2 	3U				H13EU   					 
1997041000083	19970410	00083	EU  	1997	4	10	97ZZZX1376       	1	19961105	G	7120	1176270101	SUPPORT         			BOLKMS	117   	BK117B1     	5626012	EU  										ENGINE TRUSS	OUT OF LIMITS   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					1313					ENGINE TRUSS SUPPORT DIMENSIONS OUT OF LIMITS.						1	G	7	2 	3U				H13EU   					 
1997041000084	19970410	00084	EU  	1997	4	10	97ZZZX1377       	1	19961106	G	7120	1176272101	MOUNT LINK      			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE	OUT OF LIMITS   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					0339					ENGINE MOUNT LINK DIMENSIONS OUT OF LIMITS.						1	G	7	2 	3U				H13EU   					 
1997010900782	19970109	00782	GL  	1997	1	9	97ZZZX138        	3	19961105	G	6110	B5177	PROP ASSY       			CESSNA	208   	208         	2073702	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2688 						910855		INSPECTION FOUND PROPELLER ASSY P/N B5177 CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997041000096	19970410	00096	EU  	1997	4	10	97ZZZX1389       	1	19961220	G	7933	117904221	SENSOR          			BOLKMS	BK117 	BK117C1     	5626025	EU  										OIL SYSTEM	BROKEN          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				TEMPERATURE SENSOR PROBE BROKEN.						1	G	7	2 	3U			NC	H13EU   					 
1997010900783	19970109	00783	GL  	1997	1	9	97ZZZX139        	3	19961105	G	6110	A1896	PROP ASSY       			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768385		INSPECTION FOUND PROPELLER ASSY P/N A1896 CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997041000098	19970410	00098	EU  	1997	4	10	97ZZZX1391       	1	19961211	G	6220	10513143	BALL END ASSY   			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN ROTOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1054 				7505				BEARINGS WORN ON BALL END ASSY ON MAIN ROTOR HEAD.  REPLACED 4 EACH.						1	G	7	2 	3U			NC	H13EU   					 
1997041000099	19970410	00099	EU  	1997	4	10	97ZZZX1392       	1	19961211	G	6220	10513144	BALL END ASSY   			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN ROTOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	1054 				7505				BEARINGS WORN ON MAIN ROTOR HEAD, BALL END ASSY.  REPLACED 4 EACH.						1	G	7	2 	3U			NC	H13EU   					 
1997041000100	19970410	00100	EU  	1997	4	10	97ZZZX1393       	1	19961005	G	3310	1179203103	CONTROL UNIT    			BOLKMS	BK117 	BK117C1     	5626025	EU  										LIGHTS	TRIPS BREAKER   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				1021	7505				LIGHTING CONTROL UNIT TRIPS CIRCUIT BREAKER.						1	G	7	2 	3U			NC	H13EU   					 
1997041000101	19970410	00101	SW  	1997	4	10	97ZZZX1394       	1	19961211	G	2432	RG222	BATTERY         			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	400SL	229  			CBC261763	45235				SUBMITTER STATED THERE IS  POSSIBILITY THAT BATTERY IS LEAKING.  WILL NOT HOLD CHARGE.						1	G	7	1 	3U				H2SW    					 
1997041000102	19970410	00102	EU  	1997	4	10	97ZZZX1395       	1	19961215	G	5230	116201118	ACTUATOR        			BOLKMS	117   	BK117A3     	5626015	EU  										CARGO DOOR	LEAKED          	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	4493X					S7038				CARGO DOOR STRUT LEAKED OVERNIGHT AFTER INSTALLING NEW.						1	G	7	2 	3U				H13EU   					 
1997041000104	19970410	00104	CE  	1997	4	10	97ZZZX1397       	1	19961116	G	2422	PC17A	INVERTER        			BEECH 	200   	B200        	1152922	CE  										AC SYSTEM	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	75LV	117  			9717A	BB1075				AUTOPILOT DISCONNECTED, FOUND DEFECTIVE INVERTER.						1	L	7	2 	4T				A24CE   					 
1997041000105	19970410	00105		1997	4	10	97ZZZX1398       	4	19961212	G	3422	222375034101	INDICATOR       			BELL  	222   	222         	1182122	SW  										COCKPIT DG	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW	22   			8593	47520				DG INDICATOR'S OFF FLAG DOES NOT RETRACT.						1	G	7	2 	3U				H9SW    					 
1997041000106	19970410	00106	SW  	1997	4	10	97ZZZX1399       	1	19961022	G	6330	222031605109	FLEXTURE        			BELL  	222   	222         	1182122	SW  										TRANSMISSION MT	DEBONDED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW	274  			LK0078	47520				FLEXTURE END FITTINGS DEBONDED.						1	G	7	2 	3U				H9SW    					 
1997010900107	19970109	00107	GL  	1997	1	9	97ZZZX14         	3	19961031	G	6114		HUB             			CESSNA	210   	T210K       	2073447	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	MOUNT HOLES	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8237M	3700 	100  			T21059237	1985719H	740765		DURING 100 HOUR INSPECTION, FOUND PROP HUB CRACKED AT 5 OF THE 6 MOUNTING STUDS.						1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P21EA	 
1997010900784	19970109	00784	GL  	1997	1	9	97ZZZX140        	3	19961105	G	6110	A4191	PROPELLER ASSY  			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768385		INSPECTION FOUND PROPELLER ASSY P/N A4191 CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997010900785	19970109	00785	GL  	1997	1	9	97ZZZX141        	3	19961105	G	6110	D3474	PROPELLER ASSY  			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768385		INSPECTION FOUND PROPELLER ASSY P/N D3474 WORN.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997041000324	19970410	00324	NM  	1997	4	10	97ZZZX1416       	1	19961004	G	5711		SPAR CAP        			BOEING	727   	727243      	138408D	NM  										WS 519	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, CORROSION WAS NOTED ON RT WING LOWER CAP OF FRONT SPAR, WS 519, AFT OF NR 6 L/E SLAT ACTUATOR.						2	L	7	3 	4F			RT	A3WE    					 
1997041000325	19970410	00325	NM  	1997	4	10	97ZZZX1417       	1	19961003	G	5330		SKIN            			BOEING	727   	727243      	138408D	NM  										BS 1050-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, CORROSION WAS NOTED ON EXTERNAL SKIN BETWEEN STA 1050 AND STA 1070 AT S28L.						2	L	7	3 	4F			RT	A3WE    					 
1997041000326	19970410	00326	NM  	1997	4	10	97ZZZX1418       	1	19961003	G	5330		SKIN            			BOEING	727   	727243      	138408D	NM  										BS 720B	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, CORROSION WAS NOTED ON BOTH LT AND RT SIDES OF AIR CONDITIONING FROM AIR INLET ACTUATOR ACCESS P	ANELS AT STA 720B, FROM RBL 10 TO LBL 10.					2	L	7	3 	4F			RT	A3WE    					 
1997041000327	19970410	00327	NM  	1997	4	10	97ZZZX1419       	1	19961003	G	5315		FLOOR BEAM      			BOEING	727   	727243      	138408D	NM  										BS 400 WL 208	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, CORROSION WAS NOTED ON FLOOR BEAM UPPER CORD, FS 400, WL 208.						2	L	7	3 	4F			RT	A3WE    					 
1997010900786	19970109	00786	GL  	1997	1	9	97ZZZX142        	3	19961105	G	6110	D5878C501	PROP ASSY       			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								767592		INSPECTION FOUND PROPELLER ASSY P/N D5878/C501 CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997041000328	19970410	00328	NM  	1997	4	10	97ZZZX1420       	1	19961003	G	5720		CAP             			BOEING	727   	727243      	138408D	NM  										LT WING WS 437	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, CORROSION WAS NOTED ON LT WING LOWER CAP AT WS 437.  REF:  SI 104						2	L	7	3 	4F			RT	A3WE    					 
1997041000329	19970410	00329	NM  	1997	4	10	97ZZZX1421       	1	19961003	G	5743		FITTING         			BOEING	727   	727243      	138408D	NM  										LT MLG WELL	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, THE LEFT MAIN LANDING GEAR REAR TRUNNION BEAM OUTBOARD ATTACH FITTING WAS FOUND CRACKED.  REF: S	I 106.					2	L	7	3 	4F			RT	A3WE    					 
1997041000330	19970410	00330	NM  	1997	4	10	97ZZZX1422       	1	19961002	G	5320		WEB             			BOEING	727   	727243      	138408D	NM  										BS 1136	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, CORROSION WAS NOTED ON WEB FROM FS 1136 TO FS 1166, FROM BL 20 RT TO BL 45 RT.						2	L	7	3 	4F			RT	A3WE    					 
1997041000331	19970410	00331	NM  	1997	4	10	97ZZZX1423       	1	19961002	G	5320		HAT CHANNEL     			BOEING	727   	727243      	138408D	NM  										BS 1136 BL20R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, CORROSION WAS NOTED ON HAT CHANNEL AT STA 1136, FROM BL 20R TO BL 45R.						2	L	7	3 	4F			RT	A3WE    					 
1997041000332	19970410	00332	NM  	1997	4	10	97ZZZX1424       	1	19961002	G	5320		HAT CHANNEL     			BOEING	727   	727243      	138408D	NM  										BS 1136-1160	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12411					22052				DURING C-10 INSPECTION, CORROSION WAS NOTED ON HAT CHANNEL FROM STA 1136 - STA 1166, AT BL 20R.						2	L	7	3 	4F			RT	A3WE    					 
1997041000333	19970410	00333	NM  	1997	4	10	97ZZZX1425       	1	19961002	G	5320	6549914545	TIE FITTING     			BOEING	737   	737212      	1384461	NM  										BS 1016 S27R	CORROSION       	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	161FN					20521				DURING C-4 INSPECTION, CORROSION WAS NOTED ON STRINGER TIE FITTING AT FS 1016 AT S27R.						2	L	7	2 	4F				A16WE   					 
1997041000334	19970410	00334	NM  	1997	4	10	97ZZZX1426       	1	19961003	G	5311		FRAME           			BOEING	737   	737212      	1384461	NM  										BS 787 S26R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	161FN					20521				DURING C-4 INSPECTION, CORROSION WAS NOTED ON FORWARD FRAME STA 787 BETWEEN S26R AND S27R.						2	L	7	2 	4F				A16WE   					 
1997041000335	19970410	00335	NM  	1997	4	10	97ZZZX1427       	1	19961003	G	5320		SHEAR TIE       			BOEING	737   	737212      	1384461	NM  										BS 727A	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	161FN					20521				DURING C-4 INSPECTION, CORROSION WAS NOTED ON SHEAR TIES, FORWARD AND BACK SIDE OF FRAME 727A.						2	L	7	2 	4F				A16WE   					 
1997041000337	19970410	00337	NM  	1997	4	10	97ZZZX1429       	1	19961002	G	5320		SHEAR TIE       			BOEING	727   	7272M7      	138407S	NM  										BS 351.2 S22F	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	725RW					21502				DURING C-5 INSPECTION, CORROSION WAS NOTED ON SHEAR TIE AT FS 351.2 BETWEEN S22R AND S23R.						2	L	7	3 	4F				A3WE    					 
1997010900787	19970109	00787	GL  	1997	1	9	97ZZZX143        	3	19961105	G	6110	D3474	PROP ASSY       			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								767592		INSPECTION FOUND PROPELLER ASSY P/N D3474 WORN.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997041000338	19970410	00338	NM  	1997	4	10	97ZZZX1430       	1	19961002	G	5320		ANGLE           			BOEING	727   	7272M7      	138407S	NM  										BS 351.2 WEB	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	725RW					21502				DURING C-5 INSPECTION, CORROSION WAS NOTED ON ANGLE SUPPORTING RT FLOOR WEB TO FORWARD SIDE FS 351.2 WEB.						2	L	7	3 	4F				A3WE    					 
1997041000339	19970410	00339	NM  	1997	4	10	97ZZZX1431       	1	19961002	G	5320		WEB             			BOEING	727   	7272M7      	138407S	NM  										BS 351.2 S22R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	725RW					21502				DURING C-5 INSPECTION, CORROSION WAS NOTED ON WEB FORWARD SIDE 351.2 FRAME FROM S22R TO S23R.						2	L	7	3 	4F				A3WE    					 
1997041000340	19970410	00340	NM  	1997	4	10	97ZZZX1432       	1	19961009	G	5311		FRAME           			BOEING	727   	727225      	1384077	NM  										BS 344 S25R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8880Z					21453				DURING C-2 INSPECTION, CORROSION WAS NOTED ON FRAME 344 AT S25R.						2	L	7	3 	4F				A3WE    					 
1997041000341	19970410	00341	NM  	1997	4	10	97ZZZX1433       	1	19961009	G	5320		SHEAR TIE       			BOEING	727   	727225      	1384077	NM  										BS 344 NLG BOX	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8880Z					21453				DURING C-2 INSPECTION, CORROSION WAS NOTED ON SHEAR TIE STA 344 AT THE RT SIDE OF THE NOSE GEARBOX.						2	L	7	3 	4F				A3WE    					 
1997041000342	19970410	00342	NM  	1997	4	10	97ZZZX1434       	1	19961009	G	5312		BULKHEAD        			BOEING	727   	727225      	1384077	NM  										BS 294.5 RBL 25	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8880Z					21453				DURING C-2 INSPECTION, CORROSION WAS NOTED ON THE BACKSIDE BULKHEAD STA 294.5 EXTENDING FROM RBL 25 TO RBL 45.						2	L	7	3 	4F				A3WE    					 
1997041000343	19970410	00343	NM  	1997	4	10	97ZZZX1435       	1	19961009	G	5313		STRINGER        			BOEING	727   	727225      	1384077	NM  										BS 420 S27R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8880Z					21453				DURING C-2 INSPECTION, CORROSION WAS NOTED ON S27R JUST FORWARD OF STA 420.						2	L	7	3 	4F				A3WE    					 
1997041000344	19970410	00344	NM  	1997	4	10	97ZZZX1436       	1	19961002	G	5311		FRAME           			BOEING	727   	727224      	1384076	NM  										BS 380 S6R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-10 INSPECTION, CORROSION WAS NOTED ON FRAME FS 380 BETWEEN S6R AND S7R.						2	L	7	3 	4F				A3WE    					 
1997041000345	19970410	00345	NM  	1997	4	10	97ZZZX1437       	1	19961002	G	5311		FRAME           			BOEING	727   	727224      	1384076	NM  										BS 219.8 S25L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-10 INSPECTION, CORROSION WAS NOTED ON FRAME 219.8 AT S25L.						2	L	7	3 	4F				A3WE    					 
1997041000346	19970410	00346	NM  	1997	4	10	97ZZZX1438       	1	19961009	G	5320		TEE FITTING     			BOEING	727   	727224      	1384076	NM  										BS 265	CORROSION       	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON COCKPIT FLOOR SUPPORT BEAM TRIPLE TEE FITTING AT STA 265.						2	L	7	3 	4F				A3WE    					 
1997041000347	19970410	00347	NM  	1997	4	10	97ZZZX1439       	1	19961009	G	5330		SKIN            			BOEING	727   	727224      	1384076	NM  										BS 1130-1150	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON AIRCRAFT SKIN BETWEEN STA 1130 AND STA 1150 BETWEEN S24R AND S25R	.					2	L	7	3 	4F				A3WE    					 
1997010900788	19970109	00788	GL  	1997	1	9	97ZZZX144        	3	19961105	G	6111	D7015C93	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	NR 3 SOCKET	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		INSPECTION FOUND BLADE P/N D70151/C93 BLADE, NR 3 SOCKET CRACKED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997041000348	19970410	00348	NM  	1997	4	10	97ZZZX1440       	1	19961009	G	5330		SKIN            			BOEING	727   	727224      	1384076	NM  										BS 328-344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON AIRCRAFT SKIN BETWEEN STA 328 AND STA 344 AT S24R.						2	L	7	3 	4F				A3WE    					 
1997041000349	19970410	00349	NM  	1997	4	10	97ZZZX1441       	1	19961009	G	5330		SKIN            			BOEING	727   	727224      	1384076	NM  										BS 580-720	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON AIRCRAFT SKIN BETWEEN STA 580 AND STA 720 AT S9R.						2	L	7	3 	4F				A3WE    					 
1997041000350	19970410	00350	NM  	1997	4	10	97ZZZX1442       	1	19961009	G	5330		SKIN            			BOEING	727   	727224      	1384076	NM  										BS 1172 S17L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-10 INSPECTION, LEVEL 2 CORROSION WAS NOTED ON AIRCRAFT SKIN AT BELT FRAME TIE AT STA 1172 AT S17L.						2	L	7	3 	4F				A3WE    					 
1997041000351	19970410	00351	NM  	1997	4	10	97ZZZX1443       	1	19961003	G	5320		SILL WEB        			BOEING	727   	727243      	138408D	NM  										BS 380 S17R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, CORROSION WAS NOTED ON THE R-1 DOOR BOTTOM SILL WEB BETWEEN STA 380 AND STA 420 AT S17R.						2	L	7	3 	4F			RT	A3WE    					 
1997041000352	19970410	00352	NM  	1997	4	10	97ZZZX1444       	1	19961009	G	5315		FLOOR BEAM      			BOEING	727   	727243      	138408D	NM  										BS 1130 RBL 24	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, CORROSION WAS NOTED ON UPPER SURFACE OF FLOOR BEAM AT FS 1130 AT RBL 24.						2	L	7	3 	4F			RT	A3WE    					 
1997041000353	19970410	00353	NM  	1997	4	10	97ZZZX1445       	1	19961009	G	3233	69181941	FITTING         			BOEING	727   	727243      	138408D	NM  										NLG ACTUATOR	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, NOSE LANDING GEAR ACTUATOR FITTING FOUND CRACKED AT UPPER ACTUATOR ATTACH BOLT HOLE.						2	L	7	3 	4F			RT	A3WE    					 
1997041000354	19970410	00354	NM  	1997	4	10	97ZZZX1446       	1	19961003	G	5311		FRAME           			BOEING	727   	727243      	138408D	NM  										BS 372 S16R-S17R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, CORROSION WAS NOTED ON FRAME AT STA 372 BETWEEN S16R AND S17R.						2	L	7	3 	4F			RT	A3WE    					 
1997041000355	19970410	00355	NM  	1997	4	10	97ZZZX1447       	1	19961004	G	5530		STRINGER        			BOEING	727   	727243      	138408D	NM  										V STAB 8L RIB 7	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, A CRACK WAS NOTED ON VERTICAL STABILIZER, STR 8L AT RIB NR 7.						2	L	7	3 	4F			RT	A3WE    					 
1997041000356	19970410	00356	NM  	1997	4	10	97ZZZX1448       	1	19961004	G	5320		WEB SUPPORTS    			BOEING	727   	727243      	138408D	NM  										RT TORQ BOX	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, THREE CRACKS WERE NOTED ON RT HAND LOWER TORQUE BOX HORIZONTAL WEB SUPPORTS BELOW AIRSTAIR TORQU	E TUBE SUPPORT FITTING.					2	L	7	3 	4F			RT	A3WE    					 
1997010900789	19970109	00789	GL  	1997	1	9	97ZZZX145        	3	19961105	G	6110	D3474	PROPELLER ASSY  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		INSPECTION FOUND PROPELLER ASSY P/N D3474 WORN.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997041000434	19970410	00434	NM  	1997	4	10	97ZZZX1455       	1	19961004	G	5330		SKIN            			BOEING	727   	7272J7      	138400E	NM  										BS 344 S24L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, CORROSION WAS NOTED IN EXTERNAL SKIN AT FS 344 AT S24L.						2	L	7	3 	4F				A3WE    					 
1997041000435	19970410	00435	NM  	1997	4	10	97ZZZX1456       	1	19961004	G	5313		STRINGER        			BOEING	727   	7272J7      	138400E	NM  										BS 340 S23R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, CORROSION WAS NOTED ON S23R AT STA 340.						2	L	7	3 	4F				A3WE    					 
1997041000436	19970410	00436	NM  	1997	4	10	97ZZZX1457       	1	19961004	G	5320		WEB             			BOEING	727   	7272J7      	138400E	NM  										BS 1070 S17L	CORODED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, CORROSION WAS NOTED AT L-2 DOOR FRAME CUT-OUT, LOWER AFT SIDE, STA 1070 AT S17L.						2	L	7	3 	4F				A3WE    					 
1997041000437	19970410	00437	NM  	1997	4	10	97ZZZX1458       	1	19961006	G	5313		STRINGER        			BOEING	727   	7272J7      	138400E	NM  										BS 328 S26L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, CORROSION WAS NOTED ON STR 26L AT FS 328 UNDER FLOOR WEB.						2	L	7	3 	4F				A3WE    					 
1997041000438	19970410	00438	NM  	1997	4	10	97ZZZX1459       	1	19961004	G	5347		SEAT TRACK      			BOEING	727   	7272J7      	138400E	NM  										BS 1030-1110	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, CORROSION WAS NOTED ON CABIN SEAT TRACK FROM STA 1030 TO STA 1110 AT LBL 40.						2	L	7	3 	4F				A3WE    					 
1997010900790	19970109	00790	GL  	1997	1	9	97ZZZX146        	3	19961105	G	6110	A1896	PROPELLER ASSY  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		INSPECTION FOUND PROPELLER ASSY P/N A1896 CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997041000439	19970410	00439	NM  	1997	4	10	97ZZZX1460       	1	19961004	G	5320		T CHORD         			BOEING	727   	7272J7      	138400E	NM  										BS 1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, CORROSION WAS NOTED ON LOWER T-CHORD, FLOOR BEAM STA 1070 AT LBL 30.						2	L	7	3 	4F				A3WE    					 
1997041000440	19970410	00440	NM  	1997	4	10	97ZZZX1461       	1	19961008	G	5320	69191222	CHANNEL         			BOEING	727   	7272J7      	138400E	NM  										NLG LOCK ACT	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, A CRACK WAS NOTED IN THE NOSE GEAR LOCK ACTUATOR CHANNEL.						2	L	7	3 	4F				A3WE    					 
1997041000441	19970410	00441	NM  	1997	4	10	97ZZZX1462       	1	19961004	G	5330		SKIN            			BOEING	727   	7272J7      	138400E	NM  										BS 344 S23R	DAMAGED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION,  6 EACH FASTENER HOLES FOUND KNIFE-EDGED THROUGH SKIN AT LAP SEAM, STA 344, S23R.  REF:  C53-100	-01.					2	L	7	3 	4F				A3WE    					 
1997041000442	19970410	00442	NM  	1997	4	10	97ZZZX1463       	1	19961004	G	5320		ANGLE           			BOEING	727   	7272J7      	138400E	NM  										BS 1273	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, A CRACK WAS NOTED IN ANGLE BELOW AFT AIRSTAIR ACTUATOR SUPPORT FITTING AT FS 1273.  REF:  C53-13	7-01.					2	L	7	3 	4F				A3WE    					 
1997041000443	19970410	00443	NM  	1997	4	10	97ZZZX1464       	1	19961004	G	5320		WEB             			BOEING	727   	7272J7      	138400E	NM  										BS 870	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, A 3.50 INCH CRACK WAS NOTED IN FS 870 WEB, FORWARD SIDE OF LT MAIN WHEELWELL.  REF:  C53-100-01.						2	L	7	3 	4F				A3WE    					 
1997041000444	19970410	00444	NM  	1997	4	10	97ZZZX1465       	1	19961004	G	5330		SKIN            			BOEING	727   	7272J7      	138400E	NM  										BS 1090 S18L	DENTED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, A DENT WAS NOTED ON FUSELAGE EXTERNAL AT STA 1090 AT S18L AND S19L.						2	L	7	3 	4F				A3WE    					 
1997041000445	19970410	00445	NM  	1997	4	10	97ZZZX1466       	1	19961008	G	5330		SKIN            			BOEING	727   	7272J7      	138400E	NM  										BS 340 S22L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, CORROSION WAS NOTED ON SKIN PANEL AT FS 340 BETWEEN S22F AND S23R.						2	L	7	3 	4F				A3WE    					 
1997041000446	19970410	00446	NM  	1997	4	10	97ZZZX1467       	1	19961008	G	5315		FLOOR BEAM      			BOEING	727   	7272J7      	138400E	NM  										BS 1166 BL ZERO	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	129NA					20880				DURING C-10 INSPECTION, CORROSION WAS NOTED ON LOWER FLOOR BEAM CHORD AT FS 1166 AT BL ZERO.						2	L	7	3 	4F				A3WE    					 
1997041000448	19970410	00448	NM  	1997	4	10	97ZZZX1469       	1	19961127	G	2430	A1SA	DIODE           			ROBSIN	R22   	R22BETA     		NM  										BATTERY SOLENOID	SHORTED         	D		A		A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			WP	13	83154					2470				TEN MINUTES AFTER DEPARTURE FROM PHOG CFI, NOTICED SMOKE COMING FROM CONSOLE.  MASTER WAS SWITCHED OFF BUT AFTER A PRECA	UTIONARY LANDING IN FIELD, MECHANIC FOUND OVER 20 WIRES WITH MELTED INSULATION FROM VARIOUS LOCATIONS FROM THE UPPER CON	SOLE THROUGH-WIRE LOOM TO ELECT COMPONENTS.  SEVERAL COMPONENTS WERE SHORTED AND DAMAGED.  APPARENTLY A DIODE ON BATTERY	 SOLENOID SHORTED CAUSING HIGH CURRENT FLOW THROUGH MASTER SWITCH WIRE WHICH HEATED HARNESS BUNDLE AND OTHER COMPONENTS.	  SUBMITTER RECOMMENDED INSTALLING CIRCUIT PROTECTION TO MASTER SWITCH.		1	G	7	1 	3O				H10WE   					 
1997010900791	19970109	00791	GL  	1997	1	9	97ZZZX147        	3	19961105	G	6110	A4191	PROPELLER ASSY  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		INSPECTION FOUND PROPELLER ASSY P/N A4191 CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997041000454	19970410	00454	NM  	1997	4	10	97ZZZX1475       	1	19961021	G	5320		CHORD           			BOEING	727   	727276      	138408R	NM  										BS 1177 BL50L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				STA 1127, CHORD CORRODED BL 50L.						2	L	7	3 	4F			RT	A3WE    					 
1997041000455	19970410	00455	NM  	1997	4	10	97ZZZX1476       	1	19961021	G	5320		CHORD           			BOEING	727   	727276      	138408R	NM  										BS 1177 BL25R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				STA 1177, CHORD CORRODED BETWEEN BL 25R TO BL 50R.						2	L	7	3 	4F			RT	A3WE    					 
1997041000456	19970410	00456	NM  	1997	4	10	97ZZZX1477       	1	19961021	G	5311		FRAME           			BOEING	727   	727276      	138408R	NM  										BS 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				STA 1183 FRAME CORRODED LEFT SIDE.						2	L	7	3 	4F			RT	A3WE    					 
1997041000457	19970410	00457	NM  	1997	4	10	97ZZZX1478       	1	19961017	G	5315		FLOOR BEAM      			BOEING	727   	727276      	138408R	NM  										BS 1130 LBL 10	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				DURING C-7 INSPECTION, LEVEL 2 CORROSION NOTED ON LOWER CHORD OF CABIN FLOOR BEAM AT STA 1130 AT LBL 10.						2	L	7	3 	4F			RT	A3WE    					 
1997010900792	19970109	00792	GL  	1997	1	9	97ZZZX148        	3	19961105	G	6110	C2715C33	PROPELLER ASSY  			CESSNA	210   	210         	2073402	CE  						MCAULY	2A36C	D2A36C33    	GL  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								61811		INSPECTION FOUND PROPELLER ASSY C2715/C33 NR 1 SOCKET CRACKED.						1	H	7	1 	3O			RT	3A21    		5	C	P880	 
1997041000517	19970410	00517	NM  	1997	4	10	97ZZZX1489       	1	19961002	G	5320		STRINGER TIE    			BOEING	727   	727224      	1384076	NM  										BS 560 S19R	CORROSION       	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-10 INSPECTION, CORROSION WAS NOTED ON STR TIE S19R AT FS 560.						2	L	7	3 	4F				A3WE    					 
1997010900793	19970109	00793	GL  	1997	1	9	97ZZZX149        	3	19961105	G	6111	S90M8	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	2A36C	D2A36C33    	GL  	PROPELLER	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					C999			61811		INSPECTION FOUND PROPELLER BLADE P/N S90M8 BELOW MINIMUM.						1	H	7	1 	3O			RT	3A21    		5	C	P880	 
1997041000518	19970410	00518	NM  	1997	4	10	97ZZZX1490       	1	19961004	G	5320		I BEAM          			BOEING	727   	727243      	138408D	NM  										BS 1166 RBL 45	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, CORROSION WAS NOTED ON UPPER I-BEAM AT STA 1166, AT RBL 45.						2	L	7	3 	4F			RT	A3WE    					 
1997041000519	19970410	00519	NM  	1997	4	10	97ZZZX1491       	1	19961004	G	5313		STRINGER        			BOEING	727   	727243      	138408D	NM  										BS 950F S28L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, CORROSION WAS NOTED ON S28L FROM STA 950F TO STA 970.						2	L	7	3 	4F			RT	A3WE    					 
1997041000520	19970410	00520	NM  	1997	4	10	97ZZZX1492       	1	19961004	G	5313		STRINGER        			BOEING	727   	727243      	138408D	NM  										BS950F-1010 KEEL	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, CORROSION WAS NOTED ON KEEL STRINGER S29L FROM STA 950F TO STA 1010.						2	L	7	3 	4F			RT	A3WE    					 
1997041000521	19970410	00521	NM  	1997	4	10	97ZZZX1493       	1	19961004	G	5330		SKIN            			BOEING	727   	727243      	138408D	NM  										BS 950F S28L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, CORROSION WAS NOTED ON EXTERNAL SKIN AT STA 950F AT S28L.						2	L	7	3 	4F			RT	A3WE    					 
1997041000522	19970410	00522	NM  	1997	4	10	97ZZZX1494       	1	19961003	G	5320	652558910	SUPPORT         			BOEING	727   	727243      	138408D	NM  										BS 848.95 BL 0	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, A CABIN FLOOR SUPPORT WAS CRACKED AT STA 848.95 AT BL ZERO.  REF:  SI-158.1.						2	L	7	3 	4F			RT	A3WE    					 
1997041000523	19970410	00523	NM  	1997	4	10	97ZZZX1495       	1	19961003	G	5320	65255896	SUPPORT         			BOEING	727   	727243      	138408D	NM  										BS 760.95 BL 0	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	14416					22168				DURING C-10 INSPECTION, A CRACK WAS NOTED IN CABIN FLOOR SUPPORT AT STA 760.95 AT BL ZERO.  REF:  SI-158.1.						2	L	7	3 	4F			RT	A3WE    					 
1997041000524	19970410	00524	NM  	1997	4	10	97ZZZX1496       	1	19961009	G	5330		SKIN            			BOEING	727   	727251      	138408H	NM  										BS 294 S19R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SKIN, RT FORWARD FUSELAGE STA 294 TO STA 360, EXTENDING UNDER LAP S19R	.					2	L	7	3 	4F				A3WE    					 
1997041000525	19970410	00525	NM  	1997	4	10	97ZZZX1497       	1	19961009	G	5330		SKIN            			BOEING	727   	727251      	138408H	NM  										BS 440 S18R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SKIN RT FORWARD FUSELAGE AT STA 440 EXTENDING FROM S18R TO S21R.						2	L	7	3 	4F				A3WE    					 
1997041000526	19970410	00526	NM  	1997	4	10	97ZZZX1498       	1	19961009	G	5330		SKIN            			BOEING	727   	727251      	138408H	NM  										BS 1166 S22L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, BROKEN FASTENERS AND CORROSION WAS NOTED UNDER SKIN PANEL BELOW LT AFT LAV SERVICE COMPARTMEN	T, STA 1166, S22L.					2	L	7	3 	4F				A3WE    					 
1997041000527	19970410	00527	NM  	1997	4	10	97ZZZX1499       	1	19961009	G	5312		BULKHEAD        			BOEING	727   	727251      	138408H	NM  										BS 351 S21L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, INTERGRANULAR CORROSION WAS NOTED ON LOWER CHORD OF BULKHEAD STA 351 BETWEEN S21L EXTENDING T	O S26L.					2	L	7	3 	4F				A3WE    					 
1997010900108	19970109	00108	EA  	1997	1	9	97ZZZX15         	2	19961201	G	8550	77527	FILLER TUBE     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					DIPSTICK	CRACKED         	D	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	09	949SS					317752070	L731661A			PLASTIC FILLER TUBE CRACKED AT TOP WHERE DIPSTICK SNAPS IN PLACE CAUSING OIL LEAK.  SUSPECT CAUSE OF PROBLEM:  UNIT MADE	 OF PLASTIC.  SUBMITTER STATED SHOULD BE MADE OF CAST OR MALLEABLE MATERIAL.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997010900794	19970109	00794	GL  	1997	1	9	97ZZZX150        	3	19961105	G	6111	S90M8	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	2A36C	D2A36C33    	GL  	PROPELLER	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					C983			61811		INSPECTION FOUND BLADE P/N S90M8 BELOW MINIMUM.						1	H	7	1 	3O			RT	3A21    		5	C	P880	 
1997041000528	19970410	00528	NM  	1997	4	10	97ZZZX1500       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 312 S21L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S21L EXTENDING FROM STA 312 - STA 344.						2	L	7	3 	4F				A3WE    					 
1997041000529	19970410	00529	NM  	1997	4	10	97ZZZX1501       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 312 S20L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK  INSPECTION, CORROSION WAS NOTED ON STRINGER S20L FORWARD OF STA 312.						2	L	7	3 	4F				A3WE    					 
1997041500054	19970415	00054	NM  	1997	4	15	97ZZZX1502       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 312 S22L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK  INSPECTION, CORROSION WAS NOTED ON STRINGER S22L FORWARD OF STA 312						2	L	7	3 	4F				A3WE    					 
1997041000530	19970410	00530	NM  	1997	4	10	97ZZZX1503       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 380 S22R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK  INSPECTION, CORROSION WASNOTED ON STRINGER S22R EXTENDING FROM STA 380 TO STA 440.						2	L	7	3 	4F				A3WE    					 
1997041000531	19970410	00531	NM  	1997	4	10	97ZZZX1504       	1	19961009	G	5311		FRAME           			BOEING	727   	727251      	138408H	NM  										BS 420 S21R	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK  INSPECTION, A CRACK WAS NOTED IN FRAME 420 AT S21R.						2	L	7	3 	4F				A3WE    					 
1997041000532	19970410	00532	NM  	1997	4	10	97ZZZX1505       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 380 S21R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK  INSPECTION, CORROSION WAS NOTED ON STRINGER S21R EXTENDING FROM STA 380 - STA 440.						2	L	7	3 	4F				A3WE    					 
1997041000533	19970410	00533	NM  	1997	4	10	97ZZZX1506       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 440 S23R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S23R EXTENDING FROM STA 360 - STA 440.						2	L	7	3 	4F				A3WE    					 
1997041000534	19970410	00534	NM  	1997	4	10	97ZZZX1507       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 312 S19R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S19R EXTENDING FROM STA 312 TO STA 344.						2	L	7	3 	4F				A3WE    					 
1997041000535	19970410	00535	NM  	1997	4	10	97ZZZX1508       	1	19961009	G	5320		GEARBOX         			BOEING	727   	727251      	138408H	NM  										NLG BS 320-328	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON LOWER NOSE LANDING GEAR BOX CHORD FROM STA 320 TO STA 328.						2	L	7	3 	4F				A3WE    					 
1997041000536	19970410	00536	NM  	1997	4	10	97ZZZX1509       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 312 S18R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S18R EXTENDING FROM STA 312 TO STA 328.						2	L	7	3 	4F				A3WE    					 
1997010900795	19970109	00795	GL  	1997	1	9	97ZZZX151        	3	19961105	G	6110	C1976	PROPELLER ASSY  			CESSNA	210   	210         	2073402	CE  						MCAULY	2A36C	D2A36C33    	GL  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								61811		INSPECTION FOUND PROPELLER ASSY P/N C1976 CRACKED.						1	H	7	1 	3O			RT	3A21    		5	C	P880	 
1997041000537	19970410	00537	NM  	1997	4	10	97ZZZX1510       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 360 S20R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S20R EXTENDING FROM STA 360 TO STA 380.						2	L	7	3 	4F				A3WE    					 
1997041000538	19970410	00538	NM  	1997	4	10	97ZZZX1511       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 460 S28R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S28R EXTENDING FROM STA 460 TO STA 480.						2	L	7	3 	4F				A3WE    					 
1997041000539	19970410	00539	NM  	1997	4	10	97ZZZX1512       	1	19961009	G	5311		FRAME           			BOEING	727   	727251      	138408H	NM  										BS 360 RBL 10	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON TOP CHORD OF FRAME STA 360 APPROXIMATE RBL 10.						2	L	7	3 	4F				A3WE    					 
1997041000540	19970410	00540	NM  	1997	4	10	97ZZZX1513       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 420 S27R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S27R EXTENDING FROM STA 420 TO STA 480.						2	L	7	3 	4F				A3WE    					 
1997041000541	19970410	00541	NM  	1997	4	10	97ZZZX1514       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 400 S25R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S25R EXTENDING FROM STA 400 TO STA 440.						2	L	7	3 	4F				A3WE    					 
1997041000542	19970410	00542	NM  	1997	4	10	97ZZZX1515       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 400 S24R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S24R EXTENDING FROM STA 400 TO STA 440.						2	L	7	3 	4F				A3WE    					 
1997041000543	19970410	00543	NM  	1997	4	10	97ZZZX1516       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 360 S25L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S25L JUST FORWARD OF STA 360.						2	L	7	3 	4F				A3WE    					 
1997041000544	19970410	00544	NM  	1997	4	10	97ZZZX1517       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 277 S25L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S25L FROM STA 277 TO STA 294.						2	L	7	3 	4F				A3WE    					 
1997041000545	19970410	00545	NM  	1997	4	10	97ZZZX1518       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 360 S26R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S26R EXTENDING FROM STA 360 TO STA 380.						2	L	7	3 	4F				A3WE    					 
1997041000546	19970410	00546	NM  	1997	4	10	97ZZZX1519       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 360 S24L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S24L AFT OF STA 360.						2	L	7	3 	4F				A3WE    					 
1997010900796	19970109	00796	GL  	1997	1	9	97ZZZX152        	3	19961105	G	6110	A4001	DOWEL PIN       			CESSNA	182   	182R        	2072731	CE  						MCAULY	2A34C	C2A34C204   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3080 	1478 					901245		INSPECTION FOUND PROPELLER ASSY DOWEL PIN CORRODED.						1	L	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997041000547	19970410	00547	NM  	1997	4	10	97ZZZX1520       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 380 S21L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S21L EXTENDING FROM STA 380 TO STA 400.						2	L	7	3 	4F				A3WE    					 
1997041000548	19970410	00548	NM  	1997	4	10	97ZZZX1521       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 360 S18L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S18L EXTENDING FROM STA 360 TO STA 380.						2	L	7	3 	4F				A3WE    					 
1997041000549	19970410	00549	NM  	1997	4	10	97ZZZX1522       	1	19961009	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 360 S19L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON STRINGER S29L EXTENDING FROM STA 360 TO STA 380.						2	L	7	3 	4F				A3WE    					 
1997041000550	19970410	00550	NM  	1997	4	10	97ZZZX1523       	1	19961009	G	5320		WEB             			BOEING	727   	727251      	138408H	NM  										BS 243-259	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267US					20289				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON RT SIDE NOSE WHEELWELL BOX EXTENDING FROM STA 243 TO STA 259.						2	L	7	3 	4F				A3WE    					 
1997041000551	19970410	00551	NM  	1997	4	10	97ZZZX1524       	1	19961009	G	5330		SKIN            			BOEING	727   	727230      	1384080	NM  										BS 294 S21R-S22R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED AT SKIN BULGE FUSELAGE STA 294 EXTENDING FROM S21R TGO S22R.						2	L	7	3 	4F				A3WE    					 
1997041000552	19970410	00552	NM  	1997	4	10	97ZZZX1525       	1	19961009	G	5320		SHEAR TIE       			BOEING	727   	727230      	1384080	NM  										BS 328 S26L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SHEAR TIE AFT SIDE OF FRAME STA 328 BETWEEN NOSE GEARBOX AND S26L.						2	L	7	3 	4F				A3WE    					 
1997041000553	19970410	00553	NM  	1997	4	10	97ZZZX1526       	1	19961009	G	5320		BOX WEB         			BOEING	727   	727230      	1384080	NM  										BS 294.5-312	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON THE LT SIDE OF THE NOSE GEARBOX WEB (FROM E/E BAY) FROM STA 294.5 TO S	TA 312.					2	L	7	3 	4F				A3WE    					 
1997041000554	19970410	00554	NM  	1997	4	10	97ZZZX1527       	1	19961009	G	5311		FRAME           			BOEING	727   	727230      	1384080	NM  										BS 380 S24R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON FRAME STA 380 AT S24R.						2	L	7	3 	4F				A3WE    					 
1997041700001	19970417	00001	WP  	1997	4	17	97ZZZX1528       	1	19961009	G	5311		BELT FRAME      			CVAC  	440   	440         	2422902	WP  										BS 319 S30R	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN BELT FRAME STA 319 AT S30R.						2	L	7	2 	4R				6A6     					 
1997041700002	19970417	00002	WP  	1997	4	17	97ZZZX1529       	1	19961009	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 730 S8L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				DURING C-CHECK INSPECTION, SCAB PATCH WAS REMOVED AT FS 730, S8L AND S9L, AND AIRCRAFT SKIN  WAS FOUND CORRODED BEYOND L	IMITS.					2	L	7	2 	4R				6A6     					 
1997010900797	19970109	00797	GL  	1997	1	9	97ZZZX153        	3	19961105	G	6110	B5177	PROPELLER ASSY  			CESSNA	208   	208         	2073702	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2760 						900938		INSPECTION FOUND PROPELLER ASSY P/N 35177 CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997041700003	19970417	00003	WP  	1997	4	17	97ZZZX1530       	1	19961009	G	5315		FLOOR BEAM      			CVAC  	440   	440         	2422902	WP  										BS 718 RBL 8	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN CABIN FLOOR BEAM STA 718 AT RBL 8 TO RBL 12.						2	L	7	2 	4R				6A6     					 
1997041700004	19970417	00004	WP  	1997	4	17	97ZZZX1531       	1	19961009	G	5311		FRAME           			CVAC  	440   	440         	2422902	WP  										BS 641 S25L	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN OUTBOARD FRAME FLANGE, STA 641 AT S25L.						2	L	7	2 	4R				6A6     					 
1997041700005	19970417	00005	WP  	1997	4	17	97ZZZX1532       	1	19961009	G	5313		STRINGER        			CVAC  	440   	440         	2422902	WP  										BS 712 10R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S10R AT FS 712.						2	L	7	2 	4R				6A6     					 
1997010900798	19970109	00798	GL  	1997	1	9	97ZZZX154        	3	19961105	G	6110	D5010	PROPELLER ASSY  			CESSNA	208   	208         	2073702	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2760 						900938		INSPECTION FOUND PROPELLER ASSY P/N D5010 CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997010900799	19970109	00799	GL  	1997	1	9	97ZZZX155        	3	19961105	G	6110	D3474	PROPELLER       			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789223		INSPECTION FOUND PROPELLER ASSY P/N 3474 WORN.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997010900800	19970109	00800	GL  	1997	1	9	97ZZZX156        	3	19961105	G	6111	B48201	BLADE           			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789223		INSPECTION FOUND PROPELLER BLADE CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997010900801	19970109	00801	GL  	1997	1	9	97ZZZX157        	3	19961105	G	6111	C5270	BEARING         			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	BLADE	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789223		INSPECTION FOUND BLADE BEARING CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997010900802	19970109	00802	GL  	1997	1	9	97ZZZX158        	3	19961105	G	6111	B4426	BLADE           			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789223		INSPECTION FOUND PROPELLER BLADE ASSY B4426 CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997010900803	19970109	00803	GL  	1997	1	9	97ZZZX159        	3	19961105	G	6110	8382	PROPELLER ASSY  			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		INSPECTION FOUND PROPELLER ASSY P/N 838-2 CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1997041700190	19970417	00190	NM  	1997	4	17	97ZZZX1596       	1	19961009	G	5320		GEARBOX         			BOEING	727   	727230      	1384080	NM  										NLG BS 294.5	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON TOP NLG BOX LT SIDE (FROM E/E BAY) EXTENDING FROM STA 294.5 TO STA 312	.					2	L	7	3 	4F				A3WE    					 
1997041700191	19970417	00191	NM  	1997	4	17	97ZZZX1597       	1	19961009	G	5313		STRINGER        			BOEING	727   	727230      	1384080	NM  										BS 360 S19R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S19R BETWEEN STA 360 AND STA 380.						2	L	7	3 	4F				A3WE    					 
1997041700192	19970417	00192	NM  	1997	4	17	97ZZZX1598       	1	19961009	G	5313		STRINGER        			BOEING	727   	727230      	1384080	NM  										BS 360 S20R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S20R BETWEEN STA 360 AND STA 380.						2	L	7	3 	4F				A3WE    					 
1997041700193	19970417	00193	NM  	1997	4	17	97ZZZX1599       	1	19961009	G	5313		STRINGER        			BOEING	727   	727230      	1384080	NM  										BS 380 S18R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S18R BETWEEN STA 360 AND STA 380.						2	L	7	3 	4F				A3WE    					 
1997010900109	19970109	00109		1997	1	9	97ZZZX16         	4	19961025	G	2210	SUSIII	SHUTTLE VALVE   			PIPER 	PA28  	PA28R200    	7102811	SO  										AUTOFLT	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1043X				1895	28R7535224				INTERNAL VALVE FAILED IN THE PRECISE FLIGHT SUSIII SHUTTLE VALVE.  A RIVET HEAD MIGRATED DOWNSTREAM TO THE ENGINE DRIVEN	 VACUUM PUMP.  THE VACUUM PUMP SUBSEQUENTLY FAILED DUE TO FOREIGN OBJECT INJESTION.  SUBMITTER STATED CHECK SYSTEM VISUA	LLY ON AN ANNUAL BASIS REMOVING THEM FROM SERVICE AFTER 1,000 HRS.				1	L	7	1 	3O				2A13    					 
1997010900804	19970109	00804	GL  	1997	1	9	97ZZZX160        	3	19961105	G	6110	971	PROPELLER ASSY  			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		INSPECTION FOUND PROPELLER ASSY P/N 971 BEARING CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1997041700194	19970417	00194	NM  	1997	4	17	97ZZZX1600       	1	19961009	G	5320		BOX WEB         			BOEING	727   	727230      	1384080	NM  										BS 312-328	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON RT NLG BOX WEB BETWEEN STA 312 AND STA 328 (NOTED FORM E/E BAY AREA).						2	L	7	3 	4F				A3WE    					 
1997041700195	19970417	00195	NM  	1997	4	17	97ZZZX1601       	1	19961009	G	5330		SKIN            			BOEING	727   	727230      	1384080	NM  										BS 680 S26R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED AT SKIN BULGE FS 680 AT S26R.						2	L	7	3 	4F				A3WE    					 
1997041700196	19970417	00196	NM  	1997	4	17	97ZZZX1602       	1	19961009	G	5330		SKIN            			BOEING	727   	727230      	1384080	NM  										BS 340-350	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED AT SKIN BULGE EXTENDING FROM STA 340 TO STA 350 AT S26R.						2	L	7	3 	4F				A3WE    					 
1997041700197	19970417	00197	NM  	1997	4	17	97ZZZX1603       	1	19961009	G	5313		STRINGER        			BOEING	727   	727230      	1384080	NM  										BS 312 S22L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON S22L AT STA 312.						2	L	7	3 	4F				A3WE    					 
1997041700198	19970417	00198	NM  	1997	4	17	97ZZZX1604       	1	19961008	G	5330		SKIN            			BOEING	727   	727243      	138408D	NM  										BS 1130	DAMAGED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58414					22166				DURING C-CHECK INSPECTION, A LONG DENT AND CREASE WAS NOTED IN LT AFT AIRCRAFT SKIN AT FS 1130.						2	L	7	3 	4F			RT	A3WE    					 
1997041700199	19970417	00199	NM  	1997	4	17	97ZZZX1605       	1	19961008	G	5320		SHEAR TIE       			BOEING	727   	727243      	138408D	NM  										BS 950F	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58414					22166				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SHEAR TIE AT FRAME 950F AT S28R.						2	L	7	3 	4F			RT	A3WE    					 
1997041700200	19970417	00200	NM  	1997	4	17	97ZZZX1606       	1	19961008	G	5320		SUPPORT CHANNEL 			BOEING	727   	727243      	138408D	NM  										BS 1030 S30L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58414					22166				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON SUPPORT CHANNEL AT FS 1030 FROM S30 TO S29R.						2	L	7	3 	4F			RT	A3WE    					 
1997041700201	19970417	00201	NM  	1997	4	17	97ZZZX1607       	1	19961008	G	5315		FLOOR BEAM      			BOEING	727   	727243      	138408D	NM  										BS 344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58414					22166				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON UPPER CHORD OF CABIN FLOOR BEAM FS 344.						2	L	7	3 	4F			RT	A3WE    					 
1997041700202	19970417	00202	NM  	1997	4	17	97ZZZX1608       	1	19961009	G	5315		FLOOR BEAM      			BOEING	727   	727243      	138408D	NM  										BS 890 BL ZERO	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58414					22166				DURING C-CHECK INSPECTION, A CRACK WAS NOTED IN FLOOR BEAM UPPER CHORD AT FS 890, BL ZERO.						2	L	7	3 	4F			RT	A3WE    					 
1997041700203	19970417	00203	NM  	1997	4	17	97ZZZX1609       	1	19961009	G	5320		CAP             			BOEING	727   	727243      	138408D	NM  										B S 328 LBL 20	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58414					22166				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON UPPER CAP STA 328 AT LBL 20.						2	L	7	3 	4F			RT	A3WE    					 
1997010900805	19970109	00805	GL  	1997	1	9	97ZZZX161        	3	19961105	G	6110	13333	PROPELLER ASSY  			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		INSPECTION FOUND PROPELLER ASSY P/N 13333 CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1997041700204	19970417	00204	NM  	1997	4	17	97ZZZX1610       	1	19961008	G	5347		SEAT TRACK      			BOEING	727   	727243      	138408D	NM  										BS 45.5-344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58414					22166				DURING C-CHECK INSPECTION, CORROSION WAS NOTED ON 4 EACH CABIN SEAT TRACKS FROM FS 344 GTO FS 45.5 IN THE FOLLOWING BL L	OCATIONS:  LBL 45.5.  RBL 45.5.  LBL 24.75.  RBL 24.75.					2	L	7	3 	4F			RT	A3WE    					 
1997041700205	19970417	00205	SO  	1997	4	17	97ZZZX1611       	1	19960429	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	7    				348070013				LOSS OF AIRSPEED - TRACED TO OPEN PITOT HEAT ELEMENT.  REPLACED REAR ELEMENT 4-29-96.						1	L	7	2 	3O				A7SO    					 
1997041700206	19970417	00206	SO  	1997	4	17	97ZZZX1612       	1	19960402	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 4-2-96.						1	L	7	2 	3O				A7SO    					 
1997041700211	19970417	00211	EU  	1997	4	17	97ZZZX1617       	1	19961210	G	5311		FRAME           			AMD   	FALC50	FALCON50MYST	2730106	EU  										FS 34	RIVETS MISSING  	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1902W	2246 				209				WHILE ACCOMPLISHING SB F50-218, THREE RIVETS WERE FOUND MISSING AT FUSELAGE FRAME 34; LEFT SIDE ABOVE BAGGAGE DOOR.   RI	VETS APPEAR TO HAVE BEEN MISSING SINCE MANUFACTURE OF AIRCRAFT.					2	L	7	3 	4F				A46EU   					 
1997041700212	19970417	00212		1997	4	17	97ZZZX1618       	4	19961121	G	3455	G686201	CONTROL HEAD    			AMD   	FALC50	FALCON50MYST	2730106	EU  										DUAL ADF	SHORTED         	B			AMCR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	09	254DV				119	85				DURING COCKPIT PREFLIGHT, CREW HEARD ADF NR 1 CIRCUIT BREAKER TRIP.  WITHIN A FEW MOMENTS, THE ODOR OF SOMETHING BURNING	 WAS DETECTED.  REMOVING THE ADF HEAD, THE UNIT SMELLED BURNT.  THIS SAME S/N HEAD EXPERIENCED THE SAME THING A YEAR AND	 A HALF AGO, (545 FLT HRS).  PREVIIOUS REPAIR REPORT INDICATED A FAILED POWER SUPPLY BOARD, P/N 701-0314-01.				2	L	7	3 	4F				A46EU   					 
1997041700213	19970417	00213		1997	4	17	97ZZZX1619       	4	19960410	G	2210	6225029001	SERVO MOUNT     	COLLINS     	SMT85B      	BRAERO	DH125 	BAE125800A  	1500285	EU  										ELEV CONTROL	MALFUNCTION     	B		A	EBVR	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	09	410BT	1722 			2062	NA0468				PILOT NOTED THAT ON APPROACHES WITH THE AUTOPILOT DISENGAGED, THE ELEVATOR CONTROLS WOULD CATCH WHEN SLIGHT ADJUSTMENTS 	WERE MADE.  THE SMALL AMOUNT OF PRESSURE NEEDED TO BREAK IT LOOSE WOULD CAUSE THE AIRCRAFT TO PORPOISE A FEW TIMES.  SUS	PECT INTERNAL PROBLEMS IN THE SERVO MOUNT ASSY.				2	L	7	2 	4F			RT	A3EU    					 
1997010900806	19970109	00806	GL  	1997	1	9	97ZZZX162        	3	19961105	G	6110	13336	PROPELLER ASSY  			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		INSPECTION FOUND PROPELLER ASSY P/N 13336 CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1997041700218	19970417	00218	CE  	1997	4	17	97ZZZX1624       	1	19961209	G	3020	99120867	REGULATOR VALVE 			CESSNA	500   	560CESSNA   	2076750	CE  										ENG INLET LIP	FAILED          	B		A	EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	90MF				1062	5600060				DURING PHASE INSPECTION, THE RT ENGINE INLET WAS FOUND TO HAVE BULGE SPOTS AT LIP SEAM INSIDE THE INLET.  SEVERAL RIVETS	 HAD MISSING HEADS AROUND BULGE SPOTS AND SEVERAL MORE RIVETS HAD HEADS THAT WERE PARTIALLY PULLED OFF.  THE RT ENGINE I	NLET BLEED AIR REGULATING VALVE WAS FOUND TO HAVE FAILED AND NO LONGER WOULD PROPERLY REGULATE BLEED AIR TO THE INLET LI	P CAUSING THE DAMAGE.  REPLACEMENT OF ENTIRE INLET ASSEMBLY AND BLEED AIR VALVE WAS NECESSARY.			2	L	7	2 	4F			RT	A22CE   					 
1997010900807	19970109	00807	GL  	1997	1	9	97ZZZX163        	3	19961105	G	6110	J2016	PROPELLER ASSY  			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		INSPECTION FOUND PROPELLER ASSY P/N J2016 CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1997010900808	19970109	00808	GL  	1997	1	9	97ZZZX164        	3	19961105	G	6110	3496	PROPELLER ASSY  			STBROS	SD3   	SD360       	8100606	EU  						HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		15791	4474 					EV711		INSPECTION FOUND PROPELLER ASSY P/N 3496 CRACKED.						2	H	7	2 	4T				A41EU   		6	C	P44GL	 
1997010900809	19970109	00809	GL  	1997	1	9	97ZZZX165        	3	19961105	G	6110	3807	PROPELLER ASSY  													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		903  						DN374		INSPECTION FOUND PROPELLER ASSY P/N 3807 CORRODED.																5	C	P920	 
1997041700503	19970417	00503	SW  	1997	4	17	97ZZZX1655       	1	19961219	G	2460	1101461S	RELAY           			BELL  	230   	230         	1182149	SW  										ELECTRICAL SYST	INOPERABLE      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	604  				23019				INOPERABLE RELAY.						1	G	7	2 	3U			NC	H9SW    					 
1997041700505	19970417	00505	SW  	1997	4	17	97ZZZX1657       	1	19961025	G	6320	222375023111	INDICATOR       			BELL  	230   	230         	1182149	SW  										MGT GAUGE	READS HIGH      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	501  			9209110	23019				MGT READS 50 DEGREES CELSIUS HIGH ALL THE TIME.						1	G	7	2 	3U			NC	H9SW    					 
1997041700506	19970417	00506	SW  	1997	4	17	97ZZZX1658       	1	19960928	G	3340	7028511	STROBE          			BELL  	230   	230         	1182149	SW  										BEACON	TRIPS BREAKER   	B			TI1R	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	05	4UV				02514	23019				STROBE LIGHT TRIPS CIRCUIT BREAKER.						1	G	7	2 	3U			NC	H9SW    					 
1997010900810	19970109	00810	GL  	1997	1	9	97ZZZX166        	3	19961105	G	6110	3807	PROPELLER ASSY  													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		804  						DN942		INSPECTION FOUND PROPELLER ASSY P/N 3807 CORRODED.																5	C	P920	 
1997010900811	19970109	00811	GL  	1997	1	9	97ZZZX167        	3	19961105	G	6110	3807	PROPELLER ASSY  													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			635  					AU7576		INSPECTION FOUND PROPELLER ASSY P/N 3807 CORRODED.																5	C	P920	 
1997010900812	19970109	00812	GL  	1997	1	9	97ZZZX168        	3	19961105	G	6110	3807	PROPELLER ASSY  													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		616  						DN1712		INSPECTION FOUND PROPELLER ASSY 3807 CORRODED.																5	C	P920	 
1997041700564	19970417	00564	EU  	1997	4	17	97ZZZX1681       	1	19961205	G	6240	350A08386100	WARN HORN       			SNIAS 	350   	AS350B2     	8680813	EU  										ROTOR RPM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	4055L					2916				THERE ARE 2 TYPES OF WARNING HORNS.  ONE MANUFACTURER IS KLAXON, THE OTHER IS VOXBELL.  BOTH OF THE HORNS ARE FAILING DU	E TO POOR WORKMANSHIP.  ITEMS CAUSING FAILURE ARE POOR SOLDERING POINTS AND RIVETS NOT FULLY SQUEEZED WHICH SHOULD MAKE 	CONTACT TO ACTIVATE THE HORN WHEN ROTOR RPM FALLS BELOW MINIMUM.  HAVE HAD TO ORDER 4 HORNS IN SIXTY-DAY PERIOD.				1	G	7	1 	3U				H9EU    					 
1997010900813	19970109	00813	GL  	1997	1	9	97ZZZX169        	3	19961105	G	6110	3807	PROPELLER ASSY  													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			843  					D1961		INSPECTION FOUND PROPELLER ASSY P/N 3807 CORRODED.																5	C	P920	 
1997042400005	19970424	00005	CE  	1997	4	24	97ZZZX1694       	1	19961027	G	3213	NAS464322	BOLT            			CESSNA	150   	150         	2071802	CE  										NLG TORQ LINK	DETACHED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06										BOLT CAME OUT OF JUNCTURE OF UPPER AND LOWER TORQUE LINK ASSY ON NOSE GEAR ALLOWING NOSEWHEEL TO TURN 90 DEGREES RIGHT O	F CENTER AND COLLAPSE.  SUBMITTER SUGGESTED TO SPECIAL CHECK THIS BOLT AS PART OF PILOT'S PRE-FLIGHT INSPECTION.					1	H	7	1 	3O			NT	3A19    					 
1997010900110	19970109	00110	SO  	1997	1	9	97ZZZX17         	1	19961205	G	5522	722404	ELEVATOR        			PIPER 	PA42  	PA421000    	7104225	SO  										CTWT CHANNEL	CRACKED         	B		A	FEHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	124DP					425527018				AFTER PAINT WAS CHEMICALLY REMOVED, 3 CRACKS WERE FOUND IN THE SKIN AT THE COUNTERWEIGHT CHANNEL RUNNING AFT.  2 MORE CR	ACKS WERE FOUND IN THE STRINGER AFT OF THAT CHANNEL.  LOOKING THROUGH THE ACCESS PANEL, IT WAS ALSO FOUND THAT THE STRIN	GER WAS BROKEN.				1	L	7	2 	4T			RT	A23SO   					 
1997010900814	19970109	00814	EA  	1997	1	9	97ZZZX170        	2	19961218	G	8530	SL134441	PISTON PIN      			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					CYL NR 1	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							L1817348A			INVEST OF TOO MUCH PISTON TO PIN CLEARANCE REVEALED A PISTON PIN BROKEN IN TWO IN THE MIDDLE.  IT WAS THE NR SL13444-1 P	IN MFG BY CARL BRUCHNER IN GERMANY, IDENTIFIED BY 'CB-3' ON ONE END.  INSTALLED IN CYL NR 1.  IT HAD DAMAGED THE CONNECT	ING ROD AND PISTON.  THE PINS (P/N SL13444-1) WERE REPLACED AT AT OVERHAUL 2 YEARS AND 200 HOURS PREVIOUSLY AS NEW PARTS	 IN ALL 6 CYLS.  SUPERIOR AIR PARTS, INC., HAS BEEN NOTIFIED OF THIS CONDITION.  IT SHOULD BE NOTED THAT PINS SPECIFICAL	LY SUPERIOR NR SA629690, MFG BY THE SAME COMPANY (CARL BRUCHNER), WERE THE SUBJECT OF A RECALL, REF:  SUPERIOR MANDATORY	 SB NR 96-001, 8-5-96.	1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1997010900815	19970109	00815	SO  	1997	1	9	97ZZZX171        	1	19961218	G	3230	76426	LINK ASSY       			PIPER 	PA28  	PA28R201    	7102816	SO  										NLG	CRACKED         	B		A	UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	11562					28R7837194				FOUND THE LINK ASSY CRACKED IN THE RADIUS JUST FWD OF THE ATTACH POINT FOR THE DOWNLOCK ASSY.  THIS IS ONE OF THE AREAS 	THAT NEEDS TO BE CHECKED PER SB 724A (AD 82-06-11R1), PART II, ITEM NR 3, SKETCH 3.  THIS IS A ONE-TIME INSPECTION THAT 	HAD BEEN DONE PRIOR TO THIS PART CRACKING.  SUBMITTER SUGGESTS MAKING IT A RECURRING AD EVERY 100 HOURS OR BY PARTS REPL	ACEMENT.  THE NEW LINK AND BRACE ASSEMBLY PN 76426-803 IS A MUCH BETTER PART.  PIPER HAS ADDED A SUBSTANTIAL AMOUNT OF M	ATERIAL TO THE ABOVE MENTIONED AREA.		1	L	7	1 	3O				2A13    					 
1997010900816	19970109	00816	CE  	1997	1	9	97ZZZX172        	1	19961216	G	2710	0422162	BELLCRANK       			CESSNA	140   	140         	2071602	CE  										RT AILERON	WRONG PART      	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	1772V					13907				DURING RIGGING CHECK AT ANNUAL INSPECTION FOUND THAT AILERONS COULD NOT REACH FULL TRAVEL UP OR DOWN.  THE LT AILERON TR	AVEL 21 DEGREES UP AND 11 DEGREES DOWN AND THE RT AILERON TRAVEL ONLY 13 DEGREES UP AND 18 DEGREES DOWN.  INV. FOUND INC	ORRECT BELLCRANK INSTALLED ON RT WING AILERON.				1	H	7	1 	3O			NC	A768    					 
1997010900817	19970109	00817	CE  	1997	1	9	97ZZZX173        	1	19961001	G	2710	AN410A	BOLT            			CESSNA	177   	177A        	2073706	CE  										LT AIL HORN	FELL OUT        	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	30567					17701332				DURING AN ANNUAL INSPECTION IT WAS FOUND THAT THE AN 4-10A BOLT CONNECTING THE PUSH/PULL ROD TO THE LEFT AILERON HORN HA	D BACKED OUT TO THE POINT THAT BY MOVING THE AILERON BY HAND, THE BOLT FELL OUT COMPLETELY.  THE BOLT WAS NOT SAFTIED. F	URTHER INSPECTION OF THE RIGHT AILERON FOUND THAT THE BOLT WAS LOOSE AND WAS ALSO AN 4-10A AND NOT SAFETIED.  BOTH AN 4-	10A BOLTS WERE REPLACED WITH AN 4H-10A AND PROPERLY SAFETIED.			1	H	7	1 	3O				A13CE   					 
1997010900818	19970109	00818	CE  	1997	1	9	97ZZZX174        	1	19961201	G	5320	07106082	ANGLE           			CESSNA	182   	182E        	2072712	CE  										BULKHEAD	RUSTED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	69EL					18254060				INSPECTION OF LDG GEARBOX BULKHEAD LOWER AFT SIDE, FOUND ANGLES RUSTED COMPLETELY THROUGH IN SEVERAL LOCATIONS ON FLANGE	S.  SUBMITTER SUGGESTED CAUSE IS DUE TO TRAPPED DIRT AND WATER AND INADEQUATE DRAIN HOLES OR LOCATION.					1	H	7	1 	3O			NT	3A13    					 
1997042400283	19970424	00283	NM  	1997	4	24	97ZZZX1740       	1	19961106	G	5280	65216361	DOOR SPAR       			BOEING	727   	727251      	138408H	NM  										MLG	CRACKED         	B			EG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25					800716					DURING REPAIR OF MLG DOOR, FOUND CRACKS IN REAR SPAR ON 2 UNITS.  CRACKS ARE AT LOCATION WHERE THE UP-STOP ATTACHES TO D	OOR.  BOEING HAS BEEN ASKED FOR REPAIR.					2	L	7	3 	4F				A3WE    					 
1997010900819	19970109	00819	EA  	1997	1	9	97ZZZX175        	2	19961219	G	8520		LIFTER          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					INTAKE	SPALLED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	73462					17267479	RL5028827A			FERROUS METAL FOUND IN OIL SCREEN AT INSPECTION.  AFTER FURTHER INVESTIGATION, FOUND ALL 4 INTAKE LIFTER BODIES SEVERELY	 SPALLED AND THE 2 CAM LOBES THAT OPERATE THEM WORN.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997010900820	19970109	00820	CE  	1997	1	9	97ZZZX176        	1	19961226	G	2720	04115264	BAR ASSY        			CESSNA	150   	152         	2071835	CE  										RT RUD PEDAL	BROKEN          	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	89955	8923 				15282926				PILOT REPORTED THAT DURING RUN-UP PRIOR TO FLIGHT, RIGHT RUDDER PEDAL WOULD NOT MOVE RUDDER SURFACE.  INSPECTION REVEALE	D A WELD IN RUDDER BAR ASSY HAD BROKEN AT THE ARM WHICH CONNECTS IT TO THE RUDDER PEDAL (PILOT'S RIGHT RUDDER).  CAUSE O	F BREAK:  SUSPECTED METAL FATIGUE OF WELD AREA.  FAILURE IS EXACTLY AS SHOWN IN ALERT NR 215 DATED JUNE 1996, PAGE 7, AC	 NR 73-16.			1	H	7	1 	3O			NT	3A19    					 
1997010900821	19970109	00821	EA  	1997	1	9	97ZZZX177        	2	19961231	G	7314	LW15473	PUMP            			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENG FUEL	MALFUNCTION     	B			ESMR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	9185P	427  				2837032	L2507551A			FUEL PUMP MALFUNCTION.  TWO SMALL PIECES OF A BUSHING ON THE TIP OF THE PLUNGER ASSEMBLY BROKE OFF AND WERE FOUND IN THE	 SUCTION SCREEN.  DATE CODE ON THE PUMP REVEALED MANUFACTURE WAS IN 1994.					1	L	7	1 	3O	3	O		2A13    	1E10				 
1997010900823	19970109	00823	CE  	1997	1	9	97ZZZX179        	1	19961205	G	2720	15371	PEDAL           			BBAVIA	8     	8KCAB       	2110612	CE  										RUD LT FWD	FAILED          	G	P	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	5061K					56079				THE OPERATOR REPORTS A THIRD FAILURE OF THE LEFT FORWARD RUDDER PEDAL AT THE LOWER LEFT HAND CORNER AT 65 HOURS TIMES IN	 SERVICE.  THIS FIRST AND S ECOND FAILURE OCCURRED AT 147 AND 86 HOURS RESPECTIVELY.  PART TOTAL TIME AVERAGE = 93 HOURS	.				1	H	7	1 	3O				A21CE   					 
1997010900111	19970109	00111	SO  	1997	1	9	97ZZZX18         	1	19961212	G	2810	6399816	TANK            			PIPER 	PA28  	PA28140     	7102802	SO  										LT FUEL	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	15488	3017 				287325078				UPON REMOVAL OF THE LT WING FUEL TANK FOR REPLACEMENT OF FUEL VENT HOSES, CORROSION WAS NOTED AT THE OUTBOARD SIDE FALSE	 RIB (NOSE RIB) SECTION OF THE FUEL TANK.  THE CORROSION WAS BLISTERED.  AFTER PROBING WITH THE POINT OF A METAL SCRIBE,	 IT WAS FOUND THE METAL COULD BE PENETRATED WITH LIGHT HAND PRESSURE.  THERE WAS NO EVIDENCE OF FUEL LEAKAGE.				1	L	7	1 	3O				2A13    					 
1997010900824	19970109	00824	SO  	1997	1	9	97ZZZX180        	1	19961205	G	5320	6797202	STIFFENER       		76436000    	PIPER 	PA28  	PA28R201    	7102816	SO  										NLG WELL	MISSING         	B			UC2R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	19	40024	2472 				28R7737128				THE PILOT REPORT NO DWN AND LK IND FOR THE NLG.  THE ACFT INTO THE SHOP FOR AN INSP OF THE NLG TO ID DIFFICULTY.  FOUND 	THAT THE STRUCT ABOVE THE NLG ACT ATTACH BRKT; PN 67271-800 WAS PUSHED UP APPROX .25 INCH AND IT BUCKLED THE WELL ASSY I	N SUCH A WAY THAT IT ALLOWED THE DWN AND LK SW TO  NOT MAKE CONTACT.  THE SUSPECT CAUSE OF THE DAMAGE IS THE COMBINATION	 OF THE PRESSURE EXERTED BY THE NLG ACT IN THE UP POSIT AND LACK OF ADEQUATE STRUCTURE IN THAT AREA.  THIS ACT ATTACH AL	SO DOUBLES AS THE FWD JACK POINT AND COULD HAVE BEEN WEAKENED BY REPEATED USE.  UPON FURTHER INVEST, IT WAS FOUND THAT A	 STIFFENER WAS MISSING FROM WELL ASSEMBLY; PN 76436-000, AS PER FIG 8, ITEM 47, PG 1B15 OF THE PTS MAN.	1	L	7	1 	3O				2A13    					 
1997010900825	19970109	00825	SO  	1997	1	9	97ZZZX181        	2	19961226	G	8520	6436511	STUD            								CONT  	O360  	TSIO360EB   	17025	SO  					CYL HOLD DOWN	STRETCH         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		1762 					265972R			DURING THE COURSE OF A NORMAL ENG OVERHAUL, IT WAS FOUND THAT ABOUT ONE-THIRD OF THE CYL DECK STUDS WOULD NOT HOLD SPECI	FIED TORQUE WITHOUT STRETCHING.  THE STUDS ARE A NEWER 'NECKED DOWN' DESIGN.  THE MECH REPLACED ALL CYL DECK STUDS WITH 	AN OLDER STRAIGHT DESIGN AND TORQUED THEM TO SPEC.  IT IS CRITICAL THAT THESE STUDS HOLD TORQUE.  SUBMITTER STATED IT IS	 LIKELY THAT THE REASON THAT THE STUDS WOULD NOT HOLD TORQUE IS THAT THEY WERE NOT MFG WITH THE CORRECT HARDNESS.  RECOM	MENDED THAT ALL CYL DECK STUDS BE CHECKED AT THE SPECIFIED TORQUE BEFORE FINAL ASSEMBLY AT OVERHAUL OR AT A CYLINDER CHA	NGE.						3	O			E9CE				 
1997010900826	19970109	00826	EA  	1997	1	9	97ZZZX182        	2	19960904	G	7414	103828204	HOUSING         			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ENG MAG	BROKEN          	B		A	OF1R	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	25	8186G					32R8029079	L699361A			AIRCRAFT TACK TIME 2951.81.  ENG FAILURE RESULTED IN OFF AIRPORT LANDING CAUSING DAMAGE TO AIRCRAFT OF UNREPAIRABLE AMOU	NT.  FAILURE CAUSED BY DUAL MAGNETO FALLING OFF OF ACCESSORY CASE AND DRIVE GEAR DISENGAGING FROM ENG.  EXAM SHOWS LOWER	 MAG HOLD DOWN STUD INTACT BUT NUT, WASHER, LOCKWASHER, AND HOLD DOWN CLIP MISSING.  UPPER MAG HOLD DOWN STUD INTACT WIT	H NUT, WASHER, LOCKWASHER, AND CLIP INSTALLED BUT SIGNIFICANT SECTION OF MAG HOUSING HOLD DOWN FLANGE BROKEN OFF.			1	L	7	1 	3O	3	O		A3SO    	E14EA				 
1997010900827	19970109	00827	SO  	1997	1	9	97ZZZX183        	2	19961202	G	7322	MA3SPA	CARBURETOR      	FACET       		CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					FLOAT BOWL	MALFUNCTION     	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	09	16125		2493 			15073494	20559270A			PILOT REPORTS TWO OR THREE HARD JOLTS FROM TURBULENCE WITH NEG G-FORCE.  THE ENGINE WENT TO NEAR IDLE POWER.  DISASSEMBL	Y OF THE CARB REVEALED THE PRESENCE OF A SILT CLOD IN MAIN JET.  SUBMITTER RECOMMENDS PERIODIC CLEANING OF FLOAT BOWL TO	 REMOVE BUILD UP OF SILT.  DRAINING OF THE BOWL DOES NOT REMOVE BUILD UP.				1	H	7	1 	3O	3	O		3A19    	E252				 
1997010900829	19970109	00829	EA  	1997	1	9	97ZZZX184        	2	19961202	G	7322	MA4SPA	CARBURETOR TUBE 	FACET       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ACCEL PUMP	LOOSE           	B			NE2R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CE	07	21428	1886 			CK611417	28796039	L851839A			IN FLIGHT, RPM WOULD NOT DECREASE BELOW 2000 RPM.  INVESTIGATION FOUND ACCELERATOR PUMP NOZZLE DISLODGED AND LYING IN AI	R BOX.  CARBURETOR SENT TO REPAIR STA. FOR OVERHAUL.  SUSPECT NOZZLE ADHESIVE BROKEN LOOSE WHEN SINGLE PIECE VENTURI WAS	 INSTALLED AT 1865 HRS.  LANDING WAS SAFE.  NO DAMAGE ENGINE KILLED ON FINAL, WITH MIXUTRE CONTROL.				1	L	7	1 	3O	3	O		2A13    	E274				 
1997010900830	19970109	00830	SW  	1997	1	9	97ZZZX185        	1	19961003	G	5320	340117119	TUBE            			MOONEY	M20   	M20E        	5870212	SW  										LT CABIN FRAME	SPLIT           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	333WS	4200 				323				DURING ANNUAL INSPECTION, FOUND CABIN STRUCTURAL TUBE NR 340117-119 LT HAD FILLED WITH WATER, FROZEN AND SPLIT OPEN.  RE	PAIRED IAW 43.13-1A.  INSPECTED AND SEALED STRUCTURES IAW M20-208B.					1	L	7	1 	3O				2A3     					 
1997010900833	19970109	00833	CE  	1997	1	9	97ZZZX188        	1	19961219	G	2140		RESISTOR        	JANITROL    		BEECH 	60    	B60         	1153605	CE  										HEATER CKT	FAILED          	D		A		H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	13	4646M				B3040	P464				PILOT REPORTED CABIN HEATER INOPERATIVE AND HAD SMELLED SMOKE IN CABIN.  FOUND CABIN VENTILATION BLOWER INOPERATIVE WHIC	H CAUSED OVERTEMP CONDITION.  WHEN OVERTEMP SWITCH TRIPPED, RATHER THAN OPENING HEAT FUSE (5 AMP), 10 WATT, 3 OHM RESIST	OR BURNED AND OPENED.  THIS RESISTOR BEING OPEN PROHIBITS NORMAL FUNCTION OF OVERTEMP PROTECTION CIRCUIT.  HEATER WAS SH	UT DOWN BY PILOT WITH NO FURTHER DAMAGE.  APPARENTLY THIS RESISTOR BURNED BEFORE FUSES OPENED.  EXPERIENCED IDENTICAL PR	OBLEM ON 9B655 BARON, BUT DUCT WORK WAS DAMAGED THROUGHOUT AIRCRAFT.		1	L	7	2 	3O				A12CE   					 
1997010900834	19970109	00834		1997	1	9	97ZZZX189        	4	19961211	G	3120	587961	TRANSDUCER      			PIPER 	PA28  	PA28R200    	7102811	SO  										HOBBS METER	LEAK            	C				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SO	15	55177					7335190				ON TAXI OUT PILOT FELT LIQUID ON HIS LEFT FOOT.  HE LOOKED AT HIS FOOT AND FOUND IT COVERED WITH ENGINE OIL.  HE SHUT DO	WN THE ENGINE AND DISCOVERED SOURCE OF OIL TO BE THE HOBB'S TRANSDUCER.  ABOUT THREE-FOURTHS OF A QUART OF OIL WAS SPILL	ED ON PILOT'S FOOT IN CABIN.				1	L	7	1 	3O				2A13    					 
1997010900112	19970109	00112	SO  	1997	1	9	97ZZZX19         	1	19961212	G	2810	63913194	HOSE            	DEUTSCH     		PIPER 	PA28  	PA28140     	7102802	SO  										FUEL VENT	DRY ROT         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	15488	3017 				287325078				FUEL VENT HOSES AND FUEL SUPPLY HOSES AT FUEL TANK OUTLET FOUND WITH DRY-ROT, HARD AND BRITTLE.  DATE CODE ON FUEL SUPPL	Y HOSES, 1972.  NO SIGN OF FUEL LEAKS.					1	L	7	1 	3O				2A13    					 
1997010900835	19970109	00835	NE  	1997	1	9	97ZZZX190        	2	19961003	G	8520	72877	LIFTER          		LW19340     	MAULE 	M5    	M5235C      	5460135	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					CAMSHAFT	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	5643N		383  			A7361C	L2120448A			DURING ANNUAL INSPECTION FOUND STEEL IN OIL FILTER.  ENGINE DISASSEMBLED, ALL LIFTERS AND CAMSHAFT BADLY SPALLED.  THESE	 COMPONENTS HAD A TT OF 383 HRS SINCE REGRIND AND AEROLUBE PROVIDED BY AIR SUPPORT INTERNATIONAL.					1	H	7	1 	3O	3	O		3A23    	1E4				 
1997010900837	19970109	00837	CE  	1997	1	9	97ZZZX192        	1	19961216	G	2130	99100181	AIR FILTER      		511725811   	CESSNA	421   	421C        	2076016	CE  										HEAT EXCHANGE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	88604	3147 				421C0604				CABIN PRESSURIZATION WEAK, INSPECTED PRESSURIZATION HEAT EXCHANGER IN WING.  BOTH EXCHANGERS PLUGGED WITH FELT MATERIAL.	  SUSPECT FELT MATERIAL CAME FROM ENDS OF PAPER AIR FILTERS.  VACUUM AND CLEANED HEAT EXCHANGERS, TEST FLIGHT CHECK, AND	 NORMAL.				1	L	7	2 	3O				A7CE    					 
1997010900838	19970109	00838	CE  	1997	1	9	97ZZZX193        	1	19961101	G	3211	24411009	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										RT MLG LEG	SHEARED         	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	15	95208	1612 				172RG0851				SPLINE PORTION OF PIVOT ASSY SHEARED DURING NORMAL OPERATIONAL USE.  RIGHT MAIN GEAR LEG WOULD NOT LOCK DOWN.  PILOT DID	 A GREAT JOB OF MINIMIZING DAMAGE TO A/C.  RECOMMEND FLUORESCENT PENETRANT INSPECT DURING ANNUAL INSPECTION OF SPLINE SH	AFT WHERE IT MEETS THE REST OF THE PIVOT ASSY.				1	H	7	1 	3O				3A17    					 
1997050800009	19970508	00009	CE  	1997	5	8	97ZZZX1931       	1	19961216	G	3234	2MD31AX287	SWITCH          		A4503M95    	BEECH 	100   	B100        	1152919	CE  										GEAR MOTOR CONT	STUCK CLOSED    	H	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	500KD	7971 				BE79				MECHANICS WERE WORKING ON LANDING GEAR DOWNLOCK (J-HOOK) SOLENOID.   THEY WERE CHECKING  OPERATION OF THE SOLENOID BY AC	TIVATING THE RIGHT SQUAT SWITCH.  ACFT WAS NOT ON JACKS AT THAT POINT.  GEAR HANDLE WAS VERIFIED IN  DOWN POSITION PRIOR	 TO ACTIVATION OF THE SQUAT SWITCH.  AS MECHANICS ACTIVATED SQUAT SWITCH, GEAR MOTOR STARTED TO RUN IN THE RETRACT DIREC	TION.  LANDING GEAR MOVED ENOUGH TO BREAK OVER CENTER POSITION ON BOTH MAIN GEARS AND ACFT COLLAPSED ONTO THE FLOOR.  NL	G ACTIVATED OVER CENTER, BUT NOT ENOUGH TO CAUSE GEAR TO COLLAPSE.  MAJOR LANDING GEAR DAMAGE, ENGINE WHEELWELL NACELLE 	DAMAGE, FLAP DAMAGE, HORIZ STAB DAMAGE FROM COLLAPSING ONTO THE NOSE OF ANOTHER ACFT, BUT NO ENGINE DAMAGE.	1	L	7	2 	4T				A14CE   					 
1997010900839	19970109	00839	CE  	1997	1	9	97ZZZX194        	1	19961228	G	2436	DGR6	REGULATOR       			CESSNA	182   	182P        	2075816	CE  										DC SYS	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	9970E	64   			2374	18264030				INSTALLED OVERHAULED ALTERNATOR AND NEW VOLT REGULATOR AT 769 TTSN.  AT 833 HRS REGULATOR FAILED.  INSTALLED THE OLD ORI	GINAL REGULATOR AND SYSTEM FUNCTIONS PROPERLY.  SUBMITTER SUGGESTS RECALL ALL PFT, INC. REGULATORS IN SAME BATCH FOR CON	FORMITY INSPECTION AND TEST.				1	H	7	1 	3O			NT	TA13    					 
1997010900840	19970109	00840	CE  	1997	1	9	97ZZZX195        	1	19961003	G	2821		GASCOLATOR      			BBAVIA	11    	11BC        	0191106	CE  										FUEL FILTER	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	27	9502E					11AC1137				WHILE INSPECTING A/C FOR FERRY FLIGHT FUEL WAS FOUND DRIPPING FROM GASCOLATOR.  GASCOLATOR BOWL WAS NOT PROPERLY SEATED 	ON GASKET AND BAIL NUT WAS NOT SAFTIED.  AD 47-20-01 HAD BEEN C/W 4 HRS PRIOR BY REPAIR STATION DVOR3450.					1	H	7	1 	3O				A761    					 
1997010900841	19970109	00841	EU  	1997	1	9	97ZZZX196        	1	19961129	G	3242	50028053	BRAKE ASSY      			ISRAEL	1124  	1124        	4500102	EU  										LT MLG	DISK BROKEN     	B			VT2R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	09	72787	84   			MAY86539	240				LEFT HAND BRAKE ASSEMBLY FAILED UPON LANDING.  SUBSEQUENT INVESTIGATION DISCLOSED A BROKEN STATIONARY DISK ASSEMBLY.  A 	TWO INCH SECTION OF THE DISK ASSEMBLY WAS SEPARATED.  NOTIFIED AIRCRAFT BRAKING SYSTEMS.  THE BRAKE ASSEMBLY WAS SHIPPED	 TO ABS FOR EVALUATION.  LNDS:  72.  PART TSN:  84.3 HRS.				2	M	7	2 	4F				A2SW    					 
1997010900843	19970109	00843		1997	1	9	97ZZZX198        	4	19961210	G	2562	ELT910	ELT             	NARCO       		BELL  	204   	204B        	1181404	SW  										ACFT	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	204SH		500  		13406	2019				FAA REPORTED ELT SIGNALS IN AREA; CHIEF PILOT CHECK ALL 4 OF OUR AIRCRAFT AND CHECKED THAT ALL SWITCHES WERE IN 'OFF' PO	SITION.  FAA CAME OUT AND DETERMINED THAT THIS ELT WAS OPERATING AND THAT THE SWITCH WAS 'OFF'.  REMOVED ELT FROM AIRCRA	FT AND REMOVED BATTERY TO STOP ELT SIGNAL.				1	G	7	1 	4U				H1SW    					 
1997010900844	19970109	00844	SW  	1997	1	9	97ZZZX199        	1	19961212	G	6320	70061F3352080A	HOSE            			BELL  	206   	206L1       	1182107	SW  										FREEWHEEL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	09	5748H					45490				TRANSMISSION TO FREEWHEELING UNIT HOSE WAS SEEPING AT MIDDLE OF LINE DUE TO DEFECT.  HOSE WAS REPLACED WITH SERVICEABLE 	HOSE.					1	G	7	1 	3U				H2SW    					 
1997010900095	19970109	00095		1997	1	9	97ZZZX2          	1	19961114	G	2434	ALU23	SPACER          	ELECTROSYS  	ALT9422     															ALTERNATOR	MISMANUFACTURED 	B			KC2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03					4082087					THIS ALTERNATOR IS AN ELETROSYSTEMS NEW UNIT.  THE O-RING GROOVE WAS MACHINED INCORRECTLY ON THE ALU-23 SPACER ALLOWING 	ENGINE OIL TO LEAK PAST THE XA-744AZ O-RING AND CONTAMINATING THE X-4087 DRIVE END BEARING.  THIS ALTERNATOR WAS REMOVED	 FOR A 500-HOUR BEARING INSPECTION WHEN THIS DEFECT WAS FOUND.																	 
1997010900113	19970109	00113	SO  	1997	1	9	97ZZZX20         	1	19961212	G	2810	63913193	HOSE            	DEUTSCH     		PIPER 	PA28  	PA28140     	7102802	SO  										FUEL VENT	DRY ROT         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	15488	3017 				287325078				FUEL VENT HOSES AND FUEL SUPPLY HOSES AT FUEL TANK OUTLET FOUND WITH DRY-ROT, HARD AND BRITTLE.  DATE CODE ON FUEL SUPPL	Y HOSES, 1972.  NO SIGN OF FUEL LEAKS.					1	L	7	1 	3O				2A13    					 
1997010900845	19970109	00845	WP  	1997	1	9	97ZZZX200        	1	19961129	G	6420	369H1801	SWASHPLATE      			HUGHES	369   	369HS       	4470728	WP  										T/R HEAD	BUSHING DETACHED	D				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	99	9244F					350722S				VIBRATION FELT THROUGH T/R PEDALS, SPECIFICALLY LEFT PEDALS.  UPON INSPECTION, BUSHING AT INBOARD END OF T/R SWASHPLATE 	T-HEAD HAD COME OUT, SLID INBOARD ON T/R OUTPUT SHAFT AND DAMAGED T/R OUTPUT SHAFT SEAL.					1	G	7	1 	3U				H3WE    					 
1997010900846	19970109	00846	SW  	1997	1	9	97ZZZX201        	1	19961216	G	2913	01434430001	PUMP            			BELL  	206   	206B        	1181511	SW  										HYD SYS	SEAL LEAK       	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	09	108FH	3348 			05228	2770				HYDRAULIC PUMP LEAKING STATICALLY AT INPUT SEAL.  TBO TIME IS 3600 HRS ON THIS COMPONENT.  REPLACED WITH SERVICEABLE UNI	T.					1	G	7	1 	3U				H2SW    					 
1997010900847	19970109	00847	GL  	1997	1	9	97ZZZX202        	2	19961213	G	7230	23057142	CASE HALF       			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMP	CRACKED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		656  		14830	1151D	CAE832750			DURING ANNUAL INSPECTION THE ENG COMPRESSOR CASE HALVES WERE INSPECTED AND FOUND TO BE CRACKED AND LIFTING.  REPLACED CA	SE HALVES.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997010900848	19970109	00848	GL  	1997	1	9	97ZZZX203        	2	19961218	G	7210	23034787	BEARING         		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENG GEARBOX	SPALLED         	B			EOOR	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			AL	03	5074R	3859 				1151D	CAE832750			PILOT HAD JUST RUN THE ENGINE UP TO FLIGHT IDLE IN PREPARATION FOR TAKEOFF WHEN THE ENGINE CHIP LIGHT ILLUMINATED.  A LA	RGE CHIP .0937 INCH BY .0625 INCH WAS FOUND ON THE UPPER CHIP PLUG AND SUBSEQUENT INSPECTION FOUND 2 ROLLERS WITH DEEPLY	 SPALLED AREAS ON THE WORKING SURFACES.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997010900849	19970109	00849	WP  	1997	1	9	97ZZZX204        	1	19961209	G	6320	369D2516421	NOZZLE          		369D25100505	HUGHES	369   	369D        	4470706	WP  										XMSN OIL	BENT            	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	8534 	2433 		1260044	1151D				DURING OVERHAUL OIL NOZZLE WAS FOUND BENT - PART WAS REPLACED.						1	G	7	1 	3U				H3WE    					 
1997010900850	19970109	00850	NE  	1997	1	9	97ZZZX205        	1	19961213	G	6320	7635109002050	HOUSING         			SKRSKY	S76   	S76B        	8143007	NE  										M/R GEARBOX	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	76RP	2337 			C00100027	760349				WHILE PERFORMING 150 HR INSPECTION A CRACK WAS FOUND ON THE UPPER HOUSING AFT RIGHT FOOT OF THE MAIN GEARBOX.  (UPPER HO	USING TT 2336.7).  REPLACED MAIN GEARBOX ASSEMBLY WITH A SERVICEABLE GEARBOX IAW SIKORSKY MM.  A/C TT 3091.8 HRS.  GRBOX	 P/N 76351-09600-042.				1	G	7	2 	4U				H1NE    					 
1997010900851	19970109	00851	GL  	1997	1	9	97ZZZX206        	2	19961211	G	7310	70009H75W204	HOSE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C18      	03011	GL  					FUEL PUMP	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	09	7929J					663				ENGINE DRIVEN FUEL PUMP INLET LINE LEAKING AT FLARE FITTING DUE TO A CRACK.  REPLACED WITH SERVICEABLE LINE.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997010900852	19970109	00852	SW  	1997	1	9	97ZZZX207        	1	19961205	G	6210	206010154003	WASHER          			BELL  	206   	206B        	1181511	SW  										M/R BLADE BOLT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	18FH					2599				DURING A WEEKLY INSPECTION THE M/R BLADE BOLT LOWER WASHER WAS FOUND CRACKED.  REMOVED WASHER.  INSTALLED SERVICEABLE WA	SHER.  ACFT TT 8079.6.					1	G	7	1 	3U				H2SW    					 
1997010900853	19970109	00853		1997	1	9	97ZZZX208        	4	19961216	G	3457	TNL2000T	GPS             			BELL  	206   	206B        	1181511	SW  										COCKPIT	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	108FH	102  			6153477	2770				GPS CONTINUALLY DUMPS ALL INFORMATION WITHOUT WARNING AND DISPLAYS A FAILURE CODE.  NR 08.  REPLACED WITH SERVICEABLE UN	IT.					1	G	7	1 	3U				H2SW    					 
1997010900854	19970109	00854	EA  	1997	1	9	97ZZZX209        	2	19961216	G	8530	05K21124	GUIDE           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 3 CYL EXH	WORN            	B			MQ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	8666F	174  				970634	L864751A			FOUND LOW COMPRESSION (30/80) DURING NORMAL MAINT INSPECTION.  REMOVED CYL AND FOUND .009 INCH WEAR AT PORT END OF EX GU	IDE AND .002 INCH WEAR ON VALVE STEM.  THIS WAS A LYCOMING FACTORY NEW CYL KIT INSTALLED DURING RECENT MAJOR OVERHAUL.					1	G	7	1 	3O	3	O		4H12    	1E10				 
1997010900114	19970109	00114	SO  	1997	1	9	97ZZZX21         	1	19961112	G	2740	1604000	BEARING BLOCK   			PIPER 	PA23  	PA23250     	7102308	SO  										STAB	WORN            	D				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		DE	DESCENT        	1			GL	17	22TD					277854103				STABILATOR VIBRATION, FLUTTER IN DESCENT (AT HIGH SPEED) TRACED TO MOVEMENT IN ABOVE PIVOT JOINT.  HOLE IN BLOCK, BUSHIN	G, AND BOLT ALL SEVERELY WORN.  PLAY IN JOINT NOT IMMEDIATELY EVIDENT BECAUSE OF SPRING LOADING ON BELLCRANK.  RT SIDE N	OT WORN.  WEAR ALLOWS TAB TO MOVE AND FLUTTER, INDUCING MOVEMENT IN STAB.				1	L	7	2 	3O				1A10    					 
1997010900855	19970109	00855	WP  	1997	1	9	97ZZZX210        	1	19961209	G	3213	369H60024	STRUT           		369H600152  	HUGHES	369   	369D        	4470706	WP  										RT AFT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	58267					390473D				DURING POST-FLIGHT INSPECTION, A CRACK WAS DETECTED EMANATING FROM THE BRACE LOWER ATTACH HOLE EXTENDING 3 INCHES UPWARD	 TOWARD THE DAMPER ATTACH POINT.  RECOMMEND REMOVING BRACE FROM STRUT AND INSPECTING BOLT HOLES EVERY 100 HRS.					1	G	7	1 	3U				H3WE    					 
1997010900856	19970109	00856	CE  	1997	1	9	97ZZZX211        	1	19960814	G	3211	24411001	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										LT MLG LEG	SHEARED         	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CE	07	9865B	5062 				172RG1061				A SUCCESSFUL CRASH LANDING WAS ACCOMPLISHED WITH THE LANDING GEAR SELECTED UP FOLLOWING A FAILURE OF THE LT  MLG LEG TO 	COMPLETELY LOCK DOWN.  THIS EVENT HAPPENED FOLLOWING MULTIPLE TAKEOFF AND LANDINGS DURING A TRAINING FLIGHT.  UPON THE L	AST LANDING PRIOR TO THE GEAR-UP LANDING, THE LT BRAKE WENT COMPLETELY SOFT AND SPONGY.  SEVERAL ATTEMPTS WERE MADE TO L	OCK THE LT MAIN GEAR DOWN-AND-LOCKED, HOWEVER, THEY WERE UNSUCCESSFUL.  DAMAGE OCCURRED TO THE BELLY, ENGINE AND PROPELL	ER.  INVESTIGATION REVEALED THE LT MLG PIVOT ASSY SHEARED AT THE BASE OF THE SPLINED SURFACE.  PIVOT ASSY SENT TO CESSNA	 M AND P FOR ANALYSIS AND TESTING.  PIVOT ASSY INSPECTED PREVIOUSLY BY SEB 90-1, REV 2, FOR CRACKS.	1	H	7	1 	3O				3A17    					 
1997010900858	19970109	00858	NE  	1997	1	9	97ZZZX213        	2	19961220	G	7260	107006204	GEAR            		107022013   	KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					ACCY DRIVE	PIN FAILED      	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			NM	09	311KA	443  				A940017	LE81016			N2 FAILURE OCCURRED.  UPON ENGINE DISASSEMBLY AND INSP, FAILURE WAS CAUSED BY LOCK PIN AN 122683 HOLDING BEARING SLEEVE 	IN GEAR 1-070-062-04 FALLING OUT ALLOWING GEAR POSITION TO CHANGE AND SUBSEQUENT N2 DRIVE TO FAIL.  GEAR IS COMPONENT OF	 CARRIER ASSY 1-070-220-13.				1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
1997011600012	19970116	00012	SW  	1997	1	16	97ZZZX218        	1	19961107	G	6230	206010335001	LEVER ASSY      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1081G		481  			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 480.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600013	19970116	00013	SW  	1997	1	16	97ZZZX219        	1	19961107	G	6230	206010336005	LINK IDLER      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1081G		481  			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 480.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1997010900115	19970109	00115	SO  	1997	1	9	97ZZZX22         	1	19961112	G	2740	3397208	BELLCRANK       			PIPER 	PA23  	PA23250     	7102308	SO  										STAB	WORN            	D				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		DE	DESCENT        	1			GL	17	22TD					277854103				STABILATOR VIBRATION, FLUTTER IN DESCENT (AT HIGH SPEED) TRACED TO MOVEMENT IN ABOVE PIVOT JOINT.  HOLE IN BLOCK, BUSHIN	G, AND BOLT ALL SEVERELY WORN.  PLAY IN JOINT NOT IMMEDIATELY EVIDENT BECAUSE OF SPRING LOADING ON BELLCRANK.  RT SIDE N	OT WORN.  WEAR ALLOWS TAB TO MOVE AND FLUTTER, INDUCING MOVEMENT IN STAB.				1	L	7	2 	3O				1A10    					 
1997011600014	19970116	00014	SW  	1997	1	16	97ZZZX220        	1	19961107	G	6230	206010335001	LEVER ASSY      			BELL  	206   	206L4       	1182110	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	174AL	341  	341  			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 206-010-470-10	1 BEARING.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 341.1 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1997011600015	19970116	00015	SW  	1997	1	16	97ZZZX221        	1	19961107	G	6230	206010336005	LINK IDLER      			BELL  	206   	206L4       	1182110	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	174AL	341  				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 206-010-470-10	1 BEARING.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 341.1 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1997011600016	19970116	00016	SW  	1997	1	16	97ZZZX222        	1	19961021	G	6230	2065010335001	LEVER ASSY      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206SL	690  				45245				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 690 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600017	19970116	00017	SW  	1997	1	16	97ZZZX223        	1	19961021	G	6230	206010336005	LINK IDLER      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206SL					45245				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 690 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600018	19970116	00018	SW  	1997	1	16	97ZZZX224        	1	19961113	G	6230	206010335001	LEVER ASSY      			BELL  	206   	206L3       	1182108	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350AL	361  				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 NAS6605D6 BOLTS, 1 EACH 206-010-470-10	1 BEARING.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 360.5 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600019	19970116	00019	SW  	1997	1	16	97ZZZX225        	1	19961113	G	6230	206010336005	LINK IDLER      			BELL  	206   	206L3       	1182108	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350AL	361  				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 206-010-470-10	1 BEARING.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 360.5 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600020	19970116	00020	SW  	1997	1	16	97ZZZX226        	1	19961021	G	6230	206010335001	LEVER ASSY      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57334		548  			45445				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 548.2 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600021	19970116	00021	SW  	1997	1	16	97ZZZX227        	1	19961021	G	6230	206010336005	LINK IDLER      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57334	548  				45445				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 548.2 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600023	19970116	00023	NE  	1997	1	16	97ZZZX229        	1	19961104	G	6210	7615009100051A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N	13028	466  		A08601369	760088				DURING 500 HOUR INSPECTION FOUND BLADE LEADING EDGE CRACKED AND SEPARATED AT RIGHT STATION 114 AND RIGHT STATION 154, LE	ADING EDGE LOWER SURFACE DEBONDED AT RIGHT STANDARD 100, TRAILING EDGED CRACKED AT RIGHT STATION 62.					1	G	7	2 	3U				H1NE    					 
1997010900116	19970109	00116	SO  	1997	1	9	97ZZZX23         	1	19961112	G	2740	2183103	BUSHING         			PIPER 	PA23  	PA23250     	7102308	SO  										STAB	WORN            	D	S	A		O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		DE	DESCENT        	1			GL	17	22TD					277854103				STABILATOR VIBRATION, FLUTTER IN DESCENT (AT HIGH SPEED) TRACED TO MOVEMENT IN ABOVE PIVOT JOINT.  HOLE IN BLOCK, BUSHIN	G, AND BOLT ALL SEVERELY WORN.  PLAY IN JOINT NOT IMMEDIATELY EVIDENT BECAUSE OF SPRING LOADING ON BELLCRANK.  RT SIDE N	OT WORN.  WEAR ALLOWS TAB TO MOVE AND FLUTTER, INDUCING MOVEMENT IN STAB.				1	L	7	2 	3O				1A10    					 
1997011600024	19970116	00024	NE  	1997	1	16	97ZZZX230        	1	19961023	G	6410	7610105101041	PADDLE          			SKRSKY	S76   	S76A        	8143006	NE  										T/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N	8314 	482  		A13700670X	760088				DISCOVERED DURING 500 HOUR INSPECTION, T/R PADDLE 'A' TIP CAP DEBONDED.  PADDLE 'B' PIVOT BEARING RETAINERS DEBONDED.						1	G	7	2 	3U				H1NE    					 
1997011600025	19970116	00025	NE  	1997	1	16	97ZZZX231        	1	19960805	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	13028	466  		A08601369	760088				DURING 500 HOUR INSPECTION FOUND BLADE LEADING EDGE CRACKED AND DEBONDED AT RIGHT STA 114, AND STA 154.						1	G	7	2 	3U				H1NE    					 
1997011600026	19970116	00026	SW  	1997	1	16	97ZZZX232        	1	19961021	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	293  				52064				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PA	RTS TT 293.1 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1997011600027	19970116	00027	SW  	1997	1	16	97ZZZX233        	1	19961021	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	330  				52066				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PAR	TS TT 330.3 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1997011600029	19970116	00029	SW  	1997	1	16	97ZZZX235        	1	19961021	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	310  				52117				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-01 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PAR	TS TT 310.3 HOURS.				1	G	7	1 	3U			NC	H2SW    					 
1997011600030	19970116	00030	SW  	1997	1	16	97ZZZX236        	1	19961107	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	390  				45681				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PA	RTS TT 390.0 HOURS.				1	G	7	1 	3U				H2SW    					 
1997052900292	19970529	00292	NE  	1997	5	29	97ZZZX2374       	2	19961211	G	7230	0292152880	COMPRESSOR      			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					ENGINE	COVER BROKEN    	B			VE3D	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	01	215LA		2965 			2143	7157			ENGINE WAS PRODUCING AN ODD NOISE AND HAD A HIGH FREQUENCY VIBRATION.  PREVIOUS VIBRATION CHECK WITH BRUEL AND KSAER VIB	 METER 64.4 HRS EARLIER WAS WITHIN LIMITS.  INSPECTED COMPRESSOR WITH BORESCOPE THROUGH BLEED VALVE HOLE AND FOUND TAB O	N CENTRIFUGAL COMPRESSOR COVER BROKE LOOSE AND WAS INGESTED BY IMPELLER CAUSING SIGNIFICANT DAMAGE.  SL 1708/96/ARR/31 A	DDRESSES THIS PROBLEM, BUT THE CHECKS CALL-OUT WAS NOT WHAT THIS ENGINE WAS EXPERIENCING.  THE S/L SHOULD BE CHANGED TO 	REFLECT OTHER WAYS TO INSPECT FOR THIS PROBLEM.  ALSO, PROCEDURES TO FIND IT BEFORE DAMAGE OCCURS.		1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997052900293	19970529	00293	NE  	1997	5	29	97ZZZX2375       	2	19961101	G	7412	9580115210	HE GENERATOR    			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					ENGINE IGNITER	FAILED          	B			VE3D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	2127S	399  				2213	7119			ACFT TT 5,043.8 HOURS.  HELICOPTER FAILED TO START.  AFTER TROUBLESHOOTING, FOUND BOTH IGNITERS DEFECTIVE AND H.E. GENER	ATOR (EXECUTER BOX) INOPERATIVE.  H.E. GENERATOR HAD 399.0 HRS SINCE NEW.  PAPERWORK WAS SUBMITTED TO MANUFACTURE FOR WA	RRANTY.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997011600032	19970116	00032	SW  	1997	1	16	97ZZZX238        	1	19961031	G	6210	206010200133	BLADE           			BELL  	206   	206B        	1181511	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2295F	2706 			A863	3579				DURING DAILY INSPECTION, BLADE TIP BLOCK AND WEIGHT PACKAGE CORRODED CAUSING DEFORMATION OF SPAR AT TIP.						1	G	7	1 	3U				H2SW    					 
1997010900117	19970109	00117	CE  	1997	1	9	97ZZZX24         	1	19961213	G	3211	0541153	U-BOLT          			CESSNA	182   	182B        	2072706	CE  										MLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	2340G	3278 				51640				DURING ANNUAL INSPECTION, THE MLG U-BOLT NUTS WERE CHECKED FOR SECURITY.  THE REAR RIGHT U-BOLT NUT WAS FOUND TO BE LOOS	E.  SUBSEQUENT INSPECTION REVEALED A PRE-EXISTING CRACK HAD ALLOWED THE U-BOLT TO STRETCH. THE U-BOLT WAS FOUND TO BE CR	ACKED APPROXIMATELY 60 PERCENT THROUGH THE DIAMETER OF THE BOLT.  THE CRACK WAS LOCATED THREE THREADS FROM THE BOTTOM OF	 THE THREADED PORTION OF THE BOLT, AT THE BOTTOM OF THE NUT.			1	H	7	1 	3O			NT	3A13    					 
1997011600035	19970116	00035	SW  	1997	1	16	97ZZZX241        	1	19961121	G	6210	206015001107	BLADE           		206011100025	BELL  	206   	206L1       	1182107	SW  										M/R TIP	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758L	2534 			A1310	45266				ROUTINE INSPECTION FOUND CORROSION AT TIP OF BLADE.						1	G	7	1 	3U				H2SW    					 
1997011600036	19970116	00036	SW  	1997	1	16	97ZZZX242        	1	19961113	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	487  				45775				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-10-338-001 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS.  2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PA	RTS TT 486.9 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600037	19970116	00037	SW  	1997	1	16	97ZZZX243        	1	19961107	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	475  				45779				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PA	RTS TT 475.0 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600038	19970116	00038	SW  	1997	1	16	97ZZZX244        	1	19961030	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3190P	3394 			A467	45779				DURING DAILY INSPECTION, FOUND M/R BLADE SPAR LEADING EDGE CORRODED BEYOND LIMITS.						1	G	7	1 	3U				H2SW    					 
1997011600040	19970116	00040	SW  	1997	1	16	97ZZZX246        	1	19961107	G	6230	2060103335001	LEVER ASSY      		206010350021	BELL  	206   	206L3       	1182108	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	349AL		296  			51388				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PA	RTS TT 295.8 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600041	19970116	00041	SW  	1997	1	16	97ZZZX247        	1	19961110	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		285  			51444				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605DC64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN P	ARTS TT 285.1 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600042	19970116	00042	SW  	1997	1	16	97ZZZX248        	1	19961107	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	362AL	397  				51471				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PA	RTS TT 396.6 HOURS.				1	G	7	1 	3U				H2SW    					 
1997010900118	19970109	00118	SO  	1997	1	9	97ZZZX25         	2	19961218	G	8530	646032	RETAINER        			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360LB   	17025	SO  					CYL ROCKER ARM	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1167H	1746 				250689				FOUND 3 ROCKER ARM RETAINERS BROKEN AND 2 CRACKED DURING ANNUAL INSPECTION.  PARTS HAD NOT COME LOOSE YET.						1	L	7	1 	3O	3	O		2A3     	E9CE				 
1997011600045	19970116	00045	SW  	1997	1	16	97ZZZX251        	1	19961107	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	5008K	645  				2524				DAILY INSPECTION FOUND BEARING AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SPA	CERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PAR	TS TT 645.2 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600048	19970116	00048	SW  	1997	1	16	97ZZZX254        	1	19961107	G	6230	206010335001	LEVER ASSY      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5750Y		395  			45517				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PARTS TT 39	5.0 HOURS.				1	G	7	1 	3U				H2SW    					 
1997011600049	19970116	00049	SW  	1997	1	16	97ZZZX255        	1	19961021	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	5760A	451  				45538				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605D64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN PA	RTS TT 450.7 HOURS.				1	G	7	1 	3U				H2SW    					 
1997060500460	19970605	00460	GL  	1997	6	5	97ZZZX2555       	1	19960506	G	6230	28161191	UNIVERSAL HSNG  			ENSTRM	F28   	F28F        	3300412	GL  										SWASHPLATE	CRACKED         	C			PP0M	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			WP	01	8626S	3710 			1189788Y	786				MOUNTING WEBS FOR CONTROL ROD BEARINGS AND UNIVERSAL JOINT OF LOWER SWASHPLATE FOUND CRACKED AT INSPECTION.  THIS IS A P	RIMARY FLIGHT CONTROL PART.  THIS PART HAS A RETIREMENT LIFE OF 17,700 HOURS.  PART NON-REPAIRABLE.  REPLACED WITH SERVI	CEABLE PART 28-16119-1.				1	G	7	1 	3O				H1CE    					 
1997011600050	19970116	00050	SW  	1997	1	16	97ZZZX256        	1	19961016	G	6310	206040221003	OUTER SHAFT     		206040270003	BELL  	206   	206B        	1181511	SW  										FREEWHEEL UNIT	MAKING METAL    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59541		1795 		B129175	1412				FIELD REPORTED FREEWHEEL ASSEMBLY 'MAKING METAL'.  FOUND ROLLER BEARING P/N 206-040-205-005 SPINNING IN OUTER SHAFT, GAL	LING SHAFT I.D. MAKING METAL.					1	G	7	1 	3U				H2SW    					 
1997011600051	19970116	00051	NE  	1997	1	16	97ZZZX257        	1	19961018	G	6210	7615009100049A	BLADE           			SKRSKY	S76   	S76         	8143010	NE  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	705AL	9749 	421  		A08600883	760267				DURING 500 HOUR INSPECTION FOUND UPPER SURFACE SKIN DEBONDED APPROXIMATELY 5 INCHES BY 6.50 INCHES AT RIGHT STA 53.  SKI	N CRACKED AT FORWARD EDGE OF TRIM TAB.					1	G	7	2 	3U				H1NE    					 
1997011600052	19970116	00052	NE  	1997	1	16	97ZZZX258        	1	19961021	G	6210	7615009100049A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	712AL	6408 	454  		A08600858	760280				DURING 500 HOUR INSPECTION FOUND BLADE TIP RIB DEBONDED.						1	G	7	2 	3U				H1NE    					 
1997060500486	19970605	00486	CE  	1997	6	5	97ZZZX2582       	1	19961030	G	7160	BA8101	GASKET          		BA8110      	BBAVIA	8     	8KCAB       	2110612	CE  										INDUCTION AIR	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	444PF	638  				54379				UPON ANNUAL INSPECTION, THE INDUCTION AIR FILTER GASKET WAS FOUND DETERIORATED, LOOSE ON FILTER ASSY.  BRACKET AD 96-09-	06 DOES NOT COVER THIS ASSY MODEL.  SUGGEST INCLUDING MODEL IN AD AND/OR INSPECTING ALL BRACKET AIR FILTER ASSEMBLIES FO	R AD 96-09-06 CONDITION.				1	H	7	1 	3O				A21CE   					 
1997060500490	19970605	00490	CE  	1997	6	5	97ZZZX2586       	1	19960909	G	2820	S5110	HOSE            			CESSNA	208   	208B        	2073701	CE  										FUEL SUPPLY	FAILED          	B		A	FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	746FX	250  				208B0498				DURING COMPLIANCE OF CESSNA SB CAB 96-15 'FUEL HOSE INSPECTION-REPLACEMENT', FOUND ONE OF THE MAIN FUEL SUPPLY HOSES WAS	 DETERIORATED TO THE POINT THAT FUEL FLOW WAS RESTRICTED.  SUBMITTER FEELS THIS CONDITION COULD LEAD TO AN ENGINE SHUT D	OWN IN-FLIGHT.				1	H	7	1 	3T				A37CE   					 
1997060500491	19970605	00491	CE  	1997	6	5	97ZZZX2587       	1	19960911	G	5553		BOLT            			CESSNA	208   	208         	2073702	CE  										VERT STAB ATTACH	LOOSE           	B		A	FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	9617F	5513 				20800107				INSPECTION FOUND VERTICAL STABILIZER ATTACH BOLTS LOOSE.  SUBMITTER STATED THIS IS NOT THE FIRST OCCURRENCE ON 208 MODEL	S SERVICED.					1	H	7	1 	3T			NT	A37CE   					 
1997011600053	19970116	00053	NE  	1997	1	16	97ZZZX259        	1	19961021	G	6210	7615009000049A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	712AL	13691	454  		A08600210	760280				DISCOVERED DURING 500 HOUR INSPECTION, FOUND BLADE SKIN CRACKED ALONG FORWARD EDGE OF TRIM TAB.						1	G	7	2 	3U				H1NE    					 
1997060500496	19970605	00496	SO  	1997	6	5	97ZZZX2592       	2	19960704	G	8520	649130	CRANKSHAFT      			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					NR 3 CHEEK	FAILURE         	D	L			A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			AL	03	185CA		1449 		1289007N	18504445	282598R			IN-FLIGHT FAILURE OF CRANKSHAFT RESULTED IN FORCED LANDING.  AIRCRAFT WAS DESTROYED.  PILOT HAD REPORTED INCREASE IN OIL	 TEMPERATURE (NOT ABOVE RED LINE, BUT HIGHER THAN NORMAL).  NO OTHER SYMPTOMS REPORTED, AND MAINTENANCE COULD NOT IDENTI	FY A PROBLEM.  ENGINE WAS TCU REMANUFACTURE WHICH HAD A USED CRANK INSTALLED.				1	H	7	1 	3O	3	O		3A24    	E5CE				 
1997010900119	19970109	00119	EA  	1997	1	9	97ZZZX26         	2	19961215	G	8530	SL134441	PISTON PIN      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	TO360E1A6   	41514	EA  					NR 2 CYLINDER	FAILED          	B			MX3R	C				ABORTED TAKEOFF         				Y	E	K	ENGINE STOPPAGE           	VIBRATION/BUFFET          	FLUID LOSS                	TO	TAKEOFF        	1			WP	11	8532Z	275  				447995280	RL00013572T			ENGINE FAILED ON TAKEOFF DUE TO BROKEN PISTON PIN IN NR 2 CYLINDER, RT ENGINE.  ENGINE DESTROYED, BROKEN RODS AND CASES,	 ETC.  RUINED CRANKSHAFT.  SUSPECTED CAUSE, MANUFACTURER'S DEFECT.					1	L	7	2 	3O	3	O		A19S0   	E26EA				 
1997011600054	19970116	00054	NE  	1997	1	16	97ZZZX260        	1	19960920	G	6210	7615009100049A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	768AL	10167	238  		A08600881	760031				DURING DAILY INSPECTION, FOUND UPPER SURFACE SKIN DEBONDED APPROXIMATELY 20 INCHES BY 8.50 INCHES NEAR BLADE TIP.						1	G	7	2 	3U				H1NE    					 
1997011600055	19970116	00055	EU  	1997	1	16	97ZZZX261        	1	19961018	G	5330	1053025158	SKIN            		10530102    	BOLKMS	105   	BO105CBS    	5626008	EU  										TAILBOOM	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5412J	6451 				S784				DAILY INSPECTION FOUND TAILBOOM HAS EXCESSIVE CORROSION AT CAMLOCK HOLES ON UPPER SKIN.						1	G	7	2 	3U			NC	H3EU    					 
1997011600161	19970116	00161	CE  	1997	1	16	97ZZZX265        	1	19961202	G	2822	503801775	PUMP            	AIRBORNE    		BEECH 	200   	B200        	1152922	CE  										NAC TANK	DEFECTIVE       	B	L		DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	260G	99   			5AL78	BB1525				INVESTIGATION FOR DEFECTIVE STANDBY FUEL PUMP FOUND OVERSIZE VANES IN PUMP STICKING.  PUMP OK WHEN NEW, BUT VANES SWELL 	UP WHEN IN JET FUEL.  SUGGEST TO ORDER NEW PUMPS FROM BATCH S/N 8AMXXX, AND 9AMXXX.					1	L	7	2 	4T				A24CE   					 
1997061200145	19970612	00145	CE  	1997	6	12	97ZZZX2657       	1	19960505	G	5531	07310331	RIB             			CESSNA	185   	A185F       	2072821	CE  										VERTICAL STAB	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	6964N	2400 				18504318				DURING ANNUAL INSPECTION OF AIRCRAFT, FOUND CORROSION ON RIB AT BASE OF VERTICAL STABILIZER.  FORWARD 6 INCHES OF RIB WA	S COMPLETELY DELAMINATED.  AIRCRAFT HAD BEEN ON FLOATS IN SALT WATER ENVIRONMENT.  REST OF AIRCRAFT IN GOOD CONDITION.					1	H	7	1 	3O				3A24    					 
1997011600162	19970116	00162	CE  	1997	1	16	97ZZZX266        	1	19961202	G	2822	503801775	PUMP            	AIRBORNE    		BEECH 	200   	B200        	1152922	CE  										NAC TANK	DEFECTIVE       	B		A	DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	260G	99   			10AL102	BB1525				INVESTIGATION FOR DEFECTIVE STANDBY FUEL PUMP FOUND OVERSIZE VANES IN PUMP STICKING.  PUMP OK WHEN NEW, BUT VANES SWELL 	UP WHEN IN JET FUEL.  SUGGEST TO ORDER NEW PUMPS FROM BATCH S/N 8AMXXX, AND 9AMXXX.					1	L	7	2 	4T				A24CE   					 
1997011600163	19970116	00163	EU  	1997	1	16	97ZZZX267        	2	19961223	G	7321	5225126	JUMP RATE ASSY  	WOODWARD    	8063215     						CFMINT	CFM56 	CFM563C     	13802	EU  					ORIFICE PLATE	DISBONDED       	B			UU2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					85913					TWO FUEL CONTROLS WERE RECENTLY REJECTED DURING THE BOEING FLIGHT TEST DUE TO A REPORTED PROBLEM OF FLAMEOUT DURING TAXI	.  SUBSEQUENT INVESTIGATION AT WOODWARD REVEALED A DISBONDED JUMP AND RATE ORIFICE.  THE ABSENCE OF A RATE ORIFICE RESUL	TS IN A MUCH MORE RAPID TRANSITION TO THE DECELERATION SCHEDULE THAN DESIRED.  THE CHARACTERISTICS OF THE DISBONDMENT IN	DICATED THAT ONE SURFACE OF THE JOINT DID NOT ADHERE; MOST LIKELY DUE TO INADEQUATE CLEANING OR RECONTAMINATION AFTER CL	EANING.  GEAE IS PUBLISHING A SERVICE BULLETIN RECOMMENDING IMMEDIATE REPLACMENT OF THE SUSPECT HARDWARE.							4	F			E21EU				 
1997061200160	19970612	00160	SW  	1997	6	12	97ZZZX2672       	1	19961011	G	6310	214040841101	SEAL            			BELL  	206   	206L4       	1182110	SW  										T/R OUTPUT DRIVE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	696BA					52166				REPLACED FREE WHEELING UNIT TAIL ROTOR OUTPUT DRIVE SEAL DUE TO LEAKING OIL.						1	G	7	1 	3U			NC	H2SW    					 
1997011600164	19970116	00164	EU  	1997	1	16	97ZZZX268        	2	19961223	G	7321	5225126	JUMP RATE ASSY  	WOODWARD    	8063215     						CFMINT	CFM56 	CFM563C     	13802	EU  					ORIFICE PLATE	DISBONDED       	B			UU2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					85782					TWO FUEL CONTROLS WERE RECENTLY REJECTED DURING THE BOEING FLIGHT TEST DUE TO A REPORTED PROBLEM OF FLAMEOUT DURING TAXI	.  SUBSEQUENT INVESTIGATION AT WOODWARD REVEALED A DISBONDED JUMP AND RATE ORIFICE.  THE ABSENCE OF A RATE ORIFICE RESUL	TS IN A MUCH MORE RAPID TRANSITION TO THE DECELERATION SCHEDULE THAN DESIRED.  THE CHARACTERISTICS OF THE DISBONDMENT IN	DICATED THAT ONE SURFACE OF THE JOINT DID NOT ADHERE; MOST LIKELY DUE TO INADEQUATE CLEANING OR RECONTAMINATION AFTER CL	EANING.  GEAE IS PUBLISHING A SERVICE BULLETIN RECOMMENDING IMMEDIATE REPLACMENT OF THE SUSPECT HARDWARE.							4	F			E21EU				 
1997011600165	19970116	00165	NE  	1997	1	16	97ZZZX269        	2	19961214	G	7420	5306721	LEAD            			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT ENG IGNITER	DEFECTIVE       	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	101QS	7705 				S5500101	PCE102267			DURING INSPECTION, LEFT ENGINE OUTBOARD IGNITER WOULD NOT OPS CHECK.  FOUND IGNITION CABLE DEFECTIVE DUE TO AN INTERNAL 	FAULT.  COULD NOT DETERMINE CAUSE AS EXTERNAL INSPECTION OF IGNITION CABLE APPEARED SERVICEABLE.					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
1997010900120	19970109	00120	SO  	1997	1	9	97ZZZX27         	1	19961125	G	2410		BRACKET         			PIPER 	PA28  	PA28160     	7102806	SO  										ALT BELT ADJ	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5JN					281528				ALTERNATOR BRACKET CITED IS ONE HAVING ELONGATED HOLE FOR ADJUSTING BELT TENSION.  THE CRACK LOCATION WAS AT THE ENGINE 	SIDE OF THE BRACKET, AND CRACKED COMPLETELY THROUGH.  NO REPAIR OTHER THAN REPLACEMENT.					1	L	7	1 	3O				2A13    					 
1997011600166	19970116	00166	CE  	1997	1	16	97ZZZX270        	1	19961231	G	2197	13H37A1	WIRE            			CESSNA	501   	501         	2076603	CE  										AFT CABIN A/C	MELTED          	D				K				NONE                    				B	W		SMOKE/FUMES/ODORS/SPARKS  	INADEQUATE Q C            		NR	NOT REPORTED   	1			CE	03	70CG					5010187				PILOT REPORTED SMELL IN CABIN WITH AIR CONDITIONER ON.  FOUND MAIN POWER WIRE TO MOTOR FROM CURRENT LIMITER MELTED CAUSE	D BY THE REQUIRED LIMITER OF 150 AMP BEING REPLACED WITH A 175 AMP LIMITER.  COMPRESSOR ASSY REPLACED 3-27-96 BY CESSNA 	TELEDO SERVICE CENTER.  AFT EVAPORATION BLOWER REPLACED 6-30-95 BY GREENSBORO CESSNA SERVICE CENTER.				1	L	7	2 	4F			 	A27CE   					 
1997061200779	19970612	00779	GL  	1997	6	12	97ZZZX2707       	2	19961108	G	7250	23009630	THRUST PLATE    								ALLSN 	250C  	250C20B     	03013	GL  					NR 8 BEARING	WORN            	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17										TURBINE WAS GENERATING METAL.  FOUND THE BEARING CLAMPING SURFACE OF THE THRUST PLATE WORN DUE TO SPINNING OF THE NR 8 B	EARING OUTER RACE.  FRETTING ON THE OPPOSITE SIDE OF THE THRUST PLATE INDICATED THERE MAY HAVE BEEN INSUFFICIENT TORQUE 	ON THE NR 8 BEARING SUMP NUT.									3	U			E4CE				 
1997061200786	19970612	00786	EU  	1997	6	12	97ZZZX2714       	1	19960910	G	2742	5435021	ACTUATOR        	LEARSIEGLER 		ISRAEL	1124  	1124        	4500102	EU  										HORZ STAB TRIM	BROKEN          	B	L	A	QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	87NS		2005 		708208AA	432				UPON INSPECTION FOUND LEFT HAND JACK SCREW ON PITCH TRIM ACTUATOR S/N 7082-08AA BROKEN.  HIGH CYCLES AND HEAVY USE OF TH	RUST REVERSERS CAUSE VIBRATION IN THE TAIL WHICH COULD HAVE RESULTED IN THIS FAILURE.  INSTALLED 4-3-86.  LANDINGS SOH, 	3,457.				2	M	7	2 	4F				A2SW    					 
1997061200787	19970612	00787	EU  	1997	6	12	97ZZZX2715       	1	19960911	G	2742	5435021	ACTUATOR        	LEARSIEGLER 		ISRAEL	1124  	1124        	4500102	EU  										HORZ STAB TRIM	BROKEN          	B	L	A	QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	317MQ		4123 		077800AA	421				THE BROKEN STABILIZER JACK SCREW WAS FOUND DURING A 400-HOUR AIRFRAME INSPECTION.  ISRAEL AIRCRAFT IND RELEASED A MANDAT	ORY SB RECENTLY TO INSPECT COMPONENTS WITHIN 50 HOURS OR AT THE NEXT INSPECTION.  SUBMITTER'S CONCERN IS THE METHOD THAT	 IS USED TO DETECT A DISCREPANCY IS NOT THOROUGH ENOUGH, AND SOME OPERATORS WILL NOT COMPLY UNLESS IT IS AN AD.  THIS CO	MPONENT SHOULD BE LIFE LIMITED AND INSPECTED USING NON-DESTRUCTIVE TESTING.			2	M	7	2 	4F				A2SW    					 
1997011600170	19970116	00170	EA  	1997	1	16	97ZZZX274        	2	19961218	G	8530	76189	CYLINDER        			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  					NR 6	CRACKED         	E				O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		NR	NOT REPORTED   	1			SW	15	315TG	1239 				1460163	L1459348			PILOT REPORTED DROPPING CHT ON LEFT ENGINE.  POST-FLIGHT REPORTED LARGE OIL LEAK.  FOUND NR 6 CYLINDER HAD A CRACK THROU	GH UPPER BASE FLANGE.  FORWARD THREE CYLINDER HOLD DOWN STUDS WERE BROKEN.  THIS CYLINDER WAS PURCHASED NEW FROM LYCOMIN	G AT OVERHAUL.  STUDS AND CYLINDER WERE REPLACED AND AIRCRAFT WAS RELEASED.				1	H	7	2 	3O	3	O		6A1     	1E4				 
1997011600173	19970116	00173	SO  	1997	1	16	97ZZZX277        	1	19961221	G	8011	EBB75A	BENDIX DRIVE    		MZ4206      	PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1B5    	41532	EA  					STARTER	EXCESS WORN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	5259P				83800483	24293	L612440			FOUND STARTER BENDIX DRIVE NOT ENGAGING THE RING GEAR ASSEMBLY WITH THE BENDIX GEAR TEETH TORN OFF ABOUT 50 PERCENT, AND	 THE END BRONZE BUSHING EATEN UP.  ALSO, DAMAGE TO THE TEETH OF THE RING GEAR.  THE STARTER COMMUTATOR SHOWS IT WAS FRES	HLY POLISHED WITH GOOD BRUSHES; THE GEARBOX WAS FRESHLY PACKED WITH GREASE.  THIS ENGINE HAD BEEN OVEHAULED WITHIN THE P	AST YEAR.			1	L	7	1 	3O	3	O		1A15    	E295				 
1997061200843	19970612	00843	GL  	1997	6	12	97ZZZX2770       	1	19960506	G	6230	28161191	UNIVERSAL HSNG  			ENSTRM	F28   	F28F        	3300412	GL  										SWASHPLATE	CRACKED         	C		A	PP0M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8626S	3710 			1189788H	786				MOUNTING WEBS FOR CONTROL ROD BEARINGS AND UNIVERSAL JOINT OF LOWER SWASHPLATE FOUND CRACKED AT INSPECTION.  THIS IS A P	RIMARY FLIGHT CONTROL PART.  THIS PART HAS A RETIREMENT LIFE OF 17,700 HOURS.  PART NON-REPAIRABLE.  REPLACED WITH SERVI	CEABLE PART 28-16119-1.				1	G	7	1 	3O				H1CE    					 
1997011600174	19970116	00174	SO  	1997	1	16	97ZZZX278        	1	19960911	G	2434	4111810	ALTERNATOR      			PIPER 	PA28  	PA28RT201   	7102818	SO  										BATTERY LUG	DEFECTIVE       	B			BJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	8108M		95   		5091990	28R8018006				ALTERNATOR FALLING APART AFTER 95 HRS IN SERVICE.  PART OVERHAULED BY ELECTROSYSTEMS.  CERTIFICATE NR UT2R226L.						1	L	7	1 	3O				2A13    					 
1997011600175	19970116	00175	SO  	1997	1	16	97ZZZX279        	1	19960821	G	2434	ALU8421	ALTERNATOR      			PIPER 	PA23  	PA23250     	7102308	SO  										BRUSH BLOCK	FAILED          	B			UKJR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	23	27CY		37   		A6960101	277654118				PILOT REPORTED LT ALTERNATOR LIGHT FLICKERED DURING TURBULENCE.  LIGHT CAME ON STEADY ON THE WAY TO MAINTENANCE.  REMOVE	D ALTERNATOR, HEARD SOMETHING RATTLING INSIDE.  REMOVED COOLING SHROUD AND FOUND ONE BRUSH INSIDE.  REMOVED BRUSH BLOCK 	AND FOUND A PIECE OF IT AROUND THE BRUSH HAD BROKEN AWAY.  REPLACED ALTERNATOR WITH O/H UNIT, OPS CK NORMAL.				1	L	7	2 	3O				1A10    					 
1997010900121	19970109	00121	SO  	1997	1	9	97ZZZX28         	1	19961117	G	3250	9506128	CHANNEL         			PIPER 	PA34  	PA34220T    	7103420	SO  										NLG	CRACKED         	E		A		A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			EA	05	8381M	5310 				348133086				PILOT NOTED A LOUD BANG IN NOSE GEAR AS HE TAXIED ONTO RUNWAY FOR TAKEOFF.  AFTER TAKEOFF, HE NOTICED THE NOSE WHEEL WAS	 TURNED 90 DEGREES TO THE AIRCRAFT.  PILOT DID NOT RETRACT LANDING GEAR.  AFTER LANDING, WAS UNABLE TO STEER AIRCRAFT. S	TEERING CHANNEL WAS CRACKED BOTH SIDES AT AFT END.  CRACKS ALLOWED THE NOSE GEAR STEERING BALL TO EXIT THE CHANNEL.				1	L	7	2 	3O				A7SO    					 
1997061900383	19970619	00383	EU  	1997	6	19	97ZZZX2826       	1	19960609	G	6520	350A33215300	LAMINATE HINGE  			SNIAS 	350   	AS350B      	8680801	EU  										T/R	CRACKED         	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	911NT	139  				1556				RUBBER LAMINATE IS CRACKED 360 DEGREES AROUND PART.						1	G	7	1 	3U				H9EU    					 
1997061900461	19970619	00461	GL  	1997	6	19	97ZZZX2833       	1	19960514	G	5720	V61	BLOCK           			AMTR  	EAGLE 	CHRISEAGLE2 		GL  										OUTER WING SYS	FAILED          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2FOR									AUS - DURING INVESTIGATION OF A WRINKLE IN THE FABRIC COVERING ON THE TOP WING (INBOARD) TRAILING EDGE, THE DRAG/ANTI-DR	AG WIRE REAR ATTACHMENT BLOCK AT REAR SPAR WAS FOUND BROKEN WHICH, IN TURN, CAUSED THE TRAILING EDGE TO CENTRE HOOP ATTA	CHMENT BLOCK TO FAIL.				1	Q	7	1 	3O				EXPA1Q71					 
1997010900122	19970109	00122	SW  	1997	1	9	97ZZZX29         	1	19961211	G	7810	30503502	MOUNT TUBE      		300MISSLE   	MOONEY	M20   	M20J        	5870219	SW  										MUFFLER MOUNT	BROKEN TAB      	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	9932S				3000024	241096				DURING ANNUAL INSPECTION, FOUND RT HAND FORWARD EXHAUST MUFFLER SUPPORT TUBE BROKEN AT LOWER ATTACH TAB.  THIS TUBE ASSY	 IS THE SAME ONE USED ON ROCKET ENGINEERING 305 - ROCKET CONVERSION ON M20K SERIES MOONEY.  THIS TUBE IS OF THE NEWER HE	AVY DUTY TYPE DESIGN THAT DOES NOT REQUIRE A REPETATIVE INSPECTION AS OUTLINED IN ROCKER M5B 95-305-01, OR AD 95-17-06 F	OR THE M20K CONVERTED TO ROCKET 305.  SUBMITTER RECOMMENDS INCREASED INSPECTION OF THESE MOUNTS ANY TIME LOWER COWLING I	S REMOVED, UNTIL IT IS DETERMINED IF THIS WILL BE A RECURRING PROBLEM ON THE M20J - 300 MISSLE CONVERSION.		1	L	7	1 	3O				2A3     					 
1997010900096	19970109	00096	CE  	1997	1	9	97ZZZX3          	1	19961220	G	3231	08411066	BELLCRANK       			CESSNA	421   	421B        	2076014	CE  										RT MLG DOOR	BROKEN          	D	S			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	27	100DG					421B0905				AFTER LANDING THE A/C, THE PILOT NOTICED THAT THE RT IB MLG DOOR WAS NOT CLOSED.  AFTER INSPECTION OF THE AIRCRAFT, THE 	MAIN GEAR DOOR IDLER BELLCRANK WAS FOUND BROKEN.  NO OTHER DAMAGE TO THE RETRACTION LINKAGE WAS NOTED.  IF THIS PROBLEM 	HAD NOT BEEN NOTICED BY THE PILOT, IT WOULD HAVE CAUSED THE GEAR TO BIND AND JAM AGAINST THE DOOR AND POSSIBLY NOT ALLOW	 THE GEAR TO EXTEND.  AIRFRAME TOTAL KNOWN TIME 3,300 PLUS HOURS.			1	L	7	2 	3O				A7CE    					 
1997010900123	19970109	00123	CE  	1997	1	9	97ZZZX30         	1	19961213	G	3610	1989001	VALVE           	DUKES       		CESSNA	525   	525         	2076601	CE  										RT WING ANTI-ICE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	229CJ	370  			289	5250129				AIRCRAFT HAD NO BLEED AIR TO RIGHT WING FOR ANTI-ICE PROTECTION.  FOUND SEVERAL BROKEN WELDS AT GUSSETS HOLDING STATIONA	RY PART OF VALVE CAUSING VALVE TO MOVE, AND NOT ALLOWING THE CHECK PORTION OF VALVE TO OPEN ALLOWING BLEED AIR TO THE AN	TI-ICE WING VALVE.				1	L	7	2 	4F			RT	A1WI    					 
1997071000268	19970710	00268	EU  	1997	7	10	97ZZZX3034       	1	19961217	G	3222	200876004	STRUT           			BAG   	BAE146	BAE146200A  	1500266	EU  										NLG	CRACKED         	B	S		LVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	178US				DRG261983	E2040				WHILE PERFORMING A RETURN-TO-SERVICE INSPECTION ON THE AIRCRAFT, A 4 INCH LONG CRACK WAS FOUND IN THE NLG STRUT.  THE CR	ACK WAS LOCATED APPROXIMATELY 8 INCHES BELOW TOP END OF STRUT.  TOTAL PART TIME:  8,840 HOURS, TOTAL PART CYCLES:  9,105	.  AIRCRAFT HAD BEEN IN STORAGE APPROXIMATELY 6 YEARS.				2	H	7	4 	4F			RT	A49EU   					 
1997071700105	19970717	00105	CE  	1997	7	17	97ZZZX3068       	1	19960606	G	2133	45AS630199	VALVE           			BEECH 	MU300 	400A        	1155402	CE  										PRESS REG SOV	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	01	8167Y	101  				RK67				PILOT REPORTED LOSS OF PRESSURIZATION ACCOMPANIED BY NIL AIRFLOW INTO CABIN.  PILOT SELECTED EMERGENCY PRESSURIZATION. A	IRFLOW INTO CABIN SUPPLIED BY EMERGENCY SYSTEM AND PRESSURIZATION CONTROL RESTORED.					2	H	7	2 	4F			RT	A16SW   					 
1997071700106	19970717	00106	SO  	1997	7	17	97ZZZX3069       	1	19960111	G	5346	1159BM20518XX	FITTING         			GULSTM	G1159 	G1159B      	3953535	SO  										RT ENG STRUT	CORRODED        	B	S		C9FR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8490P	10974				004				DURING PROCESS OF REMOVING RT THRUST STRUT FOR NDT, DISCOVERED SEVERE INTERGRANULAR CORROSION AT AFT/UPPER THRUST STRUT/	FUSELAGE ATTACH FITITNG, PN 1159BM20518-XX.  BRACKET IS LOCATED IN PYLON.  AREA AFFECTED SURROUNDS STRUT ATTACH BOLT/BUS	H BRACKET LOCATION, RT PYLON FS 584.  AFFECTED AREA IS COVERED BY BOLT SAFETY BRACKET, AND SURROUNDING STRUCTURE, DUCTIN	G, DIRT, ETC., MAKING INSPECTION DIFFICULT.  SUGGEST PAYING SPECIAL ATTENTION TO THIS AREA BY REMOVING RETAINING BOLT AN	D BUSHING TO INSPECT FOR CORROSION AT ATTACH LUGS.		2	L	7	2 	4F			RT	A12EA   					 
1997011600380	19970116	00380	SW  	1997	1	16	97ZZZX307        	1	19961107	G	6230	206010335001	LEVER ASSY      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27483		454  			45230				DAILY INSPECTION FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.  PARTS REQUIRING REPLACEMENT:  4 EACH 206-010-338-001 SP	ACERS, 4 EACH 206-010-337-001 BEARINGS, 2 EACH NAS6605DC64 BOLTS.  NORMAL USE CAUSES PARTS TO WEAR OUT TOO SOON.  WORN P	ARTS TT 453.5.				1	G	7	1 	3U				H2SW    					 
1997011600381	19970116	00381	NE  	1997	1	16	97ZZZX308        	1	19961014	G	6210	802324	SCREWS          			SKRSKY	S76   	S76         	8143010	NE  										TIP CAP	DEFECTIVE       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	707AL				A08602256	760189				DURING 500 HR INSPECTION OF BLADES AS SCREWS WERE BEING INSTALLED TORQUE VALUE WAS REACHED WITH ONLY APPROXIMATELY ONE-T	HIRD THREAD ENGAGEMENT OF ENTIRE GRIP LENGTH.  DISTORTED THREADS IN ONE AXIAL LOCATION ALONG GRIP LENGTH.					1	G	7	2 	3U				H1NE    					 
1997011600382	19970116	00382	NE  	1997	1	16	97ZZZX309        	1	19961014	G	6210	802324	SCREWS          			SKRSKY	S76   	S76         	8143010	NE  										TIP CAP	DEFECTIVE       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	707AL				A08602211	760189				DURING 500 HR INSPECTION OF BLADES AS SCREWS WERE BEING INSTALLED TORQUE VALUE WAS REACHED WITH ONLY APPROXIMATELY ONE-T	HIRD THREAD ENGAGEMENT OF ENTIRE GRIP LENGTH.  DISTORTED THREADS IN ONE AXIAL LOCATION ALONG GRIP LENGTH.					1	G	7	2 	3U				H1NE    					 
1997011600383	19970116	00383	NE  	1997	1	16	97ZZZX310        	1	19961014	G	6210	802324	SCREWS          			SKRSKY	S76   	S76         	8143010	NE  										TIP CAP	DEFECTIVE       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	707AL				A08601362	760189				DURING 500 HR INSPECTION OF BLADES AS SCREWS WERE BEING INSTALLED TORQUE VALUE WAS REACHED WITH ONLY APPROXIMATELY ONE-T	HIRD THREAD ENGAGEMENT OF ENTIRE GRIP LENGTH.  DISTORTED THREADS IN ONE AXIAL LOCATION ALONG GRIP LENGTH.					1	G	7	2 	3U				H1NE    					 
1997011600384	19970116	00384	NE  	1997	1	16	97ZZZX311        	1	19961014	G	6210	802324	SCREWS          			SKRSKY	S76   	S76         	8143010	NE  										TIP CAP	DEFECTIVE       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	707AL				A08600684	760189				DURING 500 HR INSPECTION OF BLADES AS SCREWS WERE BEING INSTALLED TORQUE VALUE WAS REACHED WITH ONLY APPROXIMATELY ONE-T	HIRD THREAD ENGAGEMENT OF ENTIRE GRIP LENGTH.  DISTORTED THREADS IN ONE AXIAL LOCATION ALONG GRIP LENGTH.					1	G	7	2 	3U				H1NE    					 
1997011600839	19970116	00839	SW  	1997	1	16	97ZZZX346        	1	19961114	G	6210	206011119101	BOLT NUT        		20601110021 	BELL  	206   	206B        	1181511	SW  										M/R BLADE	MISMANUFACTURED 	B		A	ENRR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	301MH				RILM11682	2371				PURCHASE NEW MAIN ROTOR BLADE NUT FROM BELL SERVICE CENTER.  DURING INSTALLATION, IT BECAME EVIDENT THAT THREADED BORE O	F NUT WAS NOT PERPENDICULAR TO BEARING FACE OF NUT.  TORQUING NUT TO REQUIRED 215 FOOT/POUND WOULD PUT EXTREME STRESS LO	ADS ON NUT AND HOLLOW BOLT POSSIBLY RESULTING IN FAILURE OF PARTS AND CATASTROPHIC FAILURE OF AIRCRAFT.				1	G	7	1 	3U				H2SW    					 
1997080700342	19970807	00342	EA  	1997	8	7	97ZZZX3468       	2	19960926	G	8520	10321700	BOLT            	PARKERHANFIN	40124       	PIPER 	PA60  	PA60700P    	7106023	NM  	LYC   	O540  	LTIO540U2A  	41533	EA  					CYL NR 6	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	6907A	787  	82   			608423022	L293468A			DURING ENGINE INSPECTION, FOUND NR 6 CYLINDER STUD AND CASE THROUGH-BOLT CRACKED.						1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
1997011600840	19970116	00840	NE  	1997	1	16	97ZZZX347        	2	19961215	G	7323	116085025	GOVERNOR        			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					ENGINE	FAILED          	D				O	A			OTHER                   	UNSCHED LANDING         			J			WARNING INDICATION        			EX	EXTERNAL LOAD  	1			NM	09	311KA	630  			5ADY1950	A940017	LE81016			OVERSPEED GOVERNOR FAILED.  PILOT WAS FORCED TO JETTISON LONG LINE, HOOKS, AND LOGS.  PILOT AUTOROTATED TOWARDS SERVICE 	LANDING, WENT T EMERGENCY GOVERNOR SETTING, AND LANDED WITH POWER.  NO DAMAGE WAS SUSTAINED.  ENGINE BEING REPAIRED BY 	ALLIED SIGNAL.				1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
1997011600841	19970116	00841	NE  	1997	1	16	97ZZZX348        	2	19961201	G	7230	430109102	BEARING         								LYC   	LTS101	LTS101650B1 	41560	NE  					NR 2	DAMAGED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17							LE45068			ENGINE REPORTEDLY MADE UNUSUAL NOISE FOLLOWED BY CHIP LIGHT DURING ENGINE START.  DISASSEMBLED, AND FOUND SEVERELY DAMAG	ED NR 2 BEARING, PN 4-301-091-02, AND NR 3 BEARING.  ALSO, FOUND PT ROTOR BLADES SHIFTED (WITHIN LIMITS), HEAVY RUB ON P	T ROTOR BLADE TIPS AND SEAL KNIVES, AND ON GAS GENERATOR ROTOR AND AXIAL ROTOR BLADE TIPS.  SUBMITTER SUSPECTS PT ROTOR 	SHIFTED FORWARD DURING START, UNLOADING THE NR 3 BEARING AND ALLOWING EXCESSIVE RADIAL MOVEMENT OF PT ROTOR.								3	U			E5NE				 
1997080700358	19970807	00358	CE  	1997	8	7	97ZZZX3484       	1	19961202	G	3213	50450182	WASHER          			CESSNA	421   	421C        	2076016	CE  										MLG SCISSORS	FAILED          	D		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	03	234CN					421C0404				ON LANDING ROLL-OUT, RT MAIN LANDING GEAR ROTATED 90 DEGREES AND BACK AGAIN.   INVESTIGATION FOUND MAIN GEAR SCISSOR CEN	TER BOLT AND BUSHING RETAINING WASHER FAILED AND ALLOWED BUSHING TO 'WALK' AND SCISSOR TO DISCONNECT, ALLOWING TIRE TO R	OTATE.  NEW P/N S1450-5H12-063 WASHERS ARE TWICE AS THICK AS THE OLD ONES.  IF OLD THINNER P/N 5045018-2 ARE WORN, THEY 	WOULD BE REPLACED WITH NEWER.			1	L	7	2 	3O				A7CE    					 
1997011600843	19970116	00843	WP  	1997	1	16	97ZZZX350        	2	19961106	G	7200		ENGINE          			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					LT ENG	FAILED          	D				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	07	27TT	12820	2864 			0122	P74505			LEFT ENG TEMPS WENT UP AND ENG STARTED MAKING NOISE, SHUT DOWN ENG.  REMOVED AND REPLACED ENG.  CAUSE UNKNOWN AT THIS TI	ME.					2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1997011600844	19970116	00844	CE  	1997	1	16	97ZZZX351        	1	19961130	G	2430	BD161	CONNECTOR       			CESSNA	500   	S550        	2076607	CE  										BATTERY	MELTED          	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	299QS					S5500099				DURING INSPECTION, FOUND BATTERY CONNECTOR CORRODED AND MELTED.  CAUSE IS BELIEVED TO BE EXCESSIVE LOOSENESS OF PLUGS. C	LOSELY INSPECTED BATTERY CONNECTOR FOR CONDITION AND LOOSENESS.					1	L	7	2 	4F			RT	A22CE   					 
1997011600845	19970116	00845	SW  	1997	1	16	97ZZZX352        	1	19961130	G	5220	NAS623211	SCREW           			CESSNA	500   	560CESSNA   	2076750	CE  										EXIT HANDLE	BROKEN          	B		A	CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	36H	3235 	3235 			5600035				DURING PRE-PURCHASE INSPECTION FOUND EMERGENCY EXIT HANDLE ATTACH SCREW BROKEN AT THE SCREW THREADS.  THE LOWER PART OF 	SCREW WITH NUT WAS MISSING.  APPEARED TO BE AN INCORRECT SCREW INSTALLED.					2	L	7	2 	4F			RT	A22CE   					 
1997011600846	19970116	00846	CE  	1997	1	16	97ZZZX353        	1	19961214	G	3010	1106P55	SWITCH          			CESSNA	500   	550         	2076604	CE  										DE-ICE BOOT	FAILED          	B			CWQR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	6862Q	9148 			3761	5500265				FLIGHT CREW REPORTED NO 'SURFACE DE-ICE' LIGHT WHEN DE-ICE BOOTS INFLATED.  DETERMINED WING AND TAIL DE-ICE BOOT PRESSUR	E SWITCHES DEFECTIVE, MOST LIKELY DUE TO WATER CONTAMINATION.  SUBMITTER SUGGESTS SWITCHES NEED TO BE INSTALLED IN A POS	ITION THAT WILL LIMIT WATER ACCESS.				1	L	7	2 	4F				A22CE   					 
1997011600847	19970116	00847	CE  	1997	1	16	97ZZZX354        	1	19961214	G	3010	1106P55	SWITCH          			CESSNA	500   	550         	2076604	CE  										DE-ICE BOOT	FAILED          	B			CWQR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	6862Q	1178 			1178	5500265				FLIGHT CREW REPORTED NO 'SURFACE DE-ICE' LIGHT WHEN DE-ICE BOOTS INFLATED.  DETERMINED WING AND TAIL DE-ICE BOOT PRESSUR	E SWITCHES DEFECTIVE, MOST LIKELY DUE TO WATER CONTAMINATION.  SUBMITTER SUGGESTS SWITCHES NEED TO BE INSTALLED IN A POS	ITION THAT WILL LIMIT WATER ACCESS.				1	L	7	2 	4F				A22CE   					 
1997011600848	19970116	00848	CE  	1997	1	16	97ZZZX355        	1	19961118	G	3830	1700079	TANK            		17000017    	CESSNA	500   	S550        	2076607	CE  										AFT CABIN	LEAKING         	B			CWQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	05	86QS	7804 				S5500086				DURING AIRCRAFT CLEANING, FOUND AIRCRAFT TOILET LEAKING.  FOUND TANK UNIT LEAKING FROM IMPROPER REPAIR.  TOILET MAINTENA	NCE MANUAL DOES NOT PERMIT SEALING OF THE TANK UNIT.  TANK UNIT SHOULD BE REPLACED IF FOUND LEAKING DUE TO THE VERY REAL	 CORROSION PROBLEM FOUND IN THE BELLIES OF S550 AIRCRAFT.				1	L	7	2 	4F			RT	A22CE   					 
1997011600850	19970116	00850	CE  	1997	1	16	97ZZZX356        	1	19961217	G	3240	AN8374D	ELBOW           			BEECH 	58    	58P         	1152744	CE  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	1858G	1699 				TJ383				PILOT REPORTED RIGHT MAIN STRUT BOTTOMED ON LANDING AND RIGHT BRAKE FAILED.  ON INSPECTION, THE FITTING ON THE WHEEL CYL	INDER WAS FOUND CRACKED.  FURTHER INVESTIGATION FOUND WHEN STRUT WAS FULLY COMPRESSED, BRAKE LINE CONTACTED GEAR DOOR LI	NK ASSY.  PN 35-815056-16 CAUSING FITTING ON BRAKE CYL TO FAIL.  SUBMITTER SUGGESTS INSPECTING ALL 58 SERIES ACFT WITH C	LEVELAND 30-93 BRAKES FOR CLEARANCE BETWEEN DOOR LINK ASSY AND BRAKE LINE WITH STRUT COMPRESSED AT EACH INSPECTION.			1	L	7	2 	3O				A23CE   					 
1997011600851	19970116	00851	CE  	1997	1	16	97ZZZX357        	1	19961127	G	3233	169380060	ACTUATOR        	GERDES      		BEECH 	23    	B24R        	1151253	CE  										LT MLG	FAILED          	B			BVMR	O	A			OTHER                   	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			EA	07	9196S	8915 			0493	MC370				FIFTEEN MINUTES INTO FLIGHT PILOT HEARD LOUD BANG, NOTED GEAR DOWN AND LOCKED.  UNABLE TO RETRACT GEAR.  AFTER AN UNEVEN	TFUL LANDING, AIRCRAFT TURNED OVER TO MAINTENANCE.  INSP FOUND NO HYDRAULIC LEAKS.  GEAR WOULD NOT RETRACT.  FOUND LEFT 	GEAR ACTUATOR'S PISTON BROKEN OFF INSIDE ACTUATOR ALLOWING FLUID TO CIRCULATE WITH NO PRESSURE.  AIRCRAFT USED FOR FLIGH	T TRAINING.  GEAR CYCLED OFTEN.			1	L	7	1 	3O				A1CE    					 
1997011600852	19970116	00852	EA  	1997	1	16	97ZZZX358        	2	19961204	G	7414	M3548	ROTOR           	SLICK       	4370        	CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  					RT MAG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	193SP	201  			95060109	17276346	RL3460236A			PERFORMED NORMAL RUN-UP PROCEDURES AND FOUND RIGHT MAG INOP.  DISASSEMBLED MAG AND FOUND ROTOR GEAR AND END OF ROTORSHAF	T LOOSE IN MAG.  POSSIBLE DEFECTIVE ROTOR MANUFACTURE OR MACHINING OF SLOT FOR CAM.					1	H	7	1 	3O	3	O	NT	3A12    	E286				 
1997011600853	19970116	00853	CE  	1997	1	16	97ZZZX359        	1	19961216	G	7921	652541	NUT             			CESSNA	206   	TU206G      	2073357	CE  										OIL COOLER STUD	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	199F	1006 				U20606137				NUT IS CRACKED (BROKEN) AND FOUND IN THE BOTTOM OF COWLING. CAUSED OIL LEAK.						1	H	7	1 	3O				A4CE    					 
1997011600854	19970116	00854	CE  	1997	1	16	97ZZZX360        	1	19961218	G	2430		CIRCUIT BREAKER 			BEECH 	58    	58          	1152740	CE  										DC SYSTEM	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SO	03	258TJ	4629 				TH988				TOTAL LOSS OF DC POWER 10 MINUTES INTO FLIGHT.  REPAIRED INOPERATIVE BATTERIES.  REPAIRED INOPERATIVE ALTERNATOR FIELD C	IRCUIT BREAKER.  REPLACED.  (CAUSE - CORROSION).					1	L	7	2 	3O				3A16    					 
1997011600855	19970116	00855	CE  	1997	1	16	97ZZZX361        	1	19961112	G	2910	51011199	LINE            			CESSNA	402   	402C        	207590R	CE  										INBD WING	LEAKS           	I				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	05	3249M	10728				402C0296				FLIGHT CREW NOTICED HYD LEAKAGE INBD WING.  INSPECTION NOTED PIN HOLE IN LINE AT HYD FLOW SWITCH AREA.  REPLACED LINE AN	D SERVICED SYSTEM.  DETERIORATION OF LINE WAS CAUSE FOR LEAKAGE.  SUBMITTER RECOMMENDS PRESSURE TESTS CONTINUE, BUT PREV	ENTIVE MAINT SHOULD BE CONSIDERED (16 YEAR OLD PART.)				1	L	7	2 	3O				A7CE    					 
1997011600856	19970116	00856	SO  	1997	1	16	97ZZZX362        	2	19961218	G	8540	632018	DRIVE GEAR      			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					ALT DRIVE	BOLTS FAILED    	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	03	4675S	656  	656  			TH689	298719R			PILOT REPORTED LOW OIL PRESSURE, AND ALTERNATOR INOP.  FOLLOWED MM FOR OIL PRESSURE RELIEF VALVE AND FOUND METAL.  REMOV	ED ALTERNATOR AND FOUND GEAR, FACE, ALTERNATOR DRIVE BOLTS HAD SHEARED.					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997011600857	19970116	00857	EA  	1997	1	16	97ZZZX363        	2	19961230	G	7414	1038255514	MAGNETO         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					LT-RT MAG	COIL CRACKED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	738YY		861  		19844K	17270353	L24576T			INSP FOUND LT AND RT COILS CRACKED.  LT AND RT BREAKERS BURNED, LT AND RT ROTORS BURNED AND DISTRIBUTER BLOCK BURNED POS	TS.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997011600858	19970116	00858	SO  	1997	1	16	97ZZZX364        	2	19961201	G	8550	AM207835AO	SEPARATOR       	AIRMAZE     		CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					AIR OIL STEP	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	726RT	416  			4F13	421C0087	604196			ENGINE OIL PUMPING OVERBOARD.  FOUND OIL AIR SEPARATOR INTERNAL SCREEN (SMALL) FAILED AND WAS BLOCKING OIL RETURN TO CRA	NKCASE.  ENGINE DAMAGE AT THIS TIME UNKNOWN.  SEPARATOR INSTALLED 411 HRS AGO NEW.  ONLY SERVICES WET VACUUM PUMP.  WENT	 TO DRY PUMP.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997011600859	19970116	00859	GL  	1997	1	16	97ZZZX365        	3	19961105	G	6110	3807	PROP ASSY       													HARTZL	HCC2Y	HCC2YR4     	GL  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1048 	358  					DN921		INSPECTION FOUND PROP ASSY P/N 3807 CORRODED.																5	C	P920	 
1997011600860	19970116	00860	NE  	1997	1	16	97ZZZX366        	3	19961105	G	6110	51171	PROP ASSY       			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5420 						HJ297		INSP FOUND PROP ASSY P/N 5117-1 CORRODED.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997011600861	19970116	00861	GL  	1997	1	16	97ZZZX367        	3	19961105	G	6110	2421	PROP ASSY       			MOONEY	M20   	M20E        	5870212	SW  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CA132		INSP FOUND PROP ASSY P/N 2421 CORRODED.						1	L	7	1 	3O				2A3     		5	C	P920	 
1997011600862	19970116	00862	GL  	1997	1	16	97ZZZX368        	3	19961105	G	6110	24281	CYLINDER        			PIPER 	PA28  	PA28R201T   	7102813	SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	PROP ASSY	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AM2596		INSP FOUND PROP ASSY CYLINDER P/N 2428-1 WORN.						1	L	7	1 	3O				2A13    		5	C	P920	 
1997011600863	19970116	00863	GL  	1997	1	16	97ZZZX369        	3	19961105	G	6110	2421	PROP ASSY       			PIPER 	PA28  	PA28R201T   	7102813	SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AM2596		INSP FOUND PROP ASSY P/N 2421 CORRODED.						1	L	7	1 	3O				2A13    		5	C	P920	 
1997011600864	19970116	00864	GL  	1997	1	16	97ZZZX370        	3	19961105	G	6111		BLADE           			MOONEY	M20   	M20         	5870202	SW  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	DAMAGED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1829 	288  		F93576			AW1974		INSP FOUND PROP BLADE WITH IMPACT DAMAGE.						1	L	7	1 	3O				2A3     		5	C	P920	 
1997011600865	19970116	00865	GL  	1997	1	16	97ZZZX371        	3	19961105	G	6111		BLADE           			MOONEY	M20   	M20         	5870202	SW  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	DAMAGED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1829 	288  		F94306			AW1974		INSP FOUND PROP BLADE WITH IMPACT DAMAGE.						1	L	7	1 	3O				2A3     		5	C	P920	 
1997011600866	19970116	00866	GL  	1997	1	16	97ZZZX372        	3	19961105	G	6110	3064	PROP ASSY       			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9815 	1746 					BU5621		INSP FOUND PROP ASSY P/N 3064 CRACKED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997011600867	19970116	00867	GL  	1997	1	16	97ZZZX373        	3	19961105	G	6110	3475A2	PROP ASSY       			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9815 	1746 					BU5621		INSP FOUND PROP ASSY P/N 3475A-2 CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997082800025	19970828	00025	SW  	1997	8	28	97ZZZX3732       	1	19960921	G	6230	206040576103	BEARING         			BELL  	206   	206L1       	1182107	SW  										M/R MAST	PITTED          	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			AL	03	600CK	830  				45787				AFTER THE THIRD CHIP LIGHT, THE MAST WAS REMOVED FOR INSPECTION.  ON INSPECTION OF THE BEARING, THE OUTER RACE WAS FOUND	 PITTED.  BEARING S/N ZV-1423.					1	G	7	1 	3U				H2SW    					 
1997082800059	19970828	00059	SO  	1997	8	28	97ZZZX3739       	2	19961231	G	8530		STUD            			PIPER 	PA28  	PA28201T    	7102819	SO  	CONT  	O360  	TSIO360F    	17025	SO  					ROCKER SHAFT	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SW	01	40437		350  			28R7703304	305289			AS A RESULT OF AN ACCIDENT, FOLLOW-UP INVESTIGATION REVEALED THE ENGINE LOST POWER DUE TO FAILURE OF THE ROCKER ARM SHAF	T HOLD-DOWN STUDS ON NR 2 CYLINDER.  AD 92-04-09 WAS C/W.  THE CYLINDER WAS AN EXCHANGE INSTALLED AT THE LAST OVERHAUL. 	 STUDS FAILED MOST LIKELY DUE TO OVERTORQUING.  THE HISTORY OF THE CYLINDER ASSEMBLY IS UNKNOWN.  SUBMITTER RECOMMENDATI	ON, MANDATORY STUD REPLACEMENT AT OVERHAUL.			1	L	7	1 	3O	3	O		2A13    	E9CE				 
1997011600868	19970116	00868	CE  	1997	1	16	97ZZZX374        	1	19961217	G	5610	1013840257	WINDSCREEN      			BEECH 	200   	200BEECH    	1152920	CE  										LT PILOT	CRACKED         	B			CWQR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	05	202KA	2489 			89043H2107	BB272				AT FL 22,000 IN ICING CONDITIONS, OUTER PANE OF LEFT PILOT POSITION WINDSCREEN CRACKED, DUE TO ANTI-ICE ELEMENT ANOMALY,	 WHICH CAUSED A TEMPERATURE DIFFERENTIAL.  ABOUT 80 EACH INSTANTANEOUS CRACKS OCCURRED.  FLIGHT DISCONTINUED.  REPLACED 	WINDSCREEN WITH NEW.				1	L	7	2 	4T				A24CE   					 
1997011600869	19970116	00869	NE  	1997	1	16	97ZZZX375        	2	19961216	G	7320	124KDC01005P	EEC             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       		NE  					LT ENG	FAILED          	C		A		O				OTHER                   				J	X		WARNING INDICATION        	ENGINE FLAMEOUT           		CL	CLIMB          	1			CE	05	8271	325  	325  			066	252			DURING INITIAL CLIMB, AT 15,500 FEET, THE LT ENGINE AMBER COMPUTER LIGHT ILLUMINATED.  FIFTEEN SECONDS LATER THE LT ENGI	NE FLAMED OUT.  TWO RESTART ATTEMPTS WERE UNSUCCESSFUL.  INVESTIGATION REVEALED A BLEED AIR CLAMP HAD COME OFF ALLOWING 	BLEED AIR TO FLOW INTO THE NACELLE.  TEAR DOWN OF THE FADEC FOUND THERMAL FUSES (110 DEGREES CELCIUS) IN BOTH CHANNELS H	AD OPENED WHICH CAUSED ENGINE TO SHUT DOWN.			2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
1997011600870	19970116	00870	GL  	1997	1	16	97ZZZX376        	3	19961105	G	6111	T101738	BLADE           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9815 	1746 		C94159			BU5621		INSP FOUND PROP ASSY P/N T10173-8 BLADE BELOW MINIMUM SPECS.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997011600871	19970116	00871	GL  	1997	1	16	97ZZZX377        	3	19961105	G	6111	T101738	BLADE           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	BELOW SPEC      	B			EY2R	D				RETURN TO BLOCK         				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9815 	1746 		C87412			BU5621		INSP FOUND PROP ASSY P/N T10173-8 BLADE BELOW MINIMUM SPECS.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997011600872	19970116	00872	GL  	1997	1	16	97ZZZX378        	3	19961105	G	6111	F84772	BLADE           			PIPER 	PA32  	PA32260     	7103206	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					C58495			CH9554		INSP FOUND PROP ASSY P/N F8477-2 BLADE BELOW MINIMUM SPECS.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1997011600873	19970116	00873	GL  	1997	1	16	97ZZZX379        	3	19961105	G	6111	F84772	BLADE           			PIPER 	PA32  	PA32260     	7103206	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					C58894			CH9554		INSP FOUND PROP ASSY P/N F8477-2 BLADE BELOW MINIMUM SPECS.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1997011600874	19970116	00874	GL  	1997	1	16	97ZZZX380        	3	19961105	G	6110	806	PROP ASSY       			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82X	HC82XK1     	GL  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4516 						143G		INSP FOUND PROP ASSY P/N 806 CORRODED.						1	L	7	1 	3O				1A15    		5	C	P878	 
1997011600875	19970116	00875	GL  	1997	1	16	97ZZZX381        	3	19961105	G	6110	8382	PROP ASSY       			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82X	HC82XK1     	GL  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4516 						143G		INSP FOUND PROP ASSY P/N 838-2 CORRODED.						1	L	7	1 	3O				1A15    		5	C	P878	 
1997011600876	19970116	00876	GL  	1997	1	16	97ZZZX382        	3	19961105	G	6110	14B	PROP ASSY       			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82X	HC82XK1     	GL  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4516 						143G		INSP FOUND PROP ASSY P/N 14B CORRODED.						1	L	7	1 	3O				1A15    		5	C	P878	 
1997011600877	19970116	00877	GL  	1997	1	16	97ZZZX383        	3	19961105	G	6110	5002	PROP ASSY       			PIPER 	PA28  	PA28R201T   	7102813	SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	PROP	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		764  	356  					AM1751		INSP FOUND PROP ASSY P/N 5002 CORRODED.						1	L	7	1 	3O				2A13    		5	C	P920	 
1997011600878	19970116	00878	GL  	1997	1	16	97ZZZX384        	3	19961105	G	6114	15941	HUB             			PIPER 	PA31  	PA31P350    	7103111	SO  						HARTZL	HCI3Y	HCI3YR2     	GL  	PROP ASSY	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								F5177A		INSP FOUND PROP ASSY P/N 1594-1 CORRODED.						1	L	7	2 	3O			RT	A8EA    		5	C	P33EA	 
1997011600880	19970116	00880	NE  	1997	1	16	97ZZZX386        	3	19961105	G	6110	5133	PROP ASSY       			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROP	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5420 						HJ297		INSP FOUND PROP ASSY P/N 5133 CRACKED.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997012300327	19970123	00327	GL  	1997	1	23	97ZZZX399        	3	19960102	G	6111	57C083867	CLAMP           													HARTZL	HCB3T	HCB3TN3     	GL  	PROP BLADE	CRACKED         	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23			245  		CC4782			BU13301		BLADE CLAMP FOUND CRACKED 2 INCHES STARTING AT COUNTERWEIGHT DOWEL PIN HOLE.																6	C	P15EA	 
1997010900097	19970109	00097	CE  	1997	1	9	97ZZZX4          	1	19961203	G	5741	AN823EA	BOLT            			CESSNA	182   	182B        	2072706	CE  										RT WING SPAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	2405G	4863 				51705				FOUND THE RT WING SPAR BOLT HEAD CORRODED DURING INSPECTION.  AFTER REMOVAL SHANK ALSO CORRODED.  SUBMITTER RECOMMENDS L	IBERAL POLICY OF REPLACING HARDWARE ON OLD AIRCAFT WHEN CORROSION IS SHOWING.					1	H	7	1 	3O			NT	3A13    					 
1997012300328	19970123	00328	EU  	1997	1	23	97ZZZX400        	1	19961220	G	2701	L13401Z1	CONTROL BRIDGE  			LET   	L13   	L13BLANIK   	1360306	EU  										CONTROL STICK	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	99950					025823				DURING ANNUAL INSPECTION, FOUND BRACKET CRACKED AT REAR CONTROL STICK ATTACHMENT ON THE CONTROL BRIDGE PART.  FAILURE OF	 PART IN THIS AREA WOULD CAUSE LOSS OF AILERON AND ELEVATOR CONTROL.					1	K	0	0 					G24EU   					 
1997012300332	19970123	00332	NM  	1997	1	23	97ZZZX404        	1	19961210	G	2430	A7807	TERMINAL        			ROBSIN	R22   	R22BETA     	7640110	NM  										BATTERY B+ LUG	BROKEN          	D	S	A		A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SW	05	40419	2785 				1617				FLAT TERMINAL ON B+ BATTERY POST BROKE IN-FLIGHT CAUSING A TOTAL ELECTRICAL FAILURE INCLUDING ROTOR AND ENGINE TACHS.						1	G	7	1 	3O			 	H10WE   					 
1997012300334	19970123	00334	SW  	1997	1	23	97ZZZX406        	1	19961216	G	5302		TAIL BOOM       			BELL  	222   	222B        	1182124	SW  										BS 219.40	CRACKED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	911RA					47150				PILOT FOUND CRACK ON PRE-FLIGHT CHECK.  CRACK WAS FOUND ON RIGHT HAND SIDE OF TAIL BOOM FORWARD OF HORIZ STAB AT BSTA 21	9.40, WL 75.  CRACK RUNS FORE AND AFT AND IS 1.25 INCHES LONG.  A/C TOTAL TIME 2353.8.  THIS CRACK IS FORWARD OF PREVIOU	S REPAIR FOR A VERTICAL CRACK AT BSTA 232, WL 75.				1	G	7	2 	3U				H9SW    					 
1997012300335	19970123	00335	EU  	1997	1	23	97ZZZX407        	1	19961223	G	6320	4638304001	SUN GEAR        			BOLKMS	105   	BO105S      	5626006	EU  										MR GR BOX	DEFECTIVE       	B			EOPR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	01										RECEIVED 2 EACH NEW SUN GEARS S/N'S 1389 AND 1368.  PERFORMED MAGNAFLUX INSPECTION ON GEARS DUE TO COMPANY POLICY.  BOTH	 FOUND TO HAVE DEFECT INDICATIONS.  VISUAL INSPECTION REVEALED NOTHING.  RETURNED TO MANUFACTURER FOR EVALUATION.					1	G	7	2 	3U				H3EU    					 
1997012300338	19970123	00338	EA  	1997	1	23	97ZZZX408        	2	19961226	G	8540	76327	GEAR            			BELL  	47    	47G5        	1181032	SW  	LYC   	O435  	VO435B1A    	41516	EA  					ACCSORY DRIVE	FAILED          	G		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			AG	AGRICULTURE    	1			GL	27	7925J		425  			25041	RL380031			DURING SPRAY RUN WHEN CROSSING THE FENCE, THE ENGINE BACKFIRED AND QUIT.  THE HELICOPTER TRAVELED APPROX 150 FEET IN THE	 AIR BEFORE THE SKIDS CONTACTED THE GROUND, SKIPPED 75 FEET AND STRUCK A SMALL HILL WHICH BROKE THE SKID AND THE TAIL BO	OM AND TAIL ROTOR.  THE ACFT CAME TO REST FACING THE OPPOSITE DIRECTION.  TEAR DOWN INSP OF ENGINE REVEALED THAT THE ACC	ESSORY DRIVE GEAR HAD FAILED DUE TO SIX BOLTS SHEARED AND THREE DOWELS FELL OUT OF PLACE.  SUBMITTER STATES ONLY THE VO-	435-B1A ENGINE HAS THIS GEAR ASSY, AND THIS ACCIDENT WOULD MAKE THE THIRD OCCURRENCE THAT HAD BEEN REPORTED TO THE FAA S	INCE MARCH 1996.	1	G	7	1 	3O	3	O		2H3     	E279				 
1997013000004	19970130	00004	SO  	1997	1	30	97ZZZX415        	2	19961220	G	8530	653191D	GASKET          								CONT  	O470  	O470*       	17026	SO  					VALVE COVER	DETERIORATED    	D				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			SW	07		2    								UPON USING A NEW SERIES VALVE COVER GASKET 653191D, FOUND THAT ALL OF THE GASKETS RECEIVED FROM THE VENDOR LEAKED.  ALL 	OF THE GASKETS WERE FOUND TO DEVELOP AN AREA WHERE THE GASKET WAS LITERALLY FALLING APART.  THERE DID NOT APPEAR TO BE A	NY LONG FIBER MATERIAL IN THE FAILED SEGMENTS THAT WOULD PROVIDE A COHESIVE PRODUCT.  THE SEGMENTS WOULD TOTALLY COLLAPS	E WITH FINGER PRESSURE.  SUBMITTER STATED THERE IS ENOUGH EVIDENCE TO SHOW THAT QUALITY CONTROL WAS NOT MAINTAINED DURIN	G MANUFACTURE OF THESE GASKETS.							3	O			E273				 
1997013000005	19970130	00005	SO  	1997	1	30	97ZZZX416        	1	19961210	G	2820	412306	LINE            			PIPER 	PA31  	PA31310     	7103103	SO  										RT WING FUEL	LEAKING         	B		A	VT3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	09	16TR	5326 				317812088				FUEL STAINS FOUND ON BOTTOM OF RIGHT WING, NEAR WING ROOT.  FURTHER INSPECTION REVEALED LEAKING FUEL LINE IN RIGHT WING 	ROOT AREA.  NOTE THAT THE CURE DATE ON THE FUEL LINE WAS THE THIRD QTR OF 1977.  REPLACED DEFECTIVE FUEL LINE WITH A NEW	 ONE AND TESTED IT WITH PUMP ON.  NEW LINE IS GOOD.  RECOMMEND CLOSER AND MORE FREQUENT INSPECTION OF THESE FUEL LINES.				1	L	7	1 	3O			RT	A20SO   					 
1997013000006	19970130	00006		1997	1	30	97ZZZX417        	4	19961209	G	6122	C29003GT23	HOUSING         			BEECH 	36    	A36         	1151604	CE  										GOV SPEED LEVER	CRACKED         	B			VT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	2531U	1436 			850573	E2301				DURING INVESTIGATION OF PROP RPM PROBLEM, IT WAS NOTED THE RPM INDICATION AT FULL THROTTLE WAS ONLY 2100 RPM.  GAINED AC	CESS TO THE GOVERNOR AND NOTED THE SPEED LEVER SHAFT WAS LOOSE AND THE END HOUSING CRACKED 360 DEGREES AROUND ITS BASE. 	 NOTE:  THIS HOUSING IS MADE OF PLASTIC.				1	L	7	1 	3O				3A15    					 
1997013000007	19970130	00007	SO  	1997	1	30	97ZZZX418        	1	19961223	G	5520	7170002	HINGE ASSY      			PIPER 	PA31  	PA31350     	7103110	SO  										RT OTBD ELEV	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3581C	1243 				318052091				SUBMITTER OPERATES TWO PIPER NAVAJO CHIEFTAIN AIRCRAFT DAILY DURING THE WORK WEEK AND FINDS THAT THE RT OUTBOARD ELEVATO	R HINGE ATTACHMENT TO THE HORIZ STAB IS AN AREA OF CONCERN DUE TO THE FREQUENCY OF THESE HINGES CRACKING.  FIND THESE HI	NGES ARE CRACKING IN THE AREAS OF THE BEND RADIUS OF THE HINGE MOUNTING FLANGES.  THESE HINGES ARE OF THE IMPROVED TYPE 	IAW WITH PIPER SB NR G87.  IT IS SUBMITTER'S OPINION THAT THESE HINGES BE MADE OF CAST MATERIAL OR CONSTRUCTED OF HEAVIE	R MATERIAL AND FIT IMPROVED.		1	L	7	2 	3O				A20SO   					 
1997013000009	19970130	00009	GL  	1997	1	30	97ZZZX419        	3	19961217	G	6111	A1851T	BEARING         		LT10282NB53R	MTSBSI	MU2   	MU2B60      	5780460	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP BLADES	DEFECTIVE       	B			RG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	429WM					1520SA		CDA3351		DEFECTIVE BLADE BEARINGS ON LT PROP.  1 BLADE STICKS IN ONE POSITION AND 2 BLADES ROUGH, FOUND DURING INSPECTION.  REPAI	RED BY HARTZELL, RETURNED AND SAME PROBLEM STILL EXISTS.  TSN 486.7 HUB.  TSN 946.0 BLADES.					1	H	7	2 	3T			RT	A10SW   		6	C	P40EA	 
1997013000010	19970130	00010	SO  	1997	1	30	97ZZZX420        	2	19961216	G	8520	35972	BOLT            								CONT  	O470  	O470R       	17026	SO  					CON ROD	NUT DEFECT      	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01							846403R4			DURING INSTALLATION AND TORQUE OF NEW CONTINENTAL P/N 35972 CON ROD BOLT, IT WAS FOUND NUT WAS DEFECTIVE.  NUT SLIPPED P	RIOR TO 39 FEET/POUNDS.  BOLT P/N 35972.  NUT P/N 626140.										3	O			E273				 
1997013000011	19970130	00011	NE  	1997	1	30	97ZZZX421        	2	19961201	G	8520		CAM             			BEECH 	18    	B18S        	1150806	CE  	PWA   	R985  	R985AN14B   	52008	NE  					NOSE CASE	RIVETS LOOSE    	B	L			A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	17			1020 							PILOT EXPERIENCED LOSS OF POWER AND MADE EMERGENCY LANDING.  FOUND VALVES NOT FUNCTIONING PROPERLY.  REMOVED PLUG IN NOS	E CASE.  INSP OF CAM RING FOUND RIVETS MISSING AND OTHERS LOOSE.  ALL 35 RIVETS WERE SHEARED AND ONLY 5 STILL THERE.					1	L	7	2 	3R	3	R		TC710   	5E1				 
1997013000012	19970130	00012	SO  	1997	1	30	97ZZZX422        	1	19961201	G	3246		WHEEL           			PIPER 	PA25  	PA25        	7102502	SO  										RT MLG	BOLTS SHEARED   	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6304Z	239  				25388				INSPECTION FOUND UPON REMOVAL OF RT MAIN GEAR WHEEL COVER, ONE OF THE THREE BOLTS THAT HOLD THE WHEEL HALVES TOGETHER WA	S SHEARED OFF.  THE NUT AND END OF THE BOLT WERE INSIDE THE WHEEL ENTRAPPED BY THE WHEEL COVER.  ACFT TT 4171.					1	L	7	1 	3O				2A10    					 
1997013000013	19970130	00013	EA  	1997	1	30	97ZZZX423        	1	19960501	G	3243		MASTER CYL      			SCWZER	G164  	G164A       	3952704	EA  										LT BRAKE	SCREWS FAILED   	D	L	A		K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17		4300 								AFTER LANDING, THE PILOT WAS TURNING THE AIRPLANE AROUND ON THE GROUND TO TAXI BACK FOR ANOTHER LOAD, WHEN THE LEFT BRAK	E PEDAL TIPPED FORWARD BEYOND THE NORMAL BRAKING ACTION AND SEEMED DISCONNECTED, AND THE BRAKE DID NOT WORK ANYMORE.  IN	SP FOUND THE THREE SCREWS THAT HOLD THE TOP OF THE BRAKE MASTER CYL IN PLACE HAD RIPPED OUT OF THE CYLINDER BASE, THUS, 	DISCONNECTING THE BRAKE MASTER CYLINDER.  THIS WILL ALSO AFFECT THE RUDDER OPERATION, AS THE PEDAL FLIPS FORWARD AND LIM	ITS THE RUDDER PEDAL TRAVEL.		1	Q	7	1 	3R				1A16    					 
1997013000014	19970130	00014	GL  	1997	1	30	97ZZZX424        	3	19961105	G	6111	S82NB6	BLADE           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					K73819YS			76870		INSPECTION FOUND PROPELLER BLADE BELOW MINIMUM.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000015	19970130	00015	GL  	1997	1	30	97ZZZX425        	3	19961105	G	6111	S82NB6	BLADE           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					F72048YS			776920		INSPECTION FOUND PROPELLER BLADE BELOW SPECS.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000016	19970130	00016	GL  	1997	1	30	97ZZZX426        	3	19961105	G	6111	S82NB6	BLADE           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					F72065YS			776920		INSPECTION FOUND PROPELLER BLADE BELOW SPECS.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000017	19970130	00017	GL  	1997	1	30	97ZZZX427        	3	19961105	G	6111	S82NB6	BLADE           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					F72066YS			776920		INSPECTION FOUND PROPELLER BLADE BELOW SPECS.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000018	19970130	00018	GL  	1997	1	30	97ZZZX428        	3	19961105	G	6110	A18996	PROP ASSY       			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								776920		INSPECTION FOUND PROPELLER ASSY CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000019	19970130	00019	GL  	1997	1	30	97ZZZX429        	3	19961105	G	6114	A4001	DOWEL PIN       			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								776920		INSPECTION FOUND PROPELLER ASSY DOWEL PIN CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000020	19970130	00020	GL  	1997	1	30	97ZZZX430        	3	19961105	G	6111	C4451	FERRULE         			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								776920		INSPECTION FOUND PROPELLER ASSY BLADE FERRULE DEFECTIVE.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000021	19970130	00021	GL  	1997	1	30	97ZZZX431        	3	19961105	G	6111	C4451	FERRULE         			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768730		INSPECTION FOUND PROPELLER BLADE FERRULE DEFECTIVE.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000022	19970130	00022	GL  	1997	1	30	97ZZZX432        	3	19961105	G	6110	A4191	PROP ASSY       			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768730		INSPECTION FOUND PROPELLER ASSY CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000023	19970130	00023	GL  	1997	1	30	97ZZZX433        	3	19961105	G	6110	A1896	PROP ASSY       			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768730		INSPECTION FOUND PROPELLER ASSY CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000024	19970130	00024	GL  	1997	1	30	97ZZZX434        	3	19961105	G	6111	S82NB6	BLADE           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					K73820YS			768730		INSPECTION FOUND PROPELLER BLADE BELOW MINIMUM.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000025	19970130	00025	GL  	1997	1	30	97ZZZX435        	3	19961105	G	6111	S82NB6	BLADE           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER	BELOW SPEC      	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					K74310YS			768730		INSPECTION FOUND PROPELLER BLADE BELOW MINIMUM.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997013000145	19970130	00145	SO  	1997	1	30	97ZZZX440        	2	19961217	G	7314	6462121	PUMP            			CESSNA	210   	210D        	2073414	CE  	CONT  	O520  	IO520A      	17032	SO  					ENG FUEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3908Y	1150 				21058408	112585R			PILOT REPORTED THAT ENGINE WOULD NOT RUN BELOW 1500 RPM ON START DUE TO FUEL PUMP INTERNAL FAILURE.						1	H	7	1 	3O	3	O		3A21    	E5CE				 
1997013000146	19970130	00146	SO  	1997	1	30	97ZZZX441        	2	19961231	G	7414	10357586	DISTRIBUTOR GEAR		101630203   	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					LT MAG	STRIPPED        	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			NE	01	406BK	1966 			D0690101ER	402C0807	278289			AFTER TAKEOFF, THE RIGHT ENGINE STARTED RUNNING ROUGH.  PILOT RECEIVED CLEARANCE TO LAND.  AFTER LANDING, PILOT PERFORME	D MAG CHECK TAXIING BACK TO GATE.  LEFT MAG WAS DEAD.  MECHANIC CHANGED MAGNETO, TIMED TO ENGINE, RAN UP GOOD.  ON DISAS	SEMBLY OF MAG, FOUND DISTRIBUTOR GEAR MISSING 5 TEETH.  GEAR WAS INSTALLED 6 YEARS AGO.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997013000147	19970130	00147	SO  	1997	1	30	97ZZZX442        	1	19961201	G	5712	78475005	RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  										RT WS 49.25	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	40724					28R7435116				DURING C/W AD 95 20-07 (SIDE BRACE STUD INSPECTION), IT WAS DISCOVERED THAT THE ADJACENT RIB (WS 49.25) WAS CRACKED IN T	HE LOWER PORTION OF THE RADIUS FOR THE FORWARD FLANGE.  THE SIDE BRACE STUD BRACKET ASSEMBLY MOUNTS ON TOP OF THE RIB FL	ANGE MAKING INSPECTION OF THIS AREA IMPOSSIBLE WITH THE SIDE BRACE STUD BRACKET ASSEMBLY INSTALLED.  THIS CONDITION WAS 	FOUND ON BOTH WINGS.  THE CRACKS START AT THE BOTTOM EDGE OF THE FLANGE RADIUS AND EXTEND UPWARD APPROXIMATELY ONE INCH.			1	L	7	1 	3O				2A13    					 
1997013000148	19970130	00148	SO  	1997	1	30	97ZZZX443        	1	19961201	G	5712	78475005	RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  										LT WS 49.25	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	40724					28R7435116				DURING C/W AD 95 20-07 (SIDE BRACE STUD INSPECTION), IT WAS DISCOVERED THAT THE ADJACENT RIB (WS 49.25) WAS CRACKED IN T	HE LOWER PORTION OF THE RADIUS FOR THE FORWARD FLANGE.  THE SIDE BRACE STUD BRACKET ASSEMBLY MOUNTS ON TOP OF THE RIB FL	ANGE MAKING INSPECTION OF THIS AREA IMPOSSIBLE WITH THE SIDE BRACE STUD BRACKET ASSEMBLY INSTALLED.  THIS CONDITION WAS 	FOUND ON BOTH WINGS.  THE CRACKS START AT THE BOTTOM EDGE OF THE FLANGE RADIUS AND EXTEND UPWARD APPROXIMATELY ONE INCH.			1	L	7	1 	3O				2A13    					 
1997013000151	19970130	00151	SO  	1997	1	30	97ZZZX446        	1	19961223	G	2140	B304090D381	HEATER          	JANITROL    		PIPER 	PA34  	PA34200T    	7103406	SO  										BURNER CAN	CRACKED         	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4490F	1483 			7781395	347670339				HEATER FAILED P.D.T. PER AD 96-20-07.  BURNER CAN CRACKED.  TSOH TRACKED VIA AIRCRAFT FLIGHT TIME = (2966 HRS) (DIVIDED 	BY 2) = 1483 HRS ON HEATER.					1	L	7	2 	3O				A7SO    					 
1997013000152	19970130	00152	EA  	1997	1	30	97ZZZX447        	2	19961124	G	8520		CONNECT ROD     			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					NR 4 CYL	FAILED          	D				A				UNSCHED LANDING         				E	K	R	VIBRATION/BUFFET          	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	CR	CRUISE         	1			NM	01	4830T					28R7235119	L2307251A			AIRCRAFT WAS FLYING 5 MILES NW OF OGD WHEN PILOT REPORTED SUDDEN OIL PRESSURE DROP.  UPON INSPECTION AFTER LANDING, THE 	ENGINE CASE WAS FOUND CRACKED.  AFTER REMOVING CYLINDERS FOUND THAT NR 4 CONNECTING ROD WAS BROKE OFF AT THE CAP.  IT IS	 UNKNOWN WHETHER THIS HAPPENED BEFORE OR AFTER OIL PRESSURE LOSS.				1	L	7	1 	3O	3	O		2A13    	1E10				 
1997013000154	19970130	00154	SO  	1997	1	30	97ZZZX449        	1	19961231	G	7810		STACK ASSY      			PIPER 	PA28  	PA28140     	7102802	SO  										NR 1 CYL EXH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	5677U	2346 				2826474				STACK ASSY HAS HAIR-LINE FRACTURE ALONG WELD ATTACHING OVERLAY AT EXHAUST PORT FLANGE.						1	L	7	1 	3O				2A13    					 
1997102300432	19971023	00432	NM  	1997	10	23	97ZZZX4490       	1	19961205	G	3233	65B105059	SUPPORT FITTING 			BOEING	747   	747121      	1384871	NM  										LT BODY LG	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	747GE					19651				LEFT BODY LANDING GEAR ACTUATOR ATTACH FITTING ON THE STA 1480 BULKHEAD WAS FOUND TO HAVE THE INBOARD LUG OF THE FITTING	 CRACKED.  BOEING SM 747-53-2298 WAS NOT TERMINATED.					2	L	7	4 	4F				A20WE   					 
1997102300433	19971023	00433	NM  	1997	10	23	97ZZZX4491       	1	19961205	G	2730	936005009	ELEVATOR PCP    			BOEING	747   	747121      	1384871	NM  										LT INBD ELEVATOR	MALFUNCTION     	C	L	A		K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SW	99	747GE					19651				WHILE TROUBLESHOOTING FOR AN UNCOMMANDED AUTOPILOT PITCH UP WHEN THE FLAPS WERE RETRACTED FROM 1 TO ZERO, A DISCREPANCY 	WAS DISCOVERED IN THE LT INBOARD ELEVATOR POWER CONTROL PACKAGE.  WITH ALL HYDRUALIC POWER OFF TO THE TAIL AND CONTROL C	OLUMN IN THE FULL FORWARD POSITION, WHEN THE NR 3 AND NR 4 HYDRAULIC SYSTEMS WERE PLACED ON (ONE AT A TIME), THE LT INBO	ARD ELEVATOR WENT TO THE FULL DOWN POSITION RAPIDLY.  CHANGED ELEVATOR PCP AND FLIGHT TESTED OK.			2	L	7	4 	4F				A20WE   					 
1997013000155	19970130	00155	CE  	1997	1	30	97ZZZX450        	1	19961224	G	3246	16201700	WHEEL           	PARKERHANFIN	40135       	CESSNA	421   	421B        	2076014	CE  										RIM	CRACKED         	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	65AE					421B0953				THREE INCH LONG CRACK FOUND IN WHEEL RIM.						1	L	7	2 	3O				A7CE    					 
1997013000156	19970130	00156	SO  	1997	1	30	97ZZZX451        	1	19961231	G	3230	AN625	BOLT            			PIPER 	PA28  	PA28R201    	7102816	SO  										NLG DRAG LINK	MISINSTALLED    	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	78QB	1498 				28R7837308				BOTH NOSE GEAR UPPER DRAG LINKS TO ENGINE MOUNT BOLTS INSTALLED BACKWARDS.  WASHER STACK ARRANGEMENT INCORRECT ALSO PER 	PIPER CHEROKEE SERVICE MANUAL.					1	L	7	1 	3O				2A13    					 
1997013000158	19970130	00158	CE  	1997	1	30	97ZZZX453        	1	19961201	G	7160		VALVE           			CESSNA	172   	172N        	2072434	CE  										CARB HEAT	GASKET LOOSE    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9419E					17272255				CARB HEAT VALVE ASSY'S FELT BROKE FREE OF VALVE ASSY.  NOTICED DURING 100 HR INSP.  LOOSENED TO THE POINT OF POSSIBLE IN	GESTION IN THE INTAKE SYSTEM.					1	H	7	1 	3O			NT	3A12    					 
1997013000159	19970130	00159	CE  	1997	1	30	97ZZZX454        	1	19961231	G	2822	41400015	PUMP            	DUKES       		CESSNA	185   	A185F       	2072821	CE  										CASTING SEAM	LEAK            	B	L	A	CF4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	9452N		409  		32100	18504359				DURING ANNUAL INSPECTION, FOUND FUEL STAIN/WEEPING ON AUX FUEL BOOST PUMP HEAD.  UPON INVESTIGATION, FOUND HEAD TO BE WE	EPING AT A CASTING SEAM ON HEAD IN A VISABLE LINE ABOUT .25 INCH LONG.  SUSPECT FLAW IN CASTING SEAM.  REPLACED PUMP WIT	H ZERO TIME OVERHAUL.  CESSNA P/N C291504-0201.				1	H	7	1 	3O				3A24    					 
1997013000160	19970130	00160	CE  	1997	1	30	97ZZZX455        	1	19961114	G	3411	S10711	TUBE            			CESSNA	172   	172P        	2072436	CE  										PITOT	MELTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	97LP	6567 				17274398				DURING A 100 HOUR INSPECTION, DISCOVERED THAT THE TWO WIRES FOR THE PITOT HEAT HAD CONTACTED AND MELTED 90 PERCENT OF TH	E WAY THROUGH THE PITOT POLYETHYLENE TUBE.  MELTING OCCURRED ONE INCH ABOVE TUBE NUT ON TOP OF PITOT TUBE BODY.  RECOMME	NDATION:  ROUTE WIRES AWAY FROM TUBE TO PREVENT WIRES FROM MELTING TUBING.				1	H	7	1 	3O			NT	3A12    					 
1997013000167	19970130	00167	EU  	1997	1	30	97ZZZX462        	1	19961105	G	7603		BRACKET         			GROB  	G115  	G115C       	1660303	EU  										CABLE SUPPORT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	115AK	72   				82054C2				DURING ACCEPTANCE INSPECTION ON NEW GROB AIRCRAFT WITH 72.2 HOURS SINCE NEW, FOUND THROTTLE CABLE SUPPORT BRACKET THAT A	TTACHES TO CARBURETOR CRACKED AT LOWER CARBURETOR MOUNT.  CRACK IS ATTRIBUTED TO PROPELLER/ENGINE VIBRATION.  BOTH ENGIN	E AND PROPELLER HAVE 72.2 HOURS SINCE NEW.  DYNAMIC BALANCE TO BE ACCOMPLISHED NEXT TO REMEDY CRACKING.				1	L	7	1 	3O			NT	A57EU   					 
1997013000168	19970130	00168	NE  	1997	1	30	97ZZZX463        	3	19961202	G	6111	SFA13M1R0A	BLADE           	HAMSTD      												HAMSTD	14SF	14SF5       	NE  	PIN BOSS	CRACKED         	B			H2SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13		14397	8397 							BLADE WAS RECEIVED FOR A MAJOR INSPECTION.  DURING DYE CHECK OF THE BLADE SHANK AS REQUIRED DURING MI, TWO LINEAR INDICA	TIONS WERE FOUND AND VERIFIED WITH FLUORESCENT PENETRANT INSPECTION.  BOTH INDICATIONS WERE ON THE BLADE PIN BOSS AREA. 	ONE IS ON THE THRUST WASHER SURFACE AND IS APPROXIMATELY .1875 INCH IN LENGTH.  THE OTHER INDICATION IS JUST BELOW THE T	HRUST WASHER SURFACE AND IS APPROXIMATELY .2187 INCH IN LENGTH.  THESE INDICATIONS ARE LOCATED APPROXIMATELY 90 DEGREES 	IN RESPECT TO EACH OTHER.												6	C	P7NE	 
1997013000231	19970130	00231	GL  	1997	1	30	97ZZZX480        	2	19961104	G	7530	23001804	TUBE            		23005367    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					BLEED VALVE	LEAK            	H				K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			SO	11	911SA				FF27824	45383	860170			AIRCRAFT EXPERIENCED TRANSIENT OVER TEMP.  HOT SECTION INSPECTION C/W, NO DAMAGE NOTED FROM OCCURRENCE.  SUSPECT CAUSE I	S AIR LEAK AT BLEED VALVE PR LINE.  LEAK CHECK MUST BE DONE WITH BLEED CONTROL SOLENOID IN OPEN POSITION.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997013000232	19970130	00232	CE  	1997	1	30	97ZZZX481        	1	19960106	G	2434	26012717	DRIVE           		C6115050201 	CESSNA	208   	208B        	2073701	CE  										STDBY ALTERNATOR	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	17	762FE	351  			258	208B0255				PILOT REPORTED WHILE EN ROUTE, STAND-BY POWER OFF LIGHT ILLUMINATED.  THE STAND-BY ALTERNATOR POWER WAS CHECKED AND STAN	D-BY POWER DID NOT COME ON LINE.  MAINTENANCE WAS DISPATCHED TO THE AIRCRAFT AND CONFRIMED STAND-BY POWER FAILURE.  THE 	STAND-BY ALTERNATOR SYSTEM WAS INSPECTED AND FOUND THE ALTERNATOR DRIVE SHAFT FAILED AT THE SHEAR POINT.  THE STAND-BY A	LTERNATOR DRIVE ASSEMBLY WAS REPLACED AND THE STAND-BY POWER SYSTEM WAS FUNCTIONALLY CHECKED AND NO DISCREPANCIES WERE F	OUND.  THE AIRCRAFT WAS RETURNED TO SERVICE.		1	H	7	1 	3T				A37CE   					 
1997013000233	19970130	00233	CE  	1997	1	30	97ZZZX482        	1	19961218	G	3230	084012515	PUSH PULL ROD   			CESSNA	310   	310R        	2074245	CE  										LT MLG	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	6102X	6218 				310R1269				DURING AN OPS NR 1 INSP, FOUND THE LT MLG PUSH/PULL ROD LOOSE AT ROD END.  DURING GEAR RETRACTION TO GAIN ACCESS TO PART	 FOR REPLACEMEN, TOTAL FAILURE OF THE ROD END OCCURRED CAUSING LOSS OF MOVEMENT OF THE LEFT MAIN GEAR ASSY TO THE UP OR 	DOWNLOCK POSITION.  SUBMITTER RECOMMENDS CLOSE INSP OF THIS AND ALL OTHER GEAR RODS' LINKAGES AND BELLCRANKS DURING INSP	.  REF AD 76-13-07 WHICH APPLIES TO SOME 400 SERIES A/C.  THIS AD DOES NOT APPLY TO THE 310 WHICH HAS THE SAME STYLE GEA	R SYSTEM.  OTHER RECOMMENDATIONS ARE POSSIBLE LIFE LIMITS SET ON THIS AND OTHER RODS AND BELLCRANKS OF THE GEAR SYSTEM.		1	L	7	2 	3O				3A10    					 
1997013000242	19970130	00242	CE  	1997	1	30	97ZZZX487        	1	19961217	G	2460		SPLICE          			CESSNA	500   	560CESSNA   	2076750	CE  										FS 234	FAILED          	C	L	A		K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			GL	05	68881					560173				INVESTIGATION FOR COMPLETE POWER FAILURE OF FWD LT GALLEY, FOUND AN INADEQUATE SINGLE WIRE CRIMP AT FS 234.0 UNDER PANEL	 261AT.  IMPROPER GAUGE SPLICE CONNECTOR ALLOWED WIRE TO PULL FREE.					2	L	7	2 	4F			RT	A22CE   					 
1997120400508	19971204	00508	SW  	1997	12	4	97ZZZX4908       	1	19960924	G	6510	406040340101	DISC PAK        			BELL  	407   	407         		SW  										T/R DISC PAK	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				SCHEDULED INSPECTION, T/R DRIVE DISC FOUND CRACKED AND SCRATCHED.  REMOVED AND REPLACED.						1	G	7	1 	3U			O	H2SW    					 
1997013000338	19970130	00338	CE  	1997	1	30	97ZZZX491        	1	19961230	G	3260	426EN98	SWITCH          			LEAR  	25    	25B         	5170511	CE  										LT MLG SQUAT	FAILED          	B			L4JR	K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	03	627WS					170				THE LT MLG SQUAT SWITCH FAILED CAUSING THE THRUST REVERSERS NOT TO DEPLOY.						2	L	7	2 	4J				A10CE   					 
1997013000339	19970130	00339		1997	1	30	97ZZZX492        	4	19961127	G	2216	49A26	CAPSTAN         	SIGMATEK    	1C4691377   	GULSTM	690TP 	690B        	7630516	SW  										TRIM SERVO	MISINSTALLED    	B			B2PR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17	690NA				2339	11359				PILOT REPORTED A FRAYED CABLE IN AFT FUSELAGE.  THE CABLE FOR THE ELEVATOR TRIM WAS FRAYED AT ELECTRIC ELEVATOR TRIM SER	VO LOCATION.  CAUSE OF FRAYING WAS DUE TO AN IMPROPERLY INSTALLED CAPSTAN, P/N 49A26, ON THE SERVO ASSY WHICH CAUSED THE	 GROOVE IN THE CAPSTAN TO WEAR AND CABLE TO FRAY.  SUBMITTER RECOMMENDS INSPECTION OF CABLE AND CAPSTAN INSTALLATION TO 	ASSURE PROPER INSTALLATION.  SERVO, P/N 1C469-1-377, EDO-AIRE.  SERVO CHANGED ABOUT 6 MOS PRIOR TO MALFUNCTION.			1	H	7	2 	3T				2A4     					 
1997013000340	19970130	00340	SW  	1997	1	30	97ZZZX493        	1	19961127	G	2731	5000115091387	CONTROL CABLE   			GULSTM	690TP 	690B        	7630516	SW  										ELEV TRIM	FRAYED          	B			B2PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	690NA					11359				PILOT REPORTED A FRAYED CABLE IN AFT FUSELAGE.  THE CABLE FOR THE ELEVATOR TRIM WAS FRAYED AT ELECTRIC ELEVATOR TRIM SER	VO LOCATION.  CAUSE OF FRAYING WAS DUE TO AN IMPROPERLY INSTALLED CAPSTAN, P/N 49A26, ON THE SERVO ASSY WHICH CAUSED THE	 GROOVE IN THE CAPSTAN TO WEAR AND CABLE TO FRAY.  SUBMITTER RECOMMENDS INSPECTION OF CABLE AND CAPSTAN INSTALLATION TO 	ASSURE PROPER INSTALLATION.  SERVO, P/N 1C469-1-377, EDO-AIRE.  SERVO CHANGED ABOUT 6 MOS PRIOR TO MALFUNCTION.			1	H	7	2 	3T			 	2A4     					 
1997013000344	19970130	00344	SO  	1997	1	30	97ZZZX497        	1	19961219	G	5320	674202	STIFFENER       		7643600     	PIPER 	PA28  	PA28R201    	7102816	SO  										NLG WELL	MISSING         	B	L	A	UC2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	3420Q	2616 				28R7737054				INSP OF ACFT FOR NOSE WHEELWELL STRUCTURE DAMAGE DUE TO MISSING STIFFENER. (P/N 6747202). REF:  SL 832 DATED JAN 25, 197	8.  SUBMITTER SUGGESTS ONE TIME INSP OF PA28R201 ACFT FOR STIFFENER INSTALLATION.					1	L	7	1 	3O				2A13    					 
1997013000345	19970130	00345	NM  	1997	1	30	97ZZZX498        	1	19961226	G	2750		FLAP ARM        			CHRIS 	HUSKY 	A1          	221020X	NM  										WING BELLCRANK	BOLTS INCORRECT 	B		A	V2AR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	9622V	595  				1154				FLAP CABLE ATTACH BOLTS AT WING BELLCRANK FOUND  TO BE INSTALLED UPSIDE DOWN.  IPC SHOWS BOLTS INSTALLED HEAD UP.  NUT S	TRIKES ADJACENT RIB AT FLAPS DOWN POSITION.  NO RECORD OF FLAP MAINTENANCE IN A/C RECORDS.					1	H	7	1 	3O			NC	A22NM   					 
1997013000346	19970130	00346	CE  	1997	1	30	97ZZZX499        	1	19961231	G	2822	41400015	PUMP            			CESSNA	185   	A185F       	2072821	CE  										FUEL BOOST	LEAKING         	B	S		CF4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	9452N		409  		32100	18504359				DURING ANNUAL INSPECTION, FOUND FUEL STAIN/WEEPING ON AUX FUEL BOOST PUMP HEAD.  UPON INVESTIGATION, FOUND HEAD TO BE WE	EPING AT A CASTING SEAM ON HEAD, IN A VISABLE LINE ABOUT .25 INCH LONG.  SUSPECT FLAW IN CASTING SEAM.  REPLACED PUMP WI	TH ZERO TIME OVERHAUL.				1	H	7	1 	3O				3A24    					 
1997010900098	19970109	00098	SO  	1997	1	9	97ZZZX5          	2	19961213	G	8530		VALVE           			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470L       	17026	SO  					CYL INTAKE	LEAK            	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11	2467F					18051699	694745LR			CONTINENTAL CYLINDER ASSY PN 653443A13.  2 OUT OF 6 CYLINDERS HAD UNACCEPTABLE LEAKS FROM INTAKE VALVES.  ABOUT 1 DROP L	IQUID SOLVENT PER MINUTE WITH VALVE SPRINGS INSTALLED.  ALSO, VALVE GUIDES ARE HOURGLASS SHAPED.  ABOUT .002 INCH SMALLE	R IN CENTER THAN ON ENDS.  THESE ARE ALL OEM NEW PARTS.				1	H	7	1 	3O	3	O		5A6     	E273				 
1997013000347	19970130	00347	SW  	1997	1	30	97ZZZX500        	1	19961204	G	8010	301265AA	DIODE           		A1077V      	BELL  	206   	206L3       	1182108	SW  										BATTERY RELAY	FAILED          	D		A		K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	99	94WP	1741 				51360				WHILE ATTEMPTING A START THE PILOT REPORTS SMOKE.  INVESTIGATION FOUND THE FOLLOWING WIRES BURNT, P16A22, P17A22, AND P1	8A22N, ALONG WITH DIODE 30-126-5AA  (MM WIRING DIAGRAM NR 2CR1) FOUND DIODE ALLOWING CURRENT TO FLOW BOTH DIRECTIONS CRE	ATING A SHORT TO GROUND.  DIODE FAILED FOR UNKNOWN REASONS.				1	G	7	1 	3U				H2SW    					 
1997013000348	19970130	00348		1997	1	30	97ZZZX501        	4	19961216	G	3421	501120401	GYRO            			LEAR  	35    	35A         	5170602	CE  										COCKPIT VG	DEFECTIVE       	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	230R				1420	130				A VERTICAL GYRO WAS INSTALLED IN AIRCRAFT IN LATE AUGUST.  THIS UNIT FAILED IN LATE OCT AND SHOWED SIGNS OF BEING HOT IN	TERNALLY (CANNON PLUG RING HAD BLUED).  THIS UNIT HAD BEEN OVERHAULED IN JUNE '96.  WAS SENT A REPLACEMENT (OVERHAULED) 	GYRO.				2	L	7	2 	4F				A10CE   					 
1997013000349	19970130	00349		1997	1	30	97ZZZX502        	4	19961222	G	2562	AK450	ELT             			AMTR  	VANS  	RV6         	05608  	GL  										FUSELAGE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	961CP				4502256	23938				ON ACCIDENT SITE, ELT WAS REMOVED FROM FUSELAGE AND SWITCH WAS IN 'ARM'.  NO OUTPUT FROM TRANSMITTER ON 121.5 WAS DETECT	ED BY RADIO RECEIVERS AT ACCIDENT SITE.  WHEN ELT WAS SHAKEN FORE AND AFT IN THE PROPER IMPACT MOTION BY HAND AT SITE, N	OTHING WAS EMITTED ON 121.5.				1	L	7	1 	3O			NC	EXPA1L71					 
1997121100121	19971211	00121	NE  	1997	12	11	97ZZZX5036       	2	19960708	G	8520		STUD            			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985*       	52008	NE  					NR 1 CYLINDER	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	38938	98   				424	JP201806			NR 1 CYLINDER STUD DEFECTIVE.  THIS IS A COMMON PROBLEM TO THESE ENGINES.  THE BASIC PROBLEM HERE IS HOW THE AD READS. S	UBMITTER BELIEVES THERE IS A NEED TO REVISE THE WORDING.					1	H	7	1 	3R	3	R		A806    	5E1				 
1997013000432	19970130	00432	SO  	1997	1	30	97ZZZX504        	2	19961118	G	8520		CRANKSHAFT      			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	BROKEN          	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NM	01	2076S					21061043				ENGINE QUIT IN-FLIGHT AND IT WAS DISCOVERED THE CRANKSHAFT HAD BROKEN IN TWO PLACES, JUST AFT OF THE FWD THRUST BEARING.	  RESEARCH OF LOGS SHOWS THAT THE AIRCRAFT WAS BELLIED 891 HOURS PRIOR TO THE CRANKSHAFT BREAKAGE, AT WHICH POINT THE BE	LLY WAS REPAIRED, A NEW PROPELLER INSTALLED, AND NO TEAR DOWN INSPECTION OF THE ENGINE PERFORMED.  LUCKILY, NO ONE WAS I	NJURED DURING THE FORCED LANDING (IFR AT NIGHT), BUT THERE NEEDS TO BE A REGULATION REQUIRING A TEAR-DOWN INSPECTION OF 	AN ENGINE FOLLOWING A PROP STRIKE.  TCM BULLETIN M84-16 RECOMMENDS TEAR DOWN IF THE PROP HAS TO BE REMOVED FOR REPAIR, B	UT IS NOT REQUIRED.  A REQUIREMENT FOR TEAR DOWN BASED ON THIS RECOMMENDATION WOULD ELIMINATE THIS 'GREY AREA'.	1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997013000437	19970130	00437	SO  	1997	1	30	97ZZZX509        	1	19961216	G	5320	6252200	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  										LT WINDSHIELD	ERODED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	15488					287325078				BRACKET LOCATED ON LT SIDE OF WINDSHIELD, PILOT'S SIDE AT LOWER AFT CORNER.  YEARS OF LEAKING WINDSHIELDS IN CONJUNCTION	 WITH FOAM IN CONTACT WITH BRACKET.  RUSTY BRACKET ERODED TO ONE-HALF ORIGINAL WALL THICKNESS.  BOLT HEADS OF AN-3 BOLTS	 RUSTED AND REDUCED TO APPROXIMATELY .030 INCH IN WEIGHT.				1	L	7	1 	3O				2A13    					 
1997013000440	19970130	00440	SO  	1997	1	30	97ZZZX512        	1	19961211	G	2430	66616002	WIRE            			PIPER 	PA34  	PA34200T    	7103406	SO  										BATTERY	BURNED          	B		A	APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8107D					348070010				BRAIDED WIRE TYPE BATTERY CABLES LOOSE AT BATTERY TERMINALS, CAUSES SEVERE VOLTAGE FLUCTUATIONS AND FLIGHT INTERRUPTION.	  OPERATOR REPORTS NUMEROUS PROBLEMS WITH THIS TYPE CABLE.  EXTREMELY DANGEROUS CONDITIONS RESULT WHEN BRAIDING COMES UN	DONE AND BATTERY TERMINALS GET LOOSE.				1	L	7	2 	3O			 	A7SO    					 
1997013000441	19970130	00441	SO  	1997	1	30	97ZZZX513        	1	19961125	G	3230		LANDING GEAR    			PIPER 	PA34  	PA34200T    	7103406	SO  										MLG	MALFUNCTION     	B			APCR	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			NM	01	8107D					348070010				PILOT DEPARTED FIELD WITH SNOW ON TAXIWAYS AND RUNWAY.  LANDING GEAR FAILED TO FULLY RETRACT DUE TO BLOCKAGE BY CHUNKS O	F ICE AND SNOW.  SUBMITTER SUGGESTS P.O.H. REVISION TO PRECLUDE OPERATION OF THIS MODEL AIRCRAFT FROM FIELDS WITH ANY FO	RM OF ICE, SNOW, SLUSH.				1	L	7	2 	3O				A7SO    					 
1997013000444	19970130	00444	SO  	1997	1	30	97ZZZX516        	1	19960107	G	7714		TACHOMETER      			PIPER 	PA34  	PA34200T    	7103406	SO  										LT ENG RPM	DEFECTIVE       	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	30964	856  				347870233				WHEN THE AIRCRAFT TACHOMETER INDICATES 2,300 RPM, THE EXTERNAL CALIBRATED TACHOMETER SHOWED THE ACTUAL ENGINE RPM AT 2,4	40 RPM.  THIS MAY HAVE BEEN A LONG TIME PROBLEM AS THE ENGINE HAS BEEN TOP OVERHAULED AT LEAST TWICE IN 1546 HRS.					1	L	7	2 	3O				A7SO    					 
1997013000445	19970130	00445	SO  	1997	1	30	97ZZZX517        	1	19960107	G	7714		TACHOMETER      			PIPER 	PA34  	PA34200T    	7103406	SO  										RT ENG RPM	DEFECTIVE       	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	30964	1546 				347870233				WHEN THE AIRCRAFT TACHOMETER INDICATES 2,300 RPM, THE EXTERNAL CALIBRATED TACHOMETER SHOWED THE ACTUAL ENGINE RPM AT 2,4	60 RPM.  THIS MAY HAVE BEEN A LONG TERM PROBLEM AS THE ENGINE HAS BEEN TOP OVERHAULED TWICE IN 1546 HRS.					1	L	7	2 	3O				A7SO    					 
1997013000446	19970130	00446	CE  	1997	1	30	97ZZZX518        	1	19961201	G	2434	ALV8402	ALTERNATOR      			CESSNA	310   	310Q        	2074242	CE  										LT ENG	LOOSE TERMINAL  	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	6248Q				25839	310Q0746				ALTERNATOR'S LOOSE CONNECTION CAUSED TERMINAL TO ARC AND BURN, AND DISCONNECT.						1	L	7	2 	3O				3A10    					 
1997013000447	19970130	00447	NE  	1997	1	30	97ZZZX519        	2	19961015	G	8530	91532	CYLINDER        			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 7 ROCKER	CRACKED         	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	03	54229		865  			160B	13823			ENGINE LOST POWER IN-FLIGHT. INVESTIGATION REVEALED THAT THE EXHAUST ROCKER HOUSING WAS CRACKED ON THE NR 7 CYLINDER.						1	Q	7	1 	3R	3	R		1A16    	5E2				 
1997013000448	19970130	00448	NE  	1997	1	30	97ZZZX520        	2	19961201	G	8520	327626	CYLINDER        			CVAC  	340   	340CVAC     	242270A	WP  	PWA   	R2800 	CB16        	52026	NE  					NR 8 CYL	ROD FAILED      	B			DJSR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			GL	23	7813B					265	P32162			ON LEVEL FLIGHT AT 6,000 MSL, ENGINE BACKFIRED AND LOSS OF OIL PRESSURE.  ENGINE SHUT DOWN AND RETURN TO PTK.						2	L	7	2 	4R	4	R		6A6     	E264				 
1997013000453	19970130	00453	CE  	1997	1	30	97ZZZX525        	1	19960120	G	2130	2481172823	MOD VALVE       			LEAR  	35    	35A         	5170602	CE  										CABIN	WIRE SHORTED    	B			GG5R	B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	05	230R					130				WHILE ON A FLIGHT THE LEFT BLEED AIR SYSTEM WENT INTO EMERGENCY.  THE AIR IN EMERGENCY IS EXTREMELY HOT.  WHILE IN EMERG	ENCY, THE AIRCRAFT FILLED WITH THICK SMOKE AND EMERGENCY DESCENT WAS PERFORMED.  A LANDING WAS MADE WITHOUT INCIDENT.  I	NVESTIGATION FOUND PROBLEM OF THE AIRCRAFT GOING INTO EMERGENCY WAS CAUSED BY WIRING GOING TO MOD VALVE RELAY BRACKET (L	EFT) GOT AGAINST A LINE GOING TO WINDSHIELD HEAT SYSTEM.  THE SMOKE WAS CAUSED BY AN IMPROPERLY INSTALLED CARPET FROM A 	RECENT INTERIOR JOB BLOCKING HEAT DUCTS.		2	L	7	2 	4F				A10CE   					 
1997020600180	19970206	00180	SO  	1997	2	6	97ZZZX527        	1	19961129	G	5245	9956100	BEARING ASSY    			PIPER 	PA32  	PA32301     	7103207	SO  										AC COND DOOR	FAILED          	B		A	C7MR	A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			SO	11	8470P	2710 				328206010				BEARING ASSY BROKE CAUSING AIR CONDITIONER CONDENSOR DOOR TO DROP INTO THE AIRSTREAM.  THIS CAUSED HEAVY VIBRATION AND A	IRCRAFT BECAME HARD TO CONTROL.  PILOT LANDED AT NEAREST AIRPORT.  THIS HAS HAPPENED TWICE BEFORE ON THIS AIRCRAFT.  SUS	PECT IMPROPER DOOR RIGGING AS A FACTOR.				1	L	7	1 	3O				A3SO    					 
1997020600183	19970206	00183		1997	2	6	97ZZZX529        	4	19960118	G	3197		WIRE HARNESS    			CESSNA	650   	650         	2076802	CE  										CB PANEL ASSY	SHORTED         	B	L		GJQR	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			NM	01	39WP					6500039				RT HAND ENGINE FAN (N1) INDICATOR CIRCUIT BREAKER TRIPPED AND WILL NOT RESET.  FOUND WIRING HARNESS IN PILOT'S CIRCUIT B	REAKER PANEL ASSEMBLY CHAFING AND SHORTING TO GROUND.  THE CHAFED WIRES AT THE AURAL WARNING NR 1 AND WARNING LIGHTS NR 	1 CIRCUIT BREAKERS WERE FOUND TO BE CAUSED BY THE PANEL ASSEMBLY MOUNTING BRACKET AND ATTACHING HARDWARE.  REPLACED AFFE	CTED WIRING. REROUTED AND SECURED WIRING TO PRECLUDE ANY FURTHER PROBLEMS.			2	L	7	2 	4F			 	A9NM    					 
1997020600184	19970206	00184		1997	2	6	97ZZZX530        	4	19960118	G	3197		WIRE            			CESSNA	650   	650         	2076802	CE  										CB PANEL	CHAFED          	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	38WP					6500039				INSP OF CB PANEL ASSY FOLLOWING FINDING CHAFED WIRING ON ANOTHER CE 650, FOUND LIKE CONDITION ON THIS ACFT.  INSP CONDUC	TED AT CESSNA SERVICE CENTER SACRAMENTO, CA.					2	L	7	2 	4F			 	A9NM    					 
1997020600186	19970206	00186	CE  	1997	2	6	97ZZZX531        	1	19961203	G	5741		FITTING         			CESSNA	177   	177B        	2073708	CE  										LT WING ATTACH	LOOSE           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	13468	2609 	2609 			17702424				DURING ANNUAL INSPECTION, IT WAS DISCOVERED THAT THERE WAS MOVEMENT IN THE WING ATTACH FITTINGS WHERE ATTACH PIN ATTACHE	S WING TO FUSELAGE.  THE AMOUNT OF MOVEMENT WAS .0035 INCH BY MEASUREMENT.					1	H	7	1 	3O				A13CE   					 
1997020600189	19970206	00189		1997	2	6	97ZZZX534        	4	19961231	G	3414	S1470N8	INDICATOR       			CESSNA	150   	150D        	2071810	CE  										AIR SPEED	MISMARKED       	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	4191U					15060191				DURING ANNUAL INSP IT WAS FOUND A PIPER AIR SPEED IND WAS INSTALLED AND INCORRECTLY MARKED.  CESSNA AIR SPEED IND LOCATE	D AND INSTALLED.  FACTORY DATA FOR MARKINGS MATCHED OLDER INST.  TCD SHEET LISTS A DIFFERENT SET OF MARKINGS TO BE DISPL	AYED ON INST. UNIT SENT FOR CALIB.				1	H	7	1 	3O				3A19    					 
1997020600190	19970206	00190	EU  	1997	2	6	97ZZZX535        	1	19961119	G	3710	211CC	PUMP            	AIRBORNE    		SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										PNEU SYS	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	470SP	128  			6AM2159	456				PNEUMATIC PUMP INSTALLED ON AIRCRAFT 8-5-96 ALONG WITH NEW VACUUM FILTERS.  ON 11-15-96 AT 128.4 HOURS PUMP FAILED BY SE	IZING AND SHEERING DRIVE SHAFT.  PUMP WAS REPLACED WITH ANOTHER NEW UNIT WITH NO SYSTEM DEFECTS NOTED.  (NOTE ORIGINAL P	UMP REPLACED AT 1002 HOURS TIME IN SERVICE.).				1	L	7	1 	3O			RT	A51EU   					 
1997020600246	19970206	00246	NM  	1997	2	6	97ZZZX543        	1	19961220	G	5320		CHORD           			BOEING	727   	727227      	1384078	NM  										FS 950 STR 29R	CORRODED        	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	555PE	41912				20837				DURING D-CHECK INSPECTION, DISCOVERED CORROSION ON THE STA 950, STR 29R, BELLY SKIN.  A SECTION OF THE LOWER FRAME CHORD	 WAS TRIMMED AWAY AND REPAIR FILLERS/ANGLES WERE INSTALLED WET WITH SEALANT.  REPAIR ACCOMPLISHED IAW EVERGREEN AIR CENT	ER - ENGINEERING CHANGE REPAIR AUTHORIZATION NR N927TS-53-002-EAC.				2	L	7	3 	4F				A3WE    					 
1997020600391	19970206	00391	CE  	1997	2	6	97ZZZX547        	1	19960329	G	5711		CARRY THRU SPAR 			BEECH 	33    	F33A        	1151425	CE  										FUSELAGE	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5599P	6624 				CE1344				INSP FOUND CRACKS IN CARRY THRU STRUCTURE.  AD 95-0-03 NOT VALID BY SERIAL NUMBER.						1	L	7	1 	3O				3A15    					 
1997020600394	19970206	00394	SO  	1997	2	6	97ZZZX550        	1	19961126	G	3260		SWITCH          			PIPER 	PA44  	PA44180     	7104402	SO  										GEAR WARN	WORN            	B			DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	923ER	200  				4496010				SWITCH ACTUATOR IS CUTTING A GROOVE IN THROTTLE RAMPS.  AS IT WEARS, IT CHANGES WHEN THE GEAR HORN SOUNDS TO A POINT WHE	RE IT WILL NOT SOUND AT ALL.  WE MAINTAIN 5 NEW AIRCRAFT OF THIS TYPE.  ALL HAVE HAD GEAR WARNING PROBLEMS.  SUBMITTER R	ECOMMENDS CHANGING THROTTLE RAMP MATERIAL TO SOMETHING HARDER THAN ALUMINUM.				1	L	7	2 	3O				A19S0   					 
1997020600398	19970206	00398	EA  	1997	2	6	97ZZZX554        	1	19961126	G	5312		BULKHEAD        		269D82203   	SCWZER	269   	269D        	8059501	EA  										BELLCRANK PIVOT	CRACKED         	B	S	A	EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	330ST	870  	870  			0001				DURING A 100 HOUR INSPECTION A BULKHEAD CRACK WAS FOUND ON THE RIGHT SIDE OF THE LATERAL PITCH BELLCRANK.  THE MOVEMENT 	OF THE CYCLIC LT AND RT WILL FLEX THE BULKHEAD THAT THE BELLCRANK SUPPORT IS ATTACHED.  THE BELLCRANK NOW MOVES FROM SID	E TO SIDE WHILE FLEXING THE CRACKS.  AIRCRAFT TIME 870 HRS.  SUBMITTER RECOMMENDATION.  THE BULKHEAD SHOULD BE MADE OUT 	OF THICKER METAL AT LEAST .025 INCH.			1	G	7	1 	3U			0	4H12    					 
1997020600399	19970206	00399	EA  	1997	2	6	97ZZZX555        	1	19961126	G	5312		BULKHEAD        			SCWZER	269   	269D        	8059501	EA  										LT CYCLIC BRG	CRACKED         	B	S		EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	330ST	869  	869  			0001				DURING 100 HR INSPECTION A CRACK WAS FOUND ON THE FWD BULKHEAD WHERE THE CYCLIC BEARING SUPPORT ATTACHES.  MOVING CYCLIC	 FWD AND AFT YOU CAN SEE THIS LOWER LEFT CORNER FLEX, THE CRACK CAN ONLY BE SEEN FROM UNDER THE LEFT SEAT AREA.  AIRCRAF	T TIME 870 HRS.  SUBMITTER STATES NEEDS TO HAVE THICKER METAL IN THIS AREA.				1	G	7	1 	3U			0	4H12    					 
1997020600400	19970206	00400	EA  	1997	2	6	97ZZZX556        	1	19961203	G	6710		BRACKET         			SCWZER	269   	269D        	8059501	EA  										IDLER BELLCRANK	EARS CRACKED    	B	S	A	EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	330ST	870  				0001				INSP FOUND FWD MOUNTING EARS CRAKCED ALL THE WAY ACROSS TOP AND BOTTOM OF THE CYCLIC LATERAL PITCH IDLER BELLCRANK BRACK	ET.  TT 870 HRS.  LOCATED UNDER CENTER SEAT.					1	G	7	1 	3U			0	4H12    					 
1997020600401	19970206	00401	SO  	1997	2	6	97ZZZX557        	2	19961216	G	8530	6674	VALVE           			UNIVAR	415   	415C        	0420302	NM  	CONT  	C85   	C8512F      	17008	SO  					NR 1 CYL EXH	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	87226					399	71092			NR 1 CYLINDER SWALLOWED EXHAUST VALVE.  HEAD OF VALVE EMBEDDED IN PISTON.						1	L	7	1 	3O	3	O		A718    	E233				 
1997020600383	19970206	00383	SO  	1997	2	6	97ZZZX570        	1	19961202	G	2510	551599	HARNESS         			PIPER 	PA46  	PA46350P    		SO  										PILOT LT SEAT	REEL FAILED     	G	P	A		A				UNSCHED LANDING         				O			OTHER                     			LD	LANDING        	1			EA	13	394PM					4622153				DURING OFF-AIRPORT IMPACT WITH DAMAGE NOT CONSIDERED TO BE MAJOR, THE PILOT SHOULDER HARNESS INERTIA REEL DETACHED FROM 	ATTACH BRACKET.  PILOT DID RECEIVE HEAD INJURIES BY IMPACT ON THE DASH.					1	L	7	1 	3O			RT	A25SO   					 
1997020600545	19970206	00545		1997	2	6	97ZZZX581        	4	19961022	G	2565	23D182132	DISCHARGE VALVE 	AIRCRUISERS 	22D22901151 															SLIDE	SPRING MISSING  	B			ET3D	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01					206741281					DURING OVERHAUL OF ESCAPE SLIDE ASSEMBLY FOUND DISCHARGE VALVE MISSING ITS BALL SPRING P/N 504S0023.  CAUSE FOR CONDITIO	N IS DUE TO ASSEMBLY ERROR DURING LAST OVERHAUL OR VALVE SERVICING.  CONDITION AS STATED COULD HAVE RESULTED IN LOSS OF 	STORED GASSES FROM SLIDE'S INFLATION BOTTLE AND/OR HAD THE POTENTIAL FOR AN UNCOMMANDED INFLATION OF THE ESCAPE SLIDE AS	SEMBLY.  SUBMITTED BY B. F. GOODRICH AES SEATTLE SERVICE CENTER, REPAIR STATION NR ET3D487L.  ADDITIONAL DETAILS, SKETCH	ES, DRAWINGS OR COMPONENT OVERHAUL MANUAL SPECIFICATIONS ARE AVAILABLE UPON REQUEST.  BFG REF SO NR 201293.															 
1997020600547	19970206	00547	WP  	1997	2	6	97ZZZX583        	1	19961115	G	5400		BANJO FITTING   			DOUG  	DC10  	DC1015      	3022118	WP  										NR 2 ENGINE	DAMAGED         	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				NR 4 BANJO FITTING ON NR 2 ENGINE UPPER FWD HOLE SCRATCHED.  COINED AND STRESS RELIEVED AND REAMED HOLE PER S/B 5523.  I	NSTALLED REPAIR BUSHINGS PER DOUGLAS ACTION NR 314520.					2	L	7	3 	4F				A22WE   					 
1997020600548	19970206	00548	WP  	1997	2	6	97ZZZX584        	1	19961115	G	5320		DOUBLER         			DOUG  	DC10  	DC1015      	3022118	WP  										FS 555-575	CORRODED        	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				NOSE LANDING GEAR AREA STA 555-575 HAS POPPED RIVETS.  REMOVED RIVETS, FOUND EXFOLIATED INTERNAL DOUBLER.  REMOVED DOUBL	ER, FABRICATED DOUBLER IAW DOUGLAS ACTION NR 315097.  ALODINED AND PRIMED FILLER AND DOUBLER IAW DC 10 SRM 51-10-01 AND 	INSTALLED PER DOUGLAS ACTION NR 315097 AND DC10 SRM 51-41-01 AND SRM 51-31-01.				2	L	7	3 	4F				A22WE   					 
1997020600549	19970206	00549	WP  	1997	2	6	97ZZZX585        	1	19961115	G	5347		SEAT TRACK      			DOUG  	DC10  	DC1015      	3022118	WP  										FS 279 NR 3	CRACKED         	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				SEAT TRACK CRACKED AT STA 279, NR 3 TRACK.  REMOVED CRACKED SECTION OF TRACK.  INSTALLED NEW SECTION OF TRACK AND SPLICE	S IAW DC10 SRM'S 53-70-00, 51-21-01, AND 51-31-01.					2	L	7	3 	4F				A22WE   					 
1997020600550	19970206	00550	WP  	1997	2	6	97ZZZX586        	1	19961115	G	5347		SEAT TRACK      			DOUG  	DC10  	DC1015      	3022118	WP  										FS 899 NR 6	CRACKED         	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				SEAT TRACK NR 6 AT STA 899 HAS DAMAGED HOLE.  REMOVED AND REPLACED SEAT TRACK FROM STA 791-910, XS-25 IAW DC10 SRM 53-70	-00 VOL I, 51-00-00, 51-21-01, 51-31-01.					2	L	7	3 	4F				A22WE   					 
1997020600551	19970206	00551	WP  	1997	2	6	97ZZZX587        	1	19961115	G	5330		SKIN            			DOUG  	DC10  	DC1015      	3022118	WP  										FS 1850	CORRODED        	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				TEMPORARY REPAIR INSTALLED ON FUSELAGE OUTER SKIN AT STA 1850, LONGERON 31-32 RT.  REMOVED TEMP REPAIR, FABRICATED REPAI	R DOUBLERS IAW DC10 SRM 51-35-02 AND 53-20-00 VOL I AND INSTALLED PER DC10 SRM 51-31-01.					2	L	7	3 	4F				A22WE   					 
1997020600552	19970206	00552	WP  	1997	2	6	97ZZZX588        	1	19961115	G	5320		FLOOR SUPPORT   			DOUG  	DC10  	DC1015      	3022118	WP  										FS 879	CORRODED        	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				TEMPORARY REPAIR INSTALLED ON FLOOR SUPPORT STA 879 BETWEEN SEAT TRACKS 2 AND 3.  REMOVED AND REPLACED FLOOR SUPPORT IAW	 DC10 SRM 51-21-01 AND 51-31-01.					2	L	7	3 	4F				A22WE   					 
1997020600553	19970206	00553	WP  	1997	2	6	97ZZZX589        	1	19961115	G	5320		DOOR FRAME      			DOUG  	DC10  	DC1015      	3022118	WP  										CARGO DOOR	CORRODED        	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				TEMP REPAIR INSTALLED ON FWD CARGO DOOR FRAME Y-886 BETWEEN LONGERONS 40 AND 42R.  REMOVED TEMP REPAIR, FABRICATED AND I	NSTALLED PERMANENT REPAIR DOUBLERS IAW DC10 SRM 53-30-00, 51-21-01, 51-40-01 VOL I, AND 53-50-00.					2	L	7	3 	4F				A22WE   					 
1997020600554	19970206	00554	WP  	1997	2	6	97ZZZX590        	1	19961115	G	5320		T-ANGLE         			DOUG  	DC10  	DC1015      	3022118	WP  										FS 1079	CRACKED         	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				PASS COMP STA 1079 LONGERON 23-24 LT CRACKED T-ANGLE.  REMOVED SHEAR TIE.  STEPPED UP HOLE AT END OF CRACK IAW DC10 SRM 	52-10-00.  FABRICATED DOUBLERS IAW DC10 SRM 52-10-00 FIG 2 VOL I.  INSTALLED DOUBLERS IAW SRM 51-21-01 VOL II, 53-00-01 	FIG 2.				2	L	7	3 	4F				A22WE   					 
1997020600555	19970206	00555	WP  	1997	2	6	97ZZZX591        	1	19961115	G	5320		SUPPORT WEB     			DOUG  	DC10  	DC1015      	3022118	WP  										FS 330-394	CRACKED         	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				FLIGHT COMP FLOOR SUPPORT WEB CRACKED STA 330 AND 394 UNDER FLIGHT ENGINEER'S SEAT.  STOP DRILLED CRACK IAW DC10 SRM 53-	00-01.  FABRICATED DOUBLER AND INSTALLED IAW DC10 SRM 53-00-01, 51-21-01, 51-31-01.					2	L	7	3 	4F				A22WE   					 
1997020600559	19970206	00559	EU  	1997	2	6	97ZZZX594        	1	19960809	G	5350	J3081X9FT	SEAL STRIP      			BRAERO	DH125 	HS125700A   	4230170	EU  										WING TO FUSE	DEBONDED        	B			PCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	91CM	62   				NA0265				WING TO FUSELAGE RUBBER SEALING STRIPS BEGAN TO UNBOND AND PULL AWAY.  STRIPS WERE INSTALLED 5-7-96.  PILOT REPORTED THE	Y ARE A POST-FLIGHT ITEM AND WERE SECURE AT LAST PREVIOUS POST-FLIGHT.  SUSPECTED CAUSE OF FAILURE TO BE IMPROPER BONDIN	G OF RUBBER TO WING SURFACE.  RECOMMEND BETTER GLUING TECHNIQUE.				2	L	7	2 	4F				A3EU    					 
1997020600560	19970206	00560	WP  	1997	2	6	97ZZZX595        	1	19961115	G	5347		SEAT TRACK      			DOUG  	DC10  	DC1015      	3022118	WP  										FS 1844-2007	CORRODED        	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				STA 2007 ANGLE REPAIR HAS IMPROPER FASTENERS AND INSUFFICIENT AMOUNT OF FASTENERS INSTALLED AND SEAT TRACK IS CORRODED F	ROM STA 1844-2007.  REMOVED AND REPLACED SEAT TRACK IAW DC10 SRM 53-70-00 VOL 1.  INSTALLED CORRECT AMOUNT AND TYPE OF F	ASTENERS IN ANGLE REPAIR IAW DC10 SRM 51-35-01.				2	L	7	3 	4F				A22WE   					 
1997020600561	19970206	00561	WP  	1997	2	6	97ZZZX596        	1	19961115	G	5320		FLOOR SUPPORT   			DOUG  	DC10  	DC1015      	3022118	WP  										FS 475	CRACKED         	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				FLOOR SUPPORT STA 475 LT AND RT OF TRACK NR 2 CRACKED.  REMOVED AND FABRICATED NEW SUPPORT IAW DC10 SRM 51-30-01 VOL II.	  ALODINED AND PRIMED AND INSTALLED SUPPORT IAW DC10 SRM 51-21-01 AND 51-31-01 VOL II.					2	L	7	3 	4F				A22WE   					 
1997021300046	19970213	00046	EU  	1997	2	13	97ZZZX599        	1	19961104	G	7120		MOUNT           			GENAVI	F22B  	F22B        	3840101	EU  										ABOVE NLG STRUT	CRACKED         	B			BONR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	706LA	347  				003				DURING PRE-FLIGHT, STUDENT NOTICED ENGINE MOUNT CRACKED ABOVE NLG STRUT.  OPENED LT COWL AND FOUND MOUNT ALSO CRACKED BE	LOW LT LOWER CLUSTER WELD.  RECOMMEND MAKING MOUNT OUT OF HEAVIER MATERIAL.					1	L	7	1 	3O			NT	A75EU   					 
1997010900099	19970109	00099	CE  	1997	1	9	97ZZZX6          	1	19961213	G	2730	081308114	ROD ASSY        			CESSNA	310   	310R        	2074245	CE  										ELEV BOB WT	RUSTED          	B			AZVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	3687G	4224 				310R0893				ROD ASSY WHICH HOLDS ELEVATOR BOB WEIGHT FOUND RUSTED THROUGH.  APPEARS TO HAVE RUSTED FROM INSIDE TUBE AS WELL AS SURFA	CE RUST ON OUTSIDE.  HOLE COMPLETELY THROUGH WALL THICKNESS OF TUBE.					1	L	7	2 	3O				3A10    					 
1997021300052	19970213	00052	CE  	1997	2	13	97ZZZX605        	1	19961218	G	5541	04330106	SPAR            			CESSNA	150   	152         	2071835	CE  										RUDDER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	49158	838  				15281171				WHILE PERFORMING 100 HR INSP RUDDER SPAR FOUND WITH 4 CRACKS RADIATING FROM STAMPED HOLE NEAR UPPER HINGE BRACKET.						1	H	7	1 	3O			NT	3A19    					 
1997021300053	19970213	00053	CE  	1997	2	13	97ZZZX606        	1	19961226	G	2410		COUPLING        	LORD        		CESSNA	421   	421C        	2076016	CE  										ALTERNATOR	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	H		WARNING INDICATION        	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			GL	19	421HP	795  				421C0831				ON CLIMB-OUT THE RIGHT ALTERNATOR WENT OFF LINE.  SOON AFTER THE OIL PRESSURE STARTED TO DECREASE AND THE OIL TEMP START	ED TO INCREASE, THE PILOT FEATHERED THE RIGHT ENGINE AND LANDED AT NEXT AIRPORT.  INVESTIGATION REVEALED THAT THE ALTERN	ATOR HAD FAILED INTERNALLY AT THE DRIVE HUB ASSY, P/N 646655.  RED RUBBER MATERIAL DISINTEGRATED AND WENT INTO THE OIL P	AN AND WAS SUCKED INTO THE OIL SUMP PLUGGING THE SCREEN.			1	L	7	2 	3O				A7CE    					 
1997021300057	19970213	00057	WP  	1997	2	13	97ZZZX610        	1	19961115	G	5730		RETAIN RING     			DOUG  	DC10  	DC1015      	3022118	WP  										WS XORS 750	DAMAGED         	B			M2AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003L					48258				DAMAGED AND ELONGATED HOLE AT WING.  STA XORS 750 ON FUEL PLATE RETAINING RING STRUCTURE.  COLD WORKED HOLE PER DOUGLAS 	ACTION NR 312451.  FABRICATED AND INSTALLED BUSHING PER DOUGLAS ACTION NR 312451.  INSTALLED RUB STRIP IAW DC10 SRM 51-4	2-04.				2	L	7	3 	4F				A22WE   					 
1997021300060	19970213	00060		1997	2	13	97ZZZX613        	4	19960120	G	3442		POWER SUPPLY    			CESSNA	208   	208B        	2073701	CE  										WX RADAR	FAILED          	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SW	15	750FX	453  	453  			208B0511				PILOT REPORTED WHILE TAXIING ACFT, HEARD A LOUD 'POP' AND THE COCKPIT FILLED WITH ELECTRICAL SMOKE.  MAINT WAS DISPATCHE	D TO THE ACFT.  UPON ARRIVAL, FOUND NO SMOKE OR ELECTRICAL SMELL IN THE CABIN.  MX STARTED THE ACFT ENG AND ALL SYSTEMS,	 NO DISCREPANCIES NOTED.  REMOVED CIRCUIT BREAKER PANEL AND GAINED ACCESS TO CIRCUIT BREAKERS, BUSS BARS AND ASSOCIATED 	WIRING, INST PANEL SWITCHES, AND NO DISCREPANCIES NOTED.  TEST FLIGHT COULD NOT DUPLICATE THE PROBLEM.  IT WAS NOTED THE	 WEATHER RADAR INDICATOR WAS INTERMITTENT.  THE SYS WAS PROPERLY DEFERRED AND ACFT WAS RETURNED TO SERVICE.  UPON REPAIR	 OF THE WX RADAR INDICATOR IT WAS NOTED THE POWER SUPPLY WAS SHORTED.	1	H	7	1 	3T				A37CE   					 
1997010200641	19970102	00641	NE  	1997	1	2	97ZZZX6189       	3	19961211	G	6111	SFA13M10A	BLADE           													HAMSTD	14SF	14SF5       	NE  	SHANK	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05		8983 			8761645					INSPECTION FOUND BLADE SHANK CRACKED AT FILLET AREA.  BLADE RETURNED TO HAM STD FOR EVALUATION.																6	C	P7NE	 
1997021300066	19970213	00066	CE  	1997	2	13	97ZZZX619        	1	19960101	G	5330		SKIN            			MTSBSI	MU2   	MU2B36A     	5780413	CE  										FS 4610	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	994PE					714SA				PERFORMING 100 HR INSPECTION, DEFORMATION OF FUSELAGE SKIN WAS NOTED ABOVE BOTH MAIN GEAR ATTACH POINTS.  FURTHER INSP W	AS REQUIRED AND THE INTERIOR WALLS OF THE ACFT WERE REMOVED.  CRACKS WERE FOUND IN FUSELAGE FRAMES AT FS 4610, 4850, AND	 5605.  INSPECT AND REPAIR OF THIS AREA IS COVERED MITSUBISHI SB NR 073/53-002A, DATED 8-12-94.  THIS PARTICULAR ACFT HA	S DAMAGE IN THESE AREAS BEYOND THE APPROVED REPAIRABLE LIMITS IN THE SB.			1	H	7	2 	3T				A10SW   					 
1997010200642	19970102	00642	EA  	1997	1	2	97ZZZX6190       	2	19961201	G	8520	LW12186	BOLT            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					CON ROD	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	9545J					283693	L1040436A			ROD BOLT NUTS BACKED OFF AND CONNECTING ROD BOLTS BROKE.  SUSPECT CAUSE WAS IMPROPER INSTALLATION OF CONNECTING ROD BOLT	 NUTS.  RECOMMENDATION:  RE-VISIT OR RE-ISSUE LYCOMING SI NR 1106D, DATED 6-9-72.					1	L	7	1 	3O	3	O		2A13    	E286				 
1997010200643	19970102	00643	WP  	1997	1	2	97ZZZX6191       	2	19961113	G	7260	31030351	BEARING         		31036016    						GARRTT	TPE331	TPE33112UHR 		WP  					ASSORY GRBOX	FAILED          	B			AE0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03		689  			951991425009		P66362C			ENGINE RECEIVED FROM AIR CARRIER FOR THIS REPAIR.  REPAIR STA NOT SURE IF THERE WAS AN IN-FLIGHT SHUT DOWN OCCURRENCE. R	EPAIR OF ENGINE WAS TO REPLACE ACCESSORY GEAR ASSEMBLY WITH OVERHAULED UNIT OF SAME PART NUMBER, CONTAINING NEW 3103035-	1 BEARINGS.  THESE BEARINGS ARE LIFE LIMITED PARTS.  (CURRENTLY TIED TO OVERHAUL OR CAM INTERVAL).  ALLIED SIGNAL HAS IS	SUED A SB, TPE331-72-0997, THAT SUPERSEDES THE ACCESSORY GEAR ASSEMBLY WITH AN IMPROVED PART, USING LARGER BEARINGS.  RE	PAIR STA DID NOT INCORPORATE THIS SB, HOWEVER.							4	T			E4WE				 
1997010200644	19970102	00644	CE  	1997	1	2	97ZZZX6192       	1	19961127	G	7500	635404767	TUBE            			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RT ENG BLEED	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	229CJ	361  				5250129	1268			PILOT REPORTED RT ENG ITT PROBLEMS.  INSP FOUND RT ENG OUTB BLEED AIR TUBE BROKEN IN FLEX TUBE AREA.  REPLACED TUBE, OPS	 CHECK OK.					1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
1997010200645	19970102	00645	GL  	1997	1	2	97ZZZX6193       	3	19961105	G	6110	A4001	DOWEL PIN       			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753558		INSPECTION FOUND DOWEL PIN CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997010200646	19970102	00646	GL  	1997	1	2	97ZZZX6194       	3	19961105	G	6110	C3274	CYLINDER        			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROP	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753558		INSPECTION FOUND PROPELLER CYLINDER WORN.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997010200647	19970102	00647	GL  	1997	1	2	97ZZZX6195       	3	19961105	G	6114	A3267	BUSHING         			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	HUB	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753558		INSPECTION FOUND PROPELLER BUSHING WORN.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997010200648	19970102	00648	GL  	1997	1	2	97ZZZX6196       	3	19961105	G	6110	C3550	CYLINDER        			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 	1480 					746034		INSPECTION FOUND PROP CYLINDER CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200649	19970102	00649	GL  	1997	1	2	97ZZZX6197       	3	19961105	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 	1480 					746034		INSPECTION FOUND HUB ASSY DEFECTIVE (WRONG APLICATION).						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200650	19970102	00650	GL  	1997	1	2	97ZZZX6198       	3	19961105	G	6110	A1896	PROP ASSY       			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 						771292		INSPECTION FOUND PROP ASSY P/N A1896 CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200651	19970102	00651	GL  	1997	1	2	97ZZZX6199       	3	19961105	G	6110	A4191	PROP ASSY       			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 						771292		INSPECTION FOUND PROP ASSY P/N A4191 CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200652	19970102	00652	GL  	1997	1	2	97ZZZX6200       	3	19961105	G	6110	D3474	PROP ASSY       			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 						771292		INSPECTION FOUND PRO ASSY P/N D3474 WORN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200653	19970102	00653	GL  	1997	1	2	97ZZZX6201       	3	19961105	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	DAMAGED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 			F73000YS			771292		INSPECTION FOUND PROP BLADE DAMAGED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200654	19970102	00654	GL  	1997	1	2	97ZZZX6202       	3	19961105	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 1 SOCKET	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791322		INSPECTION FOUND NR 1 BLADE SOCKET CRACKED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200655	19970102	00655	GL  	1997	1	2	97ZZZX6203       	3	19961105	G	6114	D7015C87	HUB             			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1229 						673758		INSPECTION FOUND PROP HUB CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200656	19970102	00656	GL  	1997	1	2	97ZZZX6204       	3	19961105	G	6111	C4451	FERRULE         			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1229 						673758		INSPECTION FOUND BLADE FERRULE CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200657	19970102	00657	GL  	1997	1	2	97ZZZX6205       	3	19961105	G	6114	B4459	ACTUATOR PIN    			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		696  						727378		INSPECTION FOUND ACTUATOR PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200658	19970102	00658	GL  	1997	1	2	97ZZZX6206       	3	19961105	G	6110	B3490	PROP ASSY       			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		696  						727378		INSPECTION FOUND PROP ASSY CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200659	19970102	00659	GL  	1997	1	2	97ZZZX6207       	3	19961105	G	6110	C3550	CYLINDER        			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		696  						727378		INSPECTION FOUND PROP CYLINDER CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200660	19970102	00660	GL  	1997	1	2	97ZZZX6208       	3	19961105	G	6110	A1896	PROP ASSY       			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		696  						727378		INSPECTION FOUND PROP ASSY CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200661	19970102	00661	GL  	1997	1	2	97ZZZX6209       	3	19961105	G	6110	A4191	PROP ASSY       			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		696  						727378		INSPECTION FOUND PROP ASSY CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200662	19970102	00662	GL  	1997	1	2	97ZZZX6210       	3	19961105	G	6111	S82NC4	BLADE           			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		696  			BG397YS			727378		INSPECTION FOUND PROPELLER BLADE CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200663	19970102	00663	GL  	1997	1	2	97ZZZX6211       	3	19961105	G	6111	C4451	FERRULE         			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	DEFECTIVE       	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		696  						727378		INSPECTION FOUND PROP BLADE FERRULE CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200664	19970102	00664	GL  	1997	1	2	97ZZZX6212       	3	19961105	G	6110	A1896	PROP ASSY       			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 	1480 					746034		INSPECTION FOUND PROP ASSY CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200665	19970102	00665	GL  	1997	1	2	97ZZZX6213       	3	19961105	G	6110	A4191	PROP ASSY       			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 	1480 					746034		INSPECTION FOUND PROP ASSY CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997010200666	19970102	00666	GL  	1997	1	2	97ZZZX6214       	3	19961105	G	6110	B2345	PISTON ROD      			CESSNA	182   	182R        	2072731	CE  						MCAULY	2D34C	B2D34C219   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7910786		PROPELLER INSPECTION FOUND PISTON ROD CORRODED.						1	L	7	1 	3O			NT	3A13    		5	C	P7EA	 
1997010200667	19970102	00667		1997	1	2	97ZZZX6215       	4	19961105	G	6113	C5046	BULKHEAD        			CESSNA	182   	182R        	2072731	CE  						MCAULY	2D34C	B2D34C219   	GL  	SPINNER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7910786		INSPECTION FOUND PROPELLER SPINNER BULKHEAD CRACKED.						1	L	7	1 	3O			NT	3A13    		5	C	P7EA	 
1997010200668	19970102	00668	GL  	1997	1	2	97ZZZX6216       	3	19961105	G	6110	C2463	NUT             			BEECH 	36    	36BEECH     	1151602	CE  						MCAULY	2A36C	2A36C23     	GL  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								641006		INSPECTION FOUND PROPELLER RETAIN NUT CRACKED.						1	L	7	1 	3O				3A15    		5	C	P880	 
1997010200669	19970102	00669	GL  	1997	1	2	97ZZZX6217       	3	19961105	G	6110	B2345	PISTON ROD      			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER	WORN            	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								870628		INSPECTION FOUND PISTON ROD WORN.						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997010200670	19970102	00670	GL  	1997	1	2	97ZZZX6218       	3	19961105	G	6114	A4001	DOWEL PIN       			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								870628		PROPELLER INSPECTION FOUND DOWEL PIN CORRODED.						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997010200671	19970102	00671	GL  	1997	1	2	97ZZZX6219       	3	19961105	G	6111		BLADE           			BEECH 	33    	F33A        	1151425	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					K91889YS			781601		PROPELLER INSPECTION FOUND BLADE CORROSION.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997010200672	19970102	00672	GL  	1997	1	2	97ZZZX6220       	3	19961105	G	6111		BLADE           			BEECH 	33    	F33A        	1151425	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					K92027YS			781601		PROPELLER INSPECTION FOUND BLADE CORROSION.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997010200673	19970102	00673	GL  	1997	1	2	97ZZZX6221       	3	19961105	G	6111		BLADE           			BEECH 	33    	F33A        	1151425	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					K91828YS			781601		PROPELLER INSPECTION FOUND BLADE CORROSION.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997021300070	19970213	00070	CE  	1997	2	13	97ZZZX623        	1	19960120	G	3240	S288930103	LINE            		26820011    	CESSNA	208   	208B        	2073701	CE  										BRAKE CYL	COLLAPSED       	D		A		K				NONE                    				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			SW	15	886FE	3982 				208B0190				PILOT REPORTED UPON LANDING AND MAKING A HARD RIGHT TURN AND HARD BRAKING THE RIGHT BRAKE WOULD NOT RELEASE.  MAINT FOUN	D THE RIGHT BRAKE RELEASED.  UPON FURTHER INSPECTION, MAINT FOUND THE RIGHT BRAKE MASTER CYLINDER UPPER SUPPLY FLEXIBLE 	LINE COLLAPSED AT THE BEND RADIUS.				1	H	7	1 	3T				A37CE   					 
1997021300462	19970213	00462	WP  	1997	2	13	97ZZZX676        	1	19961223	G	5330	59363603	SKIN            			DOUG  	DC9   	DC983       	3022083	WP  										BS 817	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9420D	19271				49824				DURING C-CHECK INSPECTION, DISCOVERED EXFOLIATION CORROSION ON THE LOWER FUSELAGE KEEL BEAM EXTERNAL SKIN ALONG THE AREA	 OF CONTACT BETWEEN THE WING/BODY FAIRING.  THE CORRODED AREA IS LOCATED AT THE CENTER OF THE EXTERNAL KEEL BEAM SKIN SU	RFACE AT LONGERON 30L, 4.0 INCHES AFT OF BS 817.  BLENDED, NDT INSPECTED AND INSTALLED REPAIR DOUBLER.  ACCOMPLISHED IAW	 EVERGREEN AIR CENTER - ENGINEERING CHANGE/REPAIR AUTHORIZATION NR N9420-53-003-EAC.			2	L	7	2 	4F			RT	A6WE    					 
1997021300463	19970213	00463	WP  	1997	2	13	97ZZZX677        	1	19961223	G	5330	593666751	SKIN            			DOUG  	DC9   	DC983       	3022083	WP  										BS 1211-1231	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9420D	19271				49824				DURING C-CHECK INSPECTION, DISCOVERED EXFOLIATION CORROSION ON THE FUSELAGE SKIN AT STA 1211 - STA 1231, BETWEEN LONGERO	NS 29R AND 30R.  TRIMMED OUT DAMAGE, NDT INSPECTED AND INSTALLED REPAIR FILLERS AND DOUBLERS.  ACCOMPLISHED IAW EVERGREE	N AIR CENTER - ENGINEERING CHANGE/REPAIR AUTHORIZATION NR N9420-53-010-EAC.				2	L	7	2 	4F			RT	A6WE    					 
1997021300465	19970213	00465	CE  	1997	2	13	97ZZZX679        	1	19960607	G	2750	MS252015	SWITCH          			CESSNA	172   	172M        	2072418	CE  										FLAP	MALFUNCTION     	G	L	A		A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			NM	11	9594V					17264396				THE AIRPLANE CRASHED 18-19 SECONDS AFTER BECOMING AIRBORNE.  THE AIRCRAFT IMPACTED TERRAIN BEYOND THE DEPARTURE END OF T	HE RUNWAY.  FLAPS WERE FULLY DOWN AT THE ACCIDENT SCENE.  THE FLAP SWITCH WAS REMOVED AND SENT TO CESSNA FOR FUNCTIONAL 	TESTING.  THIS SWITCH INCORPORATES A 'SPRING-RETURN' MECHANISM TO RETURN IT TO NEUTRAL POSITION AFTER BEING RELEASED FRO	M THE EXTEND POSITION.  CESSNA REPORTED THAT THE SWITCH DEMONSTRATED PROPER ELECTRICAL FUNCTION, BUT IMPROPER MECHANICAL	 OPERATION (THE SWITCH DID NOT RETURN TO NEUTRAL WHEN RELEASED FROM EXTEND) 'DUE TO THE SPRING RETURN MECHANISM MALFUNCT	IONING'.	1	H	7	1 	3O			NT	3A12    					 
1997021300468	19970213	00468		1997	2	13	97ZZZX682        	1	19960916	G	3710	2B729	PUMP            	AIRBORNE    																VAC SYS	SHAFT WORN      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					6AC232					VAC PUMP ARMATURE SHAFT WORN.  PUMP MAY HAVE BEEN RUN DRY.																			 
1997021300472	19970213	00472	CE  	1997	2	13	97ZZZX686        	1	19961111	G	5712	05232332	RIB             			CESSNA	172   	172I        	2072426	CE  										RT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				FOUND SURFACE TRAILING EDGE RIB'S CORRODED THROUGH IN RT WING.  REPLACED PARTS WITH NEW CESSNA PARTS.  PARTS NOT PROTECT	EDY WITH PRIMER BY CESSNA.					1	H	7	1 	3O			NT	3A12    					 
1997021300473	19970213	00473	CE  	1997	2	13	97ZZZX687        	1	19961111	G	5511	053200150	RIB             			CESSNA	172   	172I        	2072426	CE  										HORIZ STAB	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				FOUND HEAVY INTERGRANULAR CORROSION IN HORIZONTAL STABILIZER NOSE RIBS.  REMOVED AND REPLACED PARTS.  AIRCRAFT WAS BASED	 IN CENTRAL FLORIDA.  PARTS HAD NO PRIMER PROTECTION AT TIME OF MANUFACTURE.					1	H	7	1 	3O			NT	3A12    					 
1997021300474	19970213	00474	CE  	1997	2	13	97ZZZX688        	1	19961111	G	5711	05230413	SPAR            			CESSNA	172   	172I        	2072426	CE  										LT WS 137-148	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				HEAVY SURFACE CORROSION ON AFT SPAR OF LT WING BETWEEN STA 148-137.  REMOVED AND REPLACED PART.  AIRCRAFT WAS BASED IN C	ENTRAL FLORIDA.  PART HAD NO PRIMER PROTECTION FROM FACTORY.					1	H	7	1 	3O			NT	3A12    					 
1997021300475	19970213	00475	CE  	1997	2	13	97ZZZX689        	1	19961111	G	5711	05230413	SPAR            			CESSNA	172   	172I        	2072426	CE  										WS 105	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				CORROSION ON AFT SPAR CHANNEL STA 105.  REMOVED AND REPLACED PART.  AIRCRAFT WAS BASED IN CENTRAL FLORIDA.  PARTS DID NO	T HAVE ANY PRIMER PROTECTION FROM FACTORY.					1	H	7	1 	3O			NT	3A12    					 
1997021300476	19970213	00476	CE  	1997	2	13	97ZZZX690        	1	19961111	G	5711	05230151	SPAR            			CESSNA	172   	172I        	2072426	CE  										LT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				HEAVY INTERGRANULAR CORROSION ON OUTBOARD SPAR CHANNEL LT WING.  RMEOVED ADN REPLACED PART.  AIRCRAFT BASED IN CENTRAL F	LORIDA.  WINGS DID NOT HAVE ANY PRIMER PROTECTION FROM FACTORY.					1	H	7	1 	3O			NT	3A12    					 
1997021300477	19970213	00477	CE  	1997	2	13	97ZZZX691        	1	19961111	G	2752	05226304	BRACKET         			CESSNA	172   	172I        	2072426	CE  										FLAP MOTOR	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				HEAVY INTERGRANULAR CORROSION FOUND ON LOWER FLAP MOTOR BRACKET AT BOLT HOLE.  REMOVED AND REPLACED PART.  AIRCRAFT WAS 	BASED IN CENTRAL FLORIDA.  PARTS WERE NOT PROTECTED WITH PRIMER AT TIME OF MANUFACTURE.					1	H	7	1 	3O			NT	3A12    					 
1997021300478	19970213	00478	CE  	1997	2	13	97ZZZX692        	1	19961111	G	5712	05235154	RIB             			CESSNA	172   	172I        	2072426	CE  										WS 190	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				NOSE RIB CORRODED THROUGH AT STA 190 OF LT WING.  AIRCRAFT WAS BASED IN FLORIDA WITH NO FACTORY PROTECTION OF PARTS INSI	DE OF WINGS.					1	H	7	1 	3O			NT	3A12    					 
1997021300479	19970213	00479	CE  	1997	2	13	97ZZZX693        	1	19961111	G	5720	05230142	CHANNEL         			CESSNA	172   	172I        	2072426	CE  										RT WS 26	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				FOUND RIVETS POPPED ON THE LEADING EDGE OF RT WING AT STA 26.  RMEOVED AND REPLACED PART.  AIRCRAFT WAS BASED IN CENTRAL	 FLORIDA.  PARTS WERE NOT PROTECTED WITH PRIMER AT TIME OF MANUFACTURE.					1	H	7	1 	3O			NT	3A12    					 
1997021300480	19970213	00480	CE  	1997	2	13	97ZZZX694        	1	19961111	G	5711	052302012	SPAR CAP        			CESSNA	172   	172I        	2072426	CE  										RT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				HEAVY INTERGRANULAR AND SURFACE CORROSION FOUND IN RT WING FWD SPAR CAP.  REMOVED AND PRELACED PART WITH NEW CESSNA PART	.  AIRCRAFT WAS BASED IN CENTRAL FLORIDA.  PARTS WERE NOT PROTECTED WITH PRIMER AT TIME OF MANUFACTURE.					1	H	7	1 	3O			NT	3A12    					 
1997021300481	19970213	00481	CE  	1997	2	13	97ZZZX695        	1	19961111	G	5711	05230142	SPAR CHANNEL    			CESSNA	172   	172I        	2072426	CE  										RT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				HEAVY INTERGRANULAR AND SURFACE CORROSION WAS FOUND ON FWD SPAR CHANNEL OF RT WING.  REMOVED AND REPLACED PART WITH NEW 	CESSNA PART.  AIRCRAFT WAS BASED IN CENTRAL FLORIDA.  NO PRIMER PROTECTION.					1	H	7	1 	3O			NT	3A12    					 
1997021300482	19970213	00482	CE  	1997	2	13	97ZZZX696        	1	19961111	G	5711	05230152	SPAR CHANNEL    			CESSNA	172   	172I        	2072426	CE  										RT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				HEAVY INTERGRANULAR AND SURFACE CORROSION WAS FOUND ON FWD SPAR CHANNEL OF RT WING.  REMOVED AND REPLACED SPAR CHANNEL W	ITH NEW CESSNA PART.  AIRCRAFT WAS BASED IN CENTRAL FLORIDA.  PARTS NOT PROTECTED WITH PRIMER BY CESSNA.					1	H	7	1 	3O			NT	3A12    					 
1997021300483	19970213	00483	CE  	1997	2	13	97ZZZX697        	1	19961111	G	5711	05111625	SPAR            			CESSNA	172   	172I        	2072426	CE  										FWD CABIN	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				DURING A PRELIMINARY INSPECTION ON THE AIRCRAFT, HEAVY INTERGRANULAR CORROSION WAS FOUND IN THE FWD CABIN SPAR.  PART WA	S REMOVED AND REPLACED.  AIRCRAFT WAS BASED IN CENTRAL FLORIDA.  NO PRIMER ON INTERNAL PARTS BY CESSNA.					1	H	7	1 	3O			NT	3A12    					 
1997021300484	19970213	00484	CE  	1997	2	13	97ZZZX698        	1	19961111	G	5711	051212478	SPAR            			CESSNA	172   	172I        	2072426	CE  										AFT CABIN	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	894	5154 				17257119				DURING A PRELIMINARY INSPECTION OF AIRCRAFT.  HEAVY INTERGRANULAR CORROSION WAS FOUND IN THE AFT CABIN SPAR HAT SECTION.	  PART WAS REMOVED AND REPLACED.  AIRCRAFT WAS BASED IN CENTRAL FLORIDA.  NO PRIMER PROTECTION NOTED.					1	H	7	1 	3O			NT	3A12    					 
1997021300485	19970213	00485	CE  	1997	2	13	97ZZZX699        	1	19961218	G	5712	05230271	RIB             			CESSNA	172   	172P        	2072436	CE  										LT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT WING.  INTERNAL PARTS WERE NOT PRIMED DURING MANUFACTURE.  RE	PLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND CESSNA DO LIKEWISE.					1	H	7	1 	3O			NT	3A12    					 
1997010900100	19970109	00100	CE  	1997	1	9	97ZZZX7          	1	19961216	G	3213	12414232	SADDLE          			CESSNA	210   	210D        	2073414	CE  										MLG	CRACKED         	B			FC6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	3815Y	1547 				21058315				INSPECTION FOUND LANDING GEAR SADDLE CRACKED AT ACTUATOR ATTACH.						1	H	7	1 	3O				3A21    					 
1997021300486	19970213	00486	CE  	1997	2	13	97ZZZX700        	1	19961218	G	5730	05230119	SKIN            			CESSNA	172   	172P        	2072436	CE  										LT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	67688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THIS WING ASSY.  THE INTERNAL PARTS OF WING WERE NOT PROTECTE	D FROM CORROSION DURING MANUFACTURE.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND CESSNA D	O LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300487	19970213	00487	CE  	1997	2	13	97ZZZX701        	1	19961218	G	5730	05230295	SKIN            			CESSNA	172   	172P        	2072436	CE  										LT WING LE	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT WING ASSEMBLY.  THE INTERNAL PARTS OF WING WERE NOT PROTECTED	 FROM THE DAMAGING EFFECTS OF CORROSION DURING MANUFACTURE.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIM	ER.  RECOMMEND CESSNA DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300488	19970213	00488	CE  	1997	2	13	97ZZZX702        	1	19961218	G	5730	052302825	SKIN            			CESSNA	172   	172P        	2072436	CE  										LT WING LE	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS THROUGHOUT WING ASSEMBLY.  THE INTERNAL PARTS OF WING WERE NOT PROTECTED 	FROM THE DAMAGING EFFECTS OF CORROSION DURING MANUFACTURE.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIME	R.  RECOMMEND CESSNA DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300489	19970213	00489	CE  	1997	2	13	97ZZZX703        	1	19961218	G	5730	05230118	SKIN            			CESSNA	172   	172P        	2072436	CE  										RT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT WING ASSEMBLY.  THE INTERNAL PARTS OF THE WING WERE NOT PROTE	CTED FROM THE DAMAGING EFFECTS OF CORROSION DURING MANUFACTURE.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY 	PRIMER.  RECOMMEND CESSNA DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300490	19970213	00490	CE  	1997	2	13	97ZZZX704        	1	19961218	G	5730	05230294	SKIN            			CESSNA	172   	172P        	2072436	CE  										RT WING LE	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION THROUGHOUT WING ASSEMBLY.  INTERNAL PARTS OF WING WERE NOT PROTECTED FROM THE DAMAGING E	FFECTS OF CORROSION DURING MANUFACTURE.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND CESSN	A DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300491	19970213	00491	CE  	1997	2	13	97ZZZX705        	1	19961218	G	5730	052302826	SKIN            			CESSNA	172   	172P        	2072436	CE  										RT WING LE	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION THROUGHOUT WING ASSEMBLY.  INTERNAL PARTS OF WING WERE NOT PROTECTED FROM THE DAMAGING E	FFECTS OF CORROSION DURING MANUFACTURE.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND THAT 	THE MANUFACTURE DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300492	19970213	00492	CE  	1997	2	13	97ZZZX706        	1	19961218	G	5712	05230273	RIB             			CESSNA	172   	172P        	2072436	CE  										RT WING NOSE	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY SURFACE CORROSION THROUGHOUT WING ASSEMBLY.  INTERNAL PARTS OF WING WERE NOT PROTECTED FROM THE DAMAGING EFF	ECTS OF CORROSION DURING MANUFACTURE.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND MANUFAC	TURE DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300493	19970213	00493	CE  	1997	2	13	97ZZZX707        	1	19961218	G	5522	DEV0550442	SKIN            			CESSNA	172   	172P        	2072436	CE  										ELEV	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE ELEV.  CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MAN	UFACTURE RESULTING IN AN UNSAFE CONDITION.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND CE	SSNA DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300494	19970213	00494	CE  	1997	2	13	97ZZZX708        	1	19961218	G	5520	052300129	CHANNEL         			CESSNA	172   	172P        	2072436	CE  										ELEV	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE ELEV.  CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MAN	UFACTURE RESULTING IN AN UNSAFE CONDITION.  REPLACED PART, CLEANED, TREATED AND PRIMED WITH EPOXY PRIMER.  RECOMMEND CES	SNA DO LIKEWISE				1	H	7	1 	3O			NT	3A12    					 
1997021300495	19970213	00495	CE  	1997	2	13	97ZZZX709        	1	19961223	G	5520	24320011	FAIRING         			CESSNA	172   	172P        	2072436	CE  										ELEV	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE ELEV.  CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MAN	UFACTURE RESULTING IN AN UNSAFE CONDITION.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND CE	SSNA DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300496	19970213	00496	CE  	1997	2	13	97ZZZX710        	1	19961218	G	5531	05310341	RIB             			CESSNA	172   	172P        	2072436	CE  										VERT STAB	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE VERT FIN.  CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING	 MANUFACTURE RESULTING IN AN UNSAFE CONDITION.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEN	D CESSNA DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300497	19970213	00497	CE  	1997	2	13	97ZZZX711        	1	19961218	G	5512	053200176	SKIN            			CESSNA	172   	172P        	2072436	CE  										HORIZ STAB LE	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION THROUGHOUT THE HORIZ STAB.  CESSNA DID NOT PROVIDE ANY CORROSION PROTECTION AT TIME OF M	ANUFACTURE.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND CESSNA DO LIKEWISE.					1	H	7	1 	3O			NT	3A12    					 
1997021300498	19970213	00498	CE  	1997	2	13	97ZZZX712        	1	19961218	G	5532	053100696	SKIN            			CESSNA	172   	172P        	2072436	CE  										VERT FIN LE	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE VERT FIN.  CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING	 MANUFACTURE RESULTING IN AN UNSAFE CONDITION.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEN	D CESSNA DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997021300499	19970213	00499	CE  	1997	2	13	97ZZZX713        	1	19961218	G	5522	DEV0550444	SKIN            			CESSNA	172   	172P        	2072436	CE  										ELEV	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	64688	5864 				17275609				FOUND HEAVY TO SEVERE CORROSION, POPPED RIVETS, THROUGHOUT THE ELEV.  CESSNA DID NOT PRIME ANY INTERNAL PARTS DURING MAN	UFACTURE RESULTING IN AN UNSAFE CONDITION.  REPLACED PART, CLEANED, TREATED, AND PRIMED WITH EPOXY PRIMER.  RECOMMEND CE	SSNA DO LIKEWISE.				1	H	7	1 	3O			NT	3A12    					 
1997022000124	19970220	00124	CE  	1997	2	20	97ZZZX751        	1	19961223	G	2752	HE6311	DRIVE ASSY      		505211531   	BEECH 	80    	65A80       	1152808	CE  										FLAP	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	134BA		21   		405191	LD202				SOMETHING WITHIN THE 90 DEGREE DRIVE ASSY FAILED WHICH MADE THE FLAP FAIL TO EXTEND OR RETRACT.  THE ACTUATOR WAS OH 20.	6 HRS AGO.					1	L	7	2 	3O				3A20    					 
1997022000131	19970220	00131		1997	2	20	97ZZZX758        	3	19961227	G	6112	RA12884	BOOT            	RAPCO       		BEECH 	80    	65A80       	1152808	CE  										PROP DEICE	LEAD BROKEN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	95LL					LD235				THE LEADS ARE BREAKING 12 INCHES FROM THE TERMINALS.  THE LEAD IS REQUIRED TO BEND IN THIS AREA.  SUBMITTER STATED THIS 	IS THE 10TH BOOT WHICH HAS FAILED IN THIS AREA IN THE LAST FIVE WEEKS.					1	L	7	2 	3O				3A20    					 
1997022000137	19970220	00137	EU  	1997	2	20	97ZZZX764        	1	19960226	G	2422	ASH6641PF	INVERTER        	LELAND      		BRAERO	DH125 	BAE125800A  	1500285	EU  										NR 1	FAILED          	H	L	A		O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	15										DURING GND. RUN WITH ENG.'S RUNNING AND AVIONICS POWER UP, CREW STARTED THE APU.  THE NR 1 INVERTER FLUCTUATED VIOLENTLY	 AND WAS SELECTED 'OFF'.  WHEN ATTEMPT WAS MADE TO REINSTATE NR 1 INVERTER, BOTH ALTIMETERS WENT TO 60,000 FEET AND STAY	ED THERE.  WHEN THE A/C WAS SHUT DOWN, SMOKE WAS COMING OUT OF THE REAR EQUIPMENT BAY.  SOURCE WAS FOUND TO BE THE NR 1 	INVERTER.  INVERTER AND BOTH ALTIMETERS WERE CHANGED.			2	L	7	2 	4F			RT	A3EU    					 
1997022000143	19970220	00143	WP  	1997	2	20	97ZZZX770        	2	19961105	G	7250	31010922	BEARING         		310331923   						GARRTT	TPE331	TPE33112UHR 		WP  					TURBINE AFT	FAILED          	B			DSCR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	25		6864 			P823		P70129			REAR TURBINE BEARING FAILED RESULTING IN MOVEMENT OF MAIN ROTATING GROUP.  SECONDARY DAMAGE INCLUDED SEVERE RUBBING OF A	LL ROTATING COMPONENTS DUE TO FREE MOVEMENT OF MAINSHAFT CAUSED BY BEARING FAILURE.  IMPACT DAMAGE ALSO AFFECTED EXHAUST	 GAS TEMPERATURE HARNESS.  BEARING FAILURE ALSO RESULTED IN OIL SYSTEM METAL CONTAMINATION.  PART TOTAL CYCLES, 7,084.									4	T			E4WE				 
1997022000144	19970220	00144	WP  	1997	2	20	97ZZZX771        	2	19961224	G	7250	31070852	SEAL            		31038393    						GARRTT	TPE331	TPE33112UHR 		WP  					1ST STG TURB	CRACKED         	B			DSCR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	25		10816			6180402135		P70046			SEAL CRACKED AT FLANGE.  SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST	 THE 1ST STAGE ROTOR ASSY.  INCREASED TENSION CAUSES CRACKING AT FLANGE.  THIS IS A CRITICAL LIFE-LIMITED COMPONENT.  LI	MIT 20,000 CYCLES.  PART TOTAL CYCLES, 12,410.									4	T			E4WE				 
1997022000145	19970220	00145	WP  	1997	2	20	97ZZZX772        	2	19961115	G	7250	31070852	SEAL            								GARRTT	TPE331	TPE33112UHR 		WP  					1ST STG TURB	CRACKED         	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25		10257					P70048			SEAL FOUND CRACKED AT SEALING FLANGE.  SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED SEAL TENSION	 AGAINST FIRST ROTOR ASSY.  INCREASED TENSION RESULTS IN CRACKING AT FLANGE.  PART IS A CRITICAL LIFE LIMITED ROTATING G	ROUP COMPONENT.  LIMIT 20,000 CYCLES.  PART TOTAL CYCLES, 10,462.									4	T			E4WE				 
1997022000149	19970220	00149	EU  	1997	2	20	97ZZZX776        	1	19961119	G	3710	4051	VALVE           			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										STANDBY VAC	MALFUNCTION     	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	470SP	268  				456				PRECISE FLIGHT STANDBY VACUUM SYSTEM FAILED TO OPERATE WHEN SELECTED.  SUBSEQUENT INSPECTION REVEALED ACTUATION CONTROL 	CABLE TO BE LIMITED IN TRAVEL DUE TO INTERFERENCE WITH CONTROL VALVE LEVER.  PREVIOUS EXPERIENCES WITH INSTALLING THIS S	YSTEM HAVE FOUND THIS AREA TO BE TROUBLESOME TO ADJUST AND ALIGN.  ANY MOVEMENT OF CABLE SUPPORT CLAMP CAN ADVERSELY AFF	ECT SYSTEM OPERATION.			1	L	7	1 	3O			RT	A51EU   					 
1997022000150	19970220	00150	SO  	1997	2	20	97ZZZX777        	1	19961219	G	8011		STARTER         			GULSTM	G1159 	GIV         	3980115	SO  										RT ENG	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	540W	303  				1265				DURING 300 HR STARTER OIL LEVEL CHECK, OIL WAS FOUND TO BE BLACK IN COLOR.  SUSPECT BAD BEARINGS.  REMOVED AND REPLACED 	STARTER, SYSTEM OPERATES NORMALLY.					2	L	7	2 	4F			RT	A12EA   					 
1997022000151	19970220	00151	SO  	1997	2	20	97ZZZX778        	1	19961219	G	3250		SERVO VALVE     			GULSTM	G1159 	GIV         	3980115	SO  										NLG STEERING	MISADJUSTED     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	540W	303  				1265				NOSE WHEEL STEERING SYSTEM KEPT TRIPPING OFF LINE.  UPON EXTENSIVE TROUBLESHOOTING, FOUND NWS SERVO VALVE WAS CAUSING MA	LFUNCTION.  ALSO, WHEN SYSTEM WOULD TRIP OFF, IT WOULD KICK RIGHT.  FOUND THAT THE NWS RUDDER POTENTIOMETER WAS ADJUSTED	 BACKWARDS (MINUS 30MV RATHER THAN PLUS 30MV).  THIS TOLD THE SYSTEM TO TURN RIGHT WHEN THE SERVO FAILED.  RE-ADJUSTED P	OTENTIOMETER.  OPS CHECKS GOOD.			2	L	7	2 	4F			RT	A12EA   					 
1997022000152	19970220	00152	SO  	1997	2	20	97ZZZX779        	1	19961217	G	2822	RG52400B	PUMP            			PIPER 	PA31T 	PA31T       	7103124	SO  										FUEL BOOST	WIRE CHAFE      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	737WB					7620052				DURING AN EVENT 1 INSP, FOUND THE NR 1 BOOST PUMP MAIN POWER WIRE WHERE IT COMES OUT OF THE BACK OF THE PUMP HAD CHAFED 	THROUGH ON PUMP HOUSING.  EVIDENCE OF BURNED AND MELTED SHIELDING.  PUMP LOCATED IN RIGHT WING ROOT.  SUSPECT CAUSE:  PO	WER WIRE NOT PROPERLY SECURED.				1	L	7	2 	3T				A8EA    					 
1997022000155	19970220	00155	WP  	1997	2	20	97ZZZX782        	2	19960930	G	7260	31030351	BEARING         		31032321    						GARRTT	TPE331	TPE33110U   	01514	WP  					ACCESSORY GRBOX	FAILED          	B			DSCR	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	25		3793 			P374		P63074			ACCESSORY GEAR BEARING FAILED RESULTING IN LOSS OF FUEL CONTROL DRIVE AND SUBSEQUENT ENGINE SHUT DOWN IN-FLIGHT.  FAILUR	E OCCURRED UNDER NORMAL OPERATING CONDITIONS WITHIN BEARING TIME-LIFE LIMITATIONS.  SUBMITTER SUGGESTS BEARING REPLACEME	NT AT 3500 HOUR GEARBOX INSPECTION.									4	T			E4WE				 
1997022000473	19970220	00473	GL  	1997	2	20	97ZZZX786        	2	19961218	G	7261	6854424	SEAL            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					START/GEN MT	UNDER SPEC      	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	90215	3    				1698	CAE822907			3 HOURS AFTER SEAL INSTALLATION, PILOT NOTICED OIL LEAK IN STARTER/GEN AREA DURING PREFLIGHT INSP.  DURING GROUND RUN, E	NG OIL WAS FOUND TO BE LEAKING AT A RATE OF 12 DROPS PER MINUTE.  STARTER/GEN WAS REMOVED AND P/N A6854424 WAS FOUND HAL	F OUT OF SEAL BORE.  DURING ENG INSTALLATION, SEAL WAS VERIFIED FOR PROPER INSTALLATION, 3.2 HOURS PRIOR.  SEAL IS AN FA	A PMA SEAL.  SEAL WAS REMOVED FROM ENG AND OUTER DIAMETER MEASURED AT THREE DIFFERENT DEPTHS ON METAL BAND.  EACH OF THE	 MEASURED DIMENSIONS WERE UNDER THE REQUIRED MINIMUM SPECIFIED BY ALLISON.  SUBMITTER RECOMMENDS THAT ALL P/N 6854424 SE	ALS BE MEASURED FOR PROPER DIMENSION PRIOR TO INSTALLATION.	1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997022000479	19970220	00479	SO  	1997	2	20	97ZZZX792        	2	19961029	G	7310	FC30004	HOSE            			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360C      	17025	SO  					FUEL SYS	WRONG PART      	B			V2AR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	2285X					3370185				AEROQUIP FC 300-04 HOSE MEETING SAE 100R5-23 WAS FOUND INSTALLED IN REAR ENGINE FUEL SYSTEM.  THIS HOSE IS INDUSTRIAL AI	R BRAKE HOSE AND THE END FITTINGS MAY NOT BE COMPATIBLE WITH AN/MS FITTINGS.  SUBMITTER STATES THIS IS THE SECOND HOSE O	F THIS TYPE FOUND ON AN A/C.				1	H	7	2 	3O	3	O		A6CE    	E1CE				 
1997022000481	19970220	00481		1997	2	20	97ZZZX794        	4	19961018	G	3452	KT76A	TRANSPONDER     	BENDIX      		CESSNA	340   	340A        	2076405	CE  										C441/C437	DEFECTIVE       	B			DWSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	340EC				34931	340A0258				TRANSPONDER REPLIED ERRATICALLY.  REPLIES WERE NOT SYNCHRONIZED WITH INTERROGATIONS.  REPLACED LEAKY CAPACITOR C441.  DE	FECTIVE PART HAD BLACK EPOXY COATING.  REPLACEMENT PART HAD TAN COATING.  PROBLEM DISAPPEARED.  IN ADDITION, TRANSPONDER	 AUTOMATIC OVERLOAD CONTROL WAS INEFFECTIVE.  REPLACED LEAKY CAPACITOR C437.  SAME COLORS AS ABOVE.  PROBLEM DISAPPEARED	.  VERY COMMON PROBLEM.			1	L	7	2 	3O				3A25    					 
1997022000482	19970220	00482	SO  	1997	2	20	97ZZZX795        	2	19960928	G	8530	111071	CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550*      		SO  					NR 2	LOW COMPRESSION 	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4698C					18502598	264051R			COMPRESSION CHECK REVEALED NR 2 CYL LOW.  SUBMITTER STATES THIS IS THE SECOND CE 185 IO550 INSTALLED BY STC TO HAVE LOW 	COMPRESSION AT 200 HRS, FOUND IN LAST 2 MONTHS.					1	H	7	1 	3O	3	O		3A24    	E3SO				 
1997022000489	19970220	00489	CE  	1997	2	20	97ZZZX802        	1	19961220	G	7603	07501957	BRACKET         			CESSNA	185   	A185E       	2072818	CE  										THROTTLE	BROKEN          	B	L		PCYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	70194					18502047				ENGINE FAILED TO RESPOND ON TAKEOFF.  SMALL BRACKET ATTACHED TO THROTTLE BRACKET 0750195-7, ONE ARM BROKEN AND SEVERELY 	WORN WHERE THROTTLE CONTROL CABLE ATTACHES WITH SAFETY WIRE.  BRACKET (SMALL) NOT SHOWN IN PARTS BOOK.  SAME BRACKET IS 	USED ON PROP CONTROL CABLE AND WAS BROKEN AND WORN.  REPLACED 200 HOURS PREVIOUSLY.  APPEARED THAT ALL CABLES WERE PROPE	RLY INSTALLED AND RIGGED (FACTORY).			1	H	7	1 	3O				3A24    					 
1997022700058	19970227	00058	WP  	1997	2	27	97ZZZX811        	1	19961016	G	2121	58861	BEARING         	SUNDSTRANDEM	251301      	DOUG  	DC9   	DC983       	3022083	WP  										AVION COOLING	FAILED          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		2127 			2497					FAN BEARING FAILED.  BEARING INNER RACE IS BLUE FROM HEAT.  BEARING WILL NOT TURN.  BEARING TT SINCE INSTALLATION 2127 H	RS.  FAN IS FOR AVIONIC COOLING AND CARGO HEAT.  BEARING INSTALLED NEW.					2	L	7	2 	4F			RT	A6WE    					 
1997022700059	19970227	00059	EU  	1997	2	27	97ZZZX812        	1	19960910	G	2620	2591C	VALVE           			CASA  	C212  	C212200     	2410304	EU  										NR1 ENG FIRE EXT	FAILED          	B			AL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	424CA	9063 			1594	242				THE PURPOSE OF THE TWO EXTINGUISHING VALVES IS TO LEAD BY MEANS OF ITS COORDINATE ACTION, THE DISCHARGE OF EXTINGUISHING	 AGENT TOWARDS THE DESIRED ENGINE.  NR 1 ENG VALVE DISK WAS FROZEN ON SHAFT.  NR 2 ENG VALVE DISK WAS PREVENTED FROM SEA	TING DUE MILD CORROSION.  RECOMMEND:  FREQ BE CHANGED FROM EVERY 6 YEARS TO 1 YEAR FOR FUNCTIONAL TEST OF SYSTEM.				2	H	7	2 	4T				A43EU   					 
1997010900417	19970109	00417	NE  	1997	1	9	97ZZZX82         	1	19961211	G	6210	6515000003	BOLT            		641520601042	SKRSKY	S64   	S64F        		NE  										M/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		2938 			64M25901126					AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED	 IAW THE MANUFACTURER'S INSTRUCTIONS.  DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE	.  BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW	 THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK.  THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO	RRODED AREAS.  NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS.		2	G	7	2 	4U				H6EA    					 
1997022700069	19970227	00069	SO  	1997	2	27	97ZZZX822        	1	19961227	G	2913	318002	POWER PACK      			PIPER 	PA23  	PA23250     	7102308	SO  										MLG	FAILED          	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NE	05	40571					277405313				PILOT HAD TO USE EMERGENCY GEAR EXTENSION IN ORDER TO EXTEND GEAR.  THE CO2 BOTTLE DISCHARGED, BUT THE PRIORITY VALVE DI	D NOT WORK.  THE CABLE RIGGING WAS INCORRECT DUE TO CABLE SLIPPAGE WHEN RING WAS PULLED.  HYDRAULIC POWER PACK WAS REPLA	CED DUE TO INTERNAL PROBLEMS.  IMPROPER EMERGENCY CABLE RIGGING OR CABLE SLIPPAGE MADE FOR INCORRECT EMERGENCY GEAR EXTE	NSION.			1	L	7	2 	3O				1A10    					 
1997022700070	19970227	00070	EA  	1997	2	27	97ZZZX823        	2	19961220	G	8520	LW17249	CRANKSHAFT      			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					NR 3 CRANK PIN	BROKEN          	D				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			GL	19	4566H	2734 	713  			240848	L2071451A			ENGINE SEIZED IN-FLIGHT WITH NO WARNING (APPROX 5 SECONDS OF ROUGH OPERATION).  PILOT MADE UNEVENTFUL LANDING IN THE FIE	LD.  ENGINE WAS REMOVED AND DISASSEMBLED.  CRANKSHAFT FOUND BROKEN IN TWO BETWEEN NR 3 AND NR 4 CONNECTING RODS.  ENGINE	 INSPECTED FOR PROP STRIKE 253.8 HOURS PRIOR.				1	L	7	1 	3O	3	O		2A3     	1E10				 
1997022700075	19970227	00075	EA  	1997	2	27	97ZZZX828        	2	19961004	G	7322	229164	DISCHARGE TUBE  		MA4SPA      	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CARB PUMP	DETACHED        	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	01	5115E				A105126	17271717	L504376			CARBURETOR PUMP DISCHARGE TUBE ASSY CAME ADRIFT INGESTING IN ENGINE, KNOCKING LOOSE THE SOLID COMBUSTION PARTICLES IN TH	E COMBUSTION CHAMBER WHICH FOULED A NUMBER OF THE SPARK PLUGS SIMULTANEOUSLY LOSING 50 PERCENT OR MORE OF THE POWER.  BE	ING NEXT TO THE AIRSTRIP, SAFE LANDING WAS MADE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997010900418	19970109	00418	NE  	1997	1	9	97ZZZX83         	1	19961211	G	6210	6515000003	BOLT            		641520601042	SKRSKY	S64   	S64F        		NE  										M/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		2569 			64M24571092					AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED	 IAW THE MANUFACTURER'S INSTRUCTIONS.  DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE	.  BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW	 THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK.  THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO	RRODED AREAS.  NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS.		2	G	7	2 	4U				H6EA    					 
1997022700181	19970227	00181	CE  	1997	2	27	97ZZZX839        	1	19961127	G	2440	1093610165	MODULE          			BEECH 	1900  	1900C       	1154161	CE  										EXT POWER	WIRE BROKEN     	B		A	ZKGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	05										RECEIVED PART FROM REPAIR FACILITY WITH ONLY FUNCTIONAL TEST PERFORMED.  WHEN REMOVED FROM PACKAGE, FOUND NR 1 WIRE BROK	EN FROM POST ON MODULE.  RECOMMEND REPAIR FACILITY PHYSICALLY MOVE WIRE CONNECTION TO CHECK TO SEE IF THEY MAY BE BAD. S	ECOND P.C. BOARD RECEIVED IN THIS CONDITION.				2	L	7	2 	4T			RT	A24CE   					 
1997010900419	19970109	00419	NE  	1997	1	9	97ZZZX84         	1	19961211	G	6210	6515000003	BOLT            		641520601042	SKRSKY	S64   	S64F        		NE  										M/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		2500 			64M24721036					AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED	 IAW THE MANUFACTURER'S INSTRUCTIONS.  DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE	.  BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW	 THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK.  THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO	RRODED AREAS.  NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS.		2	G	7	2 	4U				H6EA    					 
1997022700185	19970227	00185	CE  	1997	2	27	97ZZZX843        	1	19961230	G	2121	50041	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  										CABIN BLOWER	SEIZED          	E				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	09	200AJ				1309	BB378				SMOKE FILLED CABIN ON A FLIGHT 12-30-96.  AIRCRAFT  RETURNED.  DETERMINED FRONT EVAPORATIVE BLOWER SEIZED.  BLOWER ONLY 	HAD 396.8 HOURS LOGGED.					1	L	7	2 	4T				A24CE   					 
1997010900420	19970109	00420	NE  	1997	1	9	97ZZZX85         	1	19961211	G	6210	6515000003	BOLT            		641520601042	SKRSKY	S64   	S64F        		NE  										M/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		2463 			64M24761104					AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED	 IAW THE MANUFACTURER'S INSTRUCTIONS.  DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE	.  BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW	 THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK.  THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO	RRODED AREAS.  NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS.		2	G	7	2 	4U				H6EA    					 
1997010900421	19970109	00421	NE  	1997	1	9	97ZZZX86         	1	19961211	G	6210	6515000003	BOLT            		641520601042	SKRSKY	S64   	S64F        		NE  										M/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		2727 			64M25471133					AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED	 IAW THE MANUFACTURER'S INSTRUCTIONS.  DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE	.  BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW	 THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK.  THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO	RRODED AREAS.  NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS.		2	G	7	2 	4U				H6EA    					 
1997010900422	19970109	00422	NE  	1997	1	9	97ZZZX87         	1	19961211	G	6210	6515000003	BOLT            		641520601042	SKRSKY	S64   	S64F        		NE  										M/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		2992 			64M33811174					AN ULTRASONIC (UT) INSPECTION OF THE M/R BLADE BOLTS RETAINING THE MAIN ROTOR BLADE SPAR TO THE BLADE CUFF WAS PERFORMED	 IAW THE MANUFACTURER'S INSTRUCTIONS.  DURING THE UT INSPECTION, CRACKS WERE DETECTED ON ONE OR MORE BOLTS ON EACH BLADE	.  BOLTS THAT WERE REMOVED FOR CRACK CONFIRMATION, CORROSION WAS EVIDENT ON THE BOLT SHANK APPROXIMATELY .500 INCH BELOW	 THE BOLT HEAD AND EXTENDING FOR APPROXIMATELY 1.000 INCH ALONG THE SHANK.  THE CRACKS WERE NOTED TO OCCUR WITHIN THE CO	RRODED AREAS.  NO CRACKING WAS NOTED OUTSIDE OF THE CORRODED AREAS.		2	G	7	2 	4U				H6EA    					 
1997010900423	19970109	00423	NE  	1997	1	9	97ZZZX88         	2	19961112	G	7230		COVER TAB       			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					CENTRIFUGAL COMP	BROKEN          	B		A	R7MD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	21UM	3335 	2489 			1674	241			PERFORMING A DAILY ON A/C, NOTED TWO METAL TABS LYING ON ENG DECK.  AFTER INQUIRING ABOUT THEM, FOUND OUT THAT THE CENTR	IFUGAL COMPRESSOR COVER WAS CRACKING AROUND CIRCUMFERENCE AND RELEASING THESE TABS FROM COVER.  THE BROKEN TABS FORTUNAT	ELY BLEW OUT BLEED VALVE AND WERE NOT INJESTED THROUGH ENGINE				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997010900424	19970109	00424	SW  	1997	1	9	97ZZZX89         	1	19961029	G	3213	206324004	SKID TUBE       			BELL  	206   	206L1       	1182107	SW  										FLOAT SKID	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2150M	2734 			691	45703				UPON ROUTINE EMERGENCY FLOAT SYSTEM 6 MONTH/500 HOUR INSPECTION, THE SKID TUBE WAS FOUND CRACKED IN THREE PLACES.  UPON 	FURTHER INSPECTION OF TUBE, THE CRACKS APPEAR TO ORIGINATE FROM THE INSERTS DUE TO IMPROPER INSTALLATION OR HOLE PREPARA	TION RATHER THAN DAMAGE FROM LANDING OR DEBRIS.  TUBE SN 702 WAS NOT CRACKED, BUT WAS ALSO CONDEMNED DUE TO UNREPAIRABLE	 CORROSION.  BOTH PARTS WERE RECEIVED PRIMED, PAINTED, AND READY TO INSTALL INCLUDING MANUFACTURER SUPPLIED/PRE-INSTALLE	D SKID SHOES.  BOTH TUBES RETURNED TO AERO ACCESSORIES FOR EVALUATION 10-29-96.		1	G	7	1 	3U				H2SW    					 
1997030600299	19970306	00299	NE  	1997	3	6	97ZZZX895        	2	19961118	G	7250	770102	BLADE           								PWA   	JT9   	JT9D7       	52054	NE  					C MOD T2	OVERTEMP        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	03										SUBMITTER CHECKED A NUMBER OF SERVICEABLE JT9D ST2 TURBINE BLADES OF PWA 1455 MATERIAL P/N 770102 WHICH HAD BEEN REMOVED	 FROM PREVIOUSLY OPERATED ENGINES AND FOUND THEM ALL TO EXHIBIT SIGNS OF AN OVERTEMPERATURE CONDITION AS DETAILED IN THE	 OEM ENGINE MANUAL.  HAS BEEN ADVISED THAT NO REPORT OF AN OVERTEMPERATURE DURING OPERATION HAD BEEN MADE BY THE PREVIOU	S OPERATOR.  THE ENGINE MANUFACTURER PWA HAS BEEN NOTIFIED.  THIS OVERTEMP PROBLEM WITH PWA 1455 MATERIAL BLADES WAS DIS	CUSSED AT THE OPERATORS CONFERENCE OCTOBER, 1996.  GEAESL HAS INTRODUCED A POLICY OF CHECKING ALL USED SERVICEABLE P/N 7	70102 BLADES PURCHASED FOR POSSIBLE OVERTEMPERATURE CONDITION.						4	F			E20EA				 
1997030600300	19970306	00300	SW  	1997	3	6	97ZZZX896        	1	19961031	G	6510	406040339105	BEARING         			BELL  	407   	407         		SW  										T/R DRIVE	SEAL TORN       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	1099R	12   				53042				FOUND T/R DRIVE SHAFT BEARING SEAL TORN.  REPLACED WITH NEW BEARING.						1	G	7	1 	3U			O	H2SW    					 
1997010900102	19970109	00102		1997	1	9	97ZZZX9          	4	19961125	G	6113	6663000	BULKHEAD        			PIPER 	PA28  	PA28160     	7102806	SO  										FWD SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5JN					281528				THE FORWARD SPINNER BOLT HOLES WERE 'DISHED' AT EACH HOLE LOCATION.  AT ONE LOCATION, THE METAL ON THE BULKHEAD WAS SO T	HIN A CRACK HAD DEVELOPED THROUGH THE HOLE.  SUBMITTER STATED OVERTORQUE OF THE PROP BOLTS WAS THE CAUSE OF THIS METAL S	TRETCHING.  THE MM LISTS THE TORQUE FOR THE .50 INCH D-BOLTS IN THE SAME AREA AS THE 3 INCH D-BOLTS.				1	L	7	1 	3O				2A13    					 
1997030600307	19970306	00307	SW  	1997	3	6	97ZZZX903        	1	19961204	G	6520	206040402101	GEARBOX         			BELL  	206   	206L3       	1182108	SW  										T/R	DEFECTIVE       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	3CW	2403 			AFS2836	51420				REPLACED DUE TO NUMEROUS ALIGNMENT BEARING CHANGES.  REPLACED WITH NEW T/R GEARBOX ASSY.						1	G	7	1 	3U				H2SW    					 
1997030600308	19970306	00308	EU  	1997	3	6	97ZZZX904        	1	19960906	G	2150	CCA6299	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  										AIR COND DRIVE	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	32FX	1    				2791				SUSPECT AIR CONDITIONER COMP BELT BROKE AND TOOK OUT HYD BELT.  FOUND BELT (AC) RUNNING TOO CLOSE TO DRIVESHAFT COUPLING	 BOLTS.  SHIMMED AC COMPRESSOR BRACKET TO OBTAIN PROPER CLEARANCE.  CHECKED COMP PULLEY TO DRIVESHAFT FOR PARALLELISM. S	UGGEST INSP OF AC BELT FOR PROPER CLEARANCE.  AIR CONDITIONER SYSTEM IS A CASEY-COPTER ACCESSORIES, P/N 350-CCA-102-24, 	STC NR SH 686NE.			1	G	7	1 	3U			NC	H9EU    					 
1997030600309	19970306	00309	EU  	1997	3	6	97ZZZX905        	1	19960906	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  										HYD DRIVE	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	32FX	1    				2791				SUSPECT AIR CONDITIONER COMP BELT BROKE AND TOOK OUT HYD BELT.  FOUND BELT (AC) RUNNING TOO CLOSE TO DRIVESHAFT COUPLING	 BOLTS.  SHIMMED AC COMPRESSOR BRACKET TO OBTAIN PROPER CLEARANCE.  CHECKED COMP PULLEY TO DRIVESHAFT FOR PARALLELISM. S	UGGEST INSP OF AC BELT FOR PROPER CLEARANCE.  AIR CONDITIONER SYSTEM IS A CASEY-COPTER ACCESSORIES, P/N 350-CCA-102-24, 	STC NR SH 686NE.			1	G	7	1 	3U			NC	H9EU    					 
1997030600312	19970306	00312	WP  	1997	3	6	97ZZZX908        	1	19961210	G	7330	369H81443	SWITCH          			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL BYPASS	INOPERATIVE     	B		A	GHHR	A				UNSCHED LANDING         				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			NM	01	5225C	633  				590497D	CAE830420			AIRCRAFT SUSTAINED MAJOR DAMAGE WHEN FUEL NOZZLE SCREEN BECAME CLOGGED AND COLLAPSED CAUSING LOSS OF POWER.  POST ACCIDE	NT INVESTIGATION BY MCDONNEL DOUGLAS AND FAA FOUND FUEL FILTER BYPASS SWITCH WAS NOT CLOSING SO PILOT HAD NO INDICATION 	THAT THE FUEL FILTER WAS IN BYPASS.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997010900426	19970109	00426	WP  	1997	1	9	97ZZZX91         	1	19961127	G	2842	774000190	FUEL SENDER     			HUGHES	269   	269C        	4470504	WP  										MAIN FUEL TANK	ARM BENT        	B	L		HIAR	A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	27	61404	980  				0010				PILOTS MADE PRECAUTIONARY LANDING DUE TO ILLUMINATION OF LOW FUEL LIGHT.  AFTER INVESTIGATION, FOUND THAT THE FUEL SENDE	R FLOAT CONTACTED THE LOW FUEL SENDING UNIT NOT ALLOWING THE FLOAT TO DROP ANY FURTHER,THEREFORE, THE GAUGE CONTINUED TO	 READ APPROX 8 GALLONS.  AFTER REMOVAL, FOUND SENDING UNIT ARM BENT.				1	G	7	1 	3O				4H12    					 
1997030600319	19970306	00319	EU  	1997	3	6	97ZZZX915        	1	19960322	G	6320	350A32106320	GASKET          		350A32011000	SNIAS 	350   	AS350B2     	8680813	EU  										EPICYCLIC	MISFIT          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	6095U					2699				NEW GASKET FROM MFG DOES NOT FIT PROPERLY.  SUBMITTER STATED THESE PARTS WHEN RECEIVED FROM A.E.C. ARE TOO SMALL IN DIAM	ETER TO CORRECTLY FIT.  AMER EUROCOPTER SAYS TO SOAK THE GASKET OR TO TEAR THE OUTSIDE PART OF THE BOLT HOLES TO MAKE IT	 FIT.  AFTER TRYING TO GET THE GASKET TO SWELL BY SOAKING, THE GASKET STILL TORE.  AMER EUROCOPTER IS AWARE OF THIS PROB	LEM, BUT AS OF LAST PHONE CALL HAS NOT DEVELOPED CORRECTION TO THE PROBLEM OF BAD FITTING GASKETS.			1	G	7	1 	3U				H9EU    					 
1997010900427	19970109	00427	SW  	1997	1	9	97ZZZX92         	1	19960612	G	6220	412018056105	CONE SEAT       			BELL  	412   	412         	1182202	SW  										M/R HEAD	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	416EH	10307			AAD00095M	33011				MALFUNCTION:  RECEIVED LOWER CONE SEAT FOR M/R HEAD THAT WAS NOT PROPERLY TAPPED AND THREADED.  SUBMITTER SUGGESTION:  T	HAT BELL QUALITY CONTROL CHECK LOWER CONE SEAT THOROUGHLY BEFORE SHIPPING TO CUSTOMER.					1	G	7	2 	4U				H4SW    					 
1997030600703	19970306	00703	SW  	1997	3	6	97ZZZX926        	1	19961029	G	3213	206324003	SKID TUBE       			BELL  	206   	206L1       	1182107	SW  										MLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2150M	2734 				45703				UPON ROUTINE EMERGENCY FLOAT SYSTEM 6 MONTH/500 HOUR INSPECTION, THE SKID TUBE WAS FOUND CRACKED IN THREE PLACES AS SKET	CHED.  UPON FURTHER INSPECTION OF TUBE, THE CRACKS APPEAR TO ORIGINATE FROM THE INSERTS DUE TO IMPROPER INSTALLATION OR 	HOLE PREPARATION RATHER THAN DAMAGE FROM LANDING ON DEBRIS.  TUBE S/N 702 WAS NOT CRACKED, BUT WAS ALSO CONDEMNED DUE TO	 UNREPAIRABLE CORROSION.  BOTH PARTS WERE RECEIVED PRIMED, PAINTED, AND READY TO INSTALL INCLUDING MANUFACTURER SUPPLIED	/PRE-INSTALLED SKID SHOES.  3 INCH LONG CRACKS.		1	G	7	1 	3U				H2SW    					 
1997010900428	19970109	00428	EA  	1997	1	9	97ZZZX93         	2	19961108	G	8500		ENGINE          			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					POWER SECTION	FAILED          	H		A	FW7L	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			EA	07	6053U					S1623	L2654851A			THE ENGINE WAS REMOVED FROM THE A/C FOR A VIBRATION OF UNKNOWN CAUSE WHICH WAS DISCOVERED DURING A POST-INSPECTION RUN-U	P.  THE USUAL TROUBLESHOOTING PROCEDURES DID NOT PRODUCE SATISFACTORY RESULTS.  THE COMPLETE ENGINE WAS SENT BACK TO THE	 LYCOMING FACTORY FOR ANALYSIS.  LYCOMING REPORTED BACK TO US THAT THE ENGINE 'FAILED' IN THE TEST CELL AND THEY WERE NO	T SURE OF THE CAUSE.  ENGINE TOTAL TIME AT REMOVAL 880.5 HOURS.			1	G	7	1 	3O	3	O		4H12    	1E10				 
1997030600710	19970306	00710	SW  	1997	3	6	97ZZZX933        	1	19961122	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078N	1825 			A1081	45389				LIGHTNING STRIKE INSPECTION FOUND M/R BLADE CORRODED AND DEBONDED AT TIP OF BLADE.						1	G	7	1 	3U				H2SW    					 
1997030600711	19970306	00711	SW  	1997	3	6	97ZZZX934        	1	19961122	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078N	3494 			A495	45389				DURING A LIGHTNING STRIKE INSPECTION, FOUND CORROSION AND DEBONDING OVER SPAR AT TIP (SKIN).						1	G	7	1 	3U				H2SW    					 
1997030600712	19970306	00712	SW  	1997	3	6	97ZZZX935        	1	19961227	G	6220	206310005101	BOLT            		206011100159	BELL  	206   	206L1       	1182107	SW  										M/R HUB	BROKE           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1084Y	948  			AAB00059	45433				M/R HUB CAME INTO OVERHAUL SHOP FOR REPAIR DUE TO LEAKING GREASE.  TECHNICIAN DID A ROUTINE TORQUE CHECK OF PILLOW BLOCK	 BOLTS.  ONE BOLT BROKE BEFORE REACHING 120 INCH/POUNDS WHICH IS MINIMUM TORQUE.  THE BOLT BROKE IN THREADS APPROXIMATEL	Y .3750 INCH FROM END.  THE BOLT SHOWED SIGNS OF CORROSION IN THREADS AT THIS POINT.  CORROSION WAS PRESENT IN THE BREAK	 AREA.  THE THREE REMAINING BOLTS WERE REPLACED.  CORROSION WAS PRESENT IN ONE OTHER BOLT IN THE SAME LOCATION.			1	G	7	1 	3U				H2SW    					 
1997030600714	19970306	00714	GL  	1997	3	6	97ZZZX937        	2	19961223	G	7260	216002	DRIVE SHAFT     		6896        	BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUEL PUMP	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	176AL	1458 				52146				DURING 1500 HOUR FUEL PUMP DRIVE SHAFT INSPECTION FOUND P/N 216002 DRIVE SHAFT WORN AND P/N 215988-1 GEAR WORN BEYOND LI	MITS.  THIS UNIT WOULD PROBABLY NOT HAVE MADE OVERHAUL WITHOUT RAILING.					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
1997030600715	19970306	00715	SW  	1997	3	6	97ZZZX938        	1	19961105	G	5320	212030495001S	WEB ASSY        			BELL  	212   	212         	1181420	SW  										HELL HOLE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	29AL					30569				MAJOR INSPECTION FOUND WEB CRACKED LOWER LEFT CORNER OF AFT WEB.  C/W T.B. 212-76-18.						1	G	7	1 	4U				H4SW    					 
1997030600716	19970306	00716	SW  	1997	3	6	97ZZZX939        	1	19961122	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3190P	3394 			A450	45779				DISCOVERED DURING DAILY INSPECTION, FOUND TIP BLOCK AND WEIGHT PACKAGE CORRODED AND CAUSED SPAR TO BECOME DEFORMED AT TI	P.					1	G	7	1 	3U				H2SW    					 
1997030600717	19970306	00717	SW  	1997	3	6	97ZZZX940        	1	19961219	G	5311	206032308103	FRAME           			BELL  	206   	206L3       	1182108	SW  										FS 231.48	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	346AL	7821 				51378				AT MAJOR INSPECTION FOUND CRACK AT BOLT ATTACH ON FRAME P/N 206-032-308-103.  SUBMITTER STATED T.B. 206L-94-169 WAS ISSU	ED TO REDUCE CRACKING OF FRAME P/N 206-032-308-103.  THIS IS NOT ADEQUATE.					1	G	7	1 	3U				H2SW    					 
1997030600718	19970306	00718	SW  	1997	3	6	97ZZZX941        	1	19961017	G	6420	206011819109	YOKE            		206011810145	BELL  	206   	206L3       	1182108	SW  										T/R HUB	MISMANUFACTURED 	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	358AL	549  	549  		AFS7556	51460				WHILE TRYING TO SET FLAP ANGLE ON BLADES, FOUND YOKE INBOARD WHERE BLADE MOUNTS ARE NOT MILLED OUT ENOUGH TO PROPERLY SE	T BLADE FLAP ANGLE.  YOKE NOT AIRWORTHY.					1	G	7	1 	3U				H2SW    					 
1997030600719	19970306	00719	EU  	1997	3	6	97ZZZX942        	1	19960828	G	6210	355A11002006	BLADE           			AEROSP	AS355 	AS355F      	8680806	EU  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	378E				3880	5214				DURING DAILY INSPECTION FOUND LOWER BLADE SURFACE CRACKED CHORDWISE AT STA 1397 MM.  CRACK EXTENDS FROM TRAILING EDGE FO	RWARD 110 MM.					1	G	7	2 	3U				H11EU   					 
1997030600720	19970306	00720	SW  	1997	3	6	97ZZZX943        	1	19961122	G	6210	206010200033	BLADE           			BELL  	206   	206B        	1181511	SW  										M/R	SEPARATION      	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3912Q	4137 			CS1577	3271				DISCOVERED DURING DAILY INSPECTION FOUND CORROSION AND SEPARATION BENEATH LOWER GRIP DOUBLES AND BETWEEN LOWER SKIN AND 	SPAR.  CORROSION ON TRAILING EDGE UPPER AND LOWER SURFACES.					1	G	7	1 	3U				H2SW    					 
1997030600721	19970306	00721	NE  	1997	3	6	97ZZZX944        	1	19961014	G	6410		BEARING         			SKRSKY	S76   	S76A        	8143006	NE  										T/R	WORN            	B			ALGR	D				RETURN TO BLOCK         				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	710AL					760279				DISCOVERED DURING 500 HOUR INSPECTION, T/R PADDLE 'A' PIVOT BEARING WORN EXCESSIVELY.  PADDLE 'B' LEADING EDGE STRIP CRA	CKED AT TIP.					1	G	7	2 	3U				H1NE    					 
1997030600722	19970306	00722	NE  	1997	3	6	97ZZZX945        	1	19960922	G	5414		SKIN            			SKRSKY	S76   	S76A        	8143006	NE  										TAIL PYLON	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	768AL					760031				DURING PHASE INSPECTION, FOUND CRACK IN PYLON SKIN ACROSS RIVET HOLE.  THIS CRACK EMANATED FROM CORROSION OF THE SKIN. F	URTHER INSPECTION REVEALED CORROSION ON VARIOUS MEMBERS IN THE PYLON.					1	G	7	2 	3U				H1NE    					 
1997030600726	19970306	00726	EU  	1997	3	6	97ZZZX949        	1	19961227	G	3212	C178131	HOSE            			BOLKMS	105   	BO105S      	5626006	EU  										FLOAT	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8775					S775				HIGH FAILURE RATE OF NR 1 AND NR 4 HOSES ON BO105 FLOATS, P/N D24873-101 AND 102 DUE TO KINKS.  REPLACED HOSES.						1	G	7	2 	3U				H3EU    					 
1997010900430	19970109	00430	WP  	1997	1	9	97ZZZX95         	1	19961127	G	6510	24597	DRIVESHAFT      			HILLER	UH12  	UH12E       	4360122	WP  										T/R	CRACKED         	B	S		NTWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	65NW		1338 			2364				DURING POST-FLIGHT INSPECTION, PILOT FOUND 1 INCH CRACKS EMANATING FROM RIVETS THAT ATTACH BALANCE WEIGHTS TO INTERIOR T	O DRIVESHAFT.  SUBMITTER RECOMMENDS THIS AREA BE DYE-PENETRANT INSPECTED DURING 1800 HR INSPECTION OF DRIVESHAFT.  SHAFT	 INSTALLED ON TURBINE CONVERTED AIRCRAFT.  (STC S4178WE).				1	G	7	1 	3O				4H11    					 
1997030600844	19970306	00844	SW  	1997	3	6	97ZZZX956        	1	19961125	G	2910	70053H000A100	LINE            			BELL  	206   	206L3       	1182108	SW  										HYD PUMP	LEAK            	H	L		N1UM	O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			EA	11	608PD	2735 				51270				WHILE FLYING BACK TO BASE, PILOT REPORTED COMPLETE HYDRAULIC FAILURE APPROX 3 MINUTES OUT.  HE CONTINUED TO BASE AND A N	ON-EVENTFUL LANDING WAS MADE.  MAINT NOTED FLUID RUNNING DOWN SIDES OF HELICOPTER.  AFTER ENTIRE DECK AREA WAS CLEANED, 	VISUAL INSPECTION REVEALED NO OBVIOUS DAMAGE.  SYSTEM SERVICED AND A/C RUN-UP PERFORMED.  AS SYSTEM PRESSURE BEGAN TO RI	SE, HYD FLUID SPRAYED IN ALL DIRECTIONS FROM THE PRESSURE LINE OFF THE PUMP IN THE AREA WHERE IT IS CLAMPED TO THE LINE 	ABOVE IT.  LINE REMOVED AND REPLACED.  SYSTEM SERVICED AND DECK CLEANED.  RUN-UP PERFORMED.  NO LEAKS NOTED.		1	G	7	1 	3U				H2SW    					 
1997030600846	19970306	00846	SW  	1997	3	6	97ZZZX958        	1	19961230	G	6520	206011731001	BEARING         			BELL  	407   	407         		SW  										T/R GEARBOX	MISMANUFACTURED 	B	L	A	HEER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH	14   				53059				TAIL ROTOR GEARBOX PITCH CHANGE MECHANISM WOULD NOT TAKE GREASE.  BELL REPRESENTATIVE HAS CONFIRMED THAT BEARING RACE DI	D NOT HAVE REQUIRED HOLE.  BELL HAS CHANGED BEARING MANUFACTURERS.  THIS BEARING IS FROM NEW MANUFACTURER.  VENDOR:  PIT	CH LIGN RBC.  VENDOR P/N :  HRBC-ORSJ-7133.1.  NOTE:  THIS BEARING IS USED IN ALL 206L SERIES AND 407 AIRCRAFT UNDER P/N	 206-011-731-001.			1	G	7	1 	3U			O	H2SW    					 
1997010900431	19970109	00431	EU  	1997	1	9	97ZZZX96         	1	19961206	G	6220	601741	BEARING         		10581022    	BOLKMS	105   	BO105LSA3   	5626020	EU  										VIB ABSORBER	ROUGH           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	911SV	3430 			3542	2033				WHILE ROTATING VIBRATION ABSORBER, BEARINGS FELT ROUGH.  AFTER PRESSING BEARING OUT OF VIB. ABS. HOUSING FOUND OUTER RAC	E CRACKED.  CORRESPONDING MARK ON HOUSING SHOWED THAT CRACK DID NOT OCCUR DURING REMOVAL.					1	G	7	2 	3U				H3AU    					 
1997030600849	19970306	00849	EA  	1997	3	6	97ZZZX961        	2	19961223	G	8530		CYLINDER        			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 2 BASE	STUDS BROKE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	19CP		932  			S1644	L2539051A			ON TWO DIFFERENT SCHWEIZER HELICOPTERS EQUIPPED WITH HIO360D1A ENGINES, NR 2 CYLINDER BROKE 6 BASE STUDS.  THE TWO THROU	GH-STUDS REMAINED INTACT IN BOTH CASES.  ONE ENGINE HAD 932 HOURS AND THE OTHER 1,424 HOURS SINCE MAJOR OVERHAUL.  BREAK	S ARE CLEAN WITH NO SIGNS OF WORKING OR LOOSENESS AND OCCURS JUST BELOW NUT.				1	G	7	1 	3O	3	O		4H12    	1E10				 
1997030600850	19970306	00850	EA  	1997	3	6	97ZZZX962        	2	19961223	G	8530		CYLINDER        			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 2 BASE	STUDS BROKE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	396CP		1425 			S1683	L2583151A			ON TWO DIFFERENT SCHWEIZER HELICOPTERS EQUIPPED WITH HIO360D1A ENGINES, NR 2 CYLINDER BROKE 6 BASE STUDS.  THE TWO THROU	GH-STUDS REMAINED INTACT IN BOTH CASES.  ONE ENGINE HAD 932 HOURS AND THE OTHER 1,424 HOURS SINCE MAJOR OVERHAUL.  BREAK	S ARE CLEAN WITH NO SIGNS OF WORKING OR LOOSENESS AND OCCURS JUST BELOW NUT.				1	G	7	1 	3O	3	O		4H12    	1E10				 
1997030600860	19970306	00860	SO  	1997	3	6	97ZZZX972        	2	19960725	G	8550	6422118	CHECK VALVE     			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360LB   	17025	SO  					TURBO OIL	CHAFED          	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	03	57195	1307 				250791	316011			BOTH TURBO CHARGER OIL LINE CHECK VALVES OUTER SURFACE WORN THROUGH BY CLAMPS CAUSING SEVERE OIL LEAK (2 QUARTS AN HOUR)	.					1	L	7	1 	3O	3	O		2A3     	E9CE				 
1997030600861	19970306	00861	SO  	1997	3	6	97ZZZX973        	2	19960725	G	8550	641068	CHECK VALVE     			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360LB   	17025	SO  					TURBO OIL	CHAFED          	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	03	57195	1307 				250791	316011			BOTH TURBO CHARGER OIL LINE CHECK VALVES OUTER SURFACE WORN THROUGH BY CLAMPS CAUSING SEVERE OIL LEAK (2 QUARTS AN HOUR)	.					1	L	7	1 	3O	3	O		2A3     	E9CE				 
1997010900433	19970109	00433	SW  	1997	1	9	97ZZZX98         	1	19960826	G	2823	10648BH11	SWITCH          			BELL  	222   	222U        	1182140	SW  										FUEL VALVE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	885AL	5227 				47552				FUEL VALVE SWITCH IS SPRING-LOADED TO FAIL IN THE 'OFF' POSITION.  IF SWITCH IS WORN, IN-FLIGHT VIBRATION COULD CAUSE SW	ITCH TO POP INTO OFF POSITION RESULTING IN IMMEDIATE ENGINE SHUT-DOWN.					1	G	7	2 	3U				H9SW    					 
1997010900434	19970109	00434	SW  	1997	1	9	97ZZZX99         	1	19960909	G	6510		DRIVESHAFT      			BELL  	206   	206L3       	1182108	SW  										SPLINE ADAPTER	BOLT LOOSE      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	215KH					51215				BOLT ON THE SPLINE ADAPTER TO THOMAS COUPLING CAME LOOSE CAUSING T/R SHAFT DAMAGE.  SUSPECT CAUSE WAS LOW TORQUE TO NUT.	  TARE TORQUE ON NUT WAS CHECKED TO BE 5 INCH/POUND AT RE-ASSEMBLY.  SUBMITTER SUGGESTED USE OF NEW HARDWARE EACH TIME S	HAFT COMPONENTS ARE DISASSEMLBED FOR MAINTENANCE.				1	G	7	1 	3U				H2SW    					 
1997031300061	19970313	00061	SW  	1997	3	13	97ZZZX991        	1	19961114	G	6210	107015001117	BLADE           			BELL  	407   	407         		SW  										M/R	PAINT FLAKE     	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	109  			A209	53044				PAINT FLAKING OFF LEADING EDGE AT TIP.						1	G	7	1 	3U			O	H2SW    					 
1997031300062	19970313	00062	SW  	1997	3	13	97ZZZX992        	1	19961114	G	6210	407015001117	BLADE           			BELL  	407   	407         		SW  										M/R	PAINT FLAKE     	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	109  			A338	53044				PAINT FLAKING OFF LEADING EDGE AT TIP.						1	G	7	1 	3U			O	H2SW    					 
1998010800420	19980108	00420		1998	1	8	98ZZZX118        	4	19960628	G	2297		WIRE            			BRAERO	1000  	BAE1251000  	1500287	EU  										PILOT SIDE PANEL	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	548QS	250  				259048				HOSE CLAMP HOLDING CUSTOM MADE AIRBOX TO PILOTS SIDE PANEL WAS POSITIONED SO THAT WORM SCREW OF CLAMP FOR SCREWDRIVER SL	OT END WAS CUTTING INTO WIRES ON TERMINAL BLOCK MOUNTED BELOW BOX CAUSING FAILURE OF AUTOPILOT TRIM SYSTEM.  THIS CONDIT	ION EXISTED ON PILOTS AND COPILOTS SIDE PANELS.  THE REPAIR WAS TO POSITION HOSE CLAMP WORM SCREW AT TOP OF AIRBOX AND C	OVERING WIRE TERMINAL BLOCK WITH PROTECTIVE TEFLON SHEET.  DAMAGED WIRES REPAIRED AS REQUIRED.			2	L	7	2 	4F			RT	A3EU    					 
1998012200141	19980122	00141	CE  	1998	1	22	98ZZZX226        	1	19960515	G	2810		SEAL            			CESSNA	182   	182P        	2075816	CE  										TANK CAP	LEAK            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	182DL					18264512				SEALS FOR PLASTIC TYPE FUEL CAPS SUPPLIED WITH AIRCRAFT ARE NO LONGER AVAILABLE. DESIGN OF FUEL TANK OPENINGS (FLUSH MOU	NT) ALLOWS WATER TO ENTER FUEL TANK IF SEAL  INTEGRITY IS LOST.					1	H	7	1 	3O			NT	TA13    					 
1998100200073	19981002	00073	CE  	1998	10	2	98ZZZX3578       	1	19960709	G	7120	AN746A	BOLT            			CESSNA	185   	A185F       	2072821	CE  										ENGINE	BROKEN          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	6166N	164  				18504302				WHEN ATEMPTING TO LOCATE AN OIL LEAK, NOTICED THE ENGINE MOVED FAIRLY EASY ON THE MOUNTS.  FURTHER INSPECTION OF THE 'LO	OSE ENGINE' PROBLEM REVEALED THE RIGHT REAR BOLT SECURING THE ENGINE TO THE AIRCRAFT MOTOR MOUNT HAD BROKEN AT THE BEGIN	NING OF THE THREADS.  164.3 HOURS EARLIER, NEW BOLTS HAD BEEN INSTALLED IAW CESSNA 185 PARTS AND SERVICE MANUALS.  WHEN 	ATTEMPTING TO REPLACE THE BOLT, THE THREADED END WAS FOUND 'BOTTOMED OUT' IN THE MOUNT BRACKET.  ALL 4 ENGINE MOUNTING B	OLTS WERE REPLACED WITH THE LOCKING HARDWARE.		1	H	7	1 	3O				3A24    					 
1998121100007	19981211	00007	SO  	1998	12	11	98ZZZX4450       	2	19961204	G	7311	63917	OIL COOLER      			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	CRACKED         	B			MK5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	23	952CC		1003 			18263638	269332R			DURING A ROUTINE INSPECTION, THE OIL COOLER WAS FOUND CRACKED AT A WELD ON ONE OF ITS SUPPORT STRUTS.  SUBMITTER SUGGEST	ED CAUSE AS DEFECTIVE PARTS AND/OR RE-MANUFACTURE PROCESS FROM THE FACTORY.					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1998121100008	19981211	00008	SO  	1998	12	11	98ZZZX4451       	2	19960311	G	8520	641963	VALVE GUIDE     			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	952CC	400  				18263638	269332R			DURING A ROUTINE COMPRESSION CHECK, THE EXHAUST VALVE WAS FOUND LEAKING ON THE NR 5 CYLINDER.  THE REMOVED CYLINDER, EXH	AUST VALVE AND GUIDE WERE FOUND WORN OUT.  SUBMITTER SUGGESTED CAUSE AS DEFECTIVE PARTS AND/OR ASSEMBLY PROCESS FROM THE	 FACTORY.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1998121100024	19981211	00024	SO  	1998	12	11	98ZZZX4467       	2	19961115	G	8520	649478	CAMSHAFT        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	SCORED          	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	954CC		800  			18265290	286937R			A ROUTINE OIL CHANGE AND OIL FILTER INSPECTION REVEALS EXCESSIVE METAL.  FURTHER INVESTIGATION FINDS THE CAMSHAFT HAS FA	ILED ON CERTAIN CAM LOBES.  ENGINE IS REMOVED FROM SERVICE.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PART.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1998121100027	19981211	00027	SO  	1998	12	11	98ZZZX4470       	2	19960907	G	8530	649168	VALVE GUIDE     			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE EXHAUST	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	954CC	700  				18265290	286937R			DURING A ROUTINE COMPRESSION CHECK, LEAKAGE WAS FOUND ON THE EXHAUST VALVES ON THE NR 1 AND NR 3 CYLINDERS.  THE REMOVED	 CYLINDERS, EXHAUST VALVES AND GUIDES WERE FOUND WORN OUT.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS AND/OR	 ASSSEMBLY PROCES FROM THE FACTORY.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1998121100030	19981211	00030	SO  	1998	12	11	98ZZZX4473       	2	19960214	G	8530	653443	VALVE GUIDE     			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE EXHAUST	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	953CC	814  				18264109	269314R			DURING A ROUTINE COMPRESSION CHECK, THE EXHAUST VALVE ON THE NR 2 CYLINDER WAS FOUND LEAKING.  THE REMOVED CYLINDER, EXH	AUST VALVE AND GUIDE WERE FOUND WORN OUT.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS OR ASSEMBLY PROCESS AT 	THE FACTORY.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1999051400482	19990514	00482	CE  	1999	5	14	99ZZZX2002       	1	19960307	G	7500	45A403061	DUCT            			BEECH 	MU300 	400A        	1155402	CE  										BLEED AIR	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05		1594 								DURING THE PHASE 4 INSPECTION, DISCOVERED THE DUCT ASSEMBLY HAD FAILED AND SEPARATED.  THE DUCT ASSEMBLY CENTER BLEED AI	R CROSS-OVER FAILED AT THE FLEX JOINT AREA WHERE WIRE MESH IS INSTALLED.  (BEECHJET 400T - COMMERCIAL COUNTERPART BEECHJ	ET 400A).				2	H	7	2 	4F			RT	A16SW   					 
1999052100084	19990521	00084	EU  	1999	5	21	99ZZZX2052       	1	19960401	G	2910		LINE            	DUNLOP      		BRAERO	DH125 	HS125700A   	4230170	EU  										HYDRAULIC SYSTEM	CORRODED        	H		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	17	500EF					257086				HYDRAULIC HOSE FAILURE DUE TO CORROSION OF METAL BRAID AND SWAGE.  THIS IS COVERED BY PLASTIC MATERIAL IN WHICH UNABLE T	O SEE UNLESS THE PLASTIC IS PEELED BACK.  NOTE:  SAME P/N HOSES ON EARLY RAYTHEON MODELS HAVE A MANDATORY LIFE LIMITATIO	N, BUT THE 700 SERIES AIRCRAFT WAS NOT INCLUDED.				2	L	7	2 	4F				A3EU    					 
1996110700104	19961107	00104	WP  	1996	11	7	A3L2207J         	1	19961104	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  	DC9   	DC981       	3022081	WP  										WHEEL	FAILURE         	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B1097					FATIGUE RELATED FAILURE OF MD80 WHEEL TIE BOLTS.  SUSPECT INSUFFICIENT TIE BOLT PRELOAD TORQUE.  SUBMITTER SUGGESTS TO U	SE SNUG ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F				A6WE    					 
1996022300409	19960223	00409	EU  	1996	2	23	A6WR95050        	1	19960117	G	2730	SL442804	ROD END         			BAG   	BAE146	BAE146200A  	1500266	EU  										ELEV G-WEIGHT	WORN            	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				FOUND WORN ROD-END ON ELEVATOR G-WEIGHT CONNECTING ROD.  REPLACED ROD-END AND RIGGED SYSTEM IAW AMM.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996022300725	19960223	00725	EU  	1996	2	23	A6WR95051        	1	19960117	G	5320	HC536B0444000	FREIGHT ANGLE   			BAG   	BAE146	BAE146200A  	1500266	EU  										FS FR 21	CRUSHED         	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				FORWARD CARGO BAY FREIGHT ANGLE AT FRAME 21 CRUSHED.  REPLACED FREIGHT ANGLE.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996020200312	19960202	00312	EU  	1996	2	2	A6WR95052        	1	19960117	G	5520	HC551B0087000	BOLT            			BAG   	BAE146	BAE146200A  	1500266	EU  										LT ELEV HINGE	DAMAGED         	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING STRUCTURAL INSPECTION, FOUND LT ELEVATOR NR 2 HINGE LOWER A-FRAME BOLT TO HAVE DAMAGED THREADS AND CORROSION.  RE	PLACED BOLTS.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996030100226	19960301	00226	EU  	1996	3	1	A6WR95053        	1	19960117	G	5520	HC551B0087000	BOLT            			BAG   	BAE146	BAE146200A  	1500266	EU  										LT ELEV HINGE	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING STRUCTURAL INSPECTION, FOUND CORROSION ON LT ELEVATOR NR 2 HINGE UPPER A-FRAME BOLT.  REPLACED BOLT.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996030100227	19960301	00227	EU  	1996	3	1	A6WR95054        	1	19960117	G	5520	HC551B0086000	BOLT            			BAG   	BAE146	BAE146200A  	1500266	EU  										RT ELEV HINGE	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING STRUCTURAL INSPECTION, FOUND RT ELEVATOR NR 1 HINGE A-FRAME LOWER BOLT CORRODED.  REPLACED BOLT.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996020900319	19960209	00319	EU  	1996	2	9	A6WR95055        	1	19960117	G	5520	HC551B0087000	BOLT            			BAG   	BAE146	BAE146200A  	1500266	EU  										RT ELEV HINGE	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	5520					E2087				DURING STRUCTURAL INSPECTION, FOUND RIGHT ELEVATOR NR 2 HINGE A-FRAME UPPER BOLT CORRODED.  REPLACED BOLT.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996022300410	19960223	00410	EU  	1996	2	23	A6WR95056        	1	19960117	G	4930	SA767006158	HOSE            			BAG   	BAE146	BAE146200A  	1500266	EU  										APU FUEL	DEFECTIVE       	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION, FOUND EXTERIOR COVERING OF APU FUEL SUPPLY HOSE BROKEN OPEN.  REPLACED FUEL HOSE.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996020900028	19960209	00028	EU  	1996	2	9	A6WR95057        	1	19960117	G	5751	HC572H0910004	BOLT            			BAG   	BAE146	BAE146200A  	1500266	EU  										RT AIL RIB	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING STRUCTURAL INSPECTION, FOUND RIGHT AILERON RIB 18 UPPER A-FRAME BOLT CORRODED.  REPLACED BOLT.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996022300411	19960223	00411	NE  	1996	2	23	A6WR95058        	2	19960117	G	7240		COMBUSTION CASE 			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 ENGINE	FLANGE CRACKED  	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087	LF05442A			DURING SCHEDULED INSPECTION, FOUND BLEED AIR FLANGE AT 3 O'CLOCK POSITION ON COMBUSTION CASE CRACKED.  REPAIRED IAW TEXT	RON (ALLIED SIGNAL) ENGINE MM.  (X)					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996022300412	19960223	00412	EU  	1996	2	23	A6WR95059        	1	19960117	G	5400	HC361C0042000	BRACKET         			BAG   	BAE146	BAE146200A  	1500266	EU  										NR 4 PYLON	BROKEN          	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION, FOUND BOTH LEFT SIDE BRACKETS SUPPORTING PRESSURE REGULATING/ISOLATION VALVE BROKEN IN NR 4	 PYLON.  REPLACED BRACKETS.  REFERENCE:  OPERATOR CONTROL NR 96ZZZX760.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996022300413	19960223	00413	EU  	1996	2	23	A6WR95060        	1	19960117	G	5400		PYLON           			BAG   	BAE146	BAE146200A  	1500266	EU  										NR 4	RIVETS SHEARED  	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION, FOUND 3 RIVETS SHEARED OFF IN NR  4 PYLON BOX AT POSITIONS B, C, D.  REPLACED FASTENERS IAW	 AVRO RL HC546H9009.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996020200313	19960202	00313	EU  	1996	2	2	A6WR95061        	1	19960117	G	5755	HC276H0075002	BOLT            			BAG   	BAE146	BAE146200A  	1500266	EU  										LT WING SPOILER	CRACKED         	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED NDT INSPECTION, FOUND CRACK INDICATION ON LEFT WING INBOARD AFT SPOILER JACK ATTACH BOLT.  REPLACED BOL	T.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996020900029	19960209	00029	EU  	1996	2	9	A6WR95062        	1	19960117	G	5753	HC579L0097000	PIVOT PIN       			BAG   	BAE146	BAE146200A  	1500266	EU  										RT FLAP NR 3	CRACKED         	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED NDT INSPECTION, FOUND NR 3 RIGHT FLAP TRACK TAB OPERATING ROD-TO-CROSSHEAD, PIVOT PIN WITH CRACK INDICA	TION.  REPLACED PIN.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996022300414	19960223	00414	EU  	1996	2	23	A6WR95063        	1	19960117	G	2710	HC270H0135004	CONTROL CABLE   			BAG   	BAE146	BAE146200A  	1500266	EU  										AILERON	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION FOUND AILERON INTERCONNECT CABLES CORRODED AT WING ROOT PULLEYS.  REPLACED CABLES.  REFERENC	E:  OPERATOR CONTROL NR 96ZZZX761.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996020900030	19960209	00030	EU  	1996	2	9	A6WR95064        	1	19960117	G	5320	H5113381C7	JO-BOLT         			BAG   	BAE146	BAE146200A  	1500266	EU  										FR 29, STR 12 RT	FAILED          	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION, FOUND BROKEN HEAD ON JO-BOLT AT FRAME 29, STR 12 RIGHT. REPLACED JO-BOLT.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996030100228	19960301	00228	EU  	1996	3	1	A6WR95065        	1	19960117	G	5320	HC537H0654000	PLATE           			BAG   	BAE146	BAE146200A  	1500266	EU  										FR 15-18	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING STRUCTURAL INSPECTION, FOUND TWO SUPPORT PLATES AT 3RD INTERCOSTAL INBOARD FROM LT FORWARD PASSENGER DOOR BETWEEN	 FUSELAGE FRAMES 15 AND 18 CORRODED.  REPLACED BOTH PLATES.  REFERENCE:  OPERATOR CONTROL NR 96ZZZX824.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996030100229	19960301	00229	EU  	1996	3	1	A6WR95066        	1	19960117	G	5320	HC537H0650006	INTERCOSTAL     			BAG   	BAE146	BAE146200A  	1500266	EU  										LT FWD FR 15-18	CORRODED        	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING STRUCTURAL INSPECTION, FOUND 2ND INTERCOSTAL INBOARD FROM LT FORWARD PASSENGER DOOR, BETWEEN FRAMES 15 AND 18, CO	RRODED.  REPLACED INTERCOSTAL.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996022300726	19960223	00726	EU  	1996	2	23	A6WR95067        	1	19960117	G	5400	HC546C0075002	BRACKET         			BAG   	BAE146	BAE146200A  	1500266	EU  										PYLON COWL MT	CRACKED         	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION, FOUND NR 1 PYLON SHOULDER COWL LORD MOUNT ATTACHMENT BRACKET CRACKED.  REPLACED BRACKET.  (	X)					2	H	7	4 	4F			RT	A49EU   					 
1996030100230	19960301	00230	EU  	1996	3	1	A6WR95068        	1	19960117	G	5400	HC546C0075002	BRACKET         			BAG   	BAE146	BAE146200A  	1500266	EU  										NR 2 PYLON MOUNT	CRACKED         	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION, FOUND NR 2 PYLON LORD MOUNT EYE BOLT BRACKET CRACKED.  REPLACED BRACKET.  (X)						2	H	7	4 	4F			RT	A49EU   					 
1996020900031	19960209	00031	EU  	1996	2	9	A6WR95069        	1	19960117	G	5400		RIVETS          			BAG   	BAE146	BAE146200A  	1500266	EU  										NR 3 PYLON	SHEARED         	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION, FOUND 4 RIVETS SHEARED OFF IN NR 3 PYLON BOX AT POSITIONS A, B, C, AND D.  REPLACED FASTENE	RS IAW AVRO RIL HC546H9009.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1996022300727	19960223	00727	EU  	1996	2	23	A6WR95070        	1	19960117	G	5400		RIVETS          			BAG   	BAE146	BAE146200A  	1500266	EU  										NR 2 PYLON BOX	SHEARED         	B			A6WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	31	292UE					E2087				DURING SCHEDULED INSPECTION FOUND 2 RIVETS SHEARED OFF IN NR 2 PYLON BOX AT POSITIONS C AND D.  REPLACED FASTENERS IAW A	VRO RIL HC546H9009.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1997041600001	19970416	00001	NM  	1997	4	16	ANCF9600001      	1	19960919	G	3240		BRAKE           	BENDIX      		BOEING	767   	767383      	1385214	NM  										MLG	OVERHEATED      	W			ANCF	C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			SO	23	984AN					24357				FLT 014 BOG-PAR.  DURING T/O ROLL AFTER PASSING 80 KNOTS, THE BRAKE TEMP LIGHT CAME ON.  WAS NECESSRY TO MAKE A REJECTED	 T/O.  INSPECTION ACCOMPLISHED ACCORDING MM 32-42800.  ALL NORMAL.  TIRES NRS 1, 2, 6, 7, AND 8 WERE CHANGED.  (X)					2	L	7	2 	4F			RT	A1NM    					 
1997041600002	19970416	00002	NM  	1997	4	16	ANCF9600002      	1	19961003	G	5210		DOOR            			BOEING	767   	767383      	1385214	NM  										LT FWD	UNLOCKED        	W			ANCF	B	A			EMER. DESCENT           	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SO	23	984AN					24357				AIR RETURN:  DURING FLIGHT FROM SKGT TO SKBO AT 28,000 FEET, FWD ENTRY DOOR LIGHT ILLUMINATED WITH EICAS MESSAGE.  FLIGH	T ATTENDANT REPORTED THE DOOR HANDLE COMING OUT OF LOCKED POSITION AND STRONG NOISE.  CABIN ALTITUDE INCREASED RAPIDLY, 	BUT WAS CONTROLLED IN MANUAL.  EMERGENCY DESCENT EXECUTED.  CABIN ALT DID NOT EXCEDE 10,000 FEET.  AIRCRAFT RETURNED TO 	SKGT.  CHECKED DOOR LOCK MECHANISM, AND FOUND LOCK OF THE DOOR LEVER (EXTERIOR SIDE) UNLOCKED.  IT WAS REPOSITIONED.  (X	)		2	L	7	2 	4F			RT	A1NM    					 
1996060600137	19960606	00137	WP  	1996	6	6	ARWR960356       	1	19960513	G	5754		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										STA XW 217.875	GOUGED          	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEFT OUTBOARD FLAP APPROXIMATE STA XW217.875 ICE SHIELD LEADING EDGE FLAP CUT-OUT AREA WITH GOUGES	 AT UPPER SKIN AREA (FRONT SPAR).  REPAIRED AREA IAW DER DWG MHA3052.  APPLIED CORROSION X IAW SRM 51-1-8 AND CLOSED L/E	 PANEL IAW SRM 51-3-0.  (X)				2	L	7	4 	4F				4A25    					 
1996060600138	19960606	00138	WP  	1996	6	6	ARWR960395       	1	19960513	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										C4 DOOR CUT-OUT	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LOWER AFT FUSELAGE C-4 CARGO DOOR CUT-OUT HAS CORROSION THROUGH.  CUT-OUT DAMAGED SECTION, FABRICA	TED DOUBLER AND TRIPLER AND INSTALLED IAW DER NR MHA 3057.  TREATED AND PRIMED IAW SRM 51-1-8, SEALED AREA IAW SRM 51-1-	14.  REPAIRED UNDER DAC GLP 1748-96-05-02-009.  (X)				2	L	7	4 	4F				4A25    					 
1996060600139	19960606	00139	WP  	1996	6	6	ARWR960418       	1	19960513	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 1180 L36	MISREPAIRED     	B			ARWR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LOWER AFT FUSELAGE HAS TEMP PLUG AT STA FS 1180.000 AND L36 APPROXIMATELY.  FABRICATED AND INSTALL	ED DOUBLER IAW DER NR M.H.A. 3061.  TREATED AND PRIMED IAW SRM 51-1-8.  INSTALLED IAW 51-1-21.  (X)					2	L	7	4 	4F				4A25    					 
1996061300056	19960613	00056	WP  	1996	6	13	ARWR960442       	1	19960514	G	5240		DOOR            			DOUG  	DC8   	DC862       	3021970	WP  										AFT ACCESS	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					47060				DURING C-CHECK, FOUND AFT FUSELAGE ACCESS DOOR, NR 60, HAS CORROSION.  REMOVED DOOR, CLEANED CORROSION, FABRICATED DOUBL	ER PER DER ARW 950082-1420.  INSTALLED REPAIR PER DER ARW 950085-1420.  (X)					2	L	7	4 	4F				4A25    					 
1996061300057	19960613	00057	WP  	1996	6	13	ARWR960447       	1	19960514	G	5320		DOUBLER         			DOUG  	DC8   	DC862       	3021970	WP  										FS 1520-1530	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AFT FUSELAGE SKIN DOUBLER HAS CORROSION FROM FS 1520.000 AND FS 1530.000 AND BETWEEN L23L AND L23R	.  REMOVED DOUBLER, REMOVED CORROSION, FABRICATED AND INSTALLED IAW DER NR 96IALE-005D-10, TREATED AND PRIMED IAW SRM 51	-1-8 AND SEALED AREA IAW SRM 51-1-4.  (X)				2	L	7	4 	4F				4A25    					 
1996060600140	19960606	00140	WP  	1996	6	6	ARWR960454       	1	19960515	G	5247		DOOR            			DOUG  	DC8   	DC862       	3021970	WP  										AFT FUS NR 62	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AFT FUSELAGE ACCESS DOOR NR 62 AND DOOR CUT-OUT HAVE CORROSION.  REMOVED CORROSION ON DOOR CUT-OUT	 IAW SRM 51-1-8, FOUND WITHIN LIMITS IAW SRM 53-2-0.  REPAIRED DOOR IAW ARW 950082-1420.  (X)					2	L	7	4 	4F				4A25    					 
1996061300058	19960613	00058	WP  	1996	6	13	ARWR960467       	1	19960514	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 1438-1480	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AFT LOWER FUSELAGE SKIN JOINT HAS CORROSION AT L31R FROM FS 1380.000 TO FS 1480.000.  CUT OUT DAMA	GED SECTION, FABRICATED FILLER AND DOUBLER, AND INSTALLED IAW DER NR 96IALE-0050-12.  TREATED AND PRIMED IAW SRM 51-1-8.	  SEALED AREA IAW SRM 51-1-14.  (X)				2	L	7	4 	4F				4A25    					 
1996060600141	19960606	00141	WP  	1996	6	6	ARWR960493       	1	19960508	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										MAIN ENT DOOR	DAMAGED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				WHILE PERFORMING C-CHECK INSPECTION, FOUND MAIN ENTRY DOOR CUT-OUT, LOWER AFT DOUBLER REPAIR, NEEDS APPROVED REPAIR COMP	LIANCE VERTIFICATION.  CUT OUT DAMAGED SECTION, FABRICATED DOUBLER AND INSTALLED IAW DER DOUGLAS NR 96-03-07-007.  TREAT	ED AND PRIMED IAW SRM 51-1-8.  REMOVED AND INSTALLED SCUFF PLATE IAW SRM 51-1-21.  (X)				2	L	7	4 	4F				4A25    					 
1996060600142	19960606	00142	WP  	1996	6	6	ARWR960595       	1	19960513	G	5320		DOUBLER         			DOUG  	DC8   	DC862       	3021970	WP  										FS 1200-1260	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND UPPER FUSELAGE SKIN DOUBLER REPAIR NEEDS APPROVED REPAIR VERIFICATION BETWEEN FS 1200.000 - FS 126	0.000, LONGERON 21L.  INSTALLED REPAIR IAW DER NR MHA 3060.  (X)					2	L	7	4 	4F				4A25    					 
1996060600143	19960606	00143	WP  	1996	6	6	ARWR960606       	1	19960522	G	5320		WINDOW FRAME    			DOUG  	DC8   	DC862       	3021970	WP  										RT FS 1020	CRACKED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND WORKING FASTENERS AND CRACK AROUND WINDOW FRAME, RT STA 1020.00.  REPAIRED IAW DER DRAWING NR GLP 	1681, SRM 51-1-8 AND SRM 51-11-40.  (X)					2	L	7	4 	4F				4A25    					 
1996061300059	19960613	00059	WP  	1996	6	13	ARWR960609       	1	19960514	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 1130-1140	MISREPAIR       	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND UPPER FUSELAGE SKIN DOUBLER REPAIR BETWEEN FS 1130.000 AND FS 1140.000 AT L21R NEED APPROVED REPAI	R VERIFICATION.  REMOVED DOUBLER, FABRICATED WITH 7075-T6.  TREATED AREAS WITH ALODINE AND F.R. PRIMER IAW SRM 51-1-8. I	NSTALLED REPAIR DOUBLER WITH FASTENERS AS REQUESTED.  ALL WORK PERFORMED PER D.E.R. ARW NR 950082-0677.  (X)				2	L	7	4 	4F				4A25    					 
1996060600144	19960606	00144	WP  	1996	6	6	ARWR960645       	1	19960515	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 270 L16R	GOUGED          	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND UPPER FUSELAGE SKIN GOUGED AT FS 270.000 AND L16R.  REMOVED DAMAGE, FABRICATED, TREATED AND PRIMED	 DOUBLER.  INSTALLED DOUBLER IAW DER 950082-0548.  (X)					2	L	7	4 	4F				4A25    					 
1996061300060	19960613	00060	WP  	1996	6	13	ARWR960655       	1	19960514	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 857-1000	DAMAGE          	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND UPPER FUSELAGE SKIN HAS AREAS WITH HEAVY BLEND-OUTS.  NEEDS TO BE CHECKED FOR LIMITS BETWEEN FS 85	7.000 AND FS 1000.000 AND BETWEEN L17R AND L21R.  FABRICATED AND INSTALLED DOUBLERS AT STA 857 IAW DER NR 96IALE-005D-11	 AND AT STA 902 IAW DER NR 961ALE-005D-9.  SEALED AREAS IAW SRM 51-1-16.  (X)				2	L	7	4 	4F				4A25    					 
1996061300415	19960613	00415	WP  	1996	6	13	ARWR960657       	1	19960522	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 980-1000	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK INSPECTION, FOUND UPPER FUSELAGE SKIN AROUND FASTENERS HAS CORROSION AND WORKING FASTENERS, RT FUSELAGE, 	STA 980.000 TO STA 1000.000.  REPAIRED IAW DER DRAWING NR GLP 1681/96-22-14-003.  TREATED AND PRIMED IAW SRM 51-1-8.					2	L	7	4 	4F				4A25    					 
1996053000058	19960530	00058	WP  	1996	5	30	ARWR960700       	1	19960426	G	5530		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										V-FIN LE ATTACH	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND VERTICAL FIN LEADING EDGE LOWER PANEL LOWER ATTACH SCREW HOLE AREA HAS CORROSION.  REMOVED DAMAGED	 AREA IAW SRM 55-2-1, FABRICATED FILLER AND DOUBLER IAW SRM 55-2-1, PAGES 17-18, ALODINED AND PRIMED IAW SRM 51-1-8.  IN	STALLED REPAIR IAW SRM 55-2-1.  REF:  OPERATOR CONTROL NR 0700.  (X)				2	L	7	4 	4F				4A25    					 
1996082900363	19960829	00363	WP  	1996	8	29	ARWR9607001      	1	19960730	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 255-265	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	1808E	6255 				46105				INNER SKIN BETWEEN FS 255 AND FS 265 CORRODED AT LONGERON 21R.  CUT OUT AREA OF CORROSION, FABRICATED AND INSTALLED 7075	.T6 .025 INCH FILLER AND 7075.T6 .032 INCH DOUBLER IAW MHA ENGINEERING, INC., E. O. MHA-3066 UNDER AMRC W. O. 960165.  (	X)				2	L	7	4 	4F				4A25    					 
1996082900362	19960829	00362	WP  	1996	8	29	ARWR9607002      	1	19960730	G	5320		ANGLE           			DOUG  	DC8   	DC862       	3021970	WP  										FS 225R-275R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	1808E	6255 				46105				FLOOR PANEL SUPPORT ANGLE AT FS 225R TO FS 273R CORRODED AT FLOOR LEVEL.  CUT OUT CORRODED AREA.  FABRICATED AND INSTALL	ED 2024.T3 .063 INCH FILLER AND 2024.T3 .071 INCH DOUBLER IAW MHA ENG. INC., E. O. MHA-3065 UNDER AMRC W. O. 960165.  (X	)				2	L	7	4 	4F				4A25    					 
1996082900361	19960829	00361	WP  	1996	8	29	ARWR9607003      	1	19960730	G	5315		FLOOR BEAM      			DOUG  	DC8   	DC862       	3021970	WP  										FS 235 LBL 66	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	1808E	6255 				46105				FLOOR BEAM AT STA 235 AT LBL 66 CORRODED SECTION AT DUCT CUT-OUT.  MECHANICALLY REMOVED CORRODED SECTION.  FABRICATED AN	D INSTALLED 7075.T6 .090 INCH DOUBLER IAW MHA ENGINEERING, INC., E. O. MHA-3067 UNDER AMRC W.O. 960165.  (X)					2	L	7	4 	4F				4A25    					 
1996060600145	19960606	00145	WP  	1996	6	6	ARWR960706       	1	19960515	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 822-857 L22R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND UPPER FUSELAGE SKIN HAS CORROSION BETWEEN FS 822.500 AND FS 857.125, L22R.  CUT OUT DAMAGED SECTIO	N, FABRICATED FILLER AND DOUBLER.  INSTALLED REPAIR IAW DER NR ARW 95 0082-1004.  TREATED AND PAINTED AREA IAW SRM 51-1-	8.  SEALED AREAS ARE IAW SRM 51-1-14.  (X)				2	L	7	4 	4F				4A25    					 
1996060600146	19960606	00146	WP  	1996	6	6	ARWR960712       	1	19960508	G	5754		SLOT DOOR       			DOUG  	DC8   	DC862       	3021970	WP  										LT WING INBD	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				WHILE PERFORMING C-CHECK, FOUND LEFT WING, INBOARD SLOT DOOR TOPSIDE, HAS EXFOLIATION CORROSION IN AREAS MARKED.  REMOVE	D CORROSION, FABRICATED AND INSTALLED DOUBLER IAW DOUBLAS AIRCRAFT ROD SKETCH NR 96-04-01-0002, AND SRM 51-1-20D AND INS	TALLED SLOT DOOR IAW SRM 51-3-0.  (X)				2	L	7	4 	4F				4A25    					 
1996060600147	19960606	00147	WP  	1996	6	6	ARWR960818       	1	19960515	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										STUB WING	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND RT WING UPPER SURFACE NR 3 STUB WING T/E HAS CORROSION.  REMOVED DAMAGED AREA, FABRICATED DOUBLER 	IAW DER ARW 950082-1011, TREATED AND PRIMED IAW SRM 51-1-8 AND INSTALLED IAW DER NR ARW 950082-1011.  (X)					2	L	7	4 	4F				4A25    					 
1996061300062	19960613	00062	WP  	1996	6	13	ARWR960947       	1	19960514	G	5754		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										INB SLOT OTB TE	DAMAGED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND RT WING UPPER SURFACE INBOARD SLOT, OUTBOARD TRAILING EDGE, HAS TEMPORARY REPAIR.  REMOVED TEMPORA	RY REPAIR, FABRICATED AND INSTALLED NEW REPAIR IAW DER NR 950082-1046.  TREATED AND PRIMED IAW SRM 51-1-8.  (X)					2	L	7	4 	4F				4A25    					 
1996060600148	19960606	00148	WP  	1996	6	6	ARWR961076       	1	19960515	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 173R-270R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DUE TO EXCESSIVE REPAIRS AND CORROSION ON SKIN FROM FS 173R TO FS 270R, STR 21R TO STR 31R, REMOVED AND REPLACED SKIN. R	EMOVED SKIN FROM FS 178.R TO FS 270.R FROM L21R TO L31 AND INSTALLED NEW SKIN IAW DER 950087-0028.  (X)					2	L	7	4 	4F				4A25    					 
1996060600149	19960606	00149	WP  	1996	6	6	ARWR961141       	1	19960515	G	5320	56417832	CAP             			DOUG  	DC8   	DC862       	3021970	WP  										FS 208 L31R-36R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE RT SIDE FRAME AT FS 208 HAS CORROSION APPROXIMATELY BETWEEN L21R AND 36R.  REMOVED AND CU	T CAP AT FS 208 FROM L17R AND L23R.  FABRICATED NEW IAW DAC 288851 AND DER 950087-0035A.  HEAT TREATED, TREATED AND PRIM	ED IAW SRM 51-1-8.  INSTALLED IAW DER 950087-0035A.  (X)				2	L	7	4 	4F				4A25    					 
1996053000059	19960530	00059	WP  	1996	5	30	ARWR961166       	1	19960426	G	5711		SPAR DOUBLER    			DOUG  	DC8   	DC862       	3021970	WP  										LT WS XCW 60	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LEFT WHEELWELL WING REAR SPAR DOUBLER AT STA XCW 60 HAS LOCAL CORROSION AT UPPER AREA.  REMOVED CO	RROSION, FOUND AREA BEYOND LIMITS IAW SRM 53-2-0.  FABRICATED MACHINED DOUBLER AND CLIP.  TREATED AND PRIMED IAW SRM 52-	1-8.  INSTALLED REPAIR IAW SRM 57-2-6.  REF:  OPERATOR CONTROL NR 1166.  (X)				2	L	7	4 	4F				4A25    					 
1996061300063	19960613	00063	WP  	1996	6	13	ARWR961354       	1	19960514	G	5330		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										FS 1530-1620	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				REMOVED AND REPLACED SKIN FROM FS 1530 TO FS 1620 AT L32R TO L32L, DUE TO CORROSION.  REMOVED AND REPLACED SKIN FROM FS 	1530 TO FS 1620 AT L32R TO L32L IAW SRM'S 53-5-2, 51-1-21, AND 51-1-20D.  TREATED AND PRIMED IAW SRM 51-1-8.  SEALED ARE	A IAW SRM 51-1-16.  SPLICE IAW DER NR 950087-0064.  (X)				2	L	7	4 	4F				4A25    					 
1996061300064	19960613	00064	WP  	1996	6	13	ARWR961425       	1	19960514	G	5313	5705593504	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 380 L29R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FS 380, L29R, FORWARD BASKET DOOR RT JAMB, HAS CORROSION.  CUT OUT DAMAGED AREA, FABRICATED REPAIR	 ANGLES IAW DER ARW 950178-0067.  INSTALLED REPAIR PER DER ARW 950178-0067.  (X)					2	L	7	4 	4F				4A25    					 
1996053000290	19960530	00290	WP  	1996	5	30	ARWR961433       	1	19960426	G	5320	5614739	BRACKET         			DOUG  	DC8   	DC862       	3021970	WP  										AC COMP RT SIDE	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND FUSELAGE RT SIDE A/C COMPARTMENT AREA SUPPORT BRACKET FOR THE AIR CONDITIONING MIXING VALVE HAS CO	RROSION IN DIFFERENT LOCATIONS.  REMOVED CORRODED BRACKET.  INSTALLED SERVICEABLE BRACKET, PN 5614739 IAW SRM 51-30 AND 	DC-8 MM 21-60-1.  (X)				2	L	7	4 	4F				4A25    					 
1996060600150	19960606	00150	WP  	1996	6	6	ARWR961744       	1	19960515	G	5751		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										LT OTBD AIL LE	CRACKED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LT OUTBOARD AILERON UPPER SURFACE AT OUTBOARD ATTACHING FITTING, L/E SKIN HAS A CRACK.  CUT DAMAGE	D SECTION, FABRICATED AND INSTALLED DOUBLER IAW DER NR 950082-1567.  TREATED AND PRIMED IAW SRM 51-1-8.  (X)					2	L	7	4 	4F				4A25    					 
1996060600151	19960606	00151	WP  	1996	6	6	ARWR961748       	1	19960513	G	5311		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										C4 DOOR	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LOWER AFT FUSELAGE C-4 DOOR CUT-OUT INNER SKIN CUT-OUT FRAME HAS HOLE AND CORROSION AROUND FRAME S	KIN.  REMOVED CORROSION IN AREA.  FOUND WITHIN LIMITS, STOP DRILLED CRACK, FABRICATED DOUBLER.  INSTALLED IAW DER NR MHA	 3062.  (X)				2	L	7	4 	4F				4A25    					 
1996060600152	19960606	00152	WP  	1996	6	6	ARWR961753       	1	19960513	G	5320		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										C4 DOOR PAN	CRACKED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND LOWER AFT FUSELAGE C-4 INTERIOR SKIN PAN (FRAME) HAS CRACKS IN DIFFERENT LOCATIONS AROUND PAN (FRA	ME).  STOP DRILLED CRACK AND REPAIRED IAW DER NR MHA 3062.  (X)					2	L	7	4 	4F				4A25    					 
1996060600153	19960606	00153	WP  	1996	6	6	ARWR961760       	1	19960513	G	5320		FRAME           			DOUG  	DC8   	DC862       	3021970	WP  										C2 DOOR PAN	CRACKED         	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, RT LOWER FUSELAGE C-2 DOOR INTERIOR SKIN PAN (FRAME) HAS CRACK AT CENTER BOTTOM.  STOP-DRILLED CRACK AND	 INSTALLED DOUBLER IAW DER NR M.H.A. 3064.  (X)					2	L	7	4 	4F				4A25    					 
1996060600154	19960606	00154	WP  	1996	6	6	ARWR961783       	1	19960513	G	5730	161E	PANEL           			DOUG  	DC8   	DC862       	3021970	WP  										WING CENTER	WRONG PART      	B			ARWR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND WING CENTER SECTION PANEL NR 161E, IS THE IMPROPER PANEL IN THAT LOCATION.  FABRICATED NEW PANEL I	AW DER M.H.A. 3063 AND SRM 51-1-8 AND SRM 51-1-30.  (X)					2	L	7	4 	4F				4A25    					 
1996061300065	19960613	00065	WP  	1996	6	13	ARWR961861       	1	19960514	G	5313	5754184505	LONGERON        			DOUG  	DC8   	DC862       	3021970	WP  										FS 145 L35R	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AFT BAGGAGE COMPARTMENT, LONGERON 35R, FS 1145, CORRODED, RIVETS POPPED.  REPAIRED LONGERON IAW D.	A.C. GLP 1745/96-04-25-002, GLP 1749 96-05-06-004.  (X)					2	L	7	4 	4F				4A25    					 
1996060600155	19960606	00155	WP  	1996	6	6	ARWR961896       	1	19960508	G	5730		SKIN            			DOUG  	DC8   	DC862       	3021970	WP  										LT WS XFS 560 LE	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				WHILE PEFORMING C-CHECK, FOUND CORROSION ON LT WING L/E AT APPROXIMATELY STA XFS 560.  INSTALLED REPAIR (DOUBLER) WITH F	ASTENERS AS REQUIRED IAW SRM 57-2-1, SEALED AREAS WITH P.R.C. 1422-B2 IAW SRM 51-1-16.  (X)					2	L	7	4 	4F				4A25    					 
1996061300066	19960613	00066	WP  	1996	6	13	ARWR961934       	1	19960514	G	5320	3705592	FITTING         			DOUG  	DC8   	DC862       	3021970	WP  										FS 1145-1160	CORRODED        	B			ARWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8969U					46070				DURING C-CHECK, FOUND AFT BAGGAGE COMPARTMENT L34R FITTING LOCATED BETWEEN FS 1145 AND FS 1160 HAS CORROSION.  REPAIRED 	END FITTING IAW DER ARW 95002-1747.  (X)					2	L	7	4 	4F				4A25    					 
1996091900005	19960919	00005	SO  	1996	9	19	AU960001         	1	19960102	G	3232	11027240306	SUPPORT         			EMB   	110   	EMB110P1    	3260122	SO  										LG DOOR ACT	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR DOOR ACTUATOR SUPPORT ASSEMBLY CRACKED INTO THREE PARTS - DOOR ACTUATOR ROD PNO 110-2721-68-07 BENT						1	L	7	2 	4T				A21SO   					 
1996091900006	19960919	00006	EA  	1996	9	19	AU960002         	2	19960102	G	8520	74309	BEARING         								LYC   	O540  	TIO540J2BD  	41532	EA  					NR 4 CON ROD	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L462561A			(AUS) ENGINE NO4 CONNECTING ROD BEARING FAILED IN AREA OF RELIEF FOR CONNECTING ROD BOLT SHANK											3	O			E14EA				 
1996091900007	19960919	00007	EU  	1996	9	19	AU960003         	1	19960103	G	7160	352002034	HOSE            			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ENG AIR INT	COLLAPSED       	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							L2549448A			(AUS) LH ENGINE INDUCTION HOSE BETWEEN ALTERNATE AIR BOX AND FUEL  CONTROL COLLAPSED - SUSPECT CAUSED BY FAULTY BATCH OF	 SCAT HOSES					1	H	7	2 	3O	3	O		A17EU   	1E4				 
1996091900008	19960919	00008	SO  	1996	9	19	AU960004         	1	19960104	G	3230	487155	SOLENOID        			PIPER 	PA31  	PA31        	7103102	SO  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					NA					(AUS) LANDING GEAR SELECTION LEVER SAFETY SOLENOID ACTUATOR HAD BEEN CABLE TIED IN A POSITION WHERE THE LANDING GEAR COU	LD BE SELECTEDTO THE 'UP' POSITION ON THE GROUND - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED MODIFICATION					1	L	7	2 	3O				A20SO   					 
1996091900009	19960919	00009	CE  	1996	9	19	AU960005         	1	19960104	G	5610	99110032	WINDSHIELD      			CESSNA	441   	441         	2076020	CE  										COCKPIT RT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WINDSHIELD CRACKED IN LOWER INBOARD CORNER - FOUND DURING X-RAY INSPECTION - INSPECTION FOUND THAT THE OUTER LA	MINATE HADBROKEN OFF ACROSS THE CORNER					1	L	7	2 	3T			RT	A28CE   					 
1996091900010	19960919	00010	EU  	1996	9	19	AU960006         	1	19960103	G	2731	HZ010H8012006	ROD             			BAC   	146   	146200A     	1500266	EU  										ELEVATOR CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ELEVATOR TRIM CONNECTING RODS CRACKED IN AREA OF AFT SWAGES - FOUND DURING INSPECTION IAW ER BA6-27-00-5A						2	H	7	4 	4F				A49EU   					 
1996091900011	19960919	00011	EA  	1996	9	19	AU960007         	2	19960101	G	8530	73456	PUSHROD         			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  					RT ENG NR 2 CYL	DISTORTED       	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							L1603751A			(AUS) NO2 CYLINDER EXHAUST VALVE PUSHROD BENT - SUSPECT PUSHROD WAS  SLIGHTLY BENT WHEN FITTED AT RECENT OVERHAUL						1	H	7	2 	3O	3	O		A31EU   	1E10				 
1996091900012	19960919	00012	CE  	1996	9	19	AU960008         	1	19960103	G	2422	PC17	INVERTER        			BEECH 	200   	200BEECH    	1152920	CE  										DC POWER DISTRIB	CONTAM-WATER    	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					23315382A					(AUS) NO1 AND NO2 INVERTERS FAILED DURING FLIGHT IN HEAVY RAIN - WHEN  AIRCRAFT RETURNED TO CLEAR AIR BOTH INVERTERS OPE	RATED NORMALLY -ON RETURN TO BRISBANE BOTH INVERTERS WERE CHECKED - ONE INVERTER WAS SENT FOR REPAIR DUE TO DETERIORATIO	N OF PROTECTIVE COATING - THE OTHER INVERTER WAS REFITTED SERVICEABLE				1	L	7	2 	4T				A24CE   					 
1996091900013	19960919	00013	CE  	1996	9	19	AU960009         	1	19960104	G	5711		SPAR            			BEECH 	55    	D55         	1152730	CE  										OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING SPAR CORRODED IN AREA BEHIND LH ENGINE - FOUND DURING  INSPECTION IAW AD/B55/29 AMDT1 - AIRCRAFT HAD BEEN 	PREVIOUSLYOPERATED IN A SALT LADEN ENVIRONMENT BY THE LAST OWNER					1	L	7	2 	3O				3A16    					 
1996091900014	19960919	00014	EU  	1996	9	19	AU960010         	1	19960103	G	7110	7271110505	COWLING         			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					ENGINE COWL SYS	DAMAGED         	W				K				NONE                    				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CL	CLIMB          	1			AU	S 							367303K			(AUS) LH ENGINE INBOARD COWL UNLATCHED - PROPELLER SLIPSTREAM HAD  DISTORTED THE COWL CRACKING SEVERAL INTERNAL STIFFENE	R FRAMES -SUSPECT LATCHES LEFT UNLOCKED FOLLOWING ENGINE SERVICING - PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6				 
1996091900015	19960919	00015	NM  	1996	9	19	AU960011         	1	19960107	G	5720	85711069	PLATE           			DHAV  	DHC8  	DHC8102     	2809003	NM  										OUTER WING SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					151					(AUS) RH LADDER PLATE HAD EXCESSIVELY WORN PANEL SCREW HOLES - INSPECTION FOUND CORROSION REMOVAL REPAIR CARRIED OUT PRE	VIOUSLY BUT NOT IN ACCORDANCE WITH APPROVED REPAIR SCHEME -  PERSONNEL/MAINTENANCE ERROR - LADDER PLATE IS A STRUCTURAL 	PLATE LOCATED ON THE UPPER WING BETWEEN THE RIGHT AND LEFT ENGINE  NACELLES				2	H	7	2 	4T			RT	A13NM   					 
1996091900016	19960919	00016	SO  	1996	9	19	AU960012         	1	19960109	G	3260		CONNECTOR       			PIPER 	PA34  	PA34200     	7103405	SO  										LG SQUAT SW	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR SQUAT SWITCH WIRING CONNECTOR LOCATED AT LH WING DISCONNECT EXCESSIVELY CORRODED AND OVERHEAT	ED - FURTHERINVESTIGATION FOUND RH MLG CONNECTOR AT RH WING DISCONNECT IN A  SIMILAR CONDITION					1	L	7	2 	3O				A7SO    					 
1996091900017	19960919	00017	SO  	1996	9	19	AU960013         	1	19960110	G	6120	D20816	ACCUMULATOR     	MCAULY      	D20816      	PIPER 	PA34  	PA34220T    	7103420	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROP CNTRL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					820123			AN6929A		(AUS) PROPELLER ACCUMULATOR EXTERNAL CASING SEVERELY CORRODED AND  CHROME FINISH DELAMINATED - WHEN THE END CAPS WERE RE	MOVED IT WASFOUND THAT THE CHROME FINISH OF THE INTERNAL BORE WAS SEVERELY DELAMINATED AND THE ACCUMULATOR WAS HEAVILY C	ONTAMINATED WITHCHROME FLAKES ON BOTH SIDES OF THE FLOATING PISTON FURTHER EXAMINATION OF THE OIL SYSTEM COULD FIND NO M	ORE CONTAMINATION - SUSPECT UNIT WAS NOT NEW WHEN FITTED AND CHROME PLATING WAS  POORLY APPLIED			1	L	7	2 	3O				A7SO    		5	C	P920	 
1996091900018	19960919	00018	NM  	1996	9	19	AU960014         	1	19960110	G	3210	400033501	SIDE BRACE      			PIPER 	PA60  	PA60601P    	7106012	NM  										MAIN GEAR SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR LOWER SIDE BRACES BROKEN AT CENTRE PIVOT POINT						1	M	7	2 	3O			RT	A17WE   					 
1996091900019	19960919	00019	CE  	1996	9	19	AU960015         	1	19960112	G	7110	1213261216	FLAP            			CESSNA	206   	U206G       	2073356	CE  										ENGINE COWL SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE RH COWL FLAP ASSEMBLY CORRODED INTERNALLY BEYOND REPAIR - AIRCRAFT OPERATES AS A SEAPLANE IN A SALT LADEN E	NVIRONMENT					1	H	7	1 	3O				A4CE    					 
1996091900020	19960919	00020	CE  	1996	9	19	AU960016         	1	19960112	G	7160	12507058	DUCT            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENG AIR INT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRBOX DUCT ASSEMBLY CRACKED BEYOND REPAIR - DUCT ASSEMBLY HAS BEEN PREVIOUSLY REPAIRED						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996091900021	19960919	00021	CE  	1996	9	19	AU960017         	1	19960111	G	2720	965240262	BELLCRANK       			BEECH 	55    	D55         	1152730	CE  										RUDDER CONTROL S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH RUDDER BELLCRANK SEVERELY CORRODED - AIRCRAFT IS USED TO CARRYLIVE SEAFOOD WITH SUBSEQUENT CONTAMINATION BY SAL	T LADEN PRODUCTS					1	L	7	2 	3O				3A16    					 
1996091900022	19960919	00022	CE  	1996	9	19	AU960018         	1	19960109	G	5312	12124027	BULKHEAD        			CESSNA	210   	210L        	2073448	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE REAR BULKHEAD CRACKED IN AREA OF RH HORIZONTAL  STABILISER FORWARD ATTACHMENT FITTING						1	H	7	1 	3O				3A21    					 
1996091900023	19960919	00023	CE  	1996	9	19	AU960019         	1	19960111	G	5523	4562	TRIM TAB        			BBAVIA	8     	8KCAB       	2110612	CE  										ELEVATOR STRUCT	DISTORTED       	W				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AU	S 										(AUS) ELEVATOR TRIM TAB DAMAGED AT INBOARD END - LOWER TRIM CABLE  TURNBUCKLE SEPARATED AT TURN BARREL - RIVETS ATTACHIN	G TRIM TAB TO TAB HINGE REPLACED APPROXIMATELY 700 HOURS PREVIOUSLY - RIVET TAILS HAD WORKED EXTENSIVELY AND WERE NOT HO	LDING THE STRUCTURETOGETHER - ONLY TWO RIVETS AT THE CONTROL ARM WERE SATISFACTORY -THE SKIN HAS TORN AWAY FROM THESE TW	O RIVETS DURING FINAL FAILURE- PERSONNEL/MAINTENANCE ERROR			1	H	7	1 	3O				A21CE   					 
1996100200001	19961002	00001	SO  	1996	10	2	AU960020         	1	19960114	G	2916		RESERVOIR       			PIPER 	PA31  	PA31        	7103102	SO  										MAIN HYD SYS	LOW QUANTITY    	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) HYDRAULIC RESERVOIR LOW QUANTITY - SUSPECT FAULTY MICROSWITCH  PREVENTED CORRECT OPERATION OF LANDING GEAR						1	L	7	2 	3O				A20SO   					 
1996091900024	19960919	00024	EA  	1996	9	19	AU960021         	2	19960109	G	8550		NOZZLE          			PIPER 	PA36  	PA36285     	7103610	SO  	LYC   	O720  	IO720A1B    	41546	EA  					ENGINE OIL SYS	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							L12775AA			(AUS) ENGINE OIL SYSTEM CONTAMINATED BY METAL - NO3 CYLINDER OIL SQUIRT NOZZLE MISSING - THE NOZZLE BALL WAS FOUND IN TH	E CRANKCASE ANDTHE REMAINDER OF THE NOZZLE WAS FOUND IN THE SUMP FOLLOWING  REMOVAL - INVESTIGATION FOUND THAT THE NOZZL	E HAD BEEN CRUSHED BETWEEN THE CONNECTING ROD CAP AND THE CRANKCASE AND DESTROYED - SUSPECT THE NOZZLE WAS UNDERTORQUED 	DURING ASSEMBLY			1	L	7	1 	3O	3	O		A10SO   	1E15				 
1996091900025	19960919	00025	CE  	1996	9	19	AU960022         	1	19960102	G	5310	24120201	STRUCTURE       			CESSNA	172   	172RG       	2072438	CE  										TAIL CONE TUNNEL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT FUSELAGE TAILCONE TUNNEL CONTAINED SEVERE CORROSION AT THE AFT END						1	H	7	1 	3O				3A17    					 
1996091900026	19960919	00026	CE  	1996	9	19	AU960023         	1	19960112	G	3230		TERMINAL        			BEECH 	76    	76          	1153005	CE  										LG EXT-RETRACT S	BROKEN          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR SELECTOR RELAY TO POWER PACK CONNECTION BROKEN AT TERMINAL						1	L	7	2 	3O				A29CE   					 
1996091900027	19960919	00027	SO  	1996	9	19	AU960024         	2	19960101	G	8530	646286	EXHAUST VALVE   	CONT        	VALVEGUIDE  	CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE CYL SEC	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			100  		B4593B4597		451133			(AUS) ENGINE CYLINDERS HAD WORN EXHAUST VALVES PN 646286 AND VALVE GUIDES PN 643767 - VALVE STEMS ALSO NECKED - SUSPECT 	CAUSED BY USE OF MOGAS					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1996091900028	19960919	00028	SW  	1996	9	19	AU960025         	1	19960108	G	2910	2781032682	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  										MAIN HYD SYS	HOLED           	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE LEAKING - INSPECTION FOUND PIN HOLE PERFORATION ONOUTSIDE RADIUS OF BEND						2	L	7	2 	4T			RT	A18SW   					 
1996091900029	19960919	00029		1996	9	19	AU960026         	1	19960115	G	7603	565549004	CABLE           																	POWER CONTROL SY	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) THROTTLE CABLE STIFF IN OPERATION - CABLE WAS NEW FITMENT -  INVESTIGATION FOUND THAT THE ROD END ATTACHING THE CA	BLE TO THE CARBURETTOR HAD BEN BENT EITHER DURING MANUFACTURE OR DURING PACKAGING/TRANSPORT																		 
1996091900030	19960919	00030	CE  	1996	9	19	AU960027         	1	19960110	G	5320		BULKHEAD        			CESSNA	182   	182H        	2072718	CE  										FWD DOOR POST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOOR POST BULKHEAD CRACKED AT BEND RELIEF NOTCH ON RH  SIDE - CRACK DISAPPEARS BEHIND DOUBLER						1	H	7	1 	3O			NT	3A13    					 
1996091900031	19960919	00031	EU  	1996	9	19	AU960028         	1	19960112	G	7160	352002034	HOSE            			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ENG AIR INT RT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ENGINE INDUCTION HOSE COLLAPSED IN MID SECTION - INNER WIRE SEPARATED FROM OUTER WALL						1	H	7	2 	3O	3	O		A17EU   	1E4				 
1996091900032	19960919	00032	EU  	1996	9	19	AU960029         	1	19960112	G	7160	352002034	HOSE            			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ENG AIR INT LT	FAILED          	W				K				NONE                    				O	E	R	OTHER                     	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE INDUCTION HOSE COLLAPSED						1	H	7	2 	3O	3	O		A17EU   	1E4				 
1996091900033	19960919	00033	EU  	1996	9	19	AU960030         	1	19960112	G	7160	352002034	HOSE            			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ENG AIR INT RT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ENGINE INDUCTION HOSE BETWEEN AIR FILTER AND FUEL SERVO UNIT  INTERNAL WIRE DISPLACED						1	H	7	2 	3O	3	O		A17EU   	1E4				 
1996091900034	19960919	00034	SW  	1996	9	19	AU960031         	1	19960115	G	5720		STRAP           			GULSTM	500   	500S        	0141107	SW  										OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING AUXILIARY SPAR TO INBOARD RIB DOUBLER CRACKED IN RADIUS -CRACK LENGTH 5MM (0.196IN) - WING TO FUSELAGE STR	AP CRACKED -FOUND DURING INSPECTION IAW AD/AC/93					1	H	7	2 	3O				6A1     					 
1996091900035	19960919	00035	CE  	1996	9	19	AU960032         	1	19960103	G	2910	58171028	PIPE            			CESSNA	404   	404CESSNA   	2075901	CE  										MAIN HYD SYS	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 										(AUS) HYDRAULIC PRESSURE PIPE CRACKED IN AREA OF BEND RADIUS - LOSS OF HYDRAULIC FLUID						1	L	7	2 	3O				A25CE   					 
1996091900036	19960919	00036	CE  	1996	9	19	AU960033         	1	19960116	G	5312		BULKHEAD        			BEECH 	55    	D55         	1152730	CE  										FS257-271	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEADS LOCATED AT FS 257.6 AND FS 271.92 CRACKED - BULKHEADS ARE LOCATED AT THE FORWARD AND AFT HORIZO	NTALSTABILISER STUB SPARS - FURTHER INVESTIGATION FOUND THAT THE CRACK WAS IDENTIFIED AS A SCORE MARK					1	L	7	2 	3O				3A16    					 
1996091900037	19960919	00037		1996	9	19	AU960034         	4	19960116	G	2562	ELT1104	ELT             			CESSNA	421   	421C        	2076016	CE  										EMERGENCY EQUIP	ACTIVATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					55101					(AUS) ELT ACTIVATED 4 HOURS AFTER LAST FLIGHT - NO INDICATION EVIDENT  ON REMOTE SWITCH - THE UNIT WAS TURNED OFF AS PER	 INSTRUCTIONS BUT STILL CONTINUED TO TRANSMIT - THE UNIT WAS THEN TURNED OFF BYDISCONNECTING THE BATTERY					1	L	7	2 	3O				A7CE    					 
1996091900038	19960919	00038	EA  	1996	9	19	AU960035         	2	19960111	G	7414	M3485	BEARING         	SLICK       	4371        						LYC   	O360  	O360A4K     	41514	EA  					ENG MAG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					92020112		L2674136A			(AUS) MAGNETO DISTRIBUTOR END BEARING LOOSE AND SPINNING IN HOUSING -  MAGNETO FILLED WITH BLACK DUST											3	O			E286				 
1996091900039	19960919	00039	EU  	1996	9	19	AU960036         	2	19960101	G	7200	MAKILA1A	ENGINE          	TMECA       	MAKILA1A    	SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					ENGINE (TURBINE	OVER TEMP       	W				K	E			NONE                    	ENGINE SHUTDOWN         			M			OVER TEMP                 			NR	NOT REPORTED   	1			AU	S 			877  		241		241			(AUS) ENGINE OVERTEMPED ON START - EGT WAS BELOW 900 DEGREES C FOR 38  SECONDS - EGT LIMITS ON START 810 DEGREES C TO 90	0 DEGREES C FOR 2 SECONDS - SUSPECT START FOLLOWED ABORTED START WHICH LEFT A  SUBSTANTIAL AMOUNT OF FUEL IN THE ENGINE					2	G	7	2 	4U	4	U		H4EU    	E12NE				 
1996091900040	19960919	00040	EU  	1996	9	19	AU960037         	1	19960116	G	7160	352002034	HOSE            			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ENG AIR INT RT	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) LH ENGINE INDUCTION AIR HOSE BETWEEN AIR BOX AND FUEL CONTROL  COLLAPSED - RH ENGINE INDUCTION HOSE INSPECTED AND 	WAS FOUND TOBE ALSO CLOSE TO FAILURE - NUMEROUS OTHER FAILURES RECORDED IN FLEET					1	H	7	2 	3O	3	O		A17EU   	1E4				 
1996091900041	19960919	00041	CE  	1996	9	19	AU960038         	1	19960112	G	2434		BRUSH           		ALTERNATOR  	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					GENERATOR-ALT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1850 				L330176			(AUS) ALTERNATOR BRUSHES WORN EXCESSIVELY - PIGTAIL JUNCTION WORN INTO SLIP RING						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996091900042	19960919	00042	CE  	1996	9	19	AU960039         	1	19960112	G	5320		DOOR POST       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					FS 65.3	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1850 							(AUS) AFT DOOR POST ASSEMBLY CRACKED IN AREA OF INNER RELIEF AT FS 65.3 TOWARDS OUTBOARD LANDING GEAR HOUSING FASTENERS						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996091900043	19960919	00043	SW  	1996	9	19	AU960041         	1	19960104	G	2560	412419	ARM             			BELL  	412   	412         	1182202	SW  										EMERGENCY EQUIP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HOIST ARM CRACKED - SOME CORROSION EVIDENT IN AREA OF CRACKING - ARM IS USED TO ATTACH A LUCAS WESTERN RESCUE WINC	H TO THEAIRCRAFT					1	G	7	2 	4U				H4SW    					 
1996091900044	19960919	00044	SO  	1996	9	19	AU960042         	1	19960109	G	5342		FITTING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ATTACH FITTINGS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER STABILATOR ATTACHMENT FITTINGS CORRODED - AIRCRAFT HAD BEEN SITTING DORMANT FOR APPROXIMATELY 12 MONTHS - CO	RROSION FORMED BETWEEN ALUMINIUM SKIN AND STEEL FITTINGS					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996091900045	19960919	00045	CE  	1996	9	19	AU960043         	1	19960112	G	5751		AILERON         			BEECH 	95    	95B55       	1152729	CE  										WING AIL RT	OUT OF BALANCE  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FOLLOWING REPAINTING WHEN THE CONTROLS WERE CHECKED FOR BALANCE  IT WAS FOUND THAT THE RH AILERON WAS 0.5 INLBS NO	SE HEAVY AND THELH AILERON WAS 8 INLBS TRAILING EDGE HEAVY - CHECKS ON AN AILERON FROM ANOTHER AIRCRAFT FOUND THAT IT WA	S ALSO OUT OF BALANCE -FOLLOWING INVESTIGATION IT IS SUSPECTED THAT THE AILERONS HAVE BEEN THAT WAY SINCE MANUFACTURE AN	D THAT IT IS THE MAINTENANCE MANUAL AILERON BALANCE PARAMETERS THAT HAVE CHANGED			1	L	7	2 	3O			RT	3A16    					 
1996091900046	19960919	00046	SW  	1996	9	19	AU960044         	1	19960105	G	3230		SEAL            			SWRNGN	SA227 	SA227AC     	8780603	SW  										LT MLG JACK	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LH MAIN LANDING GEAR RETRACTION JACK SEALS SUSPECT FAULTY						2	L	7	2 	4T			RT	A8SW    					 
1996091900047	19960919	00047	CE  	1996	9	19	AU960045         	1	19960110	G	5720		STRUT           			BOEING	75    	B75N1       	1380144	CE  										OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING INTERPLANE STRUT CRACKED ON FORWARD FACE AT TOP END OF STRUT- CRACK EXTENDS APPROXIMATELY 50.8MM (2IN) DOWN L	EADING EDGE					1	Q	7	1 	3R				A743    					 
1996091900048	19960919	00048	SO  	1996	9	19	AU960046         	1	19960105	G	5521		SPAR            		ELEVATOR    	PIPER 	PA31  	PA31350     	7103110	SO  										ELT-RT ELEV	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ELEVATOR SPARS CRACKED AT TIPS ON BOTH SIDES OF TOP ANDBOTTOM FLANGES						1	L	7	2 	3O				A20SO   					 
1996091900049	19960919	00049	EA  	1996	9	19	AU960047         	2	19960111	G	7230		BLADE           								PWA   	PT6   	PT6A34      	52043	EA  					T ENG CMPRSR/FAN	FOD             	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 							40582			(AUS) ENGINE GAS GENERATOR 1ST STAGE COMPRESSOR BLADES (15OFF) CONTAIND FOD TO THE LEADING EDGES - INVESTIGATION FOUND T	HAT THE 1ST STAGECOMPRESSOR SPACER RUBBED ON THE STATOR AND CRACKED CIRCUMFERENTIALLY LIBERATING A PIECE OF MATERIAL APP	ROXIMATELY 12.7MM (0.5IN) WIDE AND 76.2MM (3IN) LONG WHICH WAS INGESTED THROUGH THE COMPRESSOR - DAMAGE TO THE TRAILING 	EDGES OF THE 1ST STAGE STATOR BLADES - EVIDENCE OF FURTHER DAMAGE DOWNSTREAM - ONE COMPRESSOR BLADE HAD FORE AND AFT MOV	EMENT OF APPROXIMATELY5.08MM TO 7.62MM (0.2IN TO 0.3IN)							4	T			E4EA				 
1996091900050	19960919	00050	NM  	1996	9	19	AU960048         	1	19960111	G	3246	AN535A	BOLT            			PIPER 	PA60  	PA60600     	7106001	NM  										LG WHEEL/BRAKE S	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN WHEEL HUB TIE BOLTS FAILED - BOLTS HAD EITHER HEADS MISSING OR HEADS SEPARATED DURING REMOVAL - SUSPECT CAUSE	D BY BOLTS BEING OVERTORQUED					1	M	7	2 	3O			RT	A17WE   					 
1996091900051	19960919	00051	SO  	1996	9	19	AU960049         	1	19960108	G	5521		SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										LT-RT ELEV	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ELEVATOR SPARS CRACKED AT OUTBOARD TIP IN BOTH TOP AND BOTTOM RADII - CRACKS RANGE FROM 19MM TO 39MM (0.	75IN TO 1.75IN) - BOTH LH AND RH SPARS ALSO CRACKED APPROXIMATELY 9MM TO 13MM  (0.375IN TO 0.5IN) IN LENGTH AT THE OUTBO	ARD HINGE AREA				1	L	7	2 	3O				A20SO   					 
1996091900052	19960919	00052	CE  	1996	9	19	AU960050         	1	19960112	G	7603		CABLE           			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					THROTTLE	BROKEN          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 							272978R			(AUS) THROTTLE INNER CABLE BROKE APPROXIMATELY 25MM (1IN) FROM SLIDING SLEEVE INSIDE FLEXIBLE PART OF CABLE ON THE ENGIN	E SIDE - CABLE HAD A VERY MINOR KINK NEAR THE ATTACHMENT BRACKET - SUSPECT  INCORRECT INSTALLATION - PERSONNEL/MAINTENAN	CE ERROR				1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
1996091900053	19960919	00053	CE  	1996	9	19	AU960051         	1	19960118	G	5533	04310093	FITTING         			CESSNA	150   	A152        	2071836	CE  										VERT STAB STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILISER LH AND RH FITTINGS CORRODED - THE STABILIZER BRACKETS HAD NEVER BEEN PAINTSTRIPPED - FOUND DUR	ING INSPECTIONIAW AD/150/31 AMDT3 (REQUIREMENTS 2A AND 2B) - PERSONNEL/MAINTENANCE ERROR					1	H	7	1 	3O				3A19    					 
1996100300812	19961003	00812	SO  	1996	10	3	AU960052         	1	19960117	G	5521		SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										ELT OUTB ELEV	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OUTBOARD ELEVATOR SPAR WEB CRACKED - CRACK LENGTH 19.05MM (0.75IN) - FOUND DURING INSPECTION IAW AD/PA31/126 AM	DT1					1	L	7	2 	3O				A20SO   					 
1996100300813	19961003	00813	EU  	1996	10	3	AU960053         	1	19960112	G	3210	NB40075	BRACKET         			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  					MAIN GEAR SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MLG SUPPORT BRACKET FLANGES BROKEN AWAY FROM THE COLLAR IN TWOPLACES OPPOSITE ONE ANOTHER - ONE SECTION BREAK I	S APPROXIMATELY 100MM (4IN) AND THE OPPOSITE BREAK IS APPROXIMATELY 77MM (3IN) - THERE ARE CLEAR SIGNS OF INTERGRANNULAR	 CORROSION THROUGH THEBREAK AREAS - THE SUPPORT BRACKET HAS BEEN FITTED TO THE AIRCRAFTFOR 8106 HOURS - THE AIRCRAFT OPE	RATES FROM ROUGH LANDING STRIPS IN THE TORRES STRAIT AREA			1	H	7	2 	3O	3	O		A17EU   	E295				 
1996100300814	19961003	00814	EU  	1996	10	3	AU960054         	1	19960101	G	5520		ELEVATOR        			FOKKER	F28   	F28MK4000   	4990810	EU  										ELEVATOR STRUCT	OUT OF BALANCE  	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) PILOT EXPERIENCED FLUTTER THROUGH THE CONTROL COLUMN AND AIRFRAMEWHICH COMMENCED AT MACH 0.67 TO 0.69 - FLUTTER WO	RSENED TO PUMPING ACTION AND CEASED WHEN SPEED WAS REDUCED TO BELOW 0.67 MACH - SUSPECT LH ELEVATOR UNBALANCED - WEIGHTS	 ADDED TO LHELEVATOR				2	L	7	2 	4F			RT	A20EU   					 
1996100300815	19961003	00815	NE  	1996	10	3	AU960055         	2	19960121	G	7260		GEAR            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					T ENG AUX DRIVE	SEPARATED       	W				K	E			NONE                    	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							LF050235			(AUS) NO3 ENGINE ACCESSORY GEARBOX INPUT BEVEL GEAR SEPARATED FROM THE MOUNTING FLANGE IN THE CASE - THE SLIMSERTS AND B	OLTS WERE STILL ATTACHED TO THE GEAR AND BEARING HOUSING - METAL CONTAMINATION OFENGINE OIL SYSTEM					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996100300816	19961003	00816	NE  	1996	10	3	AU960056         	2	19960120	G	7200		ENGINE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE SYS	BIRD STRIKE     	W				K				NONE                    				E	C		VIBRATION/BUFFET          	F.O.D.                    		TO	TAKEOFF        	1			AU	S 										(AUS) DURING TAKEOFF THE AIRCRAFT HIT A FLOCK OF GALAHS - ALL ENGINE PARAMETERS REMAINED NORMAL FOLLOWING INGESTION - NO	1 ENGINE REQUIRED MAINTENANCE AND NO3 ENGINE WAS REMOVED FOR RECTIFICATION DUE TO MINOR DAMAGE - SEE MDR 96/0176 FOR ADD	ITIONAL INFORMATION				2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996101000314	19961010	00314	NM  	1996	10	10	AU960057         	1	19960111	G	5210	80330034	RESERVOIR       			BOEING	747   	747438      		NM  										CREW-PASS DOOR S	EMPTY           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			20   							(AUS) MAIN ENTRY DOOR EMERGENCY POWER RESERVOIR BOTTLE REQUISITIONED FROM STORES (WITH SERVICEABLE TAG) WAS EMPTY - INVE	STIGATION FOUND THAT THERE WAS A LEAK FROM THE PRESSURE GAUGE ADAPTER -  SUSPECT CAUSED BY DROPPING OR DAMAGING THE BOTT	LE AND GAUGESOMEWHERE IN THE PERIOD FOLLOWING OVERHAUL AND BEFORE DELIVERY TOTHE AIRCRAFT				2	L	7	4 	4F			RT	A20WE   					 
1996100900004	19961009	00004		1996	10	9	AU960058         	4	19960114	G	2330	6224096001	CLIP            			BOEING	747   	747338      		NM  										PA & ENTERTAINME	MISSING         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) NO3 PA SYSTEM MIGRATED FROM ITS RACK DUE TO THE ABSENCE OF A CAMLOCK CLIP RETAINER - NO AUDIBLE PA SYSTEM ON UPPER	 DECK - PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4F			RT	A20WE   					 
1996100300817	19961003	00817	NM  	1996	10	3	AU960059         	1	19960118	G	2701	5110001	CONTROL COLUMN  			CHILD 	S2    	S2APITTS    	0110201	NM  	LYC   	O360  	IO360A1A    	41514	EA  					ELEVATOR CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AB	AEROBATIC      	1			AU	S 										(AUS) AFT CONTROL COLUMN BROKE IN AREA IN LINE WITH FORE AND AFT GUSSETWELD AND PRESS TO TALK (PTT) WIRING HOLE AT BOTTO	M OF STICK					1	Q	7	1 	3O	3	O		A8SO    	1E10				 
1996101000315	19961010	00315	EA  	1996	10	10	AU960060         	2	19960118	G	8520	75061	BOLT            	LYC         	O360A1D     	MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					NR 3CYL CON ROD	BROKEN          	W				K				NONE                    				E	Y	K	VIBRATION/BUFFET          	ENGINE STOPPAGE           	FLUID LOSS                	LD	LANDING        	1			AU	S 					L665036		L665036			(AUS) NO3 CYLINDER CONNECTING ROD BOLT BROKE CAUSING OTHER BOLT TO BEND AND THEN BREAK - CONNECTING ROD WAS TORN FROM PI	STON - MAJOR INTERNAL DAMAGE TO ENGINE AND CRANKCASE					1	L	7	1 	3O	3	O		2A3     	E286				 
1996101000316	19961010	00316	SO  	1996	10	10	AU960061         	1	19960121	G	2612	1734361450F	FIRE DETECTOR   			GRUMAN	G73   	G73T        		SO  	PWA   	PT6   	PT6A34      	52043	EA  					RT ENG	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ENGINE FIRE DETECTOR GIVING FALSE FIRE INDICATION - RESISTANCECHECK OF DETECTOR WAS 8.5K OHMS						1	H	7	2 	3R	4	T		A783    	E4EA				 
1996101000317	19961010	00317	WP  	1996	10	10	AU960062         	1	19960115	G	5720	SBEHB5195	EYE BOLT        			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  										OUTER WING SYS	MISMODIFIED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING WIRE REPAIR ALL EYEBOLTS WERE REMOVED FROM THE LOWER  STARBOARD FRONT MAIN SPAR AT THE WING STRUT ATTACHMEN	T POINT - INSPECTION OF THE EYEBOLTS FOUND THAT ONE IS SUSPECTED TO HAVE A HOME MADE 'T' SECTION ATTACHED TO THE HEAD OF	 THE BOLT WITHSOLDER - UNAPPROVED PART - UNAPPROVED MODIFICATION - SEE MDR 96/0083 FOR FURTHER INFORMATION - DEFECTS APP	EAR TO BE FOR THE SAME PART ALTHOUGH DIFFERENT PART NUMBERS ARE RECORDED			1	Q	7	1 	3I				A8EU    					 
1996101000318	19961010	00318	CE  	1996	10	10	AU960063         	1	19960122	G	7820	075016189	MUFFLER         			CESSNA	185   	185B        	2072806	CE  	CONT  	O470  	IO470F      	17026	SO  					ENG NOISE SUPPRS	CRACKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 							76735			(AUS) ENGINE MUFFLER TO OVERBOARD PIPE WELDED JOINT CRACKED - SCORCHINGOF LOWER COWL IN AREA OF CRACK - A NEW EXHAUST MU	FFLER HAD BEENFITTED AT THE LAST PERIODIC INSPECTION 8 HOURS PREVIOUS - SUSPECT PIPE CONTACTED COWL IN AREA OF CUTOUT - 	PERSONNEL/MAINTENANCEERROR				1	H	7	1 	3O	3	O		3A24    	3E1				 
1996101000319	19961010	00319	SW  	1996	10	10	AU960064         	1	19960117	G	2910	27810322684	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  										MAIN HYD SYS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) STAINLESS STEEL HYDRAULIC PIPE LOCATED IN THE RH ENGINE NACELLE  AT THE REAR OF THE FIREWALL CRACKED AND LEAKING O	N BEND RADIUS - TOTAL LOSS OF HYDRAULIC PRESSURE					2	L	7	2 	4T			RT	A18SW   					 
1996101000320	19961010	00320	SW  	1996	10	10	AU960065         	1	19960119	G	6720	KP4	BEARING         			BELL  	47    	47G3B       	1181026	SW  										TAIL RTR CNTRLS	SEIZED          	W				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) TAIL ROTOR CONTROL BARREL BEARING SEIZED - BEARINGS ARE SEALED UNITS						1	G	7	1 	3O				2H3     					 
1996101000321	19961010	00321	NE  	1996	10	10	AU960066         	1	19960114	G	3150	OL327	LIGHT           			SKRSKY	S76   	S76A        	8143006	NE  										CENTRAL WARNING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MASTER CAUTION AND CAUTION ADVISORY PANEL DIODES (5OFF) BLOWN -  SUSPECT FAULTY LAMP						1	G	7	2 	3U				H1NE    					 
1996101000322	19961010	00322	EU  	1996	10	10	AU960067         	1	19960110	G	3222	8804200410	AXLE            			SOCATA	MS893 	MS893E      	8402838	EU  						HARTZL				NOSE-TAIL GEAR S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR AXLE CRACKED - FOUND DURING INSPECTION IAW AD/MSR/32						1	L	7	1 	3O				7A14    					 
1996101000323	19961010	00323	EU  	1996	10	10	AU960068         	1	19960122	G	5720	82051C2	WING            			GROB  	G115  	G115C       	1660303	EU  	LYC   									OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					82051C2					(AUS) LH AND RH WINGS CRACKED IN AREA OF LANDING GEAR ATTACHMENT						1	L	7	1 	3O			NT	A57EU   					 
1996101000324	19961010	00324	NE  	1996	10	10	AU960069         	2	19960122	G	7240		LINER           	PWA         	PW4000      						PWA   	4056  	PW4056      		NE  					T ENG BURNER SEC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0		P727316			(AUS) LH ENGINE OUTER COMBUSTION LINER CONTAINED CRACKS IN THREE ADJACENT LOUVRES (NO7, NO8 AND NO9) IN THE 5 O'CLOCK PO	SITION -NO1 IGNITOR PLUG GUIDE MISSING - NO2 IGNITOR PLUG GUIDE CRACKED  FOR 75% OF CIRCUMFERENCE										4	F			E24NE				 
1996101000325	19961010	00325		1996	10	10	AU960070         	4	19960111	G	3450	066400900	CONVERTER       		KN72        	GULSTM	GA7   	GA7         	3960401	SO  	LYC   									DEPDNT POSN DATA	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3682					(AUS) VOR/LOC CONVERTER FAULTY - CAUSED BY FAILURE OF IC105						1	L	7	2 	3O				A17SO   					 
1996102300006	19961023	00006	NE  	1996	10	23	AU960071         	2	19960102	G	7321	R6409	FCU             			BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					ENG FUEL CONTROL	FAULTY          	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			AU	S 					R6409		P715083			(AUS) NO4 ENGINE FUEL CONTROL UNIT SUSPECT FAULTY DUE TO INTERNAL  LINKAGE WEAR						2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1996101000326	19961010	00326	EA  	1996	10	10	AU960072         	2	19960122	G	8530	SL134441	PIN             			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  					ENG NR 1 CYL	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			372  				L54171A			(AUS) ENGINE NO1 PISTON PIN FRACTURED IN CENTRE CAUSING PISTON PIN BOSSTO BREAK EVENLY ON BOTH SIDES OF PISTON - DURING 	THE 100 HOURLYINSPECTION THE OIL PRESSURE FILTER WAS FOUND TO CONTAIN LARGE  AMOUNTS OF STEEL AND ALLOY AND THE ENGINE W	AS STRIPPED - DAMAGETO TAPPET BODIES, CAMSHAFT, CONNECTING RODS, CRANKCASE AND CYLINDER SKIRTS - MEF INVESTIGATION FOUND	 THAT FAILURE WAS CAUSEDBY FATIGUE ORIGINATING FROM CORROSION PITTING ON THE SURFACE OF  THE PISTON PIN			1	L	7	2 	3O	3	O		A29CE   	E286				 
1996101000327	19961010	00327	CE  	1996	10	10	AU960073         	1	19960123	G	2730	071250011	TRIM JACK       			CESSNA	185   	A185F       	2072821	CE  						MCAULY				ELEVATOR CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM JACK SCREWS LOOSE AND WORN - SPROCKET ROLL PIN LOOSE - SUSPECT LUBRICANT ON SCREW JACK DRIED OUT RES	ULTING IN PREMATURE WEAR OF SCREW AND NUT ASSEMBLIES - AIRCRAFT OPERATES INA DUSTY ENVIRONMENT					1	H	7	1 	3O				3A24    					 
1996101000328	19961010	00328	NE  	1996	10	10	AU960074         	2	19960116	G	7230		SEAL            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 BEARING	LEAKING         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 							LF05896A			(AUS) NO3 ENGINE NO2 BEARING PACK SEAL FLATTENED AND LEAKING						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996101000329	19961010	00329	CE  	1996	10	10	AU960075         	1	19960119	G	2730	040010730	CONTROL CABLE   		040010728   	CESSNA	150   	A150L       	2071828	CE  	CONT  	O200  	O200A       	17020	SO  					ELEVATOR CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					(AUS) ELEVATOR REAR TRIM CABLES PN 0400107-28 AND PN 0400107-30  SEVERELY RUSTED AND FRAYED - 75% OF STRANDS BROKEN - PR	OBLEM SHOULD HAVE BEEN FOUND DURING PERIODIC INSPECTIONS - PERSONEL/MAINTENANCE ERROR					1	H	7	1 	3O	3	O	 	3A19    	E252				 
1996101000330	19961010	00330	EU  	1996	10	10	AU960076         	1	19960116	G	2530		WIRE            			FOKKER	F28   	F28MK1000   	4990808	EU  										GALLEY	SHORTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 GALLEY CONTROL PANEL PLUG PO 6 WIRING SHORT CIRCUITED ACROSS CORNER OF REAR CONTROL PANEL.						2	L	7	2 	4F			RT	A20EU   					 
1996101000331	19961010	00331	EU  	1996	10	10	AU960077         	1	19960101	G	5520		ELEVATOR        			FOKKER	F28   	F28MK4000   	4990810	EU  										ELEVATOR STRUCT	OUT OF BALANCE  	W				K				NONE                    				F	E		FLT CONT AFFECTED         	VIBRATION/BUFFET          		CR	CRUISE         	1			AU	S 										(AUS) LH ELEVATOR STATIC BALANCE INCORRECT - ELEVATOR CONTROL FLUTTER  THROUGH CONTROL COLUMN AND AIRFRAME BETWEEN MACH 	0.67 AND MACH 0.69 - SEE MDR 96/0054 FOR ADDITIONAL INFORMATION					2	L	7	2 	4F			RT	A20EU   					 
1996101000332	19961010	00332	SO  	1996	10	10	AU960078         	2	19960119	G	8530	TM649317	CYLINDER        	CONT        	TSIO520N    	CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY				RT ENG CYL SEC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			771  		L514918					(AUS) ENGINE CYLINDER CRACKED IN AREA BETWEEN THE SPARK PLUG HOLE AND  THE EXHAUST VALVE SEAT - CRACK LENGTH 30MM (1.18I	N)					1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996101000333	19961010	00333	CE  	1996	10	10	AU960079         	1	19960124	G	3220	NAS464P5A42	BOLT            			CESSNA	206   	U206G       	2073356	CE  	CONT  									NLG DRAG LINK	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG LINK BOLT SHEARED AT NUT END ADJACENT TO  THE LAST THREADED PORTION PRIOR TO THE BOLT SHANK						1	H	7	1 	3O				A4CE    					 
1996101700152	19961017	00152	SO  	1996	10	17	AU960080         	2	19960112	G	8550	276338R	FILTER          	CONT        	GTS10520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					R ENGINE OIL SYS	CONTAM-METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					276338R		276338R			(AUS) ENGINE OIL FILTER CONTAINED HIGHER THAN NORMAL LEVELS OF FERROUS METAL - SUSPECT ALTERNATOR BEARING FAILURE						1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996101000334	19961010	00334	SW  	1996	10	10	AU960081         	1	19960123	G	6410	206010765001	BEARING         	BELL        	TRBLADE     	BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CS3336					(AUS) TAIL ROTOR BLADE FEATHERING BEARING CRACKED RADIALLY						1	G	7	1 	3U				H2SW    					 
1996101000335	19961010	00335	SW  	1996	10	10	AU960082         	1	19960123	G	6710	206001554001	SUPPORT         			BELL  	206   	206L3       	1182108	SW  	ALLSN 									M/R CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2830 							(AUS) MAIN ROTOR CONTROL BELLCRANK SUPPORT WEB CRACKED ON INSIDE SURFACE - CRACK IS THROUGH THE WEB ON THE SHORTER FLANG	E OF THESUPPORT WHERE THE THICKNESS HAS BEEN REDUCED OUTBOARD OF THE LINKPIVOT POINT - CRACK LENGTH 25.4MM (1IN) - CRACK	 HAS PROPAGATED THROUGH 90% OF WEB THICKNESS				1	G	7	1 	3U				H2SW    					 
1996101000336	19961010	00336	WP  	1996	10	10	AU960083         	1	19960115	G	5720	H35195	EYE BOLT        			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  										OUTER WING SYS	MISMODIFIED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) WING LOWER RH FRONT MAIN SPAR EYEBOLT LOCATED AT THE WING STRUT ATTACHMENT POINT HAD A HOME MADE 'T' SECTION ATTAC	HED TO BOLTHEAD WITH SOLDER - EYEBOLT IS INCIDENCE WIRE ATTACHMENT POINT AT INTERPLANE STRUT POSITION ON LOWER FRONT MAI	N SPAR - UNAPPROVEDPART/MODIFICATION - PERSONNEL/MAINTENANCE ERROR - SEE MDR 96/0062FOR FURTHER INFORMATION				1	Q	7	1 	3I				A8EU    					 
1996101000337	19961010	00337	CE  	1996	10	10	AU960084         	1	19960126	G	2150	73838415	AIRCYCLE MACHINE			CESSNA	441   	441         	2076020	CE  										CABIN COOLING SY	SEIZED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			3221 		41280					(AUS) AIR CYCLE MACHINE SEIZED						1	L	7	2 	3T			RT	A28CE   					 
1996101000338	19961010	00338	CE  	1996	10	10	AU960085         	1	19960122	G	5312	62368	BULKHEAD        		DOORPOST    	CESSNA	182   	182P        	2075816	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					62368					(AUS) LH LOWER FORWARD DOORPOST BULKHEAD CRACKED FROM BEND RELIEF NOTCH- FOUND DURING INSPECTION IAW AD/C180/74 AMDT1 AN	D CESSNA SEB95-19					1	H	7	1 	3O			NT	TA13    					 
1996101000339	19961010	00339	EA  	1996	10	10	AU960086         	2	19960112	G	8540	AN381210	SPLIT PIN       	LYC         	VO540B1B3   	BELL  	47    	47J2A       	1181106	SW  	LYC   	O540  	VO540B1B3   	41532	EA  					R ENGINE REAR SE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			940  		L					(AUS) MAGNETO IDLER GEAR RETAINING NUT PN STD 43 SEPARATED FROM BOLT  PN STD 1860 - NUT AND WASHER PNO 68545 FOUND IN AC	CESSORY HOUSING - SUSPECT CAUSED BY LACK OF SPLIT PIN TO LOCK NUT -  CARBON DEPOSITS IN SPLIT PIN HOLE INDICATE SPLIT PI	N HAD BEEN MISSING FOR SOME CONSIDERABLE TIME				1	G	7	1 	3O	3	O		2H1     	E304				 
1996101000340	19961010	00340	EA  	1996	10	10	AU960087         	2	19960127	G	7314	15473	PUMP VALVE      	LYC         	IO360C1E6   	PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					LT ENGFUEL	BLOCKED         	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		TO	TAKEOFF        	1			AU	S 					L1054451A		L1054451A			(AUS) LH ENGINE DRIVEN FUEL PUMP OUTLET VALVE BLOCKED BY FOREIGN OBJECT- ROUND RUBBER WASHER 19MM (0.74IN) IN DIAMETER W	ITH A 6MM (0.236IN) HOLE WHICH SEPARATED FROM THE DIAPHRAGM ASSEMBLY - INVESTIGATION FOUND NO DAMAGE TO THE RUBBER WASHE	R AND IT IS SUSPECTED THAT THE WASHER WAS INCORRECTLY FITTED DURING ASSEMBLY				1	L	7	2 	3O	3	O		A7SO    	1E10				 
1996101000341	19961010	00341	CE  	1996	10	10	AU960088         	1	19960118	G	2432		TERMINAL        	CESSNA      	152         	CESSNA	150   	152         	2071835	CE  										BATTERY/CHARGER	BROKEN          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			AU	S 					0					(AUS) BATTERY CABLE POSITIVE TERMINAL BROKEN - FREE END OF CABLE SHORT CIRCUITED ALTERNATOR OUTPUT TO BATTERY BOX						1	H	7	1 	3O			NT	3A19    					 
1996101000342	19961010	00342	SO  	1996	10	10	AU960089         	2	19960112	G	8540	537721	BEARING         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY				R ENGINE REAR SE	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							276338R			(AUS) CRANKCASE STARTER ADAPTER GEAR SHAFT NEEDLE BEARING DISINTEGRATED- CRANKCASE DAMAGED - OTHER COMPONENTS DAMAGED WE	RE OIL PUMP HOUSING, IMPELLERS, ENGINE BEARINGS, STARTER ADAPTER KIT SHAFT PNO EQ6642 AND CRANKSHAFT GEAR - METAL CONTAM	INATION OF OILSYSTEM - ENGINE HAD BEEN MODIFIED AND COMPLIED WITH AD/CON/71				1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996101000343	19961010	00343	CE  	1996	10	10	AU960090         	1	19960122	G	7921	635996	OIL COOLER      	CONT        	IO520M      	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY				AC,ENG OIL DIST	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			786  		565768		LH565768			(AUS) ENGINE OIL COOLER CORE LEAKING - LOSS OF 5 QUARTS OF OIL						1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996101000344	19961010	00344	NE  	1996	10	10	AU960092         	2	19960123	G	7260		BEARING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					T ENG AUX DRIVE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							PCE120282			(AUS) LH ENGINE ACCESSORY DRIVE SHAFT UPPER BEARING FAILED						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996101000345	19961010	00345	EU  	1996	10	10	AU960093         	1	19960130	G	3213	115C5201	FORK            			GROB  	G115  	G115C       	1660303	EU  	LYC   					HARTZL				NOSE-TAIL GEAR S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR WHEEL FORK CRACKED AND DELAMINATED - SUSPECT CAUSED BY UNREPORTED HEAVY LANDING						1	L	7	1 	3O			NT	A57EU   					 
1996101000346	19961010	00346	GL  	1996	10	10	AU960094         	3	19960123	G	6111	FC84756	BLADE           	HARTZL      	BHCC2YF2    	BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY S	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			80   		AN694			AN694		(AUS) BOTH PROPELLER BLADES BENT AND TWISTED - NO IMPACT DAMAGE VISIBLE- SUSPECT DAMAGE CAUSED BY MISUSE OF BLADE BATS						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P920	 
1996101000347	19961010	00347	NE  	1996	10	10	AU960095         	2	19960122	G	8520	12081	STUD            			AYRES 	S2    	S2RNORMAL   	7630202	SO  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD				R ENGINE POWER S	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					17590		17590			(AUS) NO4 CYLINDER REAR HOLD DOWN STUD BROKEN - SUSPECT STUD PREVIOUSLYCRACKED						1	L	7	1 	3R	3	R	NC	A3SW    	5E2				 
1996101000348	19961010	00348	SW  	1996	10	10	AU960096         	1	19960130	G	5302	206031004071	TAIL BOOM       	BELL        	206B        	BELL  	206   	206B        	1181511	SW  	ALLSN 									MAIN FRAME SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					BOJNO692					(AUS) TAILBOOM ASSEMBLY CONTAINED EXFOLIATION CORROSION IN THE TOP LH  SECTION ADJACENT TO THE FIRST HANGER BEARING SUPP	ORT - FURTHER INVESTIGATION FOUND SIGNIFICANT EXFOLIATION CORROSION AND TWO  CRACKS - CRACK LENGTHS 20MM (0.787IN) AND 1	5MM (0.59IN) - SUSPECTCAUSED BY A RIVET WITH A MISSING HEAD ALLOWING WATER TO INGRESS  BETWEEN THE SKIN AND A RIB WITH C	ORROSION CAUSING THE SKIN TOBULGE AND CRACK			1	G	7	1 	3U				H2SW    					 
1996101000349	19961010	00349	WP  	1996	10	10	AU960097         	2	19960109	G	7261	300143619AA1150C	FILTER          			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315     	01514	WP  					T ENGINE OIL SYS	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P0684M			(AUS) LH ENGINE OIL FILTER ELEMENT DISINTEGRATING - METAL FROM FILTER  ELEMENT CASING CONTAMINATED ENGINE OIL SYSTEM						1	H	7	2 	3T	4	T		2A4     	E4WE				 
1996101000350	19961010	00350	CE  	1996	10	10	AU960098         	1	19960131	G	5320	1054200111	FITTING         	BEECH       	76          	BEECH 	76    	76          	1153005	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ME358					(AUS) LH FUSELAGE FRAME SHEAR FITTING CRACKED IN RADIUS OF CUTOUT -  CRACK LENGTH 5MM (0.196IN)						1	L	7	2 	3O				A29CE   					 
1996101000351	19961010	00351	EU  	1996	10	10	AU960099         	1	19960105	G	3240	S876060317	HOSE            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    									LG WHEEL/BRAKE S	WORN            	W				K				NONE                    				K		J	FLUID LOSS                		WARNING INDICATION        	LD	LANDING        	1			AU	S 										(AUS) NO5 BRAKE HYDRAULIC PRESSURE HOSE WORN THROUGH - LOSS OF GREEN SYSTEM HYDRAULIC FLUID						2	L	7	2 	4F				A35EU   					 
1996101000352	19961010	00352	EU  	1996	10	10	AU960100         	1	19960125	G	2780	1905	SCREWJACK       			AIRBUS	300   	A300B4203   	3930306	EU  	GE    									LIFT AUGMNT SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			29286		1905					(AUS) LH SLAT NO3 SCREWJACK EXCESSIVELY WORN - SUSPECT SCREWJACK WAS WORN WHEN FITTED - FOUND DURING INSPECTION IAW AB3-	27-2A					2	L	7	2 	4F				A35EU   					 
1996101000353	19961010	00353	EU  	1996	10	10	AU960101         	2	19960128	G	7321	8063210	FCU             								CFMINT	CFM56 	CFM563C     	13802	EU  					ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 					WYG76817		856531			(AUS) NO1 ENGINE FUEL CONTROL UNIT FAULTY - INVESTIGATION FOUND WEAR INTHE CDP PILOT BUSHING, NEEDLE BEARINGS AND BUSHIN	G AND CDP LEVER ASSEMBLY										4	F			E21EU				 
1996101000354	19961010	00354	EA  	1996	10	10	AU960102         	2	19960119	G	7322	60260	BUSHING         	FACET       	MA45PA      	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY				ENG,FUEL CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CK817203					(AUS) CARBURETTOR THROTTLE SHAFT PNO 13-1521 AND BUSHINGS PNO 60-260 HAD EXCESSIVE CLEARANCE DUE TO WEAR IN THE BUSHINGS	 WHICH WERE WORN THROUGH CAUSING WEAR IN THE BODY OF THE CARBURETTOR AS WELL - ACCELERATOR PUMP LEVER PNO 155-226 AND CO	NNECTING ROD PNO17-372 WERE ALSO EXCESSIVELY WORN - PERSONNEL/MAINTENANCE ERROR				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996101000355	19961010	00355	CE  	1996	10	10	AU960104         	1	19960110	G	2720	03101965	SPRING          			CESSNA	172   	172M        	2072418	CE  						MCAULY				RUDDER CONTROL S	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER RETURN SPRING BROKEN						1	H	7	1 	3O			NT	3A12    					 
1996101000356	19961010	00356	EU  	1996	10	10	AU960105         	1	19960129	G	2821		GASCOLATOR      			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL				ENG,FUEL DIST SY	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 										(AUS) RH ENGINE GASCOLATOR LOOSE DUE TO RETAINER ARM MOVING AND  ALLOWING BOWL TO MOVE SIDEWAYS - FUEL LEAKING FROM GASC	OLATOR -SUSPECT CAUSED BY OVERTORQUEING OF THE RETAINER ARM CAUSING  DISTORTION OF THE ARM					1	H	7	2 	3O	3	O		A17EU   	1E4				 
1996091900054	19960919	00054	SO  	1996	9	19	AU960106         	2	19960205	G	8520	CASTINGNO631649	CRANKSHAFT      	CONT        	IO520R      						CONT  	O520  	IO520F      	17032	SO  					RT ENG CTWT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					291023R		291023R			(AUS) CRANKSHAFT COUNTERWEIGHT FERRULE HOLES ON WEBS CHIPPED DURING  REMOVAL OF COUNTERWEIGHT BUSHES											3	O			E5CE				 
1996101000357	19961010	00357	SO  	1996	10	10	AU960107         	1	19960130	G	3240	16815	BRAKE DISC      			EMB   	110   	EMB110P2    	3260124	SO  	PWA   					HARTZL				LG WHEEL/BRAKE S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1447					(AUS) LH MAIN WHEEL BRAKE DISC CRACKED IN TWO						1	L	7	2 	4T				A21SO   					 
1996101000358	19961010	00358	NE  	1996	10	10	AU960108         	2	19960120	G	7321	F4305ANSSN06	FCU             								LYC   	ALF502	ALF502R5    	41580	NE  					ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 					F4305ANSS		LF05589A			(AUS) NO1 ENGINE FUEL CONTROL UNIT FAULTY											4	F			E6NE				 
1996101000359	19961010	00359	NM  	1996	10	10	AU960109         	1	19960109	G	2913	183840ANSSN1	SEAL            			BOEING	727   	727277      	138408S	NM  										MAIN HYD SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 			16405		183840ANSS					(AUS) NO1 ENGINE DRIVEN HYDRAULIC PUMP DRIVE PAD SEAL FAILED - SYSTEM  'A' HYDRAULIC LEVEL DROPPED TO 1.8 GALLONS - CREW	 SHUT OFF FLUID SUPPLY TO PUMP CAUSING PUMP TO RUN DRY AND SELF DESTRUCT					2	L	7	3 	4F			RT	A3WE    					 
1996101000360	19961010	00360	NE  	1996	10	10	AU960110         	2	19960120	G	7261	AL366	PUMP            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE ENGINE O	FAILED          	W				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 					AL366		LF05582A			(AUS) NO3 ENGINE DRIVEN OIL PUMP FAILED DUE TO GEAR WEAR AND EROSION OFTHE HOUSING GEAR POCKETS - ALUMINIUM METAL CONTAM	INATION OF OILFILTER					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996102300008	19961023	00008	NE  	1996	10	23	AU960111         	2	19960130	G	7250		COUPLING        		9272M76G02  						GE    	CF6   	CF680A      	30025	NE  					T ENG TURBINE SE	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 							580187			(AUS) NO2 ENGINE CONTAINED A MASSIVE OIL LEAK IN THE INTAKE AREA - INSPECTION OF THE OIL SCAVENGE PUMP FOUND THE PUMP CO	NTAMINATEDWITH BRAIDED SEAL MATERIAL - HP TURBINE COUPLING NUT PRESSURE  TUBE RUPTURED AT THE TUBE TO AFT FLANGE WELDED 	JOINT -  A CIRCUMFERENTIAL CRACK OF APPROXIMATELY 228.6MM (9IN) WAS FOUND WITH TWO PIECES OF THE TUBE APPROXIMATELY 19.0	5MM BY 19.05MM (0.75IN BY 0.75IN) AND 63.5MM BY 12.7MM (2.5IN BY 0.5IN) MISSING - THIS ALLOWED HIGH TEMPERATURE AND PRES	SURE COMPRESSOR DISCHARGEAIR TO ESCAPE INTO THE COOLING AIR CAVITY OF THE HPC AND HPT ROTORS AND THEN CHANNELED FORWARD 	TO THE NO3 AIR/OIL SEAL CAUSINGTHE SEAL TO FAIL						4	F			E13NE				 
1996101000361	19961010	00361	CE  	1996	10	10	AU960112         	1	19960131	G	2820	60920000249	FITTING         			BEECH 	60    	B60         	1153605	CE  	LYC   									FUEL DISTRBUTION	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL LINE LOCATED IN RH WHEEL WELL CRACKED AND LEAKING AT FITTING						1	L	7	2 	3O				A12CE   					 
1996101700153	19961017	00153	CE  	1996	10	17	AU960113         	1	19960131	G	5712	9511002615	RIB             			BEECH 	60    	B60         	1153605	CE  	LYC   									OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING RIB LOCATED IN WHEEL WELL CRACKED FROM RIVET HOLES						1	L	7	2 	3O				A12CE   					 
1996101700154	19961017	00154	CE  	1996	10	17	AU960114         	1	19960131	G	5720	609800323	RIB             			BEECH 	60    	B60         	1153605	CE  	LYC   									OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING NACELLE SIDE RIB CONTAINED EXFOLIATION CORROSION						1	L	7	2 	3O				A12CE   					 
1996101700155	19961017	00155	CE  	1996	10	17	AU960115         	1	19960131	G	5340	041342622	HINGE           			CESSNA	150   	152         	2071835	CE  										ATTACH FITTINGS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOP DOOR HINGE CRACKED IN AFT SECTION - DOOR HINGE PIN ALSO  SHEARED						1	H	7	1 	3O			NT	3A19    					 
1996101700156	19961017	00156	CE  	1996	10	17	AU960116         	1	19960131	G	3230	358100763	DRIVE           			BEECH 	60    	B60         	1153605	CE  	LYC   									LG EXT-RETRACT S	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR EMERGENCY EXTENSION SYSTEM WORM DRIVE COUPLING  SHEARED - SUSPECT CAUSED BY HAVING EMERGENCY DRIVE CO	NNECTED DURING NORMAL OPERATION					1	L	7	2 	3O				A12CE   					 
1996101700157	19961017	00157	CE  	1996	10	17	AU960117         	1	19960129	G	7922	75944	NUT             	LYC         	VERNATHERM  	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					AC ENG OIL DIST	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			471  							(AUS) ENGINE THERMOSTATIC OIL COOLER BYPASS VALVE (VERNATHERM) NUT LOOSE - FOUND DURING INSPECTION IAW AD/LYC/78						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1996101700158	19961017	00158	EU  	1996	10	17	AU960118         	1	19960131	G	3520	592	HOUSING         	PURITANBENN 	REGULATOR   	ISRAEL	1124  	1124        	4500102	EU  										CREW&PASS OXYGEN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					592					(AUS) AIRCRAFT CABIN CREW OXYGEN REGULATOR OUTLET HOUSING CRACKED -  OXYGEN LEAKING WHEN SELECTED 'ON' - SUSPECT CRACKIN	G CAUSED BY OVERTIGHTENING OF THE FITTING INTO THE REGULATOR - PERSONNEL/MAINTENANCE ERROR					2	M	7	2 	4F				A2SW    					 
1996101700159	19961017	00159	CE  	1996	10	17	AU960119         	1	19960109	G	5312	0713608	BULKHEAD        	CESSNA      	R182        	CESSNA	182   	R182        	2072734	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					01464					(AUS) FUSELAGE FORWARD DOOR POST BULKHEAD CRACKED IN BOTH RELIEF NOTCHES - CRACK LENGTH 5MM (0.196IN)						1	H	7	1 	3O			RT	3A13    					 
1996091900055	19960919	00055	EU  	1996	9	19	AU960120         	1	19960205	G	3220	115C5201	FORK            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  					NOSE GEAR SYS	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FORK DELAMINATED - AIRCRAFT NLG HAD BEEN BOGGED IN SAND - SEE MDR 96/0093 AND MDR 96/0121 FOR FU	RTHER INFORMATION					1	L	7	1 	3O	3	O	NT	A57EU   	E286				 
1996091900056	19960919	00056	EU  	1996	9	19	AU960121         	1	19960202	G	3220	115C5201	FORK            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  					NOSE GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					82032C2					(AUS) NOSE LANDING GEAR FORK CRACKED AND DELAMINATED - FOUND DURING  INSPECTION FOLLOWING REPORTED HEAVY LANDING - SEE M	DR 96/0093 ANDMDR 96/0120 FOR FURTHER INFORMATION					1	L	7	1 	3O	3	O	NT	A57EU   	E286				 
1996091900057	19960919	00057	CE  	1996	9	19	AU960122         	1	19960202	G	6120	S139117	CONTROL CABLE   			CESSNA	337   	337G        	2075730	CE  						MCAULY	2AF34C	D2AF34C306  	GL  	PROP CNTRL SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD ENGINE PROPELLER PITCH CONTROL CABLE CORRODED INTERNALLY AND STIFF TO OPERATE - CABLE WAS PURCHASED NEW ON	 14/1195 AND HAS BEEN IN SERVICE FOR LESS THAN THREE MONTHS - SUSPECT CABLE WAS INSUFFICIENTLY LUBRICATED AT MANUFACTURE	 WHICH ALLOWED CORROSION TO DEVELOPE DURING STORAGE				1	H	7	2 	3O			 	A6CE    		5	C	P5EA	 
1996101700160	19961017	00160	NM  	1996	10	17	AU960123         	1	19960129	G	5315		FLOORBEAM       			BOEING	747   	747338      		NM  										CARGO COMPT	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FORWARD CARGO CONTAINER AT POSITION 21R JUMPED FORWARD OF RESTRAINTS AND MOVED FORWARD CONTACTING THE CENTERLINE R	ESTRAINT AT BS 635 - DAMAGE WAS CAUSED TO LONGITUDINAL FALSE FLOORBEAM BOX SECTION - ALL RESTRAINTS AND LOCKS SERVICEABL	E - SUSPECT CONTAINER BASE WARPED.				2	L	7	2 	4F			RT	A20WE   					 
1996091900058	19960919	00058	NM  	1996	9	19	AU960124         	1	19960205	G	5730		RIVET           			PIPER 	PA60  	PA60601P    	7106012	NM  										OUTER WING SYS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER WING SKIN TO MAIN SPAR CHERRY RIVETS LOOSE AND WORKING - SKIN IN NACELLE AREA SAGGING APPROXIMATELY 4.762MM 	(0.1875IN)					1	M	7	2 	3O			RT	A17WE   					 
1996091900059	19960919	00059	NE  	1996	9	19	AU960125         	2	19960201	G	7261	P20066C	OIL SYSTEM      	GARRTT      	TPE3316252M 	MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316252M 	01514	NE  					RT ENG OIL SYS	CONTAM-METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					P20066C		PZ0066C			(AUS) RH ENGINE OIL SYSTEM METAL CONTAMINATION						1	H	7	2 	3T			RT	A10SW   	E2WE				 
1996101700161	19961017	00161	CE  	1996	10	17	AU960126         	1	19960103	G	5330	0713343	SKIN            		0713344     	CESSNA	182   	182Q        	2072732	CE  										EXT PLATES/SKIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SKIN CORRODED IN AREA BENEATH SOUND INSULATION COMPOUND - SKIN PNO 071334-3 AND PNO 071334-4 - FOUND DURING INSPEC	TION IAWAD/C180/75					1	H	7	1 	3O			NT	3A13    					 
1996101700162	19961017	00162	CE  	1996	10	17	AU960127         	1	19960103	G	5330	221300011	SKIN            	CESSNA      	22130005    	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					EXT PLATES/SKIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT SKIN CORRODED UNDER SOUND INSULATION COMPOUND - LOWER LHFORWARD BELLY SKIN ALSO CORRODED - SKIN PNO 22130	00-11, PNO2213000-5 AND PNO 2213000-6 - FOUND DURING INSPECTION IAW  AD/C180/75					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1996101700163	19961017	00163	WP  	1996	10	17	AU960128         	2	19960126	G	7230	31011607	SEAL            								GARRTT	TPE331	TPE33110U   	01514	WP  					T ENG CMPRSR/FAN	LEAKING         	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			1816 							(AUS) RH ENGINE COMPRESSOR SEAL LEAKING											4	T			E4WE				 
1997010200020	19970102	00020	EU  	1997	1	2	AU960129         	1	19960203	G	3230		LANDING GEAR    			BAG   	JETSTM	JETSTM3107  	1500215	EU  										LG EXT RETRACT S	FAULTY          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR WOULD NOT RETRACT - GROUND TESTING COULD FIND NO  FAULT - SEE MDR 96/0091 AND MDR 96/0161 FOR FURTHER	 INFORMATION					2	L	7	2 	4T			RT	BA15CAA 					 
1996091900060	19960919	00060	NM  	1996	9	19	AU960130         	1	19960204	G	3230		DOOR            			DHAV  	DHC8  	DHC8102     	2809003	NM  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC BYPASS DOOR INCORRECTLY POSITIONED  PREVENTING CORRECT LANDING GEAR RETRACTION - PERSONNEL/	MAINTENANCE ERROR					2	H	7	2 	4T			RT	A13NM   					 
1996102300009	19961023	00009	NM  	1996	10	23	AU960131         	2	19960122	G	7210	31030351	BEARING         	GARRTT      	TORQUESENSOR	GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 		NM  					ENGINE REDUCTION	FAILED          	W				K				NONE                    				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 					P8240		P06269C			(AUS) RH ENGINE TORQUE SENSOR BEARING FAILED - METAL CONTAMINATION OF  OIL SYSTEM - INVESTIGATION FOUND THAT THE CHIP DE	TECTOR WIRING WAS CROSSED AT THE FIREWALL PREVENTING OPERATION OF THE CHIP DETECTOR LIGHT					1	H	7	2 	3T	4	T		2A4     	E2WE				 
1996102300010	19961023	00010	SO  	1996	10	23	AU960132         	1	19960129	G	6123		PUMP            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14SF	14SF*       	NE  	PROP CNTRL SYS	FAILED          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) BURNT OUT RH PROPELLER UNFEATHERING PUMP CAUSED NO2 EMERGENCY DC BUS CIRCUIT BREAKER CB470 (80AMP) TO TRIP						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P7NE	 
1996101700164	19961017	00164	NE  	1996	10	17	AU960133         	2	19960104	G	7310		HOSE            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					ENG,FUEL DIST SY	LOOSE           	W				K				NONE                    				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) RH ENGINE FUEL LINE TO HMU LOOSE - FUEL LEAKING FROM HOSE - HOSE HAD BEEN REPLACED DURING OVERNIGHT MAINTENANCE - 	SUSPECT HOSEINCORRECTLY TIGHTENED ALLOWING FITTING TO LOOSEN ON START -  PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997010200021	19970102	00021	EU  	1997	1	2	AU960134         	1	19960125	G	2460	A2036	RELAY           			BAG   	JETSTM	JETSTM3107  	1500215	EU  										DC POWER DIST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RELAY A2036 FAULTY - SEE MDR 96/0137 FOR ADDITIONAL INFORMATION						2	L	7	2 	4T			RT	BA15CAA 					 
1997010200022	19970102	00022	EU  	1997	1	2	AU960135         	1	19960125	G	2460	A2036	RELAY           			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	DC POWER DIST	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RELAY A2036 FAULTY - SEE MDR 96/0134 AND MDR 96/0137 FOR FURTHER INFORMATION						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1996101700165	19961017	00165	NM  	1996	10	17	AU960136         	1	19960201	G	2910	82970010149	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  										MAIN HYD SYS	WORN            	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) NO2 HYDRAULIC SYSTEM PRESSURE PIPE FROM ENGINE DRIVEN HYDRAULIC  PUMP TO PRESSURE MANIFOLD CHAFED AND HOLED ON RET	AINING CLAMP -RUBBER CUSHION LOST FROM CLAMP - SEE MDR 96/0201 FOR SIMILAR DEFECT					2	H	7	2 	4T			RT	A13NM   					 
1997010200023	19970102	00023	EU  	1997	1	2	AU960137         	1	19960124	G	2435	23079005	GENERATOR       			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	STARTER-GEN	FAULTY          	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		DE	DESCENT        	1			AU	S 					3469					(AUS) STARTER/GENERATOR FAILED - CAUSED BY INTERMITTENT OPERATION OF RELAY PNO A2036 - SEE MDR 96/0134 AND MDR 96/0135 F	OR ADDITIONAL INFORMATION					2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1996101700166	19961017	00166	SW  	1996	10	17	AU960138         	1	19960113	G	7120	2762114003	MOUNT           			SWRNGN	SA227 	SA227AC     	8780603	SW  										ENGINE MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER LH ENGINE MOUNT FOOT CRACKED IN AREA OF FLANGE WELD TO TUBECLUSTER - CRACK APPEARS TO BE LACK OF FUSION BETW	EEN THE WELD ANDTHE FLANGE/WASHER - WELD APPEARS TO BE ORIGINAL					2	L	7	2 	4T			RT	A8SW    					 
1996101700167	19961017	00167	EU  	1996	10	17	AU960139         	1	19960201	G	7110	365A24100503	COWLING         		36010A      	AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					NAC PYLON FAIRNG	DAMAGED         	W				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) TRANSMISSION RH COWLING FORWARD LATCH ASSEMBLY PNO 360-10A LOCKING PIN SHEARED ALLOWING FORWARD EDGE OF COWL TO LI	FT ANDEVENTUALLY SEPARATE FROM AIRCRAFT					1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1996101700168	19961017	00168	EU  	1996	10	17	AU960140         	2	19960111	G	8520		BEARING         								RROYCE	GIPSY 	GIPSY30*    	20005	EU  					R ENGINE POWER S	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 			1289 				66850			(AUS) LH ENGINE OIL FILTER METAL CONTAMINATION - SUSPECT FAILED MAIN BEARING											3	I			E294				 
1996091900061	19960919	00061	EA  	1996	9	19	AU960141         	2	19960208	G	7414	8120404	BEARING         	SLICK       	4150        	GULSTM	GA7   	GA7         	3960401	SO  	LYC   	O320  	O320D1D     	41508	EA  					MAGNETO	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					8120404					(AUS) MAGNETO BEARING FAILED - AD/ELEC/18 AMDT3 HAS NOT BEEN COMPLIED  WITH - PERSONNEL/MAINTENANCE ERROR - SEE MDR 96/0	142 FOR SIMILAR DEFECT					1	L	7	2 	3O	3	O		A17SO   	E274				 
1996091900062	19960919	00062	EA  	1996	9	19	AU960142         	2	19960208	G	7414	4150	MAGNETO         	SLICK       	4150        	GULSTM	GA7   	GA7         	3960401	SO  	LYC   	O320  	O320D1D     	41508	EA  					ENGINE	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					8120388		L887939A			(AUS) MAGNETO FAILED TO COMPLY WITH AD/ELEC/18 AMDT3 - PERSONNEL/MAINTENANCE ERROR						1	L	7	2 	3O	3	O		A17SO   	E274				 
1996091900063	19960919	00063	EU  	1996	9	19	AU960143         	1	19960207	G	2750		SCREWJACK       			BAC   	146   	146100A     	1500260	EU  										FLAP SYS	OUT OF ADJUST   	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) LH WING FLAP NO3 SCREW JACK DRIVE CHAINS SLACK - RH WING FLAP NO3SCREW JACK INCORRECTLY RIGGED						2	H	7	4 	4F			RT	A49EU   					 
1996091900064	19960919	00064	CE  	1996	9	19	AU960144         	1	19960207	G	2460	70HF10	DIODE           			BEECH 	200   	B200C       	1152924	CE  										DC POWER DISTRIB	FAULTY          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 										(AUS) NO1 ELECTRICAL BUS FEEDER DIODE FAULTY						1	L	7	2 	4T				A24CE   					 
1996101700169	19961017	00169	EA  	1996	10	17	AU960145         	2	19960209	G	8520	75060	BOLT            	LYC         	CONROD      	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					R ENGINE POWER S	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							L1080840			(AUS) NO2 CYLINDER CONNECTING ROD PNO 74502 BOLT INCORRECT PART - BOLT PNO 75060/1 FITTED - CORRECT PNO 74644 - INCORREC	T BOLT IS LONGERTHAN THE CORRECT ONE - IPC IS UNCLEAR ON CORRECT PART NUMBER BOLTTO BE FITTED - UNAPPROVED PART - PERSON	NEL/MAINTENANCE ERROR				1	L	7	2 	3O	3	O		1A10    	1E4				 
1996101700170	19961017	00170	SO  	1996	10	17	AU960146         	1	19960131	G	3210	78717O2	STUD            	PIPER       	ARROW       	PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3840 							(AUS) RH MAIN LANDING GEAR SIDE BRACE STUD CRACKED IN AREA UNDER SHOULDER - FOUND DURING INSPECTION IAW AD/PA28/91						1	L	7	1 	3O	3	O		2A13    	1E10				 
1996101700171	19961017	00171	EA  	1996	10	17	AU960147         	2	19960126	G	7310	D2310	GASKET          	ROMEC       	FUELPUMP    	GULSTM	680   	680FLP      	0141610	SW  	LYC   	O720  	IO720B1B    	41546	EA  					ENG,FUEL DIST SY	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					D2310		L75754			(AUS) ENGINE DRIVEN FUEL PUMP RELIEF VALVE GASKET LEAKING						1	H	7	2 	3O	3	O		2A4     	1E15				 
1996101700172	19961017	00172	NE  	1996	10	17	AU960148         	1	19960110	G	6320	763510960044	OIL SYSTEM      	SKRSKY      	MAINGEARBOX 	SKRSKY	S76   	S76C        	8143008	NE  										MAIN ROTOR TRANS	LOW PRESSURE    	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					A2310136					(AUS) MAIN TRANSMISSION GEARBOX OIL PRESSURE FELL TO 44PSI - OIL FILTERAND CHIP DETECTORS CHECKED OK - AFTER THE OIL WAS	 DRAINED AND THEGEARBOX REFILLED THE PRESSURE RETURNED TO NORMAL					1	G	7	2 	3U			NC	H1NE    					 
1996101700173	19961017	00173	GL  	1996	10	17	AU960149         	3	19960212	G	6110	783473	PROPELLER       	MCAULY      	3AF32C87N   											MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY S	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					783473			783473		(AUS) PROPELLER SEIZED DUE TO INTERNAL CORROSION - BLADE 'O' RINGS PNO A1633-52 NOT FITTED																5	C	P22EA	 
1996101700174	19961017	00174	GL  	1996	10	17	AU960150         	3	19960207	G	6110	085033427	PROPELLER       	MCAULY      	3FF32C501   	CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY S	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								806461		(AUS) PROPELLER WOULD NOT GO TO FULL FEATHER POSITION - ONLY SLIGHT  RESISTANCE FELT WHEN PROPELLER WAS MANUALLY MOVED F	ROM FEATHER TO FINE USING BLADE BATS - FOUND DURING INSPECTION IAW AD/PROP/2					1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1996101700175	19961017	00175	EU  	1996	10	17	AU960151         	1	19960129	G	5210	F5106043427	SEAL            			FOKKER	F27   	F27MK500    	4990629	EU  										CREW-PASS DOOR S	INCORRECT FIT   	W				K				NONE                    				W			INADEQUATE Q C            			CR	CRUISE         	1			AU	S 										(AUS) LH REAR DOOR SEAL INCORRECTLY INSTALLED - SEAL WAS FITTED UPSIDE DOWN - NEW SEAL ASSEMBLY HAD BEEN FITTED ON 12/9/	95 -PERSONNEL/MAINTENANCE ERROR					2	H	7	2 	4T				A817    					 
1996101700176	19961017	00176	GL  	1996	10	17	AU960152         	2	19960202	G	7230	6871443	BLADE           	ALLSN       	250C18B     	BELL  	47    	47G3B1      	1181028	SW  	ALLSN 	250C  	250C18      	03011	GL  					T ENG CMPRSR/FAN	FAILED          	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			1030 		CAC22003B		800621B			(AUS) COMPRESSOR NO2/3 ROTOR ASSEMBLY BLADE FAILED - BLADES EXITED THROUGH BOTH COMPRESSOR CASE HALVES - FURTHER DAMAGE 	TO TURBINESECTION DUE TO FOD AND OVERTEMPERATURE - AIRCRAFT IS A SOLOY TURBINE ENGINE MODIFICATION ALLISON 250C18B POWER	ED BELL 47G3B1				1	G	7	1 	3O	3	U		2H3     	E4CE				 
1996101700177	19961017	00177	GL  	1996	10	17	AU960153         	3	19960207	G	6111	787699	BLADE           	MCAULY      	3AF32C87N   	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY S	LOOSE           	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			271  		787699			787699		(AUS) PROPELLER BLADE LOOSE - BLADE COULD BE ROTATED ABOUT 50.8MM (2IN)FROM FINE PITCH TO FEATHER - INVESTIGATION FOUND 	BLADE ACTUATING PIN FAILURE IN AREA ABOVE THREAD - MENTION WAS ALSO MADE OF  FINDING FLAKES OF CHROME PLATING AND EVIDEN	CE OF SCUFFING				1	L	7	2 	3O	3	O		3A10    	E8CE	5	C	P22EA	 
1996101700178	19961017	00178	EU  	1996	10	17	AU960154         	1	19960205	G	6230	47896WVC47820X	BEARING         	AEROSP      	MAINMAST    	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 									M/R MAST/SWASHPL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					M1071					(AUS) MAIN ROTOR MAST BEARING FAILED - EVIDENCE OF EXTENSIVE PITTING AND BRINNELLING WITH CORROSION ALSO PRESENT - SUSPE	CT CORROSIONINITIATED BY CONDENSATION - AIRCRAFT IS IDLE FOR LONG PERIODS OF TIME - METAL CONTAMINATION OF MAIN TRANSMIS	SION				1	G	7	1 	3U				H9EU    					 
1996101700179	19961017	00179		1996	10	17	AU960155         	4	19960121	G	3452	205ANSSN005	CONTROLLER      			BOEING	737   	737377      		NM  										DEPDNT POSN DATA	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			3316 		205ANSSN					(AUS) A.T.C. TRANSPONDER CONTROLLER FAULTY						2	L	7	2 	4F			RT	A16WE   					 
1996102300011	19961023	00011	NM  	1996	10	23	AU960156         	1	19960201	G	3510	14326	HOSE            			BOEING	737   	737376      		NM  										CREW STA OXYGEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			563  		14326					(AUS) CAPTAINS OXYGEN MASK LOWER HOSE BURST						2	L	7	2 	4F			RT	A16WE   					 
1996101700180	19961017	00180	SO  	1996	10	17	AU960157         	2	19960131	G	8520		CRANKCASE       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1665 				565559			(AUS) CRANKCASE CRACKED IN AREA OF NO4 CYLINDER - CRACK RADIATES FORWARD FROM THE FORWARD OIL FILTER STUD - CRACK LENGTH	 135MM(5.314IN) - AIRCRAFT IS USED FOR TRAINING PURPOSES					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1996101700181	19961017	00181	SO  	1996	10	17	AU960158         	1	19960205	G	7170		PIPE            			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENG FLUID DRAIN/	INCORRECT FIT   	W				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 							L2006651A			(AUS) ENGINE INTAKE FUEL DRAIN LINE INCORRECTLY FITTED - LINE WAS  DOUBLED UP INTO A KINK PREVENTING FUEL FROM DRAINING 	- FUELLEAKED INSIDE COWLING - PERSONNEL/MAINTENANCE ERROR					1	L	7	1 	3O	3	O		2A13    	1E10				 
1996101700182	19961017	00182	SO  	1996	10	17	AU960159         	2	19960204	G	8520	6419311075	BOLT            	CONT        	TSIO520E    	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	R ENGINE POWER S	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1179 				275233R			(AUS) ENGINE CRANKCASE THROUGH BOLT SHEARED AT BASE OF NUT - BOLT GOES FROM NO2 CYLINDER LOWER FORWARD POSITION TO N03 C	YLINDER LOWER AFT POSITION - CRANKCASE ALSO CRACKED					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1996101700183	19961017	00183	SO  	1996	10	17	AU960160         	1	19960205	G	7112		BAFFLE          			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE COWL SYS	INCORRECT FIT   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							L2006651A			(AUS) ENGINE FRONT BAFFLE LOWER SIDE SEALING STRIPS INCORRECTLY FITTED - BAFFLE LOWER SIDE MATES WITH LOWER COWL - RAM A	IR ENTEREDUNDERSIDE OF ENGINE PREVENTING CORRECT COOLING - PERSONNEL/MAINTENANCE ERROR					1	L	7	1 	3O	3	O		2A13    	1E10				 
1997010200024	19970102	00024	EU  	1997	1	2	AU960161         	1	19960203	G	3230	7445B	VALVE           			BAG   	JETSTM	JETSTM3107  	1500215	EU  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					LK8509192					(AUS) EMERGENCY UNDERCARRIAGE HYDRAULIC RELEASE VALVE FAULTY - SEE MDR 96/0091 FOR FURTHER INFORMATION						2	L	7	2 	4T			RT	BA15CAA 					 
1996101700184	19961017	00184	SO  	1996	10	17	AU960163         	1	19960205	G	2510		SEAT            			PIPER 	PA28  	PA28RT201   	7102818	SO  										FLIGHT COMPARTME	INCORRECT MOD   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS SEAT HYDRAULIC ADJUSTMENT UNITS FAULTY - SEAT HAS BEEN  LOCKED IN A SINGLE POSITION BY FITTING TUBE SPACERS	 OVER THE PISTON RODS - WITH THE SEAT LOCKED IN A HIGH POSITION THE PILOTS HEAD IS IN CLOSE PROXIMITY TO THE CABIN ROOF 	- UNAPPROVEDMODIFICATION - PERSONNEL/MAINTENANCE ERROR				1	L	7	1 	3O				2A13    					 
1996101700185	19961017	00185	EA  	1996	10	17	AU960164         	2	19960205	G	7421	RME38E	SPARK PLUG      	CHAMPION    	REM38E      	PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENG,IGNITN DISTR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							IO360CIC6			(AUS) SPARK PLUGS (6OFF) FAULTY - CENTRE ELECTRODE WAS BEYOND LIMITS FOR RECONDITIONING - NO1 CYLINDER TOP SPARK PLUG HA	D TWO COPPERWASHERS FITTED - NO1 CYLINDER LOWER SPARK PLUG HAD CORE LEAKAGE -ENGINE HAD COMPLETED ONLY 38 HOURS SINCE OV	ERHAUL -PERSONNEL/MAINTENANCE ERROR				1	L	7	1 	3O	3	O		2A13    	1E10				 
1996101700186	19961017	00186	SO  	1996	10	17	AU960165         	1	19960205	G	2434	DAIE949	CONDENSER       	BOSCH       	ALTERNATOR  	PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   									DC GENERATOR-ALT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					DAIE949					(AUS) ALTERNATOR CONDENSER FAULTY - OUTER CASING WAS HOLED DUE TO WEAR CAUSED BY BEING LOOSE IN THE CLAMP BRACKET - PERS	ONNEL/MAINTENANCE ERROR					1	L	7	1 	3O				2A13    					 
1996101700187	19961017	00187	EU  	1996	10	17	AU960166         	1	19960122	G	5540	A06002011	BUSHING         	FOKKER      	RUDDERSHAFT 	FOKKER	F28   	F28MK4000   	4990810	EU  										RUDDER STRUCT SY	MISSING         	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			8595 		AFW197ANS					(AUS) RUDDER SHAFT PNO A06020-15 UPPER LUG INNER BUSH PNO A06020-11  MISSING - FLANGED BUSH PNO A06020-13 BADLY WORN - E	DDY CURRENT INSPECTION OF SHAFT ASSEMBLY FOUND UPPER AND LOWER LUGS CRACKED  IN 3 TO 4 PLACES RANGING FROM 4MM TO 5MM (0	.157IN TO 0.196IN) IN LENGTH - CRACKS WERE CORROSION RELATED - RUDDER ACTUATOR CHANGED ON 19/3/95 - PERSONNEL/MAINTENANC	E ERROR			2	L	7	2 	4F			RT	A20EU   					 
1996101700188	19961017	00188	GL  	1996	10	17	AU960167         	3	19960123	G	6111	FC84756	BLADE           	HARTZL      	HCC2YF2CHUF 	BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCC2Y	HCC2YF2     	GL  	PROPELLER ASSY S	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			80   		AN694			AN694		(AUS) PROPELLER BLADE CONTAINED TOOLING MARK DAMAGE IN BALANCE CAVITY -SUSPECT CAUSED DURING REMOVAL OF BALANCE LEAD - B	LADE SNO C49080					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P920	 
1996101700189	19961017	00189	CE  	1996	10	17	AU960168         	1	19960201	G	5720	08225501926	FITTING         	CESSNA      	402A        	CESSNA	402   	402A        	207590M	CE  										OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FITTINGS/STIFFENERS CONTAINED EXFOLIATED INTERGRANNULAR CORROSION - DURING FITTING REPLACEMENT EXTENSIVE CORR	OSION WAS ALSO FOUND IN LOWER WING STRINGERS PARTICULARLY IN AREA UNDER  FUEL CELL BAYS - AIRCRAFT PREVIOUSLY OPERATED I	N SALT LADENENVIRONMENT				1	L	7	2 	3O				A7CE    					 
1996102300012	19961023	00012		1996	10	23	AU960169         	4	19960209	G	2565		CABLE           			BOEING	767   	767238      	1385114	NM  										ESCAPE SLIDE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT OFF WING ESCAPE SLIDE SEPARATED FROM STOWAGE COMPARTMENT BUT  DID NOT INFLATE AND DEPLOY AS REQUIRED - INVESTIG	ATION FOUND THATTHE FAILURE WAS IN THE TRANSFER OF FORCE FROM THE INFLATION  TRIGGER TO THE FIRING MECHANISM WITH THE TR	IGGER CABLE BEING FED DOWN THE INCORRECT SIDE OF THE REGULATOR HOUSING SECTOR				2	L	7	2 	4F			RT	A1NM    					 
1996101700190	19961017	00190	NE  	1996	10	17	AU960170         	2	19960202	G	7230	701509	DISC            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					T ENG CMPRSR/FAN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					P76768		687560			(AUS) ENGINE 9TH STAGE HIGH PRESSURE COMPRESSOR DISC CONTAINED CORROSION PITTING IN THE BLADE SLOT PRESSURE FACES AND BL	ADE SLOTSIDES IN EXCESS OF LIMITS - FOUND DURING INSPECTION IAW PWA SB 6038 AND AD/JT8D/29 - ENGINE HAD BEEN FITTED TO A	 LOW UTILISATIONAIRCRAFT				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1996101700191	19961017	00191		1996	10	17	AU960171         	4	19960124	G	2562	69B562875	TRANSMITTER     			BOEING	747   	747238B     	1384828	NM  										EMERGENCY EQUIP	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO EMERGENCY RADIO BEACONS FITTED TO DOORS 2R, 4L AND 4R - SUSPECT BEACONS REMOVED DURING RECONFIGURATION AND FITM	ENT OF NEWTYPE ESCAPE SLIDES OR REMOVED LATER BY UNAUTHORISED PERSONS  PROBABLY FOR PERSONAL USE					2	L	7	4 	4F				A20WE   					 
1996101700192	19961017	00192	SO  	1996	10	17	AU960173         	1	19960119	G	3260	ICH214	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR SQUAT SWITCH FAULTY						1	L	7	2 	3O				A20SO   					 
1996101700193	19961017	00193	SO  	1996	10	17	AU960174         	1	19960127	G	7922		NUT             	LYC         	VERNATHERM  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					AC,ENG OIL DIST	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L566061A			(AUS) ENGINE THERMOSTATIC OIL COOLER BYPASS VALVE (VERNATHERM) NUT LOOSE - FOUND DURING INSPECTION IAW AD/LYC/78						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996101700194	19961017	00194	NE  	1996	10	17	AU960175         	2	19960122	G	7260	86A002	GEAR            	LYC         	ALF502R3A   	BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					T ENG AUX DRIVE	SEPARATED       	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) ENGINE ACCESSORY GEARBOX INPUT BEVEL GEAR SEPARATED FROM MOUNTINGFLANGE - BOLTS WERE STILL ATTACHED TO THE GEAR AN	D BEARING HOUSING - FOUND WHEN ENGINE STRIPPED FOLLOWING OIL PRESSURE LOSS - SUSPECT CAUSED BY INSUFFICIENT BACKLASH BET	WEEN THE SPIRAL INPUT GEAR AND THE BEVEL GEAR DURING INSTALLATION				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996101700195	19961017	00195	NE  	1996	10	17	AU960176         	2	19960121	G	7250		HOT SECTION     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					T ENG TURBINE SE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LF05869A			(AUS) ENGINE HOT SECTION DETERIORATED BEYOND LIMITS - FOUND DURING STRIP INSPECTION FOLLOWING BIRDSTRIKE						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996102300013	19961023	00013	NM  	1996	10	23	AU960177         	1	19960131	G	2897		WIRE            			BOEING	767   	767277      	1385128	NM  										FUEL INDICATION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRES DAMAGED IN AREA BEHIND FLIGHT ENGINEERS PANEL - WIRES  DAMAGED WERE:- 1. SINGLE TWISTED WIRE WITH TWO WIRES 	SEVERED - P61 RH SIDE PANEL WIRE NO  W062-209R18 - FUEL TEMPERATURE INDICATOR - ATA 28 WIRE NOW062-209R18 - FUEL TEMPERA	TURE INDICATOR - ATA 28 2. SINGLE WIRE SEVERED- P61 RH SIDE PANEL WIRE NO W062-615-22 - RH FUEL PRESSURE PUMP LOW PRESSU	RE - ATA 28 3. SINGLE SHEILDED WIRE SEVERED - P61 RH SIDE PANEL WIRE NO W062-81G-24 - SECOND OBSERVERS FLIGHT INTERPHONE	 - ATA 23  SUSPECT DELIBERATE DAMAGE BY PERSONS UNKNOWN		2	L	7	2 	4F			RT	A1NM    					 
1996101700196	19961017	00196	CE  	1996	10	17	AU960178         	1	19960215	G	2731	12321391	BRACKET         	CESSNA      	U206E       	CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  					ELEVATOR CONTROL	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) ELEVATOR TRIM TAB CONTROL ACTUATOR MOUNTING BRACKET BROKEN AWAY  FROM TAILPLANE CONNNECTION - AIRCRAFT IS USED FOR	 PARACHUTEOPERATIONS WITH THE DOORS OFF AND A WIND DEFLECTOR FITTED -  SUSPECT CAUSED BY EMPENNAGE BUFFETING DUE TO FITM	ENT OF WIND DEFLECTOR - SEE MDR 96/0257 FOR ADDITIONAL INFORMATION				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996101700197	19961017	00197	SW  	1996	10	17	AU960179         	1	19960130	G	5720		STRUT           			AIRPTS	A     	A9A         	0144204	SW  										OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING AFT WING STRUT AND TWO BRACES CONTAINED LIGHT CORROSION -FOUND DURING X-RAY INSPECTION						1	L	7	1 	3O				A4WE    					 
1996101700198	19961017	00198	NM  	1996	10	17	AU960180         	1	19960210	G	3240	DSC252A40230	HOSE            		G831810A    	DHAV  	DHC8  	DHC8102     	2809003	NM  										LG WHEEL/BRAKE S	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 					3892					(AUS) LH OUTBOARD BRAKE ASSEMBLY HYDRAULIC HOSE RUPTURED - LOSS OF NO1 SYSTEM HYDRAULIC FLUID DUE TO FAILURE OF HYDRAULI	C FUSE TO OPERATE AND PREVENT LOSS - SUSPECT CAUSED BY HYDRAULIC BRAKE HOSERUBBING ON THE TYRE DURING LANDING AND TAKEOF	F				2	H	7	2 	4T			RT	A13NM   					 
1996101700199	19961017	00199	CE  	1996	10	17	AU960181         	1	19960204	G	3260	1SE13	MICROSWITCH     			CESSNA	310   	310R        	2074245	CE  										LG POSITION IND	INTERMITTENT    	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH INTERMITTENT IN  OPERATION - LH MLG SIDEBRACE LOCK LINK TENSION TOO HIGH						1	L	7	2 	3O				3A10    					 
1996101700200	19961017	00200	EA  	1996	10	17	AU960182         	2	19960123	G	8540	67542	BEARING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					R ENGINE REAR SE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1914048A			(AUS) LH MAGNETO DRIVE BEARING LOCATED IN THE ENGINE ACCESSORY HOUSING FAILED - METAL CONTAMINATION OF OIL SYSTEM						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996101700201	19961017	00201	WP  	1996	10	17	AU960183         	1	19960125	G	7620	3141665	CABLE           			LKHEED	1049  	C121C       	5262118	WP  	WRIGHT	R3350 	R3350*      	67040	EA  					EMER SHUTDOWN SY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO3 ENGINE EMERGENCY SHUTOFF CABLE FAILED - SUSPECT CABLE FAILED AT A POINT WITHIN A PULLEY BLOCK WHERE THE CABLE 	HAD BEEN DAMAGED- NO CORROSION OR WEAR WAS EVIDENT					2	L	7	4 	4R	4	R		6A5     	E272				 
1996101700202	19961017	00202	SW  	1996	10	17	AU960184         	1	19960215	G	6510		WASHER          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R DRIVE SHAFT	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							820269			(AUS) TAIL ROTOR DRIVE TRAIN AFT SHORT SHAFT TO LONG TAIL ROTOR DRIVE  SHAFT DISC ASSEMBLY FITTED WITH INCORRECT TYPE FL	AT WASHERSINSTEAD OF WITH CORRECT TYPE BEVELLED WASHERS AS REQUIRED BY THE MAINTENANCE MANUAL - UNAPPROVED PART - PERSON	NEL/MAINTENANCE ERROR				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996101700203	19961017	00203	CE  	1996	10	17	AU960185         	1	19960220	G	5510	1236232	BRACKET         			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	HORZ STAB SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER REAR CENTRE SPAR REINFORCEMENT BRACKET CRACKED IN AREA OF LOWER LH FLANGE - INITIAL POINT OF	 CRACKAPPEARS TO BE AT THE BOLT HOLE WITH SECONDARY CRACKING IN BRACKETRADIUS - SUSPECT CAUSED BY PUSHING DOWN ON STABIL	ISER DURING GROUND HANDLING				1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1996101700204	19961017	00204	EU  	1996	10	17	AU960186         	1	19960124	G	3240	3034	HOSE            			PARTEN	P68   	P68B        		EU  										LG WHEEL/BRAKE S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			72   							(AUS) HYDRAULIC HOSES (3OFF) CHAFED BY METAL IDENTIFICATION TAG - HOSESWERE LOCATED AT LH AND RH BRAKES AND BETWEEN COPI	LOTS LH PEDAL AND PARK BRAKE - FOUND DURING INSPECTION IAW AD/HOSE/2					1	H	7	2 	3O				A31EU   					 
1996101700205	19961017	00205	EU  	1996	10	17	AU960187         	2	19960122	G	7320	WYG56065	FCU             								CFMINT	CFM56 	CFM563C1    	13802	EU  					ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			AU	S 			16253		WYG56065		725496			(AUS) ENGINE FUEL CONTROL UNIT FAULTY											4	F			E21EU				 
1996101700206	19961017	00206	NE  	1996	10	17	AU960188         	2	19960214	G	7261	235237790	CHIP DETECTOR   	TMECA       	ARRIEL1S1   	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					T ENGINE OIL SYS	SHORT CIRCUIT   	W				K				NONE                    				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 					15515		15515			(AUS) NO2 ENGINE FREE TURBINE CHIP DETECTOR HAD INTERNAL SHORT CIRCUIT						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
1996101700207	19961017	00207	CE  	1996	10	17	AU960189         	1	19960215	G	3230	11972	SOLENOID        	CESSNA      	CONTROLASSY 	CESSNA	425   	425         	2076018	CE  										LG EXT-RETRACT S	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					987					(AUS) LANDING GEAR EXTENSION SOLENOID INTERMITTENT IN OPERATION						1	L	7	2 	3T			RT	A7CE    					 
1996101700208	19961017	00208	SW  	1996	10	17	AU960190         	1	19960202	G	6120	4GBU80M	GOVERNOR        			GULSTM	G73   	G73         	3951802	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	23D	23D40       	NE  	PROP CNTRL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					291735		ZP10966	210267		(AUS) RH ENGINE PROPELLER GOVERNOR TRANSFER VALVE FAULTY - VALVE ALLOWED FEATHER PUMP PRESSURE TO PARTIALLY BYPASS PREVE	NTING UNFEATHERING OF PROPELLER					1	H	7	2 	3R	3	R		A783    	5E2	6	C	P719	 
1996101700209	19961017	00209	WP  	1996	10	17	AU960191         	1	19960215	G	6510	369A5518601	DRIVE SHAFT     			HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C18      	03011	GL  					T/R DRIVE SHAFT	SHEARED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) TAIL ROTOR DRIVE SHAFT SHEARED APPROXIMATELY 457.2MM (18IN) FROM THE FORWARD END - SEVERAL LONGITUDINAL CRACKS WER	E EVIDENT IN THEAREA OF THE FAILURE WHEN VIEWED UNDER X10 MAGNIFICATION					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996101700210	19961017	00210	WP  	1996	10	17	AU960192         	1	19960215	G	5530	369A2129	HOUSING         			HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C18      	03011	GL  					ATTACH FITTING S	CORRODED        	W				O				OTHER                   				F	E		FLT CONT AFFECTED         	VIBRATION/BUFFET          		TO	TAKEOFF        	1			AU	S 										(AUS) STABILIZER STRUT DAMPER SHAFT PULLED FROM FITTING DURING HEAVY VIBRATION FOLLOWING TAIL ROTOR DRIVE SHAFT FAILURE 	(MDR 96/0191) - FITTING EXHIBITED SIGNS OF SEVERE INTERGRANNULAR CORROSION - AIRCRAFT OPERATES IN A SALT LADEN ENVIRONME	NT				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1996101700211	19961017	00211	CE  	1996	10	17	AU960193         	1	19960215	G	2432	CB24380E	BATTERY         			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  					BATTERY/CHARGER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) BATTERY LEAKING ACID IN AREA AROUND POSITIVE TERMINAL SEAL - SUSPECT MANUFACTURING FAULT						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
1996101700212	19961017	00212	NE  	1996	10	17	AU960194         	1	19960219	G	6730	SS275761024	BOLT            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					R-CRAFT SERVO SY	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD MAIN ROTOR SERVO LOWER MOUNT BOLT BADLY WORN - WORN BOLT AND REMAINING TWO SERVO BOLTS WERE ALSO FOUND TO 	BE INCORRECTLYINSTALLED					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
1996101700213	19961017	00213	CE  	1996	10	17	AU960195         	1	19960111	G	2710	051010224	CONTROL CABLE   		051010513   	CESSNA	172   	172M        	2072418	CE  										AILERON CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CABLES PNO 0501015-224 (2OFF) AND AILERON BALANCE CABLE  PNO 0510105-13 (1OFF) CORRODED - TURNBARRELS PNO 	AN155B32L (1OFF), PNO AN155B165 (2OFF) AND PNO AN155B8L CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR TO PAINT STR	IPPING AND THE USEOF BICARBONATE OF SODA FOR STRIPPING - PERSONNEL/MAINTENANCE ERROR				1	H	7	1 	3O			NT	3A12    					 
1996101700214	19961017	00214	CE  	1996	10	17	AU960196         	1	19960111	G	5530		SKIN            			CESSNA	172   	172M        	2072418	CE  										VERT STAB STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER LEADING EDGE SKIN PN 0531006-96 AND LEADING  EDGE RIB PN 0531006-5 CORRODED IN AREA WHERE MASK	ED BY DORSAL FINSKIN - SUSPECT CAUSED BY INADEQUATE PROTECTION AND PROCEDURES  DURING PAINT STRIPPING - PERSONNEL/MAINTE	NANCE ERROR - SEE MDR 96/0195 FOR ADDITIONAL INFORMATION				1	H	7	1 	3O			NT	3A12    					 
1996101700215	19961017	00215	CE  	1996	10	17	AU960197         	1	19960111	G	5511	053200197	SPAR            			CESSNA	172   	172M        	2072418	CE  										HORZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER SKIN AND SPAR CRACKED IN AREA OF LIGHTENINGHOLE - FOUND DURING INSPECTION IAW CESSNA SERVICE	 BULLETIN SE94-8					1	H	7	1 	3O			NT	3A12    					 
1996101700216	19961017	00216	CE  	1996	10	17	AU960198         	1	19960111	G	2730	051010545	CONTROL CABLE   		051010544   	CESSNA	172   	172M        	2072418	CE  										ELEVATOR CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM CABLES PNO 0510105-44 AND PNO 0510105-45 AND ELEVATOR CONTROL CABLES PNO 0510105-291 AND PNO 0510105	-290CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR TO PAINT STRIPPING - SEE MDR 96/0195 FOR ADDITIONAL INFORMATION					1	H	7	1 	3O			NT	3A12    					 
1996101700217	19961017	00217	CE  	1996	10	17	AU960199         	1	19960111	G	2750	051010594	CONTROL CABLE   		051010593   	CESSNA	172   	172M        	2072418	CE  										FLAP SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP CABLES PNO 0510105-93 (2OFF) AND PNO 0510105-94 (2OFF)  CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR T	O PAINT STRIPPING - SEE MDR 96/0195 FOR ADDITIONAL INFORMATION					1	H	7	1 	3O			NT	3A12    					 
1996101700218	19961017	00218	NE  	1996	10	17	AU960200         	1	19960216	G	2560	WB5379	CABLE           			SKRSKY	S76   	S76A        	8143006	NE  										HOIST	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					033					(AUS) HOIST CABLE DAMAGED - 15 OF 19 STRANDS DAMAGED - MEF INVESTIGATION FOUND FAILURE WAS DUE TO OVERLOAD						1	G	7	2 	3U			 	H1NE    					 
1996101700219	19961017	00219	NM  	1996	10	17	AU960201         	1	19960206	G	2910	82970010149	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					MAIN HYD SYS	HOLED           	W				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) ALUMINIUM ALLOY HYDRAULIC PRESSURE PIPE LOCATED BETWEN THE ENGINE DRIVEN PUMP AND THE PRESSURE MANIFOLD HOLED DUE 	TO RUBBING ONSTRUCTURE IN AREA OF NACELLE ABOVE THE JET PIPE - LOSS OF NO2  SYSTEM HYDRAULIC FLUID					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996101700220	19961017	00220	CE  	1996	10	17	AU960202         	1	19960221	G	5312		BULKHEAD        			CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470R       	17026	SO  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH SIDE FORWARD DOORPOST BULKHEAD CRACKED - FOUND DURING  INSPECTION IAW AD/C180/75 AMDT1						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996101700221	19961017	00221	CE  	1996	10	17	AU960203         	1	19960219	G	5312	07136084	BULKHEAD        			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY				MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRUT ATTACHMENT BULKHEAD CRACKED ON LH SIDE - CRACK STARTS AT BEND RELIEF NOTCH AND GOES UNDER THE STRUT ATTACHME	NT FITTING -CRACK LENGTH APPROXIMATELY 9.525MM (0.375IN)					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1996101700222	19961017	00222	EU  	1996	10	17	AU960204         	1	19960119	G	5330		SEAL            			AIRBUS	320   	A320212     		EU  										EXT PLATES/SKIN	DETERIORATED    	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) AIRCRAFT VIBRATING BADLY DURING CLIMB - INVESTIGATION FOUND WING TO FUSELAGE BELLY SEALS ON PANELS 192ET AND 191ET	 DETERIORATED AND BOTH LH AND RH RAM AIR INLET DOORS HAD EXCESSIVE PLAY					2	L	7	2 	4F			RT	A28NM   					 
1996102300014	19961023	00014	NM  	1996	10	23	AU960205         	1	19960119	G	5320	148T274010	CHORD           			BOEING	767   	767277      		NM  	GE    									MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			23934							(AUS) AFT FUSELAGE BULKHEAD CHORD LOCATED AT STN BS1809.5 WL250 RH CRACKED THROUGH FASTENER HOLE - CRACK LENGTH 59.69MM 	(2.35IN)					2	L	7	2 	4F			RT	A1NM    					 
1996101700223	19961017	00223	WP  	1996	10	17	AU960206         	2	19960215	G	7230	8962233	BLADE           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  					T ENG CMPRSR/FAN	DAMAGED         	W				K				NONE                    				O	E	R	OTHER                     	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	IN	INSP/MAINT     	1			AU	S 					8035019787		P31286			(AUS) LH ENGINE 1ST STAGE IMPELLER DAMAGED - SECONDARY DAMAGE CAUSED TO 2ND STAGE IMPELLER						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
1996101700224	19961017	00224	EU  	1996	10	17	AU960207         	1	19960126	G	3230	E26000330H	SOLENOID        			AIRBUS	320   	A320212     		EU  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0047ANSSN					(AUS) LANDING GEAR HYDRAULIC SUPPLY SAFETY VALVE SOLENOID INTERMITTENT FAULT - INTERNAL LEAKAGE WITHIN MAIN VALVE WITH S	OLENOID OPENCAUSED CUTOFF OF LANDING GEAR HYDRAULIC SUPPLY					2	L	7	2 	4F			RT	A28NM   					 
1996101700225	19961017	00225	SO  	1996	10	17	AU960208         	2	19960219	G	7310	633958	SEAL            		628556      	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					ENG,FUEL DIST SY	UNAPPROVED PART 	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 							514615			(AUS) RH ENGINE FUEL NOZZLE SEALS PNO 633958-3 AND WASHERS PNO 640612  DETERIORATED AND IN POOR CONDITION - ON TWO NOZZL	ES THE 'O' RING PNO 630979-9 HAD BEEN SUBSTITUTED BY AN UNKNOWN BLACK RUBBER 'O' RING WHICH HAD HARDENED TO A BRITTLE CO	NDITION - TWO NOZZLES WEREPARTLY BLOCKED BY RUBBER DEPOSITS - UNAPPROVED PART				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996102200002	19961022	00002	CE  	1996	10	22	AU960209         	1	19960211	G	7603	AN35A	BOLT            			CESSNA	150   	A150M       	2071831	CE  	CONT  	O200  	O200A       	17020	SO  					POWER CONTROL SY	MISSING         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 							205388			(AUS) BOLT ATTACHING THROTTLE CABLE TO CARBURETTOR ARM MISSING CAUSING LOSS OF ENGINE CONTROL AND FORCED LANDING						1	H	7	1 	3O	3	O		3A19    	E252				 
1996102300015	19961023	00015	NM  	1996	10	23	AU960210         	1	19960115	G	5410	311T31021	PIN             			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					NAC-PYL M-FRAME	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE PYLON MID SPAR FITTING FUSE PIN CRACKED ON INNER BORE  APPROXIMATELY 23MM (0.90IN) IN FROM THE HEAD OF T	HE PIN - CRACK LENGTH APPROXIMATELY 12MM (0.47IN) - FOUND DURING EDDY CURRENT INSPECTION IAW B76-54-40-4D - CRACK CONFIR	MED BY MAGNETICPARTICLE INSPECTION				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1996101700226	19961017	00226	SO  	1996	10	17	AU960211         	1	19960221	G	5751		RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WING AIL/ELV SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH AILERON NOSE RIBS CRACKED - FOUND DURING INSPECTION IAW AD/PA44/16						1	L	7	2 	3O				A19S0   					 
1996101700227	19961017	00227	NM  	1996	10	17	AU960212         	1	19960111	G	2913	20894	BEARING         	ABEX        	ELECMOTOR   	BOEING	737   	737377      		NM  										MAIN HYD SYS	INCORRECT ASSY  	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 					223336ANSS					(AUS) HYDRAULIC SYSTEM 'A' ELECTRIC PUMP THRUST BEARING PNO 20894  INCORRECTLY ASSEMBLED CAUSING IMPELLER PNO 66410 TO R	UB ON COVER PNO 57976 DUE TO INSUFFICIENT CLEARANCE - METAL CONTAMINATION OF SYSTEM 'A' - PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4F			RT	A16WE   					 
1996101700228	19961017	00228		1996	10	17	AU960213         	4	19960123	G	6113	08550303	SUPPORT         			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY S	CRACKED         	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) RH PROPELLER SPINNER SUPPORT CRACKED AND DISLODGED FROM PROPELLER DOME - SUPPORT IS CONSTRUCTED OF NYLON MATERIAL						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1996101700229	19961017	00229	SW  	1996	10	17	AU960214         	1	19960112	G	2910	27810322682	PIPE            	SWRNGN      	SA227DC     	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT									MAIN HYD SYS	WORN            	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 					851B					(AUS) LH HYDRAULIC PIPE LEAKING FROM PIN HOLE - RH HYDRAULIC PIPE WORN AND LEAKING FROM RUBBING ON FUEL SUPPLY LINE PNO 	27-62026-273					2	L	7	2 	4T			RT	A18SW   					 
1996101700230	19961017	00230	EU  	1996	10	17	AU960215         	2	19960215	G	7230	P132P04	BLADE           								CFMINT	CFM56 	CFM563B2    	13802	EU  					T ENG CMPRSR/FAN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			18236				720483			(AUS) ENGINE HP COMPRESSOR 2ND STAGE BLADE CRACKED IN DOVETAIL AREA											4	F			E21EU				 
1996101700231	19961017	00231	SW  	1996	10	17	AU960216         	1	19960110	G	2730	2744046053	QUADRANT        			FRCHLD	SA227 	SA227DC     	3377521	SW  										ELEVATOR CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLEET CHECK CARRIED OUT ON ELEVATOR QUADRANT STEPS FOR LOOSE OR  MISSING ATTACHMENT BOLT NUT - NIL DEFECTS FOUND						2	L	7	2 	4T			RT	A18SW   					 
1996101700232	19961017	00232	EU  	1996	10	17	AU960217         	2	19960216	G	7250	3053556220	BEARING         								CFMINT	CFM56 	CFM563C1    	13802	EU  					TURBINE SECTION	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							725278			(AUS) NO1 ENGINE VIBRATION AT APPROXIMATELY 70% N1 - CREW ADVISED OF 4-5 LARGE ILLUMINATIONS FROM LEFT WING AREA - ENGIN	E REDUCED TOIDLE WHERE OPERATION APPEARED NORMAL - SUSPECT NO4 BEARING FAILURE										4	F			E21EU				 
1996101700233	19961017	00233	EU  	1996	10	17	AU960218         	1	19960220	G	3240	215042	BRAKE           			PILATS	PC12  	PC12        	7090550	EU  										LG WHEEL/BRAKE S	HIGH TEMPERATURE	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 			83   							(AUS) BRAKES OVERHEATED DURING TAXI - TWO FLAT TYRES DUE TO FUSEABLE PLUGS MELTING - IT WAS REPORTED THAT NO EXCESSIVE B	RAKING WASUSED - SUSPECT FAULTY FUSEABLE PLUGS FITTED					1	L	7	1 	3T			RT	A78EU   					 
1996101700234	19961017	00234	EU  	1996	10	17	AU960219         	1	19960130	G	3230	C242450061	UPLOCK          			AMD   	FALC50	FALCON900   	2700160	EU  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U378					(AUS) NOSE LANDING GEAR UPLOCK UNIT INTERNAL FAILURE - THIS DEFECT WAS RECEIVED FROM NO34 SQN RAAF AND IS FOR INFORMATIO	N ONLY					2	L	7	3 	4F			RT	A46EU   					 
1996101700235	19961017	00235	SO  	1996	10	17	AU960220         	1	19960221	G	7110		COWLING         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	ENGINE COWL SYS	BIRD STRIKE     	W				K				NONE                    				C			F.O.D.                    			TO	TAKEOFF        	1			AU	S 										(AUS) RH ENGINE UPPER INTAKE COWL DAMAGED BY BIRDSTRIKE						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
1996101700236	19961017	00236	CE  	1996	10	17	AU960221         	1	19960226	G	5510	123262Y1	BRACKET         			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					HORZ STAB SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER AFT LH MOUNTING REINFORCING BRACKET CRACKED ALONG BEND RADIUS ADJACENT TO LOWER OUTBOARD BOL	T - CRACK LENGTH 25MM (0.98IN)					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996101700237	19961017	00237	EA  	1996	10	17	AU960222         	2	19960201	G	7414	103493108	MAGNETO         	BENDIX      	103493108   	BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					ELEC PWR SUPPLY	CONTAM WATER    	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			1729 		F098914F		RL1378340A			(AUS) RH ENGINE RH MAGNETO FAULTY - INVESTIGATION FOUND WATER  CONTAMINATION SUSPECT CAUSED BY BLOCKAGE OF GAUZE SCREEN						1	H	7	2 	3O	3	O		A17EU   	E295				 
1996101700238	19961017	00238	SO  	1996	10	17	AU960223         	1	19960223	G	7120	8621202	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  					ENGINE MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L12272			(AUS) RH ENGINE MOUNT ASSEMBLY CRACKED IN TWO PLACES - CRACKS START IN OPPOSITE SIDES OF THE TUBE JUST BELOW THE LH TOP 	ENGINE MOUNTATTACHMENT RING BUT ABOVE THE GUSSETT PN 86212-22V - ONE CRACK HAD PROPAGATED HALF WAY AROUND THE TUBE - THE	 OTHER CRACK HADTRAVELLED INTO THE TUBE BACK TO THE FIREWALL ATTACHMENT POINT -  CRACK LENGTH APPROXIMATELY 25.4MM (1IN)	 - AD/PA44/10 (1) SB719 HAD BEEN PREVIOUSLY CARRIED OUT			1	L	7	2 	3O	3	O		A19S0   	E286				 
1996101700239	19961017	00239	SO  	1996	10	17	AU960224         	1	19960227	G	5751	8639702	RIB             	PIPER       	SEMINOLE    	PIPER 	PA44  	PA44180     	7104402	SO  										WING AIL/ELV SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON NOSE RIBS PNO 86397-02 AND PNO 86397-03 CRACKED - FOUND  DURING INSPECTION IAW AD/PA44/16						1	L	7	2 	3O				A19S0   					 
1996101700240	19961017	00240	CE  	1996	10	17	AU960225         	1	19960228	G	3210	10581002367	A FRAME         	BEECH       	B76         	BEECH 	76    	76          	1153005	CE  										MAIN GEAR SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 			575  		AAC078					(AUS) LH MAIN LANDING GEAR 'A' FRAME ASSEMBLY BROKEN AT CORROSION  TREATMENT HOLE AS INDICATED IN BEECH SB 2361 (AD/BEEC	H76/18)					1	L	7	2 	3O				A29CE   					 
1996101700241	19961017	00241	SO  	1996	10	17	AU960226         	1	19960229	G	5711	6658200	SPAR            			PIPER 	PA28  	PA28235     	7102810	SO  										OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING MAIN SPAR CONTAINED EXFOLIATION CORROSION IN AREA OF REAROUTBOARD ATTACHMENT BOLT HOLE - FOUND WHEN WING R	EMOVED FROM FUSELAGE - AIRCRAFT WAS MANUFACTURED IN 1963 AND HAD BEEN PARKED IN THE OPEN FOR THE LAST 12 MONTHS - SEE MD	R 96/0227 AND MDR 96/0228 FOR ADDITIONAL INFORMATION				1	L	7	1 	3O				2A13    					 
1996101700242	19961017	00242	SO  	1996	10	17	AU960227         	1	19960229	G	5320	6241100	CHANNEL         	PIPER       	PA28235     	PIPER 	PA28  	PA28235     	7102810	SO  	LYC   									MAIN FRAME SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2100 		2810173					(AUS) LH SIDE FUSELAGE CHANNEL SEVERELY CORRODED IN AREA ADJACENT TO THE STEEL REAR WING SPAR ATTACHMENT POINT - CHANNEL	 METAL HADCOMPLETELY OXIDISED - SUSPECT CORROSION HAD BEEN KNOWN ABOUT FOR SOME TIME AS AN AMATEURISH ATTEMPT HAD BEEN M	ADE TO TREAT THECORROSION - PERSONNEL/MAINTENANCE ERROR - SEE ALSO MDR 96/0226 AND MDR 96/0227 FOR ADDITIONAL INFORMATIO	N			1	L	7	1 	3O				2A13    					 
1996101700243	19961017	00243	SO  	1996	10	17	AU960228         	1	19960229	G	5711	6205401	SPAR            			PIPER 	PA28  	PA28235     	7102810	SO  										OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2100 							(AUS) RH WING AFT SPAR TO STEEL PLATE PN 66762-00 SEPARATED DUE TO CORROSION OF JOINING RIVETS - WHEN THE PLATE WAS REMO	VED SEVERECORROSION WAS ALSO FOUND ON THE REAR SPAR - CAUSED BY CORROSION  ACTION BETWEEN SPAR AND STEEL PLATE - SEE MDR	 96/0226 AND MDR96/0227 FOR ADDITIONAL INFORMATION				1	L	7	1 	3O				2A13    					 
1996101700244	19961017	00244	GL  	1996	10	17	AU960229         	3	19960221	G	6110	A3205	SCREW           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY S	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								ED1641		(AUS) PROPELLER SCREW LOOSE AND CONTACTING LOW PITCH STOP CAUSING  PROPELLER TO FEATHER ON SHUTDOWN						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1996101700245	19961017	00245		1996	10	17	AU960230         	4	19960222	G	6113		SUPPORT         			BEECH 	35    	M35         	1151526	CE  	CONT  	O470  	IO470C      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	PROPELLER ASSY S	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								742410		(AUS) PROPELLER SPINNER SUPPORT FAILED - SPINNER BULKHEAD CRACKED -  THIS IS THE SECOND SIMILAR OCCURRENCE ON THIS AIRCR	AFT (LAST TIMEIN AUGUST 1992) - SUSPECT CAUSED COMBINATION OF OUT OF BALANCE PROPELLER AND LOSS OF PRELOAD DUE TO EXCESS	IVE HOURS BETWEEN INSPECTIONS				1	L	7	1 	3O	3	O		3A15    	E273	5	C	P880	 
1996102200003	19961022	00003	SO  	1996	10	22	AU960231         	2	19960303	G	7320	3010466	ARM             	PWA         	324483432   	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	POWER CONTROL SY	CRACKED         	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			AU	S 					A59370					(AUS) LH ENGINE FUEL CONTROL UNIT (FCU) CONTROL ARM CRACKED AND FAILED						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1998042300011	19980423	00011	CE  	1998	4	23	AU960232         	2	19960219	G	8530	317206	CYLINDER        	CONT        		MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  					ENG CYL SEC	SEPARATED       	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 			430  		317206		317206			(AUS) NO4 CYLINDER HEAD SEPARATED FROM CYLINDER BARREL IN AREA OF SCREWTHREADS - PRE-EXISTING CRACK IN SCREW THREAD AREA						1	L	7	1 	3O	3	O		2A3     	E9CE				 
1998042300012	19980423	00012	SO  	1998	4	23	AU960235         	1	19960303	G	5751		SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										RT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH AILERON SPAR CRACKED IN AREA BEHIND INBOARD HINGE ARM ATTACHMENT POINT - FOUND DURING INSPECTION IAW AD/PA31/11	8					1	L	7	2 	3O				A20SO   					 
1998042300013	19980423	00013	NM  	1998	4	23	AU960237         	1	19960228	G	6710	A4372	BRACKET         	ROBSIN      		ROBSIN	R22   	R22BETA     		NM  										MAIN RTR CNTRL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1805 							(AUS) COLLECTIVE CONTROL SYSTEM BRACKET BROKEN - SUSPECT FAILURE INITIATED DUE TO INCORRECT ASSEMBLY AND LOCKING OF THE 	EYE END WHICH PASSES THROUGH THE BRACKET					1	G	7	1 	3O				H10WE   					 
1998042300014	19980423	00014	WP  	1998	4	23	AU960238         	1	19960204	G	6310	23623	LOCKNUT         	HILLER      	TRANSMISSION	HILLER	UH12  	UH12E       	4360122	WP  										ENG/TRANS CPLNG	LOOSE           	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 			1034 		708					(AUS) TRANSMISSION CLUTCH BEARING RETENTION NUT LOCKWIRE BROKEN  ALLOWING THE OUTER CLUTCH HOUSING TO BIND AGAINST THE F	IRST STAGECARRIER - SUSPECT CAUSED BY INSUFFICIENT TORQUE ON NUT DURING  LAST TRANSMISION OVERHAUL, NUT AND/OR BEARINGS 	NOT CORRECTLY SEATED DURING ASSEMBLY AT OVERHAUL OR LOCKWIRE PICKING UP ON SLEEVE AND BREAKING ALLOWING NUT TO LOOSEN DU	RING FREQUENT AUTOROTATIONS - TRANSMISSION FREEWHEEL LOCKUP - METAL  CONTAMINATION OF TRANSMISSION OIL FILTER			1	G	7	1 	3O				4H11    					 
1998042300015	19980423	00015	GL  	1998	4	23	AU960239         	3	19960228	G	6114	220117	HUB             	HARTZL      		MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			817  		CH1151			CH1151		(AUS) PROPELLER HUB SEVERELY CORRODED INTERNALLY IN HUB CAVITY AND AROUND ATTACHMENT BOLT FILLETS						1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
1998042300016	19980423	00016	EA  	1998	4	23	AU960240         	2	19960301	G	7421	RHM38E	SPARK PLUG      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENG,IGNITN DISTR	FOULED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			30   							(AUS) BOTTOM SPARK PLUGS IN ENGINE FOULED						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
1998042300017	19980423	00017	EU  	1998	4	23	AU960241         	1	19960215	G	3040	350A89103701	WIPER ARM       			AEROSP	AS355 	AS355F2     	8680812	EU  										WINDOW AI/DE-ICE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WINDSHIELD WIPER ARM CRACKED THROUGH PIN HOLE THAT SECURES SPRINGTO WIPER ARM						1	G	7	2 	3U				H11EU   					 
1998042300018	19980423	00018	EU  	1998	4	23	AU960242         	1	19960227	G	7160	352002034	HOSE            	LYC         		BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ENG AIR INT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L25473L2547					(AUS) LH AND RH ENGINE AIR INDUCTION HOSES FAULTY AS PER AD/BN2/57 AND SB BN2-95 - LH ENGINE HOSE WIRE SEPARATING - RH E	NGINE HOSE WIRE SEPARATING AND HOSE PARTIALLY COLLAPSED - BOTH HOSES WERE  SERVICEABLE AT LAST 50 HOUR SERVICING					1	H	7	2 	3O	3	O		A17EU   	1E4				 
1998042300019	19980423	00019	CE  	1998	4	23	AU960243         	1	19960217	G	2810		BAFFLE          			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUEL STORAGE SYS	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING FUEL SYSTEM RESERVOIR FOAM BAFFLE DISINTEGRATED - FOUND  DURING INSPECTION IAW SB 2109 PARA 1 - SUSPECT BA	FFLE HAD NOTBEEN REPLACED IAW BEECH SB 2109 PART 2 - PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1998042300020	19980423	00020	SO  	1998	4	23	AU960244         	1	19960306	G	3211	401335	BOLT            		6750200     	PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					RT MLG	INCORRECT FIT   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR TRUNNION PIN RETAINING BOLT PNO 401335 NOT  FITTED OR INCORRECTLY TORQUED FOLLOWING MAINTENAN	CE - AFTTRUNNION RETAINER PIN PNO 67502-00 DISLODGED - DAMAGE TO WING  UPPER SKIN - PERSONNEL/MAINTENANCE ERROR					1	L	7	1 	3O	3	O		2A13    	1E10				 
1998042300021	19980423	00021	SO  	1998	4	23	AU960245         	1	19960216	G	5343	AN411A	BOLT            			PIPER 	PA28  	PA28161     	7102803	SO  										LT MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR OUTBOARD ATTACHMENT BOLT FAILED - BOLT WAS  PROTRUDING FROM SKIN						1	L	7	1 	3O				2A13    					 
1998042300022	19980423	00022	CE  	1998	4	23	AU960246         	1	19960227	G	3244		TIRE            		5003064     	CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	LG WHEEL/BRAKE S	DEFLATED        	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 			87   							(AUS) RH MAIN WHEEL TYRE DEFLATED DUE TO HEAVY APPLICATION OF BRAKES CAUSING FLAT SPOT - OCCURRED DURING CREW TRAINING						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998042300023	19980423	00023		1998	4	23	AU960247         	4	19960218	G	6122	DCFU290D13T6	DRIVE SHAFT     			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROP CNTRL SYS	SHEARED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			7    		00753			794309		(AUS) PROPELLER GOVERNOR (CSU) DRIVE SHAFT SHEARED						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998042300024	19980423	00024	GL  	1998	4	23	AU960248         	1	19960123	G	3220		SPRING          			AMTR  	MAXAIR	XP503       	9570746	GL  										TAIL WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) TAIL WHEEL SPRING FAILED DURING LANDING - THIS DEFECT WAS  RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY						1	H	7	1 	3I			NT	EXPA1H71					 
1998042300025	19980423	00025	EU  	1998	4	23	AU960250         	2	19960128	G	8530		PISTON          			AMTR  	MAXAIR	XP503       	9570746	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					ENGINE CYL SEC	CRACKED         	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 										(AUS) ENGINE PISTON CROWN CRACKED - THIS DEFECT WAS RECEIVED FROM THE  AUF AND IS FOR INFORMATION ONLY						1	H	7	1 	3I	3	I	NT	EXPA1H71	EXPE3I				 
1998042300026	19980423	00026	SO  	1998	4	23	AU960253         	1	19960306	G	3210	2251200	STUD            			PIPER 	PA30  	PA30        	7103002	SO  										MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR SIDE BRACE STUDS CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA30/34						1	L	7	2 	3O				A1EA    					 
1998042300027	19980423	00027	SO  	1998	4	23	AU960256         	2	19960207	G	8530	646283	EXHAUST VALVE   	CONT        	VALVEGUIDE  	CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  					RT  ENG CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			91   		451050		451050			(AUS) ENGINE EXHAUST VALVES PNO 646283 AND VALVE GUIDES PNO 643766 WORNAND LEAKING						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1998042300028	19980423	00028	CE  	1998	4	23	AU960257         	1	19960301	G	5510	12321391	BRACKET         	CESSNA      	STABILISER  	CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  					HORZ STAB SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER TRIM ACTUATOR MOUNT BRACKET BROKEN - AIRCRAFT IS USED FOR SKYDIVING WITH DOORS REMOVED AND D	EFLECTORFITTED - SUSPECT TURBULANCE CAUSED BY DEFLECTORS CAUSES EXCESSIVETURBULANT AIRFLOW OVER EMPENNAGE - SEE MDR 96/0	178 FOR FURTHER INFORMATION				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1998042300029	19980423	00029	CE  	1998	4	23	AU960258         	1	19960308	G	2810	41423	FUEL CELL       			CESSNA	402   	402B        	207590P	CE  										FUEL STORAGE SYS	DETERIORATED    	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) LH AUXILIARY FUEL CELL DISINTEGRATING IN AREA OF CONTACT WITH  GASKET SEALER - FUEL CELLS ARE A RELATIVELY NEW ITE	M					1	L	7	2 	3O				A7CE    					 
1998042300031	19980423	00031	SW  	1998	4	23	AU960260         	1	19960213	G	2435	2008	STARTER         	AIRPRTSCORP 	STARTERGEN  	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					STARTER-GENERATO	FAULTY          	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					2008					(AUS) RH ENGINE STARTER/GENERATOR WOULD NOT ROTATE ENGINE WHEN ENGAGED						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE				 
1998042300032	19980423	00032	NE  	1998	4	23	AU960261         	2	19960220	G	7260	22080	RETAINER        	PWA         		BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					T ENG AUX DRIVE	FAILED          	W				K				NONE                    				E	X		VIBRATION/BUFFET          	ENGINE FLAMEOUT           		CR	CRUISE         	1			AU	S 					22080		688015			(AUS) NO1 ENGINE FAILED IN FLIGHT - SUSPECT CAUSED BY FAILURE OF THE CONSTANT SPEED DRIVE (CSD) SHAFT REAR BEARING RETAI	NER ALLOWINGTHE RETAINING NUT TO LOOSEN AND THE CSD SHAFT TO MOVE FORWARD ANDDISENGAGE THE DRIVE GEARS					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1998042300033	19980423	00033	SO  	1998	4	23	AU960262         	1	19960127	G	3222	702057505	STRUT           			GULSTM	AA5   	AA5         	0631410	SO  										NLG	FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NOSE LANDING GEAR TUBULAR STRUT FAILED DUE TO INTERNAL CORROSION CAUSED BY WATER ENTRAPMENT IN COVERING BOOT - NLG	 COLLAPSED -PROPELLER CONTACTED GROUND - SUSPECT BOOT HAD NOT BEEN REMOVED TOINSPECT NLG FOR SOME CONSIDERABLE TIME - PE	RSONNEL/MAINTENANCE ERROR				1	L	7	1 	3O				A16EA   					 
1996121900096	19961219	00096	NM  	1996	12	19	AU960263         	1	19960229	G	2460		CONNECTOR       			BOEING	737   	737476      		NM  										DC PWR DISTR	ARCED           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN AFT VACUUM CLEANER OUTLET CONNECTOR ON RH SIDE OF PASSENGER CABIN SHOWED EVIDENCE OF ARCING BETWEEN THE CONN	ECTOR LIVE TERMINAL AND THE MOUNTING TRIM PANEL WITH A 25.4MM (1IN) DIAMETER BURN ON THE ADJACENT SOUND PROOFING BLANKET	 - INVESTIGATION FOUND MANUFACTURER HAD FITTED INCORRECT PANELS - UNAPPROVED PART - MANUFACTURING ERROR				2	L	7	2 	4F			RT	A16WE   					 
1998042300034	19980423	00034	NE  	1998	4	23	AU960264         	2	19960228	G	7320	WYG33234	CONTROLLER      								GE    	CF6   	CF680A      	30025	NE  					POWER CONTROL SY	SEIZED          	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 					WYG33234		580242			(AUS) LH ENGINE MAIN ENGINE CONTROL (MEC) POWER LEVER SEIZED - STRIP INSPECTION OF MEC COULD FIND NO FAULTS											4	F			E13NE				 
1998042300035	19980423	00035		1998	4	23	AU960265         	1	19960304	G	7810		EXHAUST PIPE    								GARRTT	TPE331	TPE33112UA  	01514	WP  					T ENG CONE-PIPE	CRACKED         	W				K	E			NONE                    	ENGINE SHUTDOWN         			M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 										(AUS) RH ENGINE EXHAUST STUB CRACKED AROUND CIRCUMFERENCE OF THE FLANGE ALLOWING HOT EXHAUST GAS TO BURN THE PAINT ON TH	E COWLING										4	T			E4WE				 
1998042300036	19980423	00036	CE  	1998	4	23	AU960266         	1	19960306	G	3246	D30256	HUB             	MCAULY      	WHEEL       	CESSNA	172   	172N        	2072434	CE  										LG WHEEL/BRAKE S	CORRODED        	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) WHEEL HUB CORRODED - THREADS STRIPPED ALLOWING WHEEL FLANGE AND  TYRE TO SEPARATE FROM HUB						1	H	7	1 	3O			NT	3A12    					 
1998042300037	19980423	00037	WP  	1998	4	23	AU960267         	1	19960314	G	5342		ADAPTER         			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										ATTACH FITTING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL FIN REAR ATTACHMENT ADAPTER CONTAINS SEVERE EXFOLIATION CORROSION IN AREA ADJACENT TO LH AND RH ATTACHMEN	T BOLTS					2	L	7	2 	4R				A669    					 
1998042300038	19980423	00038	SO  	1998	4	23	AU960268         	2	19960313	G	8520		CRANKSHAFT      	CONT        							CONT  	O300  	O300C       	17022	SO  					ENGINE SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					32067D3C		32067D3C			(AUS) ENGINE CONTAINED NUMEROUS DEFICIENCIES MAKING IT UNSERVICEABLE FOR USE: 1. CRANKSHAFT 0.0254MM TO 0.0508MM (0.001I	N TO 0.002IN) UNDER MINIMUM LIMITS2. CRANKCASE MAIN TUNNELS 0.0254MM TO 0.0508MM (0.001IN TO0.002IN) OUT OF LIMITS3. CYL	INDERS (3OFF) REQUIRED GRINDING TO P015  4. COUNTERWEIGHTS UNSERVICEABLE AS PER CONTINENTAL SERVICE  BULLETIN  5. OIL PU	MP ACCESSORY HOUSING DAMAGED BEYOND REPAIR6. CYLINDERS (2OFF) STAMPED 'MT' UNSERVICEABLE AS PER SERVICE BULLETIN7. CYLIN	DER (1OFF) OUT OF P015 LIMITS  8. CAMSHAFT LOBES DAMAGED9. OIL PUMP IMPELLERS DAMAGED BEYOND REPAIR							3	O			E253				 
1998042300039	19980423	00039	CE  	1998	4	23	AU960271         	1	19960305	G	2820	10092004115	PIPE            			BEECH 	200   	B200C       	1152924	CE  										FUEL DISTRBUTION	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN FUEL PIPE CHAFING ON STRUCTURE IN AREA BETWEEN MAIN LANDING GEAR BAY AND WING FUEL TANK - FUEL PIPE ON VH-AMM	 IN SIMILAR CONDITION					1	L	7	2 	4T				A24CE   					 
1998042300040	19980423	00040	GL  	1998	4	23	AU960272         	3	19960312	G	6110	A163352	O-RING          	MCAULY      		CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			940  		760875			760875		(AUS) PROPELLER RETENTION NUT 'O' RING SEALS INCORRECT - PNO A1633-52  SEALS USED IN OIL FILLED HUBS FITTED INSTEAD OF C	ORRECT PNOA1633-38 SEALS - INCORRECT SEALS BIND ON THE FERRULE CAUSING EXCESSIVE FRICTION DURING OPERATION AND PREVENTIN	G FEATHERING -UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042300041	19980423	00041	EA  	1998	4	23	AU960273         	2	19960227	G	8520	L2809236A	CAM FOLLOWER    	LYC         	0360A4A     	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 					L2809236A		L2809236A			(AUS) ENGINE CAM FOLLOWERS FAILED - SEVERE INTERNAL DAMAGE TO ENGINE - METAL CONTAMINATION OF OIL SYSTEM						1	L	7	1 	3O	3	O		2A13    	E286				 
1996110100177	19961101	00177	CE  	1996	11	1	AU960274         	1	19960313	G	5312	12121273	DOUBLER         	CESSNA      	BULKHEAD    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR BULKHEAD RH TAILPLANE ATTACHMENT BRACKET DOUBLER CRACKED  THROUGH - FURTHER INSPECTION FOUND REAR BULKHEAD CR	ACKED IN THESAME AREA					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996110100178	19961101	00178	GL  	1996	11	1	AU960275         	2	19960103	G	7250		TURBINE         	ALLSN       	SERIES11    						ALLSN 	250C  	250C20      	03013	GL  					T ENG TURBINE SE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CAT34207					(AUS) ENGINE GAS PRODUCER TURBINE ASSEMBLY FAULTY - TURBINE ASSEMBLY HAD NIL HOURS SINCE OVERHAUL - GP SUPPORT MOUNTING 	FLANGE BENT - DURING DISMANTLING TO CHANGE THE SUPPORT THE FOLLOWING DEFECTIVE ITEMS WERE FOUND :-1. 1ST STAGE NGV PNO 6	895021 - CRACKED AND VALVE DAMAGED 2. 1ST STAGE NGV HEAT SHIELD PNO 6890040 - CRACKED AND WARPED3. POSITION PLUGS (2OFF)	 PNO 6845899 - WORN  4. NO8 SUMP PNO 6845632 - EXCESSIVELY DENTED PERSONNEL/MAINTENANCE ERROR								3	U			E4CE				 
1996111300007	19961113	00007	SO  	1996	11	13	AU960276         	2	19960206	G	8520	626739	COLLAR          	CONT        	CRANKSHAFT  	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C98    	GL  	R ENGINE POWER S	WRONG PART      	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							566900			(AUS) CRANKSHAFT FITTED WITH INORRECT OIL TRANSFER COLLAR - STANDARD COLLAR PNO 626739 FITTED TO M10 CRANKSHAFT RESULTIN	G IN EXCESSIVECLEARANCE - LOG BOOK ENTRY ALSO DETAILED FITMENT OF STANDARD SIZEBEARINGS FITTED ALTHOUGH THE ACTUAL BEARI	NGS WERE M010 SIZE -UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR				1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
1996110100179	19961101	00179	EA  	1996	11	1	AU960277         	2	19960308	G	7314	RG17980	PUMP            	ROMEC       	RG17980     						LYC   	O720  	IO720A1A    	41546	EA  					ENG,FUEL DIST SY	LEAKING         	W				K				NONE                    				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		CR	CRUISE         	1			AU	S 					C542		L106854A			(AUS) ENGINE DRIVEN FUEL PUMP LEAKING FROM REAR OF PUMP											3	O			1E15				 
1996111300010	19961113	00010	CE  	1996	11	13	AU960278         	1	19960206	G	2810	509200106	FUEL TANK       	GOODYEAR    	50920010    	BEECH 	65    	65          	1152802	CE  	LYC   	O480  	IGSO480A1E6 	41529	EA  	HARTZL	HCB3Z	HCB3Z202    	GL  	FUEL STORAGE SYS	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 					7689016					(AUS) LH WING INBOARD FUEL TANK DETERIORATED AND LEAKING - THE TANK WAS REMOVED AND FOUND TO BE SEALED EXTERNALLY IN NUM	EROUS PLACES WITHPR1422 COMPOUND - 2 BUTTONS FOUND ON LOWER FLOOR OF TANK BAY - TANK MANUFACTURED IN 1976 - SUSPECT TANK	 HAD BEEN LEFT NEAR EMPTYFOR AN EXTENDED TIME CAUSING THE RUBBER TO DRY OUT				1	L	7	2 	3O	3	O		3A20    	E284	5	C	P907	 
1996110100180	19961101	00180	CE  	1996	11	1	AU960279         	1	19960206	G	5720	082217564	RIB             	CESSNA      	402B        	CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					002					(AUS) LH AND RH WHEEL WELL LANDING GEAR SUPPORT RIBS PNO 0822175-65  (LH) AND PNO 0822175-65 (RH) CRACKED AND DISTORTED 	- UNDER SKINDISTORTED IN AREA OF LANDING GEAR DOOR ATTACHMENT - NUMEROUS RIVETS MISSING - AIRCRAFT IS USED FOR SHORT HAU	L OPERATIONS AT MAXIMUM WEIGHTS - SUSPECT CAUSED BY HEAVY LANDINGS				1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996110100181	19961101	00181	CE  	1996	11	1	AU960280         	1	19960314	G	5412	12534096	BULKHEAD        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIREWALL AND RH BULKHEAD CRACKED IN AREA OF EXHAUST MOUNT  ATTACHMENT - AIRCRAFT IS USED AS A FLOAT PLANE						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996110100182	19961101	00182	CE  	1996	11	1	AU960281         	1	19960314	G	5412	12534095	BULKHEAD        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIREWALL AND LH BULKHEAD CRACKED AT EXHAUST MOUNT ATTACHMENT - AIRCRAFT IS USED AS A FLOAT PLANE						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996110100183	19961101	00183	CE  	1996	11	1	AU960282         	1	19960206	G	5347	002	SEAT TRACK      	CESSNA      	402B        	CESSNA	402   	402B        	207590P	CE  										MAIN FRAME SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					002					(AUS) SEAT TRACKS LOCATED NEAR AFT ENTRY DOOR EXTENSIVELY CORRODED AT  AFT END - WHEN THE SEAT TRACKS WERE REMOVED IT WA	S FOUND THAT THE FLOOR BENEATH THE TRACKS WAS ALSO CORRODED - FORWARD BAGGAGE FLOOR ALSO SHOWS SIGNS OF CORROSION - AIRC	RAFT IS USED TO CARRY SEAFOOD WITHOUT ADEQUATE PROTECTION FROM LEAKING SALT PRODUCTS				1	L	7	2 	3O				A7CE    					 
1996110100184	19961101	00184	CE  	1996	11	1	AU960283         	1	19960314	G	2730	12346506	TORQUE TUBE     	CESSNA      	ELEVATOR    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ELEVATOR STRUCT	LOOSE  RIVETS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ELEVATOR ASSEMBLY TORQUE TUBE PNO 1234650-6 TO ELEVATOR ATTACHMENT RIVETS LOOSE AND WORKING - AIRCRAFT IS OPERA	TED AS AFLOAT PLANE					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996110100185	19961101	00185		1996	11	1	AU960284         	4	19960315	G	2561	PO723	LIFEVEST        			BOEING	747   	747*        		NM  										EMERGENCY EQUIP	INCORRECT ASSY  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LIFE JACKET CO2 CYLINDER FIRING HEAD INCORRECTLY ASSEMBLED - THE HEAD WAS WIRED CLOSED WITH COPPER WIRE INSTEAD OF	 WITH THE CORRECT PLASTIC CLIP - RISK OF WIRE ENDS PUNCTURING BLADDER -  PERSONNEL/MAINTENANCE ERROR					2	L	7	4 	4F			RT	A20WE   					 
1996110100186	19961101	00186	CE  	1996	11	1	AU960285         	1	19960228	G	5711		SPAR            			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING MAIN SPAR CONTAINED MULTIPLE CRACKS IN AREA AT TOP IN SPAR  WEB						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996110100187	19961101	00187	CE  	1996	11	1	AU960286         	1	19960318	G	5320		DOOR POST       			CESSNA	182   	182E        	2072712	CE  	CONT  	O470  	O470R       	17026	SO  					MAIN FRAME SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH REAR DOOR POST CORRODED THROUGH IN AREA OF ATTACHMENT TO  UNDERCARRIAGE BULKHEAD IN UNDER FLOOR AREA						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996110100188	19961101	00188	EU  	1996	11	1	AU960287         	1	19960316	G	7160	352002034	HOSE            	LYC         	IO540K1B5   	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ACFT ENG AIR INT	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L2550048A					(AUS) RH ENGINE INDUCTION HOSE COLLAPSED DUE TO INTERNAL WIRE  SEPARATING FROM THE HOSE - SLIGHT CORROSION WAS ALSO FOUN	D ON THEWIRE IN THE AFFECTED AREA - FOUND DURING INSPECTION IAW AD/BN2/57- LH ENGINE HOSE WAS INSPECTED AND FOUND TO BE 	SERVICEABLE - LHENGINE INTAKE HOSE BETWEEN AIR BOX AND FUEL CONTROL COLLAPSED ON THE NEXT FLIGHT - RH HOSE THEN INSPECTE	D AND FOUND TO BE COLLAPSING ALSO			1	H	7	2 	3O	3	O		A17EU   	1E4				 
1996110100189	19961101	00189	GL  	1996	11	1	AU960288         	3	19960314	G	6110	B15921	SPRING          	HARTZL      	HCC2YK2CUF  	PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY S	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			1350 		AU5509			AU5509		(AUS) PROPELLER RETAINER SPRING INCORRECT PART - EARLY MODEL SPRING PNOB1594 IN LATE MODEL SPRING RETAINER PNO B1592-1 -	 UNAPPROVED PART- PERSONNEL/MAINTENANCE ERROR					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1996110100190	19961101	00190	CE  	1996	11	1	AU960289         	1	19960312	G	6120	DCF290D2BT3	CSU             	MCAULY      	DCF290D2BT3 	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	PROP CNTRL SYS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			1510 		762113		248434R	950621		(AUS) PROPELLER CSU END CAP CRACKED AND LEAKING - THE CRACK COMMENCED  AT THE FULL FINE CONTROL STOPS AND RADIATED AROUN	D THE CENTRECOLLAR AND WAS HIDDEN BY THE CONTROL ARM RETURN SPRING - THE END CAP IS MANUFACTURED FROM A BRITTLE PLASTIC 	TYPE MATERIAL				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1996110100191	19961101	00191	CE  	1996	11	1	AU960290         	1	19960312	G	8120	47090813	VALVE           	GARRTT      	47090813    	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					TURBO SUPERCHRGR	LEAKING         	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 					RHR0102		290447R			(AUS) WASTEGATE VALVE LEAKING OIL - OIL WAS DUMPED OVERBOARD VIA THE WASTEGATE VALVE DRAIN TUBE						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996110100192	19961101	00192	NM  	1996	11	1	AU960291         	1	19960313	G	3220		NLG             			PIPER 	PA60  	PA60600A    	7106002	NM  										NOSE-TAIL GEAR S	COLLAPSED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR COLLAPSED - DAMAGE TO NOSE GEAR DOORS -  INVESTIGATION FOUND THAT THE NOSE LANDING GEAR DRAG BRA	CE ASSEMBLY REPLACEMENT IAW AD/TSA-600/41 AMDT 2 HAD NOT BEEN CARRIED OUT - PERSONNEL/MAINTENANCE ERROR					1	M	7	2 	3O			RT	A17WE   					 
1996110100193	19961101	00193	CE  	1996	11	1	AU960292         	1	19960203	G	3210		BUSHING         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY				MAIN GEAR SYS	SEPARATED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR PIVOT TORQUE LINK ATTACHMENT BOLT PULLED THE BUSH THROUGH THE CENTRE OF THE TORQUE LINK ALLOWING THE 	WHEEL ASSEMBLYTO TURN 90 DEGREES TO THE FORWARD DIRECTION OF THE AIRCRAFT -  CAUSED BY WHEEL SHIMMY - SUSPECT A NON STAN	DARD BUSH WAS FITTED APPROXIMATELY 4 YEARS PREVIOUS WITH A DIAMETER CLOSE TO THAT OF  THE BOLT HEAD - FRETTING IN SERVIC	E EVENTUALLY ALLOWED THE BOLTTO PULL THROUGH - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR			1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996110100194	19961101	00194	SO  	1996	11	1	AU960293         	2	19960201	G	8540	539800	SPRING          	CONT        	IO520M      	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					R ENGINE REAR SE	MISALIGNED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			12   				L565777			(AUS) ENGINE STARTER ADAPTER SPRING TWISTED IN HOUSING						1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996110100195	19961101	00195	EU  	1996	11	1	AU960295         	1	19960319	G	3220	68231152	FRAME           			PARTEN	P68   	P68B        		EU  										NOSETAIL GEAR S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR SUPPORT FRAME CENTRE TUBE CRACKED IN AREA AFT  OF CLAMP PNO 68-2-3115-3 - AIRCRAFT IS USED FOR T	RAINING					1	H	7	2 	3O				A31EU   					 
1996110100196	19961101	00196	EA  	1996	11	1	AU960296         	2	19960314	G	8530		CYLINDER        			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					R ENGINE CYL SEC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L104555			(AUS) LH ENGINE NO3 CYLINDER CRACKED IN AREA OF EXHAUST PORT - CRACK LENGTH 50.8MM (2IN)						1	L	7	2 	3O	3	O		A1EA    	1E12				 
1996110100197	19961101	00197	SO  	1996	11	1	AU960297         	2	19960213	G	8520	652541	NUT             			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							570318			(AUS) ENGINE CYLINDER HOLD DOWN NUT CRACKED						1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996110100198	19961101	00198	EA  	1996	11	1	AU960298         	2	19960316	G	8530	SL14995	RETAINER        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					R ENGINE CYL SEC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L2817336A			(AUS) ENGINE PUSH ROD TUBE RETAINERS (4OFF) CRACKED - RETAINERS WERE SHIPPED WITH GASKET SET PNO SL 75439-1						1	H	7	1 	3O	3	O		3A17    	E286				 
1996110100199	19961101	00199	EA  	1996	11	1	AU960299         	2	19960315	G	8530	L201552	PISTON          	LYC         	VO435A1F    	BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	VO435A1F    	41516	EA  					R ENGINE CYL SEC	WORN            	W				K				NONE                    				O	E	R	OTHER                     	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	IN	INSP/MAINT     	1			AU	S 			117  		L201552		L201552			(AUS) ALL SIX CYLINDERS FOUND TO HAVE EXCESSIVE WEAR TO PISTONS, RINGS AND VALVE TRAIN INCONSISTANT WITH TIME SINCE OVER	HAUL - SUSPECTCAUSED BY UNREPORTED ENGINE OVERSPEED					1	G	7	1 	3O	3	O		2H3     	E279				 
1996110100200	19961101	00200	CE  	1996	11	1	AU960300         	1	19960215	G	3233	12810012	ACTUATOR        	CESSNA      	RHLGACTUATOR	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					LG EXT-RETRACT S	CRACKED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					7316					(AUS) RH MAIN LANDING GEAR ACTUATOR CRACKED ALLOWING DRIVE GEAR TO DISENGAGE FROM DRIVEN GEAR						1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996110100201	19961101	00201		1996	11	1	AU960301         	1	19960318	G	7110	365A58106221	FAIRING         	AEROSP      	RHENGINECOWL						TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					ENGINE COWL SYS	BROKEN          	W				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) RH ENGINE COWL HINGE ASSEMBLY BROKEN											3	U			E19EU				 
1996110100202	19961101	00202	CE  	1996	11	1	AU960302         	1	19960211	G	2750		SWITCH          			CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C505   	GL  	FLAP SYS	BROKEN WIRE     	W				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP SELECTOR DOWN MICROSWITCH WIRE BROKEN						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996110100203	19961101	00203	SO  	1996	11	1	AU960303         	1	19960305	G	3211	9529900	SIDE BRACE      		9529902     	PIPER 	PA34  	PA34200     	7103405	SO  										MLG SYS LT/RT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR SIDE BRACE STUDS P/N 95299-00 AND P/N 95299-0 2 CRACKED - FOUND DURING MAGNETIC PARTIC	LE INSPECTION IAW AD/PA34/46.					1	L	7	2 	3O				A7SO    					 
1996110100204	19961101	00204		1996	11	1	AU960304         	3	19960318	G	6114	D70151C87HUB	HUB             	MCAULY      	3AF32C87    	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY				PROPELLER ASSY S	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			366  							(AUS) PROPELLER HUB LEAKING RED DYE - STRIP INSPECTION FOUND THAT THE  BLADE NUT EXPANSION LOCKING PLUGS OVERLAPPED - PR	OPELLER MANUAL710930 REQUIRES A MINIMUM HOLE SPACING OF 4.762MM (0.1875IN) - PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996110100205	19961101	00205	EA  	1996	11	1	AU960305         	2	19960201	G	7320	3008787	ROD END         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	POWER CONTROL SY	STIFF           	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 							57092			(AUS) ENGINE FUEL CONTROL UNIT CONTROL ROD CONNECTOR ROD END STIFF						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1996110100206	19961101	00206	GL  	1996	11	1	AU960306         	3	19960319	G	6110	C3475	BLADE NUT       	MCAULY      	3AF32C87    	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY S	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			366  		791363			791363		(AUS) PROPELLER BLADE NUTS HAD NOT BEEN REWORKED IAW THE MANUAL -  PROPELLER HAS BEEN MODIFIED TO AN OIL FILLED MODEL AT	 WHICH TIME THE 'O' RING GROOVES ARE SUPPOSED TO BE MACHINED OUT - PERSNNEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1996110100207	19961101	00207	SO  	1996	11	1	AU960307         	1	19960216	G	5551		FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  										ATTACH FITTING S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOP RH STABILATOR ATTACHMENT FITTING CORRODED - STABILATOR AND ALL FOUR FITTINGS REMOVED FOR FURTHER INSPECTION - 	INSPECTION OF TOP RH POSITION REVEALED EXTENSIVE CORROSION TO SKIN FLANGE AND  CRACKING - CRACK LENGTH 19.05MM (0.75IN) 	- FOUND DURINGINSPECTION IAW AD/PA34/40				1	L	7	2 	3O				A7SO    					 
1996110100208	19961101	00208	CE  	1996	11	1	AU960308         	1	19960301	G	5741	12107041	DOWEL           	CESSNA      	DOWEL       	CESSNA	210   	210L        	2073448	CE  										ATTACH FITTING S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					21061159					(AUS) WING TO FUSELAGE LOCATING DOWEL PINS WORN ALLOWING MOVEMENT AT ATTACHMENT POINTS - SUSPECT CAUSED BY USE OF ACF 50	 MATERIAL WORKING BETWEEN MATING SURFACES AND CAUSING MOVEMENT					1	H	7	1 	3O				3A21    					 
1996110100209	19961101	00209	EA  	1996	11	1	AU960309         	2	19960213	G	7310	LW120980210	PIPE            			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENG,FUEL DIST SY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			764  				L1607348A			(AUS) FUEL INJECTION LINES ON NO2, NO3, NO5 AND NO6 CYLINDERS CRACKED  IN AREA OF SOLDER LINE JOINT TO THE FLANGE - FOUN	D DURINGINSPECTION IAW AD/LYC/90					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996110100210	19961101	00210	SW  	1996	11	1	AU960310         	1	19960311	G	2435	03601008	BEARING         	LUCAS       	STARTERGENE 	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					STARTER-GENERATO	COLLAPSED       	W				K				NONE                    				E		J	VIBRATION/BUFFET          		WARNING INDICATION        	CR	CRUISE         	1			AU	S 					94028		P70215			(AUS) LH ENGINE DRIVEN STARTER/GENERATOR REAR BEARING COLLAPSED -  INTERNAL DAMAGE TO STARTER/GENERATOR - AIR DUCT DAMAG	ED BY COOLING FAN					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE				 
1996110100211	19961101	00211	CE  	1996	11	1	AU960311         	1	19960220	G	2730	NAS77497	BEARING         	BEECH       	95610005603 	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  					ELEVATOR CONTROL	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ELEVATOR PUSH-PULL ROD BEARING PNO NAS77-4-97 SEIZED AND  WORKING IN FITTING PNO 95-610005-3 - ELONGATED HOLE W	ORN INFITTING					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996110100212	19961101	00212	CE  	1996	11	1	AU960312         	1	19960310	G	2432	1013642105	CIRCUIT BOARD   			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  					BATTERY/CHARGER	FAULTY          	W				K				NONE                    				H	N		ELECT. POWER LOSS-50 PC   	FALSE WARNING             		CR	CRUISE         	1			AU	S 										(AUS) BATTERY CHARGE SYSTEM PRINTED WIRING BOARD FAULTY						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996110100213	19961101	00213	CE  	1996	11	1	AU960313         	1	19960131	G	5720		PLATE           		00243001811 	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	CENTRE WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTRE SECTION FORWARD SPAR WEB PLATE LOCATED AT RH UPPER WING ATTACHMENT AREA CRACKED						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1996110100214	19961101	00214	CE  	1996	11	1	AU960314         	1	19960223	G	3260	13771	SWITCH          			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					LG POSITION IND	FAULTY          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH FAULTY - NLG MICROSWITCH SUSPECT FAULTY						1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996110100215	19961101	00215	CE  	1996	11	1	AU960315         	1	19960310	G	5720		PLATE           		00243001811 	BEECH 	58    	58          	1152740	CE  	CONT  									CENTRE WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTRE SECTION FORWARD SPAR WEB PLATE CRACKED IN AREA OF LH UPPER WING ATTACHMENT AREA - CRACK LENGTH 25MM (0	.98IN) - SEVERALSMALLER CRACKS WERE FOUND AROUND THE LOCK BOLT HOLES - CRACK LENGTHS APPROXIMATELY 7MM (0.275IN)					1	L	7	2 	3O				3A16    					 
1996110100216	19961101	00216	SO  	1996	11	1	AU960316         	2	19960229	G	8520		CRANKCASE       	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							276412R			(AUS) LH ENGINE CRANKCASE CRACKED - CRACK STARTED ABOVE AND FORWARD OF NO5 CYLINDER AND EXTENDED DOWNWARDS TO THE ALTERN	ATOR ATTACHMENT PAD - VISIBLE CRACK LENGTH 110MM (4.33IN)					1	L	7	2 	3O	3	O		A25CE   	E7CE				 
1996110100217	19961101	00217	SO  	1996	11	1	AU960317         	2	19960310	G	7414	104001667	SPRING          	BENDIX      	103493505   	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					LT ENG MAG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4719		1263468C			(AUS) LH ENGINE LH MAGNETO IMPULSE COUPLING SPRING BROKEN - ENGINE HAD NOT OPERATED FOR APPROXIMATELY 8 MONTHS WHILE AIR	CRAFT WAS WAITING FOR FITMENT OF THE RH ENGINE - ENGINE WAS GROUND RUN ON AWEEKLY BASIS - SUSPECT CORROSION AS CAUSE OF 	FAILURE				1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996110100218	19961101	00218	SW  	1996	11	1	AU960318         	1	19960216	G	6220	412010190103	SPINDLE         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR HEAD	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CH219					(AUS) MAIN ROTOR HEAD SPINDLE ASSEMBLY ELASTOMERIC DAMPER BEARING  SHEARED						1	G	7	2 	4U				H4SW    					 
1996110100219	19961101	00219	SW  	1996	11	1	AU960319         	1	19960219	G	6220	412010412101	BEARING         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR HEAD	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE PITCH LINK ELASTOMERIC BEARING FAILED AROUND  INNER RACE						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1996110100220	19961101	00220	SW  	1996	11	1	AU960320         	1	19960212	G	3210	4751211113	CROSS TUBE      	BELL        	FIXEDFLOATS 	BELL  	47    	47G3B2      	1181029	SW  										MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLOAT LANDING GEAR SYSTEM REAR CROSS TUBE CRACKED AROUND CIRCUMFERENCE IN AREA APPROXIMATELY 304.8MM (12IN) OUTBOA	RD FROM THE LH MOUNT - CRACK ORIGINATED AT PREVIOUSLY DRILLED HOLE					1	G	7	1 	3O				2H3     					 
1996110100221	19961101	00221	SO  	1996	11	1	AU960321         	2	19960312	G	8530	648029P015	PISTON          			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					R ENGINE CYLINDE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							465968			(AUS) NO5 CYLINDER PISTON SKIRT BROKEN - METAL CONTAMINATION OF OIL  SYSTEM						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996110100222	19961101	00222	EU  	1996	11	1	AU960322         	1	19960304	G	2510		SEAT BELT       			MRCHTI	S205  	S20520F     		EU  										FLIGHT COMPARTME	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELTS DO NOT COMPLY WITH AD/RES/29 AMDT 1 - AUTOMOTIVE  HARDWARE USED WITH NON MIL SPEC WEBBING - UNAPPROVED 	PART					1	L	7	1 	3O				A9EU    					 
1996110100223	19961101	00223	SW  	1996	11	1	AU960323         	1	19960320	G	2510		SEAT BELT       			BELL  	47    	47G3B       	1181026	SW  										FLIGHT COMPARTME	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELTS DO NOT COMPLY WITH NOTE 2 OF AD/RES/27 AMDT1 -  UNAPPROVED PART						1	G	7	1 	3O				2H3     					 
1996110100224	19961101	00224	EA  	1996	11	1	AU960324         	2	19960209	G	7240	PCE56614	CASE            	PWA         	PT6A34      	EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  					TURBINE ENGINE C	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1211 		PCE56614		PCE56614STB			(AUS) RH ENGINE GAS GENERATOR CASE CRACKED IN AREA AROUND THE UPPER  ENGINE LORD MOUNT BRACKET ATTACHMENT RUNNING ALONG 	THE INNER EDGEOF THE WELD BEAD - CRACK LENGTH 25.4MM (1IN)					1	L	7	2 	4T	4	T		A21SO   	E4EA				 
1996110100225	19961101	00225	SW  	1996	11	1	AU960325         	1	19960204	G	5720		PANEL           	GULSTM      	G73         	GULSTM	G73   	G73         	3951802	SW  	PWA   									CENTRE WING SYS	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					JZZ					(AUS) WING CENTRE SECTION TOP HAT SECTIONS FOUND IN ANNEALED (SOFT)  CONDITION FOLLOWING HEAT TREATMENT - SUSPECT HEAT T	REATMENTINCOMPLETE					1	H	7	2 	3R				A783    					 
1996110100226	19961101	00226	CE  	1996	11	1	AU960326         	1	19960312	G	5312		BULKHEAD        			CESSNA	182   	182Q        	2072732	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOOR POST BULKHEAD CRACKED IN BEND RELIEF NOTCHES ON LH  AND RH SIDES						1	H	7	1 	3O			NT	3A13    					 
1996111300011	19961113	00011	WP  	1996	11	13	AU960327         	2	19960311	G	7240	8697281	PLENUM          	GARRTT      	TPE3311151A 	MTSBSI	MU2   	MU2B30      	5780410	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					T ENG BURNER SEC	CRACKED         	W				K				NONE                    				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 					P90181		P90181			(AUS) RH ENGINE PLENUM CHAMBER CRACKED AROUND DRAIN FITTING TAKEOFF  FLANGE - CRACK LENGTH 50.8MM (2IN) - RH ENGINE BLEE	D AIR TUBECHAFED AND LEAKING - PERSONNEL/MAINTENANCE ERROR					1	H	7	2 	3T	4	T		A2PC    	E4WE				 
1996110100227	19961101	00227	CE  	1996	11	1	AU960328         	1	19960305	G	2121	15205100109	VALVE           		1520T100109 	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					AIR DISTRIBUTION	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					2788					(AUS) PRESSURISATION SYSTEM LH FLOW PACK LOW ON FLOW - RH FLOW PACK  SOLENOID STICKING CAUSING INTERMITTENT OPERATION - 	BLEED AIR DUCTFAIL LIGHT WIRE LOOSE					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996110100228	19961101	00228	SO  	1996	11	1	AU960329         	2	19960227	G	8550	402711	STUD            	CONT        	HOUSING     	CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520J    	17040	SO  					R ENGINE OIL SYS	SEPARATED       	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 			726  				510412			(AUS) LH ENGINE DRIVEN OIL PUMP HOUSING STUD SEPARATED CAUSING OIL LEAK- STUD IS NOT USED ON THIS INSTALLATION						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
1996110100229	19961101	00229	SO  	1996	11	1	AU960330         	1	19960201	G	2720	9621200	TORQUE TUBE     			PIPER 	PA34  	PA34220T    	7103420	SO  										RUDDER STRUCT SY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TORQUE TUBE ASSEMBLY FAILED - FOUND FOLLOWING VERY STRONG WIND GUSTS WITH NO GUST LOCKS FITTED - INSPECTION	 FOUND OLDCRACKS IN TORQUE TUBE SUSPECT CAUSED BY BENDING STRESSES IMPOSED BY POOR ALIGNMENT OF RUDDER HINGE LINE AND/OR	 WIND GUST DAMAGE				1	L	7	2 	3O				A7SO    					 
1996110100230	19961101	00230	EA  	1996	11	1	AU960331         	2	19960317	G	7322	MA3PA	CARBURETTOR     	FACET       	MA3PA       	CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENG FUEL CONTROL	CONTAMINATED    	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			AU	S 					DT0269		L2303015			(AUS) CARBURETTOR MIXTURE/CUTOFF VALVE CONTAMINATED BY TWO LUMPS OF  BROWN PARTICLES APPROXIMATELY 3MM (0.118IN) IN DIAM	ETER -INVESTIGATION FOUND CORROSION IN THE CARBURETTOR AND FUEL FILTER ASSEMBLIES AND THE PARTICLES INDICATE THAT THEY A	RE THE RESULT OFCORROSION OR WEAR				1	H	7	1 	3O	3	O		3A19    	E223				 
1996110100231	19961101	00231	NE  	1996	11	1	AU960332         	2	19960226	G	7320		PROBE           			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ENG,FUEL CONTROL	BLOCKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							687513			(AUS) NO1 ENGINE PT2 PROBE BLOCKED WITH INSECT REMAINS						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1996110100232	19961101	00232	EU  	1996	11	1	AU960333         	1	19960321	G	4900		PANEL           			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU CENTRAL FIRE BOX PANEL CRACKED IN THREE PLACES - FOUND DURING INSPECTION IAW AD/BAE146/53 AMDT1						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996110100233	19961101	00233	SW  	1996	11	1	AU960334         	1	19960313	G	3213	540004501	MLG             		540001503   	MOONEY	M20   	M20J        	5870219	SW  										MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					(AUS) MAIN LANDING GEAR LEG ASSEMBLY PNO 540004-501 CRACKED ADJACENT TO BOTTOM WELD ATTACHING LOWER PIVOT SUPPORT PLATE 	TO CROSS TUBE -TRUSS ASSEMBLY PNO 540001-503 DIAGONAL TUBES CRACKED ADJACENT TO WELDS					1	L	7	1 	3O				2A3     					 
1996110100234	19961101	00234	NM  	1996	11	1	AU960335         	1	19960223	G	2170	281135	CLAMP           	GARRTT      	SEPARATOR   	BOEING	737   	737377      		NM  										HUMIDITY CONTROL	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			67   		281135					(AUS) LH AIRCONDITIONING PACK WATER SEPARATOR CLAMP SEPARATED AND SEAL DISPLACED - INVESTIGATION FOUND CLAMP THREAD STRI	PPED					2	L	7	2 	4F			RT	A16WE   					 
1996110100235	19961101	00235	SO  	1996	11	1	AU960336         	2	19960313	G	8520	1265879C	CRANKCASE       	CONT        	IO520C      	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			544  		1265879C		126879C			(AUS) CRANKCASE CRACKED FROM NO6 CYLINDER TOP REAR STUD - FURTHER  INVESTIGATION FOUND CRANKCASE WAS CRACKED IN FOUR ARE	AS -CRACKING CAUSED BY THERMAL STRESS DUE TO POWER AND TEMPERATURE LOADS IMPOSED DURING FLIGHT TRAINING					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996110100236	19961101	00236	EU  	1996	11	1	AU960337         	1	19960218	G	2910	A71671683	PIPE            			FOKKER	F28   	F28MK4000   	4990810	EU  										MAIN HYD SYS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) NO2 HYDRAULIC SYSTEM PIPE TO HYDRAULIC ACCUMULATOR CRACKED AND LEAKING AT FLARE						2	L	7	2 	4F			RT	A20EU   					 
1996110100237	19961101	00237	EU  	1996	11	1	AU960338         	1	19960321	G	5720		BOLT            			BAC   	146   	146200A     	1500266	EU  										OUTER WING SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING REAR SPAR ROOT JOINT ATTACHMENT FITTING BOLT BROKEN AT  POSITION 'A' AS REFERRED TO IN BAE SB57-33 REV3 - FOU	ND DURING INSPECTION IAW AD/BAE146/016 AMDT3					2	H	7	4 	4F				A49EU   					 
1996110100238	19961101	00238	EU  	1996	11	1	AU960339         	1	19960219	G	2822	354301015	PUMP            			BNORM 	BN2   	BN2B20      	1520302	EU  										FUEL DISTRBUTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING TIP FUEL TRANSFER PUMP FAILED						1	H	7	2 	3O				A17EU   					 
1996110100239	19961101	00239	NE  	1996	11	1	AU960340         	2	19960316	G	7321		FCU             			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 										(AUS) NO4 ENGINE FUEL CONTROL UNIT SUSPECT FAULTY - TGT ROSE TO  APPROXIMATELY 700 DEGREES C - ENGINE DISPLAY PANEL SHOW	ED TGTREACHED 929 DEGREES C FOR 3 SECONDS					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996110100432	19961101	00432	SW  	1996	11	1	AU960341         	1	19960223	G	6310	476205321	BEARING         	BELL        	TRANSMISSION	BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435D1B   	41516	EA  					ENG/TRANS CPLNG	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			448  		32078018					(AUS) MAIN ROTOR TRANSMISSION PNO 47-620-600-27 MAIN DRIVE FLANGE SHEARBOLTS PNO 047-620-485-009 SHEARED - DAMAGE TO MAI	N ROTOR SWASHPLATE AND CONTROL RODS - TAIL ROTOR DRIVE SHAFT FAILED AT FORWARD HANGER BEARING - INSPECTION FOUND THAT TH	E ROLLER BEARINGS PNO 47-620-532-1 IN THE FREEWHEEL UNIT PNO 47-620-536-7 WERE UNDERSIZE WITH THE CLUTCH DRUM BEING BEIN	G UNEVENLY WORN ANDMATCHING WEAR ON THE BRAKE SHOES - SUSPECT FAILURE CAUSED BY SLIPPING OF THE FREEWHEEL UNIT DURING FL	IGHT CAUSING A RAPID `POWER ON/POWER OFF' CONDITION TO BE APPLIED TO THE MAIN ROTOR WHICH WOULD BE FELT BY THE FLANGE DR	IVE SHEAR BOLTS CAUSING EVENTUAL FAILURE - SEE MDR 96/0433 FOR SIMILAR OCCURRENCE	1	G	7	1 	3O	3	O		2H3     	1E13				 
1996110100433	19961101	00433	CE  	1996	11	1	AU960342         	1	19960228	G	5540	25330161	BALANCE WEIGHT  			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  					RUDDER STRUCT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER MASS BALANCE WEIGHT MISSING						1	L	7	2 	3O	3	O		A34CE   	E8CE				 
1996110100434	19961101	00434	EA  	1996	11	1	AU960343         	2	19960130	G	7414	S6LN1227	MAGNETO         	BENDIX      	S6LN1227    	BNORM 	BN2MK3	BN2AMK3     	1520203	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL				ENG IGNITION	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A110031					(AUS) MAGNETO CAPACITOR LEAKING - CONTACT GAP LESS THAN 0.304MM  (0.012IN)						1	H	7	3 	3O	3	O		A29EU   	E295				 
1996110100435	19961101	00435	SO  	1996	11	1	AU960344         	2	19960228	G	8530	SA643767P5	VALVE GUIDE     			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  					R ENGINE CYLINDE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			161  				246053			(AUS) NO2, NO4 AND NO6 CYLINDER EXHAUST VALVE GUIDES WORN BEYOND LIMITS						1	L	7	2 	3O	3	O		A34CE   	E8CE				 
1996110100436	19961101	00436	EA  	1996	11	1	AU960345         	2	19960130	G	7414	IO349371	COUPLING        	BENDIX      	S6LN1227    	BNORM 	BN2MK3	BN2AMK3     	1520203	EU  	LYC   	O540  	O540E4C5    	41532	EA  					ENG IGNITION	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A275228					(AUS) MAGNETO IMPULSE COUPLING WORN IN EXCESS OF 0.3556MM (0.014IN) -  INTERNAL TIMING GEAR OUT ONE TOOTH - FOUND DURING	 INSPECTION IAW AD/ELECT/27 AMDT6					1	H	7	3 	3O	3	O		A29EU   	E295				 
1996110100437	19961101	00437	EA  	1996	11	1	AU960346         	2	19960130	G	7414	S6LN1227	MAGNETO         	BENDIX      	S6LN1227    	BNORM 	BN2MK3	BN2AMK3     	1520203	EU  	LYC   	O540  	O540E4C5    	41532	EA  					ENG IGNITION	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A94453					(AUS) MAGNETO CONTACT GAP LESS THAN 0.3048MM (0.012IN) - INTERNAL  TIMING GEAR OUT BY ONE TOOTH						1	H	7	3 	3O	3	O		A29EU   	E295				 
1996110100438	19961101	00438	CE  	1996	11	1	AU960347         	1	19960318	G	7603	12504012	BRACKET         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					THROTTLE CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) THROTTLE CONTROL CABLE ATTACHMENT BRACKET BROKEN ALLOWING INNER  AND OUTER CABLES TO MOVE TOGETHER - BRACKET WAS M	ANUFACTURED FROM0.8128MM (0.032IN) ALCLAD					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996110100439	19961101	00439	CE  	1996	11	1	AU960348         	1	19960314	G	3411		LINE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					PITOT SYS	SEPARATED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) PITOT SYSTEM PRESSURE LINE SEPARATED FROM CONNECTION TO HOURMETER AIRSPEED SWITCH - SUSPECT LINE DISCONNECTED DURI	NG REFITMENT OF TACH INDICATOR DURING AD/INST/9 CALIBRATION CHECK WHICH WAS CARRIED OUT FOLLOWING PITOT/STATIC CALIBRATI	ON CHECK				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996110100440	19961101	00440	GL  	1996	11	1	AU960349         	1	19960318	G	3230		ACTUATOR        			AMTR  	LNCAIR	320LANCAIR  	056129G	GL  										LG EXT-RETRACT S	INCORRECT RIGGED	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR INCORRECTLY RIGGED - ACTUATOR RAM PUSHED MOUNTING PLATE IN THE NLG WHEEL TUNNEL THROUGH	 THEFIBREGLASS WALL					1	L	7	1 	3O			RT	EXPA1L71					 
1996110100441	19961101	00441	NE  	1996	11	1	AU960350         	2	19960314	G	7230		FAN BLADE       	RROYCE      	RB211524G   						RROYCE	RB211 	RB211524D419	54555	NE  					T ENG CMPRSR/FAN	INCORRECT FIT   	W				K				NONE                    				E	W		VIBRATION/BUFFET          	INADEQUATE Q C            		CL	CLIMB          	1			AU	S 										(AUS) NO4 ENGINE FAN BLADES (4OFF) FITTED TO INCORRECT POSITION CAUSING VIBRATIONS - PERSONNEL/MAINTENANCE ERROR											4	F			E12EU				 
1996110100442	19961101	00442	CE  	1996	11	1	AU960351         	1	19960317	G	2460	70HF10	DIODE           			BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  					DC POWER DISTRIB	FAILED          	W				K				NONE                    				O	H		OTHER                     	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			AU	S 										(AUS) NO2 ELECTRICAL BUS FEEDER DIODE 70HF10 FAILED						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1996110100443	19961101	00443	CE  	1996	11	1	AU960352         	1	19960318	G	2610		WIRE            		AMPLFIER    	BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  					FIRE DETECTION S	SHORTED         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ENGINE FIRE DETECTOR CONTROL AMPLIFIER SUSPECT FAULTY - FURTHER INVESTIGATION FOUND A SHORT CIRCUIT IN THE WIRE	 BETWEENTHE AMPLIFIER AND THE 'T' HANDLE					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
1996110100444	19961101	00444	WP  	1996	11	1	AU960353         	1	19960225	G	6220	5143711	HUB             	HILLER      	HEAD        	HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			189  		1959					(AUS) MAIN ROTOR HUB CRACKED - FOUND DURING INSPECTION IAW AD/HIL12/22A						1	G	7	1 	3O	3	O		4H11    	E304				 
1996111300015	19961113	00015	NE  	1996	11	13	AU960354         	2	19960306	G	7240	13146	LINER           	RROYCE      	RB211524G2  						RROYCE	RB211 	RB211524G19 		NE  					TURBINE ENGINE C	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					13146		13146			(AUS) ENGINE COMBUSTION LINER HEAD BREAKING UP IN AREA BETWEEN NO2 AND NO5 BLEED STRUTS - FOUND DURING BORESCOPE INSPECT	ION IAW AD/RB211/19 AMDT1 (ROLLS ROYCE SB RB211-72-B482)										4	F			E30NE				 
1996110100445	19961101	00445	NM  	1996	11	1	AU960355         	1	19960317	G	3510		OXYGEN BOTTLE   			BOEING	747   	747438      		NM  										CREW STA OXYGEN	EMPTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CREW OXYGEN BOTTLE EMPTY - 2ND OBSERVERS OXYGEN SELECTOR FOUND INEMERGENCY POSITION - SUSPECT SELECTOR LEFT IN EME	RGENCY POSITION FOLLOWING PRE-FLIGHT CHECK					2	L	7	4 	4F			RT	A20WE   					 
1996110100446	19961101	00446	NM  	1996	11	1	AU960356         	1	19960317	G	2435	300SGL127Q	GENERATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					STARTER-GEN	FAULTY          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			5    		1116XL					(AUS) ENGINE STARTER/GENERATOR FAULTY - INSPECTION FOUND EXTENSIVE INTERNAL ARCING AND HEAT DAMAGE						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996110100447	19961101	00447	NE  	1996	11	1	AU960357         	2	19960319	G	7320	3035381	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ENG,FUEL CONTROL	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 							120201			(AUS) NO2 ENGINE P3 SENSE LINE FROM COMPRESSOR TO HMU FRACTURED AT HMU 'T' FITTING - VIBRATION FROM FAILED RH STARTER/GE	NERATOR MAY HAVECONTRIBUTED TO FAILURE (MDR 96/0356)					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996110100448	19961101	00448		1996	11	1	AU960358         	1	19960308	G	7720	6131508523	HARNESS         		733M71      						CFMINT	CFM56 	CFM563C1    	13802	EU  					ENG TEMP IND SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							85635			(AUS) NO1 ENGINE CORE HARNESS FAULTY											4	F			E21EU				 
1996110100449	19961101	00449	CE  	1996	11	1	AU960359         	1	19960313	G	7602	S17771	CABLE           			CESSNA	172   	172I        	2072426	CE  	LYC   	O320  	O320E2D     	41508	EA  					POWER CONTROL SY	FAILED          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							L2185827A	E9671		(AUS) ENGINE MIXTURE CONTROL CABLE FAILED AT WORN SECTION OF EXPOSED CABLE						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996110100450	19961101	00450	EA  	1996	11	1	AU960360         	2	19960318	G	7414	10382681	CAPACITOR       	BENDIX      	MAGNETO     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENG IGNITION	FAILED          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) LH MAGNETO CAPACITOR FAILED						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996110100451	19961101	00451	SO  	1996	11	1	AU960363         	1	19960325	G	6120	B24914S	ROD             			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY S	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								CH2018		(AUS) PROPELLER PITCH CHANGE ROD SUSPECT FAULTY - DIMENSION FROM REAR  PISTON SHOULDER TO FRONT RETAINER GROOVE AS ADVIS	ED BY HARTZELLPROPELLERS IS 10.960INCHES (278.384MM) - MEASUREMENTS ON AFFECTED ROD WAS 10.85INCHES (275.59MM) RESULTING	 IN OVER COMPRESSION OF FEATHER SPRINGS CAUSING SLOW UNFEATHERING OPERATION				1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
1996110100452	19961101	00452	CE  	1996	11	1	AU960365         	1	19960306	G	3245		TUBE            	GOODYEAR    	FLIGHTCUSTOM	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					LT MLG	DEFLATED        	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR TYRE DEFLATED DURING LANDING ROLL - INVESTIGATION COULD FIND NO FAULT WITH THE TYRE BUT THE T	UBE CONTAINED A SMALL TEAR SUSPECT CAUSED FOLLOWING DEFLATION AS TYREWAS BADLY DAMAGED DURING LANDING ROLL WHILE FLAT					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996110100453	19961101	00453	CE  	1996	11	1	AU960366         	1	19960308	G	2710	500000896	CONTROL CABLE   			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					AILERON CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH FORWARD AILERON CONTROL CABLE CONTAINED NUMEROUS BROKEN WIRES OVER A 100MM (4IN) LENGTH AT THE PULLEY LOCATED A	T THE FIREWALLAREA AT FS 100.00					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
1996110100454	19961101	00454	CE  	1996	11	1	AU960367         	1	19960229	G	5347	50150191	CHANNEL         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					SEAT SUPPORT	DESTROYED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ITEM22					(AUS) PILOT SEAT SUPPORT STRUCTURE CHANNEL DESTROYED DUE TO PROLONGED  MOVEMENT WITH THE MOUNTING SCREWS UNDONE - LOOSE 	MOUNTING SCREWS ALSO FOUND ON SIMILAR AIRCRAFT - SUSPECT DUE TO PILOTS EXCERTING PRESSURE AGAINST SEATS DURING ENTRY/EXI	T OF AIRCRAFT				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996110100455	19961101	00455	EA  	1996	11	1	AU960368         	2	19960130	G	8530	L71455	CYLINDER        	LYC         	O320B1A     	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					RT ENGI CYL SEC	OVER TEMP       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1027 		L71455		STBDL7145			(AUS) RH ENGINE INTERNAL COMPONENTS EXHIBITED SIGNS OF OVERHEATING - STEEL ITEMS BLUED AND CYLINDER BORES GLAZED - SUSPE	CT ENGINE OVERHEATED DURING EXTENSIVE GROUND RUNNING AT HIGH POWER DURING  FAULT FINDING OF THE ELECTICAL POWER SUPPLY S	YSTEM - SEE MDR 96/0369 FOR SIMILAR DEFECTS ON LH ENGINE				1	L	7	2 	3O	3	O		A1EA    	1E12				 
1996110100456	19961101	00456	EA  	1996	11	1	AU960369         	2	19960130	G	8530	L70155	CYLINDER        	LYC         	IO320B1A    	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					LT ENG CYL SEC	OVER TEMP       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1365 		L70155		L70155			(AUS) LH ENGINE INTERNAL COMPONENTS EXHIBITED SIGNS OF OVERHEATING - STEEL ITEMS BLUED - ENGINE CYLINDER BORES GLAZED - 	SUSPECT CAUSEDBY GROUND RUNNING AT HIGH POWER SETTINGS DURING FAULT FINDING OF THE ELECTRICAL POWER SUPPLY SYSTEM - SEE 	MDR 96/0368 FOR SIMILAR DEFECT ON RH ENGINE				1	L	7	2 	3O	3	O		A1EA    	1E12				 
1996110100457	19961101	00457	NM  	1996	11	1	AU960370         	1	19960301	G	6310	A1882	CLUTCH          	ROBSIN      	FREEWHEEL   	ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					ENG/TRANS CPLNG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0274					(AUS) ENGINE TO TRANSMISSION SPRAG CLUTCH ASSEMBLY DAMAGED - WEAR  EVIDENT ON CLUTCH SHAFT, CLUTCH HOUSING AND SPRAG ROL	LERS -SUSPECT CLUTCH SLIPPAGE CONTRIBUTED TO THE FAILURE OF THE FORWARDFLEX PLATE					1	G	7	1 	3O	3	O		H10WE   	E274				 
1996110100458	19961101	00458	NM  	1996	11	1	AU960371         	1	19960228	G	6310	A9471	FLEX PLATE      	ROBSIN      	A9471       	ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					ENG/TRANS CPLNG	FAILED          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			1946 							(AUS) CLUTCH TO TRANSMISSION FLEX PLATE FAILED AT ALL FOUR ATTACHMENT  POINTS - TWO LOOSE BOLTS WERE FOUND ON THE FORWAR	D YOKE ON THE TRANSMISSION - FLEX PLATE WAS A PRE 'F' MODEL					1	G	7	1 	3O	3	O		H10WE   	E274				 
1996110100459	19961101	00459	SW  	1996	11	1	AU960372         	1	19960326	G	3213	54530011	HOUSING         	OZONE       	RHMLG       	SWRNGN	SA226 	SA226TC     	8780404	SW  	ARSRCH									MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					159					(AUS) RH MAIN LANDING GEAR STRUT HOUSING CRACKED AT AFT END OF RH AND  LH SIDE DRAG BRACES						2	L	7	2 	4T			RT	A8SW    					 
1996110100460	19961101	00460	SW  	1996	11	1	AU960373         	1	19960312	G	5341	201751	ANGLE           			AIRTRC	AT400 	AT401       	0390204	SW  										ATTACH FITTING S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING ATTACHMENT ANGLES (2OFF) CRACKED ON INSIDE FACE AND CORRODED AROUND MOUNT HOLES AND LOWER HOLES						1	L	7	1 	3R				A17SW   					 
1996110100461	19961101	00461	GL  	1996	11	1	AU960375         	1	19960306	G	3213	GM1	MLG             			AMTR  	LANCAR	LANCAIR     	05616TS	GL  										MAIN GEAR SYS	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR LEG BENT IN AREA ABOVE OVERCENTRE LINK						1	L	7	1 	3O			RT	EXPA1L71					 
1996110100462	19961101	00462	WP  	1996	11	1	AU960376         	2	19960326	G	7310	15740021	HEATER          			MTSBSI	MU2   	MU2B30      	5780410	SW  	GARRTT	TPE331	TPE3311151A 	01514	WP  					ENG,FUEL DIST SY	STRIPPED        	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		TX	TAXI/GRND HDL  	1			AU	S 			1010 		301118		PQ0181C			(AUS) RH ENGINE OIL/FUEL HEATER OIL OUTLET FITTING PNO AN815-8J LOOSE  AND LEAKING DUE TO STRIPPED THREADS IN THE HEATER	 HOUSING -PERSONNEL/MAINTENANCE ERROR					1	H	7	2 	3T	4	T		A2PC    	E3WE				 
1996110100463	19961101	00463	EU  	1996	11	1	AU960377         	1	19960123	G	2610	M390166109M	RELAY           		73040102    	AIRBUS	320   	A320211     	3930320	EU  										FIRE DETECTION S	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 			19775		227					(AUS) NO1 ENGINE FIRE WARNING SYSTEM FAULTY OPERATION - CAUSED BY FIRE DETECTION UNIT RELAY K1 CONTACTS BEING CLOSED						2	L	7	2 	4F			RT	A28NM   					 
1996110100464	19961101	00464	SO  	1996	11	1	AU960378         	2	19960324	G	7314		PUMP            			CESSNA	206   	P206C       	2073312	CE  	CONT  	O520  	IO520A      	17032	SO  					ENG,FUEL DIST SY	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 										(AUS) ENGINE LOST POWER - FOLLOWING FITMENT OF A NEW FUEL PUMP THE LOW POWER WAS STILL EVIDENT - ANOTHER FUEL PUMP WAS F	ITTED AND THE POWER LOSS RETURNED AFTER A SHORT PERIOD OF OPERATION - A THIRD  FUEL PUMP RECTIFIED THE POWER LOSS - INVE	STIGATION OF THE FIRST REPLACEMENT PUMP WHICH WAS A NIL TSO ITEM WHICH HAD BEEN ON THE  SHELF FOR APPROXIMATELY THREE YE	ARS REVEALED EVIDENCE OF INTERNAL CORROSION ON THE WORKING SURFACES - INVESTIGATION OF THE OTHER PUMP REVEALED DEBRIS IN	 THE VAPOUR RETURN		1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996110100465	19961101	00465	NM  	1996	11	1	AU960379         	1	19960222	G	5720	5711098007	PANEL           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					CENTRE WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE WING INNER ACCESS PANEL EXCESSIVELY CORRODED ON THE INNER BONDED EDGE DOUBLER						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996111300016	19961113	00016	SO  	1996	11	13	AU960380         	1	19960319	G	5540		FITTING         			AYRES 	S2    	S2RG10      		SO  										ATTACH FITTING S	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) TAILPLANE LH FORWARD ATTACHMENT FITTING CRACKED - ATTACHMENT BOLT LOOSE AND THIN WASHER BETWEEN TAILPLANE AND FITT	ING WORN - PERSONNEL/MAINTENANCE ERROR					1	L	7	1 	3T			NC	A4SW    					 
1996110100466	19961101	00466	SO  	1996	11	1	AU960381         	1	19960327	G	3211	2251200	STUD            			PIPER 	PA30  	PA30        	7103002	SO  										MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR SIDE BRACE STUDS CRACKED IN RADIUS - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA30/34						1	L	7	2 	3O				A1EA    					 
1996110100467	19961101	00467	CE  	1996	11	1	AU960382         	1	19960227	G	5312	121341244	BULKHEAD        	CESSNA      	U206G       	CESSNA	206   	U206G       	2073356	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U20605004					(AUS) RH FORWARD DOOR POST BULKHEAD CRACKED IN AREA OF BEND RELIEF NOTCH - AD/CESSNA206/48 AMDT1 CARRIED OUT APPROXIMATE	LY 200 HOURSPREVIOUS					1	H	7	1 	3O				A4CE    					 
1996111300017	19961113	00017	NM  	1996	11	13	AU960383         	1	19960308	G	7120	65B903633	MOUNT           		65B903632   	BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					ENGINE MOUNTING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					65B903632		P715159			(AUS) NO4 ENGINE FORWARD ENGINE MOUNT ASSEMBLY PNO 65B90363-3 AND AFT  ENGINE MOUNT ASSEMBLY PNO 65B90363-2 ATTACHMENT L	UG BUSHES WORN -WEAR ALSO TO AFT MOUNT ATTACHMENT BOLTS					2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1996110100468	19961101	00468	SW  	1996	11	1	AU960384         	1	19960321	G	3211	S2735011055M	SUPPORT         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR OUTBOARD UPPER DRAG BRACE SUPPORT STRUCTURE CRACKED - PART NUMBERS OF CRACKED COMPONENTS:- 1.	 HAT SECTION PNO S27-35011-055M - CRACKED  2. T DOUBLER PNO S27-35011-23M  - CRACKED3. DOUBLER PNO S27-35011-017M - CRAC	KED  4. DOUBLER PNO S27-35011-074M - WORN DRAG BRACE BUSHING ATTACHMENT HOLES				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1996110100469	19961101	00469	SO  	1996	11	1	AU960385         	1	19960325	G	5751	37210	BRACKET         			PIPER 	PA34  	PA34200T    	7103406	SO  										WING AIL/ELV SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AILERON CENTRE AND INBOARD HINGE BRACKETS CORRODED - RH AILERON CENTRE HINGE BRACKET CORRODED						1	L	7	2 	3O				A7SO    					 
1996110100470	19961101	00470	CE  	1996	11	1	AU960386         	1	19960326	G	5320	081308929	DOUBLER         	CESSNA      	310R        	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1310					(AUS) NOSE WHEEL WELL LH AND RH DOUBLERS CRACKED FORE AND AFT ALONG  RIVET LINE IN AREA OF STEERING BRACKET ATTACHMENT (	STEERINGBRACKET PNO 5013040-41)					1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996110100471	19961101	00471		1996	11	1	AU960387         	4	19960130	G	3431	4366941	SELECTOR SWITCH 	BOEING      	ILSCONTROL  	BOEING	767   	767277      		NM  										LANDING DATA SYS	FAILED          	W				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			AU	S 			31660		151ANSETTS					(AUS) ILS CONTROL PANEL 36 POSITION ROTARY COURSE SELECTOR SWITCH (S2) FAILED MIDWAY BETWEEN TWO POSITIONS						2	L	7	2 	4F			RT	A1NM    					 
1996110100472	19961101	00472		1996	11	1	AU960388         	4	19960229	G	2312		TRANSCEIVER     			BEECH 	200   	200BEECH    	1152920	CE  										VHF COMMUNICATIO	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) INTERMITTENT HASH ON VHF - VHF TRANSCEIVER REPLACED - GROUND TESTOF REPLACED ITEM COULD NOT DUPLICATE PROBLEM - AV	IONICS CIRCUITBREAKER TRIPPED - INVESTIGATION FOUND THAT REPEATED STORING AND  REMOVAL ACTIONS OF HEADSET MECHANICALLY C	AUGHT AND TRIPPED CIRCUIT BREAKER ON REMOVAL - HEADSET STORAGE 'HANGER' ADJUSTED TOELIMINATE PROBLEM				1	L	7	2 	4T				A24CE   					 
1996110100473	19961101	00473	CE  	1996	11	1	AU960389         	1	19960115	G	5320	05121871	DOOR POST       		05121872    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH DOOR POST CRACKED FROM RELIEF RADIUS AT FLOOR LEVEL TO HIGH SHEAR FASTENER HOLE ON LH POST AND EXTENDING	 APPROXIMATELY7.937MM (0.3125IN) PAST HIGH SHEAR FASTENER HOLE ON RH POST -  MAXIMUM CRACK LENGTH OF 31.75MM (1.25IN) EX	TENDING OUTBOARD FROM RELIEF RADIUS				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996110100474	19961101	00474	EA  	1996	11	1	AU960390         	2	19960315	G	8520	AS16508	CAMSHAFT        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					R ENGINE POWER S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L31377		L31377			(AUS) ENGINE CAMSHAFT LOBES WORN - FOUND DURING PERIODIC INSPECTION						1	L	7	2 	3O	3	O		A19S0   	E286				 
1996110100475	19961101	00475	EA  	1996	11	1	AU960391         	2	19960315	G	8520	LW15014	CAM FOLLOWER    			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					R ENGINE POWER S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L31377		L31377L2			(AUS) LH AND RH ENGINE CAM FOLLOWERS WORN BEYOND LIMITS - LH ENGINE  CAMSHAFT REQUIRES REPLACEMENT - BOTH ENGINES HAVE H	AD LW16702ADDITIVE IAW SB 446B AND OIL CHANGE EACH 50 HOURS SINCE OVERHAUL					1	L	7	2 	3O	3	O		A19S0   	E286				 
1996110100476	19961101	00476	WP  	1996	11	1	AU960392         	1	19960313	G	5520		HINGE           			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   									ELEVATOR STRUCT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ELEVATOR MID AND OUTBOARD HINGES EXCESSIVELY WORN - APPROXIMATELY 25.4MM (1IN) MOVEMENT FORWARD AND AFT - INBOA	RDELEVATOR ATTACHMENT BRACKET PNO 1115188 WAS FOUND WITH HEAVY EXFOLIATION CORROSION - BEARING WAS ALSO UNSERVICEABLE					2	L	7	2 	4R				A669    					 
1996110100477	19961101	00477	CE  	1996	11	1	AU960393         	1	19960311	G	2731		TRIM TAB        			CESSNA	206   	U206G       	2073356	CE  										ELEVATOR CONTROL	INCORRECT RIGGED	W				K				NONE                    				F	W		FLT CONT AFFECTED         	INADEQUATE Q C            		DE	DESCENT        	1			AU	S 										(AUS) ELEVATOR TRIM TAB INCORRECTLY RIGGED - DURING INVESTIGATION IT WAS FOUND THAT THE ELEVATOR TRIM TAB WAS SET AT 5 D	EGREES 'UP' AND 25 DEGREES 'DOWN' - THE CORRECT TRAVEL SHOULD HAVE BEEN 25 DEGREES 'UP' AND 5 DEGREES 'DOWN' - AIRCRAFT 	HAS DONEAPPROXIMATELY 10 HRS SINCE LAST INSPECTION - PERSONNEL/MAINTENANCE ERROR				1	H	7	1 	3O				A4CE    					 
1996110100478	19961101	00478	WP  	1996	11	1	AU960394         	1	19960313	G	5520		BRACKET         			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   									ELEVATOR STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR STOP BRACKET AND INBOARD ELEVATOR ATTACHMENT BRACKET  RIBS CORRODED						2	L	7	2 	4R				A669    					 
1996110100972	19961101	00972	WP  	1996	11	1	AU960395         	1	19960313	G	5520		ELEVATOR        			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										ELEVATOR STRUCT	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ELEVATOR UNSERVICEABLE DUE TO POOR CONDITION AND FABRIC DETERIORATION - DRAIN HOLES WERE BLOCKED AND WATER WAS 	TRAPPED INSIDE					2	L	7	2 	4R				A669    					 
1996110100973	19961101	00973	WP  	1996	11	1	AU960396         	1	19960313	G	5530		VERTICAL FIN    			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										VERT STAB STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL FIN AND LH AND RH STRINGERS CONTAINED EXFOLIATION CORROSION						2	L	7	2 	4R				A669    					 
1996110100974	19961101	00974	WP  	1996	11	1	AU960397         	1	19960313	G	5540	31151251	BRACKET         			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										RUDDER STRUCT SY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER BRACKETS PNO 3115125-1 CONTAINED SEVERE EXFOLIATION CORROSION - IN THE AREA WHERE THE TOP BRACKET HAD CORRO	DED THROUGH THE BEARING DROPPED ONTO THE LOWER BRACKET WHICH ALSO  CONTAINED SEVERE EXFOLIATION CORROSION WHICH HAD REDU	CED THE THICKNESS TO 1.587MM (0.0625IN) - THE TOP BEARING HAD FAILED AND THE BALLS HAD FALLEN OUT ALLOWING FOWARD AND AF	T MOVEMENT OF THE RUDDER CAUSING THE MID AND LOWER BEARINGS TO ALSO FAIL			2	L	7	2 	4R				A669    					 
1996110100975	19961101	00975	CE  	1996	11	1	AU960398         	1	19960301	G	2510	5000B2500950	BUCKLE          			CESSNA	182   	182H        	2072718	CE  										FLIGHT COMPARTME	UNSAFE          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FRONT SEATS BELT BUCKLES FAULTY - BUCKLES UNDO AT THE SLIGHTEST  TOUCH WITHOUT ANY SIGNIFICANT LIFTING OF LEVER - 	THE SEAT BELTS HAVE COME UNDONE DESPITE PROPER TENSION ADJUSTMENT OF BELTS -  BUCKLES ARE MANUFACTURED BY `AMSAFE' AND W	ERE FITTED FOLLOWING CARRYING OUT OF AD/RES/29				1	H	7	1 	3O			NT	3A13    					 
1996110100976	19961101	00976	WP  	1996	11	1	AU960399         	1	19960313	G	5540	31151251	HINGE           			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										VERT STAB STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ONE REMOVAL OF THE RUDDER, SEVERE EXFOLIATE CORROSION WAS FOUND  ON THE FORWARD END OF THE TOP RUDDER HINGE ARM PN	O 3115125-1 THE FOLLOWING DEFECTS WERE ALSO FOUND: 1. FIN TOP WAS REMOVED AND FOUND TO HAVE SEVERE CORROSION ON THE  STR	UCTURE 2. REAR RIB REQUIRED REPLACEMENT 3. VERTICAL RIB REQUIRED EXTENSIVE REPAIR AND ALL OTHER AREAS REQUIRED CORROSION	 REMOVAL AND REPROTECTION 4. BOTH LH AND RH SKINS REQUIRED REPAIR AND REPROTECTION			2	L	7	2 	4R				A669    					 
1996110100977	19961101	00977	WP  	1996	11	1	AU960400         	1	19960313	G	5713		STRINGER        			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING CONTAINED EXFOLIATION CORROSION IN THE FOLLOWING AREAS BETWEEN STN 53 AND STN 107 (LH LANDING LIGHT CUT OU	T)1. STRINGERS NO3, NO4 AND NO5 IN UPPER SECTION OF THE OUTER WING 2. STRINGERS NO53, NO54 AND NO55 IN LOWER SECTION OF 	THE OUTER  WING				2	L	7	2 	4R				A669    					 
1996110100978	19961101	00978	WP  	1996	11	1	AU960401         	1	19960313	G	5330		SKIN            			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										EXT PLATES/SKIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEVERE EXFOLIATION CORROSION IN BOTH THE FRONT AND REAR SKINS, ATTACHMENT ANGLES AND DOUBLERS LOCATED IN TAIL WHEE	L BAY					2	L	7	2 	4R				A669    					 
1996111300018	19961113	00018	EU  	1996	11	13	AU960402         	1	19960321	G	2510	94231	SEAT BELT       			SAAB  	SF340 	340B        	7860101	EU  										FLIGHT COMPARTME	INCORRECT REPAIR	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELTS REWEBBED USING AUTOMOTIVE WEBBING - UNAPPROVED REPAIR - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						2	L	7	2 	4T			RT	A52EU   					 
1996110100979	19961101	00979	GL  	1996	11	1	AU960403         	3	19960307	G	6111	C4451	FERRULE         	MCAULY      	BLADE       											MCAULY	3A32C	D3A32C90    	GL  	PROPELLER ASSY S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								890699		(AUS) PROPELLER BLADE FERRULES LOCATED IN HUB BLADE SOCKETS CRACKED  THROUGH OLD DISUSED ACTUATING PIN HOLES																5	C	P21EA	 
1996110100980	19961101	00980	GL  	1996	11	1	AU960404         	3	19960307	G	6114	D5904	PROPELLER HUB   	MCAULY      	D3A32C90R   											MCAULY	3A32C	D3A32C90    	GL  	PROPELLER ASSY S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					890699			890699		(AUS) PROPELLER HUB CRACKED IN THREADED AREAS IN ALL BLADE SOCKETS - FURTHER INVESTIGATION FOUND THAT IT MAY NOT BE CRAC	KING BUTDAMAGE - MEF INVESTIGATION PENDING															5	C	P21EA	 
1996110100981	19961101	00981	GL  	1996	11	1	AU960405         	2	19960327	G	7320		CONNECTOR       		206062721103	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENG,FUEL CONTROL	HIGH RESISTANCE 	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) GOVERNOR LINEAR ACTUATOR (PNO 206062721103) EARTH TERMINAL CRIMP HAD HIGH RESISTANCE PREVENTING ACTUATOR FROM WORK	ING DURINGLANDING					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1996110100982	19961101	00982	EU  	1996	11	1	AU960406         	1	19960401	G	5341	TB2011001006	FITTING         		TB2011001007	SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										ATTACH FITTING S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING REAR ATTACHMENT FITTINGS PNO TB2011001006 AND PNO TB2011001007 HAD LOOSE BUSHINGS AND WORN HOLES						1	L	7	1 	30			NT	A51EU   					 
1996110100983	19961101	00983	SW  	1996	11	1	AU960407         	1	19960319	G	3230	ED12402	BODY            		4001391BR   	GULSTM	690TP 	690A        	0141722	SW  										MAIN GEAR SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					GA33					(AUS) MAIN LANDING GEAR INNER DRAG BRACE ATTACHMENT FLANGE BROKEN OFF  MLG BODY - VICE JAW MARKS FOUND ON OUTER SURFACE						1	H	7	2 	3T				2A4     					 
1996110100984	19961101	00984	SO  	1996	11	1	AU960408         	1	19960330	G	2750	D15224	MOTOR           			EMB   	110   	EMB110P1    	3260122	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	FLAP SYS	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP MOTOR ASSYMETRY WIRING BROKEN						1	L	7	2 	4T				A21SO   		6	C	P15EA	 
1996110100985	19961101	00985	SO  	1996	11	1	AU960409         	1	19960401	G	3230	14805A	CYLINDER        			EMB   	110   	EMB110P1    	3260122	SO  	PWA   									LG EXT RETRACT S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					110253					(AUS) NOSE LANDING GEAR ROTATING CYLINDER CRACKED ON RH SIDE UPPER WELDED AREA - CRACK LENGTH 15MM (0.59IN) - TWO SMALLE	R CRACKS WERE ALSO FOUND IN THE SAME AREA - FOUND DURING INSPECTION IAW SB110-032-0053 REV 7 PT 2 PARA 2.2.6.					1	L	7	2 	4T				A21SO   					 
1996110100986	19961101	00986	SO  	1996	11	1	AU960410         	2	19960322	G	8530	646680	CYLINDER        	CONT        	O470U       	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					R ENGINE CYL SEC	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			230  		466437					(AUS) CYLINDER AND PISTON FITTED TO NO3 POSITION WERE INCORRECT PARTS -INCORRECT CYLINDER PNO 646680 HAD A SHORT REACH S	PARK PLUG - CORRECT PNO 653444 CYLINDER HAS A LONG REACH SPARK PLUG AND  PISTON PNO 648029 WITH STEEL INSERT - DIFFERENC	E IN PISTON WEIGHTS WAS 315 GRAMS - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996110100987	19961101	00987	CE  	1996	11	1	AU960411         	1	19960315	G	3230	50410051	SPRING          	CESSNA      	LHMLGSTRUT  	CESSNA	310   	310R        	2074245	CE  										LG EXT-RETRACT S	BROKEN          	W				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK SPRING BROKEN						1	L	7	2 	3O				3A10    					 
1996110100988	19961101	00988		1996	11	1	AU960412         	4	19960322	G	3410		PIPE            			CESSNA	182   	182Q        	2072732	CE  										ENVIRONMENT DATA	DISTORTED       	W				K				NONE                    				O	I	W	OTHER                     	FLT. ATTITUDE INST.       	INADEQUATE Q C            	IN	INSP/MAINT     	1			AU	S 										(AUS) INSTRUMENT STATIC SYSTEM PIPE BETWEEN ALTIMETER AND VSI KINKED INTHREE PLACES - PERSONNEL/MAINTENANCE ERROR						1	H	7	1 	3O			NT	3A13    					 
1996110100989	19961101	00989	EA  	1996	11	1	AU960413         	2	19960226	G	7314	RA8987	GASKET          	ROMEC       	FUELPUMP    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENG,FUEL DIST SY	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 			209  		D2499		L108268A			(AUS) RH ENGINE DRIVEN FUEL PUMP GASKET RUPTURED AND LEAKING FUEL -  AD/FSM/25 HAD BEEN CARRIED OUT 25.2 HOURS PREVIOUSL	Y					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996110100990	19961101	00990	SO  	1996	11	1	AU960414         	1	19960221	G	3230	4194902	ROD             			PIPER 	PA31  	PA31350     	7103110	SO  										LG EXT-RETRACT S	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR TELESCOPIC DOWNLOCK ROD SEIZED IN THE EXTENDED POSITION - THIS AREA OF THE ROD IS COVERED BY 	A RUBBERBOOT AND WAS FOUND TO BE CORRODED AND THE BOOT CONTAINED A QUANTITY OF RED DUST - FURTHER INVESTIGATION FOUND TH	AT THE NLGDOWNLOCK ROD WAS LACKING IN LUBRICATION AND BINDING BUT WAS NOT  SEIZED				1	L	7	2 	3O				A20SO   					 
1996110100991	19961101	00991	CE  	1996	11	1	AU960415         	1	19960320	G	2742	99140563	ACTUATOR        			CESSNA	650   	650         	2076802	CE  										HORIZ STAB SYS	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			2522 							(AUS) HORIZONTAL STABILISER PRIMARY TRIM ACTUATOR FAILED INTERNALLY						2	L	7	2 	4F				A9NM    					 
1996110100992	19961101	00992	NM  	1996	11	1	AU960416         	1	19960202	G	2460	BACC18AE35	CIRCUIT BREAKER 			BOEING	737   	737377      		NM  										DC POWER DISTRIB	TRIPPED         	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) NO1 NORMAL TRANSFER CIRCUIT BREAKER C819 FAULTY - CIRCUIT BREAKER FAILED WORKSHOP CALIBRATION TESTS FOLLOWING REMO	VAL					2	L	7	2 	4F			RT	A16WE   					 
1996111300019	19961113	00019	NM  	1996	11	13	AU960417         	1	19960323	G	2920	6510	SWITCH          			BOEING	767   	76733A      		NM  	PWA   	4056  	PW4056      		NE  					AUX HYD SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					6510					(AUS) RAM AIR TURBINE (RAT) AIRSPEED SWITCH FAULTY - SUSPECT FAULTY  DIODE - RAT FAILED TO AUTODEPLOY						2	L	7	2 	RT	4	F	RT	A1NM    	E24NE				 
1996110100993	19961101	00993	EU  	1996	11	1	AU960418         	1	19960401	G	7714	408106008	GEAR            	LYC         	LTS101750B1 	BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENG PWR IND SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					LE45818E		LE45818E			(AUS) ENGINE NG SPEED PICKUP GEAR PLATE RIVETS LOOSE						1	G	7	2 	3U	3	U		H13EU   	E5NE10				 
1996110100994	19961101	00994	SW  	1996	11	1	AU960419         	1	19960215	G	5210	2724152051	BELLCRANK       			FRCHLD	SA227 	SA227DC     	3377521	SW  										CREW-PASS DOOR S	BROKEN          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) CABIN ENTRY DOOR SEAL VALVE ACTUATING TAB BROKEN FROM BELLCRANK  ASSEMBLY - DOOR SEAL WOULD NOT INFLATE - SUSPECT 	INCORRECT RIGGING AT MANUFACTURE					2	L	7	2 	4T			RT	A18SW   					 
1996110100995	19961101	00995	GL  	1996	11	1	AU960420         	3	19960329	G	6114	C98	HUB             	MCAULY      	D2A34C980   	CESSNA	188   	A188A       	2073008	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					711953			711953		(AUS) PROPELLER HUB CRACKED IN THREADED AREA OF NO2 BLADE SOCKET						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1996110100996	19961101	00996	GL  	1996	11	1	AU960421         	3	19960329	G	6111	90AT	BLADE           	MCAULY      	D2A34C98    	CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					711953			711953		(AUS) PROPELLER BLADES (2OFF) CORRODED IN AREA OF BLADE BUTT OUTER FOUR THREADS						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1996110100997	19961101	00997	CE  	1996	11	1	AU960422         	1	19960329	G	2510		SEAT BELT       			CESSNA	150   	150         	2071802	CE  										FLIGHT COMPARTME	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELTS WERE CONSTRUCTED FROM AUTOMOTIVE HARDWARE USED WITH NON MIL-SPEC WEBBING AND HAVE NO FORM OF IDENTIFICA	TION - FOUNDDURING INSPECTION IAW WITH AD/RES/29 AMDT 1 - UNAPPROVED PART -  PERSONNEL/MAINTENANCE ERROR					1	H	7	1 	3O			NT	3A19    					 
1996110100998	19961101	00998	SO  	1996	11	1	AU960423         	1	19960311	G	7922		CIRCLIP         	LYC         	VERNATHERM  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					AC,ENG OIL DIST	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					0		L761861A			(AUS) LH ENGINE OIL COOLER BYPASS VALVE (VERNATHERM) BODY CIRCLIP  BROKEN - ONE PIECE OF BROKEN CIRCLIP LODGED IN OIL PR	ESSURE RELIEF VALVE - SUSPECT CIRCLIP INCORRECTLY HEAT TREATED - RH ENGINE VERNATHERM SIMILARLY AFFECTED					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998043001174	19980430	01174	SW  	1998	4	30	AU960424         	1	19960311	G	3250	2782792001	STEERING SYSTEM 	SWRNGN      	2782792001  	FRCHLD	SA227 	SA227DC     	3377521	SW  										ACFT STEERING SY	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 					191					(AUS) NOSE WHEEL STEERING FAILED TO RESPOND TO PILOTS INPUT WHEN SPEED LEVERS SET TO HIGH AND STEERING PARK BUTTON DEPRE	SSED - GREEN NWSANNUNCIATOR LIGHT STAYED ILLUMINATED AND NO INDICATION OF AMBER  NWS FAIL LIGHT					2	L	7	2 	4T			RT	A18SW   					 
1998043001175	19980430	01175	SW  	1998	4	30	AU960425         	1	19960318	G	2844	27191523	TRANSDUCER      	EDCLIFF     	4901        	FRCHLD	SA227 	SA227DC     	3377521	SW  										FUEL INDICATION	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					36385					(AUS) FUEL PRESSURE TRANSDUCER FAULTY - RH BOOST PUMPS INDICATED LOW FUEL PRESSURE						2	L	7	2 	4T			RT	A18SW   					 
1998043001176	19980430	01176	CE  	1998	4	30	AU960426         	1	19960322	G	2110	1138000	COMPRESSOR      		1138000     	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					CABIN AIR COND	FAILED          	W				K				NONE                    				E	B	A	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                	CR	CRUISE         	1			AU	S 					07055A					(AUS) RH ENGINE DRIVEN AIRCONDITIONING COMPRESSOR FAILED DUE TO SEVERE OVERHEATING - COMPRESSOR PULLEY BEARING COLLAPSED	 - COMPRESSOR CLUTCH SECTION SEPARATED FROM THE PULLEY ASSEMBLY BUT WAS STILL  CONNECTED TO THE DRIVE SHAFT AND WAS SWUN	G AROUND CONTRIBUTING TO THE VIBRATION				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998043001177	19980430	01177	EU  	1998	4	30	AU960427         	1	19960225	G	3245	50028221	WHEEL           		50028062    	ISRAEL	1124  	1124        	4500102	EU  										LG WHEEL/BRAKE S	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			287  		DEC86319					(AUS) MAIN LANDING GEAR WHEEL TYRE FILL VALVE THREAD STRIPPED - THE  TYRE FILL GAUGE PN GP10-105-158 CAME OUT WITH THE W	HEEL THREAD STILL IN THE THREAD ON THE FILL VALVE - SUSPECT INCORRECT FITMENT OF VALVE					2	M	7	2 	4F				A2SW    					 
1998043001178	19980430	01178	CE  	1998	4	30	AU960428         	1	19960402	G	3260	JE1	MICROSWITCH     			CESSNA	310   	310R        	2074245	CE  										LG POSITION IND	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH ACTUATOR LEAF BROKEN OFF						1	L	7	2 	3O				3A10    					 
1998043001179	19980430	01179	NE  	1998	4	30	AU960429         	2	19960326	G	7210		BEARING         		310820701   	STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  					TURBINE ENG. RED	SEIZED          	W				K	E			NONE                    	ENGINE SHUTDOWN         			O			OTHER                     			CL	CLIMB          	1			AU	S 					0		106183			(AUS) LH ENGINE WAS SHUT DOWN AND FEATHERED FOR TRAINING PURPOSES - THE FEATHERED ENGINE CONTINUED TO ROTATE AT APPROXIM	ATELY 100RPM - INVESTIGATION FOUND THE MAIN OIL FILTER HEAVILY CONTAMINATED WITH METAL - CAUSED BY PLANET GEAR (PNO 3108	207-01) BEARING AND STEEL SLEEVE SEIZING				2	H	7	2 	4T	4	T		A41EU   	E26NE				 
1998043001180	19980430	01180	EU  	1998	4	30	AU960431         	1	19960328	G	7160	352002034	HOSE            	LYC         	IO540K1B5   	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					ACFT,ENG AIR INT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L2552648A					(AUS) RH ENGINE INDUCTION HOSE INTERNAL WIRE SEPARATING FROM HOSE -  FOUND DURING INSPECTION IAW AD/BN2/57						1	H	7	2 	3O	3	O		A17EU   	1E4				 
1998043001181	19980430	01181	EA  	1998	4	30	AU960432         	2	19960330	G	7322	C15159	CARBURETOR      	FACET       	MABA        	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CONTAMINATED    	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 					C15159		L1675415			(AUS) CARBURETTOR BOWL AND VENTURI CONTAMINATED - FLOAT MOUNTING SHAFT SLIGHTLY WORN						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1998043001182	19980430	01182	SW  	1998	4	30	AU960433         	1	19960328	G	6310	B121892	BEARING         		0476204859  	BELL  	47    	47G3B       	1181026	SW  										ENG/TRANS CPLNG	UNDERSIZE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B121892					(AUS) MAIN ROTOR TRANSMISSION DRIVE FLANGE SHEAR SCREWS DISTORTED -  SUSPECT DUE TO SLIPPAGE OF THE FREEWHEEL UNIT DUE T	O FITMENT OF UNDERSIZE BEARING ROLLERS AND SUBSEQUENT SHOCK LOADING DURING  RE-ENGAGEMENT - SEE ALSO MDR 96/0435 AND MDR	 96/0341				1	G	7	1 	3O				2H3     					 
1996110100999	19961101	00999	EA  	1996	11	1	AU960434         	2	19960401	G	7322	CK13983	CARBURETTOR     	FACET       	MA4SPA      	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 					CK13983		L4388427A			(AUS) CARBURETTOR FAULTY - SUSPECT TEMPORARY CONTAMINATION OR  INTERMITTENT FAILURE COMBINED WITH NON FIRING OF NO4 CYLI	NDERCAUSED ROUGH RUNNING ENGINE - CARBURETTOR ICING WAS DISMISSED AS THE CAUSE					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996110700139	19961107	00139	SW  	1996	11	7	AU960435         	1	19960328	G	6310	B121892	BEARING         		0476206831  	BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435D1A   	41516	EA  					ENG/TRANS CPLNG	UNDERSIZE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			300  		B121892					(AUS) MAIN ROTOR FREE WHEEL UNIT BEARING ROLLERS UNDERSIZE - SEE MDR 96/0433 FOR ADDITIONAL INFORMATION						1	G	7	1 	3O	3	O		2H3     	1E13				 
1996120300040	19961203	00040		1996	12	3	AU960436         	1	19960402	G	7120	AN650A	BOLT            																	ENGINE MOUNTING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FRAME LOWER RH ATTACHMENT BOLT BROKEN - WHEN REMOVING THE REMAINING BOLTS FOR INSPECTION, IT WAS FOUND THAT	 THE TORQUE ONTHE LOWER LH LOCK NUT WAS BELOW STANDARD PRACTISES																		 
1996110700140	19961107	00140	SW  	1996	11	7	AU960437         	1	19960402	G	3246	16210	WHEEL           			AIRPTS	A     	A9A         	0144204	SW  	LYC   	O540  	O540B2B5    	41532	EA  					LG WHEEL/BRAKE S	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN WHEEL FLANGE FAILED AND BROKE AWAY DURING TYRE INFLATION -  DYE PENETRANT CHECK HAD FOUND NO INDICATION OF CR	ACKING - PIECEOF FLANGE BROKEN AWAY WAS APPROXIMATELY 100MM (4IN) - SUSPECT A  CRACK APPROXIMATELY 76.2MM (3IN) LONG HAD	 EXISTED FOR SOME TIMEPRIOR TO FAILURE AS OXIDATION OF THE CENTRE SECTION OF THE BROKENFLANGE PORTION WAS PRESENT				1	L	7	1 	3O	3	O		A4WE    	E295				 
1996110700141	19961107	00141	SO  	1996	11	7	AU960438         	1	19960326	G	2740	62701047	CONTROL CABLE   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					HORIZ STAB SYS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR TRIM CABLE FRAYED AROUND TURN BARREL AT THE AIRCRAFT  TAIL - THE CABLE WAS FRAYED FOR APPROXIMATELY A Q	UARTER OF THE CABLE DIAMETER					1	L	7	1 	3O	3	O	 	2A13    	E274				 
1996110700142	19961107	00142	CE  	1996	11	7	AU960439         	1	19960407	G	5720		FITTING         		71521       	BBAVIA	8     	8KCAB       	2110612	CE  	LYC   									OUTER WING SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NSN					(AUS) WING STRUT ATTACHMENT FITTINGS (4OFF) FOUND WITH CHAFE MARKS - ALSO TWO OF THE FITTINGS HAVE SEVERAL BOLT HOLES NO	T DEBURRED -FOUND DURING INSPECTION IAW AD/CHA/25 AMDT 1					1	H	7	1 	3O				A21CE   					 
1996110700143	19961107	00143	CE  	1996	11	7	AU960440         	1	19960401	G	2410	646655	DRIVE           	CONT        	ALTERNATOR  	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					ALT-GEN DRIVE SY	SEPARATED       	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			447  		B2189170					(AUS) LH ALTERNATOR DRIVE COUPLING RUBBER AND DRIVE CASING DEBONDED						1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996110700144	19961107	00144	NE  	1996	11	7	AU960441         	3	19960228	G	6110	70096	BEARING         			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	23D	23D40       	NE  	PROPELLER ASSY S	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								N216907		(AUS) PROPELLER BLADE THRUST ROLLER BEARING PNO 70096 BROKEN INTO FIVE PIECES - THE OTHER BEARING WAS CRACKED, CORRODED 	AND HAD PIECESMISSING FROM THE ROLLER - INVESTIGATION FOUND MOISTURE HAD CAUSEDTHE BEARING TO RUST WHICH LED TO THE EVEN	TUAL BEARING FAILURE -AIRCRAFT HAS A LOW UTILISATION RATE AND HAD BEEN ORIGINALLY  FITTED TO AN OTTER SEAPLANE IN CANADA	 BEFORE BEING PURCHASED BYTHE PRESENT OWNER			1	L	7	1 	3R	3	R		A9SW    	5E2	6	C	P719	 
1996110700145	19961107	00145	GL  	1996	11	7	AU960442         	2	19960212	G	7260	23034601	OIL JET         	ALLSN       	250C30      	SNIAS 	350   	AS350B      	8680801	EU  	ALLSN 	250C  	250C30      	03013	GL  					T ENG AUX DRIVE	UNAPPROVED PART 	W		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					CAG95590		CAE895582			(AUS) DURING ENGINE INSPECTION FOLLOWING AN AIRCRAFT WIRE STRIKE, THE PINION OIL NOZZLE WAS FOUND TO BE THE INCORRECT PA	RT NUMBER ITEM FOR THE TURBINE TO GEARBOX CONFIGURATION - THE TURBINE HAD BEEN MODIFIED IAW ALLISON 250C30 SBS 72-3158 A	ND 72-3193 - THE OILNOZZLE SHOULD HAVE BEEN REPLACED AT THAT TIME WITH ITEM PNO 23035174 - PERSONNEL/MAINTENANCE ERROR -	 UNAPPROVED PART.			1	G	7	1 	3U	3	U		H9EU    	E1GL				 
1996110700146	19961107	00146	SO  	1996	11	7	AU960443         	2	19960308	G	8520	530182	CRANKSHAFT      			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	R ENGINE POWER S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			45   				661037A			(AUS) ENGINE SUFFERED TWO CRANKSHAFT MAIN BEARING EXCESSIVE WEAR INCIDENTS IN APPROXIMATELY 50 HOURS OPERATION: 1. FIRST	 OCCURRENCE WAS AT 8.5 HOURS AFTER INSTALLATION FOLLOWING OVERHAUL - ENGINE WAS INSPECTED/CHECKED, NEW BEARINGS AND A  U	SED SERVICEABLE CRANKSHAFT FITTED AND RETURNED TO SERVICE  2. SECOND OCCURRENCE, SHOWS IDENTICAL WEAR PATTERNS TO THE FI	RST - METAL CONTAMINATION OF OIL SYSTEM - METAL WAS IDENTIFIED AS  COMING FROM WORN CYLINDER BORES - BEARING SET PNO SA5	30058A6 WAS FITTED ON BOTH OCCASIONS		1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1996110700147	19961107	00147	CE  	1996	11	7	AU960444         	1	19960325	G	3211	1058100203	CONNECTOR       			BEECH 	76    	76          	1153005	CE  										MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR CONNECTOR PNO 105-810020.3 CRACKED ON THE  INBOARD LUG ADJACENT TO THE CLEVIS PIN LOCATING HOLE 	- CAUSED BY CORROSION OF LOCATING ROLL PIN IN CONNECTOR					1	L	7	2 	3O				A29CE   					 
1996120300041	19961203	00041	CE  	1996	12	3	AU960445         	1	19960322	G	7120	J96134950	MOUNT           	BEECH       	1059100101  	BEECH 	76    	76          	1153005	CE  										ENGINE MOUNTING	INCORRECT FIT   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					0					(AUS) DURING REPLACEMENT OF THE ENGINE LORD MOUNTS THE FOLLOWING DEFECTS WERE FOUND:1. NO1 ENGINE MOUNTS WERE CORRECTLY 	ASSEMBLED BUT TRANSPOSED, PNO J9613-49 WAS INSTALLED IN THE PNO J9613-50 POSITION AND  VICE VERSA  2. NO2 ENGINE LOWER M	OUNTS DID NOT HAVE THE LARGER WASHERS  (2IN BY 0.1175IN) POSITIONED BETWEEN THE ENGINE CRANKCASE ANDTHE BISCUIT MOUNT, C	AUSING THE ENGINE TO ADOPT A NOSE DOWN ATTITUDE THE INBOARD LOWER MOUNT WAS FITTED WITH THE WASHER INCORRECTLY POSITIONE	D UNDER THE BOLT HEADPERSONNEL/MAINTENANCE ERROR		1	L	7	2 	3O				A29CE   					 
1996110700148	19961107	00148	WP  	1996	11	7	AU960446         	1	19960302	G	5320	591142917	TEE SECTION     			DOUG  	DC9   	DC933F      	302207A	WP  										MAIN FRAME SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN BULGING AT L25 BETWEEN STN 1070 AND STN 1081 - WHENTHE SKIN WAS LIFTED BACK THE FOLLOWING CORROSION 	WAS FOUND:1. FILIFORM CORROSION ON FACE OF 'T' SECTION BETWEEN STN 1070 AND STN 10762. EXFOLIATION CORROSION ON ONE SIDE	 OF THE BACK FACE OF THE 'T'BETWEEN STN 1076 AND STN 1081				2	L	7	2 	4F				A6WE    					 
1996110700149	19961107	00149	SO  	1996	11	7	AU960447         	2	19960315	G	8520	649163	CRANKCASE       			CESSNA	150   	A150M       	2071831	CE  	CONT  	O200  	O200A       	17020	SO  					R ENGINE POWER S	DEFECTIVE       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			772  		25471450		25471450			(AUS) DURING RECIFICATION FOR A LEAKING PUSHROD TUBE AND REPLACEMENT OF NO1 CYLINDER, A LOWER CRANKCASE THROUGH STUD PUL	LED OUT - THE CRANK CASE WAS SPLIT AND IT WAS THEN FOUND THE FRONT BEARING HOUSING WAS 0.0010IN OUT OF ROUND AND THE MID	DLE HOUSING WAS +0.0005IN ON ONE SIDE AND -0.005IN ON THE OTHER -  PERSONNEL/MAINTENANCE ERROR				1	H	7	1 	3O	3	O		3A19    	E252				 
1996120300042	19961203	00042	NM  	1996	12	3	AU960448         	1	19960320	G	7120		BOLT            			BOEING	747   	747312      	1384932	NM  										ENGINE MOUNTING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO2 ENGINE UPPER AFT MOUNT FITTING BOLTS AND BUSHES WORN - APPROXIMATE AMOUNT OF VERTICAL MOVEMENT WAS 0.060IN DUR	ING INVESTIGATION THE FOLLOWING OTHER PROBLEMS WERE FOUND: 1. BOTH AFT FITTING ATTACHMENT BOLTS PNO 65B90383-2 WERE  EXC	ESSIVELY WORN AND STEPPED  2. BUSHINGS IN THE REAR ENGINE UPPER FITTING PNO 65B90356-35  (4 OFF) AND PNO 65B90356-36 (2 	OFF) WERE WORN FOUND DURING INSPECTION AIW ER B747-71-20-4 FOLLOWING ENGINE REMOVAL			2	L	7	4 	4F			RT	A20WE   					 
1996110700150	19961107	00150	GL  	1996	11	7	AU960449         	3	19960404	G	6111	813827	BLADE           	MCAULY      	3AF32C508   	PIPER 	PA34  	PA34220T    	7103420	SO  						MCAULY	3AF32C	3AF32C508   	GL  	PROPELLER ASSY S	FOD TEAR        	W				K				NONE                    				C			F.O.D.                    			TO	TAKEOFF        	1			AU	S 			346  		813827			813827		(AUS) FOREIGN OBJECT IMPACTED WITH BLADE TIP CAUSING TEAR IN BLADE - SUSPECT FOD CAME FROM SURFACE OF AIRFIELD						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1996110700151	19961107	00151	SO  	1996	11	7	AU960450         	2	19960324	G	7310	627346	DIAPHRAGM       	CONT        	MANIFOLDVALV	BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENG,FUEL DIST SY	LEAKING         	W				K				NONE                    				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			AU	S 			1448 		I158114C		571950			(AUS) FUEL MANIFOLD VALVE DIAPHRAGM LEAKING AT THE SHAFT ASSEMBLY						1	L	7	1 	3O	3	O		3A15    	E5CE				 
1996110700152	19961107	00152	EU  	1996	11	7	AU960451         	1	19960225	G	3520	E0390DD01S2A12A	CONNECTOR       		01P2B12A    	AIRBUS	320   	A320212     		EU  										CREW&PASS OXY	HIGH RESISTANCE 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0					(AUS) DURING AN OPERATIONAL TEST OF THE MANUAL MASK RELEASE FOR  PASSENGER OXYGEN, A NUMBER OF MASK PANELS FAILED TO REL	EASE -INVESTIGATION FOUND THAT CONNECTOR 2773VC AT STN 925 HAD A HIGH  RESISTANCE CAUSING A FLOATING VOLTAGE					2	L	7	2 	4F			RT	A28NM   					 
1996110700153	19961107	00153	SO  	1996	11	7	AU960452         	1	19960404	G	3211	9529902	STUD            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR SIDE BRACE STUD CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION (MPI) IAW AD/PA34/46						1	L	7	2 	3O	3	O		A7SO    	1E10				 
1996110700154	19961107	00154	SO  	1996	11	7	AU960453         	1	19960404	G	5741	9010443	BOLT            			GULSTM	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320E2G     	41508	EA  					ATTACH FITTING S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SHOULDER BOLTS (2OFF) CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION (MPI)						1	L	7	1 	3O	3	O		A16EA   	E274				 
1996110700155	19961107	00155	GL  	1996	11	7	AU960454         	3	19960327	G	6110		CYLINDER        													HARTZL	HC92Z	HC92ZK8     	GL  	PROPELLER ASSY S	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								1201L		(AUS) DURING PROPELLER OVERHAUL IT WAS FOUND THAT AN INCORRECT CYLINDER ASSEMBLY HAD BEEN FITTED NON-STANDARD SPACERS HA	D ALSO BEEN FITTED IN ORDER TO CHANGE THE EFFECTIVE LENGTH OF THE PITCH  CONTROL RODS - UNAPPROVED PART - PERSONNEL/MAIN	TENANCE ERROR														5	C	P892	 
1996110700156	19961107	00156	SO  	1996	11	7	AU960455         	1	19960409	G	2750		MICROSWITCH     			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	FLAP SYS	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAPS JAMMED IN THE 'UP' POSITION DUE TO THE INTERMITTENT  OPERATION OF THE 'UP' LIMIT MICROSWITCH - FLAP OVERTRAV	EL BURNT OUT MOTOR ARMATURE					1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1996110700157	19961107	00157	NM  	1996	11	7	AU960457         	1	19960321	G	3040	SYLZ50970	TEMP CONTROLLER 			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					WINDOW AI/DE-ICE	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) WINDSHIELD HEATING TEMPERATURE CONTROLLER APPLIED FULL HEAT WHEN NORMAL SELECTED DUE TO SUSPECT DEFECTIVE WARMUP S	ELECTION - THE'R WSHLD HOT' CAUTION WARNING LIGHT ILLUMINATED AND THE RH WINDSHIELD OUTER PANE CRACKED					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996110700158	19961107	00158	NE  	1996	11	7	AU960458         	2	19960407	G	7250		TURBINE BLADE   								PWA   	4056  	PW4056      		NE  					TURBINE SECTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P724208			(AUS) NO1 ENGINE FIRST STAGE HPT MISSING APPROXIMATELY HALF A BLADE -  FOUND DURING BORESCOPE INSPECTION											4	F			E24NE				 
1996110700159	19961107	00159	GL  	1996	11	7	AU960459         	2	19960331	G	7421	CH31772A	IGNITOR PLUG    								GE    	CF6   	CF680C      		GL  					ENG,IGNITN DISTR	WORN            	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) LH ENGINE 'A' AND 'B' SYSTEM IGNITION PLUGS WERE FOUND TO BE SEVERELY ERODED WITH EVIDENCE OF SPARK TRACKING THROU	GH A CRACKIN THE CERAMIC INSULATOR OF THE 'B' SYSTEM PLUG										4	F			E23EA				 
1996110700160	19961107	00160	CE  	1996	11	7	AU960460         	1	19960404	G	3297		WIRE            			BEECH 	1900  	1900D       	1154162	CE  										LG POSITION IND	BROKEN          	W				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) NLG INDICATION SYSTEM WIRE BROKEN ON LAMP HOUSING						2	L	7	2 	4T			RT	A24CE   					 
1996110700161	19961107	00161	NM  	1996	11	7	AU960461         	1	19960304	G	3233	NAS161133	O-RING          		65449121    	BOEING	737   	737377      		NM  										LG EXT-RETRACT S	INCORRECT FIT   	W		A		K				NONE                    				W			INADEQUATE Q C            			TO	TAKEOFF        	1			AU	S 			13946		TSC1583ANS					(AUS) LH MLG RETRACTION ACTUATOR 'O' RING PACKING PNO NAS1611-33 ON PISTON PNO 65-44912-1 WAS FOUND SEPARATED AND FRACTU	RED IN A NUMBER OF AREAS AND THE INNER FACE WAS BADLY DAMAGED - FURTHER INVESTIGATION FOUND THAT THE SEAL INSTALLATION W	AS INCORRECT - THE DAMAGED PACKING HAD INCORRECT BACKUP RINGS - THESE RINGS WOULD NORMALLY ONLY BE USED WHEN USING G.T. 	 SEAL PNO 7336M59521 -UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR.			2	L	7	2 	4F			RT	A16WE   					 
1996110700162	19961107	00162	EU  	1996	11	7	AU960462         	1	19960409	G	5350	36010A	LATCH           			AEROSP	SA365 	SA365C      	8680667	EU  										FAIRING SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING TURN AROUND INSPECTION, THE PILOT DISCOVERED THE LH MAIN GEARBOX FORWARD COWL HANDLE MISSING - THE ROLL PIN	 ATTACHING THE HANDLE TO THE CENTRE LOCKING SHAFT HAD SHEARED					1	G	7	2 	3U				H10EU   					 
1996110700163	19961107	00163	EU  	1996	11	7	AU960463         	1	19960101	G	5753		SKIN            			FOKKER	F27   	F27MK600    	4990706	EU  	RROYCE									WING TE SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STARBOARD OUTER FLAP SKIN CRACKED AT STN 340 - WHEN THE FLAP WAS DISMANTLED CRACKS WERE ALSO FOUND IN THE RIB - FO	UND DURINGINSPECTION IAW SB F27-57-67 - AIRCRAFT HAS BEEN PARKED IN THE  OPEN AT BRISBANE AIRPORT FOR APPROXIMATELY 6 YE	ARS				2	H	7	2 	4T				A817    					 
1996110700164	19961107	00164	WP  	1996	11	7	AU960464         	1	19960208	G	6230	269A530511	DRIVE SHAFT     			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					M/R MAST/SWASHPL	RUSTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					618270					(AUS) MAIN ROTOR DRIVE SHAFT (MAST) BORE BADLY RUSTED						1	G	7	1 	3O	3	O		4H12    	1E10				 
1996110700165	19961107	00165	SW  	1996	11	7	AU960465         	1	19960314	G	8010	H2211	SWITCH          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ENGINE CRANKING	FAULTY          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE BEGAN TO ROTATE RAPIDLY WHEN AIRCRAFT BATTERY SWITCHES SELECTED ON - SUSPECT INTERNAL SHORT ACROSS THE S	TARTER SWITCH CONTACTS CAUSED CONTACTS TO STICK					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1996110700166	19961107	00166	SW  	1996	11	7	AU960466         	1	19960331	G	2930	SS10127	PRESSURE SWITCH 			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT									HYD IND SYS	FAILED          	W				K				NONE                    				K	N		FLUID LOSS                	FALSE WARNING             		CR	CRUISE         	1			AU	S 										(AUS) LH HYDRAULIC PRESSURE SWITCH FAILED - HYDRAULIC PRESSURE ON GAUGE READING NORMAL AT 1850 PSI						2	L	7	2 	4T			RT	A18SW   					 
1996110700167	19961107	00167		1996	11	7	AU960467         	4	19960404	G	2312		RADIO SYSTEM    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					VHF COMMUNICATIO	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RADIO SYSTEM JAMMED IN TRANSMIT MODE ON THREE OCCASIONS - ON  LANDING,  AFTER EACH FAILURE THE SYSTEM OPERATED NOR	MALLY					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996110700168	19961107	00168	CE  	1996	11	7	AU960468         	1	19960411	G	2612	302158	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FIRE DET SYS	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) RH ENGINE FIRE WARNING ILLUMINATED - ON LANDING THERE WAS NO EVIDENCE OF FIRE - FIRE WARNING SENSORS REPLACED BY A	 NEW TYPE PNO 473275					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996110700169	19961107	00169	EA  	1996	11	7	AU960469         	2	19960411	G	7414	LW18378	CLAMP           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ELEC PWR SUPPLY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L49576T			(AUS) DUAL MAGNETO RETAINING CLAMP ALLOWED MAGNETO TO ROTATE ON THE  MOUNTING						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996110700170	19961107	00170	EU  	1996	11	7	AU960470         	1	19960315	G	2610		WIRE            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FIRE DETECTION S	WORN            	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING MAINTENANCE UNDER NO2 PYLON (ENGINE REMOVED), A NUMBER OF FIRE/OVERHEAT DETECTOR WIRES WERE FOUND CHAFED WH	ERE THEY ENTER THE SUPPORT SLEEVE OF THE LEADING EDGE PYLON FIRESEAL 'F' - THE  OTHER THREE PYLONS WERE INSPECTED AND TW	O HAD SIMILAR CHAFING -THE MAJORITY OF WIRES WERE CHAFED MORE THAT 50% THROUGH THE  CONDUCTORS - FOUND DURING A SCHEDULE	D 4C CHECK			2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
1996110700171	19961107	00171	SO  	1996	11	7	AU960471         	1	19960411	G	5753	6232002	RIB             		2232002     	PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  					WING TE SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING FLAP HAS EXTENSIVE CORROSION BETWEEN THE STEEL ATTACHMENT BRACKETS AND THE INTERNAL NOSE RIBS - ALL RIBS H	AD PARTED FROM THE ATTACHMENT BRACKETS - THE TRAILING SKIN RIB SITUATED UNDER AND ON THE OUTER END OF THE STRENGTHENED W	ALKWAY PORTION OF THE FLAP HAD CORRODED AWAY TO VIRTUALLY NOTHING - AIRCRAFT IS OF 1963VINTAGE WITH ONLY 2100 HOURS TTIS	 - NO CORROSION PROTECTION WAS APPLIED DURING MANUFACTURE			1	L	7	1 	3O	3	O		2A13    	E295				 
1996110700172	19961107	00172	SO  	1996	11	7	AU960472         	1	19960411	G	5753	6232000	RIB             			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING TE SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING FLAP HAS EXTENSIVE CORROSION MAINLY BETWEEN THE STEEL  ATTACHMENT BRACKETS AND INTERNAL NOSE RIBS - ALL OF	 WHICH HADDEPARTED FROM THEIR ATTACHING SURFACES DUE TO THE CORROSION - SEEMDR 96/0471 FOR FURTHER INFORMATION					1	L	7	1 	3O	3	O		2A13    	E295	5	C	P920	 
1996110700173	19961107	00173	SO  	1996	11	7	AU960473         	1	19960403	G	3246	300608	WHEEL           			EMB   	110   	EMB110P1    	3260122	SO  										LG WHEEL/BRAKE S	FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LH MAIN WHEEL TYRE RETAINING BEAD HAD SEPARATED FROM THE INNER WHEEL HALF						1	L	7	2 	4T				A21SO   					 
1996110700174	19961107	00174	EU  	1996	11	7	AU960474         	1	19960229	G	3213	5321012180	SHOCK ABSORBER  			PILATS	PC12  	PC12        	7090550	EU  										MAIN GEAR SYS	FAULTY          	W				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 										(AUS) RH MAIN LANDING GEAR STRUT STAGE 1 AND 2 PRESSURES BOTH FOUND TO BE 1000 PSI - UNABLE TO SERVICE SHOCK ABSORBER - 	SUSPECT ANINTERNAL FAILURE					1	L	7	1 	3T			RT	A78EU   					 
1996110700175	19961107	00175	CE  	1996	11	7	AU960475         	1	19960404	G	5312	0513006103	BULKHEAD        			CESSNA	172   	172         	2072402	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH DOOR POST BULKHEADS AND PLATES CRACKED BETWEEN NOTCH AND VACANT BOLT HOLE						1	H	7	1 	3O			NT	3A12    					 
1996110700176	19961107	00176	CE  	1996	11	7	AU960476         	1	19960410	G	5312		BULKHEAD        			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOOR POST BULKHEAD CRACKED ON BOTH SIDES - FOUND DURING  INSPECTION IAW AD/C180/75 AMDT 1						1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1996110700177	19961107	00177	SO  	1996	11	7	AU960477         	1	19960409	G	3250	31812	COLLAR          			PIPER 	PA23  	PA23250     	7102308	SO  										ACFT STEERING SY	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR STEERING COLLAR FRACTURED AT THE LH ATTACHMENT LUG - SUSPECT DAMAGE CAUSED BY EXCEEDING STEERING	 LIMITS DURING GROUND HANDLING					1	L	7	2 	3O				1A10    					 
1996120300043	19961203	00043	EA  	1996	12	3	AU960478         	1	19960330	G	2842	39108703082	SENSOR          			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					FUEL INDICATION	BLOCKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT FUEL QUANTITY INDICATOR OVERREADING BY 125LBS IN THE LOWER END RANGE - INVESTIGATION FOUND NO5 FUEL CELL (COLL	ECTOR TANK) FUEL QUANTITY CAPACITANCE PROBE LOWER DRAIN HOLE BLOCKED WITH  FOREIGN MATERIAL					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1996110700178	19961107	00178	SO  	1996	11	7	AU960479         	2	19960325	G	8520	642396	CRANKSHAFT      	CONT        	IO520M      	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					R ENGINE POWER S	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					565246		565246			(AUS) ENGINE CRANKSHAFT BROKEN AT NO9 CHEEK						1	L	7	2 	3O	3	O		3A10    	E5CE				 
1996110700179	19961107	00179	CE  	1996	11	7	AU960480         	1	19960415	G	5711	35410217	SPAR            			BEECH 	35    	V35A        	1151544	CE  	CONT  	O520  	IO520B      	17032	SO  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRONT SPAR CARRY THROUGH SECTION CRACKED AT BOTH  OUTBOARD SIDES						1	L	7	1 	3O	3	O		3A15    	E5CE				 
1996110700180	19961107	00180	CE  	1996	11	7	AU960481         	1	19960212	G	5711	3511006178	SPAR CAP        			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520B      	17032	SO  					OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING LOWER SPAR CAP CORRODED						1	L	7	1 	3O	3	O		3A15    	E5CE				 
1996110700181	19961107	00181	CE  	1996	11	7	AU960482         	1	19960415	G	2820	F123660156	HOSE            		F123660144  	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					FUEL DISTRBUTION	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL HOSE LEAKING BETWEEN FITTING AND HOSE - FOUND DURING  INSPECTION IAW AD/HOSE/3 AMDT5						1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1996121900097	19961219	00097	NM  	1996	12	19	AU960483         	1	19960410	G	2912	271T00703	FILTER BOWL     			BOEING	767   	767338      		NM  										MAIN HYD SYS	SEPARATED       	W				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) AIRCRAFT LANDED WITH CENTRE HYDRAULIC SYSTEM LOW PRESSURE AND  QUANTITY - INVESTIGATION FOUND THE ADP (AIR DRIVEN 	PUMP) PRESSURE FILTER BOWL SEPARATED FROM THE MODULE DUE TO FATIGUE CRACKING IN THE LAST THREAD OF THE BOWL - TOTAL LOSS	 OF HYDRAULIC FLUID				2	L	7	2 	4F			RT	A1NM    					 
1996121900098	19961219	00098	NM  	1996	12	19	AU960484         	1	19960403	G	5754		SKIN            			BOEING	767   	767338      		NM  										WING  LE FLAP	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO6 LE FLAP TRAILING UPPER SKIN HAS EXCESSIVE DELAMINATION						2	L	7	2 	4F			RT	A1NM    					 
1996110700182	19961107	00182	CE  	1996	11	7	AU960485         	1	19960416	G	2910	571702214	PIPE            			CESSNA	441   	441         	2076020	CE  										MAIN HYD SYS	CRACKED         	W				K				NONE                    				J	K		WARNING INDICATION        	FLUID LOSS                		LD	LANDING        	1			AU	S 										(AUS) HYDRAULIC PRESSURE PIPE BETWEEN PUMP AND HYDRAULIC POWER PACK  CRACKED AT BEND						1	L	7	2 	3T			RT	A28CE   					 
1996110700183	19961107	00183	CE  	1996	11	7	AU960486         	1	19960416	G	2820	510011084	PIPE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					FUEL DISTRBUTION	CORRODED        	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) LH NACELLE FUEL TANK TRANSFER PUMP TO 'T' FITTING PIPE LEAKING FUEL FROM PIN HOLE DUE TO INTERNAL CORROSION						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996110700184	19961107	00184	EA  	1996	11	7	AU960487         	2	19960418	G	7414	10349271	COIL            	BENDIX      	S6LN1208    	BEECH 	60    	A60         	1153604	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					ELEC PWR SUPPLY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			742  		A65367		L89959			(AUS) RH ENGINE LH MAGNETO 'CLEAR CASE' COIL DETERIORATED AND CASE SEVERLY CRACKED - FOUND DURING INSPECTION IAW AD/ELEC	T/66 AMDT 1 - AIRCRAFT WAS PREVIOUSLY REGISTERED AS VH-EZT					1	L	7	2 	3O	3	O		A12CE   	E10EA				 
1996110700185	19961107	00185	CE  	1996	11	7	AU960488         	1	19960418	G	2810		CAP             			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  					FUEL STORAGE SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK CAPS LEAKING - REPLACED BY TYPE PNO SK182-8513 - FOUND DURING INSPECTION IAW AD/CESSNA180/70 AMDT 1						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996111400001	19961114	00001	CE  	1996	11	14	AU960489         	1	19960418	G	2161	7468331	SWITCH          			CESSNA	441   	441         	2076020	CE  										CABIN TEMP. CONT	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 					PNHS738443					(AUS) PRESSURISATION SYSTEM AIRCYCLE MACHINE OVERTEMPERATURE SWITCH  FAULTY GIVING FALSE ACM OVERTEMPERATURE INDICATION,	 CAUSINGCONSEQUENT CABIN PRESSURE FAILURE AND EMERGENCY PRESSURISATION ACTUATION					1	L	7	2 	3T			RT	A28CE   					 
1996111400002	19961114	00002	WP  	1996	11	14	AU960490         	1	19960321	G	5311		FRAME           			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										ATTACH FITTING S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEVERE EXFOLIATION CORROSION FOUND IN THE FOLLOWING LOCATIONS: 1. TAIL SECTION FRAME STN 703 AT THE TWO ATTACHING 	BOLT LOCATION  WITH AREA OF CORROSION COVERING APPROXIMATELY FOUR (4) SQUARE INCHES AT EACH LOCATION - DEPTH OF CORROSIO	N HAD PENETRATED  RIGHT THROUGH THE FRAME 2. LH ENGINE NACELLE AT STN 174 TO STN 200 STRINGERS				2	L	7	2 	4R				A669    					 
1996111400003	19961114	00003	CE  	1996	11	14	AU960491         	1	19960416	G	5720	316321	FITTING         		316322      	BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O320  	AEIO320E2B  	41508	EA  					OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BOTH FORWARD WING STRUT FITTINGS PNO 3-1362-1 AND PNO 3-1632-2 CRACKED - ALL FOUR FORWARD AND REAR FITTING PIECES 	CRACKED - FOUND DURING DYE PENETRANT INSPECTION					1	H	7	1 	3O	3	O		A21CE   	1E12				 
1996111400004	19961114	00004	CE  	1996	11	14	AU960492         	1	19960415	G	5551	1231325KAO	FITTING         			CESSNA	206   	U206G       	2073356	CE  	LYC   	O540  	TIO540F2BD  	41532	EA  					HORZ STAB SYS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							567898			(AUS) HORIZONTAL STABILISER WAS REMOVED DUE TO EXCESSIVE MOVEMENT -  INVESTIGATION FOUND THAT EACH OF THE TWO FORWARD AT	TACHMENT FITTINGS HAD FOUR OF THE FIVE RIVETS SHEARED - SUSPECT INCORRECT GROUND HANDLING TECHNIQUE					1	H	7	1 	3O	3	O		A4CE    	E14EA				 
1996111400005	19961114	00005	SO  	1996	11	14	AU960493         	1	19960325	G	2822	751799	FILTER          			PIPER 	PA34  	PA34200T    	7103406	SO  										FUEL XSFER PUMP	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH NACELLE TANK ELECTRIC TRANSFER PUMP FILTER ELEMENT PNO 751-799MISSING - PERSONNEL/MAINTENANCE ERROR						1	L	7	2 	3O				A7SO    					 
1996111400006	19961114	00006	SO  	1996	11	14	AU960494         	1	19960325	G	5553	6244404	FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  										VERT STAB STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILISER FORWARD SPAR ATTACHMENT FITTING CORRODED AT  FRAME STN 259.31						1	L	7	2 	3O				A7SO    					 
1996111400007	19961114	00007	SO  	1996	11	14	AU960495         	1	19960325	G	5541	9620900	RIB             	PIPER       	PA34200T    	PIPER 	PA34  	PA34200T    	7103406	SO  										RUDDER STRUCT SY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER LOWER RIB CORRODED IN AREA OF STEEL TORQUE TUBE ASSEMBLY  DUE TO DISSIMILAR METAL CONTACT						1	L	7	2 	3O				A7SO    					 
1996111400008	19961114	00008	SO  	1996	11	14	AU960496         	1	19960325	G	3211	6704013	FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  										MAIN GEAR SYS	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MLG FORWARD TRUNNION FITTING LOOSE - 3 OF 4 ATTACHMENT BOLTS  LOOSE AND OTHER BOLT MISSING - ATTACHMENT BOLT HO	LES ELONGATED DUE TO MOVEMENT OF FITTING - FITTING WAS ATTACHED BY NAS TYPE  BOLTS INSTEAD OF WITH THE CORRECT AN TYPE A	S PER THE IPC - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O				A7SO    					 
1996111400009	19961114	00009	CE  	1996	11	14	AU960497         	1	19960418	G	5341	EB126	NUT             			BEECH 	33    	F33A        	1151425	CE  										ATTACH FITTING S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING ATTACHMENT BOLT NUT CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/BEECH33/41 - AIRCRAFT IS FOREI	GN REGISTERED N93RS					1	L	7	1 	3O				3A15    					 
1996111400010	19961114	00010	CE  	1996	11	14	AU960498         	1	19960419	G	2110	2322A2	HOSE            			CESSNA	208   	208B        	2073701	CE  										CABIN COMPRESSOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) AIRCONDITIONING SYSTEM COMPRESSOR DISCHARGE SERVICE VALVE HOSE 'BLEW OFF' ELBOW FITTING CAUSING LOSS OF FREON AND 	COMPRESSOR OIL- DISCHARGE PIPE IS CLAMPED TO THE DISCHARGE SERVICE VALVE					1	H	7	1 	3T				A37CE   					 
1996111400011	19961114	00011	SO  	1996	11	14	AU960499         	1	19960411	G	8011	ESEBB75A	DRIVE UNIT      	PRESTOLITE  	NO1724206   	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320C1A    	41508	EA  					ENGINE CRANKING	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					IF000589					(AUS) ENGINE STARTER MOTOR DRIVE LOCKED IN THE ENGAGED POSITION						1	L	7	2 	3O	3	O		A1EA    	1E12				 
1996111400012	19961114	00012	EU  	1996	11	14	AU960500         	1	19960416	G	7170	0174078010	DRAIN VALVE     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENG FLUID DRAIN/	INCORRECT ASSY  	W				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 					0174078010		585			(AUS) ENGINE STARTER DRAIN VALVE LEAKING FUEL AT BODY SPLIT LINE - CAUSED BY INCORRECT ASSEMBLY AT OVERHAUL - PERSONNEL/	MAINTENANCE ERROR					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1996111400013	19961114	00013	EU  	1996	11	14	AU960501         	1	19960310	G	5340		FITTING         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  					ATTACH FITTING S	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH FRONT WING ATTACHMENT FITTING AT FUSELAGE DAMAGED - FUSELAGE  PANELS LH AND RH SIDE ABOVE MAIN SPARS DISTORTED						1	L	7	1 	30	3	O	NT	A51EU   	E286				 
1997010200025	19970102	00025	EU  	1997	1	2	AU960502         	1	19960412	G	2120		DUCT            			BAG   	JETSTM	JETSTM3107  	1500215	EU  										AIR DISTRIBUTION	BLEW OUT        	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) PRESSURISATION SYSTEM LH AIR CYCLE MACHINE (ACM) SUPPLY DUCT SPLIT AND BLEW OFF - RH FLOW CONTROL VALVE WAS REPLAC	ED DUE TO INADEQUATE AIR SUPPLY FLOW TO MAINTAIN PRESSURISATION					2	L	7	2 	4T			RT	BA15CAA 					 
1996111400014	19961114	00014	SO  	1996	11	14	AU960503         	2	19960416	G	8530		EXHAUST VALVE   			CESSNA	310   	310J        	2074226	CE  	CONT  	O470  	IO470V      	17026	SO  					R ENGINE CYL SEC	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							147669			(AUS) ENGINE COMPRESSION LEAKAGE FROM EXHAUST VALVES ON ALL 6 CYLINDERS- FOUND DURING COMPRESSION CHECK IAW AD/ENG/4 AMD	T 5 - ENGINECALENDER TIME SINCE OVERHAUL WAS 19 YEARS					1	L	7	2 	3O	3	O		3A10    	3E1				 
1996111400015	19961114	00015	EA  	1996	11	14	AU960504         	2	19960417	G	7414	10682054	DISTRIBUTOR     	BENDIX      	DARN2021    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ELEC PWR SUPPLY	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			348  		5026468R					(AUS) MAGNETO RH SIDE DISTRIBUTOR GEAR BUSHING LOOSE CAUSING DAMAGE TO THE GEAR SHAFT - MAGNETO CAPACITOR OPEN CIRCUITED						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1996111400016	19961114	00016	CE  	1996	11	14	AU960505         	1	19960419	G	5720	3163212	FITTING         		316322      	BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360H1A  	41514	EA  					OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					75295LAND					(AUS) WING STRUT FITTINGS (4OFF) PNO 3-1632-1 AND PNO 3-1632-2 CRACKED IN THE CORNER OF THE RECTANGULAR HOLLOW SECTIONS 	- FOUND DURINGINSPECTION IAW AD/CHA/25 AND SL408 - AIRCRAFT HAS ONLY 103 HOURS TIME SINCE NEW WITH 20 HOURS OF AEROBATIC	 TIME				1	H	7	1 	3O	3	O		A21CE   	1E10				 
1996111400017	19961114	00017	CE  	1996	11	14	AU960506         	1	19960423	G	7120	630694	BRACKET         		630695      	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE MOUNTING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							172700R			(AUS) LH ENGINE LOWER MOUNT BRACKETS PNO 630694 AND PNO 630695 BROKEN						1	L	7	2 	3O	3	O		3A16    	E5CE				 
1996111400018	19961114	00018	CE  	1996	11	14	AU960507         	1	19960404	G	5312		BULKHEAD        			CESSNA	182   	182P        	2075816	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOOR BULKHEAD CRACKED						1	H	7	1 	3O			NT	TA13    					 
1996111400019	19961114	00019	NM  	1996	11	14	AU960508         	1	19960411	G	2920	BACR13CG2A	RELAY           			BOEING	767   	767238      		NM  										AUX HYD SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RAM AIR TURBINE (RAT) FAILED TO DEPLOY DURING TEST DUE TO FAILUREOF THE AIR/GROUND SYSTEM 2 RELAY K213						2	L	7	2 	4F			RT	A1NM    					 
1996111400020	19961114	00020	WP  	1996	11	14	AU960509         	2	19960315	G	7210		GEAR            								GARRTT	TPE331	TPE33110U   	01514	WP  					ENGINE REDUCTION	PITTED          	W				K				NONE                    				C			F.O.D.                    			CL	CLIMB          	1			AU	S 							P42106			(AUS) ENGINE SUFFERED A LIGHTNING STRIKE - DOME REMOVED AND GEARING  FOUND TO BE PITTED											4	T			E4WE				 
1996111400021	19961114	00021	NE  	1996	11	14	AU960510         	2	19960415	G	7261		OIL SYSTEM      								PWA   	PWA120	PW125B      		NE  					TURBINE ENGINE O	CONTAM-METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							TM124027			(AUS) ENGINE OIL FILTER CONTAMINATED WITH METAL											4	T			E20NE				 
1996111400022	19961114	00022	EU  	1996	11	14	AU960511         	1	19960418	G	2910	F8553048401	HOSE            			FOKKER	F27   	F27MK50     		EU  										MAIN HYD SYS	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		DE	DESCENT        	1			AU	S 										(AUS) HYDRAULIC HOSE IN LH WHEEL WELL RUPTURED - LOSS OF HYDRAULIC FLUID CAUSED ENGINE DRIVEN HYDRAULIC PUMP TO RUN DRY 	AND FAIL -SUSPECT HOSE FAILURE CAUSED BY INTERFERENCE WITH THE MLG LOCK  LINK DURING THE RETRACTION CYCLE - HOSE IS OF T	EFLON CONSTRUCTIONWITH METAL BRAIDED REINFORCEMENT WITH A WORKING PRESSURE OF  3500PSI				2	H	7	2 	4T			RT	A817    					 
1996111400023	19961114	00023	SO  	1996	11	14	AU960512         	2	19960402	G	8530	643767P005	VALVE GUIDE     	CONT        	O470R       	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  					R ENGINE CYLINDE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1317665P		1317665P			(AUS) NO1 CYLINDER EXHAUST VALVE GUIDE AND VALVE STEM WORN AND LEAKING - VALVE GUIDE AND VALVE ARE ONLY 70 HOURS TSN						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996111400024	19961114	00024	EU  	1996	11	14	AU960513         	1	19960411	G	5610	NF20216402	WINDSHIELD      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FLT CMPT WINDOW	DELAMINATED     	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					235789					(AUS) RH `B' WINDSCREEN OUTER PANE DELAMINATED AND A LARGE SECTION SEPARATED						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996111400025	19961114	00025	EA  	1996	11	14	AU960515         	2	19960126	G	7310	LW120980200	PIPE            			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					ENG,FUEL DIST SY	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			CR	CRUISE         	1			AU	S 			133  				L1723151A			(AUS) NO1 CYLINDER EXHAUST VALVE SEAT DROPPED CONTACTING THE PISTON  AND CAUSING CYLINDER FAILURE - ENGINE WAS BULK STRI	PPED AND INVESTIGATION OF NO1 CYLINDER ASSEMBLY FOUND:  1. EXTERNAL SIGNS OF OVERHEATING 2. FUEL INJECTION PIPE FLOW 7PP	H - NORMAL IS 30PPH - FURTHERINVESTIGATION FOUND THE OUTSIDE DIAMETER OF THE PIPE WAS 0.124IN COMPARED TO THE OTHER CYLI	NDER PIPE DIAMETERS OF 0.128IN.  ENGINE WAS OVERHAULED IN CANADA - SUSPECT WRONG PIPE FITTED  CAUSING LOWER FUEL FLOW RE	SULTING IN CYLINDER OVERHEAT - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR		1	G	7	1 	3O	3	O		H1CE    	1E10				 
1996111400026	19961114	00026	SO  	1996	11	14	AU960516         	1	19960412	G	2740	26701111	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					HORIZ STAB SYS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) HORIZONTAL STABILISER TRIM CABLE BROKEN IN AREA WHERE CABLE  PASSES THROUGH THE SERVO TRIM PULLEYS AND CAPSTAN						1	L	7	1 	3O	3	O	 	2A13    	1E10				 
1996111400027	19961114	00027	EU  	1996	11	14	AU960517         	2	19960307	G	7310	9375M18G01	MANIFOLD        								CFMINT	CFM56 	CFM563C1    	13802	EU  					ENG,FUEL DIST SY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							721762			(AUS) ENGINE FUEL MANIFOLD 'Y' TUBE CRACKED - CRACK LENGTH 19.05MM (0.75IN) - FOUND DURING FLUORESCENT PENETRANT INSPECT	ION										4	F			E21EU				 
1996111400028	19961114	00028	NM  	1996	11	14	AU960518         	1	19960415	G	4930	36080004	FCU             			BOEING	737   	737376      		NM  										APU POWER PLANT	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			453  							(AUS) APU SHUTDOWN DUE TO FLUCTUATING EGT, FREQUENCY AND VOLTAGE - SUSPECT FAULTY FCU						2	L	7	2 	4F			RT	A16WE   					 
1996111400029	19961114	00029	EU  	1996	11	14	AU960519         	1	19960417	G	3241	322	INDICATOR       			AIRBUS	300   	A300B4203   	3930306	EU  										LG WHEEL/BRAKE S	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					322					(AUS) BRAKING SYSTEM ANTI-SKID INDICATOR/TEST PANEL FAULTY DUE TO  SUSPECTED SHORTING TEST SWITCH - AUTO-BRAKE SYSTEM WO	ULD NOT OPERATE					2	L	7	2 	4F				A35EU   					 
1996111400030	19961114	00030	EU  	1996	11	14	AU960520         	1	19960406	G	4990		O-RING          		GTCP36150M  	BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					APU OIL SYS	FAILED          	W				K				NONE                    				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		TO	TAKEOFF        	1			AU	S 							P210UC			(AUS) APU ENGINE OIL SYSTEM QUANTITY LOW - SMOKE OBSERVED FROM EXHAUST - GENERATOR DRIVE CARBON SEAL LEAKING - MAIN CAUS	E OF OIL LOSS ISCONSIDERED TO BE A FAILED `O' RING SEAL ON THE OIL FILLER/DIPSTICK					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996111400031	19961114	00031	EU  	1996	11	14	AU960521         	1	19960303	G	2750		FLAP            			AIRBUS	320   	A320212     		EU  										FLAP SYS	OUT OF ADJUST   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH TRAILING EDGE FLAP INTERCONNECT STRUT MISRIGGED						2	L	7	2 	4F			RT	A28NM   					 
1996111400032	19961114	00032		1996	11	14	AU960522         	4	19960423	G	6122	8971613T	GOVERNOR        	WOODWARD    	210739      	CESSNA	441   	441         	2076020	CE  										PROP CNTRL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 			2461 		1434511M					(AUS) LH ENGINE PROPELLER GOVERNOR (CSU) FAULTY						1	L	7	2 	3T			RT	A28CE   					 
1996111400033	19961114	00033	SO  	1996	11	14	AU960523         	2	19960412	G	8530	6480291	PISTON          			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					R ENGINE CYL SEC	FAILED          	W				K				NONE                    				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CL	CLIMB          	1			AU	S 			1233 				286636R			(AUS) ENGINE NO5 PISTON DISINTEGRATED - RH CRANKCASE HALF CRACKED IN AREA BELOW PUSH ROD TUBES TO FRONT ENGINE MOUNT - C	RACK LENGTH 76.2MM (3IN) - ENGINE WAS A CONTINENTAL REMANUFACTURED UNIT					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996111400034	19961114	00034	EU  	1996	11	14	AU960525         	1	19960422	G	5713		STRINGER        			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  					OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING STRINGERS CRACKED FROM RIVET HOLES - ALL CRACKS WERE LESS THAN 12.7MM (0.5IN) IN LENGTH - FOUND DUR	ING INSPECTIONIAW AD/P68/42					1	H	7	2 	3O	3	O		A31EU   	1E10				 
1996111400035	19961114	00035	SW  	1996	11	14	AU960526         	1	19960313	G	5710		WING            			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					CENTRE WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTRE SECTION SEVERELY CORRODED - THE FOLLOWING ITEMS  NEEDED REPAIR: 1.PNO 210022-091 - WING RIB INBOARD FU	SELAGE ATTACHMENT - LH 2.  PNO 210022-901 - WING RIB INBOARD FUSELAGE ATTACHMENT - RH 3.PNO 210029-4 - WING RIB INBOARD 	UNDERCARRIAGE BAY  4.  PNO 210104-000 - HINGE ARM FLAP INBOARD5.PNO 210105-501 - HINGE ARM FLAP OUTBOARD 6.  PNO 210059-	007 - FITTING WING ATTACHMENT REAR SPAR - LH7.PNO 210059-007 - FITTING WING ATTACHMENT REAR SPAR - RH  8.  PNO 210011-00	0 - SPLICE PLATE SPAR CAP UPPER 9.PNO 210010-000 - SPLICE PLATE SPAR CAP LOWER 10. PNO 210054-505 - STUB SPAR ASSEMBLY11	. PNO 210000-111 - STRINGER SPAR WEB 12. PNO 210000-112 - STRINGER SPAR WEB 13. PNO 210020-007 - WEB REAR SPAR	1	L	7	1 	3O	3	O		2A3     	1E10				 
1996111400036	19961114	00036	SO  	1996	11	14	AU960527         	1	19960406	G	3010	36E966A	REGULATOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					ICE-RAIN PROTECT	LEAKING         	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 					RF1812					(AUS) RH DE-ICE SYSTEM PRESSURE REGULATOR LEAKING AIR						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996111400037	19961114	00037	SO  	1996	11	14	AU960528         	1	19960422	G	3230	12038594001	MODULE          			EMB   	120   	EMB120      	3260201	SO  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					120186					(AUS) LANDING GEAR CONTROL MODULE FAULTY						2	L	7	2 	4T			RT	A31SO   					 
1996111400038	19961114	00038	SO  	1996	11	14	AU960529         	1	19960428	G	8120	LW127996S116	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					TURBO SUPERCHRGR	DETERIORATED    	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) ENGINE LOST POWER DUE TO FAILURE OF HOSE BETWEEN AIRBOX PNO  LW-12799-6S116 AND DIFFERENTIAL CONTROLLER - STRATOFL	EX 193.4HOSE HAD DETERIORATED DUE TO HEAT FROM ADJACENT TURBOCHARGER					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996111400039	19961114	00039	SO  	1996	11	14	AU960530         	1	19960320	G	5753		FLAP            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					WING TE SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLAPS CORRODED IN AREA BETWEEN STEEL HINGE FITTINGS AND NOSERIBS AND SPARS						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996111400040	19961114	00040	SO  	1996	11	14	AU960531         	1	19960320	G	5711	62054	SPAR            	PIPER       	PA32        	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING REAR SPARS CORRODED IN AREA BENEATH STEEL FITTINGS AS REFERRED TO IN AD/PA28/40 AND AD/PA32/27 - THE CORROSIO	N WAS ONLYFOUND FOLLOWING REMOVAL OF THE FITTINGS					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996111400041	19961114	00041	CE  	1996	11	14	AU960532         	1	19960320	G	5343	15411211	FITTING         			CESSNA	182   	182E        	2072712	CE  	CONT  	O470  	O470R       	17026	SO  					ATTACH FITTING S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR FORGED ALUMINIUM ATTACHMENT FITTING CORRODEDON THE UPPER EDGE BENEATH THE FLOOR SHEETING						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1996111400042	19961114	00042	SO  	1996	11	14	AU960533         	1	19960320	G	5541	63544	RIB             	PIPER       	PA32        	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					RUDDER STRUCT SY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER BUTT RIB CORRODED BENEATH TORQUE TUBE STEEL PLATE						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1996111400043	19961114	00043	CE  	1996	11	14	AU960534         	1	19960429	G	3260		MICROSWITCH     			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					LG POSITION IND	FAULTY          	W				K				NONE                    				P			NO WARNING INDICATION     			LD	LANDING        	1			AU	S 							294632R			(AUS) LANDING GEAR MICROSWITCH ACTUATING ARM BROKEN OFF - WARNING HORN FAILED TO OPERATE AND AIRCRAFT LANDED WITH GEAR R	ETRACTED					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996111400044	19961114	00044	CE  	1996	11	14	AU960535         	1	19960429	G	2897		WIRE            			CESSNA	402   	402B        	207590P	CE  										FUEL INDICATION	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING TIP FUEL TANK CONTENTS WIRE WORN BY TIP TANK LOWER SKIN INNER SURFACE - WIRE WAS INADEQUATELY RESTRAINED AND 	CLAMPED					1	L	7	2 	3O			 	A7CE    					 
1996111400045	19961114	00045	CE  	1996	11	14	AU960536         	1	19960419	G	3260	1CH1066	SWITCH          	WESTERNHYD  	NLGACTUATOR 	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 					1409					(AUS) NOSE LANDING GEAR DOWNLOCK SWITCH FAULTY						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1996111400046	19961114	00046	SW  	1996	11	14	AU960537         	1	19960416	G	6230	471501841	PLATE           	BELL        	SWASHPLATE  	BELL  	47    	47G3B       	1181026	SW  										M/R MAST/SWASHPL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ASP20					(AUS) MAIN ROTOR SWASHPLATE CONTROL PLATE FORE/AFT CYCLIC INPUT HORN LUG CRACKED AND BROKEN ON LH SIDE						1	G	7	1 	3O				2H3     					 
1996111400047	19961114	00047	CE  	1996	11	14	AU960538         	1	19960328	G	8120		BEARING         	GARRTT      	TURBOCHARGER	CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  					TURBO SUPERCHRGR	FAILED          	W				K				NONE                    				R	K		PARTIAL RPM/PWR LOSS      	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) ENGINE TURBOCHARGER IMPELLER BEARING FAILED						1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996111400048	19961114	00048	CE  	1996	11	14	AU960539         	1	19960330	G	5720	50110231	FITTING         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH STUB WING ATTACHMENT FITTING CONTAINED EXFOLIATION CORROSION  - FURTHER CORROSION FOUND FOLLOWING REMOVAL OF TH	E FITTING					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996111400049	19961114	00049	CE  	1996	11	14	AU960540         	1	19960417	G	2510		SEAT BELT       			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					FLIGHT COMPARTME	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELTS USED AUTOMOTIVE HARDWARE WITH NON MIL-SPEC WEBBING -  UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1996121900099	19961219	00099	SO  	1996	12	19	AU960541         	2	19960328	G	8500		ENGINE          			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	ENGINE (RECIPROC	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							284712	EE2125A		(AUS) ENGINE FAILED - AIRCRAFT CRASHED - SUSPECT ENGINE STARVED OF FUEL DURING RH TURN						1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P25EA	 
1996121900100	19961219	00100	CE  	1996	12	19	AU960542         	1	19960222	G	3244		TIRE            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3AF34C	3AF34C74    	GL  	MAIN GEAR SYS	FOULED          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) RH MAIN LANDING GEAR TYRE FOULING ON AFT EDGE OF WHEEL WELL -  TYRE HAD BEEN RECENTLY FITTED						1	L	7	2 	3O				A25CE   		5	C	P22EA	 
1996121900101	19961219	00101	NE  	1996	12	19	AU960543         	2	19960308	G	7261		SEAL            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	T ENGINE OIL SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							785597			(AUS) LH ENGINE INTERNAL OIL LEAK DUE TO CARBON BUILDUP IN THE MIDFRAME ASSEMBLY - NO1 CARBON SEAL WORN						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1996121900102	19961219	00102	NM  	1996	12	19	AU960544         	1	19960206	G	3230	R291206EE0260T	HOSE            			BOEING	737   	737377      		NM  										LG EXT-RETRACT S	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CL	CLIMB          	1			AU	S 										(AUS) RH MAIN LANDING GEAR ACTUATOR UP HYDRAULIC HOSE BURST AT A POINT APPROXIMATELY MIDWAY ALONG ITS LENGTH - LOSS OF S	YSTEM 'A' HYDRAULICS					2	L	7	2 	4F			RT	A16WE   					 
1996121900103	19961219	00103	NE  	1996	12	19	AU960545         	2	19960318	G	7230		DAMPER          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	T ENG CMPRSR/FAN	BROKEN          	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 							785592			(AUS) RH ENGINE NO3 BEARING LOCKNUT INERTIA DAMPER BROKEN - METAL  CONTAMINATION OF ENGINE OIL SYSTEM						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1996121900104	19961219	00104	NE  	1996	12	19	AU960546         	2	19960415	G	7261		CHIP DETECTOR   			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	T ENGINE OIL SYS	CONTAM-METAL    	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		LD	LANDING        	1			AU	S 							785604			(AUS) RH ENGINE OIL SYSTEM CHIP DETECTOR CONTAMINATED WITH METAL						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1996121900105	19961219	00105	EU  	1996	12	19	AU960547         	1	19960429	G	3060	DS2336	FILTER          			FOKKER	F27   	F27MK50     		EU  										PROP/ROTOR AI-DI	SPARKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE DE-ICE WIRING LOOM RF FILTER WIRE RUBBING ON PROPELLER  SHAFT - SUSPECT WIRING LOOM TOO LONG - PERSONNEL/MA	INTENANCE ERROR					2	H	7	2 	4T			RT	A817    					 
1996121900106	19961219	00106	SO  	1996	12	19	AU960548         	1	19960218	G	2434	12872	BEARING         	PRESTOLITE  	ALTERNATOR  	PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	AC GENERATOR-ALT	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					12872					(AUS) ALTERNATOR REAR BEARING FAILED - BRUSHES WORN OUT						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1996121900107	19961219	00107	NM  	1996	12	19	AU960549         	1	19960429	G	7931	APT761000100D	TRANSMITTER     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ENG OIL IND SYS	FAULTY          	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 										(AUS) RH ENGINE OIL PRESSURE TRANSMITTER FAULTY						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996121900108	19961219	00108	SO  	1996	12	19	AU960550         	2	19960422	G	8520	646778	CONNECTING ROD  			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	R ENGINE POWER S	DISTORTED       	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 							211176			(AUS) RH ENGINE NO6 CYLINDER CONNECTING ROD BENT DUE TO HYDRAULIC  LOCK DUE TO EXCESSIVE FUEL IN CYLINDER						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1996121900109	19961219	00109	SO  	1996	12	19	AU960551         	1	19960328	G	3230	67748003	VALVE           			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	2D34C215    	GL  	LG EXT-RETRACT S	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR EMERGENCY EXTENSION VALVE LEAKING DUE TO FAULTY 'O' RING SEALS						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P7EA	 
1996121900110	19961219	00110	EA  	1996	12	19	AU960552         	2	19960329	G	8520	LW72877	TAPPET          	LYC         	CAMSHAFT    	PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	R ENGINE POWER S	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1097351A			(AUS) NO1 AND NO2 CYLINDER TAPPET BODIES PNO LW72877 SPALLED - CAMSHAFT PNO LW18840 FORWARD LOBE WORN						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
1996121900111	19961219	00111	SO  	1996	12	19	AU960553         	1	19960430	G	5712		RIB             			PIPER 	PA25  	PA25150     	7102503	SO  	LYC   	O320  	O320A2B     	41508	EA  	MCAULY	1A170	1A170GM     	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING RIBS AND STIFFENERS CONTAINED SEVERE EXFOLIATION  CORROSION AND CRACKING OF INBOARD TRAILING EDGE A	SSEMBLIES PNO 61217-000 AND PNO 61217-001 - CORROSION ALSO FOUND IN NUMEROUS WING WALK RIBS PNO 61224-000 - WING SKINS P	NO 61158-010, PNO 61158-011, PNO 61329-000 AND PNO 61329-001 - RH WING INTERNAL  STRUT PNO 61101-000 CONTAINED SEVERE CO	RROSION IN AREA WHERE THE REAR SPAR ATTACHMENT FITTING IS RIVETTED TO THE STRUT - AIRCRAFT WAS CONSTRUCTED IN 1959 AND I	S USED FOR AGRICULTURAL SPRAYING		1	H	7	1 	3O	3	O		EXPA1H71	E274	5	N	P857	 
1996121900112	19961219	00112	EU  	1996	12	19	AU960554         	1	19960221	G	7712		CTOT SYSTEM     			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	POWER CONTROL SY	INOPERATIVE     	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							785465785	DRG143990DA		(AUS) LH ENGINE CTOT (CONSTANT TORQUE ON TAKE-OFF SYSTEM) INOPERATIVE  DUE TO INTERMITTENT ELECTRICAL PROBLEM						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
1996121900113	19961219	00113	CE  	1996	12	19	AU960555         	1	19960420	G	3230	9880710116530004	SWITCH          			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR MOTOR PRESSURE SWITCH WIRE BROKEN AT SOLDERED JOINT - FAILURE WAS COVERED BY HEAT SHRINK MAKING IT DI	FFICULT TODETECT					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1996121900114	19961219	00114	CE  	1996	12	19	AU960556         	1	19960423	G	2434	5061369	DIODE           		ALTERNATOR  	CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C505   	GL  	DC GENERATOR-ALT	FAULTY          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			118  		5061369					(AUS) LH ALTERNATOR DIODES LOOSE AND BROKEN						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1996121900115	19961219	00115	EU  	1996	12	19	AU960557         	1	19960415	G	3211	NB40075	BRACKET         		RHMLG       	BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR BRACKET CRACKED AND BROKEN						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1996121900116	19961219	00116	SO  	1996	12	19	AU960558         	1	19960502	G	6120	B3804T	SPRING          	HARTZL      	GOVERNOR    	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROP CNTRL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			6    		B3804T					(AUS) PROPELLER GOVERNOR SPEEDER SPRING FAILED						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1996121900117	19961219	00117	SO  	1996	12	19	AU960559         	1	19960404	G	7120	8621202V	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	ENGINE MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ENGINE MOUNT FRAMES CRACKED						1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P9EA	 
1996121900118	19961219	00118	WP  	1996	12	19	AU960560         	2	19960426	G	7260	310183616	HOUSING         	GARRTT      	TPE33110UA  	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	T ENG AUX DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2870 		P54299		P54299			(AUS) ENGINE ACCESSORY HOUSING CRACKED IN GUSSET CASTING ADJACENT TO THE RH ENGINE MOUNTING PAD - CRACK LENGTH 25.4MM (1	IN)					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
1996121900119	19961219	00119	SW  	1996	12	19	AU960561         	1	19960131	G	5340		RIVET           			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ATTACH FITTING S	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER RH ATTACHMENT BRACKET RIVETS (8OFF) SHEARED						1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
1996121900120	19961219	00120		1996	12	19	AU960562         	4	19960425	G	3140	6226190204	COMPUTER        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	CENTRAL COMPUTER	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					2084					(AUS) NO2 AHRS COMPUTER FAULTY - BENCH CHECK COULD FIND NO FAULTS						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
1996121900121	19961219	00121	SO  	1996	12	19	AU960563         	1	19960420	G	3230	2060500005	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					LG EXT-RETRACT S	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					344					(AUS) NOSE LANDING GEAR ACTUATOR OUT OF ADJUSTMENT						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996121900122	19961219	00122	SO  	1996	12	19	AU960564         	1	19960501	G	3211	9529902	SIDE BRACE      			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR SIDE BRACE STUDS CRACKED IN RADIUS - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/	PA34/46					1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920	 
1996121900123	19961219	00123	NM  	1996	12	19	AU960565         	1	19960426	G	5753	65B15946	FITTING         			BOEING	747   	747238B     	1384828	NM  										WING TE SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SYSTEM NO2 TRACK AFT SUPPORT FITTING FRACTURED AT FASTENER  BOLT HOLE - CRACKING WAS INITIATED BY CORROSION A	T THE FASTENER BOLT HOLE - AFT FLAP DRIVE ROD PNO 65B15651-3 ALSO FOUND BENT					2	L	7	4 	4F				A20WE   					 
1996121900124	19961219	00124	CE  	1996	12	19	AU960566         	1	19960417	G	3210	10581002367	A FRAME         			BEECH 	76    	76          	1153005	CE  										MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR ASSEMBLY 'A' FRAME CRACKED IN WELDED AREA AND THE CORROSION TREATMENT HOLE - FOUND DURING INS	PECTION IAW AD/B76/18 AND SB 2361					1	L	7	2 	3O				A29CE   					 
1996121900125	19961219	00125	EU  	1996	12	19	AU960567         	1	19960327	G	5320	TB1021029165	STIFFENER       			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE STIFFENER LH CRACKED IN AREA OF TORQUE TUBE SUPPORT REAR ANCHOR NUT HOLE - FOUND DURING INSPECTION IAW SO	CATA 10-77-53					1	L	7	1 	30	3	O	NT	A51EU   	E286	5	C	P920	 
1996121900126	19961219	00126	CE  	1996	12	19	AU960568         	1	19960429	G	2710	1260505187	CABLE           			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	AILERON CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					REARENGINE		286357R	941620		(AUS) RH AILERON/RUDDER INTERCONNECT CABLE FRAYED DUE TO CHAFING ON  EACH END OF THE STEEL TUBE COVERING THE CABLE						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1996121900127	19961219	00127	EU  	1996	12	19	AU960569         	1	19960302	G	5210	254ANSSNO04	CYLINDER        			AIRBUS	320   	A320212     		EU  										CREW-PASS DOOR S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					254ANSSNO					(AUS) L1 DOOR ASSIST CYLINDER CORRODED IN AREA OF MANIFOLD CONNECTED TOTHE GAUGE - CORROSION RAN RADIALLY AROUND THE END	 FACE - LOSS OF CYLINDER PRESSURE					2	L	7	2 	4F			RT	A28NM   					 
1996121900128	19961219	00128	NM  	1996	12	19	AU960570         	1	19960316	G	3213	19335LH193	TRUNNION        			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					MAIN GEAR SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					19335LH					(AUS) LH AND RH MAIN LANDING GEAR OUTER CYLINDER AFT TRUNNIONS CONTAINED UNACCEPTABLE CORROSION DURING ULTRASONIC AND ED	DY CURRENT INSPECTIONS IAW ER B76-32-10-24 - RH OUTER CYLINDER  CORRODED IN AREA OF JOURNAL CHAMFER AT THE 2 O'CLOCK POS	ITION -LH TRUNNION CORRODED IN AREA OF INBOARD CROSS BOLT HOLE AT THE 6 O'CLOCK POSITION - SUSPECT CAUSED BY CRACKING OF	 THE FILLET SEAL ALLOWING MOISTURE INGRESS			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1996121900129	19961219	00129	GL  	1996	12	19	AU960571         	2	19960401	G	7320	6876376	PIPE            			GOVT  	N22   	N22B        	3880102	WP  	ALLSN 	250B  	250B17B     	03010	GL  	HARTZL	HCA3V	HCA3VF7     	GL  	ENG,FUEL CONTROL	CRACKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							880049	DS95		(AUS) COMPRESSOR SCROLL TO PC FILTER INLET PIPE CRACKED ACROSS FLARE AND PARTIALLY BLOCKED WITH CARBON						1	H	7	2 	3T	3	T		A7PC    	E10CE	5	C	P6EA	 
1996121900130	19961219	00130	EU  	1996	12	19	AU960572         	1	19960422	G	3060	9682913221	TIMER SWITCH    			PILATS	PC12  	PC12        	7090550	EU  										PROP/ROTOR AI-DI	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U0029					(AUS) PROPELLER DE-ICE SYSTEM TIMER FAULTY - TIMER NOT SWITCHING BETWEEN BLADES - TIMER IS PERMANENTLY POWERED EVEN WHEN	 SWITCHED OFF					1	L	7	1 	3T			RT	A78EU   					 
1996121900131	19961219	00131	EU  	1996	12	19	AU960573         	1	19960401	G	2750	9787320012	WARNING UNIT    		FDWU95      	PILATS	PC12  	PC12        	7090550	EU  										FLAP DRIVE SYS	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 					3326					(AUS) FLAP DRIVE WARNING UNIT FAULTY						1	L	7	1 	3T			RT	A78EU   					 
1996121900132	19961219	00132	EU  	1996	12	19	AU960574         	1	19960428	G	5720	109	WINGLET         			PILATS	PC12  	PC12        	7090550	EU  										WING TIP SYS	DAMAGED         	W				K				NONE                    				C			F.O.D.                    			TX	TAXI/GRND HDL  	1			AU	S 					109					(AUS) LH WINGLET STRUCK RUDDER OF A STATIONARY PC-12 (VH-FMP) DURING TAXI - WINGLET DAMAGED - DAMAGE ALSO TO UPPER RUDDE	R HINGE AND RUDDER TRIM TAB ACTUATOR SUPPORT OF THE STATIONARY AIRCRAFT					1	L	7	1 	3T			RT	A78EU   					 
1996121900133	19961219	00133	CE  	1996	12	19	AU960575         	1	19960504	G	5312	FS15576	BULKHEAD        			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD LOCATED AT FS 155.76 CRACKED AT LOWER RH CORNER- CRACK EXTENDED FOR THE FULL WIDTH OF THE ANGLE						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1996121900134	19961219	00134	GL  	1996	12	19	AU960576         	1	19960425	G	3222	76053	FORK            			NAMER 	NA260 	T28B        	6402506	GL  						HAMSTD	43D	43D50       	NE  	NOSE-TAIL GEAR S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FORK CRACKED IN TWO PLACES:  1. IN THE RADIUS OF THE UPPER FORK SWIVEL SHAFT2. IN THE RADIUS ADJ	ACENT TO THE FORK OF THE NLG WHEEL SPINDLE(AXLE)FOUND DURING MAGNETIC PARTICLE INSPECTION (MPI)					1	L	7	1 	4R			RT	EXPA1L71		6	C	P8879	 
1996121900135	19961219	00135	SO  	1996	12	19	AU960577         	2	19960329	G	8530	646100	CYLINDER        			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	R ENG CYL SEC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			576  				239180H			(AUS) NO3 CYLINDER EXTENSIVELY CRACKED IN THE AREA AT THE TOP OF THE CYLINDER BORE WITH A TOTAL OF THREE CRACKS						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1996121900136	19961219	00136	NE  	1996	12	19	AU960578         	1	19960429	G	5210	7620903902107	LATCH           			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					CREW-PASS DOOR S	UNLOCKED        	W				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) CABIN SLIDING DOOR OPENED IN FLIGHT - INVESTIGATION FOUND THAT EITHER THE DOOR LATCH WAS NOT FULLY LOCKED OR A PAS	SENGER OPERATED THE LATCH DURING FLIGHT					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
1996121900137	19961219	00137	GL  	1996	12	19	AU960579         	3	19960502	G	6110	692935	O-RING          	MCAULY      	3AF32C75LW  	BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY S	WRONG  PART     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					692935			692935		(AUS) PROPELLER BLADE RETENTION NUT 'O' RINGS WERE THE INCORRECT TYPE  CAUSING EXCESSIVE BINDING ON FERRULE - PERSONNEL/	MAINTENANCE ERROR - UNAPPROVED PART					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1996121900138	19961219	00138	EA  	1996	12	19	AU960580         	2	19960417	G	8520	LW1883785	CAMSHAFT        	LYC         	O320B2C     	ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					R ENGINE POWER S	WRONG PART      	W				K				NONE                    				E	R	W	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	INADEQUATE Q C            	NR	NOT REPORTED   	1			AU	S 			198  		RL1220239A		RL1220239A			(AUS) CAMSHAFT SUSPECT FAULTY - COMPARISON WITH A NEW ITEM FOUND THAT  THE CAM PROFILE WAS DIFFERENT - INVESTIGATION FOU	ND THAT THE CAMSHAFT WAS MARKED IN SMALL LETTERS WITH THE PNO LW18837-85 BUT WAS ALSO MARKED WITH THE PNO 76097 WHICH IS	 THE PART NUMBER FOR INSTALLATION IN FIXED WING APPLICATIONS - THERE IS ALSO EVIDENCE THAT THE CAMSHAFT HAS BEEN REGROUN	D - UNAPPROVED PART -PERSONNEL/MAINTENANCE ERROR			1	G	7	1 	3O	3	O		H10WE   	E274				 
1996121900139	19961219	00139	CE  	1996	12	19	AU960581         	1	19960417	G	7603	AH37A	BOLT            		NUT         	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	POWER CONTROL SY	SEPARATED       	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 							604164			(AUS) ENGINE THROTTLE CONTROL UNIT ARM PNO 5055002-1 ATTACHMENT NUT PNOMS21044N3 AND BOLT PNO AH37A SEPARATED FROM ARM A	ND WERE FOUND ONTHE FLOOR OF THE ENGINE BAY - THE NUT WAS OF THE METAL LOCK TYPE AND INVESTIGATION FOUND THAT IT COULD B	E SPUN ONTO THE BOLT BY HAND - PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
1996121900140	19961219	00140	EU  	1996	12	19	AU960582         	1	19960429	G	5755	A16053410	HINGE           			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					WING SPOILER SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					SH47					(AUS) RH WING OUTBOARD LIFT DUMPER NO5 PANEL INBOARD HINGE LUG CRACKED						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1996121900141	19961219	00141		1996	12	19	AU960583         	1	19960421	G	7160	365A54103301	AIR INTAKE      								TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					ACFT,ENG AIR INT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							275			(AUS) ENGINE INTAKE FLANGE LOWER PORTION BROKE AWAY AND ENTERED THE  ENGINE CAUSING DAMAGE TO THE COMPRESSOR											3	U			E19EU				 
1996121900142	19961219	00142	SO  	1996	12	19	AU960584         	2	19960425	G	8530	648045	PISTON          			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					R ENGINE CYLINDE	DAMAGED         	W				K				NONE                    				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			AU	S 			1005 				552607			(AUS) NO2 CYLINDER PISTON SEVERELY ERODED AND HOLED IN THE AREA OF THE OIL RING GROOVE - METAL CONTAMINATION OF OIL SYST	EM - NO4CRANKSHAFT BEARING ALSO TURNED					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1996121900143	19961219	00143	CE  	1996	12	19	AU960585         	1	19960424	G	7603	1005241771	LEVER           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	POWER CONTROL SY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH FUEL CONTROL LEVER FAILED IN AN AREA LEVEL WITH THE PEDESTAL  QUADRANT - LEVER EXHIBITED ADVANCED WEAR IN AREA 	OF FAILURE -FURTHER INVESTIGATION SHOWED SIMILAR WEAR IN THE RH LEVER -  SUSPECT LEVER HAD BEEN BENT AND RESTRAIGHTENED 	AT ONE TIME WHICH CAUSED CRACKING AND EVENTUAL FAILURE				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1996121900144	19961219	00144	CE  	1996	12	19	AU960586         	1	19960506	G	3260	ICH1066	MICROSWITCH     	CESSNA      	MLGACTUATOR 	CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	LG POSITION IND	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		NR	NOT REPORTED   	1			AU	S 					3747					(AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH FAULTY						1	L	7	2 	3T	3	T	RT	A7CE    	E4EA	6	C	P15EA	 
1996121900145	19961219	00145	SO  	1996	12	19	AU960587         	1	19960504	G	3230	1159H200116	O-RING          			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     		EU  					LG EXT-RETRACT S	DETERIORATED    	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR UP MANIFOLD TO PIPE PNO 1159H-40016-238 LGU6 UNION  'O' RING SEAL DETERIORATED DUE TO SKYDROL CONTAMI	NATION - THEREWAS ALSO EVIDENCE OF THE MANIFOLD HAVING BEEN INCORRECTLY  MASKED/PAINTED DURING MANUFACTURE PREVENTING CO	RRECT SEATING OFTHE UNION AND THE SQUEEZING OUT OF THE 'O' RING - LOSS OF  HYDRAULIC FLUID - PERSONNEL/MAINTENANCE ERROR	 - MANUFACTURINGERROR			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
1996121900146	19961219	00146	CE  	1996	12	19	AU960588         	1	19960320	G	5720	NAS15237M	BOLT            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING BOLTS CORRODED DUE TO COVERING OF BARIUM CHROMATE						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1996121900147	19961219	00147	CE  	1996	12	19	AU960589         	1	19960401	G	5711		SPAR            			CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING CONTAINED SEVERE EXFOLIATION CORROSION IN THE UPPER  FORWARD SPAR EXTRUSIONS, EXFOLIATION CORROSION AND CR	ACKING IN THE MAIN SPAR AND CORROSION IN THE INNER SPAR WEB - CORROSION  APPEARS TO HAVE BEEN PREVIOUSLY TREATED WITH LP	S TYPE COMPOUND				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1996121900148	19961219	00148	EA  	1996	12	19	AU960590         	2	19960430	G	7261		CHIP DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE ENGINE O	CONTAMINATED    	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 							80713			(AUS) LH ENGINE CHIP DETECTOR ILLUMINATED - INSPECTION FOUND A VERY  FINE METALLIC HAIR ACROSS THE PROBES - AFTER CLEANI	NG AND REINSTALLING IAW PRATT AND WHITNEY MAINTENANCE MANUAL THE  AIRCRAFT WAS OPERATED FOR 15 FLIGHT HOURS AND THE CHIP	 DETECTORREINSPECTED WITH NO CONTAMINATION EVIDENT				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1996121900149	19961219	00149	CE  	1996	12	19	AU960591         	1	19960509	G	2612	302158	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECT SYS	CONTAM-WATER    	W				K				NONE                    				F	N		FLT CONT AFFECTED         	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 										(AUS) RH ENGINE FIRE DETECTOR ACTIVATED DUE TO MOISTURE ON THE SENSORS - FIRE BOTTLE DISCHARGED						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1996121900150	19961219	00150	EU  	1996	12	19	AU960592         	1	19960507	G	3260	A204D14	SCREW           	ROTOL       	200921732   	STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  	HARTZL	HCB5M	HCB5MP3     	GL  	LG POSITION IND	LOOSE           	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) NOSE LANDING GEAR ABUTTMENT PLATE OUT OF ADJUSTMENT						2	H	7	2 	4T	4	T		A41EU   	E4EA	6	C	P44GL	 
1996121900151	19961219	00151	NM  	1996	12	19	AU960593         	1	19960422	G	3260		INDICATION SYS  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LG POSITION IND	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) NOSE LANDING GEAR INDICATION SYSTEM FAULTY - EXTENSIVE INVESTIGATION COULD FIND NO FAULT WITH THE SYSTEM						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996121900152	19961219	00152	NM  	1996	12	19	AU960594         	1	19960402	G	7710		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ENG PWR IND SYS	FLUCTUATES      	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) RH ENGINE EXPERIENCED TORQUE FLUCTUATIONS - EXTENSIVE  INVESTIGATION COULD FIND NO FAULTS						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996121900153	19961219	00153	CE  	1996	12	19	AU960595         	1	19960429	G	2730	040010762	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	ELEVATOR CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								LCO29		(AUS) ELEVATOR CONTROL CABLES WORN AND FRAYED - AIRCRAFT IS USED FOR AEROBATICS						1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1996121900154	19961219	00154	EA  	1996	12	19	AU960597         	2	19960507	G	8530		VALVE GUIDE     								LYC   	O320  	O320D1A     	41508	EA  					R ENGINE CYLINDE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1620439A			(AUS) ENGINE CYLINDER EXHAUST VALVE GUIDES (3OFF) EXCESSIVELY WORN - VALVE GUIDES WERE WITHIN SERVICE LIMITS BUT WOULD N	OT LAST TO THENEXT TOP END OVERHAUL										3	O			E274				 
1996121900155	19961219	00155	WP  	1996	12	19	AU960598         	2	19960501	G	7210	31039401	SUPPORT         	GARRTT      	TPE331      	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE REDUCTION	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 					P70144		P70144			(AUS) ENGINE TORQUE RING SUPPORT ASSEMBLY FAULTY						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1996121900156	19961219	00156	CE  	1996	12	19	AU960599         	1	19960116	G	2823		VALVE           			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	FUEL DISTRBUTION	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FUEL SHUTOFF VALVE FAULTY - PERSONNEL/MAINTENANCE ERROR						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1996121900157	19961219	00157	SO  	1996	12	19	AU960600         	1	19960406	G	3220	6708403	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					NOSE-TAIL GEAR S	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG BRACE ATTACHMENT TRUNNION DAMAGED - ALLOY CASTING APPEARS TO BE CRYSTALLISED AT THE DRAG BR	ACE ATTACHMENTPOINT - SUSPECT CAUSED BY LOCALISED HEATING TO REMOVE/REPLACE  BUSHES - PERSONNEL/MAINTENANCE ERROR - UNAP	PROVED PROCEDURE				1	L	7	2 	3O	3	O		A19S0   	E286				 
1996121900158	19961219	00158	CE  	1996	12	19	AU960601         	1	19960424	G	5343	MS2047069	RIVET           	CESSNA      	SUPPORT     	CESSNA	182   	182Q        	2072732	CE  						MCAULY	2A34C	2A34C203    	GL  	ATTACH FITTING S	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR STRUT SUPPORT LOWER ATTACHMENT RIVET (1OFF) SHEARED - DURING REPLACEMENT OF THE RIVET THE HEA	DS OF THE RIVETSEACH SIDE OF THE SHEARED RIVET ALSO FELL OFF					1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1996121900159	19961219	00159	CE  	1996	12	19	AU960602         	1	19960510	G	6120	B3529	LINK            	MCAULY      	D3A32C88M   	CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY S	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			390  		743799		743799			(AUS) PROPELLER NO1 BLADE PITCH CHANGE LINK BROKEN - FURTHER INSPECTION FOUND INCORRECT BLADE RETENTION NUT 'O' RINGS FI	TTED - PROPELLER IS GREASE FILLED WITH OIL FILLED PROPELLER 'O' RINGS FITTED TO UNMODIFIED GROOVES - PERSONNEL/MAINTENAN	CE ERROR - UNAPPROVEDPART				1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P21EA	 
1996121900160	19961219	00160	EU  	1996	12	19	AU960603         	1	19960314	G	5320	40875	RIB             		40876       	GROB  	G115  	G115C       	1660303	EU  						SNSNCH	72C	72CK        	EA  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH FLOOR RIBS PNO 40875 AND PNO 40876 CRACKED - CRACKS  START IN THE RIB ANGLE AND FOLLOW NEAR THE EDGE OF 	THE FRONT FLOOR FRAME PNO 40882 - HONEYCOMB CORES ALSO PARTLY SEPARATED AT THE CRACKS - SUSPECT CAUSED BY HARD LANDINGS					1	L	7	1 	3O			NT	A57EU   		5	N	P9045	 
1996121900161	19961219	00161	CE  	1996	12	19	AU960604         	1	19960424	G	5312	07125033	BULKHEAD        			CESSNA	182   	182Q        	2072732	CE  						MCAULY	2A34C	2A34C203    	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD CRACKED IN AREA OF LOWER CURVED SECTION - CRACKLENGTH 6.35MM (0.25IN)						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1996121900162	19961219	00162	NM  	1996	12	19	AU960605         	1	19960509	G	5510	348AR	FAIRING         			BOEING	767   	767284      		NM  	PWA   	4056  	PW4056      		NE  					HORZ STAB SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH HORIZONTAL STABILISER TIP DAMAGED BY COLLISION WITH TOWED 747 AIRCRAFT - DAMAGE TO THE FOLLOWING AREAS:- 1. END	 TIP CLOSURE FAIRING FIBREGLASS PANEL SEVERED  2. LOWER FIBREGLASS PANEL SEVERED AT OUTBOARD EDGE 3. END CLOSURE TIP ASS	EMBLY TORN AND DISTORTED TOWING ACCIDENT - PERSONNEL/MAINTENANCE ERROR				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
1996121900163	19961219	00163	SO  	1996	12	19	AU960606         	1	19960509	G	2612	1734361450F	FIRE DETECTOR   			GRUMAN	G73   	G73T        		SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION S	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FIRE DETECTOR FAULTY - SUSPECT DUE TO SALT/WATER/OIL  CONTAMINATION						1	H	7	2 	3R	4	T		A783    	E4EA	6	C	P15EA	 
1996121900164	19961219	00164	SO  	1996	12	19	AU960607         	1	19960429	G	3211	20829000	STUD            			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1D5    	41532	EA  	MCAULY	2D36C	2D36C28     	GL  	MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR SIDE BRACE STUD CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA24/44						1	L	7	1 	3O	3	O		1A15    	E295	5	C	P901	 
1996121900165	19961219	00165	CE  	1996	12	19	AU960608         	1	19960426	G	3260		INDICATOR       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	LG POSITION IND	BROKEN WIRE     	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) RH MAIN LANDING GEAR INDICATOR LAMP WIRE BROKEN						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1996121900166	19961219	00166	SO  	1996	12	19	AU960612         	1	19960501	G	3230	4198300	HOOK            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LG EXT-RETRACT S	SEIZED          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK HOOK STIFF ON PIVOT BOLT PNO AN5-46- AIRCRAFT OPERATES FROM UNPREPARED STRIPS IN A S	ALT LADEN ENVIRONMENT WITH HIGH HUMIDITY					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1996121900167	19961219	00167	SO  	1996	12	19	AU960613         	2	19960502	G	8500		ENGINE          			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE (RECIPROC	LOW POWER       	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							567451			(AUS) ENGINE POWER LOSS - INVESTIGATION COULD FIND NO CAUSE FOR THE  PROBLEM - A SMALL AMOUNT OF WATER WAS FOUND IN THE 	LH FUEL TANK					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1996121900168	19961219	00168	EU  	1996	12	19	AU960618         	1	19960317	G	2120	14SNO009	VALVE           			AIRBUS	320   	A320212     		EU  										AIR DISTRIBUTION	FAULTY          	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 					14SNO00					(AUS) SKIN AIR OUTLET VALVE ACTUATOR FAULTY - FURTHER INVESTIGATION  FOUND AN OPEN CIRCUIT COMMUTATOR BAR ON THE CLOSED 	DRIVE END					2	L	7	2 	4F			RT	A28NM   					 
1996121900169	19961219	00169	EU  	1996	12	19	AU960619         	1	19960429	G	2520	833455	DIAPHRAGM       			AIRBUS	320   	A320212     		EU  										PASSENGER COMPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ECONOMY PASSENGER SEAT PAN DIAPHRAGMS (20OFF) CRACKED IN AREA  BELOW RIVET LINE ATTACHING DIAPHRAGM TO REAR TUBULA	R SEAT BEAM					2	L	7	2 	4F			RT	A28NM   					 
1996121900170	19961219	00170	SO  	1996	12	19	AU960620         	2	19960510	G	8530		PISTON RING     			CESSNA	182   	182E        	2072712	CE  	CONT  	O470  	O470R       	17026	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	R ENGINE CYLINDE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							987337R			(AUS) INCORRECT PISTON RING SETS FITTED TO ALL PISTONS - PNO 632932  PISTONS FITTED WHICH SHOULD HAVE RECTANGULAR TOP RI	NGS AS PER SB M91-4 - PISTONS WERE FITTED WITH TAPERED RINGS - DAMAGE TO PISTONS AND MINOR SCORING TO CYLINDERS - VALVE 	SEATS APPEAR TO BEINCORRECTLY CUT - 3 PISTON PINS HAVE LOOSE PLUGS - NO1 CYLINDER  HAS VERY DEEP SCORING FROM PREVIOUS H	ONING - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR			1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P920	 
1996121900171	19961219	00171	CE  	1996	12	19	AU960621         	1	19960508	G	5311		RIB             			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE RIB LOCATED AT STN 81 IN AREA OF REAR SEAT FORWARD  ATTACHMENT NUTS CRACKED LONGITUDINALLY IN SEVERAL PLA	CES - CRACK LENGTHS 50.8MM TO 76.2MM (2IN TO 3IN)					1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1996121900172	19961219	00172	NM  	1996	12	19	AU960622         	1	19960513	G	2434	948F4582	GENERATOR       			BOEING	737   	737476      		NM  										DC GENERATOR-ALT	FAULTY          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 					ZG10586					(AUS) NO1 GENERATOR FAILED AND DROPPED OFF LINE - INTERMITTENT APU DELAY OFF SYSTEM						2	L	7	2 	4F			RT	A16WE   					 
1996121900173	19961219	00173	SO  	1996	12	19	AU960623         	2	19960501	G	8530	629404	EXHAUST VALVE   	CONT        	O200A       	CESSNA	150   	A150M       	2071831	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	R ENGINE CYLINDE	SEIZED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							252880			(AUS) EXHAUST VALVE STICKING IN VALVE GUIDE DUE TO CARBON BUILDUP						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1996121900174	19961219	00174	NE  	1996	12	19	AU960624         	2	19960509	G	7240		LINER           	RROYCE      	RB211524G   						RROYCE	RB211 	RB211524G19 		NE  					T ENG BURNER SEC	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE COMBUSTION LINER HEAD SECTION BREAKING UP - FOUND DURING  BORESCOPE INSPECTION IAW AD/RB211/19A1 AND ROLLS 	ROYCE SERVICE BULLETIN RB211-72-B482										4	F			E30NE				 
1996121900175	19961219	00175	CE  	1996	12	19	AU960625         	1	19960502	G	3260	404EN16	SWITCH          			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LG POSITION IND	FAILED          	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH INTERNAL FAILURE						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997010200026	19970102	00026	NE  	1997	1	2	AU960626         	2	19960507	G	8550	827	SEAL            	PWA         		DOUG  	DC4   	C54E        	3021530	WP  	PWA   	R2000 	2SD13G      	52021	NE  	HAMSTD	23E	23E50       	NE  	R ENGINE INT OIL	FAILED          	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 					P107816		P107816			(AUS) NO4 ENGINE OIL SYSTEM NOSE SCAVENGE SYSTEM PIPE UNION SEAL FAILED- LOSS OF ENGINE OIL						2	L	7	4 	4R	4	R		A762    	E230	6	C	P603	 
1996121900176	19961219	00176	CE  	1996	12	19	AU960627         	1	19960502	G	2121	1013841001	BLOWER          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AIR DISTRIBUTION	FAULTY          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 					1100ECH					(AUS) AIRCONDITIONING SYSTEM FORWARD EVAPORATOR VENT BLOWER FAN FAULTY - SUSPECT BURNT OUT CIRCUIT						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997010200027	19970102	00027	NE  	1997	1	2	AU960628         	2	19960503	G	7414	SF14RN	MAGNETO         			DOUG  	DC4   	C54E        	3021530	WP  	PWA   	R2000 	R2000*      	52023	NE  	HAMSTD	23E	23E50       	NE  	NR 3&4 ENG	CONTAM-WATER    	W				K				NONE                    				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 							P108363P107			(AUS) NO3 AND NO4 ENGINE MAGNETOS CONTAMINATED WITH MOISTURE						2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603	 
1996121900177	19961219	00177	CE  	1996	12	19	AU960629         	1	19960503	G	2120	5055434	VALVE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AIR DISTRIBUTION	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					1619					(AUS) RH BLEED AIR BYPASS VALVE FAULTY - INVESTIGATION FOUND VALVE BUTTERFLY DAMAGED DUE TO A LOOSE SECURING SCREW ALLOW	ING THE PLATE TO ROTATE OUT OF ALIGNMENT WITH THE VALVE BORE					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1996121900178	19961219	00178	CE  	1996	12	19	AU960630         	1	19960502	G	2610		DETECTOR        			BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION S	CONTAM-WATER    	W				K				NONE                    				F	B	N	FLT CONT AFFECTED         	SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             	DE	DESCENT        	1			AU	S 										(AUS) LH ENGINE FIRE DETECTION SYSTEM CONTAMINATED WITH WATER WHEN FLYING THROUGH HEAVY RAIN - FALSE FIRE WARNING CAUSED	 ENGINE TOBE SHUT DOWN AND FIRE BOTTLE OPERATED					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
1996121900179	19961219	00179	SW  	1996	12	19	AU960631         	1	19960510	G	2120	880276	PIPE            			GULSTM	690TP 	690         	0141720	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	CABIN PRESSURE C	CRACKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) AIRCONDITIONING BLEED AIR SYSTEM SUSPECT LEAKING AT CONNECTION - AD/AC/95 HAD BEEN CARRIED OUT TWO MONTHS PREVIOUS	LY -INVESTIGATION FOUND THAT BLEED AIR LINE PNO 880276 WAS CRACKED ATTHE BASE OF THE FLARE WHERE IT CONNECTS TO THE VALV	E ASSEMBLY PNO880228-1				1	H	7	2 	3T				2A4     		6	C	P15EA	 
1996121900180	19961219	00180	CE  	1996	12	19	AU960632         	1	19960505	G	2610		DETECTOR        			BEECH 	99    	C99         	1154006	CE  	PWA   	PT6   	PT6A36      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION S	CONTAM-WATER    	W				E				ENGINE SHUTDOWN         				F	B	N	FLT CONT AFFECTED         	SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             	DE	DESCENT        	1			AU	S 										(AUS) RH ENGINE FIRE WARNING SYSTEM CONTAMINATED WITH WATER WHEN FLYINGTHROUGH HEAVY RAIN - FALSE FIRE WARNING CAUSED EN	GINE TO BE SHUT DOWN AND FIRE BOTTLE OPERATED - DURING REPLACEMENT OF FIRE BOTTLEIT WAS FOUND THAT THE BOTTLE DID NOT DI	SCHARGE				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
1996121900181	19961219	00181	CE  	1996	12	19	AU960633         	1	19960418	G	5312	0713608	BULKHEAD        	CESSNA      	182P        	CESSNA	182   	182P        	2075816	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					61428					(AUS) FORWARD DOORPOST BULKHEAD CRACKED AT RELIEF NOTCHES ON BOTH LH AND RH SIDES - CRACK LENGTH 7MM (0.275IN)						1	H	7	1 	3O			NT	TA13    					 
1996121900182	19961219	00182	GL  	1996	12	19	AU960634         	2	19960504	G	7261	890274	CHIP DETECTOR   	ALLSN       	250C30S     	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					TURBINE ENGINE O	CONTAM-METAL    	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 					890274		890274			(AUS) ENGINE CHIP DETECTOR CONTAINED A FINE SLIVER OF METAL - CHIP DETECTOR WAS CLEANED AND AN ENGINE SERVICEABILITY CHE	CK WASPERFORMED - NO FURTHER CONTAMINATION WAS FOUND AND AIRCRAFT  RETURNED TO SERVICE					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996121900183	19961219	00183	EU  	1996	12	19	AU960635         	1	19960418	G	5730		SKIN            			BNORM 	BN2MK3	BN2AMK3     	1520203	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	OUTER WING SYS	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING INTERIOR SKIN DAMAGED IN AREA ADJACENT TO REAR WING  ATTACHMENT DUE TO ANGLE GRINDER DIGGING INTO AND THRO	UGH INTERIORSKIN - FOUND DURING INSPECTION IAW AD/BNT/17-2 - PERSONNEL/MAINTENANCE ERROR					1	H	7	3 	3O	3	O		A29EU   	E295	5	C	P9EA	 
1996121900184	19961219	00184	SO  	1996	12	19	AU960636         	1	19960322	G	2810		FUEL TANK       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	FUEL STORAGE SYS	EMPTY           	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE SURGED DUE TO LACK OF FUEL						1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
1996121900185	19961219	00185	SO  	1996	12	19	AU960637         	1	19960515	G	3230	1217222123	HOSE            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LG EXT-RETRACT S	RUPTURED        	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK HOSE RUPTURED - LOSS OF HYDRAULIC  FLUID						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1996121900186	19961219	00186	WP  	1996	12	19	AU960638         	2	19960129	G	7250	30747553	BLADE           			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					TURBINE SECTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P97270			(AUS) NO1 ENGINE THIRD STAGE LOW PRESSURE TURBINE BLADE SHROUD TIP SEPARATED - MINOR DAMAGE TO OTHER LP TURBINE BLADES -	 THIS DEFECTWAS RECEIVED FROM 34 SQN RAAF AND IS FOR INFORMATION ONLY					2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
1996121900187	19961219	00187	SO  	1996	12	19	AU960639         	1	19960515	G	2910	MS287785	SEAL            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MAIN HYD SYS	DISTORTED       	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RH MAIN LANDING GEAR DOOR DROPPED INTO AIRFLOW - INVESTIGATION FOUND PRESSURE SIDE HYDRAULIC SERVICE COUPLING LEAK	ING UNDER PRESSURE DUE TO FLATTENED 'O' RING SEAL					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1996121900188	19961219	00188	EA  	1996	12	19	AU960640         	2	19960302	G	8530	LW12966	VALVE SEAT      	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	R ENGINE CYLINDE	SEPARATED       	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1298 		L810361A		L810361A			(AUS) NO1 CYLINDER VALVE SEAT SEPARATED - NO2 CYLINDER PISTON RING LANDWORN						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1996121900189	19961219	00189		1996	12	19	AU960641         	1	19960214	G	7603		CABLE           								ROTAX 	503   	ROTAX503    	55555	EU  					POWER CONTROL SY	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE THROTTLE CONTROL CABLE FAILED - THIS DEFECT WAS RECEIVED  FROM THE AUF AND IS FOR INFORMATION ONLY											3	I			EXPE3I				 
1996121900190	19961219	00190	SO  	1996	12	19	AU960642         	1	19960314	G	6120	7489410	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROP CNTRL SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE PROPELLER PITCH CONTROL CABLE BROKE AT THE FORWARD ENGINE CABLE MOUNT UNDER THE PROPELLER GOVERNOR						1	L	7	2 	3O			 	A20SO   		5	C	P33EA	 
1996121900191	19961219	00191	SO  	1996	12	19	AU960643         	1	19960313	G	3210	40284300	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	MAIN GEAR SYS	INCORRECT MOD   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR LOWER SIDE BRACE LINK ASSEMBLY ILLEGALLY MODIFIED BY ADHERING A SPACER PLATE TO THE BUTT JOINT OF THE	 OVER CENTRE JOINT FACE - FOUND DURING INSPECTION IAW AD/PA31/114 - UNAPPROVEDPART - UNAPPROVED MODIFICATION - PERSONNEL	/MAINTENANCE ERROR				1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1996121900192	19961219	00192	NE  	1996	12	19	AU960644         	2	19960503	G	7260	3087	SEAL            	TMECA       	NO1MODULE   	SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					TURBINE ENG. ACC	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 			827  		3087		3527			(AUS) NO2 ENGINE NO1 MODULE AIR/OIL SUPERIOR DRIVE CARBON SEAL SUSPECT LEAKING - FACTORY STRIP INSPECTION COULD FIND NO 	REAL PROBLEMS BUT COMMENTED THAT THE ACCESSORY GEARBOX BREATHER PIPE MAY HAVE  BEEN POSITIONED TOO FAR FORWARD CAUSING H	IGH OIL CONSUMPTION				1	G	7	2 	3U	3	U		H1NE    	E19EU				 
1996121900193	19961219	00193	SO  	1996	12	19	AU960645         	1	19960518	G	7120	7197204	BRACKET         			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE UPPER OUTBOARD ENGINE MOUNT TO FIREWALL ATTACHMENT BRACKET CRACKED THROUGH VERTICAL FACE FROM TOP WELD L	INE EXTENDING DOWN BETWEEN RIVET HOLES - CRACK LENGTH 9MM (0.35IN)					1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
1996121900194	19961219	00194	NM  	1996	12	19	AU960646         	1	19960304	G	7720	11046	PROBE           			BOEING	737   	737377      		NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					ENG TEMP IND SYS	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					11046					(AUS) NO2 ENGINE THERMOCOUPLE 'G' PROBE HAD APPROXIMATELY 3/4 OF ITS LENGTH BROKEN OFF - TGT HARNESS LOWER SECTION FAILE	D RESISTANCECHECKS					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
1997010200028	19970102	00028	NM  	1997	1	2	AU960647         	1	19960514	G	4930		PIPE            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  					APU FUEL DIST	CHAFED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) APU FUEL FEED PIPE LOCATED IN RH WING CHAFED THROUGH BY MAIN BLEED AIR SUPPLY DUCT SHROUD - FUEL LEAKING - SUSPECT	 CAUSED BYINCORRECT POSITIONING OF FUEL LINE					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997010200029	19970102	00029	EU  	1997	1	2	AU960648         	1	19960513	G	4990	SP3967464	BEARING         	SUNDSTRANDEM	4500506     	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					APU OIL SYS	INCORRECT FIT   	W		A		K				NONE                    				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 					SP3967464					(AUS) APU OIL COOLER FAN THRUST BEARING FAILED DUE TO INCORRECT FITMENT(FITTED BACK TO FRONT) - METAL CONTAMINATION OF A	PU OIL COOLER MATRIX, OIL FILTERS (2OFF) AND CHIP DETECTOR					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996091900065	19960919	00065	NE  	1996	9	19	AU960649         	2	19960519	G	7321	216381021	FCU             	LYC         	ALF502R5    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENG	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			8276 		LF05091					(AUS) NO3 ENGINE FUEL CONTROL UNIT INTERNAL LEAKAGE PAST SERVO PISTON  SEALS TOGETHER WITH DAMAGED SERVO SPOOL, PLATE AN	D SLEEVE					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996091900066	19960919	00066	EA  	1996	9	19	AU960650         	2	19960520	G	7310		HOSE            								LYC   	O360  	O360A1F6    	41514	EA  					ENG,FUEL DIST SY	SEPARATED       	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FUEL SYSTEM HOSE BETWEEN PRIMER SOLENOID VALVE AND PRIMER SYSTEM 'T' FITTING SEPARATED AT HOSE FITTING AT '	T' END										3	O			E286				 
1997010200030	19970102	00030	CE  	1997	1	2	AU960651         	1	19960516	G	2820	0800400238	PIPE            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	FUEL DISTRBUTION	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL PIPE BETWEEN WING ROOT AND FUSELAGE BULKHEAD CORRODED THROUGH WALL THICKNESS - OTHER FUEL PIPES CONTAINED SUR	FACECORROSION WITHIN LIMITS					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997010200031	19970102	00031	CE  	1997	1	2	AU960652         	1	19960510	G	5712		RIB             			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR WHEEL WELL WING RIBS AND SKINS CRACKED						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997010200032	19970102	00032	CE  	1997	1	2	AU960653         	1	19960510	G	5711	512203112	SPAR CAP        	CESSNA      	RHSPARCAP   	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING SPAR CAPS PNO 5122031-1 (LH) AND PNO 512203-2 (RH)CORRODED IN AREA OF NACELLE FUEL TANKS - WING SKI	NS AND CHANNELS ALSO CORRODED					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1996091900067	19960919	00067	CE  	1996	9	19	AU960654         	1	19960520	G	2820	O8OO4OO238	PIPE            			CESSNA	310   	310R        	2074245	CE  										FUEL DISTRBUTION	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL PIPE FROM WING ROOT TO FUSELAGE BULKHEAD CORRODED THROUGH WALL THICKNESS - OTHER FUEL PIPES CONTAINED SURFACE	 CORROSIONWITHIN LIMITS					1	L	7	2 	3O				3A10    					 
1997010200033	19970102	00033	WP  	1997	1	2	AU960655         	1	19960515	G	5530		TAILPLANE       			GOVT  	N22   	N22B        	3880102	WP  	ALLSN 	250B  	250B17B     	03010	GL  	HARTZL	HCA3V	HCA3VF7     	GL  	VERT STAB STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH SECTIONS OF TAILPLANE CRACKED IN EIGHT PLACES - MOST CRACKING WAS FOUND TO ORIGINATE FROM RIVETS IN RIBS	 AND INTERCOSTAL ANGLES - TWO CRACKS WERE ALSO FOUND IN THE SKIN -  NUMEROUS RIVETS WORKING - FOUND DURING INSPECTION IA	W NMD-55-34				1	H	7	2 	3T	3	T		A7PC    	E10CE	5	C	P6EA	 
1997010200034	19970102	00034	EA  	1997	1	2	AU960656         	2	19960513	G	7414	A197987	CONDENSER       	BENDIX      	SLN20       	PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2B5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	ELEC PWR SUPPLY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A197987		L1968540			(AUS) MAGNETO CONDENSER SEPARATED FROM MOUNTING LUG - PIGTAIL BROKEN - POINTS BURNT						1	L	7	1 	3O	3	O		2A10    	E295	5	N	P874	 
1997010200035	19970102	00035	SO  	1997	1	2	AU960657         	1	19960517	G	5320		ANGLE           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	NLG WELL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR WHEEL WELL LH AND RH LOWER ANGLES CRACKED IN AREA WHERE NLG DRAG BRACE PIVOT BRACKET ATTACHES AN	D TO WHICH THENOSE GEAR DOOR HINGES ATTACH					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P9EA	 
1996091900068	19960919	00068		1996	9	19	AU960658         	1	19960520	G	7713	6111	GAUGE           																	ENG PWR IND SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					173572					(AUS) MANIFOLD PRESSURE GAUGE AND LINE CONTAMINATED WITH OIL																			 
1997010200036	19970102	00036	EA  	1997	1	2	AU960659         	2	19960423	G	7210	SN91C8083024765	GEAR            	PWA         							PWA   	PT6   	PT6A27      	52043	EA  					ENG RED GR BOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					PCE42228		PCE42228			(AUS) ENGINE REDUCTION GEARBOX 1ST STAGE SUN GEAR DAMAGED - RELATED  PARTS HAD SECONDARY DAMAGE - ENGINE WAS FITTED TO M	ALAYSIAN AIRLINES 9M-MDO										4	T			E4EA				 
1997010200037	19970102	00037		1997	1	2	AU960660         	1	19960112	G	7160		AIR BOX         								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ACFT,ENG AIR INT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE INTAKE SYSTEM AIR BOX FAULTY - CRACKS IN AREA OF AIR  FILTER - CARBURETTOR ATTACHMENT RING BROKEN OFF											3	O			E286	5	C	P27EA	 
1997010200038	19970102	00038	EU  	1997	1	2	AU960661         	1	19960515	G	3220		FORK            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	NOSE-TAIL GEAR S	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FORK ASSEMBLY DELAMINATING IN AREA OF RADIUS						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
1996091900069	19960919	00069	EU  	1996	9	19	AU960662         	1	19960521	G	2842		TRANSMITTER     			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360F1A6    	41514	EA  					FUEL INDICATION	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH FUEL TRANSMITTER FLOATS DETERIORATED						1	L	7	1 	3O	3	O	NT	A57EU   	E286				 
1997010200039	19970102	00039	NM  	1997	1	2	AU960663         	1	19960517	G	5710		WING            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  					WING LE SYS	BIRD STRIKE     	W				K				NONE                    				C			F.O.D.                    			DE	DESCENT        	1			AU	S 										(AUS) AIRCRAFT SUFFERED A BIRDSTRIKE BY A LARGE WEDGETAIL EAGLE - THE  EAGLE GLANCED OFF THE LH WINDSCREEN AND STRUCK TH	E LH WING LEADING EDGE BETWEEN THE FUSELAGE AND THE ENGINE JUST INBOARD OF THE PROPELLER ARC CAUSING SEVERE DAMAGE TO TH	E LEADING EDGESTRUCTURE, ELECTRICAL WIRING AND PLUMBING BETWEEN STN YW57.20 ANDYW42.00 - MAJOR DAMAGE ALSO OCCURRED TO T	HE FRONT SPAR AND LOWER WING SKIN IN THE SAME AREA INCLUDING SEPARATION OF THE LOWER SPARBOOM FROM THE MACHINED WEB AND 	BUCKLING OF THE LOWER SKIN		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997010200040	19970102	00040	CE  	1997	1	2	AU960664         	1	19960507	G	3231	ARB4EDUS	ROD END         	CESSNA      		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LG EXT-RETRACT S	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					402C0049					(AUS) LH MAIN LANDING GEAR DOOR LINK ASSEMBLY INBOARD RODEND FAILED IN THE AREA OF THE NUT						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997010200041	19970102	00041		1997	1	2	AU960665         	4	19960503	G	2562	MN1300	BATTERY         		E01         	CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ELT EQUIP	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					003441					(AUS) REMOTE ELT BATTERIES LEAKING CAUSING CORROSION DAMAGE TO THE ENTIRE UNIT						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1996091900070	19960919	00070	NE  	1996	9	19	AU960666         	3	19960522	G	6111	6607132766	BLADE           													ROTOL	R389	R3894123F25 	NE  	PROPELLER ASSY S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					SF34013217			DRG202188		(AUS) PROPELLER BLADE SUSPECT CRACKED - FOUND DURING ULTRASONIC FLAW DETECTION OF THE INNER AND OUTER ROOT SLEEVES IAW N	DT TECHNIQUEP20/0H6 - FURTHER INVESTIGATION FOUND THE INDICATIONS TO BE RESIN CRACKING WHICH IS NOT CONSIDERED TO BE A D	EFECT														6	C	P30NE	 
1996091900071	19960919	00071		1996	9	19	AU960667         	1	19960520	G	7820		MUFFLER         								ROTAX 	912   	ROTAX912    	55555	EU  					ENG EXH	SEPARATED       	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) ENGINE EXHAUST SYSTEM MUFFLER SEPARATED FROM NO4 CYLINDER SUPPORT AND EXHAUST PIPE AT THE WELDED JOINT BETWEEN MUF	FLER AND PIPE -MUFFLER WAS RETAINED BY NO2 CYLINDER PIPE AND THE FIREWALL SHOCK MOUNT										3	I			EXPE3I				 
1996091900072	19960919	00072	EA  	1996	9	19	AU960668         	2	19960523	G	8530	F1890	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					RT  ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			747  		F1890		L1226539A			(AUS) NO2 CYLINDER CRACKED IN AREA OF EXHAUST PORT - CRACKING ALSO FOUND BETWEEN THE VALVE SEATS						1	L	7	1 	3O	3	O		2A13    	E274				 
1997010200042	19970102	00042	EA  	1997	1	2	AU960669         	2	19960518	G	7322	75029611	BRACKET         								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENG,FUEL CONTROL	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					75029611		L3406836A			(AUS) CARBURETTOR FLOAT PIVOT PIN BRACKET FRACTURED - CARBURETTOR  FLOODING											3	O			E286	5	C	P27EA	 
1996091900073	19960919	00073	EA  	1996	9	19	AU960670         	2	19960523	G	7310		HOSE            								LYC   	O360  	O360A1F6    	41514	EA  					ENG FUEL DIST SY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE PRIMER HOSE FAULTY - END FITTINGS CAN BE PULLED AWAY FROM HOSE											3	O			E286				 
1996091900074	19960919	00074	EU  	1996	9	19	AU960671         	1	19960522	G	2730		CONTROL ROD     			GROB  	G115  	G115C       	1660303	EU  										ELEV CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR PUSH-PULL CONTROL ROD WORN AND SCORED BY POP RIVETS HOLDING THE PLASTIC TUBE GUIDE - RIVETS EXTEND TOO FA	R AND WORE INTO CONTROL ROD					1	L	7	1 	3O			NT	A57EU   					 
1996091900075	19960919	00075	EU  	1996	9	19	AU960672         	1	19960523	G	2810		FUEL TANK       			GROB  	G115  	G115C       	1660303	EU  										FUEL STORAGE SYS	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) RH FUEL TANK LEAKING AT RH AFT TANK FITTING						1	L	7	1 	3O			NT	A57EU   					 
1996091900076	19960919	00076	SO  	1996	9	19	AU960673         	2	19960520	G	8530	353395	CYLINDER        	CONT        	IO360HB     						CONT  	O360  	IO360HB     	17025	SO  					RT  ENGINE CYL	FAILED          	W				O				OTHER                   				E	K	B	VIBRATION/BUFFET          	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	CL	CLIMB          	1			AU	S 					353395		353395			(AUS) ENGINE NO2 CYLINDER HAD NIL COMPRESSION - LOSS OF OIL QUANTITY AND PRESSURE - METAL CONTAMINATION OF OIL FILTER											3	O			E1CE				 
1997010200043	19970102	00043	SO  	1997	1	2	AU960674         	2	19960425	G	7314	6307514	PUMP            			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	ENG,FUEL DIST SY	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			8    		A2675278		218478R			(AUS) RH ENGINE DRIVEN FUEL PUMP FAILED DUE TO FOD						1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA	 
1996091900077	19960919	00077	EU  	1996	9	19	AU960675         	1	19960523	G	3222		AXLE            			GROB  	G115  	G115C       	1660303	EU  										NOSE WHEEL	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL AXLE SUSPECT INCORRECT SIZE - AXLE WAS APPROXIMATELY  10MM (0.393IN) SHORTER THAN NEW ITEM						1	L	7	1 	3O			NT	A57EU   					 
1996091900078	19960919	00078	EA  	1996	9	19	AU960676         	2	19960523	G	7310		HOSE            								LYC   	O360  	O360A1F6    	41514	EA  					ENG FUEL DIST SY	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE PRIMER HOSE PULLED OFF END FITTING PNO 311-2D AT SOLENOID VALVE CONNECTION											3	O			E286				 
1997010200044	19970102	00044	EA  	1997	1	2	AU960677         	2	19960418	G	8530		EXHAUST VALVE   								LYC   	O360  	O360A4K     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	R ENG CYL NR 1	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							L2704436A			(AUS) NO1 CYLINDER EXHAUST VALVE HAD APPROXIMATELY 33% OF THE VALVE  HEAD MISSING											3	O			E286	5	N	P857	 
1997010200045	19970102	00045	EU  	1997	1	2	AU960678         	1	19960518	G	7930	230384601	PROCESSOR       	LYC         		BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENG OIL IND SYS	FAULTY          	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		TX	TAXI/GRND HDL  	1			AU	S 					LF05863A					(AUS) NO2 ENGINE DUAL LOW OIL PRESSURE PROCESSOR FAULTY - CAUSES INTERFERENCE WITH MASTER WARNING SYSTEM - LYCOMING MODI	FICATION79-2-0013D HAD BEEN CARRIED OUT					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1996091900079	19960919	00079	SO  	1996	9	19	AU960679         	2	19960520	G	8520	63026143	BEARING         	CONT        	COUNTERWGHT 						CONT  	O360  	IO360HB     	17025	SO  					RT ENG CTRWT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							353395			(AUS) CRANKSHAFT COUNTERWEIGHT ROLLER BEARING PNO 630261-43 INCORRECT  PART - CORRECT PART NUMBER FITTED SHOULD HAVE BEE	N PNO 630261-44 - COUNTERWEIGHT RETAINING WASHER WORN INTO COUNTERWEIGHT - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR										3	O			E1CE				 
1997010200046	19970102	00046	SO  	1997	1	2	AU960680         	1	19960516	G	3230		O-RING          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LG EXT-RETRACT S	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR HYDRAULC SYSTEM PRESSURE REDUCER VALVE 'O' RING SEAL FAILED						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1996091900080	19960919	00080	EU  	1996	9	19	AU960681         	1	19960521	G	3240	50028202	WHEEL           			ISRAEL	1124  	1124        	4500102	EU  										LG WHEEL/BRAKE S	FRACTURED       	W		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			312  		INNERWHEEL					(AUS) MAIN LANDING GEAR WHEEL BRAKE DRIVE PAD KEY SECTION SEPARATED  FROM WHEEL (ONE PIECE CASTING) - OVERLOAD FRACTURE 	CAUSED BY REDUCTION IN WHEEL CROSS SECTION DUE TO GROOVING FROM LOOSE  DUST/WATER SHIELD					2	M	7	2 	4F				A2SW    					 
1997010200047	19970102	00047	SW  	1997	1	2	AU960682         	1	19960208	G	5340	51700365165	BRACKET         		51700367165 	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	ATTACH FITTING S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING ROOT BRACKETS PNO 5170036-5-165 AND PNO 5170036-7-165  CRACKED - FOUND DURING INSPECTION IAW AD/AC/93						1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA	 
1997010200048	19970102	00048	SW  	1997	1	2	AU960683         	1	19960209	G	5340	51700367165	BRACKET         		51700367165 	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	ATTACH FITTING S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING ROOT BRACKETS PNO 5170036-5-165 AND PNO 5170036-7-165  CRACKED - FOUND DURING INSPECTION IAW AD/AC/93						1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA	 
1997010200049	19970102	00049	CE  	1997	1	2	AU960684         	1	19960503	G	2434	A103214	BEARING         	PRESTOLITE  		CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	AC GENERATOR-ALT	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			1368 		A103214					(AUS) RH ENGINE ALTERNATOR BEARINGS DESTROYED - DRIVE AND DRIVEN GEARS DAMAGED - METAL CONTAMINATION OF OIL SYSTEM						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997010200050	19970102	00050	SO  	1997	1	2	AU960685         	1	19960411	G	5520	MS202533	PIN             	AYRES       		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR STRUCT	DISPLACED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							PCE57394	BU17835		(AUS) RH ELEVATOR TRIM TAB HINGE PIN MOVED INBOARD						1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997010200051	19970102	00051	CE  	1997	1	2	AU960686         	1	19960513	G	5320	07136381	REINFORCEMENT   		07136382    	CESSNA	182   	182Q        	2072732	CE  										MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE REINFORCEMENTS PNO 0713638-1 (LH) AND PNO 0713638-2 (RH), SUPPORT ANGLES PNO 0753600-11 (LH) AND PNO 0753	600-12 (RH),TUNNEL BULKHEADS PNO 0713631-1 (LH) AND PNO 0713631-6 (RH) WERE  BENT, DISTORTED AND CRACKED - FIREWALL DIST	ORTED AFT BY 12.7MM (0.5IN) IN THE AREA OF THE UPPER NOSE LANDING GEAR SUPPORT CASTING - SUSPECT CAUSED BY HEAVY LANDING				1	H	7	1 	3O			NT	3A13    					 
1996091900081	19960919	00081	GL  	1996	9	19	AU960687         	3	19960522	G	6114	D220116	HUB             	HARTZL      	HCC2YK2     	PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	BLADE SOCKET	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			311  		AV3856			AV3856		(AUS) PROPELLER HUB SEVERELY CORRODED IN AREA OF BLADE SOCKETS						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997010200052	19970102	00052	NE  	1997	1	2	AU960688         	2	19960108	G	7250	AS3218173	RING            	PWA         							PWA   	PT6   	PT6A42      	52043	NE  					TURBINE SECTION	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4405 		94202		94202			(AUS) ENGINE POWER TURBINE DISC NO3 BEARING COVER PNO 3103204-01 MOVED REARWARDS CONTACTING THE 2ND STAGE POWER TURBINE 	DISC RIM PNO3029313 - SUSPECT RETAINING RING PNO AS3218-173 NOT FITTED AT  LAST ASSEMBLY - PERSONNEL/MAINTENANCE ERROR										4	T			E4EA				 
1996091900082	19960919	00082	SW  	1996	9	19	AU960689         	1	19960521	G	6320	0476206283	BEARING         	BELL        	TRANSMISSION	BELL  	47    	47G3B       	1181026	SW  										MAIN ROTOR XMSN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			80   		B12344					(AUS) MAIN TRANSMISSION LOWER SUN GEAR BEARING CAGE DISINTEGRATED -  BEARING OIL PRESSURE JETS WERE ALSO FOUND TO BE BLO	CKED WITH A NON FERROUS METAL (METAL DID NOT ORIGINATE FROM THE TRANSMISSION)- TRANSMISSION HAD BEEN FITTED FOR APPROXIM	ATELY 80 HOURS -FURTHER INVESTIGATION FOUND THAT THE PREVIOUS TRANSMISSION FITTEDALSO HAD BLOCKED OIL JETS - IT IS SUSPE	CTED THAT AS THEHELICOPTER HAD PREVIOUSLY HAD AN ENGINE FAILURE FOR METAL IN THE FILTER, THE COSHARED ENGINE/TRANSMISSIO	N OIL COOLER HAD NOT BEEN CLEANED OR REPLACED - METAL CONTAMINATION OF TRANSMISSION OIL  SYSTEM		1	G	7	1 	3O				2H3     					 
1996091900083	19960919	00083	EU  	1996	9	19	AU960690         	1	19960527	G	6210	1178016602	BRACKET         			BOLKMS	117   	BK117B2     	5626013	EU  										M/R  BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE PENDULUM VIBRATION ABSORBER ASSEMBLIES (4OFF) LOWER PLATE BRACKETS CRACKED IN AREA OF INBOARD FLA	NGE DUE TOEXFOLIATION CORROSION					1	G	7	2 	3U			NC	H13EU   					 
1996091900084	19960919	00084	GL  	1996	9	19	AU960692         	3	19960522	G	6114	D220116	HUB             	HARTZL      	HCC2YK2CUF  	BNORM 	BN2   	BN2A26      	1520226	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1698 		AU7431			AU7431		(AUS) PROPELLER HUB CRACKED FROM HUB MOUNTING AREA TO BLADE SOCKET - CRACK LENGTH 35MM (1.37IN)						1	H	7	2 	3O				A17EU   		5	C	P920	 
1996091900085	19960919	00085	NM  	1996	9	19	AU960693         	1	19960520	G	6710		BOLT            	ROBSIN      	A2051       	ROBSIN	R22   	R22BETA     		NM  										MAIN RTR CNTRL S	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			204  		0					(AUS) COLLECTIVE CONTROL SYSTEM YOKE P/N A205-1 HAD BOLT, JOURNALS,  WASHERS AND NUTS MISSING - ITEMS FOUND IN AREA OF B	ELLY PANEL					1	G	7	1 	3O				H10WE   					 
1997010200053	19970102	00053	NM  	1997	1	2	AU960695         	1	19960511	G	4920		TURBINE         	GARRTT      	GTCP85129K  	BOEING	737   	737476      		NM  										APU ENGINE SYS	SEPARATED       	W		A		K				NONE                    				O	E		OTHER                     	VIBRATION/BUFFET          		IN	INSP/MAINT     	1			AU	S 										(AUS) APU FAILED DURING GROUND RUN - INVESTIGATION FOUND LARGE PIECES  OF METAL IN THE MUFFLER AND THE LOWER SHROUD - SU	BSTANTIAL EXTERNAL DAMAGE WAS ALSO PRESENT - FURTHER INSPECTION FOUND THAT THE APU HAD MOVED IN ITS MOUNTS - SUSPECT FAI	LURE DUE TO SEPARATION OF THE TURBINE WHEEL				2	L	7	2 	4F			RT	A16WE   					 
1997010200054	19970102	00054		1997	1	2	AU960696         	1	19960513	G	7830		SLIDER          								CFMINT	CFM56 	CFM563C     	13802	EU  					T ENG THRUST REV	SEPARATED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THRUST REVERSER NO2 OUTBOARD REVERSER HALF LOWER SLIDER SEPARATED FROM THE SLIDER TRACK - TRANSLATING COWL 	HAD BEEN RECENTLY REMOVED TO CARRY OUT A LOWER BLOCKER DOOR HINGE REPLACEMENT - PERSONEL/MAINTENANCE ERROR										4	F			E21EU				 
1997010200055	19970102	00055	NM  	1997	1	2	AU960697         	1	19960429	G	5510	7575564511	BEAM            			BOEING	737   	737377      		NM  										HORZ STAB SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH HORIZONTAL STABILISER LOWER TRAILING EDGE BEAM COVER PLATE  CONTAINED SEVERE EXFOLIATION CORROSION						2	L	7	2 	4F			RT	A16WE   					 
1997010200056	19970102	00056	EU  	1997	1	2	AU960698         	1	19960503	G	5750	68160351	PLATE           			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	WING TE SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SYSTEM HINGE PLATES BADLY CORRODED IN AREA OF PIVOT BOLT  HOLES - UPPER ATTACHMENT BEARING SEIZED DUE TO LACK	 OF LUBRICATION					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200057	19970102	00057	EU  	1997	1	2	AU960699         	1	19960503	G	7120	J961340	MOUNT           			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE MOUNTING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE TOP OUTBOARD LORD MOUNT PLATE CONTAINED EXFOLIATION  CORROSION - PLATE WAS ALSO SEPARATED FROM THE RUBBE	R MOUNT ASSEMBLY					1	H	7	2 	3O	3	O		A31EU   	1E10				 
1997010200058	19970102	00058	EU  	1997	1	2	AU960700         	1	19960412	G	3230	SA7670006123	HOSE            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LG EXT-RETRACT S	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) RH MAIN LANDING GEAR ACTUATOR DOWN LINE FLEXIBLE HOSE BURST IN AREA JUST BELOW 90 DEGREE UNION WHERE HOSE ATTACHES	 TO MANIFOLD -LOSS OF GREEN SYSTEM HYDRAULIC FLUID					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997010200059	19970102	00059	EU  	1997	1	2	AU960701         	1	19960503	G	7120	J961340	MOUNT           			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE MOUNTING	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT RUBBERS DETERIORATED						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010800002	19970108	00002	EU  	1997	1	8	AU960702         	1	19960314	G	2750		GEARBOX         			AIRBUS	320   	A320212     		EU  										RTINB FLAP	MIS RIGGED      	W		A		K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) RH INBOARD FLAP OUTER ROTARY GEARBOX MISRIGGED						2	L	7	2 	4F			RT	A28NM   					 
1997010200060	19970102	00060	EU  	1997	1	2	AU960703         	1	19960503	G	5540	68340451	BRACKET         			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	RUDDER STRUCT SY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER HINGE BRACKET CONTAINED EXFOLIATION CORROSION IN THE AREA BETWEEN THE HINGE UPPER FORK LUGS - CORROSION ALS	O IN THE AREA OFTHE PIVOT BOLT HOLE - PIVOT BUSH SEIZED DUE TO LACK OF LUBRICATION - THE HINGE FITTING FAILED THROUGH TH	E PIVOT BOLTHOLE WHEN ATTEMPTING TO REMOVE THE BOLT				1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200061	19970102	00061		1997	1	2	AU960704         	4	19960517	G	3452	AT150	TRANSPONDER     			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4A5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	DEPDNT POSN DATA	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					25256					(AUS) TRANSPONDER FAILED TO OPERATE DUE TO A FAULTY CAVITY BAND PASS FILTER IN THE RECEIVER						1	L	7	1 	3O	3	O		A3SO    	E295	5	C	P920	 
1997010200062	19970102	00062		1997	1	2	AU960705         	4	19960517	G	3452	RT359A	TRANSPONDER     			CESSNA	182   	182R        	2072731	CE  										DEPDNT POSN DATA	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					29367					(AUS) TRANSPONDER FAILED DUE TO UNSERVICEABLE CAVITY						1	L	7	1 	3O			NT	3A13    					 
1997010200063	19970102	00063	EU  	1997	1	2	AU960706         	1	19960503	G	3242	16424A	BRAKE DISC      			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LG WHEEL/BRAKE S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH BRAKE DISCS CORRODED THROUGH IN AREA OF WELD						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200064	19970102	00064	NM  	1997	1	2	AU960707         	1	19960127	G	5720		CHORD           			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					WING LE SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING LEADING EDGE RIB 'T' AT STN 269.298 CORRODED ON THE  BOTTOM FLANGE - FURTHER INVESTIGATION FOUND A SECTION	 OF THE CHORD APPROXIMATELY 152.4MM (6IN) FROM THE WING FRONT SPAR AND APPROXIMATELY 50.8MM (2IN) IN LENGTH COMPLETELY C	ORRODED AWAY				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997010200065	19970102	00065	EA  	1997	1	2	AU960708         	2	19960503	G	8540		GEAR            			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	R ENGINE REAR SE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE STARTER RING GEAR WORN - BENDIX DRIVE GEAR ON STARTER  MOTOR ALSO WORN - ENGINE HAD DIFFICULTY IN CRANKI	NG					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200066	19970102	00066	EU  	1997	1	2	AU960709         	1	19960503	G	2434		ALTERNATOR      			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AC GENERATOR-ALT	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE DRIVEN ALTERNATOR FAULTY - ALTERNATOR HOUSING LOOSE DUETO LOOSE RETAINING BOLTS AND A WORN ALTERNATOR AT	TACHMENT HOUSING- THE REPLACEMENT ALTERNATOR WAS SUPPLIED WITHOUT TAGS AND ON  INSPECTION WAS FOUND TO BE INCORRECTLY AS	SEMBLED AND THE ATTACHMENT HOLE IN THE HOUSING HAD BEEN ILLEGALY REWORKED -  SUSPECT BY AN AUTOMOTIVE REPAIRER - PERSONN	EL/MAINTENANCE ERROR -UNAPPROVED PART			1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200067	19970102	00067	EU  	1997	1	2	AU960710         	1	19960503	G	7110		COWLING         			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE COWL SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ENGINE TOP COWLS BADLY CORRODED AND CRACKED - LH ENGINEOIL DIPSTICK ACCESS DOOR TORN AND ALMOST SEPARATE	D					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200068	19970102	00068	GL  	1997	1	2	AU960711         	3	19960503	G	6110		PROPELLER       	LYC         		PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY S	INCORRECT ASSY  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					AV3743					(AUS) LH ENGINE PROPELLER INCORRECTLY ASSEMBLED - PROPELLER FEATHERED  DURING LANDING CAUSING ENGINE TO STALL - PROPELLE	R WOULD NOT FULLY FEATHER AND WOULD NOT RELATCH INTO NORMAL POSITION WHEN  UNFEATHERED - INVESTIGATION FOUND INCORRECT A	SSEMBLY, LEAKINGGREASE, INOPERATIVE LATCHING MECHANISM, WORN PISTON AND INCORRECTBLADE ANGLES - PERSONNEL/MAINTENANCE ER	ROR			1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200069	19970102	00069	EU  	1997	1	2	AU960712         	1	19960503	G	2710		CONTROL CABLE   			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERON CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON BALANCE CABLE FAULTY - CABLE WORN BEYOND LIMITS IAW  AD/P68/23 AMDT2 - TURNBUCKLE NOT IN SAFETY (TOO SHORT	) - SIX THREADS SHOWING EITHER SIDE OF TURNBUCKLE - PERSONNEL/MAINTENANCEERROR					1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
1997010200070	19970102	00070	EA  	1997	1	2	AU960713         	2	19960503	G	8500		ENGINE          	LYC         		PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE (RECIPROC	INCORRECT DATA  	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ENGINE DATA PLATES CONTAINED DIFFERENT TIMING DATA - BOTH ENGINES ARE IDENTICAL TYPES - ONE DATA PLATE S	TATES 20DEGREES WHILE THE OTHER STATES 25 DEGREES					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200071	19970102	00071	EU  	1997	1	2	AU960714         	1	19960503	G	2822	C8100F	PUMP            	WELDON      	C8100F      	PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUEL DISTRBUTION	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 					13A1229					(AUS) LH AND RH FUEL PUMPS LEAKING EXCESSIVELY FROM GRAVITY DRAINS - PUMPS ARE LOCATED IN THE ENGINE BAY ADJACENT TO THE	 MUFFLERSYSTEM					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200072	19970102	00072	EA  	1997	1	2	AU960715         	2	19960503	G	8530	LW12987	CYLINDER        			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	R ENG CYLINDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE CYLINDERS CRACKED AND CORRODED:-  1. TWO CYLINDERS EXCESSIVELY CORRODED/RUSTED IN AREA OF CYLINDER  BASE  2	. ONE CYLINDER CRACKED IN AREA OF UPPER SPARK PLUG HOLE 3. ONE CYLINDER CRACKED FROM EXHAUST PORT BETWEEN COOLING FINSAN	D BADLY CORRODED IN THE AREA OF THE EXHAUST PORT FLANGE				1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200073	19970102	00073	EU  	1997	1	2	AU960716         	1	19960503	G	5712		RIB             			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	OUTER WING SYS	INCORRECT MOD   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING RIB LOCATED IN ENGINE BAY ILLEGALLY MODIFIED - A HOLE HAD BEEN DRILLED THROUGH THE RIB STAINLESS STEEL FIR	E BARRIER TO FACILITATE PUSHROD REMOVAL - THE HOLE WAS LEFT UNCOVERED ALLOWINGA POSSIBLE ENGINE FIRE TO PENETRATE TO THE	 FIBREGLASS LEADINGEDGE AREA CONTAINING FUEL PLUMBING - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED MODIFICATION				1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200074	19970102	00074	EU  	1997	1	2	AU960717         	1	19960503	G	6120	75167	PIPE            			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROP CNTRL SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER CONSTANT SPEED UNIT (CSU) RIGID PIPE, STEEL 'B' NUTS AND SLEEVE BADLY CORRODED/RUSTED						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200075	19970102	00075	EA  	1997	1	2	AU960718         	2	19960503	G	7314	AC6441271	PUMP            			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENG,FUEL DIST SY	LOOSE SCREWS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ENGINE DRIVEN FUEL PUMP COVER SCREWS LOOSE						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200076	19970102	00076	EA  	1997	1	2	AU960719         	2	19960417	G	8520	72877	TAPPET          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	R ENGINE POWER S	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1739 				L254668A			(AUS) RH ENGINE NO4 CYLINDER EXHAUST TAPPET BODY FAILED ALLOWING EXHAUST VALVE TO REMAIN CLOSED						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997010200077	19970102	00077	SO  	1997	1	2	AU960720         	1	19960123	G	5720	62129008	STIFFENER       			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING REAR SPAR STIFFENER CRACKED AND CORRODED - STEEL REAR  SPAR BRACKET CONTAINED MINOR CORROSION - FOUND DURI	NG INSPECTION IAW AD/PA32/27 AMDT1					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997010200078	19970102	00078	EA  	1997	1	2	AU960721         	2	19960525	G	7414	M3525	COIL            	SLICK       							LYC   	O360  	AEIO360B2F  	41514	EA  					ELEC PWR SUPPLY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					89090006		L2368351A			(AUS) RH MAGNETO COIL CRACKED											3	O			1E10				 
1997010200079	19970102	00079	NM  	1997	1	2	AU960722         	1	19960111	G	5330		SKIN            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					EXT PLATES/SKIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT LOWER SKIN CORRODED AND SPLIT IN THE AREA OF THE LH RAM AIR INTAKE BETWEEN STRINGERS 27LH AND 28LH AT FRA	ME AT STN 700 - AREA OF CORROSION APPROXIMATELY 50.8MM BY 76.2MM (2IN BY 3IN) -  INVESTIGATION FOUND THAT THE EXFOLIATIO	N CORROSION WAS CAUSED BY A SALT WATER SPILL ORIGINATING FROM THE CARGO				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997010200080	19970102	00080	EU  	1997	1	2	AU960723         	1	19960331	G	2435	8374	GENERATOR       	LEARSIEGLER 	23079005    	BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	START/GENERATO	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			457  		8374					(AUS) LH ENGINE STARTER/GENERATOR FAILED						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1997010200081	19970102	00081		1997	1	2	AU960724         	4	19960504	G	3130	1574	RECORDER        	GARRTT      	9804100FHV  	BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	DATA RECORDER SY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			763  		1574					(AUS) FLIGHT DATA RECORDER FAULTY - FAILURE WARNING LIGHT ILLUMINATED						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1997010200082	19970102	00082	SO  	1997	1	2	AU960725         	2	19960524	G	8530	646657	CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	R ENGINE CYLINDE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			780  				552106			(AUS) ENGINE CYLINDER CRACKED FROM SPARK PLUG HOLE						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
1997010200083	19970102	00083	SO  	1997	1	2	AU960726         	2	19960317	G	8550		SPRING          	CONT        		CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	R ENGINE INT OIL	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					275442R		275442R			(AUS) ENGINE OIL PRESSURE RELIEF VALVE SPRING WAS AN INCORRECT PART -  FOUND DURING POST INSTALLATION GROUND RUN - ENGIN	E WAS A FACTORY REMANUFACTURED ENGINE - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997010200084	19970102	00084		1997	1	2	AU960727         	1	19960528	G	7820		MUFFLER         								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENG NOISE SUPPRS	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) RH EXHAUST MUFFLER ASSEMBLY FAILED AT FORWARD END IN AREA OF INLET PIPE TO END PLATE WELDED JOINT											3	O			E286	5	C	P27EA	 
1997010200085	19970102	00085	EU  	1997	1	2	AU960728         	1	19960528	G	3201	11505012	SUPPORT         			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FAIRING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WHEEL SPAT SUPPORT BRACKET CRACKED						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
1997010200086	19970102	00086	EU  	1997	1	2	AU960729         	1	19960527	G	3201	11505013	SUPPORT         			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FAIRING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WHEEL SPAT SUPPORT BRACKET CRACKED						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
1997010200087	19970102	00087	NM  	1997	1	2	AU960730         	1	19960521	G	5610	8SC0043012	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					FLT CMPT WINDOW	FAILED          	W				K				NONE                    				B	A		SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		CR	CRUISE         	1			AU	S 										(AUS) RH FORWARD COCKPIT WINDSCREEN SHORT CIRCUITED WHEN HEATER TURNED FROM 'WARM UP' TO 'NORMAL' - FLASH FROM TERMINALS	 WAS FOLLOWED BYA FIRE - WINDSCREEN WAS ALSO CRACKED CIRCUMFERENTIALLY FOLLOWED  BY SHATTERING OF THE OUTER PANEL - SUSP	ECT CAUSED BY MOISTURE INGRESS INTO THE INTERNAL BUSBAR CAUSING SHORT CIRCUIT				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997010200088	19970102	00088	NM  	1997	1	2	AU960731         	1	19960513	G	7910	3006084	CAP             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					AC,ENG OIL TANK	DAMAGED         	W				K				NONE                    				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			AU	S 							120032			(AUS) ENGINE OIL FILLER CAP LUG BROKEN - LOSS OF APPROXIMATELY THREE LITRES OF OIL						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997010200089	19970102	00089	EU  	1997	1	2	AU960732         	1	19960529	G	2730	115C4412	CONTROL ROD     			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360F1A6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ELEVATOR CONTROL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL ROD DAMAGED BY POP RIVET IN AREA OF FUSELAGE  STATION ME 6150MM - THE POP RIVET IS USED AS A LIMI	T STOP FOR ASLIDING TUBE BEARING					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
1997010200090	19970102	00090	NM  	1997	1	2	AU960733         	1	19960516	G	3244	319K281	TYRE            		314353      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LG WHEEL/BRAKE S	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1926					(AUS) RH MAIN LANDING GEAR INBOARD TYRE LEAKING EXCESSIVELY THROUGH  SIDEWALL PLY VENTS - TYRE WENT COMPLETELY FLAT						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997010200091	19970102	00091		1997	1	2	AU960734         	1	19960529	G	7160	115C6662	AIR BOX         								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ACFT,ENG AIR INT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CARBURETTOR AIR BOX CRACKED FROM BEND RELIEF HOLES											3	O			E286	5	C	P27EA	 
1997010200092	19970102	00092		1997	1	2	AU960735         	4	19960530	G	3452	TR661A	TRANSPONDER     			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  					DEPDNT POSN DATA	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					5024					(AUS) TRANSPONDER NOT WORKING - INVESTIGATION FOUND OFF/ON/MODEC/TEST  SELECTOR ON FRONT FACE NOT CONNECTED TO SWITCH WA	FER ON PCB DUETO OVERLOAD FAILURE OF THE SWITCH SHAFT					1	L	7	1 	3O	3	O		2A13    	E274				 
1997010200093	19970102	00093	SO  	1997	1	2	AU960736         	2	19960529	G	8520		CRANKCASE       			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	R ENGINE POWER S	CRACKED         	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 							191100			(AUS) CRANKCASE CRACKED IN AREA OF NO1 BEARING - CRACK ALSO IN CRANKCASE TOP FLANGE AT 7TH HOLE FROM THE FRONT - NO1 BEA	RINGSPINNING AND BREAKING UP - FRETTING OF CRANKCASE MATING FACES  INDICATES EXCESSIVE MOVEMENT POSSIBLY DUE TO INSUFFIC	IENT THROUGHBOLT TENSION				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997010200094	19970102	00094	GL  	1997	1	2	AU960737         	3	19960524	G	6110		O-RING          	MCAULY      		CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY S	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					711057			711057		(AUS) PROPELLER CONTAINED THE FOLLOWING FAULTS:- 1. INCORRECT RETENTION NUT 'O' RINGS FITTED2. RETENTION NUT NOT TORQUED	 3. NO MOLY KOTE LUBRICANT ON FERRULE THREADS OR BLADE THREADS4. OLD TYPE PRESSURE LATCH STILL FITTED - SHOULD HAVE BEEN	REPLACED WITH LATEST CENTRIFUGAL LATCH AS PER MANUAL 710930 5. ACTUATING PIN DEPTH IN FERRULE EXCEEDS MAXIMUM PERMITTED 	 PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART			1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1997010200095	19970102	00095	GL  	1997	1	2	AU960738         	3	19960523	G	6114	AU3908	HUB             			PIPER 	PA34  	PA34200     	7103405	SO  	CONT  	O360  	IO360C      	17025	SO  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY S	ILLEGAL REPAIR  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					AU3908			AU3908		(AUS) PROPELLER LEAKING OIL - INVESTIGATION FOUND THAT THE PROPELLER HUB HAD BEEN ILLEGALY REPAIRED/MODIFIED BY MACHININ	G IN THEPRELOAD PLATE AREA - SUSPECT HUB HAD SUFFERED FROM A PREVIOUS  GROUND STRIKE - PERSONNEL/MAINTENANCE ERROR - UNA	PPROVED REPAIR				1	L	7	2 	3O	3	O		A7SO    	E1CE	5	C	P920	 
1997010200096	19970102	00096	SW  	1997	1	2	AU960739         	1	19960228	G	6120	7715979002	VALVE           	GARRTT      		FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROP CNTRL SYS	STICKING        	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 								931689		(AUS) PROPELLER CONTROL UNIT CHECK VALVE STICKING						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
1997010200097	19970102	00097	NM  	1997	1	2	AU960740         	1	19960517	G	2140		DUCT            			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					HEATING SYSTEM	CRACKED         	W		A		K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) CABIN HEATER DUCTING CRACKED - HOT AIR CAUSED FREIGHT TO SMOULDER						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1997010200098	19970102	00098		1997	1	2	AU960741         	4	19960515	G	2565	B101124	SLIDE           			BOEING	767   	767238      		NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					EMERGENCY EQUIP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B101124					(AUS) LH OFF WING SLIDE FAULTY - SLIDING SURFACE DEFECTIVE						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
1997010200099	19970102	00099	NM  	1997	1	2	AU960742         	1	19960512	G	3210		BOLT            			BOEING	747   	747238B     	1384828	NM  										MAIN GEAR SYS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO10 MAIN WHEEL RETAINING AXLE NUT LOCKING BOLTS LOOSE - HUBCAP  CRACKED IN SEVERAL PLACES						2	L	7	4 	4F				A20WE   					 
1997010200100	19970102	00100		1997	1	2	AU960743         	4	19960523	G	2565		SLIDE           			BOEING	747   	747438      		NM  										EMERGENCY EQUIP	FAULTY          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH NO3 MAIN ENTRY DOOR ESCAPE SLIDES WOULD NOT DEPLOY DURING TEST - DOOR POWER ASSIST BOTTLES WOULD NOT FIR	E					2	L	7	4 	4F			RT	A20WE   					 
1997010200101	19970102	00101	NE  	1997	1	2	AU960744         	2	19960509	G	7240		LINER           								RROYCE	RB211 	RB211524G19 		NE  					TURBINE ENGINE C	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							13059			(AUS) NO1 ENGINE COMBUSTION LINER HEAD DAMAGE EXCEEDED MAINTENANCE MANUAL LIMITS - FOUND DURING BOROSCOPE INSPECTION IAW	 AD/RB211/19AMDT1 AND ROLLS ROYCE SERVICE BULLETIN RB211-72-B482										4	F			E30NE				 
1997010200102	19970102	00102	SO  	1997	1	2	AU960745         	1	19960514	G	7931	APT79100080D	TRANSMITTER     			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					ENG OIL IND SYS	FLUCTUATES      	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					338612179					(AUS) RH ENGINE OIL PRESSURE TRANSMITTER FLUCTUATING						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997010200103	19970102	00103	WP  	1997	1	2	AU960746         	1	19960526	G	6220	362093	CONTROL ROTOR   	HILLER      		HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					10068					(AUS) MAIN ROTOR HEAD CONTROL ROTOR CRACKED AT SPAR END THROUGH THE  FIRST BOLT HOLE FOR APPROXIMATELY 50% OF CIRCUMFERE	NCE - FOUND DURING INSPECTION IAW AD/HIL12/17 AMDT4					1	G	7	1 	3O	3	O		4H11    	E304				 
1997010200104	19970102	00104	CE  	1997	1	2	AU960747         	1	19960521	G	2720	12604188	TORQUE TUBE     			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RUDDER CONTROL S	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH RUDDER TORQUE TUBE FAILED IN AREA OF WELD ATTACHING THE MAIN  TUBE TO THE SHORT VERTICAL STUB - VERTICAL STUB I	S BOLTED TO THE RH RUDDER PEDAL					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997010200105	19970102	00105	WP  	1997	1	2	AU960748         	1	19960402	G	6220	5143711	ROTOR HUB       	HILLER      		HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			773  		10452					(AUS) MAIN ROTOR HUB CRACKED IN AREA OF THREADED CUFF AND TRUNNION BOLTHOLE EXTENDING DOWN THE INNER HUB SURFACE - CRACK	 LENGTH APPROXIMATELY 6.35MM (0.25IN) - FOUND DURING INSPECTION IAW  AD/HIL12/22A					1	G	7	1 	3O	3	O		4H11    	E304				 
1997010200106	19970102	00106	SO  	1997	1	2	AU960749         	2	19960522	G	8540	531178	RETAINER        	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	R ENGINE REAR SE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1458 		606607		606607			(AUS) ENGINE LH MAGNETO DRIVE CUSHION RETAINER FAILED						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997010200107	19970102	00107	CE  	1997	1	2	AU960750         	1	19960520	G	2910	510011171	PIPE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	MAIN HYD SYS	FRACTURED       	W				K				NONE                    				O	K	J	OTHER                     	FLUID LOSS                	WARNING INDICATION        	DE	DESCENT        	1			AU	S 										(AUS) LH HYDRAULIC SYSTEM PRESSURE PIPE LEAKING - LOSS OF HYDRAULIC  FLUID						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997010200108	19970102	00108		1997	1	2	AU960751         	1	19960528	G	6120	G9811P16	PIN             													HAMSTD	14SF	14SF23      	NE  	PROP CNTRL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO2 ENGINE PROPELLER FEATHER CONTROLLER PLUG FAULTY DUE TO UNDERSIZE PIN AT G9811-P16																6	C	P7NE	 
1997010200109	19970102	00109	EU  	1997	1	2	AU960752         	1	19960517	G	5713		STRINGER        	PARTEN      	P68B        	PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING UPPER SKIN STRINGERS CRACKED - UPPER WING SKIN ALSO CRACKED - FOUND DURING INSPECTION IAW AD/P68/42						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200110	19970102	00110	SW  	1997	1	2	AU960753         	1	19960314	G	3230	790270505	CYLINDER        			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	LG EXT-RETRACT S	DAMAGED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION CYLINDER SHAFT BENT - NOSE LANDING  GEAR COLLAPSED DURING LANDING ROLL - SUSPECT SHAF	T PREVIOUSLY BENT BY TOWING INCIDENT OR HEAVY LANDING					1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA	 
1997010200111	19970102	00111	EU  	1997	1	2	AU960754         	1	19960425	G	2150	8182833ANSN	TURBINE         	NORMALAIR   		BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					CABIN COOLING SY	SEIZED          	W		A		K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 			10814		8182833AN					(AUS) RIVET ATTACHING BAFFLE TO PLENUM/TORUS FAILED AND WAS INGESTED BYTHE RH AIRCONDITIONING PACK COOLING TURBINE CAUSI	NG IT TO SEIZE -INVESTIGATION FOUND THAT THE PLENUM/TORUS BAFFLE ASSEMBLY PNO  1344D710 CAME LOOSE DUE TO THE FAILURE OF	 THE ATTACHMENT RIVETS AND HAD CUT THROUGH THE PLENUM/TORUS OUTER SKIN ALLOWING THE RIVET HEADS TO ENTER AND DAMAGE THE 	TURBINE - THE MUFF INLET PIPEWAS ALSO FOUND TO BE CRACKED DUE TO THE SEVERE VIBRATION			2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997010200112	19970102	00112	SW  	1997	1	2	AU960755         	1	19960603	G	3240	2785004079	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LG WHEEL/BRAKE S	CHAFED THRU     	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LH BRAKE SYSTEM HYDRAULIC PIPE CHAFED THROUGH BY ELEVATOR CONTROL CABLE - LOSS OF HYDRAULIC FLUID - SUSPECT PIPE D	AMAGED DURING AIRCRAFT ASSEMBLY CAUSING IT TO COME IN CONTACT WITH THE ELEVATOR CABLE					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997010200113	19970102	00113	NM  	1997	1	2	AU960756         	1	19960601	G	2612	8987322	CIRCUIT BOARD   		V61423      	BOEING	767   	76733A      		NM  	PWA   	4056  	PW4056      		NE  					FIRE DETECTION S	FAULTY          	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 					2518M683P		P727317			(AUS) RH ENGINE FIRE DETECTION SYSTEM PRINTED CIRCUIT CARD M683 IN P54 CARD RACK FAULTY - FALSE FIRE WARNING ON RH ENGIN	E RESULTED IN DISCHARGE OF BOTH FIRE BOTTLES					2	L	7	2 	RT	4	F	RT	A1NM    	E24NE				 
1997010200114	19970102	00114		1997	1	2	AU960757         	4	19960525	G	2213	6224717003	MODE CONTROL    			BOEING	757   	757200      	1384950	NM  										FLIGHT CONTROLLE	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 					6224717003					(AUS) AUTOPILOT SYSTEM MODE CONTROL PANEL (MCP) FAULTY DUE TO FAILURE  OF 'POWER DROP OUT TEST' - A9Q204AND M12 REPLACED						2	L	7	2 	4F			RT	A2NM    					 
1997010200115	19970102	00115	SO  	1997	1	2	AU960758         	1	19960516	G	3211	225200	STUD            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR SIDE BRACE STUDS CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA30/34						1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
1997010200116	19970102	00116	SO  	1997	1	2	AU960759         	2	19960331	G	8530	629404	VALVE           			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	R ENG CYL EXH	STICKING        	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			100  				12091D6B			(AUS) EXHAUST VALVE STUCK - OTHER FIVE VALVES TIGHT IN VALVE GUIDES						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1997010800003	19970108	00003	NE  	1997	1	8	AU960761         	2	19960509	G	8530	166313	PISTON          	PWA         	R2000       	DOUG  	DC4   	C54E        	3021530	WP  	PWA   	R2000 	R2000*      	52023	NE  	HAMSTD	23E	23E50       	NE  	R ENGINE CYLINDE	BURNT           	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 			889  		P107816		P107816			(AUS) NO4 ENGINE NO 10 CYLINDER PISTON BURNT - ENGINE OIL VENTING OVERBOARD						2	L	7	4 	4R	4	R		A762    	5E5	6	C	P603	 
1997010200117	19970102	00117	SO  	1997	1	2	AU960762         	1	19960528	G	5751	86399803	RIB             	PIPER       	8656219     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	WING AIL/ELV SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					448195001					(AUS) AILERON RIBS PNO 86399-803 AND PNO 86399-003 CRACKED						1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
1997010800011	19970108	00011	EU  	1997	1	8	AU960763         	1	19960529	G	7712	97521206	TRANSMITTER     			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67      	52043	NE  					ENG PWR IND SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) ENGINE TORQUE PRESSURE TRANSMITTER INTERNAL FAILURE						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
1997010200459	19970102	00459	NM  	1997	1	2	AU960764         	1	19960520	G	5530	220000	HINGE           		220018201   	PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					VERT STAB STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIN HINGE ASSEMBLIES CORRODED						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1997010200460	19970102	00460	NM  	1997	1	2	AU960765         	1	19960506	G	5330		SKIN            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					EXT PLATES-SKIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR FUSELAGE LOWER SKIN CONTAINED EXFOLIATION CORROSION AT  FUSELAGE STATION 1050 AND BENEATH STRINGER 27 - DURIN	G PROBING INSPECTION SKIN BROKE AWAY LEAVING A 12.7MM (0.5IN) HOLE - SUSPECT CAUSED BY SALT WATER SPILLAGE					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997010200461	19970102	00461	NE  	1997	1	2	AU960766         	2	19960519	G	7230		FAN BLADE       			BOEING	737   	737377      		NM  	GE    	CFM56 	CFM563B1    	13802	NE  					TURBINE ENGINE C	BIRD STRIKE     	W				K				NONE                    				E	C		VIBRATION/BUFFET          	F.O.D.                    		TO	TAKEOFF        	1			AU	S 							721553			(AUS) NO2 ENGINE SUFFERED A BIRD STRIKE CAUSING SEVERE FAN BLADE DAMAGE - ONE FAN BLADE FRAGMENT EXITED FORWARD OF THE E	NGINE AND PENETRATED THE NOSE AND FAN COWLS					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
1997010200462	19970102	00462	NM  	1997	1	2	AU960767         	1	19960103	G	5320		BEAM            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MAIN FRAME SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT CONTAINED LEVEL 2 CORROSION ON LOWER CHORD OF CABIN FLOOR BEAM IN SECTION 46 - AREA OF CORROSION 508MM BY	 25.4MM BY2.032MM (20IN BY 1IN BY 0.80IN)					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997010200463	19970102	00463	EU  	1997	1	2	AU960768         	1	19960529	G	3150	TB11512	CONNECTOR       			PILATS	PC12  	PC12        	7090550	EU  										CENTRAL WARNING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRAL ADVISORY WARNING SYSTEM (CAWS) CONNECTOR HAD TWO PINS  SHORTING OUT DUE TO FAILURE OF CONNECTOR INSULATION						1	L	7	1 	3T			RT	A78EU   					 
1997010200464	19970102	00464	EA  	1997	1	2	AU960769         	2	19960501	G	8520	LW11036S	CRANKCASE       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			503  				L632748C			(AUS) ENGINE CRANKCASE CRACKED IN AREA OF NO2 CYLINDER FORWARD UPPER HOLD DOWN STUD HOLE - CRACK LENGTH 31.75MM (1.25IN)						1	H	7	2 	3O	3	O		6A1     	1E4				 
1997010200465	19970102	00465	SO  	1997	1	2	AU960770         	1	19960218	G	5610	8660804	WINDOW          		8660217     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	FLT CMPT WINDOW	BROKEN          	W				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) PILOTS PERSPEX SIDE WINDOW FAILED AND PARTS SEPARATED FROM AIRCRAFT DUE TO CRAZING - WINDOW IS PART OF THE EMERGEN	CY EXIT DOOR ASSEMBLY					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
1997010200466	19970102	00466	NM  	1997	1	2	AU960771         	1	19960103	G	5310		FUSELAGE        			BOEING	737   	737377      		NM  										FUSELAGE STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE CONTAINED LEVEL 2 CORROSION						2	L	7	2 	4F			RT	A16WE   					 
1997010200467	19970102	00467	NM  	1997	1	2	AU960772         	1	19960103	G	5310		FUSELAGE        			BOEING	737   	737377      		NM  										FUSELAGE STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT CONTAINED LEVEL 2 CORROSION						2	L	7	2 	4F			RT	A16WE   					 
1997010200468	19970102	00468	CE  	1997	1	2	AU960773         	1	19960503	G	3230	12802061	GUIDE           			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					LG EXT-RETRACT S	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK MECHANISM SPRING GUIDE CRACKED AND  DISTORTED						1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1997010200469	19970102	00469	EU  	1997	1	2	AU960774         	2	19960329	G	7250	9527M50G07	NGV             								CFMINT	CFM56 	CFM563C     	13802	EU  					TURBINE SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			315  				720724			(AUS) ENGINE HIGH PRESSURE TURBINE NOZZLE GUIDE VANES (23OFF) DAMAGED -NGVS HAD SEVERE TRAILING EDGE FALLOUT AND WERE DI	STORTED										4	F			E21EU				 
1997010200470	19970102	00470	CE  	1997	1	2	AU960775         	1	19960607	G	2430		WIRE            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	AC GENERATOR-ALT	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							280208R	D3A34C4048		(AUS) ALTERNATOR BATTERY WIRE DETERIORATED INTERNALLY - WIRE FRACTURED AND ARCING						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
1997010200471	19970102	00471	CE  	1997	1	2	AU960776         	1	19960603	G	3222		NLG             			CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	NOSE-TAIL GEAR S	SEPARATED       	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR SEPARATED FROM AIRCRAFT DURING LANDING (TORN OFF) - SUSPECT CAUSED BY HEAVY LANDING AND/OR INCOR	RECT LANDINGTECHNIQUE - PILOT ERROR					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997010200472	19970102	00472	SO  	1997	1	2	AU960777         	2	19960603	G	8530	649163A2	CYLINDER        	CONT        	IO470V0     	CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	R ENGINE NR 5	SEPARATED       	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			520  		455399		520			(AUS) RH ENGINE NO5 CYLINDER HEAD SEPARATED FROM BARREL - SUSPECT  PRE-EXISTING CRACK						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1997010200473	19970102	00473	SW  	1997	1	2	AU960778         	1	19960606	G	6220	206011113103	TRUNNION        	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					GDLM122299		833095			(AUS) MAIN ROTOR HUB TRUNNION CRACKED IN RADIUS - FAILURE ANALYSIS GROUP COULD FIND NO EVIDENCE OF CRACKING USING BOTH F	LUORESCENTDYE PENETRANT AND MAGNETIC PARTICLE INSPECTION TECHNIQUES -  THERE WAS EVIDENCE OF REWORK BY POLISHING - PART 	RETURNED TO BELLHELICOPTER FOR FURTHER INVESTIGATION				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997010200474	19970102	00474	EA  	1997	1	2	AU960779         	2	19960530	G	7414	M3548	ROTOR           	SLICK       	4370        	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	ELEC PWR SUPPLY	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			238  		95100288		L1185439A			(AUS) MAGNETO ROTOR FAILED AT THE BASE OF THE CAM RECESS						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997010200475	19970102	00475	CE  	1997	1	2	AU960780         	1	19960603	G	2612	303267	AMPLIFIER       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION S	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) RH ENGINE FIRE WARNING SYSTEM FIRE CONTROL AMPLIFIER FAULTY						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997010200476	19970102	00476	CE  	1997	1	2	AU960781         	1	19960601	G	2612	302158	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION S	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) RH ENGINE FORWARD UPPER DETECTOR FAULTY						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997010200477	19970102	00477	CE  	1997	1	2	AU960782         	1	19960606	G	2612		DETECTION SYSTEM			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION S	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CR	CRUISE         	1			AU	S 										(AUS) RH ENGINE FIRE DETECTION SYSTEM FAULTY - SEE MDR 96/0780 AND MDR 96/0781 FOR FURTHER INFORMATION						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997010200478	19970102	00478	CE  	1997	1	2	AU960783         	1	19960513	G	5340	0512122	BLOCK           	CESSNA      		CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	ATTACH FITTING S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE WING SPAR BEARING BLOCK CONTAINS SEVERE INTERGRANNULAR  EXFOLIATION CORROSION						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1997010200479	19970102	00479	CE  	1997	1	2	AU960784         	1	19960422	G	3230	583800901	MOTOR           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520F      	17032	SO  					LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					3976					(AUS) LANDING GEAR ELECTRIC MOTOR ARMATURE SEGMENT FAULTY						1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997010200480	19970102	00480	SO  	1997	1	2	AU960785         	1	19960604	G	3213		TORQUE LINK     	PIPER       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MAIN GEAR SYS	SHEARED         	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		TO	TAKEOFF        	1			AU	S 										(AUS) RH MAIN LANDING GEAR SEPARATED FROM AIRCRAFT DUE TO OLEO TOP TORQUE LINK SHEARING						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997010200481	19970102	00481	SO  	1997	1	2	AU960786         	1	19960418	G	2432	G35	BATTERY         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	BATTERY/CHARGER	OVERHEAT FIRE   	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) BATTERY CAUGHT FIRE DUE TO INCORRECT STARTING TECHNIQUE - START  HELD ON CONTINUOUSLY - PERSONNEL ERROR						1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
1997010200482	19970102	00482	GL  	1997	1	2	AU960787         	3	19960516	G	6110	A163570	SCREW           			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	PROPELLER ASSY S	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								832220		(AUS) PROPELLER CYLINDER RETAINING SCREWS (3OFF14) BROKEN - OTHER  SCREWS (9OFF14) LOOSE - SUSPECT INSUFFICIENT TORQUE O	N SCREWS AT LAST INSTALLATION - SOME FRETTING DAMAGE TO GASKET					1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P7EA	 
1997010200483	19970102	00483	CE  	1997	1	2	AU960788         	1	19960304	G	2913	105932E	POWER PACK      			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					105932E					(AUS) HYDRAULIC POWER PACK ELECTRIC MOTOR RUNNING SLOW - SLOW TO BUILD UP HYDRAULIC PRESSURE						1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
1997010200484	19970102	00484	SO  	1997	1	2	AU960789         	1	19960530	G	3411		FITTING         			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  	SNSNCH	76E	M76EMMS     	EA  	ENVIRONMENT DATA	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRSPEED INDICATOR PITOT LINE FITTING AND PIPE INCORRECT AUTOMOTIVE PARTS - PERSONNEL/MAINTENANCE ERROR - UNAPPROV	ED PART - FOUND DURING PITOT SYSTEM LEAK CHECK IAW AD/INST/8					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA4	 
1997010200485	19970102	00485	SO  	1997	1	2	AU960790         	1	19960530	G	2820		PIPE            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  	SNSNCH	76E	M76EMMS     	EA  	FUEL DISTRBUTION	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SUPPLY PIPE BETWEEN FUEL SHUTOFF AND FIREWALL BULKHEAD  FITTING KINKED FROM HAND BENDING - PIPE IS MALLEABLE 	COPPER FITTED DURING MODIFICATION FOR USE OF MOGAS IAW FAA STC SA2660CE,SE2563CE AND SE2587CE - PERSONNEL/MAINTENANCE ER	ROR				1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA4	 
1997010200486	19970102	00486	GL  	1997	1	2	AU960793         	1	19960509	G	5343		FITTING         			DHAV  	DHC1  	DHC1TMK10   	2801712	GL  										ATTACH FITTING S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR SUPPORT CASTING CRACKED BEYOND LIMITS - FURTHER INVESTIGATION ALSO FOUND CRACKING IN THE RH M	LG SUPPORTCASTING WHICH WAS WITHIN LIMITS - FOUND DURING X-RAY INSPECTION  IAW AD/DHC1/28-4					1	L	7	1 	3O				EXPA1L71					 
1997010200487	19970102	00487	EU  	1997	1	2	AU960794         	1	19960604	G	2730		TRIM SYSTEM     			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  	HARTZL	HCB5M	HCB5MP3     	GL  	ELEVATOR CONTROL	STUCK           	W				K				NONE                    				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) ELEVATOR TRIM SYSTEM JAMMED - INVESTIGATION FOUND THE METAL  PORTION OF A SMALL GLOBE IN THE CONSOLE WHICH MAY HAV	E BEENCAUGHT IN THE CHAIN CAUSING THE PROBLEM BUT COULD FIND NO OTHER  FAULTS WITH THE SYSTEM WHICH THEN OPERATED NORMAL	LY				2	H	7	2 	4T	4	T		A41EU   	E4EA	6	C	P44GL	 
1997010200488	19970102	00488	GL  	1997	1	2	AU960795         	3	19960611	G	6110		PROPELLER       			AMTR  	LNCAIR	320LANCAIR  	056129G	GL  						HARTZL	HCF2Y	HCF2Y*      	GL  	PROPELLER ASSY S	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								FE239		(AUS) INCORRECT PROPELLER FITTED TO AIRCRAFT - PROPELLER FITTED WAS A  HARTZELL MODEL HC-F2YL-2/F7666A-4 - CORRECT PROPE	LLER MODEL IS A HARTZELL MODEL HC-F2YL-1/F8468D-14 (DIFFERENT HUB, BLADES AND  ANGLE SETTINGS) - HUB PNO C3230-6 - BLADE	 PNO F7666A-4 - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART				1	L	7	1 	3O			RT	EXPA1L71		5	C	P27EA	 
1997010200489	19970102	00489	EU  	1997	1	2	AU960796         	1	19960510	G	5610	92274H8274ANS	WINDSHIELD      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FLT CMPT WINDOW	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					92274H8274					(AUS) LH `B' WINDSCREEN ARCED AT TOP LEFT HAND CORNER AND THEN THE OUTER GLASS PLY SHATTERED - SUSPECT FAILURE WAS HEAT 	RELATED					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997010200490	19970102	00490	EA  	1997	1	2	AU960797         	2	19960606	G	8520	LW17760	CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	R ENGINE POWER S	FAILED          	W				K				NONE                    				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			AU	S 							L720561A			(AUS) ENGINE CRANKSHAFT FAILED THROUGH WEBS OF NO1 AND NO2 BIG END JOURNALS - NO1 AND NO2 CYLINDERS AND CONNECTING RODS 	DAMAGED					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997010200491	19970102	00491	EU  	1997	1	2	AU960798         	1	19960429	G	5610	NP1701022	WINDSHIELD      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FLT CMPT WINDOW	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					90218H3813A					(AUS) RH `B' WINDSCREEN OUTER GLASS PLY SHATTERED - SUSPECT CAUSED BY  ARCING						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997010200492	19970102	00492	SO  	1997	1	2	AU960799         	1	19960607	G	7602	24894007	CABLE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	POWER CONTROL SY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ENGINE MIXTURE CONTROL INNER CABLE BROKEN APPROXIMATELY 10MM  (0.39IN) FROM SWAGING TO CABLE CONTROL ROD AT THE	 ENGINE END					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA	 
1997010200493	19970102	00493	NM  	1997	1	2	AU960800         	1	19960601	G	2424	RH747	GCU             			BOEING	737   	737476      		NM  										AC REGULATOR	FAULTY          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 					RH747					(AUS) ELECTRICAL SYSTEM SUFFERED MOMENTARY LOSS OF POWER ON SEVERAL  OCCASIONS - SUSPECT CAUSED BY RH GENERATOR CONTROL 	UNIT (GCU)					2	L	7	2 	4F			RT	A16WE   					 
1997010200494	19970102	00494	CE  	1997	1	2	AU960801         	1	19960605	G	5730		SKIN            			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER WING SKINS CRACKED - WING ANGLE TO SKIN ATTACHMENT RIVET HOLES ELONGATED- FOUND DURING INSPECTION IAW AD/C40	0/105 AMDT1 (NOT APPLICABLE TO THIS AIRCRAFT SERIAL NUMBER)					1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997010200495	19970102	00495		1997	1	2	AU960802         	4	19960531	G	3425	NK11062	EFIS SYSTEM     			BOEING	737   	737376      		NM  										INSTRUMENT PANEL	FAILED          	W				K				NONE                    				I			FLT. ATTITUDE INST.       			CR	CRUISE         	1			AU	S 					NK11062					(AUS) AUTOPILOT `B' DISCONNECTED - EFIS DISPLAYS BLANK - FLIGHT  INSTRUMENTS FAILED - NIL CBS TRIPPED - AFTER 15 SECONDS	 NORMAL OPERATION WAS RESUMED - SUSPECT CAUSED BY FAULTY GCU					2	L	7	2 	4F			RT	A16WE   					 
1997010200496	19970102	00496	SO  	1997	1	2	AU960803         	1	19960605	G	5520	317912110	ELEVATOR        	PIPER       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					317912110					(AUS) LH AND RH ELEVATORS CRACKED - FOUND DURING RADIOGRAPHIC  INSPECTION IAW AD/PA31/126						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997010200497	19970102	00497	NE  	1997	1	2	AU960804         	2	19960604	G	7412	3038137	EXCITER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ELEC PWR SUPPLY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2406 				120122			(AUS) ENGINE IGNITION EXCITER BOX FAULTY						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997010200498	19970102	00498		1997	1	2	AU960805         	1	19960323	G	7930	230376303	HARNESS         								LYC   	ALF502	ALF502R5    	41580	NE  					ENG OIL IND SYS	DAMAGED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 							LF05506A			(AUS) NO1 ENGINE OIL INDICATION SYSTEM HARNESS DAMAGED AND SHORT CIRCUITING ON PYLON DRAIN PIPE ON FRONT RH COWLING											4	F			E6NE				 
1997010200499	19970102	00499	NM  	1997	1	2	AU960807         	1	19960602	G	2913	GENM29503011	PUMP            			BOEING	737   	737376      		NM  										MAIN HYD SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 					157225B					(AUS) ENGINE DRIVEN HYDRAULIC PUMP LEAKING FROM SPLINE DRIVE CAVITY -  LOSS OF 'A' SYSTEM PRESSURE AND HYDRAULIC FLUID						2	L	7	2 	4F			RT	A16WE   					 
1997010200500	19970102	00500	SO  	1997	1	2	AU960808         	2	19960528	G	8530	646460	EXHAUST VALVE   	CONT        		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	R ENGINE CYLINDE	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							237339R	AN444913		(AUS) LH ENGINE NO5 CYLINDER EXHAUST VALVE FAILED - SUSPECT CAUSED BY  EXCESSIVE LEANING OF ENGINE						1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920	 
1997010200501	19970102	00501	SO  	1997	1	2	AU960809         	1	19960503	G	5310		TUBE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE STEP TUBE CRACKED - AIRCRAFT HAS BEEN MODIFIED IAW SB672AND AD/PA28/81						1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
1997010200502	19970102	00502	SO  	1997	1	2	AU960810         	1	19960503	G	3230	1742002	BRACE           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	MAIN GEAR SYS	CRACKED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DRAG LINK FITTING SUPPORT BRACE CRACKED IN AREA OF ATTACHMENT BOLT						1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
1997010200503	19970102	00503	SW  	1997	1	2	AU960812         	1	19960522	G	7810	4606AC	CLAMP           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T ENG CONE-PIPE	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 							CAE830380			(AUS) ENGINE EXHAUST CLAMP FAILED IN RIVETTED AREA DUE TO CORROSION  FROM EXHAUST GASSES						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997010200504	19970102	00504		1997	1	2	AU960813         	4	19960301	G	6113		BULKHEAD        			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER ASSY S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH SPINNER BULKHEADS CRACKED - SUSPECT CAUSED BY ROUGH  RUNNING ENGINES						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997010200505	19970102	00505	CE  	1997	1	2	AU960814         	1	19960301	G	5720		HINGE           			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	OUTER WING SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING LOWER FORWARD SPAR TO LEADING EDGE `D' SECTION  HINGE AND HINGE PINS WORN - MAXIMUM AMOUNT OF WEAR 	IS LOCATED BETWEEN WING ROOT TO JUST OUTBOARD OF ENGINE					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997010200506	19970102	00506	CE  	1997	1	2	AU960815         	1	19960301	G	5540	NIAS5054J	BEARING         			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	RUDDER STRUCT SY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER BEARINGS (2OFF) CORRODED INTERNALLY - AIRCRAFT OPERATES IN A SALT LADEN ENVIRONMENT - SUSPECT BEARINGS ORIG	INAL FITMENT					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997010200507	19970102	00507	EU  	1997	1	2	AU960816         	1	19960611	G	2720		PEDAL           			FOKKER	F27   	F27MK50     		EU  										COPILOT RUDDER	MALFUNCTION     	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) INTERMITTENT KNOCKING NOISE COMING FROM COPILOTS RUDDER PEDAL  AREA - INVESTIGATION COULD FIND NO FAULTS						2	H	7	2 	4T			RT	A817    					 
1997010200508	19970102	00508	EU  	1997	1	2	AU960817         	1	19960612	G	3234	114044003	VALVE           			FOKKER	F27   	F27MK50     		EU  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE FAULTY - LANDING GEAR WOULD NOT  RETRACT FOLLOWING `UP' SELECTION						2	H	7	2 	4T			RT	A817    					 
1997010200509	19970102	00509	SO  	1997	1	2	AU960818         	1	19960607	G	3230	14595	ACTUATOR        			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CR	CRUISE         	1			AU	S 					1454					(AUS) LH MAIN LANDING GEAR DOWNLOCK ACTUATOR FAULTY - MICROSWITCH  STRIKER NOT ACTIVATING MICROSWITCH						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997010200510	19970102	00510	SW  	1997	1	2	AU960819         	1	19960530	G	6320	3076	BEARING         	BELL        		BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435D1A   	41516	EA  					MAIN ROTOR TRANS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3076					(AUS) TRANSMISSION FAN DRIVE BEARING FAILED - METAL CONTAMINATION OF OIL SYSTEM						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997010200511	19970102	00511	EA  	1997	1	2	AU960820         	2	19960613	G	7322	252405411	FCU             			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				O	Y		OTHER                     	ENGINE STOPPAGE           		LD	LANDING        	1			AU	S 					75654		RL2427351A			(AUS) RH ENGINE FUEL CONTROL UNIT FUEL/AIR MIXTURE SUSPECT OUT OF  ADJUSTMENT - PERSONNEL/MAINTENANCE ERROR						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997010200512	19970102	00512	SW  	1997	1	2	AU960821         	1	19960514	G	2910	79024681	PIPE            			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	MAIN HYD SYS	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) HYDRAULIC PIPE LOCATED IN WING ROOT AREA CONTAINED A PINHOLE LEAK DUE TO CORROSION ON THE OUTER RADIUS OF THE 90 D	EGREE BEND					1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA	 
1997010200513	19970102	00513	SW  	1997	1	2	AU960822         	1	19960520	G	6320	476205521	BEARING         			BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435D1A   	41516	EA  					MAIN ROTOR TRANS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			75   		B12344					(AUS) MAIN TRANSMISSION COOLING FAN DRIVE BEARING FAILED - METAL CONTAMINATION OF TRANSMISSION OIL SYSTEM						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997010200514	19970102	00514	SW  	1997	1	2	AU960823         	1	19960412	G	6230	0471301101	BEARING         			BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435D1A   	41516	EA  					M/R MAST/SWASHPL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1166 		047130114					(AUS) MAIN ROTOR MAST BEARING FAILED - SUSPECT CAUSED BY HEAVY LANDING - METAL CONTAMINATION OF OIL SYSTEM						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997010200515	19970102	00515	CE  	1997	1	2	AU960824         	1	19960607	G	3250	24670031	BUNGEE          			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ACFT STEERING SY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT STEERING SYSTEM BUNGEE JACK SCREW BROKEN DUE TO A WORN  HOUSING - SYSTEM HAD BEEN MODIFIED IAW AD/CESSNA1	70/45					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
1997010200516	19970102	00516	EA  	1997	1	2	AU960825         	2	19960607	G	8520		CRANKSHAFT      	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	R ENGINE POWER S	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 							L720561A			(AUS) ENGINE CRANKSHAFT BROKEN - CRANKCASE BROKEN - CAMSHAFT DAMAGED - NO1 AND NO2 CYLINDERS DAMAGED - CONNECTING RODS B	ENT - SEE MDR 96/0797 FOR FURTHER INFORMATION					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997010200517	19970102	00517	NM  	1997	1	2	AU960826         	1	19960513	G	7910	3006084	CAP             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					AC,ENG OIL TANK	DAMAGED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CL	CLIMB          	1			AU	S 							120032			(AUS) RH ENGINE OIL FILLER CAP DAMAGED - ONE LOCKING LUG BROKEN OFF -  APPROXIMATELY 3 LITRES OF OIL LOST - DUPLICATE OF	 MDR 96/0731					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997010200518	19970102	00518	NM  	1997	1	2	AU960827         	1	19960529	G	2750	745583A	CONTROL CABLE   			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					FLAP SYS	FAILED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP CABLE SWAGED END FITTING SEPARATED FROM CABLE OUTER SHEATH -INNER CABLE DAMAGED - FOUND DURING INSPECTION IAW	 AD/DHC8/8					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997010200519	19970102	00519	SO  	1997	1	2	AU960828         	2	19960613	G	8540	653583	SHAFT           	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	R ENGINE REAR SE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4527		239145R			(AUS) ENGINE STARTER SHAFT AND CRANKSHAFT GEAR TEETH WORN - STARTER KIT PNO EQ6642 - SEE MDR 96/0908 FOR FURTHER INFORMA	TION					1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997010200520	19970102	00520	CE  	1997	1	2	AU960829         	1	19960606	G	5712		RIB             			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	OUTER WING SYS	MIS MFG         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING END RIB NOT RIVETTED TO THE MAIN SPAR - SUSPECT RIVETS NOT INSTALLED AT MANUFACTURE						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1997010200521	19970102	00521	SW  	1997	1	2	AU960830         	1	19960614	G	2520	2790567033	SEAT            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					PASSENGER COMPAR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER SEAT BACK BROKEN						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997010200522	19970102	00522	SO  	1997	1	2	AU960831         	1	19960610	G	3260	6741103	SWITCH          		JE73        	PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LG POSITION IND	BROKEN          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH LEAF ACTUATOR BROKEN						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
1997010200523	19970102	00523	SW  	1997	1	2	AU960832         	1	19960605	G	7810		PIPE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					T ENG CONE-PIPE	CRACKED         	W				K				NONE                    				F	B	J	FLT CONT AFFECTED         	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE EXHAUST SYSTEM SHORT PIPE CRACKED - HOT EXHAUST GASSES  ACTIVATED FIRE WARNING SYSTEM AND FIRE BOTTLE WAS D	ISCHARGED					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997010200524	19970102	00524	SW  	1997	1	2	AU960833         	1	19960607	G	7712	27191587	INDICATOR       		6112104     	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ENG PWR IND SYS	FLUCTUATES      	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					PORT77102					(AUS) LH ENGINE TORQUE INDICATOR FLUCTUATING						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997010800012	19970108	00012	SO  	1997	1	8	AU960834         	2	19960601	G	7322	2523047	NEEDLE          		NA53A1      	CESSNA	140   	140         	2071602	CE  	CONT  	C90   	C90*        	17009	SO  					ENG,FUEL CONTROL	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CARBURETTOR FLOAT NEEDLE RUBBER TIP HARDENED AND DEFORMED -  OBSOLETE PART						1	H	7	1 	3O	3	O	NC	A768    	E252				 
1997010200525	19970102	00525	GL  	1997	1	2	AU960835         	2	19960606	G	7240	6899081	LINER           			SNIAS 	350   	AS350B      	8680801	EU  	ALLSN 	250C  	250C30      	03013	GL  					TURBINE ENGINE C	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			941  				CAT890502			(AUS) ENGINE COMBUSTION ASSEMBLY AIR SURROUND TO COMBUSTION LINER  ATTACHMENT SADDLES (3OFF) FAILED AT WELDS - SADDLES W	ERE INGESTEDTHROUGH THE ENGINE					1	G	7	1 	3U	3	U		H9EU    	E1GL				 
1997011600471	19970116	00471	NM  	1997	1	16	AU960836         	1	19960614	G	3246	AN35A	BOLT            			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540G1B5   	41532	EA  					LG WHEEL/BRAKE S	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WHEEL RIM TIE BOLT HEAD SEPARATED						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1997011600472	19970116	00472	NE  	1997	1	16	AU960837         	3	19960523	G	6111	SFA13M10A	BLADE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER ASSY S	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5380 					644		(AUS) PROPELLER BLADE FAILED NDT INSPECTION AS PER HS ASB 14SF-61-A95  - AD/PHS/21						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
1997011600473	19970116	00473	EU  	1997	1	16	AU960838         	1	19960509	G	3230	C242450061	UPLOCK          			AMD   	FALC50	FALCON900   	2700160	EU  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR UPLOCK UNIT FAULTY - THIS DEFECT WAS RECEIVED  FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ON	LY					2	L	7	3 	4F			RT	A46EU   					 
1997011600474	19970116	00474	EU  	1997	1	16	AU960839         	1	19960307	G	3230	9036001	CLUTCH          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LG EXT-RETRACT S	SLIPPED         	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 			13079		487GB170H					(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR CLUTCH SLIPPING						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997011600475	19970116	00475	EU  	1997	1	16	AU960840         	2	19960418	G	7322		CARBURETTOR     								ROTAX 	912   	ROTAX912    	55555	EU  					ENG,FUEL CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) CARBURETTOR LEAKING FUEL INTO AIR FILTER BOX VIA CARBURETTOR COMPENSATING LINE - THIS DEFECT WAS RECEIVED FROM THE	 AUF AND IS FOR INFORMATION ONLY										3	I			EXPE3I				 
1997011600476	19970116	00476	CE  	1997	1	16	AU960841         	1	19960613	G	5330	081125077	SKIN            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	EXT PLATES/SKIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CORRODED IN AREA OF LH LOWER BELLY - INVESTIGATION FOUND EXTENSIVE CORROSION IN THE AREA BENEATH THE	 HEATER DUCTING PNO 0813769-1					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997011600477	19970116	00477	SO  	1997	1	16	AU960842         	1	19960619	G	2810	527881	FUEL CELL       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL STORAGE SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					7716216					(AUS) FUEL CELL SPLIT AT DRAIN FITTING NIPPLE - CELL WAS FITTED IN 1978						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997011600478	19970116	00478	CE  	1997	1	16	AU960843         	1	19960516	G	7120	MS2000646M	BOLT            			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  	ENGINE MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							555307			(AUS) ENGINE MOUNT ATTACHMENT BOLT CRACKED UNDER HEAD - FOUND DURING NDT INSPECTION IAW AD/B55/74						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P5EA	 
1997011600479	19970116	00479	CE  	1997	1	16	AU960844         	1	19960515	G	7120	9691001061	MOUNT           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	ENGINE MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							287203R			(AUS) ENGINE MOUNT STRUCTURE CRACKED IN FOUR PLACES - FOUND DURING NDT INSPECTION IAW AD/B55/74						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997011600480	19970116	00480	EU  	1997	1	16	AU960845         	1	19960618	G	2750		ACTUATOR        			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FLAP SYS	CONTAM-WATER    	W				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLAPS LOCKED IN ZERO DEGREES POSITION - INVESTIGATION FOUND WATER INGRESS INTO FLAP ACTUATOR BALLNUTS - AEROSHELL 	7 GREASE USED					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997011600481	19970116	00481	EU  	1997	1	16	AU960846         	1	19960608	G	3230		SEAL            			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LG EXT-RETRACT S	DETERIORATED    	W				K				NONE                    				W			INADEQUATE Q C            			LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR ACTUATOR SEALS DETERIORATED AND LEAKING - CAUSED BY FAILURE TO CORRECTLY MASK LANDING GEAR RA	M DURING PAINTING ALLOWING RAM SHAFT TO BE COVERED IN PAINT WHICH DAMAGED RAM SEALS - PERSONNEL/MAINTENANCE ERROR					1	L	7	1 	3O	3	O	RT	A51EU   	1E4	5	C	P920	 
1997011600482	19970116	00482	CE  	1997	1	16	AU960847         	1	19960618	G	3230	1055800015	PIPE            	BEECH       	B76         	BEECH 	76    	76          	1153005	CE  										LG EXT-RETRACT S	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC 'UP' PIPE FLARE CRACKED AND LEAKING AT  CONNECTION TO POWER PACK - INVESTIGATION FOUND POOR	 QUALITY FLARE- PIPE HAD BEEN REFLARED ON 20 OCTOBER 1992 -  PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O				A29CE   					 
1997011600483	19970116	00483	SO  	1997	1	16	AU960848         	1	19960619	G	3260	487820	SWITCH          			PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360A1A     	41514	EA  					LG POSITION IND	SEIZED          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR WARNING MICROSWITCH SEIZED IN 'SAFE' POSITION						1	L	7	1 	3O	3	O		1A15    	E286				 
1997011600484	19970116	00484	CE  	1997	1	16	AU960849         	1	19960619	G	3230	HMXFG	ROD END         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520F      	17032	SO  					LG EXT-RETRACT S	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION ACTUATOR FORWARD RODEND FAILED						1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997011600485	19970116	00485	EA  	1997	1	16	AU960850         	2	19960609	G	7320		FCU             			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							80438			(AUS) ENGINE LOST POWER DURING TAKEOFF - INVESTIGATION COULD FIND NO FAULTS - SUSPECT FUEL CONTROL PROBLEM						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997011600486	19970116	00486	CE  	1997	1	16	AU960851         	1	19960616	G	2612	302158	DETECTOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION S	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FIRE DETECTORS FAULTY - CONTINUING FALSE FIRE WARNING INDICATIONS						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997011600487	19970116	00487	EA  	1997	1	16	AU960852         	2	19960410	G	7322	30766	FLOAT           	FACET       	MA4SPA      	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENG,FUEL CONTROL	DETERIORATED    	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			2000 							(AUS) CARBURETTOR FLOAT DETERIORATED - FLOAT ABSORBING FUEL CAUSING  EXCESSIVELY RICH CONDITION						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997011600488	19970116	00488	SO  	1997	1	16	AU960853         	2	19960519	G	7421	RHM40E	SPARK PLUG      	CONT        	TSIO350EB   	PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360E   	17025	SO  	MCAULY	3AF34C	3AF34C502   	GL  	ENG,IGNITN DISTR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE HAD INCORRECT SPARK PLUGS FITTED - PERSONNEL/MAINTENANCE  ERROR - UNAPPROVED PART						1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
1997011600489	19970116	00489	SO  	1997	1	16	AU960854         	2	19960507	G	8520	649478	CAMSHAFT        	CONT        	O470U       	CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	R ENGINE POWER S	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					470326		470326	821588		(AUS) ENGINE CAMSHAFT LOBE FOR NO5 CYLINDER EXHAUST VALVE AND  CORRESPONDING LIFTER BADLY PITTED AND GALLED						1	L	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997011600490	19970116	00490	CE  	1997	1	16	AU960855         	1	19960318	G	3211	24411001	PIVOT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR PIVOT CRACKED AT THE OUTBOARD END OF THE  SPLINED AREA - FURTHER INVESTIGATION FOUND LH MLG P	IVOT ALSO CRACKED					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
1997011600491	19970116	00491	EA  	1997	1	16	AU960856         	2	19960425	G	8540	LW13796	SHAFT           	LYC         	O320A2D     	BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2D     	41508	EA  					R ENGINE REAR SE	WORN            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE CRANKSHAFT LH IDLER GEAR SHAFT ATTACHMENT HOLES ELONGATED,LOCKWIRE BROKEN, BOLTS NECKED AND SHAFT LOOSE						1	H	7	1 	3O	3	O	NC	A759    	E274				 
1997011600492	19970116	00492	CE  	1997	1	16	AU960857         	1	19960620	G	2612	64123473275	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FIRE DETECTION S	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LH ENGINE FIRE DETECTION SYSTEM FAULTY - INVESTIGATION COULD FIND NO FAULTS WITH THE SYSTEM - A LEAKING GASKET ON 	THE FLOW PACK MAYHAVE ALLOWED HOT AIR ONTO THE LOWER REAR SENSOR - FOLLOWING  REPLACEMENT OF THE FLOW PACK ON THE NEXT F	LIGHT THE FIRE WARNING SYSTEM AGAIN ACTIVATED - FURTHER INVESTIGATION FOUND THE TWO REAR BULKHEAD FIRE SENSORS TO BE FAU	LTY			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997011600493	19970116	00493	EA  	1997	1	16	AU960858         	2	19960616	G	8520		CONNECTING ROD  			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1C160	1C160DTM    	GL  	R ENGINE POWER S	FAILED          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		TO	TAKEOFF        	1			AU	S 										(AUS) NO3 CYLINDER CONNECTING ROD FAILED IN AREA APPROXIMATELY HALF WAY BETWEEN THE BIG END AND THE GUDGEON PIN BUSHING 	- FAILURE INVESTIGATION FOUND EVIDENCE OF A PRE-EXISTING FLAW IN THE PISTON PIN BEARING HOUSING WHICH WAS HEAVILY OXIDIS	ED				1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P910	 
1997011600494	19970116	00494	SO  	1997	1	16	AU960859         	1	19960619	G	3230		DOWNLOCK HOOK   			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LG EXT-RETRACT S	MALFUNCTION     	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK HOOK STIFF - HOOK DID NOT FULLY  ENGAGE						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997012200004	19970122	00004	SO  	1997	1	22	AU960860         	2	19960607	G	8530	649317P010	CYLINDER        	CONT        	IO520BE     	BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	R ENGINE CYLINDE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			513  		571950		571950			(AUS) NO2 CYLINDER HEAD SEPARATED FROM BARREL						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA	 
1997011600495	19970116	00495	EU  	1997	1	16	AU960861         	1	19960621	G	2110		MOTOR           		021003      	BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	CABIN COMPRESSOR	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) AIRCONDITIONING SYSTEM DISCHARGE PIPE BURST - FAILURE WAS DUE TO FAILURE OF THE CONDENSER COOLING FAN MOTOR RESULT	ING IN AN INCREASE OF DISCHARGE PRESSURE					1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1997011600496	19970116	00496	CE  	1997	1	16	AU960862         	1	19960430	G	7120	J1245412	MOUNT           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE MOUNTING	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1210 				286011R			(AUS) FORWARD LH RUBBER ENGINE MOUNT PERISHED AND HOLED - SUSPECT  CAUSED BY EXHAUST AFTER PROTECTIVE HEAT SHROUD FELL O	FF					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997011600497	19970116	00497		1997	1	16	AU960863         	1	19960624	G	7120	14W677	MOUNT           		14W678A     						LYC   	O540  	IO540K1C5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	ENGINE MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OUTBOARD LOWER ENGINE MOUNT ATTACHMENT FITTING CRACKED - CRACK LENGTH 38.1MM (1.5IN) - AIRCRAFT IS A RILEY CONV	ERSION AND THE DEFECT IS PART OF THAT CONVERSION										3	O			1E4	5	C	P6EA	 
1997011600498	19970116	00498	EU  	1997	1	16	AU960864         	1	19960603	G	6320	711	BOLT            	AEROSP      	BEVELGEARBOX	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR XMSN	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					711		945			(AUS) MAIN GEARBOX BEVEL GEAR BOLTS LOOSE - FOUND DURING INSPECTION IAWAD/ECUR/21						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997011600499	19970116	00499	WP  	1997	1	16	AU960865         	1	19960620	G	2910	467031	UNION           	BENDIX      	REGULATOR   	DOUG  	DC4   	C54E        	3021530	WP  										MAIN HYD SYS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			AU	S 					8V0202					(AUS) HYDRAULIC PRESSURE REGULATOR `T' UNION CRACKED AND LEAKING FROM  THE AREA OF THE UNION NECK IN THE VICINITY OF A P	REVIOUS WELD REPAIR - CRACK LENGTH 20MM (0.787IN) - LOSS OF HYDRAULIC FLUID					2	L	7	4 	4R				A762    					 
1997011600500	19970116	00500	EU  	1997	1	16	AU960866         	1	19960621	G	5620	SD3117982	WINDOW          			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  	HARTZL	HCB5M	HCB5MP3     	GL  	PAX COMPT WINDOW	SEPARATED       	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		CR	CRUISE         	1			AU	S 										(AUS) PASSENGER OUTER WINDOW AT SEAT POSITION 7A SEPARATED DURING  FLIGHT - INSPECTION FOUND THAT THE WINDOW PANE AND TH	E RUBBER SEAL WERE MISSING - THIS WINDOW HAD BEEN REPLACED ON 04 JUNE 1996- LOSS ATTRIBUTED TO REUSE OF ORIGINAL SEAL DU	RING WINDOW REPLACEMENT - SUSPECT SEAL HAD BEEN DETERIORATED BY ENGINE EXHAUST GASSES				2	H	7	2 	4T	4	T		A41EU   	E4EA	6	C	P44GL	 
1997011600501	19970116	00501		1997	1	16	AU960867         	4	19960621	G	6113	22501215	BULKHEAD        			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY				PROPELLER ASSY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER SPINNER BULKHEAD CRACKED IN AREA OF INNER RING - MOUNT BACK PLATES PNO C504-6/2 ALSO CRACKED						1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1997011600502	19970116	00502	GL  	1997	1	16	AU960868         	1	19960221	G	3246		WHEEL           			AMTR  	MAXAIR	XP503       	9570746	GL  	ROTAX 	503   	ROTAX503    	55555	EU  					LG WHEEL/BRAKE S	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			LD	LANDING        	1			AU	S 										(AUS) LH WHEEL FAILED DUE TO INSUFFICIENT WELD - PERSONNEL/MAINTENANCE ERROR - THIS DEFECT WAS RECEIVED FROM THE AUF AND	 IS FOR INFORMATION ONLY					1	H	7	1 	3I	3	I	NT	EXPA1H71	EXPE3I				 
1997011600503	19970116	00503		1997	1	16	AU960872         	1	19960331	G	7820		MUFFLER         								ROTAX 	912   	ROTAX912    	55555	EU  					ENG NOISE SUPPRS	FAILED          	W				K	E			NONE                    	ENGINE SHUTDOWN         			O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) ENGINE TAIL PIPE SEPARATED FROM MUFFLER - THIS DEFECT WAS  RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY											3	I			EXPE3I				 
1997011600504	19970116	00504	GL  	1997	1	16	AU960873         	1	19960406	G	3213		AXLE            			AMTR  	MAXAIR	XP503       	9570746	GL  	ROTAX 	503   	ROTAX503    	55555	EU  					MAIN GEAR SYS	FAILED          	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		CL	CLIMB          	1			AU	S 										(AUS) LH AXLE FAILED - LH WHEEL AND AXLES SEPARATED FROM LANDING GEAR  LEG HELD ONLY BY BRAKE CABLE - AIRCRAFT HAD HEAVY	 LANDING TWO DAYS PREVIOUS - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY					1	H	7	1 	3I	3	I	NT	EXPA1H71	EXPE3I				 
1997011600505	19970116	00505	EU  	1997	1	16	AU960874         	2	19960401	G	8500		ENGINE          			AMTR  	MAXAIR	XP503       	9570746	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					ENGINE (RECIPROC	FAILED          	W				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			AU	S 										(AUS) ENGINE RAN ROUGH AND STOPPED - AIRCRAFT LANDED IN SHALLOW WATER  ON BEACH DAMAGING ELEVATOR AND ELEVATOR CONTROL R	OD - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY					1	H	7	1 	3I	3	I	NT	EXPA1H71	EXPE3I				 
1997011600506	19970116	00506	EU  	1997	1	16	AU960875         	1	19960622	G	5210		LOCK            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					CREW-PASS DOOR S	REQ LUBE        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PASSENGER DOOR COULD NOT BE OPENED FROM INSIDE AIRCRAFT -WHEN OPENED FROM OUTSIDE THE DOOR MECHANISM SOUND	ED ROUGH IN OPERATION - MECHANISM WAS LUBRICATED AND EXERCISED AND NOW OPERATES NORMALLY					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997011600507	19970116	00507	CE  	1997	1	16	AU960876         	1	19960412	G	5712		RIB             			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING RIBS AND SKINS CRACKED IN AREA OF WHEEL WELLS						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997011600508	19970116	00508		1997	1	16	AU960877         	4	19960610	G	2565	3499	SLIDE           			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					EMERGENCY EQUIP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			877  		3499					(AUS) DOOR 3R SLIDE FAILED TO DROP OUT OF CONTAINER						2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1997011600509	19970116	00509	EA  	1997	1	16	AU960878         	2	19960621	G	7310	3040637	FUEL LINE       	PWA         	PT6A65      	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENG,FUEL DIST SY	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					32212		32212			(AUS) PIPE BETWEEN FUEL FLOW TRANSMITTER AND FUEL CONTROL UNIT WORN  THROUGH IN THREE PLACES DUE TO CONTACT WITH GENERAT	OR COOLINGDUCT - FUEL LEAKING FROM PIPE					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997011600510	19970116	00510	NM  	1997	1	16	AU960879         	1	19960622	G	3231	82910010177	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LG EXT-RETRACT S	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DOOR ALUMINIUM HYDRAULIC PIPE LEAKING FROM PIN HOLE ON BEND RADIUS						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997011600511	19970116	00511	NM  	1997	1	16	AU960880         	1	19960625	G	3244	319K281	TYRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LG WHEEL/BRAKE S	DEFLATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			550  		1777					(AUS) LH MAIN LANDING GEAR OUTER TYRE DEFLATED - CARCASS PLY SEPARATION CAUSED LEAKAGE FROM INNER LINER VENT HOLES						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997011600512	19970116	00512	SO  	1997	1	16	AU960881         	2	19960618	G	8530		CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	R ENG CYL NR 6	SEPARATED       	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							243678R			(AUS) LH ENGINE NO6 CYLINDER SEPARATED - SEE MDR 96/0906 FOR FURTHER INFORMATION						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997011600513	19970116	00513	CE  	1997	1	16	AU960882         	1	19960621	G	7500		DUCT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENG,BLEED AIR SY	LEAKING         	W				K	E			NONE                    	ENGINE SHUTDOWN         			J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 							PCE70273			(AUS) RH ENGINE FIRE WARNING SYSTEM ACTIVATED - INVESTIGATION COULD  FIND NO FAULTS EXCEPT FOR A FEW MINOR LEAKS FROM TH	E BLEED AIR DUCTS WHICH MAY OR MAY NOT HAVE CAUSED THE FIRE WARNING					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997011600514	19970116	00514		1997	1	16	AU960883         	1	19960619	G	7820	MAI10	DIFFUSER        		MAIRHS      						ROTAX 	912   	ROTAX912    	55555	EU  					ENG NOISE SUPPRS	CRACKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			283  				4380796			(AUS) MUFFLER FORWARD INLET DIFFUSER CRACKED AND SEPARATED FROM MUFFLER BODY											3	I			EXPE3I				 
1997011600515	19970116	00515	CE  	1997	1	16	AU960884         	1	19960501	G	3220	11582006821	PLATE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NOSE-TAIL GEAR S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1037 							(AUS) NOSE LANDING GEAR SHOCK ABSORBER REINFORCEMENT PLATE CRACKED IN  LOWER WELDED AREA - CRACK LENGTH 28MM (1.1IN)						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997011600516	19970116	00516		1997	1	16	AU960885         	1	19960619	G	7820	MAI10	DIFFUSER        		MAI         						ROTAX 	912   	ROTAX912    	55555	EU  					ENG NOISE SUPPRS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			174  				4076053			(AUS) MUFFLER FORWARD DIFFUSER CRACKED RADIALLY FROM DIFFUSER HOLE											3	I			EXPE3I				 
1997011600517	19970116	00517		1997	1	16	AU960886         	1	19960619	G	7820	MAI10	DIFFUSER        		MAILHSRHS   						ROTAX 	912   	ROTAX912    	55555	EU  					ENG NOISE SUPPRS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			291  				4380746			(AUS) MUFFLER FORWARD DIFFUSER CRACKED AND SEPARATED FROM MUFFLER BODY											3	I			EXPE3I				 
1997011600518	19970116	00518	EU  	1997	1	16	AU960887         	1	19960411	G	3240		LOOM            			AIRBUS	320   	A320212     		EU  										LG WHEEL/BRAKE S	TRANSPOSED      	W				K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR WHEEL SPEED TRANSDUCER HARNESSES TRANSPOSED - NO1 WHEEL TRANSDUCER LOOM CONNECTED TO NO2 WHEE	L AND VICE VERSARESULTING IN NO1 BRAKE RELEASING WHEN NO2 WHEEL SKIDDING - NO2 TYRE BLEW OUT DAMAGING NO1 WHEEL AND NO2 	BRAKE ASSEMBLY -PERSONNEL/MAINTENANCE ERROR				2	L	7	2 	4F			RT	A28NM   					 
1997011600519	19970116	00519	EU  	1997	1	16	AU960888         	1	19960504	G	2782	02832ANSSN01	ACTUATOR        			AIRBUS	320   	A320212     		EU  										NR 2 SLAT OUTB	FAULTY          	W		A		K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 					02832ANSS					(AUS) NO2 SLAT RH OUTBOARD SLAT ACTUATOR FAULTY - SUSPECT MOISTURE INGRESS CAUSED FREEZING AT ALTITUDE PREVENTING SLAT A	CTUATION					2	L	7	2 	4F			RT	A28NM   					 
1997012800005	19970128	00005	GL  	1997	1	28	AU960889         	3	19960508	G	6110	3AF32C504C	PROPELLER       	MCAULY      	3AF32C504C  	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY S	FOD DAMAGE      	W				K				NONE                    				C			F.O.D.                    			LD	LANDING        	1			AU	S 			36   		930486		1266139C	930486		(AUS) RH PROPELLER STUCK SHEEP ON LANDING ROLL - SUBSEQUENT INSPECTION FOUND BLADE LOOSE IN HUB						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997012300047	19970123	00047	SO  	1997	1	23	AU960890         	2	19960428	G	8530	276347R	BOLT            	CONT        	CYLINDER    	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	R ENGINE CYLINDE	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 			1198 		276347R		276347R			(AUS) ENGINE CYLINDER ROCKER SHAFT RETAINING BOLTS FAILED						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997012300048	19970123	00048	GL  	1997	1	23	AU960891         	3	19960627	G	6111	FC76632R	BLADE           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY S	UNDERSIZE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			42   		AA			ED3061		(AUS) PROPELLER BLADES UNDERSIZE AS PER MANUFACTURERS MINIMUM LIMITS INMANUAL - PROPELLER MODEL IN LOGBOOK INCORRECT - C	YLINDER PRESSUREDECAL INCORRECT - PERSONEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1997012300049	19970123	00049	NE  	1997	1	23	AU960892         	2	19960625	G	7321	WYG29323ANSETT	FCU             								GE    	CF6   	CF680A      	30025	NE  					ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 					WYG29323ANS		580169			(AUS) LH ENGINE FUEL CONTROL UNIT FAULTY											4	F			E13NE				 
1997012300050	19970123	00050	CE  	1997	1	23	AU960893         	1	19960627	G	5530	9664000011	RIB             	BEECH       	96640000608 	BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	VERT STAB STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					TE750					(AUS) VERTICAL STABILISER AFT SPAR UPPER RIB PNO 96-640000-11 AND LOWERRIB PNO 96-640000-105 SEVERELY CORRODED - RIBS SU	PPORT RUDDER PIVOT FLANGES - INVESTIGATION FOUND MORE CORROSION IN FUSELAGE AND AFT CABIN FLOOR STRUCTURE, LUGGAGE DOOR 	FRAME - STEP SUPPORT,WINGS, NACELLES AND LH ENGINE MOUNT STRUCTURE BEHIND FIREWALL -  AIRCRAFT HAS OPERATED IN A SALT WA	TER ENVIRONMENT SINCE 1980			1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997012300051	19970123	00051	CE  	1997	1	23	AU960894         	1	19960611	G	5711	5122031	SPAR CAP        	CESSNA      	402         	CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING MAIN SPAR UPPER SPAR CAP CONTAINED SCATTERED PATCHES OF  EXFOLIATION CORROSION IN AREA FROM OUTBOARD OF EN	GINE NACELLE TO THE WING TIP					1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997012300052	19970123	00052	SO  	1997	1	23	AU960895         	2	19960603	G	7414	91090044	SHAFT           	SLICK       	4347        	HUGHES	269   	269C        	4470504	WP  	CONT  	O360  	IO360C      	17025	SO  					ELEC PWR SUPPLY	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					91090044		L3455336A			(AUS) LH MAGNETO BREAKER POINT DRIVE SHAFT FRACTURED IN AREA OF CAM  SLOT						1	G	7	1 	3O	3	O		4H12    	E1CE				 
1997012300053	19970123	00053	GL  	1997	1	23	AU960896         	3	19960627	G	6110	C83860	CLAMP           			BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720A1B    	41546	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER ASSY S	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								BJ1511		(AUS) PROPELLER CLAMP FAULTY - CLAMP APPEARS TO HAVE FORGING FLAW -  SUSPECT MANUFACTURING FAULT						1	L	7	2 	3O	3	O		3A20    	1E15	5	C	P6EA	 
1997012300054	19970123	00054	NM  	1997	1	23	AU960897         	1	19960509	G	3213	015T15048	CYLINDER        			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4576ANSETT					(AUS) RH MAIN LANDING GEAR OUTER CYLINDER AFT TRUNNION CRACKED AND CORRODED IN AREA OF FILLET SEAL						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1997012300055	19970123	00055	NM  	1997	1	23	AU960898         	1	19960406	G	3213	R7904ANSETTSN	CYLINDER        			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			33912		R7904ANSETT					(AUS) RH MAIN LANDING GEAR OUTER CYLINDER AFT TRUNNION CRACKED AND CORRODED IN AREA OF FILLET SEAL						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1997012300056	19970123	00056	SO  	1997	1	23	AU960899         	2	19960623	G	7414	103493932	COVER           	BENDIX      	S6RN1205    						CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	ELEC PWR SUPPLY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A27432					(AUS) MAGNETO CORRODED BETWEEN MAGNETO COVER PNO 10-349393-2 AND CAPACITOR PNO 10-349276											3	O			E5CE	5	C	P21EA	 
1997012300057	19970123	00057	NE  	1997	1	23	AU960900         	2	19960627	G	7260	601017079	SEAL            	ROTOL       	GEARBOX     	FOKKER	F27   	F27MK500    	4990629	EU  	RROYCE	DART  	DART5357R   	54509	NE  	ROTOL	R4304	R1934304    	EU  	TURBINE ENG. ACC	LEAKING         	W				K				NONE                    				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			AU	S 					EWA1897					(AUS) NO2 ENGINE ACCESSORY GEARBOX ALTERNATOR DRIVE PAD 'GITZ' SEAL  DAMAGED AND LEAKING - LOSS OF APPROXIMATELY 3.5 PIN	TS OF OIL					2	H	7	2 	4T	4	T		A817    	E297	6	C	P899	 
1997012300058	19970123	00058	GL  	1997	1	23	AU960901         	3	19960627	G	6110	B3807	NUT             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY S	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			42   		AA			ED3061		(AUS) PROPELLER PISTON UNIT LOOSE ON CONTROL ROD DUE TO INSUFFICIENT TORQUE ON THE NUT PNO B3807 - PERSONNEL/MAINTENANCE	 ERROR - SEEALSO MDR 96/0891					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1997012300059	19970123	00059	EU  	1997	1	23	AU960902         	1	19960629	G	2434	503106680003	GENERATOR       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					DC GENERATOR-ALT	DISINTEGRATED   	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 					TE1117					(AUS) NO1 ENGINE DRIVEN GENERATOR DISINTEGRATED - DAMAGE CAUSED TO NO1 ENGINE THROTTLE CABLE - INVESTIGATION FOUND DEFOR	MATION OF THE BACK PLATE CASTING WHICH MAY HAVE ALLOWED A MISALIGNMENT RESULTING IN INTERNAL FAILURE					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997012300060	19970123	00060	CE  	1997	1	23	AU960903         	1	19960618	G	3240	1280509102	PIPE            			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LG WHEEL/BRAKE S	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 							62530	931710		(AUS) BRAKE PIPE FAILED AT FLARE - LOSS OF HYDRAULIC FLUID CAUSED BRAKE FAILURE ALLOWING AIRCRAFT TO RUN OFF AIRSTRIP AN	D DAMAGE PROPELLER - SUSPECT CAUSED BY ROCKS ON LANDING STRIP					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997012300061	19970123	00061	EU  	1997	1	23	AU960904         	1	19960614	G	2842	NB57D2411	TRANSMITTER     			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUEL INDICATION	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RH TIP TANK FUEL CONTENTS TRANSMITTER FLOAT MISSING - THE FLOAT  RETAINING CLIP WAS STILL IN POSITION SUGGESTING T	HAT THE FLOAT HAD DISINTEGRATED					1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1997012300062	19970123	00062	EA  	1997	1	23	AU960905         	2	19960625	G	8520	LW14658	CRANKSHAFT      	LYC         	O320H2AD    						LYC   	O320  	O320H2AD    	41508	EA  					R ENGINE POWER S	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					RL428076T		RL428076T			(AUS) CRANKSHAFT HAD 0.9144MM (0.036IN) RUNOUT AT PROPELLER FLANGE - CAMSHAFT LOBES (2OFF0 BADLY WORN - LIFTER BODIES BA	DLY PITTED -FOUND DURING ENGINE BULK STRIP										3	O			E274				 
1997012300063	19970123	00063	SO  	1997	1	23	AU960906         	2	19960608	G	8520	243678R	GEAR            	CONT        	IO520CB     	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	R ENGINE POWER S	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					243678R		243678R			(AUS) CRANKCASE CRACKED - CAMSHAFT GEAR AND MAGNETO IDLER GEAR DAMAGED - MAGNETO IDLER GEAR SHAFT BENT - MAGNETO DRIVE G	EARS BADLYSPALLED - FOUND DURING ENGINE BULK STRIP FOLLOWING DISCOVERY OF  SEVERAL BROKEN CYLINDER BASE STUDS - PERSONNE	L/MAINTENANCE ERROR				1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997012300064	19970123	00064	SO  	1997	1	23	AU960907         	2	19960613	G	8540	653583	GEAR            	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	R ENGINE REAR SE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4456		276021R			(AUS) ENGINE STARTER SHAFT GEAR AND CRANKSHAFT GEAR TEETH WORN ABNORMALLY - ENGINE STARTER KIT PNO EQ6642						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997012300065	19970123	00065	SO  	1997	1	23	AU960908         	2	19960426	G	8540	653583	SHAFT           	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	R ENGINE REAR SE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4541		239180H			(AUS) ENGINE STARTER SHAFT AND CRANKSHAFT GEAR TEETH WORN EXCESSIVELY -FOUND DURING ENGINE BULK STRIP FOR CRACKED CRANKC	ASE IN AREA OFNO4 CYLINDER BASE STUDS - THIS ASSEMBLY IS THE IMPROVED TYPE PURCHASED IN KIT FORM FROM CONTINENTAL AS PNO	 EQ6042				1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997012800006	19970128	00006	SO  	1997	1	28	AU960910         	2	19960605	G	7314	A227413	PUMP            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					ENG,FUEL DIST SY	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			129  		A227413		294578R			(AUS) ENGINE DRIVEN FUEL PUMP SUSPECT FAULTY - STRIP INSPECTION COULD  FIND NO FAULTS						1	H	7	1 	3O	3	O		3A21    	E5CE				 
1997012300066	19970123	00066	SW  	1997	1	23	AU960911         	1	19960614	G	6220	47120252011	GRIP            	BELL        	4763BKH4    	BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435D1B   	41516	EA  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					K363		RL314952			(AUS) MAIN ROTOR HEAD GRIPS CRACKED - FOUND DURING EDDY CURRENT  INSPECTION IAW AD/BELL47/92 AMDT4						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997012300067	19970123	00067	CE  	1997	1	23	AU960912         	1	19960625	G	2720	505243263	ARM             		505243264   	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	RUDDER CONTROL S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS RUDDER PEDAL ARMS BOTH CRACKED IN UPPER AREA OF THE 'I' SECTION - FOUND DURING INSPECTION IAW AD/BEECH55/69	 AMDT2					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997012300068	19970123	00068	SO  	1997	1	23	AU960913         	1	19960603	G	5310		FUSELAGE        			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320C1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	FUSELAGE STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRFRAME STRUCTURE CONTAINED NUMEROUS TYPES OF CORROSION IN ALL  AREAS						1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
1997012300069	19970123	00069	CE  	1997	1	23	AU960914         	1	19960702	G	3297	ISEI3	WIRE            	CESSNA      	310R        	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LG POSITION IND	SEPARATED       	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE PULLED OUT OF PREVIOUS BUTT CONNECTOR REPAIR						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
1997012300070	19970123	00070	GL  	1997	1	23	AU960915         	3	19960507	G	6110	A3237	PISTON          	HARTZL      	HCC2YK2CFU  	PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					AV3743			AV3743		(AUS) PROPELLER PISTON WORN THROUGH ANODISING - CYLINDER SLUDGED - DURING ASSEMBLY THE FEATHER AND LATCH ANGLES WERE FOU	ND TO BE APPROXIMATELY 2 DEGREES TOO FINE					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997012300071	19970123	00071	CE  	1997	1	23	AU960916         	1	19960531	G	3230	224110213	PIVOT           	CESSNA      	R182        	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					LG EXT-RETRACT S	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR ACTUATOR GEAR PLATE BEARING SPIGOT ON THE PIVOT ASSEMBLY CRACKED - LOSS OF HYDRAULIC BRAKE FL	UID					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1997012300072	19970123	00072	NE  	1997	1	23	AU960917         	3	19960624	G	6111	851630	DEICE BOOT      	HAMSTD      	BLADE       	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER ASSY S	SHORT CIRCUIT   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8278 		851630			RH860108		(AUS) PROPELLER BLADE DE-ICE BOOT BURNT OUT - BLADE HOLED						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
1997012300073	19970123	00073	EA  	1997	1	23	AU960918         	2	19960614	G	8530	75089	PISTON          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	R ENGINE CYLINDE	DAMAGED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			826  		109153		L10560			(AUS) ENGINE NO3 CYLINDER PISTON RING FOUND BROKEN AND PISTON DAMAGED  IN LINE WITH EXHAUST VALVE - SUSPECT CAUSED BY DE	TONATION					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997012300074	19970123	00074	CE  	1997	1	23	AU960919         	1	19960703	G	3297	D6H22	WIRE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LG POSITION IND	CHAFED          	W				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR POSITION INDICATOR CIRCUIT BREAKER TRIPPED FOLLOWING GEAR SELECTION 'DOWN' - INVESTIGATION FOUND WIRE	 NO.D6H22 HAD CHAFED AGAINST THE OXYGEN BOTTLE LH SIDE ZONE 121 APPROXIMATELY  152MM (6IN) FROM J162					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997012300075	19970123	00075	NM  	1997	1	23	AU960920         	1	19960618	G	2613	116982195	CONNECTOR       			BOEING	737   	737376      		NM  										FIRE DETECT SYS	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 					116982195					(AUS) NO1 ENGINE OVERHEAT WARNING SYSTEM FAULTY - LOOP A AND B CORE  DETECTOR, CONNECTORS D3088 AND D3096 AND ASSOCIATED	 WIRING REPLACED					2	L	7	2 	4F			RT	A16WE   					 
1997012300076	19970123	00076	NM  	1997	1	23	AU960921         	1	19960617	G	2730	029	SPRING          			BOEING	737   	737376      		NM  										ELEVATOR CONTROL	BROKEN          	W				K				NONE                    				O	F		OTHER                     	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 			20496		029					(AUS) CO-PILOT'S CONTROL COLUMN ELEVATOR FEEL AND CENTERING UNIT PRIMARY SPRING BROKEN						2	L	7	2 	4F			RT	A16WE   					 
1997012300077	19970123	00077	WP  	1997	1	23	AU960922         	1	19960617	G	5315	992239501	FLOORBEAM       			DOUG  	DC9   	DC933F      	302207A	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					BS 937	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEVEL 2 CORROSION ON LOWER `T' OF FLOORBEAM AT FUSELAGE STN 937.						2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997012300078	19970123	00078	WP  	1997	1	23	AU960923         	1	19960617	G	5320	1766648	ANGLE           			DOUG  	DC9   	DC933F      	302207A	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					ATTACH FITTING S	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEVEL 2 EXFOLIATION CORROSION AT BOTTOM OF `T' ANGLE (ATTACHMENT ANGLE) OF FUSELAGE TO CANTED PRESSURE PANEL IN RH	 WHEEL WELL					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997012300079	19970123	00079	EU  	1997	1	23	AU960924         	1	19960413	G	2910		PTU             			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MAIN HYD SYS	MALFUNCTIONED   	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) HYDRAULIC SYSTEM POWER TRANSFER UNIT (PTU) CAUSING HIGH  TEMPERATURE WARNING IN THE 'YELLOW' HYDRAULIC SYSTEM						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997012300080	19970123	00080	EA  	1997	1	23	AU960925         	2	19960617	G	8520	SL13884M03	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	R ENGINE POWER S	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L251261			(AUS) ENGINE NO1 MAIN BEARING SEIZED TO CRANKSHAFT DURING START -  ENGINE HAD DONE 17.5 HOURS SINCE A TOP OVERHAUL WAS C	ARRIED OUT					1	L	7	2 	3O	3	O		1A10    	E14EA	5	C	P9EA	 
1997012300081	19970123	00081	SO  	1997	1	23	AU960926         	1	19960630	G	3710		PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PRESS-VAC DIST S	INCORRECT FIT   	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 							L466461			(AUS) LH ENGINE VACUUM PUMP INCORRECTLY SEATED ON ACCESSORY PLATE - THEPUMP WAS RESTING ON AN ACCESSORY CASE OIL HOSE 45	 DEGREE FITTING - THE VACUUM PUMP HAD BEEN FITTED JUST PRIOR TO FLIGHT - ENGINE  OIL LEAKING - PERSONNEL/MAINTENANCE ERR	OR				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997012300082	19970123	00082	EU  	1997	1	23	AU960927         	1	19960705	G	3230	HTE210014	ACTUATOR        		HTE96811    	BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR (MOTOR) WAS DEFECTIVE - THE ACTUATOR WAS CHANGED AND GROUND CHECKS CARRIED OU	T - ON 'DOWN' SELECTION THE POWER TRANSFER UNIT RAN CONTINUOUSLY - THE FAULT WAS TRACED TO THE LANDING GEAR SELECTOR VAL	VE - THE VALVE WAS REPLACED - LANDING GEAR SYSTEM CHECKED SERVICEABLE				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997012300083	19970123	00083	SO  	1997	1	23	AU960928         	2	19960606	G	8530	649317CEAI	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	R ENGINE CYLINDE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1428 				247926R			(AUS) ENGINE NO2 ENGINE CYLINDER CRACKED IN THE INLET PORT - CRACK LENGTH APPROXIMATELY 40MM (1.5IN) - THE CRACK WAS DIF	FICULT TO SEE DUE TO THE ENGINE BAFFLING					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
1997012300084	19970123	00084	EA  	1997	1	23	AU960929         	2	19960618	G	8520	LW18402	CRANKCASE       			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L10013394			(AUS) ENGINE CRANKCASE CRACKED IN THE LH FORWARD SECTION - CRACK LENGTH APPROXIMATELY 32MM (1.25IN) - CRANKCASE HAD BEEN	 WELD REPAIRED IN THIS AREA AT LAST OVERHAUL - SUSPECT INCORRECT HEAT TREATMENT  FOLLOWING WELD REPAIR					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997012300085	19970123	00085	GL  	1997	1	23	AU960930         	1	19960514	G	5720	V61	BLOCK           			AMTR  	EAGLE 	CHRISEAGLE2 		GL  	LYC   	O360  	IO360A1A    	41514	EA  	SNSNCH	76E	76EM8       	EA  	OUTER WING SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					V61					(AUS) DURING INVESTIGATION OF A WRINKLE IN THE FABRIC COVERING ON THE  TOP WING (INBOARD) TRAILING EDGE, THE DRAG/ANTI-D	RAG WIRE REAR ATTACHMENT BLOCK AT REAR SPAR WAS FOUND BROKEN WHICH IN TURN CAUSED THE TRAILING EDGE TO CENTRE HOOP ATTAC	HMENT BLOCK TO FAIL				1	Q	7	1 	3O	3	O		EXPA1Q71	1E10	5	N	P4EA	 
1997012300086	19970123	00086	GL  	1997	1	23	AU960931         	1	19960708	G	2120		INTAKE          			AMTR  	VAREZE	VARIEZE     		GL  	LYC   	O320  	O320D3G     	41508	EA  					AIR DISTRIBUTION	BLOCKED OFF     	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) COCKPIT AIR INTAKE ILLEGALLY MODIFIED (SEALED OFF) PREVENTING AIR INTAKE INTO COCKPIT AND CAUSING LACK OF OXYGEN T	O PILOT AND PASSENGER - TWO MONTHS PRIOR TO THIS INCIDENT THE PILOT SEALED THE COCKPIT AIR INTAKE OPENING LOCATED IN FRO	NT OF THE NOSE WHEELCOMPARTMENT WITH MASKING TAPE - TO COMPENSATE FOR THE AIR LOSS,  THE PILOT WOULD OPEN THE LANDING LI	GHT TO RECEIVE COOLING AIR INTO THE CABIN - BECAUSE THIS FLIGHT WAS GOING TO BE AROUND 9500 FT AND HEADING SOUTH (FROM N	ORTHERN QUEENSLAND) THE LANDING LIGHTWAS CLOSED CAUSING THE LACK OF AIR TO THE COCKPIT - UNAPPROVED PART/MODIFICATION		1	M	7	1 	3O	3	O		EXPA1M71	E274				 
1997012300087	19970123	00087	CE  	1997	1	23	AU960932         	1	19960301	G	3230	98812021	SOLENOID        			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	LG EXT-RETRACT S	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 							27006112			(AUS) LANDING GEAR CONTROL SOLENOID PNO 9881202-1 HAD INSULATION BREAKDOWN - LANDING GEAR FAILED TO EXTEND ELECTRICALLY 	- EXTENDED SAFELY WITH MECHANICAL HYDRAULIC HAND PUMP					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997012300088	19970123	00088	EA  	1997	1	23	AU960933         	2	19960503	G	8530	LW16740	VALVE           			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	R ENGINE CYL EXH	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					L2162651A		L2162651A			(AUS) ENGINE NO3 CYLINDER EXHAUST VALVE BROKEN - DAMAGE TO PISTON AND  CYLINDER BORE - SUSPECT CAUSED BY OPERATING ENGIN	E AT CONTINUOUS HIGH TEMPERATURES WITH LEAN MIXTURES					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997012300089	19970123	00089	CE  	1997	1	23	AU960934         	1	19960702	G	2450	TR992	POWER UNIT      			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AC POWER DISTRIB	BURNT OUT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH NO4 POWER UNIT BURNT OUT CAUSING COMPLETE FAILURE TO THE RH CABIN LIGHTING CIRCUIT - INVERTER PNO 18-994 FOUND 	UNSERVICEABLE PROBABLY DUE TO THE FAILURE OF POWER UNIT - FOUND DURING INSPECTION IAW AD/ELECT/67 AND ALC IB 90-001					2	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
1997012300090	19970123	00090	CE  	1997	1	23	AU960935         	1	19960703	G	5511	53200197	SPAR            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	HORZ STAB SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAILPLANE FORWARD SPAR AND CENTRE SKIN CRACKED - FOUND DURING  INSPECTION IAW AD/C170/59						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997012800007	19970128	00007	NE  	1997	1	28	AU960936         	2	19960703	G	7200		ENGINE          								PWA   	PW120 	PW123       		NE  					ENGINE (TURBINE/	POWER LOSS      	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 							PCE123269			(AUS) NO1 ENGINE POWER LOSS - ON TAKE-OFF ENGINE POWER SET AT 90%  TORQUE - POWER ROLLED BACK ON NO1 ENGINE BY 2% THEN R	ECOVERED -TORQUE INCREASED TO 100% - TAKE-OFF WAS ABORTED AT APPROXIMATELY 85 KNOTS										4	T			E20NE				 
1997012300091	19970123	00091	WP  	1997	1	23	AU960938         	2	19960526	G	7261	8650914	GASKET          								GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	TURBINE ENGINE O	DETERIORATED    	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 							P42140			(AUS) TURBINE OIL SYSTEM SCAVENGE PUMP COVER GASKET DETERIORATED AND LEAKING - COVER WAS LOOSE ALTHOUGH THE RETAINING SC	REWS WERE STILL TIGHT										4	T			E4WE	6	C	P61GL	 
1997012300092	19970123	00092	NE  	1997	1	23	AU960939         	2	19960527	G	7260	3022375	OIL SEAL        								PWA   	PWA120	PW125B      		NE  					TURBINE ENG. ACC	DAMAGED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 							TM124050			(AUS) ENGINE DRIVEN HYDRAULIC PUMP DRIVE SEAL LEAKING - PARTIAL LOSS OF ENGINE OIL											4	T			E20NE				 
1997012300093	19970123	00093	EA  	1997	1	23	AU960940         	2	19960709	G	7414	M3548	ROTOR           	SLICK       	4270        	CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	ELEC PWR SUPPLY	BROKEN          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			920  		92100032		L3256036A	DJ049		(AUS) MAGNETO ROTOR SHAFT FAILED AT THE CONTACT BREAKER END AT BASE OF CUTOUT FOR FIBRE CAM CAUSING TOTAL FAILURE OF MAG	NETO - UNIT HAD OPERATED FOR 312 HRS SINCE INSPECTION IAW AD/ELEC/48					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P857	 
1997012300534	19970123	00534	SO  	1997	1	23	AU960941         	1	19960705	G	7922	L153668A	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	AC,ENG OIL DIST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L153668A		L153668A			(AUS) ENGINE OIL COOLER THERMOSTATIC BYPASS VALVE (VERNATHERM) RETENTION NUT SEPARATED FROM UNIT - THE NUT WAS LOCATED I	N THE OIL SUPPLY LINE TO THE OIL COOLER - SUSPECT AD/LYC/78 HAD NOT  BEEN COMPLIED WITH					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997012300535	19970123	00535	CE  	1997	1	23	AU960942         	1	19960704	G	3230	HM4	ROD END         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LG EXT-RETRACT S	FAILED          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LH MLG UPLOCK PUSH/PULL ROD ASSEMBLY PNO 0641142-1 FAILED AT ROD END IN THE AREA JUST OUTBOARD OF CHECKNUT PNO AN3	16-4R ON THE INBOARD RODEND - SUSPECT CAUSED BY SLIGHT MISRIGGING OF LANDING  GEAR					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997012300536	19970123	00536		1997	1	23	AU960943         	1	19960626	G	6120	70953	NUT             	MCAULY      	C290D2T4    															PROP CNTRL SYS	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1930 		70953					(AUS) PROPELLER CONSTANT SPEED UNIT (CSU) FLYWEIGHT PIN NUT SEPARATED -THE PIN SECURES THE FLYWEIGHT AND DISC TOGETHER (	FLYWEIGHT ASSEMBLY PNO A20063) - THE PIN THEN MOVED OUT DUE TO CENTRIFUGAL FORCE CONTACTING THE INSIDE BODY AND WORE A G	ROOVE 0.794MM (0.0312IN) DEEP - THE HEAD OF THE PIN HAD ALSO WORN AWAY - THE NUT TAB WASHER WAS FOUND JAMMED BETWEEN THE	 SPEEDER SPRING AND THE END FITTING - THE FLYWEIGHT SPACERS WERE FOUND LOOSE IN  FLYWEIGHT CHAMBER BUT THERE WAS NO SIGN	 OF THE NUT															 
1997012300537	19970123	00537	EA  	1997	1	23	AU960944         	2	19960705	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D3G     	41508	EA  					R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2000 							(AUS) CRANKSHAFT CRACKED INTERNALLY - CRACK LENGTH APPROXIMATELY 50MM  (2IN) - THE CRACK WAS LOCATED AT THE BASE OF A CO	RROSION PIT AND WAS FOUND AFTER THE INTERNAL DIAMETER WAS HONED TO REMOVE THE  PIT - FOUND DURING INTERNAL CORROSION INS	PECTION OF A CRANKSHAFT IAW LYCOMING SB 505A									3	O			E274				 
1997012300538	19970123	00538		1997	1	23	AU960945         	1	19960628	G	6120	B20897	COVER           	MCAULY      	DCFS290D7T3 															PROP CNTRL SYS	OVERSIZE        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			97   		790876					(AUS) PROPELLER CONSTANT SPEED UNIT (CSU) CONTROL SHAFT AND COVER  LEAKING OIL - THE CSU WAS RETURNED TO THE OVERHAUL FA	CILITY WHEREIT WAS DISMANTLED - INSPECTION OF THE COVER BORE FOUND IT  OVERSIZE BY 0.0762MM (0.003IN) - INSPECTION FOUND	 22 OTHER COVERS IN STOCK TO BE ALSO OVERSIZE - MANUFACTURING ERROR/QUALITY CONTROL PROBLEM																	 
1997012300539	19970123	00539	SO  	1997	1	23	AU960946         	2	19960705	G	8520	6461402	STUD            			CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	R ENGINE POWER S	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			76   				1106324A			(AUS) NO5 CYLINDER BASE STUD (1OFF) SHEARED OFF - STUD WAS FOUND IN  BOTTOM COWL						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1997012300540	19970123	00540	EU  	1997	1	23	AU960947         	1	19960711	G	5713	0303	STRINGER        			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING AND ENGINE NACELLE UPPER EIGHT STRINGERS (4OFF  EACH SIDE) BETWEEN RIBS 6 AND 8 CRACKED - FOUND DUR	ING INSPECTION IAW PARTENAVIA SB93 AND AD/P68/42					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997012300541	19970123	00541		1997	1	23	AU960949         	4	19960626	G	3418	450742	DETECTOR        		C522014     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STALL WARNING SYSTEM LIFT DETECTOR MICROSWITCH OPEN CIRCUITED						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997012300542	19970123	00542	EU  	1997	1	23	AU960950         	1	19960424	G	5711		SPAR WEB        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OUTER WING REAR SPAR WEB CRACKED AT APPROXIMATELY STN 5115  RUNNING FROM LOWEST RIVET - CRACK LENGTH 5MM (0.196	IN) - FOUND DURING EDDY CURRENT INSPECTION IAW ER F28-57-10-22C PART 2					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997012300543	19970123	00543	EU  	1997	1	23	AU960951         	1	19960503	G	2450	72741484OAV2	TERMINAL        			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AC POWER DISTRIB	ARCING          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) NO1 AC GENERATOR BUS TERMINAL BLOCK `A' PHASE `B' STUD ARCING						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997012300544	19970123	00544	SO  	1997	1	23	AU960952         	2	19960214	G	8520	629726AB	CAMSHAFT        	CONT        	TSIO520E    	CESSNA	402   	402A        	207590M	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	R ENGINE POWER S	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1232 		183701R					(AUS) RH ENGINE CAMSHAFT FAILED AND COMPLETELY SEPARATED APPROXIMATELY 30MM (1.18IN) FROM THE FORWARD END CONTAINING THE	 EXPANSION PLUG					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997012300545	19970123	00545	CE  	1997	1	23	AU960953         	1	19960709	G	2721	12614715	WHEEL           		12614621    	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RUDDER CONTROL S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TRIM WHEEL GEAR PNO 1261471-5 AND SPROCKET PNO 1261462-1  HAD WORN TEETH - TEETH WERE WORN TO THE EXTENT TH	AT THE TEETH SLIPPED PAST EACH OTHER WITHOUT ACTIVATING THE CHAIN					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997012300546	19970123	00546	SO  	1997	1	23	AU960954         	1	19960701	G	3260	451848	MICROSWITCH     			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					LG POSITION IND	ARM BROKEN      	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH ACTUATING LEVER ARM BROKEN OFF						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1997012300547	19970123	00547	CE  	1997	1	23	AU960955         	1	19960630	G	3244	277K061	TYRE            	GOODYEAR    	5003064     	CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	LG WHEEL/BRAKE S	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					SAM13					(AUS) LH MAIN LANDING GEAR TYRE JAMMED IN WING CUTOUT PREVENTING LANDING GEAR FROM LOCKING IN THE `UP' POSITION - SUSPEC	T CAUSED BY OUTSIDE DIAMETER OF TYRE BEING TOO LARGE - TYRE WAS R1 (1ST RETREAD)					1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997012300548	19970123	00548		1997	1	23	AU960956         	4	19960113	G	2561	9409871940986	CYLINDER        	DUNLOP      	LIFEJACKET  	SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					EMERGENCY EQUIP	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					940987194					(AUS) LIFE JACKET CO2 INFLATION BOTTLES UNSCREWED FROM FIRING MECHANISM- LIFE JACKET SERIAL NUMBERS 9409871 AND 9409866 	- ANTI-TAMPERING INDICATORS WERE STILL IN PLACE					2	G	7	2 	4U	4	U		H4EU    	E12NE				 
1997012300549	19970123	00549	EU  	1997	1	23	AU960957         	1	19960703	G	2910	332A75211100	PIPE            			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					MAIN HYD SYS	CRACKED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NO2 HYDRAULIC SYSTEM PIPE CRACKED AND LEAKING - LOSS OF HYDRAULICFLUID						2	G	7	2 	4U	4	U		H4EU    	E12NE				 
1997012300550	19970123	00550	SO  	1997	1	23	AU960958         	1	19960703	G	2425		AMMETER         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	AC INDICATING SY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AMMETER FLUCTUATING OVER 20 AMPS						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997012800014	19970128	00014	GL  	1997	1	28	AU960959         	2	19960712	G	7320	6870035	PIPE            	ALLSN       	250C20R     	HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20R2    		GL  					ENG,FUEL CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CAE295286		CAE295286			(AUS) ENGINE POWER TURBINE GOVERNOR TO FUEL CONTROL UNIT PIPE (PC LINE)LOOSE AT FCU END - `B' NUT HOLDING BY APPROXIMATE	LY HALF A THREAD					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997012300551	19970123	00551	GL  	1997	1	23	AU960960         	2	19960626	G	7240	6899081	LINER           	ALLSN       	250C30      	SNIAS 	350   	AS350B      	8680801	EU  	ALLSN 	250C  	250C30      	03013	GL  					TURBINE ENGINE C	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			921  		CAT90303		CAE890502			(AUS) ENGINE COMBUSTION LINER FAILED - SPACER CLIPS (6OFF) PNO 23003111SEPARATED FROM LINER PRIMARY SECTION PNO 23004562	 AT THE VACUUM BRAZED JOINT ALLOWING THE WATER SHIELD TO SEPARATE FROM THE LINER AND AT LEAST ONE CLIP TO CONTACT THE TU	RBINE CAUSING FOD - PERSONNEL/MAINTENANCE ERROR - DEFECTIVE REPAIRS CARRIED OUT IN USA				1	G	7	1 	3U	3	U		H9EU    	E1GL				 
1997012300552	19970123	00552	SO  	1997	1	23	AU960961         	2	19960712	G	8550	N3N	SPRING          	CESSNA      	12509211    	CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	R ENGINE INT OIL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					N3N		240713R	942330		(AUS) ENGINE OIL FILTER ADAPTER PNO 1250921-1 BYPASS SPRING BROKEN INTOTHREE PIECES - VALVE CAP PNO 0756022-1 FOUND ON O	IL PRESSURE RELIEF VALVE SEAT - FURTHER INSPECTION FOUND SPRINGS ON TWO OTHER AIRCRAFT BADLY WORN					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997012300553	19970123	00553	SW  	1997	1	23	AU960963         	1	19960615	G	6320	214040118001	BEARING         	BELL        	TRANSMISSION	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR TRANS	FAULTY          	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 			3944 		ABW45031		CPPS60614			(AUS) TRANSMISSION MAIN INPUT QUILL DUPLEX BEARING CONTAINED ONE DELAMINATED BALL - NIL DAMAGE TO INNER RACE						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1997012300554	19970123	00554		1997	1	23	AU960964         	4	19960521	G	2370		CVR SYSTEM      	FRCHLD      	A100A       	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					AUDIO/VIDEO MONI	INCORRECT WIRED 	W		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT VOICE RECORDER INCORRECTLY WIRED - RECORDS ONLY AREA MICROPHONE CHANNEL - PERSONNEL/MAINTENANCE ERROR						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997012300555	19970123	00555	CE  	1997	1	23	AU960965         	1	19960623	G	3230	8A0900046	HOSE            		8000        	CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  					LG EXT-RETRACT S	INCORRECT REPAIR	W				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		TO	TAKEOFF        	1			AU	S 					80068					(AUS) RH MAIN LANDING GEAR FLOAT RETRACTION ACTUATOR LEAKING FROM `UP' PRESSURE HOSE - LOSS OF HYDRAULIC FLUID - INVESTI	GATION FOUNDTHAT HOSE BRAIDING HAD BEEN DAMAGED SOME TIME PREVIOUSLY AND DAMAGE HAD BEEN REPAIRED WITH AN UNKNOWN BLACK 	SUBSTANCE AND WRAPPED WITH PVC TAPE - SUSPECT DAMAGE AND REPAIR DONE DURING  FLOAT ASSEMBLY - THIS AIRCRAFT IS FITTED WI	TH WIPLINE FLOATS - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED REPAIR			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
1997012300556	19970123	00556	CE  	1997	1	23	AU960966         	1	19960620	G	2510		SEAT BELT       			CESSNA	182   	182         	2072702	CE  										FLIGHT COMPARTME	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT HARDWARE AND WEBBING WAS OF AUTOMOTIVE ORIGIN -  PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART						1	H	7	1 	3O			NT	3A13    					 
1997012300557	19970123	00557	SO  	1997	1	23	AU960967         	2	19960702	G	8520		COLLAR          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	R ENGINE POWER S	WORN            	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							9175244			(AUS) ENGINE LOW OIL PRESSURE - SUSPECT CRANKSHAFT TRANSFER COLLAR OR  MAIN BEARINGS WORN						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P920	 
1997012300558	19970123	00558	SO  	1997	1	23	AU960968         	2	19960625	G	8530	646743	PISTON          	CONT        	TSIO360GB4  	MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360G    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	R ENGINE CYLINDE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			1000 		309728					(AUS) NO3 CYLINDER/PISTON COMBINATION INCORRECT - A +015IN OVERSIZE  PISTON PNO 646743 WAS FITTED TO A STANDARD SIZE CYL	INDER PNO 649484 - PISTON HAD PICKED UP IN CYLINDER BORE - METAL CONTAMINATION OF OIL SYSTEM - CYLINDER HAD BEEN CHANGED	 ON 13NOVEMBER 1995 AT 2027 HOURS - PERSONNEL/MAINTENANCE ERROR -  UNAPPROVED PART				1	L	7	1 	3O	3	O		2A3     	E9CE	5	C	P920	 
1997012300559	19970123	00559	SO  	1997	1	23	AU960969         	2	19960624	G	7414	1051324	SPRING          	BENDIX      	S6RN25      	CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470J       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	ELEC PWR SUPPLY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					510001		403623A	621508		(AUS) LH MAGNETO IMPULSE COUPLING SPRING BROKEN						1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P880	 
1997012800015	19970128	00015	EA  	1997	1	28	AU960970         	2	19960701	G	7414	91050078	POINTS          	SLICK       	4347        	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360C1A   	41514	EA  					ELEC PWR SUPPLY	OUT OF ADJUST   	W				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			AU	S 					91050078					(AUS) MAGNETO POINTS GAP TOO SMALL						1	G	7	1 	3O	3	O		4H12    	1E10				 
1997012300560	19970123	00560	CE  	1997	1	23	AU960971         	1	19960628	G	7430	A1196A	SWITCH          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	IGNITION SWITCH	BURNT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L240676			(AUS) ENGINE IGNITION SWITCH CONTACT CUPS (3OFF) PNO A-1196-A AND  TERMINAL BOARD PNO A-546-A WORN AND BURNT - FOUND DUR	ING INSPECTION IAW AD/ELEC/59 AMDT1					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997012300561	19970123	00561	CE  	1997	1	23	AU960972         	1	19960501	G	2510		SEAT BELT       			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	FLIGHT COMPARTME	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELTS CONTAINED NON APPROVED HARDWARE AND WEBBING - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1997012300562	19970123	00562	CE  	1997	1	23	AU960973         	1	19960704	G	2510		SEAT BELT       			CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	FLIGHT COMPARTME	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELTS MANUFACTURED FROM AUTOMOTIVE HARDWARE AND WEBBING - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1997012300563	19970123	00563		1997	1	23	AU960974         	4	19960703	G	2562	506590101	BATTERY         	NARCO       	ELT         	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	TSIO520C    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	EMERGENCY LOCATO	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					22042					(AUS) ELT BATTERY PACK LEAKING - CORROSIVE MATERIAL FROM THE BATTERY HAD LEAKED ONTO THE AIRFRAME STRUCTURE CAUSING CORR	OSION - EXPIRRATION DATE OF BATTERY IS 22 MAY 1996					1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P21EA	 
1997012300564	19970123	00564	SO  	1997	1	23	AU960975         	2	19960621	G	7414	A27432	CAPACITOR       	BENDIX      	1200SERIES  						CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	ELEC PWR SUPPLY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A27432		1219148B	735437		(AUS) RH MAGNETO CAPACITOR CORRODED IN AREA OF CONTACT WITH CASE											3	O			E5CE	5	C	P21EA	 
1997012300565	19970123	00565	NM  	1997	1	23	AU960978         	1	19960609	G	2910	82940010107	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					MAIN HYD SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			17897							(AUS) HYDRAULIC PIPE LEAKING FROM PIN HOLE IN PIPE - LOSS OF HYDRAULIC FLUID						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997012300566	19970123	00566	EU  	1997	1	23	AU960979         	1	19960715	G	3210		BEARING         			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MAIN GEAR SYS	REQ LUBE        	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RH AND LH MAIN LANDING GEAR SIDE STAY BEARINGS STIFF - AN ATTEMPTTO REGREASE THE BEARINGS FOUND THAT THE GREASE WO	ULD NOT ENTER TH INNER BEARINGS - REMOVAL OF THE SIDE STAYS FOUND THAT THE  EXISTING GREASE WAS HARD AND DETERIORATED -	 BEARINGS LAST GREASEDIN APRIL 1996 - AIRCRAFT HAS A LOW UTILISATION RATE				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997012300567	19970123	00567	NM  	1997	1	23	AU960980         	1	19960602	G	2782	111015	PISTON          			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					LIFT AUGMNT SYS	FRACTURED       	W				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			AU	S 					ANSETTSN0					(AUS) NO6 LEADING EDGE KRUEGER FLAP ACTUATOR PISTON PNO 1110-15 BROKEN IN TWO IN THE RADIUS OF THE EXTENDED LOCKING KEY 	GROOVE					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997012300568	19970123	00568	NM  	1997	1	23	AU960981         	1	19960626	G	3246	0534	WHEEL           			BOEING	737   	737376      		NM  										LG WHEEL/BRAKE S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0534					(AUS) LH OUTBOARD MAIN WHEEL ASSEMBLY OUTBOARD HALF CRACKED IN SPOKE - FOUND DURING ROUTINE TYRE CHANGE						2	L	7	2 	4F			RT	A16WE   					 
1997012300569	19970123	00569	NM  	1997	1	23	AU960982         	1	19960506	G	2820	69588063	DIODE           			BOEING	737   	737377      		NM  										FUEL DISTRBUTION	BURNT OUT       	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO1 REFUELLING VALVE DIODE ASSEMBLY M565 BURNT OUT - SUSPECT CAUSED BY MOISTURE INGRESS WITH SUBSEQUENT FREEZING A	T ALTITUDE					2	L	7	2 	4F			RT	A16WE   					 
1997012300570	19970123	00570	NE  	1997	1	23	AU960983         	2	19960624	G	7261		O-RING          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE ENGINE O	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 							LF05597A			(AUS) NO4 ENGINE MAIN OIL FILTER CAP `O' RING SEAL DAMAGED (CUT) - LOSSOF ENGINE OIL						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997012300571	19970123	00571		1997	1	23	AU960984         	4	19960618	G	2216	7002800914	ACTUATOR        			AMD   	FALC50	FALCON900   	2700160	EU  										AUTOPILOT TRIM S	FAULTY          	W				K				NONE                    				F	W		FLT CONT AFFECTED         	INADEQUATE Q C            		NR	NOT REPORTED   	1			AU	S 			18   							(AUS) AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) YAW DAMPER LINEAR ACTUATOR PIN G TO ACTUATOR HOUSING HAD NO INTERNAL CONNEC	TION THEREFORE THE ACTUATOR WAS NOT ELECTRICALLY BONDED TO THE AIRCRAFT MAKING THE SYSTEM SUSCEPTIBLE TO INDUCED VOLTAGE	.				2	L	7	3 	4F			RT	A46EU   					 
1997012300572	19970123	00572	GL  	1997	1	23	AU960985         	3	19960501	G	6140	86595610	SWITCH          			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP CNTRL SYS	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER BETA PRESSURE SWITCH FAULTY						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997012300573	19970123	00573	GL  	1997	1	23	AU960986         	3	19960702	G	6140	8659565	SWITCH          			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP CNTRL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER BETA PRESSURE SWITCH FAULTY						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997012300574	19970123	00574	CE  	1997	1	23	AU960987         	1	19960709	G	6120	8659565	SWITCH          			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP CNTRL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER BETA PRESSURE SWITCH FAULTY						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997012800016	19970128	00016	EU  	1997	1	28	AU960988         	1	19960509	G	2782	02967SN012	ACTUATOR        			AIRBUS	320   	A320212     		EU  										WING TE SYS	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 					02967SN01					(AUS) WING LHS OUTBOARD NO2 AND NO5 SLAT ACTUATORS FAULTY - SUSPECT  CAUSED BY INCREASED BREAKOUT TORQUE AT LOW TEMPERAT	URES					2	L	7	2 	4F			RT	A28NM   					 
1997012300575	19970123	00575	EU  	1997	1	23	AU960989         	1	19960305	G	5220		DOOR            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					CABIN EMERG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH OVERWING EMERGENCY EXIT DOOR OUTER RADIUS CRACKED IN THE FOLLOWING AREAS:-1. RH FORWARD EMERGENCY EXIT C	RACKED IN FORWARD AND AFT LOWER CORNERS - CRACK LENGTH 25.4MM (1IN) 2. LH REAR EMERGENCY EXIT CRACKED IN LOWER AFT CORNE	R - CRACK LENGTH 6.35MM (0.25IN)				2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997012300576	19970123	00576	EU  	1997	1	23	AU960990         	1	19960305	G	5312		WEB             			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD WEB LOCATED BETWEEN HORIZONTAL BEAMS II AND III AND VERTICAL BEAMS 425L AND 1050L CRACKED V	ERTICALLY - CRACK LENGTH 52MM (2IN) - FOUND DURING EDDY CURRENT INSPECTION IAW ER F28-53-10-15K PART 4					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997012300577	19970123	00577	NM  	1997	1	23	AU960991         	1	19960701	G	5310	A0202	FRAME           			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN FRAME SYS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1170 							(AUS) FUSELAGE UPPER FRAME TUBE BROKEN IN AREA OF LH GEARBOX MOUNT CLUSTER						1	G	7	1 	3O	3	O		H10WE   	E274				 
1997012300578	19970123	00578	CE  	1997	1	23	AU960992         	1	19960501	G	3260	12430192	BRACKET         			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LG EXT-RETRACT S	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR SQUAT SWITCH BRACKET BENT						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997012300579	19970123	00579	GL  	1997	1	23	AU960993         	3	19960626	G	6114		HUB             			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	PROPELLER ASSY S	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			235  					691800		(AUS) PROPELLER HUB CRACKED AND LEAKING IN TWO PLACES						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997012300580	19970123	00580	EA  	1997	1	23	AU960994         	2	19960501	G	7320	3024973	COUPLING        			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENG,FUEL CONTROL	SHEARED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			DE	DESCENT        	1			AU	S 							57172			(AUS) RH ENGINE DRIVEN FUEL PUMP TO FCU DRIVE COUPLING SHEARED - SUSPECT CAUSED BY FAILURE OF FCU FRONT BEARING - ENGINE	 SUFFERED A MAJOR OVERTEMPERATURE, OVERTORQUE AND OVERSPEED					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997012300581	19970123	00581	CE  	1997	1	23	AU960995         	1	19960628	G	3230	1018100211	TORQUE TUBE     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LG EXT-RETRACT S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR RETRACTION MECHANISM TORQUE TUBE HAD A GROOVE  WORN AROUND ONE END - SUSPECT CAUSED BY DISPLACED	/INCORRECTLYFITTED ADEL CLIP					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997012300582	19970123	00582	CE  	1997	1	23	AU960996         	1	19960626	G	5312	121340711	BULKHEAD        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOORPOST BULKHEAD CRACKED						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997012300583	19970123	00583	CE  	1997	1	23	AU960997         	1	19960704	G	3231	08411065	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LG EXT-RETRACT S	BROKEN          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LH MAIN LANDING GEAR INNER DOOR OPERATING LINKAGE IDLER BELLCRANKBROKEN						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997012300584	19970123	00584	SW  	1997	1	23	AU960999         	1	19960722	G	7712	2060704481	PIPE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENG PWR IND SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TORQUE SYSTEM ALUMINIUM PIPE CRACKED AND LEAKING -  AIRCRAFT IMPORTED FROM SOUTH AFRICA						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997012300585	19970123	00585	WP  	1997	1	23	AU961000         	2	19960719	G	7261		OIL SYSTEM      	GARRTT      	TPE33110UF  						GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	TURBINE ENGINE O	CONTAM-METAL    	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 			3207 		P42036		P42036			(AUS) ENGINE OIL SYSTEM CONTAMINATED WITH METAL PARTICLES											4	T			E4WE	6	C	P61GL	 
1997012300586	19970123	00586	EU  	1997	1	23	AU961001         	1	19960716	G	2910	HTE8815	VALVE           			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	MAIN HYD SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH HYDRAULIC SHUT-OFF VALVE FAILED TO OPERATE						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1997012300587	19970123	00587	NM  	1997	1	23	AU961002         	1	19960614	G	6710	A4372	LOCATING TAB    	ROBSIN      	JACKSHAFT   	ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN RTR CNTRL S	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COLLECTIVE JACKSHAFT LOCATING TAB BROKEN ALLOWING JACKSHAFT TO FLOAT AND THE MAIN ROTOR REAR CONTROL PUSH-PULL TUB	E TO CONTACTTHE LOWER FAIRING FRAME					1	G	7	1 	3O	3	O		H10WE   	E274				 
1997012800017	19970128	00017	EU  	1997	1	28	AU961003         	1	19960601	G	2910	EO2001170	HOUSING         			AIRBUS	320   	A320212     		EU  										MAIN HYD SYS	CRACKED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					0092ANSETT					(AUS) YELLOW HYDRAULIC SYSTEM GROUND SERVICING MANIFOLD CRACKED ON REAR FACE IN AREA OF FOUR HOLE PLUGS - REMOVAL OF PLU	GS REVEALED THAT THE MANIFOLD HOUSING AND PLUG THREADS WERE CRACKED COMPLETELY  THROUGH - LOSS OF HYDRAULIC FLUID					2	L	7	2 	4F			RT	A28NM   					 
1997012300588	19970123	00588	SO  	1997	1	23	AU961004         	2	19960508	G	8520	IO520F	CRANKCASE       			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			538  				572674			(AUS) CRANKCASE CRACKED FROM NO2 CYLINDER MOUNT PAD						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997012300589	19970123	00589	NM  	1997	1	23	AU961005         	1	19960513	G	2612	894481	DETECTOR        			BOEING	737   	737377      		NM  										FIRE DETECTION S	CONTAM-WATER    	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) APU FIRE DETECTOR CONTAMINATED WITH MOISTURE AND OTHER FOREIGN MATERIAL - FALSE FIRE WARNING CAUSED EXTINGUISHER T	O BEDISCHARGED					2	L	7	2 	4F			RT	A16WE   					 
1997012300590	19970123	00590	NM  	1997	1	23	AU961006         	1	19960528	G	2913	20894	BEARING         	ABEX        	56193       	BOEING	737   	737377      		NM  										MAIN HYD SYS	FAILED          	W		A		K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 					220500MFS					(AUS) SYSTEM 'A' HYDRAULIC PUMP ELECTRIC MOTOR FAILED - INVESTIGATION  FOUND METAL CONTAMINATION - FURTHER INVESTIGATION	 FOUND THAT THE LOCKWIRE ON TWO ATTACHMENT SCREWS PNO NAS1352-08H6 SECURING  CYLINDER BARREL PNO 56550 TO CYLINDER BEARI	NG PNO 56445 WASMISSING - LOCKWIRE ON THE REMAINING FOUR SCREWS WAS BROKEN - IN  ADDITION THE TRUNNION BEARING PNO 21830	 WAS BRINNELED - PUMP HOUSING THRUST BEARING PNO 20894 BREAKING UP			2	L	7	2 	4F			RT	A16WE   					 
1997012300591	19970123	00591	EA  	1997	1	23	AU961007         	2	19960722	G	8550	LW13388	SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	R ENGINE INT OIL	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 							L381661A			(AUS) ENGINE OIL FILTER ADAPTER SEAL SPLIT AND LEAKING - SUSPECT DUE TO DETERIORATION CAUSED BY OLD AGE						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997012300592	19970123	00592	NE  	1997	1	23	AU961008         	2	19960416	G	7230	310454601	BEARING         								PWA   	PWA120	PW125B      		NE  					TURBINE ENGINE C	WORN            	W				E				ENGINE SHUTDOWN         				O			OTHER                     			DE	DESCENT        	1			AU	S 							124027			(AUS) RH ENGINE NO4 BEARING FAILED - COMPRESSOR AND TURBINE RUBBING											4	T			E20NE				 
1997012300593	19970123	00593	NM  	1997	1	23	AU961009         	1	19960717	G	3520	E28180	PBE             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					CREW&PASS OXYGEN	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ARHH0308					(AUS) PROTECTIVE BREATHING EQUIPMENT (PBE) HAD UNCOMMANDED EXPANSION INSTORAGE CASE						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997012300594	19970123	00594	SO  	1997	1	23	AU961010         	2	19960722	G	8550		SPRING          	CONT        	TS10520EB   						CONT  	O520  	TSIO520E    	17040	SO  					R ENGINE INT OIL	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			AU	S 							271406R			(AUS) ENGINE OIL PRESSURE RELIEF VALVE SPRING WAS INCORRECT PART - CORRECT SPRING PNO 634150 - UNAPPROVED PART - ENGINE 	WAS A CONTINENTAL REBUILD ENGINE - SEE ALSO MDR 96/0726										3	O			E8CE				 
1997012300595	19970123	00595	CE  	1997	1	23	AU961011         	1	19960621	G	5712	A120119	WEB             	CESSNA      	441         	CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	OUTER WING SYS	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING REAR SPAR WEB DISBONDED IN AREA BEHIND ENGINE FIRE BOTTLE- FOUND DURING ULTRASONIC INSPECTION IAW AD/CESSN	A400/103 AMDT2					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997012300596	19970123	00596	CE  	1997	1	23	AU961012         	1	19960719	G	3233	98820212	BEARING         			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LG EXT-RETRACT S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR BEARING END CRACKED IN AREA OF ROLL PINS AS INDICATED IN CESSNA SB95-20						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997012300597	19970123	00597	SW  	1997	1	23	AU961014         	1	19960627	G	2436	484183	RELAY           			GULSTM	112   	114         	7630314	SW  	LYC   	O540  	IO540T4B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	DC REGULATOR	MIS WIRED       	W				K				NONE                    				H	W		ELECT. POWER LOSS-50 PC   	INADEQUATE Q C            		DE	DESCENT        	1			AU	S 										(AUS) OVERVOLTAGE RELAY INCORRECTLY WIRED - 'BATTERY' AND 'LOAD' LEADS TRANSPOSED CAUSING OVERVOLTAGE RELAY TO MALFUNCTI	ON - LOSS OF BATTERY VOLTAGE - LOGBOOK FAILED TO REVEAL ANY WORK CARRIED OUT  IN THIS AREA - PERSONNEL/MAINTENANCE ERROR					1	L	7	1 	3O	3	O		A12SO   	1E4	5	C	P920	 
1997012300598	19970123	00598	SO  	1997	1	23	AU961015         	2	19960528	G	8520		BOLT            			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	R ENGINE POWER S	BROKEN          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							286610R			(AUS) ENGINE NO5 CYLINDER HOLDDOWN NUTS MISSING AND THROUGH BOLTS  BROKEN - CRANKCASE CRACKED						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997012300599	19970123	00599	CE  	1997	1	23	AU961016         	1	19960625	G	2510		SEAT BELT       			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FLIGHT COMPARTME	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) UNAPPROVED SEAT BELT WEBBING AND HARDWARE - UNAPPROVED PART						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997012300600	19970123	00600	SO  	1997	1	23	AU961017         	1	19960702	G	2120	MS3505821	SWITCH          			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	AIR DISTRIBUTION	BURNT           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 										(AUS) CABIN FRESH AIR BLOWER SWITCH FAULTY - SWITCH WIRES BURNT						1	L	7	1 	3O	3	O		2A13    	E295	5	C	P27EA	 
1997012300601	19970123	00601	CE  	1997	1	23	AU961018         	1	19960619	G	3222	12430211	BEARING         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	NOSE-TAIL GEAR S	INCORRECT FIT   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR OLEO UPPER BEARING PNO 1243021-1 AND RETAINER  PNO 841200-19 SEPARATED - INVESTIGATION FOUND THA	T THE BEARING HAD BEEN INSTALLED UPSIDE DOWN PREVENTING CORRECT SEATING OF THE RETAINER - PERSONNEL/MAINTENANCE ERROR					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P3EA	 
1997012300602	19970123	00602	SO  	1997	1	23	AU961019         	2	19960715	G	7414	10357586	GEAR            	BENDIX      	S6RN205     	CESSNA	402   	402A        	207590M	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ELEC PWR SUPPLY	STRIPPED        	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			AU	S 					6279008ER					(AUS) MAGNETO DISTRIBUTOR GEAR TEETH STRIPPED						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997012300603	19970123	00603	SO  	1997	1	23	AU961020         	2	19960715	G	7414	10382584	POINTS          	BENDIX      	SGRN205     	CESSNA	402   	402A        	207590M	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ELEC PWR SUPPLY	WORN            	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					A103642					(AUS) MAGNETO POINTS WORN						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997012800018	19970128	00018	SO  	1997	1	28	AU961021         	2	19960726	G	7414	10357592	SEAL            	BENDIX      	S6RSC205    	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ELEC PWR SUPPLY	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 			15   		D309606ER					(AUS) MAGNETO OIL SEAL LOOSE IN HOUSING ALLOWING MAGNETO TO FILL WITH  OIL						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997012300604	19970123	00604	EA  	1997	1	23	AU961022         	2	19960612	G	8530	LW11633	CYLINDER        			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	R ENG CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1159 				L1726815			(AUS) ENGINE CYLINDER CRACKED FROM EXHAUST VALVE SEAT THROUGH SPARK  PLUG HOLE						1	L	7	1 	3O	3	O		A18SO   	E223	5	N	P9045	 
1997012300605	19970123	00605	NM  	1997	1	23	AU961023         	1	19960716	G	2910	AS116080264	HOSE            			BOEING	737   	737376      		NM  										MAIN HYD SYS	BURST           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC 'B' SYSTEM ENGINE DRIVEN PUMP PRESSURE HOSE BURST -  LOSS OF HYDRAULIC FLUID						2	L	7	2 	4F			RT	A16WE   					 
1997012300606	19970123	00606	EU  	1997	1	23	AU961024         	1	19960720	G	2750	CHA722438	TORQUE TUBE     			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					FLAP SYS	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH FLAP TORQUE TUBE SHEARED IN AREA OF ATTACHMENT TO LH SHOCK  ABSORBER						2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1997012300607	19970123	00607	EU  	1997	1	23	AU961025         	1	19960726	G	3246	AHA1489	WHEEL           			BAC   	146   	146300A     	1500267	EU  										LG WHEEL/BRAKE S	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					MO187					(AUS) NO4 WHEEL ASSEMBLY HAD APPROXIMATELY 381MM TO 457.2MM (15IN TO 18IN) OF THE OUTER RIM MISSING - TYRE WAS STILL INF	LATED					2	H	7	4 	4F			RT	A49EU   					 
1997012300608	19970123	00608	SO  	1997	1	23	AU961026         	1	19960625	G	2822	10470	CIRCLIP         	WELDON      	BOOSTPUMP   	PIPER 	PA28  	PA28180     	7102808	SO  										FUEL DISTRBUTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			139  		15626					(AUS) FUEL BOOST PUMP BLADE CIRCLIP SNAPPED						1	L	7	1 	3O				2A13    					 
1997012300609	19970123	00609	EU  	1997	1	23	AU961027         	1	19960722	G	6410	330A12000534	BLADE           			SNIAS 	SA330 	SA330J      	8680612	EU  	TMECA 	TURMO4	TURMO4C     	60008	EU  					TAIL ROTOR BLADE	FAULTY          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					WAC6143					(AUS) TAIL ROTOR BLADE LEADING EDGE EROSION STRIP SEPARATED FROM BLADE CAUSING HIGH FREQUENCY VIBRATION - SUSPECT CAUSED	 BY DEFECTIVE BOND BETWEEN BLADE LEADING EDGE AND EROSION STRIP					2	G	7	2 	4U	4	U		H4EU    	E10EU				 
1997012300610	19970123	00610	SO  	1997	1	23	AU961028         	1	19960723	G	3213	5768006	HOUSING         			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR OLEO HOUSING ASSEMBLY CRACKED FROM TOP TO BOTTOM THROUGH THE SHARP RADIUS AT THE BASE OF THE 	SIDE BRACE ATTACHMENT LUG - LOSS OF OLEO PRESSURE					1	L	7	2 	4T	4	T		A23SO   	E4EA	6	C	P15EA	 
1997012300611	19970123	00611	EA  	1997	1	23	AU961029         	2	19960717	G	7314	75247	PUMP            			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENG,FUEL DIST SY	FAULTY          	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							L2173248A			(AUS) ENGINE DRIVEN FUEL PUMP PUMPING FUEL INTO OIL SUMP LOWERING OIL  VISCOSITY AND SUBSEQUENTLY LOWERING OIL PRESSURE 	- INVESTIGATION FOUND THE PUMP DRAIN LINE BLOCKED INSIDE PUMP AND FAILURE OF BOTH OIL AND FUEL DIAPHRAGMS					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997012300612	19970123	00612	EU  	1997	1	23	AU961030         	1	19960701	G	2820	F128271	HOSE            			FOKKER	F27   	F27MK100    	4990617	EU  	RROYCE	DART  	DART5147    		EU  	ROTOL	R4304	R1934304    	EU  	FUEL DISTRBUTION	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL PUMP COLLECTOR TANK TO FIREWALL FUEL HOSE LOCATED IN RH WHEEL WELL FRAYED AND WORN - CAUSED BY INCORRECT FITM	ENT OF GREASE NIPPLE ON LANDING GEAR - PERSONNEL/MAINTENANCE ERROR					2	H	7	2 	4T	4	T		A817    	E283	6	C	P899	 
1997012300613	19970123	00613	EU  	1997	1	23	AU961031         	1	19960717	G	3260	RL980961	RELAY           			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  	HARTZL	HCB5M	HCB5MP3     	GL  	LG POSITION IND	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR RELAY FAULTY						2	H	7	2 	4T	4	T		A41EU   	E4EA	6	C	P44GL	 
1997012300614	19970123	00614	CE  	1997	1	23	AU961032         	1	19960715	G	2731		TRIM WHEEL      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR CONTROL	MIS INSTALLED   	W				K				NONE                    				F	W		FLT CONT AFFECTED         	INADEQUATE Q C            		TO	TAKEOFF        	1			AU	S 										(AUS) TRIM WHEEL INCORRECTLY INSTALLED DURING PREVIOUS MAINTENANCE - INCORRECT ORIENTATION OF TRIM INDICATION IN RELATIO	N TO TRIM TAB - PERSONNEL/MAINTENACE ERROR					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997012300615	19970123	00615		1997	1	23	AU961033         	4	19960714	G	2210		AUTOPILOT       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AUTOPILOT SYSTEM	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AUTOPILOT SUSPECT FAULTY - GROUND CHECK COULD FIND NO FAULTS - DEFECT NOT CONFIRMED						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997012300616	19970123	00616	SO  	1997	1	23	AU961034         	1	19960625	G	2434	30081001	GENERATOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					DC GENERATOR-ALT	FAULTY          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 					555					(AUS) RH DC GENERATOR FAULTY						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997012300617	19970123	00617	CE  	1997	1	23	AU961035         	1	19960724	G	7160		BALANCE TUBE    			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENG,FUEL DIST SY	SEPARATED       	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 							069700R	735173		(AUS) ENGINE INDUCTION SYSTEM BALANCE TUBE SEPARATED AT ONE END - MOUNT ALSO BROKEN AWAY FROM TUBE						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997012300618	19970123	00618	CE  	1997	1	23	AU961036         	1	19960724	G	6120	8692454	VALVE           			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP CNTRL SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4213 							(AUS) PROPELLER FEATHERING VALVE WORN IN ROLL PIN AREA OF THE REAR CLEVIS						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997012300619	19970123	00619	CE  	1997	1	23	AU961037         	1	19960702	G	2720	35524138	BELLCRANK       	BEECH       	B58         	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	RUDDER CONTROL S	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) COPILOTS RUDDER BELLCRANK BROKEN IN THE VICINITY OF THE CROSSOVER PUSHROD ATTACHMENT HORN - FURTHER INVESTIGATION 	FOUND THAT THE FAILURE WAS CAUSED BY THE INCORRECT REMOVAL OF THE RUDDER STOP BAR AND EMBRITTLEMENT OF THE BAR					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997012300620	19970123	00620	CE  	1997	1	23	AU961038         	1	19960724	G	3411		STATIC SYSTEM   			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ENVIRONMENT DATA	MIS INSTALLED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) UNAPPROVED INSTALLATION OF INSTRUMENT STATIC LINE SYSTEM - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
1997012300621	19970123	00621	EU  	1997	1	23	AU961039         	1	19960723	G	2731		TRIM            			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ELEVATOR CONTROL	FOD JAMMED      	W		A		K				NONE                    				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) ELEVATOR TRIM JAMMED - INSPECTION FOUND A 100MM (4IN) PAPER CLIP LODGED IN THE CONTROL CABLES ADJACENT TO THE ELEV	ATOR TRIM CHAIN (CLIP IS PART OF THE AIRCRAFT TRIM AND IS NORMALLY ATTACHED TO A BULKHEAD IN THE FLIGHT DECK) - INVESTIG	ATION ALSO FOUND THEGEARBOX CHAIN LOWER ATTACHMENT BOLT CASTELLATED NUT AND WASHER MISSING				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997012300622	19970123	00622	GL  	1997	1	23	AU961040         	2	19960728	G	7323	23007506	GOVERNOR        	ALLSN       	250C20      	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			172  		CAE821056		CAE821056			(AUS) ENGINE N2 GOVERNOR FAULTY - SUSPECT INTERNAL FAILURE						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997012300623	19970123	00623	GL  	1997	1	23	AU961041         	3	19960726	G	6110		PROPELLER       			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER ASSY S	SLUDGED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 								DJ10647A107		(AUS) LH AND RH PROPELLERS SLUDGED - PROPELLERS WOULD NOT FEATHER						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997012300624	19970123	00624	GL  	1997	1	23	AU961042         	3	19960722	G	6110		PROPELLER       			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER ASSY S	SLUDGED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 								DJ8817A		(AUS) LH PROPELLER SLUDGED - PROPELLER WOULD NOT FEATHER						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997012300625	19970123	00625	EA  	1997	1	23	AU961043         	2	19960422	G	8520	LW16514	CAMSHAFT        	LYC         	LW16507     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	R ENGINE POWER S	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L54272TL		L54272T			(AUS) LH AND RH ENGINES HAD SPALLED CAMSHAFT EXHAUST LOBES AND ASSOCIATED TAPPETS - BOTH THE ENGINES  ARE OF LATE MODIFI	CATION STATUS WITH LARGE TAPPETS AND LUBRICATING SLOTS IN THE TAPPET GUIDE BORES - LW16702 ADDITIVE IS USED AT EACH OIL 	CHANGE - METAL CONTAMINATION OF OIL SYSTEM				1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
1997012300626	19970123	00626	EA  	1997	1	23	AU961044         	2	19960613	G	8530	3116	STUD            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	R ENGINE CYLINDE	BROKEN          	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) ENGINE ROCKER ARM STUD BROKEN - PUSHROD BENT - LOSS OF ENGINE OIL						1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
1997012300627	19970123	00627	EA  	1997	1	23	AU961045         	2	19960726	G	7322	13662	BRACKET         		MA45        						LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENG,FUEL CONTROL	CRACKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 					7503812		L3414636A			(AUS) CARBURETTOR FLOAT BRACKET CRACKED CAUSING CARBURETTOR FLOODING											3	O			E286	5	C	P27EA	 
1997012300628	19970123	00628	CE  	1997	1	23	AU961046         	1	19960710	G	5312		BULKHEAD        			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRONT DOOR POST BULKHEAD CRACKED ON BOTH SIDES - CRACK  LENGTHS - RH SIDE 6.35MM (0.25IN) - LH SIDE 4.762	MM (0.1875IN)					1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
1997020600195	19970206	00195	NM  	1997	2	6	AU961047         	1	19960723	G	3230	54C546349	VALVE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR DOOR SEQUENCING VALVE (SOLENOID) FAULTY						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997020600196	19970206	00196	WP  	1997	2	6	AU961048         	1	19960727	G	6220	269A1329	DROOP STOP      	HUGHES      	269A10025   	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					M/R	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR DROOP STOP RING CRACKED IN SEVERAL PLACES						1	G	7	1 	3O	3	O		4H12    	1E10				 
1997020600197	19970206	00197	NM  	1997	2	6	AU961049         	1	19960726	G	3234	NA16126	O-RING          		AN8156D     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LG EXT-RETRACT S	DETERIORATED    	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE HYDRAULIC UNION (PNO AN815-6D) `O' RING SEAL DETERIORATED AND LEAKING						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997020600198	19970206	00198	EA  	1997	2	6	AU961050         	2	19960711	G	8530	145644	VALVE GUIDE     	CURTIS      		LKHEED	1049  	C121C       	5262118	WP  	WRIGHT	R3350 	R3350*      	67040	EA  	HAMSTD	43E	43E60       	NE  	R ENGINE CYLINDE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			946  		A613		W560299			(AUS) ENGINE CYLINDER EXHAUST VALVE GUIDE WORN AND LOOSE IN CYLINDER HEAD						2	L	7	4 	4R	4	R		6A5     	E272	6	C	P871	 
1997020600199	19970206	00199	EU  	1997	2	6	AU961051         	1	19960730	G	2820	NB57A42463	GASCOLATOR      			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUEL DISTRBUTION	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 							L2550048A			(AUS) RH ENGINE GASCOLATOR BOWL DISLODGED AND THE CLAMP SPRING ARM DISCONNECTED - FUEL LEAKING						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1997020600200	19970206	00200	EU  	1997	2	6	AU961052         	1	19960701	G	2150	B31WA3023	SEPARATOR       			AMD   	FALC50	FALCON900   	2700160	EU  										CABIN COOLING SY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					T556					(AUS) CABIN COOLING SYSTEM LOW PRESSURE WATER SEPARATOR INTERNAL COALESCER SWIRL VANE COLLAPSED - THIS DEFECT WAS RECEIV	ED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ONLY					2	L	7	3 	4F			RT	A46EU   					 
1997020600201	19970206	00201	EU  	1997	2	6	AU961053         	1	19960711	G	3230	C242450061	UPLOCK          			AMD   	FALC50	FALCON900   	2700160	EU  										LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					U375					(AUS) NOSE LANDING GEAR UPLOCK UNIT INTERNAL FAILURE - THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFOR	MATION ONLY					2	L	7	3 	4F			RT	A46EU   					 
1997020600202	19970206	00202	SW  	1997	2	6	AU961054         	1	19960615	G	2910	2781032273	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MAIN HYD SYS	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE LOCATED IN LH ENGINE NACELLE AREA CRACKED AND LEAKING ON BEND RADIUS						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997020600203	19970206	00203	CE  	1997	2	6	AU961055         	1	19960326	G	3210		BUSHING         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MAIN GEAR SYS	MIS MFG         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR SIDE BRACE BUSHES WORN - INVESTIGATION FOUND THAT BUSHES WERE MANUFACTURED FROM INCORRECT MATERI	AL (PHOSPHORBRONZE) - UNAPPROVED PART					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997020600204	19970206	00204	CE  	1997	2	6	AU961056         	1	19960327	G	2750	0860207134	CONTROL CABLE   		0860207135  	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	FLAP SYS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP CABLES PNO 0860207-134 AND PNO 0860207-135 FRAYED						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
1997022000001	19970220	00001	EU  	1997	2	20	AU961057         	1	19960520	G	7540	M61069002	CONTACTOR       			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	ENG,BLEEDAIR IND	OPEN CIRCUIT    	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		NR	NOT REPORTED   	1			AU	S 										(AUS) LH ENGINE ANTI-ICE SYSTEM CONTACTOR OPEN CIRCUIT						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997020600205	19970206	00205	CE  	1997	2	6	AU961058         	1	19960705	G	2140	G721526	PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	HEATING SYSTEM	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			309  							(AUS) CABIN HEATER FUEL PUMP DIAPHRAGM RUPTURED AND LEAKING FUEL INTO  SHROUD - SHROUD DRAIN BLOCKED BY WASP NEST						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997020600206	19970206	00206		1997	2	6	AU961059         	4	19960119	G	2561	80MK2	LIFEVEST        			SKRSKY	S76   	S76A        	8143006	NE  										EMERGENCY EQUIPM	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOT REPORTED THAT LIFEJACKET MAIN WEBBING RESTRAINING STRAP WAS MISSING (FOUND ON FLOOR OF AIRCRAFT) - FURTHER C	HECKING OF AIRCRAFT FLEET FOUND THAT THE STRAP WAS NOT ATTACHED (STITCHED)  TO THE JACKET ON A FURTHER SIXTEEN LIFE JACK	ETS - ON THREE OFTHESE JACKETS THE STRAP WAS ROUTED THROUGH THE JACKET OUTER  VALISE ONLY AND NOT THROUGH THE JACKET ATT	ACHMENT POINT -PERSONNEL/MAINTENANCE ERROR			1	G	7	2 	3U				H1NE    					 
1997020600207	19970206	00207	SO  	1997	2	6	AU961060         	2	19960710	G	8530	125834CCM	CYLINDER        	CONT        	IO520M      	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	R ENGINE CYLINDE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			66   		125834CCM		1258347			(AUS) ENGINE CYLINDER CRACKED IN AREA OF TOP SPARK PLUG HOLE						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997020600208	19970206	00208	SO  	1997	2	6	AU961061         	2	19960711	G	8520		CRANKSHAFT      	CONT        	IO470L      						CONT  	O470  	IO470L      	17026	SO  					R ENGINE POWER S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CS917524L		CS917524L			(AUS) CRANKSHAFT MAIN BEARING JOURNALS 0.0508MM (0.002IN) UNDER MINIMUMALLOWABLE LIMITS - CONNECTING ROD JOURNALS 0.0127	MM (0.0005IN) UNDER MINIMUM ALLOWABLE LIMITS - CRANKCASE MAIN TUNNELS ALSO OUT OF LIMITS										3	O			3E1				 
1997020600209	19970206	00209	WP  	1997	2	6	AU961062         	2	19960701	G	7510		VALVE           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENG,AIR ANTI-ICE	FAULTY          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							P31286			(AUS) RH ENGINE ANTI-ICE VALVE AND PLENUM DRAIN VALVE FAULTY						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
1997020600210	19970206	00210	WP  	1997	2	6	AU961063         	2	19960703	G	7230		DIFFUSER        			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	TURBINE ENGINE C	BIRD STRIKE     	W				K				NONE                    				E	C		VIBRATION/BUFFET          	F.O.D.                    		TO	TAKEOFF        	1			AU	S 							P31182			(AUS) LH ENGINE SUFFERED BIRDSTRIKE - COMPRESSOR DIFFUSER VANE LEADING EDGES ROLLED BACK - BIRD REMAINS FOUND IN DIFFUSE	R, FUEL NOZZLES AND TURBINE EXHAUST PATH					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
1997020600211	19970206	00211	CE  	1997	2	6	AU961064         	1	19960730	G	5753	35165050611	FLAP            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					WING TE SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLAP DAMAGED BY CONTACT WITH UNKNOWN OBJECT - IMPACT DAMAGE ON UNDERSIDE CAUSED BENDING FROM CENTRE WITH BUCK	LING TO THE SPAR AND SKINS MAKING IT UNREPAIRABLE - NO DAMAGE TO MOUNTING POIUNTS OR WING					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1997020600212	19970206	00212	SO  	1997	2	6	AU961065         	2	19960720	G	8520	530386	BEARING         	CONT        	O470L       	CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470L       	17026	SO  	HARTZL	HC82X	HC82XF1     	GL  	R ENGINE POWER S	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					600345		6003405			(AUS) ENGINE NO3 MAIN BEARING SPALLED - BEARING HAD ROTATED						1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P878	 
1997020600213	19970206	00213	NE  	1997	2	6	AU961066         	2	19960719	G	7261	230361401	VALVE           	GARRTT      	230349102   	BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE ENGINE O	FAULTY          	W				K				NONE                    				O	K	J	OTHER                     	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			AU	S 							LF5935A			(AUS) NO2 ENGINE OIL/FUEL HEATER BYPASS VALVE FAULTY						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997020600214	19970206	00214	CE  	1997	2	6	AU961067         	1	19960618	G	3260	602EN16	SWITCH          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					LG POSITION IND	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		DE	DESCENT        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH HAD HIGH RESISTANCE IN THE`DOWN' POSITION						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1997020600215	19970206	00215	NM  	1997	2	6	AU961068         	1	19960723	G	4940	AJA4N176	CONTACTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					APU START-IGN SY	SEIZED          	W				K				NONE                    				O	B		OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			AU	S 					00191					(AUS) APU STARTER CONTACTOR SEIZED						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997020600216	19970206	00216	EU  	1997	2	6	AU961069         	1	19960725	G	3230	1849E	UPLOCK          			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 					LK8607621					(AUS) NOSE LANDING GEAR UPLOCK HOOK FAULTY						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1997020600217	19970206	00217	CE  	1997	2	6	AU961070         	1	19960629	G	3220		FRICTION BRAKE  			CESSNA	650   	650         	2076802	CE  										NOSE-TAIL GEAR S	CONTAM-WATER    	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR CENTERING AND FRICTION BRAKE DAMPER SYSTEM CONTAMINATED WITH WATER CAUSING LUBRICATION TO BE WAS	HED OUT AND PREVENTING NLG FROM RETRACTING - AIRCRAFT WAS LANDING AND TAKING OFF IN HEAVY RAIN					2	L	7	2 	4F				A9NM    					 
1997020600218	19970206	00218	NM  	1997	2	6	AU961071         	1	19960713	G	2434		WIRE            			BOEING	747   	747438      	       	NM  										DC GENERATOR-ALT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO4 GENERATOR FEED WIRE CHAFED THROUGH BY CONTACT WITH CARGO ACCESS DOOR UPPER LATCH						2	L	7	4 	4F			RT	A20WE   					 
1997020600219	19970206	00219	CE  	1997	2	6	AU961072         	1	19960805	G	3233	99810057651	ACTUATOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2332 		ALG1197					(AUS) RT MAIN LANDING GEAR ACTUATOR INTERNAL GEARS STRIPPED - SUSPECT  CAUSED BY ADJUSTMENT OF UPLOCK MICROSWITCH ALLOWI	NG OVERTRAVEL OFTHE ACTUATOR					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
1997020600220	19970206	00220	NM  	1997	2	6	AU961073         	1	19960620	G	3250	276005M7	VALVE           			BOEING	747   	747438      		NM  										ACFT STEERING SY	INCORRECT ASSY  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL STEERING SYSTEM METERING VALVE FAULTY - INVESTIGATION FOUND AN INCORRECTLY ASSEMBLED CHECK VALVE						2	L	7	4 	4F			RT	A20WE   					 
1997020600221	19970206	00221	NE  	1997	2	6	AU961074         	2	19960614	G	7320		REGULATOR       			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				O	M		OTHER                     	OVER TEMP                 		TO	TAKEOFF        	1			AU	S 										(AUS) NO1 ENGINE FUEL FLOW REGULATOR FAULTY - ENGINE OVERSPED TO 107%  FOR APPROXIMATELY 10 SECONDS - EGT 710 DEGREES C						2	L	7	4 	4F	4	F		A20WE   	E12EU				 
1997020600222	19970206	00222	NM  	1997	2	6	AU961075         	1	19960503	G	5754		FLAP            			BOEING	747   	747438      		NM  										WING LE SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO11 AND NO16 LEADING EDGE FLAPS DAMAGED						2	L	7	4 	4F			RT	A20WE   					 
1997022000002	19970220	00002		1997	2	20	AU961076         	1	19960504	G	7830		FAIRING         								RROYCE	RB211 	RB211524G19 		NE  					T ENG THRUST REV	SEPARATED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NO3 ENGINE THRUST REVERSER TRANSFER DRIVE FAIRING ADRIFT IN FAN  EXIT - DAMAGE TO BLOCKER DOORS, OIL FEED LINE AND	 ONE FUEL VENTDRAIN										4	F			E30NE				 
1997020600223	19970206	00223	NM  	1997	2	6	AU961077         	1	19960523	G	3244		TYRE            			BOEING	747   	747438      		NM  										LG WHEEL/BRAKE S	DAMAGED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RH WING LANDING GEAR LEFT FORWARD TYRE (7F) DAMAGED - LARGE GASH EVIDENT IN SIDEWALL						2	L	7	4 	4F			RT	A20WE   					 
1997020600224	19970206	00224	EA  	1997	2	6	AU961078         	2	19960618	G	7322	105199	CARBURETTOR     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENG,FUEL CONTROL	FAULTY          	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			AU	S 					CR27633					(AUS) CARBURETTOR SUSPECT FAULTY						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
1997020600225	19970206	00225	CE  	1997	2	6	AU961079         	1	19960715	G	2910	S1236C60155	HOSE            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	MAIN HYD SYS	DETERIORATED    	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC HOSE FAILED - LOSS OF HYDRAULIC FLUID - DURING PRESSURETESTING THE HOSE EXPANDED BETWEEN THE BRAIDING - 	HOSE INTERIOR DETERIORATED AND CONTAMINATED THE HYDRAULIC SYSTEM					1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997020600226	19970206	00226	CE  	1997	2	6	AU961080         	1	19960805	G	5730		SKIN            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH OUTER WING LEADING EDGE AND LOWER WING SKINS CORRODED  IN AREA BETWEEN SKIN, BONDING AGENT AND WAFFLE DO	UBLER					1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997020600227	19970206	00227	CE  	1997	2	6	AU961081         	1	19960718	G	3230	50450101	TORQUE TUBE     			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	LG EXT-RETRACT S	FAILED          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LH MAIN LANDING GEAR RETRACTION SYSTEM TORQUE TUBE SPLIT - INBOARD LANDING GEAR DOOR ACTUATING ROD ROD-END PNO 504	5025-1MISSING FROM MLG RETRACTION LINKAGE IDLER BELLCRANK PNO 0841106-5DUE TO LOSS OF TORQUE OF THE ATTACHMENT NUT					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P5EA	 
1997020600228	19970206	00228	CE  	1997	2	6	AU961082         	1	19960726	G	3260	1SE13	SWITCH          			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	LG POSITION IND	DIRTY           	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH DIRTY						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P5EA	 
1997020600229	19970206	00229		1997	2	6	AU961083         	4	19960731	G	6113	085503014	SPINNER BLKHD   		085503015   	CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	PROPELLER ASSY S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1367 					722224		(AUS) PROPELLER SPINNER BULKHEAD CRACKED FROM ATTACHMENT SCREW HOLES - SUSPECT CRACKS HAD EXISTED FOR SOME TIME - INVEST	IGATION FOUND THAT THE DOUBLER ASSEMBLY PNO 0895008-4 HAD NOT BEEN FITTED -  PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P5EA	 
1997020600230	19970206	00230	CE  	1997	2	6	AU961084         	1	19960804	G	3310	E50R1325A	RHEOSTAT        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	CREW STA LIGHT S	BURNT           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) PILOTS PANEL LIGHTING RHEOSTAT SHORT CIRCUITED						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997020600231	19970206	00231	SW  	1997	2	6	AU961085         	1	19960807	G	5342	301971	BRACKET         			AIRTRC	AT500 	AT502       	0390303	SW  	PWA   	PT6   	PT6A15AG    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ATTACH FITTING S	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD FIN ATTACHMENT BRACKET BROKEN IN AREA DESCRIBED IN AIRTRACTOR SB 138 - AIRCRAFT IS FITTED WITH A 6.35MM (0	.25IN)PLATE					1	L	7	1 	3T	4	T	NC	A9SW    	E4EA	6	C	P15EA	 
1997020600232	19970206	00232	CE  	1997	2	6	AU961086         	1	19960729	G	6120		CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	PROP CNTRL SYS	SEPARATED       	W				C				ABORTED TAKEOFF         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE CONSTANT SPEED UNIT (CSU) CONTROL CABLE SEPARATED FROM CSU AND RODEND AND BOLT ASSEMBLY MISSING - INVEST	IGATION FOUND THAT MAINTENANCE HAD BEEN CARRIED OUT ON THE CSU PRIOR TO THE  OCCURRENCE (CSU ADJUSTMENT)					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
1997020600233	19970206	00233	EA  	1997	2	6	AU961087         	2	19960802	G	7261		OIL SYSTEM      			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  	HARTZL	HCB5M	HCB5MP3     	GL  	TURBINE ENGINE O	LOW PRESSURE    	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) RH ENGINE OIL PRESSURE LOSS						2	H	7	2 	4T	4	T		A41EU   	E4EA	6	C	P44GL	 
1997020600234	19970206	00234	EA  	1997	2	6	AU961088         	2	19960619	G	8520	11F20022S3	CRANKCASE       	LYC         	TIO540A2C   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	R ENGINE POWER S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1456 		L629061A		L629061A			(AUS) ENGINE CRANKCASE CRACKED FROM NO6 CYLINDER FORWARD UPPER CYLINDERFLANGE STUD TO NO6 CYLINDER INLET VALVE TAPPER GU	IDE					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997020600235	19970206	00235	SW  	1997	2	6	AU961089         	1	19960802	G	3213	S0310335R	SEAL            	OZONE       	MLG         	GULSTM	690TP 	695B        	3970610	SW  						ROTOL	R306	R306382F7   	GL  	MAIN GEAR SYS	WORN            	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					802					(AUS) RH MAIN LANDING GEAR OLEO SEAL FAILED - INSUFFICIENT OLEO  EXTENSION AFTER TAKEOFF RESULTED IN THE RH MAIN WHEEL C	ONTACTING THE RH MLG DOOR CAUSING SLIGHT DAMAGE					1	H	7	2 	4T			RT	2A4     		6	C	P8EU	 
1997020600236	19970206	00236	WP  	1997	2	6	AU961090         	1	19960719	G	5412		FIREWALL        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					NAC-PYL M-FRAME	DAMAGED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) VERTICAL FIREWALL LOWER DIAGONAL CENTRAL TUBE AND ATTACHING  DOUBLERS SEPARATED FROM FIREWALL DURING HARD LANDING						1	G	7	1 	3O	3	O		H11NM   	E295				 
1997020600237	19970206	00237	NM  	1997	2	6	AU961091         	1	19960728	G	2760		SWITCH          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					DRAG-SPOILER SYS	OUT OF ADJUST   	W				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) LH AND RH OUTBOARD ROLL SPOILER JAM SWITCHES OUT OF ADJUSTMENT						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997020600238	19970206	00238	CE  	1997	2	6	AU961092         	1	19960726	G	2910	572710012	HOSE            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	MAIN HYD SYS	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC HOSE DETERIORATED AND BREAKING DOWN INTERNALLY - RUBBER PARTICLES CONTAMINATED HYDRAULIC SYSTEM						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997020600239	19970206	00239	EA  	1997	2	6	AU961093         	2	19960701	G	8520	76097	CAMSHAFT        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	R ENGINE POWER S	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1587 				L4968027A			(AUS) CAMSHAFT EXHAUST VALVE LOBES AND ASSOCIATED TAPPETS PNO 72877  WORN - WEAR WAS BETWEEN 4.572MM AND 5.08MM (0.180IN	 AND 0.200IN)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997020600240	19970206	00240	CE  	1997	2	6	AU961094         	1	19960805	G	7120		BOLT            		9401120     	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE MOUNTING	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							L1105839A			(AUS) ENGINE VIBRATION ISOLATOR MOUNT BOLTS INCORRECT PART (INCORRECT  LENGTH) - SPACERS BETWEEN ENGINE AND MOUNTS NOT I	NSTALLED - RH UPPER MOUNT BOLT NUT SEPARATED - LH LOWER MOUNT BOLT NUT SPLIT - SUSPECT NUTS ALSO INCORRECT PART AS THEY 	ARE DIFFERENT TO THENUTS SPECIFIED IN THE IPC - PERSONNEL/MAINTENANCE ERROR -  UNAPROVED PART				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997020600241	19970206	00241	CE  	1997	2	6	AU961095         	1	19960806	G	2410	640934	GEAR            	PRESTOLITE  		CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ALT-GEN DRIVE SY	SEPARATED       	W				K				NONE                    				O	H		OTHER                     	ELECT. POWER LOSS-50 PC   		IN	INSP/MAINT     	1			AU	S 			1313 		IOK00008					(AUS) ALTERNATOR DRIVE GEAR FAILED - GEAR FACE HAD SEPARATED FROM HUB  ALLOWING GEAR TO FREEWHEEL						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997020600242	19970206	00242	CE  	1997	2	6	AU961096         	1	19960725	G	2434	ALT9422R	BEARING         	CONT        		CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C505   	GL  	DC GENERATOR-ALT	LOOSE           	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					555171					(AUS) RH ENGINE DRIVEN ALTERNATOR SLIP RING END BEARING LOOSE IN END HOUSING - BEARING HOUSING SUPPORT WEBS CRACKED AND 	BROKEN					1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997020600564	19970206	00564	SW  	1997	2	6	AU961097         	1	19960801	G	6322	476618015	COOLING FAN     			BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435A1A   	41516	EA  					ENG ASSRY COOL S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			298  		476618015		L24752			(AUS) ENGINE COOLING FAN BLADE CRACKED AT BASE						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997020600565	19970206	00565	NE  	1997	2	6	AU961098         	2	19960622	G	7240	9192M65G06	COMBUSTOR       								GE    	CF6   	CF680A      	30025	NE  					TURBINE ENGINE C	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4601 				LH			(AUS) ENGINE COMBUSTOR OUTER COWL CRACKED AND BROKEN											4	F			E13NE				 
1997020600566	19970206	00566	EU  	1997	2	6	AU961099         	2	19960730	G	7320	L923ANSETTSNO	REGULATOR       			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					ENG,FUEL FLOW	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			2516 		L923ANSETT		9688			(AUS) NO2 ENGINE FUEL FLOW REGULATOR (FFR) SUSPECT FAULTY						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997020600567	19970206	00567	NM  	1997	2	6	AU961100         	1	19960723	G	2710	BACC13AP4E5371	CONTROL CABLE   			BOEING	747   	747312      	1384932	NM  										AILERON CONTROL	FRAYED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CABLE AB13 LOCATED IN AREA OF LH REAR SPAR HAD SIX OF  SEVEN STRAND BROKEN AT CABLE DRUM AT WS 776.98 - CA	BLE AA11 ALSO DAMAGED WITH NUMEROUS BROKEN STRANDS - SUSPECT CAUSED BY INCORRECT INSTALLATION AND ALIGNMENT WITH BOTH CA	BLES BEING IN THE SAME DRUM GROOVE - PERSONNEL/MAINTENANCE ERROR				2	L	7	4 	4F			RT	A20WE   					 
1997020600568	19970206	00568	EU  	1997	2	6	AU961101         	1	19960730	G	5220	A322520843	STRAP           			AIRBUS	320   	A320212     		EU  										CABIN EMERG DOOR	FOUL RUD PEDAL  	W				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) CABIN ACCESS HATCH SAFETY STRAP CENTRE EYELETS MISSING ALLOWING  STRAP TO HANG DOWN AND CONTACT INBOARD RUDDER CAB	LE AT FAIRLEAD JUNCTION AT FUSELAGE FRAME 23 - RUDDER PEDALS JAMMED					2	L	7	2 	4F			RT	A28NM   					 
1997020600569	19970206	00569	SO  	1997	2	6	AU961102         	1	19960623	G	5741	640030X2	FITTING         	PIPER       	PA25235     	PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	OUTER WING SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7095 		254396		L1146840	J1017		(AUS) LH AND RH WING FRONT SPARS CRACKED ON LOWER RADIUS OF FRONT AND  REAR WING TO FUSELAGE ATTACHMENT LUGS						1	L	7	1 	3O	3	O		2A10    	E295	5	N	P874	 
1997020600570	19970206	00570	EU  	1997	2	6	AU961103         	1	19960409	G	3230	HTE2501A	MOTOR           		HTE21004    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LG EXT-RETRACT S	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					688GB295H					(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR HIGH RESISTANCE DUE TO POOR BRUSH CONTACT WITH COMMUTATOR						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997020600571	19970206	00571	NE  	1997	2	6	AU961104         	2	19960730	G	7250		TURBINE         			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					1ST STAGE	FAILED          	W		A		O				OTHER                   				M			OVER TEMP                 			TO	TAKEOFF        	1			AU	S 							LF05903A			(AUS) NO2 ENGINE FAILED - TGT INCREASED TO 957 DEGREES - SUSPECT CAUSEDBY 1ST STAGE TURBINE RUB						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997020600572	19970206	00572	EU  	1997	2	6	AU961105         	1	19960720	G	3310		LIGHT           			AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					CREW STA LIGHT S	FAULTY          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) COPILOTS MAP LIGHT WIRING INSULATION WORN AND SHORT CIRCUITING TO  GROUND						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1997020600573	19970206	00573	EA  	1997	2	6	AU961106         	2	19960808	G	8500		ENGINE          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE (RECIPROC	ROUGH RUNNING   	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) ENGINE RAN ROUGH FOR SEVERAL SECONDS - SUSPECT FUEL PROBLEM -  INVESTIGATION COULD FIND NO CAUSE AND THERE WAS NO 	REPETITION OF THE PROBLEM					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997020600574	19970206	00574		1997	2	6	AU961107         	1	19960809	G	7110	10191011715	COWLING         								PWA   	PT6   	PT6A60      	52043	NE  					ENGINE COWL SYS	DOOR FAILED     	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		CL	CLIMB          	1			AU	S 										(AUS) LH INBOARD ENGINE COWL DOOR SEPARATED ALONG HINGE LINE - DAMAGE  TO ONE WINDOW AND MINOR SCRATCHES AND DENTS TO FU	SELAGE										4	T			E4EA				 
1997020600575	19970206	00575	EU  	1997	2	6	AU961108         	1	19960416	G	2820		FUEL SYSTEM     			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL DISTRBUTION	CONTAMINATED    	W				K				NONE                    				E	X		VIBRATION/BUFFET          	ENGINE FLAMEOUT           		TO	TAKEOFF        	1			AU	S 										(AUS) NO1 ENGINE FUEL FEED PIPE CONTAMINATED BY AIR IN LINES - AIRCRAFTHAD BEEN COMPLETELY DEFUELLED THE PREVIOUS NIGHT 	- THERE IS NO REQUIREMENT FOR BLEEDING OF THE FUEL SYSTEM FOLLOWING COMPLETE DEFUEL					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997020600576	19970206	00576	EU  	1997	2	6	AU961109         	1	19960308	G	3230	HTE2501A	MOTOR           			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LG EXT-RETRACT S	SEIZED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 			11175		1187GB213H					(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR FAULTY - INVESTIGATION FOUND INSULATION VARNISH IN THE AIR GAP BETWEEN THE AR	MATURE AND FIELD POLES AND POOR BRUSH CONTACT					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997020600577	19970206	00577	GL  	1997	2	6	AU961110         	2	19960729	G	7250	6853279	TURBINE WHEEL   	ALLSN       	250C20B     						ALLSN 	250C  	250C20B     	03013	GL  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1006 		CAT36694		CAE831447			(AUS) FOURTH STAGE TURBINE WHEEL CRACKED THROUGH RIM											3	U			E4CE				 
1997020600578	19970206	00578	GL  	1997	2	6	AU961111         	2	19960724	G	7250	6886407	TURBINE WHEEL   	ALLSN       	250C20      	HUGHES	369   	369C        	4470704	WP  	ALLSN 	250C  	250C20      	03013	GL  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CAT31663		CAE801081BA			(AUS) FIRST STAGE TURBINE WHEEL CRACKED - TURBINE LABYRINTH SEAL PICKED UP ON STATIONARY SEAL - SECOND STAGE NGV PNO 687	8426 CRACKED INCURVIC COUPLING					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997020600579	19970206	00579	GL  	1997	2	6	AU961112         	2	19960722	G	7250	6840406	TURBINE BOLT    	ALLSN       	250C30      						ALLSN 	250C  	250C30      	03013	GL  					TURBINE SECTION	LOOSE NUT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CAT98211		CAE895801			(AUS) GAS PRODUCER TURBINE BOLT NUT LOOSE											3	U			E1GL				 
1997020600580	19970206	00580	NE  	1997	2	6	AU961113         	2	19960810	G	8530	399353CP	CYLINDER        	PWA         	R985AN14B   	DHAV  	DHC2  	DHC2EVANS   	2801832	EA  	PWA   	R985  	R985AN14B   	52008	NE  					R ENGINE CYLINDE	CRACKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 					4224237		4224237			(AUS) NO8 CYLINDER CRACKED - DURING REMOVAL TOP OF CYLINDER SEPARATED  FROM CYLINDER BODY						1	H	7	1 	3O	3	R		A806    	5E1				 
1997020600581	19970206	00581	EU  	1997	2	6	AU961114         	1	19960621	G	2133	VFT210700	ACTUATOR        			AIRBUS	320   	A320212     		EU  										PRESS. REGUL/OUT	CORRODED        	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					20ANSETTS					(AUS) AVIONICS VENT SYSTEM SKIN AIR INLET VALVE ACTUATOR INOPERATIVE - SUSPECT CAUSED BY CORROSION BUILDUP ON THE CLOSED	 POSITION LIMIT MICROSWITCH (S2)					2	L	7	2 	4F			RT	A28NM   					 
1997020600582	19970206	00582	NM  	1997	2	6	AU961115         	1	19960807	G	2150	7DR1830M5	ACTUATOR        	UNITEDTECH  	PACKVALVE   	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					CABIN COOLING SY	FAULTY          	W				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			18116		901038					(AUS) CABIN COOLING SYSTEM PACK VALVE ACTUATOR JAMMED IN FULL BYPASS POSITION (BUTTERFLY CLOSED)						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997020600583	19970206	00583	SW  	1997	2	6	AU961116         	1	19960810	G	2910	27810321039	PIPE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					MAIN HYD SYS	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE LOCATED IN LH WHEEL BAY LEAKING AT 90 DEGREE BEND DUE TO CORROSION PITTING						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997020600584	19970206	00584	SO  	1997	2	6	AU961117         	1	19960804	G	3231		VALVE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR DOOR SOLENOID VALVE SUSPECT FAULTY						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997020600585	19970206	00585	SO  	1997	2	6	AU961118         	1	19960802	G	7100	311591101A	HARNESS         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					ENG ELEC HARNESS	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 							115662			(AUS) ENGINE ELECTRICAL HARNESS SUSPECT FAULTY						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997020600586	19970206	00586	CE  	1997	2	6	AU961119         	1	19960729	G	2432		TERMINAL        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BATTERY/CHARGER	CORRODED        	W				K				NONE                    				J	H		WARNING INDICATION        	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			AU	S 										(AUS) BATTERY MONITOR SHUNT TERMINAL CORRODED PREVENTING CORRECT CONTACT						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997020600587	19970206	00587	NM  	1997	2	6	AU961120         	1	19960627	G	3230		SPRING          			BOEING	747   	747438      		NM  										LG EXT-RETRACT S	FOULED          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) BOTH WING LANDING GEAR UPLOCK OVERCENTRE SPRINGS FOULING ON J7 AND J8 JUNCTION BOXES						2	L	7	4 	4F			RT	A20WE   					 
1997020600588	19970206	00588	NM  	1997	2	6	AU961121         	1	19960530	G	5220		LATCH           			BOEING	747   	747438      		NM  										CABIN EMERG DOOR	INCORRECT RIGGED	W		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT DECK ESCAPE HATCH LATCH PINS INCORRECTLY FITTED - SPACERS AND BEARINGS ALSO FOUND TO BE IN WRONG STACKUP CO	NFIGURATION					2	L	7	4 	4F			RT	A20WE   					 
1997022000003	19970220	00003		1997	2	20	AU961122         	1	19960805	G	7740		COMPUTER        								RROYCE	RB211 	RB211535E4  	54555	NE  					ENG INTGRT INSTR	CONTAM-WATER    	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) AREA ABOVE E3 AND E4 ELECTRONICS PACK CONTAMINATED BY WATER  DURING HEAVY RAIN STORM - RIGHT EICAS COMPUTER ALSO C	ONTAMINATED BY WATER										4	F			E12EU				 
1997020600589	19970206	00589	EU  	1997	2	6	AU961123         	1	19960811	G	3260		CIRCUIT BOARD   			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LG POSITION IND	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR WARNING SYSTEM NOSE LANDING GEAR DOWNLOCK PRINTED CIRCUIT BOARD FAULTY						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997020600590	19970206	00590	NM  	1997	2	6	AU961124         	1	19960805	G	2520	908621	FITTING         		908622      	BOEING	737   	737377      		NM  										PASSENGER COMPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT ATTENDANT SEAT ROLLER FITTINGS CRACKED - BOTH FITTINGS PNO90862-1 AND PNO 90862-2 CRACKED IN FORWARD SEAT -	 INBOARD FITTINGPNO 90862-1 CRACKED IN AFT SEAT					2	L	7	2 	4F			RT	A16WE   					 
1997020600591	19970206	00591	NE  	1997	2	6	AU961125         	2	19960808	G	7261		OIL SYSTEM      								CFMINT	CFM56 	CFM565A1    		NE  					TURBINE ENGINE O	CONTAM-METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							731140			(AUS) NO1 ENGINE OIL SYSTEM FRONT SCAVENGE MAGNETIC PLUG CONTAMINATED  WITH METAL TYPE M50 AND 4340											4	F			E29NE				 
1997020600592	19970206	00592	EA  	1997	2	6	AU961127         	2	19960806	G	7320	3010466	LEVER           		3244834     	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENG,FUEL CONTROL	BROKEN          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 					A89271		56681			(AUS) ENGINE FUEL CONTROL UNIT LEVER BROKEN OFF AT BASE - ENGINE RETURNED TO FLIGHT IDLE - SUSPECT PRE-EXISTING CRACK CA	USED BY IMPACT					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997020600593	19970206	00593	CE  	1997	2	6	AU961128         	1	19960805	G	5730		SKIN            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH LOWER WING SKINS CORRODED IN AREA BETWEEN SKIN, BONDING  AGENT AND WAFFLE DOUBLER ON OUTER LEADING EDGE 	ASSEMBLIES					1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997020600594	19970206	00594	CE  	1997	2	6	AU961129         	1	19960811	G	1210		FUEL SYSTEM     			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUEL STORAGE SYS	WRONG FUEL      	W				K				NONE                    				E	Y	M	VIBRATION/BUFFET          	ENGINE STOPPAGE           	OVER TEMP                 	CR	CRUISE         	1			AU	S 							566275			(AUS) AIRCRAFT FILLED WITH AVTUR - ENGINE DAMAGED DUE TO DETONATION -  METAL CONTAMINATION OF OIL SYSTEM - PERSONNEL/MAI	NTENANCE ERROR- UNAPPROVED PART (FUEL)					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997020600595	19970206	00595	SW  	1997	2	6	AU961130         	1	19960729	G	5520	442451	BOLT            			GULSTM	112   	114         	7630314	SW  	LYC   	O540  	IO540T4A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ELEVATOR STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR HINGE BOLT CORRODED - FOUND DURING ELEVATOR BEARING CHANGE WHEN ELEVATORS REMOVED						1	L	7	1 	3O	3	O		A12SO   	1E4	5	C	P920	 
1997020600596	19970206	00596	CE  	1997	2	6	AU961131         	1	19960809	G	7120		SPACER          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE MOUNTING	MIS INSTALLED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							61034139A			(AUS) ENGINE INCORRECTLY INSTALLED IN ENGINE MOUNTS - LOWER VIBRATION  SHOCK MOUNT CONTAINED AN INCORRECT NUMBER OF SPAC	ERS - AS ARESULT THE PROPELLER SPINNER BACKING PLATE HAD WORN ON THE LOWER COWL - PERSONNEL/MAINTENANCE ERROR					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997020600597	19970206	00597	CE  	1997	2	6	AU961132         	1	19960806	G	5541	3363000017	SPAR            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C406    	GL  	RUDDER STRUCT SY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							573470	951740		(AUS) RUDDER SPAR CRACKED - FOUND DURING INSPECTION IAW AD/BEECH33/36  AMDT1						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA	 
1997020600598	19970206	00598	SO  	1997	2	6	AU961133         	1	19960814	G	5711		SPAR FITTING    	PIPER       	REARSPAR    	PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	OUTER WING SYS	FAILED RIVETS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING REAR SPAR FITTING ATTACHMENT RIVETS FAILED - HEADS FELL OFF - FOUND DURING INSPECTION IAW AD/PA28/40						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
1997020600599	19970206	00599	CE  	1997	2	6	AU961134         	1	19960802	G	2810	120040684	VENT            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	FUEL STORAGE SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FUEL TANK VENT LINE DAMAGED DUE TO EXCESSIVE BEND IN LINE - LINE PARTIALLY BLOCKED						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997020600600	19970206	00600	EU  	1997	2	6	AU961135         	1	19960731	G	3213		OLEO SUPPORT    		NS40D403    	BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAIN GEAR SYS	SHEARED RIVET   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH LANDING GEAR OLEO SUPPORT FITTING PNO NS-40-C-075 TO MLG TUBE PNO NS-40-D-403 ATTACHMENT RIVETS SHEARED ALLOWIN	G THE MLG WHEEL ASSEMBLY TO TURN RELATIVE TO THE AIRCRAFT CENTRELINE - OCCURRED  DURING MINIMUM RADIUS TURN DURING TAXI					1	H	7	2 	3O	3	O	RT	A17EU   	E295	5	C	P920	 
1997020600601	19970206	00601	EU  	1997	2	6	AU961136         	1	19960807	G	5511	NB30079	RIB             			BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	HORZ STAB SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH HORIZONTAL STABILISER INNER NOSE RIB CRACKED AT STN 11.40 - SUSPECT CAUSED BY HORIZONTAL STABILISER BEING USED 	AS AMAINTENANCE STAND IN LIEU OF THE CORRECT ITEM -  PERSONNEL/MAINTENANCE ERROR					1	H	7	2 	3O	3	O	RT	A17EU   	E295	5	C	P920	 
1997020600602	19970206	00602	GL  	1997	2	6	AU961137         	2	19960809	G	7323	3292	GOVERNOR DRIVE  	BENDIX      	PTGOVERNOR  	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENG,FUEL CONTROL	FAILED SHAFT    	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CL	CLIMB          	1			AU	S 			1646 		3292		CAE801666BA			(AUS) ENGINE POWER TURBINE GOVERNOR DRIVE SHAFT SHEARED DUE TO FAILURE OF DRIVE BEARING SUSPECT DUE TO DETERIORATED AND/	OR LOST GREASE					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997020600603	19970206	00603	NM  	1997	2	6	AU961138         	1	19960722	G	3230		MLG             			BOEING	737   	737476      		NM  										MAIN GEAR SYS	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) RH MAIN LANDING GEAR FAILED TO LOCK DOWN						2	L	7	2 	4F			RT	A16WE   					 
1997020600604	19970206	00604	NM  	1997	2	6	AU961139         	1	19960801	G	3246	1864	WHEEL           			BOEING	737   	737376      		NM  										LG WHEEL/BRAKE S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1864					(AUS) LH INBOARD MAIN WHEEL CRACKED BETWEEN TIE BOLT HOLE AND  OVERINFLATION VALVE ACCESS HOLE - FOUND DURING ROUTINE TY	RECHANGE					2	L	7	2 	4F			RT	A16WE   					 
1997020600605	19970206	00605	NM  	1997	2	6	AU961140         	1	19960731	G	3246	0262	WHEEL           			BOEING	737   	737376      		NM  										LG WHEEL/BRAKE S	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0262					(AUS) LH INBOARD MAIN WHEEL CRACKED BETWEEN TIE BOLT HOLE AND  OVERINFLATION VALVE ACCESS HOLE - FOUND DURING ROUTINE TY	RECHANGE					2	L	7	2 	4F			RT	A16WE   					 
1997020600606	19970206	00606	CE  	1997	2	6	AU961141         	1	19960814	G	3234		SELECTOR        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR SELECTOR WHEEL LOCKING GRUB SCREW LOOSE						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1997020600607	19970206	00607	CE  	1997	2	6	AU961142         	1	19960814	G	5312	24120044	BULKHEAD        	CESSNA      	24120013    	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0940					(AUS) FUSELAGE BULKHEADS CRACKED IN THE FOLLOWING LOCATIONS: 1. PNO 2412001-3 BULKHEAD LOWER LH STN 108.0 - CRACK LENGTH	 27MM  (1.06IN)  2. PNO 2412001-4 BULKHEAD LOWER RH STN 108.0 - CRACK LENGTH 30MM  (1.18IN)  3. PNO 2412004-4 BULKHEAD L	OWER RH STN 124.0 - CRACK LENGTH 22MM  (0.866IN) 4. PNO 2412004-5 BULKHEAD LOWER LH STN 124.0 - CRACK LENGTH 9MM (0.354I	N) CRACKS EXTEND FROM INBOARD EDGE TOWARDS FUSELAGE SKIN IN BAGGAGE AREA AT FLOOR LEVEL - FORWARD BULKHEADS AT STN 108.0	 SHOW SIGNS  OF DEFORMATION AND STRUCTURE DISTRESS		1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
1997020600608	19970206	00608	NM  	1997	2	6	AU961143         	1	19960810	G	5330		SKIN            			BOEING	767   	76733A      		NM  	PWA   	4056  	PW4056      		NE  					EXT PLATES/SKIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED - CRACK LENGTH 38.1MM (1.5IN) - FURTHER  INVESTIGATION OF REAR CARGO FLOOR REVEALED EXFOLIAT	ION CORROSION					2	L	7	2 	RT	4	F	RT	A1NM    	E24NE				 
1997020600609	19970206	00609	EU  	1997	2	6	AU961144         	1	19960809	G	3310	LT52A	LIGHTING DIMMER 			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	CREW STA LIGHT S	FAULTY          	W				K				NONE                    				O	B		OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 					6124					(AUS) PILOTS PANEL LIGHT DIMMER FAILED						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1997020600610	19970206	00610	CE  	1997	2	6	AU961145         	1	19960729	G	2520		SEAT BELT       			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470R       	17026	SO  					PASSENGER COMPAR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) BOTH REAR SEATS FITTED WITH AUTOMOTIVE SEAT BELTS - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997020600611	19970206	00611	NM  	1997	2	6	AU961146         	1	19960721	G	5730	72031	PANEL           		654587      	BOEING	737   	737376      		NM  										OUTER WING SYS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING NO1 FUEL BOOST PUMP ACCESS PANEL MISSING						2	L	7	2 	4F			RT	A16WE   					 
1997020600612	19970206	00612	EU  	1997	2	6	AU961147         	1	19960802	G	2910	NAS16126	SEAL            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					MAIN HYD SYS	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) GREEN HYDRAULIC SYSTEM UNION SEAL LEAKING - SEAL WAS LOCATED AT  RH KRUGER FLAP RETURN LINE UNION - LOSS OF HYDRAU	LIC FLUID					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1997022000633	19970220	00633	CE  	1997	2	20	AU961148         	1	19960815	G	5312	24120521	DOUBLER         	CESSNA      	BULKHEAD    	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EMPENAGE TO FUSELAGE ATTACHMENT BULKHEAD CRACKED - SEE ALSO MDR  95/0816 AND MDR 96/1142 FOR SIMILAR DEFECTS						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
1997022000634	19970220	00634	CE  	1997	2	20	AU961149         	1	19960812	G	7810	12502642	EXHAUST PIPE    			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	R ENG COLLECTOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RH EXHAUST COLLECTOR NO5 RISER PIPE RUBBING ON NO3 INLET MANIFOLD CAUSING WEAR DAMAGE TO BOTH ITEMS - COLLECTOR AS	SEMBLY WAS NOT A GENUINE CESSNA PART AND APPEARS TO HAVE BEEN INCORRECTLY MANUFACTURED - A GENUINE CESSNA PART FITTED CO	RRECTLY -PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
1997030300004	19970303	00004	GL  	1997	3	3	AU961150         	3	19960730	G	6110		PROPELLER       			PIPER 	PA60  	PA60601     	7106010	NM  	LYC   	O540  	IO540S1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER ASSY	GROUND STRIKE   	W				K				NONE                    				C			F.O.D.                    			LD	LANDING        	1			AU	S 							L1935848A	CK4187A		(AUS) RH ENGINE SUFFERED A PROPELLER STRIKE - ALL THREE BLADES DAMAGED IN AREA APPROXIMATELY 50.8MM (2IN) FROM TIP						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
1997022000635	19970220	00635	CE  	1997	2	20	AU961151         	1	19960731	G	2820	10192000016	PIPE            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL DISTRBUTION	CHAFED          	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR TORQUE TUBE PNO 101-810021-3 RUBBING ON INCORRECTLY POSITIONED FUEL LINE BETWEEN THE NACELLE 	TANK AND THE AUXILIARY TANK WEARING A HOLE IN THE FUEL LINE AND DAMAGING THE  TORQUE TUBE - FUEL LEAKING - PERSONNEL/MAI	NTENANCE ERROR				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997022000636	19970220	00636	GL  	1997	2	20	AU961152         	3	19960815	G	6111		RETENTION NUT   			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROP BLADE	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								722497		(AUS) NO3 PROPELLER BLADE RETENTION NUT LOOSE AND LOCK PLUGS MISSING - SUSPECT RETENTION NUT UNDERTORQUED - PERSONNEL/MA	INTENANCE ERROR					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1997022000637	19970220	00637	EA  	1997	2	20	AU961153         	2	19960614	G	8530	75089	PISTON          	LYC         	CYLINDER    	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	R ENGINE CYL	DAMAGED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 					109153		110560			(AUS) NO3 CYLINDER PISTON DAMAGED AND PISTON RINGS BROKEN - SUSPECT  CAUSED BY DETONATION						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997022000638	19970220	00638	SW  	1997	2	20	AU961154         	1	19960508	G	5310		FUSELAGE        			GULSTM	690TP 	690         	0141720	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	MAIN FRAME SYS	BIRD STRIKE     	W				K				NONE                    				C			F.O.D.                    			LD	LANDING        	1			AU	S 										(AUS) AIRCRAFT HIT BY SEAGULL DURING LANDING						1	H	7	2 	3T				2A4     		6	C	P15EA	 
1997022000639	19970220	00639	EA  	1997	2	20	AU961155         	2	19960809	G	8530		CYLINDER        								LYC   	O540  	IO540K1C5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	R ENGINE CYL	DAMAGED         	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		LD	LANDING        	1			AU	S 							L538248			(AUS) NO3 ENGINE NO6 CYLINDER AND CRANKCASE DAMAGED - AIRCRAFT HAD BEEN IDLE FROM NOVEMBER 1995 UNTIL JUNE 1996 - THE EN	GINES HAD NOT BEEN INHIBITED OR REGULARLY GROUND RUN DURING THAT TIME										3	O			1E4	5	C	P6EA	 
1997022000640	19970220	00640	NE  	1997	2	20	AU961156         	1	19960525	G	2823		SEAL            		SELECTVALVE 	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					FUEL DIST	LEAKING         	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) FUEL SELECTOR VALVE SHAFT SEAL LEAKING ALLOWING AIR TO ENTER FUELSYSTEM						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1997022000641	19970220	00641	NM  	1997	2	20	AU961157         	1	19960630	G	2130		PRESSURIZATION  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					CABIN PRESS CONT	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AIRCRAFT DEPRESSURISED - CABIN CREW REPORTED CABIN DOOR MAKING NOISE - GROUND CHECKS CARRIED OUT ON DOOR SEAL AND 	SYSTEM COULD FIND NO FAULTS					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997022000642	19970220	00642	CE  	1997	2	20	AU961158         	1	19960808	G	2510		SEAT BELT       			CESSNA	172   	172B        	2072406	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	FLT COMPARTMENT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT WEBBING AND HARDWARE WAS OF AUTOMOTIVE ORIGIN -  UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1997022000643	19970220	00643	CE  	1997	2	20	AU961159         	1	19960808	G	2510		SEAT BELT       			BEECH 	35    	P35BEECH    	1151530	CE  	CONT  	O470  	IO470N      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	FLT COMPARTMENT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT HARDWARE AND WEBBING WAS OF AUTOMOTIVE ORIGIN -  UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P880	 
1997022000644	19970220	00644	NM  	1997	2	20	AU961160         	1	19960620	G	5311	AD461	FRAME           			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER LH FUSELAGE FRAME CRACKED AT UPPER REAR ATTACHMENT LUG - FOUND DURING NON-DESTRUCTIVE TESTING						1	G	7	1 	3O	3	O		H10WE   	E274				 
1997022000645	19970220	00645	CE  	1997	2	20	AU961161         	1	19960801	G	3230	MS2451020	CIRCUIT BREAKER 			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	LG EXT-RETRACT	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR RETRACTION MOTOR CIRCUIT BREAKER FAULTY						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997022000646	19970220	00646	CE  	1997	2	20	AU961162         	1	19960627	G	2434	ALV2006AS	BEARING         	PRESTOLITE  	ALTERNATOR  	CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	DC GEN/ALT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			557  		A10896					(AUS) ALTERNATOR SLIP RING END BEARING INNER RACE LOOSE ON ROTOR SHAFT						1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
1997022000647	19970220	00647	CE  	1997	2	20	AU961163         	1	19960805	G	5550	07311001415	FITTING         		073110015   	CESSNA	188   	A188B       	2073005	CE  						MCAULY	3A32C	D3A32C90    	GL  	VERT STAB STRUCT	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER LOWER ATTACHMENT FITTING NOT SECURED BY RIVETS ON TOP AND BOTTOM SIDES - SUSPECT MANUFACTURING ERROR						1	L	7	1 	3O				A9CE    		5	C	P21EA	 
1997022000648	19970220	00648	NM  	1997	2	20	AU961164         	1	19960731	G	3231	400088001	BELLCRANK       			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					LG EXT-RETRACT	SHEARED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOOR BELLCRANK SHEARED						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1997022000649	19970220	00649	WP  	1997	2	20	AU961165         	1	19960730	G	5720	40852001	PIN             			WTHRLY	620   	620         	9630602	WP  	PWA   	R985  	R985AN1     	52008	NE  					OUTER WING SYS	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) WING HINGE PINS FAULTY - DEPTH OF THREADED HOLES VARIES BETWEEN  21.463MM AND 21.844MM (0.845IN AND 0.860IN) - MAX	IMUM DEPTH OF HOLE IS 21.336MM (0.840IN) - FOUND DURING INSPECTION IAW WEATHERLY SERVICE NOTE NO15					1	L	7	1 	3R	3	R		A26WE   	5E1				 
1997022000650	19970220	00650	CE  	1997	2	20	AU961166         	1	19960609	G	3230		PIPE            			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					LG EXT-RETRACT	CRACKED         	W				K				NONE                    				O	J	K	OTHER                     	WARNING INDICATION        	FLUID LOSS                	LD	LANDING        	1			AU	S 							L1799661A			(AUS) MAIN LANDING GEAR DOWN LINE CRACKED - NOSE AND RH MLG COLLAPSED  ON LANDING						1	L	7	1 	3O	3	O		A1CE    	1E10				 
1997022000651	19970220	00651	SW  	1997	2	20	AU961167         	1	19960808	G	3230		LANDING GEAR    			MTSBSI	MU2   	MU2B30      	5780410	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	LG EXT-RETRACT S	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR WOULD NOT EXTEND IN NORMAL OR EMERGENCY MODES						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997022000652	19970220	00652	NE  	1997	2	20	AU961168         	2	19960813	G	7230	310652101	COMPRESSOR BLADE	PWA         	PT6A42      	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					TURB ENG COMP	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1740 		PCE94283		PCE94283			(AUS) RH ENGINE COMPRESSOR FIRST STAGE BLADES DAMAGED BY FOD - AIRCRAFTHAD PREVIOUSLY OPERATED FROM GRAVEL STRIPS						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997022000653	19970220	00653	CE  	1997	2	20	AU961169         	1	19960806	G	5330	1054400005	SKIN            			BEECH 	76    	76          	1153005	CE  										EXT PLATES/SKIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR FUSELAGE SKIN CRACKED IN SIX PLACES IN AREA AROUND TWO  RIVETS AT STN 210 BULKHEAD AND NEAR STRINGER PNO 105-	440000-11 - CRACK LENGTHS 6MM (0.236IN) - SUSPECT CAUSED BY OIL CANNING OF THE SKIN - STRINGER IS NOT CONNECTED TO THE B	ULKHEAD AT THIS POINT				1	L	7	2 	3O				A29CE   					 
1997022000654	19970220	00654	CE  	1997	2	20	AU961170         	1	19960806	G	5330	1054400006	SKIN            			BEECH 	76    	76          	1153005	CE  										EXT PLATES/SKIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR FUSELAGE SKIN CRACKED IN FIVE PLACES AROUND TWO RIVETS AT STN 210 BULKHEAD AND NEAR STRINGER PNO HSJ 5893 - C	RACK LENGTHSAPPROXIMATELY 10MM (0.393IN) - SUSPECT CAUSED BY OIL CANNING OF  THE SKIN - STRINGER IS NOT ATTACHED TO THE 	BULKHEAD AT THIS POINT				1	L	7	2 	3O				A29CE   					 
1997030300005	19970303	00005	SO  	1997	3	3	AU961171         	1	19960819	G	5711		SPAR            	PIPER       	LHWING      	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	OUTER WING SYS	MISSING RIVET   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING MAIN SPAR TOP CAP REAR FLANGE INBOARD MISSING RIVETS - NEW MAIN SPAR AND TOP REAR WING SKIN FITTED IN JUNE	 1977 FOLLOWING HEAVY LANDING REPAIRS - PERSONNEL/MAINTENANCE ERROR					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997022000655	19970220	00655	SO  	1997	2	20	AU961172         	1	19960530	G	5312	6244403	BULKHEAD        			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MAIN FRAME SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIN FORWARD SPAR ATTACHMENT BRACKET AND FUSELAGE BULKHEAD LOCATED AT FS 228 CORRODED						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997022000656	19970220	00656	SO  	1997	2	20	AU961173         	1	19960530	G	5340	6241300	FITTING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ATTACH FITTING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR ATTACHMENT FITTINGS, FUSELAGE STRINGERS AND SKIN  CORRODED - FOUND DURING INSPECTION IAW AD/PA32/75						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997022000657	19970220	00657	EU  	1997	2	20	AU961174         	1	19960327	G	5330		SKIN            			FOKKER	F27   	F27MK50     		EU  										EXT PLATES/SKIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR FUSELAGE SKIN CRACKED IN ZONE 300 IN AREA APPROXIMATELY 177.8MM (7IN) BELOW LH AND RH HORIZONTAL STABILISER A	T FS 21580 -1. FS 21580 LH CRACKED IN TWO AREAS - CRACK LENGTHS 88.9MM AND114.3MM (3.5IN AND 4.5IN) - IN ADDITION INTERN	AL VERTICAL  FRAME CRACKED IN SEVERAL AREAS WITH SMALL SECTIONS BROKEN AWAY2. FS 21580 RH - CRACK LENGTH 63.5MM (2.5IN)				2	H	7	2 	4T			RT	A817    					 
1997022000658	19970220	00658	NE  	1997	2	20	AU961175         	2	19960810	G	7240		ATOMIZER        			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ENG,FUEL DIST SY	HOLED           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							687608			(AUS) NO3 ENGINE COMBUSTION CHAMBER NO4 ATOMISER HOLED - FOUND DURING  BORESCOPE INSPECTION IAW PWJ-72-40-72						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997022000659	19970220	00659	NM  	1997	2	20	AU961176         	1	19960712	G	2130	7638102	CONTROLLER      			BOEING	737   	73733A      	1384673	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					CABIN PRESSURE	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 			13022		BG1542ANSET					(AUS) CABIN PRESSURE CONTROLLER SUSPECT FAULTY - CONTROLLER CHANGED -  WORKSHOP INSPECTION COULD FIND NO FAULTS BUT PRES	SURISATIONSYSTEM NOW OPERATES NORMALLY					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
1997030300006	19970303	00006	EU  	1997	3	3	AU961177         	1	19960816	G	3260		INDICATOR       			HWKSLY	DH104 	DH104*      		EU  						HWKSLY	PD143	PD143312    	EU  	LG POSITION IND	SEIZED          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR MECHANICAL FLAG INDICATION SYSTEM SEIZED IN THE `UP' INDICATION POSITION						1	L	7	2 	3I				A807    		5	C	P916	 
1997022000660	19970220	00660	SO  	1997	2	20	AU961178         	1	19960709	G	3230	604ENI6	SWITCH          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LG EXT-RETRACT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH FAULTY - FOUND DURING  INSPECTION IAW AD/EMB110/42						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997022000661	19970220	00661	SO  	1997	2	20	AU961179         	1	19960709	G	2730	4A321404	TORQUE TUBE     			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ELEVATOR TORQUE TUBE CRACKED FROM TAPER PLUG HOLES - FOUND  DURING INSPECTION IAW SB110-027-0079						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997022000662	19970220	00662	NM  	1997	2	20	AU961180         	1	19960712	G	5241	65C340689	HINGE           			BOEING	737   	737377      		NM  										SERVICE DOOR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD GALLEY SERVICE DOOR LOWER GATE HINGE CRACKED - FOUND DURING INSPECTION IAW AD/B737/97						2	L	7	2 	4F			RT	A16WE   					 
1997022000663	19970220	00663	NM  	1997	2	20	AU961181         	1	19960720	G	5241	65C340689	HINGE           			BOEING	737   	73733A      	1384673	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					SERVICE DOOR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD GALLEY SERVICE DOOR LOWER GATE HINGE CRACKED - FOUND DURING INSPECTION IAW AD/B737/97						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
1997022000664	19970220	00664	NM  	1997	2	20	AU961182         	1	19960709	G	5241	65C340689	HINGE           			BOEING	737   	737377      		NM  										SERVICE DOOR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD GALLEY SERVICE DOOR LOWER GATE HINGE CRACKED - FOUND DURING INSPECTION IAW AD/B737/97						2	L	7	2 	4F			RT	A16WE   					 
1997022000665	19970220	00665	NM  	1997	2	20	AU961183         	1	19960715	G	5241	65C340689	HINGE           			BOEING	737   	737377      		NM  										SERVICE DOOR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD GALLEY SERVICE DOOR LOWER GATE HINGE CRACKED - FOUND DURING INSPECTION IAW AD/B737/97						2	L	7	2 	4F			RT	A16WE   					 
1997022000666	19970220	00666	CE  	1997	2	20	AU961184         	1	19960806	G	3297	MS252531	WIRE            	CESSNA      	310R        	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					LG POSITION IND	LOOSE           	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			AU	S 					0531					(AUS) LANDING GEAR WARNING SYSTEM FAULTY - FAULT TRACED TO TERMINAL  WIRE G7C20 DISCONNECTED FROM FLAP						1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
1997022000667	19970220	00667	SO  	1997	2	20	AU961185         	1	19960807	G	2510		SHAFT           	PACIFICSCIEN	SEATBELT    	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	FLT COMPARTMENT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS SHOULDER BELT INERTIA REEL CENTRE SHAFT BROKEN -  INVESTIGATION FOUND THAT THE STAINLESS STEEL BELT GUIDE H	AD WORN THROUGH THE CENTRE SHAFT					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997022000668	19970220	00668	CE  	1997	2	20	AU961186         	1	19960612	G	5720	07214003	ANGLE           			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	OUTER WING SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING INSPECTION OF LH AND RH WINGS MISSING RIVET HEADS WERE  FOUND ON THE WING UPPER SKIN THROUGH THE MAIN SPAR 	INBOARD TOP CAP - FOLLOWING REMOVAL AND DISASSEMBLY OF THE WINGS THE SEVERE  EXFOLIATION CORROSION WAS FOUND ON THE FOLL	OWING ANGLES ANDPLATES:- 1. LH WING PNO 0721400-3, PNO 0523315, PNO 071402-1 AND PNO 071402-3  2. RH WING PNO 0721400-4,	 PNO 0523315-1, PNO 071402-23. RH WING LOWER TENSION ANGLE PNO 0721402-4 AT THE WING STRUTATTACHMENT POINT SHOWED SIGNS 	OF STRESS CORROSION BELOW THE  STRUT BOLT HOLE FAILURE OF WHICH WOULD BE CATASTROPHIC  AIRCRAFT IS APPROXIMATELY 34 YEAR	S OLD	1	H	7	1 	3O	3	O		3A21    	3E1	5	C	P3EA	 
1997022000669	19970220	00669	CE  	1997	2	20	AU961187         	1	19960523	G	5730	10140451	SKIN            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					CENTRE WING SYS	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SKIN DELAMINATED - FOUND DURING INSPECTION IAW  AD/BEECH200/43 AMDT5 (BEECH SB 2040 REV 3)						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997022000670	19970220	00670	CE  	1997	2	20	AU961188         	1	19960728	G	2730		COLLAR          			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	ELEVATOR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ELEVATOR TORQUE TUBE COLLAR CRACKED						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997022000671	19970220	00671	NM  	1997	2	20	AU961189         	1	19960820	G	3213	765155V	TORQUE LINK     			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					MAIN GEAR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR TORQUE LINKS CRACKED - FOUND DURING FLUORESCENT DYE PENETRANT CHECK						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1997022000672	19970220	00672	CE  	1997	2	20	AU961190         	1	19960801	G	5312	0713608	BULKHEAD        			CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	MAIN FRAME SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FORWARD DOORPOST BULKHEAD CRACKED IN BEND RELIEF NOTCH - FOUND DURING INSPECTION IAW  AD/CESSNA180/75						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997022000673	19970220	00673	NM  	1997	2	20	AU961191         	1	19960816	G	2820		FUEL SYSTEM     			BOEING	757   	757200      	1384950	NM  										FUEL DISTRBUTION	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RH ENGINE RECEIVED FUEL FROM RH TANK ONLY,  CAUSING OUT OF BALANCE CONDITION - INVESTIGATION COULD FIND NO FAULTS 	WITH THE FUEL SYSTEM					2	L	7	2 	4F			RT	A2NM    					 
1997022000674	19970220	00674	NM  	1997	2	20	AU961192         	1	19960818	G	2430	BSK122H30PE	CONNECTOR       			BOEING	757   	757200      	1384950	NM  										DC GENERATING SY	BROKEN          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			AU	S 										(AUS) LH ENGINE PYLON ELECTRICAL CONNECTOR D1014P HAD BROKEN WIRE TO PIN 12						2	L	7	2 	4F			RT	A2NM    					 
1997022000675	19970220	00675	EA  	1997	2	20	AU961193         	2	19960820	G	8520	LW15452	CRANKCASE       	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	R ENG POWER SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1639 		L51768A		L51768A			(AUS) RH ENGINE RH CRANKCASE HALF CRACKED IN AREA OF NO1 CYLINDER LOWER AFT THROUGH BOLT						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997022000676	19970220	00676	EU  	1997	2	20	AU961194         	1	19960721	G	5210	AE4014Z003	SPRING          			AMD   	FALC50	FALCON900   	2700160	EU  										CREW-PASS DOOR S	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					338284					(AUS) PASSENGER DOOR COMPENSATING CYLINDER DOOR ACTUATOR SPRING  DELAMINATED AND CRACKED - THIS DEFECT WAS RECEIVED FROM	 NO34 SQUADRON RAAF AND IS FOR INFORMATION ONLY					2	L	7	3 	4F			RT	A46EU   					 
1997022000677	19970220	00677	CE  	1997	2	20	AU961195         	1	19960731	G	5210	AN35	BOLT            			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	CREW-PASS DOOR S	SHEARED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) PASSENGER MAIN ENTRANCE DOOR DRIVE CAPSTAN CABLE CLAMP BOLT  SHEARED ALLOWING THE DOOR TO INDICATE `LOCKED' WHEN T	HE LOWERLOCK PINS WERE ONLY PARTIALLY LOCKED					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997022000678	19970220	00678	CE  	1997	2	20	AU961196         	1	19960822	G	7930	1200106247	PIPE            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	ENG OIL IND SYS	WORN            	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) ENGINE OIL PRESSURE PIPE LOCATED BETWEEN FIREWALL AND OIL  PRESSURE GAUGE WORN THROUGH AND LEAKING DUE TO CHAFING 	BY SCAT HOSE					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997022000679	19970220	00679	SO  	1997	2	20	AU961197         	1	19960826	G	5310		TUBE            			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	MAIN FRAME SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE STRUCTURE LH REAR LONGITUDINAL TUBE LOCATED TO THE REAR OF THE LH PASSENGER DOOR CORRODED THROUGH IN THRE	E PLACES IN A 152.4MM (6IN) LENGTH					1	H	7	1 	3O	3	O		1A6     	E274	5	N	P88614	 
1997022000680	19970220	00680	GL  	1997	2	20	AU961198         	3	19960826	G	6114	C87	HUB             	MCAULY      	C87         	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			1594 		752980			752980		(AUS) PROPELLER HUB BLADE NUT EXPANSION LOCK PLUG INCORRECTLY DRILLED  - PERSONNEL/MAINTENANCE ERROR						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997022000681	19970220	00681	NM  	1997	2	20	AU961199         	1	19960819	G	3220		BOLT            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  					NOSE-TAIL GEAR	JAMMED GEAR     	W		A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR WOULD NOT EXTEND - AIRCRAFT LANDED WITH NLG  RETRACTED - INVESTIGATION FOUND THAT A NEW NLG WAS 	RECEIVEDWITHOUT THE TOP SECTION OF THE PROXIMITY SENSOR PROTECTIVE COVER - A NEW ONE WAS MANUFACTURED AND FITTED WITH HE	XAGON HEADED BOLTSINSTEAD OF THE CORRECT COUNTERSUNK ITEMS REQUIRED BY THE MANUFACTURER - INTERNAL SPACERS WERE ALSO USE	D TO OBTAIN THE CORRECT INTERNAL CLEARANCE BETWEEN THE COVER AND THE PROXIMITY SENSORS - THE USE OF THE HEXAGON BOLTS AN	D SPACERS RESULTED IN THE BOLTS CONTACTING THE UPPER DRAG BRACE DURING NLG RETRACTION  PREVENTING NLG EXTENSION - DAMAGE	 CAUSED TO THE UNDERSIDE OF THE AIRCRAFT - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997022000682	19970220	00682	WP  	1997	2	20	AU961200         	2	19960806	G	7200		ENGINE          			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE TURBINE	SEIZED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							P70210			(AUS) ENGINE SEIZED - ENGINE HUNG DURING START AND WAS HARD TO PULL  THROUGH WITH PROPELLER						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997030300007	19970303	00007	EU  	1997	3	3	AU961201         	1	19960510	G	6120	665031886326REVT	MOTOR           	WOODWARD    	GOVERNOR    	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	HMU CNTRL SYS	LOOSE           	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		TO	TAKEOFF        	1			AU	S 			374  		WYG54779		785499			(AUS) RH ENGINE HYDROMECHANICAL UNIT (HMU) TORQUE MOTOR RETAINING BOLTS(3OFF) LOOSE AND RETURN FLOW `O' RING DAMAGED - S	USPECT INCORRECTLY TORQUED DURING LAST SHOP VISIT					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997022000683	19970220	00683	CE  	1997	2	20	AU961202         	1	19960812	G	5312	M20470AD5	RIVET           			CESSNA	320   	320D        	2074512	CE  	CONT  	O520  	TSIO520B    	17040	SO  					MAIN FRAME SYS	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NA					(AUS) RH AND LH AFT CANTED BULKHEAD RIVETS DETERIORATED - RIVET HEADS  MISSING						1	L	7	2 	3O	3	O		3A25    	E8CE				 
1997022000684	19970220	00684	EA  	1997	2	20	AU961203         	2	19960815	G	7414	M3004	SUPPORT         	SLICK       	4251        	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	DISTRIBUTOR GEAR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			973  		2010068R		L2813136A			(AUS) MAGNETO DISTRIBUTOR GEAR BEARING SUPPORT DAMAGED - FOUND DURING  INSPECTION IAW AD/ELEC/46 - INTERNAL DAMAGE TO MA	GNETO					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
1997030300008	19970303	00008	EU  	1997	3	3	AU961204         	1	19960807	G	3260	7232206581	PLATE           		UPLOCKHOOK  	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	LG POSITION IND	LOOSE           	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR UPLOCK HOOK STRIKER PLATE BOLT MISSING (1OFF2)						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997022000685	19970220	00685	WP  	1997	2	20	AU961205         	2	19960729	G	7210		RING            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TURBINE ENG. RED	FAULTY          	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 							P70145	940909		(AUS) ENGINE TORQUE RING FAULTY						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997022000686	19970220	00686	SW  	1997	2	20	AU961206         	1	19960220	G	3243	HP1431031	ROD             		MASTERCYL   	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LG WHEEL/BRAKE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					2756					(AUS) LH TOE BRAKE MASTER CYLINDER PISTON ROD FAILED AT BOTTOM THREAD  OF EYE END						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997030300009	19970303	00009	NE  	1997	3	3	AU961207         	2	19960119	G	7230	6058T86G01	COMPRESSOR      	GE          	CT79B       	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	TURBINE ENGINE	FOD             	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AU	S 			1176 		785487		785487			(AUS) LH ENGINE COMPRESSOR DAMAGED DUE TO FOD - INSPECTION FOUND ONE 1ST STAGE BLADE BENT FORWARD AND SEVERAL OTHER BLAD	ES DAMAGED -SUSPECT DUE TO ICE INGESTION - MID FRAME DESWIRL CONE RING ALSO  CRACKED AND DAMAGED					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997022000687	19970220	00687	SW  	1997	2	20	AU961208         	1	19960602	G	3220		STRUT           			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NOSE-TAIL GEAR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR STRUT CONTAMINATED BY AIR - STRUT SEALS HAD  BEEN REPLACED ON THE 1ST JUNE 1996 AND THE HYDRAULI	C SIDE HAD NOTBEEN FULLY BLED (CONTAINED AND AIRLOCK)					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997022000688	19970220	00688	SW  	1997	2	20	AU961209         	1	19960822	G	2460		LOOM            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	DC POWER DISTRIB	WORN            	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) AFT AVIONICS WIRING LOOM PARTIALLY CUT THROUGH BY AIRCONDITIONER ANTIVIBRATION BASE MOUNT - LOOM IS ROUTED THROUGH	 THE GAP BETWEENTHE MOUNT AND A STRUCTURAL RIB AND PROVIDES POWER FOR THE CVR, ELT, FDR AND AIRCONDITIONING SYSTEM					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997022000689	19970220	00689	GL  	1997	2	20	AU961210         	3	19960823	G	6114	TCM6958	HUB             	MCAULY      	1A103TCM    	CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	PROPELLER ASSY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			300  					R775268		(AUS) PROPELLER HUB CRACKED ADJACENT TO BOLT HOLES AS INDICATED IN MCCAULEY SB 219						1	H	7	1 	3O				3A19    		5	N	P50GL	 
1997022000690	19970220	00690	SO  	1997	2	20	AU961211         	1	19960823	G	7120	3802000	FRAME           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT FRAME CRACKED IN CLUSTER WELD ADJACENT TO THE RH  DRAG BRACE BUSHING - CRACK LENGTH 20MM (0.787IN)						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997022000691	19970220	00691		1997	2	20	AU961212         	4	19960827	G	2562		SWITCH          		ELT         	CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	EMERGENCY LOCATO	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELT `G' SWITCH FAULTY						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1997022000692	19970220	00692	CE  	1997	2	20	AU961213         	1	19960826	G	5511	2719	SPAR            	CESSNA      	172         	CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	HORZ STAB SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					2719					(AUS) HORIZONTAL STABILISER FRONT SPAR AND DOUBLER CRACKED - FOUND DURING INSPECTION IAW AD/C170/59 - AIRCRAFT IS USED F	OR CATTLE MUSTERING					1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
1997022000693	19970220	00693	NE  	1997	2	20	AU961214         	2	19960820	G	7210		GEAR BOX        			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					TURBINE ENG. RED	MAKING METAL    	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 			2076 				15077			(AUS) NO1 ENGINE REDUCTION GEARBOX MAGNETIC PLUG CONTAMINATED WITH TYPE3 METAL PARTICLES - SOME TYPE 1 AND TYPE 2 PARTIC	LES ALSO ON GEARBOX MAGNETIC PLUGS					1	G	7	2 	3U	3	U		H1NE    	E19EU				 
1996022300415	19960223	00415	SO  	1996	2	23	BTVR11996        	1	19960119	G	5610	1159SCB31024	WINDSHIELD      	PPG         		GULSTM	G1159 	GIV         	3980115	SO  										RT SIDE	CRACKED         	B			BTVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	41CP				91282H9190	1179				OUTER LAYER OF GLASS FOUND TO HAVE MULTIPLE CRACKS OVER THE ENTIRE SURFACE.  ALL GLASS WAS FOUND TO HAVE STAYED INTACT. 	 THE CRACKS APPEAR TO HAVE ORIGINATED AT THE LOWER CENTER AREAS OF THE GLASS ADJACENT TO THE FRAME.  (X)					2	L	7	2 	4F			RT	A12EA   					 
1996080600001	19960806	00001	EU  	1996	8	6	CA960103002      	1	19960102	G	3320	S2806102	SOCKET          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					SIDEWALL LIGHT	BURNT           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								LF05465A			(CAN)SMOKE COMING FROM SIDEWALL LIGHTING ROW 16 DEF. SOCKET FOR LIGHT BAR FOUND BURNED FROM ELECTRICAL ARCING. LAMP HOLD	ER REPLACED.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1996082900084	19960829	00084	GL  	1996	8	29	CA960110005      	3	19960102	G	6114	C5480	HUB             													MCAULY	2A34C	2A34C66     	GL  	NR1 SOCKET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1591 	741  					733444		(CAN)PROPELLER RECEIVED FOR CALENDAR TIME OVERHAUL. AS PER SERVICE BULLETIN 205B EDDY CURRENT CRACK DETECTION WAS PERFOR	MED ON PROPELLER HUB THREADED SOCKETS. CRACK DETECTED ON #1 SOCKET.															5	C	P3EA	 
1996090500243	19960905	00243	EU  	1996	9	5	CA960111013      	1	19960103	G	3230		PUSH PULL ROD   			GROB  	103CAT	G103TWNASTIR	1660202	EU  										MLG ACTUATOR	BEARING FAILED  	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA											(CAN)UNDERCARRIAGE COLLAPSED FOLLOWING TOUCHDOWN. INSPECTION OF THE SYSTEM REVEALED THE ROD END BEARING, AT THE END OF T	HE ACTUATOR PUSH/PULL ROD WHERE IT ATTACHES TO THE SECONDARY ACTUATOR ARM HAD COME OUT OF THE ROD END BEARING RETAINING 	RING. THE ROD THREADED PORTION OF THE ROD END WAS BENT, AS WAS THE ACTUATOR ARM TO WHICH IT WAS ATTACHED. THE LEFT GEAR 	DOOR WAS WORN THROUGH, REAR HINGE POINT ON THE DOOR WAS TORN AND FRONT HINGE BENT. THE BRAKE ACTUATOR ARM WAS BENT IN.			1	K	0	0 					G39EU   					 
1996091600007	19960916	00007	NM  	1996	9	16	CA960111016      	1	19960110	G	2917		FLOW REGULATOR  			BOEING	727   	727171C     	1384057	NM  										LT WELL HYD	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)HYDRAULIC FLOW REGULATOR IN LH WHEEL WELL LEAKING. REPLACED. STRIP REPORT INDICATES THAT THE INTERNAL SEALS WERE AT	 FAULT.					2	L	7	3 	4F				A3WE    					 
1996090500260	19960905	00260	NM  	1996	9	5	CA960115010      	1	19960109	G	2435	03600923	BEARING         	LUCAS       	23088002A   	DHAV  	DHC8  	DHC8*       		NM  										STARTER/GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1451 		420					(CAN)STARTER GENERATOR FAILURE CAUSED MINOR DAMAGE TO GENERATOR.						2	H	7	2 	4T			RT	A13NM   					 
1996090500270	19960905	00270	NE  	1996	9	5	CA960115020      	2	19960103	G	7230		BEARING         								PWA   	JT15  	JT15D1      	52060	NE  					COMP SHAFT NR 1	DISTRESSED      	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA			4721 	1844 				77326			(CAN)DURING DESCENT THE CREW REPORTED HEAVY VIBRATION AND NOISE FROM #1 ENGINE. THE ENGINE WAS SHUTDOWN. ENGINE TEARDOWN	 INDICATES MAJOR DISTRESS TO THE #1 BEARING.										4	F			E1NE				 
1996090500273	19960905	00273	CE  	1996	9	5	CA960115101      	1	19960111	G	2730	0510105291	CONTROL CABLE   	CESSNA      	0510105291  	CESSNA	172   	172M        	2072418	CE  										ELEV AFT PULLEY	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4458 								(CAN)DURING THE PREFLIGHT INSPECTION THE PILOT MOVED THE ELEVATOR AND HEARD A RUBBING NOISE AGAINST THE SKIN. INSPECTION	 REVEALED THE UPPER ELEVATOR CABLE WAS SEVERELY FRAYED AT THE AFT PULLEY LOCATION. TH E PULLEY WAS FOUND TO MOVE FREELY 	BUT HAD A SLIGHT GROOVE. A TIMELY AND THOROUGH PREFLIGHT MAY HAVE PREVENTED AN ACCIDENT.				1	H	7	1 	3O			NT	3A12    					 
1996090500276	19960905	00276		1996	9	5	CA960116002      	4	19960108	G	2562	2016	BATTERY         	POINTER     	C4000       															AT EXIT HOLE	CHAFED WIRE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)DURING ANNUAL RECERTIFICATION OF ELT, 3 OF THE BATTERY PACKS WERE NOTED WITH WIRES CHAFED AT THE EXIT HOLE ON TOP O	F BATTERY.																		 
1996090500279	19960905	00279	EA  	1996	9	5	CA960116007      	1	19960111	G	3213		PINS AND BEARING	ROTOL       	6008508071  	CNDAIR	CL600 	CL6001A11   	1900302	EA  										MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5537 								(CAN)MAIN LANDING GEAR SHOCK STRUT ATTACH PINS AND BEARINGS CORRODED AND SOME WEAR PROBLEMS AS WELL.						2	L	7	2 	4F			RT	A21EA   					 
1996090500291	19960905	00291		1996	9	5	CA960122005      	1	19960111	G	2913	3065476	DRIVE GEAR      	EASTERN     	1213HBG310  															OIL PUMP	MIS INSTALLED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						OM30651					(CAN)SUBMITTER STATES THAT THE DRIVE GEAR WAS INSTALLED BACKWARDS RESULTING IN FAILURE AND MAJOR DAMAGE TO THE PUMP.																			 
1996090500296	19960905	00296	SO  	1996	9	5	CA960122011      	1	19960106	G	5344	4810100	FLOOR RIB       			PIPER 	PA31T 	PA31T       	7103124	SO  										DOOR HINGE AREA	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6067 								(CAN)FUSELAGE FLOOR RIB CRACKED AT STN 222.19 WHERE THE CABIN DOOR HINGE IS ATTACHED. A 1/2 IN  CRACK IS LOCATED IN THE 	CORNER WHERE THE PLATE FOR THE CABIN DOOR HINGE IS BOLTED. SUBMITTER STATES THAT THIS LOCATION IS HARD TO SEE WITHOUT RE	MOVING THE PLATE FIRST. SEE ALSO SDR 960122012, CRACK AT STN 224.9.				1	L	7	2 	3T				A8EA    					 
1996090500297	19960905	00297	SO  	1996	9	5	CA960122012      	1	19960106	G	5344	4522402	FLOOR RIB       			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   									DOOR HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6069 								(CAN)FUSELAGE FLOOR RIB FOUND CRACKED AT STN 224.9 IN THE UPPER CORNER WHERE THE CABIN DOOR HINGE IS RIVETED. SEE ALSO S	DR 960122011 FOR A CRACK OF THE SAME DESCRIPTION AT STN.22.19					1	L	7	2 	3T				A8EA    					 
1996090500318	19960905	00318		1996	9	5	CA960123012      	1	19960112	G	2435	03601018	BEARING         	LUCAS       	23079005    															START/GENERATOR	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA				787  		5427					(CAN)STARTER GENERATOR BEARING FAILED AT THE ANTI-DRIVE END.																			 
1996121200498	19961212	00498	EA  	1996	12	12	CA960123022      	2	19960116	G	8530		VALVE           			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	#4 CYLINDER	JAMMED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			3189 	649  				L4004427A	720159		(CAN) NON FERROUS METAL IN THE MAIN AND SUCTION OIL SCREENS. ZERO COMPRESSION ON #4 CYLINDER, SUSPECT A JAMMED VALVE. #4	 CYLINDER REMOVED AND SENT FOR REPAIR.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1996091200850	19960912	00850	EU  	1996	9	12	CA960123027      	2	19960102	G	7200		ENGINE          								RROYCE	SPEY  	SPEY55515P  	54521	EU  					TAIL PIPE	MAKING METAL    	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								9796			(CAN)VIBRATIONS FELT AT FL250. POWER REDUCED FROM 94 PERCENT TO 91 PERCENT & VIBRATIONS INCREASED. ENGINE WAS SHUTDOWN &	 FLIGHT DIVERTED. POST FLIGHT INSPECTION FOUND METAL IN TAILPIPE & DAMAGE TO BOTH THE LP & HP SYSTEMS. FURTHER DETAILS W	ILL FOLLOW ENGINE TEARDOWN.									4	F			E2EU				 
1996091900543	19960919	00543	NM  	1996	9	19	CA960126025      	1	19960119	G	2435	03600923	BEARINGS        	LUCAS       	23088002A   	DHAV  	DHC8  	DHC8*       		NM  										STARTER ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1447 		353					(CAN)BOTH STARTER GENERATOR BEARINGS ON THE ROTOR FAILED. FOUND ON THE BENCH.						2	H	7	2 	4T			RT	A13NM   					 
1996091900549	19960919	00549	SW  	1996	9	19	CA960126032      	1	19960111	G	5320		TUBE STRUCTURE  			MOONEY	M20   	M20J        	5870219	SW  										VENT WINDOW	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2575 								(CAN)CORROSION FOUND ON AIRCRAFT TUBULAR STRUCTURE IN AREAS OF PILOTS VENT WINDOWS AND BELOW BOTH AIR VENTS ON THE SIDES	 OF THE AIRCRAFT. CORROSION ALSO FOUND ON THE OVERHEAD TUBE BY THE AIR VENT.					1	L	7	1 	3O				2A3     					 
1996091900551	19960919	00551	CE  	1996	9	19	CA960126034      	1	19960112	G	2730	05130631	BRACKET         	CESSNA      	05130631    	CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  					ELEV BELLCRANK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5948 					29320D4D			(CAN)AT THE ANNUAL INSPECTION OF THIS AIRCRAFT THE FORWARD ELEVATOR BELLCRANK SUPPORT BRACKET WAS FOUND CRACKED. THE LOC	ATION IS AT THE LEFT FORWARD ATTACHMENT ANGLE UNDER THE CABIN FLOOR AFT OF THE FUEL S ELECTOR. THE TOP BAR SUPPORTING TH	E BELLCRANK CENTRE BOLT WAS ALSO FOUND BROKEN. THE PART WAS NOT REPAIRABLE AND THEREFORE WAS REPLACED WITH NEW P/N 05130	63-1. SUBMITTER NOTES THAT THE REPLACEMENT PART WAS FOUND TO BE MORE ROBUST THAN THE ORIGINAL.			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1997011600064	19970116	00064	CE  	1997	1	16	CA960126036      	1	19960115	G	2913	99120624	PUMP            			CESSNA	500   	560CESSNA   	2076750	CE  										LT ENG HYD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			921  	921  							(CAN) DURING A VISUAL INSPECTION ON PHASE 4, FOUND OUTBOARD UPPER HOUSING ATTACH BOLT HOLE AREA CRACKED ON L/H ENGINE DR	IVEN HYDRAULIC PUMP.					2	L	7	2 	4F			RT	A22CE   					 
1996091900570	19960919	00570	CE  	1996	9	19	CA960129013      	1	19960116	G	2910	249A4TB	CHECK VALVE     			CESSNA	441   	441         	2076020	CE  										HYD SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			5389 								(CAN)HYDRAULIC CHECK VALVE UNDER #2 PASSENGER SEAT LEAKED AND CONTAMINATED BOTH THE INSTRUMENT AIR PRESSURE LINES AND TH	E WATER SEPARATOR. UPON DISASSEMBLY OF THE VALVE, THE 'O' RINGS WERE FOUND DEFECTIVE.					1	L	7	2 	3T			RT	A28CE   					 
1996100300803	19961003	00803	EA  	1996	10	3	CA960131001      	1	19960125	G	5310		STRUCTURE       	DHAV        		DHAV  	DHC2  	DHC2EVANS   	2801832	EA  										FORWARD FRAME	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)IN REFERENCE TO SB 2/49 FORWARD FUSELAGE FRAME TUBULAR STRUCTURE FOUND CORRODED USING RADIOGRAPHY TECHNIQUE.SUBMITE	R NOTES THAT ULTR ASONIC TECHNIQUE WAS INITIALLY USED BUT 'NO R EADING' LED TO FRAME REJECTION.  WHEN RADIOGRAPHY WAS US	ED PITTING CORROSION WAS FOUND.  THUS THEY FEEL THAT A RADIOGRAPH INSPECTION WILL PROVIDE A MORE POSITIVE RESULT AS WELL	L AS PROVIDING A PERMANENT RECORD.			1	H	7	1 	3O				A806    					 
1997011600067	19970116	00067	CE  	1997	1	16	CA960131012      	1	19960120	G	2920	551701084	HYDRAULIC LINE  			CESSNA	500   	560CESSNA   	2076750	CE  										AUX.HYD. SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			929  								(CAN) FOLLOWING A TENSION CHECK OF AILERON CABLES TO CLEAR A REPORTED DEFECT, THE AREA AT AILERON SECTOR (PANEL NO.271AT	C) WAS INSPECTED FOR CLEANLINESS AND THE AUXILIARY HYDRAULIC LINE SHOWED CHAFING MARKS PRESUMABLY CAUSED BY CONTACT WITH	 THE AILERON SECTOR. THIS HYDRAULIC LINE WAS PROBABLY MOVED DURING A PREVIOUS ACCESS TO THIS AREA WHICH CANNOT BE DETERM	INED.			2	L	7	2 	4F			RT	A22CE   					 
1996101000416	19961010	00416	SW  	1996	10	10	CA960131014      	1	19960123	G	6510	2060403389	HANGER ASSEMBLY 			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					LUG AREA	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE802381			(CAN)WHEN CARRYING OUT ASB 206-95-86 REV.B, INSPECTION OF TAIL ROTOR DRIVESHAFT HANGER ASSEMBLY AND SPRING. A VISIBLE WE	AR STEP IN THE FILLET RADIUS OF THE HANGER LUG WAS FOUND.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996101000417	19961010	00417	CE  	1996	10	10	CA960131201      	1	19960106	G	3240	0500106194	LINE            	CESSNA      	0500106194  	CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300D       	17022	SO  					BRAKE	ABRAIDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4381 					28272D3D			(CAN)UPPER ELEVATOR CABLE ABRAIDED THE ALUMINUM BRAKE LINE. REPAIRED AND AIRCRAFT RETURNED TO SERVICE.						1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1996101000419	19961010	00419	EA  	1996	10	10	CA960202002      	1	19960115	G	3010	15323C	VALVE           	BENDIX      		DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					DEICE	CORRODED        	W				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA						244461U		PCE42076			(CAN)DURING PREFLIGHT THE DEICE SYSTEM TESTED AND RH DEICE BOOT WOULD NOT INFLATE. RH DISTRIBUTOR VALVE REPLACED. VALVE 	CORRODED INTERNALLY.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1996101000420	19961010	00420	EA  	1996	10	10	CA960202003      	1	19960115	G	2822	2532310102	PUMP            			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					FUEL	LOW PRESSURE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				528  		2210		PCE42076			(CAN)DURING MAINTENANCE TO FIND START PROBLEM, FUEL PUMP OUTPUT PRESSURE FOUND TOO LOW						1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1996101000422	19961010	00422	NM  	1996	10	10	CA960202007      	1	19960126	G	2435	03600923	BEARING         	LUCAS       	23088002A   	DHAV  	DHC8  	DHC8*       		NM  	PWA   	120   	PW120       		NE  					GEN DRIVE END	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1021 		1284		120896			(CAN)DRIVE END BEARING FAILED ON STARTER GENERATOR.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996101000423	19961010	00423	EU  	1996	10	10	CA960202008      	1	19960122	G	8200	2220FG	TANK UNIT       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    		EU  					MENTHENOL	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								14902			(CAN)WATER MENTHENOL TANK DOES NOT INDICATE CONTENTS OF TANK IN THE 20-27 RANGE.						2	L	7	2 	3T	4	T		A24EU   	A196				 
1996101000433	19961010	00433		1996	10	10	CA960202019      	4	19960119	G	2360	211SC1	STATIC WICK     	CHELTON     		EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118       		NE  	HAMSTD	14RF	14RF9       	NE  	WINGS & ELEV	CORRODED        	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			CA								PCE115667	880130		(CAN)ON DESCENT IN LIGHT RAIN, AIRCRAFT HAD RADIO RECEPTION FAILURE, BUT COMMUNICATION TRANSMISSION WAS NORMAL. 8 STATIC	 WICKS HAD TO BE REPLACED. 2 ON EACH WING AND 2 ON EACH ELEVATOR. RESISTANCE CHECKS T O BE INCREASED TO 1200 HOURS FROM 	4000.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
1996101000439	19961010	00439	NE  	1996	10	10	CA960202025      	2	19960109	G	7322		FCU             			DHAV  	DHC8  	DHC8*       		NM  	PWA   	PW120 	PW123       		NE  					#1 ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CL	CLIMB          	1			CA			4139 					123223			(CAN)IN CLIMB #1 ENGINE PARAMETERS DECREASED AND PILOT SHUT THE ENGINE DOWN. THE #1 ENGINE MAIN FUEL CONTROL UNIT (MFCU)	 WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996102300007	19961023	00007	NE  	1996	10	23	CA960202026      	2	19960125	G	7310		"O" RING PACKING								PWA   	PW120 	PW126A      		NE  					FUEL MANIFOLD	DAMAGED         	W				E				ENGINE SHUTDOWN         				A			FLAME/FIRE                			CL	CLIMB          	1			CA			4578 	458  				124535			(CAN)DURING A LANDING ROLL THERE WAS A FIRE ON #1 ENGINE. POST FLIGHT THE FIRE WAS CONFIRMED TO ORIGINATE FROM A DAMAGED	 FUEL MANIFOLD PACKING THAT WAS REPLACED THE PREVIOUS DAY AFTER A FUEL LEAK WAS DETEC TED.										4	T			E2ONE				 
1996101000443	19961010	00443	EA  	1996	10	10	CA960205006      	2	19960115	G	7230	310082903	VALVE COMP BLEED			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					DOWEL	STICKING        	W				E				ENGINE SHUTDOWN         				O			OTHER                     			IN	INSP/MAINT     	1			CA				5133 				PCE42076			(CAN)FOLLOWING CORRECTION OF A STARTING SNAG THE ENGINE WOULD NOT RESPOND TO THE THROTTLE BUT WOULD STAGNATE AND TEMPERA	TURES WOULD CLIMB UNTIL THE FUEL WAS SHUTOFF. INVESTIGATION FOUND THAT DUE TO EXTREMECOLD WEATHER THE LUBRICANT ON THE G	UIDE DOWEL OF THE COMPRESSOR SURGE BLEED VALVE WOULD NOT PERMIT IT TO OPEN AND RELIEVE THE COMPRESSOR TO PERMIT ACCELERA	TION. THE EXISTING LUBRICANT WAS CLEANED FROM THE DOWEL AND FRESH LUBRICANT WAS APPLIED AND THE ENGINE OPERATED NORMALLY	 AFTERWARD.		1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1996101000886	19961010	00886	EU  	1996	10	10	CA960208102      	1	19960129	G	5244	A5247504000600	HANDLE          	AIRBUS      	A52475000008	AIRBUS	310   	A310304     		EU  										LOWER AC DOOR	WORN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN)ON CLIMB AT 8,000 FEET DOOR WARNING OCCURRED FOR LOWER ACCESS DOORS. AS THIS WAS FIRST FLIGHT AFTER A "C" CHECK, TH	E CREW ELECTED TO RETURN TO BASE. MAINTENANCE CHECK REVEALED DOOR HANDLE FOR LOWER AC CESS DOOR WAS FOUND RELEASED. AIRB	US SB A310-52-2040 CORRECTS THIS PROBLEM OF INADVERTENT RELEASE.				2	L	7	2 	4F			RT	A35EU   					 
1996101000906	19961010	00906	EU  	1996	10	10	CA960212029      	1	19960202	G	2910		RELIEF VALVE    			AIRBUS	320   	A320212     		EU  	GE    	CFM56 	CFM565A     	13802	NE  					YELLOW SYS HYD	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA								731350			(CAN)DURING FLIGHT, YELLOW HYDRAULIC SYSTEM LOW PRESSURE INDICATION. AIRCRAFT RETURNED TO BASE FOR MAINTENANCE. INVESTIG	ATION REVEALED PRESSURE RELIEF VALVE LEAKING DUE TO DETERIORATION OF SEALS. HYDRAULIC SEALS REPLACED AND LEAK CHECKED CA	RRIED OUT IN ACCORDANCE WITH MM 05-51-11.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
1999081200318	19990812	00318	EA  	1999	8	12	CA960212031      	2	19960202	G	8520		ROD             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					CRANKCASE	BROKEN          	W				A				UNSCHED LANDING         				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) A CONNECTING ROD BROKE AND DAMAGED THE CRANKCASE.  THE PROPELLER WAS IN FEATHER, THEREFORE,THE ROD HIT THE INSIDE 	OF THE ENGINE A FEW MOMENTS BEFORE THE ENGINE STOPPED TURNING.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997011600068	19970116	00068	CE  	1997	1	16	CA960212032      	1	19960131	G	3340	D758520	LANDING LIGHT   			CESSNA	500   	560CESSNA   	2076750	CE  										R/H MAIN GEAR	LOW CLEARANCE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING DAILY INSPECTION, THE R/H OLEO EXTENSION WAS LOW AND THERE WAS VERY LITTLE CLEARANCE BETWEEN TIRE AND 	LIGHT. IF OLEO HAD BOTTOMED OUT, THE LIGHT WOULD HAVE PRESSED INTO THE TIRE ABOUT 1/8". THE TIRE WAS NOT NEW. THE LIGHT 	WAS ADJUSTED TO PROVIDE CLEARANCE FOR THE TIRE. THE LIGHTS WERE ORIGINALLY INSTALLED IN ACCORDANCE WITH SB 560-33-12.				2	L	7	2 	4F			RT	A22CE   					 
1996121200504	19961212	00504	NE  	1996	12	12	CA960212037      	2	19960205	G	7322		FCU             								PWA   	PT6   	PT6A25      	52043	NE  					DRIVE BEARING	DAMAGED         	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			2700 					52110			(CAN) DURING A FLIGHT, ENGINE PARAMETERS SUDDENLY INCREASED WHILE IN CRUISE. THE ENGINE DID NOT RESPOND TO POWER LEVER I	NPUTS. THE PILOT DIVERTED FLIGHT TO THE POINT OF ORIGIN AND SECURED THE ENGINE BEFORE DESCENDING. INSPECTION REVEALED A 	DAMAGED FUEL CONTROL UNIT GOVERNOR DRIVE BEARING. THE FUEL PUMP WAS REMOVED AND THE FCU WAS SENT FOR REPAIR.									3	T			E4EA				 
1996121200505	19961212	00505	NE  	1996	12	12	CA960212038      	2	19960207	G	7250		BLADE           								PWA   	120   	PW120A      		NE  					LP TURBINE	FRACTURED       	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								120057			(CAN) IN CRUISE, THE WASHROOM SMOKE DETECTOR ALARM SOUNDED AND A SLIGHT ODOUR OF OIL IN THE CABIN WAS NOTICED. POST FLIG	HT INSPECTION REVEALED A VIBRATION IN THE CONTROLS DURING ENGINE START. UPON ENGINE REMOVAL, TWO LP TURBINE BLADES WERE 	FOUND TO BE FRACTURED AT MID-SPAN.									4	T			E20NE				 
1996101000915	19961010	00915		1996	10	10	CA960214008      	4	19960209	G	3442	RT1401B400083101	RT UNIT         	BENDIX      	RT1401B40008															MOD BOARD	BURNT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1439					(CAN)REPAIR TO CIRCUIT BOARD FOUND TO BE LESS THAN SATISFACTORY CAUSING A SHORT AND BURN OUT IN THE MODULATOR BOARD.																			 
1998041000454	19980410	00454		1998	4	10	CA960214009      	4	19960202	G	3418	9002EN3	SWITCH          			BRAERO	DH125 	BAE125800A  	1500285	EU  										CASE INTERNAL	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SIGNAL SUMMING UNIT (SSU) FAIL LIGHT COMES ON INDICATING A FAULT IN THE STALL PROTECTION SYSTEM.  SUBMITTER STATES	 THEY HAVE REPLACED THREE UNITS WITHIN THE LAST 200 HOURS.					2	L	7	2 	4F			RT	A3EU    					 
1996101000918	19961010	00918		1996	10	10	CA960214012      	4	19960208	G	3422	6225812001	FLUX VALVE      	COLLINS     	6225812001  	BEECH 	90    	C90A        	1152911	CE  										COMPASS SYS	OIL SOAKED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						7551					(CAN)AIRCRAFT COMPASS SYSTEM REPORTED UNRELIABLE. EXAMINATION OF COMPASS COMPONENTS AND WIRING REVEALED THAT THE FLUX VA	LVE WAS SATURATED WITH INSTRUMENT OIL. COLLINS CONFIRMED THAT THE LOSS OF OIL COULD R ESULT IN FAILURE OF THE COMPONENT.	 FLUX VALVE WAS REPLACED.				1	L	7	2 	3T			RT	3A20    					 
1996101000924	19961010	00924	EU  	1996	10	10	CA960214018      	1	19960124	G	5210	FE12700002	DOOR STRIKER    			AIRBUS	320   	A320212     		EU  										DOOR 1R	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)DURING INSPECTION OF THE PASSENGER DOORS ACTUATOR STRIKER MECHANISM,DOOR 1R FOUND JAMMED WITHOUT CORROSION. REF AOT	 52-12. MAINTENANCE ACTION INVOLVED CLEANING AND LUBRICATION STRIKER MECHANISM. STRIKER MECHANISM FUNCTIONALLY CHECKED S	EVERAL TIMES, OPERATED SATISFACTORILY.				2	L	7	2 	4F			RT	A28NM   					 
1996101000926	19961010	00926	SO  	1996	10	10	CA960214020      	1	19960205	G	2140	B3040	HEAD GASKET     	JANITROL    	B3040       	PIPER 	PA31T 	PA31T       	7103124	SO  										HEATER	LEAKING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			168  			1128883					(CAN)HEATER FAILED PRESSURE DECAY TEST. INVESTIGATION FOUND THE HEAD GASKET TO BE LEAKING. REPLACED THE HEAD GASKET AND 	APPLIED PERMATEX #1372 AS PER JANITROL OVERHAUL MANUAL. SUBMITTER SUSPECTS THE PERMATEX SEALANT WAS LEFT OUT DURING THE 	LAST OVERHAUL.				1	L	7	2 	3T				A8EA    					 
1996101000929	19961010	00929	CE  	1996	10	10	CA960221201      	1	19960102	G	2913	10138800519	MOTOR           	AIRIGHT     	10138800519 	BEECH 	300   	300BEECH    	1152930	CE  										POWER PACK	WEAK            	W		A		A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			17   			271					(CAN)THE AIRCRAFT WAS IN CRUISE FLIGHT WHEN THE LANDING GEAR HANDLE RED LIGHT CAME ON AND THE PILOTS OBSERVED THE GEAR B	EGIN TO LOWER. INSPECTION REVEALED THAT THE HYDRAULIC POWER PACK HAD FAILED AND WAS A LLOWING THE GEAR TO DROP AS THIS A	IRCRAFT DOES NOT HAVE UPLOCKS. THE 60 AMP POWER PACK BREAKER WAS RESET AND THE GEAR WAS CYCLED. THE MOTOR OF THE POWER P	ACK OPERATED SLOWER THAN NORMAL AND EVENTUALLY THE 60 AMP BREAKER POPPED AGAIN. THE POWER PACK WAS REPLACED AND THE AIRC	RAFT RETURNED TO SERVICE.		2	L	7	2 	4T				A24CE   					 
1996102400387	19961024	00387	EU  	1996	10	24	CA960222001      	1	19960213	G	2432	052000	TERMINAL NUTS   			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT									BATTERY	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)TERMINAL NUTS ON BATTERY WERE FOUND LOOSE AFTER 20 HOURS INSTALLATION. NUTS WERE TORQUE CHECKED AND WITNESS MARKED.	 CHECKED NUTS AGAIN AND WERE FOUND LOOSE AGAIN. NEW NUTS WERE ORDERED AND WHEN RECEIV ED, WERE OF A DIFFERENT TYPE.					2	L	7	2 	4F				A3EU    					 
1997011600075	19970116	00075	EA  	1997	1	16	CA960222009      	2	19960122	G	8520	9645200	BREATHER        								LYC   	O360  	IO360C1E6   	41514	EA  					ENG OIL	BLOCKED         	W				A	B	E		UNSCHED LANDING         	EMER. DESCENT           	ENGINE SHUTDOWN         		K	Y		FLUID LOSS                	ENGINE STOPPAGE           		CL	CLIMB          	1			CA								L1215751A			(CAN) AFTER TAKEOFF, THE PILOT NOTICED THE OIL PRESSURE DROPPING ON THE RIGHT ENGINE. AS IT APPROACHED THE CAUTION ARC O	N THE GAUGE, HE ELECTED TO SHUT DOWN ENGINE AND RETURN TO AIRPORT.HE THEN NOTICED LEFT ENGINE PRESSURE DROPPING AND DECL	ARED AN EMERGENCY. ENGINE SEIZED AND A WHEELS UP LANDING WAS MADE SHORT OF THE RUNWAY. MAINTENANCE STAFF DETERMINED THE 	PROBLEM TO BE LOSS OF OIL DUE TO FROZEN ENGINE BREATHERS.								3	O			1E10				 
1996102400396	19961024	00396	CE  	1996	10	24	CA960222017      	1	19960124	G	5521	07346013	SPAR            	CESSNA      	07346013    	CESSNA	180   	180         	2072602	CE  										ELEV OUTB HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3890 								(CAN)THE ELEVATOR SPAR WAS FOUND CRACKED DURING THE ANNUAL 100 HOUR INSPECTION. SUBMITTER REPORTS THAT AN UNAPPROVED REP	AIR WAS ALSO FOUND DURING THE REPAIR.					1	H	7	1 	3O			NC	5A6     					 
1996102400397	19961024	00397	SO  	1996	10	24	CA960222018      	1	19960212	G	5310	225387	TUBING          	PIPER       	PA22150     	PIPER 	PA22  	PA22150     	7102210	SO  										STRUCTURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2566 			225387			25734		(CAN) AIRCRAFT WAS INSPECTED AND FOUND TO HAVE SEVERAL CRACKS AND CORROSION IN STRUCTURAL TUBING, AS PER SKETCH, THAT AP	PEARS TO BE THE RESULT OF WATER FREEZING.  SUBMITTER REPORTS THAT THE INSPECTION WOULD NOT HAVE SHOWN THESE DEFECTS WITH	 OUT HAVING LIFTED THE FLOOR PANELS.				1	H	7	1 	3O				1A6     					 
1996102400398	19961024	00398	NM  	1996	10	24	CA960222019      	1	19960208	G	3097		WIRE HARNESS    			DHAV  	DHC8  	DHC8102     	2809003	NM  										INTAKE HEAT	BURNED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA											(CAN)DURING FLIGHT WHEN ENTERING ICING CONDITIONS, CREW SELECTED ENGINE INTAKE BYPASS DOOR OPEN. LEFT HAND EMERGENCY FUE	L SHUTOFF VALVE CLOSED AND ENGINE SHUTDOWN. INSPECTION INDICATED THAT 115 VOLT AC INTAKE HEAT WIRE HAD SHORTED ON A HARN	ESS SUPPORT TRAY UNDER THE FLOOR AT PASSENGER SEAT, ROW 3. THE SHORTED WIRE HAD CAUSED A WIRE BUNDLE TO BURN.				2	H	7	2 	4T			RT	A13NM   					 
1996102400399	19961024	00399		1996	10	24	CA960222020      	4	19960208	G	2562	11513241	SCREWS          		RESCU406    															ELT FRAME	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN)LOOSE SCREWS FOUND INSIDE ELT. FRAME USED DURING CONSTRUCTION HAD HELICOILS MOUNTED OFF CENTRE CAUSING INSUFFICIENT	 THREAD ENGAGEMENT FOR SCREWS SECURING PC BOARD. FIVE UNITS FROM AFFECTED BATCH S/N'S107 THROUGH 263 RETURNED IN THIS CO	NDITION. SIL BEING RAISED TO ADDRESS ISSUE.																	 
1996102400400	19961024	00400		1996	10	24	CA960222021      	4	19960214	G	2210	82210010001	CONTROL CABLE   			DHAV  	DHC8  	DHC8311     	1386006	EA  										AUTO PILOT	MISINSTALLED    	W		A		O				OTHER                   				F	W		FLT CONT AFFECTED         	INADEQUATE Q C            		CR	CRUISE         	1			CA			1864 								(CAN)IN CRUISE,AT FL250,WITH AUTO PILOT ON, AIRCRAFT OSCILLATING ABOUT LATERAL AXIS,APPROX. 60 TO 80 FEET.INSPECTION FOU	ND NO TENSION ON THE AUTOPILOT SERVO CABLE WHICH SHOULD BE 15 TO 20 LBS.LH ELEVATOR CONTROL CABLE TENSION WITH SERVO DIS	CONNECTED WAS FOUND TO BE 35 LBS & SHOULD BE 70,PLUS OR MINUS 7 LBS.SERVO CONTROL RH CABUCKLE ATTACH TO ELEVATOR CONTROL	 CABLE, INCORRECTLY INSTALLED.CABUCKLE YOKE WAS FITTED TO ELEVATOR CONTROL CABLE 180 DEGREES OUT CAUSING SERVO CABLE TO 	BE INTERTWINED WITH ELEVATOR CONTROL CABLE.LH ELEVATOR & RH CABLE TURNBUCKLE INCORRECTLY ADJUSTED.FORWARD CABLE ATTACH T	O TURNBUCKLE & AFT CABLE ATTACH TO TURNBUCKLE WERE STILL IN SAFETY BUT MISALIGNED CAUSING TWISTING OF THE AFT CABLE.AIRC	2	H	7	2 	4T			RT	A13NM   					 
1996102400403	19961024	00403		1996	10	24	CA960222027      	4	19960209	G	2562	MN1300	BATTERY         	ACK         	E01         	AMTR  	RWEXEC	ROTORWAYEXEC		GL  										ELT	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			40   			014332					(CAN)DURING ELT RECERTIFICATION CHECK A POWDERED DUST NOTICED ON CASE. UNIT FAILED TO ACTIVATE WHEN TURNED ON OR IN ARME	D POSITION. ALL BATTERIES FOUND CHAFED, TWO WERE CORRODED, AND SEVERAL HAD LOW VOLTAG E. SUBMITTER SUGGESTS CAUSE IS RES	ULT OF USE IN HELICOPTER WITH HIGHER VIBRATIONS. BATTERIES WERE MANUFACTURED BY DURACELL.				1	G	7	1 	3O				EXPA1G71					 
1996102400404	19961024	00404	NM  	1996	10	24	CA960222028      	1	19960214	G	2710	532DB	PANEL           	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  										RH AND LH	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUGED FROM LOW	ER JAM-SWITCH CABLE CLAMPS.					2	H	7	2 	4T			RT	A13NM   					 
1996102400405	19961024	00405	EA  	1996	10	24	CA960222029      	1	19960214	G	2710	532DB	PANEL           	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RH AND LH	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06, BOTH LEFT (P/N 532DB) AND RIGHT (P/N 632DB) PANEL GOUGED FROM LOWER JAM-SWI	TCH CABLE CLAMPS.					2	H	7	2 	4T			RT	A13NM   					 
1996102400406	19961024	00406	EA  	1996	10	24	CA960222030      	1	19960214	G	2710	532DB	PANELS          	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RH AND LH	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06, BOTH LEFT (P/N 532DB) AND RIGHT (P/N 632DB) PANELS GOUGED FROM LOWER JAM-SW	ITCH CABLE CLAMPS.					2	H	7	2 	4T			RT	A13NM   					 
1996102400407	19961024	00407	EA  	1996	10	24	CA960222031      	1	19960214	G	2710	632DB	PANEL           	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RIGHT HAND	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 RIGHT HAND PANEL GOUGED FROM LOWER JAM-SWITCH CABLE CLAMPS.						2	H	7	2 	4T			RT	A13NM   					 
1996102400408	19961024	00408	EA  	1996	10	24	CA960222032      	1	19960214	G	2710	532DB	PANELS          	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										LH AND RH	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUDED FROM LOW	ER JAM-SWITCH CABLE CLAMPS.					2	H	7	2 	4T			RT	A13NM   					 
1996102400409	19961024	00409	EA  	1996	10	24	CA960222033      	1	19960214	G	2710	532DB	PANELS          	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RH AND LH	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUGED FROM LOW	ER JAM-SWITCH CABLE CLAMPS.					2	H	7	2 	4T			RT	A13NM   					 
1996102400410	19961024	00410	EA  	1996	10	24	CA960222034      	1	19960214	G	2710	632DB	PANEL           	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RIGHT HAND	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 RIGHT HAND PANEL GOUGED FROM LOWER JAM-SWITCH CABLE CLAMP.						2	H	7	2 	4T			RT	A13NM   					 
1996102400411	19961024	00411	EA  	1996	10	24	CA960222035      	1	19960214	G	2710	532DB	PANELS          	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RH AND LH	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUGED FROM LOW	ER JAM-SWITCH CABLE CLAMPS.					2	H	7	2 	4T			RT	A13NM   					 
1996102400412	19961024	00412	EA  	1996	10	24	CA960222036      	1	19960214	G	2710	632DB	PANEL           	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RIGHT HAND	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 RIGHT HAND PANEL GOUGED FROM LOWER JAM-SWITCH CABLE CLAMP.						2	H	7	2 	4T			RT	A13NM   					 
1996102400413	19961024	00413	EA  	1996	10	24	CA960222037      	1	19960214	G	2710	632DB	PANEL           	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RIGHT HAND	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-O6 RIGHT HAND PANEL GOUGED FROM LOWER JAM-SWITCH CABLE CLAMP.						2	H	7	2 	4T			RT	A13NM   					 
1996102400414	19961024	00414	EA  	1996	10	24	CA960222038      	1	19960214	G	2710	532DB	PANELS          	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RH AND LH	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)FOUND AS A RESULT OF SD ALERT AL-95-06 BOTH LEFT HAND (P/N 532DB) AND RIGHT HAND (P/N 632DB) PANELS GOUGED FROM LOW	ER JAM-SWITCH CLAMPS.					2	H	7	2 	4T			RT	A13NM   					 
1997011600077	19970116	00077	SO  	1997	1	16	CA960222201      	2	19960329	G	8520		MAIN BEARING    			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	#2 BEARING	FRETTED         	W				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			CA								228430R	890661		(CAN) DURING CRUISE ENGINE STARTED TO VIBRATE AND THEN STOPPED. AIRCRAFT RETURNED TO ORIGIN AND LANDED SAFELY. IT WAS DI	SCOVERED THAT ENGINE HAD STOPPED DUE TO #2 MAIN BEARING FAILURE. TEARDOWN REVEALED THAT THE #2 BEARING HAD TURNED IN THE	 CRANKCASE STOPPING THE OIL FROM FLOWING TO THE NUMBER 2 CONNECTING ROD. THE CONNECTING ROD THEN FAILED AND DAMAGED THE 	CRANKCASE, CAMSHAFT AND CYLINDERS. THIS CAUSED THE ENGINE TO QUIT RUNNING.			1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
1996102400418	19961024	00418		1996	10	24	CA960223003      	4	19960201	G	2312	TH4502NNNB	COM CONTROL     			HUGHES	500N  	500N        	3027374	SW  										COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1825					(CAN)TAC/COM CONTROL HEAD HAD BEEN CHECKED TWICE FOR COMPLAINTS, BUT NO FAULT FOUND. SNAGS INCLUDED INTERMITTENT RESPONS	E TO MOMENTARY SWITCHES OF 'CHANNEL SELECT' AND 'RADIO NEXT', AND ALSO UNIT WOULD IND ICATE RECEPTION WHEN NO AUDIO COUL	D BE HEARD. BOTH SNAGS VERIFIED IN A HELICOPTER WITH AN IFR 2000 COMM ANALYZER. BOTH SNAGS VERIFIED WITH AT LEAST ONE RH	 IN SCAN MODE. SUBMITTER SUGGESTS A DEFICIENCY IN MANUFACTURE TEST PROCEDURES. UNIT RETURNED TO MANUFACTURER.			1	G	7	1 	3U			NC	H3WE    					 
1996102400419	19961024	00419	NM  	1996	10	24	CA960223004      	1	19960216	G	2435	03600923	BEARING         	LUCAS       	23088002A   	DHAV  	DHC8  	DHC8*       		NM  										START/GEN	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA				1447 		353					(CAN)BEARING FAILURE ON STARTER-GENERATOR CAUSED DAMAGE TO ROTOR, STATOR, SPEED P/U AND FAN.						2	H	7	2 	4T			RT	A13NM   					 
1997011600079	19970116	00079	CE  	1997	1	16	CA960223009      	1	19960215	G	7120	160128	MOUNT           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	ENG BULKHEAD	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4071 								(CAN) CORROSION WAS DETECTED ON BOTH ENGINE MOUNTS AND BOTH ENGINES WERE REMOVED TO EFFECT APPROVED REPAIR UNDER RDA AUT	HORITY. DURING RE-RIVETING OF ASSEMBLY, IT BROKE IN TWO DUE TO THE CORROSION. IT WAS STATED THAT OVER 50 PERCENT OF THE 	STRUCTURE INTEGRITY HAD BEEN COMPROMISED. AFTER FURTHER INVESTIGATION, IT WAS DISCOVERED THAT AD 75-23-08R5 HAD NOT BEEN	 FULLY COMPLIED WITH.			1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997011600080	19970116	00080	EA  	1997	1	16	CA960223012      	2	19960216	G	8540	72245	SUPPORT ASSEMBLY			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					RING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1206 				L1001548			(CAN) RING GEAR SUPPORT ASSEMBLY HAD A CIRCUMFERENTIAL CRACK APPROXIMATELY 16" LONG.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1997011600081	19970116	00081		1997	1	16	CA960223016      	4	19960215	G	2210		AUTO  TRIM SYS  			CESSNA	500   	560CESSNA   	2076750	CE  										AUTO PILOT	FAULTY          	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) WHILE FLYING WITH AUTO PILOT ENGAGED, THE AUTO-TRIM SYSTEM (MISS-TRIM) LIGHT COMES ON AND THE SYSTEM IS UNABLE TO 	CORRECT THIS SITUATION THUS DISENGAGES THE AUTOPILOT AFTER A SHORT PERIOD OF TIME. CESSNA HAS BEEN MADE AWARE OF THE PRO	BLEM AND STATES THERE SHOULD BE A FIX AVAILABLE SOON. THIS PROBLEM ONLY HAPENS AT HIGH SPEED CRUISE AND/OR AT THE TOP EN	D OF A CLIMB.			2	L	7	2 	4F			RT	A22CE   					 
1997011600087	19970116	00087	EU  	1997	1	16	CA960227009      	1	19960103	G	3213		AXLE BARREL     			BRAERO	DH125 	BAE125800A  	1500285	EU  										R/H MAIN GEAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2466 								(CAN) DURING A SEAL REPLACEMENT, IT WAS DISCOVERED THAT THERE WAS CORROSION BEYOND LIMITS ON THE UPPER MATING SURFACE. I	T IS LOCATED AT THE AREA WHERE THE OLEO STRUT SLIPS INTO THE AXLE BARREL AND CONTACTS IN TWO LOCATIONS. THIS IS SEALED A	T THE FACTORY AND WOULD NOT HAVE BEEN DISCOVERED UNTIL THE 4500 HOUR INTERVAL FOR OVERHAUL.				2	L	7	2 	4F			RT	A3EU    					 
1997011600091	19970116	00091	WP  	1997	1	16	CA960227014      	2	19960213	G	7261		OIL SYSTEM      								GARRTT	TFE731	TFE7313     	01518	WP  					LT ENG	DEPLETED        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA			5076 					P90279			(CAN) L/H OIL PRESSURE DROPPED AND L/H LOW OIL PRESSURE LIGHT CAME ON. ENGINE SHUT DOWN, AND AIRCRAFT LANDED.  FOUND LOW	ER COWL AND ENGINE SOAKED WITH OIL AND OIL TANK EMPTY. NO EVIDENCE OF OIL IN JET PIPE OR BYPASS DUCT. ENGINE AND COWL WA	SHED DOWN, AND OIL TANK TOPPED UP. AIR/OIL BREATHER REPLACED, ENGINE RUN-UP AND TEST FLIGHT CARRIED OUT WITH NO FAULT FO	UND, OIL CONSUMPTION NORMAL.								4	F			E6WE				 
1997011600093	19970116	00093	SO  	1997	1	16	CA960227024      	1	19960220	G	2150	643368	BALL BEARING    			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					IDLER PULLEY	DISINTEGRATED   	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2471 	2471 				273625R			(CAN) WHILE PERFORMING ENGINE MAINTENANCE, IT WAS NOTICED THAT THE AIR CONDITIONING IDLER SHEAVE (PULLEY) WAS NOT ALIGNE	D WITH THE COMPRESSOR PUMP SHEAVE AS IS NORMALLY THE CASE. FURTHER INVESTIGATION WARRANTED DISASSEMBLY, AND IT WAS FOUND	 THAT THE IDLER SHEAVE BEARING HAD COMPLETELY DISINTEGRATED. SUBSEQUENT LOADS IMPOSED ON THE SHEAVE RESULTED IN WEAR ON 	THE ASSOCIATED PARTS AND HARDWARE REQUIRING THEIR REPLACEMENT.			1	L	7	1 	3O	3	O		A25SO   	E8CE				 
1996110100003	19961101	00003	SO  	1996	11	1	CA960229202      	1	19960218	G	3220		NLG SCISSORS    			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  									NOSE GEAR	UNFASTENED      	W				A				UNSCHED LANDING         				O			OTHER                     			LD	LANDING        	1			CA											(CAN)THE NOSE GEAR WOULD NOT EXTEND WHEN SELECTED. AIRCRAFT MADE A NOSE GEAR UP LANDING. INVESTIGATION FOUND THAT THE NO	SE GEAR WAS UNFASTENED TO FACILITATE EASIER GROUND HANDLING AND THE BOLT WAS REPLACED INCORRECTLY THUS ALLOWING THE NOSE	 WHEEL TO TWIST AND PROBABLY JAM IN THE WHEEL WELL.				1	L	7	2 	3O				A7SO    					 
1997012200002	19970122	00002	EA  	1997	1	22	CA960304004      	1	19960213	G	2810		FUEL            			FLEET 	80    	FLEET80     		EA  	CONT  	C85   	C8512F      	17008	SO  					FUEL TANK/CARB	CONTAMINATED    	W				K				NONE                    				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	AP	APPROACH       	1			CA								23500612			(CAN) DURING FINAL APPROACH, ENGINE STARTED TO RUN ROUGH, BUT WORKING THROTTLES SEEMED TO FIX PROBLEM. ON SHORT FINAL, E	NGINE QUIT AND THEN PROPELLER STOPPED. GLIDE INITIATED BUT LANDED SHORT IN A SHED. INVESTIGATION REVEALED THAT FUEL LINE	 FROM STRAINER HAD BROKEN ON IMPACT, AND WATER AND CONTAMINATIONS WERE FOUND IN REMAINING 1.5 GALLONS OF FUEL. ENGINE ST	OPPAGE MAY HAVE BEEN DUE TO CARB ICE AND FUEL STARVATION.			1	H	7	1 	3O	3	O		788     	E233				 
1997011600100	19970116	00100	NE  	1997	1	16	CA960304005      	1	19960210	G	2913	66WA400	PUMP            			SKRSKY	S64   	S64E        	8142604	NE  										1ST STG HYD PUMP	MAKING METAL    	W				A	O			UNSCHED LANDING         	OTHER                   			F			FLT CONT AFFECTED         			EX	EXTERNAL LOAD  	1			CA				52   							(CAN) DURING HOVER AFTER 18 MINUTES OF FLIGHT, THIS LOGGING HELICOPTER DEVELOPED A STIFFNESS OF CYCLIC AND THEN COLLECTI	VE PITCH. SLINGING WAS ABORTED AND PRECAUTIONARY LANDING WAS CARRIED OUT. AFTER FURTHER INVESTIGATION, IT WAS DISCOVERED	 THAT THERE WAS METALLIC MATERIAL IN THE FIRST STAGE HYDRAULIC PUMP AND SUBSEQUENT DOWNLINE SYSTEM INCLUDING AFT SERVO B	ANK. CONSEQUENTLY, AFCS SERVO AND ALL COMPONENTS OF THE FIRST STAGE HYDRAULIC SYSTEM WERE REPLACED. THE AIRCRAFT WAS THE	N GROUND AND FLIGHT TESTED.		2	G	7	2 	4U				H4EA    					 
1997011600104	19970116	00104	CE  	1997	1	16	CA960304011      	1	19960213	G	3040		DEICE TANK      			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520J    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	VENT LINE WELD	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								503204	871603		(CAN) 1 INCH CRACK AT WELDMENT OF VENT LINE AND LOWER SECTION TANK SKIN. AREA APPEARS CORRODED AND VENT LINE SECTION BEL	OW TANK APPEARS TO HAVE HAD AN IMPACT.					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
1996110100006	19961101	00006	SO  	1996	11	1	CA960304012      	1	19960217	G	3243		MASTER CYLINDER 	PIPER       		PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   									BRAKE	FROZEN WATER    	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			546  								(CAN) BRAKE REPORTED TO NOT BE CAPABLE OF HOLDING THE AIRCRAFT. INVESTIGATION FOUND THAT THE AIRCRAFT HAD BEEN STORED OU	TSIDE DURING FREEZING TEMPS AND THAT AN AMOUNT OF WATER HAD FROZEN IN THE MASTER CYLINDER THUS DEGRADING BRAKING PERFORM	ANCE. THE MASTER CYLINDER AND BRAKES WERE BLED AND THE AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3T				A8EA    					 
1997011600105	19970116	00105	SO  	1997	1	16	CA960305201      	1	19960229	G	7810	646463181	EXHAUST TEE     			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520B    	17040	SO  					MOUNT BOSS AREA	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			252  					802510			(CAN) EXTENSIVE CRACKING OF THIS EXHAUST COMPONENT CAUSED A LOSS OF MANIFOLD PRESSURE DUE TO TURBOCHARGER INACTIVITY. TH	E LEFT REAR ENGINE ISOLATOR RECEIVED HEAT DAMAGE AS WELL. INITIAL METALURGICAL TESTS INDICATE STRESS CRACKING LIKELY CAU	SED BY INSTALLATION PRELOAD.				1	L	7	1 	3O	3	O		A25SO   	E8CE				 
1996110100013	19961101	00013	NM  	1996	11	1	CA960306014      	1	19960228	G	5755	532DB	PANEL           	DHAV        		DHAV  	DHC8  	DHC8*       		NM  										SPOILER QUADRANT	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)INSPECTION AS A RESULT OF SERVICE DIFFICULTY ALERT AL-95-06 FOUND ROLL SPOILER PANELS BOTH LEFT HAND AND RIGHT HAND	 (632DB) GROOVED FROM THE WIRE BUNDLE ON THE ROLL SPOILER QUADRANT. NO CONTROL PROBLE MS FOUND. SB 8-27-80V IS BEING USE	D TO REPAIR. SB STILL UNDER REVIEW.				2	H	7	2 	4T			RT	A13NM   					 
1996110100015	19961101	00015	CE  	1996	11	1	CA960306016      	1	19960223	G	3246	AN770A	BOLT            	EDO         	249A2870    	CESSNA	180   	180G        	2072616	CE  						MCAULY				FLOATS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						619620					(CAN) AFTER ROUTINE CHANGE OVER FROM FLOATS TO SKIS, A FLOAT BOLT WAS CHECKED FOR ITS CONDITION. IT WAS FOUND TO BE CORR	ODED TO THE POINT WHERE REPLACEMENT WAS DEEMED TO BE NECESSARY. FUTHER INVESTIGATION FOUND SPREADER BAR BOLTS AND LOWER 	LIFT STRUT BOLTS CORRODED BEYOND ACCEPTABLE LIMITS. ALL WERE REPLACED WITH NEW HARDWARE.				1	H	7	1 	3O				5A6     					 
1996110100021	19961101	00021	EA  	1996	11	1	CA960311008      	1	19960229	G	7600	C6CEM14323	QUADRANT        	DHAV        		DHAV  	DHC6  	DHC6        	2802606	EA  										COCKPIT	WARPED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)NEW QUADRANT BEING INSTALLED TO SATISFY CF-73-06R2. AT INSTALLATION IT WAS FOUND DISTORTED AT THE LOWER FORWARD END	. NO INTERFERENCE NOTED, BUT QUADRANT WAS NOT USED. MARKS ON QUADRANT. MELT 950556 AND 12215/0.					1	H	7	2 	3T			RT	A9EA    					 
1996110100024	19961101	00024	EA  	1996	11	1	CA960311011      	1	19960303	G	7830	22850201481	TORQUE BOX      			CNDAIR	CL600 	CL6002B19   		EA  										LH NACELLE TR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5217 								(CAN)FORWARD FRAME INBOARD FLANGE OF TORQUE BOX FOUND CRACKED AT RADIUS AND A PIECE IS MISSING. CAUSE UNKNOWN.						2	L	7	2 	4F			RT	A21EA   					 
1996110100033	19961101	00033	CE  	1996	11	1	CA960311022      	1	19960301	G	3242	16404700	BRAKE DISC      	CLEVELAND   	4074A       	CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					BOLT HOLES	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			713  					520066			(CAN)WHILE CARRYING OUT AN INSPECTION ON A FLOAT AIRCRAFT, WHEEL REMOVED. AXLE REMOVED TO SERVICE BEARINGS AND REPLACE B	RAKE DISC AND THEN FOUND CRACKS ALONG THE BOLT HOLES. ALL THREE HOLE WERE FOUND CRACK ED.					1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1997011600121	19970116	00121	EA  	1997	1	16	CA960311034      	1	19960301	G	7930	601600143	TUBE ASSEMBLY   			CNDAIR	CL600 	CL6002B16   	1900305	EA  										RT ENG	LOOSE           	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA			2113 								(CAN) AFTER 5 MINUTES IN CRUISE AT FL350, R/H ENGINE OIL PRESSURE SLOWLY DECREASED FROM 85 TO 25 PSI. WHEN RED WARNING L	IGHT BLINKED, ENGINE SHUT DOWN. CHECKED AND SECURED OIL TUBE BETWEEN OIL PRESSURE TRANSMITTER AND 'B' SUMP SYSTEM. HIGH 	POWER RUN CARRIED OUT, NO LEAK FOUND, RESERVOIR TOPPED UP.				2	L	7	2 	4F			RT	A21EA   					 
1997011600122	19970116	00122	NE  	1997	1	16	CA960311035      	2	19960224	G	7200		ENGINE          			LKHEED	1011  	10113851    	5265010	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					NR 2	MAKING METAL    	W		A		E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			39223	2262 				10256			(CAN) DURING CLIMB, VIBRATION INCREASED STEADILY. ENGINE SHUT DOWN AND AIRCRAFT RETURNED TO AIRPORT. FOUND HEAVY METAL C	ONTAMINATION FROM LOCATION BEARINGS (MAGNETIC CHIP DETECTOR). #2 ENGINE REPLACED AND CHECKED SERVICEABLE.					2	L	7	3 	4F	4	F		A23WE   	E12EU				 
1997011600126	19970116	00126	EU  	1997	1	16	CA960312021      	1	19960208	G	4950		B-NUT           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					APU GAS GEN VENT	LOOSE           	W				A	D			UNSCHED LANDING         	RETURN TO BLOCK         			E	O		VIBRATION/BUFFET          	OTHER                     		CL	CLIMB          	1			CA								875			(CAN) APPROXIMATELY 1 MINUTE AFTER TAKEOFF, A POP WAS HEARD. AIRCRAFT LANDED BACK AT STAGING AREA. INVESTIGATION REVEALE	D GAS GENERATOR VENT LINE HAD COME UNDONE AT THE 'B' NUT. NUT WAS RE-INSTALLED AND TORQUED. GROUND RUN SUCCESSFULLY. AIR	CRAFT RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
1996110100384	19961101	00384	EU  	1996	11	1	CA960313009      	1	19960302	G	2910	201042056	LINE            			AIRBUS	320   	A320212     		EU  	GE    									LH ANTI SKID  HY	RUPTURED        	W				H				DEACTIVATE SYST/CIRCUITS				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN)LOSS OF GREEN HYDRAULIC SYSTM DURING FLIGHT. LOSS WAS CAUSED BY RUPTURED HYDRAULIC LINE ON LEFT ANTI-SKID MODULE. D	EFECTIVE LINE REPLACED AND SYSTEM CHECKED FOR LEAKS.					2	L	7	2 	4F			RT	A28NM   					 
1996110100386	19961101	00386	EU  	1996	11	1	CA960313011      	1	19960222	G	3246	AGA1481	HUB             	DUNLOP      	AHA1489     	BAG   	BAE146	BAE146200A  	1500266	EU  										MLG  WHEEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5242 			KJ217					(CAN)2 CRACKS APPROXIMATELY 1 INCH LONG FOUND ORIGINATING FROM LIGHTENING HOLES.						2	H	7	4 	4F			RT	A49EU   					 
1996110100405	19961101	00405	SO  	1996	11	1	CA960315021      	1	19960305	G	3220	8361802	TRUNNION        			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  									LEFT HAND FORK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2471 								(CAN)A FULL PENETRATION CRACK, 5 CM IN LENGTH, WAS FOUND ON THE NOSE TRUNNION AS INDICATED. REPLACEMENT PART WAS P/N 836	06-07 AND TRUNNION KIT P/N 766-211.					1	L	7	1 	3O				A25SO   					 
1996110100411	19961101	00411	SW  	1996	11	1	CA960320001      	1	19960215	G	5740		BOLT            	BLANCA      		BBAVIA	7     	7GCBC       	1220601	SW  	LYC   									WING ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3175 								(CAN)DURING SPAR REPLACEMENT ON THE WING, ALL BOLTS WERE FOUND TO BE CORRODING WHERE THEY CONTACT THE WOOD. THE HEAD AND	 THREAD OF THE BOLTS WAS FOUND TO BE CLEAN AND BRIGHT BUT THE SHANK OF THE BOLT IN TH E WOOD SHOWS SERIOUS CORROSION.					1	H	7	1 	3O			NC	A759    					 
1996110100413	19961101	00413	SW  	1996	11	1	CA960320003      	1	19960215	G	5711		SPAR            	BLANCA      	7GCBC       	BBAVIA	7     	7GCBC       	1220601	SW  	LYC   									L/H WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3175 								(CAN)SUBJECT SPAR INDICATED IRREGULAR LINES ACROSS THE GRAIN AT 14 INCHES AND 92 INCHES FROM THE ROOT END, BOTH FORE AND	 AFT FACES. REFERENCE MATERIAL ENCYCLOPEDIA OF WOOD CHAPTER 4, FIG.4-32 AND FIG.4-8A.SUBMITTER EXPLAINS HE HAS SEEN THIS	 BEFORE AND HAS SUBMITTED ANOTHER SDR #951027007, 19 OCTOBER 1995.				1	H	7	1 	3O			NC	A759    					 
1996110100418	19961101	00418	SO  	1996	11	1	CA960320013      	1	19960314	G	3230	67189000	LINE            	PIPER       	67189000    	PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   									GEAR DOWN	CORRODED/FAILED 	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA			3700 								(CAN)PILOT HAD TO ACTIVATE THE EMERGENCY EXTENSION SINCE THE NORMAL GEAR DOWN SELECTION WAS INOPERATIVE. INVESTIGATION R	EVEALED THAT THE HYDRAULIC LINE HAD FAILED. THE LOCATION OF THE FAILED LINE IS UNDER  THE RIGHT CORNER OF THE WINDSHIELD	 AND CORROSION FOLLOWED BY FAILURE ON THE LINE WAS CAUSED BY TRAPPED MOISTURE IN THE INSULATION. SUBMITTER STATES THAT T	HIS PROBLEM HAS BEEN SEEN BEFORE.			1	L	7	1 	3O				2A13    					 
1996110100422	19961101	00422	WP  	1996	11	1	CA960320019      	1	19960306	G	3260	24085571018	LEVER           			CVAC  	440   	440         	2422902	WP  										NLG DOWNLOCK	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN)AFTER TAKEOFF THE NOSE LANDING GEAR REFUSED TO RETRACT. CONFIRMED BY TOWER AND AIRCRAFT LANDED. BROKEN DOWNLOCK LEV	ER DUE TO MISADJUSTED DOWN LOCK MICROSWITCH. LEVER REPLACED AND SWITCH ADJUSTED.					2	L	7	2 	4R				6A6     					 
1996110100428	19961101	00428	SO  	1996	11	1	CA960320026      	1	19960314	G	3230	6714600	UPPER DRAG LINK 	PIPER       		PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   									MOUNT ATTACHMENT	WORN            	W				K				NONE                    				J	N	W	WARNING INDICATION        	FALSE WARNING             	INADEQUATE Q C            	IN	INSP/MAINT     	1			CA			3700 								(CAN) IT WAS NOTED THAT THE NOSE GEAR LIGHT WAS EITHER SLOW TO ACTIVATE OR WOULD NOT ACTIVATE AT ALL. INVESTIGATION FOUN	D THAT THERE WAS SO MUCH PLAY IN THE UPPER BEARING AREA OF THE DRAG LINK THAT THE NOSE GEAR LIMIT SWITCH COULD BE ACTIVA	TED/DEACTIVATED JUST BY MOVING THE NOSE GEAR BY HAND. INSPECTION FOUND THAT THE BOLTS WASHERS AND BUSHINGS HAD BEEN INST	ALLED INCORRECTLY AND THE BEARING WAS NOT THE CORRECT PART NUMBER. THIS COMBINATION OF PROBLEMS CAUSED THE HOLE TO ELONG	ATE AND THE DRAG LINK TO BE SCRAPPED.		1	L	7	1 	3O				2A13    					 
1996110700230	19961107	00230	EA  	1996	11	7	CA960325003      	1	19960312	G	3213	17135	CAP END         	ROTOL       	601R8500151 	CNDAIR	CL600 	CL6002B19   		EA  										LH MLG STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2485 			0241B1C					(CAN)SHOCK STRUT UPPER AND LOWER ATTACHMENT LUGS PIN PISTON CAP ENDS CRACKED AND EARS TORN OFF. ON DISASSEMBLY LOWER PIN	 PISTON WAS FOUND CRACKED.					2	L	7	2 	4F			RT	A21EA   					 
1996110700254	19961107	00254	EU  	1996	11	7	CA960327016      	1	19960305	G	3230		TARGETS         			AIRBUS	320   	A320212     		EU  										NOSE LDG WELL	LOOSE           	W				O				OTHER                   				J	O		WARNING INDICATION        	OTHER                     		CL	CLIMB          	1			CA											(CAN)LANDING GEAR SELECTED UP ON CLIMB DEPARTURE, ECAM MESSAGE WARNING INDICATED NOSE GEAR NOT UPLOCKED, NOSE LDG REMAIN	ED EXTENDED. LANDING GEAR SELECTED DOWN, BOTH MAIN LANDING GEAR REMAINED RETRACTED. L ANDING GEAR THEN SELECTED UP AND N	ORMAL OPERATION OCCURRED. THE FOLLOWING MAINTENANCE ACTION TOOK PLACE, NOSE LANDING GEAR SENSORS INSPECTED SATISFACTORIL	Y, TARGETS (GAPS) CHECKED: 24GA ADJUSTED AND TARGETS 36GA AND 38GA FOUND LOOSE AND WERE SECURED.			2	L	7	2 	4F			RT	A28NM   					 
1997011600139	19970116	00139		1997	1	16	CA960328001      	4	19960318	G	3416	152734	SUPPORT RING    			BRAERO	DH125 	HS125700A   	4230170	EU  										LOCATING SLOT	MODIFIED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) SUPPORT RING HAD BEEN MODIFIED AS DESCRIBED IN SERVICE ALERT AV-93-07R1 14 OCTOBER 1993.						2	L	7	2 	4F				A3EU    					 
1996110700261	19961107	00261	NM  	1996	11	7	CA960328006      	1	19960318	G	3240	MS2125006008	BOLT            			DHAV  	DHC8  	DHC8*       		NM  										BRAKE	OUT OF SPEC     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)DURING ASSEMBLY OF DHC8 BRAKE UNIT BOLTS P/N MS21250-06008 WERE REPLACED WITH NEW STOCK. ON TORQUING BOLTS TO CORRE	CT SPEC. IN ACCORDANCE WITH BF GOODRICH MAINTENANCE MANUAL.BOLTS WERE NOTED TO BE STRETCHING. BOLTS HAD STRETCHED .024 I	NCHES AND DEFINITE NECKING OF THE THREADED SECTION HAD OCCURRED. BOLTS ALL FROM ONE BATCH. ALL THESE BOLTS REMOVED FROM 	STOCK FOR A TOTAL OF 50.			2	H	7	2 	4T			RT	A13NM   					 
1996111400264	19961114	00264	EA  	1996	11	14	CA960409024      	2	19960208	G	7261	3022375	SEAL            			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					R/H ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			CL	CLIMB          	1			CA			261  					PCE42076			(CAN) DURING CLIMB, THE R/H ENGINE OIL PRESSURE WAS NOTED TO BEGIN FLUCTUATING. THE ENGINE TORQUE STARTED TO FLUCTUATE A	ND AS A RESULT, THE CREW SHUT DOWN THE ENGINE AND RETURNED TO AIRPORT. MAINTENANCE FOUND THAT THE OIL WAS LEAVING THE EN	GINE FROM THE ENGINE DRIVEN FUEL PUMP DRIVE SEAL. WHEN THE SEAL CARRIER WAS REMOVED, THE SEAL WAS FOUND TO HAVE MIGRATED	 FROM THE CARRIER. A NEW SEAL WAS INSTALLED IN THE CARRIER AND THE ENGINE AND AIRCRAFT WERE RETURNED TO SERVICE.			1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1996111400265	19961114	00265	NM  	1996	11	14	CA960409025      	1	19960321	G	3240	65179783	VALVE SWIVEL    			BOEING	727   	727171C     	1384057	NM  										BRAKE RT MLG	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				904  							(CAN)RH MAIN GEAR BRAKE SWIVEL VALVE LEAKING UNDER PRESSURE. REPLACED.						2	L	7	3 	4F				A3WE    					 
1997031100005	19970311	00005	GL  	1997	3	11	CA960412006      	2	19960402	G	7250	23031938	NOZZLE          								ALLSN 	250C  	250C20      	03013	GL  					TURB 2ND STAGE	CRACKED         	W				A	B	E		UNSCHED LANDING         	EMER. DESCENT           	ENGINE SHUTDOWN         		J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		HO	HOVERING       	1			CA			3302 					CAT15239			(CAN) FORCED LANDING DUE TO ENGINE FAILURE. TEARDOWN REVEALED 2ND STAGE TURBINE NOZZLE CRACKED AROUND THE INSIDE CIRCUMF	ERENCE. SPECIFICALLY THEY WERE IN THE BEND RADIUS OF THE 2ND STAGE NOZZLE DIAPHRAGM. THESE NOZZLES HAVE BEEN SENT TO COM	PANY FOR ANALYSIS.									3	U			E4CE				 
1996111400280	19961114	00280	EU  	1996	11	14	CA960412017      	1	19960402	G	5320	15S53572604204	STRAP           	AEROSP      		AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  					LH MLG  WELL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17306								(CAN)DURING AIRCRAFT BLOCK CHECK THE STRAP USED TO REINFORCE THE MAIN LANDING GEAR WHEEL WELL WAS FOUND CRACKED. THIS ON	E ON THE LEFT SIDE. OPERATOR NOTES THAT THEY HAVE SSEN THIS BEFORE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
1996111400292	19961114	00292	EA  	1996	11	14	CA960415008      	2	19960411	G	7414	1051324	IMPULSE SPRING  	BENDIX      	D4LN2021    	CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					DUAL MAG	BROKEN          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			2295 	758  		3437		L13680			(CAN)ON CLIMBOUT, ENGINE RPM DROPPED TO IDLE. EXAMINATION REVEALED THE DUAL MAGNETO IMPULSE SPRING BROKEN. AWD 78-09-07 	NOT COMPLIED WITH.					1	H	7	1 	3O	3	O		A20CE   	1E10				 
1996111400297	19961114	00297		1996	11	14	CA960415017      	4	19960415	G	3416	804710DH	STOPS           	AEROMECH    	804710DH    															ALTIMETER	MISRIGGED       	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						8388					(CAN) ALTIMETER FAILED BENCH TEST AS PER SERVICE DIFFICULTY ADVISORY AV-93-07R1, NO STOPS ON BAROMETRIC KNOBVERY LITTLE 	RESISTANCE FELT AT 30 90 & DID NOT STOP AND WENT PAST 31 50  IT DID THE SAME ON THE BOTTOM END GOING PAST 28.10.																		 
1996121200533	19961212	00533	CE  	1996	12	12	CA960418010      	1	19960305	G	7603	5052456849	CONTROL LEVER   	BEECH       	5052456849  	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					AT PEDESTAL	GROOVED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12050					PCE52489			(CAN) WHILE INSPECTING OF THE THROTTLE LEVER PEDESTAL A GROOVE WAS FOUND TO HAVE BEEN WORN BY RUBBING THE CATCH PLATE. S	IMILAR CONDITION FOUND ON BOTH THE RIGHT AND LEFT CONTROL LEVERS. SUBMITTER STATES THAT BEECH NOW MAKES THE PLATES OF A 	SOFTER MATERIAL AND RECOMMENDS INSPECTING THIS AREA CLOSELY.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1996111400621	19961114	00621	NE  	1996	11	14	CA960418016      	2	19960325	G	7250	214112605	SCREW           	LYC         	214105720   						LYC   	ALF502	ALF502R5    	41580	NE  					HEAT SHIELD	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A457					(CAN)ON REMOVAL OF THE 4TH ROTOR, A SCREW WAS FOUND LOOSE AND PROTRUDING APPROXIMATELY 3/16 INCH FROM THE REAR HEAT SHIE	LD WITH ASSOCIATED DAMAGE IN THE AREA OF THE BLADE ROOTS. RIVET HEADS WORN DOWN AND L IGHTLY RUBBING ON ROTOR DISC. MANU	FACTURER SUGGESTED A REVISED TORQUE VALUE FOR THE SCREW.									4	F			E6NE				 
1996111400622	19961114	00622	SO  	1996	11	14	CA960418201      	2	19960402	G	8540		MOUNTING PAD    	CONT        		CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520BB   	17040	SO  					ALTERNATOR PAD	MISMACHINED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				674  				236988R			(CAN)MOUNTING HOLE AND PAD FOR ALTERNATOR MACHINED APPROXIMATELY .080 INCH TOO FAR FORWARD CAUSING ALTERNATOR DRIVE GEAR	 NOT MESHING PROPERLY.					1	L	7	2 	3O	3	O		3A10    	E8CE				 
1996111400624	19961114	00624	NM  	1996	11	14	CA960419002      	1	19960408	G	3010	153212A	VALVE           	BENDIX      		DHAV  	DHC8  	DHC8*       		NM  										DEICE SYSTEM	SEIZED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						RF3377					(CAN)DEICE DISTRIBUTION CONTROL VALVE SEIZED DUE TO CORROSION. DRAIN HOLES FOUND OBSTRUCTED BY POTTING COMPOUND CAUSING 	ACCUMULATION OF MOISTURE AND SUBSEQUENT FAILURE.					2	H	7	2 	4T			RT	A13NM   					 
1996111400637	19961114	00637	NM  	1996	11	14	CA960422006      	1	19960219	G	2620	A805586	CUTTER KNIFE    		A80680026   	BOEING	727   	727         	1384001	NM  										FIRE EXTINGUISH	MISMATCH        	W		A		O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						B3431					(CAN)SUBJECT EXTINGUISHER IS A SHOCK WAVE TYPE OF FIRE EXTINGUISHER. ITEM WAS RECEIVED FOR OVERHAUL WITH A CUTTER KNIFE 	TYPE OUTLET P/N A805586 INSTALLED. FIRE EXTINGUISHER WAS NONFUNCTIONAL IN THE CONFIGURATION RECEIVED AND WOULD NOT HAVE 	FUNCTIONED IN AN EMERGENCY SITUATION. CORRECT P/N OF SHOCK WAVE TYPE OUTLET REQUIRED ON THIS FIRE EXTINGUISHER IS A80680	3-1. MSB ISSUED TO PRECLUDE THIS TYPE OF MISCONFIGURATION.			2	L	7	3 	4F				A3WE    					 
1996112100164	19961121	00164	GL  	1996	11	21	CA960424018      	3	19960423	G	6110	BU10602	PISTON SEAL     	HARTZL      		DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1159 		BU10602		PCE42076	BU10602		(CAN)SLIGHT OIL TRACE AFT OF PROP SPINNER . PISTON SEAL REPLACED						1	H	7	2 	3T	4	T		A9EA    	E4EA	6	C	P15EA	 
1996121200535	19961212	00535	CE  	1996	12	12	CA960424021      	1	19960409	G	3231	ART5CR	ROD END         		C3500A      	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	NLG	BROKEN          	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1132 					564221	763171		(CAN) BOW WHEEL FAILED TO RETRACT, FOUND ROD END HAD BEEN BROKEN NEXT TO THE CENTRE BALL ALLOWING THE ROD END TO PULL AW	AY FROM THE BALL END. SUSPECT INCORRECT RIGGING DUE TO THE 1/4 INCH DISTANCE OF THE ROD END FROM THE GEAR WITH THE GEAR 	MANUALLY RETRACTED UP AND THE ACTUATOR IS FULLY RETRACTED.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P3EA	 
1996121200536	19961212	00536	SO  	1996	12	12	CA960424022      	1	19960326	G	3211	2082900	STUD            	PIPER       		PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1A     	41532	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3155 					L392640			(CAN) INSPECTION OF STUDS AS PER AWD 95-20-07 REVEALED FINE LINEAR CRACK INDICATIONS AT THE RADIUS UNDER THE BOLT HEAD. 	THE BOLTS WERE REJECTED.					1	L	7	1 	3O	3	O		1A15    	E295				 
1996121200537	19961212	00537	CE  	1996	12	12	CA960424023      	1	19960330	G	5312		BULKHEAD        			CESSNA	210   	210G        	2073430	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	STA 230.1	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								1106394A	72066		(CAN) DURING A 100 HOUR ANNUAL INSPECTION A CRACK WAS FOUND ON THE AFT BULKHEAD AT STA. 230.1. THE BULKHEAD IS AN ATTACH	 FOR THE VERTICAL FIN. THE CRACK IS LOCATED ON THE RIGHT HAND SIDE FROM THE CUT OUT FOR THE RUDDER CABLES AND MIGRATES T	OWARD THE LOWER RIGHT HAND BOLT.				1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1996121200538	19961212	00538	CE  	1996	12	12	CA960424024      	1	19960330	G	5330		SKIN            			CESSNA	210   	210G        	2073430	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	STA 59.7	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								1106394A	72066		(CAN) SKIN AT STATION 59.7 FOUND CRACKED ON BOTH SIDES FROM THE LANDING GEAR CUTOUT TOWARDS THE DOOR FRAME. THE SUBMITTE	R STATES THAT THE CRACK APPEARS TO EXTEND THROUGH AT LEAST TWO SKINS ABOUT 1.5 INCHES LONG.					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1996112100173	19961121	00173	WP  	1996	11	21	CA960429001      	2	19960411	G	8530	35175	MOUNTING BOLT   	DHAV        	GM10103     	DHAV  	DHC1  	DHC1B2      	2801736	GL  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					VALVE RKR BOX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				254  				DHC120			(CAN)PILOT FOUND #3 ROCKER BOX LOOSE AND TWO NUTS INSIDE LOWER COWLING. MAINTENANCE FOUND #3 ROCKER BOX MOUNTING BOLTS H	AD BACKED OFF AND FALLEN INTO BOX COVER. ALSO, THE MOUNTING BOLTS ON ALL THREE REMAINING ROCKER BOXES HAD LOST THEIR TOR	QUE LEADING TO BELIEVE THAT INCORRECT TORQUE WAS APPLIED AT LAST OVERHAUL 15 YEAR PREVIOUS.				1	L	7	1 	3O	3	I		EXPA1L71	A8EU				 
1996121200541	19961212	00541	SO  	1996	12	12	CA960429008      	1	19960404	G	3213	78033	TORQUE LINKS    	PIPER       	78033       	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3031 					L2232127A	K13495		(CAN) TORQUE LINKS INSPECTED AS PER AWD AND FOUND CRACKED IN THE LOCATION SHOWN IN THE SERVICE MANUAL. CRACKS WERE DYE P	ENETRANT CHECKED BUT SUBMITTER STATES THAT THE CRACKS WERE VISIBLE WITH A 10X MAGNIFYING GLASS.					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1996112100179	19961121	00179	NE  	1996	11	21	CA960429009      	2	19960411	G	7250	123022	TURBINE CASE    	PWA         	PW123       	DHAV  	DHC8  	DHC8301     		NM  	PWA   	PW120 	PW123       		NE  					NR 2 ENG	PUNCTURED       	W		A		A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			E	A	T	VIBRATION/BUFFET          	FLAME/FIRE                	ENGINE CASE PENETRATION   	CL	CLIMB          	1			CA			5857 			123022		123022			(CAN)AFTER TAKEOFF, VIBRATION FROM #2 ENGINE FOLLOWED BY ENGINE FIRE.  AFM PROCEDURES CARRIED OUT, BOTH BOTTLES DISCHARG	ED. FIRE EXTINGUISHED BUT LATER REIGNITED  AFTER LANDING, AIRPORT FIRE CREW EXTINGUISHED FIRE. A LARGE QUANTITY OF RESID	UAL OIL NOTED IN THE NACELLE AREA WHICH COULD BE THE SOURCE OF SECOND FIRE. HOLE IN THE FRONT OF THE TURBINE SUPPORT CAS	E AT THE 8 O'CLOCK POSITION WITH BLADE AND SHROUD SEGMENT DEBRIS IN THE NACELLE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996112100188	19961121	00188	SO  	1996	11	21	CA960502049      	2	19960415	G	8530		PISTON PIN      			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	REAR ENG	FRACTURED       	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J	R		WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA			130  					352477	793546		(CAN) CLIMBING THROUGH 5,200 FEET, REAR ENGINE RPM STARTED FLUCTUATING 200-300 RPM. OIL PRESSURE DROPPED TO ZERO, ENGINE	 FEATHERED. ENGINE TEARDOWN REVEALED BROKEN PISTON PIN. SUPERIOR AIR PART.					1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
1996112100189	19961121	00189	EU  	1996	11	21	CA960502051      	1	19960422	G	3297	3425144	WIRE            			BAG   	BAE146	BAE146200A  	1500266	EU  										LT MLG DWNLK	DEFECTIVE       	W		A		A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN)GEAR SELECTED UP,BUT LH MLG CONTINUED TO INDICATE DOWN & LOCKED.GEAR CYCYLED BUT STILL NO GOOD.INSPECTION FOUND WIR	E #34-25-144 WAS CAUSING A LOW RESISTANCE AT PIN 18 OF LEFT GEAR DOWNLOCK CARD,CAUSIN G A CONSTANT DOWNLOCK INDICATION.F	URTHER INVESTIGATION FOUND RELAY 3425-K10 OF THE WINDSHEAR SYSTEM DID NOT HAVE POWER APPLIED TO PIN #7.ALSO WIRE IN POSI	TION WA6Y IN CB PANEL 131-12-00 HAD BEEN STOWED AS PART OF SB 34-143-50016E.THIS WAS TO ENABLE THE STEEP APPROACH ADAPTO	R INSTALLED AS PER SB TO WORK.IT WAS THEN FOUND THAT WIRE 3425-143 HAD BEEN SPLICED TO WIRE WH100.THIS WIRE WAS THEN REM	OVED BY SB 34-143-50016E.WIRE 3425-143 WAS THEN REMOVED FROM SPLICE AND TERMINATED INTO PIN WA6Y IN CB PANEL.	2	H	7	4 	4F			RT	A49EU   					 
1996121900777	19961219	00777	SO  	1996	12	19	CA960502054      	1	19960422	G	7110	65202800	COWLING LATCH   			PIPER 	PA32  	PA32260     	7103206	SO  										RT FWD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON PREPARATION FOR PAINTING, THE FOUR COWLING LATCHES REMOVED. FORWARD R.H. LATCH CRACKED ACROSS THE ATTACH HOLES.						1	L	7	1 	3O				A3SO    					 
1997030600665	19970306	00665	SW  	1997	3	6	CA960502057      	1	19960328	G	5610	36004311SS	WINDSHIELD      			GULSTM	690TP 	695A        	7630519	SW  						ROTOL	R306	R306382F7   	GL  	LEFT SIDE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									66070820823		(CAN) LEFT HAND WINDSHIELD FOUND CRACKED.						1	H	7	2 	4T				2A4     		6	C	P8EU	 
1997030600666	19970306	00666	CE  	1997	3	6	CA960502061      	1	19960418	G	2730		CONTROL         			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ELEVATOR	OBSTRUCTED      	W				K				NONE                    				F	W		FLT CONT AFFECTED         	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA								290847R	950199		(CAN) ELEVATOR CONTROL OBSTRUCTED BY INSTALLATION OF GPS ANNUNCIATOR UNIT. ELEVATOR CONTROL STRIKING BACK OF INSTALLED U	NIT NOT PERMITTING FULL ELEVATOR UP TRAVEL.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1996112100196	19961121	00196		1996	11	21	CA960507003      	4	19960208	G	3422	6225812001	FLUX VALVE      	COLLINS     	6225812001  	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					COMPASS SYS	OIL SOAKED      	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						7111		PCE25675			(CAN)AIRCRAFT COMPASS SYSTEM REPORTED UNRELIABLE. EXAMINATION OF COMPASS COMPONENTS AND WIRING REVEALED THAT THE FLUX VA	LVE WAS SATURATED WITH INSTRUMENT OIL. COLLINS CONFIRMED THAT THE LOSS OF OIL COULD R ESULT IN FAILURE OF THE COMPONENT.	 FLUX VALVE REPLACED.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
1996121000001	19961210	00001	NE  	1996	12	10	CA960507010      	2	19960409	G	7261	LA153	PUMP            	LYC         	218324001   	CNDAIR	CL600 	CL600*      		EA  	LYC   	ALF502	ALF502L2    	41580	NE  					PIN HOLE IN CASE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						LA153		LF030363S			(CAN)OIL FOUND IN COWLING AND ON GROUND . OIL PUMP HAD A PINHOLE IN THE CASING, VERIFIED BY EDDY CURRENT INSPECTION						2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
1996112700002	19961127	00002	NM  	1996	11	27	CA960507013      	1	19960423	G	2435		WIRE            	LUCAS       	23088002A   	DHAV  	DHC8  	DHC8*       	       	NM  										LT - RT GEN	CHAFED          	W				L				ABORTED APPROACH        				H	I	J	ELECT. POWER LOSS-50 PC   	FLT. ATTITUDE INST.       	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN)ON APPROACH, AND DURING GEAR SELECTION, BOTH #1 AND #2 DC GENERATOR ANNUNCIATORS FLASHED FOLLOWED BY AUXILIARY INVE	RTER, RUDDER FULL PRESSURE, GPWS #1 STALL WARN WITH HORN, AND THE MASTER WARNING AND  CAUTION LIGHTS FLICKERING. OFF FLA	GS ALSO CYCLING ON PILOTS INSTRUMENTS. INSPECTION FOUND GENERATOR FIELD WIRES ON BOTH LEFT AND RIGHT SIDES CHAFING ON EN	GINE STRUTS.			2	H	7	2 	4T			RT	A13NM   					 
1996121900788	19961219	00788	GL  	1996	12	19	CA960508004      	2	19960517	G	7261		LINES           			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  					NR 3 ENG	BLOCKED         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) DURING CLIMBOUT, THERE WAS AN OIL LOSS INDICTION FOR NR 4 ENGINE.  IN-FLIGHT SHUTDOWN WAS CARRIED OUT AND A 3 ENGI	NE LANDING CONDUCTED WITHOUT INCIDENT.  REAR COMPRESSOR, FRONT TURBINE BEARING SCAVENGE LINES WERE FOUND BLOCKED WITH CA	RBON.  LINES WERE BLOWN OUT WITH COMPRESSED AIR, FILTERS CHANGED AND AIRCRAFT RETURNED TO SERVICE.				2	H	7	4 	4T	4	T		A1SO    	E282				 
1996112700010	19961127	00010	EA  	1996	11	27	CA960509201      	2	19960425	G	7320	76772	HOSE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					#3 & #1 CYLINDER	DETERIORATED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			489  					L673261A			(CAN)PILOT REPORTED ROUGH RUNNING ENGINE ACCOMPANIED BY BLACK EXHAUST. PIECES OF INJECTOR AIR BLEED HOSE FOUND INSIDE TH	E NOZZLE ASSEMBLES.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996121900789	19961219	00789	CE  	1996	12	19	CA960509202      	1	19960308	G	5712		RIBS            			BEECH 	95    	95          	1153402	CE  	LYC   	O360  	O360A1A     	41514	EA  					WS 94.864	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2413536A			(CAN) RIGHT WING RIBS AT W.S. 94.864, 108.281 AND 122.500 FOUND BENT AND BUCKLED UNDER THE UPPER WING SKIN. POSSIBLY CAU	SED BY OVERPRESSURE OF FUEL IN AUXILIARY TANK (THERMAL EXPANSION ).					1	L	7	2 	3O	3	O		3A16    	E286				 
1996112700011	19961127	00011	EU  	1996	11	27	CA960510101      	1	19960430	G	2400	7308228	UPLOCK          			AIRBUS	310   	A310304     		EU  										RAM AIR TURB	LOCK FAILED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14947	14947							(CAN)DURING WALK AROUND/DAILY CHECK ON AIRCRAFT, RAM AIR TURBINE (R.A.T.) WAS FOUND DEPLOYED. BOTH DEPLOY HANDLES IN THE	 COCKPIT WERE FOUND WITNESSED WIRED IN THE STOWED POSITION. MAINTENANCE CHECK FOUND TH E UPLOCK MECHANISM INOPERATIVE. U	PLOCK REPLACED AND SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4F			RT	A35EU   					 
1996112700012	19961127	00012	EU  	1996	11	27	CA960510102      	1	19960421	G	2722	81681	ACTUATOR        			AIRBUS	310   	A310304     		EU  										RUDDER	JAMMED          	W		A		A				UNSCHED LANDING         				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		CL	CLIMB          	1			CA			9937 	9937 							(CAN)ON CLIMB OUT, RUDDER TRAVEL #1 AND #2 FAILED QUICKLY IN SEQUENCE, UNABLE TO RESET. MAINTENANCE ACTION INVOLVED CHAN	GING RUDDER VARIABLE STOP ACTUATOR.					2	L	7	2 	4F			RT	A35EU   					 
1996112700014	19961127	00014	NE  	1996	11	27	CA960513001      	2	19960408	G	7250	120111	TURBINE DISC    	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					FIRTREE	FRACTURED       	W		A		A				UNSCHED LANDING         				X	M		ENGINE FLAMEOUT           	OVER TEMP                 		CL	CLIMB          	1			CA			3683 			120111		120111			(CAN)DURING CLIMB, LOUD BANG FOLLOWED BY HIGH ITT ABOVE 950 DEGREES AND ENGINE FLAME OUT  MOLTEN DEBRIS IN THE EXHAUST W	ITH ALL THREE #6/7 OIL TUBES FRACTURED  ENGINE TEARDOWN HAS REVEALED FRACTURE OF TWO  LP TURBINE DISC FIRTREE WITH RELEA	SE OF THREE LPT BLADES. THE DISC/BLADE ASSEMBLY TO BE RETURNED TO P&WC FOR INVESTIGATION.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996112700015	19961127	00015	NE  	1996	11	27	CA960513002      	2	19960403	G	7250		TURBINE DISC    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					FIRTREE	FRACTURED       	W		A		A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			9988 	5395 				120050			(CAN)CLIMBING THROUGH 2,800 FEET, A LOUD SOUND WAS HEARD FROM PORT ENGINE. THE ENGINE WAS SECURED AND RETURNED TO BASE. 	DISASSEMBLY AT P&WC REVEALED ON LPT DISC FIRTREE HAD FRACTURED BELOW THE FIRST SERRAT ION AND RELEASED TWO BLADES.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996112700016	19961127	00016	NE  	1996	11	27	CA960513003      	2	19960319	G	7310		FUEL LINE MAIN  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					FLOW DIVIDER	LOOSE           	W				A				UNSCHED LANDING         				Y	K		ENGINE STOPPAGE           	FLUID LOSS                		TO	TAKEOFF        	1			CA			11162	6155 				120312			(CAN)ON TAKEOFF, THE ENGINE SPOOLED DOWN AND THE AIRCRAFT RETURNED TO THE GATE. POST FLIGHT INSPECTION FOUND FUEL SPILL 	ON THE COWLINGS. THE NUT FROM THE MAIN FUEL LINE TO THE FLOW DIVIDER HAD LOOSENED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996112700017	19961127	00017	NE  	1996	11	27	CA960513004      	2	19960324	G	7321		FUEL CONTRL UNIT			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					ENG	FAILED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10118	4481 				97351			(CAN)OVER THE PAST SEVERAL DAYS, THE ENGINE HAD EXPERIENCED REPEATED SURGES. AFTER A LENGTHY TROUBLESHOOTING, THE PROBLE	M WAS RESOLVED BY CHANGING THE FCU. THIS PARTICULAR UNIT HAD BEEN INSTALLED ONLY THRE E DAYS PRIOR TO THE ONSET OF THE S	URGING.				2	H	7	2 	4T	4	T		A41EU   	E4EA				 
1996112700018	19961127	00018	EA  	1996	11	27	CA960513005      	2	19960403	G	7250		BLADE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COMP TURBINE	FRACTURED       	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			4629 	1742 				81501			(CAN)ENGINE SHUTDOWN FOLLOWING AN INCREASE IN ITT. AS THE POWER LEVER WAS BEING RETARDED, DRBRIS WAS SEEN TO BE COMING F	ROM THE EXHAUST. INITIAL REPORT INDICATE THIS TO BE A COMPRESSOR TURBINE BLADE FRACTU RE.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1996121000002	19961210	00002		1996	12	10	CA960513006      	1	19960321	G	7712		TRANSDUCER      								PWA   	PT6   	PT6A6       	52043	EA  					ENG TORQUE	FAILED          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			1681 					103172			(CAN)ON TAKEOFF, TORQUE INDICATION DECAYED THROUGH 60 PSI FROM 68 PSI. POWER REDUCTION WAS ALSO AUDIBLE. THE ELECTRONIC 	LIMITER UNIT WARNING LIGHT ILLUMINATED AND THE CREW ISOLATED THE ELECTRONIC LIMITER S YSTEM. POST EVENT DOWNLOAD OF THE 	ELU REVEALED A FAULT CODE RELATING TO TORQUE PRESSURE. TORQUE TRANSDUCER REPLACED.									3	T			E4EA				 
1996121000003	19961210	00003		1996	12	10	CA960513007      	1	19960320	G	7714		TRANSDUCER      								PWA   	PT6   	PT6A6       	52043	EA  					ENG TORQUE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			2045 					130140			(CAN)ON APPROACH, THERE WAS A COCKPIT WARNING AND INDICATION OF LOSS OF TORQUE, APPARENTLY WITHOUT A DROP IN ENGINE POWE	R. TORQUE TRANSDUCER DEFECTIVE.										3	T			E4EA				 
1998041700397	19980417	00397	CE  	1998	4	17	CA960513015      	1	19960509	G	2820	560010939	FUEL LINE       			CESSNA	414   	414A        	2075907	CE  										SPAR WEB	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3336 								(CAN) FUEL LINE CHAFED ON EDGE OF THE HOLE WHERE IT PASSES THROUGH THE MAIN WING SPAR LT SIDE.  LINE INSPECTED AND FOUND	 WITHIN CHAFE LIMITS OF CESSNA SB MEB 87-7.  LINE REPOSITIONED TO PROVIDE CLEARANCE.  MANUFACTURER INSTALLED SPIRAL CHAF	E STRIP TO PROVIDE PROTECTION.  EXAMINATION OF RT SIDE DID NOT INDICATE CHAFING, HOWEVER, LINE WAS VERY CLOSE IN PROXIMI	TY TO EDGE OF HOLE (.015 INCH).  MANY FUEL LINES PASS THROUGH THE WING SPAR IN THIS AREA LEFT AND RIGHT AND ALL HAVE THE	 POTENTIAL TO CHAFE.		1	L	7	2 	3O				A7CE    					 
1998041700399	19980417	00399	EU  	1998	4	17	CA960514001      	1	19960506	G	7830	0330132	ROD ASSEMBLY    			AMD   	FALC20	FALCON200   	2730150	EU  	GARRTT	ATF3  	ATF36A4     	29002	WP  					RH THRUST REVRSR	DISCONNECTED    	W				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			CA								P20110			(CAN) PILOTS REPORTED RT THRUST REVERSER TRANSIT LIGHT SLOW TO EXTINGUISH DURING STOW CYCLE.  HAD TO CYCLE A FEW TIMES B	EFORE LIGHT WOULD EXTINGUISH.  INSPECTION PANELS REMOVED AND FOUND INBOARD LOWER END OF SCREWJACK TRANSMISSION ROD ASSY 	WAS NOT IN SAFETY AND BECAME DISCONNECTED.  SECURING BOLT WAS INSTALLED IN YOKE AND TAB WASHER BENT OVER TO SECURE BOLT.	  THRUST REVERSER CHECK COMPLETED AND AIRCRAFT RETURNED TO SERVICE.  THE AIRCRAFT HAD COMPLETED 222.5 HOURS SINCE LAST W	ORK PERFORMED IN THIS AREA.		2	L	7	2 	4F	4	F	RT	A7EU    	E7WE				 
1996121900793	19961219	00793	CE  	1996	12	19	CA960515003      	1	19960111	G	3411	58031	STATIC SENSOR   	NARCO       	AR850       	CESSNA	185   	A185F       	2072821	CE  						MCAULY	2A34C	D2A34C58    	GL  	HOUSING	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						58031			788769		(CAN) PIEZO STATIC SENSOR HOUSING ASSEMBLY LEAKING IN EXCESS OF LIMITS						1	H	7	1 	3O				3A24    		5	C	P3EA	 
1996121900794	19961219	00794	CE  	1996	12	19	CA960515004      	1	19960507	G	3411	20186	STATIC SENSOR   	NARCO       	AR850       	CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	HOUSING ASSEMBLY	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						20186		1090767SR	950428		(CAN) PIEZO STATIC SENSOR HOUSING LEAKING IN EXCESS OF LIMITS						1	H	7	1 	3O	3	O		3A21    	3E1	5	C	P3EA	 
1996121900795	19961219	00795	SO  	1996	12	19	CA960515005      	1	19960326	G	3411	12644	STATIC SENSOR   	NARCO       	AR850       	PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					HOUSING ASSEMBLY	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						12644		PCE92402			(CAN) PIEZO STATIC SENSOR HOUSING LEAKING IN EXCESS OF LIMITS						1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
1996121900799	19961219	00799	CE  	1996	12	19	CA960517103      	1	19960501	G	5312	823400109	BULKHEAD        	CESSNA      		CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT AFT INB FLNGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2999 					519328			(CAN) BULKHEAD ASSEMBLY BUCKLED AND CRACKED FROM LIGHTENING HOLE THROUGH TO INBOARD FLANGE.						1	L	7	2 	3O	3	O		3A25    	E8CE				 
1996112700045	19961127	00045	NE  	1996	11	27	CA960521002      	2	19960511	G	7313		FUEL NOZZLES    								PWA   	PWA120	PW125B      		NE  					NR 1 ENG	LEAKING SEAL    	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			8123 					125093			(CAN)PRIOR TO DEPARTURE, FUEL LEAKAGE WAS DETECTED FROM FUEL NOZZLES ON #1 ENGINE. TWO FUEL NOZZLES AND THE FLOW DIVIDER	 REPLACED. AFTER NEXT FLIGHT, FUEL WAS AGAIN LEAKING. ONE MORE FUEL NOZZLE REPLACED.										4	T			E20NE				 
1996112700046	19961127	00046	NE  	1996	11	27	CA960521003      	2	19960515	G	7261		TRANSFER TUBE   			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      		NE  					#6 & #7 BEARINGS	FRACTURED       	W		A		A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			K			FLUID LOSS                			CR	CRUISE         	1			CA			17989	13194				120399			(CAN)IN CRUISE AT 9K, #1 ENGINE LOW OIL PRESSURE LIGHT ILLUMINATED. ENGINE SHUT DOWN. INSPECTION REVEALED THE OIL TRANSF	ER TUBE FEEDING THE #6 & #7 BEARINGS WAS FRACTURED. A TEMPORARY OIL LINE WAS FITTED A ND A DRY MOTORING RUN WAS ATTEMPTE	D PRODUCING LOUD NOISE FROM THE ENGINE. FURTHER INSPECTION SHOWED LARGE QUANTITY OF METAL ON THE CHIP DETECTOR.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996112700047	19961127	00047	EA  	1996	11	27	CA960521004      	2	19960515	G	7210	86256	RED GEARBOX     	PWA         		DHAV  	DHC7  	DHC7*       		EA  	PWA   	PT6   	PT6A50      	52043	EA  					NR 1 ENG	FAILED          	W		A		D				RETURN TO BLOCK         				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			CA			28674	3513 		86256		PS86256			(CAN)WHILE TAXIING IN PREPARATION FOR TAKEOFF, #1 ENGINE OIL PRESSURE DECAYED AND THE PROPELLER WENT INTO AN UNCOMMANDED	 FEATHER POSITION ENGINE SECURED AND RETURNED TO GATE.  LARGE AMOUNT OF METAL FOUND ON THE REDUCTION GEAR BOX CHIP DETEC	TOR. ENGINE INSTALLED 3 DAYS PREVIOUSLY.				2	H	7	4 	4T	4	T	RT	A20EA   	E4EA				 
1996112700048	19961127	00048	EA  	1996	11	27	CA960521005      	2	19960510	G	7230		BLADES          			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  					COMPRESSOR TURB	FRACTURED       	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			9601 	2729 				22325			(CAN)IN CRUISE, #2 ENGINE PARAMETERS DROPPING. ENGINE SECURED AND RETURN TO POINT OF DEPARTURE. INVESTIGATION REVEALED T	HE COMPRESSOR TURBINE BLADES FRACTURED NEAR THE ROOT PLATFORM.					1	L	7	2 	3T	3	T		3A20    	E4EA				 
1996112700049	19961127	00049	NE  	1996	11	27	CA960521006      	2	19960510	G	7230		COMPRESSOR      								PWA   	PT6   	PT6A60A     	52043	NE  					NR 1 ENG	DAMAGED         	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		DE	DESCENT        	1			CA			1805 					95083			(CAN)DURING DESCENT, LARGE TORQUE FLUCTUATIONS ON #1 ENGINE ACCOMPANIED BY FLAMES FROM THE EXHAUST AND SMOKE IN THE CABI	N. ENGINE SECURED AND LANDED OK. LARGE AMOUNT OF OIL IN THE EXHAUST AREA AND SIGNIFIC ANT DAMAGE IN THE COMPRESSOR AREA.										4	T			E4EA				 
1996112700050	19961127	00050	EA  	1996	11	27	CA960521007      	2	19960510	G	7250		BLADES          	PWA         		AIRTRC	AT500 	AT502A      	0390306	SW  	PWA   	PT6   	PT6A45R     	52043	EA  					TURBINE	FRACTURED       	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			22581	11122				84131			(CAN)SHORTLY AFTER TAKEOFF, A LOUD BANG WAS HEARD ACCOMPANIED BY A LOSS OF POWER. AIRCRAFT LANDED IN A PLOWED FIELD, NO 	DAMAGE. INSPECTION REVEALED PERFORATIONS OF THE EXHAUST STUBS AND DUCT, SEVERAL POWERTURBINE BLADES FRACTURED AT MID SPA	N.				1	L	7	1 	3T	4	T	NC	A17SW   	E4EA				 
1996112700051	19961127	00051	EA  	1996	11	27	CA960521008      	2	19960509	G	7250		GAS GENERATOR   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					NR 2 ENG	SEIZED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			13571	6197 				32481			(CAN)IN CRUISE, #2 ENGINE STOPPED SUDDENLY WITH NO WARNING OF UNUSUAL ENGINE PARAMETERS. RETURNED TO ALBUQUERQUE WITHOUT	 INCIDENT. INSPECTION REVEALED THE GAS GENERATOR SECTION SEIZED AND METAL CONTAMINATI ON OF THE OIL FILTER. THE POWER TU	RBINE ROTATES FREELY.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1996112700052	19961127	00052	CE  	1996	11	27	CA960521009      	1	19960508	G	7810		EXHAUST DUCT    			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					NR 1 ENG	CRACKED         	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			13550	6296 				32512			(CAN)DURING CRUISE, A LOUD BANG WAS HEARD AND THE #1 ENGINE AUTOFEATHERED. ENGINE SECURED AND LANDED OK. A 6 INCH CRACK 	FOUND IN THE BIFURCATED EXHAUST DUCT AT THE 9 O'CLOCK POSITION.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1996112700053	19961127	00053	NE  	1996	11	27	CA960521010      	2	19960509	G	7250		BLADE           	PWA         							PWA   	PT6   	PT6A25      	52043	NE  					POWER TURBINE	FRACTURED       	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			Y			ENGINE STOPPAGE           			AB	AEROBATIC      	1			CA			5199 					48076			(CAN)FOLLOWING A STALL EXERCISE DURING FLIGHT TRAINING, ON POWER APPLICATION, THERE WAS AN EXPLOSION FROM THE ENGINE. EN	GINE WAS SECURED AND A LANDING MADE. AFTER ENGINE SPLIT AT THE "C" FLANGE, A FRACTURE D POWER TURBINE BLADE WAS EVIDENT.										3	T			E4EA				 
1996112700073	19961127	00073		1996	11	27	CA960524013      	4	19960516	G	3413	RC201LB	INDICATOR       			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					RATE OF CLIMB	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA								P653620B			(CAN)DURING CRUISE THE LIGHTING CIRCUIT BREAKER FOR THE THIRD CREWMAN'S PANEL TRIPPED, THE CIRCUIT BREAKER WAS RESET AND	 POPPED AGAIN. SYSTEM NOT RESET. CABIN RATE OF CLIMB INDICATOR HAD SHORTED, REPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1996112700074	19961127	00074		1996	11	27	CA960524014      	4	19960516	G	3416	40416410020	DIAPHRAGM       		1122343     	DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					ALTIMETER	DEFECTIVE       	W				K				NONE                    				I			FLT. ATTITUDE INST.       			TX	TAXI/GRND HDL  	1			CA						EGH2390		PCE42076			(CAN) DURING TAXI AND GROUND OPERATION THE ALTIMETER WOULD SHOW A DISCREPANCY TO AIRPORT ALTITUDE. INSTRUMENT REPLACED A	ND SHOP CHECK FOUND FAULT WITH THE DIAPHRAGM.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1996112700076	19961127	00076	NM  	1996	11	27	CA960524017      	1	19960516	G	2435	03600923	BEARING         	LUCAS       	23088002A   	DHAV  	DHC8  	DHC8*       		NM  										START/GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				330  		810					(CAN) STARTER GENERATOR HAD A PREMATURE BEARING FAILURE.						2	H	7	2 	4T			RT	A13NM   					 
1996112700077	19961127	00077		1996	11	27	CA960524018      	1	19960430	G	3241	AC60742	FLYWHEEL        	DUNLOP      	AC60742     															BRAKE MAXARET	IMPROPER LUBE   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						491					(CAN) WRONG LUBRICATION IN FLYWHEEL SIDE.																			 
1996112700082	19961127	00082	EA  	1996	11	27	CA960524023      	1	19960507	G	7800	85411358003	HEAT SHIELD     	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										RIGHT HAND EXH	SEPARATED       	W		A		K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) RIGHT HAND HORIZONTAL STABILIZER FOUND DAMAGED ON ARRIVAL. FURTHER INVESTIGATION REVEALED THAT THE RIGHT HAND EXHA	UST FLOATING HEAT SHIELD HAD DEPARTED IN FLIGHT AND CONTACTED THE STABILIZER. CREW REPORTED HEARING OR FEELING NOTHING. 	RH ENGINE EXHAUST HEAT SHIELD WAS PRE MOD 8/1664. LEFT HAND WAS POST MOD.				2	H	7	2 	4T			RT	A13NM   					 
1996112700086	19961127	00086	EA  	1996	11	27	CA960527005      	2	19960517	G	7414	10391586	DISTRIBUTOR BLOC	BENDIX      	103492901   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					ENG MAG	WORN BUSHING    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13   			1015567		L313361A			(CAN)DISTRIBUTOR BUSHING WORN AT A VERY RAPID RATE UNTIL DISTRIBUTOR GEAR ARM BEGAN INTERFERING AGAINST DISTRIBUTOR BLOC	K CONTACTS.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996112700087	19961127	00087	SW  	1996	11	27	CA960527006      	1	19960415	G	5711		SPAR            			BBAVIA	7     	7BCM        	2110106	SW  	CONT  	C85   	C8512F      	17008	SO  					REAR SPAR ROOT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								102725R			(CAN)ON INSPECTION THE REAR SPAR WAS FOUND FAILED (CRACKED) AT THE RIGHT HAND REAR SPAR ROOT END BISCUIT. IT WAS NOTED T	O HAVE FAILED ACROSS THE TOP AT THE SECTION OF THE SPAR THAT IS MILLED OUT TO ACCOMMODATE THE BISCUIT DOUBLERS. SUBMITTE	R STATES THAT THE AIRCRAFT WAS BUILT IN 1947 AND THAT THE SPAR APPEARS TO BE ORIGINAL.				1	H	7	1 	3O	3	O		A759    	E233				 
1996112700088	19961127	00088	CE  	1996	11	27	CA960527007      	1	19960501	G	5711		SPAR            	BLANCA      		BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O320  	AEIO320E1B  	41508	EA  					O/B OF ROOT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1648 					L547555A			(CAN)THE REAR SPAR EXHIBITS SIGNS OF WOOD COMPRESSION FAILURE AT THE 46 INCH LOCATION OUTBOARD FROM THE ROOT.						1	H	7	1 	3O	3	O		A21CE   	1E12				 
1996121900807	19961219	00807	NM  	1996	12	19	CA960527102      	1	19960517	G	5751		SKIN            	STINSON     		UNIVAR	108   	1083        	9230408	NM  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	AIL BAL WGT ATT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2349 					6665366	688039		(CAN) CRACK 3/8 INCH LONG RADIATING FROM 3 HOLES FOR THE ATTACHMENT OF THE STEEL BALANCE WEIGHT ON THE OUTBOARD LEADING 	EDGE OF RIGHT HAND AILERON.					1	H	7	1 	3O	3	O		A767    	E273	5	C	P3EA	 
1996121900808	19961219	00808	NM  	1996	12	19	CA960527103      	1	19960518	G	5751		SKIN            	STINSON     		UNIVAR	108   	1083        	9230408	NM  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	AIL BAL WGHT ATT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2510 					514656R	63447		(CAN) CRACKS 1/4 INCH LONG RADIATING FROM 3 HOLES FOR THE ATTACHMENT OF THE STEEL BALANCE WEIGHT ON THE OUTBOARD LEADING	 EDGE OF RIGHT HAND AILERON.					1	H	7	1 	3O	3	O		A767    	E273	5	C	P880	 
1996121900809	19961219	00809	SO  	1996	12	19	CA960528103      	1	19960506	G	2740	69623004	TUBE            	PIPER       		PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320B2B     	41508	EA  					STAB WEIGHT END	DEFECTIVE       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								L476739			(CAN) PREPARING THE TUBE FOR INSTALLATION, THERE WAS A BLOB OF PAINT IN THE AREA OF MOUNTING OF THE WEIGHT. ON REMOVING 	THE BLOB OF PAINT, A FOLD IN THE METAL AND A 3 INCH LONGITUDINAL CRACK IN THE TUBE WAS REVEALED. MATERIAL DEFECT. POOR Q	UALITY CONTROL.				1	L	7	1 	3O	3	O		2A13    	E274				 
1996112700094	19961127	00094	NM  	1996	11	27	CA960529002      	1	19960522	G	2421	31708001A	AC GENERATOR    	LUCAS       		DHAV  	DHC8  	DHC8*       		NM  										ROTOR	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LARGE PIECE OF METAL FOUND ON CHIP DETECTOR. SMALL SECTION OF ROTOR IRON LAMINATION STACK MISSING. ALSO FOUND A PI	ECE OF HELI-COIL LOOSE INSIDE OF GENERATOR.					2	H	7	2 	4T			RT	A13NM   					 
1996112700095	19961127	00095	SO  	1996	11	27	CA960529003      	2	19960515	G	7322	C324391	ICO VALVE       	MARVELSCHEB 	103878      	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	MIX CONTROL	INCORRECT ASSY  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						C324391		563812	765933		(CAN)MIXTURE CONTROL AND IDLE CUT-OFF INOPERATIVE. UNIT ASSEMBLED INCORRECTLY WITH MIXTURE CONTROL AND I C O  VALVE OUT 	OF THE VALVE BORE					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
1996120500360	19961205	00360	EA  	1996	12	5	CA960529007      	1	19960524	G	2422	MS250242	RELAY           			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					#1 INVERTER	INTERMITTENT    	W				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA								PCE42076			(CAN) #1 INVERTER INDICATED A FAILURE UNTIL THE SELECTOR SWITCH WAS CYCLED AND THE PROBLEM CLEARED. MAINTENANCE CHANGED 	THE INVERTER SELECTOR RELAY.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1996120500361	19961205	00361	EA  	1996	12	5	CA960529008      	1	19960528	G	7500	DAS10011	TUBE            	DEVORE      		DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					BLEED AIR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE42076			(CAN) DURING INSPECTION REQUIRED BY MANUFACTURERS INSPECTION PROGRAM THE BLEED AIR DUCTS IN THE WING WERE FOUND TO BE CR	ACKED BETWEEN THE INNER AND OUTER TUBE ON BOTH THE LEFT AND RIGHT SIDE. SB 6/355, USED TO REPAIR AND MOD 6/1614 INSTALLE	D IMPROVED TUBES.				1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1996120500362	19961205	00362	NM  	1996	12	5	CA960529009      	1	19960524	G	3150	D203W3	SWITCH          	GRIMES      	75003821    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					ANNUN PANEL	SHORTED         	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA						428		P653620B			(CAN)DURING FLIGHT THE FLIGHT ENGINEERS DOOR ANNUNCIATOR PANEL TEST SWITCH FAILED AND RESULTED IN ALL LIGHTS ILLUMINATIN	G. THE PANEL WAS REPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1996121900812	19961219	00812	CE  	1996	12	19	CA960529010      	1	19960522	G	2721	17670667	SCREW ACTUATOR  			CESSNA	177   	177B        	2073708	CE  						MCAULY	2D34C	B2D34C211   	GL  	RUDDER TRIM	BROKEN          	W				K				NONE                    				O	F		OTHER                     	FLT CONT AFFECTED         		LD	LANDING        	1			CA			5487 						797366		(CAN) ON APPROACH IN A FORWARD SLIP, RUDDER TRIM INOPERATIVE. RUDDER TRIM SCREW ACTUATOR SHAFT BROKEN MID SHAFT AT THE S	HOULDER OF TRAVERSE THREAD.					1	H	7	1 	3O				A13CE   		5	C	P7EA	 
1996120500366	19961205	00366	CE  	1996	12	5	CA960530002      	1	19960401	G	2434	PU1605	FAN             	PRESTOLITE  	ALE8105A    	BEECH 	23    	A2319       	1151212	CE  	LYC   	O320  	O320E2C     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ALTERNATOR	BROKEN          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			1878 					L1759327A	K3029		(CAN)PILOT HEARD LOUD BANG FOLLOWED BY AMMETER SHOWING DISCHARGE. ALTERNATOR SEPARATED FROM ENGINE. HOUSING MOUNTING LUG	S BROKEN OFF BY VIBRATION DUE TO IMBALANCE FOLLOWING A PORTION OF THE FAN BREAKING OF F.					1	L	7	1 	3O	3	O		A1CE    	E274	5	N	P88614	 
1996121900817	19961219	00817	SO  	1996	12	19	CA960604001      	1	19960512	G	3230	2128600	MOTOR           	BOSCH       	M072218A    	PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360A1D     	41514	EA  					GEAR EXTEND	BURNT           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			CA			2824 			36461		L363136			(CAN) LANDING GEAR REFUSED TO EXTEND AND LOCK. EMERGENCY EXTEND SUCCESSFUL. ELECTRICAL MOTOR BURNT OUT.						1	L	7	1 	3O	3	O		1A15    	E286				 
1996120500367	19961205	00367	EA  	1996	12	5	CA960604002      	2	19960517	G	7414	9050365	BEARING CAP ASSY	SLICK       	4250        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					MAG ROTOR SHAFT	FAILED          	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA						9050365		L2739436A			(CAN)ENGINE ROUGH ON RUN UP.  MAGNETO SEPARATED FROM ENGINE AND HANGING FROM HARNESS. MAGNETO SEIZED AND MOUNTING FLANGE	 FRACTURED. ROTOR SHAFT SEIZED DUE TO BEARING FAILURE ENSUING FROM OUTER RACE OF BEARING SPINNING WITHIN THE BEARING CAP	 ASSEMBLY. BEARING CAP ASSEMBLY LACKED THE "J" MARKING SEPCIFIED IN SB 2-88A ALTHOUGH THIS MAGNETO FALLS INTO THE SERIAL	 NUMBER RANGE FOR THE SB.			1	L	7	1 	3O	3	O		2A13    	E286				 
1996120500368	19961205	00368	SO  	1996	12	5	CA960604003      	2	19960524	G	8530		CYLINDER        			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	ENGINE	NOT FIRING      	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				155  				352839	793546		(CAN)IN CRUISE AT 9.5K, ENGINE RAN ROUGH AND BACKFIRED, SHUTDOWN.						1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
1996120500372	19961205	00372		1996	12	5	CA960604007      	1	19960418	G	7830		THRUST REVERSER 								GE    	CFM56 	CFM565A     	13802	NE  					NR 1 ENG	SHEARED HYD LINE	W				L				ABORTED APPROACH        				K			FLUID LOSS                			DE	DESCENT        	1			CA											(CAN)THRUST REVERSER LH LOWER LATCH RETURN LINE #1 ENGINE SHEARED AT MIDPOINT CAUSING LOSS OF HYDRAULIC FLUID GREEN SYST	EM. AIRCRAFT USED ALTERNATE GEAR EXTENSION AND LANDED SAFELY. LINE SENT TO NRC FOR AN ALYSIS.										4	F			E29NE				 
1996120500380	19961205	00380	NM  	1996	12	5	CA960605002      	1	19960524	G	3222		STRUT           			BOEING	727   	72725       	1384006	NM  										NLG	LEAKING         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WHEN GEAR WAS SELECTED UP ON CLIMB OUT THE NOSE GEAR DOOR LIGHT REMAINED ON AND THERE WAS AN UNSAFE LANDING GEAR W	ARNING, GEAR EXTENDED AND AIRCRAFT LANDED.					2	L	7	3 	4F				A3WE    					 
1996120500381	19961205	00381	CE  	1996	12	5	CA960605004      	1	19960529	G	3213	52435183	FORK BOLT       			CESSNA	414   	414         	2075908	CE  										L/H TORQUE TUBE	SHEARED         	W				L	O			ABORTED APPROACH        	OTHER                   			J			WARNING INDICATION        			LD	LANDING        	1			CA			1323 								(CAN)PILOT REPORTED L/H GEAR UNSAFE LIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. ON ROLL-OUT, THE L/H GEAR DOWN LIGHT CAME O	N. INSPECTION REVEALED THAT THE L/H FORK BOLT WAS SHEARED OFF FLUSH WITH THE TORQUE T UBE. AD #76-13-07 REQUIRES REPLACE	MENT OF THESE BOLTS EVERY 2,000 HOURS TIME IN SERVICE. THIS AIRCRAFT WAS IN COMPLIANCE WITH THIS AD, HOWEVER, THE OVERCE	NTER TENSION WAS HIGHER THAN THE EQUIPMENT COULD MEASURE. BOTH FORK BOLTS WERE REPLACED, AND OVERCENTER TENSION WAS ADJU	STED TO THE SPECIFIED 50 LBS. SUBMITTER SUGGESTS THAT RIGGING OF GEAR SHOULD BE PART OF THE PROCEDURE AT TIME OF BOLT RE	PLACEMENT.	1	L	7	2 	3O			RT	A7CE    					 
1999081200319	19990812	00319	EA  	1999	8	12	CA960605005      	1	19960528	G	5312	C2FS533	BULKHEAD        			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					BS 228	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12503					PCE40557			(CAN) AFT FULL BULKHEAD AT STA 228 FOUND CRACKED ON BOTH LEFT AND RIGHT SIDES WHERE RUDDER CONTROL RODS PASS THROUGH THE	 BULKHEAD.  CRACKS RADIATE FROM HOLES .0937 INCH TO .50 INCH TOWARDS THE VERTICAL STABILIZER ATTACHMENT.  ANOTHER .50 IN	CH CRACK WAS FOUND AT THE TOP OF THE BULKHEAD BETWEEN THE VERTICAL STABILIZER TWO ATTACH POINTS FROM THE BEND RELIEF CUT	-OUT.  SUBMITTER STATED TWO OTHER DHC-2 MKIII AIRCRAFT WERE INSPECTED AND THE SAME CRACKS WERE FOUND AT THE CONTROL ROD 	PASS THROUGH AFT FULL BULKHEADS REPLACED WITH NEW UNITS.		1	H	7	1 	3T	4	T		A806    	E4EA				 
1996120500384	19961205	00384	SO  	1996	12	5	CA960606002      	2	19960527	G	8520	639292	SPLIT PIN       	CONT        	646321      	MAULE 	M5    	M5210C      	5460134	SO  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2A34C	D2A34C67    	GL  	#5 CONROD	DETACHED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				320  				351203	752647		(CAN)ON ANNUAL INSPECTION, ONE SPLIT PIN FOUND IN THE SUCTION OIL SCREEN. OIL PAN REMOVED FOR INTERNAL INSPECTION. #5 CO	NROD BEARING CAP MISSING ONE COTTER PIN, REPLACED.					1	H	7	1 	3O	3	O		3A23    	E1CE	5	C	P3EA	 
1996120500386	19961205	00386	SO  	1996	12	5	CA960606004      	2	19960517	G	8530		VALVE GUIDE     	CONT        		CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	EXHAUST VALVE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				513  				693105LR	731568		(CAN)ON 100 HOUR INSPECTION, LOW COMPRESSION IN CYLINDER. EXHAUST VALVE GUIDE LOOSE IN CYLINDER HEAD.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1996121900827	19961219	00827	SO  	1996	12	19	CA960610001      	1	19960516	G	5412	5048	FIREWALL        	MAULE       	M4210C      	MAULE 	M4    	M4210C      	5460112	SO  	CONT  	O360  	IO360A      	17025	SO  	MCAULY	2A34C	D2A34C67    	GL  	R/H CORNER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1070C		10557	681071		(CAN) DURING AN ENGINE CHANGE, FIREWALL WAS FOUND TO BE CORRODED EXCESSIVELY. FIREWALL WAS REPLACED AS PER MAINTENANCE M	ANUAL. SUBMITTER NOTES THAT THE MATERIAL OF THE FIREWALL IS GALVANIZED STEEL.					1	H	7	1 	3O	3	O		3A23    	E1CE	5	C	P3EA	 
1996120500390	19961205	00390	SW  	1996	12	5	CA960610004      	1	19960520	G	7120	162301	RUBBER BUSHING  	LORD        		BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					ENG MOUNT	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			474  					L1967536A			(CAN)ON ANNUAL INSPECTION, THE LOWER RIGHT ENGINE MOUNT RUBBER BUSHING FOUND SEVERELY DETERIORATED. THIS MOUNT IS DIRECT	LY BELOW THE OIL FILLER TUBE AND IS SUSCEPTIBLE TO OIL SPILLAGE.					1	H	7	1 	3O	3	O		A21CE   	E286				 
1996121900829	19961219	00829	CE  	1996	12	19	CA960610009      	1	19960618	G	5511	07326116	RIB             	CESSNA      		CESSNA	185   	A185E       	2072818	CE  						MCAULY	2A34C	D2A34C58    	GL  	HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5596 						744927		(CAN) DURING A 100 HOUR INSPECTION, HORIZONTAL STABILIZER RIB P/N 0732611 WAS FOUND CRACKED. WITH THE STABILIZER REMOVED	 FOR REPAIR, EIGHT (8) NOSE RIBS WERE FOUND CRACKED OR CRUSHED. SUBMITTER STATES THAT THIS AREA IS DIFFICULT TO INSPECT 	WITH THE STABILIZER INSTALLED.				1	H	7	1 	3O				3A24    		5	C	P3EA	 
1996120500394	19961205	00394		1996	12	5	CA960610010      	4	19960531	G	2562	168	'G' SWITCH      			CESSNA	500   	560CESSNA   	2076750	CE  										ELT TRANSMITTER	FAILED TEST     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1144 								(CAN)'G' SWITCH FAILED DURING ANNUAL CERTIFICATION TEST IN ACCORDANCE WITH AIRWORTHINESS REGULATIONS. 'G' SWITCH REPLACE	D AND RE-CERTIFIED FOR RETURN TO SERVICE.					2	L	7	2 	4F			RT	A22CE   					 
1998041700401	19980417	00401	CE  	1998	4	17	CA960610011      	1	19960531	G	3242	215295	BRAKE ASSY      			CESSNA	500   	560CESSNA   	2076750	CE  										PLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1132 								(CAN) DURING ROUTINE INSPECTION, FOUND WEAR PLATE EXCESSIVELY WORN EVEN WITH 0.150 INCH REMAINING ON THE WEAR INDICATOR 	(NORMALLY BRAKE SHOULD BE REMOVED WHEN THE INDICATOR IS FLUSH WITH THE BRAKE HOUSING).  UPON DIS-ASSEMBLY OF THE BRAKE U	NIT, WEAR ON PLATE WAS 0.048 INCH WHERE ACTUAL ALLOWABLE IS 0.070 INCH.  ROTOR MINIMUM LIMIT IS 0.300 INCH, AND ACTUAL W	AS 0.268 INCH.  SAME CONDITION WAS FOUND ON OTHER SIDE OF AIRCRAFT.  PART TC:  909.			2	L	7	2 	4F			RT	A22CE   					 
1996120500397	19961205	00397	NM  	1996	12	5	CA960611001      	1	19960520	G	7120		STRUT           	LORD        	87110016011 	DHAV  	DHC8  	DHC8102     	2809003	NM  										NR 1 ENG AFT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13905								(CAN)#1 ENGINE REAR OUTBOARD ENGINE MOUNT VERTICAL STRUT FOUND BROKEN.						2	H	7	2 	4T			RT	A13NM   					 
1996120500401	19961205	00401	SO  	1996	12	5	CA960611006      	2	19960517	G	8530		ROCKER SHAFT    	CONT        	641917      	CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					NR 4 CYL	BROKEN BOSS     	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA				811  				626372AR			(CAN)ON TAKEOFF, AT FULL POWER, ABORTED DUE TO SEVERE ENGINE VIBRATION. #4 CYLINDER VALVE ROCKER SHAFT BOSSES BROKEN ACR	OSS BOTH VALVES.					1	H	7	1 	3O	3	O		3A19    	E252				 
1996121900836	19961219	00836	NE  	1996	12	19	CA960612005      	1	19960606	G	5302	6120762651	PYLON           			SKRSKY	S61   	S61N        	8142104	NE  										90 DEG FITTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 90 DEGREE GEARBOX FITTING CRACKED AT THE ATTACHMENT AREA OF THE WEB AND BOTH SIDE SKINS.						2	G	7	2 	4U				1H15    					 
1996121900837	19961219	00837		1996	12	19	CA960612013      	1	19960605	G	2830	15D024A066	BEARING         	WELDON      	70D10       															PUMP MOTOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA						03561					(CAN) BEARING REMOVED WAS NOT AS RECOMMENDED BY COMPONENT MANUFACTURER.																			 
1996121900838	19961219	00838		1996	12	19	CA960612014      	1	19960605	G	2823	102549E	BEARING         	ITT         	AV16B1667D  															FUEL SOV	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA						R124286					(CAN) BEARING REMOVED WAS NOT AS RECOMMENDED BY COMPONENT MANUFACTURER.																			 
1996121900839	19961219	00839	CE  	1996	12	19	CA960612018      	1	19960606	G	2913	OAS29401	HYDPOWER PACK   	OZONE       	OAS29401    	CESSNA	210   	210E        	2073416	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	HYD SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						296		112324R	726919		(CAN) THE HYDRAULIC RESERVOIR WAS FOUND TO BE CONTAMINATED WITH A FILM OF SLUDGE. FURTHER INVESTIGATION FOUND TEFLON TAP	E ON THE VARIOUS FITTINGS AND TEFLON CONTAMINATION THROUGHOUT THE UNIT.					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1996121200208	19961212	00208		1996	12	12	CA960612023      	4	19960527	G	6122	210628G	OVERSPEED GOV   			DHAV  	DHC2  	DHC2EVANS   	2801832	EA  										PROP	FAILED          	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				601  							(CAN)PILOT DID OVERSPEED TEST BEFORE TAKEOFF. PROP SPEED, HOWEVER NOTED TO BE LOW. SOLENOID FOR TEST HAD FAILED AND OVER	SPEED GOVERNOR NEEDED TO BE REPLACED.					1	H	7	1 	3O				A806    					 
1996121200211	19961212	00211	NE  	1996	12	12	CA960612026      	2	19960118	G	7210	310703301	BEARING         			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			10431					121018			(CAN)METAL ON THE RGB CHIP DETECTOR. #15 BEARING SPALLED SEVERELY. SMALL AMOUNT OF RESIDUAL MAGNETISM DETECTED ON PROPEL	LER SHAFT AND #18 AND #19 BEARING RACES.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
1996121200212	19961212	00212	NE  	1996	12	12	CA960612027      	2	19960118	G	7210	310120201	BEARING         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					RGB NR 14 BRG	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11758					115521			(CAN)METAL ON RGB CHIP DETECTOR. #14 BEARING OUTER RACE SPALLED, ROLLERS FLAKING AND CAGE CRACKED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996121200213	19961212	00213	NE  	1996	12	12	CA960612028      	2	19960130	G	7210	310406201	BEARING         			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					RGB NR 18 BRG	SPALLED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12880	1125 				120460			(CAN)METAL ON THE RGB CHIP DETECTOR. #18 BEARING BALLS SPALLED. ELECTRICAL PITTING FOUND ON #15 AND #19 BEARINGS ON IDLE	R DRIVE, THEREFORE THE SPALLING ON THE #18 BEARING IS LIKELY DUE TO ELECTRICAL DISCHA RGE FROM AN EXTERNAL AIRCRAFT SOUR	CE.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
1996121200216	19961212	00216	NE  	1996	12	12	CA960612031      	2	19960108	G	7230	311362301	BEARING         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       		NE  					NR 5 BRG CAGE	FRACTURED       	W		A		K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			13630	2994 				115309			(CAN)ENGINE REPORTED MAKING "GRUMBLING" NOISES.  METAL CONTAMINATION OF THE OIL FILTER AND METAL FLAKES ON THE TURBOMACH	INE CHIP DETECTOR.  #5 BEARING FAILED DUE TO FAILURE OF ONE SEPARATOR OF THE BEARING CA GE ALLOWING ONE ROLLER TO MOVE O	UT OF POSITION AND SKIDDING OF THAT ROLLER.  NO OBVIOUS REASON FOR THE CAGE FAILURE.  THIS BEARING HAD BEEN REPLACED 299	4 HOURS PREVIOUS FOLLOWING A HP STUBSHAFT BOLT FAILURE.			2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996121900842	19961219	00842	CE  	1996	12	19	CA960614007      	1	19960606	G	2620		RETAINING CLIP  	RAYTHN      	1015700215  	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FIRE EXT SWITCH	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2290 					PCE25648			(CAN) ON INSPECITON OF THE ENGINE FIRE EXTINGUISHER ELECTRICAL SYSTEM, IT WAS NOTED THAT THE FIRE EXTINGUISHER MICROSWIT	CH ON THE PANEL ACTIVATING BUTTON HAD COME OFF THE HOLDING CLIP RENDERING THE BUTTON INOPERATIVE. THE SWITCH MANUFACTURE	R - RAYTHEON - INDICATES A REPLACEMENT SWITCH IS BEING PRODUCED.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
1996121900843	19961219	00843	CE  	1996	12	19	CA960614010      	1	19960605	G	5720	052356529	WING TIP        	CESSNA      		CESSNA	150   	152         	2071835	CE  										LT WING	CRACKED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			LD	LANDING        	1			CA			3462 								(CAN) STUDENT ATTEMPTING TO LAND DRAGGED LEFT WING TIP ON RUNWAY. WING TIP CRACKED, NO OTHER DAMAGE.						1	H	7	1 	3O			NT	3A19    					 
1996121200244	19961212	00244	NE  	1996	12	12	CA960614015      	2	19960401	G	7210	310924401	BEARING         	PWA         		AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	120   	PW120       		NE  					RGB NR 15 BR	SPALLED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14134	5708 		120661		120661			(CAN)REDUCTION GEAR BOX REPORTED MAKING METAL. #15 BEARING HAD SEVERE SPALLING ON THE ROLLERS AND OUTER RACE.						2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
1996121200245	19961212	00245	NE  	1996	12	12	CA960614016      	2	19960404	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                     			IN	INSP/MAINT     	1			CA			6812 			121140		121140			(CAN)METAL ON THE REDUCTION GEAR BOX CHIP DETECTOR. #15 BEARING INNER RACE SPALLED. ELECTRICAL DISCHARGE PITTING ON #15 	ROLLERS AND #18 BEARING LIKELY FROM STRAY ELECTRICAL DISCHARGE FROM SOME AIRCRAFT COM PONENT.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
1996121200246	19961212	00246	NE  	1996	12	12	CA960614017      	2	19960409	G	7210	310119101	BEARING         	PWA         		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					RGB NR 10 BRG	SPALLED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17032			120417		120417			(CAN)REDUCTION GEAR BOX MAKING METAL. LEFT HAND #10 BEARING, ONE BALL SPALLED. REMAINING OIL IN THE GEARBOX WAS VERY DIR	TY AND FOUND TO CONTAIN HIGH LEVELS OF PHOSPHORUS AND VANADIUM. SEVERAL OTHER BEARING S HAD PITS AND DISCOLORATION SIMIL	AR TO CORROSION THAT MAY BE RELATED TO THE CONTAMINATED OIL.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996121200247	19961212	00247	NE  	1996	12	12	CA960614018      	2	19960503	G	7260	311196801	TOWERSHAFT      			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					UPPER SHOULDER	FRACTURED       	W		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			10813					120956			(CAN)IN CRUISE, LOSS OF OIL PRESSURE AND ENGINE STOPPED. THE TOWERSHAFT FRACTURED IMMEDIATELY BELOW THE UPPER BEVEL GEAR	 AND BEARING. THIS RESULTED IN LOSS OF DRIVE TO BOTH THE FUEL PUMP AND THE OIL PUMP,  THUS SHUTTING DOWN THE ENGINE. REA	SON FOR THE FAILURE COULD NOT BE ASCERTAINED.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
1996121200248	19961212	00248	NE  	1996	12	12	CA960614019      	2	19960530	G	7210	310709001	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			14724	8138 		115151		115151			(CAN)REDUCTION GEAR BOX CONTAMINATED WITH METAL. #19 BEARING INNER RACE CRACKED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996121200249	19961212	00249	NE  	1996	12	12	CA960614020      	2	19960205	G	7210	310703301	BEARING         	PWA         		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					RGB NR 15 BRG	SPALLED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9266 			121064		121064			(CAN)REDUCTION GEARBOX METAL CONTAMINATION. #15 BEARING HAD A LARGE SPALL OVER 60 DEGREES OF THE OUTER RACE. SEVERAL STE	EL COMPONENTS WERE HEAVILY MAGNETISED AND #18 AND #19 BEARINGS SHOWING SIGNS OF ELECT RICAL PITTING LEADING TO BELIEVE T	HAT LIGHTNING STRIKE IS LIKELY THE CAUSE OF THE BEARING FAILURE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1996121200250	19961212	00250	NE  	1996	12	12	CA960614021      	2	19960308	G	7210	310924401	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			7573 			121172		121172			(CAN)REDUCTION GEARBOX METAL CONTAMINATION. #15 BEARING SUFFERED A MAJOR FAILURE WITH SPALLING ON THE ROLLERS AND THE OU	TER RACE. NOTE: ENGINE LOGS INDICATE THAT M50 BEARING MATERIAL PLATELETS WERE DISCOVE RED IN THE RGB 2 MONTHS BEFORE THI	S FAILURE BUT NO FURTHER METAL WAS FOUND IN A SAMPLE TAKEN 10 DAYS LATER.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
1996121200251	19961212	00251	NE  	1996	12	12	CA960614022      	2	19960319	G	7250	MS969611	BOLTS           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       		NE  					INTERSTAGE FLANG	BROKEN          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13584					115244			(CAN)BOLT FOUND LODGED IN POWER TURBINE BLADE ON ROUTINE BORESCOPE INSPECTION. 2 BROKEN BOLTS ON THE INTERSTAGE CASE FLA	NGE. SEVERE CORROSION AT ALL BOLT POSITIONS OF THE INTERSTAGE CASE REAR FLANGE. THIS  ENGINE WAS PRE SB 21175.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996121200252	19961212	00252	NE  	1996	12	12	CA960614023      	2	19960403	G	7230	311267601	CUP WASHER      			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       		NE  					#4 BEARNING UNIT	WRONG PART      	W		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			13693					115440			(CAN)OPERATOR REPORTED THE ENGINE MAKING A GROWLING NOISE. #4 BEARING FAILED DUE TO THE INSTALLATION OF THE WRONG PART N	UMBER RETAINING NUT CUP WASHER. THE CUP WASHER INSTALLED, P/N 3112676-01 IS NOT APPLI CABLE TO THE PW118 AND IS TOO LARG	E TO LOCK PROPERLY ON THE IMPELLER ASSEMBLY.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996121200253	19961212	00253	NE  	1996	12	12	CA960614024      	2	19960605	G	7210	311192701	BEARING         	PWA         		EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       		NE  					RGB NR 8 BRG	SPALLED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13400	3480 		115307		115307			(CAN)REPORTED METAL ON THE CHIP DETECTOR. NOS.8, 9 & 15 BEARINGS SPALLED WITH #8 SHOWING THE MOST DAMAGE. THE CAGE OF #8	 BEARING WAS BROKEN IN 2 PLACES AND HAD SECTIONS MISSING, SEVERAL ROLLERS WERE SEVERELY WORN. #15 BEARING HAD ELECTRICAL	 DISCHARGE PITTING WHICH APPEARS DUE TO LIGHTNING STRIKE.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996121200261	19961212	00261	SO  	1996	12	12	CA960619031      	2	19960610	G	8520	633976	COUNTERWEIGHT PL	CONT        		MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	IO360G      	17025	SO  					CRANKSHAFT	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			875  			A574M2		309568			(CAN) THE ENGINE DEVELOPED A SLIGHT VIBRATION INFLIGHT. THE ENGINE OIL PRESSURE & VACUUM SUCTION DROPPED TO ZERO. THE ST	ANDBY VACUUM RESTORED SUCTION. THE ENGINE OPERATING TEMPERATURE INCREASED BUT STAYED IN THE GREEN. THE MANIFOLD PRESSURE	 WAS NORMAL. POST FLIGHT INSPECTION REVEALED THAT A CRANKSHAFT COUNTERWEIGHT PIN RETAINER PLATE HAD FAILED ALLOWING THE 	PIN TO FALL INTO THE CRANKCASE, THE LOOSE PIN FRACTURED AN INTAKE VALVE PUSH ROD CREATING A REDUCTION IN OIL PRESSURE. T	HE VACUUM PUMP SHAFT SHEAR BUSHING ALSO FAILED. NO OBVIOUS CAUSE FOR THE RETAINER PLATE WAS DETERMINED.		1	L	7	1 	3O	3	O		2A3     	E1CE				 
1998041700402	19980417	00402	GL  	1998	4	17	CA960619033      	2	19960522	G	7250	23031938	NOZZLE          								ALLSN 	250C  	250C20R2    		GL  					2ND STAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3121 					CAT15310			(CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM. NOZZLES SENT TO MANUFACTURER.  PART TC:  4,2	14.										3	U			E4CE				 
1998041700403	19980417	00403	GL  	1998	4	17	CA960619034      	2	19960522	G	7250	23031938	NOZZLE          								ALLSN 	250C  	250C20R2    		GL  					2ND STAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3026 								(CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM.  NOZZLES SENT TO MANUFACTURER.  PART TC:  3,	694.										3	U			E4CE				 
1998041700404	19980417	00404	GL  	1998	4	17	CA960619035      	2	19960522	G	7250	23031938	NOZZLE          								ALLSN 	250C  	250C20R2    		GL  					2ND STAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2669 								(CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM. NOZZLES SENT TO MANUFACTURER.  PART TC:  3,3	68.										3	U			E4CE				 
1998041700405	19980417	00405	GL  	1998	4	17	CA960619036      	2	19960522	G	7250	23031938	NOZZLE          								ALLSN 	250C  	250C20R2    		GL  					2ND STAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3499 								(CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM.  NOZZLES SENT TO MANUFACTURER.  PART TC:  3,	030.										3	U			E4CE				 
1998041700406	19980417	00406	GL  	1998	4	17	CA960619037      	2	19960522	G	7250	23031938	NOZZLE          								ALLSN 	250C  	250C20R2    		GL  					2ND STAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2498 								(CAN) CRACKS FOUND IN THE BEND RADIUS OF THE SECOND STAGE NOZZLE DIAPHRAGM.  NOZZLES SENT TO MANUFACTURER.  TWO INCH LON	G CRACK WITH CRAZE CRACKS OVER 50 PERCENT OF CIRCUMFERENCE.  PART TC:  3,527.										3	U			E4CE				 
1996122600537	19961226	00537	CE  	1996	12	26	CA960620002      	1	19960611	G	2436		REGULATOR       			CESSNA	172   	172M        	2072418	CE  										ALTERNATOR SYS	MALFUNCTION     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING RUN-UP FOR OIL CHANGE THE ALTERNATOR SWITCH WAS CYCLED AND THE AMMETER SHOWED A FULL CHARGE. IN THE 'ON' PO	SITION A NORMAL RATE OF CHARGE WAS NOTED. WITH THE MASTER IN THE 'OFF' POSITION THE PANEL LIGHTS BECAME VERY BRIGHT. THE	 AUTOMOTIVE VOLTAGE REGULATOR WAS REPLACED AND THE SYSTEM FUNCTIONED PROPERLY.				1	H	7	1 	3O			NT	3A12    					 
1996121200269	19961212	00269	SO  	1996	12	12	CA960620009      	2	19960531	G	7314	3512	GASKET          	CONT        	6381541     	CESSNA	206   	P206B       	2073309	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	FUEL PUMP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3167 			3512		1107924A	711498		(CAN) SLIGHT LEAK AT FUEL PUMP BODY  GASKET REPLACED						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1996122600551	19961226	00551	CE  	1996	12	26	CA960620026      	1	19960513	G	7910	AS9413117	O-RING          			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					L/H OIL CAP	CUT             	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			K			FLUID LOSS                			CR	CRUISE         	1			CA			2010 	2010 				P89737			(CAN) 'O' RING P/N AS9413-117 WAS DAMAGED WHEN OIL CAP WAS INSTALLED. CONDITION CAUSED OIL TO LEAK FROM ENGINE IN FLIGHT	 AND DUE TO LOW OIL PRESSURE, AN IN-FLIGHT SHUTDOWN WAS CARRIED OUT. AIRCRAFT LANDED WITH NO FURTHER INCIDENT. 'O' RING 	WAS REPLACED AND ENGINE SERVICED WITH OIL AND RETURNED TO SERVICE.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1996121200276	19961212	00276	NE  	1996	12	12	CA960620029      	2	19960605	G	7260	310137101	BEARING         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       		NE  					FUEL PUMP DRIVE	SPALLED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18800	9823 				115070			(CAN) ENGINE METAL CONTAMINATION. FUEL PUMP DRIVE BEARING HEAVILY SPALLED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1996121200278	19961212	00278	EA  	1996	12	12	CA960620201      	2	19960519	G	7414	1052945	ROTATING SHAFT  	BENDIX      	105136029   	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					WOODRUFF KEY	SHEARED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			803  					L967436A			(CAN) PILOT NOTICED A 250 RPM DROP ON THE RIGHT MAGNETO DURING RUN-UP, AS WELL AS SIGNIFICANT ROUGH RUNNING WHEN ONLY TH	E RIGHT MAGNETO WAS SELECTED. AFTER SHUTDOWN THE RIGHT MAGNETO WAS REMOVED AND DISASSEMBLED. INSPECTION OF THE MAGNETO R	EVEALED A SHEARED MAGNET SHAFT AT THE WOODRUFF KEY LOCATION.				1	L	7	1 	3O	3	O		2A13    	E286				 
1996122600556	19961226	00556	SO  	1996	12	26	CA960625012      	1	19960521	G	2701	62839000	SPROCKET        			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  					CONTROL YOKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3977 					L3284927A			(CAN) ON ANNUAL INSPECTION, FOUND CONTROL YOKE SPROCKET CRACKED AT WELD. STOP PIN LOOSE BUT STILL IN PLACE.						1	L	7	1 	3O	3	O		2A13    	E274				 
1996121200289	19961212	00289	SO  	1996	12	12	CA960625201      	2	19960620	G	7414	103493542	FLYWEIGHTS      	BENDIX      	103493501   	BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	3A32C	3A32C406    	GL  	MAGNETO	DESTROYED       	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA						A72932		22233373BA	922052		(CAN) FLYWEIGHTS JAMMED ON STOP PIN, WHICH SHEARED PIN. PIN AND FLYWEIGHTS WERE FOUND IN THE ENGINE OIL SUMP. THE ENGINE	 GEAR TRAIN WAS DAMAGED. THE FAILURE WAS DUE TO EXCESSIVE WEAR ON FLYWEIGHTS AND FLYWEIGHT AXLE.					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA	 
1996122600561	19961226	00561	EU  	1996	12	26	CA960703003      	1	19960620	G	5510	G102	HORIZONTAL STAB 			GROB  	ASTIR 	G102STDAST3 		EU  										ELEVATOR HINGE	DELAMINATED     	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			1101 								(CAN) MOMENTARY CONTROL FLUTTER IN FLIGHT. UPON LANDING AN INSPECTION REVEALED THE MYLAR STRIP WHICH IS TAPED TO THE UPP	ER SKIN AND EXTENDS OVER THE ELEVATOR CONTROL SURFACE WAS MISSING. THE UPPER SKIN LAMINATE DIRECTLY OVER THE TWO CENTRE 	HINGES FOR THE ELEVATOR HAD DELAMINATED FROM HINGE TAB.				1	K	0	0 	0 			0	G33EU   					 
1996122600564	19961226	00564		1996	12	26	CA960703007      	4	19960618	G	3422	5223874	AMPLIFIER       			BOEING	727   	727         	1384001	NM  										INST AMP	LOOSE           	W				A				UNSCHED LANDING         				I			FLT. ATTITUDE INST.       			CL	CLIMB          	1			CA											(CAN) CAPTAINS GYRO FAILED ON ROTATION. AUXILIARY POSITON SELECTED, NO FIX. AIRCRAFT RETURNED. MAINTENANCE FOUND INSTRUM	ENT AMP LOOSE IN ITS MOUNTING BRACKET. AMP HAD BEEN INSTALLED 2 MONTHS EARLIER.					2	L	7	3 	4F				A3WE    					 
1996121200298	19961212	00298	EA  	1996	12	12	CA960703013      	1	19960528	G	5312	C2FS533	BULKHEAD        	DHAV        		DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					AFT FS 228	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11071					PCE42145			(CAN) AFT FULL BULKHEAD AT STA. 228 FOUND CRACKED ON BOTH LEFT AND RIGHT SIDES WHERE RUDDER CONTROL RODS PASS THROUGH TH	E BULKHEAD. CRACKS RADIATE FROM HOLES 3/32" TO 1/2" TOWARDS THE VERTICAL STAB ATTACHMENT. TWO OTHER AIRCRAFT WERE FOUND 	WITH SAME CRACKS.				1	H	7	1 	3T	4	T		A806    	E4EA				 
1996121200304	19961212	00304	EA  	1996	12	12	CA960703019      	1	19960717	G	2421	721428	ID GENERATOR    	SUNSTRAND   		CNDAIR	CL600 	CL6001A11   	1900302	EA  										ENGINE GEARBOX	DEFECTIVE       	W				K				NONE                    				J			WARNING INDICATION        			DE	DESCENT        	1			CA						305232					(CAN) GENERATOR TRIPPPING OFF LINE. METAL IN SCAVENGE FILTER AND ON CHIP DETECTOR. COMPONENT CAUSING TROUBLE WILL HAVE T	O BE DETERMINED ON TEARDOWN.					2	L	7	2 	4F			RT	A21EA   					 
1999052800001	19990528	00001		1999	5	28	CA960703022      	1	19960619	G	7810		CLIP            								ALLSN 	501D  	501D13D     	03004	GL  					NR 1 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA				124  				501261			(CAN) POSSIBLE RUPTURE AND LOSS IN-FLIGHT OF ATTACHING BAND/CLIP ON THE EXHAUST PIPE OF NR 1 ENGINE CAUSING A FIRE ALARM	 IN THE EXHAUST PIPE ZONE.  EMERGENCY PROCEDURES CARRIED OUT, ENGINE STOPPED AND PROPELLER FEATHERED.   PRECAUTIONARY LA	NDING MADE.									4	T			E282				 
1996122600572	19961226	00572	NM  	1996	12	26	CA960703033      	1	19960613	G	2923	AO293	SEAL            		65W01025    	BOEING	720   	720023B     	1383841	NM  	PWA   	JT3D  	JT3D3B      	52039	NE  					AUX PUMP	BLOWN           	W				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA						AO293		645267			(CAN) AFTER LANDING THE F E  NOTICED AN ACCUMULATION OF HYDRAULIC FLUID IN AREA OF L/H WHEEL. FUNCTION CHECK CARRIED OUT	 AND FLUID WAS LEAKING FROM BETWEEN HEAD AND MAIN BODY OF AUXILIARY PUMP WHICH WAS REPLACED					2	L	7	4 	4F	4	F		4A28    	1E8				 
1996122600575	19961226	00575	CE  	1996	12	26	CA960708001      	1	19960616	G	2571		BATTERY BOX TUBE			CESSNA	182   	182Q        	2072732	CE  						MCAULY	2A34C	C2A34C204   	GL  	BOX DRAIN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5160 						773867		(CAN) BATTERY BOX DRAIN TUBE FOUND BROKEN AND HAD ALLOWED VAPOURS TO ENTER THE AREA UNDER THE BATTERY BOX AND CORRODE TH	E STRUCTURE.					1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1996121200319	19961212	00319	NE  	1996	12	12	CA960708007      	2	19960626	G	7210	310709001	BEARING         	PWA         							PWA   	118   	PW118       		NE  					RGB NR 19 BRG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								115256			(CAN) THE REDUCTION GEARBOX (RGB) WAS SENT FOR INVESTIGATION AND REPAIR BECAUSE THE RGB WAS MAKING METAL. THE CAUSE OF T	HE RGB MAKING METAL WAS AN AXIAL CRACK ON THE INNER RACE OF THE #19 BEARING AND THE SPALLING OF THE #18 BEARING INNER RI	NG PLAIN HALF.									4	T			E20NE				 
1996122600577	19961226	00577	NE  	1996	12	26	CA960709001      	2	19960626	G	7260	4002T00G09	DRIVE SPLINE    			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581101    	30011	NE  					STARTER DRIVE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING AN ATTEMPTED START, THE STARTER MOTOR WOULD NOT ENGAGE. ON REMOVING STARTER, ENGINE SIDE OF ENGAGE DRIVE BE	CAME UNATTACHED.					2	G	7	2 	4U	4	U		1H15    	1E3				 
1996122600579	19961226	00579	GL  	1996	12	26	CA960711002      	2	19960702	G	7250	6898663	TURBINE BLADES  			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					3 AND 4 STAGE	DAMAGED         	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA											(CAN) A #2 ENGINE ICP CHECK WAS BEING CONDUCTED WHEN #1 ENGINE WAS OBSERVED STARTING TO DECELERATE ACCOMPANIED BY A FUEL	 PRESSURE CAUTION LIGHT. WHILE TROUBLESHOOTING #1 ENGINE PROBLEM ENG FAILED. UPON SHUT DOWN AND INVESTIGATION, A POWER T	URBINE FAILURE WAS OBSERVED.				1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996122600583	19961226	00583	SW  	1996	12	26	CA960711011      	1	19960618	G	5551	22123	BRACKET         	BLANCA      	22123       	BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					MID LWR BRACKET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2797 			4374		L188836A			(CAN) CRACKS FROUND IN LEFT AND RIGHT ARM OF THE LOWER AFT STAB BRACKET. THIS PART HAS BEEN FOUND CRACKED BEFORE AND REP	AIRED BY WELDING. THESE LATEST CRACKS WERE FOUND THROUGH OR NEXT TO THE PREVIOUS REPAIRS. WELD REPAIRS WERE ONCE AGAIN C	ARRIED OUT.				1	H	7	1 	3O	3	O		A21CE   	E286				 
1996121200333	19961212	00333	EA  	1996	12	12	CA960711012      	2	19960703	G	8500		ENGINE          			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					POWER SECT	VIBRATIONS      	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA				530  				L2155736A			(CAN) PILOT REPORTED AN ENGINE VIBRATION THAT WAS MOST NOTABLE AT 1000-1200 RPM. PROP HAS BEEN OVERHAULED AND BALANCED, 	SWAPPED FROM A SISTER AIRCRAFT AND TRACKED CHECKED. CARBURETOR HAS BEEN CHECKED, VIBRATION WAS SEVERE ENOUGH TO LOOSEN T	HE THROUGH BOLTS ON THE ALTERNATOR. DYNAMIC BALANCING IS GOING TO BE CARRIED OUT.				1	H	7	1 	3O	3	O		A21CE   	E286				 
1996121200334	19961212	00334		1996	12	12	CA960711013      	1	19960708	G	2432	CBC182166	VENT CAP        	CONCORDEBATT	CB35        															BATTERY	TOO SMALL       	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			250  			CBC182166					(CAN) BATTERY VENT CAPS WILL NOT REMAIN TIGHT DUE TO CAP THREADS POORLY MADE.  THE THREADS SEEM TO BE TOO SMALL AND WOUL	D NOT ENGAGE THE CELL COVERS ENOUGH TO STAY TIGHTSEVERAL OTHER AIRCRAFT CHECKED WITH SAME BATTERY MAKE AND HAVE THE SAME	 PROBLEM. EACH CAP HAS RUBBER CAP CONNECTED TO A VENT MANIFOLD THAT VENTS OVERBOARD. WHEN THE BATTERY CAP COMES LOOSE IN	 THE THREADS IN THE BATTERY, FLUID CAN SPILL OUT.																 
1996122600584	19961226	00584	CE  	1996	12	26	CA960711014      	1	19960709	G	7920	56001093	LINE ASSEMBLY   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					WASTE GATE	CHAFED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								278434R			(CAN) WASTE GATE OIL SUPPLY LINE FOUND CHAFED ON ENGINE MOUNT BEAM FLANGE. P/N MS21919WCH4 CLAMP AND ASSOCIATED MOUNT BO	LT, SPACER, WASHER AND NUT ALSO MISSING WHICH ALLOWED LINE TO DROP DOWN ONTO MOUNT BEAM FLANGE. SUBMITTER STATES AREA IS	 INCONVENIENT TO INSPECT AND THE DEFECT WAS ONLY FOUND DURING ENGINE CHANGE PROCESS.				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1996122600585	19961226	00585	CE  	1996	12	26	CA960711015      	1	19960606	G	2620		RETAINING CLIP  	RAYTHN      	1015700215  	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FIRE EXT SWITCH	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2295 					PCE25637			(CAN) ON INSPECTION OF THE ENGINE FIRE EXTINGUISHER ELECTRICAL SYSTEM, IT WAS NOTED THAT THE FIRE EXTINGUISHER MICROSWIT	CH ON THE PANEL ACTIVATING BUTTON HAD COME OFF THE HOLDING CLIP, RENDERING THE BUTTON INOPERATIVE. THE SWITCH MANUFACTUR	ER - RAYTHEON - INDICATES THAT A REPLACEMENT SWITCH IS BEING PRODUCED.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
1996122600587	19961226	00587	SO  	1996	12	26	CA960711201      	1	19960618	G	2435	603871	FLANGE          	AUXILEC     	8013C       	PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					START/GEN	BROKEN LEGS     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			954  					PCE92560			(CAN) THE STARTER/GENERATOR QUICK ATTACH-DETACH FLANGE WAS FOUND TO HAVE BROKEN LEGS DURING AN INSPECTION. THE PILOT NOT	ED A DIFFERENT NOISE WHILE STARTING THE AIRCRAFT.					1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
1996121200337	19961212	00337		1996	12	12	CA960712103      	4	19960702	G	3445		TRANSPONDER     			AIRBUS	310   	A310300     		EU  										TCAS SYS	MALFUNCTION     	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) WHILE VMC AT FL350 IN LEVEL FLIGHT NEAR THE AUTUN VOR, AIRCRAFT EXPERIENCED AT FULL TCAS ADVISORY & RESOLUTION. FI	RST A TARGET DISPLAYED ON THE IVSI AT THE 2-3 O'CLOCK POSITION AT 2-3 NM RANGE AT THE SAME ALTITUDE, ACCOMPANIED BY AN A	URAL WARNING. APPROXIMATELY 2 SECONDS LATER THE IVSI/TCAS LIT UP RED DIRECTING A CLIMB ACCOMPANIED WITH AN AURAL CLIMB C	OMMAND. VISUAL CONFIRMATION COMBINED WITH UNREALISTIC SPEED OF THE WARNING SEQUENCE LED CREW TO SUSPECT VALIDITY OF WARN	ING. THIS INCIDENT OCCURRED IN IMC CONDITIONS & WAS BELIEVED AT THE TIME TO BE A NEAR MISS. THE TCAS AND TRANSPONDER COM	PUTERS WERE REPLACED AND ARE BEING EVALUATED.	2	L	7	2 	4F			RT	A35EU   					 
1998050100204	19980501	00204	CE  	1998	5	1	CA960715004      	1	19960717	G	2710	55653813	QUADRANT        			CESSNA	501   	501         	2076603	CE  										LT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15055								(CAN) DURING ROUTINE INSPECTION, THE LT AILERON QUADRANT WAS SUSPECTED TO BE CRACKED.   AS A PRECAUTION, THE RT QUADRANT	 WAS INSPECTED AS WELL.  THE LT QUADRANT WAS REPLACED AND RT WAS CHECKED BY EDDY CURRENT AND FOUND TO BE SERVICEABLE.  P	ART TC:  18,996.				1	L	7	2 	4F				A27CE   					 
1996122600596	19961226	00596		1996	12	26	CA960715201      	4	19960709	G	2562	0025004	BATTERY         	MARTECH     	EB2BCD      	MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ELT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						8546		L41751			(CAN) ON ROUTINE INSPECTION OF THE ELT CORROSION WAS NOTED ON THE LOWER END OF THE CASE. INVESTIGATION FOUND THE BATTERY	 HAD LEAKED AND CORRODED THE INSIDE OF THE CASE AND BOTTOM OF THE PC BOARD.					1	L	7	1 	3O	3	O		2A3     	1E10				 
1996122600603	19961226	00603	NM  	1996	12	26	CA960716009      	1	19960618	G	3320	BA080061	BALLAST         	BRUCE       		DHAV  	DHC8  	DHC8101     	2809002	NM  										SEAT ROW 7	BURNT           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) SMOKE IN CABIN COMING FROM BUFFET CEILING. OVERHEAD PANELS REMOVED AND MAINTENANCE FOUND INOPERATIVE LIGHTS AT SEA	T ROW 7. TWO BALLASTS WERE FOUND FAULTY. BOTH UNITS WERE AT MOD 'D' STATUS. MOD 'G' INTRODUCED DESIGN CHANGES TO PREVENT	 THESE OCCURRENCES.				2	H	7	2 	4T			RT	A13NM   					 
1996121200343	19961212	00343	EA  	1996	12	12	CA960722001      	2	19960711	G	8530		VALVE SEAT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					#6 CYLINDER	DISLODGED       	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				660  				L1449868A			(CAN) AFTER LANDING THE PILOT NOTICED THE NR 2 ENGINE WAS RUNNING ROUGH AT IDLE. INVESTIGATION FOUND THERE WAS NO COMPRE	SSION ON #6 CYLINDER. AFTER THE CYLINDER WAS REMOVED IT WAS REVEALED THE EXHAUST VALVE SEAT WAS DISLODGED FROM THE CYLIN	DER AND HOLDING THE VALVE PARTLY OPEN.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1996122600617	19961226	00617	SW  	1996	12	26	CA960722008      	1	19960711	G	2730	31072	CONTROL CABLE   		31072       	BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  					ELEV  AFT PULLY	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L1868036A			(CAN) ON INSPECTION THE ELEVATOR CABLE WAS FOUND FRAYED WHERE IT PASSES OVER THE UPPER REAR PULLEY.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
1998050100206	19980501	00206	GL  	1998	5	1	CA960723016      	2	19960626	G	7260	6894171	BEARING         								ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			4430 					CAE835686			(CAN) NR 2 ENGINE MAGNETIC PLUG WARNING LIGHT CAME ON IN-FLIGHT.  PILOT REDUCED POWER TO IDLE ON NR 2 ENGINE AND RETURNE	D TO RAMP.  LOWER MAGNETIC PLUG HAD HEAVY ACCUMULATION OF FINE METAL PARTICLES.  FURTHER INVESTIGATION REVEALED THAT NR 	2 1/2 BEARING WAS THE SOURCE OF METAL AND THE SPUR ADAPTER GEAR SHAFT WHERE NR 2 1/2 BEARING RIDES HAS DAMAGE FROM THE B	EARING.								3	U			E4CE				 
1997010200219	19970102	00219	EA  	1997	1	2	CA960723557      	1	19960709	G	2432	160458005	FIN STOCK       		237BC1011C  	CNDAIR	CL600 	CL6002B16   	1900305	EA  										BATTERY CHARGER	LOOSE           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			9    			262					(CAN) CONVOLUTED FIN STOCK IS BONDED INTO PLACE AS A 'HEAT SINK' IN THE BATTERY CHARGER. THE STOCK CAME LOOSE AND AS THE	 TECHNICIAN WAS CHECKING SOME COMPONENTS IT CAME IN TOUCH WITH A POWERED TRANSISTOR CAUSING A SHORT. ARCING OCCURRED. SE	VEN OTHER UNITS WERE FOUND WITH THE SAME PROBLEM OF A LOOSE FIN STOCK.				2	L	7	2 	4F			RT	A21EA   					 
1998050100207	19980501	00207		1998	5	1	CA960724402      	4	19960621	G	3460	13442RE	DATA BASE       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FLT MANAGMNT SYS	ERROR           	W				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) WHEN DOING A FLIGHT MANAGEMENT SYSTEM APPROACH, FMS DISENGAGED AND STEERING COMMANDS WENT OFF THE SCREEN.  PILOT U	NABLE TO RE-ENGAGE APPROACH.  AIRCRAFT PERFORMED CORRECTLY ON NORMAL APPROACH (ILS).  WHILE UNDER INVESTIGATION, MANUFAC	TURER CONTACTED AND THEY INFORMED SUBMITTER THAT THE DATABASE WAS IN ERROR AND UPDATED DISKS WERE SENT TO INSTALL NEW UP	DATED DATABASE.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997010200224	19970102	00224	SO  	1997	1	2	CA960724403      	2	19960726	G	8520	40644	MAIN BEARING    			TMPSON	NAVION	NAVIONA     	6150104	SW  	CONT  	E225  	E2254       	17015	SO  					CRANKCASE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			770  					30025D34			(CAN) CRANKCASE ASSEMBLY RECEIVED FOR INSPECTION AFTER REPORTS OF HIGH OIL TEMPERATURE, LOW OIL PRESSURE AND STIFFNESS O	F PROP ROTATION. CRANKCASE DISMANTLED, CLEANED AND INSPECTED. INSPECTION FOUND THE #5 MAIN BEARING SEIZED. FAILURE TYPIC	AL OF OIL STARVATION, FURTHER INSPECTION REVEALED A LARGE AMOUNT OF RUBBER DEBRIS IN THE SUCTION TUBE, CHOKING THE SUCTI	ON SCREEN. CRANKCASE OVERHAULED.			1	L	7	1 	3O	3	O		A782    	E267				 
1998050100208	19980501	00208	WP  	1998	5	1	CA960729001      	1	19960716	G	7921	315341	ACTUATOR        			CVAC  	340   	340CVAC     	242270A	WP  										OIL COOLER DOOR	FAILED          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			M			OVER TEMP                 			CL	CLIMB          	1			CA				879  							(CAN) FLIGHT CREW ON CLIMB-OUT NOTICED NR 2 ENGINE OIL TEMP HIGH AT APPROX 85 DEGREES CELSIUS.  OIL COOLER DOOR WAS MANU	ALLY SELECTED OPEN TO COOL OIL.  DID NOT RECTIFY PROBLEM.  POWER LEVEL RETARDED TO 1,000 H.P., NO CHANGE.  OIL TEMP CONT	INUED TO RISE AND WAS E-HANDLED AT 100 DEGREES CELSIUS.  REPLACED OIL COOLER AND AIRCRAFT DEPARTED WITH NO FURTHER PROBL	EMS.  AIRCRAFT TT:  20,551 HOURS.			2	L	7	2 	4R				6A6     					 
1997121800386	19971218	00386	CE  	1997	12	18	CA960729006      	1	19960722	G	3230	99810022	PLATE           		5081033513  	BEECH 	100   	A100        	1152915	CE  										DRAG BRACE	BENT            	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			1310 			XL95206					(CAN) RIGHT HAND DOWN LOCK PLATE BENT ON LANDING GIVING UNSAFE GEAR.						1	L	7	2 	3T				A14CE   					 
1997121800387	19971218	00387	CE  	1997	12	18	CA960729007      	1	19960717	G	2752	505211516	PISTON          		505212224   	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RT FLAP ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2544 			944D91		PCE25636			(CAN) DURING ROUTINE MAINTENANCE IT WAS OBSERVED THAT THE RIGHT HAND INBOARD FLAP ACTUATOR PISTON WAS CRACKED ALONG ITS 	LENGTH. CRACK ORIGINATED AT THE PLUG HOLE. REFERENCE BEECH IPC 27-50-30, FIG 50-30, ITEM 15. SDR 960807007 PERTAINS TO S	AME CONDITION.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
1997010200233	19970102	00233	SO  	1997	1	2	CA960729010      	2	19960709	G	8520		MAIN BEARINGS   								CONT  	O470  	O470K       	17026	SO  					#2 & #3 BEARING	SPUN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1040 				486559K			(CAN) ENGINE WAS UNABLE TO MAINTAIN MINIMUM OIL PRESSURE IN CRUISE AND PROP CONTROL WAS DIFFICULT. ENGINE WAS DISMANTLED	 FOR INSPECTION WHICH REVEALED #2 & #3  MAINS HAD SPUN IN THE CRANKCASE. CRANKCASE ASSEMBLY OVERHAULED AND ENGINE WAS RE	TURNED TO SERVICE.									3	O			E273				 
1998050100209	19980501	00209	GL  	1998	5	1	CA960729014      	1	19960522	G	6710	206062721011	ACTUATOR        			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    		GL  					ENG GOV	FAILURE         	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA								CAE831288			(CAN) AFTER STARTING THE ENGINE, THE PILOT WAS UNABLE TO RAISE THE ROTOR RPM ABOVE 90 PERCENT NR.  THERE WAS NO BEEP TRI	M RANGE AVAILABLE AND THE ENGINE WAS SHUT DOWN.  ON INSPECTION, FOUND THE INTERNAL STOP OF THE LINEAR ACTUATOR HAD FAILE	D AND THE SHAFT WAS OVER EXTENDED PUTTING THE ENGINE GOVERNOR AT FULL DECREASE.  THE SHAFT HAD BEEN EXTENDED TO THE POIN	T THAT ITS THREADS AND THE THREADS OF THE ACTUATING SCREW HAD SEPARATED MAKING IT UNABLE TO RETRACT.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997010200237	19970102	00237	NE  	1997	1	2	CA960729016      	2	19960717	G	7210	310709001	BEARING         	PWA         							PWA   	118   	PW118       		NE  					RGB NR 19	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								115321			(CAN) THE ENGINE, WHICH WAS MAKING METAL, WAS SENT FOR INVESTIGATION/OVERHAUL. DISASSEMBLY FOUND THE #19 BEARING IN THE 	REDUCTION GEARBOX SPALLED ON THE INNER RACE. THIS IS THE CAUSE OF THE RGB MAKING METAL. THERE WERE NO CONTRIBUTING FACTO	RS FOR THE #19 BEARING SPALLING, THEREFORE THIS IS CONSIDERED TO BE A PRIMARY FAILURE OF THE #19 BEARING. THE BEARING WA	S REPLACED.								4	T			E20NE				 
1997121800389	19971218	00389	CE  	1997	12	18	CA960729019      	1	19960702	G	2730	MS178254	CASTLE NUT      		26121191    	CESSNA	208   	208B        	2073701	CE  										AFT ELEVATOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			119  								(CAN) AFT TAIL ACCESS PANEL WAS REMOVED AND AFT ELEVATOR BELLCRANK PIVOT WAS FOUND TO BE MISSING THE CASTLE NUT AND COTT	ER PIN. INSTALLED AND AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3T				A37CE   					 
1998020500595	19980205	00595	CE  	1998	2	5	CA960731001      	1	19960713	G	3260	903610373	SWITCH          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					LEFT MAIN	FAILED          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA								PCE25664			(CAN) ON LANDING GEAR DOWN AND LOCKED, PILOT SELECTED FULL FLAPS AND THE RED LIGHT IN THE GEAR HANDLE CAME ON, WITH GEAR	 WARNING HORN ACTIVATED. AIRCRAFT LANDED OK AFTER TOWER CONFIRMATION OF GEAR DOWN. INVESTIGATION FOUND THE LEFT MAIN DOW	N LOCK SWITCH ASSEMBLY HAD FAILED. SWITCH REPLACED, BUT THEN FAILED AGAIN A COUPLE OF DAYS LATER. REPLACED AGAIN AND OK 	THIS TIME.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
1997010200255	19970102	00255	EA  	1997	1	2	CA960801014      	1	19960626	G	2915	6607P96A	PRESSURE SWITCH 	CONSOLCNTRLS		DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					HYDRAULIC SYSTEM	LOW SETTTING    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA						2757		PCE42076			(CAN) DURING INSPECTION IT WAS FOUND THAT THE HYDRAULIC SYSTEM WAS PRODUCING ONLY 1350 PSI. CORRECT PRESSURE IS 1575. A 	NEW PRESSURE CUTOUT SWITCH WAS INSTALLED.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997010200256	19970102	00256	EA  	1997	1	2	CA960801015      	1	19960720	G	7500		BELLOWS         		C6VE10231C  	DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					RT BLEED AIR	CRACKED         	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				25822				PCE42076			(CAN) RIGHT HAND BLEED AIR SYSTEM NOT RESPONDING TO SELECTOR SWITCH IN THE COCKPIT. INVESTIGATION FOUND THAT BLEED AIR D	UCT BELLOWS HAD FAILED AND WAS ALLOWING AIR TO ESCAPE AT ALL TIMES.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997010200257	19970102	00257	EA  	1997	1	2	CA960801016      	1	19960720	G	7500		BELLOWS         		C6VE10081C  	DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					RT ENG BLEED	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				25844				PCE42076			(CAN) DURING TAKEOFF CHECKS IT WAS NOTED THERE WAS NO CHANGE IN RIGHT HAND ENGINE INDICATION WHEN BLEED AIR WAS SELECTED	 ON. MAINTENANCE FOUND THE BLEED AIR LINE HAD FAILED AT THE EXPANSION BELLOWS ALLOWING BLEED AIR TO ESCAPE AT ALL TIMES.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1998041700408	19980417	00408	GL  	1998	4	17	CA960801021      	2	19960726	G	7230	6876667	EXDUCER         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE830970			(CAN) WHILE DOING A TURBINE CHANGE, AME FOUND A CRACK IN THE COMPRESSOR DISCHARGE TUBE.   SUSPECT CRACK WAS CAUSED BY ME	CHANICAL DAMAGE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998041700411	19980417	00411	EU  	1998	4	17	CA960802004      	1	19960726	G	2700	L1340213A402092M	CABLES          			LET   	L13   	L13BLANIK   	1360306	EU  										PULLEYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1304 								(CAN) WHILE CARRYING OUT AN ITRAN INSPECTION, A MOUSE NEST PROMPTED AN INSPECTION FOR CORROSION UNDER THE COCKPIT FLOOR.	  CABLES IN THAT AREA WERE FOUND TO HAVE AN UNACCEPTABLE AMOUNT OF BROKEN WIRES IN THE AREA OVER THE PULLEYS.  THE PREVI	OUS LOGS SHOW THAT THE CABLES WERE REPLACED IN JULY OF 1995.  AN AME FAMILIAR WITH THIS AIRCRAFT TOLD THE SUBMITTER THAT	 THIS AREA HAS HAD PROBLEMS BEFORE.			1	K	0	0 					G24EU   					 
1997121800391	19971218	00391	CE  	1997	12	18	CA960802007      	1	19960726	G	3240	0690190	ANCHOR BOLT     	CLEVELAND   	07517100    	CESSNA	208   	208B        	2073701	CE  										RH AXLE	MISSING NUT     	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			226  								(CAN) THE ANCHOR BOLT IS NORMALLY ATTACHED TO THE AXLE TORQUE PLATE WITH AN FIBER LOCKNUT (P/N AN 365). ON THIS OCCURREN	CE THE LOWER ANCHOR BOLT ON THE RH SIDE LOST THE ATTACHMENT NUT WHICH CAUSED THE BOLT TO BACK OUT OF THE TORQUE PLATE AN	D COME IN CONTACT WITH THE WHEEL HALF BOLTS. THIS CONDITION CAUSED DAMAGE TO THE TORQUE PLATE, WHEEL HALF BOLTS, ANCHOR 	BOLT AND BRAKE UNIT. THE LOCKNUTS ON THE OTHER ANCHOR BOLTS WERE CHECKED AND IT WAS FOUND THAT THE GREEN NYLON INSERT WA	S SQUEEZED OUT PART WAY, IN SOME CASES, LESS THAN 1/2 A THREAD WAS SHOWING. IT IS RECOMMENDED ADJUSTING THE THICKNESS OF	 THE WASHERS AND USING A STEEL LOCKNUT.	1	H	7	1 	3T				A37CE   					 
1997121800395	19971218	00395	CE  	1997	12	18	CA960807007      	1	19960730	G	2752	505211958	PISTON          	BEECH       	505212234   	BEECH 	90    	C90A        	1152911	CE  										FLAP ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			119  			847B93					(CAN) DURING OPERATION IN GROUND CHECK THE FLAP WAS NOTED TO BE NOISY. TRACKS LUBED TO NO EFFECT. INVESTIGATION FOUND TH	E ACTUATOR PISTON WAS SPLIT ALONG ITS LENGTH, APPROXIMATELY 4.5 INCHES FROM THE END.NEW ACTUATOR INSTALLED AND RIGGING C	HECKS COMPLETED. SDR 960729007 PERTAINS TO SAME CONDITION.				1	L	7	2 	3T			RT	3A20    					 
1997010200272	19970102	00272	NE  	1997	1	2	CA960808012      	2	19960731	G	7210	310924401	BEARING         								PWA   	120   	PW120       		NE  					RGB NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			13930	5772 				120481			(CAN) THE REDUCTION GEARBOX (RGB) WAS FOUND BY THE OPERATOR TO HAVE METAL CONTAMINATION. DISASSEMBLY OF THE RGB REVEALED	 THE SOURCE OF THE METAL CONTAMINATION WAS THE #15 BEARING WHICH HAD SPALLED BADLY ON THE OUTER RACE. SECONDARY DAMAGE F	ROM THE CONTAMINATES WAS RESTRICTED TO SEVERAL OTHER BEARINGS AND NO GEARS WERE FOUND DAMAGED SUFFICIENTLY TO REQUIRE RE	PLACEMENT.								4	T			E20NE				 
1997010200273	19970102	00273	NE  	1997	1	2	CA960808013      	2	19960731	G	7250	MS969611	BOLT            								PWA   	PW121 	PW121       	52124	NE  					INTERSTAGE CASE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12457					120870			(CAN) THE ENGINE WAS UNDERGOING ROUTINE INSPECTION AND WAS OBSERVED TO HAVE SUSTAINED CONSIDERABLE POWER TURBINE DAMAGE.	 DISASSEMBLY FOUND THE ENGINE HAD SUFFERED A FRACTURE OF ONE INTERSTAGE CASE BOLT, WHICH RELEASED THE BOLT HEAD WHICH WA	S SUBSEQUENTLY INGESTED BY THE POWER TURBINE CAUSING EXTENSIVE SECONDARY DAMAGE. THE INTERSTAGE CASE REAR FLANGE WAS COR	RODED IN THE LOCATION THAT THE BOLT FAILED, WITH THE CORROSION PRODUCTS INCREASING THE LOCAL FLANGE THICKNESS CONSIDERAB	LY, RESULTING IN BOLT STRETCH AND FAILURE.							4	T			E20NE				 
1997010200274	19970102	00274	NE  	1997	1	2	CA960808014      	2	19960729	G	7210	310924401	BEARING         								PWA   	119   	PW119B      		NE  					RGB NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5095 					116023			(CAN) THE REDUCTION GEARBOX (RGB) WAS FOUND TO HAVE METAL CONTAMINATION. DISASSEMBLY OF THE RGB REVEALED THE SOURCE OF T	HE METAL CONTAMINATION WAS THE #15 BEARING WHICH HAD SPALLED BADLY ON THE INNER RACE, AROUND APPROXIMATELY 90 PERCENT OF	 THE CIRCUMFERENCE. SECONDARY DAMAGE FROM THE CONTAMINATS WAS RESTRICTED TO THREE OTHER SECOND STAGE BEARINGS.									4	T			E20NE				 
1997121800400	19971218	00400	CE  	1997	12	18	CA960813005      	1	19960807	G	5520	3361000039	FITTING         	BEECH       	33610000609 	BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      		SO  					LT RT ELEV	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								675757			(CAN) ON BOTH LEFT HAND AND RIGHT HAND ELEVATOR THE LOWER BOLT (P/N AN23-10A) COULD BE TURNED BY HAND						1	L	7	1 	3O	3	O		3A15    	E3SO				 
1997030600669	19970306	00669	CE  	1997	3	6	CA960826018      	1	19960809	G	3710	3116D	HOSE FITTING    			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					VAC HOSE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								803709L4			(CAN) DURING INSPECTION OF THE VACUUM HOSE FITTING. THE "B" NUT WAS FOUND CRACKED. SUBMITTER SUSPECTS THAT AN OVERTORQUI	NG OF THE NUT TOOK PLACE.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1998111300568	19981113	00568		1998	11	13	CA960826046      	1	19960812	G	2822	TF70251	BEARING         	TRW         	TF57800     															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						TF784743W					(CAN) OEM USES ONLY N.D. BEARINGS.  BEARING REMOVED WAS MANUFACTURED BY FAFNIR.																			 
1998111300569	19981113	00569		1998	11	13	CA960826047      	1	19960812	G	2110	CYRB234	BEARING         	BARBERCOL   	SYLC9868    															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						695					(CAN) BEARING REMOVED HAS NO MANUFACTURERS NAME ON IT.  OEM USES BEARINGS MADE BY NMB.																			 
1998111300570	19981113	00570		1998	11	13	CA960826048      	1	19960812	G	2822	1075256	BEARING         	DELCO       	A7535A1     															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						65439					(CAN) OEM USES ONLY NEW DEPARTURE BEARING.  BEARING REMOVED WAS AN MRC.																			 
1998111300571	19981113	00571		1998	11	13	CA960826049      	1	19960812	G	2822	5331514	BEARING         	DELCO       	A7535A1     															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						65439					(CAN) OEM USES ONLY N.D. BEARING, REMOVED WAS A SMT.																			 
2000020500767	20000205	00767		2000	2	5	CA960826050      	1	19960812	G	7714	X12060	BEARING         		AG34        															TACHOMETER GEN	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						35268					(CAN) OEM USES NMB BEARINGS, BEARING REMOVED WAS NEW DEPARTURE.																			 
1998111300572	19981113	00572		1998	11	13	CA960826051      	1	19960812	G	6220	X12061	BEARING         	SUNDSTRANDEM	AG34        															MAIN ROTOR	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						25268					(CAN) OEM USES BEARINGS MANUFACTURED BY NMB.   BEARING REMOVED WAS MADE BY NEW DEPARTURE.																			 
1998111300573	19981113	00573		1998	11	13	CA960826052      	1	19960812	G	6220	8492071	BEARING         	LUCAS       	32005007    															MAIN ROTOR	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						208114					(CAN) OEM PUTS THEIR PART NUMBER ON THE BEARING.  BEARING REMOVED DID NOT HAVE PROPER PART NUMBER ON IT.																			 
1998111300574	19981113	00574		1998	11	13	CA960826053      	1	19960812	G	2822	STE48	BEARING         	INTERTECHNIQ	2070C11     															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						2035					(CAN) OEM USES BEARING WITH A 'O' FRICTION TYPE SEAL.  BEARING REMOVED HAD STANDARD SEAL.																			 
1998111300575	19981113	00575		1998	11	13	CA960826054      	1	19960812	G	2822	226603	BEARING         		1227232000  															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						PE2427					(CAN) OEM USES IKS HALF SEALED, HALF SHIELDED BEARING.  BEARING REMOVED WAS SEALED ON BOTH SIDES AND MADE BY MRC.																			 
1998111300576	19981113	00576		1998	11	13	CA960826055      	1	19960812	G	2822	4045685	BEARING         	HYDROAIRE   	85816       															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						H208					(CAN) OEM USES SKF BEARING.  BEARING REMOVED HAD NO NAME ON IT.																			 
1998111300577	19981113	00577		1998	11	13	CA960826056      	1	19960812	G	2822	4045685	BEARING         	HYDROAIRE   	85816       															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						H922A					(CAN) OEM USES BEARING MANUFACTURED BY SKF.   BEARING REMOVED WAS MADE BY MRC.																			 
1998111300578	19981113	00578		1998	11	13	CA960826057      	1	19960812	G	2822	TF70251	BEARING         	TRW         	TF57800     															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						TF84743W					(CAN) OEM USES ONLY N.D. BEARINGS.  BEARING REMOVED WAS MANUFACTURED BY FAFNIR.																			 
1998111300579	19981113	00579		1998	11	13	CA960826058      	1	19960812	G	2435	07111337	BEARING         	LUCAS       	23064001    															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						2710					(CAN) OEM USES PART NUMBER STAMPED ON BEARING.  BEARING REMOVED WAS MADE BY NORMA AND DID NOT HAVE PROPER NUMBER ON IT.																			 
1998111300580	19981113	00580		1998	11	13	CA960826059      	1	19960812	G	2435	07111259	BEARING         	LUCAS       	23064001    															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						2710					(CAN) OEM USES BEARING MADE BY BARDEN AND HAS THEIR PART NUMBER STAMPED ON IT.  BEARING REMOVED WAS MADE BY FAG.																			 
1998111300581	19981113	00581		1998	11	13	CA960826060      	1	19960812	G	2822	RD56167	BEARING         	ROMEC       	RG52400D    															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						B1969					(CAN) OEM USES SEALED 39PP FAFNIR BEARING.  BEARING REMOVED WAS SHIELDED.																			 
1998111300582	19981113	00582		1998	11	13	CA960826061      	1	19960812	G	2822	RD561661	BEARING         	ROMEC       	RG52400D    															ARMATURE	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						B1969					(CAN) OEM USES NMB BEARING WITH 'O' FRICTION MICARTA SEALS.  BEARING REMOVED HAD NO MANUFACTURERS NAME ON IT.																			 
1997010200300	19970102	00300	NM  	1997	1	2	CA960826068      	1	19960628	G	3320	1640513	CONNECTOR       			DHAV  	DHC8  	DHC8301     		NM  										COCKPIT	OVERHEATED      	W				E				ENGINE SHUTDOWN         				B	M		SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 		TX	TAXI/GRND HDL  	1			CA											(CAN) ON POST ENGINE START CHECK, CREW NOTICED AN ELECTRICAL BURNING SMELL FOLLOWED BY SMOKE FROM BEHIND THE COPILOT'S S	EAT. SMOKE COMING FROM THE OVERHEAD BIN CONNECTOR THAT HAD SEVERELY OVERHEATED.					2	H	7	2 	4T			RT	A13NM   					 
1997011600940	19970116	00940		1997	1	16	CA960826070      	1	19960809	G	2435		PLUG            	LUCAS       	BCO9101     						PWA   	PT6   	PT6A50      	52043	EA  					SHAFT STARTR GEN	FOD             	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						0		86011			(CAN) WHILE CARRYING OUT SERVICE BULLETIN 4182, SPLIT SHAFT INSTALLATION, THE REAR CASE HAD TO BE OPENED. A 3/4" X 1/4" 	ROUND PLUG THREADED ON ONE END WAS FOUND LYING IN THE BOTTOM OF THE CASE. A PRATT & WHITNEY SERVICE REP WAS ON SITE & ID	ENTIFIED THE PLUG AS HAVING CAME FROM THE END OF THE STARTER GENERATOR SHAFT. THE STARTER GENERATOR WAS INSPECTED & THE 	PLUG WAS FOUND PROPERLY INSTALLED. THERE WAS NO WAY OF DETERMINING WHERE THE PLUG CAME FROM OR HOW LONG IT HAD BEEN IN T	HE CASE. IT IS A LUCAS MODIFICATION TO PUT THE PLUG IN THE STARTER GENERATOR SHAFT. TO GET INTO THE CASE THE PLUG WOULD 	HAVE TO HAVE GONE THROUGH THE AIR OIL SEPARATOR & THEN DROP INTO THE CASE.						4	T			E4EA				 
1997011600943	19970116	00943	EA  	1997	1	16	CA960826074      	1	19960814	G	2421	0085	SENSE WIRE      	SUNDSTRAND  	722822      	CNDAIR	CL600 	CL6002A12   	1900304	EA  										GEN FIELD	OPENED          	W				O				OTHER                   				O	H		OTHER                     	ELECT. POWER LOSS-50 PC   		DE	DESCENT        	1			CA						0085					(CAN) ON DESCENT GENERATOR FAILED.   TROUBLE SHOOTING FOUND OPEN FIELD SENSE WIRE						2	L	7	2 	4F			RT	A21EA   					 
1997011600944	19970116	00944	EA  	1997	1	16	CA960826075      	1	19960811	G	3320	BV501258	RECEPTACLE      			CNDAIR	CL600 	CL600*      		EA  										GALLEY	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FLOURESCENT LIGHT ASSEMBLY LOCATED BEHIND COFFEE MAKER HAD A SHORTED RECEPTACLE. A BURNING SMELL NOTED AND SHORTLY	 AFTER THE GALLEY LIGHT CB POPPED. SUSPECT MOISTURE FROM COFFEE MAKER CAUSED PROBLEM WITH RECEPTACLE. COFFEE MAKER TO BE	 RELOCATED.				2	L	7	2 	4F			RT	A21EA   					 
1997030600675	19970306	00675	SO  	1997	3	6	CA960826076      	1	19960815	G	3233	SFA2325	ACTUATOR        			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					MLG	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA			121  					0			(CAN) THE PILOT WAS UNABLE TO RETRACT THE GEAR. AFTER A SAFE LANDING, MAINTENANCE FOUND THE MAIN LANDING ACTUATOR HAD LE	AKED ALL OF ITS HYDRAULIC FLUID PAST THE O-RING.					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1997010200303	19970102	00303		1997	1	2	CA960826104      	1	19960710	G	6310	3024680	CLUTCH ASSEMBLY 	PWA         	3024780     						PWA   	PT6T  	PT6T6       	52045	EA  					#2 ENGINE SIDE	DISENGAGED      	W				A				UNSCHED LANDING         				O			OTHER                     			EX	EXTERNAL LOAD  	1			CA				1857 		CPGB1591		CPPS72009			(CAN) THE HELICOPTER WAS LIFTING A LOAD, WHEN THE FREEWHEEL CLUTCH INSIDE THE COMBINING GEARBOX DECOUPLED OR DISENGAGED 	ON THE #2 ENGINE SIDE.  THE #2 ENGINE WENT TO FLIGHT IDLE.  THE PILOT RELEASED THE LOAD AND LANDED AS SOON AS POSSIBLE. 	 THE COMBINING GEARBOX WAS REMOVED AND SHIPPED TO A REPAIR STATION.									4	U			E22EA				 
1997013000467	19970130	00467	NE  	1997	1	30	CA960827019      	2	19960801	G	7250	MS969611	CASE BOLTS      								PWA   	120   	PW120       		NE  					INTERSTAGE CASE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								120080			(CAN) ROUTINE BOROSCOPE INSPECTION REVEALED THE 1ST STAGE POWER TURBINE BLADES HAD SMALL NOTCHES IN THE LEADING EDGE NEA	R THE ROOT AND TIP PLATFORM. TEARDOWN OF THE ENGINE FOUND MULTIPLE FAILURES OF THE INTERSTAGE CASE BOLTS. THIS RELEASED 	THE INTERSTAGE CASE ASSEMBLY ON THE RIGHT HAND SIDE OF THE ENGINE WHICH THEN MOVED BACK UNTIL THE TRAILING EDGE OF THE I	NNER AND OUTER PLATFORMS OF THE PT1 STATOR ASSEMBLY CONTACTED THE LEADING EDGE OF THE PT1 ROTOR BLADES CAUSING THE OBSER	VED GROOVE.							4	T			E20NE				 
1997013000470	19970130	00470	SO  	1997	1	30	CA960827103      	1	19960711	G	2810		TANKS           	PIPER       		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					RT AND LT FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3118 			0		L604936			(CAN) BOTH FUEL TANKS FOUND TO BE LEAKING FROM VARIOUS POINTS. FUEL LINES ALSO LEAKING. PHOTOS OF THE AIRCRAFT SUGGEST M	AINTENANCE NEGLECT.					1	L	7	1 	3O	3	O		2A13    	E286				 
1997013000471	19970130	00471	SO  	1997	1	30	CA960827104      	1	19960711	G	5730		PANEL           	PIPER       		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3118 			0		L604936			(CAN) TWO CRACKS WERE FOUND ON THE BOTTOM OF THE WING PANEL. THE FIRST CRACK APPROXIMATELY 5 INCHES LONG AND STARTING 3 	1/2 INCHES FORWARD OF THE SPAR. THE SECOND CRACK IS APPROXIMATELY 3 1/2 INCHES LONG AND STARTING FROM THE FOURTH RIVET O	N THE FORWARD ROW OF THE SPAR RIVETS. SUBMITTER STATES THAT BOTH CRACKS APPEAR TO HAVE BEEN THERE FOR SOME TIME. PHOTOS 	TAKEN OF THE AIRCRAFT AND SUBMITTED WITH SDR 960827103 SUGGEST A LACK OF MAINTENANCE ON THIS AIRCRAFT.			1	L	7	1 	3O	3	O		2A13    	E286				 
1997013000472	19970130	00472	EA  	1997	1	30	CA960828001      	2	19960712	G	7320	3014216	P3 TUBE         								PWA   	PT6   	PT6A34      	52043	EA  					FCU SIDE	FRACTURED       	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA			2975 					57311			(CAN) ON APPROACH THE #1 ENGINE ROLLED BACK TO IDLE. THE ENGINE WAS SECURED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. PO	ST FLIGHT INSPECTION FOUND A FRACTURED P3 TUBE NEAR THE COUPLING NUT ON THE FCU SIDE. THE TUBE HAD BEEN INSPECTED ON 22 	MAY 1996.									4	T			E4EA				 
1997013000473	19970130	00473	NE  	1997	1	30	CA960828002      	2	19960719	G	7320	3017394	P3 TUBE         								PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL CONTROL	FRACTURED       	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				554  				63492			(CAN) DURING FLIGHT THE #2 ENGINE BEGAN TO ROLL BACK UNTIL THE ENGINE REACHED MINIMUM FUEL FLOW. THE PILOT SWITCHED TO M	ANUAL, THE POWER WAS RESTORED AND THE FLIGHT COMPLETED. POST FLIGHT INSPECTION FOUND THE P3 TUBE WAS FRACTURED AT THE EN	D OF THE TUBE.									4	U			E22EA				 
1997013000474	19970130	00474	NE  	1997	1	30	CA960828003      	2	19960621	G	7250		BLADE           								PWA   	120   	PW120A      		NE  					LOW PRESS TURBIN	FRACTURED       	W				E	F	A		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	UNSCHED LANDING         		M			OVER TEMP                 			CL	CLIMB          	1			CA			12500					120826			(CAN) AT 8000 FEET ON CLIMB OUT THE #1 ENGINE TORQUE FLUCTUATED 7-8 PERCENT. THE ITT THEN INCREASED TO 780 DEGREES CELCI	US AND SUBSEQUENTLY THE TORQUE DROPPED TO 50 PERCENT. A GRINDING NOISE WAS HEARD FOLLOWED BY A FIRE WARNING. THE ENGINE 	WAS SECURED AND THE FIRE BOTTLE WAS DISCHARGED. THE FIRE WARNING EXTINGUISHED AND AN UNEVENTFUL LANDING WAS MADE. POST F	LIGHT INSPECTION FOUND ONE LOW PRESSURE TURBINE BLADE LIBERATED FROM THE DISK.								4	T			E20NE				 
1997013000475	19970130	00475	NE  	1997	1	30	CA960828004      	2	19960704	G	7260		TOWER SHAFT     								PWA   	120   	PW120A      		NE  					ACCESSORY GEARBX	FRACTURED       	W				E				ENGINE SHUTDOWN         				J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			CA			1513 					120371			(CAN) DURING CRUISE THE #2 ENGINE TORQUE DROPPED TO ZERO AND THE LOW OIL PRESSURE LIGHT CAME ON. THE ENGINE WAS SHUTDOWN	. POST FLIGHT INSPECTION FOUND LARGE PIECES OF METAL IN THE OIL TANK CHIP DETECTOR. THE METAL CONTAMINATION WAS A RESULT	 OF THE FRACTURE OF THE BEVEL GEAR OF THE ACCESSORY GEARBOX TOWER SHAFT.									4	T			E20NE				 
1997013000477	19970130	00477	NE  	1997	1	30	CA960828006      	2	19960717	G	7311		FUEL  OIL COOLER								PWA   	PWA120	PW125B      		NE  					#2 ENGINE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								124247			(CAN) TWO MINUTES AFTER TAKEOFF #2 ENGINE OIL PRESSURE FLUCTUATIONS AND LOW OIL PRESSURE WAS EXPERIENCED. POWER WAS REDU	CED AND OIL PRESSURE RECOVERED. TWO ATTEMPTS TO INCREASE POWER CONFIRMED THAT OIL PRESSURE OCCURRED ONLY AT HIGH POWER S	ETTINGS. POWER WAS REDUCED AND AIRCRAFT RETURNED TO BASE. GROUND INSPECTION REVEALED HIGH OIL LEVEL WITH FUEL ODOR. FUEL	 COOLED OIL COOLER REPLACED AND AIRCRAFT RETURNED TO SERVICE.								4	T			E20NE				 
1997013000478	19970130	00478	NE  	1997	1	30	CA960828007      	2	19960811	G	7324		FLOW DIVIDER    								PWA   	PWA120	PW125B      		NE  					#1 ENGINE	FAULTY          	W				O				OTHER                   				X	R		ENGINE FLAMEOUT           	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			CA								125020			(CAN) ON APPROACH #1 ENGINE SUFFERED TORQUE FLUCTUATIONS BEFORE FLAMING OUT. THE FUEL FLOW DIVIDER WAS REPLACED AND THE 	AIRCRAFT RETURNED TO SERVICE.										4	T			E20NE				 
1997013000479	19970130	00479	NE  	1997	1	30	CA960828008      	2	19960806	G	7311		FUEL OIL COOLER 								PWA   	PWA120	PW125B      		NE  					#2 ENGINE	INTERNAL LEAK   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								125027			(CAN) AFTER 30 MINUTES OF LEVEL FLIGHT A LOW OIL PRESSURE LIGHT ILLUMINATED ON #2 ENGINE, FOLLOWED BY A PRESSURE DROP TO	 ZERO. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT DIVERTED. POST FLIGHT INSPECTION SHOWED THE OIL SYSTEM WAS CONTAMINATED 	WITH FUEL. THE CAUSE WAS IDENTIFIED AS INTERNAL LEAKAGE OF THE FUEL COOLED OIL COOLER (FCOC).									4	T			E20NE				 
1997021100003	19970211	00003	NM  	1997	2	11	CA960830001      	1	19960815	G	5230	655343315	FRAME  STOP     			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					FWD CARGO DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P653620B			(CAN) FORWARD CARGO DOOR AFT FRAME STOP CRACKED. REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997013000480	19970130	00480	NE  	1997	1	30	CA960830002      	2	19960802	G	7250		BLADE           								PWA   	JT8   	JT8D7A      	52053	NE  					SHROUD	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			34011	14511				P674612B			(CAN) AS A RESULT OF THE FINDINGS OF AN INSPECTION REQUIRED BY PRATT & WHITNEY SERVICE BULLETIN #5913, THE #2 ENGINE WAS	 TO BE REMOVED DUE TO EXCESSIVE WEAR ON THE TURBINE BLADE SHROUD CROSS NOTCH. THE ENGINE WAS REMOVED FOR REPAIR AND RESU	RFACEING OF THE TURBINE BLADES.									4	F			E2EA				 
1997013000484	19970130	00484	NM  	1997	1	30	CA960909004      	1	19960805	G	2820	384453001	VTO DEVICE      	SIMMONDS    	384453001   	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					FUEL SYS	CORROSION       	W				H				DEACTIVATE SYST/CIRCUITS				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA						6315AB		P653620B			(CAN) #3 FUEL TANK WOULD NOT ACCEPT FUEL.  COCKPIT INSTRUMENT DISCONNECTED AND FUEL ENTERED TANK.  VTO DEVICE REPLACED. 	 REPAIR REPORT INDICATED INTERNAL CORROSION AND GROUND WIRE BROKEN.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997013000485	19970130	00485	EU  	1997	1	30	CA960909006      	1	19960727	G	6330	350A381018	CROSSBEAM       	AEROSP      		AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					ATTACH LUGS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE832365			(CAN) CRACKS FOUND IN MGB SUSPENSION CROSSBEAM END LUGS AS DESCRIBED IN TELEX SB 05.00.29 AND AD 96-155-053(B).						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1997013000491	19970130	00491	NE  	1997	1	30	CA960909014      	2	19960709	G	7530	216035029	ACTUATOR BLEED  								LYC   	ALF502	ALF502R5    	41580	NE  					#3 ENGINE	INOPERATIVE     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) MAINTENANCE FOUND THE BLEED BAND OPENING/CLOSING WAS IMPOSSIBLE TO ADJUST ON THE #3 ENGINE, DUE TO THE INCORRECT A	SSEMBLY OF THE FCU ADJUSTMENT MECHANISM. THE COMPLETE BLEED BAND ACTUATING MECHANISM WAS REMOVED, THE ACTUATOR WAS CLEAN	ED. THE TRIGGER LINE MECHANISM, WHICH WAS INCORRECTLY ASSEMBLED, WAS FITTED WITH A NEW FLARED FITTING. A FLARELESS FITTI	NG WAS PREVIOUSLY INSTALLED. THE ENGINE GROUND RUN SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE.								4	F			E6NE				 
1997013000494	19970130	00494	NE  	1997	1	30	CA960909017      	2	19960708	G	7324	34050	FLOW DIVIDER    								LYC   	ALF502	ALF502R5    	41580	NE  					#2 ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) #2 ENGINE WOULD NOT START AFTER REFUELING STOP. DURING THE START SEQUENCE EXCESSIVE FUEL STARTED DRIPPING FROM THE	 EXHAUST PIPE. THIS FUEL IGNITED CAUSING SOME TORCHING AT THE EXHAUST STACKS. MAINTENANCE FOUND THE FLOW DIVIDER AND CHE	CK VALVE TO BE INCREASING FUEL FLOW. THE VALVE WAS REMOVED AND CLEANED AND CHECKED SERVICEABLE AND THE AIRCRAFT RETURNED	 TO SERVICE.								4	F			E6NE				 
1997013000498	19970130	00498	NE  	1997	1	30	CA960909021      	2	19960709	G	7530	216035029	ACTUATOR BLEED  								LYC   	ALF502	ALF502R5    	41580	NE  					#1 ENGINE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAINTENANCE FOUND #1 ENGINE BLEED BAND ACTUATOR AND THE TRIGGER LINE BLOCKED WITH CARBON. THE BLEED BAND ACTUATOR 	WOULD NOT CLOSE DURING ENGINE OPERATION. MAINTENANCE CLEANED AND PURGED THE BLEED BAND ACTUATOR PLUS ALL TRIGGER LINES A	ND CONTROL MECHANISM OF ALL CARBON PARTICLES. ENGINE GROUND RUN SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.									4	F			E6NE				 
1997020600069	19970206	00069	CE  	1997	2	6	CA960909029      	1	19960823	G	2823	0716102	SELECTOR CUP    	CESSNA      	0716102     	CESSNA	180   	180         	2072602	CE  										FUEL INDICATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4100 								(CAN) THE FUEL SELECTOR EXTENSION SHAFT UP THROUGH THE CONSOLE IS SQURE. OVER A PERIOD OF TIME THE SHAFT HAS WORN A FLAT	 SPOT IN THE BRACKET THAT HOLDS THE FUEL INDICATOR CUP. THIS WAS FOUND TO PREVENT THE PILOT FROM MAKING A QUICK SELECTIO	N BETWEEN TANKS.				1	H	7	1 	3O			NC	5A6     					 
1997020600070	19970206	00070	SW  	1997	2	6	CA960909030      	1	19960823	G	7160	22142	VALVE           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					AIR INTAKE	MISSING RIVETS  	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			421  					L2691136A			(CAN) TWO RIVETS FOUND MISSING AND ALL OTHERS WERE FOUND TO BE LOOSE, ATTACHING BOTH REINFORCING STRIPS.						1	H	7	1 	3O	3	O		A21CE   	E286				 
1997020600071	19970206	00071	EA  	1997	2	6	CA960909032      	1	19960821	G	2926	82960010191	TUBE            			DHAV  	DHC8  	DHC8311     	1386006	EA  										NR 2 HYD RESV	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA			2    								(CAN) IN FLIGHT DEPLETION OF #2 HYDRAULIC RESERVOIR DUE TO CRACKED PRESSURE TRANSDUCER TUBE. MOD 8/2865 ISSUED TO ADDRES	S THIS DEFECT, CHANGED TUBE TO A HOSE.					2	H	7	2 	4T			RT	A13NM   					 
1997020600076	19970206	00076	CE  	1997	2	6	CA960909037      	1	19960813	G	7120	045100336	MOUNT           	CESSNA      	045100336   	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					LWR OLEO CLAMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3525 					L2453615			(CAN) DURING MAINTENANCE A CRACK WAS FOUND AT THE WELD POINT WERE THE TUBE INTERSECTS THE LOWER OLEO STRUT CLAMP. RIGHT 	HAND TUBE WAS ESTIMATED WITH 50 PERCENT GOOD WELD.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997020600081	19970206	00081	NE  	1997	2	6	CA960909042      	2	19960823	G	7260	311196801	GEARSHAFT       								PWA   	120   	PW120       		NE  					ACCESSORY GEARBX	FRACTURED       	W				E				ENGINE SHUTDOWN         				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CA								121229			(CAN) THE OPERATOR REPORTS THAT THE ENGINE EXPERIENCED AN AUTOFEATHER AND SHUTDOWN DURING FLIGHT. THE CAUSE OF THE SHUTD	OWN AND AUTOFEATHER WAS LOSS OF OIL PRESSURE, CAUSED BY A LOSS OF ACCESSORY DRIVE TRAIN INTEGRITY WHICH PROVIDES THE POW	ER TO THE OIL PUMP. THE ANGLE DRIVE (TOWER SHAFT) WAS FOUND TO HAVE FRACTURED IMMEDIATELY BELOW THE UPPER RETAINING NUT.									4	T			E20NE				 
1997020600082	19970206	00082	NE  	1997	2	6	CA960909043      	2	19960823	G	7250	MS969611	CASE            								PWA   	118   	PW118       		NE  					INTERSTAGE CASE	BOLT FAILED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9609 					115294			(CAN) THE ENGINE WAS REMOVED FROM SERVICE AFTER THE OPERATOR NOTED EXTENSIVE POWER TURBINE DAMAGE DURING A ROUTINE WALK 	AROUND. TEARDOWN OF THE ENGINE REVEALED AN INTERSTAGE CASE BOLT HAD FRACTURED LIBERATING THE BOLT HEAD CAUSING DAMAGE TO	 THE 1ST STAGE POWER TURBINE BLADES AND POSSIBLY CONTRIBUTING TO THE DAMAGE ON THE 2ND STAGE PT STATOR ASSEMBLY AND 2ND 	STAGE ROTOR ASSEMBLY.								4	T			E20NE				 
1997020600083	19970206	00083	NE  	1997	2	6	CA960909044      	2	19960822	G	7210	310703301	BEARING         								PWA   	120   	PW120       		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9176 					120626			(CAN) THE REDUCTION GEARBOX WAS FOUND TO HAVE METAL FLAKES OF BEARING MATERIAL ON THE CHIP DETECTOR. THE SOURCE OF THE M	ETAL CONTAMINATION WAS FOUND TO BE THE #15 BEARING WHICH HAD SPALLED BADLY ON THE OUTER RACE WITH SUBSTANTIAL MATERIAL L	OSS. THIS WAS A RESULT OF ELECTRICAL EROSION PITTING, WHICH WAS ALSO FOUND ON THE #19 BEARING.									4	T			E20NE				 
1997020600084	19970206	00084	NE  	1997	2	6	CA960909045      	2	19960819	G	7250	311260201	PT BLADE LP     								PWA   	120   	PW120       		NE  					TURBINE INTERSTG	AIRFOIL FRACTURE	W				E	O			ENGINE SHUTDOWN         	OTHER                   			X			ENGINE FLAMEOUT           			CL	CLIMB          	1			CA			14706	9142 				120656			(CAN) THE AIRCRAFT WAS CLIMBING THROUGH 6,000 FEET WHEN THE PILOT NOTED A DROP IN OIL PRESSURE FOLLOWED BY A LOUD BANG. 	A FIREBALL WAS OBSERVED AND THE ENGINE SUBSEQUENTLY SHUTDOWN. THE CAUSE OF THE IN-FLIGHT SHUTDOWN WAS THE FAILURE OF THE	 #4, #5 AND #6 BEARINGS AND THE MASSIVE DAMAGE SUSTAINED TO THE INTERSTAGE AREA. WHILE THE FAILURE SEQUENCE IS NOT ABSOL	UTELY CLEAR, IT IS THE OPINION OF THE OVERHAULER THAT THE CATASTROPHIC FAILURE ORIGINATED WITH AN EARLIER LOSS OF A SING	LE LOW PRESSURE TURBINE AIRFOIL NEAR THE BLADE PLATFORM DUE TO FATIGUE CRACKING.							4	T			E20NE				 
1997020600085	19970206	00085	NE  	1997	2	6	CA960909046      	2	19960801	G	7313		NOZZLE TIP      								PWA   	118   	PW118       		NE  					FUEL NOZZLE	MISSING         	W				K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		NR	NOT REPORTED   	1			CA			8338 	2662 				115410			(CAN) THE CAUSE OF THE FUEL NOZZLE LIBERATION WAS IMPROPER TORQUING AND/OR LOCKING OF THE FUEL NOZZLE TIP. FOUR OTHER FU	EL NOZZLES WERE INADEQUATELY TORQUED OR LOCKED. THERE WAS EXTENSIVE HOT SECTION BURNING DAMAGE FROM THE IRREGULAR SPRAY 	PATTERN OF THE SEPARATED NOZZLE INCLUDING: BASE METAL BURNING OF BOTH COMBUSTIONS LINERS AND THE SMALL EXIT DUCT, BURNIN	G DAMAGE ON 4 HP TURBINE VANE RING SEGMENTS, BURNING ON THE FRONT FLANGE OF THE TURBINE SUPPORT CASE, BURNING AND OVERHE	ATING OF ALL THE TURBINE BLADES, BURNING ON SEVERAL SHROUD SEGMENTS, BURN THROUGH ON THE VANES OF EVERY TURBINE STATOR A	ND BURN THROUGH ON 1 TURBINE INTERSTAGE CASE STRUT.						4	T			E20NE				 
1997020600116	19970206	00116	NE  	1997	2	6	CA960910041      	2	19960829	G	7261	030137180	VENT PIPE       			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					ENG AFT BEARING	PLUGGED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA			1953 					7139			(CAN) PILOT REPORTED SMOKE COMING FROM ENGINE REAR BEARING AREA.OIL LEAKAGE AT VENT PIPE ATTACH FLANGE. VENT PIPE REMOVE	D AND FOUND PLUGGED WITH CARBON DEPOSITS.  CLEANED AND REINSTALLED.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997020600117	19970206	00117	NE  	1997	2	6	CA960910042      	2	19960828	G	7313		O RINGS         								PWA   	PW120 	PW123       		NE  					FUEL NOZZLES	LEAKING         	W				F				ACTIVATE FIRE EXT.      				O	B		OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			CA			4500 					123263			(CAN) FOLLOWING LANDING, PRIOR TO SHUTDOWN, FUMES WERE SEEN COMING FROM THE #1 ENGINE NACELLE. THE FIRE EXTINGUISHERS WE	RE ACTIVATED. INSPECTION REVEALED FOUR FUEL NOZZLE "O" RINGS DAMAGED. THE "O" RINGS WERE REPLACED AND THE AIRCRAFT RETUR	NED TO SERVICE. THE "O" RINGS HAD BEEN REPLACED 24 HOURS PRIOR TO THIS INCIDENT.									4	T			E20NE				 
1997021300500	19970213	00500	EU  	1997	2	13	CA960916002      	1	19960814	G	6330	350A381018	CROSSBEAM       	AEROSP      		AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	250C  	250C20F     	03013	GL  					M/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE840969			(CAN) CRACKS FOUND IN MGB SUSPENSION CROSSBEAM END LUGS AS DESCRIBED IN TELEX SB 05.00.29 AND AD 96-155-053(B).						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1997021300501	19970213	00501	EU  	1997	2	13	CA960916003      	1	19960814	G	6330	350A381018	CROSSBEAM       	AEROSP      		AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					M/R GR BOX	CRACKED LUGS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE840374			(CAN) CRACKS FOUND IN MGB SUSPENSION CROSSBEAM END LUGS AS DESCRIBED IN TELEX SB 05.00.29 AND AD 96-155-053(B).						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1997021300506	19970213	00506	EU  	1997	2	13	CA960916011      	1	19960812	G	6320	4638302024	BEARING         		4638001001  	BOLKMS	105   	BO105CBS    	5626008	EU  										M/R GR BOX	PEELING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2552 			1224					(CAN) L/H INPUT BEARING ROLLERS PEELING.						1	G	7	2 	3U			NC	H3EU    					 
1997010200307	19970102	00307	SW  	1997	1	2	CA960916018      	1	19960905	G	6200		MAIN ROTOR      			BELL  	206   	206B        	1181511	SW  										M/R	RPM DROOP       	W				B				EMER. DESCENT           				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) AIRCRAFT UNDERGOING PRODUCTION FLIGHT TEST. AFTER PERFORMING EVALUATION OF ROTOR FOR VIBRATION, THE PILOT STARTED 	APPROACH. AS THE PILOT BEGAN TO PULL TORQUE THE ROTOR RPM STARTED TO DROOP. INCIDENT UNDER INVESTIGATION. MORE INFO TO F	OLLOW.				1	G	7	1 	3U				H2SW    					 
1997021300512	19970213	00512	NE  	1997	2	13	CA960916022      	2	19960820	G	7250	MS969601	BOLTS           								PWA   	120   	PW120A      		NE  					COOLING BAFFLE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3286 				120864			(CAN) UPON TEARDOWN OF ENGINE IT WAS REVEALED THAT 11 OF THE 26 RETAINING BOLTS FOR THE COOLING BAFFLE WERE FRACTURED. T	HIS IS AN ON GOING PROBLEM. THE SUBMITTER STATES THAT PRATT & WHITNEY HAS INTRODUCED A NUMBER OF MODS TO DATE WHICH HAS 	NOT ADDRESSED THE PROBLEM.									4	T			E20NE				 
1997021300513	19970213	00513	EA  	1997	2	13	CA960916023      	2	19960830	G	8530	SL16740	VALVE           								LYC   	O360  	IO360A3B6   	41514	EA  					EXH VALVE	SEVERE WEAR     	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			127  					L2086051A			(CAN) DURING TROUBLESHOOTING TO DETERMINE CAUSE OF ROUGH RUNNING ENGINE OIL FILTER WAS REMOVED AND FERROUS METAL PARTICL	ES WERE FOUND. ENGINE WAS DISMANTLED AND #1 AND #3 CYLINDER EXHAUST VALVES WERE FOUND SEVERELY WORN.										3	O			1E10				 
1997021300514	19970213	00514	SW  	1997	2	13	CA960916024      	1	19960829	G	2435	23917	CONNECTOR       	LEARSIEGLER 	23032027    	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					START/GEN	BURNT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				206  		23917		0			(CAN) STARTER-GENERATOR ELECTRIC TERMINAL CONNECTOR BURNT						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997030600683	19970306	00683		1997	3	6	CA960923001      	4	19960923	G	3416	152734	SUPPORT RING    	AEROMECH    	804710HD    															LOCATING SLOT	MODIFIED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						8691					(CAN) SUPPORT RING HAS LOCATING SLOT MODIFIED AS OUTLINED IN SERVICE DIFFICULTY ALERT AV-93-07R1.																			 
1998050100210	19980501	00210	CE  	1998	5	1	CA960923002      	1	19960708	G	5210		VALVE           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					DOOR SEAL	FAILED          	W				B	G	I		EMER. DESCENT           	O2 MASK DEPLOYED        	CABIN DEPRESSURIZATION  		J			WARNING INDICATION        			CR	CRUISE         	1			CA								71760			(CAN) AIRCRAFT EN ROUTE WHEN PRESSURE BEGAN DECREASING AT UNCONTROLLABLE RATE.  OXYGEN MASKS DEPLOYED AND DONNED, AIRCRA	FT LANDED SAFELY AT ALTERNATE SITE.  MAINTENANCE FOUND MOISTURE TRAPPED IN DOOR SEAL AIR SUPPLY LINE.  PURGED AIR USING 	LT ENGINE TO SUPPLY BLEED AIR AND MANUALLY ACTIVATING PLUNGER TO ALLOW AIR TO FLOW FREELY THROUGH SEAL.  AIRCRAFT TT:  2	,277 HOURS.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1998050100211	19980501	00211	CE  	1998	5	1	CA960923003      	1	19960904	G	5210		SEAL            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN DOOR	MALFUNCTIONED   	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA								71760			(CAN) DURING FLIGHT AT 5,000 FEET ASL, FLIGHT CREW NOTICED A GRADUAL LOSS OF CABIN PRESSURIZATION UNTIL THE AIRCRAFT CAB	IN ALTITUDE MATCHED AIRCRAFT ALTITUDE.  AIRCRAFT RETURNED TO BASE UNPRESSURIZED.  AIRCRAFT PRESSURIZATION SYSTEM GROUND 	CHECKED WITHOUT FAULTS.  DOOR SEAL LINE PURGED AS A PRECAUTION.  AIRCRAFT TT:  2,277.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1998050100212	19980501	00212	WP  	1998	5	1	CA960923010      	2	19960911	G	7250	8650821	TIE BOLT NUT    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					NR 2 TURB WHEEL	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22175	6093 				P54054C			(CAN) ON MORNING WALK-AROUND, ENGINE WAS STIFF TO ROTATE.  ENGINE REPLACED.  ENGINE WAS DIS-ASSEMBLED BY FIELD REP AND F	OUND THAT NR 2 TURBINE WHEEL TIE BOLT NUT WAS NOT THE ONE STATED IN THE LATEST SB (331-72-0592, 9/88).  NUT P/N SHOULD H	AVE BEEN 3108066-1 NOT 865082-1.  PART TC:  31,937.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997021300526	19970213	00526	SO  	1997	2	13	CA960923012      	2	19960715	G	8530		PISTON          			CESSNA	140   	140         	2071602	CE  	CONT  	C90   	C9012F      	17009	SO  					#2 CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1153 				418099			(CAN) DURING THE ANNUAL AIRCRAFT INSPECTION THE #2 CYLINDER COMPRESSION CHECK WAS LOW AT 43/80. UPON REMOVAL OF THE CYLI	NDER, THE PISTON WAS FOUND CRACKED IN TWO PLACES ON THE WRIST PIN BOSSES. A NEW CYLINDER AND PISTON WILL BE INSTALLED.					1	H	7	1 	3O	3	O	NC	A768    	E252				 
1997021300536	19970213	00536	NE  	1997	2	13	CA960923025      	2	19960912	G	7210	310709001	BEARING         								PWA   	118   	PW118       		NE  					RED GEARBX NR 19	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12944					115511			(CAN) METAL CONTAMINATION IN REDUCTION GEARBOX FROM SPALLED #19 BEARING.											4	T			E20NE				 
1998050100213	19980501	00213	CE  	1998	5	1	CA960923026      	1	19960619	G	5210		DOOR SEAL       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN	LEAKING         	W				O	B			OTHER                   	EMER. DESCENT           			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PILOT REQUESTED RAPID DESCENT TO 10,000 FEET AND ADVERSION TO ALTERNATE LANDING SITE.  PILOT REPORTED DOOR SEAL LE	AKING AND A SLOW DEPRESSURIZATION.  RUN-UP RT ENGINE AND WITH DOOR OPENED, DEPRESSED THE PLUNGER FOR THE DOOR SEAL VALVE	 AND ALLOWED THE SYSTEM TO PURGE OFF WATER WHICH WAS FOUND IN THE SYSTEM.  AIRCRAFT TT:  2,198 HOURS.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997022000090	19970220	00090	EA  	1997	2	20	CA960924021      	1	19960915	G	7931	356677499502	TRANSMITTER     			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					ENG OIL PRESS	INTERMITTENT    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA								PCE42076			(CAN) DURING FLIGHT THE ENGINE OIL PRESSURE INDICATION DROPPED TO 20 PSI, THERE WAS NO PROPELLER RPM CHANGE AND NO LOW O	IL PRESSURE WARNING LIGHT. A PRECAUTIONARY SHUTDOWN WAS CARRIED OUT AND THE AIRCRAFT RETURNED TO BASE. THE OIL PRESSURE 	WAS CONFRIMED WITH A DIRECT READING GAUGE AND THE OIL PRESSURE TRANSMITTER WAS DETERMINED TO BE THE FAULT. THE UNIT WAS 	REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997041500007	19970415	00007	CE  	1997	4	15	CA960924024      	1	19960901	G	2434	ALV1012S	BRUSHES         	PRESTOLITE  	ALT9510R    	CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ALTERNATOR	HIGH RESISTANCE 	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA			50   					228430R	890661		(CAN) AIRCRAFT ALTERNATORS WOULD NOT BALANCE. INSPECTION REVEALED A HIGH FIELD RESISTANCE. THE BRUSHES WERE FOUND TO HAV	E A RESISTANCE OF 15-30 OHMS. REPLACEMENT BRUSHES SOLVED THE PROBLEM. SUBMITTER STATES THAT THIS IS THE THIRD SUCH OCCUR	RENCE.				1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
1997121800401	19971218	00401	EA  	1997	12	18	CA960924028      	2	19960916	G	7310	35040284	FUEL HOSE       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE CYLINDER	RUPTURED        	W				D	E			RETURN TO BLOCK         	ENGINE SHUTDOWN         			A	B	K	FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	TX	TAXI/GRND HDL  	1			CA								L608248			(CAN) WHILE TAXIING, PILOT NOTICED FLAMES COMING FROM LEFT ENGINE. THE ENGINE WAS SHUT DONW AND FLAMES WENT OUT. ENGINE 	COWLING AREA WAS FOAMED AS A PRECAUTIONARY MEASURE WHEN THE COWLS WERE REMOVED A FLEX FUEL LINE FROM THE FUEL DISTRIBUTO	R ON THE TOP OF THE ENGINE DOWN BETWEEN #1 ABD #3 CYLINDERS TO THE FUEL SERVO WAS RUPTURED. ALSO THE #3 IGNITION LEAD WA	S OFF AND LAYING BY THE SPARK PLUG. A CHECK OF THE OTHER FLEX HOSES IN BOTH ENGINE COMPARTMENTS REVEALED DATE CODES RANG	ING FROM 1976 TO 1990 AND THE RUPTURED HOSE DID NOT HAVE ANY IDENTIFICATION TAG.		1	L	7	2 	3O	3	O		1A10    	1E4				 
1997022000095	19970220	00095	NE  	1997	2	20	CA960924033      	2	19960905	G	7260	625926	FLANGE          			BOEING	747   	747128      	1384894	NM  	PWA   	JT9   	JT9D7A      	52054	NE  					ANGLE GEARBOX	CRACKED         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA								662439			(CAN) DURING FLIGHT THE #4 ENGINE OIL CONSUMPTION WAS OBSERVED. ENGINE WAS OPERATED AT REDUCED THRUST UNTIL OIL PRESSURE	 INDICATION WAS OBSERVED AND OIL QUANTITY AT 0.7 GALLONS.PRECAUTIONARY SHUTDOWN WAS CARRIED OUT. POST FLIGHT I NSPECTION	 FOUND A FLANGE CRACKED AT THE OIL RETURN LINE TO THE ANGLE GEARBOX. THE FLANGE AND "O" RING WERE REPLACED AND THE AIRCR	AFT RETURNED TO SERVICE.			2	L	7	4 	4F	4	F		A20WE   	E20EA				 
1997022000099	19970220	00099	SO  	1997	2	20	CA960924040      	2	19960901	G	7322	103237	CARBURETOR      		MS3SPA      	CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300C       	17022	SO  					FLOAT	MIS MODIFIED    	W				A				UNSCHED LANDING         				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		CR	CRUISE         	1			CA						4011672		21806D3C			(CAN) MODIFICATION OF CARBURETOR SINGLE PIECE VENTURI AND METAL FLOAT INSTALLATION WAS DONE IMPROPERLY. THE SPRING WHICH	 BRINGS DOWN THE NEEDLE WHEN THE FLOAT DROPS AS THE FUEL LEVEL LOWERS WAS INSTALLED TO THE FRONT INSTEAD OF FROM THE LEF	T OR RIGHT SIDE. IN THIS CONFIGURATION THE FLOAT IS JAMMED IN THE UP POSITION AND FUEL IS PREVENTED FROM ENTERING THE CA	RBURETOR.			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1997041500008	19970415	00008	SO  	1997	4	15	CA960924041      	1	19960916	G	5753	95504000	BRACKET         	PIPER       	95504000    	PIPER 	PA34  	PA34200T    	7103406	SO  										FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5845 								(CAN) WHILE CARRYING OUT AWD 96-10-03, BRACKET 95504-000 WAS FOUND CRACKED AT THE 3 TOP NOTCHES. REPLACED WITH NEW PART.						1	L	7	2 	3O				A7SO    					 
1997022000100	19970220	00100	EA  	1997	2	20	CA960924042      	2	19960923	G	7314		PUMP            								PWA   	PT6   	PT6A27      	52043	EA  					ENG FUEL	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								41774			(CAN) FUEL PUMP AND COUPLING SPLINE WEAR, WITH THE COUPLING SPINNING FREELY. AIRCRAFT RETURNED TO SERVICE AFTER FUEL PUM	P REPLACEMENT.										4	T			E4EA				 
1997022000101	19970220	00101	NE  	1997	2	20	CA960924043      	2	19960916	G	7210		PLUG            								PWA   	119   	PW119B      		NE  					REDUCTION GEARBX	DAMAGED         	W				E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		NR	NOT REPORTED   	1			CA			4613 					116012			(CAN) THE #1 ENGINE WAS SHUTDOWN FOLLOWING THE LOSS OF MAIN OIL PRESSURE, WHICH WAS SUBSEQUENTLY FOUND TO BE CAUSED BY D	AMAGED THREADS ON A PLUG ON THE REDUCTION GEARBOX.										4	T			E20NE				 
1997022000107	19970220	00107		1997	2	20	CA960927002      	4	19960917	G	3421	25861376	GYRO            			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					RH HSI	FAULTY          	W				K				NONE                    				P			NO WARNING INDICATION     			CR	CRUISE         	1			CA				111  				16227			(CAN) IN LEVEL FLIGHT, THE R/H HSI INTERMITENTLY INDICATED 10 DEGREES NOSE DOWN WITH NO FLAGS SHOWING. SHORTLY AFTER THE	 UNIT WAS INSTALLED, IT TOOK 20 MINUTES TO SPOOL UP ON ONE LEG BUT THE FAULT COULD NOT BE DUPLICATED. THE VERTICAL GYRO 	WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T		1A17    	E297				 
1997031300259	19970313	00259	CE  	1997	3	13	CA961002006      	1	19960829	G	2435	8462751	STARTER         			CESSNA	185   	A185F       	2072821	CE  										COILS	SHORTED         	W				O				OTHER                   				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		TX	TAXI/GRND HDL  	1			CA			25   	20   		10009517					(CAN) STARTER FIELD COILS LOOSE ON POLE SHOES RUBBED ON THE THROUGH BOLTS CREATING A DEAD HIGH AMPERAGE SHORT RESULTING 	IN BOTH MASTER SOLENOID AND STARTER SOLENOID CONTACT PLATES WELDING TO TERMINALS - A VERY DANGEROUS AND FIRE CONDITION -	 SUSPECT INSUFFICIENT CLEARANCE IN DESIGN AND/OR MANUFACTURE BETWEEN COIL AND THROUGH BOLTS.				1	H	7	1 	3O				3A24    					 
1997031300260	19970313	00260	EA  	1997	3	13	CA961002007      	1	19960918	G	2750		FORK END        	DHAV        	C6CW10831   	DHAV  	DHC6  	DHC6        	2802606	EA  										FLAP ROD	MIS MANUFACTURED	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) THE NEW FLAP ROD COULD NOT BE INSTALLED AS THE FORK END WAS TOO NARROW TO ACCEPT THE BEARING OF THE ATTACHING ROD 	BETWEEN THE FORKS. NO EVIDENCE OF DAMAGE. ROD PURCHASED NEW FROM BRAD.					1	H	7	2 	3T			RT	A9EA    					 
1997031300261	19970313	00261	EA  	1997	3	13	CA961002009      	1	19960918	G	2750		FORK END        	DHAV        	C6CW10831   	DHAV  	DHC6  	DHC6        	2802606	EA  										FLAP ROD	MIS MANUFACTURED	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) NEW FLAP ROD WOULD NOT BE INSTALLED BECAUSE THE FORK END OF THE ROD WAS TOO NARROW TO ACCEPT THE BEARING OF THE AT	TACHING ROD. NO DAMAGE FOUND ON ROD. SUBMITTER CONCERNED THAT SOME MAY TRY TO FORCE ROD INTO PLACE.					1	H	7	2 	3T			RT	A9EA    					 
1997031300267	19970313	00267	NE  	1997	3	13	CA961002016      	2	19960920	G	7210	311657901	PINION GEAR     								PWA   	120   	PW120       		NE  					RED GR BOX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8987 					121159			(CAN) ROUTINE FILTER AND CHIP DETECTOR CHECKS FOUND THE REDUCTION GEARBOX WAS GENERATING ALLOY STEEL FLAKES. THE ENGINE 	WAS SENT TO R&O FOR INVESTIGATION. THE SOURCE OF THE METAL FLAKES WAS FOUND TO BE FROM SEVERAL SPALLED AREAS ON THE R/H 	SECOND STAGE PINION GEAR.									4	T			E20NE				 
1997031800006	19970318	00006	EA  	1997	3	18	CA961003011      	2	19960926	G	8530	62388	CAP VALVE STEM  			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	#1 CYLINDER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			202  					L982551A	830489		(CAN) ENGINE WAS OVERHAULED 15 AUGUST 1994. ANNUAL 100 HOUR INSPECTION JULY 1995 FOUND #1 CYLINDER COMPRESSION LOW (50 P	SI), CYLINDER WAS REMOVED, REPAIRED AND REINSTALLED UNDER WARRANTY BY OVERHAULER. NEXT 103.3 HOUR ANNUAL INSPECTION FOUN	D FOUR (4) ROCKER BOX COVERS LEAKING, #1 CYLINDER INTAKE CAP VALVE STEM MISSING AND METAL CONTAMINATION IN THE OIL FILTE	R.			1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
1998050100215	19980501	00215	NE  	1998	5	1	CA961007004      	2	19960909	G	7261	6029T27G03	OIL JET         			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					NR 1 OIL JET	OBSTRUCTED      	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				1680 				295106			(CAN) DURING GROUND RUN FOLLOWING ENGINE INSTALLATION, IT WAS OBSERVED THAT NR 2 ENGINE OIL PRESSURE WAS HIGHER THAN NOR	MAL (60 VICE 45 PSI).  ENGINE REMOVED AND A PIECE OF O-RING WAS FOUND OBSTRUCTING NR 1 OIL JET.  ENGINE INSTALLED AND GR	OUND RUN NORMAL.				2	G	7	2 	4U	4	U		1H15    	1E3				 
1997031300279	19970313	00279	SO  	1997	3	13	CA961007005      	2	19960919	G	8520		PISTON ROD      			CESSNA	310   	310         	2074202	CE  	CONT  	O470  	O470B       	17026	SO  					BEARING HOUSING	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	K	E	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	VIBRATION/BUFFET          	CR	CRUISE         	1			CA								506956BR			(CAN) ROD FAILURE AT CRANKSHAFT, ROD BROKE IN HALF. ROD EXITED THROUGH TOP OF CRANKCASE REAR LEFT SIDE.						1	L	7	2 	3O	3	O	RT	3A10    	E273				 
1999043000062	19990430	00062	CE  	1999	4	30	CA961007013      	1	19960805	G	6320	8681942	SUN GEAR        			MTSBSI	MU2   	MU2B36      	5780412	CE  										TRANSMISSION	FRACTURED       	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			10490	1635 				P20062C			(CAN) PILOT NOTED SEVERE VIBRATION WITH NO WARNING.  PRIOR TO SHUTDOWN, THE TORQUE WENT TO ZERO.  AIRCRAFT RETURNED OK. 	 INSPECTION REVEALED THE PLANETARY PIN P/N 868051-1 WAS CHAFED BY THE PLANETARY GEAR P/N 358268-1 WHICH IN TURN ABNORMAL	LY LOADED THE SUN GEAR WHICH SUBSEQUENTLY FAILED.				1	H	7	2 	3T			RT	A10SW   					 
1998020500609	19980205	00609	CE  	1998	2	5	CA961007018      	1	19961002	G	3252	0543004	ARM             			CESSNA	182   	182         	2072702	CE  										SHIMMY DAMPENER	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA			4329 								(CAN) AFTER LANDING SHIMMY DEVELOPED EITHER CAUSING ARM TO BREAK OR ARM WAS ALREADY BROKEN. STEERING FOUND OK AND FLUID 	LEVEL IN SHIMMY DAMPENER AND OLEO WAS CORRECT.					1	H	7	1 	3O			NT	3A13    					 
1997031300287	19970313	00287	NE  	1997	3	13	CA961007026      	2	19960920	G	7210	310703301	BEARING         								PWA   	120   	PW120A      		NE  					RED GEARBX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21127	17248		10A293		120141			(CAN) THE REDUCTION GEARBOX WAS FOUND TO BE GENERATING METAL ANALYSED TO BE M50. THE PRINCIPAL SOURCE OF THE METAL CONTA	MINATION WAS FOUND TO BE #15 BEARING WHICH HAD SPALLED BADLY ON THE OUTER RACE WITH SUBSTANTIAL MATERIAL LOSS. THIS APPE	ARED TO BE THE RESULT OF ELECTRICAL EROSION PITTING, WHICH WAS ALSO FOUND ON #19 BEARING.									4	T			E20NE				 
1997031300288	19970313	00288	NE  	1997	3	13	CA961007027      	2	19960927	G	7210	310703301	BEARING         								PWA   	118   	PW118       		NE  					RED GEARBX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13843	5639 				115472			(CAN) REDUCTION GEARBOX (RGB) SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED THE RGB WAS MAKING METAL. TH	E CAUSE OF THE REDUCTION GEARBOX MAKING METAL WAS SPALLED OF THE #15 BEARING INNER RACE.										4	T			E20NE				 
1997031300289	19970313	00289	NE  	1997	3	13	CA961007028      	2	19960926	G	7313		NOZZLE          								PWA   	120   	PW120       		NE  					NR 2 ENG NR 9	CRACKED BOSS    	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA								120058			(CAN) LOSS OF POWER ON #2 ENGINE DURING TAKEOFF. GROUND INSPECTION FOUND THE #9 FUEL NOZZLE BOSS CRACKED AND THE GASKET 	DISTRESSED.										4	T			E20NE				 
1997031300290	19970313	00290	NE  	1997	3	13	CA961007029      	2	19960830	G	7322		FUEL CONTRL     								PWA   	PW120 	PW124B      		NE  					#2 ENGINE	BROKEN FLYWEIGHT	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA								124108			(CAN) DURING CLIMB THE #2 ENGINE LOST POWER. A RELIGHT ATTEMPT PROVED UNSUCCESSFUL. INVESTIGATION FOUND ONE OF THE MAIN 	FUEL CONTROL FLYWEIGHTS HAD BROKEN OFF. UNIT IS BEING RETURNED FOR INVESTIGATION.										4	T			E2ONE				 
1997031300291	19970313	00291	NE  	1997	3	13	CA961007030      	2	19960924	G	7260		SPUR GEAR       								PWA   	118   	PW118       		NE  					NR 2 ENG GEARBX	FAILED          	W				O				OTHER                   				X			ENGINE FLAMEOUT           			CL	CLIMB          	1			CA			20701	10725				115119			(CAN) JUST PRIOR TO COMPLETION OF AIRCRAFT CLIMBOUT, WITHOUT WARNING THE #2 ENGINE SHUTDOWN. POST FLIGHT INSPECTION CONF	IRMED AS ACCESSORY DRIVE SPUR GEAR DISTRESS.										4	T			E20NE				 
1997032000002	19970320	00002	SW  	1997	3	20	CA961009010      	2	19961002	G	7210	3024780	GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COMB GRBOX	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16526	236  							(CAN) WHILE CONDUCTING A 150 HOUR INSPECTION BRASS PARTICLES WERE FOUND IN THE COMBINING GEARBOX. C-BOX WAS REPLACED.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1997032000003	19970320	00003	NE  	1997	3	20	CA961009011      	2	19960926	G	7210	310600201	INPUT PISTON    								PWA   	PW121 	PW121       	52124	NE  					RED GR BOX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6995 					121043			(CAN) ENGINE SENT FOR ROUTINE OVERHAUL. MAINTENANCE TAG STATED REDUCTION GEARBOX WAS MAKING METAL. THE REDUCTION GEARBOX	 WAS INSPECTED AND THE PROBLEM WAS CAUSED BY A SPALLED INPUT PISTON.										4	T			E20NE				 
1997032000004	19970320	00004	EA  	1997	3	20	CA961011001      	2	19961001	G	7261	MS9388017	O-RING          	PWA         	303589      	DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					#1 ENG OIL XSFR	LEAKING         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA			1083 	1083 				40403			(CAN) LOW OIL PRESSURE ON #1 ENGINE FORCED AN INFLIGHT SHUTDOWN. POST FLIGHT INSPECTION FOUND AN OIL LEAK AT THE OIL PRE	SSURE TRANSFER TUBE. THE "O" RING WAS FOUND PINCHED AND LEAKING.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997032000005	19970320	00005	SO  	1997	3	20	CA961011002      	2	19960927	G	7322	666916KIT	FLOAT           	MARVELSCHEB 	MA45A1048931	CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	CARBURETOR	BADLY WORN      	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			750  					1918508R	785682		(CAN) PILOT COMPLAINED OF INTERMITTENT FUEL LEAK FROM CARBURETOR. DISASSEMBLY OF CARBURETOR REVEALED FLOAT HINGE BADLY W	ORN ALLOWING CONTACT OF FLOAT WITH SIDES OF FLOAT CHAMBER RESULTING IN SEVERE WEAR ON SIDES OF METAL FLOATS. FUEL VALVE 	RETAINER CLIP WORN INTO FUEL STEM (30 PERCENT). FLOAT LEVEL ADJUSTMENT TAB WORN APPROXIMATELY 50 PERCENT AT POINT OF CON	TACT WITH FUEL VALVE RESULTING IN INCREASED FLOAT LEVEL, TO POINT WHERE VALVE NO LONGER CLOSED. WEAR SEEMS EXCESSIVE FOR	 TIME ON COMPONENT.		1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
1997032000006	19970320	00006	SO  	1997	3	20	CA961011003      	2	19960930	G	8550	539937	OIL SUMP        			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	FLANGE	CRACKED         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA								803599L4	621309		(CAN) OIL LEAK AT OIL SUMP. RETORQUE OF SUMP BOLTS MADE LEAK WORSE. REMOVAL OF OIL SUMP REVEALED CRACK AT MOUNTING FLANG	E. THE AIRCRAFT IS USED TO TOW GLIDERS OFF GRASS STRIP AND THIS NO DOUBT CONTRIBUTED TO THIS FAILURE.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P880	 
1997032000008	19970320	00008	SO  	1997	3	20	CA961016002      	2	19960816	G	8550	530763A1	OIL SUMP        			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  					FWD DRAIN PLUG	CRACKED         	W				K				NONE                    				K	O		FLUID LOSS                	OTHER                     		IN	INSP/MAINT     	1			CA				576  				12403D6A			(CAN) DURING ANNUAL INSPECTION AN OIL LEAK REPORTED BY THE OWNER LED TO INSPECTION OF THE OIL SUMP. EIGHT SMALL CRACKS W	ERE FOUND FROM THE FORWARD DRAIN PLUG, ONLY TWO WERE LEAKING. THE CRACKS HAD ORIGINATED INSIDE THE SUMP AND WERE CAUSED 	BY CORROSION PITTING.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1999043000063	19990430	00063	EU  	1999	4	30	CA961016004      	1	19961010	G	3260	42196010201	SPEED SWITCH    			AMD   	FALC20	FALCON200   	2730150	EU  										MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PREMATURE FAILURE OF THIS PART NUMBER SPEED SWITCH HAS HAPPENED A NUMBER OF TIMES.  REPORTS SHOW THE COMPONENTS AR	E OUT OF CALIBRATION, AND THE CONTACTS ARE DIRTY.					2	L	7	2 	4F			RT	A7EU    					 
1997032000014	19970320	00014	NE  	1997	3	20	CA961016011      	2	19961004	G	7210	310924401	BEARING         								PWA   	120   	PW120       		NE  					RED GEARBX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13967	1538 				120324			(CAN) THE REDUCTION GEARBOX WAS FOUND TO BE MAKING METAL WHICH WAS IDENTIFIED TO BE M50. THE REDUCTION GEARBOX WAS DISMA	NTLED AND INSPECTED AND THE SOURCE OF THE METAL CONTAMINATION WAS SPALLING OF THE #15 BEARING.										4	T			E20NE				 
1997032000015	19970320	00015	NE  	1997	3	20	CA961016012      	2	19961007	G	7210	310924401	BEARING         								PWA   	PW121 	PW121       	52124	NE  					REDUCTION GEARBX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10947	8830 				120916			(CAN) THE REDUCTION GEARBOX WAS SENT FOR INVESTIGATION AND REPAIR AFTER M50 METAL WAS FOUND IN A SOAP SAMPLE. INVESTIGAT	ION FOUND THE SOURCE OF THE METAL WAS SPALLING OF THE #15 BEARING.										4	T			E20NE				 
1997032000016	19970320	00016	NE  	1997	3	20	CA961016013      	2	19961004	G	7250	311260201	BLADE           								PWA   	120   	PW120       		NE  					LP TURBINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17610	6098 				120562			(CAN) ROUTINE HOT SECTION INSPECTION (HSI) FOUND THE ENGINE HAD SUFFERED A FRACTURE OF ONE LP PRESSURE TURBINE BLADE. TH	E FRACTURE OCCURRED AT 60 PERCENT OF THE BLADE HEIGHT AND CAUSED SECONDARY DAMAGE TO THE BALANCE OF THE LP BLADES AND TO	 THE OTHER TURBINE COMPONENTS.									4	T			E20NE				 
1997032000017	19970320	00017	EA  	1997	3	20	CA961018001      	1	19961008	G	5520	C6TEM101529	HINGE FITTING   	DHAV        	C6TE100111  	DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					LT ELEV	HOLE ELONGATED  	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) PILOT INDICATED INTERMITTENT VIBRATION AT LOWER SPEEDS. UPON INSPECTION, THE LEFT ELEVATOR WAS FOUND TO HAVE EXCES	SIVE PLAY AT OUTBOARD HINGE. BOTH FITTING AND HINGE ARM WERE REPLACED AS THE BOLT HOLE WAS ELONGATED.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1999043000064	19990430	00064	EU  	1999	4	30	CA961018003      	1	19961009	G	2435	03601018	BEARING         	LEARSIEGLER 	23075008    	AMD   	FALC20	FALCON200   	2730150	EU  										START/GENERATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				48   							(CAN) UNITS NOT MEETING MANUFACTURER'S RECOMMENDED TBO'S DUE TO PREMATURE BEARING  FAILURE.  IN MOST CASES, THE PROBLEM 	IS AIR CREW SNAG, A RUMBLING FROM THE STARTER/GENERATOR.  THIS FOUND ON TWO DIFFERENT GENERATORS.					2	L	7	2 	4F			RT	A7EU    					 
1997010200316	19970102	00316	NM  	1997	1	2	CA961018005      	1	19960620	G	3320	16405130	CONNECTOR       			DHAV  	DHC8  	DHC8301     		NM  										OVERHEAD BIN	BURNT           	W				E				ENGINE SHUTDOWN         				B	M		SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 		TX	TAXI/GRND HDL  	1			CA											(CAN) AT START OF POST ENGINE START CHECKS, THE CREW NOTICED AN ELECTRICAL BURNING SMELL, FOLLOWED BY SMOKE FROM BEHIND 	THE COPILOT SEAT. ONCE THE ENGINES SHUTDOWN, DC POWER REMOVED AND THE PASSENGER DOOR OPENED THE SMOKE SUBSIDED. OVERHEAD	 BIN CONNECTOR HAD BECOME SEVERELY OVERHEATED (OVER SEAT 1CD). INVESTIGATION UNDERWAY AT DHI AND BRAD. ALSO WIRE P/N 1-6	40523-0.			2	H	7	2 	4T			RT	A13NM   					 
1998020500440	19980205	00440	SO  	1998	2	5	CA961018006      	1	19961003	G	2730	AN36	BOLT            		4030700     	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					ELEV CABLE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								52694			(CAN) ELEVATOR CABLE ATTACHMENT BOLT FOUND WORN WHERE THE CABLE ATTACHES TO THE ELEVATOR BELLCRANK. BOLT HAD TO BE REMOV	ED TO SEE WEAR.					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
1998020500441	19980205	00441	SO  	1998	2	5	CA961018007      	1	19961003	G	2730	4926502	BEARING         		4030700     	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					PUSHPULL ROD	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			969  					52694			(CAN) ELEVATOR BELLCRANK FOUND WORN WHERE PUSH/PULL ROD IS ATTACHED. AD HAD BEEN COMPLIED WITH 969 HOURS PREVIOUS WITH N	O PROBLEM FOUND. RECOMMEND CHANGE AT 1000 HOURS.					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
1998020500442	19980205	00442	NE  	1998	2	5	CA961018008      	1	19961018	G	5330		SKIN            			CONAER	LA4   	LA4         	5110302	NE  	LYC   	O360  	O360A1A     	41514	EA  					INTERIOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1565 					L894236A			(CAN) INTERIOR OF FUSELAGE SKIN AND BULKHEADS FOUND CORRODED WHERE GLUE IS USED TO SECURE INSULATION TO COMPONENTS INSID	E THE CABIN.					1	H	7	1 	3O	3	O		1A13    	E286				 
1998020500443	19980205	00443	SO  	1998	2	5	CA961018009      	1	19960927	G	5740	6210200	SUPPORT BRACKET 			PIPER 	PA28  	PA28140     	7102802	SO  										LT RT AIL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5190 								(CAN) LEFT AND RIGHT AILERON BELLCRANK SUPPORT BRACKETS FOUND CRACKED AT FORWARD ATTACHMENT BOLT HOLES. RIGHT SIDE P/N 6	2102-01.					1	L	7	1 	3O				2A13    					 
1997032000027	19970320	00027	NE  	1997	3	20	CA961018028      	2	19961009	G	7250	310410401	PT BLADE        								PWA   	118   	PW118       		NE  					2ND STAGE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14861	4107 				115241			(CAN) TURBOMACHINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED 2ND STAGE PT BLADE DAMAGE.  DISASSE	MBLY FOUND THE CAUSE OF THE PT BLADE DAMAGE ON THE TURBOMACHINE WAS A FRACTURE OF ONE, 2ND STAGE PT BLADE HALF WAY DO WN	 THE AIRFOIL AND THE RESULTING LOSS OF HALF OF THE AIRFOIL.									4	T			E20NE				 
1999043000068	19990430	00068	GL  	1999	4	30	CA961021005      	2	19960710	G	7250	6886407	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					1ST STAGE	SEPARATED       	W				O				OTHER                   				M	E		OVER TEMP                 	VIBRATION/BUFFET          		LD	LANDING        	1			CA			415  			CAT33356		CAE833904			(CAN) WHILE COMING IN TO LAND, THE PILOT NOTICED A SUDDEN INCREASE IN TOT AND VIBRATION LEVELS.  LANDED IMMEDIATELY, NO 	PROBLEMS.  TURBINE INSPECTION REVEALED ONE 1ST STAGE BLADE HAD SEPARATED FROM THE TURBINE DISC AT APPROXIMATELY .150 INC	HES FROM BLADE ROOT.  NO VISUAL INDICATION OF TIP RUB, EXCESSIVE TEMPERATURE, OR CORROSION.  LAB ANALYSIS INDICATED A SU	SPECTED HIGH CYCLE, LOW STRESS FATIGUE FROM A DESIGN CONTOUR CHANGE IN TRAILING EDGE OF BLADES.			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997032000119	19970320	00119	SW  	1997	3	20	CA961022013      	1	19961012	G	3213	54530051	YOKE            	SWRNGN      		SWRNGN	SA226 	SA226*      		SW  										MAIN GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						PAL32325					(CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BE	EN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGU	E AS SOME NEW YOKES HAVE BEEN RECEIVED WITH CRACKS.				2	L	7	2 	4T			RT	A56W    					 
1997032000122	19970320	00122	SO  	1997	3	20	CA961023003      	2	19961115	G	8530	SA501867	LOCK TAB        								CONT  	O360  	IO360D      	17025	SO  					ROCKER STUD NUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								553135D			(CAN) DURING INSPECTION WHILE BENDING THE TAB THAT SECURES THE ROCKER STUD NUT THE TAB CRACKED/BROKE.											3	O			E1CE				 
1998020500445	19980205	00445	CE  	1998	2	5	CA961025006      	1	19961010	G	2916	511700712	SIGHT TUBE      	CESSNA      	511700728   	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					HYD IND	MELTED          	W				A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CL	CLIMB          	1			CA								519153			(CAN) THE NOSE GEAR FAILED TO LOCK IN THE UP POSITION AFTER TAKEOFF PREVENTING THE HYDRAULIC SYSTEM FROM CYCLING TO 'OPE	N CENTRE' OPERATION. CONTINUED HYDRAULIC PRESSURE RAISED FLUID TEMPERATURE TO MELT PLASTIC RESERVOIR SIGHT TUBE AND SUBS	EQUENT LOSS OF HYDRAULIC FLUID. INITIAL FAILURE TO LOCK IN UP POSITION WAS LIKELY CAUSED BY INCORRECT ATTACHMENT OF LECT	RO TUG TOWING STRAP, RESULTING IN SLIGHT DEFORMATION OF UPLOCK ARM ON NOSE GEAR STRUT.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1998020500446	19980205	00446	CE  	1998	2	5	CA961025007      	1	19961010	G	3230	249A4TT2	CHECK VALVE     			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3372 					519153			(CAN) DURING GROUND RETRACTION TESTS, THE GEAR FAILED TO RETRACT. HYDRAULIC PRESSURE CLIMBED SUFFICIENTLY TO TRIP PNEUMA	TIC BLOWDOWN SYSTEM. PROBLEM TRACED TO CHECK VALVE WHICH ALLOWED HYDRAULIC PRESSURE TO BE APPLIED TO GEAR UP, GEAR DOWN 	AND PNEUMATIC BLOWDOWN SYSTEM SIMULTANEOUSLY. DISASSEMBLY OF VALVE REVEALED CONTAMINATION WHICH APPEARED TO BE A SMALL P	IECE OF O-RING MATERIAL.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997032700084	19970327	00084	EA  	1997	3	27	CA961028002      	1	19961021	G	2750	19501100	BODY            	SYNCRO      	SKA1943A    	DHAV  	DHC6  	DHC6        	2802606	EA  										FLAP SELECTOR	MIS MANUFACTUED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) THIRD BATCH (5 EACH) OF FLAP SELECTOR VALVE BODIES REJECTED BECAUSE THE THREADS IN THE PORTS (A) ARE EXCESSIVELY L	ONG CAUSING 'O' RINGS TO REST ON THE LAST THREAD RATHER THAN THE SMOOTH WALL OF THE BORE. THIS RESULTS IN EXTERNAL LEAKA	GE OF HYDRAULIC FLUID AND CONTAMINATION OF THE COCKPIT AREA ANYTIME SELECTION IS MADE. BRAD NOTIFIED. CORRECTIVE ACTION 	PENDING.			1	H	7	2 	3T			RT	A9EA    					 
1998020500451	19980205	00451	CE  	1998	2	5	CA961105003      	1	19961028	G	2820	1009200272	FUEL LINE       			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RT WING	BLOCKED         	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			K			FLUID LOSS                			CL	CLIMB          	1			CA								PCE25641			(CAN) DURING CLIMB PILOT REPORTED FUEL LEAK AT THE TRAILING EDGE OF THE RIGHT HAND WING. RH ENGINE SHUT DOWN AND SINGLE 	ENGINE LANDING CARRIED OUT. EVENTUALLY FOUND THAT WHEN LINE WAS REMOVED FOR OBSTRUCTION TEST, THE LINE WAS FOUND BLOCKED	. DURING MANUFACTURING PROCESS THE LINES HAD BEEN WELDED TO ANOTHER LINE WITH NO HOLES FOR THE FUEL FLOW. MANUFACTURER N	OTIFIED. THIS IS A MULTIPLE LINE WITH 3 SECTIONS.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
1997032700104	19970327	00104	EA  	1997	3	27	CA961112010      	1	19961101	G	3040	SYLZ50157	CONTROLLER      	BARBERCOL   		DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					LT WINDSHIELD	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA						1194B		PCE42076			(CAN) DURING FLIGHT THE LEFT HAND WINDSHIELD HEAT SYSTEM CIRCUIT BREAKER POPPED. INSPECTION FOUND THAT THE WINDSHIELD HE	AT CONTROLLER FOR THE LEFT SIDE WAS NOT CONTROLLING THE TIME ON AND OFF, THUS THE WINDSHIELD WAS BEING HEATED LONGER THA	N RECOMMENDED.				1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997041500016	19970415	00016	NM  	1997	4	15	CA961112011      	1	19961106	G	2131	10251831	CONTROLLER      	ALLIED SIGNA		BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					CABIN PRESS	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			CA						125539		P653620B			(CAN) DURING DESCENT THE FLIGHT CREW NOTICED THE PRESSURIZATION WOULD NOT INITIALLY RESPOND TO THE CHANGING ALTITUDE, TH	EN IT WOULD CAUSE A RAPID CABIN PRESSURE CHANGE TO CATCH UP WITH THE AIRCRAFT ALTITUDE. POST FLIGHT TROUBLESHOOTING LED 	TO THE CHANGE OF THE AUTOMATIC PRESSURE CONTROLLER AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1998040200021	19980402	00021	EU  	1998	4	2	CA961112012      	1	19960207	G	4950	011469914	VALVE           	SUNDSTRAND  	011469914   	AMD   	FALC20	FALCON200   	2730150	EU  										APU BLEED	FAILED          	W				A	B	I		UNSCHED LANDING         	EMER. DESCENT           	CABIN DEPRESSURIZATION  		G			MULTIPLE FAILURE          			CL	CLIMB          	1			CA						071					(CAN) CABIN PRESSURE STARTED TO CLIMB AFTER PASSING THROUGH 18,000 FEET.  MAINTENANCE TROUBLESHOOTING REVEALED SWITCH ON	 APU BLEED VALVE (199H) FAILED IN THE OPEN POSITION.  TEAR DOWN REPORT REQUESTED FROM FALCON JET FOR DEFECTIVE VALVE.					2	L	7	2 	4F			RT	A7EU    					 
1998041700420	19980417	00420	WP  	1998	4	17	CA961112025      	2	19961017	G	7314	307085057	FUEL PUMP       	GARRTT      		BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					NR 1 ENG	FAILED          	W				O				OTHER                   				X			ENGINE FLAMEOUT           			TX	TAXI/GRND HDL  	1			CA			4220 			P91317		P91317			(CAN) ON START OF NR 1 ENGINE, THE ITT REACHED 600 DEGREES CENTIGRADE AND THE ENGINE AUTOMATICALLY SHUT-DOWN.  MAINTENAN	CE REVEALED THE CAUSE WAS FAILURE OF THE HIGH PRESSURE PUMP.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
1997040200015	19970402	00015	EA  	1997	4	2	CA961112031      	1	19961029	G	2435	215T50901010	DUCT INLET      		215T5091018 	CNDAIR	CL215 	CL2151A10   		EA  										START/GEN COOL	SPLIT           	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			51   								(CAN) WELD AT COOLING DUCT ASSEMBLY HAS NO METAL PENETRATION. SKIN JOINT SPLIT AND IT CHAFED ON THE OIL RETURN LINE WHIC	H PASSED BETWEEN THIS DUCT ASSEMBLY, AND THE COMPRESSOR OF THE ENGINE. THE CHAFING WAS DEEP ENOUGH TO HAVE TO REPLACE TH	E LINE. VISUAL INSPECTION OF ANOTHER AIRCRAFT SHOWS A SIMILAR PROBLEM WILL OCCUR. CANADAIR HAS BEEN ADVISED.				2	H	7	2 	4R				A14EA   					 
1997041500018	19970415	00018		1997	4	15	CA961112040      	1	19960730	G	7810	115024003	DIFFUSER        		113063008   						LYC   	T53   	T5313B      	41549	NE  					COMBUSTOR EXH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LE07605			(CAN) EXHAUST DIFFUSER RECEIVED FOR INSPECTION, 4" X 1" METAL BREAK-OFF AND 2" CIRCUMFERENTIAL CRACK FOUND ON FORWARD FA	CE OF THE INNER CONE. CAUSE OF CRACK AND BREAK IS UNKNOWN.										4	U			E17EA				 
1998020500460	19980205	00460	SO  	1998	2	5	CA961115013      	1	19961106	G	2720	6342005	PEDAL BAR       		6345919     	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					LT HAND	CRACKED         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			9201 					L4764427A			(CAN) LEFT RUDDER PEDAL BAR CRACKED IN FLIGHT. AIRCRAFT LANDED FROM RIGHT SEAT. RUDDER AND BRAKES LOST TO LEFT SEAT. PIP	ER SERVICE LETTER 671 COVERS THE PROBLEM.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997041500046	19970415	00046	EA  	1997	4	15	CA961118015      	1	19961110	G	2530	AE0405A00	FAN             			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					GALLEY EXHAUST	OVERLOAD        	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			CA			1122 					GEE807385			(CAN) DIRECT CURRENT EMERGENCY BUS CAUTION LIGHT ON AT FL180 ON CLIMB OUT. AT SAME TIME CIRCUIT BREAKER C5 GALLEY FAN PO	PPED AND WOULD NOT RESET. CIRCUIT BREAKER R7 POPPED AS A RESULT OF CIRCUIT BREAKER C5 GALLEY EXHAUST FAN FAULT. FAN REPL	ACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997041500048	19970415	00048	EA  	1997	4	15	CA961120002      	2	19961215	G	8530		OIL RING        			CESSNA	172   	172         	2072402	CE  	LYC   	O320  	O320H2AD    	41508	EA  					#4 CYLINDER	FAILED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA								RL489676TA			(CAN) LOSS OF ENGINE POWER IN FLIGHT. ENGINE CONTINUED TO OPERATE AND FLIGHT CONTINUED TO DESTINATION. POST FLIGHT INSPE	CTION FOUND #4 CYLINDER OIL RING FAILED.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997042200007	19970422	00007	SW  	1997	4	22	CA961120010      	1	19960913	G	2821	206005	FUEL FILTER     			BELL  	206   	206B        	1181511	SW  										OUTLET PORT	UNMODIFIED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) MODIFICATION OF OUTLET BLEED PORT NOT INSTALLED. THIS CONDITION COULD LEAD TO ENGINE FLAME OUT (REF: BELL ASB 206-	86-34).					1	G	7	1 	3U				H2SW    					 
1997042200009	19970422	00009	NE  	1997	4	22	CA961120012      	2	19961106	G	7230	310454601	BEARING         								PWA   	120   	PW120A      		NE  					HP SHAFT NR 4	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11372					121127			(CAN) ENGINE SENT FOR INVESTIGATION AND REPAIR AFTER OPERATOR REPORTED HP ROTOR LOCKUP.  IT WAS ALSO REPORTED THAT THERE	 WAS NO FILTER BYPASS AND THE ENGINE HAD BEEN INVOLVED IN A LIGHTNING STRIKE.  DISASSEMBLY FOUND THE CAUSE OF THE HP ROT	OR LOCKUP WAS A CATASTROPHIC FAILURE OF THE NR 4 BEARING.  THE FAILURE OF THE NR 4 BEARING APPEARS TO BE THE RESULT OF E	ITHER INSUFFICIENT TORQUING OF THE NR 4 BEARING RETAINING NUT AT THE LAST BUILD, OR THE FAILURE OF THE NR 4 BEARING RETA	INING NUT CUPWASHER TO PREVENT THE NR 4 BEARING RETAINING NUT FROM ROTATING.							4	T			E20NE				 
1997042200012	19970422	00012	NM  	1997	4	22	CA961125005      	1	19961115	G	2720		CONTROL         	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  										RUDDER	LOCKED          	W		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) AT V1 SPEED #1 ALTERNATOR FELL OFF LINE, AFTER ROTATION, SELECTED GEAR UP, DURING RETRACTION, RUDDER CONTROL LOCKE	D UP, (BOTH RUDDER AND PEDALS).  AT 100 FEET, AIRSPEED 120 TO 130 KNOTS, EMERGENCY DECLARED AND GEAR SELECTED DOWN. DURI	NG EXTENSION RUDDER CONTROL WAS RESTORED. ALL OTHER INDICATIONS NORMAL. WEATHER REPORTED AS LOW TEMP WITH RAIN DRIZZLE. 	OPERATOR PROVIDED TROUBLESHOOTING INFO BY MANUFACTURER. COMPLETE RUDDER SYSTEM FROM FRONT TO BACK OF AIRCRAFT WAS INSPEC	TED WITH NOTHING FOUND. MOISTURE MAY HAVE CAUSED FREEZING PROBLEMS. TO LOCK RUDDER SYSTEM AS REPORTED, RUDDER QUADRANT(S	) AND/OR RUDDER PEDALS NEED TO BE JAMMED. EVEN WITH HYDRAULIC PROBLEM, RUDDER PEDALS WOULD STILL BE MOVEABLE.	2	H	7	2 	4T			RT	A13NM   					 
1997042200016	19970422	00016	WP  	1997	4	22	CA961125009      	1	19961112	G	2530	CA167072	ELECT RECEPTACLE			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					GALLEY OVEN	SHORTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								P657239D			(CAN) FLIGHT ATTENDANT REPORT SMOKE & SPARKS COMING FROM GALLEY OVEN AT POSITION #19. MAINTENANCE ACTION INVOLVED INSTAL	LING NEW RECEPTACLE AND OVEN CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997042200017	19970422	00017	EA  	1997	4	22	CA961125010      	1	19961107	G	2760	270003	PCU             	CNDAIR      		CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					LT HAND SPOILER	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			1048 					GEE807389			(CAN) FLIGHT SPOILER FAULT MESSAGE. CIRCUIT BREAKER RESET, MESSAGE STILL ON. LEFT HAND FLIGHT SPOILER REMAINED WHITE AFT	ER GROUND LIFT DUMP TEST. REQUIRED MAINTENANCE ACTION (27-60-421) CARRIED OUT. LEFT HAND SPOILER RE-RIGGED DUE TO ASYMME	TRY FAULT AND LEFT HAND INBOARD FLIGHT SPOILER POWER CONTROL UNIT (PCU) CHANGED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997042200018	19970422	00018	EA  	1997	4	22	CA961125012      	1	19961113	G	2750	855D1005	BPSU            	CNDAIR      		CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					RIGHT HAND FLAP	FAILED          	W				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			CA			4267 					807317			(CAN) ON TAKEOFF THE CREW REPORTED FLAP FAIL AMBER CAUTION MESSAGE. RIGHT HAND BRAKE AND POSITION SENSOR UNIT CHANGED AS	 PER MM 27-51-10. SB'S 601R-27-043 (WATER INGRESS) AND -045 HARNESS REPLACEMENT, MAY APPLY. ALSO SB 601R-27-056 REPLACEM	ENT OF -5 BPSU WITH A -7 APPLIES.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997042200019	19970422	00019	SW  	1997	4	22	CA961125015      	1	19961013	G	8010	MS25089C5	SWITCH          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					STARTER SWITCH	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE800419BA			(CAN) SWITCH WOULD NOT ENGAGE STARTER WHEN DEPRESSED. STARTER BUTTON ENGAGED WHEN MOVED FROM SIDE TO SIDE.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997042200020	19970422	00020	CE  	1997	4	22	CA961126002      	1	19961118	G	7120	12510104	BRACKET         			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE MT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9067 					286169R	792737		(CAN) CRACK WAS FOUND DURING A VISUAL INSPECTION OF THE ENGINE COMPARTMENT WHILE PERFORMING AN ENGINE CHANGE.						1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P47GL	 
1997042200021	19970422	00021	EU  	1997	4	22	CA961126003      	1	19961118	G	5414		SKIN            	BNORM       		BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								RL815340			(CAN) SKIN ON THE NACELLE AFT CLOSURE FOUND CRACKED AT AREA DIRECTLY ABOVE THE LANDING GEAR FAIRING. THE REAR NACELLE BU	LKHEAD PASSES THROUGH THE CRACKED PLATE.					1	H	7	2 	3O	3	O		A17EU   	E295				 
1997042200022	19970422	00022	EU  	1997	4	22	CA961126004      	1	19961118	G	5522	NB31233	ELEVATOR        	BNORM       		BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					RIGHT SIDE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								RL815340			(CAN) RIGHT SIDE ELEVATOR AT 44 INCHES INBOARD OF TIP SMOKING RIVETS NOTED WHICH LED TO DISCOVERY OF A CRACK. FURTHER IN	VESTIGATION NOTED THAT PILOTS HAD BEEN VERBALLY REPORTING SOME VIBRATION.					1	H	7	2 	3O	3	O		A17EU   	E295				 
1997042200023	19970422	00023	NM  	1997	4	22	CA961128001      	1	19961120	G	7931	APT761000100DW	TRANSMITTER     			DHAV  	DHC8  	DHC8301     		NM  	PWA   	PW120 	PW123       		NE  					OIL SYSTEM	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) #2 ENGINE OIL PRESSURE DROPPED TO ZERO ON CLIMBOUT. THERE WAS NO WARNING LIGHT INDICATION. AIRCRAFT RETURNED TO BA	SE. POST FLIGHT INSPECTION FOUND THE OIL PRESSURE TRANSMITTER FAULTY. THE OIL PRESSURE TRANSMITTER WAS REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200024	19970422	00024	NM  	1997	4	22	CA961128002      	1	19961120	G	3060	7826891	BRUSH BLOCK     	HAMSTD      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  	HAMSTD	14SF	14SF7       	NE  	NR2 PROPELLER	BURNT           	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA						900742		120226	881010		(CAN) RIGHT HAND TRANSFORMER RECTIFIER UNIT (TRU) FAILED. CIRCUIT BREAKER WOULD NOT RESET. POST FLIGHT INSPECTION FOUND 	THE #2 PROP DE-ICE BRUSH BLOCK BURNT CAUSING THE R/H "B" PHASE CIRCUIT BREAKER TO "POP". BRUSH BLOCK REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
1997042200025	19970422	00025	NM  	1997	4	22	CA961128003      	1	19961114	G	2160	7787272	PACK VALVE      	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					NR 2 BLEED	JAMMED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA								120854			(CAN) BLEED AIR SMELL IN CABIN AFTER TAKEOFF, FOLLOWED BY LAVATORY SMOKE ALARM AND THE #2 BLEED HOT CAUTION LIGHT IN FUL	L HOT POSITION. SMOKE AND SMELL FROM FULL HOT AIR IN THE AIR CONDITIONING SYSTEM. PACK VALVE REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200026	19970422	00026	NM  	1997	4	22	CA961128004      	1	19961120	G	2910	82970010391	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LH MLG AFT DOOR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								120165			(CAN) HYDRAULIC LEAK NOTED FROM LEFT HAND MAIN LANDING GEAR AFT DOOR HYDRAULIC LINE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200027	19970422	00027	NE  	1997	4	22	CA961128005      	3	19961120	G	6112	86553115	BLADE           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  	HAMSTD	14SF	14SF15      	NE  	BLADE HEATER	BURNED HOLE     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								123126	901008		(CAN) PROPELLER DE-ICE UNSERVICEABLE. #2 PROPELLER BLADE FOUND WITH A HOLE BURNED IN THE DE-ICE BOOT BY A SHORT CIRCUIT 	IN THE DE-ICE HEATER.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
1997042200028	19970422	00028	NE  	1997	4	22	CA961128006      	2	19961120	G	7230	230098401	BEARING CAGE    								LYC   	ALF502	ALF502R5    	41580	NE  					#3 BEARING	BREAKING APART  	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LF05629A			(CAN) #2 ENGINE OIL FILTER IMPENDING BY-PASS BUTTON EXTENDED. #2 FULL FLOW CHIP DETECTOR FOUND TO BE METAL CONTAMINATED.	 METAL ANALYSIS FOUND TO BE #3 BEARING CAGE MATERIAL. ON DISASSEMBLY #3 BEARING CAGE WAS FOUND TO BE BREAKING APART.										4	F			E6NE				 
1997042200029	19970422	00029	NM  	1997	4	22	CA961128008      	1	19961127	G	2420	10014B22	SENSOR WIRE     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					AC GEN CKT	BROKEN          	W				H				DEACTIVATE SYST/CIRCUITS				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA								120840			(CAN) AC GENERATOR HOT CAUTION LIGHT ILLUMINATED IN FLIGHT. AC GENERATOR CIRCUIT BREAKER PULLED. SNAG FOUND TO BE BROKEN	 SENSOR WIRE AT PLUG 2421J4, PIN 11.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200030	19970422	00030	NM  	1997	4	22	CA961128012      	1	19961120	G	6220	A1551	SPACER          			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					SPINDLE ASSEMBLY	CORRODED        	W				K				NONE                    				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			CA			837  					L1662739A			(CAN) PILOT REPORTED A CYCLIC STICK AND MAIN ROTOR VIBRATION. IT WAS FOUND THAT THE SPINDLE BEARINGS WERE ROUGH. AFTER D	ISASSEMBLY THE INNER SPACER (P/N A155-1) WAS FOUND TO BE SEVERELY CORRODED AND PITTED. THE PART LOOKED TO HAVE BAD MACHI	NING. THE BEARINGS BECAME ROUGH DUE TO THE METAL OFF THE SPACER.				1	G	7	1 	3O	3	O		H10WE   	E274				 
1997042200031	19970422	00031	SO  	1997	4	22	CA961128014      	1	19961121	G	7712	650086	TORQUEMETER     	HAMSTD      	6850209     	LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	TORQUE PICKUP	LOOSE           	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA				3450 		650086		550195	235867		(CAN) IN CRUISE NR 3 ENGINE TORQUE INDICATION FAILED.  POST FLIGHT MAINTENANCE INSPECTION FOUND THE TORQUE PICKUP TO BE 	RUBBING ON THE TORQUE SHAFT AND SOME TORQUEMETER ATTACHMENT NUTS MISSING AT THE REDUCTION GEARBOX ATTACH POINT.  AIRCRAF	T FERRIED FOR ENGINE CHANGE.				2	H	7	4 	4T	4	T		A1SO    	E282	6	C	P906	 
1997042200032	19970422	00032	WP  	1997	4	22	CA961128024      	1	19961122	G	7810	9063239	CLAMP BAND      			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13      	03004	GL  					LT EXH	WORN            	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			M			OVER TEMP                 			CR	CRUISE         	1			CA								500589			(CAN) LEFT HAND ZONE 1 FIRE WARNING ILLUMINATED. ENGINE SECURED AND FIRE BOTTLES DISCHARGED. AIRCRAFT LANDED SAFELY. MAI	NTENANCE CHECK FOUND LEFT HAND EXHAUST PIPE UNIVERSAL COUPLING HAD SEPARATED ALLOWING EXHAUST GASES TO ENTER ENGINE NACE	LLE. COUPLING FAILED DUE TO WEAR OF FLANGE AND CLAMP BAND. COUPLING REPLACED.				2	L	7	2 	4R	4	T		6A6     	E282				 
1997042200033	19970422	00033	NE  	1997	4	22	CA961128026      	2	19961121	G	7210	3100662301	BEARING         								PWA   	118   	PW118       		NE  					RED GEARBX NR 18	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15250	4993 				115219			(CAN) METAL ON THE CHIP DETECTOR CAUSED THE REDUCTION GEARBOX TO BE REMOVED AND SENT FOR INVESTIGATION AND REPAIR. INSPE	CTION OF THE RGB FOUND THE #18 BEARING TO HAVE A SEVERELY SPALLED REAR INNER HALF RACE. MATERIAL LOSS EXTENDED AROUND MO	ST OF THE CIRCUMFERENCE. SUBSTANTIAL MATERIAL LOSS OCCURRED AND SECONDARY DAMAGE WAS SUSTAINED BY SEVERAL OTHER 2ND STAG	E BEARINGS.								4	T			E20NE				 
1997042200034	19970422	00034	EA  	1997	4	22	CA961128027      	1	19961119	G	3260		SENSOR          			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					NOSE	OUT OF ADJUST   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			4391 					807195			(CAN) UNABLE TO RETRACT NOSE GEAR. FOUND NOSE GEAR SENSOR OUT OF ADJUST.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997042200035	19970422	00035		1997	4	22	CA961128030      	4	19961117	G	2350	G699306	ATC CNTRL PANEL 			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					COCKPIT	ELECT SHORT     	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								P656860D			(CAN) AIRCRAFT RETURNED TO GATE DUE TO AIR TRAFFIC CONTROL PANEL  ELECTRICAL SHORT AND CIRCUIT BREAKER ATC-1 POPPED. ATC	 CONTROL PANEL REPLACED AND SYSTEM CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997042200036	19970422	00036	WP  	1997	4	22	CA961128031      	1	19961117	G	2560	375321399	LANYARD BRACKET 			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					GALLEY DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P657459D			(CAN) GALLEY DOOR CHUTE PACK CAME ADRIFT. UNABLE TO INSTALL DUE TO BROKEN LANYARD ATTACHMENT BRACKET. MAINTENANCE INSTAL	LED NEW BRACKET CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997042200037	19970422	00037	NE  	1997	4	22	CA961128032      	2	19961102	G	7322	7733333	FUEL CONTRL UNIT	HAMSTD      							PWA   	JT9   	JT9D7R4D    	52054	NE  					#1 ENGINE	FAULTY          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								709606			(CAN) 15 MINUTES INTO FLIGHT THERE WAS NO POWER RESPONSE FROM THE LEFT HAND THROTTLE (#1 ENGINE). AIRCRAFT RETURNED TO P	OINT OF DEPARTURE. POST FLIGHT INSPECTION FOUND #1 ENGINE FUEL CONTROL UNIT FAULTY. FCU REPLACED. GROUND RUN CARRIED OUT	 AND CHECKED SERVICEABLE.									4	F			E3NE				 
1997042200038	19970422	00038	EA  	1997	4	22	CA961128033      	1	19961121	G	3230		BRACKET         			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					NOSE	MISALIGNED      	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			788  					GEE807399			(CAN) GEAR UNSAFE ON RETRACTION. NOSE WHEEL REMAINED DOWN AND WOULD NOT RETRACT. FOUND NOSE GEAR PROXIMITY SENSOR BRACKE	T MISALIGNED ON OLEO EXTEND.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997042200039	19970422	00039	CE  	1997	4	22	CA961203001      	1	19961106	G	3260	MS243311	SWITCH          	MITSUELECT  		MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					NLG SWITCH	BROKEN WIRE     	W				L				ABORTED APPROACH        				J	N		WARNING INDICATION        	FALSE WARNING             		AP	APPROACH       	1			CA								P20276C			(CAN) DURING APPROACH THE PILOT COULD NOT GET AN INDICATION OF THE NOSE GEAR DOWN AND LOCKED. EMERGENCY EXTENSION PERFOR	MED AND THE AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND A BROKEN WIRE WHERE THE WIRES ENTER A SEALED SWITCH. THE SWITCH WA	S REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
1997042200040	19970422	00040	NE  	1997	4	22	CA961203003      	2	19961104	G	7200		ENGINE          			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					#2 ENGINE	OIL BYPASS LITE 	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J			WARNING INDICATION        			CR	CRUISE         	1			CA								665763			(CAN) DURING CLIMB #2 ENGINE LOW OIL PRESSURE/FILTER BYPASS ILLUMINATED. POST FLIGHT INSPECTION OF THE OIL FILTER FOUND 	NO FAULT. THE ENGINE WAS GROUND RUN SERVICEABLE. ITEM DEFERRED PER MEL TO NITE STOP FOR FURTHER INVESTIGATION.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997042200041	19970422	00041	SW  	1997	4	22	CA961203008      	1	19960925	G	6420	204011769001	BEARING RACE    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					T/R TRUNNION	ROUGH           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			289  					CAE895063			(CAN) DURING INSPECTION OF TAIL ROTOR, A ROUGH, RATCHETING FEELING WAS NOTICED. FURTHER INSPECTION REVEALED THAT THE INN	ER BEARING RACE WAS CRACKED.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997042200042	19970422	00042	SW  	1997	4	22	CA961203010      	1	19961125	G	6230	206010441001	BEARING         			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					SWASHPLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3220 					CAE895715			(CAN) UNUSUAL PLAY IN SWASHPLATE. INSPECTION FOUND TEFLON ON BEARINGS WORN AWAY.						1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
1997042200043	19970422	00043	NE  	1997	4	22	CA961203012      	2	19961125	G	7260	602070009	BEARING         	DOWTY       		BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5352    	54509	NE  					ACCESSORY GEARBX	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			AP	APPROACH       	1			CA				568  		DRG106164		7149			(CAN) FORWARD TUNNEL SHAFT BEARING FAILED CAUSING FORWARD END CAP OF SHAFT TO DISCONNECT FROM INPUT SHAFT. SUSPECT BEARI	NG FAILURE ATTRIBUTED T OIL STARVATION; PLUGGED JET AND/OR PUMP FAILURE. GEARBOX SHIPPED FOR TEARDOWN.					2	L	7	2 	3T	4	T		A24EU   	E297				 
1997042200044	19970422	00044	SO  	1997	4	22	CA961203014      	1	19961119	G	3231		RODS            	EMB         		EMB   	110   	EMB110P1    	3260122	SO  										NLG DOORS	MIS ADJUSTED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF GEAR SELECTED UP. GEAR INSTRANSIT LIGHT REMAINED ON. INSPECTION FOUND THAT THE NOSE LANDING GEAR DOOR W	ERE ADJUSTED TOO TIGHT AND WITH THE AIR LOADS IN FLIGHT WOULD PULL GEAR DOWN ENOUGH TO BREAK THE UP SWITCH GIVING THE IN	TRANSIT LIGHT. DOOR RODS ADJUSTED.				1	L	7	2 	4T				A21SO   					 
1997042200045	19970422	00045	NM  	1997	4	22	CA961203015      	1	19961116	G	5280	85420056103	HINGE ARM       	DHAV        	85420047001 	DHAV  	DHC8  	DHC8301     		NM  	PWA   	PW120 	PW123       		NE  					RIGHT MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16589					123045			(CAN) DURING WALK AROUND, THE FORWARD HINGE ARM ON THE RIGHT HAND MAIN LANDING GEAR FORWARD GEAR DOOR WAS FOUND BROKEN O	FF. GEAR DOOR ALSO HAD COMPOSITE DAMAGE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200046	19970422	00046	NM  	1997	4	22	CA961203016      	1	19961118	G	5280	83231046001	BUSHING         	DHAV        	85420014009 	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					MLG DOOR ARM	MISSING         	W				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			CA								120388			(CAN) ON A WALK AROUND IT WAS NOTICED THAT THE FORWARD GEAR DOOR FOR THE RIGHT HAND MAIN LANDING GEAR WAS JAMMED TIGHT A	GAINST THE DRAG STRUT. INSPECTION FOUND THAT THE THREADED BUSHING WHICH SECURES THE FORWARD DOOR ACTUATOR CONNECTING BOL	T ROD NAS6204-13H TO FORWARD DOOR REAR HINGE HAD LOOSENED AND FALLEN OFF. DURING FLIGHT THE CONNECTING ROD BOLT HAD MIGR	ATED OUT HALFWAY AND WHEN GEAR WAS EXTENDED, THE BOLT CONTACTED AND DAMAGED THE NACELLE STRUCTURE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200047	19970422	00047	NM  	1997	4	22	CA961203017      	1	19961122	G	5280	83231046001	BUSHING         	DHAV        	85420014009 	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					RT MLG DOOR ARM	MISSING         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								120817			(CAN) AFTER TAKEOFF CREW NOTICED THAT FORWARD GEAR DOOR FOR THE RIGHT HAND MAIN LANDING GEAR WAS NOT CLOSED, AND WAS FLA	PPING AROUND. ALL GEAR INDICATIONS NORMAL. BOLT NAS6204-13H AND THREADED BUSHING WHICH CONNECTS FORWARD DOOR ACTUATOR CO	NNECTING ROD WAS MISSING AND FORWARD HINGE ARM WAS FOUND BENT.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200048	19970422	00048	NE  	1997	4	22	CA961203018      	2	19961125	G	7314	311169301	SPUR GEAR       								PWA   	118   	PW118       		NE  					FUEL PUMP DRIVE	DAMAGED TEETH   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			20705	10728				115119			(CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED AN INFLIGHT SHUTDOWN. INSPECTION FOUND TH	E CAUSE OF THE INFLIGHT SHUTDOWN WAS A FAILURE OF THE MAIN ACCESSORY DRIVE GEAR AND THE FUEL PUMP DRIVE GEAR. THE MAIN A	CCESSORY DRIVE (SPUR) GEAR HAD DAMAGE TO ALL ITS TEETH WITH THREE TEETH BROKEN OFF, CAUSING LOSS OF DRIVE TO THE FUEL PU	MP RESULTING IN ENGINE FUEL STARVATION AND INFLIGHT SHUTDOWN.								4	T			E20NE				 
1997042200049	19970422	00049	EA  	1997	4	22	CA961203019      	2	19961112	G	7414	4373	MAGNETO         	SLICK       		PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					LH MAGNETO	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				391  		94110070		L2371751A			(CAN) ENGINE SHUTDOWN WITHOUT INCIDENT. ON NEXT START BOTH THE RIGHT HAND AND LEFT HAND MAGNETOS WERE DEAD, NO SPARK.						1	H	7	2 	3O	3	O		A31EU   	1E10				 
1997042200050	19970422	00050	SW  	1997	4	22	CA961203020      	1	19961121	G	6230	206010455103	CAP             			BELL  	206   	206B        	1181511	SW  										SWASHPLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15266	5363 							(CAN) DURING A SWASHPLATE INSPECTION, GREASE WAS FOUND AROUND THE TOP SEAL. COVER REMOVED AND SEAL AND CAP REPLACED.						1	G	7	1 	3U				H2SW    					 
1997042200051	19970422	00051	SW  	1997	4	22	CA961203021      	1	19961119	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L        	1181522	SW  										UPPER DECK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RESTRAINT BEARING FELT LOOSE. FOUND SWAGED BEARING LOOSE IN RESTRAINT.						1	G	7	1 	3U				H2SW    					 
1997042200052	19970422	00052	EA  	1997	4	22	CA961205001      	2	19961126	G	7310	3011849	TUBE ASSEMBLY   			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					FUEL BYPASS	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA								PCE50447			(CAN) THE PILOT NOTICED A SUBSTANTIAL INCREASE IN FUEL FLOW PRIOR TO LANDING. POST FLIGHT INSPECTION FOUND THE FUEL SYST	EM BYPASS LINE CRACKED AT THE SLEEVE, WHICH IS SILVER SOLDERED ONTO THE END OF THE STAINLESS STEEL LINE. THE SUBMITTER S	TATES THIS SAME FAULT HAS OCCURRED THREE OTHER TIMES ON COMPANY AIRCRAFT. THE PILOT DID NOT SHUTDOWN THE ENGINE, BUT STA	TED IF THE FAULT HAD OCCURRED ON A LONGER TRIP OR IN CRUISE HE WOULD HAVE HAD TO DO AN INFLIGHT SHUTDOWN.			1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997042200053	19970422	00053	NM  	1997	4	22	CA961205002      	1	19961128	G	2770	NAS130431	BOLT            	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ELEVATOR	RUSTED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18721					120305			(CAN) BOLTS HOLDING RUBBER BUMPERS ON ELEVATOR GUST LOCKS ARE SEVERELY CORRODED. COULD CAUSE ELEVATOR LOCK UP IF BOLTS S	EPARATED. FLEET INSPECTION UNDERWAY. MOD SB 8-55-14 TO BE INCORPORATED AS POSSIBLE FIX. (MORE RESEARCH NEEDS TO BE DONE 	ON THIS SB AS FIX.)				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200054	19970422	00054	NM  	1997	4	22	CA961205003      	1	19961129	G	2770	NAS130431	BOLT            	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ELEVATOR	RUSTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16218					120226			(CAN) BOLTS HOLDING RUBBER BUMPERS ON ELEVATOR GUST LOCKS ARE SEVERELY CORRODED. COULD CAUSE ELEVATOR LOCK UP IF BOLTS S	EPARATED. FLEET INSPECTION SO FAR HAS FOUND 7 AIRCRAFT WITH PROBLEM. SB 8-55-14 BEING INCORPORATED AS POSSIBLE FIX.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200055	19970422	00055	NM  	1997	4	22	CA961205004      	1	19961129	G	2770	NAS130431	BOLTS           	DHAV        		DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW120 	PW123       		NE  					ELEVATOR	RUSTED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25321					123138			(CAN) BOLTS THAT HOLD RUBBER BUMPERS TO ELEVATOR GUST LOCK FOUND SEVERELY CORRODED. COULD CAUSE ELEVATOR LOCK UP IF BOLT	 SEPARATED. FLEET INSPECTION HAS FOUND 7 OF THESE SO FAR. SB 8-55-14 BEING INCORPORATED AND MAY BE FIX.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042200056	19970422	00056	NM  	1997	4	22	CA961205005      	1	19961203	G	2770	NAS130431	BOLT            	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ELEVATOR	RUSTED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19069					PCE120304			(CAN) BOLTS THAT HOLD ELEVATOR GUST LOCK ASSEMBLY RUBBER BUMPERS FOUND RUSTED 1/2 WAY THROUGH. FAILURE OF THIS BOLT COUL	D CAUSE THE SPRING LOADED GUST LOCK PIN TO EXTEND LOCKING THE ELEVATOR. SEVEN RUSTED BOLTS FOUND SO FAR IN FLEET.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800001	19970428	00001	NM  	1997	4	28	CA961205006      	1	19961203	G	2770	NAS130431	BOLTS           	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ELEVATOR	RUSTED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			16470					120165			(CAN) BOLTS THAT HOLD ELEVATOR GUST LOCK RUBBERS FOUND TO BE SEVERELY RUSTED. FAILURE OF THESE BOLTS COULD CAUSE THE SPR	ING LOADED PIN TO EXTEND CAUSING THE ELEVATORS TO LOC UP. OPERATOR HAD FOUND THIS A FEW DAYS PREVIOUS ON ANOTHER AIRCRAF	T. FLEET CAMPAIGN HAS FOUND 7 FAILURES SO FAR.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800002	19970428	00002	NM  	1997	4	28	CA961205007      	1	19961203	G	2770	NAS130431	BOLTS           	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ELEVATOR	RUSTED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			25639					120056			(CAN) BOLTS THAT HOLD GUST LOCK RUBBER BUMPERS FOUND SEVERELY RUSTED. FAILURE OF THIS BOLT COULD CAUSE THE SPRING LOADED	 GUST LOCK PIN TO EXTEND LOCKING UP THE ELEVATORS. OPERATOR HAD FOUND THIS SAME PROBLEM A FEW DAYS PREVIOUS ON ANOTHER A	IRCRAFT. FLEET CHECK HAS FOUND 7 CASES SO FAR.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800003	19970428	00003	NM  	1997	4	28	CA961205008      	1	19961203	G	2760		WIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					SPOILER CLUTCH	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								120840			(CAN) TOP LEFT HAND ROLL SPOILER CLUTCH SWITCH WIRE FOUND BROKEN.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800004	19970428	00004	EA  	1997	4	28	CA961205009      	1	19961203	G	2760		WIRE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					NR 2 SPOILER JAM	SHORTED         	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA								123132			(CAN) PFCS SPLR 2 "PUSH OFF" ILLUMINATED IN FLIGHT. FOUND #2 SPOILER JAM MICRO SWITCH WIRES BROKEN AND SHORTING TO GROUN	D.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800005	19970428	00005	NM  	1997	4	28	CA961205010      	1	19961203	G	7500		O-RINGS         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					#2 BLEED AIR	LEAKING         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			10508					120083			(CAN) SMOKE IN THE CABIN FROM #2 ENGINE BLEED AIR. FOUND NL O-RINGS LEAKING.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800006	19970428	00006	CE  	1997	4	28	CA961205011      	1	19961128	G	3232	AA5C	GEAR DOOR       	MITSUELECT  		MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					CLUTCH	FROZEN          	W				L				ABORTED APPROACH        				J	O		WARNING INDICATION        	OTHER                     		AP	APPROACH       	1			CA			507  					P20276C			(CAN) ICE CONTAMINATION IN THE GEAR DOOR ACTUATOR CAUSED THE PILOT ABORT THE APPROACH. SUBSEQUENT CYCLING OF THE GEAR PR	ODUCED A GEAR DOWN AND LOCKED CONDITION WHEREBY THE AIRCRAFT LANDED SAFELY.					1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
1997042800007	19970428	00007	SO  	1997	4	28	CA961205012      	1	19961130	G	5210	487494	SPRING          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					DOOR LATCH	BROKEN          	W				K				NONE                    				J	O		WARNING INDICATION        	OTHER                     		AP	APPROACH       	1			CA			13967					L726561A			(CAN) DURING APPROACH THE PILOT RECEIVED THE DOOR AJAR WARNING LIGHT. AIRCRAFT LANDED SAFELY AND MAINTENANCE FOUND A BRO	KEN SPRING WHERE THE SPRING ATTACHES TO THE DOORS INTERNAL SAFETY LATCH. SPRING WAS REPLACED AND THE DOOR RIGGED AND RET	URNED TO SERVICE.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997042800008	19970428	00008	WP  	1997	4	28	CA961205014      	1	19961129	G	3241	46AB	FUSE BODY       	PNEUDRAULICS	61912       	DOUG  	DC10  	DC1030      	3023501	WP  	GE    	CF6   	CF650C2     	30018	NE  					NR 3 HYD SYS	CRACKED         	W				H	O			DEACTIVATE SYST/CIRCUITS	OTHER                   			K			FLUID LOSS                			LD	LANDING        	1			CA						46AB		517762			(CAN) ON LANDING AUTO BRAKE SYSTEM ACTIVATED AND #3 HYDRAULIC SYSTEM LOST FLUID IMMEDIATELY  AIRCRAFT TOWED TO GATE  MAI	NTENANCE FOUND BODY OF HYDRAULIC FUSE CRACKED  FUSE REPLACED AND #3 HYDRAULIC SYSTEM SERVICED.					2	L	7	3 	4F	4	F		A22WE   	E23EA				 
1997042800009	19970428	00009	SO  	1997	4	28	CA961205015      	1	19961106	G	2140	B3040	BURNER CAN      	JANITROL    	B3040       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					HEATER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1500 					L186061A			(CAN) WHILE CHECKING AD 82-07-02 A CRACK WAS DETECTED. SUBMITTER INSTALLED A NEW HEATER.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997042800010	19970428	00010	SO  	1997	4	28	CA961205016      	1	19961203	G	5312	5269400	BULKHEAD        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					LT RT WING FITTN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11417					L186061A			(CAN) ON INSPECTION A 1.5 INCH CRACK WAS FOUND ON BOTH THE LEFT AND RIGHT SIDE WHERE THE FRONT FITTINGS ATTACH TO THE WI	NG.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997042800011	19970428	00011	SO  	1997	4	28	CA961205017      	1	19961203	G	5751		SPAR            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11417					L186061A			(CAN) WHILE CARRYING OUT AD 96-21-03 A CRACK WAS FOUND UNDER THE HINGE. SUBMITTER INSTALLED A NEW AILERON SPAR.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997042800012	19970428	00012	SO  	1997	4	28	CA961205018      	1	19961203	G	5751	2570400	BEARINGS        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11417					L186061A			(CAN) WHILE WORKING ON THE AILERON SYSTEM WEAR WAS NOTED IN THE LEFT AILERON OUTBOARD BEARING. SIMILAR PLAY WAS NOTED ON	 THE RIGHT SIDE. COMPONENTS REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997042800013	19970428	00013	NE  	1997	4	28	CA961205020      	2	19961122	G	7250	311180101	BLADE           								PWA   	118   	PW118       		NE  					HP TURBINE	FRACTURED       	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA			7650 					115497			(CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE ENGINE MADE A LOUD BANG AND FEATHERED SOME TIME AFTER TKAEO	FF. DISASSEMBLY OF THE ENGINE REVEALED THE CAUSE OF THE INFLIGHT SHUTDOWN WAS A HP TURBINE BLADE WHICH HAD FRACTURED THR	OUGH THE FIR TREE ROOT. THIS INITIAL FAILURE CAUSED HEAVY DAMAGE TO THE REMAINING HP TURBINE BLADES.									4	T			E20NE				 
1998020500466	19980205	00466	CE  	1998	2	5	CA961216001      	1	19961026	G	5740	AN824A	BOLT            			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					LH  RH SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3325 					0			(CAN) AFTER REMOVAL OF THE LEFT AND RIGHT WINGS FOR A DETAILED INSPECTION, PITTING CORROSION WAS FOUND IN BOTH LEFT AND 	RIGHT FORE AND AFT SPAR WING ATTACH BOLTS. CORROSION WAS ALSO EVIDENT IN THE REAR SPAR ECCENTRIC BUSHINGS P/N 0512123 OF	 THE INTERNAL BORES.				1	H	7	1 	3O	3	O		3A19    	E252				 
1997042800014	19970428	00014	EA  	1997	4	28	CA961216003      	1	19961023	G	8120		SURPERCHARGER   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					IMPELLER SHAFT	FAILED BUSHING  	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				931  				17954			(CAN) ENGINE SUPERCHARGER PRESSURE FLUCTUATING AND MAKING A HIGH PITCH SOUND. NO METAL WAS FOUND IN THE OIL SCREEN. INSP	ECTION FOUND THE IMPELLER WITH EXCESSIVE MOVEMENT. ON DISASSEMBLY THE EXCESSIVE IMPELLER MOVEMENT WAS CAUSED BY THE FAIL	URE OF THE SUPERCHARGER SHAFT BUSHING, BECAUSE OF AN UNAPPROVED REPAIR TO THE OIL FEED GALLERY PLUG THREADS WITH SOME TY	PE OF COMPOUND WITH A FIBEROUS TEXTURE. THIS SAME COMPOUND WAS FOUND CLOGGING THE OIL PORT TO THE BUSHING. WHEN THE BUSH	ING SEIZED TO THE SHAFT TWO TEETH WERE SNAPPED OFF THE FLOATING GEAR DRIVE.		1	H	7	1 	3R	3	R		A806    	5E1				 
1997042800015	19970428	00015	EU  	1997	4	28	CA961216004      	1	19961120	G	6320	369D2551021	DRIVESHAFT      			HUGHES	369   	369FF       		EU  	ALLSN 	250C  	250C30      	03013	GL  					MGB	TEETH MISSING   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3131 					CAE900134			(CAN) MAIN DRIVESHAFT INSPECTED DURING 300 HOUR INSPECTION. 7 OUT OF 34 TEETH ON OUTPUT SPLINE TO MAIN TRANSMISSION FOUN	D CRACKED.					1	G	7	1 	3U	3	U		H3WE    	E1GL				 
1997042800016	19970428	00016	EU  	1997	4	28	CA961216005      	1	19961122	G	2432	18826003	BATTERY         	MARATHON    		FOKKER	F28   	F28MK1000   	4990808	EU  										CELLS	THERMAL DAMAGE  	W				K				NONE                    				J	M		WARNING INDICATION        	OVER TEMP                 		TX	TAXI/GRND HDL  	1			CA			1962 	154  							(CAN) ON ARRIVAL, CREW NOTED #1 BATTERY HOT LIGHT ON. MAINTENANCE FOUND BATTERY HAD SUFFERED AN APPARENT THERMAL RUNAWAY	, RESULTING IN 6 CELLS RUPTURED AND DAMAGE TO 11 OTHERS. BATTERY BOX CONTAINED DAMAGE. BATTERY HAD BEEN DEEP CYCLED 154 	HOURS - 66 DAYS PREVIOUS. DISCUSSION WITH AIRLINES INDICATED THAT THE BATTERY IS A 19 CELL TYPE. THERE HAS BEEN AN ONGOI	NG PROBLEM OF BATTERIES FOR THE AIRLINE - NOT WITH THERMAL RUNAWAYS BUT AT LEAST WITH ENOUGH DIFFICULTIES THAT THE AIRCR	AFT MANUFACTURER WAS CONTACTED TO REPLACE TYPE OF BATTERY. THE AIRCRAFT MANUFACTURER HAS DECLINED TO MOVE TO ANOTHER TYP	E BATTERY. ISSUE ONGOING AT THIS TIME FOR AIRLINE.	2	L	7	2 	4F			RT	A20EU   					 
1997042800017	19970428	00017	SO  	1997	4	28	CA961216009      	2	19961203	G	7314	6467586A2	FUEL PUMP       			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	ANEROID	SCREW STRIPPED  	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA				930  				307636	823131		(CAN) ON CLIMB OUT THE PILOT NOTICED THE FUEL FLOW GAUGE READING HIGH (IN THE RED) AND THE ENGINE STARTED TO RUN ROUGH, 	WITH LOSS OF POWER. THE MIXTURE WAS RETARDED AND THE FUEL FLOW DECREASED AND POWER INCREASED. AIRCRAFT RETURNED TO BASE.	 POST FLIGHT INSPECTION FOUND THE FUEL PUMP ANEROID ADJUSTING SCREW STRIPPED AND EXTENDED OUT 2". THIS ALLOWED THE FUEL 	PRESSURE TO INCREASE PAST THE DESIRED SETTING. THE FUEL PUMP WAS REPLACED.			1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
1998020500467	19980205	00467		1998	2	5	CA961216010      	1	19961206	G	2430	51509350	CONTACTOR       	LUCAS       	51509002R   															DC SYS	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						1155					(CAN) WRONG PART NUMBER LINE CONTACTOR INSTALLED, UNAUTHORIZED CONFIGURATION, UNCERTIFIED FOR FLIGHT.																			 
1997042800018	19970428	00018	EU  	1997	4	28	CA961216011      	1	19961204	G	6720	3160S8700355	CONTROL TUBE    			AEROSP	SA316 	SA316B      	8680207	EU  	TMECA 	ARTST3	ARTOUSTE3B  	60003	EU  					T/R CONTROL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2439 					2447			(CAN) CLAMP ON PITOT STATIC TUBE CHAFED A HOLE IN TAIL ROTOR CONTROL TUBE.						1	G	7	1 	4U	3	U		H1IN    	E11N				 
1997042800019	19970428	00019	EA  	1997	4	28	CA961216012      	2	19961115	G	7261	3008127	GEARSHAFT       			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					OIL PUMP	SHEARED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CL	CLIMB          	1			CA				3168 				50054			(CAN) ON CLIMBOUT THE #2 ENGINE TORQUE DOPPED. THE ENGINE FEATHERED AND SHUTDOWN. POST FLIGHT INSPECTION FOUND THE OIL P	UMP GEARSHAFT HAD SHEARED.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997042800020	19970428	00020	EA  	1997	4	28	CA961216013      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			899  					L1661939A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800021	19970428	00021	EA  	1997	4	28	CA961216014      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			777  					L1584839A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800022	19970428	00022	EA  	1997	4	28	CA961216015      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1373 					L1754739A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800023	19970428	00023	EA  	1997	4	28	CA961216016      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1327 					L1754839A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800024	19970428	00024	EA  	1997	4	28	CA961216017      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1463 					L1756039A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800025	19970428	00025	EA  	1997	4	28	CA961216018      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1414 					L1754539A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800026	19970428	00026	EA  	1997	4	28	CA961216019      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1312 					L1759239A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800027	19970428	00027	EA  	1997	4	28	CA961216020      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1291 					L1490839A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIAITO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800028	19970428	00028	EA  	1997	4	28	CA961216021      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1316 					L1758239A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800029	19970428	00029	EA  	1997	4	28	CA961216022      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1366 					L1758339A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800030	19970428	00030	EA  	1997	4	28	CA961216023      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1319 					L1758439A3			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800031	19970428	00031	EA  	1997	4	28	CA961216024      	2	19961203	G	8520	LW17060	CRANKSHAFT      								LYC   	O320  	O320D2A     	41508	EA  					INSIDE DIAMETER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1275 					L1758539A			(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITT	ING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL IN	DICATED PITTING IN THE AREA 02.00" LONG INWARD FROM THE EXPANSION PLUG. CAUSE OF THE CORROSION WAS DETERMINED AS EXCESSI	VE MOISTURE CONTENT IN THE OIL SYSTEM. SOLUTION TO THE PROBLEM IS UNDER DISCUSSION BETWEEN LYCOMING AND SLINGSBY AVIATIO	N. ENGINE WAS REJECTED AND WAS BEING SENT OUT FOR A NEW CRANKSHAFT.							3	O			E274				 
1997042800032	19970428	00032	SW  	1997	4	28	CA961216025      	1	19960928	G	3230	27810321046	TUBE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					LH GEAR DOWN	LEAKING PINHOLE 	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			7425 					44727			(CAN) DURING DI HYDRAULIC FLUID WAS NOTED SEEPING FROM THE LOWER OUTBOARD AREA OF THE CENTRE SECTION. THE LEFT HAND GEAR	 DOWN LINE WAS FOUND LEAKING FROM A SMALL PIN HOLE WHEN HYDRAULIC SYSTEM PSI WAS UP TO NORMAL OPERATING PRESSURE. TO FIN	D PIN HOLE THE PROTECTIVE PLASTIC HAD TO BE CUT AWAY FROM THE LINE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997042800033	19970428	00033	NM  	1997	4	28	CA961216029      	1	19961119	G	5610	85C0043011	WINDSHIELD      	PPG         		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LH OUTER PANE	SHATTTERED      	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			6700 			91103H9110		120360			(CAN) DURING CLIMBOUT A BIRD STRUCK THE CAPTAINS WINDSCREEN. OUTER NON STRUCTURAL PLY SHATTERED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800034	19970428	00034	NM  	1997	4	28	CA961216030      	1	19961202	G	3310	7002537	CONTROL BOX     	GRIMES      	7002537     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ADVISORY SYSTEM	BURNING SMELL   	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA			3447 			0417		120384			(CAN) ON DESCENT AN ELECTRICAL BURNING SMELL WAS NOTICED AND ADVISORY LIGHTS WERE FLICKERING. FLICKERING AND SMELL STOPP	ED WHEN ADVISORY LIGHTS SELECTED TO BRIGHT. ADVISORY LIGHT CONTROL BOX REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800035	19970428	00035	NE  	1997	4	28	CA961216031      	3	19961129	G	6114	97722	BARREL SUPPORT  			CNDAIR	CL215 	CL2151A10   		EA  						HAMSTD	43E	43E60       	NE  	PROP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1583 					N195039		(CAN) PROPELLER WAS IN SHOP FOR AD 81-13-06R2 INSPECTION. BARREL SUPPORT WAS FOUND CRACKED. BARREL SUPPORT WAS REPLACED.	 PROP BLADES HAD LEADING EDGE SPRAY CUTS FILLED. PROPELLER BARREL BOLTS WERE FOUND CORRODED. THE BOLTS WERE REPLACED. PR	OPELLER WAS ALODINED AND BALANCED.				2	H	7	2 	4R				A14EA   		6	C	P871	 
1997042800036	19970428	00036	NE  	1997	4	28	CA961216032      	3	19961129	G	6114	92368	BOLTS           													HAMSTD	43E	43E60       	NE  	PROP BARREL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1257 					N190031		(CAN) PROPELLER WAS IN SHOP FOR COMPLIANCE WITH AD 81-13-06R2 INSPECTION. THE SHANKS OF THE BARREL BOLTS WERE FOUND CORR	ODED. THE BOLTS WERE REPLACED. THE LEADING EDGES OF THE BLADES WERE FOUND WITH SPRAY CUTS. THE CUTS WERE FILLED AND THE 	BLADES ALODINED AND BALANCED.														6	C	P871	 
1997042800037	19970428	00037	EU  	1997	4	28	CA961216033      	1	19961123	G	3222	23067005	SHOCK ABSORBER  	MESSIER     	23175005    	AIRBUS	320   	A320212     		EU  										NLG UPPER CYL	MISALIGNED      	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) DURING LANDING FOLLOWING AN AIR TURNBACK DUE TO LANDING GEAR WARNING MESSAGES, BOTH NOSE WHEELS DEFLATED. INVESTIG	ATION REVEALED THAT NOSE WHEELS WERE ROTATED 90 DEGREES TO AIRCRAFT CENTRE LINE. FURTHER INVESTIGATION DETERMINED THE CA	USE TO BE A MISALIGNED SHOCK ABSORBER CENTERING CAM DURING REASSEMBLY OF THE SHOCK ASBORBER AFTER SEAL REPLACEMENT. AS A	 RESULT OF THE MISALIGNMENT THE SHOCK ABSORBER WAS INCORRECTLY INDEXED IN THE LANDING GEAR LEG ALLOWING THE NOSE WHEELS 	TO CASTER UP TO 90 DEGREES IN ONE DIRECTION.		2	L	7	2 	4F			RT	A28NM   					 
1997042800038	19970428	00038	SW  	1997	4	28	CA961216034      	1	19961203	G	7603	C817225	POWER CABLE     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	FIREWALL ATTACH	SEVERED         	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA								P44542C	DRG189188		(CAN) AS THE POWER LEVERS WERE ADVANCED FOR TAXI, THE RIGHT HAND ENGINE DID NOT RESPOND. INVESTIGATION REVEALED THAT THE	 CABLE ASSEMBLY ATTACHED TO THE PROP PITCH CONTROL HAD DETACHED DUE TO INTERNAL FAILURE AT THE ENGINE FIREWALL.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
1997042800039	19970428	00039	EA  	1997	4	28	CA961216036      	2	19961202	G	7200		ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					#2 ENGINE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				90   				PCE32567			(CAN) DURING GROUND INSPECTION MAINTENANCE PERSONNEL WERE UNABLE TO TURN THE RIGHT HAND PROPELLER. THE ENGINE WAS REMOVE	D FOR INVESTIGATION.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997042800040	19970428	00040	EA  	1997	4	28	CA961216037      	2	19961109	G	8530	LW13447	CYLINDER        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					ENGINE	WRONG RINGS     	W				A				UNSCHED LANDING         				M	W		OVER TEMP                 	INADEQUATE Q C            		CL	CLIMB          	1			CA								L447661			(CAN) AFTER TAKEOFF THE CYLINDER AND OIL TEMPERATURES BECAME HIGH AND THE OIL PRESSURE WAS DROPPING, THE PILOT RETURNED 	TO BASE. TWO CYLINDERS HAD RECENTLY BEEN REPLACED AND INVESTIGATION HAD FOUND THAT THE WRONG PISTON RINGS HAD BEEN INSTA	LLED. THE ENGINE WAS REPLACED.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997042800041	19970428	00041	NM  	1997	4	28	CA961216038      	1	19961130	G	5330		SKIN            	DHAV        		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ATC XPONDER ANT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			26000					120367			(CAN) DURING INSPECTION OF THE BOND ANTENNA FOR THE ATC TANSPONDER IT WAS NOTED THAT THE FUSELAGE SKIN WAS CORRODED. THE	 ANTENNA WAS REMOVED FOR FURTHER INVESTIGATION WHICH DISCLOSED SEVERE CORROSION AND DELAMINATION OF THE SKIN APPROXIMATE	LY 4 TO 5 INCHES ON EITHER SIDE OF THE ANTENNA CUT-OUT. THE ANTENNA IS LOCATED ON THE UNDERSIDE OF THE FUSELAGE AT STATI	ON 258.5. REPAIRED AS PER RD 8-53-2477.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800042	19970428	00042	GL  	1997	4	28	CA961216039      	3	19961204	G	6110	57B1938	VALVE STEM      			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ACCUMULATOR	DISLODGED       	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA			647  					L364061A	BP3469		(CAN) PILOT REPORTED PROP RPM FLUCTUATIONS ON PREVIOUS FLIGHT. ON NEXT FLIGHT REPORTED NO PROP CONTROL WITH PROP LEVER. 	PILOT ABORTED FLIGHT. INSPECTION FOUND BOTH VALVE STEM AND DUST COVER LYING INSIDE THE PROP SPINNER DOME COVER, PROPELLE	R ACCUMULATOR PRESSURE AND LEAK CHECK CARRIED OUT AT 100 HOUR INSPECTION 40.8 HOURS PRIOR TO THIS OCCURRENCE. NO FAULT W	AS FOUND AT THAT TIME.			1	L	7	2 	3O	3	O		1A10    	E14EA	5	C	P9EA	 
1997042800043	19970428	00043	NE  	1997	4	28	CA961216040      	2	19961202	G	7250	310510301R2W	TURBINE BLADE   								PWA   	118   	PW118A      		NE  					1ST STAGE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14652	3182 				115421			(CAN) THE ENGINE WAS SHIPPED FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR FOUND THERE WAS A FRACTURE OF A PT1 TURBINE	 BLADE. DISASSEMBLY FOUND THE FRACTURED PT BLADE TO BE A WALBAR RECOATED BLADE (P/N 3105103-01-R2W) AND THE FAILURE OCCU	RRED APPROXIMATELY 0.25" ABOVE THE PLATFORM. THIS BLADE IS NOT A CURRENTLY ACCEPTABLE BLADE PER THE PWC MANUALS AND ITS 	INSTALLATION IN THE PT ASSEMBLY AT THE TIME OF THE LAST SHOP VISIT SHOULD NOT HAVE OCCURRED. SUBSTANTIAL EVIDENCE EXISTS	 THAT RECOATED BLADES ARE FAILURE PRONE, ALTHOUGH IT IS NOT CLEAR WHETHER THE RECOATING PROCESS OR SIMPLY HIGH TIME IS T	HE PRIMARY CAUSE OF THE FAILURE.						4	T			E20NE				 
1997042800044	19970428	00044	EU  	1997	4	28	CA961217001      	1	19961205	G	3230		LANDING GEAR    			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					UPLOCK	ICED UP         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								LF05567A			(CAN) LEFT HAND MAIN LANDING GEAR UNSAFE LIGHT REMAINED ON WITH GEAR SELECTED UP. AIRCRAFT RETURNED TO AIRPORT. ICE CLEA	NED FROM GEAR UPLCOK AND UPLOCK LUBRICATED.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997042800045	19970428	00045	EU  	1997	4	28	CA961217002      	1	19961212	G	2750	676101258	RESOLVER        	BRAERO      		BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING FLAPS	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA								LF05464A			(CAN) WING FLAPS STUCK AT 0 DEGREES. FOUND GREEN MAIN RESOLVER OPEN. RESOLVER REPLACED AND RE-RIGGED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997042800046	19970428	00046	EA  	1997	4	28	CA961218002      	2	19961008	G	8500		ENGINE          			DOUG  	DC3   	R4D8        	3021474	WP  	WRIGHT	R1820 	R182080     	67020	EA  						FAILED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CA				820  				W507415			(CAN) ENGINE FAILED IN FLIGHT. AIRCRAFT RETURNED TO BASE. ENGINE REMOVED AND SENT FOR REPAIR. FURTHER REPORT TO FOLLOW.						2	L	7	2 	4R	4	R		6A2     	E259				 
1997042800047	19970428	00047	CE  	1997	4	28	CA961218003      	1	19961210	G	3710	442CW12	PUMP            	RAPCO       		BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					VAC SYS	FAILURE         	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA				8    				1257547CA			(CAN) OVERHAULED VACUUM PUMP INSTALLED AFTER VACUUM PUMP FAILURE. EIGHT HOURS LATER THE VACUUM PUMP SEIZED AND FAILED FO	R NO APPARENT REASON. THIS IS THE SECOND "RAPCO" PUMP TO FAIL EARLY.					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997042800048	19970428	00048	CE  	1997	4	28	CA961218004      	1	19961206	G	2435	23048018	GENERATOR       			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	#2 ENGINE	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		DE	DESCENT        	1			CA				222  				P50842	BU6310		(CAN) #2 ENGINE STARTER GENERATOR FAILED IN FLIGHT. THERE WAS A SLIGHT SMELL OF SMOKE IN THE COCKPIT PRIOR TO FAILURE. A	FTER THE FAILURE THERE WAS A BRIEF FLICKER OF #2 ENGINE FIRE DETECTION LIGHT. THE RIGHT HAND GENERATOR LIGHT ALSO ILLUMI	NATED. DUE TO THE INCREASE IN THE SMELL OF SMOKE THE GENERATOR AND THE RH BLEED AIR WAS TURNED OFF AND THE FLIGHT WAS CO	MPLETED WITHOUT FURTHER PROBLEM.			1	L	7	2 	3T	4	T		3A20    	E4EA	6	C	P15EA	 
1998043000042	19980430	00042	CE  	1998	4	30	CA961218006      	1	19961206	G	5711		SPAR            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  					RIGHT WING	FAILED          	W				E	O			ENGINE SHUTDOWN         	OTHER                   			F	O		FLT CONT AFFECTED         	OTHER                     		LD	LANDING        	1			CA			30219								(CAN) ON LANDING, THERE WAS A MAJOR FAILURE OF THE RIGHT WING STRUCTURE BETWEEN THE NACELLE AND THE FUSELAGE.  TSB INVES	TIGATING.  PART TC:  22,672.					1	L	7	2 	3T	3	T		A14CE   	E4EA				 
1997042800049	19970428	00049	EA  	1997	4	28	CA961218008      	2	19961206	G	7200		ENGINE          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  					#1 POSITION	FAILED          	W				B	E	A		EMER. DESCENT           	ENGINE SHUTDOWN         	UNSCHED LANDING         		A			FLAME/FIRE                			CR	CRUISE         	1			CA			11440	7870 				PCE56069			(CAN) DURING FLIGHT LOUD BANGS WERE HEARD FROM THE #1 ENGINE WITH FLAMES COMING FROM THE EXHAUST STACKS. AN ENGINE FIRE 	DRILL WAS CARRIED OUT AND THE ENGINE SHUTDOWN. THE AIRCRAFT RETURNED TO BASE WITHOUT INCIDENT. THE ENGINE WAS REMOVED FO	R INVESTIGATION. REPORT TO FOLLOW.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997042800050	19970428	00050	NM  	1997	4	28	CA961218011      	1	19961119	G	3251	89891	LINK            	DOWTY       	8900111     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								120358			(CAN) DURING TAXI THE TECHNICIAN LOST STEERING CONTROL. INVESTIGATION FOUND THAT THE LINK WAS BROKEN AT THE RETAINER GRO	OVE AND THE AREA WAS CORRODED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800051	19970428	00051	EA  	1997	4	28	CA961218016      	1	19961211	G	3010	6243843	SENSOR          	CNDAIR      		CNDAIR	CL600 	CL6002B19   		EA  										WING RH INB LE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) RIGHT HAND INBOARD LEADING EDGE TEMP SENSOR FOUND CRACKED. THE SENSOR HAD NOT BEEN INSTALLED AS PER THE MAINTENANC	E TASK. THE BRACKET SHIELD HAD NOT BEEN INSTALLED OVER THE SENSOR AS SPECIFIED IN THE AMM. THEREFORE THE SENSOR WAS DAMA	GED BY TORQUING THE MOUNTING SCREW.				2	L	7	2 	4F			RT	A21EA   					 
1997042800052	19970428	00052	SO  	1997	4	28	CA961218017      	1	19961212	G	8120	LW12127	TRANSITION ASSY 			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					TURBOCHARGER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7420 					L339761A			(CAN) TURBOCHARGER TRANSITION ASSEMBLY FOUND CRACKED ON INSPECTION.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997042800053	19970428	00053	WP  	1997	4	28	CA961220001      	1	19961209	G	5710		WING FITTING    			DOUG  	DC6   	DC6B        	3021712	WP  						HAMSTD	43E	43E60       	NE  	TANK AREA WS 421	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									201611		(CAN) DURING MAINTENANCE INSPECTION CORROSION WAS DISCOVERED IN THE #1 AND #4 ALTERNATE FUEL TANK AREAS JUST INBOARD OF 	WS 421 ON THE BATH TUB FITTINGS. CORRODED AREAS WILL BE CLEANED, REPAIRED AND TREATED. THE DEFINED AREAS WILL BE MONITOR	ED FOR CORROSION AND INSPECTED ANNUALLY DURING THE WINTER MAINTENANCE PROGRAM.				2	L	7	4 	4R				6A4     		6	C	P871	 
1997042800054	19970428	00054	WP  	1997	4	28	CA961220002      	1	19961206	G	5742	33209801	FITTING         			DOUG  	DC6   	DC6B        	3021712	WP  						HAMSTD	43E	43E60       	NE  	NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									201611		(CAN) THE FITTING IDENTIFIED IS MOUNTED AND COVERED PREVENTING IT FROM BEING CLEANED AND INSPECTED OR TREATED FOR CORROS	ION. THE FITTING WAS FOUND TO BE CRACKED DURING WINTER MAINTENANCE INSPECTION. ALL AIRCRAFT WILL BE NDT CHECKED USING UL	TRASONIC AND EDDY CURRENT TECHNIQUES. AFTER ALL AIRCRAFT INSPECTED LONG TERM MAINTENANCE PROGRAM WILL BE INITIATED.				2	L	7	4 	4R				6A4     		6	C	P871	 
1997042800055	19970428	00055	EU  	1997	4	28	CA961220004      	1	19961205	G	2121		FAN             			AIRBUS	320   	A320211     	3930320	EU  										ACM FAN	BROKEN BLADE    	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) SMOKE DETECTED IN CABIN, EMERGENCY DECLARED, AIR PACK REGULATOR FAULT ON UPPER ECAM. ON ARRIVAL WHITE SMOKE NOTED 	ON OPENING PACK DOOR. MAINTENANCE ACTION INVOLVED CHANGING #2 BYPASS VALVE. ACM FOUND SEIZED AND TURBINE THREW BLADE. FU	RTHER INVESTIGATION REVEALED BLADE BROKE FROM FAN AND NOT TURBINE. AFTER ACM AND TURBINE BYPASS VALVE REPLACED, ENGINES 	RAN AND PACKS OPERATED CHECKS SERVICEABLE.			2	L	7	2 	4F			RT	A28NM   					 
1997042800056	19970428	00056	WP  	1997	4	28	CA961220009      	1	19961125	G	3610	14J63600	DUCT CLAMP      			DOUG  	DC10  	DC1030      	3023501	WP  	GE    	CF6   	CF650C2     	30018	NE  					#2 ENGINE	BROKEN          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			G	J		MULTIPLE FAILURE          	WARNING INDICATION        		TO	TAKEOFF        	1			CA								517392			(CAN) ON TAKEOFF ROLL PRESSURE REGULATOR DUCT #2 ENGINE FAILED CAUSING EXCESSIVE DAMAGE TO PNEUMATIC DUCTING, SENSING LI	NES, OIL SCAVANGE AND OIL DUMP LINES. ALSO THERE WAS DAMAGE TO SUROUNDING STRUCTURE. NACELLE TEMPERATURE ROSE TO 240 DEG	REES C AND FOLLOWED THROTTLE. MANIFOLD LIGHT CAME ON. ALL DAMAGED PARTS REMOVED AND REPLACED.				2	L	7	3 	4F	4	F		A22WE   	E23EA				 
1997042800057	19970428	00057		1997	4	28	CA961220010      	4	19961220	G	3416	152734	SUPPORT RING    	AEROMECH    	804710DH    	DHAV  	DHC8  	DHC8*       		NM  										ALTIMETER	MODIFIED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						8455					(CAN) SUPPORT RING FOUND ILLEGALLY MODIFIED AS OUTLINED IN SERVICE DIFFICULTY ADVISORY AV-93-07R1.						2	H	7	2 	4T			RT	A13NM   					 
1997042800058	19970428	00058	SW  	1997	4	28	CA961220011      	1	19961129	G	2730	2744026011	TORQUE TUBE     			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					ELEVATOR	CRACKED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27546					P54183			(CAN) AS PART OF 8000 BLOCK INSPECTION THE ELEVATORS ARE REMOVED FOR INSPECTION. THE ELEVATOR TORQUE TUBES ARE NOT SPECI	FICALLY IDENTIFIED AS REQUIRING SPECIAL ATTENTION. HOWEVER, INSPECTION FOUND THAT THE LEFT ELEVATOR TORQUE TUBE ASSEMBLY	 WAS CRACKED AT THE 'FORK END'. THE RIGHT HAND TUBE WAS FOUND TO HAVE A BADLY WORN INBOARD HINGE FITTING. SB 226-27-050,	 TO INSPECT TUBE FOR INTERNAL CORROSION WAS ACCOMPLISHED SEVERAL YEARS EARLIER, AND FAA AD 96-21-05 WAS RECENTLY COMPLIE	D WITH. DETECTION OF CRACKS WAS NOT A REQUIREMENT. RIGHT ELEVATOR WAS REPLACED USING AN UPDATED TORQUE TUBE ASSEMBLY P/N	 27-44016-007 AND LEFT TUBE WAS REPAIRED USING SAME NEW P/N.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997042800059	19970428	00059	GL  	1997	4	28	CA961220012      	3	19961207	G	6111		PROPELLER       													MCAULY	1C160	1C160CTM    	GL  	BLADE LE EDGES	OUT OF SPECS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER SENT FOR CORROSION INSPECTION, BLADE ANGLES WERE FOUND OUT OF SPECIFICATIONS. LEADING EDGES TRIMMED TO R	EMOVE EROSION DAMAGE.															5	N	P910	 
1997042800060	19970428	00060	NM  	1997	4	28	CA961220013      	1	19961212	G	2710	8270052001	CONTROL CABLE   			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18605					120817			(CAN) LEFT HAND LOWER INBOARD AILERON CABLE FOUND CHAFING ON CLAMP P/N DSC70-40. CLAMP WAS INSTALLED IMPROPERLY SECURING	 SHROUD P/N DSC213-15, ON TO REFUEL/TRANSFER LINE AT LEFT HAND AFT SPAR STN YW196.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800061	19970428	00061	EA  	1997	4	28	CA961220014      	1	19961012	G	2721	C6CFM11771	QUADRANT GEAR   	DHAV        		DHAV  	DHC6  	DHC6300     		EA  										RUD SERVO TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19285								(CAN) DURING INVESTIGATION FOR MINOR RUDDER SERVO TAB FREEPLAY, THE GEARED TAB MECHANISM WAS REMOVED AND DISASSEMBLED FO	R WEAR INSPECTION. LEVER P/N C6CFM1409-27 WAS FOUND LOOSELY ATTACHED TO QUAD GEAR. QUAD GEAR HAD TWO CRACKS IN THE KEY R	OOT OF THE BOSS AREA. CRACKS WERE NOT VISIBLE UNTIL GEAR REMOVED FROM GEARED MECHANISM DUE TO FELT RING INSTALLATION. ON	E CRACK FOUND ON ANOTHER AIRCRAFT. FLEET WIDE CHECK TO BE CARRIED OUT.			1	H	7	2 	3T				A9EA    					 
1997042800062	19970428	00062	NE  	1997	4	28	CA961220015      	2	19961211	G	7250	310920201	BLADES          								PWA   	118   	PW118       		NE  					LP TURBINE	MULTIPLE FAILURE	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			19943	16548				115036			(CAN) THE OPERATOR REPORTED DURING A START ATTEMPT THE PROP DID NOT ROTATE. THE OPERATOR REMOVED THE POWER TURBINE AND F	OUND EVIDENCE OF DAMAGE. THE ENGINE WAS SENT FOR INVESTIGATION AND REPAIR. ENGINE DISASSEMBLY FOUND MULTIPLE FAILURES OF	 THE LP TURBINE BLADES. THE CAUSE OF THE BLADE FAILURES WAS CLEARLY RELATED TO CORROSION ATTACK OF THE CORED PASSAGE THR	OUGH THE BLADES.								4	T			E20NE				 
1997042800063	19970428	00063	NE  	1997	4	28	CA961220016      	2	19961209	G	7250	311362301	BEARING         								PWA   	120   	PW120A      		NE  					HP ROTOR NR 5	FRACTURED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			21503	7070 				120086			(CAN) THE OPERATOR NOTICED A GRINDING NOISE ON SHUTDOWN AND METAL FILINGS WERE FOUND IN THE MAIN OIL PRESSURE FILTER AND	 ON THE CHIP DETECTOR.  THE ENGINE WAS SENT FOR INVESTIGATION.  THE CAUSE OF THE GRINDING NOISE AND METAL IN THE FILTERS	 WAS FOUND TO BE THE FAILURE OF THE NR 5 BEARING CAGE.									4	T			E20NE				 
1997042800064	19970428	00064	SO  	1997	4	28	CA961223001      	1	19961216	G	3412	W200043418	WIRE            			EMB   	120   	EMB120RT    	3260202	SO  										CB 0304	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18571								(CAN) DURING INSPECTION SEVERAL WIRES AND AN INSULATION BLANKET WERE FOUND BURNED. THE WIRES HAD BURNED UP TO 6 INCHES O	F WIRE AND HAD ALSO BURNED SEVERAL TYWRAPS INSIDE COCKPIT OVERHEAD CIRCUIT BREAKER PANEL. WIRE WHICH APPEARS TO HAVE CAU	SED DAMAGE WAS CONNECTED FROM TAT PROBE INDICATOR CIRCUIT BREAKER (CB0304) TO WINDSHIELD WIPER LEFT CIRCUIT BREAKER (CB0	385).			2	L	7	2 	4T			RT	A31SO   					 
1997042800065	19970428	00065	NM  	1997	4	28	CA961223002      	1	19961205	G	2421	31708001A	GENERATOR       			DHAV  	DHC8  	DHC8301     		NM  	PWA   	PW120 	PW123       		NE  					NR 2 AC	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			11514					123075			(CAN) THE #2 AC GENERATOR FAILED ON DEPARTURE. AIRCRAFT RETURNED TO AIRPORT. RGB CHIP DETECTOR FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800066	19970428	00066	EA  	1997	4	28	CA961223003      	1	19961206	G	3230	83220001001	NOSE  GEAR      	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  					EXT MECH	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA						723		123192			(CAN) ON APPROACH NOSE GEAR DID NOT EXTEND. SUCCESSFUL ALTERNATE GEAR EXTENSION CARRIED OUT. GEAR INSPECTED, CLEANED, IN	CLUDING DRAG STRUT ASSEMBLY, DRAG STRUT ACTUATOR AND BEARING, GEAR DOOR MECHANISM, AND THE MECHANICAL SEQUENCE VALVE RIG	GING CHECKED. NOTHING FOUND.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800067	19970428	00067	SO  	1997	4	28	CA961223004      	2	19961203	G	8530	642343CN	CYLINDER        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					#1 CYLINDER	SEPARATED       	W				A				UNSCHED LANDING         				B	E	K	SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          	FLUID LOSS                	CL	CLIMB          	1			CA			415  					239802R			(CAN) DURING CLIMBOUT THE #1 ENGINE HAD A LOSS OF POWER FOLLOWED BY ROUGH RUNNING. ON RETURN TO THE AIRPORT OIL WAS NOTI	CED ESCAPING THROUGH THE #1 ENGINE COWLING. POST FLIGHT INSPECTION FOUND THE #1 CYLINDER HEAD LYING IN THE COWLING. THE 	CYLINDER WAS REMOVED; THE OIL DRAINED; THE ENGINE AND FILTERS WERE CHECKED FOR DAMAGE. A NEW #1 CYLINDER WAS INSTALLED A	ND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997042800068	19970428	00068	NE  	1997	4	28	CA961223006      	2	19961216	G	7200		ENGINE          			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					#2 POSITION	MAKING METAL    	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA			13564	6164 				PCE93186			(CAN) DURING FLIGHT #2 ENGINE CHIP DETECTOR ILLUMINATED. ENGINE WAS SHUTDOWN AND AIRCRAFT LANDED WITHOUT INCIDENT. ENGIN	E WAS REMOVED FOR INVESTIGATION. REPORT TO FOLLOW.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997042800069	19970428	00069	NE  	1997	4	28	CA961223008      	2	19961213	G	8500		ENGINE          			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  					#1 POSITION	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				66   				457481			(CAN) WHILE IN CRUISE THE #1 ENGINE DEVELOPED A POWER LOSS AND BEGAN TO RUN ROUGH. THE ENGINE WAS SHUTDOWN AND THE AIRCR	AFT LANDED WITHOUT INCIDENT. UPON FURTHER INVESTIGATION THE STATUS WILL BE UPDATED.					2	L	7	2 	4R	4	R		A669    	5E4				 
1997042800070	19970428	00070	EU  	1997	4	28	CA961230003      	1	19961210	G	2612	8934100450A	CONTROL UNIT    			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 2 FIRE DET	FAULTY          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA			17049					9052			(CAN) #2 ENGINE HAD A FIRE WARNING INDICATION IN FLIGHT. #2 ENGINE WAS SHUTDOWN AND FIRE WARNING WENT OUT, SO FIRE BOTTL	ES WERE NOT ACTIVATED. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE COULD NOT DUPLICATE FAULT ON THE GROUND. AL	L SYSTEMS CHECKED NORMAL. PRECAUTIONARY REPLACEMENT OF THE FIRE DETECTOR CONTROL UNIT WAS CARRIED OUT FOR TROUBLESHOOTIN	G OF THE INTEGRAL K2 RELAY.			2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997032700112	19970327	00112	NM  	1997	3	27	CA961230006      	1	19961216	G	3230		LANDING GEAR    			DHAV  	DHC8  	DHC8102     	2809003	NM  										NOSE & RT MAIN	FAILED          	W				O				OTHER                   				G	O		MULTIPLE FAILURE          	OTHER                     		AP	APPROACH       	1			CA											(CAN) AIRCRAFT LANDED WITH RIGHT MAIN LANDING GEAR AND NOSE LANDING GEAR IN THE RETRACT POSITION. LEFT MAIN WAS DOWN AND	 LOCKED.					2	H	7	2 	4T			RT	A13NM   					 
1997042800071	19970428	00071	EA  	1997	4	28	CA961230008      	1	19961211	G	3010	6243843	SENSOR          			CNDAIR	CL600 	CL6002B19   		EA  										LT WING INB LE	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) LEFT HAND, INBOARD LEADING EDGE WING TEMP SENSOR, NOT INSTALLED AS PER MAINTENANCE TASK. THE BRACKET HAD NOT BEEN 	INSTALLED OVER THE SENSOR AS SPECIFIED IN THE AMM. THEREFORE, THE SENSOR WAS DAMAGED WHEN THE MOUNTING SCREWS WERE TORQU	ED DOWN.				2	L	7	2 	4F			RT	A21EA   					 
1997042800072	19970428	00072	SW  	1997	4	28	CA961230009      	1	19961202	G	5210	2724147003	HINGE           	SWRNGN      		SWRNGN	SA226 	SA226T      	8780122	SW  										PAX DOOR AFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABIN DOOR FOUND WITH EXCESSIVE LATERAL MOVEMENT WHEN MOVED OPEN OR CLOSED. IT WAS ALSO NOTED THAT DOOR GUIDES WOU	LD CONTACT THE FUSELAGE FRAME WHEN CLOSING. INSPECTION FOUND THAT THE DOOR HINGE HAD A 2 1/2" CRACK WHICH HAD TRAVELLED 	ACROSS 3 OF THE ATTACHMENT HOLES AND TERMINATED AT THE FOURTH.				2	L	7	2 	4T			RT	A5SW    					 
1997042800073	19970428	00073	SW  	1997	4	28	CA961230010      	1	19961217	G	2910	MS21926W16	ELBOW           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FLEX LINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								CPPS61075			(CAN) DURING DAILY INSPECTION AME FOUND HYDRAULIC OIL ON FLOOR UNDER AIRCRAFT HELL HOLE. AFTER INVESTIGATION, THE AME FO	UND OIL DRIPPING FROM THE INLET ELBOW OF THE #1 HYDRAULIC PUMP. THE FLEX LINE WAS DISCONNECTED AND ELBOW FOUND CRACKED.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1997042800074	19970428	00074	NE  	1997	4	28	CA961230011      	2	19961216	G	7260	311169301	GEAR            								PWA   	118   	PW118       		NE  					ACCESSORY DRIVE	LOSS OF TEETH   	W				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			21293	13404				115135			(CAN) THE OPERATOR REPORTED THE ENGINE SHUTDOWN (UNCOMMANDED) DURING FLIGHT. THE ENGINE WAS REMOVED FROM SERVICE AND SEN	T FOR OVERHAUL. ENGINE DISASSEMBLY REVEALED THE INFLIGHT SHUTDOWN WAS CAUSED BY A LOSS OF DRIVE TO THE FUEL PUMP, WHICH 	RESULTED IN LOSS OF FUEL AND OIL PRESSURE, SHUTTING THE ENGINE DOWN. THE LOSS OF DRIVE TO THE FUEL PUMP WAS CAUSED BY TH	E FAILURE OF THE GEAR TEETH ON THE MAIN ACCESSORY DRIVE GEAR AND THE MATING TEETH OF THE FUEL PUMP DRIVE GEAR.								4	T			E20NE				 
1997042800075	19970428	00075	EA  	1997	4	28	CA961230012      	1	19961219	G	5200		WEB             	CNDAIR      		CNDAIR	CL215 	CL2151A10   		EA  										ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1313 								(CAN) WATER BOMBER DOOR WOULD NOT CLOSE COMPLETELY. INSPECTION SHOWED CRACKS IN THE WEB WHERE WATER BOMBER ACTUATOR ATTA	CHES TO FRAME. CRACKS EXTENDED FROM SPIGOTS TO LIGHTNING HOLES IN FRAME. TWO AIRCRAFT IN FLEET WITH SAME PROBLEM.					2	H	7	2 	4R				A14EA   					 
1997042800076	19970428	00076	EA  	1997	4	28	CA961230013      	2	19961212	G	7323	25249994	GOVERNOR        	ALLIED SIGNA		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					#1 ENGINE	FAULTY          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA				3123 		A9091		CPPS61495			(CAN) UPON DEPARTURE THE LOW SIDE GOVERNOR FAILED ON THE #1 ENGINE. #1 THROTTLE WAS ROLLED BACK TO IDLE, GOVERNOR SELECT	ED TO MANUAL AND THROTTLE ROLLED UP TO 4 PERCENT BELOW #2 ENGINE. THE FLIGHT WAS CONCLUDED WITHOUT FURTHER INCIDENT.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1997042800077	19970428	00077	EU  	1997	4	28	CA961230014      	1	19961204	G	8120	139312	SUPERCHARGER    	DOWTY       	60207009    	BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    		EU  					#2 ENGINE	FAULTY          	W		A		E				ENGINE SHUTDOWN         				O	J		OTHER                     	WARNING INDICATION        		CR	CRUISE         	1			CA				2504 		DRG14206021		19427			(CAN) DURING CRUISE 30 MINUTES AFTER DEPARTURE THE #2 ENGINE RPM INDICATOR WENT TO ZERO. HYDRUALIC FLOW LIGHT GENERATOR 	AND ALTERNATOR LIGHTS ILLUMINATED. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO BASE. POST FLIGHT INSPECTION OF 	THE GEARBOX FOUND THE MAIN DRIVE SHAFT SHEARED, THE SUPERCHARGER SEIZED AND GENERATOR QUILL SHAFT SHEARED. ALL AFFECTED 	PARTS REPLACED. THE AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	3T	4	T		A24EU   	A196				 
1997042800078	19970428	00078	EA  	1997	4	28	CA961230016      	1	19961219	G	5200		WEB             	CNDAIR      		CNDAIR	CL215 	CL2151A10   		EA  										ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WATER BOMBER DOOR WOULD NOT CLOSE COMPLETELY. INSPECTION SHOWED CRACKS IN THE WEB WHERE WATER BOMBER ACTUATOR ATTA	CHES TO FRAME. CRACKS EXTENDED FROM SPIGOTS TO LIGHTNING HOLES IN FRAME. TWO AIRCRAFT IN FLEET WITH SAME PROBLEM.					2	H	7	2 	4R				A14EA   					 
1997042800079	19970428	00079	NE  	1997	4	28	CA961231002      	2	19961220	G	7250	3039512	LP TURBINE      			DHAV  	DHC8  	DHC8301     		NM  	PWA   	PW120 	PW123       		NE  					BALDE TIPS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7823 					123045			(CAN) DURING BOROSCOPE INSPECTION THE LP TURBINE BLADES WERE FOUND DAMAGED AT THE TIPS. THE ENGINE WAS REPLACED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800080	19970428	00080		1997	4	28	CA961231003      	1	19961220	G	7500	311269001	VENTURI P3      								PWA   	PW120 	PW123       		NE  					BASE OF FITTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14737					123010			(CAN) DURING INSPECTION DUST WAS FOUND AROUND THE INSULATION COVERING THE P3 BLEED VENTURI. REMOVED INSULATION AND FOUND	 A 2" CRACK IN THE VENTURI TUBE. THE TUBE WAS REPLACED.										4	T			E20NE				 
1998020500477	19980205	00477	CE  	1998	2	5	CA961231004      	1	19961226	G	5410	58540028	BEAM ASSEMBLY   			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	NR1 ENG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10612						76618		(CAN) NR1 FORWARD ENGINE BEAM CRACKS FOUND ON BOTH THE LEFT AND RIGHT ENGINE BEAM INBOARD AND OUTBOARD. CRACKS LOCATED D	IRECTLY UNDER THE MOUNT AND/OR ORIGINATING FROM END OF THE BEAM AND IN A CIRCULAR SHAPEOF ANCHOR NUT FORWARD END. CRACKS	 EXTENDING THROUGH THE BEAM DOUBLER AND FORWARD LEG OF BEAM.				1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998020500478	19980205	00478	CE  	1998	2	5	CA961231005      	1	19961226	G	5343	52130409	WEB             			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	NLG GEAR ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10612						76618		(CAN) FORWARD NOSE GEAR TUNNEL WEB, NOSE GEAR ATTACH AREA, FOUND CRACKED AROUND ATTACHING BOLTS, CRACKS CIRCULAR UNDER N	UTS. LEFT P/N 5213040-10 . NOSE GEAR DRAG BRACE ATTACH AREA LEFT, CRACK FOUND IN TUNNEL SKIN AND DOUBLER LEFT SIDE TOP A	FT CORNER.				1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997042800081	19970428	00081	SO  	1997	4	28	CA970106001      	1	19961210	G	5520	5499402	HINGE           			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					ELEVATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3063 					PCE50170			(CAN) DURING INSPECTION AN ELEVATOR HINGE WAS FOUND BROKEN.						1	L	7	2 	3T	4	T		A8EA    	E4EA				 
1997042800082	19970428	00082		1997	4	28	CA970106002      	4	19961018	G	2562	1104	BATTERY         			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ELT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2578248A			(CAN) ELT BATTERY LEAKING CAUSING THE CASE MOUNTING PLATE TO CRACK.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1997042800083	19970428	00083	NM  	1997	4	28	CA970106003      	1	19961214	G	3230	54C546349	SEQUENCING VALVE			DHAV  	DHC8  	DHC8201     	2809001	NM  										LEFT GEAR DOORS	FAILED          	W				A				UNSCHED LANDING         				J	O		WARNING INDICATION        	OTHER                     		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, LANDING GEAR SELECTED UP AND GEAR RETRACTED, BUT THE LEFT GEAR DOORS REMAINED OPEN. GEAR SELECTED D	OWN AND LEFT GEAR REMAINED UP AND LOCKED. EMERGENCY GEAR EXTENSION CARRIED OUT. THE RONSON SEQUENCING VALVE FOR THE LEFT	 LANDING GEAR HAD REMAINED ENERGIZED CAUSING THE PROBLEM.				2	H	7	2 	4T			RT	A13NM   					 
1998041700421	19980417	00421	EU  	1998	4	17	CA970106004      	1	19960929	G	4930	100644200	FUEL MANIFOLD   	SUNDSTRANDEM	T62T40C3    	AMD   	FALC20	FALCON200   	2730150	EU  										APU	CRACKED         	W				F				ACTIVATE FIRE EXT.      				A	B	K	FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	TX	TAXI/GRND HDL  	1			CA						851751					(CAN) CRACK DEVELOPED IN FUEL MANIFOLD WHILE APU OPERATING.  FUEL COLLECTED IN TAIL CONE AND FIRE STARTED. IGNITION SOUR	CE UNKNOWN.  APU EXTINGUISHER FIRED AND APU SHUT DOWN.  PORTABLE EXTINGUISHER ALSO USED.  SUNDSTRAND OPTIONAL SB T-62T-4	9-113 INSTALLS A FATIGUE RESISTANT FUEL MANIFOLD.				2	L	7	2 	4F			RT	A7EU    					 
1997042800084	19970428	00084	GL  	1997	4	28	CA970106005      	3	19961121	G	6114	57D220117	HUB             			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NR 2 SOCKET	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1869 	572  				L1006040	CH972		(CAN) DURING CALENDAR TIME INSPECTION THE PROPELLER HUB WAS FOUND CORRODED IN THE #2 SOCKET. IN ACCORDANCE WITH HARTZELL	 MANUAL NO CORROSION IS PERMITTED.					1	L	7	1 	3O	3	O		A3SO    	E295	5	C	P920	 
1997042800085	19970428	00085	GL  	1997	4	28	CA970106006      	1	19961119	G	2701	2027040800	CONTROL STICK   			DIAMON	DA20A1	DA20A1      	05626UX	GL  										STICK SUPPORT	RUBBING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RUBBING BETWEEN P/N 20-2704-08-00 CONTROL STICK SUPPORT AT THE PILOTS LOCATION AND BOLT P/N AN364-428 AT END OF CO	NTROL ROD. APPEARS THAT THE NEW PARTS INSTALLED IN AIRCRAFT AT LATER DATES HAD A LARGER "LIGHTENING" HOLE AND THUS NO RU	BBING.				1	L	7	1 	3O			NT	TA4CH   					 
1997042800086	19970428	00086	SO  	1997	4	28	CA970106007      	2	19960930	G	8530	653426	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					AT COOLING FINS	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			1514 					250825SO			(CAN) INSPECTION FOUND CYLINDER CRACKED AT COOLING FINS AFTER AIRCRAFT MADE FORCED LANDING IN FIELD.						1	H	7	1 	3O	3	O		3A19    	E252				 
1997042800087	19970428	00087	CE  	1997	4	28	CA970106008      	1	19961121	G	3246	16119A	WHEEL HALF      	CLEVELAND   	40135       	CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NLG BEAD FLANGE	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			5018 					235232R			(CAN) CREW NOTED WHEEL NOISE ON LANDING. INVESTIGATION REVEALED THE INBOARD WHEEL HALF CRACKED AT THE BEAD FLANGE, APPRO	XIMATELY 4 INCHES LONG.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997042800089	19970428	00089	CE  	1997	4	28	CA970106010      	1	19961223	G	5320	12114223	DOUBLER         	CESSNA      	12114223    	CESSNA	210   	T210G       	2073432	CE  	CONT  	O520  	TSIO520C    	17040	SO  					BOLT HOLES	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2644 					14040266			(CAN) CRACKS DISCOVERED AROUND BOLT HOLES ON THE OUTBOARD SIDE OF THE DOUBLER. LEFT HAND SIDE OF THE MAIN LANDING GEAR.						1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997042800090	19970428	00090	CE  	1997	4	28	CA970107001      	1	19961231	G	3233	1053840021	ACTUATOR        	GERDES      	1053840021  	BEECH 	76    	76          	1153005	CE  										LT GEAR	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA						0152REVD					(CAN) IN LEVEL FLIGHT A LOUD BANG WAS HEARD FROM THE LEFT SIDE OF THE AIRCRAFT. THE GEAR WAS LOWERED AND A SUCCESSFUL LA	NDING COMPLETED. THE LEFT HAND ACTUATOR CYLINDER WAS FOUND TO HAVE FAILED AT THE ROD END.					1	L	7	2 	3O				A29CE   					 
1997042800091	19970428	00091	CE  	1997	4	28	CA970107002      	1	19961220	G	3240	10558000015	BRAKE LINE      			BEECH 	76    	76          	1153005	CE  										WING	CUT             	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) BRAKE LINE FOUND CUT IN THE WING BY A CONTROL CABLE. REPAIRED AND RETURNED TO SERVICE.						1	L	7	2 	3O				A29CE   					 
1997042800092	19970428	00092	SO  	1997	4	28	CA970107004      	1	19961230	G	3230		REDUCING VALVE  			EMB   	110   	EMB110P1    	3260122	SO  										MLG	OUT OF ADJUST   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON TAKEOFF LANDING GEAR SELECTED TO RETRACT. RED IN TRANSIT LIGHT WOULD NOT GO OUT. GEAR LEVER TO EXTEND AND THREE	 GREEN INDICATED. PRESSURE REDUCING VALVE FOUND TO BE LOW AT 1300 PSI. VALVE ADJUSTED TO 1400+/-50 PSI.					1	L	7	2 	4T				A21SO   					 
1997042800093	19970428	00093	SO  	1997	4	28	CA970107005      	1	19961218	G	8120	LW12778	ACTUATOR GATE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					TURBOCHARGER	EXCESS WEAR     	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA				1781 				L124968A			(CAN) ABORTED TAKEOFF DUE TO ENGINE OVER BOOST. WASTE GATE FOUND TO BE SOURCE OF THE PROBLEM. THE ENGINE WAS REPLACED.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997042800094	19970428	00094	NE  	1997	4	28	CA970107006      	2	19961226	G	7314	50087350	FUEL PUMP       	SUNDSTRAND  		AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     		NE  					LOW STAGE	SHEARED SHAFT   	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			7358 			0619		V0349			(CAN) ENGINE DID NOT PRODUCE TAKEOFF POWER AND WAS DIFFICULT TO START. INVESTIGATION FOUND THE TWO STAGE FUEL PUMP WAS N	OT DELIVERING THE VOLUME OF FUEL REQUIRED, DUE TO A SHEARED DRIVE.					2	L	7	2 	4F	4	F	RT	A28NM   	E311NE				 
1997042800095	19970428	00095	NM  	1997	4	28	CA970107009      	1	19961218	G	3230	54C546347	VALVE           	KAISER      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LANDING GEAR	BROKEN          	W				O				OTHER                   				K			FLUID LOSS                			CL	CLIMB          	1			CA			25448			0111		120248			(CAN) AFTER TAKEOFF #2 HYDRAULIC SYSTEM PRESSURE AND QUANTITY INDICATED ZERO. INSPECTION FOUND THE MAIN LANDING GEAR SEQ	UENCE VALVE SEPARATED BETWEEN THE VALVE BODY AND THE ELECTRICAL SOLENOID.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800096	19970428	00096	NE  	1997	4	28	CA970107010      	2	19961220	G	7250	311330301	PT BLADE        								PWA   	118   	PW118       		NE  					POWER TURBINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13687					115332			(CAN) OPERATOR NOTICED DAMAGE IN THE POWER TURBINE AND THE ENGINE WAS SHIPPED FOR INVESTIGATION AND OVERHAUL. DISASSEMBL	Y FOUND THE ENGINE HAD SUFFERED THE FAILURE OF TWO PT1 BLADES. THEY HAD FAILED A SHORT DISTANCE BELOW THE OUTER PLATFORM	. THIS IS AN UNUSUAL FAILURE AND PWC SUGGESTS THAT FROM EXPERIENCE IT COULD BE ASSOCIATED WITH MICROSTRUCTURAL DAMAGE RE	SULTING FROM AN OVERTEMPERATURE EXCURSION OR HOT START.								4	T			E20NE				 
1997042800099	19970428	00099		1997	4	28	CA970109003      	1	19961213	G	3610	S210T120101	SHUTOFF VALVE   	HAMSTD      							GE    	CF6   	CF680C2B6   		NE  					#1 ENGINE AIR	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						0216		690255			(CAN) AIR TURNBACK DUE TO "LT ENG HPSOV (HIGH PRESSURE SHUTOFF VALVE)" EICAS MESSAGE ON DURING TAKEOFF AND REMANING ON D	URING  CLIMB. COULD NOT ERASE MESSAGE. SELECTED #1 ENGINE BLEED AIR OFF. REPLACED #1 HPSOV.										4	F			E13NE				 
1997050100356	19970501	00356	EA  	1997	5	1	CA970109018      	1	19961217	G	3246		BEARING         		32100011    	CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					NLG LT WHEEL	GRINDING        	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA			3357 					807267			(CAN) EXCESSIVE VIBRATION FELT ON TAKEOFF. TAKEOFF REJECTED. SUSPECTED NOSE GEAR TIRE. FOUND LEFT HAND NOSE WHEEL BEARIN	G GRINDING.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050100357	19970501	00357	EA  	1997	5	1	CA970109019      	1	19961209	G	2131	21197645	SELECTOR PANEL  			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					PRESSURIZATION	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			3307 					807267			(CAN) AIRCRAFT WOULD NOT DEPRESSURIZE. PRESSURIZATION SELECTOR PANEL REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050100358	19970501	00358	EA  	1997	5	1	CA970109020      	1	19961217	G	3260		SENSOR          			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					GROUND SHIFT	CONTAMINATED    	W				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CL	CLIMB          	1			CA			1319 					GEE807389			(CAN) AFTER TAKEOFF, MULTIPLE EICAS MESSAGES APPEARED. ALSO MEMENTARY PASSENGER DOOR WARNING. GROUND SHIFT PROXIMITY SEN	SOR CONTAMINATED WITH ICE AND GREASE. ALSO FOUND PASSENGER EXTERIOR DOOR HANDLE RELEASE LEVER NOT FLUSH WHEN HANDLE CLOS	ED. NOSE GEAR PROXIMITY SENSOR AND TARGET CLEANED. PASSENGER DOOR HANDLE RELEASE LEVER LUBRICATED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050100359	19970501	00359	EU  	1997	5	1	CA970109021      	1	19961213	G	3230		GEAR LOCK       			AIRBUS	320   	A320211     	3930320	EU  										RH LANDING GEAR	FOUND INSTALLED 	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, UNABLE TO RETRACT LANDING GEAR. GEAR RECYCLED NO CHANGE. LEFT GEAR NOT UPLOCKED INDICATION ON ECAM 	COMPUTER. AIRCRAFT RETURNED TO BASE. MAINTENANCE CHECK REVEALED RH GEAR LOCK INSTALLED. LOCK REMOVED, NO FAULT ON CFDS (	CENTRALIZED FAULTY DISPLAY SYSTEM). SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4F			RT	A28NM   					 
1997050100360	19970501	00360	EU  	1997	5	1	CA970109022      	1	19961215	G	3230		SENSOR BOLT     			AIRBUS	320   	A320211     	3930320	EU  										MLG	LOOSE           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, LANDING GEAR WOULD NOT RETRACT. GEAR RECYCLED, NO CHANGE. AIRCRAFT RETURNED TO BASE. MAINTENANCE TR	OUBLESHOOTING FOUND SENSOR TARGET BOLT LOOSE. SENSOR BOLT RETIGHTENED AND GEAR SWING CARRIED OUT AND SYSTEM CHECKED SERV	ICEABLE.				2	L	7	2 	4F			RT	A28NM   					 
1997050100361	19970501	00361	WP  	1997	5	1	CA970109023      	1	19961202	G	3310	53989	LIGHT RHEOSTAT  			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					CAPT MAP LIGHT	ELECT SHORT     	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								P657716D			(CAN) ON TAXIING OUT, SMOKE OBSERVED COMING FROM CAPTAIN'S MAP LIGHT. TROUBLESHOOTING REVEALED WIRES SHORTED ON RHEOSTAT	. DEFECTIVE RHEOSTAT CHANGED.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050100362	19970501	00362	WP  	1997	5	1	CA970109024      	1	19961214	G	2530	60529042	COOLING FAN     			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					GALLEY	INOPERATIVE     	W				O	H			OTHER                   	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA								P657460D			(CAN) ELECTRICAL SMOKE FUMES IN FRONT OF GALLEY AREA DURING DESCENT. GALLEY POWER REMOVED AND SMELL DISSIPATED. MAINTENA	NCE TROUBLESHOOTING REVEALED RH COOLING FAN INOPERATIVE POPPING CIRCUIT BREAKER. DEFECTIVE FAN REPLACED AND OPERATIONALL	Y CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050100363	19970501	00363	WP  	1997	5	1	CA970109025      	1	19961217	G	2530	CA167072	ELECT SOCKET    			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					GALLEY OVEN	BROKEN WIRE     	W				O	H			OTHER                   	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA								P657239D			(CAN) ON DESCENT, STRONG ELECTRICAL SMELL COMING FROM FORWARD GALLEY. GALLEY POWER TURNED OFF. TROUBLESHOOTING REVEALED 	GALLEY OVEN UNIT PIN #3 ON RECEPTACLE WIRING SHORTED. WIRE REPAIRED AND SOCKET REPLACED. CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997063000001	19970630	00001	WP  	1997	6	30	CA970109026      	1	19961212	G	3213		OLEO SEALS      			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					NOSE LDG OLEO	LEAKING         	W				A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CL	CLIMB          	1			CA								P657363D			(CAN) AFTER TAKEOFF AND GEAR SELECTED UP, NOSE GEAR UNSAFE LIGHT CAME ON ACCOMPANIED BY A LOUD NOISE COMING FROM NOSE WH	EEL WELL AREA. QRH (QUICK REFERENCE HANDBOOK) DRILL CARRIED OUT AND AIRCRAFT LANDED SAFELY. MAINTENANCE TROUBLESHOOTING 	REVEALED NOSE OLEO FLAT AND LEAKING. NOSE OLEO SEALS REPLACED AND OLEO SERVICED. CHECK SWING CARRIED OUT SERVICEABLE.				2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050100365	19970501	00365	NE  	1997	5	1	CA970109030      	2	19961217	G	7200	HC361H0064000	FLANGE          								LYC   	ALF502	ALF502R5    	41580	NE  					AROUND LIP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LF05083			(CAN) INSPECTION FOUND CRACK AROUND ENGINE FLANGE LIP.											4	F			E6NE				 
1997050100366	19970501	00366	WP  	1997	5	1	CA970109031      	1	19961205	G	3234		SELECT LEVER    			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13      	03004	GL  					MLG	SEIZED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								501634			(CAN) LH POWER LEVER FROZEN IN CLIMB OUT. ON LANDING THE LANDING GEAR LEVER WOULD NOT RELEASE TO DOWN POSITION AND REQUI	RED THE USE OF THE EMERGENCY EXTENSION. ONCE LANDED MAINTENENACE CHECKED THE POWER LEVER AND RETRACTION SYSTEM AND BOTH 	OPERATED NORMALLY. LH POWER LEVER AND GEAR RETRACTIOIN LINKAGE AND CONTROL SYSTEMS INSPECTED FROM PEDESTAL TO LH FUEL CO	NTROL UNIT FOR CORRECT ROUTING AND OPERATION. MOISTURE WAS FOUND ON CABLES AND FUSELAGE PRESSURE SEALS LH SIDE. SUSPECT 	FROZEN CONTROLS DUE TO SLUSH THROWN INTO WHEEL WELL AND FREEZING CAUSING CONTROLS TO TEMPORARILY SEIZE. CABLES AND LINKA	GE CLEANED AND LUBRICATED AS PER MAINTENANCE MANUAL.	2	L	7	2 	4R	4	T		6A6     	E282				 
1997050600004	19970506	00004	EU  	1997	5	6	CA970110001      	1	19961218	G	2760	503243000	PIVOT ARM       			SZD   	24    	SZD244A     	8221004	EU  										DIVE BRAKE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			306  								(CAN) WHILE PERFORMING PZL-BIELSKO SB BA-047/50-3/94, THE R/H WING INBOARD DIVE BRAKE PIVOT ARM BOLT WAS FOUND COMPLETEL	Y LOOSENED OFF. THE THREADED PORTION HAD DISENGAGED FROM THE NUTPLATE. ACTIVATION OF DIVE BRAKE CAUSED POSITIVE ROTATION	 OF THE BOLT.				1	K	0	0 					G10EU   					 
1997050100369	19970501	00369		1997	5	1	CA970110004      	4	19961231	G	2350		LIGHTING PANEL  			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					CABIN SAT/COMM	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			163  					PCE93184			(CAN) WHILE IN CRUISE FLIGHT SMOKE WAS NOTED COMING FROM THE RIGHT HAND SAT/COMM AUDIO PANEL LOCATED IN THE CABIN. CIRCU	IT BREAKERS PULLED AND THE PANEL WAS REPLACED AFTER A SAFE LANDING.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997050100370	19970501	00370	CE  	1997	5	1	CA970110005      	1	19961213	G	7712	26060113	INDICATOR       		26060113    	CESSNA	208   	208B        	2073701	CE  										ENG TORQUE	LEAKING         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			98   			233					(CAN) TORQUE INDICATOR WAS NOTED TO BE LEAKING AND FILLING WITH OIL.						1	H	7	1 	3T				A37CE   					 
1997050100371	19970501	00371	NM  	1997	5	1	CA970113001      	1	19961010	G	2720	NAS755010	BUSHING         			DHAV  	DHC8  	DHC8301     		NM  										RUDDER HINGE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS REPORT FROM CAA INDICATING THAT EXCESSIVE PLAY WAS NOTED IN THE LOWER PORTION OF BOTH THE TOP AND BOTTOM TRAI	L-TO-FORE RUDDER HINGE POINTS. IT WAS FOUND THAT A BUSHING WAS MISSING. THE HINGE POINTS HAD BEEN PREVIOUSLY REPAIRED US	ING OVERSIZED BUSHES (SB 8-27-48) BUT THAT THE INTERNAL BUSHES HAD BEEN OMITTED. THERE WERE NO FLIGHT PROBLEMS REPORTED 	NOR ANY DAMAGE DUE TO THE MISSING BUSHINGS. FLEET CHECK INITIATED.			2	H	7	2 	4T			RT	A13NM   					 
1997050100373	19970501	00373	EA  	1997	5	1	CA970114003      	2	19961212	G	8550	NBSIG575	BREATHER TUBE   			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					CRANKCASE	FROZEN          	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA			12284					RL1327440			(CAN) CRANKCASE BREATHER LINE FROZE. CRANKCASE PRESURIZED AND OIL DIP STICK WAS BLOWN OUT OF SECURE POSITION. OIL WAS ES	CAPING, PILOT NOTICED OIL ON ENGINE NACELLE AND SHUTDOWN ENGINE. NO SECONDARY HOLE IN BREATHER LINE FOUND.					1	H	7	2 	3O	3	O		A17EU   	E295				 
1997050100374	19970501	00374	NM  	1997	5	1	CA970114007      	1	19961219	G	2910		0-RING          		2403001001  	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					SPOILER TRUNNION	LEAKING         	W				O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA			20440	1061 				120275			(CAN) ON CLIMB OUT CREW NOTICED #1 HYDRAULIC QUANTITY WAS DECREASING. FLAPLESS LANDING CARRIED OUT. MAINTENANCE FOUND TH	AT THE FLIGHT SPOILER UNLOADING VALVE WAS LEAKING AT THE LOWER TRUNNION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997050100375	19970501	00375	EA  	1997	5	1	CA970114008      	1	19961220	G	7922	37031	THERMOSTAT ACT  			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	OIL COOLER	FAULTY          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J	K		WARNING INDICATION        	FLUID LOSS                		CL	CLIMB          	1			CA			12516					PCE86394	237121		(CAN) FIFTEEN MINUTES IN CLIMB THE #2 ENGINE BEGAN TO LOSE OIL PRESSURE. THE CREW ELECTED TO SHUT THE ENGINE DOWN. POST 	FLIGHT INSPECTION FOUND THE OIL COOLER VERNATHERM THERMOSTATIC ACTUATOR WAS LEAKING CAUSING A GRADUAL LOSS OF OIL PRESSU	RE. FURTHER INSPECTION FOUND THE "O" RING HAD BECOME FLATTENED AND HARDENED OVER TIME. THE "O" RING WAS REPLACED AND THE	 AIRCRAFT RETURNED TO SERVICE.			2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
1997050100376	19970501	00376	EU  	1997	5	1	CA970114009      	2	19961230	G	7311	KB35782A	OIL COOLER      			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    		EU  					#1 ENGINE	CRACKED CORE    	W				D	E			RETURN TO BLOCK         	ENGINE SHUTDOWN         			J	K		WARNING INDICATION        	FLUID LOSS                		TX	TAXI/GRND HDL  	1			CA			24411	4191 				19181			(CAN) AIRCRAFT DEPARTED RAMP WHEN PILOT RECEIVED A LOW OIL PRESSURE WARNING FROM THE #1 ENGINE. AIRCRAFT RETURNED TO RAM	P. INSPECTION FOUND THE OIL COOLER HAD FAILED RESULTING IN LOST OF OIL AND SUBSEQUENT LOW OIL PRESSURE WARNING.					2	L	7	2 	3T	4	T		A24EU   	A196				 
1997050100377	19970501	00377	SO  	1997	5	1	CA970114010      	2	19961229	G	8530	CH73ER	CYLINDER        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	#5 POSITION	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			1024 					L276323R	931863		(CAN) #1 ENGINE RUNNING ROUGH ON TAKEOFF. AIRCRAFT RETURNED TO BASE. POST FLIGHT INSPECTION FOUND #5 CYLINDER HEAD SEPAR	ATED FROM THE BARREL, WITH A THREE INCH CRACK FROM THE INTAKE VALVE TO THE INTAKE PORT.					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
1997050100378	19970501	00378	CE  	1997	5	1	CA970114011      	1	19961227	G	2140	CAS40121	HEATER          	SOUTHWIND   	8472C       	CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					CABIN	PUMP FAILED     	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			156  			5436		L519205			(CAN) THE HEATER FAILED IN CRUISE FLIGHT AND COULD NOT BE RESTARTED. MAINTENANCE FOUND THE IGNITION COIL SWOLLEN AND LEA	KING OIL AND THE FUEL PUMP ALSO LEAKING. UNITS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
1998040200027	19980402	00027	CE  	1998	4	2	CA970114012      	1	19961231	G	3240		BRAKE           			CESSNA	500   	500CESSNA   	2076602	CE  										RT MAIN	FROZEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE AIRCRAFT LANDED AND THE RT MAIN WHEEL SKIDDED AND EVENTUALLY BLEW.  INVESTIGATION REVEALED THAT THE RT BRAKE H	AD ICED UP AND SUBSEQUENTLY FROZE UP.  THE AIRPORT OF DEPARTURE HAD SOME SNOW ON THE RUNWAY AND CAUSED THE ICING.  AIRCR	AFT MOVED TO HANGAR FOR WARMING AND BRAKE FREELY ROTATED.				1	L	7	2 	4F				A22CE   					 
1997050100379	19970501	00379	CE  	1997	5	1	CA970114013      	1	19960912	G	2720	07600129	RUDDER BAR      	CESSNA      	07600129    	CESSNA	185   	A185F       	2072821	CE  						MCAULY	2A34C	D2A34C58    	GL  	RUDDER PEDAL LT	BROKEN          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			3992 						748323		(CAN) WHILE TAXIING THE RUDDER BAR BROKE AT THE OUTBOARD PEDAL ATTACH REINFORCEMENT. SE 72-36 MOD. FOUND AND INCORPORATE	D.					1	H	7	1 	3O				3A24    		5	C	P3EA	 
1998040200028	19980402	00028	CE  	1998	4	2	CA970114015      	1	19961220	G	3230	AN8336D	ELBOW           			LEAR  	35    	31A         	5170531	CE  										RETRACT ACTUATOR	LOOSE           	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA			420  								(CAN) DURING A WALK AROUND, HYDRAULIC FLUID WAS NOTICED LEAKING FROM THE NOSE GEAR AREA.  GEAR AREA CLEANED UP AND GEAR 	SWING CARRIED OUT.  FLUID NOTICED LEAKING FROM AROUND THE RETRACT LINE OF THE NOSE GEAR ACTUATOR.  FITTING FOUND TO BE L	OOSE.  FITTING TIGHTENED AND LEAK CHECK CARRIED OUT.   PART TC:  279.				2	L	7	2 	4F			RT	A10CE   					 
1997050100380	19970501	00380	NE  	1997	5	1	CA970114016      	1	19961221	G	7921	481141029	OIL COOLER      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  	HAMSTD	14SF	14SF5       	NE  	NR1 ENG	CRACKED CORE    	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J	K		WARNING INDICATION        	FLUID LOSS                		TO	TAKEOFF        	1			CA			9655 	4286 		AC10141		120721	880920		(CAN) ON TAKEOFF ROLL, THE CREW NOTED A LOW OIL PRESSURE ON #1 ENGINE. AIRCRAFT RETURNED TO BLOCKS. OIL COOLER CORE FOUN	D CRACKED AND LEAKING.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
1997050100381	19970501	00381	EU  	1997	5	1	CA970114018      	1	19961223	G	2430	10200311	GCU             	AUXILEC     		AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  	HAMSTD	14SF	14SF5       	NE  	#1 ENG	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			13835			512734		120905	880501		(CAN) AFTER STARTING #1 ENGINE DURING TAXI, THE CREW OBSERVED A DC GENERATOR FAULT. THE AIRCRAFT WAS RETURNED TO THE BLO	CKS. #1 GCU REPLACED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
1997050100383	19970501	00383	EA  	1997	5	1	CA970114020      	1	19961226	G	3260		SENSOR          			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					NLG	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			4369 					807213			(CAN) NOSE GEAR WOULD NOT RETRACT. NOSE GEAR SENSOR FOUND OUT OF ADJUSTMENT. RIGGED AS PER MAINTENANCE MANUAL.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050100384	19970501	00384	WP  	1997	5	1	CA970114022      	1	19961226	G	3231		GEARDOOR        			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					RH MAIN LDG	NO EXTENSION    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P656860D			(CAN) ON RETRACTION RH LANDING GEAR UNSAFE LIGHT REMAINED ON WITH GEAR DOOR OPEN LIGHT. RECYCLED GEAR AND DOWN LOCK INDI	CATION NORMAL. GEAR RETRACTED GIVING SAME RESULTS. AIRCRAFT RETURNED TO BASE. INSPECTION REVEALED SOME DAMAGE TO RH LAND	ING GEAR CUT OUT AREA OF FUSELAGE. SUSPECT RH MAIN LANDING DOOR DID NOT EXTEND ON RETRACTION, CAUSING DAMAGE TO FALSE WO	RK AFT OF RH MAIN LANDING GEAR. BOTH MAIN LANDING GEAR OLEOS SERVICED AND FALSE WORK REPAIRED. SEVERAL LANDING GEAR CHEC	K SWINGS CARRIED OUT SERVICEABLE.		2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050100385	19970501	00385	EA  	1997	5	1	CA970114023      	1	19961230	G	5210	H34149	DOOR HANDLE     			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	FAILED          	W				B	I			EMER. DESCENT           	CABIN DEPRESSURIZATION  			J			WARNING INDICATION        			CL	CLIMB          	1			CA			1537 					GEE807365			(CAN) CLIMBING THROUGH 14,000 FEET, THE CREW GOT A DOOR HANDLE WARNING FOLLOWED BY A PASSENGER DOOR WARNING. THE FLIGHT 	THEN DESCENDED THROUGH 13,000 FEET AND DEPRESSURIZED. THE WARNING LIGHT WENT OUT. OUTER DOOR HANDLE REPLACED AND DOOR ME	CHANISM RIGGED AS PER MAINTENANCE MANUAL.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050100386	19970501	00386	EA  	1997	5	1	CA970114024      	1	19961227	G	3260		SENSOR          			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG S23	ICED UP         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			3637 					807165			(CAN) UNABLE TO RAISE NOSE LANDING GEAR. FOUND ICE ON SENSOR #S23 AND TARGET. SENSOR AND TARGET CLEANED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050100391	19970501	00391	CE  	1997	5	1	CA970115001      	1	19961230	G	3211	1091200281	DRAG LEG        			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA			3581 					PCE92278			(CAN) AIRCRAFT LANDED ON ICY RUNWAY WITH FROZEN BRAKES AND CAME TO A JARRING STOP WHEN CLEAR RUNWAY WAS ENCOUNTERED. INS	PECTION FOUND THE RADII OF THE LEFT HAND DRAG LEG CRACKED.					1	L	7	2 	4T	4	T		A31CE   	E4EA				 
1997050600005	19970506	00005	NE  	1997	5	6	CA970115004      	2	19961223	G	7200		ENGINE          			BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5352    	54509	NE  					POWER SECT	MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			AP	APPROACH       	1			CA				3957 				7149			(CAN) ENGINE WAS SHUTDOWN DURING APPROACH DUE TO ILLUMINATED OIL PRESSURE WARNING LIGHT. POST FLIGHT INSPECTION FOUND ME	TAL IN THE OIL FILTER. THE ENGINE WAS REMOVED.					2	L	7	2 	3T	4	T		A24EU   	E297				 
1997050100394	19970501	00394	EU  	1997	5	1	CA970115007      	1	19961017	G	6330	350A38101832	CROSSBEAM       			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					XMSN MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								257			(CAN) DGACD AD 96-156-071(B) CARRIED OUT, CRACK IN RADIUS OF THIN ATTACHMENT LUG FOUND.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997050800725	19970508	00725	SO  	1997	5	8	CA970124002      	2	19961216	G	8520		TRANSFER TUBE   			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	CRANKSHAFT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1740 				286169R	792737		(CAN) DURING TEARDOWN OF A TIME EXPIRED ENGINE IT WAS DISCOVERED THE OIL TRANSFER TUBE IN THE CRANKSHAFT TO THE #6 CONNE	CTING ROD HAD WORKED LOOSE AND BEGAN WEARING INTO THE CONNECTING ROD BEARING. THIS TUBE IS FIXED AT MANUFACTURE. THE CRA	NKSHAFT WAS SCRAPPED.				1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P47GL	 
1997051300022	19970513	00022	CE  	1997	5	13	CA970124003      	1	19961004	G	6120	993800075	CONTROL CABLE   			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RT PROP	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			12677					PCE52489	FY952		(CAN) CABLE BROKE WHERE IT ATTACHES TO THE BELLCRANK ASSEMBLY UNDER THE PEDESTAL. CABLE BROKE AT THE SWAGE INSIDE THE TE	LESCOPING TUBES. SUBMITTER STATES CABLE INSPECTION IS DIFFICULT AT THIS LOCATION. PILOTS REPORTED ROUGHNESS IN THE CONTR	OL FOLLOWED BY THE FAILURE WHEN FORCE APPLIED. NEW PART INSTALLED.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	5	C	STC	 
1997050800737	19970508	00737	WP  	1997	5	8	CA970129008      	1	19961123	G	2910	7927177799	HYDRAULIC LINE  			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					RT HYD SYS	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA								P654119D			(CAN) DURING TEST FLIGHT, RIGHT HYDRAULIC FLUID LOST. HYDRAULIC BRAKE PRESSURE READ 3400 P.S.I. PRIOR TO PRESSURE LOSS. 	NEW HYDRAULIC LINE FABRICATED AND INSTALLED AND LEAK CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050800738	19970508	00738	WP  	1997	5	8	CA970129009      	1	19961124	G	2120	9267531	DUCT            			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					LH AIRCONDITION	DAMAGED         	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA								P656844D			(CAN) AT FLIGHT LEVEL 350 PRESSURIZATION UNCONTROLLABLE FLOW LIGHT CAME ON. EMERGENCY DESCENT CARRIED OUT. MAINTENANCE T	ROUBLESHOOTING FOUND DUCTING ON LEFT HAND AIR CYCLING MACHINE DETACHED AND DUCTING ON RH PACK CRACKED AND FLEX CONNECTOR	 BROKEN. DUCTING ON LH AIR CONDITIONING AIR CYCLING MACHINE CONNECTED AND SECURED. DUCTING AND CONNECTOR ON RH AIR CYCLI	NG MACHINE REPLACED AND OPERATIONAL LEAK CHECK CARRIED OUT SERVICEABLE.			2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050800739	19970508	00739	WP  	1997	5	8	CA970129011      	1	19961124	G	2780	59225321	SLAT            			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					#2 L/H EXT BRKT	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA								P654059D			(CAN) NO SLAT EXTEND LIGHT ON AND SLAT DISAGREE LIGHT ON. LOUD BANG HEARD AT FLAPS 40 DEGREES. TROUBLESHOOTING FOUND SLA	T L/H #1 IDLER EXTEND BRACKET BROKEN. MAINTENANCE REPLACED #2 L/H SLAT AND NEW L/H #1 IDLER BRACKET INSTALLED. OPERATION	AL CHECK CARRIED OUT SERVICEABLE.				2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050800740	19970508	00740	WP  	1997	5	8	CA970129012      	1	19961129	G	3244	JT8D7B	TIRE            			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					#4 TIRE	BLOWN           	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA								P657716D			(CAN) DURING TAKEOFF ROLL, AIRCRAFT MADE A LURCH TO THE RIGHT ACCOMPANIED BY COMPRESSOR POP AND BLIP IN RIGHT ENGINE PRE	SSURE RATIO AND FOLLOWED BY A BURNING RUBBER SMELL. ALL INDICATIONS SUBSEQUENTLY RETURNED TO NORMAL. MAINTENANCE INVESTI	GATION REVEALED #4 TIRE HAD BLOWN AND PIECES WERE INGRESSED INTO RH ENGINE, SOME COMPRESSOR FAN BLADES WERE FOUND DAMAGE	D. RH ENGINE CHANGED.			2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050800741	19970508	00741	EU  	1997	5	8	CA970129013      	1	19961121	G	5610	STA320261	WINDSHIELD      			AIRBUS	320   	A320211     	3930320	EU  										FORWARD POSITION	SHATTERED       	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT FLIGHT LEVEL 390 FIRST OFFICERS WINDSHIELD SHATTERED. THERE WAS NO FORWARD VISIBILITY THROUGH WINDSHIELD. FLIGH	T DESCENDED TO FLIGHT LEVEL 230. AIRCRAFT REQUIRED TO LAND AT ALTERNATE BASE. UPON ARRIVAL MAINTENANCE INSTALLED NEW WIN	DSHIELD.				2	L	7	2 	4F			RT	A28NM   					 
1997050800742	19970508	00742	EA  	1997	5	8	CA970129014      	1	19961125	G	2750	860D10018ABC	FECU            	CNDAIR      		CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					FLAPS	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			3026 					807267			(CAN) FLAPS FAILED AFTER TAKEOFF. CIRCUIT BREAKER RESET - NO GOOD. FLAPS STUCK AT 8 DEGREES. REPLACED FLAP ELECTRONIC CO	NTROL UNIT AND ALSO BRAKE POSITION SENSING UNIT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050800743	19970508	00743	EA  	1997	5	8	CA970129015      	1	19961119	G	3230		PROXIMITY SWITCH			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					NOSE GEAR	OUT OF ADJUST   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			5036 					807157			(CAN) NOSE GEAR WOULD NOT RETRACT. LANDING GEAR EXTEND AND RETRACT CENTRE PROXIMITY SWITCH ADJUSTED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050800744	19970508	00744	NE  	1997	5	8	CA970129016      	2	19961227	G	7220		FAN BLADES      								PWA   	4056  	PW4056      		NE  					#2 ENGINE	DAMAGED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA								P724414			(CAN) HIGH VIBRATION ON #2 ENGINE WITH FAN BLADE SHINGLING. INSPECTION FOUND ALL FAN BLADES SHINGLED, MANY BLADES DAMAGE	D AT MID SPAN SHROUD AREA, TWO BLADES ARE BENT OR TWISTED, MANY BLADES WTIH CONTACT SURFACES "B" AND "A" DAMAGED. THE EN	GINE PICKED UP HEAVY SNOW (OR SLUSH) DURING TAKEOFF. ALL FAN BLADES REMOVED. STAGE 2 FAN EXIT VANES AND EXHAUST CHECKED 	SERVICEABLE. FAN BLADE SET WAS REPLACED. ENGINE GROUND RUN AND VIBRATION SURVEY CARRIED OUT SERVICEABLE.								4	F			E24NE				 
1997050800747	19970508	00747		1997	5	8	CA970130003      	4	19961119	G	2210	169	AMPLIFIER       	COLLINS     	5222852001  	CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					AUTO PILOT	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						169		501421			(CAN) AUTO PILOT CAME OFF LINE AND COCKPIT FILLED WITH SMOKE.  TROUBLESHOOTING OF PROBLEM REVEALED AUTO PILOT AMP WAS DE	FECTIVE.  AMP REMOVED AND SYSTEM DEACTIVATED, ALSO WIRING IN THE AREA WAS INSPECTED  NO OTHER FAULT FOUND.					2	L	7	2 	4R	4	T		6A6     	E282				 
1997050800748	19970508	00748	CE  	1997	5	8	CA970130004      	1	19961105	G	3260	MS243311	SWITCH          	MITSUELECT  		MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					NLG	WIRE BROKEN     	W				L				ABORTED APPROACH        				J	N		WARNING INDICATION        	FALSE WARNING             		AP	APPROACH       	1			CA								P20276C			(CAN) ON APPROACH THE CREW WERE UNABLE TO GET A GREEN LIGHT ON THE NOSE GEAR. THE SYSTEM WAS CYCLED AND A SUCCESSFUL LAN	DING WAS MADE. INVESTIGATION REVEALED A BROKEN WIRE AT THE ENTRY TO THE SWITCH LOCATION. THE SWITCH WAS REPLACED AND GEA	R SWINGS CHECKED OUT.				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
1998040200035	19980402	00035	GL  	1998	4	2	CA970131001      	2	19960930	G	7250	6871505	BEARING         								ALLSN 	250C  	250C20B     	03013	GL  					TURBINE NR 5	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								CAE831949			(CAN) DURING GROUND RUN PROCEDURE, THE MAGNETIC CHIP DETECTOR LIGHT CAME ON.  ENGINE SHUT DOWN IN NORMAL CONDITION.  MET	ALLIC PARTICLES WERE FOUND ON THE BOTTOM OF THE CHIP DETECTOR.  TURBINE REMOVED AND DISMANTLED.  NR 5 BEARING BALL RETAI	NER FOUND BROKEN.  FURTHER INSPECTION FOUND NO OTHER FAULT WITH ENGINE.  TURBINE REBUILT.									3	U			E4CE				 
1997050800763	19970508	00763	EA  	1997	5	8	CA970203009      	2	19961126	G	8520	11F20022D3	CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					#6 CYL FLANGE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1588 				L51968A			(CAN) PILOT REPORTED AN OIL LEAK, INSPECTION FOUND THE CRANKCASE WAS CRACKED ALONG THE #6 CYLINDER FLANGE.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997051500279	19970515	00279	EU  	1997	5	15	CA970203016      	1	19961215	G	2721	1415502297	BRACKET         			BAG   	JETSTM	JETSTM4112  		EU  										RUD TRIM	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			4312 								(CAN) PRONOUNCED FLUTTER IN FLIGHT FROM RUDDER. RUDDER TRIM UPPER BEARING ASSEMBLY REPLACED.						1	L	7	2 	4T			RT	A196    					 
1997051500289	19970515	00289	CE  	1997	5	15	CA970206010      	1	19961218	G	7810		EXHAUST DUCT    			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					SKI JUMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P50702			(CAN) PIECE OF SKI JUMP BROKE OFF AND CAME IN CONTACT WITH THE POWER TURBINE. DEFECT FOUND DURING A ROUTINE NOZZLE CHANG	E. POWER SECTION SENT FOR REPAIR, THE EXHAUST DUCT WAS FOUND WITH A FAILED SKI JUMP AND INNER SECTION. THE FAILED MATERI	AL FROM THE EXHAUST DUCT MOVED UP INTO THE PATH OF THE POWER TURBINE. THIS MATERIAL IMPACTED AND RUBBED ALL THE POWER TU	RBINE BLADES AND CAUSED THE INSULATION BLANKET TO BE TORN APART. FAILURE OF THE SKI JUMP AREA OF THE EXHAUST DUCT MAY BE	 DUE TO THE PROPAGATION OF A CRACK IN THIS SECTION OR ROTATION OF THE #3 BEARING COVER INSIDE THE INNER CONE AREA OF THE	 EXHAUST DUCT. SB 1430 WAS EMBODIED WHICH INCORPORATES AN INTEGRAL #3 BEARING COVER WITH THE INNER SECTION OF THE EXHAUS	1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997061900515	19970619	00515	SO  	1997	6	19	CA970206012      	1	19961212	G	2436		WIRE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					VOLTAGE REGULATR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			1213 					PCE51676			(CAN) SUBMITTER SUSPECTS INCORRECT WIRING OF SYSTEM PERFORMED. VARIOUS FAULTS WITH VOLTAGE REGULATOR AND GENERATOR SYSTE	MS.					1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
1997051500297	19970515	00297	EA  	1997	5	15	CA970210007      	2	19961107	G	7314	0532310103	FUEL PUMP       			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					#2 ENGINE	FAULTY          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA				5503 				PCE40068			(CAN) ON APPROACH IT WAS NOTICED THE FUEL FLOW FLUCTUATED WHEN THE POWER WAS RETARDED ON THE #2 ENGINE. ALL OTHER #2 ENG	INE PARAMETERS WERE NORMAL. AFTER LANDING AND PASSENGERS DEPLANING AN ENGINE GROUND RUN WAS CARRIED OUT. WHEN THE POWER 	LEVER WAS ADVANCED BEYOND FLIGHT IDLE THE FUEL FLOW WOULD FLUCTUATE AND A POPPING SOUND COULD BE HEARD FROM THE #2 ENGIN	E. THE #2 ENGINE FUEL CONTROL UNIT AND THE ENGINE FUEL PUMP WERE REPLACED AND THE ENGINE GROUND RUN SERVICEABLE. THE FCU	 AND FUEL PUMP WERE SENT FOR INSPECTION AND INVESTIGATION.		1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997051500298	19970515	00298	EA  	1997	5	15	CA970210008      	2	19961112	G	7414	4370	MAGNETO         	SLICK       		PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					LH MAGNETO	FAULTY          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				391  		94080245		L2371751A			(CAN) ENGINE SHUTDOWN WITHOUT INCIDENT. ON NEXT START BOTH THE RIGHT HAND AND LEFT HAND MAGNETOS WERE DEAD, NO SPARK.						1	H	7	2 	3O	3	O		A31EU   	1E10				 
1997051500311	19970515	00311	NE  	1997	5	15	CA970217002      	2	19960203	G	7322		FUEL CONTROL    			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					#3 ENGINE	FAULTY          	W				A	F			UNSCHED LANDING         	ACTIVATE FIRE EXT.      			O			OTHER                     			CL	CLIMB          	1			CA								653874			(CAN) ON DEPARTURE THE CREW NOTICED EXCESSIVE DUCT PRESSURE AND A DROP OF E.P.R. ON #3 ENGINE, THE AIRCRAFT DIVERTED. PO	ST FLIGHT MAINTENANCE TROUBLE SHOOTING REPLACED THE FUEL CONTROL UNIT; PRESSURE RATIO BLEED CONTROL VALVE AND THE START 	BLEED CONTROL VALVE. A BOROSCOPE INSPECTION WAS CARRIED OUT AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997051500312	19970515	00312	NE  	1997	5	15	CA970217003      	2	19960205	G	7230	766933001	COMPRESSOR CASE 			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					#3 ENGINE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA				2058 		UAL332		653874			(CAN) ON DEPARTURE THE CREW OBSERVED HIGH N2, HIGH FUEL FLOW AND HIGH EGT AND AN ABNORMALLY HIGH ACCELERATION RATE ON #3	 ENGINE. THE AIRCRAFT DIVERTED. POST FLIGHT INSPECTION FOUND THE 12 O'CLOCK POSITION 8TH STAGE BLEED VALVE HAD SEPARATED	 FROM THE COMPRESSOR CASE ALONG THE WELD SEAM OF THE MOUNTING PAD FOR THE VALVE. THE VALVE ASSEMBLY WAS FOUND IN THE AFT	 PORTION OF THE ENGINE, LODGED AGAINST THE MIXER ASSEMBLY.			2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997052900238	19970529	00238	EA  	1997	5	29	CA970226004      	2	19961016	G	7230	3015956	SPACER          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					2ND STAGE COMP	DAMAGED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			9349 	3398 				CPPS60514			(CAN) DURING A START ATTEMPT OF #1 ENGINE THE PILOT WAS UNABLE TO OBTAIN ANY N1 ROTATION. WHEN A SECOND START WAS ATTEMP	TED AN AUDIBLE "CLUNK" WAS HEARD. THE STARTER GENERATOR AND TACHOMETER WERE REMOVED TO ATTEMPT TO MANUALLY ROTATE N1 DRI	VE. NO ROTATION WAS POSSIBLE. THE POWER SECTION WAS REMOVED AND DISASSEMBLY FOUND DAMAGE TO THE COMPRESSOR BLADES, STATO	R, SPACER AND AIR SEAL.			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1997060500759	19970605	00759	NE  	1997	6	5	CA970305001      	2	19960429	G	7240	726560	COMBUSTION CASE 			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					INNER COMB CASE	LIBERATED       	W		A		K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA								848940			(CAN) THE ENGINE WAS REMOVED AND SENT FOR INVESTIGATION DUE TO HIGH EGT AND TREND ANALYSIS THAT INDICATED HOT SECTION DI	STRESS. INVESTIGATION FOUND THE INNER COMBUSTION CASE HAD LIBERATED FROM THE FORWARD FLANGE. IT APPEARED TO SUFFER FROM 	METAL FATIGUE. ALL THE HARDWARE ATTACHED TO THE INNER COMBUSTION CASE SHIFTED AFT CAUSING STATIONARY PARTS TO RUB ON THE	 1ST STAGE TURBINE. THE INNER HEAT SHIELDS REMAINED INTACT PREVENTING A FIRE. THE REPORT SUGGESTS THAT CATASTROPHIC FAIL	URE WAS IMMINENT.		2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997060500771	19970605	00771	SW  	1997	6	5	CA970311016      	1	19960906	G	7712	32447065	TORQUE CONTROL  			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					#1 ENGINE	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA			3658 	963  				CPPS60963			(CAN) 25 PERCENT TORQUE SPLIT. #1 ENGINE 3-4 PERCENT LOW N1, 50-70 DG LOW.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1999081200320	19990812	00320	SW  	1999	8	12	CA970311062      	1	19961121	G	5313	206031314023	LONGERON        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE BAY	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								CAE800471BA			(CAN) AN UNAPPROVED REPAIR WAS INCORPORATED ON THE ENGINE LONGERON.  THE STRUCTURAL REPAIR MANUAL DOES NOT ALLOW REPAIR 	OF THIS ASSY.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1999081200321	19990812	00321	SW  	1999	8	12	CA970311072      	1	19961125	G	5320	206031314049	CHANNEL         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								CAE821443			(CAN) UNAPPROVED REPAIR INCORPORATED.  NO REPAIRS ALLOWED IN THIS AREA PER STRUCTURES REPAIR MANUAL.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2000020500771	20000205	00771	SO  	2000	2	5	CA970312003      	1	19961228	G	5280	4752932	HINGE           			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE41649	BU5276		(CAN) RIGHT INBOARD GEAR DOOR CRACKED.   APPROXIMATELY .250 INCH DEEP AND ORIGINATING AT INSIDE RADIUS OF CURVE.   REPAI	RED.					1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA	 
1998040200059	19980402	00059		1998	4	2	CA970326005      	1	19961112	G	6320	4638305024	BEARING         																	LT INPUT MGB	PEELING         	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA			2517 								(CAN) LEFT HAND INPUT BEARING,ON MAIN TRANSMISSION, PEELING.																			 
1997061200852	19970612	00852	CE  	1997	6	12	CA970326007      	1	19961120	G	5610	LP345	WINDSHIELD      			CESSNA	172   	172M        	2072418	CE  										CORNERS	DISTORTED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) NEW WINDSHIELD ORDERED.  WINDSHIELD FOUND UNACCEPTABLE BY CUSTOMER. DISTORTION PREVENTED CLEAR VIEW. A SECOND WIND	SHIELD ORDERED WAS ALSO FOUND UNACCEPTABLE DUE TO DISTORTION P/N 0513230-12.					1	H	7	1 	3O			NT	3A12    					 
1999081200322	19990812	00322	SW  	1999	8	12	CA970327011      	1	19961114	G	2913	41000455	BOLT            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					HYDRAULIC SERVO	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				1136 				CAE8223126			(CAN) SERVO SENT FOR REPAIR.  PER AD CF96-11R2 AND BELL SB 206-67A-01, A BOLT WAS FOUND SUSPECT.  UNIT REPAIRED, BOLT RE	PLACED.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997071700397	19970717	00397	CE  	1997	7	17	CA970421022      	1	19961204	G	5730		SKIN            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	WS 63.45	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4050 	4050 				290440R	890661		(CAN) WING SKIN CRACKED, APPROXIMATELY 3 INCHES LONG, DEVELOPED ON TOP SKIN AT STATION 63.45 RUNNING FORE AND AFT BETWEE	N BULKHEAD AND MAIN GEAR SIDE BRACE UPPER ATTACH POINT REINFORCEMENT. SUBMITTER STATES THAT THEY ARE DIFFICULT TO DETECT	 PRIOR TO BECOMING 3 INCHES IN LENGTH, DUE TO CARPET AND OTHER ITEMS. THEY REPORT HAVING REPAIRED 3 SIMILAR CRACKS IN C4	01 AND C402 AIRCRAFT.			1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
1998041700529	19980417	00529	WP  	1998	4	17	CA970422023      	1	19960416	G	6300	COO75	FANSHAFT        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TAPERED SHAFT	FRETTING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			400  					L2486340A			(CAN) FANWHEEL REMOVED FOR OTHER MAINTENANCE.  FRETTING AND METAL TRANSFER NOTICED BETWEEN THE FANSHAFT AND FANWHEEL.						1	G	7	1 	3O	3	O		H11NM   	E295				 
1997070300309	19970703	00309	EA  	1997	7	3	CA970508001      	2	19960727	G	8500		ENGINE          			PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320D2A     	41508	EA  					OIL SCREEN	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L488439			(CAN) DURING ANNUAL INSPECTION METAL FILINGS WERE FOUND IN THE ENGINE OIL SCREENS. THE AIRCRAFT REMAINS GROUNDED PENDING	 ENGINE TEARDOWN.					1	L	7	1 	3O	3	O		2A13    	E274				 
1998041700555	19980417	00555	SW  	1998	4	17	CA970513007      	1	19960430	G	3213	206033108001	SADDLE          			BELL  	206   	206L4       	1182110	SW  										CROSSTUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKID GEAR SHIFTED LATERALLY ALLOWING SADDLE TO WEAR ON LUG ON SKID CROSS TUBE.						1	G	7	1 	3U			NC	H2SW    					 
1997072500029	19970725	00029	GL  	1997	7	25	CA970527012      	3	19960522	G	6111	S82NC2	BLADE           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			630  					279872R	860568		(CAN) PROPELLER RECEIVED FOR OVERHAUL. PROPELLER BLADE WAS FOUND WITH CRACKED THREADS. PROPELLER WAS NEW IN 1986, CORROS	ION INSPECTION CARRIED OUT IN 1992. THIS WAS THE FIRST OVERHAUL, NOT REQUIRED BY CARS, BUT DONE AT CUSTOMERS REQUEST. TH	E PROPELLER WAS SCRAPPED AND REPLACED WITH A NEW HARTZELL.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997110600629	19971106	00629	NE  	1997	11	6	CA970820010      	3	19961106	G	6111	7756722	BLADE PIN       	HAMSTD      	SFA13M10A   											HAMSTD	14SF	14SF7       	NE  	PROP BLADE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				6881 		852797					(CAN) INCORRECT BLADE PIN WAS FOUND INSTALLED. NO PART NUMBER ON THE PIN. HAMILTON STANDARD HAVE SIMILAR LOOKING PARTS, 	THE DIFFERENCES ARE DASH NUMBER AND LENGTH. 775672-1 LENGTH 2.48", 775672-2 LENGTH 2.58". SB 14SF-61-A43 WAS ISSUED TO A	DDRESS THIS PROBLEM. THE SUBMITTER STATES THIS IS THE SECOND TIME HE HAS CAME ACROSS THIS PROBLEM.														6	C	P7NE	 
1999043000071	19990430	00071	WP  	1999	4	30	CA971128007      	2	19960709	G	7210	3583605	BEARING         			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER SHAFT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				466  					CDA3110		(CAN) AFT PROPELLER SHAFT BEARING FOUND CORRODED.						1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40E	 
1998111800012	19981118	00012	EA  	1998	11	18	CA980915004      	2	19960621	G	7414	4353	MAGNETO         								LYC   	O360  	AEIO360A1E  	41514	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			396  					L2662551A			(CAN) DURING FLIGHT, THERE WAS AN EXCESSIVE DROP ON RIGHT HAND MAGNETO.  AIRCRAFT LANDED.  DURING GROUND RUN BY MAINTENA	NCE THE RT MAG FAILED.  RT MAG SIMULTANEOUSLY FIRING ON ALL 4 PLUGS.  RT MAG REPLACED WITH NEW UNIT.										3	O			1E10				 
1996040500073	19960405	00073	WP  	1996	4	5	CHI1515          	1	19960205	G	6410	369D2161531	BLADE           			HUGHES	369   	369E        	4470707	WP  										T/R	CRACKED         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1611W	3394 			0022221331	0319E				TAIL ROTOR BLADE, PN 369A1619-17, WAS FOUND CRACKED AT ONE OF THE MOUNTING RIVET HOLES.  THE CRACK EXTENDED FROM THE RIV	ET TO THE OUTBOARD EDGE OF FITTING.  (X)					1	G	7	1 	3U				H3WE    					 
1996042400001	19960424	00001	CE  	1996	4	24	CHI1542          	1	19960104	G	2910	51001198	HYD LINE        			CESSNA	414   	414A        	2075907	CE  										RT WING	CORROSION PIT   	B			CHIR	O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			NM	09	2712V	2377 				414A0610				DURING FLIGHT TO 'RUN IN' NEW CYLINDER NR 5 RIGHT ENGINE, 40 MINUTES INTO FLIGHT HYDRAULIC FLOW LIGHTS STARTED TO FLICKE	R ON AND OFF.  WITHIN 10 MINUTES BOTH LIGHTS FLICKERING STAYING ON LONGER.  DECIDED TO SLOW AIRCRAFT AND EXTEND GEAR.  W	HEN ACTUATED ONLY MAINS CAME DOWN AND LOCKED, PUT GEAR DOWN WITH EMERGENCY SYSTEM PER P.O.H., NOSE GEAR LOCKED DOWN, LAN	DED AIRCRAFT.  (X)			1	L	7	2 	3O				A7CE    					 
1996072500275	19960725	00275	SW  	1996	7	25	CHI1543          	1	19960430	G	6410	206016201103	BLADE           		2060118103  	BELL  	206   	206B        	1181511	SW  										T/R	DELAMINATED     	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	10ED	1516 			TAH2183	1960				BOTH BLADES WERE FOUND DELAMINATED ON THE DOUBLERS AT THE BUTT END.  NOTE:  THE BLADES WERE REPAINTED IN 1991 - 353.7 HO	URS AGO.  REFERENCE:  OPERATOR CONTROL NR 96ZZZX3668.  (X)					1	G	7	1 	3U				H2SW    					 
1996101700261	19961017	00261	WP  	1996	10	17	CHI1593          	1	19960916	G	3213	369D292115	SKID TUBE       			HUGHES	369   	369D        	4470706	WP  										LEFT	CRACKED         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	501CH					170050D				LEFT GEAR SKID TUBE CRACKED ON BOTH SIDES UNDER FORWARD GEAR LEG SADDLE.  CRACKS ORIGINATE FROM NUTPLATE ACCESS HOLE ON 	BOTTOM SIDE UNDER ABRASION STRIP AND PROGRESS UPWARD ON BOTH SIDES THROUGH ENTER HOLES (UNUSED) AND STOP APPROXIMATELY 2	.25 INCHES FROM EACH OTHER.  REPLACED SKID TUBE WITH NEW PART.  SOR MSG NR 056845 SENT TO MDHC.  CRACKED SECTION OF TUBE	 BEING SENT TO MDHC FOR FURTHER INVESTIGATION.  (X)			1	G	7	1 	3U				H3WE    					 
1996110700279	19961107	00279	WP  	1996	11	7	CHI1595          	1	19960904	G	6210	369A10045	BLADE PIN       			HUGHES	369   	369D        	4470706	WP  										M/R BLADE	FAILED          	B		A	CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	502CH				0098846097	180252D				DURING THE 100-HOUR INSPECTION WHILE BLADES WERE BEING REMOVED FOR INSPECTION, THE MAIN ROTOR BLADE PIN S/N 09884-6097 F	ELL APART.  THE BLADE PIN SHANK BROKE AT THE POINT WHERE THE THREADS START.  PART TT:  4667.2.  PART HAS A LIFE LIMIT OF	 7600 HRS.  (X)				1	G	7	1 	3U				H3WE    					 
1997021300228	19970213	00228	WP  	1997	2	13	CHIR823C         	1	19961231	G	6420	369D2170721	BEARING         		369D21610503	HUGHES	369   	369E        	4470707	WP  										T/R YOKE	DISBOND         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1611W		1155 		W39420862	0319E				DURING 300-HOUR INSPECTION, ONE OF THE OUTBOARD ELASTOMERIC BEARINGS FELL OUT WHEN THE T/R ASSY WAS DISASSEMBLED.  THE G	LUE BOND HAD FAILED.  THERE  SEEMED TO BE ONLY A SMALL AMOUNT OF GLUE.  SOR SENT TO MDHC 12-30-96 ON THIS PART/PROBLEM. 	 (X)				1	G	7	1 	3U				H3WE    					 
1999040200485	19990402	00485	SW  	1999	4	2	CZMA061341       	1	19960112	G	6710	4061300	SWITCH          			BELL  	412   	412         	1182202	SW  										CYCLIC	STUCK           	E			CZMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	911BE	2471 				36018				PILOT'S CYCLIC TRIGGER SWITCH STICKING IN THE ICS POSITION.  REPLACED DEFECTIVE SWITCH.						1	G	7	2 	4U				H4SW    					 
1999040200486	19990402	00486	SW  	1999	4	2	CZMA061343       	1	19960919	G	6220	212060823105	BAFFLE          			BELL  	412   	412         	1182202	SW  										DEBRIS SCREEN	DEFECTIVE       	E			CZMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	911BE	3015 				36018				CREDIT FOR REPLACEMENT PART REPLACED PART WITH NEW FROM BHT.						1	G	7	2 	4U				H4SW    					 
1996030100231	19960301	00231	NM  	1996	3	1	DP2R5836         	1	19960117	G	5330		AIRFRAME CROWN  			BOEING	727   	72723       	1384004	NM  										BS 751-950	DELAMINATED     	B			DP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1985	72148				18441				AD 90-20-18.  AIRFRAME CROWN DELAMINATION NOTED AS FOLLOWS:  BS 950, STR 1.  BS 950, STR 2R.  BS 950, STR 3R.  BS 751, S	TR 8-10 LT AND RT.  BS 775, STR 8-10 LT AND RT.  BS 825, STR 8-10 LT AND RT.  BS 850, STR 8-10, LT AND RT.  (X)					2	L	7	3 	4F				A3WE    					 
1996022300728	19960223	00728	EU  	1996	2	23	DP2R5889         	1	19960117	G	5313		STRINGER        			BAC   	111   	111203AE    	1480208	EU  										GS 236 STR 23R	CRACKS          	B			DP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1543					017				AD 83-15-08 R1 FOUND STRINGER CRACKED.  BS 236 STR 23R, .080 INCH LINEAR INDICATION.  BS 500, STR 23R, 2 EACH LINEAR IND	ICATIONS, EACH .300 INCH LENGTH.  (X)					2	L	7	2 	4F				A5EU    					 
1997112600255	19971126	00255	GL  	1997	11	26	EY2R9600001      	3	19960101	G	6114	C4206C55	HUB             			BEECH 	55    	9555        	1152702	CE  						MCAULY	2AF34C	2AF34C55    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								722170		PROP CRACKED IN HUB THREAD AREA						1	L	7	2 	3O				3A16    		5	C	P5EA	 
1997112600256	19971126	00256	GL  	1997	11	26	EY2R9600002      	3	19960101	G	6114	C5480C66	HUB             			CESSNA	180   	180         	2072602	CE  						MCAULY	3AF34C	3AF34C*     	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727893		HUB CRACKED IN NR2 BLADE SOCKET						1	H	7	1 	3O			NC	5A6     		5	C	P22EA	 
1997112600257	19971126	00257	GL  	1997	11	26	EY2R9600003      	3	19960101	G	6114	D7027C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780071		PROP HUB CRACKED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997112600258	19971126	00258	GL  	1997	11	26	EY2R9600004      	3	19960101	G	6114	C3475	NUT             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	HUB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760917		PROP HUB NUT CRACKED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997112600259	19971126	00259	GL  	1997	11	26	EY2R9600005      	3	19960101	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 3 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								784126		PROP HUB CRACKED NR3 SOCKET						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997112600260	19971126	00260	GL  	1997	11	26	EY2R9600006      	3	19960101	G	6114	C4451	FERRULE         			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	HUB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782680		PROP CRACKED IN FERULE BEARING AREA						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997112600261	19971126	00261	GL  	1997	11	26	EY2R9600007      	3	19960101	G	6110	C5304	SPRING HOUSING  			CESSNA	208   	208B        	2073701	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3797 						840997		SPRING HOUSING CRACKED						1	H	7	1 	3T				A37CE   		5	C	P60GL	 
1997112600262	19971126	00262	GL  	1997	11	26	EY2R9600008      	3	19960101	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747975		NR 2 BLADE SOCKET CRACKED						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997112600263	19971126	00263	GL  	1997	11	26	EY2R9600009      	3	19960101	G	6111	S82NC2	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN K66887YS, CRACKED IN THREAD AREA						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997112600264	19971126	00264	GL  	1997	11	26	EY2R9600010      	3	19960101	G	6111	13019S	CLAMP           			SWRNGN	SA226 	SA226AT     	8780405	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	BLADE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			668  					BV2031		CLAMP CRACKED IN THE INBOARD RADIUS						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA	 
1997112600265	19971126	00265	GL  	1997	11	26	EY2R9600011      	3	19960101	G	6110	1851T	BEARING         			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV1423		PROP ASSY BEARING CRACKED						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997112600266	19971126	00266	GL  	1997	11	26	EY2R9600012      	3	19960101	G	6110	1851T	BEARING         			BEECH 	18    	18*         		CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV811		PROP ASSY BEARING CRACKED						1	L	7	2 	3R				A765    		6	C	P15EA	 
1997112600267	19971126	00267	GL  	1997	11	26	EY2R9600013      	3	19960101	G	6111	15941	FEATHER SPRING  			BEECH 	95    	95B55       	1152729	CE  						HARTZL	HCC2Y	HCC2YF2     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN263		PROP ASSY FEATHERING SPRING CRACKED						1	L	7	2 	3O			RT	3A16    		5	C	P920	 
1997112600268	19971126	00268	GL  	1997	11	26	EY2R9600014      	3	19960101	G	6111	FJC7666A	BLADE           			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	BUTT AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU3182		BLADE SN C43336, CRACKED IN BUTT AREA						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997112600269	19971126	00269	GL  	1997	11	26	EY2R9600015      	3	19960201	G	6110		FIX PITCH       			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	NR 1 MT HOLE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								RP773425		NR 1 MOUNTING HOLE						1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997112600270	19971126	00270	GL  	1997	11	26	EY2R9600016      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	ROD HOLE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								687544		HUB PISTON ROD HOLE CRACKED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997112600271	19971126	00271	GL  	1997	11	26	EY2R9600017      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791237		HUB HAS CRACKED IN NR1 & 3 SOCKETS						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997120300014	19971203	00014	GL  	1997	12	3	EY2R9600018      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREADS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								773157		HUB CRACKED IN THREADS						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997112600272	19971126	00272		1997	11	26	EY2R9600019      	4	19960201	G	6113	22835	BULKHEAD        			BEECH 	95    	95B55       	1152729	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	HUB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3932 						AN3034		BULKHEAD CRACKED IN HUB BOLT HOLES						1	L	7	2 	3O			RT	3A16    		5	C	P920	 
1997112600273	19971126	00273	GL  	1997	11	26	EY2R9600020      	3	19960201	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780880		PROP HUB CRACKED						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997120400064	19971204	00064		1997	12	4	EY2R9600021      	4	19960201	G	6113	3064	BULKHEAD        			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1322 					BU2699		INSPECTION FOUND THE PROP BULKHEAD CRACKED						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997120400065	19971204	00065	GL  	1997	12	4	EY2R9600022      	3	19960201	G	6114	5976	CUP             			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	SPRING RETAINER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1322 					BU2699		INSP FOUND PROP SPRING RETAINER CUP CRACKED						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997120400066	19971204	00066	GL  	1997	12	4	EY2R9600023      	3	19960201	G	6114	5976	CUP             			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	SPRING RETAINER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			2053 					BU4223		INSP FOUND PROP SPRING RETAINER CUP CRACKED						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997120400067	19971204	00067	GL  	1997	12	4	EY2R9600024      	3	19960201	G	6114	18912A	PILOT TUBE      			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU3995		INSP FOUND PROP PILOT TUBE CRACKED						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1997120400068	19971204	00068	GL  	1997	12	4	EY2R9600025      	3	19960201	G	6114	18916	PILOT TUBE      			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU3996		INSP FOUND PROP PILOT TUBE CRACKED						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1997120400069	19971204	00069	GL  	1997	12	4	EY2R9600026      	3	19960201	G	6111	13019S	CLAMP           			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2089		INSP FOUND PROP CLAMP CRACKED						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997120400070	19971204	00070	GL  	1997	12	4	EY2R9600027      	3	19960201	G	6114	1891	PILOT TUBE      			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2089		PILOT TUBE HAS LONGITUDINAL CRACKS						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997120400071	19971204	00071	GL  	1997	12	4	EY2R9600028      	3	19960201	G	6110	1901	LINK ARM        			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2089		INSP FOUND PROP LINK ARM CRACKED						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997120400072	19971204	00072	GL  	1997	12	4	EY2R9600029      	3	19960201	G	6110	30283	BRACKET         			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP HIGH STOP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2120		INSP FOUND HIGH STOP BRACKET CRACKED						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997120400073	19971204	00073	GL  	1997	12	4	EY2R9600030      	3	19960201	G	6110	3252	FORK            			GULSTM	500   	500S        	0141107	SW  						HARTZL	HCC3Y	HCC3YR      	GL  	PITCH CONTROL	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CK1256		PC FORK CRACKED IN RADIUS WHERE BLOCK SEATS						1	H	7	2 	3O				6A1     		5	C	P25EA	 
1997120400074	19971204	00074	GL  	1997	12	4	EY2R9600031      	3	19960301	G	6114	C6447C23	HUB             			BEECH 	35    	V35         	1151538	CE  						MCAULY	2A36C	2A36C23     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								644421		HUB CRACKED IN THREAD AREA						1	L	7	1 	3O				3A15    		5	C	P880	 
1997120400075	19971204	00075	GL  	1997	12	4	EY2R9600032      	3	19960301	G	6114	D7015C87	HUB             			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								804599		HUB OUTER SURFACE CRACKED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997120400076	19971204	00076	GL  	1997	12	4	EY2R9600033      	3	19960301	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								737636		PILOT BORE FOR CRANKSHAFT CRACKED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997120400077	19971204	00077	GL  	1997	12	4	EY2R9600034      	3	19960301	G	6114	D5970C58	HUB             			CESSNA	182   	182E        	2072712	CE  						MCAULY	2A34C	D2A34C58    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780308		HUB CRACKED IN NR 1 SOCKET						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997120400078	19971204	00078	GL  	1997	12	4	EY2R9600035      	3	19960301	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								734660		HUB CRACKED IN NR1 SOCKET						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997120400079	19971204	00079	GL  	1997	12	4	EY2R9600036      	3	19960301	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								754218		HUB CRACKED IN NR 1 SOCKET						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997120400080	19971204	00080	GL  	1997	12	4	EY2R9600037      	3	19960301	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803791		HUB CRACKED IN NR 1 SOCKET						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997120400081	19971204	00081	GL  	1997	12	4	EY2R9600038      	3	19960301	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821935		HUB CRACKED IN NR2 SOCKET, 7 O'CLOCK POSITION						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997120400082	19971204	00082	GL  	1997	12	4	EY2R9600039      	3	19960301	G	6114	D5904C90	HUB             			CESSNA	206   	206CESSNA   	2073302	CE  						MCAULY	3A32C	D3A32C90    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								870996		INSP FOUND HUB CRACKED						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997120400083	19971204	00083	GL  	1997	12	4	EY2R9600040      	3	19960301	G	6114	D7037C80	HUB             													MCAULY	3AF32C	D3AF32C80   	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								681261		HUB SOCKET CRACKED																5	C	P22EA	 
1997120400084	19971204	00084	GL  	1997	12	4	EY2R9600041      	3	19960301	G	6114	D7037C80	HUB             			CESSNA	210   	210K        	2073446	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	BLADE SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								681261		HUB CRACKED IN BLADE SOCKET						1	H	7	1 	3O				3A21    		5	C	P22EA	 
1997120400085	19971204	00085	GL  	1997	12	4	EY2R9600042      	3	19960301	G	6114	D5347C73	HUB             			CESSNA	210   	210K        	2073446	CE  						MCAULY	2A34C	E2A34C73    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								764788		HUB CRACKED IN NR 1 SOCKET						1	H	7	1 	3O				3A21    		5	C	P3EA9	 
1997120400086	19971204	00086	GL  	1997	12	4	EY2R9600043      	3	19960301	G	6111	8433A4	BLADE           			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	SHOULDER AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN B29226, CRACKED IN SHOULDER AREA						1	H	7	2 	3O				6A1     		5	C	P6EA	 
1997120400087	19971204	00087	GL  	1997	12	4	EY2R9600044      	3	19960401	G	6114	C2835C23	HUB             			BEECH 	36    	36BEECH     	1151602	CE  						MCAULY	2A36C	2A36C23     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								735725		INSP FOUND HUB CRACKED						1	L	7	1 	3O				3A15    		5	C	P880	 
1997120400088	19971204	00088	GL  	1997	12	4	EY2R9600045      	3	19960401	G	6114	C6447C23	HUB             			BEECH 	35    	V35         	1151538	CE  						MCAULY	2A36C	2A36C23     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760424		INSP FOUND HUB CRACKED						1	L	7	1 	3O				3A15    		5	C	P880	 
1997120400089	19971204	00089	GL  	1997	12	4	EY2R9600046      	3	19960401	G	6114	D4883C55	HUB             			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								695706		HUB CRACKED IN NR 2 SOCKET						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997120400090	19971204	00090	GL  	1997	12	4	EY2R9600047      	3	19960401	G	6114	D4883C55	HUB             			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								785046		HUB CRACKED IN NR 2 SOCKET						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997120400091	19971204	00091	GL  	1997	12	4	EY2R9600048      	3	19960401	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								712253		INSP FOUND HUB CRACKED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997120400092	19971204	00092	GL  	1997	12	4	EY2R9600049      	3	19960401	G	6110	C3475	NUT             			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										PROP ASSY NUT CRACKED IN THREAD AREA						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997120400093	19971204	00093	GL  	1997	12	4	EY2R9600050      	3	19960401	G	6114	D7019C92	HUB             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								694040		INSP FOUND PROP HUB CRACKED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100133	19971211	00133	GL  	1997	12	11	EY2R9600051      	3	19960401	G	6110	2202	SPLIT BEARING   			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP9080		PROP ASSY HAS A CRACKED SPLIT BEARING						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997121100134	19971211	00134	GL  	1997	12	11	EY2R9600052      	3	19960401	G	6110	15921	SPRING RETAINER 			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								ED796		PROP ASSY HAS A CRACKED SPRING RETAINER						1	L	7	2 	3O				A23CE   		5	C	P36EA	 
1997121100135	19971211	00135	GL  	1997	12	11	EY2R9600053      	3	19960401	G	6110	32532	PITCH CHANGE BLK			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4833 	1698 					ED2833		PROP ASSY HAS A PITCH CHANGE BLOCK CRACKED						1	L	7	2 	3O				A23CE   		5	C	P36EA	 
1997121100136	19971211	00136	GL  	1997	12	11	EY2R9600054      	3	19960501	G	6114	C4211C76	HUB             			BEECH 	35    	35BEECH     	1151502	CE  						MCAULY	3A32C	3A32C76     	GL  	SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								752887		HUB BLADE SOCKET CRACKED						1	L	7	1 	3O				A777    		5	C	P21EA	 
1997121100137	19971211	00137	GL  	1997	12	11	EY2R9600055      	3	19960501	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								721934		HUB CRACKED IN THREAD AREA						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100138	19971211	00138	GL  	1997	12	11	EY2R9600056      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREADS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN F651YS, THREADS CRACKED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100139	19971211	00139	GL  	1997	12	11	EY2R9600057      	3	19960501	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								799116		HUB CRACKED IN NR1 SOCKET						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100140	19971211	00140	GL  	1997	12	11	EY2R9600058      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790630		BLADE SN K92082YS CRACKED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121100141	19971211	00141	GL  	1997	12	11	EY2R9600059      	3	19960501	G	6111	C4451	FERRULE         			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794518		PROP ASSY BLADE FERRULE CRACKED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100142	19971211	00142	GL  	1997	12	11	EY2R9600060      	3	19960501	G	6114	D5894C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	RETAIN THREADS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739542		HUB CRACKED IN RETENTION THREADS						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121100143	19971211	00143	GL  	1997	12	11	EY2R9600061      	3	19960501	G	6114	D5894C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	RETAIN THREADS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								751875		HUB CRACKED IN RETENTION THREADS						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121100144	19971211	00144	GL  	1997	12	11	EY2R9600062      	3	19960501	G	6114	C4716C203	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								762755		HUB CRACKED IN NR2 SOCKET						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100145	19971211	00145	GL  	1997	12	11	EY2R9600063      	3	19960501	G	6111	C4902	NUT             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	BLADE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								762755		BLADE NUT CRACKED						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100146	19971211	00146	GL  	1997	12	11	EY2R9600064      	3	19960501	G	6114	D4887C81	HUB             			CESSNA	310   	310J        	2074226	CE  						MCAULY	2AF34C	D2AF34C81   	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								663578		PROP ASSY HUB CRACKED						1	L	7	2 	3O				3A10    		5	C	P5EA	 
1997121100147	19971211	00147	GL  	1997	12	11	EY2R9600065      	3	19960501	G	6114	D7037C80	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								681261		HUB CRACKED IN NR 1 SOCKET						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997122900009	19971229	00009	GL  	1997	12	29	EY2R9600066      	3	19960501	G	6110	1977P	CLAMP           			DHAV  	DHC2  	DHC2*       	2800108	EA  						HARTZL	HCB3R	HCB3R302    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			2037 					1065N		PROP ASSY CLAMP CRACKED						1	H	7	1 	3R				A806    		5	C	P28EA	 
1997122900010	19971229	00010	GL  	1997	12	29	EY2R9600067      	3	19960501	G	6110	5244	PROPELLER       			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCCA3A	PHCA3VF5    	GL  	HUB ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DH20		PROP ASSY P/N 5244 IS CRACKED						1	L	7	2 	3O				A23CE   		5	C	P6EA	 
1997122900011	19971229	00011	GL  	1997	12	29	EY2R9600068      	3	19960501	G	6110	5244	PROPELLER       			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCCA3A	PHCA3VF5    	GL  	HUB ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DH21		PROPELLER ASSY P/N 5244 IS CRACKED						1	L	7	2 	3O				A23CE   		5	C	P6EA	 
1997121100148	19971211	00148	GL  	1997	12	11	EY2R9600069      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	SOCKETS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774447		HUB ASSY HAS ALL THREE SOCKETS CRACKED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100149	19971211	00149	GL  	1997	12	11	EY2R9600070      	3	19960601	G	6114	C3550	FEATHER CYLINDER			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	HUB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755780		FEATHER CYLINDER SCREW HOLES CRACKED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121100150	19971211	00150	GL  	1997	12	11	EY2R9600071      	3	19960601	G	6114	D7019C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1642 						805941		HUB ASSY CRACKED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121100151	19971211	00151	GL  	1997	12	11	EY2R9600072      	3	19960601	G	6114	C4716C98	HUB             			CESSNA	188   	188B        	2073007	CE  						MCAULY	2A34C	D2A34C98    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2666 	1333 					890754		HUB CRACKED IN THREAD AREA						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100152	19971211	00152	GL  	1997	12	11	EY2R9600073      	3	19960601	G	6114	D5347C73	HUB             			BELL  	206   	206B        	1181511	SW  						MCAULY	2A34C	E2A34C73    	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1187 						850614		HUB ASSY CRACKED						1	G	7	1 	3U				H2SW    		5	C	P3EA9	 
1997121100153	19971211	00153	GL  	1997	12	11	EY2R9600074      	3	19960601	G	6111	13019S	CLAMP           			DHAV  	DHC3  	DHC3        	2800202	EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								11412		PROP ASSY BLADE CLAMP CRACKED						1	H	7	1 	3R				A815    		6	C	P15EA	 
1997121100154	19971211	00154	GL  	1997	12	11	EY2R9600075      	3	19960601	G	6110	18912A	PILOT TUBE      			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2018 						BU13373		PROPELLER ASSY PILOT TUBE CRACKED						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997121100431	19971211	00431	GL  	1997	12	11	EY2R9600076      	3	19960601	G	6110	18912A	PILOT TUBE      			DHAV  	DHC3  	DHC3        	2800202	EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU8685		PROP PILOT TUBE HAS 3" CRACK						1	H	7	1 	3R				A815    		6	C	P15EA	 
1997121100432	19971211	00432	GL  	1997	12	11	EY2R9600077      	3	19960601	G	6110	18916A	PILOT TUBE      			DHAV  	DHC3  	DHC3        	2800202	EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU8685		PROP PILOT TUBE CRACKED						1	H	7	1 	3R				A815    		6	C	P15EA	 
1997121100433	19971211	00433	GL  	1997	12	11	EY2R9600078      	3	19960601	G	6111	T101731	BLADE           			DHAV  	DHC3  	DHC3        	2800202	EA  						HARTZL	HCB3T	HCB3TN3     	GL  	SHANK	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU8685		PROP BLADE SHANK SN 636978, IS CRACKED						1	H	7	1 	3R				A815    		6	C	P15EA	 
1997121100434	19971211	00434	GL  	1997	12	11	EY2R9600079      	3	19960601	G	6111	T10282H	BLADE           			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP LE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6770 	896  					BU13800		HARD ALLOY BLADES CRACKED IN L.E.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997121100435	19971211	00435	GL  	1997	12	11	EY2R9600080      	3	19960601	G	6111	T10282H	BLADE           			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6770 	896  					BU13800		BLADE CRACKED.  REWORKED, SN C69741						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997121100436	19971211	00436	GL  	1997	12	11	EY2R9600081      	3	19960601	G	6111	T10282H	BLADE           			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6770 	896  					BU13800		PROP BLADE CRACKED.  REWORKED, SN C69640						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997121100437	19971211	00437	GL  	1997	12	11	EY2R9600082      	3	19960601	G	6111	T10282H	BLADE           			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6770 	896  					BU13800		PROP BLADE CRACKED.  REWORKED, SN C55993						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997121100438	19971211	00438	GL  	1997	12	11	EY2R9600083      	3	19960601	G	6114	3493	STOP            			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB4T	HCB4TN3     	GL  	HIGH PITCH	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		100  								HUB HIGH PITCH STOP BROKEN						1	H	7	2 	3T				A2PC    		6	C	P40EA	 
1997121100439	19971211	00439	GL  	1997	12	11	EY2R9600084      	3	19960601	G	6111	F8475D4	BLADE           			PIPER 	PA32  	PA32300     	7103212	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			456  					CH7205		BLADE SN D11148, FLANGES CRACKED						1	L	7	1 	3O				A3SO    		5	C	P920	 
1997121100440	19971211	00440	GL  	1997	12	11	EY2R9600085      	3	19960601	G	6111	F8475D4	BLADE           			PIPER 	PA32  	PA32300     	7103212	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			456  					CH7205		BLADE SN D3698, FLANGES CRACKED						1	L	7	1 	3O				A3SO    		5	C	P920	 
1997121100441	19971211	00441	GL  	1997	12	11	EY2R9600086      	3	19960601	G	6110	24182	PISTON ROD      			PIPER 	PA24  	PA24400     	7102408	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4550 						CH2967		PROP PISTON ROD CRACKED						1	L	7	1 	3O				1A15    		5	C	P920	 
1997121100442	19971211	00442	GL  	1997	12	11	EY2R9600087      	3	19960601	G	6114	24573	FORK            			PIPER 	PA24  	PA24400     	7102408	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PITCH CHANGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH2967		PROP PITCH CHANGE FORK CRACKED						1	L	7	1 	3O				1A15    		5	C	P920	 
1997121100443	19971211	00443	GL  	1997	12	11	EY2R9600088      	3	19960601	G	6111	F7666A2	BLADE           			PIPER 	PA28  	PA28R200    	7102811	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH11897		BLADE SN H60744, FLANGE CRACKED						1	L	7	1 	3O				2A13    		5	C	P920	 
1997121100444	19971211	00444	GL  	1997	12	11	EY2R9600089      	3	19960701	G	6114	C4239C23	HUB             			BEECH 	35    	V35         	1151538	CE  						MCAULY	2A36C	2A36C23     	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								711435		HUB CRACKED IN THREAD AREA						1	L	7	1 	3O				3A15    		5	C	P880	 
1997121100445	19971211	00445	GL  	1997	12	11	EY2R9600090      	3	19960701	G	6114	C4239C23	HUB             			BEECH 	33    	3533        	1151402	CE  						MCAULY	2A36C	2A36C23     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								744502		HUB CRACKED						1	L	7	1 	3O				3A15    		5	C	P880	 
1997121100446	19971211	00446	GL  	1997	12	11	EY2R9600091      	3	19960701	G	6114	C4239C23	HUB             			BEECH 	33    	3533        	1151402	CE  						MCAULY	2A36C	2A36C23     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774507		HUB CRACKED IN THREAD AREA						1	L	7	1 	3O				3A15    		5	C	P880	 
1997121100447	19971211	00447	GL  	1997	12	11	EY2R9600092      	3	19960701	G	6114	C4206C55	HUB             			BEECH 	58    	58          	1152740	CE  						MCAULY	2AF34C	2AF34C55    	GL  	SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								723821		HUB CRACKED IN BOTH BLADE SOCKETS						1	L	7	2 	3O				3A16    		5	C	P5EA	 
1997121100448	19971211	00448	GL  	1997	12	11	EY2R9600093      	3	19960701	G	6114	D5892C75	HUB             			BEECH 	55    	9555        	1152702	CE  						MCAULY	3AF32C	3AF32C75    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								696160		HUB CRACKED IN THREAD AREA						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997122900019	19971229	00019	GL  	1997	12	29	EY2R9600094      	3	19960701	G	6114	D7015C75	HUB             			BEECH 	55    	9555        	1152702	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								696160		HUB CRACKED						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997121100449	19971211	00449	GL  	1997	12	11	EY2R9600095      	3	19960701	G	6114	D7015C87	HUB             			CESSNA	401   	401         	207590C	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911101		HUB CRACKED IN THREAD AREA						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100450	19971211	00450	GL  	1997	12	11	EY2R9600096      	3	19960701	G	6114	D5892C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3348 	573  					733241		HUB CRACKED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100451	19971211	00451	GL  	1997	12	11	EY2R9600097      	3	19960701	G	6114	D5892C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3348 	573  					743081		HUB CRACKED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100452	19971211	00452	GL  	1997	12	11	EY2R9600098      	3	19960701	G	6114	D7015C87	HUB             			CESSNA	401   	401         	207590C	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								900221		HUB CRACKED IN NR 2 SOCKET						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100453	19971211	00453	GL  	1997	12	11	EY2R9600099      	3	19960701	G	6114	C65HUB				CESSNA	310   	310         	2074202	CE  						MCAULY	2A34C	D2A34C*     	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								724508		HUB CRACKED IN THREAD AREA						1	L	7	2 	3O			RT	3A10    		5	C	P3EA	 
1997121100454	19971211	00454	GL  	1997	12	11	EY2R9600100      	3	19960701	G	6114	D4237C65	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	2AF34C	D2AF34C65   	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								730063		HUB CRACKED IN NR2 SOCKET						1	L	7	2 	3O			RT	3A10    		5	C	P5EA	 
1997121100455	19971211	00455	GL  	1997	12	11	EY2R9600101      	3	19960701	G	6110	3496	FEATHER SPRING  			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		18952	3058 					FW264		PROP FEATHERING SPRING CRACKED						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997121100456	19971211	00456	GL  	1997	12	11	EY2R9600102      	3	19960801	G	6110	C3112	RETAIN RING     			ADAMS 	A50S  	A55         	0050103	SO  						MCAULY	2AF34C	2AF34C55    	GL  	RPOP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								695613		PROP RETAIN RING CRACKED						1	B	0	0 					A15SO   		5	C	P5EA	 
1997121100457	19971211	00457	GL  	1997	12	11	EY2R9600103      	3	19960801	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								776628		HUB CRACKED IN NR1 SOCKET						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121100458	19971211	00458	GL  	1997	12	11	EY2R9600104      	3	19960801	G	6110	3496	FEATHER SPRING  			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		17663	4081 					FW868		FEATHER SPRING CRACKED, 5 PCS., SPIRAL MARK ON FLAT EDGE						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997121100459	19971211	00459	GL  	1997	12	11	EY2R9600105      	3	19960801	G	6111	FJC7666A	BLADE           			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			157  					AU7121		BLADE SN H69746, TIP BROKE OFF 12"						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997121100460	19971211	00460	GL  	1997	12	11	EY2R9600106      	3	19960901	G	6114	C5480C66	HUB             			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C66     	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911125		HUB CRACKED IN THREAD AREA						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997121100461	19971211	00461	GL  	1997	12	11	EY2R9600107      	3	19960901	G	6114	D6602C76	HUB             			BEECH 	35    	V35A        	1151544	CE  						MCAULY	3A32C	3A32C76     	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								676269		HUB CRACKED IN THREAD AREA						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997121100462	19971211	00462	GL  	1997	12	11	EY2R9600108      	3	19960901	G	6114	D7027C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798862		HUB CRACKED IN THREAD AREA						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100463	19971211	00463	NE  	1997	12	11	EY2R9600109      	3	19960901	G	6111	5133	BLADE           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROP LE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								HJ117A		PROP BLADE LEADING EDGE CRACKED						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997121100464	19971211	00464	GL  	1997	12	11	EY2R9600110      	3	19960901	G	6114	32517	HUB             			CESSNA	340   	340A        	2076405	CE  						HARTZL	HCC3Y	PHCC3YF2    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								EB2248		PROP HUB CRACKED						1	L	7	2 	3O				3A25    		5	C	P25EA	 
1997121100465	19971211	00465	GL  	1997	12	11	EY2R9600111      	3	19960901	G	6114	FC84686R	BLADE           			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN D70235 CRACKED						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1997121100466	19971211	00466	GL  	1997	12	11	EY2R9600112      	3	19960901	G	6114	FC84686R	BLADE           			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN D73964 CRACKED						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1997121100467	19971211	00467	GL  	1997	12	11	EY2R9600113      	3	19960901	G	6111	FC84686R	BLADE           			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN E45280 CRACKED						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1997121100468	19971211	00468	GL  	1997	12	11	EY2R9600114      	3	19961001	G	6110		PROPELLER       			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	LE BOLT HOLES	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								K771825		2 CRACKS IN LEAD EDGE BOLT HOLES						1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997121100469	19971211	00469	GL  	1997	12	11	EY2R9600115      	3	19961001	G	6114	D6602C76	HUB             			BEECH 	35    	V35         	1151538	CE  						MCAULY	3A32C	3A32C76     	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800310		HUB CRACKED IN THREAD AREA						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997122900020	19971229	00020	GL  	1997	12	29	EY2R9600116      	3	19961001	G	6114	D7015C87	HUB             			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								687084		HUB CRACKED IN THREAD AREA						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100470	19971211	00470	GL  	1997	12	11	EY2R9600117      	3	19961001	G	6111	S82NC4	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789172		BLADE NR1 SOCKET CRACKED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100471	19971211	00471	GL  	1997	12	11	EY2R9600118      	3	19961001	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790274		NR 1 BLADE SOCKET UNDER WELCH PLUG CRACKED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997122900021	19971229	00021	GL  	1997	12	29	EY2R9600119      	3	19961001	G	6114	C4716C58	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C58    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								735820		HUB CRACKED IN THREAD AREA						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997122900022	19971229	00022	GL  	1997	12	29	EY2R9600120      	3	19961001	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902390		PROP HUB CRACKED						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100472	19971211	00472	GL  	1997	12	11	EY2R9600121      	3	19961001	G	6110	1851T	BEARING         			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU1332		PROP ASSY BEARING CRACKED						1	L	7	2 	3T				3A20    		6	C	P15EA	 
1997121100473	19971211	00473	GL  	1997	12	11	EY2R9600122      	3	19961001	G	6110	1891	PILOT TUBE      			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU1332		PROP ASSY IS CRACKED .  ALL 3 PILOT TUBES						1	L	7	2 	3T				3A20    		6	C	P15EA	 
1997121100474	19971211	00474	GL  	1997	12	11	EY2R9600123      	3	19961001	G	6110	30283	STOP BRACKET    			GULSTM	690TP 	690         	0141720	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP HIGH STOP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV3133		HIGH STOP BRACKET CRACKED.  ALL 3 CRACKED AT PIN						1	H	7	2 	3T				2A4     		6	C	P15EA	 
1997121100475	19971211	00475	GL  	1997	12	11	EY2R9600124      	3	19961001	G	6110	30283	STOP BRACKET    			GULSTM	690TP 	690         	0141720	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP HIGH STOP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV3155		PROP HIGH STOP BRACKETCRACKED.  ALL 3 CRACKED AT PIN						1	H	7	2 	3T				2A4     		6	C	P15EA	 
1997121100476	19971211	00476	GL  	1997	12	11	EY2R9600125      	3	19961001	G	6110	2202	SPLIT BEARING   			PIPER 	PA32  	PA32R300    	7103213	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			3320 					CH1108		PROP SPLIT BEARING CRACKED						1	L	7	1 	3O				A3SO    		5	C	P920	 
1997121100477	19971211	00477	GL  	1997	12	11	EY2R9600126      	3	19960901	G	6114	D7015C87	HUB             			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								764989		PROP HUB ASSY IS CRACKED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121100478	19971211	00478	GL  	1997	12	11	EY2R9600127      	3	19960901	G	6110	2202	SPLIT BEARING   			PIPER 	PA23  	PA23150     	7102303	CE  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BC157		PROP ASSY SPLIT BEARING CRACKED						1	L	7	2 	3O			RT	1A10    		5	C	P920	 
1997122900023	19971229	00023	NE  	1997	12	29	EY2R9600128      	3	19961001	G	6111	AG1002	BLADE RING      			CVAC  	240   	600240D     	2422660	WP  						HAMSTD	12D	12D40       	NE  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1710882		PROP SN 778365, BROKEN BLADE RING						1	L	7	2 	4T			RT	2L72    		5	C	P257	 
1997122900024	19971229	00024	GL  	1997	12	29	EY2R9600129      	3	19961001	G	6110	PFA12D19B	SHEATH          			DHAV  	DHC7  	DHC7*       		EA  						HAMSTD	24PF	24PF305     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		18628	4803 					237492		PROP ASSY HAS 3 SHEATHS CRACKED						2	H	7	4 	4T			RT	A20EA   		6	C	P1NE	 
1997121100479	19971211	00479	GL  	1997	12	11	EY2R9600130      	3	19961001	G	6114	C1579C18	HUB             			CESSNA	180   	180         	2072602	CE  						MCAULY	2A34C	2A34C*      	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								55080		HUB CRACKED IN THREADS AREA						1	H	7	1 	3O			NC	5A6     		5	C	P3EA	 
1997121100480	19971211	00480	GL  	1997	12	11	EY2R9600131      	3	19961001	G	6114	C5480C66	HUB             			CESSNA	180   	180A        	2072604	CE  						MCAULY	2A34C	2A34C66     	GL  	MT FLANGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791490		HUB CRACKED IN MOUNTING FLANGE						1	H	7	1 	3O				5A6     		5	C	P3EA	 
1997121100481	19971211	00481	GL  	1997	12	11	EY2R9600132      	3	19961001	G	6114	C5480C66	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	2A34C66     	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800085		HUB CRACKED IN THREADS						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100482	19971211	00482	GL  	1997	12	11	EY2R9600133      	3	19961001	G	6111	C2463	NUT             			BEECH 	36    	36BEECH     	1151602	CE  						MCAULY	2A36C	2A36C23     	GL  	BLADE RETAIN	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								641006		BLADE RETAIN NUT CRACKED						1	L	7	1 	3O				3A15    		5	C	P880	 
1997121100483	19971211	00483	GL  	1997	12	11	EY2R9600134      	3	19961001	G	6111	S90M8	BLADE           			CESSNA	182   	182         	2072702	CE  						MCAULY	2A36C	2A36C29     	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN A4420YS, THREAD AREA CRACKED						1	H	7	1 	3O			NT	3A13    		5	C	P880	 
1997121100484	19971211	00484	GL  	1997	12	11	EY2R9600135      	3	19961001	G	6114	C4526C29	HUB             			CESSNA	180   	180G        	2072616	CE  						MCAULY	2A36C	2A36C29     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								601681		PROP HUB ASSY CRACKED						1	H	7	1 	3O				5A6     		5	C	P880	 
1997121100485	19971211	00485	GL  	1997	12	11	EY2R9600136      	3	19961001	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747043		HUB CRACKED IN BLADE SOCKET						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100486	19971211	00486	GL  	1997	12	11	EY2R9600137      	3	19961001	G	6114	D5892C87	HUB             			CESSNA	402   	402A        	207590M	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795594		PROP HUB ASSY CRACKED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100487	19971211	00487	GL  	1997	12	11	EY2R9600138      	3	19961001	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								776015		HUB CRACKED IN THREADS						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100488	19971211	00488	GL  	1997	12	11	EY2R9600139      	3	19961001	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791322		HUB CRACKED IN NR1 SOCKET						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100489	19971211	00489	GL  	1997	12	11	EY2R9600140      	3	19961001	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	BLADE SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								771316		HUB CRACKED IN BLADE SOCKET						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121100490	19971211	00490	GL  	1997	12	11	EY2R9600141      	3	19961001	G	6114	D7015C93	HUB             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	NR 3 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		HUB CRACKED IN NR3 SOCKET						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121100491	19971211	00491	GL  	1997	12	11	EY2R9600142      	3	19961001	G	6114	C4716C58	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								831190		PROP ASSY HUB CRACKED						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997121100492	19971211	00492	GL  	1997	12	11	EY2R9600143      	3	19961001	G	6114	C4716C58	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C58    	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697479		HUB CRACKED IN NR2 SOCKET						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100493	19971211	00493	GL  	1997	12	11	EY2R9600144      	3	19961001	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								756845		RED DYE LEAK.  HUB CRACKED						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100494	19971211	00494	GL  	1997	12	11	EY2R9600145      	3	19961001	G	6110	C4902	NUT             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROP HUB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								756845		NUT CRACKED WITH HUB						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100666	19971211	00666	GL  	1997	12	11	EY2R9600146      	3	19961001	G	6110	C1976	RETAIN NUT      			CESSNA	210   	210         	2073402	CE  						MCAULY	2A36C	D2A36C33    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								61811		PROP ASSY RETAIN NUT CRACKED						1	H	7	1 	3O			RT	3A21    		5	C	P880	 
1997121100667	19971211	00667	GL  	1997	12	11	EY2R9600147      	3	19961001	G	6114	C2715C33	HUB             			CESSNA	210   	210         	2073402	CE  						MCAULY	2A36C	D2A36C33    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								61811		HUB CRACKED IN NR1 SOCKET						1	H	7	1 	3O			RT	3A21    		5	C	P880	 
1997122900032	19971229	00032	GL  	1997	12	29	EY2R9600148      	3	19961001	G	6114	D5904C58	HUB             			CESSNA	185   	A185F       	2072821	CE  						MCAULY	3A32C	D3A32C90    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795820		HUB CRACKED IN THREAD AREA						1	H	7	1 	3O				3A24    		5	C	P21EA	 
1997122900033	19971229	00033	GL  	1997	12	29	EY2R9600149      	3	19961001	G	6114		SPIDER          			DHAV  	DHC2  	DHC2*       	2800108	EA  						HARTZL	HCB3R	HCB3R304    	GL  	PROP HUB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										SPIDERS CRACKED IN SPLINES OF HUB						1	H	7	1 	3R				A806    		5	C	P28EA	 
1997121100668	19971211	00668	GL  	1997	12	11	EY2R9600150      	3	19961001	G	6110	3064	BULKHEAD        			BEECH 	100   	B100        	1152919	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9815 	1746 					BU5621		PROP ASSY CRACKED BULKHEAD						1	L	7	2 	4T				A14CE   		6	C	P15EA	 
1997121100669	19971211	00669	GL  	1997	12	11	EY2R9600151      	3	19961001	G	6110	3496	FEATHER SPRING  			STBROS	SD3   	SD360       	8100606	EU  						HARTZL	HCB5M	HCB5MP3     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		15791	4473 					EV711		PROP ASSY FEATHERING SPRING BROKEN						2	H	7	2 	4T				A41EU   		6	C	P44GL	 
1997121100670	19971211	00670	GL  	1997	12	11	EY2R9600152      	3	19961001	G	6111	FL7666A2	BLADE           			CONAER	LA4   	LA4200      	5110310	NE  						HARTZL	HCC2Y	HCC2YK1     	GL  	SHANK	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN D66432, CRACKED NEAR SHANK IN LIP						1	H	7	1 	3O				1A13    		5	C	P920	 
1997121100671	19971211	00671	GL  	1997	12	11	EY2R9600153      	3	19961001	G	6110	2202	SPLIT BEARING   			PIPER 	PA44  	PA44180T    	7104404	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU2583		PROP ASSY SPLIT BEARING CRACKED AT TOP OF RACE						1	L	7	2 	3O				A19SO   		5	C	P920	 
1997122900034	19971229	00034	GL  	1997	12	29	EY2R9600154      	3	19961001	G	6111	F8468A8R	BLADE           			CESSNA	206   	206CESSNA   	2073302	CE  						HARTZL	HCC3Y	HCC3YF1     	GL  	SHANK	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								EC117A		BLADE SN H58903, CRACKED NEAR SHANK IN LIP						1	H	7	1 	3O				A4CE    		5	C	P25EA	 
1997121100672	19971211	00672	GL  	1997	12	11	EY2R9600155      	3	19961001	G	6110	2202	SPLIT BEARING   			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP7307		PROP ASSY SPLIT BEARING CRACKED						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997121100673	19971211	00673	NE  	1997	12	11	EY2R9600156      	3	19961001	G	6111	5133	BLADE           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROP LE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5420 						HJ297		BLADE CRACKED LEADING EDGE						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997121100674	19971211	00674	CE  	1997	12	11	EY2R9600157      	3	19961101	G	6111	2153192	BEARING         			BEECH 	35    	D35         	1151510	CE  						BEECH	215	215*        	CE  	BLADE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								4959		BLADE BEARING RACE CRACKED						1	L	7	1 	3O				A777    		5	C	P873	 
1997121100675	19971211	00675	GL  	1997	12	11	EY2R9600158      	3	19961101	G	6114	D5892C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								702046		PROP HUB ASSY CRACKED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100676	19971211	00676	GL  	1997	12	11	EY2R9600159      	3	19961101	G	6114	D5892C93	HUB             			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4020 	1379 					796457		PROP HUB ASSY CRACKED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100677	19971211	00677	NE  	1997	12	11	EY2R9600160      	3	19961101	G	6110	C5291	COUNTERWEIGHT   			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2584 						911019		PROP ASSY COUNTERWEIGHT CRACKED						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1997121100678	19971211	00678	NE  	1997	12	11	EY2R9600161      	3	19961101	G	6111	5133	BLADE           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	LEADING EDGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5150 	539  					HJ272		BLADE ASSY LE SHEATH CRACKED						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997121100679	19971211	00679	NE  	1997	12	11	EY2R9600162      	3	19961101	G	6111	5133	BLADE           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	LE SHEATH	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4652 						HJ310		BLADE LEADING EDGE SHEATH CRACKED						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997121100680	19971211	00680	NE  	1997	12	11	EY2R9600163      	3	19961101	G	6111	5133	BLADE           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	LE SHEATH	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		7846 	1350 					HJ583		BLADE LEADING EDGE SHEATH CRACKED						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997121100681	19971211	00681	GL  	1997	12	11	EY2R9600164      	3	19961201	G	6114	C2835C23	HUB             			BEECH 	33    	35B33       	1151406	CE  						MCAULY	2A36C	2A36C23     	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			238  					671575		HUB NR2 SOCKET, HAS CRACK 12" LONG						1	L	7	1 	3O				3A15    		5	C	P880	 
1997122900035	19971229	00035	GL  	1997	12	29	EY2R9600165      	3	19961201	G	6114	D5892C87	HUB             			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREAD AREAS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								792390		THREAD AREAS OF HUB ARE CRACKED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100682	19971211	00682	GL  	1997	12	11	EY2R9600166      	3	19961201	G	6110	C4451	FERRULE         			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1223 					741352		5 HOLES IN BLADE PIN HOLE, DIMPLED AND FERRULE CRACKED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100683	19971211	00683	GL  	1997	12	11	EY2R9600167      	3	19961201	G	6114	C4716C98	HUB             			LKHEED	188   	188A        	5262602	WP  						MCAULY	2A34C	D2A34C98    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789111		NR1 SOCKET, NR 1&2 THREADS CRACKED, 12" LONG						2	L	7	4 	4T			RT	4A22    		5	C	P3EA	 
1997121100684	19971211	00684	GL  	1997	12	11	EY2R9600168      	3	19961201	G	6114	D4887C81	HUB             			CESSNA	310   	310J        	2074226	CE  						MCAULY	2AF34C	D2AF34C81   	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								714258		PROP HUB ASSY CRACKED IN THREAD AREA						1	L	7	2 	3O				3A10    		5	C	P5EA	 
1997121100685	19971211	00685	GL  	1997	12	11	EY2R9600169      	3	19961201	G	6114	D3944C88	HUB             			CESSNA	206   	P206C       	2073312	CE  						MCAULY	3A32C	D3A32C88    	GL  	NR 2 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			512  					692219		HUB ASSY NR2 SOCKET, NR5 THREAD CRACKED, 2" LONG						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997121100686	19971211	00686	GL  	1997	12	11	EY2R9600170      	3	19961201	G	6111	C4451	FERRULE         			CESSNA	206   	P206C       	2073312	CE  						MCAULY	3A32C	D3A32C88    	GL  	BLADE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			512  					692219		BLADE PIN HOLE DIMPLED, CAUSED FERRULE CRACK						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997121100687	19971211	00687	GL  	1997	12	11	EY2R9600171      	3	19961201	G	6114	C5347C73	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	E2A34C73    	GL  	THREAD CRACKED	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								900797		THREAD AREAS OF HUB CRACKED						1	H	7	1 	3O			NT	3A13    		5	C	P3EA9	 
1997121100688	19971211	00688	GL  	1997	12	11	EY2R9600172      	3	19961201	G	6111	F7666A	BLADE           			MAULE 	M5    	M5200       		SO  						HARTZL	HCE2Y	HCE2YR1BF   	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH15008		BLADE SN H77743 IS CRACKED						1	H	7	1 	3O				3A23    		5	C	P9EA	 
1997121100689	19971211	00689	GL  	1997	12	11	EY2R9600173      	3	19961201	G	6110	3252	FORK            			BEECH 	55    	9555        	1152702	CE  						HARTZL	HCC3Y	PHCC3YF2    	GL  	PITCH CHANGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								EB798		PROP ASSY PITCH CHANGE FORK IS CRACKED						1	L	7	2 	3O				3A16    		5	C	P25EA	 
1997122900036	19971229	00036	GL  	1997	12	29	EY2R9600174      	3	19961201	G	6110	2202	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6195 						BP239		PROP ASSY BEARING IS CRACKED						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997122900037	19971229	00037	GL  	1997	12	29	EY2R9600175      	3	19961201	G	6110	24914S	ROD             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6195 						BP8909		PROP ASSY ROD CRACKED						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997121100690	19971211	00690	GL  	1997	12	11	EY2R9600176      	3	19961201	G	6114	D7027C87	HUB             			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1627 					692141		HUB ASSY CRACKED THREADS						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100691	19971211	00691	GL  	1997	12	11	EY2R9600177      	3	19961201	G	6114	D7027C87	HUB             			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								693472		HUB ASSY THREAD CRACKED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100692	19971211	00692	GL  	1997	12	11	EY2R9600178      	3	19961201	G	6111	S90AT8	BLADE           													MCAULY	2A34C	E2A34C73    	GL  	THREADS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		400  						900797		BLADE SN JH105YS, CRACKED THREADS																5	C	P3EA9	 
1997121100693	19971211	00693	GL  	1997	12	11	EY2R9600179      	3	19961201	G	6114	C6447C23	HUB             			BEECH 	36    	36BEECH     	1151602	CE  						MCAULY	2A36C	2A36C23     	GL  	BOLT SOCKETS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								66085		HUB ASSY CRACKED IN BOLT SOCKETS						1	L	7	1 	3O				3A15    		5	C	P880	 
1997121100694	19971211	00694	GL  	1997	12	11	EY2R9600180      	3	19961201	G	6110	C3092	RETAIN NUT      			CESSNA	210   	210         	2073402	CE  						MCAULY	2A34C	E2A34C73    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774298		PROP ASSY RETAIN NUT CRACKED THREADS						1	H	7	1 	3O			RT	3A21    		5	C	P3EA9	 
1997121100695	19971211	00695	GL  	1997	12	11	EY2R9600181      	3	19961201	G	6114	D6608C205	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	B2A34C205   	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830312		HUB ASSY CRACKED THREADS						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100696	19971211	00696	GL  	1997	12	11	EY2R9600182      	3	19961201	G	6114	D6608C205	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	B2A34C205   	GL  	THREAD AREA	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								850679		HUB ASSY CRACKED THREADS						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997121100697	19971211	00697	GL  	1997	12	11	EY2R9600183      	3	19961201	G	6110	40191	BETA COLLAR     			STBROS	SD3   	SD360       	8100606	EU  						HARTZL	HCB5M	HCB5MP3     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		13167	4311 					EV712		PROP ASSY BETA COLLAR CRACKED						2	H	7	2 	4T				A41EU   		6	C	P44GL	 
1997121100698	19971211	00698	NE  	1997	12	11	EY2R9600184      	3	19961201	G	6111	E10950K	BLADE           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	STA 18 INCH	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4539 						HJ241		BLADE IS CRACKED AT 18" STATION						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997121100699	19971211	00699	GL  	1997	12	11	EY2R9600185      	3	19961201	G	6114	D4344C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	NR 3 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794515		HUB ASSY CRACKED IN NR3 SOCKET, NR3 THREAD						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121100700	19971211	00700	GL  	1997	12	11	EY2R9600186      	3	19961201	G	6114	C4716C58	HUB             													MCAULY	2A34C	D2A34C58    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1438 					701466		MDR ISSUED ON HUB ASSY CRACKED																5	C	P3EA	 
1997121100701	19971211	00701	GL  	1997	12	11	EY2R9600187      	3	19961201	G	6114	C4716C58	HUB             			CESSNA	210   	210         	2073402	CE  						MCAULY	2A34C	D2A34C58    	GL  	NR 1 SOCKET	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								666825		HUB ASSY CRACKED IN NR1 SOCKET						1	H	7	1 	3O			RT	3A21    		5	C	P3EA	 
1997122900038	19971229	00038	GL  	1997	12	29	EY2R9600188      	3	19961201	G	6114	C4883C55	HUB             			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	BLADE SOCKETS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								676027		HUB ASSY CRACKED IN BOTH BLADE SOCKETS						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997122900039	19971229	00039	GL  	1997	12	29	EY2R9600189      	3	19961201	G	6111	C3112	BLADE NUTS      			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								676027		PROP ASSY BLADE NUTS CRACKED						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997121100702	19971211	00702	GL  	1997	12	11	EY2R9600190      	3	19961201	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								693311		PROP ASSY HUB CRACKED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100703	19971211	00703	GL  	1997	12	11	EY2R9600191      	3	19961201	G	6110	2202	BEARING         			BBAVIA	8     	8GCBC       	1220803	SW  						HARTZL	HCC2Y	HCC2YF1     	GL  	PROP ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH21278		PROP ASSY BEARING CRACKED						1	H	7	1 	3O				A21CE   		5	C	P920	 
1997121100704	19971211	00704	GL  	1997	12	11	EY2R9600192      	3	19960101	G	6110		PROPELLER       			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	HUB ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								RDA013		FIXED PITCH PROP ASSY IS CORRODED						1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997121100705	19971211	00705	GL  	1997	12	11	EY2R9600193      	3	19960101	G	6110	B3414	PISTON ROD PIN  			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C201    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2617 						723706		PROP ASSY PISTON ROD PIN ASSY CORRODED						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997121100706	19971211	00706	GL  	1997	12	11	EY2R9600194      	3	19960101	G	6110	C3903	SPLIT RETAINER  			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C201    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2617 						723706		PROP ASSY SPLIT RETAINER CRACKED						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997121100707	19971211	00707	GL  	1997	12	11	EY2R9600195      	3	19960101	G	6110	C5263	CYLINDER        			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C201    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2617 						723706		PROP ASSY CYLINDER CORRODED						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997121100708	19971211	00708	GL  	1997	12	11	EY2R9600196      	3	19960101	G	6110	C5270	RETAIN BEARING  			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C201    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2617 						723706		PROP ASSY RETAIN BEARING CORRODED						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997121100709	19971211	00709	GL  	1997	12	11	EY2R9600197      	3	19960101	G	6111	90DA8	BLADE           			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C201    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								693743		BLADE ASSY SN C78439 IS CORRODED						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997121100710	19971211	00710	GL  	1997	12	11	EY2R9600198      	3	19960101	G	6111	90DA8	BLADE           			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C201    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								693743		BLADE ASSY SN B39063 IS CORRODED						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997121100711	19971211	00711	GL  	1997	12	11	EY2R9600199      	3	19960101	G	6110		PROPELLER       			CESSNA	182   	182Q        	2072732	CE  						MCAULY	2A34C	2A34C203    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			158  					765426		PROP ASSY IS CORRODED						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997121100712	19971211	00712	GL  	1997	12	11	EY2R9600200      	3	19960101	G	6111	90AT8	BLADE           			CESSNA	182   	182J        	2072722	CE  						MCAULY	2A34C	2A34C66     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								810720		BLADE ASSY SN C37703 IS CORRODED						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997121100713	19971211	00713	GL  	1997	12	11	EY2R9600201      	3	19960101	G	6111	90M8	BLADE           			UNIVAR	108   	1082        	9230406	NM  						MCAULY	2A36C	2A36C29     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								641271		BLADE ASSY SN K31785YS IS CORRODED						1	H	7	1 	3O				A767    		5	C	P880	 
1997121100714	19971211	00714	GL  	1997	12	11	EY2R9600202      	3	19960101	G	6111	90M8	BLADE           			UNIVAR	108   	1082        	9230406	NM  						MCAULY	2A36C	2A36C29     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								641271		BLADE ASSY SN C45338YS IS CORRODED						1	H	7	1 	3O				A767    		5	C	P880	 
1997121100715	19971211	00715	GL  	1997	12	11	EY2R9600203      	3	19960101	G	6114	C2343C29	HUB             			UNIVAR	108   	1082        	9230406	NM  						MCAULY	2A36C	2A36C29     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								641271		PROP ASSY HUB IS CORRODED						1	H	7	1 	3O				A767    		5	C	P880	 
1997122900040	19971229	00040	GL  	1997	12	29	EY2R9600204      	3	19960101	G	6111	78FF0	BLADE           			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								842577		BLADE ASSY SN K99201 IS CORRODED						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997122900041	19971229	00041	GL  	1997	12	29	EY2R9600205      	3	19960101	G	6111	78FF0	BLADE           			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								842577		BLADE ASSY SN K99210 IS CORRODED						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997122900042	19971229	00042	GL  	1997	12	29	EY2R9600206      	3	19960101	G	6110	A1896	CYLINDER PIN    			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								842577		PROP ASSY CYLINDER PIN IS CORRODED						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997122900043	19971229	00043	GL  	1997	12	29	EY2R9600207      	3	19960101	G	6110	A4001	DOWEL           			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								842577		PROP ASSY DOWEL IS CORRODED						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997122900044	19971229	00044	GL  	1997	12	29	EY2R9600208      	3	19960101	G	6110	B4458	ACTUATING  PIN  			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	BLADE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								842577		PROP ASSY BLADE ACTUATING PIN CORRODED						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1997121100716	19971211	00716	GL  	1997	12	11	EY2R9600209      	3	19960101	G	6114	D6602C76	HUB             			BEECH 	35    	V35         	1151538	CE  						MCAULY	3A32C	3A32C76     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								701254		PROP HUB ASSY IS CORRODED						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997121100717	19971211	00717	GL  	1997	12	11	EY2R9600210      	3	19960101	G	6110	A4001	DOWEL           			BEECH 	35    	35BEECH     	1151502	CE  						MCAULY	3A32C	3A32C76     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803085		PROP ASSY DOWEL IS CORRODED						1	L	7	1 	3O				A777    		5	C	P21EA	 
1997121100718	19971211	00718	GL  	1997	12	11	EY2R9600211      	3	19960101	G	6110	B4460	ACTUATING  PIN  			BEECH 	35    	35BEECH     	1151502	CE  						MCAULY	3A32C	3A32C76     	GL  	BLADE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803085		BLADE ACTUATING PIN IS CORRODED						1	L	7	1 	3O				A777    		5	C	P21EA	 
1997121100719	19971211	00719	GL  	1997	12	11	EY2R9600212      	3	19960101	G	6110	C2987	RETAIN BEARING  			BEECH 	35    	35BEECH     	1151502	CE  						MCAULY	3A32C	3A32C76     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803085		PROP ASSY RETAIN BEARING CORRODED						1	L	7	1 	3O				A777    		5	C	P21EA	 
1997121100720	19971211	00720	GL  	1997	12	11	EY2R9600213      	3	19960101	G	6110	C4904	NUT             			BEECH 	35    	35BEECH     	1151502	CE  						MCAULY	3A32C	3A32C76     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803085		PROP ASSY NUT IS CORRODED						1	L	7	1 	3O				A777    		5	C	P21EA	 
1997121100721	19971211	00721	GL  	1997	12	11	EY2R9600214      	3	19960101	G	6111	S82NC2	BLADE           			BEECH 	35    	35BEECH     	1151502	CE  						MCAULY	3A32C	3A32C76     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803085		BLADE SN K103846YS IS CORRODED						1	L	7	1 	3O				A777    		5	C	P21EA	 
1997121100722	19971211	00722	GL  	1997	12	11	EY2R9600215      	3	19960101	G	6111	S82NC2	BLADE           			BEECH 	35    	35BEECH     	1151502	CE  						MCAULY	3A32C	3A32C76     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803085		BLADE SN K103399YS IS CORRODED						1	L	7	1 	3O				A777    		5	C	P21EA	 
1997121100723	19971211	00723	GL  	1997	12	11	EY2R9600216      	3	19960101	G	6110	C5270	RETAIN BEARING  			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2184 						816016		PROP ASSY RETAIN BEARING IS CORRODED						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997121100724	19971211	00724	GL  	1997	12	11	EY2R9600217      	3	19960101	G	6110	C2987	RETAIN  BEARING 													MCAULY	3AF32C	3AF32C75    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								700159		PROP ASSY RETAIN BEARING IS CORRODED																5	C	P22EA	 
1997121100725	19971211	00725	GL  	1997	12	11	EY2R9600218      	3	19960101	G	6110	A3550	FEATHER CYLINDER			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								769624		PROP ASSY FEATHER CYLINDER IS CORRODED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100726	19971211	00726	GL  	1997	12	11	EY2R9600219      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								711915		PROP ASSY RETAIN BEARING CORRODED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100727	19971211	00727	GL  	1997	12	11	EY2R9600220      	3	19960101	G	6110	C2987	RET. BEARING    			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								723586		PROP ASSY RETAIN BEARING IS CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100728	19971211	00728	GL  	1997	12	11	EY2R9600221      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								756523		PROP ASSY RETAIN BEARING CORRODED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100729	19971211	00729	GL  	1997	12	11	EY2R9600222      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								769624		PROP ASSY RETAIN BEARING IS CORRODED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100730	19971211	00730	GL  	1997	12	11	EY2R9600223      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780978		PROP ASSY RETAIN BEARING IS CORRODED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100731	19971211	00731	GL  	1997	12	11	EY2R9600224      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7710826		PROP ASSY RETAIN BEARING IS CORRODED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100732	19971211	00732	GL  	1997	12	11	EY2R9600225      	3	19960101	G	6110	C3475	NUT             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								769624		PROP ASSY NUT IS CORRODED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100733	19971211	00733	GL  	1997	12	11	EY2R9600226      	3	19960101	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								723586		PROP ASSY FEATHER CYLINDER IS CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100734	19971211	00734	GL  	1997	12	11	EY2R9600227      	3	19960101	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								724316		PROP FEATHER CYLINDER IS CORRODED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100735	19971211	00735	GL  	1997	12	11	EY2R9600228      	3	19960101	G	6110	C3550	FEATHER CYLINDER			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7710826		PROP ASSY FEATHER CYLINDER IS CORRODED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100736	19971211	00736	GL  	1997	12	11	EY2R9600229      	3	19960101	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780978		PROP HUB ASSY CORRODED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100737	19971211	00737	GL  	1997	12	11	EY2R9600230      	3	19960101	G	6111	S82NC4	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								711915		BLADE SN F40097YS IS CORRODED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997121100738	19971211	00738	GL  	1997	12	11	EY2R9600231      	3	19960101	G	6111	82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746949		BLADE SN K62721YS IS CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100739	19971211	00739	GL  	1997	12	11	EY2R9600232      	3	19960101	G	6111	82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746949		BLADE SN K62780YS IS CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100740	19971211	00740	GL  	1997	12	11	EY2R9600233      	3	19960101	G	6111	82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746949		BLADE SN K62754YS IS CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100741	19971211	00741	GL  	1997	12	11	EY2R9600234      	3	19960101	G	6110	B4459	ACTUATING PIN   			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760917		BLADE ACTUATING PIN IS CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100742	19971211	00742	GL  	1997	12	11	EY2R9600235      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760917		PROP ASSY RETAIN BEARING CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100743	19971211	00743	GL  	1997	12	11	EY2R9600236      	3	19960101	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760917		PROP ASSY HUB IS CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100744	19971211	00744	GL  	1997	12	11	EY2R9600237      	3	19960101	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760917		BLADE SN K62727YS IS CORRODED						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997121100745	19971211	00745	GL  	1997	12	11	EY2R9600238      	3	19960101	G	6111	82NC2	BLADE           			CESSNA	206   	U206F       	2073333	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4513 						771226		BLADE SN KK041YSI CORRODED						1	H	7	1 	3O				A4CE    		5	C	P22EA	 
1997121100746	19971211	00746	GL  	1997	12	11	EY2R9600239      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	206   	U206F       	2073333	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4513 						771226		PROP ASSY RETAIN BEARING IS CORRODED						1	H	7	1 	3O				A4CE    		5	C	P22EA	 
1997121100747	19971211	00747	GL  	1997	12	11	EY2R9600240      	3	19960101	G	6110	C4451	FERRULE         			CESSNA	206   	U206F       	2073333	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4513 						771226		PROP ASSY FERRULE IS CORRODED						1	H	7	1 	3O				A4CE    		5	C	P22EA	 
1997121100748	19971211	00748	GL  	1997	12	11	EY2R9600241      	3	19960101	G	6110	C4451	FERRULE         			CESSNA	206   	U206F       	2073333	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902458		PROP ASSY FERRULE IS CORRODED						1	H	7	1 	3O				A4CE    		5	C	P22EA	 
1997121100749	19971211	00749	GL  	1997	12	11	EY2R9600242      	3	19960101	G	6110	C4902	NUT             			CESSNA	206   	U206F       	2073333	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4513 						771226		PROP ASSY NUT IS CORRODED						1	H	7	1 	3O				A4CE    		5	C	P22EA	 
1997121100750	19971211	00750	GL  	1997	12	11	EY2R9600243      	3	19960101	G	6114	D5904C90	HUB             			CESSNA	206   	U206F       	2073333	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4513 						771226		PROP ASSY HUB IS CORRODED						1	H	7	1 	3O				A4CE    		5	C	P22EA	 
1997121100751	19971211	00751	GL  	1997	12	11	EY2R9600244      	3	19960101	G	6110	C1896	CYLINDER PIN    			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940191		PROP ASSY CYLINDER PIN IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121100752	19971211	00752	GL  	1997	12	11	EY2R9600245      	3	19960101	G	6111	82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782680		BLADE SN K76547 IS CORRODED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121800684	19971218	00684	GL  	1997	12	18	EY2R9600246      	3	19960101	G	6111	82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782680		PROP BLADE SN K77092 IS CORRODED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121800685	19971218	00685	GL  	1997	12	18	EY2R9600247      	3	19960101	G	6110	C3550	FEATHER CYLINDER			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733547		PROP FEATHER CYLINDER IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800686	19971218	00686	GL  	1997	12	18	EY2R9600248      	3	19960101	G	6110	C3550	FEATHER CYLINDER			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800011		PROP FEATHER CYLINDER IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800687	19971218	00687	GL  	1997	12	18	EY2R9600249      	3	19960101	G	6111	S82NC55	BLADE           			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733547		PROP BLADE SN F39058YS IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800688	19971218	00688	GL  	1997	12	18	EY2R9600250      	3	19960101	G	6110	C2987	BEARING         			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP RETAIN	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								741001		PROP ASSY RETAINING BEARING IS CORRODED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121800689	19971218	00689	GL  	1997	12	18	EY2R9600251      	3	19960101	G	6111	S82NC4	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										PROP BLADE SN F48474YS IS CORRODED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121800690	19971218	00690	GL  	1997	12	18	EY2R9600252      	3	19960101	G	6110	B3490	PISTON ROD PIN  			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779469		PROP ASSY PISTON ROD PIN IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800691	19971218	00691	GL  	1997	12	18	EY2R9600253      	3	19960101	G	6110	C1896	CYLINDER PIN    			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779469		PROP ASSY CYLINDER PIN IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800692	19971218	00692	GL  	1997	12	18	EY2R9600254      	3	19960101	G	6110	C4191	DOWEL           			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779469		PROP ASSY DOWEL IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800693	19971218	00693	GL  	1997	12	18	EY2R9600255      	3	19960101	G	6110	C1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780708		PROP ASSY CYLINDER PIN IS CORRODED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121800694	19971218	00694	GL  	1997	12	18	EY2R9600256      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780708		PROP ASSY RETAINING BEARING IS CORRODED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121800695	19971218	00695	GL  	1997	12	18	EY2R9600257      	3	19960101	G	6110	B3490	PISTON ROD PIN  			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940191		PROP ASSY PISTON ROD PIN IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800696	19971218	00696	GL  	1997	12	18	EY2R9600258      	3	19960101	G	6114	B4459	BLADE ACT PIN   			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940191		PROP ASSY BLADE ACTUATING PIN IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800697	19971218	00697	GL  	1997	12	18	EY2R9600259      	3	19960101	G	6110	C2987	RETAIN  BEARING 			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940191		PROP ASSY RETAINING BEARING IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800698	19971218	00698	GL  	1997	12	18	EY2R9600260      	3	19960101	G	6110	C3550	FEATHER CYLINDER			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779469		PROP ASSY FEATHER CYLINDER IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800699	19971218	00699	GL  	1997	12	18	EY2R9600261      	3	19960101	G	6110	C4191	DOWEL           			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940191		PROP ASSY DOWEL IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800700	19971218	00700	GL  	1997	12	18	EY2R9600262      	3	19960101	G	6110	C7036	NUT             			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940191		PROP ASSY NUT C7036 IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800701	19971218	00701	GL  	1997	12	18	EY2R9600263      	3	19960101	G	6114	D7015C93	HUB             			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779122		PROP ASSY HUB IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800702	19971218	00702	GL  	1997	12	18	EY2R9600264      	3	19960101	G	6110	C3550	FEATHER CYLINDER			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								725977		PROP ASSY FEATHER CYLINDER IS CORRODED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121800703	19971218	00703	GL  	1997	12	18	EY2R9600265      	3	19960101	G	6114	D7019C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								716065		PROP HUB ASSY IS CORRODED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997121800704	19971218	00704	GL  	1997	12	18	EY2R9600266      	3	19960101	G	6110	C5270	RETAIN BEARING  			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								840801		PROP ASSY RETAINING BEARING IS CORRODED						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800705	19971218	00705	GL  	1997	12	18	EY2R9600267      	3	19960101	G	6110	C5270	RETAIN  BEARING 			CESSNA	208   	208B        	2073701	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3797 						840997		PROP ASSY RETAINING BEARING IS CORRODED						1	H	7	1 	3T				A37CE   		5	C	P60GL	 
1997121800706	19971218	00706	GL  	1997	12	18	EY2R9600268      	3	19960101	G	6110	D5010	CYLINDER        			CESSNA	208   	208B        	2073701	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3797 						840997		PROP ASSY CYLINDER IS CORRODED						1	H	7	1 	3T				A37CE   		5	C	P60GL	 
1997121800707	19971218	00707	GL  	1997	12	18	EY2R9600269      	3	19960101	G	6114	C4326C214	HUB             			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C214   	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								788787		PROP HUB ASSY IS CORRODED						1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
1997121800708	19971218	00708	GL  	1997	12	18	EY2R9600270      	3	19960101	G	6110	C4326C218	HUB             			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C218   	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821459		PROP HUB ASSY IS CORRODED						1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
1997121800709	19971218	00709	GL  	1997	12	18	EY2R9600271      	3	19960101	G	6110	C5270	RETAIN BEARING  			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C218   	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821459		PROP ASSY RETAINING BEARING						1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
1997121800710	19971218	00710	GL  	1997	12	18	EY2R9600272      	3	19960101	G	6111	G90DHB8	BLADE           			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C218   	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821459		BLADE SN CA325 IS CORRODED						1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
1997121800711	19971218	00711	GL  	1997	12	18	EY2R9600273      	3	19960101	G	6111	G90DHB8	BLADE           			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C218   	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821459		BLADE SN CA337IS CORRODED						1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
1997121800712	19971218	00712	GL  	1997	12	18	EY2R9600274      	3	19960101	G	6114	2201	HUB             			PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN4181		PROP HUB ASSY IS CORRODED						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997121800713	19971218	00713	GL  	1997	12	18	EY2R9600275      	3	19960101	G	6110	C3903	SPLIT RETAINER  			CESSNA	336   	336         	2075602	CE  						MCAULY	2AF34C	D2AF34C302  	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								728673		PROP ASSY SPLIT RETAINER IS CORRODED						1	H	7	2 	3O				A2CE    		5	C	P5EA	 
1997121800714	19971218	00714	GL  	1997	12	18	EY2R9600276      	3	19960101	G	6110	C2987	RETAIN BEARING  			CESSNA	210   	210L        	2073448	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2953 	1371 					710981		PROP ASSY RETAINING BEARING IS CORRODED						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997121800715	19971218	00715	GL  	1997	12	18	EY2R9600277      	3	19960101	G	6110	C4902	NUT             			CESSNA	210   	210L        	2073448	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2953 	1371 					710981		PROP ASSY NUT PN C4902 IS CORRODED						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997121800716	19971218	00716	GL  	1997	12	18	EY2R9600278      	3	19960101	G	6110	C5262	CYLINDER        			CESSNA	210   	210L        	2073448	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2953 	1371 					710981		PROP ASSY CYLINDER IS CORRODED						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997121800717	19971218	00717	GL  	1997	12	18	EY2R9600279      	3	19960101	G	6110	C5262	CYLINDER        			CESSNA	206   	P206B       	2073309	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								714263		PROP ASSY CYLINDER IS CORRODED						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997121800718	19971218	00718	GL  	1997	12	18	EY2R9600280      	3	19960101	G	6111	S82NC2	BLADE           			CESSNA	210   	210L        	2073448	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2953 	1371 					710981		BLADE SN K95680YS IS CORRODED						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997121800719	19971218	00719	GL  	1997	12	18	EY2R9600281      	3	19960101	G	6111	S82NC2	BLADE           			CESSNA	210   	210L        	2073448	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2953 	1371 					710981		BLADE SN K94806YS IS CORRODED						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997121800720	19971218	00720	GL  	1997	12	18	EY2R9600282      	3	19960101	G	6111	S82NC2	BLADE           			CESSNA	210   	210L        	2073448	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2953 	1371 					710981		BLADE SN K95331YS IS CORRODED						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997121800721	19971218	00721	GL  	1997	12	18	EY2R9600283      	3	19960101	G	6110	C4451	FERRULE         			CESSNA	206   	TU206D      	2073344	CE  						MCAULY	3A32C	D3A32C90    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								850716		PROP ASSY FERRULE IS CORRODED						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997121800722	19971218	00722	GL  	1997	12	18	EY2R9600284      	3	19960101	G	6110	C5262	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								786048		PROP ASSY CYLINDER IS CORRODED						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1997121800723	19971218	00723	GL  	1997	12	18	EY2R9600285      	3	19960101	G	6110	31A	CLAMP           			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2V	HCA2V*      	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								F3197		PROP ASSY CLAMP IS CORRODED						1	L	7	1 	3O				1A15    		5	C	P24EA	 
1997121800724	19971218	00724	GL  	1997	12	18	EY2R9600286      	3	19960101	G	6110	31A	CLAMP           			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2V	HCA2V*      	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								F3207		PROP ASSY CLAMP IS CORRODED						1	L	7	1 	3O				1A15    		5	C	P24EA	 
1997121800725	19971218	00725	GL  	1997	12	18	EY2R9600287      	3	19960101	G	6110	8268	PROP ASSY       			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2V	HCA2V*      	GL  	PROP	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		811  						J1161		PROP ASSY PART(PN 8268) IS CPRRODED						1	L	7	1 	3O				1A15    		5	C	P24EA	 
1997121800726	19971218	00726	GL  	1997	12	18	EY2R9600288      	3	19960101	G	6110	971	SPLIT BEARING   			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2V	HCA2V*      	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		811  						J1161		PROP ASSY SPLIT BEARING IS CORRODED						1	L	7	1 	3O				1A15    		5	C	P24EA	 
1998010500015	19980105	00015	GL  	1998	1	5	EY2R9600289      	3	19960101	G	6110	1851	BEARING         			BEECH 	18    	D18S        	1151004	CE  						HARTZL	HCB3P	HCB3P302    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5358 	1355 					923N		PROP ASSY BEARING IS CORRODED						1	L	7	2 	3R				A765    		5	C	P29EA	 
1998010500016	19980105	00016	GL  	1998	1	5	EY2R9600290      	3	19960101	G	6110	1851	BEARING         			BEECH 	18    	D18S        	1151004	CE  						HARTZL	HCB3R	HCB3R302    	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5358 	1355 					694N		PROP ASSY BEARING IS CORRODED						1	L	7	2 	3R				A765    		5	C	P28EA	 
1998010500017	19980105	00017	GL  	1998	1	5	EY2R9600291      	3	19960101	G	6110	130195	CLAMP           			EMB   	110   	EMB110*     		SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8331 	2830 					BU3847		PROP ASSY CLAMP IS CORRODED						1	L	7	2 	4T			RT	A21SO   		6	C	P15EA	 
1998010500018	19980105	00018	GL  	1998	1	5	EY2R9600292      	3	19960101	G	6110	1851T	BEARING         			EMB   	110   	EMB110*     		SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8331 	2830 					BU3847		PROP ASSY BEARING IS CORRODED						1	L	7	2 	4T			RT	A21SO   		6	C	P15EA	 
1998010500019	19980105	00019	GL  	1998	1	5	EY2R9600293      	3	19960101	G	6110	790100018	STEEL BALL      			EMB   	110   	EMB110*     		SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8331 	2830 					BU3847		PROP ASSY STEEL BALL IS CORRODED						1	L	7	2 	4T			RT	A21SO   		6	C	P15EA	 
1997121800727	19971218	00727	GL  	1997	12	18	EY2R9600294      	3	19960101	G	6110	790100018	STEEL BALL      			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3027 	1196 					CD1153M1		PROP ASSY STEEL BALL IS CORRODED						1	H	7	2 	3T				A2PC    		6	C	P40EA	 
1997121800728	19971218	00728	GL  	1997	12	18	EY2R9600295      	3	19960101	G	6110	790100018	STEEL BALL      			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3027 	1196 					CD1159M1		PROP ASSY STEEL BALL IS CORRODED						1	H	7	2 	3T				A2PC    		6	C	P40EA	 
1997123100234	19971231	00234	GL  	1997	12	31	EY2R9600296      	3	19960101	G	6110	790100016	STEEL BALL      			GULSTM	112   	114         	7630314	SW  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1344 	543  					CH20680		STEEL BALL CORRODED.						1	L	7	1 	3O				A12SO   		5	C	P920	 
1997123100235	19971231	00235	GL  	1997	12	31	EY2R9600297      	3	19960101	G	6110	2067	MTG. STUD       			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1938 	232  					CJ838		MOUNTING STUD FOUND CORRODED.						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1997123100236	19971231	00236	GL  	1997	12	31	EY2R9600298      	3	19960101	G	6110	2202	SPLIT BEARING   			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4975 	1810 					CJ344		SPLIT BEARING HAS CORROSION.						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1997123100237	19971231	00237	GL  	1997	12	31	EY2R9600299      	3	19960101	G	6110	2202	SPLIT BEARING   			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1938 	232  					CJ838		SPLIT BEARING HAS CORROSION.						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1997123100238	19971231	00238	GL  	1997	12	31	EY2R9600300      	3	19960101	G	6110	24573	PITCH CHG FORK  			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1938 	232  					CJ838		PITCH CHANGE FORK CORRODED.						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1997123100239	19971231	00239	GL  	1997	12	31	EY2R9600301      	3	19960101	G	6114	24772	HUB             			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4975 	1810 					CJ344		HUB FOUND CORRODED.						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1997123100240	19971231	00240	GL  	1997	12	31	EY2R9600302      	3	19960101	G	6114	24773	HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP3875		HUB FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100241	19971231	00241	GL  	1997	12	31	EY2R9600303      	3	19960101	G	6114	24773	HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP6195		HUB FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100242	19971231	00242	GL  	1997	12	31	EY2R9600304      	3	19960201	G	6110		PROPELLER       			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								R773623		CORROSION FOUND ON FIX-PITCHED PROPELLER.						1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997123100243	19971231	00243	GL  	1997	12	31	EY2R9600305      	3	19960201	G	6110	C3411	BEARING RACE    			CESSNA	172   	172K        	2072430	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755593		BEARING RACE FOUND WITH CORROSION.						1	H	7	1 	3O			NT	3A12    		5	C	P3EA	 
1997123100244	19971231	00244	GL  	1997	12	31	EY2R9600306      	3	19960201	G	6110	C3903	SPLIT RETAINER  			CESSNA	172   	172K        	2072430	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755593		SPLIT RETAINER FOUND TO BE CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P3EA	 
1997123100245	19971231	00245	GL  	1997	12	31	EY2R9600307      	3	19960201	G	6114	C4239C66	HUB             			CESSNA	182   	182B        	2072706	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								731416		HUB FOUND CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100246	19971231	00246	GL  	1997	12	31	EY2R9600308      	3	19960201	G	6114	C5480C66	HUB             			CESSNA	180   	180         	2072602	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783777		HUB FOUND CORRODED.						1	H	7	1 	3O			NC	5A6     		5	C	P3EA	 
1997123100247	19971231	00247	GL  	1997	12	31	EY2R9600309      	3	19960201	G	6114	C5480C66	HUB             			CESSNA	180   	180         	2072602	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								823120		HUB FOUND CORRODED.						1	H	7	1 	3O			NC	5A6     		5	C	P3EA	 
1997123100248	19971231	00248	GL  	1997	12	31	EY2R9600310      	3	19960201	G	6110	C2987	RETAIN BEARING  			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2833 	631  					781342		RETAIN BEARING FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997123100249	19971231	00249	GL  	1997	12	31	EY2R9600311      	3	19960201	G	6114	D5880C508	HUB             			PIPER 	PA34  	PA34220T    	7103420	SO  						MCAULY	3AF32C	3AF32C508   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								851633		HUB FOUND CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1997123100250	19971231	00250	GL  	1997	12	31	EY2R9600312      	3	19960201	G	6110	A16349	BALL BEARING    			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								832248		CORROSION FOUND ON BALL BEARING.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100251	19971231	00251	GL  	1997	12	31	EY2R9600313      	3	19960201	G	6110	A16349	BALL BEARING    			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2200 	437  					840493		CORROSION FOUND ON BALL BEARING.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100252	19971231	00252	GL  	1997	12	31	EY2R9600314      	3	19960201	G	6110	C2987	RETAIN BEARING  			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			709  					761779		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100253	19971231	00253	GL  	1997	12	31	EY2R9600315      	3	19960201	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						780874		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100254	19971231	00254	GL  	1997	12	31	EY2R9600316      	3	19960201	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						790739		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100255	19971231	00255	GL  	1997	12	31	EY2R9600317      	3	19960201	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	T310Q       	2074244	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800234		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100256	19971231	00256	GL  	1997	12	31	EY2R9600318      	3	19960201	G	6110	C3475	NUT             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						790739		NUT FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100257	19971231	00257	GL  	1997	12	31	EY2R9600319      	3	19960201	G	6110	C3475	NUT             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800234		NUT FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100258	19971231	00258	GL  	1997	12	31	EY2R9600320      	3	19960201	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	T310Q       	2074244	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739404		FEATHER CYLINDER FOUND WITH CORROSION.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100259	19971231	00259	GL  	1997	12	31	EY2R9600321      	3	19960201	G	6110	C3550	FEATHER CYLINDER			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			709  					761779		FEATHER CYLINDER FOUND WITH CORROSION.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100260	19971231	00260	GL  	1997	12	31	EY2R9600322      	3	19960201	G	6110	C4451	FERRULE         			CESSNA	310   	T310Q       	2074244	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739404		CORROSION FOUND ON FERRULE.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100261	19971231	00261	GL  	1997	12	31	EY2R9600323      	3	19960201	G	6110	C4451	FERRULE         			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						780874		CORROSION FOUND ON FERRULE.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100262	19971231	00262	GL  	1997	12	31	EY2R9600324      	3	19960201	G	6110	C4451	FERRULE         			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						790739		CORROSION FOUND ON FERRULE.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100263	19971231	00263	GL  	1997	12	31	EY2R9600325      	3	19960201	G	6110	C4451	FERRULE         			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800234		CORROSION FOUND ON FERRULE.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100264	19971231	00264	GL  	1997	12	31	EY2R9600326      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	T310Q       	2074244	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739404		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100265	19971231	00265	GL  	1997	12	31	EY2R9600327      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						780874		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100266	19971231	00266	GL  	1997	12	31	EY2R9600328      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790297		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100267	19971231	00267	GL  	1997	12	31	EY2R9600329      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790628		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100268	19971231	00268	GL  	1997	12	31	EY2R9600330      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790739		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100269	19971231	00269	GL  	1997	12	31	EY2R9600331      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	T310Q       	2074244	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800234		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100270	19971231	00270	GL  	1997	12	31	EY2R9600332      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	T310Q       	2074244	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739404		BLADE, SN F45471YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100271	19971231	00271	GL  	1997	12	31	EY2R9600333      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	T310Q       	2074244	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739404		BLADE, SN F45225YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100272	19971231	00272	GL  	1997	12	31	EY2R9600334      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	T310Q       	2074244	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739404		BLADE, SN F45244YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100273	19971231	00273	GL  	1997	12	31	EY2R9600335      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790297		BLADE, SN K92607, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100274	19971231	00274	GL  	1997	12	31	EY2R9600336      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790297		BLADE, SN K92081, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100275	19971231	00275	GL  	1997	12	31	EY2R9600337      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790297		BLADE, SN K92608, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100276	19971231	00276	GL  	1997	12	31	EY2R9600338      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790628		BLADE, SN EB140, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100277	19971231	00277	GL  	1997	12	31	EY2R9600339      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790628		BLADE, SN EF120, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100278	19971231	00278	GL  	1997	12	31	EY2R9600340      	3	19960201	G	6111	S82NC4	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790628		BLADE, SN EF094, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100279	19971231	00279	GL  	1997	12	31	EY2R9600341      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			709  					761779		BLADE, SN K99017YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100280	19971231	00280	GL  	1997	12	31	EY2R9600342      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			709  					761779		BLADE, SN K98877YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100281	19971231	00281	GL  	1997	12	31	EY2R9600343      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			709  					761779		BLADE, SN K98973YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100282	19971231	00282	GL  	1997	12	31	EY2R9600344      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						780874		BLADE, SN K96093YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100283	19971231	00283	GL  	1997	12	31	EY2R9600345      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						780874		BLADE, SN K95783YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100284	19971231	00284	GL  	1997	12	31	EY2R9600346      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1655 						780874		BLADE, SN K95918YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100285	19971231	00285	GL  	1997	12	31	EY2R9600347      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790739		BLADE, SN K96121YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100286	19971231	00286	GL  	1997	12	31	EY2R9600348      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790739		BLADE, SN K95793YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100287	19971231	00287	GL  	1997	12	31	EY2R9600349      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790739		BLADE, SN K95795YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100288	19971231	00288	GL  	1997	12	31	EY2R9600350      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800234		BLADE, SN K86543, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100289	19971231	00289	GL  	1997	12	31	EY2R9600351      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800234		BLADE, SN K85795, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100290	19971231	00290	GL  	1997	12	31	EY2R9600352      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800234		BLADE, SN K85902, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100291	19971231	00291	GL  	1997	12	31	EY2R9600353      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794034		HUB CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100292	19971231	00292	GL  	1997	12	31	EY2R9600354      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								773157		BLADE, SN F38706YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100293	19971231	00293	GL  	1997	12	31	EY2R9600355      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								710420		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100294	19971231	00294	GL  	1997	12	31	EY2R9600356      	3	19960201	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755740		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100295	19971231	00295	GL  	1997	12	31	EY2R9600357      	3	19960201	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780522		CYLINDER PIN CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100296	19971231	00296	GL  	1997	12	31	EY2R9600358      	3	19960201	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780522		DOWELL DISCOVERED TO BE CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100297	19971231	00297	GL  	1997	12	31	EY2R9600359      	3	19960201	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791430		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100298	19971231	00298	GL  	1997	12	31	EY2R9600360      	3	19960201	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7810050		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100299	19971231	00299	GL  	1997	12	31	EY2R9600361      	3	19960201	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791430		DOWEL DISCOVERED TO BE CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100300	19971231	00300	GL  	1997	12	31	EY2R9600362      	3	19960201	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7810050		DOWEL FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100301	19971231	00301	GL  	1997	12	31	EY2R9600363      	3	19960201	G	6110	C4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780708		DOWEL FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100302	19971231	00302	GL  	1997	12	31	EY2R9600364      	3	19960201	G	6110	C7036	NUT             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791430		NUT CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100303	19971231	00303	GL  	1997	12	31	EY2R9600365      	3	19960201	G	6110	C7036	NUT             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7810050		NUT FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100304	19971231	00304	GL  	1997	12	31	EY2R9600366      	3	19960201	G	6110	2202	SPLIT BEARING   			BEECH 	55    	9555        	1152702	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3932 						AN3034		FOUND CORROSION IN SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P920	 
1997123100305	19971231	00305	GL  	1997	12	31	EY2R9600367      	3	19960201	G	6114	D4887C81	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	2AF34C	D2AF34C81   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								772913		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P5EA	 
1997123100306	19971231	00306	GL  	1997	12	31	EY2R9600368      	3	19960201	G	6110	1303A	BEARING         			PIPER 	PA24  	PA24        	7102402	SO  						HARTZL	HC92Z	HC92ZK8     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5489 						990L		BEARING FOUND CORRODED.						1	L	7	1 	3O				1A15    		5	C	P892	 
1997123100307	19971231	00307	GL  	1997	12	31	EY2R9600369      	3	19960201	G	6110	13088	PILOT TUBE      			PIPER 	PA24  	PA24        	7102402	SO  						HARTZL	HC92Z	HC92ZK8     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5489 						990L		PILOT TUBE FOUND CORRODED.						1	L	7	1 	3O				1A15    		5	C	P892	 
1997123100308	19971231	00308	GL  	1997	12	31	EY2R9600370      	3	19960201	G	6110	130195	CLAMP           			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CORROSION FOUND ON CLAMP.						1	L	7	2 	3T				3A20    		6	C	P15EA	 
1997123100309	19971231	00309	GL  	1997	12	31	EY2R9600371      	3	19960201	G	6111	T10173B8	BLADE           			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN 62744, FOUND CORRODED.						1	L	7	2 	3T				3A20    		6	C	P15EA	 
1997123100310	19971231	00310	GL  	1997	12	31	EY2R9600372      	3	19960201	G	6110	1851T	BEARING         			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU10928		BEARING FOUND CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997123100311	19971231	00311	GL  	1997	12	31	EY2R9600373      	3	19960201	G	6110	5862	PTCH CHG ROD    			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1322 					BU2699		PITCH CHANGE ROD FOUND BENT.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997123100312	19971231	00312	GL  	1997	12	31	EY2R9600374      	3	19960201	G	6110	1851T	BEARING         			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU3995		BEARING FOUND WITH CORROSION.						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1997123100313	19971231	00313	GL  	1997	12	31	EY2R9600375      	3	19960201	G	6110	1851T	BEARING         			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2089		BEARING FOUND WITH CORROSION.						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997123100314	19971231	00314	GL  	1997	12	31	EY2R9600376      	3	19960201	G	6110	1851T	BEARING         			BEECH 	35    	B35         	1151506	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FW1010		BEARING FOUND WITH CORROSION.						1	L	7	1 	3O				A777    		6	C	P56GL	 
1997123100315	19971231	00315	GL  	1997	12	31	EY2R9600377      	3	19960201	G	6114	4993	HUB             			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4131 	2448 					FY35A		HUB FOUND CORRODED.						1	L	7	2 	4T				A24CE   		5	C	STC	 
1997123100316	19971231	00316	GL  	1997	12	31	EY2R9600378      	3	19960201	G	6110	2202	SPLIT BEARING   			PIPER 	PA32  	PA32*       		SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2715 						BP715		SPLIT BEARING FOUND CORRODED.						1	L	7	1 	3O				A3SO    		5	C	P9EA	 
1997123100317	19971231	00317	GL  	1997	12	31	EY2R9600379      	3	19960201	G	6110	2202	SPLIT BEARING   			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP9059		SPLIT BEARING FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100318	19971231	00318	GL  	1997	12	31	EY2R9600380      	3	19960201	G	6110	2431	BOLT            			BEECH 	33    	F33         	1151423	CE  						HARTZL	HCC3Y	PHCC3YF1    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2030 						EE1402		CORROSION FOUND ON BOLT.						1	L	7	1 	3O				3A15    		5	C	P25EA	 
1997123100319	19971231	00319	GL  	1997	12	31	EY2R9600381      	3	19960201	G	6114	32518R	HUB             			BEECH 	33    	F33         	1151423	CE  						HARTZL	HCC3Y	PHCC3YF1    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2030 						EE1402		HUB, SN EE1402, FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P25EA	 
1997123100320	19971231	00320	GL  	1997	12	31	EY2R9600382      	3	19960301	G	6114	C3910C201	HUB             													MCAULY	2A34C	2A34C201    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								725913		HUB FOUND CORRODED.																5	C	P3EA	 
1997123100321	19971231	00321	GL  	1997	12	31	EY2R9600383      	3	19960301	G	6114	C3910C201	HUB             			CESSNA	180   	180         	2072602	CE  						MCAULY	2A34C	2A34C201    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								700261		CORROSION FOUND ON HUB.						1	H	7	1 	3O			NC	5A6     		5	C	P3EA	 
1997123100322	19971231	00322	GL  	1997	12	31	EY2R9600384      	3	19960301	G	6110	A4001	DOWEL           			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2804 	535  					750557		CORROSION FOUND ON DOWEL.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100323	19971231	00323	GL  	1997	12	31	EY2R9600385      	3	19960301	G	6114	C5480C66	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								754537		CORROSION FOUND ON HUB.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100324	19971231	00324	GL  	1997	12	31	EY2R9600386      	3	19960301	G	6110	C2464	FERRULE         			CESSNA	182   	182         	2072702	CE  						MCAULY	2A36C	2A36C29     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2436 	797  					61275		FERRULE CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P880	 
1997123100325	19971231	00325	GL  	1997	12	31	EY2R9600387      	3	19960301	G	6111	82NDB2	BLADE           			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C406    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN BF319, FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997123100326	19971231	00326	GL  	1997	12	31	EY2R9600388      	3	19960301	G	6111	82NDB2	BLADE           			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C406    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN BF307, FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997123100327	19971231	00327	GL  	1997	12	31	EY2R9600389      	3	19960301	G	6111	82NDB2	BLADE           			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C406    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN BF318, FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997123100328	19971231	00328	GL  	1997	12	31	EY2R9600390      	3	19960301	G	6110	C4001	DOWEL           			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815822		DOWEL FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997123100329	19971231	00329	GL  	1997	12	31	EY2R9600391      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								820713		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100330	19971231	00330	GL  	1997	12	31	EY2R9600392      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								820713		CORROSION FOUND ON DOWEL.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100331	19971231	00331	GL  	1997	12	31	EY2R9600393      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								820985		CYLINDER PIN CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100332	19971231	00332	GL  	1997	12	31	EY2R9600394      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								820985		CORROSION FOUND ON DOWEL.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100333	19971231	00333	GL  	1997	12	31	EY2R9600395      	3	19960301	G	6111	S82N4	BLADE           			CESSNA	320   	320D        	2074512	CE  						MCAULY	3AF32C	3AF32C72    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN C89048YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100334	19971231	00334	GL  	1997	12	31	EY2R9600396      	3	19960301	G	6111	S82N4	BLADE           			CESSNA	320   	320D        	2074512	CE  						MCAULY	3AF32C	3AF32C72    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN 31160YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100335	19971231	00335	GL  	1997	12	31	EY2R9600397      	3	19960301	G	6114	D7015C72	HUB             			CESSNA	320   	320D        	2074512	CE  						MCAULY	3AF32C	3AF32C72    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								690905		CORROSION FOUND ON HUB.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100336	19971231	00336	GL  	1997	12	31	EY2R9600398      	3	19960301	G	6114	D7015C87	HUB             			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								754662		CORROSION FOUND ON HUB.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100337	19971231	00337	GL  	1997	12	31	EY2R9600399      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753352		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100338	19971231	00338	GL  	1997	12	31	EY2R9600400      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753352		DOWEL PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100339	19971231	00339	GL  	1997	12	31	EY2R9600401      	3	19960301	G	6110	B3490	PISTON ROD PIN  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753352		CORROSION FOUND ON PISTON ROD PIN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100340	19971231	00340	GL  	1997	12	31	EY2R9600402      	3	19960301	G	6110	C7036	NUT             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753352		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100341	19971231	00341	GL  	1997	12	31	EY2R9600403      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727522		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100342	19971231	00342	GL  	1997	12	31	EY2R9600404      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7810424		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100343	19971231	00343	GL  	1997	12	31	EY2R9600405      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727522		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100344	19971231	00344	GL  	1997	12	31	EY2R9600406      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7810424		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100345	19971231	00345	GL  	1997	12	31	EY2R9600407      	3	19960301	G	6110	B3490	PISTON ROD PIN  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7810424		CORROSION FOUND ON PISTON ROD PIN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100346	19971231	00346	GL  	1997	12	31	EY2R9600408      	3	19960301	G	6110	C7036	NUT             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727514		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100347	19971231	00347	GL  	1997	12	31	EY2R9600409      	3	19960301	G	6110	C7036	NUT             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727522		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100348	19971231	00348	GL  	1997	12	31	EY2R9600410      	3	19960301	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727514		CORROSION FOUND ON HUB.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100349	19971231	00349	GL  	1997	12	31	EY2R9600411      	3	19960301	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727522		CORROSION FOUND ON HUB.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100350	19971231	00350	GL  	1997	12	31	EY2R9600412      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								765319		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100351	19971231	00351	GL  	1997	12	31	EY2R9600413      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								765319		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100352	19971231	00352	GL  	1997	12	31	EY2R9600414      	3	19960301	G	6110	C7036	NUT             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								765319		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100353	19971231	00353	GL  	1997	12	31	EY2R9600415      	3	19960301	G	6114	D7015C87	HUB             			CESSNA	402   	402A        	207590M	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791892		CORROSION FOUND ON HUB.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100354	19971231	00354	GL  	1997	12	31	EY2R9600416      	3	19960301	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								791238		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100355	19971231	00355	GL  	1997	12	31	EY2R9600417      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779611		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100356	19971231	00356	GL  	1997	12	31	EY2R9600418      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779760		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100357	19971231	00357	GL  	1997	12	31	EY2R9600419      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779611		CORROSION ON DOWEL.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100358	19971231	00358	GL  	1997	12	31	EY2R9600420      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779760		CORROSION ON DOWELL.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100359	19971231	00359	GL  	1997	12	31	EY2R9600421      	3	19960301	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779760		RETAIN BEARING CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100360	19971231	00360	GL  	1997	12	31	EY2R9600422      	3	19960301	G	6110	C7036	NUT             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779611		CORROSION FOUND ON NUT.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100361	19971231	00361	GL  	1997	12	31	EY2R9600423      	3	19960301	G	6111	S82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779611		BLADE, SN F81396YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100362	19971231	00362	GL  	1997	12	31	EY2R9600424      	3	19960301	G	6111	S82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779611		BLADE, SN K86826YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100363	19971231	00363	GL  	1997	12	31	EY2R9600425      	3	19960301	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782374		CORROSION FOUND ON HUB.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100364	19971231	00364	GL  	1997	12	31	EY2R9600426      	3	19960301	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779171		CORROSION FOUND ON HUB.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100365	19971231	00365	GL  	1997	12	31	EY2R9600427      	3	19960301	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN F41011YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100366	19971231	00366	GL  	1997	12	31	EY2R9600428      	3	19960301	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								737636		BLADE, SN F40982YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100367	19971231	00367	GL  	1997	12	31	EY2R9600429      	3	19960301	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								737636		BLADE, SN F90645YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100368	19971231	00368	GL  	1997	12	31	EY2R9600430      	3	19960301	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								737636		BLADE, SN F41010YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100369	19971231	00369	GL  	1997	12	31	EY2R9600431      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789634		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100370	19971231	00370	GL  	1997	12	31	EY2R9600432      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794049		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100371	19971231	00371	GL  	1997	12	31	EY2R9600433      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789634		CORROSION FOUND ON DOWEL.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100372	19971231	00372	GL  	1997	12	31	EY2R9600434      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794049		CORROSION FOUND ON DOWEL.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100373	19971231	00373	GL  	1997	12	31	EY2R9600435      	3	19960301	G	6110	B4459	BLADE ACT PIN   			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789634		CORROSION FOUND ON BLADE ACT. PIN						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100374	19971231	00374	GL  	1997	12	31	EY2R9600436      	3	19960301	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789634		RETAIN BEARING FOUND WITH CORROSION.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100375	19971231	00375	GL  	1997	12	31	EY2R9600437      	3	19960301	G	6110	C3550	FEATHER CYLINDER			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								802952		FEATHER CYLINDER FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100376	19971231	00376	GL  	1997	12	31	EY2R9600438      	3	19960301	G	6110	C7036	NUT             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794049		CORROSION FOUND ON NUT.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100377	19971231	00377	GL  	1997	12	31	EY2R9600439      	3	19960301	G	6110	C4450	FERRULE         			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727005		CORROSION FOUND ON FERRULE.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100378	19971231	00378	GL  	1997	12	31	EY2R9600440      	3	19960301	G	6110	C7036	NUT             			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727005		NUT CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100379	19971231	00379	GL  	1997	12	31	EY2R9600441      	3	19960301	G	6114	D7019C92	HUB             			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727005		CORROSION FOUND ON HUB.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100380	19971231	00380	GL  	1997	12	31	EY2R9600442      	3	19960301	G	6111	S90LF0	BLADE           			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727005		BLADE, SN B16100YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100381	19971231	00381	GL  	1997	12	31	EY2R9600443      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726157		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100382	19971231	00382	GL  	1997	12	31	EY2R9600444      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726157		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100383	19971231	00383	GL  	1997	12	31	EY2R9600445      	3	19960301	G	6110	C2987	RETAIN BEARING  			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726157		RETAIN BEARING CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100384	19971231	00384	GL  	1997	12	31	EY2R9600446      	3	19960301	G	6110	C7036	NUT             			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726157		NUT CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100385	19971231	00385	GL  	1997	12	31	EY2R9600447      	3	19960301	G	6114	D7019C92	HUB             			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726157		HUB FOUND WITH CORROSION.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100386	19971231	00386	GL  	1997	12	31	EY2R9600448      	3	19960301	G	6110	A3267	ADAPTER         			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								765319		CORROSION FOUND ON ADAPTER.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100387	19971231	00387	GL  	1997	12	31	EY2R9600449      	3	19960301	G	6110	C4451	FERRULE         			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								765319		FERRULE CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100388	19971231	00388	GL  	1997	12	31	EY2R9600450      	3	19960301	G	6114	D7019C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739711		CORROSION FOUND ON HUB.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100389	19971231	00389	GL  	1997	12	31	EY2R9600451      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								813209		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100390	19971231	00390	GL  	1997	12	31	EY2R9600452      	3	19960301	G	6110	B4459	BLADE ACT PIN   			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								813209		BLADE ACT PIN CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100391	19971231	00391	GL  	1997	12	31	EY2R9600453      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3139 	1430 					812966		CYLINDER PIN CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100392	19971231	00392	GL  	1997	12	31	EY2R9600454      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3139 	1430 					812966		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100393	19971231	00393	GL  	1997	12	31	EY2R9600455      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2594 	702  					757208		CYLINDER PIN CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100394	19971231	00394	GL  	1997	12	31	EY2R9600456      	3	19960301	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2594 	702  					930080		CYLINDER PIN CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100395	19971231	00395	GL  	1997	12	31	EY2R9600457      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2594 	702  					757208		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100396	19971231	00396	GL  	1997	12	31	EY2R9600458      	3	19960301	G	6110	A4191	DOWEL           			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2594 	702  					930080		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100397	19971231	00397	GL  	1997	12	31	EY2R9600459      	3	19960301	G	6110	B48201	ACT PIN ASSY    			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2594 	702  					757208		ACT PIN ASSY CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100398	19971231	00398	NE  	1997	12	31	EY2R9600460      	3	19960301	G	6110	D40354	SLIP RING       			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1956 						911610		SLIP RING FOUND CORRODED.						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1997123100399	19971231	00399	GL  	1997	12	31	EY2R9600461      	3	19960301	G	6114	C5078C220	HUB             			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								881543		CORROSION FOUND ON HUB.						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1997123100400	19971231	00400	GL  	1997	12	31	EY2R9600462      	3	19960301	G	6114	220118	HUB             			PIPER 	PA34  	PA34220T    	7103420	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN750		CORROSION FOUND ON HUB.						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997123100401	19971231	00401	GL  	1997	12	31	EY2R9600463      	3	19960301	G	6114	220118	HUB             			PIPER 	PA34  	PA34220T    	7103420	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN3392		CORROSION FOUND ON HUB.						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997123100402	19971231	00402	GL  	1997	12	31	EY2R9600464      	3	19960301	G	6110	2202	SPLIT BEARING   			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCJ2Y	BHCJ2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DZ117		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P37EA	 
1997123100403	19971231	00403	GL  	1997	12	31	EY2R9600465      	3	19960301	G	6114	D6603C88	HUB             			CESSNA	206   	P206        	2073304	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								740892		HUB CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997123100404	19971231	00404	GL  	1997	12	31	EY2R9600466      	3	19960301	G	6114	D6603C88	HUB             			CESSNA	206   	P206        	2073304	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								805990		HUB CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997123100405	19971231	00405	GL  	1997	12	31	EY2R9600467      	3	19960301	G	6110	A4001	DOWEL           			TMPSON	NAVION	NAVIONH     	6150122	SW  						MCAULY	3A32C	D3A32C90    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								745434		CORROSION FOUND ON DOWEL.						1	L	7	1 	3O				A782    		5	C	P21EA	 
1997123100406	19971231	00406	GL  	1997	12	31	EY2R9600468      	3	19960301	G	6114	D5904C90	HUB             			CESSNA	206   	206CESSNA   	2073302	CE  						MCAULY	3A32C	D3A32C90    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739418		HUB CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997123100407	19971231	00407	GL  	1997	12	31	EY2R9600469      	3	19960301	G	6110	14962	PILOT TUBE      			TMPSON	NAVION	NAVION*     	6150130	SW  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								F1961		CORROSION FOUND ON PILOT TUBE.						1	L	7	1 	3O				A782    		5	C	P23EA	 
1997123100408	19971231	00408	GL  	1997	12	31	EY2R9600470      	3	19960301	G	6110	83810	CLAMP           			TMPSON	NAVION	NAVION*     	6150130	SW  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								F1961		CLAMP CORRODED.						1	L	7	1 	3O				A782    		5	C	P23EA	 
1997123100409	19971231	00409	GL  	1997	12	31	EY2R9600471      	3	19960301	G	6110	83811	CLAMP           			PIPER 	PA23  	PA23150     	7102303	CE  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								K2739N		CLAMP CORRODED.						1	L	7	2 	3O			RT	1A10    		5	C	P23EA	 
1997123100410	19971231	00410	GL  	1997	12	31	EY2R9600472      	3	19960301	G	6110	83811	CLAMP           			PIPER 	PA23  	PA23150     	7102303	CE  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								K306		CLAMP CORRODED.						1	L	7	2 	3O			RT	1A10    		5	C	P23EA	 
1997123100411	19971231	00411	GL  	1997	12	31	EY2R9600473      	3	19960301	G	6110	14B	BEARING         													HARTZL	HC82X	HC82XF1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								T349		BEARING CORRODED.																5	C	P878	 
1997123100412	19971231	00412	GL  	1997	12	31	EY2R9600474      	3	19960301	G	6110	8382	CLAMP           													HARTZL	HC82X	HC82XF1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								T349		CLAMP CORRODED.																5	C	P878	 
1997123100413	19971231	00413	GL  	1997	12	31	EY2R9600475      	3	19960301	G	6114	84019B	HUB             													HARTZL	HC82X	HC82XF1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								T349		CORROSION FOUND ON HUB.																5	C	P878	 
1997123100414	19971231	00414	GL  	1997	12	31	EY2R9600476      	3	19960301	G	6110	969	SPLIT RING      													HARTZL	HC82X	HC82XF1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								T349		SPLIT RING CORRODED.																5	C	P878	 
1997123100415	19971231	00415	GL  	1997	12	31	EY2R9600477      	3	19960301	G	6111	V843310	BLADE           			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCA2X	HCA2XK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN 90218, FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P908	 
1997123100416	19971231	00416	GL  	1997	12	31	EY2R9600478      	3	19960301	G	6110	1851T	BEARING         			GULSTM	G73   	G73         	3951802	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		14430	2985 					BU2127		BEARING CORRODED.						1	H	7	2 	3R				A783    		6	C	P15EA	 
1997123100417	19971231	00417	GL  	1997	12	31	EY2R9600479      	3	19960301	G	6110	790100018	STEEL BALL      			GULSTM	G73   	G73         	3951802	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU1860		STEEL BALL CORRODED.						1	H	7	2 	3R				A783    		6	C	P15EA	 
1997123100418	19971231	00418	GL  	1997	12	31	EY2R9600480      	3	19960301	G	6110	83867	CLAMP           			GULSTM	G73   	G73         	3951802	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		14430	2985 					BU2127		CLAMP CORRODED.						1	H	7	2 	3R				A783    		6	C	P15EA	 
1997123100419	19971231	00419	GL  	1997	12	31	EY2R9600481      	3	19960301	G	6114	220117	HUB             			PIPER 	PA32  	PA32260     	7103206	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH4094		CORROSION FOUND ON HUB.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1997123100420	19971231	00420	GL  	1997	12	31	EY2R9600482      	3	19960301	G	6111	F84772	BLADE           			PIPER 	PA32  	PA32260     	7103206	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH4094		BLADE, SN D4042, FOUND CORRODED.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1997123100421	19971231	00421	GL  	1997	12	31	EY2R9600483      	3	19960301	G	6110	2202	SPLIT BEARING   			CESSNA	182   	182         	2072702	CE  						HARTZL	HCC3Y	HCC3YF1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1873 	168  					EC176		CORROSION FOUND ON SPLIT BEARING.						1	H	7	1 	3O			NT	3A13    		5	C	P25EA	 
1997123100422	19971231	00422	GL  	1997	12	31	EY2R9600484      	3	19960301	G	6114	32511R	HUB             			PIPER 	PA28  	PA28R200    	7102811	SO  						HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DY60		HUB FOUND CORRODED.						1	L	7	1 	3O				2A13    		5	C	P25EA	 
1997123100423	19971231	00423	GL  	1997	12	31	EY2R9600485      	3	19960301	G	6114	32511	HUB             			PIPER 	PA60  	PA60600     	7106001	NM  						HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CK1927		HUB FOUND CORRODED.						1	M	7	2 	3O			RT	A17WE   		5	C	P25EA	 
1997123100424	19971231	00424	GL  	1997	12	31	EY2R9600486      	3	19960301	G	6110	790100016	STEEL BALL      			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP7785		STEEL BALL FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100425	19971231	00425	GL  	1997	12	31	EY2R9600487      	3	19960301	G	6114	32857	HUB             			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								ED2589		CORROSION FOUND ON HUB.						1	L	7	2 	3O				A23CE   		5	C	P36EA	 
1998010700007	19980107	00007	GL  	1998	1	7	EY2R9600488      	3	19960401	G	6114	D7037C80	HUB             			CESSNA	310   	310L        	2074230	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								666083		CORROSION FOUND ON HUB.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998010700008	19980107	00008	GL  	1998	1	7	EY2R9600489      	3	19960401	G	6114	D7037C80	HUB             			CESSNA	310   	310L        	2074230	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								769239		CORROSION FOUND ON HUB.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100426	19971231	00426	GL  	1997	12	31	EY2R9600490      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								730410		RETAIN BEARING CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100427	19971231	00427	GL  	1997	12	31	EY2R9600491      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								731300		RETAIN BEARING CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100428	19971231	00428	GL  	1997	12	31	EY2R9600492      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								744241		RETAIN BEARING CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100429	19971231	00429	GL  	1997	12	31	EY2R9600493      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								766765		RETAIN BEARING CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100430	19971231	00430	GL  	1997	12	31	EY2R9600494      	3	19960401	G	6110		RETAIN BEARING  			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794953		RETAIN BEARING CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100431	19971231	00431	GL  	1997	12	31	EY2R9600495      	3	19960401	G	6114	D7015C87	HUB             			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								673158		CORROSION FOUND ON HUB.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100432	19971231	00432	GL  	1997	12	31	EY2R9600496      	3	19960401	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					721970		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100433	19971231	00433	GL  	1997	12	31	EY2R9600497      	3	19960401	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								784317		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100434	19971231	00434	GL  	1997	12	31	EY2R9600498      	3	19960401	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					7810422		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100435	19971231	00435	GL  	1997	12	31	EY2R9600499      	3	19960401	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733287		CYLINDER PIN CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100436	19971231	00436	GL  	1997	12	31	EY2R9600500      	3	19960401	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					721970		DOWEL FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100437	19971231	00437	GL  	1997	12	31	EY2R9600501      	3	19960401	G	6110	A4191	DOWEL           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733287		DOWEL FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100438	19971231	00438	GL  	1997	12	31	EY2R9600502      	3	19960401	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733313		DOWEL FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100439	19971231	00439	GL  	1997	12	31	EY2R9600503      	3	19960401	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								784317		DOWEL FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100440	19971231	00440	GL  	1997	12	31	EY2R9600504      	3	19960401	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					7810422		DOWEL FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100441	19971231	00441	GL  	1997	12	31	EY2R9600505      	3	19960401	G	6110	B4459	BLADE ACT PIN   			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					721970		BLADE ACT PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100442	19971231	00442	GL  	1997	12	31	EY2R9600506      	3	19960401	G	6110	B4459	BLADE ACT PIN   			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733287		BLADE ACT PIN FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100443	19971231	00443	GL  	1997	12	31	EY2R9600507      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					721970		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100444	19971231	00444	GL  	1997	12	31	EY2R9600508      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733287		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100445	19971231	00445	GL  	1997	12	31	EY2R9600509      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					7810422		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100446	19971231	00446	GL  	1997	12	31	EY2R9600510      	3	19960401	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					7810422		FEATHER CYLINDER CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100447	19971231	00447	GL  	1997	12	31	EY2R9600511      	3	19960401	G	6110	C4451	FERRULE         			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					721970		FERRULE FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100448	19971231	00448	GL  	1997	12	31	EY2R9600512      	3	19960401	G	6110	C4451	FERRULE         			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733287		FERRULE FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100449	19971231	00449	GL  	1997	12	31	EY2R9600513      	3	19960401	G	6110	C4451	FERRULE         			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					7810422		FERRULE FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100450	19971231	00450	GL  	1997	12	31	EY2R9600514      	3	19960401	G	6110	C7036	NUT             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					721970		CORROSION FOUND ON NUT.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100451	19971231	00451	GL  	1997	12	31	EY2R9600515      	3	19960401	G	6110	C7036	NUT             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733287		CORROSION FOUND ON NUT.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100452	19971231	00452	GL  	1997	12	31	EY2R9600516      	3	19960401	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733313		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100453	19971231	00453	GL  	1997	12	31	EY2R9600517      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	320   	320E        	2074514	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747347		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100454	19971231	00454	GL  	1997	12	31	EY2R9600518      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	320   	320E        	2074514	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747406		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100455	19971231	00455	GL  	1997	12	31	EY2R9600519      	3	19960401	G	6110	C3475	NUT             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								724578		NUT FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100456	19971231	00456	GL  	1997	12	31	EY2R9600520      	3	19960401	G	6110	C3550	FEATHER CYLINDER			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								724578		FEATHER CYLINDER FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100457	19971231	00457	GL  	1997	12	31	EY2R9600521      	3	19960401	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								775854		CYLINDER PIN CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100458	19971231	00458	GL  	1997	12	31	EY2R9600522      	3	19960401	G	6110	C7036	NUT             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								775854		CORROSION FOUND ON NUT.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100459	19971231	00459	GL  	1997	12	31	EY2R9600523      	3	19960401	G	6111	S90LF0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								775854		BLADE, SN B24646YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100460	19971231	00460	GL  	1997	12	31	EY2R9600524      	3	19960401	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780456		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100461	19971231	00461	GL  	1997	12	31	EY2R9600525      	3	19960401	G	6110	C5270	RETAIN BEARING  			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1391 	715  					830266		RETAIN BEARING FOUND WITH CORROSION.						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1997123100462	19971231	00462	GL  	1997	12	31	EY2R9600526      	3	19960401	G	6110	2224	PROPELLER       			PIPER 	PA28  	PA28*       		SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3196 	759  					AM1840		PROPELLER ASSY FOUND CORRODED						1	L	7	1 	3O				2A13    		5	C	P920	 
1997123100463	19971231	00463	GL  	1997	12	31	EY2R9600527      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	185   	185         	2072802	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								710952		RETAIN BEARING FOUND CORRODED.						1	H	7	1 	3O			NC	3A24    		5	C	P3EA	 
1997123100464	19971231	00464	GL  	1997	12	31	EY2R9600528      	3	19960401	G	6114	C2715C33	HUB             			CESSNA	210   	210B        	2073410	CE  						MCAULY	2A36C	D2A36C33    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		605  						745830		HUB FOUND WITH CORROSION.						1	H	7	1 	3O				3A21    		5	C	P880	 
1997123100465	19971231	00465	GL  	1997	12	31	EY2R9600529      	3	19960401	G	6110	C2987	RETAIN BEARING  			CESSNA	210   	210L        	2073448	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3830 	921  					752306		RETAIN BEARING FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997123100466	19971231	00466	GL  	1997	12	31	EY2R9600530      	3	19960401	G	6110	A4001	DOWEL           			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								801364		DOWEL CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100467	19971231	00467	GL  	1997	12	31	EY2R9600531      	3	19960401	G	6110	B48202	ACT PIN ASSY    			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								801364		ACT PIN ASSY FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100468	19971231	00468	GL  	1997	12	31	EY2R9600532      	3	19960401	G	6110	C3903	SPLIT RETAINER  			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								801364		CORROSION FOUND ON SPLIT RETAINER.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100469	19971231	00469	GL  	1997	12	31	EY2R9600533      	3	19960401	G	6110	14B	BEARING         			CESSNA	180   	180         	2072602	CE  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								T1843N		BEARING CORRODED.						1	H	7	1 	3O			NC	5A6     		5	C	P23EA	 
1997123100470	19971231	00470	GL  	1997	12	31	EY2R9600534      	3	19960401	G	6110	14B	BEARING         			CESSNA	310   	310G        	2074218	CE  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1425 					F1739		BEARING CORRODED.						1	L	7	2 	3O				3A10    		5	C	P23EA	 
1997123100471	19971231	00471	GL  	1997	12	31	EY2R9600535      	3	19960401	G	6110	14A	BEARING         			CESSNA	310   	310A        	2074204	CE  						HARTZL	HC82X	HC82XF2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								F2202		BEARING CORRODED.						1	L	7	2 	3O				3A10    		5	C	P878	 
1997123100472	19971231	00472	GL  	1997	12	31	EY2R9600536      	3	19960401	G	6110	1496	PILOT TUBE      			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82X	HC82XK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								618G		PILOT TUBE FOUND WITH CORROSION.						1	L	7	1 	3O				1A15    		5	C	P878	 
1997123100473	19971231	00473	GL  	1997	12	31	EY2R9600537      	3	19960401	G	6110	1331	SPLIT RING      			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			320  					1008F		CORROSION FOUND ON SPLIT RING.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100474	19971231	00474	GL  	1997	12	31	EY2R9600538      	3	19960401	G	6110	1308	PILOT TUBE      			PIPER 	PA24  	PA24        	7102402	SO  						HARTZL	HC92Z	HC92ZK8     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1286L		PILOT TUBE FOUND WITH CORROSION.						1	L	7	1 	3O				1A15    		5	C	P892	 
1997123100475	19971231	00475	GL  	1997	12	31	EY2R9600539      	3	19960401	G	6110	1301A	CLAMP           			BEECH 	50    	G50         	1152532	CE  						HARTZL	HC93Z	HC93Z202    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1548A		CLAMP CORRODED.						1	L	7	2 	3O				5A4     		5	C	P891	 
1997123100476	19971231	00476	GL  	1997	12	31	EY2R9600540      	3	19960401	G	6110	1303A	BEARING         			BEECH 	50    	G50         	1152532	CE  						HARTZL	HC93Z	HC93Z202    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								690A		BEARING CORRODED.						1	L	7	2 	3O				5A4     		5	C	P891	 
1997123100477	19971231	00477	GL  	1997	12	31	EY2R9600541      	3	19960401	G	6110	1308	PILOT TUBE      			BEECH 	50    	G50         	1152532	CE  						HARTZL	HC93Z	HC93Z202    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1548A		PILOT TUBE FOUND WITH CORROSION.						1	L	7	2 	3O				5A4     		5	C	P891	 
1997123100478	19971231	00478	GL  	1997	12	31	EY2R9600542      	3	19960401	G	6110	1308	PILOT TUBE      			BEECH 	50    	G50         	1152532	CE  						HARTZL	HC93Z	HC93Z202    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								690A		PILOT TUBE FOUND WITH CORROSION.						1	L	7	2 	3O				5A4     		5	C	P891	 
1997123100479	19971231	00479	GL  	1997	12	31	EY2R9600543      	3	19960401	G	6110	83810	CLAMP           			CESSNA	320   	320B        	2074508	CE  						HARTZL	HCA2V	HCA2VF2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								Y2618		CLAMP CORRODED.						1	L	7	2 	3O				3A25    		5	C	P24EA	 
1997123100480	19971231	00480	GL  	1997	12	31	EY2R9600544      	3	19960401	G	6110	1851T	BEARING         			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU392		CORROSION FOUND ON BEARING.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997123100481	19971231	00481	GL  	1997	12	31	EY2R9600545      	3	19960401	G	6110	1891A	PILOT TUBE      			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU392		PILOT TUBE FOUND CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997123100482	19971231	00482	GL  	1997	12	31	EY2R9600546      	3	19960401	G	6114	84060	HUB             			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU392		CORROSION FOUND ON HUB.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997123100483	19971231	00483	GL  	1997	12	31	EY2R9600547      	3	19960401	G	6110	83865	CLAMP           			EMB   	110   	EMB110*     		SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			3669 					BU11710		CLAMP CORRODED.						1	L	7	2 	4T			RT	A21SO   		6	C	P15EA	 
1997123100484	19971231	00484	GL  	1997	12	31	EY2R9600548      	3	19960401	G	6110	18912A	PILOT TUBE      			MTSBSI	MU2   	MU2B        	5780404	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV452		PILOT TUBE FOUND WITH CORROSION.						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997123100485	19971231	00485	GL  	1997	12	31	EY2R9600549      	3	19960401	G	6110	1851T	BEARING         			STBROS	SD3   	SD360       	8100606	EU  						HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		22514	706  					EV134		BEARING CORRODED.						2	H	7	2 	4T				A41EU   		6	C	P44GL	 
1997123100486	19971231	00486	GL  	1997	12	31	EY2R9600550      	3	19960401	G	6110	2432	BOLT            			CESSNA	172   	172         	2072402	CE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH22812		BOLT FOUND CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P920	 
1997123100487	19971231	00487	GL  	1997	12	31	EY2R9600551      	3	19960401	G	6114	220116	HUB             			PARTEN	P68   	P68B        		EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1625 					AU4481		HUB FOUND CORRODED.						1	H	7	2 	3O				A31EU   		5	C	P920	 
1997123100488	19971231	00488	GL  	1997	12	31	EY2R9600552      	3	19960401	G	6111	FC7666A4	BLADE           			PARTEN	P68   	P68B        		EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1625 					AU4481		BLADE, SN D11451, FOUND WITH CORROSION.						1	H	7	2 	3O				A31EU   		5	C	P920	 
1997123100489	19971231	00489	GL  	1997	12	31	EY2R9600553      	3	19960401	G	6111	FC7666A4	BLADE           			PARTEN	P68   	P68B        		EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1625 					AU4481		BLADE, SN D11394, FOUND WITH CORROSION.						1	H	7	2 	3O				A31EU   		5	C	P920	 
1997123100490	19971231	00490	GL  	1997	12	31	EY2R9600554      	3	19960401	G	6110	2202	SPLIT BEARING   			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3456 	960  					BG125		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100491	19971231	00491	GL  	1997	12	31	EY2R9600555      	3	19960401	G	6110	2202	SPLIT BEARING   			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3449 	960  					BG1600		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100492	19971231	00492	GL  	1997	12	31	EY2R9600556      	3	19960401	G	6110	2202	SPLIT BEARING   			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			758  					DJ1538		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997123100493	19971231	00493	GL  	1997	12	31	EY2R9600557      	3	19960501	G	6114	C3910C203	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								754900		HUB CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100494	19971231	00494	GL  	1997	12	31	EY2R9600558      	3	19960501	G	6110	C3411	BEARING RACE    			CESSNA	172   	172K        	2072430	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800627		BEARING RACE CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P3EA	 
1997123100495	19971231	00495	GL  	1997	12	31	EY2R9600559      	3	19960501	G	6114	C4211C76	HUB             			BEECH 	36    	36BEECH     	1151602	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								740263		HUB CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997123100496	19971231	00496	GL  	1997	12	31	EY2R9600560      	3	19960501	G	6114	D6603C88	HUB             			CESSNA	210   	210         	2073402	CE  						MCAULY	3A32C	3A32C*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								750803		HUB CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P21EA	 
1997123100497	19971231	00497	GL  	1997	12	31	EY2R9600561      	3	19960501	G	6110	C5270	RETAIN BEARING  			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821250		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100498	19971231	00498	GL  	1997	12	31	EY2R9600562      	3	19960501	G	6114	D5882C507	HUB             			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815927		HUB CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100499	19971231	00499	GL  	1997	12	31	EY2R9600563      	3	19960501	G	6111	G82NEB8	BLADE           			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN BH432, FOUND CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100500	19971231	00500	GL  	1997	12	31	EY2R9600564      	3	19960501	G	6111	G82NEB8	BLADE           			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN BH434, FOUND CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100501	19971231	00501	GL  	1997	12	31	EY2R9600565      	3	19960501	G	6111	G82NEB8	BLADE           			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN BI935, FOUND CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100502	19971231	00502	GL  	1997	12	31	EY2R9600566      	3	19960501	G	6111	S82NC4	BLADE           			CESSNA	320   	320F        	2074516	CE  						MCAULY	3AF32C	3AF32C72    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								703825		BLADE, SN 31158YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100503	19971231	00503	GL  	1997	12	31	EY2R9600567      	3	19960501	G	6111	S82NC4	BLADE           			CESSNA	320   	320F        	2074516	CE  						MCAULY	3AF32C	3AF32C72    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760336		BLADE, SN C40376YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100504	19971231	00504	GL  	1997	12	31	EY2R9600568      	3	19960501	G	6111	S82NB6	BLADE           			BEECH 	55    	9555        	1152702	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783253		BLADE, SN K101554YS, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100505	19971231	00505	GL  	1997	12	31	EY2R9600569      	3	19960501	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747159		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100506	19971231	00506	GL  	1997	12	31	EY2R9600570      	3	19960501	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								797174		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100507	19971231	00507	GL  	1997	12	31	EY2R9600571      	3	19960501	G	6110	C3475	NUT             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747159		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100508	19971231	00508	GL  	1997	12	31	EY2R9600572      	3	19960501	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								737905		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100509	19971231	00509	GL  	1997	12	31	EY2R9600573      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN F629YS, CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100510	19971231	00510	GL  	1997	12	31	EY2R9600574      	3	19960501	G	6114	D7015C87	HUB             			CESSNA	401   	401         	207590C	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								751198		HUB CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100511	19971231	00511	GL  	1997	12	31	EY2R9600575      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								787149		BLADE, SN K88765YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100512	19971231	00512	GL  	1997	12	31	EY2R9600576      	3	19960501	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726481		RETAIN BEARING FOUND WITH CORROSION.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100513	19971231	00513	GL  	1997	12	31	EY2R9600577      	3	19960501	G	6110	C4451	FERRULE         			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726481		FERRULE FOUND WITH CORROSION.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100514	19971231	00514	GL  	1997	12	31	EY2R9600578      	3	19960501	G	6110	C7036	NUT             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726481		NUT CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100515	19971231	00515	GL  	1997	12	31	EY2R9600579      	3	19960501	G	6110	D3474	PISTON ROD ASSY 			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726481		FOUND CORROSION ON PISTON ROD ASSY.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100516	19971231	00516	GL  	1997	12	31	EY2R9600580      	3	19960501	G	6110	B3490	PISTON ROD PIN  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								748132		FOUND CORROSION ON PISTON ROD ASSY.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100517	19971231	00517	GL  	1997	12	31	EY2R9600581      	3	19960501	G	6111	B4459	BLADE ACT PIN   			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747892		BLADE ACT PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100518	19971231	00518	GL  	1997	12	31	EY2R9600582      	3	19960501	G	6111	B4459	BLADE ACT PIN   			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								748132		BLADE ACT PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100519	19971231	00519	GL  	1997	12	31	EY2R9600583      	3	19960501	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3428 	501  					723023		FEATHER CYLINDER FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100520	19971231	00520	GL  	1997	12	31	EY2R9600584      	3	19960501	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3428 	501  					723458		FEATHER CYLINDER FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100521	19971231	00521	GL  	1997	12	31	EY2R9600585      	3	19960501	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747892		FEATHER CYLINDER FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100522	19971231	00522	GL  	1997	12	31	EY2R9600586      	3	19960501	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								748132		FEATHER CYLINDER FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100523	19971231	00523	GL  	1997	12	31	EY2R9600587      	3	19960501	G	6110	C7036	NUT             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3428 	501  					723458		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100524	19971231	00524	GL  	1997	12	31	EY2R9600588      	3	19960501	G	6110	C7036	NUT             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747892		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100525	19971231	00525	GL  	1997	12	31	EY2R9600589      	3	19960501	G	6110	C7036	NUT             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								748132		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100526	19971231	00526	GL  	1997	12	31	EY2R9600590      	3	19960501	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3428 	501  					723023		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100527	19971231	00527	GL  	1997	12	31	EY2R9600591      	3	19960501	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3428 	501  					723458		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100528	19971231	00528	GL  	1997	12	31	EY2R9600592      	3	19960501	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747892		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100529	19971231	00529	GL  	1997	12	31	EY2R9600593      	3	19960501	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								748132		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100530	19971231	00530	GL  	1997	12	31	EY2R9600594      	3	19960501	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								740286		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100531	19971231	00531	GL  	1997	12	31	EY2R9600595      	3	19960501	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782374		HUB CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100532	19971231	00532	GL  	1997	12	31	EY2R9600596      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795337		BLADE, SN K96453YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100533	19971231	00533	GL  	1997	12	31	EY2R9600597      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795337		BLADE, SN K96440YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100534	19971231	00534	GL  	1997	12	31	EY2R9600598      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795337		BLADE, SN K96436YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100535	19971231	00535	GL  	1997	12	31	EY2R9600599      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790630		BLADE, SN K92092YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100536	19971231	00536	GL  	1997	12	31	EY2R9600600      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790630		BLADE, SN K92062YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100537	19971231	00537	GL  	1997	12	31	EY2R9600601      	3	19960501	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								790819		BLADE, SN K92524YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100538	19971231	00538	GL  	1997	12	31	EY2R9600602      	3	19960501	G	6110	A1896	CYLINDER PIN    			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								761198		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100539	19971231	00539	GL  	1997	12	31	EY2R9600603      	3	19960501	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794518		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100540	19971231	00540	GL  	1997	12	31	EY2R9600604      	3	19960501	G	6110	A4191	DOWEL           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								761198		DOWEL CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100541	19971231	00541	GL  	1997	12	31	EY2R9600605      	3	19960501	G	6110	A4191	DOWEL           			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794518		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100542	19971231	00542	GL  	1997	12	31	EY2R9600606      	3	19960501	G	6110	C7036	NUT             			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794518		NUT CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100543	19971231	00543	GL  	1997	12	31	EY2R9600607      	3	19960501	G	6114	D7015C93	HUB             			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794518		HUB FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100544	19971231	00544	GL  	1997	12	31	EY2R9600608      	3	19960501	G	6110	A1896	CYLINDER PIN    			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760862		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100545	19971231	00545	GL  	1997	12	31	EY2R9600609      	3	19960501	G	6110	A4191	DOWEL           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760862		DOWEL FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100546	19971231	00546	GL  	1997	12	31	EY2R9600610      	3	19960501	G	6110	C4451	FERRULE         			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			453  					7710747		FERRULE FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100547	19971231	00547	GL  	1997	12	31	EY2R9600611      	3	19960501	G	6110	C7036	NUT             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			453  					7710747		NUT FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100548	19971231	00548	GL  	1997	12	31	EY2R9600612      	3	19960501	G	6110	C2987	RETAIN BEARING  			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								730390		RETAIN BEARING FOUND WITH CORROSION.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100549	19971231	00549	GL  	1997	12	31	EY2R9600613      	3	19960501	G	6110	C7036	NUT             			CESSNA	421   	421C        	2076016	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								694532		NUT FOUND WITH CORROSION.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100550	19971231	00550	GL  	1997	12	31	EY2R9600614      	3	19960501	G	6114	D5894C92	HUB             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								748237		HUB FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100551	19971231	00551	GL  	1997	12	31	EY2R9600615      	3	19960501	G	6114	D7019C92	HUB             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733129		HUB FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100552	19971231	00552	GL  	1997	12	31	EY2R9600616      	3	19960501	G	6110	B48201	ACT PIN ASSY    			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								769147		ACT PIN ASSY FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1997123100553	19971231	00553	GL  	1997	12	31	EY2R9600617      	3	19960501	G	6110	B48201	ACT PIN ASSY    			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								771839		ACT PIN ASSY FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1997123100554	19971231	00554	GL  	1997	12	31	EY2R9600618      	3	19960501	G	6110	P501459401	PROPELLER       			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								761556		EXCESSIVE INTERNAL DAMAGE & CORR						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1997123100555	19971231	00555	GL  	1997	12	31	EY2R9600619      	3	19960501	G	6110	C5116	FEEDBACK COLLAR 			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902362		FEEDBACK COLLAR CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997123100556	19971231	00556	GL  	1997	12	31	EY2R9600620      	3	19960501	G	6110	C5503	BETA ROD        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902362		BETA ROD FOUND CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997123100557	19971231	00557	GL  	1997	12	31	EY2R9600621      	3	19960501	G	6110	C5503	BETA ROD        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								910691		BETA ROD FOUND CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997123100558	19971231	00558	GL  	1997	12	31	EY2R9600622      	3	19960501	G	6110	D5010	CYLINDER        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								910691		CYLINDER FOUND CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997123100559	19971231	00559	NE  	1997	12	31	EY2R9600623      	3	19960501	G	6114	D6153C652	HUB             			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		15814	2454 					881745		HUB FOUND CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1997123100560	19971231	00560	GL  	1997	12	31	EY2R9600624      	3	19960501	G	6110	C3411	BEARING RACE    			MOONEY	M20   	M20K        	5870220	SW  						MCAULY	2D34C	B2D34C214   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								797211		BEARING RACE CORRODED.						1	L	7	1 	3O				2A3     		5	C	P7EA	 
1997123100561	19971231	00561	GL  	1997	12	31	EY2R9600625      	3	19960501	G	6110	C5270	RETAIN BEARING  			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								870599		RETAIN BEARING FOUND WITH CORROSION.						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1997123100562	19971231	00562	GL  	1997	12	31	EY2R9600626      	3	19960501	G	6110	B3905	BASE ASSY PIN   			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1202 						921377		BASE ASSY PIN.						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1998010700009	19980107	00009	GL  	1998	1	7	EY2R9600627      	3	19960501	G	6111	74E0	BLADE           			MOONEY	M20   	M20         	5870202	SW  						MCAULY	2D34C	B2D34C53    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								701181		BLADE, SN A10840, FOUND CORRODED.						1	L	7	1 	3O				2A3     		5	C	P7AE	 
1998010700010	19980107	00010	GL  	1998	1	7	EY2R9600628      	3	19960501	G	6111	74E0	BLADE           			MOONEY	M20   	M20         	5870202	SW  						MCAULY	2D34C	B2D34C53    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								701181		BLADE, SN A5868, FOUND CORRODED.						1	L	7	1 	3O				2A3     		5	C	P7AE	 
1997123100563	19971231	00563	GL  	1997	12	31	EY2R9600629      	3	19960501	G	6110	2202	SPLIT BEARING   			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN1446		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P920	 
1997123100564	19971231	00564	GL  	1997	12	31	EY2R9600630      	3	19960501	G	6110	24573	PITCH CHGE FORK 			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN1446		PITCH CHANGE FORK CORRODED.						1	L	7	2 	3O				3A16    		5	C	P920	 
1997123100565	19971231	00565	GL  	1997	12	31	EY2R9600631      	3	19960501	G	6111	FC84756	BLADE           			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN1446		BLADE, SN C77820, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P920	 
1997123100566	19971231	00566	GL  	1997	12	31	EY2R9600632      	3	19960501	G	6111	FC84756	BLADE           			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN1446		BLADE, SN 64981, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P920	 
1997123100567	19971231	00567	GL  	1997	12	31	EY2R9600633      	3	19960501	G	6110	2202	SPLIT BEARING   			BEECH 	95    	95B55       	1152729	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN2167		SPLIT BEARING HAS CORROSION.						1	L	7	2 	3O			RT	3A16    		5	C	P920	 
1997123100568	19971231	00568	GL  	1997	12	31	EY2R9600634      	3	19960501	G	6110	2202	SPLIT BEARING   			BEECH 	95    	95B55       	1152729	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN2184		SPLIT BEARING HAS CORROSION.						1	L	7	2 	3O			RT	3A16    		5	C	P920	 
1997123100569	19971231	00569	GL  	1997	12	31	EY2R9600635      	3	19960501	G	6110	24915	PITCH CHANGE ROD			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCJ2Y	BHCJ2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DZ895		PITCH CHANGE ROD FOUND WITH CORROSION.						1	L	7	2 	3O				3A16    		5	C	P37EA	 
1997123100570	19971231	00570	GL  	1997	12	31	EY2R9600636      	3	19960501	G	6110	S76C2	BLADE           			MAULE 	M5    	M5220C      	5460133	SO  						MCAULY	2A34C	D2A34C67    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								758280		BLADE, SN B49631YS, FOUND WITH CORROSION.						1	H	7	1 	3O				3A23    		5	C	P3EA	 
1997123100571	19971231	00571	GL  	1997	12	31	EY2R9600637      	3	19960501	G	6110	B2345	PISTON TUBE     			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								891351		PISTON TUBE FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100572	19971231	00572	GL  	1997	12	31	EY2R9600638      	3	19960501	G	6110	PL4664	KIT ASSY        			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								891351		PROPELLER KIT ASSY FOUND CORRODED						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100573	19971231	00573	GL  	1997	12	31	EY2R9600639      	3	19960501	G	6111	78CBA2	BLADE           			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								736926		BLADE, SN K73867, FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100574	19971231	00574	GL  	1997	12	31	EY2R9600640      	3	19960501	G	6110	C4451	FERRULE         			CESSNA	210   	T210*       		CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								770656		FERRULE FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997123100575	19971231	00575	GL  	1997	12	31	EY2R9600641      	3	19960501	G	6110	C5262	CYLINDER        			CESSNA	210   	T210*       		CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								770656		CYLINDER FOUND WITH CORROSION.						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997123100576	19971231	00576	GL  	1997	12	31	EY2R9600642      	3	19960501	G	6110	A4001	DOWEL           			CESSNA	210   	210M        	2073450	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								785659		DOWEL CORRODED.						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1997123100577	19971231	00577	GL  	1997	12	31	EY2R9600643      	3	19960501	G	6114	D5858C402	HUB             			CESSNA	206   	206CESSNA   	2073302	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								861233		HUB FOUND WITH CORROSION.						1	H	7	1 	3O				A4CE    		5	C	P47GL	 
1997123100578	19971231	00578	GL  	1997	12	31	EY2R9600644      	3	19960501	G	6110	C4001	DOWEL           			CESSNA	206   	U206        	2073306	CE  						MCAULY	D3A34	D3A34C404   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2194 	410  					811646		DOWEL CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P47GL	 
1997123100579	19971231	00579	GL  	1997	12	31	EY2R9600645      	3	19960501	G	6114	D4190C307	HUB             			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								736926		HUB FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100580	19971231	00580	GL  	1997	12	31	EY2R9600646      	3	19960501	G	6110	1303	BEARING         			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1798F		BEARING CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100581	19971231	00581	GL  	1997	12	31	EY2R9600647      	3	19960501	G	6110	1303A	BEARING         			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1544F		BEARING CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100582	19971231	00582	GL  	1997	12	31	EY2R9600648      	3	19960501	G	6110	1330	PROPELLER       			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1543F		PROP ASSY CORRODED						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100583	19971231	00583	GL  	1997	12	31	EY2R9600649      	3	19960501	G	6110	1331	SPLIT RING      			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1543F		CORROSION FOUND ON SPLIT RING.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100584	19971231	00584	GL  	1997	12	31	EY2R9600650      	3	19960501	G	6110	1331	SPLIT RING      			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1544F		CORROSION FOUND ON SPLIT RING.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100585	19971231	00585	GL  	1997	12	31	EY2R9600651      	3	19960501	G	6110	83830	CLAMP           			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1543F		CLAMP CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100586	19971231	00586	GL  	1997	12	31	EY2R9600652      	3	19960501	G	6110	83830	CLAMP           			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1544F		CLAMP CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100587	19971231	00587	GL  	1997	12	31	EY2R9600653      	3	19960501	G	6110	1301	CLAMP           			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92Z	HC92ZK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1141F		CLAMP CORRODED.						1	L	7	2 	3O				3A16    		5	C	P892	 
1997123100588	19971231	00588	GL  	1997	12	31	EY2R9600654      	3	19960501	G	6110	8382	CLAMP           			BEECH 	35    	B35         	1151506	CE  						HARTZL	HCA2X	HCA2X*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CLAMP CORRODED.						1	L	7	1 	3O				A777    		5	C	P908	 
1997123100589	19971231	00589	GL  	1997	12	31	EY2R9600655      	3	19960501	G	6110	83867	CLAMP           			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CLAMP CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997123100590	19971231	00590	GL  	1997	12	31	EY2R9600656      	3	19960501	G	6110	83867	CLAMP           			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CLAMP CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997123100591	19971231	00591	GL  	1997	12	31	EY2R9600657      	3	19960501	G	6110	1891	PILOT TUBE      			AYRES 	S2    	S2RT34NORMAL	0970106	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU17784		PILOT TUBE FOUND WITH CORROSION.						1	L	7	1 	3T				A3SW    		6	C	P15EA	 
1997123100592	19971231	00592	GL  	1997	12	31	EY2R9600658      	3	19960501	G	6110	1851T	BEARING         			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU13149		BEARING CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100593	19971231	00593	GL  	1997	12	31	EY2R9600659      	3	19960501	G	6110	1851T	BEARING         			AIRTRC	AT400 	AT400       	0390202	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU14660		BEARING CORRODED.						1	L	7	1 	3T				A9SW    		6	C	P15EA	 
1997123100594	19971231	00594	GL  	1997	12	31	EY2R9600660      	3	19960501	G	6110	1891	PILOT TUBE      			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU17706		PILOT TUBE FOUND CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100595	19971231	00595	GL  	1997	12	31	EY2R9600661      	3	19960501	G	6110	1891	PILOT TUBE      			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU17852		PILOT TUBE FOUND CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100596	19971231	00596	GL  	1997	12	31	EY2R9600662      	3	19960501	G	6110	1891	PILOT TUBE      			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU18954		PILOT TUBE FOUND CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100597	19971231	00597	GL  	1997	12	31	EY2R9600663      	3	19960501	G	6110	1891	PILOT TUBE      			AIRTRC	AT400 	AT400       	0390202	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU3882		PILOT TUBE FOUND CORRODED.						1	L	7	1 	3T				A9SW    		6	C	P15EA	 
1997123100598	19971231	00598	GL  	1997	12	31	EY2R9600664      	3	19960501	G	6110	30215	PISTON UNIT     			AIRTRC	AT400 	AT400       	0390202	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU3882		PISTON UNIT FOUND CORRODED.						1	L	7	1 	3T				A9SW    		6	C	P15EA	 
1997123100599	19971231	00599	GL  	1997	12	31	EY2R9600665      	3	19960501	G	6110	868AS	PTCH CHANGE ROD 			AIRTRC	AT400 	AT400       	0390202	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU3882		PITCH CHANGE ROD FOUND CORRODED.						1	L	7	1 	3T				A9SW    		6	C	P15EA	 
1997123100600	19971231	00600	GL  	1997	12	31	EY2R9600666      	3	19960501	G	6110	1851T	BEARING         			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4155 						BU13998		BEARING CORRODED.						1	L	7	2 	4T				A24CE   		6	C	P15EA	 
1997123100601	19971231	00601	GL  	1997	12	31	EY2R9600667      	3	19960501	G	6110	1891	PILOT TUBE      			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU12693		PILOT TUBE FOUND CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100602	19971231	00602	GL  	1997	12	31	EY2R9600668      	3	19960501	G	6111	T10282	BLADE           			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU12693		BLADE, SN E85574, FOUND CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100603	19971231	00603	GL  	1997	12	31	EY2R9600669      	3	19960501	G	6110	1851T	BEARING         			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3897 						BU16570		BEARING CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997123100604	19971231	00604	GL  	1997	12	31	EY2R9600670      	3	19960501	G	6110	13019S	CLAMP           			AIRTRC	AT300 	AT301       	0390103	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV2014		CLAMP CORRODED.						1	L	7	1 	3R				A9SW    		6	C	P15EA	 
1997123100605	19971231	00605	GL  	1997	12	31	EY2R9600671      	3	19960501	G	6110	1851T	BEARING         			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FW1151		BEARING CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100606	19971231	00606	GL  	1997	12	31	EY2R9600672      	3	19960501	G	6110	3475A3	LOW STOP COLLAR 			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FW1151		LOW STOP COLLAR FOUND CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100607	19971231	00607	GL  	1997	12	31	EY2R9600673      	3	19960501	G	6110	3475A3	LOW STOP COLLAR 			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FW1151		LOW STOP COLLAR FOUND CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100608	19971231	00608	GL  	1997	12	31	EY2R9600674      	3	19960501	G	6111	M10476	BLADE           			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FW1151		BLADE FOUND CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100609	19971231	00609	GL  	1997	12	31	EY2R9600675      	3	19960501	G	6110	83867	CLAMP           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CD402		CLAMP FOUND CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P40EA	 
1997123100610	19971231	00610	GL  	1997	12	31	EY2R9600676      	3	19960501	G	6114	220117	HUB             			MOONEY	M20   	M20E        	5870212	SW  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH22351		HUB FOUND CORRODED.						1	L	7	1 	3O				2A3     		5	C	P920	 
1997123100611	19971231	00611	GL  	1997	12	31	EY2R9600677      	3	19960501	G	6114	220116	HUB             			GRTLKS	2T1   	2T1A1       	3910107	NM  						HARTZL	HCC2Y	HCC2Y*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DN932		HUB FOUND CORRODED.						1	Q	7	1 	3O				A18EA   		5	C	P920	 
1997123100612	19971231	00612	GL  	1997	12	31	EY2R9600678      	3	19960501	G	6110	24182	PISTON ROD      			PIPER 	PA32  	PA32260     	7103206	SO  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH25452		PISTON ROD CORRODED.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1997123100613	19971231	00613	GL  	1997	12	31	EY2R9600679      	3	19960501	G	6110	2431	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG1381		BOLT CORRODED.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100614	19971231	00614	GL  	1997	12	31	EY2R9600680      	3	19960501	G	6110	2431	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG3943		BOLT CORRODED.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100615	19971231	00615	GL  	1997	12	31	EY2R9600681      	3	19960501	G	6110	2433	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG1381		BOLT CORRODED.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100616	19971231	00616	GL  	1997	12	31	EY2R9600682      	3	19960501	G	6110	2433	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG3943		BOLT CORRODED.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100617	19971231	00617	GL  	1997	12	31	EY2R9600683      	3	19960501	G	6110	24914S	PITCH CHANGE ROD			PIPER 	PA30  	PA39        	7103902	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG1716		PITCH CHANGE ROD FOUND CORRODED.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100618	19971231	00618	GL  	1997	12	31	EY2R9600684      	3	19960501	G	6110	F84774	BLADE           			PIPER 	PA32  	PA32RT300T  	7103216	SO  						HARTZL	HCE2Y	HCE2YR1BF   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DK1424		BLADE, SN D961511, FOUND CORRODED.						1	L	7	1 	3O				A3SO    		5	C	P9EA	 
1997123100619	19971231	00619	GL  	1997	12	31	EY2R9600685      	3	19960501	G	6110	F84774	BLADE           			PIPER 	PA32  	PA32RT300T  	7103216	SO  						HARTZL	HCE2Y	HCE2YR1BF   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DK1424		BLADE, SN D885229, FOUND CORRODED.						1	L	7	1 	3O				A3SO    		5	C	P9EA	 
1997123100620	19971231	00620	GL  	1997	12	31	EY2R9600686      	3	19960501	G	6110	2202	SPLIT BEARING   			PIPER 	PA31  	PA31325     	7103105	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DJ9058A		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997123100621	19971231	00621	GL  	1997	12	31	EY2R9600687      	3	19960501	G	6111	FC84686R	BLADE           			PIPER 	PA31  	PA31325     	7103105	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DJ9058A		BLADE, SN H19056, FOUND CORRODED.						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997123100622	19971231	00622	GL  	1997	12	31	EY2R9600688      	3	19960501	G	6110	3475A2	LOW STOP COLLAR 			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCCA3A	PHCA3VF5    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DH20		CORROSION FOUND ON LOW STOP COLLAR.						1	L	7	2 	3O				A23CE   		5	C	P6EA	 
1997123100623	19971231	00623	GL  	1997	12	31	EY2R9600689      	3	19960501	G	6110	3475A2	LOW STOP COLLAR 			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCCA3A	PHCA3VF5    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DH21		CORROSION FOUND ON LOW STOP COLLAR.						1	L	7	2 	3O				A23CE   		5	C	P6EA	 
1997123100624	19971231	00624	GL  	1997	12	31	EY2R9600690      	3	19960501	G	6110	971	SPLIT BEARING   			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCCA3A	PHCA3VF5    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DH20		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A23CE   		5	C	P6EA	 
1997123100625	19971231	00625	GL  	1997	12	31	EY2R9600691      	3	19960501	G	6110	971	SPLIT BEARING   			BEECH 	58    	58P         	1152744	CE  						HARTZL	HCCA3A	PHCA3VF5    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DH21		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A23CE   		5	C	P6EA	 
1997123100626	19971231	00626	GL  	1997	12	31	EY2R9600692      	3	19960601	G	6114	C3910C203	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755185		HUB CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100627	19971231	00627	GL  	1997	12	31	EY2R9600693      	3	19960601	G	6110	C5270	RETAIN BEARING  			CESSNA	172   	172K        	2072430	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								910336		RETAIN BEARING FOUND CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P3EA	 
1997123100628	19971231	00628	GL  	1997	12	31	EY2R9600694      	3	19960601	G	6110	C5270	RETAIN BEARING  			CESSNA	172   	172K        	2072430	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								910336		RETAIN BEARING FOUND CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P3EA	 
1997123100629	19971231	00629	GL  	1997	12	31	EY2R9600695      	3	19960601	G	6110	C5270	RETAIN BEARING  			CESSNA	172   	172K        	2072430	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								910336		RETAIN BEARING FOUND CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P3EA	 
1997123100630	19971231	00630	GL  	1997	12	31	EY2R9600696      	3	19960601	G	6110	A4001	DOWEL           			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C50     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3854 	493  					741216		DOWEL CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100631	19971231	00631	GL  	1997	12	31	EY2R9600697      	3	19960601	G	6111	S90A8	BLADE           			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C50     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3854 	493  					741216		BLADE FOUND WITH CORROSION.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100632	19971231	00632	GL  	1997	12	31	EY2R9600698      	3	19960601	G	6110	A16349	BALL BEARING    			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C406    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		530  						911534		BALL BEARING CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997123100633	19971231	00633	GL  	1997	12	31	EY2R9600699      	3	19960601	G	6110	C3903	SPLIT RETAINER  			CESSNA	320   	320         	2074502	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								811497		CORROSION FOUND ON SPLIT RETAINER.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100634	19971231	00634	GL  	1997	12	31	EY2R9600700      	3	19960601	G	6110	C3903	SPLIT RETAINER  			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								811285		CORROSION FOUND ON SPLIT RETAINER.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100635	19971231	00635	GL  	1997	12	31	EY2R9600701      	3	19960601	G	6110	C3903	SPLIT RETAINER  			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								932390		CORROSION FOUND ON SPLIT RETAINER.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100636	19971231	00636	GL  	1997	12	31	EY2R9600702      	3	19960601	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								920046		CYLINDER PIN CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100637	19971231	00637	GL  	1997	12	31	EY2R9600703      	3	19960601	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								920330		CYLINDER PIN CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100638	19971231	00638	GL  	1997	12	31	EY2R9600704      	3	19960601	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								920046		DOWEL CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100639	19971231	00639	GL  	1997	12	31	EY2R9600705      	3	19960601	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								920330		DOWELL CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100640	19971231	00640	GL  	1997	12	31	EY2R9600706      	3	19960601	G	6110	C3903	SPLIT RETAINER  			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821060		CORROSION FOUND ON SPLIT RETAINER.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100641	19971231	00641	GL  	1997	12	31	EY2R9600707      	3	19960601	G	6114	C4326C206	HUB             			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821060		HUB FOUND CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100642	19971231	00642	GL  	1997	12	31	EY2R9600708      	3	19960601	G	6110	C5270	RETAIN BEARING  			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821060		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100643	19971231	00643	GL  	1997	12	31	EY2R9600709      	3	19960601	G	6110	C7036	NUT             			CESSNA	320   	320         	2074502	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								711484		NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100644	19971231	00644	GL  	1997	12	31	EY2R9600710      	3	19960601	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								777497		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100645	19971231	00645	GL  	1997	12	31	EY2R9600711      	3	19960601	G	6110	C3475	NUT             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								777497		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100646	19971231	00646	GL  	1997	12	31	EY2R9600712      	3	19960601	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774447		RETAIN BEARING CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100647	19971231	00647	GL  	1997	12	31	EY2R9600713      	3	19960601	G	6110	C7036	NUT             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774447		NUT CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100648	19971231	00648	GL  	1997	12	31	EY2R9600714      	3	19960601	G	6110	C7036	NUT             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783146		NUT CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100649	19971231	00649	GL  	1997	12	31	EY2R9600715      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								682245		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100650	19971231	00650	GL  	1997	12	31	EY2R9600716      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								682424		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100651	19971231	00651	GL  	1997	12	31	EY2R9600717      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4368 	1382 					726136		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100652	19971231	00652	GL  	1997	12	31	EY2R9600718      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733152		HUB FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100653	19971231	00653	GL  	1997	12	31	EY2R9600719      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5851 	368  					756558		HUB FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100654	19971231	00654	GL  	1997	12	31	EY2R9600720      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783146		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100655	19971231	00655	GL  	1997	12	31	EY2R9600721      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								814168		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100656	19971231	00656	GL  	1997	12	31	EY2R9600722      	3	19960601	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815998		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100657	19971231	00657	GL  	1997	12	31	EY2R9600723      	3	19960601	G	6111	S82NC4	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								814168		BLADE, SN BD1029YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100658	19971231	00658	GL  	1997	12	31	EY2R9600724      	3	19960601	G	6111	S82NC4	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								814168		BLADE, SN BD1015YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100659	19971231	00659	GL  	1997	12	31	EY2R9600725      	3	19960601	G	6111	S82NC4	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								814168		BLADE, SN BF119YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100660	19971231	00660	GL  	1997	12	31	EY2R9600726      	3	19960601	G	6111	S82NC4	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815998		BLADE, SN BG409YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100661	19971231	00661	GL  	1997	12	31	EY2R9600727      	3	19960601	G	6111	S82NC4	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815998		BLADE, SN BG348YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100662	19971231	00662	GL  	1997	12	31	EY2R9600728      	3	19960601	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774447		BLADE, SN K76165YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100663	19971231	00663	GL  	1997	12	31	EY2R9600729      	3	19960601	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774447		BLADE, SN K76240YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100664	19971231	00664	GL  	1997	12	31	EY2R9600730      	3	19960601	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774447		BLADE, SN K76239YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100665	19971231	00665	GL  	1997	12	31	EY2R9600731      	3	19960601	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783146		BLADE, SN K76877YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100666	19971231	00666	GL  	1997	12	31	EY2R9600732      	3	19960601	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783146		BLADE, SN F75090YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100667	19971231	00667	GL  	1997	12	31	EY2R9600733      	3	19960601	G	6110	C2987	RETAIN BEARING  			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								799902		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100668	19971231	00668	GL  	1997	12	31	EY2R9600734      	3	19960601	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								734167		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100669	19971231	00669	GL  	1997	12	31	EY2R9600735      	3	19960601	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753351		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100670	19971231	00670	GL  	1997	12	31	EY2R9600736      	3	19960601	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								773769		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100671	19971231	00671	GL  	1997	12	31	EY2R9600737      	3	19960601	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783822		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100672	19971231	00672	GL  	1997	12	31	EY2R9600738      	3	19960601	G	6110	A4191	DOWEL           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								734167		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100673	19971231	00673	GL  	1997	12	31	EY2R9600739      	3	19960601	G	6110	A4191	DOWEL           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								773769		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100674	19971231	00674	GL  	1997	12	31	EY2R9600740      	3	19960601	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783822		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100675	19971231	00675	GL  	1997	12	31	EY2R9600741      	3	19960601	G	6110	C7036	NUT             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								734167		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100676	19971231	00676	GL  	1997	12	31	EY2R9600742      	3	19960601	G	6110	C2987	RETAIN BEARING  			CESSNA	402   	402A        	207590M	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								737350		RETAIN BEARING CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100677	19971231	00677	GL  	1997	12	31	EY2R9600743      	3	19960601	G	6111	82NC2	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3096 	309  					816304		BLADE, SN BJ550YS, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P22EA	 
1997123100678	19971231	00678	GL  	1997	12	31	EY2R9600744      	3	19960601	G	6110	C4451	FERRULE         			CESSNA	210   	210         	2073402	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3096 	309  					816304		FERRULE CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P22EA	 
1997123100679	19971231	00679	GL  	1997	12	31	EY2R9600745      	3	19960601	G	6110	C4904	NUT             			CESSNA	210   	210         	2073402	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3096 	309  					816304		NUT CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P22EA	 
1997123100680	19971231	00680	GL  	1997	12	31	EY2R9600746      	3	19960601	G	6110	C5262	CYLINDER        			CESSNA	210   	210         	2073402	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3096 	309  					816304		CYLINDER FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P22EA	 
1997123100681	19971231	00681	GL  	1997	12	31	EY2R9600747      	3	19960601	G	6110	C7036	NUT             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755780		NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100682	19971231	00682	GL  	1997	12	31	EY2R9600748      	3	19960601	G	6114	D7015C93	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1005 					783104		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100683	19971231	00683	GL  	1997	12	31	EY2R9600749      	3	19960601	G	6111	90LF0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1642 						743229		BLADE, SN IA029, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100684	19971231	00684	GL  	1997	12	31	EY2R9600750      	3	19960601	G	6111	B4459	BLADE ACT PIN   			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1642 						743229		BLADE ACT PIN FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100685	19971231	00685	GL  	1997	12	31	EY2R9600751      	3	19960601	G	6110	C4550	FERRULE         			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		944  						739301		FERRULE FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100686	19971231	00686	GL  	1997	12	31	EY2R9600752      	3	19960601	G	6110	C7036	NUT             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1642 						805941		NUT CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100687	19971231	00687	GL  	1997	12	31	EY2R9600753      	3	19960601	G	6114	D7019C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		944  						739301		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100688	19971231	00688	GL  	1997	12	31	EY2R9600754      	3	19960601	G	6111	S90LF0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								711725		BLADE, SN HL080YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100689	19971231	00689	GL  	1997	12	31	EY2R9600755      	3	19960601	G	6111	S90LF0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								711725		BLADE, SN HL062YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100690	19971231	00690	GL  	1997	12	31	EY2R9600756      	3	19960601	G	6111	S90LF0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								711725		BLADE, SN OA037YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100691	19971231	00691	GL  	1997	12	31	EY2R9600757      	3	19960601	G	6111	S90LF0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		944  						739301		BLADE FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100692	19971231	00692	GL  	1997	12	31	EY2R9600758      	3	19960601	G	6111	90UMB0	BLADE           			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830433		BLADE, SN CB356, FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997123100693	19971231	00693	GL  	1997	12	31	EY2R9600759      	3	19960601	G	6111	90UMB0	BLADE           			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830433		BLADE, SN CB258, FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997123100694	19971231	00694	GL  	1997	12	31	EY2R9600760      	3	19960601	G	6111	90UMB0	BLADE           			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830433		BLADE, SN CB257, FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997123100695	19971231	00695	GL  	1997	12	31	EY2R9600761      	3	19960601	G	6111	90UMB0	BLADE           			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830437		BLADE, SN CB179, FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997123100696	19971231	00696	GL  	1997	12	31	EY2R9600762      	3	19960601	G	6111	90UMB0	BLADE           			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830437		BLADE, SN CB433, FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997123100697	19971231	00697	GL  	1997	12	31	EY2R9600763      	3	19960601	G	6111	90UMB0	BLADE           			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830437		BLADE, SN CB178, FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997123100698	19971231	00698	GL  	1997	12	31	EY2R9600764      	3	19960601	G	6114	D5878C501	HUB             			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830433		HUB FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997123100699	19971231	00699	GL  	1997	12	31	EY2R9600765      	3	19960601	G	6114	D5878C501	HUB             			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								830437		HUB FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997123100700	19971231	00700	GL  	1997	12	31	EY2R9600766      	3	19960601	G	6110	A3267	ADAPTER         			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1005 					804734		CORROSION FOUND ON ADAPTER.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100701	19971231	00701	GL  	1997	12	31	EY2R9600767      	3	19960601	G	6110	A3267	ADAPTER         			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			250  					804734		CORROSION FOUND ON ADAPTER.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100702	19971231	00702	GL  	1997	12	31	EY2R9600768      	3	19960601	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755998		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100703	19971231	00703	GL  	1997	12	31	EY2R9600769      	3	19960601	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760509		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100704	19971231	00704	GL  	1997	12	31	EY2R9600770      	3	19960601	G	6110	A4191	DOWEL           			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755998		DOWEL CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1997123100705	19971231	00705	GL  	1997	12	31	EY2R9600771      	3	19960601	G	6110	A4191	DOWEL           			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760509		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998010700011	19980107	00011	NE  	1998	1	7	EY2R9600772      	3	19960601	G	6114	D5886C601	HUB             			CESSNA	441   	441         	2076020	CE  						MCAULY	4HFR34	4HFR34C660  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								841350		HUB FOUND CORRODED.						1	L	7	2 	3T			RT	A28CE   		5	C	3PNE	 
1998010700012	19980107	00012	NE  	1998	1	7	EY2R9600773      	3	19960601	G	6114	D5886C601	HUB             			CESSNA	441   	441         	2076020	CE  						MCAULY	4HFR34	4HFR34C660  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								841830		HUB FOUND CORRODED.						1	L	7	2 	3T			RT	A28CE   		5	C	3PNE	 
1997123100706	19971231	00706	NE  	1997	12	31	EY2R9600774      	3	19960601	G	6110	B5162	REVERSE STOP    			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2834 						890505		CORROSION FOUND ON REVERSE STOP SCREW.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1997123100707	19971231	00707	NE  	1997	12	31	EY2R9600775      	3	19960601	G	6110	D6174	CYLINDER        			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2834 						890505		CYLINDER FOUND CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1997123100708	19971231	00708	NE  	1997	12	31	EY2R9600776      	3	19960601	G	6110	A163919	NUT             			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2834 						890503		NUT FOUND CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1997123100709	19971231	00709	NE  	1997	12	31	EY2R9600777      	3	19960601	G	6110	A1896	CYLINDER PIN    			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		14000	4758 					880393		CORROSION FOUND ON CYLINDER.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1997123100710	19971231	00710	NE  	1997	12	31	EY2R9600778      	3	19960601	G	6110	B5162	REVERSE STOP    			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2834 						890503		CORROSION FOUND ON REVERSE STOP SCREW.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1997123100711	19971231	00711	NE  	1997	12	31	EY2R9600779      	3	19960601	G	6110	D6174	CYLINDER        			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2834 						890503		CYLINDER CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1997123100712	19971231	00712	GL  	1997	12	31	EY2R9600780      	3	19960601	G	6111	90DHA4	BLADE           			CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	B2A34C205   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2804 	1202 					831317		BLADE, SN GK56, FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100713	19971231	00713	GL  	1997	12	31	EY2R9600781      	3	19960601	G	6111	90DHA4	BLADE           			CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	B2A34C205   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2804 	1202 					831317		BLADE, SN GK05, FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100714	19971231	00714	GL  	1997	12	31	EY2R9600782      	3	19960601	G	6114	C6608C205	HUB             			CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	B2A34C205   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2804 	1202 					831317		CORROSION FOUND ON HUB.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100715	19971231	00715	GL  	1997	12	31	EY2R9600783      	3	19960601	G	6114	D4326C207	HUB             			CESSNA	177   	177         	2073704	CE  						MCAULY	2D34C	B2D34C207   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								774490		CORROSION FOUND ON HUB.						1	H	7	1 	3O			NT	A13CE   		5	C	P7EA	 
1997123100716	19971231	00716	GL  	1997	12	31	EY2R9600784      	3	19960601	G	6111	90DHB8	BLADE           			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C218   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								802969		BLADE, SN BF964, FOUND CORRODED.						1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
1997123100717	19971231	00717	GL  	1997	12	31	EY2R9600785      	3	19960601	G	6111	90DHB8	BLADE           			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C218   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								802969		BLADE, SN CA326, FOUND CORRODED.						1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
1997123100718	19971231	00718	GL  	1997	12	31	EY2R9600786      	3	19960601	G	6114	D5045C218	HUB             			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C218   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								802969		HUB FOUND CORRODED.						1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
1997123100719	19971231	00719	GL  	1997	12	31	EY2R9600787      	3	19960601	G	6114	22015	HUB             			PIPER 	PA46  	PA46310P    	7104605	SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1379 						AM2728		HUB FOUND CORRODED.						1	L	7	1 	3O				A25SO   		5	C	P920	 
1997123100720	19971231	00720	GL  	1997	12	31	EY2R9600788      	3	19960601	G	6111	90AT4	BLADE           			CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2666 	1333 					890754		BLADE, SN IJ120YS, FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100721	19971231	00721	GL  	1997	12	31	EY2R9600789      	3	19960601	G	6111	90AT4	BLADE           			CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2666 	1333 					890754		BLADE, SN IJ089YS, FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100722	19971231	00722	GL  	1997	12	31	EY2R9600790      	3	19960601	G	6111	78CAA0	BLADE           			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C306  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821929		BLADE FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100723	19971231	00723	GL  	1997	12	31	EY2R9600791      	3	19960601	G	6114	D4476C306	HUB             			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C306  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821929		HUB FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100724	19971231	00724	GL  	1997	12	31	EY2R9600792      	3	19960601	G	6114	D4190C307	HUB             			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								734246		HUB FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100725	19971231	00725	GL  	1997	12	31	EY2R9600793      	3	19960601	G	6111	L78CBA2	BLADE           			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								734246		BLADE, SN K77066, FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100726	19971231	00726	GL  	1997	12	31	EY2R9600794      	3	19960601	G	6111	L78CBA2	BLADE           			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								734246		BLADE, SN K76674, FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100727	19971231	00727	GL  	1997	12	31	EY2R9600795      	3	19960601	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310P        	2074238	CE  						MCAULY	2AF34C	D2AF34C71   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								788660		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P5EA	 
1997123100728	19971231	00728	GL  	1997	12	31	EY2R9600796      	3	19960601	G	6110	C3475	NUT             			CESSNA	310   	310P        	2074238	CE  						MCAULY	2AF34C	D2AF34C71   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								788660		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P5EA	 
1997123100729	19971231	00729	GL  	1997	12	31	EY2R9600797      	3	19960601	G	6110	C5270	RETAIN BEARING  			CESSNA	180   	180A        	2072604	CE  						MCAULY	3A32C	D3A32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								831717		RETAIN BEARING CORRODED.						1	H	7	1 	3O				5A6     		5	C	P21EA	 
1997123100730	19971231	00730	GL  	1997	12	31	EY2R9600798      	3	19960601	G	6114	D6603C88	HUB             			CESSNA	210   	210         	2073402	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								715483		HUB FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P21EA	 
1997123100731	19971231	00731	GL  	1997	12	31	EY2R9600799      	3	19960601	G	6111	S82NC2	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								715483		BLADE, SN K65734YS, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P21EA	 
1997123100732	19971231	00732	GL  	1997	12	31	EY2R9600800      	3	19960601	G	6111	S82NC2	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								715483		BLADE, SN K65733YS, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P21EA	 
1997123100733	19971231	00733	GL  	1997	12	31	EY2R9600801      	3	19960601	G	6111	S82NC2	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								715483		BLADE, SN K65732YS, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P21EA	 
1997123100734	19971231	00734	GL  	1997	12	31	EY2R9600802      	3	19960601	G	6110	A4001	DOWEL           			CESSNA	210   	P210N       	2073454	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								796954		DOWEL CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1997123100735	19971231	00735	GL  	1997	12	31	EY2R9600803      	3	19960601	G	6110	A4001	DOWEL           			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								796956		DOWEL CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100736	19971231	00736	GL  	1997	12	31	EY2R9600804      	3	19960601	G	6110	C3411	BEARING RACE    			CESSNA	210   	210N        	2073453	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								801266		BEARING RACE FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1997123100737	19971231	00737	GL  	1997	12	31	EY2R9600805      	3	19960601	G	6110	C3903	SPLIT RETAINER  			CESSNA	210   	210N        	2073453	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								801266		CORROSION FOUND ON SPLIT RETAINER.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1997123100738	19971231	00738	GL  	1997	12	31	EY2R9600806      	3	19960601	G	6110	C3475	NUT             			CESSNA	310   	310N        	2074234	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								666649		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100739	19971231	00739	GL  	1997	12	31	EY2R9600807      	3	19960601	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310N        	2074234	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								666649		FEATHER CYLINDER CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100740	19971231	00740	GL  	1997	12	31	EY2R9600808      	3	19960601	G	6110	971	SPLIT BEARING   			BEECH 	58    	58          	1152740	CE  						HARTZL	HCA3V	EHCA3VF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BR571		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P6EA	 
1997123100741	19971231	00741	GL  	1997	12	31	EY2R9600809      	3	19960601	G	6110	14B	BEARING         			GULSTM	680   	680         	0141602	SW  						HARTZL	HC83V	HC83V202    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1672 	59   					D1182N		BEARING CORRODED.						1	H	7	2 	3O				2A4     		5	C	P14EA	 
1997123100742	19971231	00742	GL  	1997	12	31	EY2R9600810      	3	19960601	G	6110	14B	BEARING         			GULSTM	680   	680         	0141602	SW  						HARTZL	HC83V	HC83V202    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1672 	59   					D1183N		BEARING CORRODED.						1	H	7	2 	3O				2A4     		5	C	P14EA	 
1997123100743	19971231	00743	GL  	1997	12	31	EY2R9600811      	3	19960601	G	6110	1301	CLAMP           			BEECH 	95    	B95A        	1153406	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1207F		CLAMP CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100744	19971231	00744	GL  	1997	12	31	EY2R9600812      	3	19960601	G	6110	1301	CLAMP           			BEECH 	95    	B95A        	1153406	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1208F		CLAMP CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1997123100745	19971231	00745	GL  	1997	12	31	EY2R9600813      	3	19960601	G	6110	971	SPLIT BEARING   			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								H1049		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				1A10    		5	C	P24EA	 
1997123100746	19971231	00746	GL  	1997	12	31	EY2R9600814      	3	19960601	G	6111	84334	BLADE           			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCA2X	HCA2XK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								H106		BLADE, SN A18604, FOUND CORRODED.						1	H	7	2 	3O				6A1     		5	C	P908	 
1997123100747	19971231	00747	GL  	1997	12	31	EY2R9600815      	3	19960601	G	6110	971	SPLIT BEARING   			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCA2X	HCA2XK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								H106		CORROSION FOUND ON SPLIT BEARING.						1	H	7	2 	3O				6A1     		5	C	P908	 
1997123100748	19971231	00748	GL  	1997	12	31	EY2R9600816      	3	19960601	G	6110	1851T	BEARING         			GULSTM	G73   	G73         	3951802	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3744 	2984 					BU14300		BEARING CORRODED.						1	H	7	2 	3R				A783    		6	C	P15EA	 
1997123100749	19971231	00749	GL  	1997	12	31	EY2R9600817      	3	19960601	G	6110	83865	CLAMP           			GULSTM	G73   	G73         	3951802	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3744 	2984 					BU14300		CLAMP CORRODED.						1	H	7	2 	3R				A783    		6	C	P15EA	 
1997123100750	19971231	00750	GL  	1997	12	31	EY2R9600818      	3	19960601	G	6110	84060	HUB             			GULSTM	G73   	G73         	3951802	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3744 	2984 					BU14300		PILOT TUBES REMOVED & REPLACED.						1	H	7	2 	3R				A783    		6	C	P15EA	 
1997123100751	19971231	00751	GL  	1997	12	31	EY2R9600819      	3	19960601	G	6110	1851T	BEARING         			MTSBSI	MU2   	MU2B30      	5780410	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3551 	1300 					BV4246		BEARING CORRODED.						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1997123100752	19971231	00752	GL  	1997	12	31	EY2R9600820      	3	19960601	G	6110	3406	CYLINDER        			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		14107	3709 					FW633		CORROSION FOUND ON CYLINDER.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100753	19971231	00753	GL  	1997	12	31	EY2R9600821      	3	19960601	G	6110	1851T	BEARING         			BEECH 	300   	300BEECH    	1152930	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FW297		BEARING CORRODED.						2	L	7	2 	4T				A24CE   		6	C	P56GL	 
1997123100754	19971231	00754	GL  	1997	12	31	EY2R9600822      	3	19960601	G	6110	1851T	BEARING         			STBROS	SD3   	SD360       	8100606	EU  						HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		14395	4470 					EV624		CORROSION FOUND ON BEARING.						2	H	7	2 	4T				A41EU   		6	C	P44GL	 
1997123100755	19971231	00755	GL  	1997	12	31	EY2R9600823      	3	19960601	G	6111	FC7666A2	BLADE           			BBAVIA	8     	8KCAB       	2110612	CE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			348  					DN1558		BLADE, SN E84429, FOUND CORRODED.						1	H	7	1 	3O				A21CE   		5	C	P920	 
1997123100756	19971231	00756	GL  	1997	12	31	EY2R9600824      	3	19960601	G	6111	FC7666A2	BLADE           			BBAVIA	8     	8KCAB       	2110612	CE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			348  					DN1558		BLADE, SN E83260, FOUND CORRODED.						1	H	7	1 	3O				A21CE   		5	C	P920	 
1997123100757	19971231	00757	GL  	1997	12	31	EY2R9600825      	3	19960601	G	6110	2202	SPLIT BEARING   			BNORM 	BN2   	BN2A        	1520204	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU2053		CORROSION FOUND ON SPLIT BEARING.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1997123100758	19971231	00758	GL  	1997	12	31	EY2R9600826      	3	19960601	G	6110	2202	SPLIT BEARING   			BNORM 	BN2   	BN2A3       	1520215	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU7443		CORROSION FOUND ON SPLIT BEARING.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1997123100759	19971231	00759	GL  	1997	12	31	EY2R9600827      	3	19960601	G	6110	2202	SPLIT BEARING   			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1063 						FY518		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3T				3A20    		5	C	STC	 
1997123100760	19971231	00760	GL  	1997	12	31	EY2R9600828      	3	19960601	G	6114	4993	HUB             			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1063 						FY518		HUB FOUND CORRODED.						1	L	7	2 	3T				3A20    		5	C	STC	 
1997123100761	19971231	00761	GL  	1997	12	31	EY2R9600829      	3	19960601	G	6110	60711	PITCH CHG ROD   			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1063 						FY1240		PITCH CHANGE ROD FOUND CORRODED.						1	L	7	2 	3T				3A20    		5	C	STC	 
1997123100762	19971231	00762	GL  	1997	12	31	EY2R9600830      	3	19960601	G	6114	24831	HUB             			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG712		HUB FOUND CORRODED.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100763	19971231	00763	GL  	1997	12	31	EY2R9600831      	3	19960601	G	6114	24831	HUB             			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG714		HUB FOUND CORRODED.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100764	19971231	00764	GL  	1997	12	31	EY2R9600832      	3	19960601	G	6110	2202	SPLIT BEARING   			PIPER 	PA30  	PA39        	7103902	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG317		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100765	19971231	00765	GL  	1997	12	31	EY2R9600833      	3	19960601	G	6110	2202	SPLIT BEARING   			PIPER 	PA30  	PA39        	7103902	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1739		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100766	19971231	00766	GL  	1997	12	31	EY2R9600834      	3	19960601	G	6110	2202	SPLIT BEARING   			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								634		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100767	19971231	00767	GL  	1997	12	31	EY2R9600835      	3	19960601	G	6110	2202	SPLIT BEARING   			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP3903		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100768	19971231	00768	GL  	1997	12	31	EY2R9600836      	3	19960601	G	6110	2202	SPLIT BEARING   			PIPER 	PA31  	PA31325     	7103105	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DJ5094		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997123100769	19971231	00769	GL  	1997	12	31	EY2R9600837      	3	19960601	G	6110	23813	FEATHERING SPRNG			BEECH 	60    	60          	1153602	CE  						HARTZL	HCF3Y	HCF3YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1479 						DA1508		CORROSION FOUND ON FEATHERING SPRING.						1	L	7	2 	3O				A12CE   		5	C	P31EA	 
1997123100770	19971231	00770	GL  	1997	12	31	EY2R9600838      	3	19960601	G	6110	971	SPLIT BEARING   			BEECH 	58    	58          	1152740	CE  						HARTZL	HCA3V	PHCA3VF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BR440		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P6EA	 
1997123100771	19971231	00771	GL  	1997	12	31	EY2R9600839      	3	19960601	G	6114	84082	HUB             			BEECH 	35    	V35         	1151538	CE  						HARTZL	HCA3V	PHCA3VF4    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			465  					BL164		HUB FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P6EA	 
1997123100772	19971231	00772	GL  	1997	12	31	EY2R9600840      	3	19960601	G	6110	2202	SPLIT BEARING   			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2472 						ED1215		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P36EA	 
1997123100773	19971231	00773	GL  	1997	12	31	EY2R9600841      	3	19960601	G	6110	3237	PISTON UNIT     			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2472 						ED2543		PISTON UNIT CORRODED.						1	L	7	2 	3O				3A16    		5	C	P36EA	 
1997123100774	19971231	00774	GL  	1997	12	31	EY2R9600842      	3	19960601	G	6114	32857	HUB             			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2472 						ED1215		HUB FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P36EA	 
1997123100775	19971231	00775	GL  	1997	12	31	EY2R9600843      	3	19960601	G	6111	FC76632R	BLADE           			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2472 						ED1215		BLADE, SN H36796, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P36EA	 
1997123100776	19971231	00776	GL  	1997	12	31	EY2R9600844      	3	19960601	G	6111	FC76632R	BLADE           			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2472 						ED1215		BLADE, SN H36799, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P36EA	 
1997123100777	19971231	00777	GL  	1997	12	31	EY2R9600845      	3	19960601	G	6111	FC76632R	BLADE           			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2472 						ED2543		BLADE, SN F98274, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P36EA	 
1997123100778	19971231	00778	GL  	1997	12	31	EY2R9600846      	3	19960601	G	6111	FC76632R	BLADE           			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2472 						ED2543		BLADE, SN F98278, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P36EA	 
1997123100779	19971231	00779	GL  	1997	12	31	EY2R9600847      	3	19960701	G	6110	C3411	BEARING RACE    			CESSNA	177   	177B        	2073708	CE  						MCAULY	2D34C	2D34C*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779804		BEARING RACE CORRODED.						1	H	7	1 	3O				A13CE   		5	C	P7EA	 
1997123100780	19971231	00780	GL  	1997	12	31	EY2R9600848      	3	19960701	G	6110	A1896	CYLINDER PIN    			BEECH 	55    	D55         	1152730	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								796163		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100781	19971231	00781	GL  	1997	12	31	EY2R9600849      	3	19960701	G	6110	A4001	DOWEL           			BEECH 	55    	D55         	1152730	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								796163		DOWEL FOUND WITH CORROSION.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100782	19971231	00782	GL  	1997	12	31	EY2R9600850      	3	19960701	G	6111	S82NB6	BLADE           			BEECH 	55    	D55         	1152730	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								796163		BLADE, SN F14967YS, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100783	19971231	00783	GL  	1997	12	31	EY2R9600851      	3	19960701	G	6110	A1896	CYLINDER PIN    			BEECH 	55    	D55         	1152730	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697561		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100784	19971231	00784	GL  	1997	12	31	EY2R9600852      	3	19960701	G	6110	A4001	DOWEL           			BEECH 	55    	D55         	1152730	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697561		DOWEL CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100785	19971231	00785	GL  	1997	12	31	EY2R9600853      	3	19960701	G	6111	S82NB6	BLADE           			BEECH 	55    	D55         	1152730	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697561		BLADE, SN F11710YS, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100786	19971231	00786	GL  	1997	12	31	EY2R9600854      	3	19960701	G	6111	S82NB6	BLADE           			BEECH 	55    	D55         	1152730	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697561		BLADE, SN F12557YS, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100787	19971231	00787	GL  	1997	12	31	EY2R9600855      	3	19960701	G	6110	C4451	FERRULE         			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697985		FERRULE CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100788	19971231	00788	GL  	1997	12	31	EY2R9600856      	3	19960701	G	6110	C4451	FERRULE         			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779568		FERRULE CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100789	19971231	00789	GL  	1997	12	31	EY2R9600857      	3	19960701	G	6110	C3550	FERRULE         			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747485		FEATHER CYLINDER CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100790	19971231	00790	GL  	1997	12	31	EY2R9600858      	3	19960701	G	6110	S82NC7	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747485		BLADE, SN F23333YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100791	19971231	00791	GL  	1997	12	31	EY2R9600859      	3	19960701	G	6111	S82NC7	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								747485		BLADE, SN F19644YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100792	19971231	00792	GL  	1997	12	31	EY2R9600860      	3	19960701	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789450		FEATHER CYLINDER CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100793	19971231	00793	GL  	1997	12	31	EY2R9600861      	3	19960701	G	6110	C7036	NUT             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789450		NUT CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100794	19971231	00794	GL  	1997	12	31	EY2R9600862      	3	19960701	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		CYLINDER PIN CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100795	19971231	00795	GL  	1997	12	31	EY2R9600863      	3	19960701	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		DOWEL CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100796	19971231	00796	GL  	1997	12	31	EY2R9600864      	3	19960701	G	6110	B3490	PISTON ROD PIN  			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		PISTONR ROD FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100797	19971231	00797	GL  	1997	12	31	EY2R9600865      	3	19960701	G	6111	B4459	BLADE ACT PIN   			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		BLADE ACT PIN CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100798	19971231	00798	GL  	1997	12	31	EY2R9600866      	3	19960701	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1190 					733315		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100799	19971231	00799	GL  	1997	12	31	EY2R9600867      	3	19960701	G	6110	C2987	RETAIN BEARING  			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100800	19971231	00800	GL  	1997	12	31	EY2R9600868      	3	19960701	G	6110	C4451	FERRULE         			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		FERRULE CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100801	19971231	00801	GL  	1997	12	31	EY2R9600869      	3	19960701	G	6110	C7036	NUT             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		NUT FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100802	19971231	00802	GL  	1997	12	31	EY2R9600870      	3	19960701	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		CORROSION FOUND ON HUB.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100803	19971231	00803	GL  	1997	12	31	EY2R9600871      	3	19960701	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2573 						793864		BLADE, SN F28561YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100804	19971231	00804	GL  	1997	12	31	EY2R9600872      	3	19960701	G	6110	A1896	CYLINDER PIN    			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1496 						722254		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100805	19971231	00805	GL  	1997	12	31	EY2R9600873      	3	19960701	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1496 						722254		DOWEL PIN CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100806	19971231	00806	GL  	1997	12	31	EY2R9600874      	3	19960701	G	6110	C3475	NUT             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1190 					783577		NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100807	19971231	00807	GL  	1997	12	31	EY2R9600875      	3	19960701	G	6110	C4451	FERRULE         			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1496 						722254		FERRULE CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100808	19971231	00808	GL  	1997	12	31	EY2R9600876      	3	19960701	G	6111	S82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1190 					783577		BLADE, SN K85709YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100809	19971231	00809	GL  	1997	12	31	EY2R9600877      	3	19960701	G	6110	A1896	CYLINDER PIN    			PIPER 	PA34  	PA34200T    	7103406	SO  						MCAULY	3AF34C	3AF34C502   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1580 					788537		CYLINDER PIN CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1997123100810	19971231	00810	GL  	1997	12	31	EY2R9600878      	3	19960701	G	6110	A4191	DOWEL           			PIPER 	PA34  	PA34200T    	7103406	SO  						MCAULY	3AF34C	3AF34C502   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1580 					788537		DOWEL CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1997123100811	19971231	00811	GL  	1997	12	31	EY2R9600879      	3	19960701	G	6114	C4801C204	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	C2A34C204   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								776119		HUB FOUND CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100812	19971231	00812	GL  	1997	12	31	EY2R9600880      	3	19960701	G	6114	C4810C204	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	C2A34C204   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								781441		HUB FOUND CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100813	19971231	00813	GL  	1997	12	31	EY2R9600881      	3	19960701	G	6114	D4326C211	HUB             			CESSNA	177   	177         	2073704	CE  						MCAULY	2D34C	B2D34C211   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								757500		HUB FOUND CORRODED.						1	H	7	1 	3O			NT	A13CE   		5	C	P7EA	 
1997123100814	19971231	00814	GL  	1997	12	31	EY2R9600882      	3	19960701	G	6110	B48202	ACT PIN ASSY    			BEECH 	33    	F33A        	1151425	CE  						MCAULY	3A32C	D3A32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1539 	467  					850989		ACT PIN ASSY FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1997123100815	19971231	00815	GL  	1997	12	31	EY2R9600883      	3	19960701	G	6110	C5264	CYLINDER        			CESSNA	206   	TU206G      	2073357	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902242		CORROSION FOUND ON CYLINDER.						1	H	7	1 	3O				A4CE    		5	C	P47GL	 
1997123100816	19971231	00816	GL  	1997	12	31	EY2R9600884      	3	19960701	G	6114	D5858C402	HUB             			CESSNA	206   	TU206G      	2073357	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902242		HUB FOUND CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P47GL	 
1997123100817	19971231	00817	GL  	1997	12	31	EY2R9600885      	3	19960701	G	6110	B48202	ACT PIN ASSY    			CESSNA	210   	T210N       	2073456	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815224		ACT PIN ASSY CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1997123100818	19971231	00818	GL  	1997	12	31	EY2R9600886      	3	19960701	G	6110	C3903	SPLIT RETAINER  			CESSNA	210   	T210N       	2073456	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815224		CORROSION FOUND ON SPLIT RETAINER						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1997123100819	19971231	00819	GL  	1997	12	31	EY2R9600887      	3	19960701	G	6110	C5270	RETAIN BEARING  			CESSNA	210   	T210N       	2073456	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815224		RETAIN BEARING FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1997123100820	19971231	00820	GL  	1997	12	31	EY2R9600888      	3	19960701	G	6110	38B	BEARING         			FRCHLD	24    	24R46       	3370514	EA  						HARTZL	HC12V	HC12V20*    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								P477		BEARING CORRODED.						1	H	7	1 	3I				A706    		5	C	P46GL	 
1997123100821	19971231	00821	GL  	1997	12	31	EY2R9600889      	3	19960701	G	6110	83888	CLAMP           			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CLAMP CORRODED.						1	L	7	2 	4T				A24CE   		6	C	P15EA	 
1997123100822	19971231	00822	GL  	1997	12	31	EY2R9600890      	3	19960701	G	6110	1851T	BEARING         			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU12944		BEARING CORRODED.						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1997123100823	19971231	00823	GL  	1997	12	31	EY2R9600891      	3	19960701	G	6110	1851T	BEARING         			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU9021		BEARING CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997123100824	19971231	00824	GL  	1997	12	31	EY2R9600892      	3	19960701	G	6110	3475A2	LOW STOP COLLAR 			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU9021		CORROSION FOUND ON COLLAR.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1997123100825	19971231	00825	GL  	1997	12	31	EY2R9600893      	3	19960701	G	6110	1851T	BEARING         			DHAV  	DHC6  	DHC6100     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			328  					BU1222		BEARING CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997123100826	19971231	00826	GL  	1997	12	31	EY2R9600894      	3	19960701	G	6110	1851T	BEARING         			DHAV  	DHC6  	DHC6100     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			328  					BU2305		BEARING CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997123100827	19971231	00827	GL  	1997	12	31	EY2R9600895      	3	19960701	G	6110	18912A	PILOT TUBE      			DHAV  	DHC6  	DHC6100     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			328  					BU1222		PILOT TUBE FOUND CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997123100828	19971231	00828	GL  	1997	12	31	EY2R9600896      	3	19960701	G	6110	1851T	BEARING         			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		20791	3036 					BU7082		BEARING CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1997123100829	19971231	00829	GL  	1997	12	31	EY2R9600897      	3	19960701	G	6111	T102826	BLADE           			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN H13058, FOUND CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100830	19971231	00830	GL  	1997	12	31	EY2R9600898      	3	19960701	G	6111	T102826	BLADE           			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN H13052, FOUND CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100831	19971231	00831	GL  	1997	12	31	EY2R9600899      	3	19960701	G	6111	T102826	BLADE           			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN H13053, FOUND CORRODED.						1	L	7	1 	3R			NC	A4SW    		6	C	P15EA	 
1997123100832	19971231	00832	GL  	1997	12	31	EY2R9600900      	3	19960701	G	6110	1851T	BEARING         			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		18952	3058 					FW253		BEARING CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100833	19971231	00833	GL  	1997	12	31	EY2R9600901      	3	19960701	G	6110	1851T	BEARING         			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		18952	3058 					FW264		BEARING CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100834	19971231	00834	GL  	1997	12	31	EY2R9600902      	3	19960701	G	6110	338614H	BOLT            			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		18952	3058 					FW253		BOLT CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100835	19971231	00835	GL  	1997	12	31	EY2R9600903      	3	19960701	G	6110	338614H	BOLT            			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		18952	3058 					FW264		BOLT CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1997123100836	19971231	00836	GL  	1997	12	31	EY2R9600904      	3	19960701	G	6114	220116	HUB             			BNORM 	BN2   	BN2A3       	1520215	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4002 	2002 					AU139		HUB FOUND CORRODED.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1997123100837	19971231	00837	GL  	1997	12	31	EY2R9600905      	3	19960701	G	6110	2202	SPLIT BEARING   			BNORM 	BN2   	BN2A3       	1520215	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4002 	2002 					AU139		CORROSION FOUND ON SPLIT BEARING.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1997123100838	19971231	00838	GL  	1997	12	31	EY2R9600906      	3	19960701	G	6110	2202	SPLIT BEARING   			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU1124		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997123100839	19971231	00839	GL  	1997	12	31	EY2R9600907      	3	19960701	G	6114	32512	HUB             			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CK325		HUB FOUND CORRODED.						1	H	7	2 	3O				6A1     		5	C	P25EA	 
1997123100840	19971231	00840	GL  	1997	12	31	EY2R9600908      	3	19960701	G	6114	32512	HUB             			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CK325		HUB FOUND CORRODED.						1	H	7	2 	3O				6A1     		5	C	P25EA	 
1997123100841	19971231	00841	GL  	1997	12	31	EY2R9600909      	3	19960701	G	6114	32512	HUB             			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CK386		HUB FOUND CORRODED.						1	H	7	2 	3O				6A1     		5	C	P25EA	 
1997123100842	19971231	00842	GL  	1997	12	31	EY2R9600910      	3	19960701	G	6110	2202	SPLIT BEARING   			PIPER 	PA30  	PA39        	7103902	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1889 	330  					BG1742		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100843	19971231	00843	GL  	1997	12	31	EY2R9600911      	3	19960701	G	6110	2202	SPLIT BEARING   			PIPER 	PA30  	PA39        	7103902	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1889 	330  					BG1748		CORROSIONF OUND ON SPLIT BEARING.						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1997123100844	19971231	00844	GL  	1997	12	31	EY2R9600912      	3	19960801	G	6110	C4450	FERRULE         			BEECH 	55    	95A55       	1152704	CE  						MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								695613		FERRULE CORRODED.						1	L	7	2 	3O				3A16    		5	C	P5EA	 
1997123100845	19971231	00845	GL  	1997	12	31	EY2R9600913      	3	19960801	G	6114	D7015C93	HUB             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1376 					799581		HUB FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100846	19971231	00846	GL  	1997	12	31	EY2R9600914      	3	19960801	G	6110		PROP            			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								683684		PROP ASSY CORRODED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100847	19971231	00847	GL  	1997	12	31	EY2R9600915      	3	19960801	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								703948		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100848	19971231	00848	GL  	1997	12	31	EY2R9600916      	3	19960801	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783928		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100849	19971231	00849	GL  	1997	12	31	EY2R9600917      	3	19960801	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2790 						910789		CORROSION FOUND ON SCREW.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997123100850	19971231	00850	GL  	1997	12	31	EY2R9600918      	3	19960801	G	6110	A4427	RING            			MOONEY	M20   	M20         	5870202	SW  						MCAULY	2D34C	B2D34C214   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2017 	539  					779855		CORROSION FOUND ON RING.						1	L	7	1 	3O				2A3     		5	C	P7EA	 
1997123100851	19971231	00851	GL  	1997	12	31	EY2R9600919      	3	19960801	G	6110	A4001	DOWEL           			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	C2A34C204   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								807774		DOWEL CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997123100852	19971231	00852	GL  	1997	12	31	EY2R9600920      	3	19960801	G	6110	A1896	CYLINDER PIN    			CESSNA	337   	337H        	2075732	CE  						MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4785 	913  					779147		CYLINDER PIN CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100853	19971231	00853	GL  	1997	12	31	EY2R9600921      	3	19960801	G	6110	A4001	DOWEL           			CESSNA	337   	337H        	2075732	CE  						MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4785 	913  					779147		DOWEL CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100854	19971231	00854	GL  	1997	12	31	EY2R9600922      	3	19960801	G	6110	A1896	CYLINDER PIN    			CESSNA	337   	337H        	2075732	CE  						MCAULY	2AF34C	D2AF34C310  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4785 	913  					780550		CORROSION FOUND CYLINDER PIN.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100855	19971231	00855	GL  	1997	12	31	EY2R9600923      	3	19960801	G	6110	A4001	DOWEL           			CESSNA	337   	337H        	2075732	CE  						MCAULY	2AF34C	D2AF34C310  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4785 	913  					780550		DOWEL CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100856	19971231	00856	GL  	1997	12	31	EY2R9600924      	3	19960801	G	6110	A1896	CYLINDER PIN    			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C59   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								704088		CYLINDER PIN CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100857	19971231	00857	GL  	1997	12	31	EY2R9600925      	3	19960801	G	6110	A4001	DOWEL           			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C59   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								704088		DOWEL CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997123100858	19971231	00858	GL  	1997	12	31	EY2R9600926      	3	19960801	G	6110	14B	BEARING         			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								K1463N		BEARING CORRODED.						1	L	7	2 	3O				1A10    		5	C	P23EA	 
1997123100859	19971231	00859	GL  	1997	12	31	EY2R9600927      	3	19960801	G	6111	PROPELLER	BLADES          			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HC82X	HC82XL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								K1252		BLADES, SN'S 91373,01495, FOUND CORRODED						1	L	7	2 	3O				1A10    		5	C	P878	 
1997123100860	19971231	00860	GL  	1997	12	31	EY2R9600928      	3	19960801	G	6110	1303A	BEARING         			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92Z	HC92ZK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1682F		BEARING CORRODED.						1	L	7	2 	3O				3A16    		5	C	P892	 
1997123100861	19971231	00861	GL  	1997	12	31	EY2R9600929      	3	19960801	G	6110	1331	SPLIT RING      			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92Z	HC92ZK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1682F		CORROSION FOUND ON SPLIT RING.						1	L	7	2 	3O				3A16    		5	C	P892	 
1997123100862	19971231	00862	GL  	1997	12	31	EY2R9600930      	3	19960801	G	6110	83830	CLAMP           			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92Z	HC92ZK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1682F		CLAMP CORRODED.						1	L	7	2 	3O				3A16    		5	C	P892	 
1997123100863	19971231	00863	GL  	1997	12	31	EY2R9600931      	3	19960801	G	6110	853	FEATHERING SPRNG			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92Z	HC92ZK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1682F		CORROSION FOUND ON FEATHERING SPRING.						1	L	7	2 	3O				3A16    		5	C	P892	 
1997123100864	19971231	00864	GL  	1997	12	31	EY2R9600932      	3	19960801	G	6110	84060	PILOT TUBE      			AIRTRC	AT400 	AT400A      	0390203	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU18837		CORROSION FOUND ON PILOT TUBES.  REPLACED PILOT TUBES.						1	L	7	1 	3T				A9SW    		6	C	P15EA	 
1997123100865	19971231	00865	GL  	1997	12	31	EY2R9600933      	3	19960801	G	6110	790100016	BALL BEARING    			AIRTRC	AT400 	AT400A      	0390203	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU18837		BALL BEARING CORRODED.						1	L	7	1 	3T				A9SW    		6	C	P15EA	 
1997123100866	19971231	00866	GL  	1997	12	31	EY2R9600934      	3	19960801	G	6114	220117	HUB             			PIPER 	PA28  	PA28R180    	7102809	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1240 	770  					AW1137		HUB CORRODED.						1	L	7	1 	3O				2A13    		5	C	P920	 
1997123100867	19971231	00867	GL  	1997	12	31	EY2R9600935      	3	19960801	G	6110	2202	SPLIT BEARING   			PIPER 	PA28  	PA28R180    	7102809	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1240 	770  					AW1137		CORROSION FOUND ON SPLIT BEARING.						1	L	7	1 	3O				2A13    		5	C	P920	 
1997123100868	19971231	00868	GL  	1997	12	31	EY2R9600936      	3	19960801	G	6111	F7666A	BLADE           			PIPER 	PA28  	PA28R180    	7102809	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1240 	770  					AW1137		BLADE, SN B24230, FOUND CORRODED.						1	L	7	1 	3O				2A13    		5	C	P920	 
1997123100869	19971231	00869	GL  	1997	12	31	EY2R9600937      	3	19960801	G	6111	F7666A	BLADE           			PIPER 	PA28  	PA28R180    	7102809	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1240 	770  					AW1137		BLADE, SN C3762, FOUND CORRODED.						1	L	7	1 	3O				2A13    		5	C	P920	 
1997123100870	19971231	00870	GL  	1997	12	31	EY2R9600938      	3	19960801	G	6114	220117	HUB             			CONAER	LA4   	LA4200      	5110310	NE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH1609		HUB CORRODED.						1	H	7	1 	3O				1A13    		5	C	P920	 
1997123100871	19971231	00871	GL  	1997	12	31	EY2R9600939      	3	19960801	G	6110	790100018	BALL BEARING    			BNORM 	BN2   	BN2A3       	1520215	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU42		BALL BEARING CORRODED.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1997123100872	19971231	00872	GL  	1997	12	31	EY2R9600940      	3	19960801	G	6114	24772R	HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP2764		HUB CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100873	19971231	00873	GL  	1997	12	31	EY2R9600941      	3	19960901	G	6110	130035908	CAP SCREW       			SWRNGN	SA226 	SA226TC     	8780404	SW  						ROTOL	R321	R321482F8   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		11083	4352 					DRG58982		CORROSION FOUND ON CAP SCREW.						2	L	7	2 	4T			RT	A8SW    		6	C	P61GL	 
1997123100874	19971231	00874	GL  	1997	12	31	EY2R9600942      	3	19960901	G	6110	A10210E	BOLT            			SWRNGN	SA226 	SA226TC     	8780404	SW  						ROTOL	R321	R321482F8   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		11083	4352 					DRG58982		CORROSION FOUND ON BOLT.						2	L	7	2 	4T			RT	A8SW    		6	C	P61GL	 
1997123100875	19971231	00875	GL  	1997	12	31	EY2R9600943      	3	19960901	G	6114	C3910C201	HUB             			CESSNA	180   	180H        	2072618	CE  						MCAULY	2A34C	2A34C201    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								735447		HUB CORRODED.						1	H	7	1 	3O				5A6     		5	C	P3EA	 
1997123100876	19971231	00876	GL  	1997	12	31	EY2R9600944      	3	19960901	G	6114	C3910C203	HUB             			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		743  	230  					752704		HUB CORRODED.						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997123100877	19971231	00877	GL  	1997	12	31	EY2R9600945      	3	19960901	G	6110	C3411	BEARING RACE    			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								797355		BEARING RACE FOUND CORRODED.						1	L	7	2 	3O				A25CE   		5	C	P22EA	 
1997123100878	19971231	00878	GL  	1997	12	31	EY2R9600946      	3	19960901	G	6110	A16346	BALL BEARING    			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								813310		BALL BEARING CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100879	19971231	00879	GL  	1997	12	31	EY2R9600947      	3	19960901	G	6110	C5270	RETAIN BEARING  			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3745 	674  					841466		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100880	19971231	00880	GL  	1997	12	31	EY2R9600948      	3	19960901	G	6110	C5270	RETAIN BEARING  			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3745 	674  					841467		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100881	19971231	00881	GL  	1997	12	31	EY2R9600949      	3	19960901	G	6110	A16349	BALL BEARING    			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								861371		BALL BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100882	19971231	00882	GL  	1997	12	31	EY2R9600950      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								822089		DOWEL CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100883	19971231	00883	GL  	1997	12	31	EY2R9600951      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								822439		DOWEL CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1997123100884	19971231	00884	GL  	1997	12	31	EY2R9600952      	3	19960901	G	6110	A1896	CYLINDER PIN    			PIPER 	PA34  	PA34220T    	7103420	SO  						MCAULY	3AF32C	3AF32C508   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								814783		CYLINDER PIN CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1997123100885	19971231	00885	GL  	1997	12	31	EY2R9600953      	3	19960901	G	6110	A4191	DOWEL           			PIPER 	PA34  	PA34220T    	7103420	SO  						MCAULY	3AF32C	3AF32C508   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								814783		DOWEL CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1997123100886	19971231	00886	GL  	1997	12	31	EY2R9600954      	3	19960901	G	6110	A1896	CYLINDER PIN    			PIPER 	PA34  	PA34220T    	7103420	SO  						MCAULY	3AF32C	3AF32C509   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								814791		CYLINDER PIN CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1997123100887	19971231	00887	GL  	1997	12	31	EY2R9600955      	3	19960901	G	6110	C5270	RETAIN BEARING  			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940739		RETAIN BEARING.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1997123100888	19971231	00888	GL  	1997	12	31	EY2R9600956      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782818		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100889	19971231	00889	GL  	1997	12	31	EY2R9600957      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782818		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100890	19971231	00890	GL  	1997	12	31	EY2R9600958      	3	19960901	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782818		BLADE, SN K85269YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100891	19971231	00891	GL  	1997	12	31	EY2R9600959      	3	19960901	G	6111	S82NC55	BLADE           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782818		BLADE, SN K85267YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100892	19971231	00892	GL  	1997	12	31	EY2R9600960      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								804818		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100893	19971231	00893	GL  	1997	12	31	EY2R9600961      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								804818		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100894	19971231	00894	GL  	1997	12	31	EY2R9600962      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753330		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100895	19971231	00895	GL  	1997	12	31	EY2R9600963      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4772 						788627		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100896	19971231	00896	GL  	1997	12	31	EY2R9600964      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4772 						789445		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100897	19971231	00897	GL  	1997	12	31	EY2R9600965      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753330		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100898	19971231	00898	GL  	1997	12	31	EY2R9600966      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4772 						788627		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100899	19971231	00899	GL  	1997	12	31	EY2R9600967      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4772 						789445		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100900	19971231	00900	GL  	1997	12	31	EY2R9600968      	3	19960901	G	6110	B3490	PISTON ROD PIN  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753330		PISTON ROD PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100901	19971231	00901	GL  	1997	12	31	EY2R9600969      	3	19960901	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753330		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100902	19971231	00902	GL  	1997	12	31	EY2R9600970      	3	19960901	G	6110	C7036	NUT             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753330		CORROSION FOUND ON NUT.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100903	19971231	00903	GL  	1997	12	31	EY2R9600971      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798440		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100904	19971231	00904	GL  	1997	12	31	EY2R9600972      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798443		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100905	19971231	00905	GL  	1997	12	31	EY2R9600973      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798440		DOWEL CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100906	19971231	00906	GL  	1997	12	31	EY2R9600974      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798443		DOWEL CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100907	19971231	00907	GL  	1997	12	31	EY2R9600975      	3	19960901	G	6110	B3490	PISTON ROD PIN  			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798443		PISTON ROD PIN FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100908	19971231	00908	GL  	1997	12	31	EY2R9600976      	3	19960901	G	6110	C2987	RETAIN BEARING  			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798443		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100909	19971231	00909	GL  	1997	12	31	EY2R9600977      	3	19960901	G	6110	C7036	NUT             			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798443		NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100910	19971231	00910	GL  	1997	12	31	EY2R9600978      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								911178		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100911	19971231	00911	GL  	1997	12	31	EY2R9600979      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								911178		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100912	19971231	00912	GL  	1997	12	31	EY2R9600980      	3	19960901	G	6110	B3490	PISTON ROD PIN  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								911178		PISTON ROD PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100913	19971231	00913	GL  	1997	12	31	EY2R9600981      	3	19960901	G	6110	C7036	NUT             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								911178		CORROSION FOUND ON NUT.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100914	19971231	00914	GL  	1997	12	31	EY2R9600982      	3	19960901	G	6110	B4460	BLADE ACT PIN   			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940196		BLADE ACT PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100915	19971231	00915	GL  	1997	12	31	EY2R9600983      	3	19960901	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								745607		HUB CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100916	19971231	00916	GL  	1997	12	31	EY2R9600984      	3	19960901	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1772 					783143		HUB CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997123100917	19971231	00917	GL  	1997	12	31	EY2R9600985      	3	19960901	G	6110	A18961	CYLINDER PIN    			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3436 	1174 					782013		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100918	19971231	00918	GL  	1997	12	31	EY2R9600986      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3436 	1174 					782013		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100919	19971231	00919	GL  	1997	12	31	EY2R9600987      	3	19960901	G	6110	C7036	NUT             			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3436 	1174 					782013		NUT CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100920	19971231	00920	GL  	1997	12	31	EY2R9600988      	3	19960901	G	6110	C3411	BEARING RACE    			PIPER 	PA34  	PA34200T    	7103406	SO  						MCAULY	3AF34C	3AF34C502   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3021 	975  					789767		BEARING RACE FOUND CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1997123100921	19971231	00921	GL  	1997	12	31	EY2R9600989      	3	19960901	G	6111	S82NC55	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803690		BLADE, SN BD1023YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100922	19971231	00922	GL  	1997	12	31	EY2R9600990      	3	19960901	G	6110	A1896	CYLINDER PIN    			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								763069		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100923	19971231	00923	GL  	1997	12	31	EY2R9600991      	3	19960901	G	6110	A4191	DOWEL           			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								763069		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1997123100924	19971231	00924	GL  	1997	12	31	EY2R9600992      	3	19960901	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2848 						902582		CORROSION FOUND ON SCREW.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997123100925	19971231	00925	GL  	1997	12	31	EY2R9600993      	3	19960901	G	6111	G78TCA0	BLADE           			CESSNA	177   	177RG       	2073709	CE  						MCAULY	2D34C	B2D34C207   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1256 	582  					832495		BLADE, SN DF067, FOUND CORRODED.						1	H	7	1 	3O				A20CE   		5	C	P7EA	 
1997123100926	19971231	00926	GL  	1997	12	31	EY2R9600994      	3	19960901	G	6111	G78TCA0	BLADE           			CESSNA	177   	177RG       	2073709	CE  						MCAULY	2D34C	B2D34C207   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1256 	582  					832495		BLADE, SN DF052, FOUND CORRODED.						1	H	7	1 	3O				A20CE   		5	C	P7EA	 
1997123100927	19971231	00927	GL  	1997	12	31	EY2R9600995      	3	19960901	G	6110	A3124	GUIDE SPRING    			CESSNA	182   	182         	2072702	CE  						MCAULY	2D34C	B2D34C214   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3465 	1803 					783681		GUIDE SPRING FOUND CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P7EA	 
1997123100928	19971231	00928	GL  	1997	12	31	EY2R9600996      	3	19960901	G	6110	C4451	FERRULE         			CESSNA	206   	P206A       	2073308	CE  						MCAULY	3A32C	D3A32C90    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								851261		FERRULE CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997123100929	19971231	00929	GL  	1997	12	31	EY2R9600997      	3	19960901	G	6110	14B	BEARING         			HELIO 	H395  	H395A       	4300206	CE  						HARTZL	HC82V	HC82V201    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7682N		BEARING CORRODED.						1	H	7	1 	3O				1A8     		5	C	P23EA	 
1997123100930	19971231	00930	GL  	1997	12	31	EY2R9600998      	3	19960901	G	6110	83810	CLAMP           			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5507 	1755 					H1062		CORROSION FOUND ON CLAMP.						1	L	7	2 	3O				1A10    		5	C	P24EA	 
1997123100931	19971231	00931	GL  	1997	12	31	EY2R9600999      	3	19960901	G	6110	971	SPLIT BEARING   			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5507 	1755 					H1062		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				1A10    		5	C	P24EA	 
1997123100932	19971231	00932	GL  	1997	12	31	EY2R9601000      	3	19960901	G	6110	1977	CLAMP           			DOUG  	B18   	B18A        	3020605	WP  						HARTZL	HCB3R	HCB3R302    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CORROSION FOUND ON CLAMP.						2	M	7	2 	4R				2577    		5	C	P28EA	 
1997123100933	19971231	00933	GL  	1997	12	31	EY2R9601001      	3	19960901	G	6110	13081	PILOT TUBE      			BEECH 	80    	65B80       	1152812	CE  						HARTZL	HCB3Z	HCB3Z302    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								831J		PILOT TUBE FOUND CORRODED.						1	L	7	2 	3O				3A20    		5	C	P907	 
1997123100934	19971231	00934	GL  	1997	12	31	EY2R9601002      	3	19960901	G	6110	1851	BEARING         			BEECH 	80    	65B80       	1152812	CE  						HARTZL	HCB3Z	HCB3Z302    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								831J		BEARING CORRODED.						1	L	7	2 	3O				3A20    		5	C	P907	 
1997123100935	19971231	00935	GL  	1997	12	31	EY2R9601003      	3	19960901	G	6110	1851	BEARING         			BEECH 	80    	65B80       	1152812	CE  						HARTZL	HCB3Z	HCB3Z302    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								865J		BEARING CORRODED.						1	L	7	2 	3O				3A20    		5	C	P907	 
1997123100936	19971231	00936	GL  	1997	12	31	EY2R9601004      	3	19960901	G	6110	83817	CLAMP           			BEECH 	80    	65B80       	1152812	CE  						HARTZL	HCB3Z	HCB3Z302    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								831J		CORROSION FOUND ON CLAMP.						1	L	7	2 	3O				3A20    		5	C	P907	 
1997123100937	19971231	00937	GL  	1997	12	31	EY2R9601005      	3	19960901	G	6110	83817	CLAMP           			BEECH 	80    	65B80       	1152812	CE  						HARTZL	HCB3Z	HCB3Z302    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								865J		CORROSION FOUND ON CLAMP.						1	L	7	2 	3O				3A20    		5	C	P907	 
1997123100938	19971231	00938	GL  	1997	12	31	EY2R9601006      	3	19960901	G	6114	32511R	HUB             			CESSNA	207   	207         	2073602	CE  						HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		225  						DY2050		HUB CORRODED.						1	H	7	1 	3O				A16CE   		5	C	P25EA	 
1997123100939	19971231	00939	NE  	1997	12	31	EY2R9601007      	3	19960901	G	6114	3932	HUB             			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								HJ117A		HUB CORRODED.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997123100940	19971231	00940	GL  	1997	12	31	EY2R9601008      	3	19961001	G	6111	90DA8	BLADE           			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C201    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								72258		BLADE, SN B12911, FOUND CORRODED.						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997123100941	19971231	00941	GL  	1997	12	31	EY2R9601009      	3	19961001	G	6111	90DA8	BLADE           			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C201    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								72258		BLADE, SN B12748, FOUND CORRODED.						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997123100942	19971231	00942	GL  	1997	12	31	EY2R9601010      	3	19961001	G	6111	90DHB16E	BLADE           			MOONEY	M20   	M20K        	5870220	SW  						MCAULY	2A34C	2A34C*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821428		BLADE, SN H1099, FOUND CORRODED.						1	L	7	1 	3O				2A3     		5	C	P3EA	 
1997123100943	19971231	00943	GL  	1997	12	31	EY2R9601011      	3	19961001	G	6111	90DHB16E	BLADE           			MOONEY	M20   	M20K        	5870220	SW  						MCAULY	2A34C	2A34C*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821428		BLADE, SN H1087, FOUND CORRODED.						1	L	7	1 	3O				2A3     		5	C	P3EA	 
1997123100944	19971231	00944	GL  	1997	12	31	EY2R9601012      	3	19961001	G	6111	82NEA55	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								816080		BLADE, SN BD618, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100945	19971231	00945	GL  	1997	12	31	EY2R9601013      	3	19961001	G	6114	D5888C505	HUB             			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815922		HUB CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100946	19971231	00946	GL  	1997	12	31	EY2R9601014      	3	19961001	G	6111	S82NC4	BLADE           			CESSNA	320   	320D        	2074512	CE  						MCAULY	3AF32C	3AF32C72    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								686532		BLADE, SN C33529YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100947	19971231	00947	GL  	1997	12	31	EY2R9601015      	3	19961001	G	6114	D7015C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								73270		HUB CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100948	19971231	00948	GL  	1997	12	31	EY2R9601016      	3	19961001	G	6114	D7015C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								732094		HUB CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100949	19971231	00949	GL  	1997	12	31	EY2R9601017      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								73270		BLADE, SN F35476YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100950	19971231	00950	GL  	1997	12	31	EY2R9601018      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								73270		BLADE, SN F35761YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100951	19971231	00951	GL  	1997	12	31	EY2R9601019      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								73270		BLADE, SN F33462YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100952	19971231	00952	GL  	1997	12	31	EY2R9601020      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								732094		BLADE, SN F35930YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100953	19971231	00953	GL  	1997	12	31	EY2R9601021      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								732094		BLADE, SN F35903YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100954	19971231	00954	GL  	1997	12	31	EY2R9601022      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								732094		BLADE, SN F35778YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100955	19971231	00955	GL  	1997	12	31	EY2R9601023      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798951		BLADE, SN F41236YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100956	19971231	00956	GL  	1997	12	31	EY2R9601024      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798951		BLADE, SN F41359YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100957	19971231	00957	GL  	1997	12	31	EY2R9601025      	3	19961001	G	6111		BLADE           			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								799131		BLADES, SN'S K100294YS, K100298YS, K100724YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100958	19971231	00958	GL  	1997	12	31	EY2R9601026      	3	19961001	G	6110	C3903	SPLIT RETAINER  			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								841269		CORROSION FOUND ON SPLIT RETAINER.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1997123100959	19971231	00959	GL  	1997	12	31	EY2R9601027      	3	19961001	G	6110	C5270	RETAIN BEARING  			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								841269		RETAIN BEARING CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1997123100960	19971231	00960	GL  	1997	12	31	EY2R9601028      	3	19961001	G	6110	D40099	SLIP RING       			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								841269		CORROSION FOUND ON SPLIT RING.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1997123100961	19971231	00961	GL  	1997	12	31	EY2R9601029      	3	19961001	G	6114	220118	HUB             			PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN5991		HUB CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997123100962	19971231	00962	GL  	1997	12	31	EY2R9601030      	3	19961001	G	6111	90AT4	BLADE           			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902390		BLADE, SN KH07445, FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100963	19971231	00963	GL  	1997	12	31	EY2R9601031      	3	19961001	G	6111	90AT4	BLADE           			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902390		BLADE, SN KH06645, FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997123100964	19971231	00964	GL  	1997	12	31	EY2R9601032      	3	19961001	G	6111	80GF0	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	2AF34C	D2AF34C52   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								751077		BLADE, SN C30806YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P5EA	 
1997123100965	19971231	00965	GL  	1997	12	31	EY2R9601033      	3	19961001	G	6111	80GF0	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	2AF34C	D2AF34C52   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								751077		BLADE, SN B29888YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P5EA	 
1997123100966	19971231	00966	GL  	1997	12	31	EY2R9601034      	3	19961001	G	6111	90DFA10	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								788478		BLADE, SN B136412, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100967	19971231	00967	GL  	1997	12	31	EY2R9601035      	3	19961001	G	6111	90DFA10	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								788478		BLADE, SN B09515, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100968	19971231	00968	GL  	1997	12	31	EY2R9601036      	3	19961001	G	6111	90DFA10	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								788478		BLADE, SN B98523, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100969	19971231	00969	GL  	1997	12	31	EY2R9601037      	3	19961001	G	6110	C5264	CYLINDER        			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								788478		CYLINDER CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100970	19971231	00970	GL  	1997	12	31	EY2R9601038      	3	19961001	G	6114	D5858C402	HUB             			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								788478		HUB CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100971	19971231	00971	GL  	1997	12	31	EY2R9601039      	3	19961001	G	6110	971	SPLIT BEARING   			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCA2X	HCA2XF2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								H107		CORROSION FOUND ON SPLIT BEARING.						1	H	7	2 	3O				6A1     		5	C	P908	 
1997123100972	19971231	00972	GL  	1997	12	31	EY2R9601040      	3	19961001	G	6110	84082	PILOT TUBE      			BEECH 	80    	65A80       	1152808	CE  						HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1472 	944  					BJ468		R & R PILOT TUBES						1	L	7	2 	3O				3A20    		5	C	P6EA	 
1997123100973	19971231	00973	GL  	1997	12	31	EY2R9601041      	3	19961001	G	6110	84082	PILOT TUBE      			BEECH 	80    	65A80       	1152808	CE  						HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1472 	944  					BJ481		R & R PILOT TUBES						1	L	7	2 	3O				3A20    		5	C	P6EA	 
1997123100974	19971231	00974	GL  	1997	12	31	EY2R9601042      	3	19961001	G	6110	971	SPLIT BEARING   			BEECH 	58    	58          	1152740	CE  						HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1472 	944  					BJ481		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P6EA	 
1997123100975	19971231	00975	GL  	1997	12	31	EY2R9601043      	3	19961001	G	6111	V84332R	BLADE           			BEECH 	80    	65A80       	1152808	CE  						HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1472 	944  					BJ468		BLADE, SN B69968, FOUND CORRODED.						1	L	7	2 	3O				3A20    		5	C	P6EA	 
1997123100976	19971231	00976	GL  	1997	12	31	EY2R9601044      	3	19961001	G	6111	V84332R	BLADE           			BEECH 	80    	65A80       	1152808	CE  						HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1472 	944  					BJ468		BLADE, SN A20549, FOUND CORRODED.						1	L	7	2 	3O				3A20    		5	C	P6EA	 
1997123100977	19971231	00977	GL  	1997	12	31	EY2R9601045      	3	19961001	G	6111	V84332R	BLADE           			BEECH 	80    	65A80       	1152808	CE  						HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1472 	944  					BJ468		BLADE, SN 111092, FOUND CORRODED.						1	L	7	2 	3O				3A20    		5	C	P6EA	 
1997123100978	19971231	00978	GL  	1997	12	31	EY2R9601046      	3	19961001	G	6114	24772	HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1998 					BP1655		HUB CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100979	19971231	00979	GL  	1997	12	31	EY2R9601047      	3	19961001	G	6114	24772	HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1998 					BP5731		CORROSION FOUND ON HUB.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1997123100980	19971231	00980	GL  	1997	12	31	EY2R9601048      	3	19960901	G	6110	C5971	COUNTERWEIGHT   			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1500 						921207		COUNTERWEIGHT CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100981	19971231	00981	GL  	1997	12	31	EY2R9601049      	3	19960901	G	6110	C2987	RETAIN BEARING  			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								743983		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997123100982	19971231	00982	GL  	1997	12	31	EY2R9601050      	3	19960901	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								764989		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100983	19971231	00983	GL  	1997	12	31	EY2R9601051      	3	19960901	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								801079		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100984	19971231	00984	GL  	1997	12	31	EY2R9601052      	3	19960901	G	6110	C3475	NUT             			CESSNA	320   	320         	2074502	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								760968		NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100985	19971231	00985	GL  	1997	12	31	EY2R9601053      	3	19960901	G	6110	C3475	NUT             			CESSNA	320   	320         	2074502	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								764755		NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100986	19971231	00986	GL  	1997	12	31	EY2R9601054      	3	19960901	G	6110	C3475	NUT             			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								801079		NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100987	19971231	00987	GL  	1997	12	31	EY2R9601055      	3	19960901	G	6110	C3550	FEATHER CYLINDER			CESSNA	320   	320         	2074502	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								764755		CORROSION FOUND ON FEATHER CYLINDER.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100988	19971231	00988	GL  	1997	12	31	EY2R9601056      	3	19960901	G	6111	S82NC4	BLADE           			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								713447		BLADE, SN F25242YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997123100989	19971231	00989	GL  	1997	12	31	EY2R9601057      	3	19960901	G	6110	C2987	RETAIN BEARING  			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768641		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100990	19971231	00990	GL  	1997	12	31	EY2R9601058      	3	19960901	G	6110	C3475	NUT             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768641		NUT CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1997123100991	19971231	00991	GL  	1997	12	31	EY2R9601059      	3	19960901	G	6110	2202	SPLIT BEARING   			BEECH 	55    	9555        	1152702	CE  						HARTZL	HCJ2Y	BHCJ2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DZ442		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P37EA	 
1997123100992	19971231	00992	GL  	1997	12	31	EY2R9601060      	3	19960901	G	6110	A4577	LINK            			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								840414		CORROSION FOUND ON LINK.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100993	19971231	00993	GL  	1997	12	31	EY2R9601061      	3	19960901	G	6110	C4784	PISTON          			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								840414		PISTON CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100994	19971231	00994	GL  	1997	12	31	EY2R9601062      	3	19960901	G	6110	C5264	CYLINDER        			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								840414		CYLINDER CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1997123100995	19971231	00995	GL  	1997	12	31	EY2R9601063      	3	19960901	G	6110	C2987	RETAIN BEARING  			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798498		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100996	19971231	00996	GL  	1997	12	31	EY2R9601064      	3	19960901	G	6110	C3475	NUT             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798498		NUT CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1997123100997	19971231	00997	GL  	1997	12	31	EY2R9601065      	3	19960901	G	6110	1303A	BEARING         			CONAER	LA4   	LA4         	5110302	NE  						HARTZL	HC92W	HC92W*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								2404Z		BEARING CORRODED.						1	H	7	1 	3O				1A13    		5	C	P16EA	 
1997123100998	19971231	00998	GL  	1997	12	31	EY2R9601066      	3	19960901	G	6110	2202	SPLIT BEARING   			BEECH 	58    	58TC        	1152746	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								ED952		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				A23CE   		5	C	P36EA	 
1998042900132	19980429	00132	GL  	1998	4	29	EY2R9601067      	3	19961001	G	6114	C3910C201	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C201    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								800691		HUB CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998042900133	19980429	00133	GL  	1998	4	29	EY2R9601068      	3	19961001	G	6114	C3910C203	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								742514		HUB CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998042900134	19980429	00134	GL  	1998	4	29	EY2R9601069      	3	19961001	G	6114	C3910C203	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								756040		HUB CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998042900135	19980429	00135	GL  	1998	4	29	EY2R9601070      	3	19961001	G	6110	A4001	DOWEL           			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C203    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								870628		DOWEL CORRODED.						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1998042900136	19980429	00136	GL  	1998	4	29	EY2R9601071      	3	19961001	G	6111	S90AT8	BLADE           			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN B23171YS, FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1998042900137	19980429	00137	GL  	1998	4	29	EY2R9601072      	3	19961001	G	6111	S90AT8	BLADE           			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN B20147YS, FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1998042900138	19980429	00138	GL  	1998	4	29	EY2R9601073      	3	19961001	G	6114	C4526C29	HUB             			CESSNA	180   	180H        	2072618	CE  						MCAULY	2A36C	2A36C29     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								62347		HUB CORRODED.						1	H	7	1 	3O				5A6     		5	C	P880	 
1998042900139	19980429	00139	GL  	1998	4	29	EY2R9601074      	3	19961001	G	6114	C4526C29	HUB             			CESSNA	180   	180G        	2072616	CE  						MCAULY	2A36C	2A36C29     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								591058		HUB CORRODED.						1	H	7	1 	3O				5A6     		5	C	P880	 
1998042900140	19980429	00140	NE  	1998	4	29	EY2R9601075      	3	19961001	G	6110	55210	PROPELLER       			STNSON	SM8   	SM8A        	8630802	GL  						HAMSTD	2B	2B20        	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			101  					T20363		CORRODED PROP ASSY						1	H	7	1 	3R				ATC295  		5	C	P255	 
1998042900141	19980429	00141	GL  	1998	4	29	EY2R9601076      	3	19961001	G	6111	82NB2	BLADE           			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN C44573YS, FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1998042900142	19980429	00142	GL  	1998	4	29	EY2R9601077      	3	19961001	G	6111		BLADES          			BEECH 	33    	F33A        	1151425	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								781601		BLADES, SN'S K91889YS,K92027YS,K91828YS, FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1998042900143	19980429	00143	GL  	1998	4	29	EY2R9601078      	3	19961001	G	6110	A1896	PIN             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1858 	755  					851043		CORROSION FOUND ON CYLINDER PIN.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998042900144	19980429	00144	GL  	1998	4	29	EY2R9601079      	3	19961001	G	6110	A4191	DOWEL           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1858 	755  					851043		DOWEL CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998042900145	19980429	00145	GL  	1998	4	29	EY2R9601080      	3	19961001	G	6110	A16349	BEARING         			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1501 						940211		BALL BEARING CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900146	19980429	00146	GL  	1998	4	29	EY2R9601081      	3	19961001	G	6110	A1896	PIN             			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		625  						920675		CYLINDER PIN CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1998042900147	19980429	00147	GL  	1998	4	29	EY2R9601082      	3	19961001	G	6110	A4191	DOWEL           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		625  						920675		DOWEL CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1998042900148	19980429	00148	GL  	1998	4	29	EY2R9601083      	3	19961001	G	6114	D6468C8	HUB             			BEECH 	23    	A23         	1151204	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								686186		HUB CORRODED.						1	L	7	1 	3O				A1CE    		5	C	P22EA	 
1998042900149	19980429	00149	GL  	1998	4	29	EY2R9601084      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN K62383YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900150	19980429	00150	GL  	1998	4	29	EY2R9601085      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								739707		BLADE FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1998042900151	19980429	00151	GL  	1998	4	29	EY2R9601086      	3	19961001	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								684435		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1998042900152	19980429	00152	GL  	1998	4	29	EY2R9601087      	3	19961001	G	6111	S82NC4	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								684435		BLADE, SN C41944YS, FOUND CORRODED.						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1998042900153	19980429	00153	GL  	1998	4	29	EY2R9601088      	3	19961001	G	6110	A1896	CYLINDER PIN    			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			696  					727378		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900154	19980429	00154	GL  	1998	4	29	EY2R9601089      	3	19961001	G	6110	A4191	DOWEL           			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			696  					727378		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900155	19980429	00155	GL  	1998	4	29	EY2R9601090      	3	19961001	G	6110	B3490	PIN             			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			696  					727378		CORROSION FOUND ON PISTON ROD PIN.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900156	19980429	00156	GL  	1998	4	29	EY2R9601091      	3	19961001	G	6110	B4459	BLADE ACT PIN   			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			696  					727378		BLADE ACT PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900157	19980429	00157	GL  	1998	4	29	EY2R9601092      	3	19961001	G	6110	C3550	CYLINDER        			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			696  					727378		CORROSION FOUND ON FEATHER C YLINDER.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900158	19980429	00158	GL  	1998	4	29	EY2R9601093      	3	19961001	G	6111	S82NC4	BLADE           			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			696  					727378		BLADE, SN BG397YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900159	19980429	00159	GL  	1998	4	29	EY2R9601094      	3	19961001	G	6110	A1896	PIN             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 	1480 					746034		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900160	19980429	00160	GL  	1998	4	29	EY2R9601095      	3	19961001	G	6110	A1896	PIN             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 						771292		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900161	19980429	00161	GL  	1998	4	29	EY2R9601096      	3	19961001	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 	1480 					746034		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900162	19980429	00162	GL  	1998	4	29	EY2R9601097      	3	19961001	G	6110	A4191	DOWEL           			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 						771292		DOWEL CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900163	19980429	00163	GL  	1998	4	29	EY2R9601098      	3	19961001	G	6110	C3550	CYLINDER        			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 	1480 					746034		CORROSION FOUND ON CYLINDER.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900164	19980429	00164	GL  	1998	4	29	EY2R9601099      	3	19961001	G	6111	S82NC55	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN K103232YS, FOUND ON CYLINDER.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900165	19980429	00165	GL  	1998	4	29	EY2R9601100      	3	19961001	G	6110	C4451	FERRULE         			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1229 					673758		FERRULE FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900166	19980429	00166	GL  	1998	4	29	EY2R9601101      	3	19961001	G	6114	D7015C87	HUB             			CESSNA	310   	310P        	2074238	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1229 					673758		HUB CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900167	19980429	00167	GL  	1998	4	29	EY2R9601102      	3	19961001	G	6111	82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		BLADE, SN K82853YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900168	19980429	00168	GL  	1998	4	29	EY2R9601103      	3	19961001	G	6111	82NC55	BLADE           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		BLADE, SN K82928YS, FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900169	19980429	00169	GL  	1998	4	29	EY2R9601104      	3	19961001	G	6110	A1896	PIN             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900170	19980429	00170	GL  	1998	4	29	EY2R9601105      	3	19961001	G	6110	A1896	PIN             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900171	19980429	00171	GL  	1998	4	29	EY2R9601106      	3	19961001	G	6110	A4191	DOWEL           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		DOWEL CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900172	19980429	00172	GL  	1998	4	29	EY2R9601107      	3	19961001	G	6110	A4191	DOWEL           			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		DOWEL CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900173	19980429	00173	GL  	1998	4	29	EY2R9601108      	3	19961001	G	6110	B3490	PISTON ROD PIN  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		PISTON ROD PIN FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900174	19980429	00174	GL  	1998	4	29	EY2R9601109      	3	19961001	G	6110	C2987	BEARING         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900175	19980429	00175	GL  	1998	4	29	EY2R9601110      	3	19961001	G	6110	C2987	RETAIN BEARING  			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900176	19980429	00176	GL  	1998	4	29	EY2R9601111      	3	19961001	G	6110	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		FERRULE FOUND WITH CORROSION.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900177	19980429	00177	GL  	1998	4	29	EY2R9601112      	3	19961001	G	6110	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		FERRULE FOUND WITH CORROSION.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900178	19980429	00178	GL  	1998	4	29	EY2R9601113      	3	19961001	G	6110	A1896	PIN             			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768385		CYLINDER PIN FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998042900179	19980429	00179	GL  	1998	4	29	EY2R9601114      	3	19961001	G	6110	A4191	DOWEL           			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768385		DOWEL CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998042900180	19980429	00180	GL  	1998	4	29	EY2R9601115      	3	19961001	G	6110	B4426	RETAIN RING     			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789223		RETAIN RING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998042900181	19980429	00181	GL  	1998	4	29	EY2R9601116      	3	19961001	G	6110	B48201	ACT PIN ASSY    			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789223		ACT PIN ASSY FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998042900182	19980429	00182	GL  	1998	4	29	EY2R9601117      	3	19961001	G	6110	C5270	BEARING         			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789223		RETAIN BEARING CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998042900183	19980429	00183	GL  	1998	4	29	EY2R9601118      	3	19961001	G	6110	D3474	ROD             			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								767592		PISTON ROD ASSY FOUND WITH CORROSION.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998042900184	19980429	00184	GL  	1998	4	29	EY2R9601119      	3	19961001	G	6114	D5878C501	HUB             			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								767592		HUB FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998042900185	19980429	00185	GL  	1998	4	29	EY2R9601120      	3	19961001	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2760 						900938		SCREW CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900186	19980429	00186	GL  	1998	4	29	EY2R9601121      	3	19961001	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2688 						910855		SCREW  CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900187	19980429	00187	GL  	1998	4	29	EY2R9601122      	3	19961001	G	6110	D5010	CYLINDER        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2760 						900938		CYLINDER FOUND CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900188	19980429	00188	GL  	1998	4	29	EY2R9601123      	3	19961001	G	6114	C208	HUB             			CESSNA	177   	177B        	2073708	CE  						MCAULY	2D34C	B2D34C208   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								778236		HUB FOUND CORRODED.						1	H	7	1 	3O				A13CE   		5	C	P7EA	 
1998042900189	19980429	00189	GL  	1998	4	29	EY2R9601124      	3	19961001	G	6110	B2345	PISTON TUBE     			CESSNA	182   	182R        	2072731	CE  						MCAULY	2D34C	B2D34C219   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7910786		PISTON TUBE FOUND CORRODED.						1	L	7	1 	3O			NT	3A13    		5	C	P7EA	 
1998042900190	19980429	00190	GL  	1998	4	29	EY2R9601125      	3	19961001	G	6110	C5046	PLATE           			CESSNA	182   	182R        	2072731	CE  						MCAULY	2D34C	B2D34C219   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7910786		PLATE CORRODED.						1	L	7	1 	3O			NT	3A13    		5	C	P7EA	 
1998042900191	19980429	00191	GL  	1998	4	29	EY2R9601126      	3	19961001	G	6114	C5078C220	HUB             			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								803354		HUB FOUND CORRODED.						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1998042900192	19980429	00192	GL  	1998	4	29	EY2R9601127      	3	19961001	G	6110	5002X118	PIN             			PIPER 	PA28  	PA28R201T   	7102813	SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		764  	356  					AM1751		PIN CORRODED.						1	L	7	1 	3O				2A13    		5	C	P920	 
1998042900193	19980429	00193	GL  	1998	4	29	EY2R9601128      	3	19961001	G	6114	C4801C204	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	C2A34C204   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								767053		CORROSION FOUND ON HUB.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998042900194	19980429	00194	GL  	1998	4	29	EY2R9601129      	3	19961001	G	6110	A4001	DOWEL           			CESSNA	182   	182R        	2072731	CE  						MCAULY	2A34C	C2A34C204   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3080 	1478 					901245		DOWEL CORRODED.						1	L	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998042900195	19980429	00195	GL  	1998	4	29	EY2R9601130      	3	19961001	G	6114	C4716C58	HUB             			CESSNA	206   	206CESSNA   	2073302	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755346		CORROSION FOUND ON HUB.						1	H	7	1 	3O				A4CE    		5	C	P3EA	 
1998042900196	19980429	00196	GL  	1998	4	29	EY2R9601131      	3	19961001	G	6110	C3054	FERRULE         			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								777021		FERRULE FOUND CORRODED.						1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1998042900197	19980429	00197	GL  	1998	4	29	EY2R9601132      	3	19961001	G	6110	A1896	PIN             			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753558		CYLINDER PIN FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998042900198	19980429	00198	GL  	1998	4	29	EY2R9601133      	3	19961001	G	6110	A4001	DOWEL           			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753558		DOWEL CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998042900199	19980429	00199	GL  	1998	4	29	EY2R9601134      	3	19961001	G	6111	G80VA0	BLADE           			CESSNA	185   	185E        	2072816	CE  						MCAULY	D3A34	D3A34C403   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								861348		BLADE, SN BK472, FOUND CORRODED.						1	H	7	1 	3O				3A24    		5	C	P47GL	 
1998042900200	19980429	00200	GL  	1998	4	29	EY2R9601135      	3	19961001	G	6111	G80VA0	BLADE           			CESSNA	185   	185E        	2072816	CE  						MCAULY	D3A34	D3A34C403   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								861348		BLADE, SN BK434, FOUND CORRODED.						1	H	7	1 	3O				3A24    		5	C	P47GL	 
1998042900201	19980429	00201	GL  	1998	4	29	EY2R9601136      	3	19961001	G	6111	G80VA0	BLADE           			CESSNA	185   	185E        	2072816	CE  						MCAULY	D3A34	D3A34C403   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								861348		BLADE, SN BG318, FOUND CORRODED.						1	H	7	1 	3O				3A24    		5	C	P47GL	 
1998042900202	19980429	00202	GL  	1998	4	29	EY2R9601137      	3	19961001	G	6110	A1896	PIN             			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768730		CYLINDER PIN FOUND WITH CORROSION.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1998042900203	19980429	00203	GL  	1998	4	29	EY2R9601138      	3	19961001	G	6110	A4191	DOWEL           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	D3AF32C35   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768730		DOWEL CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1998042900204	19980429	00204	GL  	1998	4	29	EY2R9601139      	3	19961001	G	6111	S82NC2	BLADE           			CESSNA	310   	310K        	2074228	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN F73319YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900205	19980429	00205	GL  	1998	4	29	EY2R9601140      	3	19961001	G	6111	S82NC2	BLADE           			CESSNA	310   	310K        	2074228	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN F32952YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900206	19980429	00206	GL  	1998	4	29	EY2R9601141      	3	19961001	G	6111	S82NC2	BLADE           			CESSNA	310   	310K        	2074228	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN F32834YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900207	19980429	00207	GL  	1998	4	29	EY2R9601142      	3	19961001	G	6110	14B	BEARING         			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4516 						143G		BEARING CORRODED.						1	L	7	1 	3O				1A15    		5	C	P23EA	 
1998042900208	19980429	00208	GL  	1998	4	29	EY2R9601143      	3	19961001	G	6110	806	CYLINDER        			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4516 						143G		CYLINDER CORRODED.						1	L	7	1 	3O				1A15    		5	C	P23EA	 
1998042900209	19980429	00209	GL  	1998	4	29	EY2R9601144      	3	19961001	G	6110	8382	CLAMP           			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4516 						143G		CLAMP CORRODED.						1	L	7	1 	3O				1A15    		5	C	P23EA	 
1998042900210	19980429	00210	GL  	1998	4	29	EY2R9601145      	3	19961001	G	6110	14962	PILOT TUBE      			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1531 					H1786		CORROSION FOUND ON PILOT TUBES.  REMOVED AND REPLACED PILOT TUBES.						1	L	7	2 	3O				1A10    		5	C	P24EA	 
1998042900211	19980429	00211	GL  	1998	4	29	EY2R9601146      	3	19961001	G	6110	14962	PILOT TUBE      			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9880 	789  					H610		CORROSION FOUND ON PILOT TUBES.  REMOVED AND REPLACED PILOT TUBES.						1	L	7	2 	3O				1A10    		5	C	P24EA	 
1998042900212	19980429	00212	GL  	1998	4	29	EY2R9601147      	3	19961001	G	6110	83812	CLAMP           			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1531 					H1786		CLAMP CORRODED.						1	L	7	2 	3O				1A10    		5	C	P24EA	 
1998042900213	19980429	00213	GL  	1998	4	29	EY2R9601148      	3	19961001	G	6110	971	BEARING         			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1531 					H1786		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				1A10    		5	C	P24EA	 
1998042900214	19980429	00214	GL  	1998	4	29	EY2R9601149      	3	19961001	G	6110	971	BEARING         			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9880 	789  					H610		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				1A10    		5	C	P24EA	 
1998042900215	19980429	00215	GL  	1998	4	29	EY2R9601150      	3	19961001	G	6110	13333	BOLT            			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		BOLT FOUND CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1998042900216	19980429	00216	GL  	1998	4	29	EY2R9601151      	3	19961001	G	6110	13336	BOLT            			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		BOLT FOUND CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1998042900217	19980429	00217	GL  	1998	4	29	EY2R9601152      	3	19961001	G	6110	8382	CLAMP           			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		CLAMP FOUND CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1998042900218	19980429	00218	GL  	1998	4	29	EY2R9601153      	3	19961001	G	6110	971	BEARING         			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		SPLIT BEARING FOUND CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1998042900219	19980429	00219	GL  	1998	4	29	EY2R9601154      	3	19961001	G	6110	J2016	BEARING         			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2X	HCA2XK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J477		BEARING FOUND CORRODED.						1	L	7	1 	3O				1A15    		5	C	P908	 
1998042900220	19980429	00220	GL  	1998	4	29	EY2R9601155      	3	19961001	G	6110	971	BEARING         			BEECH 	80    	65A80       	1152808	CE  						HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1472 	944  					BJ468		SPLIT BEARING FOUND CORRODED.						1	L	7	2 	3O				3A20    		5	C	P6EA	 
1998042900221	19980429	00221	GL  	1998	4	29	EY2R9601156      	3	19961001	G	6111	T10173B8	BLADE           			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU16490		BLADE, SN B21030, FOUND CORRODED.						1	L	7	2 	4T				A24CE   		6	C	P15EA	 
1998042900222	19980429	00222	GL  	1998	4	29	EY2R9601157      	3	19961001	G	6110	3475A2	STOP COLLAR     			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9815 	1746 					BU5621		LOW STOP COLLAR FOUND WITH CORROSION.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998042900223	19980429	00223	GL  	1998	4	29	EY2R9601158      	3	19961001	G	6110	1851T	BEARING         			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		10073	2099 					FW559		BEARING FOUND CORRODED.						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1998042900224	19980429	00224	GL  	1998	4	29	EY2R9601159      	3	19961001	G	6111	LT10574FS	BLADE           			DORNER	DO228 	DO228*      		EU  						HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CD1876		BLADE, SN H05668, FOUND CORRODED.						1	H	7	2 	4T			RT	A16EU   		6	C	P40EA	 
1998042900225	19980429	00225	GL  	1998	4	29	EY2R9601160      	3	19961001	G	6111	LT10574FS	BLADE           			DORNER	DO228 	DO228*      		EU  						HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CD1876		BLADE, SN H05667, FOUND CORRODED.						1	H	7	2 	4T			RT	A16EU   		6	C	P40EA	 
1998042900226	19980429	00226	GL  	1998	4	29	EY2R9601161      	3	19961001	G	6111	LT10574FS	BLADE           			DORNER	DO228 	DO228*      		EU  						HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CD1876		BLADE, SN F58721, FOUND CORRODED.						1	H	7	2 	4T			RT	A16EU   		6	C	P40EA	 
1998042900227	19980429	00227	GL  	1998	4	29	EY2R9601162      	3	19961001	G	6110	2421	SOCKET SET SCREW			MOONEY	M20   	M20E        	5870212	SW  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CA132		PROP ASSY SOCKET SCREW CORRODED						1	L	7	1 	3O				2A3     		5	C	P920	 
1998042900228	19980429	00228	GL  	1998	4	29	EY2R9601163      	3	19961001	G	6114	220116	HUB             			BNORM 	BN2   	BN2B20      	1520302	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1999 					AU4803		CORROSION FOUND ON HUB.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1998042900229	19980429	00229	GL  	1998	4	29	EY2R9601164      	3	19961001	G	6110	2202	BEARING         			BNORM 	BN2   	BN2B20      	1520302	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1999 					AU4803		CORROSION FOUND ON SPLIT BEARING.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1998042900230	19980429	00230	GL  	1998	4	29	EY2R9601165      	3	19961001	G	6111	F7666A	BLADE           			PIPER 	PA28  	PA28R180    	7102809	SO  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN H57236, FOUND CORRODED.						1	L	7	1 	3O				2A13    		5	C	P920	 
1998042900231	19980429	00231	GL  	1998	4	29	EY2R9601166      	3	19961001	G	6110	3807	BOLT            													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			635  					AU7576		BOLT FOUND CORRODED.																5	C	P920	 
1998042900232	19980429	00232	GL  	1998	4	29	EY2R9601167      	3	19961001	G	6110	3807	BOLT            													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		616  						DN1712		BOLT FOUND CORRODED.																5	C	P920	 
1998042900233	19980429	00233	GL  	1998	4	29	EY2R9601168      	3	19961001	G	6110	3807	BOLT            													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			843  					DN1961		BOLT FOUND CORRODED.																5	C	P920	 
1998042900234	19980429	00234	GL  	1998	4	29	EY2R9601169      	3	19961001	G	6110	3807	BOLT            													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		903  						DN374		BOLT FOUND CORRODED.																5	C	P920	 
1998042900235	19980429	00235	GL  	1998	4	29	EY2R9601170      	3	19961001	G	6110	3807	BOLT            													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1048 	357  					DN921		BOLT FOUND CORRODED.																5	C	P920	 
1998042900236	19980429	00236	GL  	1998	4	29	EY2R9601171      	3	19961001	G	6110	3807	BOLT            													HARTZL	HCC2Y	HCC2YR4     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		804  						DN942		BOLT FOUND CORRODED.																5	C	P920	 
1998042900237	19980429	00237	NE  	1998	4	29	EY2R9601172      	3	19961001	G	6110	51171	CLAMP           			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5420 						HJ297		PROP ASSY COUNTERWEIGHT CLAMP FOUND CORRODED.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1998042900238	19980429	00238	GL  	1998	4	29	EY2R9601173      	3	19961001	G	6110	15941	SPRING          			PIPER 	PA31  	PA31P350    	7103111	SO  						HARTZL	HCI3Y	HCI3YR2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								F5177A		CORROSION FOUND ON FEATHERING SPRING.						1	L	7	2 	3O			RT	A8EA    		5	C	P33EA	 
1998042900239	19980429	00239	GL  	1998	4	29	EY2R9601174      	3	19961001	G	6110	971	SPLIT BEARING   			BEECH 	55    	95A55       	1152704	CE  						HARTZL	HCA3V	PHCA3VF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			307  					BR701		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				3A16    		5	C	P6EA	 
1998042900240	19980429	00240	GL  	1998	4	29	EY2R9601175      	3	19961101	G	6110	130035908	CAP SCREW       			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		21844	5889 					DRG418385		CAP SCREW FOUND CORRODED.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1998042900241	19980429	00241	GL  	1998	4	29	EY2R9601176      	3	19961101	G	6110	660706613	SLEEVE          			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		10721	5750 					DRG725489		CORROSION FOUND ON SLEEVE.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1998042900242	19980429	00242	GL  	1998	4	29	EY2R9601177      	3	19961101	G	6110	850000058	BALL SET        			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		10721	5750 					DRG725489		CORROSION FOUND ON BALL SET.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1998042900243	19980429	00243	GL  	1998	4	29	EY2R9601178      	3	19961101	G	6110		PROPELLER       			CESSNA	150   	150         	2071802	CE  						MCAULY	1A101	1A101HCM    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								G10243		CORROSION FOUND ON FIXED-PITCH PROPELLER.						1	H	7	1 	3O			NT	3A19    		5	N	P918	 
1998042900244	19980429	00244	GL  	1998	4	29	EY2R9601179      	3	19961101	G	6110		PROPELLER       			CESSNA	140   	140         	2071602	CE  						MCAULY	1B90	1B90CM      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								49746		CORROSION FOUND ON FIXED-PITCH PROPELLER.						1	H	7	1 	3O			NC	A768    		5	N	P842	 
1998042900245	19980429	00245	GL  	1998	4	29	EY2R9601180      	3	19961101	G	6110		PROPELLER       			CESSNA	140   	140         	2071602	CE  						MCAULY	1B90	1B90CM      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								24403		CORROSION FOUND ON FIXED-PITCH PROPELLER.						1	H	7	1 	3O			NC	A768    		5	N	P842	 
1998042900246	19980429	00246	GL  	1998	4	29	EY2R9601181      	3	19961101	G	6110		PROPELLER       			BBAVIA	7     	7AC         	2110102	SW  						MCAULY	1B90	1B90CM      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								33791		CORROSION FOUND ON FIXED-PITCH PROPELLER.						1	H	7	1 	3O				A759    		5	N	P842	 
1998042900247	19980429	00247	GL  	1998	4	29	EY2R9601182      	3	19961101	G	6110		PROPELLER       			PIPER 	J3    	PA11        	7101102	SO  						MCAULY	1B90	1B90CM      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								28425		CORROSION FOUND ON FIXED-PITCH PROPELLER.						1	H	7	1 	3O				A691    		5	N	P842	 
1998042900248	19980429	00248	GL  	1998	4	29	EY2R9601183      	3	19961101	G	6110		PROPELLER       			GULSTM	AA5   	AA5         	0631410	SO  						MCAULY	1C172	1C172*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								P71063		CORROSION FOUND ON FIXED-PITCH PROPELLER.						1	L	7	1 	3O				A16EA   		5	N	P910	 
1998042900249	19980429	00249	CE  	1998	4	29	EY2R9601184      	3	19961101	G	6114	279100	HUB             			BEECH 	50    	50          	1152502	CE  						BEECH	279	279100      	CE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1485		HUB, SN 78, FOUND CORRODED.						1	L	7	2 	3O				5A4     		5	C	P885	 
1998042900250	19980429	00250	CE  	1998	4	29	EY2R9601185      	3	19961101	G	6111	27920798	BLADE           			BEECH 	50    	50          	1152502	CE  						BEECH	279	279100      	CE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1485		BLADE, SN 81160, FOUND CORRODED.						1	L	7	2 	3O				5A4     		5	C	P885	 
1998042900251	19980429	00251	CE  	1998	4	29	EY2R9601186      	3	19961101	G	6111	27920798	BLADE           			BEECH 	50    	50          	1152502	CE  						BEECH	279	279100      	CE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								1485		BLADE, SN 81164, FOUND CORRODED.						1	L	7	2 	3O				5A4     		5	C	P885	 
1998042900252	19980429	00252	GL  	1998	4	29	EY2R9601187      	3	19961101	G	6110	B2417	COVER PLATE     			BEECH 	35    	B35         	1151506	CE  						MCAULY	2A36C	2A36C23     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								696231		CORROSION FOUND ON SPLIT COVER PLATE.						1	L	7	1 	3O				A777    		5	C	P880	 
1998042900253	19980429	00253	GL  	1998	4	29	EY2R9601188      	3	19961101	G	6114	C2835C23	HUB             			BEECH 	35    	V35B        	1151548	CE  						MCAULY	2A36C	2A36C23     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								66981		HUB FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P880	 
1998042900254	19980429	00254	GL  	1998	4	29	EY2R9601189      	3	19961101	G	6110	C4904	NUT             			BEECH 	35    	V35B        	1151548	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								674507		CORROSION FOUND ON NUT.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1998042900255	19980429	00255	GL  	1998	4	29	EY2R9601190      	3	19961101	G	6114	D6602C76	HUB             			BEECH 	35    	V35B        	1151548	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								674507		CORROSION FOUND ON HUB.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1998042900256	19980429	00256	GL  	1998	4	29	EY2R9601191      	3	19961101	G	6110	C3411	BEARING         			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2993 	1650 					814245		BEARING RACE CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1998042900257	19980429	00257	GL  	1998	4	29	EY2R9601192      	3	19961101	G	6110	C3903	RETAINER        			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2993 	1650 					814245		SPLIT RETAINER FOUND CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1998042900258	19980429	00258	GL  	1998	4	29	EY2R9601193      	3	19961101	G	6110	C2987	BEARING         			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								702046		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900259	19980429	00259	GL  	1998	4	29	EY2R9601194      	3	19961101	G	6110	C2987	BEARING         			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4020 	1379 					796457		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900260	19980429	00260	GL  	1998	4	29	EY2R9601195      	3	19961101	G	6110	C2987	BEARING         			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4020 	1379 					799790		RETAIN BEARING FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900261	19980429	00261	GL  	1998	4	29	EY2R9601196      	3	19961101	G	6114	D5892C93	HUB             			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4020 	1379 					799790		CORROSION FOUND ON HUB.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900262	19980429	00262	GL  	1998	4	29	EY2R9601197      	3	19961101	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								911090		SCREW CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900263	19980429	00263	GL  	1998	4	29	EY2R9601198      	3	19961101	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2490 						911608		SCREW CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900264	19980429	00264	GL  	1998	4	29	EY2R9601199      	3	19961101	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2791 						910787		SCREW CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900265	19980429	00265	GL  	1998	4	29	EY2R9601200      	3	19961101	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2995 						911606		SCREW CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900266	19980429	00266	NE  	1998	4	29	EY2R9601201      	3	19961101	G	6110	C5328	FEATHER SPRING  			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		10750	828  					881053		CORROSION FOUND ON FEATHER SPRING.						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1998042900267	19980429	00267	NE  	1998	4	29	EY2R9601202      	3	19961101	G	6110	A163563	SCREW           			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2584 						911019		SCREW CORRODED.						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1998042900268	19980429	00268	NE  	1998	4	29	EY2R9601203      	3	19961101	G	6110	B5162	REVRS STOP SCREW			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2584 						911016		CORROSION FOUND ON REVERSE STOP SCREW.						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1998042900269	19980429	00269	NE  	1998	4	29	EY2R9601204      	3	19961101	G	6110	D6174	CYLINDER        			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2584 						911016		CYLINDER CORRODED.						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1998042900270	19980429	00270	NE  	1998	4	29	EY2R9601205      	3	19961101	G	6110	D6174	CYLINDER        			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2584 						911019		CYLINDER CORRODED.						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1998042900271	19980429	00271	GL  	1998	4	29	EY2R9601206      	3	19961101	G	6110	C6263	CYLINDER        			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	C2A34C204   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1771 						767948		CYLINDER CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998042900272	19980429	00272	GL  	1998	4	29	EY2R9601207      	3	19961101	G	6110	C3411	BEARING         			CESSNA	180   	180K        	2072624	CE  						MCAULY	2A34C	C2A34C204   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								765710		CORROSION FOUND ON BEARING RACE.						1	H	7	1 	3O				5A6     		5	C	P3EA	 
1998042900273	19980429	00273	GL  	1998	4	29	EY2R9601208      	3	19961101	G	6110	A16349	BEARING         			CESSNA	182   	182F        	2072714	CE  						MCAULY	3A32C	D3A32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		676  						910981		BALL BEARING CORRODED.						1	H	7	1 	3O			NT	3A13    		5	C	P21EA	 
1998042900274	19980429	00274	GL  	1998	4	29	EY2R9601209      	3	19961101	G	6111	90DFA10	BLADE           			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		BLADE, SN 124558, FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900275	19980429	00275	GL  	1998	4	29	EY2R9601210      	3	19961101	G	6111	90DFA10	BLADE           			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		BLADE, SN 125221, FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900276	19980429	00276	GL  	1998	4	29	EY2R9601211      	3	19961101	G	6111	90DFA10	BLADE           			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		BLADE, SN 125242, FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900277	19980429	00277	GL  	1998	4	29	EY2R9601212      	3	19961101	G	6110	A3125	SPRING          			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		CORROSION FOUND ON PITCH RETURN SPRING						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998011500001	19980115	00001	GL  	1998	1	15	EY2R9601213      	3	19961101	G	6110	A4002	PROPELLER       			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		PROPELLER ASSY IS CORRODED						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900278	19980429	00278	GL  	1998	4	29	EY2R9601214      	3	19961101	G	6110	A4738	PISTON LINK PIN 			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		CORROSION FOUND ON PISTON LINK PIN.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900279	19980429	00279	GL  	1998	4	29	EY2R9601215      	3	19961101	G	6110	B48202	ACTUATOR PIN    			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		ACT PIN ASSEMBLY FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900280	19980429	00280	GL  	1998	4	29	EY2R9601216      	3	19961101	G	6110	C3903	RETAINER        			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		CORROSION FOUND ON SPLIT RETAINER.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900281	19980429	00281	GL  	1998	4	29	EY2R9601217      	3	19961101	G	6110	C4784	PISTON          			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		PISTON CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900282	19980429	00282	GL  	1998	4	29	EY2R9601218      	3	19961101	G	6110	C5264	CYLINDER        			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		CYLINDER CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900283	19980429	00283	GL  	1998	4	29	EY2R9601219      	3	19961101	G	6110	C5270	BEARING         			CESSNA	210   	T210M       	2073451	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7911143		RETAIN BEARING CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900284	19980429	00284	GL  	1998	4	29	EY2R9601220      	3	19961101	G	6110	1303A	BEARING         			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8435 	1391 					1680F		BEARING CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1998042900285	19980429	00285	GL  	1998	4	29	EY2R9601221      	3	19961101	G	6110	1303A	BEARING         			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8435 	1391 					1681F		BEARING CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1998042900286	19980429	00286	GL  	1998	4	29	EY2R9601222      	3	19961101	G	6110	853	SPRING          			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8435 	1391 					1680F		CORROSION FOUND ON FEATHERING SPRING.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1998042900287	19980429	00287	GL  	1998	4	29	EY2R9601223      	3	19961101	G	6110	853	SPRING          			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8435 	1391 					1681F		CORROSION FOUND ON FEATHERING SPRING.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1998042900288	19980429	00288	GL  	1998	4	29	EY2R9601224      	3	19961101	G	6110	971	BEARING         			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2V	HCA2V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			430  					J1625		CORROSION FOUND ON SPLIT BEARING.						1	L	7	1 	3O				1A15    		5	C	P24EA	 
1998042900289	19980429	00289	GL  	1998	4	29	EY2R9601225      	3	19961101	G	6110	971	SPLIT BEARING   			PIPER 	PA24  	PA24250     	7102404	SO  						HARTZL	HCA2V	HCA2V*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								J263		CORROSION FOUND ON SPLIT BEARING.						1	L	7	1 	3O				1A15    		5	C	P24EA	 
1998042900290	19980429	00290	GL  	1998	4	29	EY2R9601226      	3	19961101	G	6110	83888	CLAMP           			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										CLAMPS, SN'S EK395, EK359, FOUND CORRODED.						1	L	7	2 	3T				3A20    		6	C	P15EA	 
1998042900291	19980429	00291	GL  	1998	4	29	EY2R9601227      	3	19961101	G	6111	T10282N4	BLADE           			AIRTRC	AT400 	AT400       	0390202	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE, SN H44122, FOUND CORRODED.						1	L	7	1 	3T				A9SW    		6	C	P15EA	 
1998042900292	19980429	00292	GL  	1998	4	29	EY2R9601228      	3	19961101	G	6110	1851T	BEARING         			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		14123	3404 					BU14783		BEARING CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1998042900293	19980429	00293	GL  	1998	4	29	EY2R9601229      	3	19961101	G	6110	1851T	BEARING         			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		24237	2961 					BU7083		BEARING CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1998042900294	19980429	00294	GL  	1998	4	29	EY2R9601230      	3	19961101	G	6110	1851T	BEARING         			ISRAEL	101   	ARAVA101    		EU  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU7523		BEARING CORRODED.						1	H	7	2 	3T				A32EU   		6	C	P15EA	 
1998042900295	19980429	00295	GL  	1998	4	29	EY2R9601231      	3	19961101	G	6110	83867	CLAMP           			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		24237	2961 					BU7083		CLAMPS, SN'S EF2929, EF8442, AND EF9704, FOUND CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1998042900296	19980429	00296	GL  	1998	4	29	EY2R9601232      	3	19961101	G	6110	338614H	BOLT            			BEECH 	300   	300BEECH    	1152930	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3613 	815  					FW842		BOLT CORRODED.						2	L	7	2 	4T				A24CE   		6	C	P56GL	 
1998042900297	19980429	00297	GL  	1998	4	29	EY2R9601233      	3	19961101	G	6114	220117	HUB             			CESSNA	172   	172         	2072402	CE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH27570		HUB CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P920	 
1998042900298	19980429	00298	GL  	1998	4	29	EY2R9601234      	3	19961101	G	6114	22013	HUB             			PIPER 	PA28  	PA28*       		SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH5946		HUB CORRODED.						1	L	7	1 	3O				2A13    		5	C	P920	 
1998042900299	19980429	00299	GL  	1998	4	29	EY2R9601235      	3	19961101	G	6111	F7666A	BLADE           			CESSNA	172   	172         	2072402	CE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH27570		BLADE, SN F52834, FOUND CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P920	 
1998042900300	19980429	00300	GL  	1998	4	29	EY2R9601236      	3	19961101	G	6111	F7666A	BLADE           			CESSNA	172   	172         	2072402	CE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH27570		BLADE, SN F52931, FOUND CORRODED.						1	H	7	1 	3O			NT	3A12    		5	C	P920	 
1998042900301	19980429	00301	GL  	1998	4	29	EY2R9601237      	3	19961101	G	6114	220117	HUB             			PIPER 	PA32  	PA32301     	7103207	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH7157		HUB FOUND CORRODED.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1998042900302	19980429	00302	GL  	1998	4	29	EY2R9601238      	3	19961101	G	6110	2202	BEARING         			PIPER 	PA32  	PA32301     	7103207	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH7157		CORROSION FOUND ON SPLIT BEARING.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1998042900303	19980429	00303	GL  	1998	4	29	EY2R9601239      	3	19961101	G	6110	2202	BEARING         			BNORM 	BN2   	BN2         	1520202	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU5625		CORROSION FOUND ON SPLIT BEARING.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1998042900304	19980429	00304	GL  	1998	4	29	EY2R9601240      	3	19961101	G	6110	2202	BEARING         			BNORM 	BN2   	BN2         	1520202	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU5967		CORROSION FOUND ON SPLIT BEARING.						1	H	7	2 	3O				A17EU   		5	C	P920	 
1998042900305	19980429	00305	GL  	1998	4	29	EY2R9601241      	3	19961101	G	6110	2202	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP6431		CORROSION FOUND ON SPLIT BEARING.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998042900306	19980429	00306	GL  	1998	4	29	EY2R9601242      	3	19961201	G	6114	D7015C87	HUB             			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1507 						7910597		HUB FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900307	19980429	00307	GL  	1998	4	29	EY2R9601243      	3	19961201	G	6110	C7036	LOCKNUT         			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1507 						7910597		CORROSION FOUND ON LOCKNUT.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900308	19980429	00308	GL  	1998	4	29	EY2R9601244      	3	19961201	G	6110	B4459	ACT PIN         			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1507 						7910597		ACT. PIN RUSTED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900309	19980429	00309	GL  	1998	4	29	EY2R9601245      	3	19961201	G	6111	S82NC2	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								694041		BLADE, SN K56449YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900310	19980429	00310	GL  	1998	4	29	EY2R9601246      	3	19961201	G	6111	S82NC2	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								694041		BLADE, SN K56826YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900311	19980429	00311	GL  	1998	4	29	EY2R9601247      	3	19961201	G	6111	S82NC4	BLADE           			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								737982		BLADE, SN F40087YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900312	19980429	00312	GL  	1998	4	29	EY2R9601248      	3	19961201	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1223 					741352		NR 1 SOCKET FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900313	19980429	00313	GL  	1998	4	29	EY2R9601249      	3	19961201	G	6110	C2987	RACE            			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1223 					741352		CORROSION FOUND ON RACE.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900314	19980429	00314	GL  	1998	4	29	EY2R9601250      	3	19961201	G	6110	C40603	PISTON          			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								755780		PISTON CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900315	19980429	00315	GL  	1998	4	29	EY2R9601251      	3	19961201	G	6111	C2987	BEARING         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746944		BLADE BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900316	19980429	00316	GL  	1998	4	29	EY2R9601252      	3	19961201	G	6110	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746944		FERRULE CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900317	19980429	00317	GL  	1998	4	29	EY2R9601253      	3	19961201	G	6110	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746944		FERRULE CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900318	19980429	00318	GL  	1998	4	29	EY2R9601254      	3	19961201	G	6110	C3475	RETAIN NUT      			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746944		RETAIN NUT FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900319	19980429	00319	GL  	1998	4	29	EY2R9601255      	3	19961201	G	6110	C40603	PISTON          			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746953		PISTON CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900320	19980429	00320	GL  	1998	4	29	EY2R9601256      	3	19961201	G	6110	C3475	RETAIN NUT      			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746953		RETAIN NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900321	19980429	00321	GL  	1998	4	29	EY2R9601257      	3	19961201	G	6110	C3475	RETAIN NUT      			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746953		RETAIN NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900322	19980429	00322	GL  	1998	4	29	EY2R9601258      	3	19961201	G	6110	C3475	RETAIN NUT      			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746953		RETAIN NUT CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900323	19980429	00323	GL  	1998	4	29	EY2R9601259      	3	19961201	G	6111	C2987	BEARING         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								746953		BLADE BEARING FOUND CORRODED.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998042900324	19980429	00324	GL  	1998	4	29	EY2R9601260      	3	19961201	G	6111	PROPELLER	RETAINERS       			CESSNA	402   	402C        	207590R	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								785572		BLADES,  SN'S F44301YS, F44956YS,  AND F44460YS, FOUND CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900325	19980429	00325	GL  	1998	4	29	EY2R9601261      	3	19961201	G	6111	S90LF0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								860386		BLADE, SN C31669YS, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998042900326	19980429	00326	GL  	1998	4	29	EY2R9601262      	3	19961201	G	6110	C4458	ACT PIN         			CESSNA	337   	337A        	2075704	CE  						MCAULY	2AF34C	D2AF34C59   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2250 						693055		ACT. PIN FOUND RUSTED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998042900327	19980429	00327	GL  	1998	4	29	EY2R9601263      	3	19961201	G	6114	D4885	HUB             			CESSNA	337   	337A        	2075704	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2250 						653785		HUB FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998042900328	19980429	00328	GL  	1998	4	29	EY2R9601264      	3	19961201	G	6111	L76C0	BLADE           			CESSNA	337   	337A        	2075704	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2250 						653785		BLADE, SN D2514YS, FOUND CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998042900329	19980429	00329	GL  	1998	4	29	EY2R9601265      	3	19961201	G	6110	C4905	LOCKNUT         			CESSNA	337   	337A        	2075704	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2250 						653785		LOCKNUT CORRODED.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998042900330	19980429	00330	GL  	1998	4	29	EY2R9601266      	3	19961201	G	6110	C2987	RACE            			CESSNA	206   	P206C       	2073312	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			512  					692219		RACE CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1998042900331	19980429	00331	GL  	1998	4	29	EY2R9601267      	3	19961201	G	6114	D5858C404	HUB             			CESSNA	206   	U206        	2073306	CE  						MCAULY	D3A34	D3A34C404   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			2643 					851392		HUB CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P47GL	 
1998042900332	19980429	00332	GL  	1998	4	29	EY2R9601268      	3	19961201	G	6110	C5270	BEARINGS        			CESSNA	206   	U206        	2073306	CE  						MCAULY	D3A34	D3A34C404   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			2643 					851392		BEARINGS FOUND CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P47GL	 
1998042900333	19980429	00333	GL  	1998	4	29	EY2R9601269      	3	19961201	G	6110	C3903	RETAINERS       			CESSNA	206   	U206        	2073306	CE  						MCAULY	D3A34	D3A34C404   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			2643 					851392		RETAINERS FOUND CORRODED.						1	H	7	1 	3O				A4CE    		5	C	P47GL	 
1998042900334	19980429	00334	GL  	1998	4	29	EY2R9601270      	3	19961201	G	6111	T10173E8	BLADE           			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2510		BLADE, SN B51837, FOUND CORRODED.						1	L	7	2 	4T				A24CE   		6	C	P15EA	 
1998042900335	19980429	00335	GL  	1998	4	29	EY2R9601271      	3	19961201	G	6110	2202	BEARING         			PIPER 	PA32  	PA32300     	7103212	SO  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3331 						CH12928		BEARING FOUND CORRODED.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1998042900336	19980429	00336	GL  	1998	4	29	EY2R9601272      	3	19961201	G	6111	F8475D4	BLADE           			PIPER 	PA32  	PA32300     	7103212	SO  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3331 						CH12928		SHANK FOUND CORRODED.						1	L	7	1 	3O				A3SO    		5	C	P920	 
1998042900337	19980429	00337	GL  	1998	4	29	EY2R9601273      	3	19961201	G	6110	C7036	NUT             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6108 						753019		NUT CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900338	19980429	00338	GL  	1998	4	29	EY2R9601274      	3	19961201	G	6111	T10173E8	BLADE           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2510		BLADE, SN B51384, FOUND CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998042900339	19980429	00339	GL  	1998	4	29	EY2R9601275      	3	19961201	G	6111	T10173E8	BLADE           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2510		BLADE, SN B51383, FOUND CORRODED						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998042900340	19980429	00340	GL  	1998	4	29	EY2R9601276      	3	19961201	G	6111	T10173E8	BLADE           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2491		BLADE, SN B51827, FOUND CORRODED						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998042900341	19980429	00341	GL  	1998	4	29	EY2R9601277      	3	19961201	G	6111	T10173E8	BLADE           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2491		BLADE, SN B51441, FOUND CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998042900342	19980429	00342	GL  	1998	4	29	EY2R9601278      	3	19961201	G	6111	T10173E8	BLADE           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2491		BLADE, SN B51073, FOUND CORRODED.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998042900343	19980429	00343	GL  	1998	4	29	EY2R9601279      	3	19961201	G	6111	90UMB0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			55   					776790		BLADE SHANK, SN K76136, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1998042900344	19980429	00344	GL  	1998	4	29	EY2R9601280      	3	19961201	G	6111	90UMB0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			55   					776790		BLADE SHANK, SN K76140,  FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1998042900345	19980429	00345	GL  	1998	4	29	EY2R9601281      	3	19961201	G	6111	90UMB0	BLADE           			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			55   					776790		BLADE SHANK, SN K76153, FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1998042900346	19980429	00346	GL  	1998	4	29	EY2R9601282      	3	19961201	G	6111	90DFA10	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	2A34C	D2A34C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815622		BLADE, SN BH469, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P3EA	 
1998042900347	19980429	00347	GL  	1998	4	29	EY2R9601283      	3	19961201	G	6111	90DFA10	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	2A34C	D2A34C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815622		BLADE, SN BH489, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P3EA	 
1998042900348	19980429	00348	GL  	1998	4	29	EY2R9601284      	3	19961201	G	6111	90DFA10	BLADE           			CESSNA	210   	210         	2073402	CE  						MCAULY	2A34C	D2A34C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815622		BLADE, SN BH500, FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P3EA	 
1998042900349	19980429	00349	GL  	1998	4	29	EY2R9601285      	3	19961201	G	6114	D5858C402	HUB             			CESSNA	210   	210         	2073402	CE  						MCAULY	2A34C	D2A34C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815622		HUB FOUND CORRODED.						1	H	7	1 	3O			RT	3A21    		5	C	P3EA	 
1998042900350	19980429	00350	GL  	1998	4	29	EY2R9601286      	3	19961201	G	6114	D5926	HUB             			BOEING	75    	A75N1       	1380134	CE  						MCAULY	41D59	41D5926     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AC4215977		HUB FOUND CORRODED.						1	Q	7	1 	3R				A743    		5	N	781	 
1998042900351	19980429	00351	GL  	1998	4	29	EY2R9601287      	3	19961201	G	6111	MC42	BLADE           			BOEING	75    	A75N1       	1380134	CE  						MCAULY	41D59	41D5926     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AC4215977		BLADE, SN 424274, FOUND CORRODED.						1	Q	7	1 	3R				A743    		5	N	781	 
1998042900352	19980429	00352	GL  	1998	4	29	EY2R9601288      	3	19961201	G	6111	S82NC4	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								714662		BLADE, SN F26105YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900353	19980429	00353	GL  	1998	4	29	EY2R9601289      	3	19961201	G	6111	S82NC4	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								714662		BLADE, SN F26088YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900354	19980429	00354	GL  	1998	4	29	EY2R9601290      	3	19961201	G	6111	S82NC4	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								714662		BLADE, SN F26156YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900355	19980429	00355	GL  	1998	4	29	EY2R9601291      	3	19961201	G	6111	T10282N4	BLADE           													HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BUA19181		BLADE, SHANK AREA, SN H76638, FOUND CORRODED.																6	C	P15EA	 
1998042900356	19980429	00356	GL  	1998	4	29	EY2R9601292      	3	19961201	G	6111	T10282N4	BLADE           													HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BUA19181		BLADE, SHANK AREA, SN H76629, FOUND CORRODED.																6	C	P15EA	 
1998042900357	19980429	00357	GL  	1998	4	29	EY2R9601293      	3	19961201	G	6111	T10282N4	BLADE           													HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BUA19181		BLADE, SN H76636, SHANK AREA, FOUND CORRODED.																6	C	P15EA	 
1998042900358	19980429	00358	GL  	1998	4	29	EY2R9601294      	3	19961201	G	6111		BLADE           			PIPER 	PA23  	PA23        	7102302	SO  						HARTZL	HC82X	HC82XL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								K2314N		BLADE,  SN'S 103647, 104122, FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P878	 
1998042900359	19980429	00359	GL  	1998	4	29	EY2R9601295      	3	19961201	G	6110	C4451	FERRULE         			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5217 	1299 					696110		FERRULE FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900360	19980429	00360	GL  	1998	4	29	EY2R9601296      	3	19961201	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5217 	1299 					696110		HUB FOUND WITH CORROSION.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900361	19980429	00361	GL  	1998	4	29	EY2R9601297      	3	19961201	G	6110	C4451	FERRULE         			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2895 	1295 					797157		FERRULE FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900362	19980429	00362	GL  	1998	4	29	EY2R9601298      	3	19961201	G	6111	S82NC55	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2895 	1295 					797157		BLADE, SN F84468YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900363	19980429	00363	GL  	1998	4	29	EY2R9601299      	3	19961201	G	6111	S82NC55	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2895 	1295 					797157		BLADE, SN F90225YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900364	19980429	00364	GL  	1998	4	29	EY2R9601300      	3	19961201	G	6111	S82NC55	BLADE           			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2895 	1295 					797157		BLADE, SN K95983YS, FOUND CORRODED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998010700013	19980107	00013	GL  	1998	1	7	EY2R9601301      	3	19961201	G	6110	C3550	CYLINDER        			CESSNA	310   	310L        	2074230	CE  						MCAULY	D3AF32	D3AF32C87   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1234 	436  					728522		CYLINDER FOUND WITH CORROSION.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998010700014	19980107	00014	GL  	1998	1	7	EY2R9601302      	3	19961201	G	6110	C3550	CYLINDER        			CESSNA	310   	310L        	2074230	CE  						MCAULY	D3AF32	D3AF32C87   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1234 	436  					728509		CYLINDER FOUND WITH CORROSION.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998042900365	19980429	00365	GL  	1998	4	29	EY2R9601303      	3	19961201	G	6110	C5270	BEARING         			CESSNA	210   	T210*       		CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7810149		BEARING RACE FOUND CORRODED.						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998042900366	19980429	00366	GL  	1998	4	29	EY2R9601304      	3	19961201	G	6110	B5177	SCREW           			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2887 						911091		SCREW CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900367	19980429	00367	GL  	1998	4	29	EY2R9601305      	3	19961201	G	6110	D5010	CYLINDER        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2887 						911091		CYLINDER CORRODED.						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998042900368	19980429	00368	GL  	1998	4	29	EY2R9601306      	3	19961201	G	6110	C5270	BEARING         			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1872 						910156		BEARING CORRODED.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1998042900369	19980429	00369	GL  	1998	4	29	EY2R9601307      	3	19961201	G	6114	D7019C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3692 	1168 					738767		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998042900370	19980429	00370	GL  	1998	4	29	EY2R9601308      	3	19961201	G	6110	C7036	NUT             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3692 	1168 					738767		NUT CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998042900371	19980429	00371	GL  	1998	4	29	EY2R9601309      	3	19961201	G	6110	1826	SPRING          			SWRNGN	SA226 	SA226AT     	8780405	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV4526		SPRING CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA	 
1998042900372	19980429	00372	GL  	1998	4	29	EY2R9601310      	3	19961201	G	6110	3498	SPRING          			SWRNGN	SA226 	SA226AT     	8780405	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV4526		SPRING CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA	 
1998042900373	19980429	00373	GL  	1998	4	29	EY2R9601311      	3	19961201	G	6110	1851T	BEARING         			SWRNGN	SA226 	SA226AT     	8780405	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV4526		BEARING CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA	 
1998042900374	19980429	00374	GL  	1998	4	29	EY2R9601312      	3	19961201	G	6110	83867	CLAMP           			SWRNGN	SA226 	SA226AT     	8780405	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV4526		CLAMP CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA	 
1998042900375	19980429	00375	GL  	1998	4	29	EY2R9601313      	3	19961201	G	6111	M10876ASK	BLADE           			STBROS	SD3   	SD360       	8100606	EU  						HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		13167	4311 					EV712		BLADE, SN F91132, FOUND CORRODED.						2	H	7	2 	4T				A41EU   		6	C	P44GL	 
1998042900376	19980429	00376	NE  	1998	4	29	EY2R9601314      	3	19961201	G	6110	792	BEARING         			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4539 						HJ241		PROP ASSY BEARING CORRODED.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1998042900377	19980429	00377	GL  	1998	4	29	EY2R9601315      	3	19961201	G	6110	1851T	BEARING         			SWRNGN	SA226 	SA226AT     	8780405	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV2796		BEARING CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA	 
1998042900378	19980429	00378	GL  	1998	4	29	EY2R9601316      	3	19961201	G	6114	D4344C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795316		HUB FOUND CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998042900379	19980429	00379	GL  	1998	4	29	EY2R9601317      	3	19961201	G	6110	C2987	RACES           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795316		RACES CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998042900380	19980429	00380	GL  	1998	4	29	EY2R9601318      	3	19961201	G	6110	C2987	RACES           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								794515		RACES CORRODED.						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998042900381	19980429	00381	GL  	1998	4	29	EY2R9601319      	3	19961201	G	6110	C2987	RACES           			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5695 	772  					795378		RACES CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900382	19980429	00382	GL  	1998	4	29	EY2R9601320      	3	19961201	G	6110	C3903	KEEPERS         			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2993 	1650 					814976		CORROSION FOUND ON KEEPERS.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1998042900383	19980429	00383	GL  	1998	4	29	EY2R9601321      	3	19961201	G	6110	C3411	RACES           			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2993 	1650 					814976		RACES CORRODED.						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1998042900384	19980429	00384	GL  	1998	4	29	EY2R9601322      	3	19961201	G	6110	C3903	KEEPERS         			CESSNA	401   	401         	207590C	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			866  					820094		CORROSION FOUND ON KEEPERS.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900385	19980429	00385	GL  	1998	4	29	EY2R9601323      	3	19961201	G	6110	C3411	RACES           			CESSNA	401   	401         	207590C	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			866  					820094		RACES CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900386	19980429	00386	GL  	1998	4	29	EY2R9601324      	3	19961201	G	6110	B3490	RACES           			CESSNA	401   	401         	207590C	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			866  					820094		RACES CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998042900387	19980429	00387	GL  	1998	4	29	EY2R9601325      	3	19961201	G	6110	C5270	RACES           			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	D3A32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1704 						931567		RACES CORRODED.						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1998042900388	19980429	00388	GL  	1998	4	29	EY2R9601326      	3	19961201	G	6114	24772R	HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP6434		HUB FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998042900389	19980429	00389	GL  	1998	4	29	EY2R9601327      	3	19961201	G	6110	2202	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP6434		BEARING CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998042900390	19980429	00390	GL  	1998	4	29	EY2R9601328      	3	19961201	G	6111	F84657R	BLADE           			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP6434		BLADE, SN C37674, FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998042900391	19980429	00391	GL  	1998	4	29	EY2R9601329      	3	19961201	G	6111	F84657R	BLADE           			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP6434		BLADE, SN C38521, FOUND CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998042900392	19980429	00392	GL  	1998	4	29	EY2R9601330      	3	19961201	G	6110	2202	RACES           			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP7417		RACES CORRODED.						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998042900393	19980429	00393	GL  	1998	4	29	EY2R9601331      	3	19961201	G	6111	FC84756	BLADE           			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			147  					AN2518		BLADE, SN E50359, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P920	 
1998042900394	19980429	00394	GL  	1998	4	29	EY2R9601332      	3	19961201	G	6111	FC84756	BLADE           			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			147  					AN2518		BLADE, SN E50404, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P920	 
1998042900395	19980429	00395	GL  	1998	4	29	EY2R9601333      	3	19961201	G	6110	2202	BEARINGS        			BEECH 	55    	E55         	1152732	CE  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			147  					AN2518		BEARINGS CORRODED.						1	L	7	2 	3O				3A16    		5	C	P920	 
1998042900396	19980429	00396	GL  	1998	4	29	EY2R9601334      	3	19961201	G	6110	1851T	BEARINGS        			DHAV  	DHC6  	DHC6300     		EA  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			2938 					BU12633		BEARINGS CORRODED.						1	H	7	2 	3T				A9EA    		6	C	P15EA	 
1998042900397	19980429	00397	GL  	1998	4	29	EY2R9601335      	3	19961201	G	6110	2202	BEARINGS        			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU1601		BEARINGS CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P920	 
1998042900398	19980429	00398	GL  	1998	4	29	EY2R9601336      	3	19961201	G	6110	2202	BEARINGS        			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU1577		BEARINGS CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P920	 
1998042900399	19980429	00399	GL  	1998	4	29	EY2R9601337      	3	19961201	G	6110	1851	BEARING         			SWRNGN	SA226 	SA226AT     	8780405	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BV3013		BEARING CORRODED.						2	L	7	2 	4T			RT	A5SW    		6	C	P15EA	 
1998042900400	19980429	00400	GL  	1998	4	29	EY2R9601338      	3	19961201	G	6114	2201	HUB             			PIPER 	PA28  	PA28*       		SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH19579		CORROSION FOUND ON HUB.						1	L	7	1 	3O				2A13    		5	C	P920	 
1998042900401	19980429	00401	GL  	1998	4	29	EY2R9601339      	3	19961201	G	6114	2201	HUB             			PIPER 	PA34  	PA34*       		SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN3046		CORROSION FOUND ON HUB.						1	L	7	2 	3O			RT	A7SO    		5	C	P920	 
1998042900402	19980429	00402	GL  	1998	4	29	EY2R9601340      	3	19961201	G	6114	2201	HUB             			PIPER 	PA34  	PA34*       		SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN2055		CORROSION FOUND ON HUB.						1	L	7	2 	3O			RT	A7SO    		5	C	P920	 
1998042900403	19980429	00403	GL  	1998	4	29	EY2R9601341      	3	19961201	G	6114	C5480C66	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								68889		CORROSION FOUND ON HUB.						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998042900404	19980429	00404	GL  	1998	4	29	EY2R9601342      	3	19961201	G	6110	C4450	FERRULES        			CESSNA	310   	310K        	2074228	CE  						MCAULY	2AF34C	D2AF34C81   	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								751494		FERRULES CORRODED.						1	L	7	2 	3O				3A10    		5	C	P5EA	 
1998042900405	19980429	00405	GL  	1998	4	29	EY2R9601343      	3	19961201	G	6110	2202	BEARING         			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN4587		BEARING CORRODED.						1	L	7	2 	3O				A7SO    		5	C	P920	 
1998042900406	19980429	00406	GL  	1998	4	29	EY2R9601344      	3	19961201	G	6110	24913	ROD             			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN4587		CORROSION FOUND O PITCH CHANGE ROD.						1	L	7	2 	3O				A7SO    		5	C	P920	 
1998042900407	19980429	00407	GL  	1998	4	29	EY2R9601345      	3	19961201	G	6110	14B	BEARING         			PIPER 	PA23  	PA23160     	7102304	SO  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								507R		BEARING CORRODED.						1	L	7	2 	3O				1A10    		5	C	P23EA	 
1998042900408	19980429	00408	GL  	1998	4	29	EY2R9601346      	3	19961201	G	6110	83811	CLAMP           			PIPER 	PA23  	PA23160     	7102304	SO  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								507R		CLAMP CORRODED.						1	L	7	2 	3O				1A10    		5	C	P23EA	 
1998042900409	19980429	00409	GL  	1998	4	29	EY2R9601347      	3	19961201	G	6110	87	JACK PLATE      			BLANCA	1419  	1419        	1220402	GL  						HARTZL	HC12V	HC12V20*    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								6234		CORROSION FOUND ON JACK PLATE.						1	L	7	1 	3O				1A3     		5	C	P46GL	 
1998042900410	19980429	00410	GL  	1998	4	29	EY2R9601348      	3	19961201	G	6110	14B	BEARING         			BLANCA	1419  	1419        	1220402	GL  						HARTZL	HC12V	HC12V20*    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								6234		BEARING CORRODED.						1	L	7	1 	3O				1A3     		5	C	P46GL	 
1998042900411	19980429	00411	GL  	1998	4	29	EY2R9601349      	3	19961201	G	6110	83812	CLAMP           			BLANCA	1419  	1419        	1220402	GL  						HARTZL	HC12V	HC12V20*    	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								6234		CORROSION FOUND ON CLAMP.						1	L	7	1 	3O				1A3     		5	C	P46GL	 
1998042900412	19980429	00412	GL  	1998	4	29	EY2R9601350      	3	19961201	G	6114	4214	HUB             			BEECH 	23    	B24R        	1151253	CE  						HARTZL	HCM2Y	HCM2YR      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								EN260		HUB FOUND CORRODED.						1	L	7	1 	3O				A1CE    		5	C	P43GL	 
1998042900413	19980429	00413	GL  	1998	4	29	EY2R9601351      	3	19961201	G	6110	38	THRUST BEARING  													HARTZL	HC12X	HC12X*      	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7751		CORROSION FOUND ON THRUST BEARING.																5	C	P845	 
1998042900414	19980429	00414	GL  	1998	4	29	EY2R9601352      	3	19961201	G	6111	844712A	BLADE           			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								858F		BLADE, SN C1610, SHANK AREA, FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1998042900415	19980429	00415	GL  	1998	4	29	EY2R9601353      	3	19961201	G	6110	1303	BEARING         			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								858F		BEARING CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1998042900416	19980429	00416	GL  	1998	4	29	EY2R9601354      	3	19961201	G	6110	1301	CLAMP           			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								858F		PROP SHOULDER CLAMP FOUND CORRODED.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1998042900417	19980429	00417	GL  	1998	4	29	EY2R9601355      	3	19961201	G	6110	855	ROD             			BEECH 	95    	B95         	1153404	CE  						HARTZL	HC92W	HC92WK2     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								858F		CORROSION FOUND ON PITCH CHANGE ROD.						1	L	7	2 	3O				3A16    		5	C	P16EA	 
1998042900418	19980429	00418	GL  	1998	4	29	EY2R9601356      	3	19961201	G	6110	C4904	RETAIN NUT      			BEECH 	36    	A36         	1151604	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								801062		RETAIN NUT FOUND CORRODED.						1	L	7	1 	3O				3A15    		5	C	P22EA	 
1998011500002	19980115	00002	GL  	1998	1	15	EY2R9601358      	3	19960601	G	6111	M10476	BLADE           			BEECH 	300   	300BEECH    	1152930	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1787 	316  					FW854		BLADE, SN H16195, FOUND CORRODED.						2	L	7	2 	4T				A24CE   		6	C	P56GL	 
1998011500003	19980115	00003	GL  	1998	1	15	EY2R9601359      	3	19960701	G	6110	2202	SPLIT BEARING   			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		248  						FY1155		SPLIT BEARING ONE RACE WOULD NOT DEMAGNETIZE.  SUSPECT LIGHTNING.						1	L	7	2 	4T				A24CE   		5	C	STC	 
1998011500004	19980115	00004	GL  	1998	1	15	EY2R9601361      	3	19960801	G	6110	2202	SPLIT BEARING   			PIPER 	PA28  	PA28R201T   	7102813	SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2809 	283  					AM1784		PROPELLER MAGNETIZED.  SUSPECT LIGHTNING						1	L	7	1 	3O				2A13    		5	C	P920	 
1998011500005	19980115	00005	GL  	1998	1	15	EY2R9601362      	3	19960901	G	6111	114HCA0	BLADE           													MCAULY	5JFR	B5JFR36C1101	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		899  						951374		BLADE SN PD017 DAMAGED.  SUSPECT LIGHTNING																5	C	P15WE	 
1998011500006	19980115	00006	GL  	1998	1	15	EY2R9601366      	3	19960101	G	6110	C4451	FERRULE         			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								842577		SNAP RING GROOVE DAMAGED						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
1998011500007	19980115	00007	GL  	1998	1	15	EY2R9601367      	3	19960101	G	6114	C4211C76	HUB             			BEECH 	35    	V35         	1151538	CE  						MCAULY	3A32C	3A32C76     	GL  	PROPELLER ASSY	MIS DRILLED     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03		2165 	1016 					723315		PROP ASSY HUB DRILLED PAST .152						1	L	7	1 	3O				3A15    		5	C	P21EA	 
1998011500008	19980115	00008	GL  	1998	1	15	EY2R9601368      	3	19960101	G	6110	D7015C72	HUB             			CESSNA	320   	320C        	2074510	CE  						MCAULY	3AF32C	3AF32C72    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								742238		HUB WELCH PLUG HOLES TOO CLOSE						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998011500009	19980115	00009	GL  	1998	1	15	EY2R9601369      	3	19960101	G	6114	D7015C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7710826		PROP ASSY HUB EXPANSION HOLE TOO DEEP						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998011500010	19980115	00010	GL  	1998	1	15	EY2R9601370      	3	19960101	G	6114	D7027C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								756523		PROP ASSY HUB EXPANSION HOLES TOO CLOSE						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998011500011	19980115	00011	GL  	1998	1	15	EY2R9601373      	3	19960101	G	6114	D7015C87	HUB             			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								762832		PROP HUB ASSY HAS IMPROPER SAFETY HOLE						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998011500012	19980115	00012	GL  	1998	1	15	EY2R9601374      	3	19960101	G	6110	B4459	ACTUATING  PIN  			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								752145		BLADE ACTUATING PIN BENT						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998011500013	19980115	00013	GL  	1998	1	15	EY2R9601375      	3	19960101	G	6114	D7015C93	HUB             			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								782680		PROP HUB ASSY DRILLED PAST .152						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998011500014	19980115	00014	GL  	1998	1	15	EY2R9601376      	3	19960101	G	6110	C3267	ADAPTER         			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								741001		DAMAGE ON INSIDE BUSHING						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998011500015	19980115	00015	NE  	1998	1	15	EY2R9601379      	3	19960101	G	6110	D5170	PISTON ROD      			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								80392		HEAD BROKEN LOOSE FROM ROD ASSY.						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1998011500016	19980115	00016	NE  	1998	1	15	EY2R9601380      	3	19960101	G	6110	D5170	PISTON ROD      			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER ASSY	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								81168		HEAD BROKEN LOOSE FROM ROD ASSY.						2	L	7	2 	4T			RT	A8SW    		6	C	3PNE	 
1998011500017	19980115	00017	GL  	1998	1	15	EY2R9601382      	3	19960101	G	6114	840139	HUB             			BEECH 	100   	A100        	1152915	CE  						HARTZL	HCB4T	HCB4TN3     	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			548  					EAA1169		PROP HUB ASSY FAILED S.B. 196A						1	L	7	2 	3T				A14CE   		6	C	P40EA	 
1998011500018	19980115	00018	GL  	1998	1	15	EY2R9601387      	3	19960101	G	6110	24182	PISTON ROD      			CESSNA	172   	172         	2072402	CE  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH6594		PROP ASSY PISTON ROD BENT						1	H	7	1 	3O			NT	3A12    		5	C	P920	 
1998011500019	19980115	00019	GL  	1998	1	15	EY2R9601391      	3	19960101	G	6111	FC84754	BLADE           			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4975 	1810 					CJ344		BLADE SN F05216, PIN WORN						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1998011500020	19980115	00020	GL  	1998	1	15	EY2R9601392      	3	19960101	G	6111	FC84754	BLADE           			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4975 	1810 					CJ344		BLADE SN F05201, PIN WORN						1	L	7	2 	3O				A20SO   		5	C	P9EA	 
1998011500021	19980115	00021	GL  	1998	1	15	EY2R9601393      	3	19960101	G	6111	F7673DR	BLADE           			PIPER 	PA32  	PA32301T    	7103209	SO  						HARTZL	HCE3Y	HCE3YR1     	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE BEARING BORE OVERSIZE						1	L	7	1 	3O				A3SO    		5	C	P33EA	 
1998011500022	19980115	00022	GL  	1998	1	15	EY2R9601396      	3	19960101	G	6111	FJC84686R	BLADE           			PIPER 	PA31  	PA31310     	7103103	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1956 					DJ10046A		BLADE SN E34407, BORE OVERSIZED						1	L	7	1 	3O			RT	A20SO   		5	C	P33EA	 
1998011500023	19980115	00023	GL  	1998	1	15	EY2R9601397      	3	19960101	G	6111	FJC84686R	BLADE           			PIPER 	PA31  	PA31310     	7103103	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			1956 					DJ10046A		BLADE SN E35512, BORE OVERSIZED						1	L	7	1 	3O			RT	A20SO   		5	C	P33EA	 
1998011500024	19980115	00024	GL  	1998	1	15	EY2R9601398      	3	19960101	G	6110	24041	LOW PTCH STOP   			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER ASSY	STRIPPED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DJ4732		PROP LOW PITCH STOP HAS STRIPPED THREADS						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1998011500025	19980115	00025	GL  	1998	1	15	EY2R9601403      	3	19960201	G	6110	PROPELLER	FIX PITCH       			CESSNA	172   	172         	2072402	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								KJ005		3 HOLES IN HUB FROM STOP DRILL						1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1998011500026	19980115	00026	GL  	1998	1	15	EY2R9601404      	3	19960201	G	6110	A16349	BALL BEARING    			CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	FRETTED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		489  						910548		PROP ASSY BALLS FRETTED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998011500027	19980115	00027	GL  	1998	1	15	EY2R9601405      	3	19960201	G	6110	C5270	RETAIN  BEARING 			CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER ASSY	FRETTED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		489  						910548		PROP ASSY RETAIN BEARING RACES FRETTED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998011500028	19980115	00028	GL  	1998	1	15	EY2R9601406      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03			709  					761779		PROP ASSY HUB WELCH PLUGS DRILLED WRONG						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998011500029	19980115	00029	GL  	1998	1	15	EY2R9601407      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								687544		BLADE DAMAGED DUE TO DRILL MARK IN BALANCE HOLE						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1998011500030	19980115	00030	GL  	1998	1	15	EY2R9601408      	3	19960201	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								713768		HUB STAKING PLUG HOLE IN WRONG PLACE						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1998011500031	19980115	00031	GL  	1998	1	15	EY2R9601409      	3	19960201	G	6111	B4459	ACTUATING  PIN  			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780522		BLADE ACTUATING PIN DAMAGE  NO REPAIR						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998011500032	19980115	00032	GL  	1998	1	15	EY2R9601411      	3	19960201	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780522		BLADE HAS SCRATCH IN RADIUS OF THREAD						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998011500033	19980115	00033	NE  	1998	1	15	EY2R9601412      	3	19960201	G	6110	C5387	ACTUATI PIN     			CESSNA	425   	425         	2076018	CE  						MCAULY	4HFR34	4HFR34C762  	NE  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902350		ACTUATING PIN DAMAGED						1	L	7	2 	3T			RT	A7CE    		6	C	3PNE	 
1998011500034	19980115	00034	GL  	1998	1	15	EY2R9601413      	3	19960201	G	6111	83867	CLAMP           			BEECH 	90    	B90         	1152912	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP ASSY	PITTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE CLAMP HAS PITS IN RADIUS						1	L	7	2 	3T				3A20    		6	C	P15EA	 
1998011500035	19980115	00035	GL  	1998	1	15	EY2R9601414      	3	19960201	G	6110	5862	PITCH CHANGE ROD			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			2053 					BU4223		PITCH CHANGE ROD IS BENT.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998011500036	19980115	00036	GL  	1998	1	15	EY2R9601415      	3	19960201	G	6110	30012	LOW STOP COLLAR 			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU3996		LOW STOP COLLAR IS OUT OF ROUND						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1998011500037	19980115	00037	GL  	1998	1	15	EY2R9601416      	3	19960201	G	6110	13019S	CLAMP           			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	MIS DRILLED     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03								BU2089		CLAMP SCREW HOLES MISDRILLED						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1998011500038	19980115	00038	GL  	1998	1	15	EY2R9601417      	3	19960201	G	6110	83867	CLAMP           			MTSBSI	MU2   	MU2*        		SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER ASSY	MIS DRILLED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU2120		CLAMP SCREW HOLES MISDRILLED						1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1998011500039	19980115	00039	GL  	1998	1	15	EY2R9601422      	3	19960201	G	6110	4991	HUB             			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FY415A		HUB O'RING GROOVE DAMAGE						1	L	7	2 	4T				A24CE   		5	C	STC	 
1998011500040	19980115	00040	GL  	1998	1	15	EY2R9601423      	3	19960201	G	6114	4991	HUB             			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FY416A		THREADS PULLED ON HUB						1	L	7	2 	4T				A24CE   		5	C	STC	 
1998011500041	19980115	00041	GL  	1998	1	15	EY2R9601426      	3	19960301	G	6114	C5480C66	HUB             			CESSNA	182   	182         	2072702	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								683275		HUB HAS IMPROPER CYL. MTG. HOLE						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998011500042	19980115	00042	GL  	1998	1	15	EY2R9601427      	3	19960301	G	6110	D3474	PISTON ROD ASSY 			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C507   	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								820985		PROP PISTON ROD ASSY WORN						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1998011500043	19980115	00043	GL  	1998	1	15	EY2R9601430      	3	19960301	G	6110	C3474	PISTON ROD ASSY 			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753352		PROP PISTON ROD ASSY WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998011500044	19980115	00044	GL  	1998	1	15	EY2R9601431      	3	19960301	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								756462		HUB STAKING PIN HOLES TOO CLOSE						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1998011500045	19980115	00045	GL  	1998	1	15	EY2R9601434      	3	19960301	G	6110	D3474	PISTON ROD ASSY 			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727514		PROP PISTON ROD ASSY WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998011500046	19980115	00046	GL  	1998	1	15	EY2R9601437      	3	19960301	G	6110	D3474	PISTON ROD ASSY 			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3406 	1101 					779611		PROP PISTON ROD ASSY WORN						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998011500047	19980115	00047	GL  	1998	1	15	EY2R9601438      	3	19960301	G	6110	C4451	FERRULE         			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	MIS DRILLED     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03								789634		PROP FERRULE HOLES DRILLED TOO CLOSE						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998011500048	19980115	00048	GL  	1998	1	15	EY2R9601440      	3	19960301	G	6110	D3474	PISTON ROD ASSY 			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								802952		PROP PISTON ROD ASSY WORN						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998011500049	19980115	00049	GL  	1998	1	15	EY2R9601441      	3	19960301	G	6110	D3474	PISTON ROD ASSY 			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								727005		PROP PISTON ROD ASSY WORN						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998011500050	19980115	00050	GL  	1998	1	15	EY2R9601443      	3	19960301	G	6110	D3474	PISTON ROD ASSY 			CESSNA	421   	421A        	2076012	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								726157		PROP PISTON ROD ASSY WORN						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998011500051	19980115	00051	GL  	1998	1	15	EY2R9601444      	3	19960301	G	6114	D7019C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								740705		PROP HUB ALIGNMENT STUD PULLED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998011500052	19980115	00052	GL  	1998	1	15	EY2R9601445      	3	19960301	G	6111	S90LF0	BLADE           			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								781644		BLADE SN B20325YS, THREADS SCRATCHED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998011500053	19980115	00053	GL  	1998	1	15	EY2R9601452      	3	19960301	G	6114	D5878C501	HUB             			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								781134		HUB BEARING RACE MATING AREA DAMAGED						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998011500054	19980115	00054	GL  	1998	1	15	EY2R9601453      	3	19960301	G	6110	C3474	PISTON ROD ASSY 			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3139 	1430 					812996		PROP PISTON ROD ASSY WORN						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998011500055	19980115	00055	GL  	1998	1	15	EY2R9601455      	3	19960301	G	6111	S82N4	BLADE           			CESSNA	182   	182E        	2072712	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								780308		BLADE SN C89035YS, THREAD DAMAGE						1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1998012200001	19980122	00001	GL  	1998	1	22	EY2R9601456      	3	19960301	G	6114	D4887C81	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	2AF34C	D2AF34C81   	GL  	PROP ASSY	FRETTED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								7772913		PROP HUB HAS EXCESSIVE FRETTING.						1	L	7	2 	3O			RT	3A10    		5	C	P5EA	 
1998020500244	19980205	00244	GL  	1998	2	5	EY2R9601458      	3	19960301	G	6114	D7037C80	HUB             													MCAULY	3AF32C	D3AF32C80   	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								654650		HUB STAKING PIN HOLES TOO CLOSE																5	C	P22EA	 
1998020500245	19980205	00245	GL  	1998	2	5	EY2R9601459      	3	19960301	G	6114	24772	HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP9141		HUB PISTON ROD BORE ABOVE MAXIMUM						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998012200002	19980122	00002	GL  	1998	1	22	EY2R9601460      	3	19960301	G	6110	884	SPRING          			PIPER 	PA23  	PA23150     	7102303	CE  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								K2739N		PROP ASSY SPRING WORN						1	L	7	2 	3O			RT	1A10    		5	C	P23EA	 
1998012200003	19980122	00003	GL  	1998	1	22	EY2R9601461      	3	19960301	G	6114	84074	HUB             			BEECH 	18    	18S         	1150802	CE  						HARTZL	HCB3R	HCB3R304    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								A6596A		HUB HAS DEEP DEEP SCRATCHES BETWEEN SPLINES						1	L	7	2 	3R				TC710   		5	C	P28EA	 
1998012200004	19980122	00004	GL  	1998	1	22	EY2R9601462      	3	19960301	G	6110	30012	LOW STOP COLLAR 			BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BU12196		PROP LOW STOP COLLAR IS WORN						1	L	7	2 	4T				A24CE   		6	C	P15EA	 
1998012200005	19980122	00005	GL  	1998	1	22	EY2R9601466      	3	19960301	G	6114	220117	HUB             			CESSNA	177   	177         	2073704	CE  						HARTZL	HCC2Y	HCC2YR1     	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH24362		HUB GREASE FITTING HOLE DAMAGED						1	H	7	1 	3O			NT	A13CE   		5	C	P920	 
1998012200006	19980122	00006	GL  	1998	1	22	EY2R9601467      	3	19960301	G	6110	24182	PISTON ROD      			CESSNA	182   	182         	2072702	CE  						HARTZL	HCC3Y	HCC3YF1     	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1873 	168  					EC176		PROP ASSY PISTON ROD ASSY DAMAGED						1	H	7	1 	3O			NT	3A13    		5	C	P25EA	 
1998020500246	19980205	00246	GL  	1998	2	5	EY2R9601473      	3	19960401	G	6110	D3474	PISTON ROD ASSY 			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2454 	1338 					721970		PISTON ROD ASSY WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998012200007	19980122	00007	GL  	1998	1	22	EY2R9601474      	3	19960401	G	6110	D3474	PISTON ROD ASSY 			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								733313		PROP ASSY PISTON ROD ASSY WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998012200008	19980122	00008	GL  	1998	1	22	EY2R9601475      	3	19960401	G	6110	D3474	PISTON ROD      			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								784317		PROP ASSY PISTON ROD ASSY IS WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998012200009	19980122	00009	GL  	1998	1	22	EY2R9601480      	3	19960401	G	6114	D7019C92	HUB             			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	STRIPPED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								743413		PROP ASSY HUB DOWEL PIN HOLE STUD STRIPPED						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998012200010	19980122	00010	GL  	1998	1	22	EY2R9601483      	3	19960401	G	6114	D4197C90	HUB             			CESSNA	206   	P206A       	2073308	CE  						MCAULY	3A32C	D3A32C90    	GL  	PROPELLER ASSY	MIS DRILLED     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03		3698 	972  					754862		PROP HUB WELCH PLUG HOLES DRILLED WRONG						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1998012200011	19980122	00011	GL  	1998	1	22	EY2R9601488      	3	19960401	G	6110	2020	BEARING         			CESSNA	172   	172         	2072402	CE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH22812		PROP ASSY BEARING WORN						1	H	7	1 	3O			NT	3A12    		5	C	P920	 
1998012200012	19980122	00012	GL  	1998	1	22	EY2R9601489      	3	19960401	G	6114	3276	HUB             			PIPER 	PA31  	PA31P       	7103120	SO  						HARTZL	HCC3Y	HCC3YN      	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								DG519		PROP ASSY HUB DAMAGED						1	L	7	2 	3O				A8EA    		5	C	P25EA	 
1998020500247	19980205	00247	GL  	1998	2	5	EY2R9601497      	3	19960501	G	6110	B4459	BLADE ACT PIN   			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3428 	501  					723023		BLADE ACTUATING PIN DAMAGED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998012200013	19980122	00013	GL  	1998	1	22	EY2R9601498      	3	19960501	G	6111	B4459	ACTUATING PIN   			CESSNA	310   	310Q        	2074242	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3428 	501  					723458		PROP ASSY BLADE ACTUATING PIN WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998012200014	19980122	00014	GL  	1998	1	22	EY2R9601501      	3	19960501	G	6110	B4650	LINK ASSY       			CESSNA	414   	414         	2075908	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			453  					7710747		PROP LINK ASSY IS BENT						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998012200015	19980122	00015	GL  	1998	1	22	EY2R9601502      	3	19960501	G	6110	D3474	PISTON ROD ASSY 			CESSNA	421   	421         	2076010	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								771839		PROP ASSY PISTON ROD ASSY IS WORN						1	L	7	2 	3O			RT	A7CE    		5	C	P45GL	 
1998012200016	19980122	00016	GL  	1998	1	22	EY2R9601504      	3	19960501	G	6110	B3478	RETAIN  RING    			CESSNA	210   	210M        	2073450	CE  						MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								785659		PROP ASSY RETAIN RING IS BENT						1	H	7	1 	3O				3A21    		5	C	P21EA	 
1998012200017	19980122	00017	GL  	1998	1	22	EY2R9601507      	3	19960501	G	6114	84059	HUB             			PIPER 	PA23  	PA23150     	7102303	CE  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5125 	1111 					K851N		PROP HUB THREADS MISSING						1	L	7	2 	3O			RT	1A10    		5	C	P23EA	 
1998012200018	19980122	00018	GL  	1998	1	22	EY2R9601509      	3	19960501	G	6110	3475A2	LOW STOP COLLAR 			BEECH 	90    	C90         	1152913	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3181 	1979 					BU16874		PROP ASSY LOW STOP COLLAR BENT						1	L	7	2 	3T				3A20    		6	C	P15EA	 
1998012200019	19980122	00019	GL  	1998	1	22	EY2R9601513      	3	19960501	G	6112	4E26241	SLIP RING       			BEECH 	1900  	1900C       	1154161	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER ASSY	DEBONDED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FW984		PROP ASSY SLIP RING DEBONDED, INSULATOR CRACKED						2	L	7	2 	4T			RT	A24CE   		6	C	P56GL	 
1998020500248	19980205	00248	GL  	1998	2	5	EY2R9601514      	3	19960501	G	6110	868AS	PITCH CHANGE ROD			BEECH 	35    	B35         	1151506	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								FW1117		PITCH CHANGE ROD DEFECTIVE						1	L	7	1 	3O				A777    		6	C	P56GL	 
1998012200020	19980122	00020	GL  	1998	1	22	EY2R9601516      	3	19960501	G	6110	3494	HIGH PTCH STOP  			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CD402		PROPELLER ASSY HIGH PITCH STOP FOUND BENT.						1	L	7	2 	3T				A14CE   		6	C	P40EA	 
1998012200021	19980122	00021	GL  	1998	1	22	EY2R9601517      	3	19960501	G	6110	83034	HIGH PTCH STOP  			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CD402		HIGH PITCH STOP FOUND BENT.						1	L	7	2 	3T				A14CE   		6	C	P40EA	 
1998012200022	19980122	00022	GL  	1998	1	22	EY2R9601525      	3	19960501	G	6110	24914S	PITCH CHANGE ROD			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG1381		PROP ASSY PITCH CHANGE ROD WORN						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1998012200023	19980122	00023	GL  	1998	1	22	EY2R9601534      	3	19960601	G	6110	C3474	PISTON ROD ASSY 			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821060		PISTON ROD ASSY BENT						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1998012200024	19980122	00024	GL  	1998	1	22	EY2R9601535      	3	19960601	G	6110	C4283	CYLINDER        			CESSNA	303   	T303        	2073820	CE  						MCAULY	3AF32C	3AF32C506   	GL  	PROPELLER ASSY	DENTED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								821060		PROP ASSY CYLINDER DENTED						1	L	7	2 	3O				A34CE   		5	C	P57GL	 
1998012200025	19980122	00025	GL  	1998	1	22	EY2R9601540      	3	19960601	G	6111	C4459	ACTUATING PIN   			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								783822		PROP ASSY BLADE ACTUATING PIN DAMAGED						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998012200026	19980122	00026	GL  	1998	1	22	EY2R9601545      	3	19960601	G	6110	C3550	FEATHER CYLINDER			CESSNA	421   	421         	2076010	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								805941		PROP ASSY FEATHER ASSY .067 LARGER THAN NORMAL						1	L	7	2 	3O			RT	A7CE    		5	C	P22EA	 
1998020500249	19980205	00249	GL  	1998	2	5	EY2R9601550      	3	19960601	G	6114	D7019C92	HUB             			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			400  					768477		PROP HUB HAS PULLED STUD						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998012200027	19980122	00027	NE  	1998	1	22	EY2R9601551      	3	19960601	G	6111	L106LA0	BLADE           			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2834 						890503		BLADE SN JC011, RADIUS DAMAGED						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1998012200028	19980122	00028	GL  	1998	1	22	EY2R9601552      	3	19960601	G	6110	C3418	PISTON          			CESSNA	182   	182         	2072702	CE  						MCAULY	2D34C	B2D34C214   	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								786792		PROP ASSY PISTON IS DAMAGED						1	H	7	1 	3O			NT	3A13    		5	C	P7EA	 
1998012200029	19980122	00029	GL  	1998	1	22	EY2R9601554      	3	19960601	G	6110	A31504	ROLL PIN        			CESSNA	210   	210         	2073402	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								796954		PROP ASSY ROLL PIN BENT						1	H	7	1 	3O			RT	3A21    		5	C	P47GL	 
1998012200030	19980122	00030	GL  	1998	1	22	EY2R9601555      	3	19960601	G	6111	S82NC4	BLADE           			CESSNA	310   	310L        	2074230	CE  						MCAULY	3AF32C	D3AF32C80   	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								663778		BLADE SN K77739YS, SCRATCH IN THREADS						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998012200031	19980122	00031	GL  	1998	1	22	EY2R9601556      	3	19960601	G	6111	S90AT8	BLADE           			CESSNA	206   	P206B       	2073309	CE  						MCAULY	2A34C	E2A34C73    	GL  	PROPELLER	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1187 						850614		BLADE SN EJ299YS, THREADS CHIPPED.						1	H	7	1 	3O				A4CE    		5	C	P3EA9	 
1998012200032	19980122	00032	GL  	1998	1	22	EY2R9601557      	3	19960601	G	6111	S90AT8	BLADE           			CESSNA	206   	P206B       	2073309	CE  						MCAULY	2A34C	E2A34C73    	GL  	PROPELLER ASSY	STRIPPED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1187 						850614		BLADE SN EJ247YS, THREADS CHIPPED						1	H	7	1 	3O				A4CE    		5	C	P3EA9	 
1998020500250	19980205	00250	GL  	1998	2	5	EY2R9601558      	3	19960601	G	6114	84096	HUB             			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCA2X	HCA2XK2     	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								H2803		HUB PILOT TUBE BORE WORN						1	H	7	2 	3O				6A1     		5	C	P908	 
1998020500251	19980205	00251	GL  	1998	2	5	EY2R9601559      	3	19960601	G	6114	84096	HUB             			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCA2X	HCA2XK2     	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								H2804		HUB PILOT TUBE BORE DEFECTIVE						1	H	7	2 	3O				6A1     		5	C	P908	 
1998012200033	19980122	00033	GL  	1998	1	22	EY2R9601560      	3	19960601	G	6110	13019S	CLAMP           			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	MISDRILLED      	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03		6715 						BV5314		PROP ASSY CLAMP HAS MISDRILLED 321 SCREWS.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998012200034	19980122	00034	GL  	1998	1	22	EY2R9601561      	3	19960601	G	6110	30012	LOW STOP COLLAR 			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6715 						BV5314		LOW STOP COLLAR IS .30 INCH OUT OF ROUND.						1	L	7	2 	3T				A14CE   		6	C	P15EA	 
1998012200035	19980122	00035	GL  	1998	1	22	EY2R9601562      	3	19960601	G	6197	38012	WIRE            			BEECH 	100   	100BEECH    	1152916	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2018 						BU13376		PROP ASSY I.D. WIRE DAMAGE						1	L	7	2 	3T			 	A14CE   		6	C	P15EA	 
1998012200036	19980122	00036	GL  	1998	1	22	EY2R9601564      	3	19960601	G	6110	24573	PITCH CHANGE    			BNORM 	BN2   	BN2A3       	1520215	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROP ASSY FORK	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU7443		PROP ASSY PITCH CHANGE FORK WORN						1	H	7	2 	3O				A17EU   		5	C	P920	 
1998012200037	19980122	00037	GL  	1998	1	22	EY2R9601568      	3	19960601	G	6114	32517	HUB             			BEECH 	95    	95B55       	1152729	CE  						HARTZL	HCC3Y	PHCC3YF2    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1545 						EB1496		PROP HUB DOWEL PINS ENLARGED						1	L	7	2 	3O			RT	3A16    		5	C	P25EA	 
1998012200038	19980122	00038	GL  	1998	1	22	EY2R9601570      	3	19960701	G	6114	D7015C75	HUB             			BEECH 	55    	D55         	1152730	CE  						MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697561		PROP HUB OUTSIDE DAMAGE						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1998012200039	19980122	00039	GL  	1998	1	22	EY2R9601571      	3	19960701	G	6110	C3550	FEATHER CYLINDER			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697985		PROP FEATHER CYLINDER WORN						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998012200040	19980122	00040	GL  	1998	1	22	EY2R9601572      	3	19960701	G	6110	C3550	FEATHER CYLINDER			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								779568		PROP FEATHER CYLINDER WORN						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998012200041	19980122	00041	GL  	1998	1	22	EY2R9601573      	3	19960701	G	6114	D7015C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								697985		HUB EXPANSION HOLE TOO DEEP						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998012200042	19980122	00042	GL  	1998	1	22	EY2R9601574      	3	19960701	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	MIS DRILLED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								698455		NR1 SOCKET, STAKNG PIN DRILLED WRONG						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1998012200043	19980122	00043	GL  	1998	1	22	EY2R9601575      	3	19960701	G	6114	D7015C87	HUB             			CESSNA	310   	310         	2074202	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								690742		PROP HUB STAKING PIN HOLE TOO DEEP						1	L	7	2 	3O			RT	3A10    		5	C	P22EA	 
1998012200044	19980122	00044	GL  	1998	1	22	EY2R9601576      	3	19960701	G	6114	D7015C87	HUB             			CESSNA	340   	340CESSNA   	2076404	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	MIS DRILLED     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								721859		HUB STAKING PIN HOLE DRILLED WRONG						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998012200045	19980122	00045	GL  	1998	1	22	EY2R9601577      	3	19960701	G	6110	C5503	BETA ROD        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2566 						910058		PROP BETA ROD WORN						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998012200046	19980122	00046	GL  	1998	1	22	EY2R9601578      	3	19960701	G	6110	D5010	CYLINDER        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER ASSY	GROOVED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2566 						910058		PROP ASSY CYLINDER GROOVED EXCESSIVELY						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998012200047	19980122	00047	GL  	1998	1	22	EY2R9601579      	3	19960701	G	6110	A16349	BALL BEARING    			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	PROPELLER ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5633 	1131 					814657		PROP ASSY BEARINGS FLAT						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1998012200048	19980122	00048	GL  	1998	1	22	EY2R9601580      	3	19960701	G	6110	C5264	CYLINDER        			CESSNA	210   	T210N       	2073456	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								815224		PROP ASSY CYLINDER DAMAGED						1	H	7	1 	3O				3A21    		5	C	P47GL	 
1998012200049	19980122	00049	GL  	1998	1	22	EY2R9601581      	3	19960701	G	6110	127	COVER PLATE     			FRCHLD	24    	24R46       	3370514	EA  						HARTZL	HC12V	HC12V20*    	GL  	PROPELLER ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								P477		PROP ASSY COVER PLATE BENT						1	H	7	1 	3I				A706    		5	C	P46GL	 
1998012200050	19980122	00050	GL  	1998	1	22	EY2R9601585      	3	19960701	G	6110	30012	LOW STOP COLLAR 			PIPER 	PA31T 	PA31T1      	7103126	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								35843		CARBON BLOCK CUT GROOVE IN BETA RING						1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1998020500252	19980205	00252	GL  	1998	2	5	EY2R9601588      	3	19960701	G	6114	220118	HUB             			PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	HCC2YF2     	GL  	PROP ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AN4270		HUB DAMGED IN MOUNTING O'RING AREA						1	L	7	2 	3O				A7SO    		5	C	P920	 
1998020500253	19980205	00253	GL  	1998	2	5	EY2R9601589      	3	19960701	G	6114	220117	HUB             			CESSNA	172   	172         	2072402	CE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								CH28614		HUB HAS OVERSIZE QUAD SEAL GROOVE						1	H	7	1 	3O			NT	3A12    		5	C	P920	 
1998020500254	19980205	00254	GL  	1998	2	5	EY2R9601592      	3	19960701	G	6111	FC74792R	BLADE           			BEECH 	60    	60          	1153602	CE  						HARTZL	HCF3Y	HCF3YR2     	GL  	PROP ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										BLADE SN D2825, NICKED						1	L	7	2 	3O				A12CE   		5	C	P31EA	 
1998020500255	19980205	00255	GL  	1998	2	5	EY2R9601593      	3	19960801	G	6111	80VHA35	BLADE           			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	2D34C*      	GL  	PROP ASSY	GALLED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4459 						7910322		BLADE SN IB026, GALLED BAD						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1998020500256	19980205	00256	GL  	1998	2	5	EY2R9601594      	3	19960801	G	6111	80VHA35	BLADE           			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	2D34C*      	GL  	PROP ASSY	GALLED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4459 						7910322		BLADE SN IB008, GALLED BAD						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1998020500257	19980205	00257	GL  	1998	2	5	EY2R9601595      	3	19960801	G	6114	C5078C220	HUB             			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	2D34C*      	GL  	PROP ASSY	GALLED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4459 						7910322		HUB ASSY GALLED BAD						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1998020500258	19980205	00258	GL  	1998	2	5	EY2R9601597      	3	19960801	G	6111	S82NC2	BLADE           			CESSNA	188   	A188B       	2073005	CE  						MCAULY	3A32C	D3A32C90    	GL  	PROP ASSY	FAILED          	B				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	03								891793		BLADE SN JE035YS, SLUNG TIP WHILE IN FLT						1	L	7	1 	3O				A9CE    		5	C	P21EA	 
1998020500259	19980205	00259	GL  	1998	2	5	EY2R9601606      	3	19960901	G	6110	D3474	PISTON ROD ASSY 			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4772 						788627		PISTON ROD ASSY WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998020500260	19980205	00260	GL  	1998	2	5	EY2R9601607      	3	19960901	G	6110	D3474	PISTON ROD ASSY 			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4772 						789445		PISYON ROD ASSY WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998020500261	19980205	00261	GL  	1998	2	5	EY2R9601608      	3	19960901	G	6110	D3474	PISTON ROD ASSY 			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798440		PISTON ROD ASSY WORN						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998020500262	19980205	00262	GL  	1998	2	5	EY2R9601609      	3	19960901	G	6110	D3474	PISTON ROD ASSY 			CESSNA	335   	335         	2075601	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								798443		PISTON ROD ASSY WORN						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998020500263	19980205	00263	GL  	1998	2	5	EY2R9601610      	3	19960901	G	6110	C3550	FEATHER CYLINDER			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								940196		FEATHER CYLINDER WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998020500264	19980205	00264	GL  	1998	2	5	EY2R9601613      	3	19960901	G	6110	C5116	FEEDBACK COLLAR 			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		233  						952165		PROP ASSY FEEDBACK COLLAR OUT OF ROUND						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998020500265	19980205	00265	GL  	1998	2	5	EY2R9601614      	3	19960901	G	6110	B2345	PISTON TUBE     			CESSNA	182   	182         	2072702	CE  						MCAULY	2D34C	B2D34C214   	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3465 	1803 					783681		PISTON TUBE WORN						1	H	7	1 	3O			NT	3A13    		5	C	P7EA	 
1998020500266	19980205	00266	GL  	1998	2	5	EY2R9601615      	3	19960901	G	6111	S90AT8	BLADE           			CESSNA	210   	210D        	2073414	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROP ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								721718		SCRATCH IN THREADS OF BLADE  SN K84876YS						1	H	7	1 	3O				3A21    		5	C	P3EA	 
1998020500267	19980205	00267	GL  	1998	2	5	EY2R9601618      	3	19961001	G	6111	S78FM0	BLADE           			BEECH 	55    	9555        	1152702	CE  						MCAULY	2AF36C	2AF36C89    	GL  	PROP ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										THREADS SCRATCHED ON BLADE SN 29825YS						1	L	7	2 	3O				3A16    		5	C	P911	 
1998020500268	19980205	00268	GL  	1998	2	5	EY2R9601619      	3	19961001	G	6111	S78FM0	BLADE           			BEECH 	55    	9555        	1152702	CE  						MCAULY	2AF36C	2AF36C89    	GL  	PROP ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										THREADS SCRATCHED ON BLADE SN 29825YS						1	L	7	2 	3O				3A16    		5	C	P911	 
1998020500269	19980205	00269	GL  	1998	2	5	EY2R9601627      	3	19961001	G	6110	7384302	RACE            			DHAV  	DHC7  	DHC7*       		EA  						HAMSTD	24PF	24PF305     	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		18628	4803 					237492		PROP ASSY RACES CHATTERED						2	H	7	4 	4T			RT	A20EA   		6	C	P1NE	 
1998020500270	19980205	00270	GL  	1998	2	5	EY2R9601628      	3	19961001	G	6110	B2345	PISTON TUBE     			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C203    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								870628		PROP ASSY PISTON TUBE WORN						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1998020500271	19980205	00271	GL  	1998	2	5	EY2R9601631      	3	19961001	G	6110	D3474	PISTON ROD ASSY 			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2780 						771292		PISTON ROD ASSY WORN						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1998020500272	19980205	00272	GL  	1998	2	5	EY2R9601633      	3	19961001	G	6110	D3474	PISTON ROD ASSY 			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		PISTON ROD ASSY WORN						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998020500273	19980205	00273	GL  	1998	2	5	EY2R9601634      	3	19961001	G	6110	D3474	PISTON ROD ASSY 			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795375		PISTON ROD ASSY WORN						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998020500274	19980205	00274	GL  	1998	2	5	EY2R9601635      	3	19961001	G	6114	D7015C93	HUB             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								795369		HUB ASSY BUSHING HOLE OVERSIZE						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1998020500275	19980205	00275	GL  	1998	2	5	EY2R9601636      	3	19961001	G	6110	D3474	PISTON ROD ASSY 			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								768385		PISTON ROD ASSY WORN						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998020500276	19980205	00276	GL  	1998	2	5	EY2R9601637      	3	19961001	G	6110	D3474	PISTON ROD ASSY 			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								789223		PISTON ROD ASSY WORN						1	L	7	2 	3O				A7CE    		5	C	P45GL	 
1998020500277	19980205	00277	GL  	1998	2	5	EY2R9601639      	3	19961001	G	6110	24281	CYLINDER UNIT   			PIPER 	PA28  	PA28R201T   	7102813	SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AM2596		PROP CYLINDER UNIT WORN						1	L	7	1 	3O				2A13    		5	C	P920	 
1998020500278	19980205	00278	GL  	1998	2	5	EY2R9601640      	3	19961001	G	6110	A3267	ADAPTER         			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753558		PROP ASSY ADAPTER WORN						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998020500279	19980205	00279	GL  	1998	2	5	EY2R9601641      	3	19961001	G	6110	C3274	FEATHER CYLINDER			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								753558		FEATHER CYLINDER ASSY WORN						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998020500280	19980205	00280	GL  	1998	2	5	EY2R9601653      	3	19961001	G	6110	660709612	CYLINDER        			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		21893	5973 					DRG936282		PROP ASSY CYLINDER WORN						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1998020500281	19980205	00281	GL  	1998	2	5	EY2R9601654      	3	19961001	G	6110	860013002	SPRING          			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		21893	5973 					DRG936282		PROP ASSY SPRING WORN						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1998020500282	19980205	00282	GL  	1998	2	5	EY2R9601655      	3	19961001	G	6110	860014002	SPRING          			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		21893	5973 					DRG936282		PROP ASSY SPRING WORN						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1998020500283	19980205	00283	GL  	1998	2	5	EY2R9601656      	3	19961101	G	6114	660709201	HUB             			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		21844	5889 					DRG418385		PROP ASSY HUB DEFECTIVE						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
1998020500284	19980205	00284	CE  	1998	2	5	EY2R9601657      	3	19961101	G	6110	B200373	PITCH SCREW     			BEECH 	35    	F35         	1151514	CE  						BEECH	215	215108      	CE  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			662  					41714		PROP ASSY PITCH CHANGE SCREW WORN						1	L	7	1 	3O				A777    		5	C	P873	 
1998020500285	19980205	00285	CE  	1998	2	5	EY2R9601658      	3	19961101	G	6114	215107	HUB             			BEECH 	35    	D35         	1151510	CE  						BEECH	215	215*        	CE  	PROP ASSY	SCORED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								4959		HUB SCORED FROM BEARING						1	L	7	1 	3O				A777    		5	C	P873	 
1998020500286	19980205	00286	CE  	1998	2	5	EY2R9601659      	3	19961101	G	6110	B200373	PITCH SCREW     			BEECH 	35    	D35         	1151510	CE  						BEECH	215	215*        	CE  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								4959		PROP ASSY PITCH CHANGE SCREW WORN						1	L	7	1 	3O				A777    		5	C	P873	 
1998020500287	19980205	00287	GL  	1998	2	5	EY2R9601662      	3	19961101	G	6110	C5503	BETA ROD        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2490 						911608		PROP ASSY BETA ROD WORN						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998020500288	19980205	00288	GL  	1998	2	5	EY2R9601663      	3	19961101	G	6110	D5010	CYLINDER        			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2490 						911608		PROP ASSY CYLINDER PLATING BLISTERED						1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998020500289	19980205	00289	NE  	1998	2	5	EY2R9601664      	3	19961101	G	6114	D6153C652	HUB             			SWRNGN	SA226 	SA226AC     	8780402	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		10269	3143 					890764		PROP HUB ASSY HAS WORN SHIM SET						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
1998020500290	19980205	00290	GL  	1998	2	5	EY2R9601665      	3	19961101	G	6111	B4163	BASE ASSY  PIN  			CESSNA	337   	337E        	2075721	CE  						MCAULY	2AF34C	D2AF34C302  	GL  	PROP ASSY	OTHERLOOSE      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								712397		PROPELLER BLADE PIN LOOSE.  PREVENTED ACTUATION.						1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1998020500291	19980205	00291	GL  	1998	2	5	EY2R9601672      	3	19961201	G	6110	C3550	CYLINDER        			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROP ASSY	SCORED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6108 						832375		PROP ASSY CYLINDER I.D. SCORED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998020500292	19980205	00292	GL  	1998	2	5	EY2R9601677      	3	19961201	G	6110	24913	ROD             			BNORM 	BN2   	BN2         	1520202	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								AU5083		PROP ASSY ROD HAS BAD THREADS						1	H	7	2 	3O				A17EU   		5	C	P920	 
1998020500293	19980205	00293	GL  	1998	2	5	EY2R9601678      	3	19961201	G	6110	24914S	ROD             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ASSY	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP8008		PROP ASSY ROD BENT						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998020500294	19980205	00294	GL  	1998	2	5	EY2R9601681      	3	19961201	G	6110	C3550	CYLINDER        			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROP ASSY	SCORED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		6108 						753019		PROP ASSY CYLINDER I.D. SCORED						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998020500295	19980205	00295	GL  	1998	2	5	EY2R9601682      	3	19961201	G	6110	24914S	ROD             			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ2Y	BHCJ2YF2    	GL  	PROP ASSY	STRIPPED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4600 						DZ336		PROP ASSY ROD THREAD STRIPPED						1	L	7	2 	3O				3A16    		5	C	P37EA	 
1998020500296	19980205	00296	GL  	1998	2	5	EY2R9601683      	3	19961201	G	6110	24914S	ROD             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BP6390		PROP ASSY ROD IS DEFECTIVE						1	L	7	2 	3O				1A10    		5	C	P9EA	 
1998021100005	19980211	00005	NE  	1998	2	11	EY2R9601684      	3	19961201	G	6110	6071	ROD             			SOCATA	TBM   	TBM700      	8682000	EU  						HARTZL	HCE4N	HCE4N3      	NE  	PROP ASSY	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								HH32		PROP ASSY SN 1321 IS DEFECTIVE						1	L	7	1 	3T			RT	A60EU   		5	C	P10NE	 
1998020500297	19980205	00297	GL  	1998	2	5	EY2R9601691      	3	19961001	G	6111	76634	BLADE           			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROP ASSY	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								BG2659		PITCH CHANGE KNOB BELOW MINIMUM						1	L	7	2 	3O				A1EA    		5	C	P9EA	 
1996020200314	19960202	00314	SW  	1996	2	2	GCHA9622         	1	19960116	G	2810	206063688001	HOSE            			BELL  	206   	206L1       	1182107	SW  										FUEL CELL VENT	LEAKING         	I			GCHA	K				NONE                    				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		CR	CRUISE         	1			WP	19	1075S	16439				45366				PILOT REPORTED STRONG FUEL SMELL IN COCKPIT.  FOUND THE R/H SIDE FLEX LINE  LEAKING APPROX 7" FROM CENTER FITTING. REMOV	ED AND REPLACED FORWARD FUEL CELL VENT HOSE ASSY WITH SERVICEABLE  PART NUMBER 206-063-688-001					1	G	7	1 	3U				H2SW    					 
1996112700284	19961127	00284	SW  	1996	11	27	GJQR0000097      	1	19961022	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	DEBONDED        	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	102FW	226  			A20323	621905				C/W ASB 204-96-48 DUE TO POSSIBILITY OF DEBONDING OF THE MAIN SPAR LEADING EDGE DOUBLER.  SEE AD 96-12-26.  REPLACED WIT	H NEW BLADES FROM CSF STOCK.  (X)					1	G	7	1 	4U				EXPA1G71					 
1996112700283	19961127	00283	SW  	1996	11	27	GJQR0000098      	1	19961022	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	DEBONDED        	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	102FW	226  			A20318	621905				C/W ASB 204-96-48 DUE TO POSSIBILITY OF DEBONDING OF THE MAIN SPAR LEADING EDGE DOUBLER.  SEE AD 96-12-26.  REPLACED WIT	H NEW BLADES FROM CSF STOCK.  (X)					1	G	7	1 	4U				EXPA1G71					 
1997020600185	19970206	00185	SW  	1997	2	6	GJQR9600100      	1	19961209	G	6410	206016201131	BLADE           			BELL  	206   	206B        	1181511	SW  										T/R	DEBONDED        	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	96NW	264  			CS873	4389				BLADE REPLACED DUE TO DEBOND DETECTED DURING POST FLIGHT.  BLADE MAKES CLICKING SOUND AND DELAMINATION PRESENT AT BLADE 	ROOT DOUBLER AREA.  (X)					1	G	7	1 	3U				H2SW    					 
1996121200113	19961212	00113	SW  	1996	12	12	GJQR9663         	1	19960201	G	5320	206020114131S	FAIRING         			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	MIS MFG         	H			GJQR	L				ABORTED APPROACH        				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	13	53W					3587				THIS FAIRING WAS ORDERED FROM BELL - BUT IT DOESN'T FIT - IT IS ONE-HALF INCH SHORT.						1	G	7	1 	3U				H2SW    					 
1996062700389	19960627	00389	SW  	1996	6	27	GJQR9664         	1	19960201	G	6320	206075678107	INDICATOR       			BELL  	206   	206L        	1181522	SW  										TRANSMISSION	ERRATIC         	H			GJQR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	13	108W	1344 				52034				INDICATOR IS ERRATIC - WILL NOT READ ABOVE 50 DEGREE - DROPS TO ZERO DURING FLIGHT, UNRELIABLE. REPLACED WITH NEW INDICA	TOR FROM BELL.					1	G	7	1 	3U				H2SW    					 
1996122600464	19961226	00464	SW  	1996	12	26	GJQR9675         	1	19960528	G	3213	206033108001	FITTING         			BELL  	206   	206L        	1181522	SW  										RT CROSSTUBE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	108W	1122 				52034				FWD CROSS TUBE STRAP ASSY. WORN INTO RIGHT FW.CROSS TUBE FITTING. REPLACED FITTING PER PRODUCT SUPPORT WEAR  LIMITS.						1	G	7	1 	3U				H2SW    					 
1996122600465	19961226	00465	SW  	1996	12	26	GJQR9680         	1	19960528	G	6410	206310105101	BEARING         			BELL  	206   	206L        	1181522	SW  										T/R BLADE	DEFECTIVE       	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	108W	863  				52034				INSTALLED BEARING  IN T/R BLADE TO C/W TB206L-94-172 REV.A PT. I.  BLADE ALIGNMENT WOULD NOT MEET THE DIMENSIONAL REQUIR	EMENT DUE TO THE AXIAL PLAY IN THE NEW BEARING. REPLACED WITH NEW BEARING FROM CSF STOCK.					1	G	7	1 	3U				H2SW    					 
1996122600466	19961226	00466	SW  	1996	12	26	GJQR9681         	1	19960528	G	6410	206010733003	SLEEVE          			BELL  	206   	206L        	1181522	SW  										T/R BLADE	DEFECTIVE       	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	108W	863  				52034				INSTALLED BRG. IN T/R BLADE TO W/C TB206L-94-172 REV.A,PT.I.  BLADE ALIGHNMENT WOUD NOT MEET THE DIMENSIONAL REQUIREMENT	 DUE TO THE AXIAL PAY IN THE NEW BEARING. REPLACED WITH NEW STOCK FROM CSF.					1	G	7	1 	3U				H2SW    					 
1996011900170	19960119	00170	NE  	1996	1	19	GMAL9501021      	2	19960102	G	7323	116085025	GOVERNOR        			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					ENG OVERSPEED	DEFECTIVE       	H			GMAL	O				OTHER                   				J			WARNING INDICATION        			EX	EXTERNAL LOAD  	1			NM	09	132KA	410  				A940004				PILOT REPORTED GOVERNOR DECAY FROM 104 PERCENT NR DOWN TO 97 PERCENT NR DURING HOVER.  PROBLEM INTERMITTENT EVERY 3 TO 4	 TURNS DURING LOGGING OPERATIONS.  (X)					1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
1996020900639	19960209	00639	NE  	1996	2	9	GMAL9501022      	2	19960102	G	7210	103022903	SEAL HOUSING    			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					OUTPUT GEARSHAFT	CRACKED         	H	S		GMAL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	132KA	410  				940004				CIRCUMFERENCE CRACK OF OUTPUT GEAR SHAFT HOUSING IN STEP-DOWN RADIUS OF HOUSING, LEFT AND RIGHT SIDES 2:00 O'CLOCK TO 5:	00 O'CLOCK AND 7:00 O'CLOCK TO 10:00 O'CLOCK POSITIONS.  (X)					1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
1996031500401	19960315	00401	SW  	1996	3	15	GMAL9501023      	1	19960102	G	2121	K986127	FAN             			KAMAN 	K1200 	K1200       	05625F6	SW  										AIR DIST	FAILED          	H			GMAL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	134KA	411  				A940006				FAN MOTOR BEARINGS WORN.  FAN WILL NOT ROTATE.  FAN WAS INSTALLED AT A/C TT 560.8 HOURS ON 8-10-95.  PREVIOUS FAN WAS RE	PLACED FOR SAME PROBLEM.  TOTAL TIME, AIRCRAFT, 560.8 HOURS.  (X)					1	G	7	1 	4F			NT	TR7BO   					 
1996020900640	19960209	00640	NE  	1996	2	9	GMAL9501024      	2	19960102	G	7210	103022903	SEAL HOUSING    			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					OUTPUT GEARSHAFT	CRACKED         	H			GMAL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	134KA	600  				940006				CIRCUMFERENCE CRACK OF OUTPUT GEARSHAFT SEAL HOUSING IN STEP-DOWN RADIUS OF HOUSING, LEFT AND RIGHT SIDES.  (X)						1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
1996020900641	19960209	00641	NE  	1996	2	9	GMAL9501025      	2	19960102	G	7210	103022903	SEAL HOUSING    			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					OUTPUT GEARSHAFT	CRACKED         	H			GMAL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	135KA	719  				A940007	LE81004			CIRCUMFERENCE CRACK OF OUTPUT GEARSHAFT SEAL HOUSING IN STEP-DOWN RADIUS OF HOUSING, 2:00 O'CLOCK TO 6:00 O'CLOCK POSITI	ONS.  THIS SEAL RETAINER WAS REPLACED BY LYCOMING AT TOTAL TIME 583.6 ENGINE HOURS.  (X)					1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
1998042400255	19980424	00255	SW  	1998	4	24	HAI00000067      	1	19960307	G	2840	222366621103	FUEL FILTER     			BELL  	206   	206L        	1181522	SW  										BYPSSS SWITCH	MALFUNCTION     	H				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			FS	01	108W					52034				AIRFRAME FUEL FILTER IMPENDING BYPASS SWITCH MALFUNCTIONING.  BYPASS LIGHT COMES ON AND OFF WITH NO CONTAMINATION FOUND 	IN FILTER. REPLACED WITH NEW FILTER.					1	G	7	1 	3U				H2SW    					 
1998042400256	19980424	00256	SW  	1998	4	24	HAI00000068      	1	19960307	G	6310	289051098	SEAL            			BELL  	206   	206B        	1181511	SW  										ENG /XMSN	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	345RR					2107				SEAL IS WORN EXCESSIVELY.  CUSTOMER COMPLAINT IS THAT ALL OF THE "2890" SERIES SEALS  WITH THE BLACK MATERIAL SEEM TO WE	AR DEEPER GROOVES AT A FASTER RATE THAN THE CHICAGO RAWHIDE SEALS WITH THE RED MATERIAL.  THIS IS FOR INFORMATION ONLY.					1	G	7	1 	3U				H2SW    					 
1998042400257	19980424	00257		1998	4	24	HAI00000069      	1	19960404	G	2550	206072903101	CABLE ASSY      																	CARGO HOOK	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		1421 								WHILE FERTILIZING DURING A FUEL STOP ON A NORMAL WALK-AROUND,  NOTICED SOMETHING HANGING DOWN BELOW THE CARGO HOOK.  FUR	THER INVESTIGATION,  FOUND THE CARGO HOOK EMERGENCY RELEASE CABLE BROKEN COMPLETELY THROUGH 2 INCHES FROM CONNECTION ON 	CARGOHOOK. REPLACED WITH NEW CABLE.																	 
1998042400258	19980424	00258	SW  	1998	4	24	HAI00000075      	1	19960528	G	3213	206033108001	FITTING         			BELL  	206   	206L        	1181522	SW  										RT CROSSTUBE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	108W	1122 				52034				FWD CROSS TUBE STRAP ASSY WORN INTO RIGHT FWD CROSS TUBE FITTING. REPLACED FITTING PER PRODUCT SUPPORT WEAR  LIMITS.						1	G	7	1 	3U				H2SW    					 
1998042400259	19980424	00259	SW  	1998	4	24	HAI00000076      	1	19960528	G	6320	206040810103	INDICATOR       			BELL  	206   	206L        	1181522	SW  										TRANSMISSION	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	108W	1526 				52034				DURING 1500 TRANSMISSION SUN GEAR INSPECTION COMPLETED TB206L-95-183 PER BULLETIN.   REPLACED WITH NEW PART FROM BHT						1	G	7	1 	3U				H2SW    					 
1998042400260	19980424	00260	SW  	1998	4	24	HAI00000080      	1	19960528	G	6410	206310105101	BEARING         			BELL  	206   	206L        	1181522	SW  										T/R BLADE	DEFECTIVE       	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	108W	863  				52034				INSTALLED BEARING  IN T/R BLADE TO C/W TB206L-94-172 REV.A PT. I.  BLADE ALIGNMENT WOULD NOT MEET THE DIMENSIONAL REQUIR	EMENT DUE TO THE AXIAL PLAY IN THE NEW BEARING. REPLACED WITH NEW BEARING FROM CSF STOCK.					1	G	7	1 	3U				H2SW    					 
1998042400261	19980424	00261	SW  	1998	4	24	HAI00000081      	1	19960528	G	6410	206010733003	SLEEVE          			BELL  	206   	206L        	1181522	SW  										T/R BLADE	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	108W	863  				52034				INSTALLED BRG. IN T/R BLADE TO W/C TB206L-94-172 REV.A,PT.I.  BLADE ALIGHNMENT WOULD NOT MEET THE DIMENSIONAL REQUIREMEN	T DUE TO THE AXIAL PAY IN THE NEW BEARING. REPLACED WITH NEW STOCK FROM CSF.					1	G	7	1 	3U				H2SW    					 
1998042400262	19980424	00262		1998	4	24	HAI00000084      	1	19960627	G	7933	MS280343	TEMP BULB       																	OIL TEMP	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01										INSTALLED NEW PART FROM CSF STOCK AND IT FAILED. REPLACED WITH NEW PART FROM CSF STOCK.																			 
1998042400263	19980424	00263	GL  	1998	4	24	HAI00000088      	2	19961018	G	7210	406340104101	SEAL            								ALLSN 	250C  	250C30      	03013	GL  					ENG GR BOX	TORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01										SEAL IS TORN. REPLACED WITH NEW SEAL FROM CSF STOCK.											3	U			E1GL				 
1998042400269	19980424	00269	SW  	1998	4	24	HAIGJQR0063      	1	19960201	G	5350	206020114131S	FAIRING         			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	MIS MFG         	H			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	13	53W					3587				THIS FAIRING WAS ORDERED FROM BELL - BUT IT DOESN'T FIT - IT IS ONE-HALF INCH SHORT.						1	G	7	1 	3U				H2SW    					 
1998042400270	19980424	00270	SW  	1998	4	24	HAIGJQR0064      	1	19960201	G	6320	206075678107	INDICATOR       			BELL  	206   	206L        	1181522	SW  										XMSN TEMP	FAILED          	H			GJQR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	13	108W	1344 				52034				INDICATOR IS ERRATIC - WILL NOT READ ABOVE 50 DEGREE - DROPS TO ZERO DURING FLIGHT, UNRELIABLE. REPLACED WITH NEW INDICA	TOR FROM BELL.					1	G	7	1 	3U				H2SW    					 
1998042400271	19980424	00271	SW  	1998	4	24	HAIGJQR0100      	1	19961204	G	6410	206016201131	BLADE           			BELL  	206   	206B        	1181511	SW  										T/R	DEBONDED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	96NW	264  				4389				BLADE REPLACED DUE TO DEBOND DETECTED DURING POST FLIGHT.  BLADE MAKES CLICKING SOUND AND DELAMINATION PRESENT AT BLADE 	ROOT DOUBLER AREA. REPLACED WITH CSF STOCK.					1	G	7	1 	3U				H2SW    					 
1997041000498	19970410	00498	SW  	1997	4	10	HAIW6HR0048      	1	19961112	G	3340	G62504	LIGHT           		222175302105	BELL  	222   	222U        	1182140	SW  										STROBE	CIRCUIT-GROUNDED	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	429MA	116  				47523				PART IS CIRCUIT-GROUNDED. LIGHT WILL NOT EXTEND AND POPS CIRCUIT BREAKER.						1	G	7	2 	3U				H9SW    					 
1997041000499	19970410	00499	SW  	1997	4	10	HAIW6HR0049      	1	19961112	G	2840	7G547	SWITCH          		206061600021	BELL  	206   	206B1       	1181503	SW  										FUEL SYS	DEFECTIVE       	E		A	W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	68TJ				206	1301				FUEL PRESSURE SWITCH IS DEFECTIVE.  PART APPEARED TO BE DEFECTIVE UPON INSTALLATION.  2 OTHER SWITCHES PREVIOUSLY INSTAL	LED FAILED WITHIN 5 MINS.  OF USE..  REPLACED WITH NEW.					1	G	7	1 	3U				H2SW    					 
1997041000500	19970410	00500	SW  	1997	4	10	HAIW6HR0050      	1	19961113	G	2913	65132	PUMP            		222180004107	BELL  	222   	222U        	1182140	SW  										#1 POSITION HYD	WORN EXCESSIVELY	E			W6HR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	21	415MA					47568				PUMP IS WORN EXCESSIVELY. PUMP LEAKS AT SHAFT SEAL. PUMP HAS ONLY BEEN INSTALLED 1 MONTH.   BHT P/N: 222-380-009-103. . 	REPLACED WITH SERVICEABLE UNIT.					1	G	7	2 	3U				H9SW    					 
1997041000501	19970410	00501	SW  	1997	4	10	HAIW6HR0054      	1	19961212	G	6330	222031662105	BEARING         		222031662105	BELL  	222   	222U        	1182140	SW  										XMSN MT	WORN EXCESSIVELY	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	429MA	490  			0814	47523				PART IS WORN EXCESSIVELY. ELASTOMERIC MATERIAL IS EXTRUDING. PART BEING HELD FOR DISPOSITION.  RDM 12-31-96.						1	G	7	2 	3U				H9SW    					 
1997041000502	19970410	00502	SW  	1997	4	10	HAIW6HR0055      	1	19961212	G	6330	LB9130251NV	FLEXURE         		222031601105	BELL  	222   	222U        	1182140	SW  										NODAL BEAM	BROKEN          	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	415MA	189  				47568				PART IS BROKEN. RUBBER IS SEPERATED FROM END FITTINGS.						1	G	7	2 	3U				H9SW    					 
1997041000503	19970410	00503	SW  	1997	4	10	HAIW6HR0056      	1	19961212	G	6330	LB9130251NV	FLEXURE         		222031601106	BELL  	222   	222U        	1182140	SW  										NODAL BEAM	BROKEN          	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	415MA	189  				47568				PART IS BROKEN. RUBBER IS SEPERATED FROM END FITTINGS. RETURNED TO MANU FOR CREDIT ( REQUEST REPLACEMENT PART)						1	G	7	2 	3U				H9SW    					 
1997041000504	19970410	00504	NE  	1997	4	10	HAIW6HR0061      	2	19961220	G	7320	222360703101	SOLENOID        		222060001103	BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					FUEL CONTROL	CIRCUIT-SHORTED 	E			W6HR	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			WP	21	429MA	2    				47523				PART IS CIRCUIT-SHORTED.  PART FAILED - PART GOT EXTREMELY HOT. REPLACED WITH NEW PART  - WORKS O.K..						1	G	7	2 	3U	3	U		H9SW    	E5NE				 
1997041000505	19970410	00505	NE  	1997	4	10	HAIW6HR0062      	2	19961230	G	7320	222360703101	SOLENOID        		222060001103						LYC   	LTS101	LTS101750C1 	41560	NE  					FUEL CONTROL	DEFECTIVE       	E			W6HR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21										PART IS DEFECTIVE. UPON OPENING PACKAGE DURING "RECEIVING INSPECTION" FOUND LEVER ASSY. 'RETURN SPRING' OUT OF PLACE & U	NWOUND. HOLDING UNIT FOR DISPOSITION.										3	U			E5NE				 
1997041000506	19970410	00506	SW  	1997	4	10	HAIW6HR0063      	1	19961230	G	3340	G62504	LIGHT           		222175302105	BELL  	222   	222U        	1182140	SW  										SEARCH	SEIZED          	E			W6HR	K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	21	429MA					47523				PART IS SEIZED.  ASSY. WILL NOT EXTEND OR RETRACT.  ASSY. HAS BEEN IN SERVICE 2 WEEKS SINCE REPAIR.						1	G	7	2 	3U				H9SW    					 
1996011900254	19960119	00254	GL  	1996	1	19	HEEA966329       	2	19960102	G	7250	23032345	COUPLING        		23033185    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					3RD STAGE	STEP WEAR       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y	453  			CAT70022	45192	CAE860583			ENGINE REMOVED DUE TO TURBINE 3RD STAGE WHEEL REPLACEMENT.  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				 
1996011900255	19960119	00255	GL  	1996	1	19	HEEA966330       	2	19960102	G	7250	6886407	BLADE           		6898735     	AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					1ST STAGE WHEEL	ERROSION        	E			HEEA	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	03	5791M	951  			CAT25125	5116	CAE840056			ENGINE REMOVED DUE TO LOW POWER AND OIL LEAKING.  UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING:  50% OF 1ST STAG	E WHEEL SULFIDATED AND DELAMINATED ON FORWARD SIDE OF BLADES AND EROSION OF ALL LEADING EDGES AND BLADE TIPS. SCRAPPED 1	ST STAGE WHEEL.				1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1996011900256	19960119	00256	GL  	1996	1	19	HEEA966331       	2	19960102	G	7250	6886407	BLADE           		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					1ST STAGE WHEEL	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E	725  			CAT31716F	S806	CAE836341			ENGINE REMOVED DUE TO CYCLED OUT 2ND STAGE WHEEL.  UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING:  SULFIDATION OF	 1ST STAGE WHEEL BLADES CAUSING DELAMINATION ON AFT SIDE OF LEADING EDGES. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996011900257	19960119	00257	GL  	1996	1	19	HEEA966332       	2	19960102	G	7250	6886407	BLADE           		6898735     	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					1ST STAGE WHEEL	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2285B	1493 			CAT40231	3642	CAE836318			ENGINE REMOVED DUE TO CYCLED OUT WHEELS.  UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING:  SULFIDATION CAUSING SLI	GHT DELAMINATION ON FORWARD SIDE OF ALL 1ST STAGE WHEEL BLADES AND EROSION ON LEADING EDGE. SCRAPPED 1ST STAGE WHEEL.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1996011900258	19960119	00258	GL  	1996	1	19	HEEA966334       	2	19960102	G	7250	6886407	BLADE           		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					1ST STAGE WHEEL	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	105WK	832  			CAT38001F	S812	CAE834578			ENGINE REMOVED DUE TO CYCLED OUT WHEELS.  UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING:  SULFIDATION ON ALL 1ST 	STAGE WHEEL BLADES CAUSING SLIGHT DELAMINATION. SCRAPPED 1ST STAGE WHEEL.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996011900259	19960119	00259	EU  	1996	1	19	HEEA966335       	1	19960102	G	7712		TORQUEMETER     		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	7170D	798  			CAT127943	S840	CAE822237F			ENGINE REMOVED DUE TO TORQUE METER LEAKING.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996011900260	19960119	00260		1996	1	19	HEEA966340       	4	19960104	G	2370	9806019001	CVR             			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7128R	3066 				36007				CVR INTERMITTENTLY INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1996011900261	19960119	00261		1996	1	19	HEEA966341       	4	19960104	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	62127					52023				DOES NOT TRANSMIT CODE 0401 OR 1201 NO REPLY. REPLACED DEFECTIVE V101 CAVITY OSCILLATOR.  ADJUSTED AS NEEDED AND BENCH C	HECK GOOD.					1	G	7	1 	3U				H2SW    					 
1996011900262	19960119	00262		1996	1	19	HEEA966342       	4	19960104	G	2312	40001278500	TRANSCEIVER     		RT406F      	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7171A					S838				NO MIC GAIN DEVIATION. REPLACED SYNTHESIZER BOARD P/N 300-014140-00 FROM ANOTHER UNIT.  REPAIRED PROBLEM.  UNIT BENCH CH	ECK GOOD.					1	G	7	2 	3U				H3EU    					 
1996011900263	19960119	00263	SW  	1996	1	19	HEEA966343       	1	19960104	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				ALL NEEDLES HAVE EXCESSIVE NEEDLE SPLIT.  #1 AND ROTOR NEEDLES STICK.						1	G	7	2 	4U				H4SW    					 
1996011900264	19960119	00264	SW  	1996	1	19	HEEA966344       	1	19960104	G	6220	412010179105	CONE            		412010100193	BELL  	412   	412         	1182202	SW  										M/R HUB	FRETTING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z	3242 			AAD50024	33077				FRETTING FABRIC GALLED OUT.						1	G	7	2 	4U				H4SW    					 
1996011900265	19960119	00265	SW  	1996	1	19	HEEA966345       	1	19960104	G	6220	412010124109	BOLT            		412010100193	BELL  	412   	412         	1182202	SW  										M/R	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z	2234 			AAD50024	33077				PLATING FLAKING AT EDGE OF BOLT SHANK.						1	G	7	2 	4U				H4SW    					 
1996011900266	19960119	00266	SW  	1996	1	19	HEEA966346       	1	19960104	G	6220	412010124109	BOLT            		412010100193	BELL  	412   	412         	1182202	SW  										M/R	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z	2234 			AAD50024	33077				PLATING FLAKING AT EDGE OF BOLT SHANK.						1	G	7	2 	4U				H4SW    					 
1996011900267	19960119	00267	SW  	1996	1	19	HEEA966347       	1	19960104	G	6220	412010124109	BOLT            		412010100193	BELL  	412   	412         	1182202	SW  										M/R	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z	2234 			AAD50024	33077				PLATING FLAKING AT EDGE OF BOLT SHANK.						1	G	7	2 	4U				H4SW    					 
1996011900268	19960119	00268	SW  	1996	1	19	HEEA966348       	1	19960104	G	5302	206032308003	FRAME           			BELL  	206   	206L1       	1182107	SW  										TAILBOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				CRACKED IN UPPER L/H CORNER. REPLACED WITH SERVICEABLE FRAME.						1	G	7	1 	3U				H2SW    					 
1996011900269	19960119	00269	SW  	1996	1	19	HEEA966349       	1	19960104	G	5302	206032308103S	FRAME           			BELL  	206   	206L3       	1182108	SW  										TAILBOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8589X					51487				FRAME CRACKED UPPER R/H BOLT AREA. REPLACED WITH SERVICEABLE FRAME.						1	G	7	1 	3U				H2SW    					 
1996011900270	19960119	00270	SW  	1996	1	19	HEEA966350       	1	19960104	G	5302	206032308103	FRAME           			BELL  	206   	206L1       	1182107	SW  										TAILBOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2251Z					45756				PART IS CRACKED.  L/H UPPER T/B FITTING CRACKED P/N 206-031-329-003.  TAILBOOM MOUNT FRAME P/N 206-032-308-103S CRACKED 	AT UPPER L/H MOUNT HOLE. REPLACED FITTING UPPER L/H SIDE WITH 206-031-329-103S AND REPLACED T/B FRAME WITH P/N 206-032-3	08-103S.				1	G	7	1 	3U				H2SW    					 
1996011900271	19960119	00271	SW  	1996	1	19	HEEA966351       	1	19960104	G	5320	206031200076	STRAP           			BELL  	206   	206B        	1181511	SW  										AFT CABIN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2269A					3608				PART IS CRACKED.  AFT CABIN OVERHEAD BOX BEAM R/H STRAP P/N 206-031-200-076 CRACKED OUT AT CENTER R/H SUPPORT. INSTALLED	 NEW STRAP ASSEMBLY.					1	G	7	1 	3U				H2SW    					 
1996011900272	19960119	00272		1996	1	19	HEEA966352       	4	19960104	G	2210	214074303115	AMPLIFIER ASSY  			BELL  	214   	214ST       	1182106	SW  										AUTOFLT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				PITCH WILL NOT ENGAGE.						2	G	7	2 	4U				H10SW   					 
1996011900273	19960119	00273	NE  	1996	1	19	HEEA966353       	2	19960104	G	7320	3240864	SCREEN ASSY     		324473513   	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL INLET	SPRING FAILED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22347				B14461	36005				AIRCRAFT EXPERIENCED 10% TORQUE SPLIT IN FLIGHT WITH TORQUE AT OR ABOVE 90%.  UPON CHECK OF SINGLE ENGINE BEEP RANGES NO	TED #1 ENGINE FULL INCREASE RPM 2% HIGH.  WHEN THROTTLE WAS ROLLED BACK TO IDLE, THE ENGINE WOULD DECEL ONLY TO 74% N1 I	NSTEAD OF  61%.  ALSO THE THROTTLE WOULD SELF-ADVANCE RAPIDLY TO FULL OPEN POSITION IF IT WASN'T HELD OR FRICTIONED.  RE	PLACED THE AFCU AND DURING SWAP OF FUEL TUBES FOUND PIECES OF THE FUEL INLET SCREEN ASSEMBLY SPRING IN THE INLET PORT, A	ND ADDITIONAL PIECES LODGED IN THE PORT.  IT APPEARS THAT THE INLET SCREEN ASSEMBLY MAY HAVE BEEN INSTALLED INCORRECTLY 	FROM THE MANUFACTURER. REPLACED AFCU.  NOTE:  THE AFCU WAS OVERHAULED BY PRATT & WHITNEY MAY 1995	1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1996011900274	19960119	00274	SW  	1996	1	19	HEEA966354       	1	19960104	G	5321	412030324101	PANEL           			BELL  	412   	412         	1182202	SW  										RT FLOOR	WRONG STUD      	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	3893N					33010				STUD P/N 120-064-3HN WAS INSTALLED IN WRONG POSITION. HAD TO REMOVE IT TO MAKE REPAIR TO STYROFOAM AND INSTALL PROPER ST	UD P/N 120-142-1. REMOVED PANEL AND MADE HOLE IN STYROFOAM.  REMOVED STUD AND INSTALLED SERVICEABLE STUD.  REPAIRED HOLE	 AND REINSTALLED PANEL.				1	G	7	2 	4U				H4SW    					 
1996011900275	19960119	00275	EU  	1996	1	19	HEEA966355       	1	19960104	G	3242	419210E	CALIPER         			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR BRAKE	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	624MB					S751				PISTON WILL NOT RETRACT. REPLACED WITH SERVICEABLE CALIPER.						1	G	7	2 	3U				H3EU    					 
1996011900276	19960119	00276	EU  	1996	1	19	HEEA966356       	1	19960104	G	2810	FTA017522	CELL            			BOLKMS	105   	BO105S      	5626006	EU  										AUX TANK	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				AFT FUEL CELL LEAKING FUEL. INSTALLED SERVICEABLE FUEL CELL.						1	G	7	2 	3U				H3EU    					 
1996011900277	19960119	00277	NE  	1996	1	19	HEEA966357       	1	19960104	G	6210	7615009100041A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2743E	7948 				760155				PART IS CRACKED.  SPAR CRACK AT THE TIP.  THE CRACK STARTED FROM THE OUTER HOLE FOR THE "C" BLOCK BOLT. SCRAPPED M/R BLA	DE.					1	G	7	2 	3U				H1NE    					 
1996011900278	19960119	00278	NE  	1996	1	19	HEEA966358       	1	19960104	G	6210	7615009100051A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U	9252 				760167				BLADE IS CRACKED.  SPAR CRACKED AT ROOT END. SCRAPPED M/R BLADE.						1	G	7	2 	3U				H1NE    					 
1996011900279	19960119	00279	NE  	1996	1	19	HEEA966359       	1	19960104	G	6321	7819712	ARMATURE        			SKRSKY	S76   	S76A        	8143006	NE  										ROTOR BRAKE	SHORTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G					760232				ARMATURE SHORTED.  IT WAS INSTALLED IN ROTOR BRAKE S/N 479.						1	G	7	2 	3U				H1NE    					 
1996011900280	19960119	00280		1996	1	19	HEEA966360       	4	19960104	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				WILL NOT READ OUT CORRECT ALTITUDE. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H1NE    					 
1996011900281	19960119	00281		1996	1	19	HEEA966361       	4	19960104	G	3455	066104701	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT ADF	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5427S					760168				WILL NOT POINT CORRECTLY IN TEST MODE AND CANNOT ADJUST VOLUME. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H1NE    					 
1996011900282	19960119	00282		1996	1	19	HEEA966362       	4	19960105	G	2312	40001278500	TRANSCEIVER     		RT406       	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT VHF	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5418A					S800				NO TRANSMIT DEVIATION AND WEAK RECEIVE.						1	G	7	2 	3U				H3EU    					 
1996011900283	19960119	00283		1996	1	19	HEEA966363       	4	19960105	G	3442	MI585202	ANT PEDESTAL    			BELL  	214   	214ST       	1182106	SW  										RADAR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				RADAR DOES NOT PAINT TARGETS.						2	G	7	2 	4U				H10SW   					 
1996012600208	19960126	00208		1996	1	26	HEEA966364       	4	19960105	G	3442	MI5853011	INDICATOR       	HONEYWELL   	P500        															COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR HAS BLANK DISPLAY.																			 
1996012600209	19960126	00209	SW  	1996	1	26	HEEA966365       	1	19960105	G	5330	214030325103	DOOR ASSY       			BELL  	214   	214ST       	1182106	SW  										TAIL BOOM ACCESS	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				DOOR IS CRACKED.  DOOR CRACKED 4.3" FROM EDGE AT AFT L/H BOLT HOLE GOING INBOARD.  (THIS DOOR WAS NEW STYLE THICKER DOOR	)  REPLACED AS PER ASB 214ST-82-4 DATED 11-19-82 FROM 214-030-325-003 TO 214-030-324-103. COMPLIED WITH TB 214ST-95-144 	DATED 3-13-95 AND REPLACED ACCESS DOOR.				2	G	7	2 	4U				H10SW   					 
1996012600210	19960126	00210	EU  	1996	1	26	HEEA966366       	1	19960105	G	5210	350A2510842001	HANDLE          			SNIAS 	350   	AS350B2     	8680813	EU  										DOOR LATCH ASSY	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				LOCK PIN HANDLE BROKE OFF. REPLACED LATCH ASSEMBLY.						1	G	7	1 	3U				H9EU    					 
1996012600211	19960126	00211		1996	1	26	HEEA966367       	4	19960105	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	707AE					760276				ENTER BUTTON INTERMITTENT. SENT TO ARNAV SYSTEMS FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H1NE    					 
1996012600212	19960126	00212	SW  	1996	1	26	HEEA966368       	1	19960105	G	7810	212061201012	EJECTOR ASSY    			BELL  	412   	412         	1182202	SW  										RT EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				EJECTOR ASSY EXCESSIVE INTERFERENCE WITH EXHAUST STACK.						1	G	7	2 	4U				H4SW    					 
1996012600213	19960126	00213		1996	1	26	HEEA966369       	4	19960105	G	3457	0110014700	ANTENNA         	GARMIN      		BELL  	206   	206L1       	1182107	SW  										COCKPIT GPS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5000K					45167				GPS ANTENNA WILL NOT PICK UP SATELLITE.						1	G	7	1 	3U				H2SW    					 
1996012600214	19960126	00214		1996	1	26	HEEA966370       	4	19960105	G	3416	212070238007	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	ERROR           	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				PILOT REPORTED NEEDLE HAS 700 FOOT ERROR						1	G	7	2 	4U				H4SW    					 
1996012600215	19960126	00215	NE  	1996	1	26	HEEA966371       	1	19960105	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										T/R	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K	9015 				760082				HOLE THROUGH THE LEADING EDGE STRIP ON PADDLE "B".						1	G	7	2 	3U				H1NE    					 
1996012600216	19960126	00216	SW  	1996	1	26	HEEA966372       	1	19960105	G	6220	412010190103	SPINDLE         			BELL  	412   	412         	1182202	SW  										M/R	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K	5553 				36001				BEARING UNBONDED FROM SPINDLE. SENT TO LORD MANUFACTURING FOR INSPECTION AND REPAIR.						1	G	7	2 	4U				H4SW    					 
1996012600217	19960126	00217		1996	1	26	HEEA966373       	4	19960105	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	6748D					51106				BENCH CHECK NEEDED.  INSPECTED UNIT AND FOUND UNIT HAS NO TRANSMIT.  FOUND OUTPUT OF MICROPROCESSOR I405 TO BE BAD.  REP	LACED INTEGRATED CIRCUITS I402 AND I406.  REPLACED CAVITY OSCILLATOR V101.  REPLACED BROKEN TRANSISTOR Q415 AND INSTALLE	D HEATSINKBEHIND TRANSISTOR Q415.  REPLACED RESISTOR/CAPACITOR PACK RM401.				1	G	7	1 	3U				H2SW    					 
1996012600218	19960126	00218		1996	1	26	HEEA966374       	4	19960105	G	2312	40001452502	TRANSCEIVER     		RT138F      	BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT VHF	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	132AE					7238				WEAK TRANSMIT AND RECEIVE. ADJUSTED GUARD RECEIVER CRYSTAL AND ADJUSTED MIC GAIN DEVIATION.  REPAIRED PROBLEM.  UNIT BEN	CH CHECK GOOD.					1	G	7	2 	3U			NC	H13EU   					 
1996012600219	19960126	00219	GL  	1996	1	26	HEEA966375       	2	19960108	G	7230	23035262	BEARING         		23033193    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COMP NR 1 BRG	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8589X	364  			CAC90854	51487	CAE890024			ENGINE REMOVED DUE TO CRACKED SCROLL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING:  2 EACH CRACKS IN SEPERA	TOR ON #1 ROLLER BEARING AND WORN TANGS AND TANGSLOTS ON CARBON SEAL ASSEMBLY. NEW PARTS INSTALLED. REFERENCE:  AFA#2445	3A.  NOTE:  SEE MMIR#6376 FOR CARBON SEAL ASSEMBLY.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1996012600220	19960126	00220	GL  	1996	1	26	HEEA966376       	2	19960108	G	7230	23004513	CARBON SEAL     		23033193    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COMPRESSOR	WORN TANGS      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8589X	364  			CAC90854	51487	CAE890024			ENGINE REMOVED DUE TO CRACKED SCROLL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING:  2 EACH CRACKS IN SEPERA	TOR ON #1 ROLLER BEARING AND WORN TANGS AND TANGSLOTS ON CARBON SEAL ASSEMBLY. NEW PARTS INSTALLED.REFERENCE:  AFA#24453	A.  NOTE:  SEE MMIR#6375 FOR #1 ROLLER BEARING.				1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1996012600221	19960126	00221	GL  	1996	1	26	HEEA966377       	2	19960108	G	7250	6886407	WHEEL           		6898735     						ALLSN 	250C  	250C20B     	03013	GL  					1ST STAGE	BLADE DELAM     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		1737 			CAT37072		CAE836462			ENGINE REMOVED DUE TO TURBINE OVERHAUL.  UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING:  SULFIDATION CAUSING DELA	MINATION ON ALL 1ST STAGE WHEEL BLADES AND EROSION OF ALL LEADING EDGES. SCRAPPED 1ST STAGE WHEEL.										3	U			E4CE				 
1996012600222	19960126	00222		1996	1	26	HEEA966378       	4	19960109	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	706AE					760275				LOSES WAYPOINTS WITH POWER OFF AND UNIT UNRELIABLE.						1	G	7	2 	3U				H1NE    					 
1996012600223	19960126	00223	EU  	1996	1	26	HEEA966379       	1	19960109	G	6310	4638202007	CLUTCH          		4638001004  	BOLKMS	105   	BO105S      	5626006	EU  										FREEWHEEL	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4294R	177  			1328	S860				CLUTCH SLIPPAGE AND SUDDEN ENGAGEMENT. REPLACED WITH SERVICEABLE CLUTCH.						1	G	7	2 	3U				H3EU    					 
1996012600224	19960126	00224	EU  	1996	1	26	HEEA966380       	1	19960109	G	3242	AHA1121M0D1234	CALIPER         			BOLKMS	105   	BO105S      	5626006	EU  										CALIPER	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4302G					S853				PISTON WILL NOT RETRACT. REPLACED WITH SERVICEABLE CALIPER.						1	G	7	2 	3U				H3EU    					 
1996012600225	19960126	00225	EU  	1996	1	26	HEEA966381       	1	19960109	G	6710	SC50811	SERVO CONTROL   			SNIAS 	350   	AS350B2     	8680813	EU  										CYCLIC RT/LT	BINDING         	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	60951	1686 				2771				CYCLIC HAS BINDING WHEN THE CYCLIC IS MOVED LEFT AND RIGHT. REPLACED WITH SERVICEABLE SERVO.						1	G	7	1 	3U				H9EU    					 
1996012600226	19960126	00226	SW  	1996	1	26	HEEA966382       	1	19960109	G	2432	3055401C	BATTERY         			BELL  	206   	206L1       	1182107	SW  										DC SYS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2770Y					45291				BATTERY WILL NOT ACCEPT A CHARGE.  INSPECTED BY ACCESSORY SHOP AND FOUND THIS BATTERY WAS REMOVED NUMEROUS TIMES FOR BEI	NG WEAK.					1	G	7	1 	3U				H2SW    					 
1996012600227	19960126	00227	NE  	1996	1	26	HEEA966383       	1	19960109	G	2435	230811011	ARMATURE        			SKRSKY	S76   	S76A        	8143006	NE  										START/GEN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CAUSES UNIT TO DRAW EXCESSIVE AMPS ON SEATER AND ARMATURE SHOWS SIGNS OF MAGNETISM ON GROWLER. .  RECEIVED REWOUND ON 10	-20-95.					1	G	7	2 	3U				H1NE    					 
1996012600228	19960126	00228	SW  	1996	1	26	HEEA966384       	1	19960109	G	6330	206033506103	RESTRAINT       			BELL  	206   	206L        	1181522	SW  										TRANSMISSION	BEARING WORN    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077B	1439 				52037				TRANSMISSION RESTRAINT BEARINGS WORN.						1	G	7	1 	3U				H2SW    					 
1996012600229	19960126	00229		1996	1	26	HEEA966386       	4	19960109	G	3423	C2300DL4B	COMPASS         	MASCO       																COCKPIT	MIS MFG         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BAD FROM STOCK.  ONE WIRE IS MISSING.  NEEDS TWO WIRES.																			 
1996012600230	19960126	00230	EU  	1996	1	26	HEEA966387       	1	19960109	G	2434	230321823	STATOR          			BOLKMS	105   	BO105S      	5626006	EU  										DC GEN	MIS OHAULED     	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										STATOR BRUSH LEADS ARE TOO SHORT TO REACH BRUSH BOX SCREWS.   RECEIVED REWOUND 3-23-95.						1	G	7	2 	3U				H3EU    					 
1996012600231	19960126	00231	SW  	1996	1	26	HEEA966388       	1	19960109	G	7722	35712519129	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10814					45415				INDICATOR READS HIGH AT 700 DEGREES AND ABOVE.						1	G	7	1 	3U				H2SW    					 
1996012600232	19960126	00232	NE  	1996	1	26	HEEA966389       	1	19960109	G	2435	230811011	ARMATURE        			SKRSKY	S76   	S76A        	8143006	NE  										START/GEN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INSTALLED ARMATURE IN STARTER GENERATOR AND FOUND ARMATURE CAUSES EXCESSIVE ARCHING.						1	G	7	2 	3U				H1NE    					 
1996012600233	19960126	00233		1996	1	26	HEEA966390       	4	19960109	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	3911L					33023				INDICATOR FLAG STICKS OUT OF VIEW.						1	G	7	2 	4U				H4SW    					 
1996021300003	19960213	00003	EU  	1996	2	13	HEEA966391       	1	19960109	G	3340	02471131	SEARCH LIGHT    			BOLKMS	117   	BK117A3     	5626015	EU  										REFLECTOR	MIS REPAIRED    	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										SEARCH LIGHT FOCUS REFLECTOR LOOSE, WILL NOT FOCUS.   TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H13EU   					 
1996021300004	19960213	00004		1996	2	13	HEEA966392       	4	19960109	G	3416	8140BS20LW	ALTIMETER       																	COCKPIT	MIS REPAIRED    	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										ENCODING ALTIMETER NEEDLE LOOSE IN CASE WHEN PART RECEIVED FROM REPAIR.																			 
1996012600234	19960126	00234	SW  	1996	1	26	HEEA966393       	1	19960110	G	2730	214001970107	ACTUATOR ASSY   			BELL  	214   	214ST       	1182106	SW  										ELEV SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				ACTUATOR ASSY DEFECTIVE.  #1 ELEVATOR SYSTEM INOPERATIVE.						2	G	7	2 	4U				H10SW   					 
1996012600235	19960126	00235	EU  	1996	1	26	HEEA966394       	1	19960110	G	7712	305731365	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										ENG TORQUE	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	1401 				2820				TORQUE IND. READS LOW IN UPPER RANGE.						1	G	7	1 	3U				H9EU    					 
1996012600236	19960126	00236	SW  	1996	1	26	HEEA966395       	1	19960110	G	5260	214001426101	BRACKET         			BELL  	214   	214ST       	1182106	SW  										STEP ACTUATOR	MIS MACHINED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				BRACKET IS NOT MACHINED PROPERLY.  UNABLE TO INSTALL BEARING BETWEEN BRACKET AS REQUIRED.						2	G	7	2 	4U				H10SW   					 
1996012600237	19960126	00237		1996	1	26	HEEA966396       	4	19960110	G	2210	7012409901	PITCH ACTUATOR  			BOLKMS	117   	BK117B1     	5626012	EU  										AUTOPILOT SYS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	117BK					7229				UNIT UNABLE TO TEST AUTO PILOT SYSTEM.						1	G	7	2 	3U				H13EU   					 
1996012600238	19960126	00238	EU  	1996	1	26	HEEA966397       	1	19960110	G	7714	1179405603	INDICATOR N1    			BOLKMS	117   	BK117B1     	5626012	EU  										ENG N1	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	117BK					7229				N1 INDICATOR INOPERATIVE.  NO GAUGE INDICATION ON ENGINE START.						1	G	7	2 	3U				H13EU   					 
1996012600239	19960126	00239		1996	1	26	HEEA966398       	4	19960110	G	3416	10222011886	ALTIMETER       			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	117BK					7229				ALTIMETER INOPERATIVE.						1	G	7	2 	3U				H13EU   					 
1996012600240	19960126	00240	EU  	1996	1	26	HEEA966399       	1	19960110	G	2432	501122803	BATTERY         			BOLKMS	117   	BK117B1     	5626012	EU  										EMERG POWER	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	117BK					7229				EMERGENCY POWER BATTERY INOPERATIVE.						1	G	7	2 	3U				H13EU   					 
1996012600241	19960126	00241	EU  	1996	1	26	HEEA966400       	1	19960110	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										ENG N1	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	117BK					7229				ENGINE N1 INDICATOR INOPERATIVE.						1	G	7	2 	3U				H13EU   					 
1996012600242	19960126	00242	SW  	1996	1	26	HEEA966401       	1	19960110	G	6340	214074280107	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N	54   				33010				COULD NOT ADJUST RPM LIMIT DETECTOR.						1	G	7	2 	4U				H4SW    					 
1996012600243	19960126	00243	SW  	1996	1	26	HEEA966402       	1	19960110	G	7931	206075677103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE OIL	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8587X					51464				OIL PRESSURE READS TOO HIGH OUT OF TOLERANCE.						1	G	7	1 	3U				H2SW    					 
1996012600244	19960126	00244	SW  	1996	1	26	HEEA966403       	1	19960110	G	2840	384178103	SWITCH          			BELL  	412   	412         	1182202	SW  										FUEL INDICATION	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22608					33075				SWITCH PIN D NOT GROUNDED TO CASE.  CAUSES INDICATOR TO FLUCTUATE.						1	G	7	2 	4U				H4SW    					 
1996012600245	19960126	00245	NE  	1996	1	26	HEEA966404       	1	19960110	G	7810	7630507003044	EJECTOR         			SKRSKY	S76   	S76A        	8143006	NE  										EXHAUST	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										EJECTOR IMPROPER . RETURN TO SERVICE AS PER BATON ROUGE, LA FSDO.						1	G	7	2 	3U				H1NE    					 
1996012600246	19960126	00246	SW  	1996	1	26	HEEA966405       	1	19960110	G	2435	230811010	ARMATURE        			BELL  	206   	206L1       	1182107	SW  										START/GEN	SHORTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ARMATURE IS SHORTED AND CAUSING EXCESSIVE ARCHING.  RECEIVED REWOUND BY THRUST TECH AVIATION ON 6-7-95.  INSTALLED ON AI	RCRAFT ON 6-16-95 AND FAILED ON 11-21-95.					1	G	7	1 	3U				H2SW    					 
1996012600247	19960126	00247	SW  	1996	1	26	HEEA966406       	1	19960110	G	6710	214001347005	ACTUATOR ROTARY 			BELL  	412   	412         	1182202	SW  										CYCLIC	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7128R					36007				ROTARY ACTUATOR CAUSED BINDING IN LATERAL MOVEMENT OF CYCLIC.						1	G	7	2 	4U				H4SW    					 
1996012600248	19960126	00248		1996	1	26	HEEA966407       	4	19960110	G	3421	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546K					760082				VERT GYRO TUMBLES ADI.						1	G	7	2 	3U				H1NE    					 
1996012600249	19960126	00249	SW  	1996	1	26	HEEA966408       	1	19960110	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENG TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				NR1 ENGINE NEEDLE WILL NOT GO TO ZERO; INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1996012600250	19960126	00250	SW  	1996	1	26	HEEA966409       	1	19960110	G	2435	230321827	FIELD ASSY      			BELL  	206   	206L1       	1182107	SW  										START/GEN	OPEN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INSTALLED STATOR IN LIMIT.  HAD NO VOLTAGE OUTPUT ON TEST.  REMOVED AND FOUND STATOR TO HAVE OPEN WINDING, TO SHUNT WIND	ING AT A, D & E.					1	G	7	1 	3U				H2SW    					 
1996012600251	19960126	00251	SW  	1996	1	26	HEEA966412       	1	19960111	G	3212	214073929105	VALVE           			BELL  	214   	214ST       	1182106	SW  										FLOAT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FLOAT VALVE LEAKING OUT OF VENT PORT.						2	G	7	2 	4U				H10SW   					 
1996012600252	19960126	00252	EU  	1996	1	26	HEEA966413       	1	19960111	G	5610	706A39821064	SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  										SKY WINDOW	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				SEAL TORN. REPLACED WITH SERVICEABLE SEAL.						1	G	7	1 	3U				H9EU    					 
1996012600253	19960126	00253	EU  	1996	1	26	HEEA966414       	1	19960111	G	6720	350A33214501	ROD BEARING     			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				BEARING WORN. REPLACED WITH SERVICEABLE T/R P/C LINK.						1	G	7	1 	3U				H9EU    					 
1996012600254	19960126	00254	EU  	1996	1	26	HEEA966415       	1	19960111	G	2840	C100U4	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL INDICATING	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				FUEL TANK LIGHT SWITCH STICKS. REPLACED FUEL TANK PUSH BUTTON LIGHT SWITCH DUE TO STICKING.						1	G	7	1 	3U				H9EU    					 
1996012600255	19960126	00255	EU  	1996	1	26	HEEA966416       	1	19960111	G	5220	350A25109521	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										JETTISON DOOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				STRUT WILL NOT HOLD DOOR OPEN. REPLACED DOOR SWITCH.						1	G	7	1 	3U				H9EU    					 
1996012600256	19960126	00256	EU  	1996	1	26	HEEA966417       	1	19960111	G	5200	AIR106	HANDLE          			SNIAS 	350   	AS350B2     	8680813	EU  										DOOR	BROKE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				HANDLE BROKE AND CAME OFF "D" RING. REPLACED WITH SERVICEABLE HANDLE.						1	G	7	1 	3U				H9EU    					 
1996012600257	19960126	00257		1996	1	26	HEEA966418       	4	19960111	G	3422	200DC	GYRO COMPASS    			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6095S					2777				GYRO CYCLES ON/OFF DURING FLIGHT. REPLACED WITH SERVICEABLE GYRO.						1	G	7	1 	3U				H9EU    					 
1996012600258	19960126	00258	EU  	1996	1	26	HEEA966419       	1	19960111	G	3340	4580	LAMP            			SNIAS 	350   	AS350B2     	8680813	EU  										LANDING LIGHT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				LANDING LIGHT BULB BURNT. REPLACED WITH SERVICEABLE BULB.						1	G	7	1 	3U				H9EU    					 
1996012600259	19960126	00259	EU  	1996	1	26	HEEA966420       	1	19960111	G	6520	350A33215300	BEARING         		350A33211905	SNIAS 	350   	AS350B2     	8680813	EU  										T/R HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R	236  			A21A	2862				LAMINATED HINGE BEARINGS WORN. INSTALLED NEW TAIL ROTOR HUB ASSEMBLY.						1	G	7	1 	3U				H9EU    					 
1996012600260	19960126	00260	SW  	1996	1	26	HEEA966421       	1	19960111	G	2840	206063656001	TRANSMITTER     			BELL  	206   	206L1       	1182107	SW  										FUEL SYS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSMITTER HIGH OUT OF TOLERANCE, WILL NOT ADJUST AT FULL SCALE.						1	G	7	1 	3U				H2SW    					 
1996012600261	19960126	00261	EU  	1996	1	26	HEEA966422       	1	19960111	G	6720	AC67032	SERVO           			AEROSP	AS355 	AS355F1     	8680810	EU  										T/R	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5797X	1548 				5182				LEAKING AT PILOT VALVE AND BOTH ENDS OF CYLINDER ALSO OUT OF TIMING. SENT TO AMERICAN EUROCOPTER CORP. ..THEIR PROPERTY 	BEING RETURNED.  (PHI REQUESTS FOR CREDIT)					1	G	7	2 	3U				H11EU   					 
1996012600262	19960126	00262		1996	1	26	HEEA966423       	4	19960111	G	3420	6220876001	INDICATOR       		VIR30AGM    	BEECH 	200   	200CBEECH   	1152926	CE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39PH					BL3				DEAD NEEDLE; CONTINUOUS FLAG.  TIME SINCE REPAIR 4:00.						1	L	7	2 	4T				A24CE   					 
1996012600263	19960126	00263	EU  	1996	1	26	HEEA966424       	1	19960111	G	7160	350A54108421	SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  										ENG INTAKE	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				ENGINE AIR INTAKE SEAL TORN. REPLACED WITH SERVICEABLE SEAL.						1	G	7	1 	3U				H9EU    					 
1996012600264	19960126	00264	SW  	1996	1	26	HEEA966427       	1	19960112	G	6300	230030535101	ROD END         			BELL  	230   	230         	1182149	SW  										M/R	BEARING WORN    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	736  				23009				BEARING WORN; TEFLON GONE AND BEARING STARTING TO BECOME GALLED.						1	G	7	2 	3U			NC	H9SW    					 
1996012600265	19960126	00265	SW  	1996	1	26	HEEA966428       	1	19960112	G	6320	222340057103	CHIP DETECTOR   			BELL  	230   	230         	1182149	SW  										TRANSMISSION	SHORTED         	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	230UN	2588 				23009				CHIP PLUG HAS INTERNAL SHORT CAUSING TRANS CHIP LIGHT.						1	G	7	2 	3U			NC	H9SW    					 
1996012600266	19960126	00266	SW  	1996	1	26	HEEA966429       	1	19960112	G	6710	206062721105	ACTUATOR        			BELL  	230   	230         	1182149	SW  										M/R	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	473  				23009				ACTUATOR INTERMITTENTLY INOPERATIVE.						1	G	7	2 	3U			NC	H9SW    					 
1996012600267	19960126	00267	SW  	1996	1	26	HEEA966430       	1	19960112	G	7600	222060790101	BELLCRANK ASSY  			BELL  	230   	230         	1182149	SW  										ENG CONTROL	BEARING WORN    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	2731 				23009				BELLCRANK BEARING WORN.						1	G	7	2 	3U			NC	H9SW    					 
1996012600268	19960126	00268	NE  	1996	1	26	HEEA966431       	1	19960112	G	6210	7615009100051	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D	11742				760077				PART IS CRACKED.  BLADE IS DUE FOR TIME EXTENSION AND ALSO HAS SEPARATION ON THE TITANIUM LEADING EDGE STRIP WITH A CHOR	DWISE CRACK NEAR THE INBOARD END OF THE NICKEL STRIP.					1	G	7	2 	3U				H1NE    					 
1996012600269	19960126	00269		1996	1	26	HEEA966432       	4	19960112	G	2312	071121525	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	707AE					760276				CONTROL UNIT HAS CONSTANT STATIC. REPLACED FADED DISPLAY LENS, INTERMITTENT S102 TRANSFER SWITCH.  ALSO REPLACED HEADER 	P201 AND APPLIED HUMISEAL FOR HEADER MODIFICATION.  INSPECTED AND UNIT BENCH CHECK GOOD.					1	G	7	2 	3U				H1NE    					 
1996012600270	19960126	00270		1996	1	26	HEEA966433       	4	19960112	G	2312	4000103000	TRANSCEIVER     	WULFSBERG   	RT450       															COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSMIT POWER INTERMITTENT. TROUBLESHOT AND REPLACED C1  CAPACITOR, C2 CAPACITOR, C7 CAPACITOR, C8 CAPACITOR, CR1 DIODE	.  REPAIRED INTERMITTENT TRANSMIT PROBLEM.  BENCH CHECK GOOD.																		 
1996012600271	19960126	00271		1996	1	26	HEEA966434       	4	19960112	G	2312	4000106010	CONTROL UNIT    		C10         	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911NC					7026				NOT ALL PL TONES MATCH THUMBWHEEL TO DIGITAL READOUT. TROUBLESHOT AND REPLACED 8 EACH CRIMP CONNECTOR SOCKETS.  REPAIRED	.  BENCH CHECK GOOD.					1	G	7	2 	3U				H13EU   					 
1996012600272	19960126	00272		1996	1	26	HEEA966435       	4	19960112	G	3444	066106103	RADAR  ALTIMETER			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7171A					S838				NEEDLE STAYS ABOVE 50 FEET.  DOESN'T MOVE AFTER PRESSING BUTTON. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H3EU    					 
1996012600273	19960126	00273		1996	1	26	HEEA966436       	4	19960112	G	3453	4530093	RECEIVER        		ARNAV20     	BELL  	206   	206L3       	1182108	SW  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31077					51520				"O" BUTTON DOES NOT ILLUMINATE, "ENT" BUTTON HAS TO BE PRESSED VERY HARD AND SEVERAL TIMES TO FUNCTION.						1	G	7	1 	3U				H2SW    					 
1996012600274	19960126	00274	SW  	1996	1	26	HEEA966437       	1	19960112	G	2435	36B510954G2	CLUTCH          			BELL  	214   	214ST       	1182106	SW  										START/GEN	SLIPPAGE        	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										FAILS CLUTCH SLIPPAGE TEST.  IT WAS TESTED AS RECEIVED BY ACCESSORY OVERHAUL SHOP AND SLIPPED AT 195 INCH POUNDS.  TEST 	SPECS - 325 TO 375 INCH POUNDS.  ALSO END PLAY IS AT MAX .010 TEST-SPECS .004-.010.					2	G	7	2 	4U				H10SW   					 
1996012600275	19960126	00275		1996	1	26	HEEA966438       	4	19960112	G	2370	9806019001	CVR             			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	3122H	2633 				760233				CVR WILL NOT TEST OR WORK.						1	G	7	2 	3U				H1NE    					 
1996012600276	19960126	00276	NE  	1996	1	26	HEEA966439       	1	19960112	G	6210	7615009043051	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										M/R	MIS REPAIRED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TIP CAP WAS REPAIRED AT CTI 12-11-95.  THE TIP CAP DOES NOT FIT.   THE TOP LEADING EDGE HOLE DOES NOT LINE UP AND THE AB	RASION STRIP IS NOT STRAIGHT, PREVENTING THE TIP CAP TO FIT PROPERLY, ALSO THERE IS AN EXCESSIVE AMOUNT OF HYSOL EA9309.	3NABETWEEN THE TOP INSIDE DOUBLER AND THE SKIN OF THE TIP CAP. SENT TO COMPOSITE TECHNICS FOR WARRANTY REPAIR.				1	G	7	2 	3U				H1NE    					 
1996020200323	19960202	00323	NE  	1996	2	2	HEEA966440       	1	19960115	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										LINER FOUND TO BE OBLONG MIC READING 6.232 AND 6.2155.  MISMANUFACTURED - LINER IS OUT OF ROUND.						1	G	7	2 	3U				H1NE    					 
1996020200324	19960202	00324	EU  	1996	2	2	HEEA966441       	1	19960115	G	6321	350A32050002	BRAKE ASSY      			SNIAS 	350   	AS350B2     	8680813	EU  										ROTOR	WORN EXCESSIVELY	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951	1525 				2771				BRAKE ASSY  IS WORN EXCESSIVELY.  BRAKE PAD IS WORN.						1	G	7	1 	3U				H9EU    					 
1996020200325	19960202	00325	EU  	1996	2	2	HEEA966442       	1	19960115	G	6220	827S115X140X12FP	SHAFT SEAL      		105141081   	BOLKMS	105   	BO105S      	5626006	EU  										M/R	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			SW	03	4391S	2    			050081	S787				SHAFT SEAL LEAKING IN FLIGHT.  NO STATIC LEAK.						1	G	7	2 	3U				H3EU    					 
1996020200326	19960202	00326	EU  	1996	2	2	HEEA966443       	1	19960115	G	7160	350A54108004	INTAKE AIR      			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R	499  				2862				AIR INTAKE IS CRACKED.						1	G	7	1 	3U				H9EU    					 
1996020200327	19960202	00327	SW  	1996	2	2	HEEA966444       	1	19960115	G	5302	206031329101	FITTING         			BELL  	206   	206L1       	1182107	SW  										TAILBOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2759U					45267				L/H FITTING CRACKED IN THREE PIECES. REPLACED FITTING WITH NEW .						1	G	7	1 	3U				H2SW    					 
1996020200328	19960202	00328	SW  	1996	2	2	HEEA966445       	1	19960115	G	5302	206031329101	FITTING         			BELL  	206   	206L1       	1182107	SW  										TAILBOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745N					45489				L/H UPPER FITTING CRACKED AROUND RIVETS. REPLACED WITH SERVICEABLE FITTING.						1	G	7	1 	3U				H2SW    					 
1996020200329	19960202	00329	SW  	1996	2	2	HEEA966446       	1	19960115	G	5320	205030710008	FITTING         			BELL  	212   	212         	1181420	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805	14148				31106				PART IS CRACKED.  ANGLE CRACKED IN HALF DUE TO FASTENER HOLES NOT DEBURRED. REMOVED AND REPLACED ANGLE WITH SHIMS NEEDED	 AND PROPER HARDWARE.  DEBURR HOLES AT ALL LOCATIONS OF FASTENERS.					1	G	7	1 	4U				H4SW    					 
1996020200330	19960202	00330		1996	2	2	HEEA966447       	4	19960115	G	3444	066304400	ALTIMETER LIGHT 			BELL  	412   	412         	1182202	SW  										RADAR ALT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				DH LIGHT INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1996020200331	19960202	00331	EU  	1996	2	2	HEEA966448       	1	19960115	G	7400	355A72302300	SENSOR ASSY     			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					AUTO RELIGHT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5796S					5164				AUTO RELIGHT COMES ON IN FLIGHT. REPLACED WITH SERVICEABLE TRANSDUCER.						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1996020200332	19960202	00332	NE  	1996	2	2	HEEA966449       	2	19960115	G	7210	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMBINING	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z	18020				33077				COMBINING GEAR BOX IS TRANSFERRING OIL TO BOTH ENGINES, 1 QUART OIL PER 4 FLIGH T HOURS.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1996020200333	19960202	00333		1996	2	2	HEEA966450       	4	19960115	G	3416	54025100034	ALERTER         																	COCKPIT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ALERT LIGHT ON UNIT AND ON ALL ALTIMETERS,  FLASHES ON THEN GOES OUT AT 1000 FEET BEFORE DESIRED ALTITUDE.   AT 750 FEET	 BEFORE DESIRED ALTITUDE LIGHTS COME ON AND FUNCTIONS NORMALLY.  UNIT CHECKED AT SEVERAL ALTITUDE SETTINGS IN CLIMB AND 	DESCENT AND FUNCTIONED THE SAME.																	 
1996020200334	19960202	00334	EU  	1996	2	2	HEEA966451       	1	19960115	G	2121	420800001	BLOWER          			SNIAS 	350   	AS350B2     	8680813	EU  										AIR DIST	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ	254  				2653				BROKEN FAN CAUSED MOTOR TO BURN UP.						1	G	7	1 	3U				H9EU    					 
1996020200335	19960202	00335	NE  	1996	2	2	HEEA966452       	2	19960115	G	7320	6038T62P24	HMU             			BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT72A       	30030	NE  					THROTTLE	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				BINDING THROTTLE NEAR IDLE CUT OFF.						2	G	7	2 	4U	4	U		H10SW   	E8NE				 
1996020200336	19960202	00336		1996	2	2	HEEA966453       	4	19960115	G	3444	6223201001	ALTIMETER       			KING A														COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	39PH					BL3				RADIO ALTIMETER ERRATIC ALTITUDE READOUT.																			 
1996020200337	19960202	00337	NE  	1996	2	2	HEEA966454       	1	19960115	G	3610	7650007903102	VALVE           			SKRSKY	S76   	S76A        	8143006	NE  										BLEED SOV	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31219	8627 				760230				BLEED SOV SOLENOID INOPERATIVE.						1	G	7	2 	3U				H1NE    					 
1996020200338	19960202	00338	NE  	1996	2	2	HEEA966455       	1	19960115	G	3230	7665001801103	BOTTLE          			SKRSKY	S76   	S76A        	8143006	NE  										GEAR BLOW DOWN	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	792CH	148  				760193				BOTTLE LEAKING THROUGH HEAD VALVE ASSEMBLY.						1	G	7	2 	3U				H1NE    					 
1996020200339	19960202	00339	SW  	1996	2	2	HEEA966456       	1	19960115	G	6240	214074280105	DETECTOR        			BELL  	214   	214ST       	1182106	SW  										LOW RPM WARN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M	539  				28102				LOW RPM LIGHT INOPERATIVE.						2	G	7	2 	4U				H10SW   					 
1996020200340	19960202	00340	SW  	1996	2	2	HEEA966457       	1	19960115	G	2824	L88010501	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2258F					33073				VALVE INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1996020200341	19960202	00341	EU  	1996	2	2	HEEA966459       	1	19960115	G	7110	TL100AXE12L55	FASTENER        			SNIAS 	350   	AS350B2     	8680813	EU  										COWL	EXCESS WORN     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				FASTENER  IS WORN EXCESSIVELY.  HINGE WORN AND LATCH HOOK WORN. REPLACED WITH SERVICEABLE LATCH ASSEMBLY.						1	G	7	1 	3U				H9EU    					 
1996020200342	19960202	00342	EU  	1996	2	2	HEEA966460       	1	19960115	G	6330	704A33633151	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										M/R XMSN	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951	1995 				2771				DURING 2000 HOUR INSPECTION FOUND BEARING SEPARATED. REPLACED WITH SERVICEABLE BEARING.						1	G	7	1 	3U				H9EU    					 
1996020200343	19960202	00343	EU  	1996	2	2	HEEA966461       	1	19960115	G	3213	350A41104620	SHOE            			SNIAS 	350   	AS350B2     	8680813	EU  										RT FWD SKID	EXCESS WORN     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				FOUND RIGHT FORWARD SKID SHOE WORN THROUGH. REPLACED WORN SHOE						1	G	7	1 	3U				H9EU    					 
1996020900089	19960209	00089	SW  	1996	2	9	HEEA966464       	1	19960115	G	5610	M2063401	WINDSHIELD      			BELL  	206   	206L1       	1182107	SW  										COCKPIT LT	MIS MFG         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1077A					45382				WINDSHIELD IS MANUFACTURED TOO SMALL TO PROPERLY FIT WINDSHIELD FRAME.						1	G	7	1 	3U				H2SW    					 
1996020900090	19960209	00090	SW  	1996	2	9	HEEA966465       	1	19960116	G	6240	214175233101	SENSOR          			BELL  	230   	230         	1182149	SW  										M/R RPM	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	2617 				23009				MAIN ROTOR NEEDLE ON TRIPLE TACH IS ERRATIC.						1	G	7	2 	3U			NC	H9SW    					 
1996020900091	19960209	00091	SW  	1996	2	9	HEEA966466       	1	19960116	G	2150	230325003101	HOSE            			BELL  	230   	230         	1182149	SW  										AIR COND	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	2582 				23009				AIRCONDITION RETURN VENT HOSE TORN AND COLLAPSED. SCRAPPED IN FIELD.						1	G	7	2 	3U			NC	H9SW    					 
1996020900092	19960209	00092	SW  	1996	2	9	HEEA966467       	1	19960116	G	6420	222012714001	BEARING         			BELL  	230   	230         	1182149	SW  										T/R	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	2588 				23009				T/R BEARING RACE WORN.						1	G	7	2 	3U			NC	H9SW    					 
1996020900093	19960209	00093		1996	2	9	HEEA966468       	4	19960116	G	2312	069102409	TRANSCEIVER     		KX155       															COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSCEIVER INOPERATIVE.  UNIT BURNT AND SPACER MISSING ON REAR OF CHASSIS AND AUDIO BOARD.																			 
1996020900094	19960209	00094		1996	2	9	HEEA966469       	4	19960116	G	2312	064102300	TRANSCIEVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT VHF	LOW POWER       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8045T					28101				TRANSCEIVER LOW OUTPUT POWER. REPLACED TRANSISTORS Q109 AND 110.  REPAIRED.  INSTALLED MOD 2.  REPLACED HEADER J304 AND 	APPLIED HUMISEAL TO HEADER.  REPLACED TRANSMIT HEATSINK DUE TO SCREW BEING BROKEN IN HOLE.  FOUND FREQUENCY UNABLE TO AD	JUST TO SPECS.  REPLACED CRYSTAL Y101.REPAIRED.  ADJUSTED C/SQUELCH AND SIDETONE.  BENCH CHECK GOOD.				2	G	7	2 	4U				H10SW   					 
1996020900095	19960209	00095		1996	2	9	HEEA966470       	4	19960116	G	3455	066107200	RECEIVER        		KR87        	BELL  	206   	206L3       	1182108	SW  										COCKPIT ADF	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				BENCH CHECK NEEDED. INSPECTED AND TESTED.  FOUND HOLE STRIPPED IN HEATSINK.  REPLACED HEATSINK.  REPAIRED.  REPLACED DIS	PLAY DUE TO INOPERATIVE SEGMENTS.  REPAIRED.  APPLIED DOW CORNING #4 COMPOUND TO DISPLAY.  BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW    					 
1996020900096	19960209	00096		1996	2	9	HEEA966471       	4	19960116	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	32041					51539				2 YEAR INSPECTION DUE. REPLACED WEAK V101 CAVITY OSCILLATOR.  ADJUSTED FREQUENCY.  BENCH CHECK GOOD.						1	G	7	1 	3U				H2SW    					 
1996020900097	19960209	00097		1996	2	9	HEEA966472       	4	19960116	G	3453	4530103	RECEIVER        		ARNAV21     	BELL  	206   	206B        	1181511	SW  										COCKPIT LORAN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2275Q					3625				DISPLAYS "OSCILLATOR ERROR".						1	G	7	1 	3U				H2SW    					 
1996020900098	19960209	00098		1996	2	9	HEEA966473       	4	19960116	G	3421	1113034	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT ATTITUDE	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				ATTITUDE GYRO WILL NOT ERECT.						2	G	7	2 	4U				H10SW   					 
1996020900099	19960209	00099	SW  	1996	2	9	HEEA966474       	1	19960116	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	NEEDLE SPLIT    	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22608					33075				#1 AND #2 NEEDLES HAVE A 3% SPLIT. SENT TO AIR DALLAS INSTRUMENTS FOR WARRANTY REPAIR.  TIME SINCE REPAIR 17:00.						1	G	7	2 	4U				H4SW    					 
1996020900100	19960209	00100	SW  	1996	2	9	HEEA966476       	1	19960116	G	2436	206075447007	REGULATOR       			BELL  	206   	206L3       	1182108	SW  										DC SYS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3108E					51498				VOLTAGE REGULATOR WOULD NOT HOLD VOLTAGE SETTING.						1	G	7	1 	3U				H2SW    					 
1996020900101	19960209	00101	GL  	1996	2	9	HEEA966477       	2	19960119	G	7230	23031922	SHAFT           		6890550     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	FRETTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	967MB	54   			CAC40338	S737	CAE835381			ENGINE REMOVED DUE TO METAL IN OIL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING:  1) FRETTING ON SPUR ADPAT	ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D.  2) EXCESSI	VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE.  3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M	ETAL IN OIL.  4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING.  NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD	APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET.  SEE MMIR'S NR 6	477 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED.	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996020900102	19960209	00102	GL  	1996	2	9	HEEA966478       	2	19960119	G	7230	23039791	SPLINE ADAPTER  		6890550     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	FRETTING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	967MB	54   			CAC40338	S737	CAE835381			ENGINE REMOVED DUE TO METAL IN OIL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING:  1) FRETTING ON SPUR ADPAT	ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D.  2) EXCESSI	VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE.  3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M	ETAL IN OIL.  4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING.  NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD	APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 64	77 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED.	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996020900103	19960209	00103	GL  	1996	2	9	HEEA966479       	2	19960119	G	7230	672665690	SPIRAL LOCK RING		6890550     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	DISLODGED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	967MB	54   			CAC40338	S737	CAE835381			ENGINE REMOVED DUE TO METAL IN OIL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING:  1) FRETTING ON SPUR ADPAT	ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D.  2) EXCESSI	VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE.  3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M	ETAL IN OIL.  4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING.  NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD	APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 64	77 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED.	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996020900104	19960209	00104	GL  	1996	2	9	HEEA966480       	2	19960119	G	7230	23034787	BEARING         		6890550     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR 2.5	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	967MB	54   			CAC40338	S737	CAE835381			ENGINE REMOVED DUE TO METAL IN OIL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING:  1) FRETTING ON SPUR ADPAT	ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D.  2) EXCESSI	VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE.  3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M	ETAL IN OIL.  4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING.  NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD	APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 64	77 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED.	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996020900105	19960209	00105	GL  	1996	2	9	HEEA966481       	2	19960119	G	7230	6898977	COUPLING        		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	967MB	54   			CAT40070	S737	CAE835381			ENGINE REMOVED DUE TO METAL IN OIL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING:  1) FRETTING ON SPUR ADPAT	ER GEARSHAFT DUE TO RETAINING RING NOT IN SPLINE ADAPTER GROOVE AND GROOVED NR 2 1/2 BEARING INNER RACE O.D.  2) EXCESSI	VE WEAR ON SPLINE ADAPTER RETAINING RING GROOVE.  3) SPIRAL LOCK RING BECOMING DISLODGED IN SPLINE ADAPTER AND CAUSING M	ETAL IN OIL.  4) GROOVED AND DENTED ROLLERS IN NR 2 1/2 BEARING.  NOTE: NR 2 1/2 BEARING INNER RACE REMOVED FROM SPUR AD	APTER GEARSHAFT AND SENT WITH OTHER PARTS AND N1 COUPLING BEING SENT FOR INSPECTION AS N1 SHAFTING SET. SEE MMIR'S NR 64	77 THROUGH NR 6481 FOR ADDITIONAL PARTS REPLACED.	1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996020900106	19960209	00106	GL  	1996	2	9	HEEA966482       	2	19960119	G	7210	6876925A	TUBE ASSY       		6894171     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENG GR BOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5421E	7173 			CAG39055	S806	CAE270055			ENGINE REMOVED DUE TO OIL LEAKING AT GEARBOX SPLIT LINE.  UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING:  OIL TRA	NSFER TUBE FAILED DIMENSIONAL CHECK IN ACCORDANCE WITH CEB1307. INSTALLED A NEW OIL TUBE ASSY.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1996020900107	19960209	00107	SW  	1996	2	9	HEEA966483       	1	19960119	G	5302	206031329003	FITTING         			BELL  	206   	206L1       	1182107	SW  										TAILBOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1076T					45373				UPPER L/H TAILBOOM FITTING CRACKED.						1	G	7	1 	3U				H2SW    					 
1996020900108	19960209	00108	EU  	1996	2	9	HEEA966484       	1	19960119	G	6320	1171261201	BEARING         		1171200501  	BOLKMS	117   	BK117B1     	5626012	EU  										M/R GR BOX	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		2313 			KA0474					BEARING INNER RACE, ROLLERS AND OUTER RACE SPALLING EXCESSIVELY.						1	G	7	2 	3U				H13EU   					 
1996020900109	19960209	00109	SW  	1996	2	9	HEEA966485       	1	19960119	G	6240	206075681105	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										DUAL TACH	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	363BH					51345				INDICATOR GLASS FOGGED UP.						1	G	7	1 	3U				H2SW    					 
1996020900110	19960209	00110		1996	2	9	HEEA966486       	4	19960119	G	3454	066107810	RECEIVER        		KNR634A     	SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT NAV	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	89H	205  				760406				NAV RECEIVER BAD FROM STOCK.  BLUE LIGHT STAYS ON MARKER BEACON INDICATOR.   TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H1NE    					 
1996020900111	19960209	00111	EU  	1996	2	9	HEEA966487       	1	19960119	G	6520	350A33200403	SPIDER          			SNIAS 	350   	AS350B2     	8680813	EU  										T/R	BOOT LOOSE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951	1248 				2771				DUST BOOT  P/N 350A33-2069-20 COMING LOOSE FROM SPIDER ASSY AND SLIDING ON SHAFT.						1	G	7	1 	3U				H9EU    					 
1996020900112	19960209	00112	EU  	1996	2	9	HEEA966488       	1	19960119	G	2610	0301037070	HARNESS         			SNIAS 	350   	AS350B2     	8680813	EU  										FIRE DETECTOR	B NUT LOOSE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				B-NUT UNBONDED FROM HARNESS.						1	G	7	1 	3U				H9EU    					 
1996020900113	19960209	00113		1996	2	9	HEEA966489       	4	19960119	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219	2607 				760230				#1 ROLL CHATTERS.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND TEST POINT E.4 OUT OF CALIBRATION.						1	G	7	2 	3U				H1NE    					 
1996020900114	19960209	00114	GL  	1996	2	9	HEEA966490       	2	19960119	G	7314	D10731812A	PUMP            								ALLSN 	250C  	250C20B     	03013	GL  					STATOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STATOR INSULATION COVERING WINDINGS HANGS OVER LIP OF HOUSING AND CANNOT BE ASSEMBLED ON PUMP.											3	U			E4CE				 
1996020900115	19960209	00115	SW  	1996	2	9	HEEA966491       	1	19960119	G	5320	206033100261	SHELL ASSY      			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MIS MFG         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10814					45415				TRANSITION AREA ALONG AFT EDGE MISALIGNED.  RECESS FOR FUEL CROSS OVER LINE NOT CENTERED ON SHELL ASSY.						1	G	7	1 	3U				H2SW    					 
1996020900116	19960209	00116	NE  	1996	2	9	HEEA966492       	1	19960119	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				TIP CAP HAS INTERNAL DOUBLER SEPARATED BEYOND LIMITS AND LEADING EDGE ABRASION STRIP CRACKED AND SEPARATED.						1	G	7	2 	3U				H1NE    					 
1996020900117	19960209	00117	EU  	1996	2	9	HEEA966493       	1	19960119	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6607K					S841				MAST MOMENT SYSTEM INOPERATIVE.  BLOWS FUSES.						1	G	7	2 	3U				H3EU    					 
1996020900118	19960209	00118	EU  	1996	2	9	HEEA966494       	1	19960119	G	6240	10594575	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 SYSTEM INOPERATIVE.  BLOWS FUSES.						1	G	7	2 	3U				H3EU    					 
1996020900119	19960209	00119	SW  	1996	2	9	HEEA966495       	1	19960119	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT TORQUE	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				#2 NEEDLE INTERMITTENTLY STICKS AT 0 AND 38%.						1	G	7	2 	4U				H4SW    					 
1996020900120	19960209	00120	SW  	1996	2	9	HEEA966496       	1	19960119	G	6220	412010124109	BOLT            		412010100151	BELL  	412   	412         	1182202	SW  										M/R	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X	1183 			AAD00032	33115				TUNGSTEN CARBIDE COATING FLAKING OFF.						1	G	7	2 	4U				H4SW    					 
1996020900121	19960209	00121	SW  	1996	2	9	HEEA966497       	1	19960119	G	6220	412010124109	BOLT            		412010100151	BELL  	412   	412         	1182202	SW  										M/R	COAT FLAKE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X	1183 			AAD00032	33115				BOLT TUNGSTEN CARBIDE COATING FLAKING OFF.  S/N A732, A50 AND A716						1	G	7	2 	4U				H4SW    					 
1996020900122	19960209	00122	SW  	1996	2	9	HEEA966498       	1	19960119	G	6220	412010124109	BOLT            		412010100151	BELL  	412   	412         	1182202	SW  										M/R	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X	1183 			AAD00032	33115				BOLT TUNGSTEN CARBIDE COATING FLAKING OFF.  S/N A726 & A750						1	G	7	2 	4U				H4SW    					 
1996020900123	19960209	00123	SW  	1996	2	9	HEEA966499       	1	19960119	G	6420	214011801117	HUB             			BELL  	214   	214ST       	1182106	SW  										T/R	WONT BALANCE    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T	431  				28101				INSPECT AND REPAIR DUE TO UNABLE TO BALANCE.						2	G	7	2 	4U				H10SW   					 
1996020900124	19960209	00124	SW  	1996	2	9	HEEA966500       	1	19960123	G	3340	214175127103	POWER SUPPLY    			BELL  	214   	214ST       	1182106	SW  										DC SYS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				POWER SUPPLY INOPERATIVE.						2	G	7	2 	4U				H10SW   					 
1996020900125	19960209	00125	SW  	1996	2	9	HEEA966501       	1	19960123	G	7120	230322452	PLATE           			BELL  	206   	206L1       	1182107	SW  										MOUNT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10814					45415				MOUNTING PLATE  CORRODED.  (CORROSION ON CLAMP FLANGE) REPLACED WITH SERVICEABLE MOUNTING PLATE.						1	G	7	1 	3U				H2SW    					 
1996020900126	19960209	00126		1996	2	9	HEEA966502       	4	19960123	G	3452	066106200	TRANSCEIVER     		KT76        	BELL  	206   	206B        	1181511	SW  										COCKPIT ATC	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2277A					3630				NO RECEPTION BY TOWER. REPLACED WEAK V101 CAVITY OSCILLATOR.  ADJUSTED FREQUENCY.  BENCH CHECK GOOD.						1	G	7	1 	3U				H2SW    					 
1996020900590	19960209	00590		1996	2	9	HEEA966503       	4	19960123	G	3444	066104800	ALTIMETER       		KRA405      	BELL  	214   	214ST       	1182106	SW  										COCKPIT RAD ALT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				RADAR ALTIMETER INOPERATIVE. PERFORMED COMPLETE CALIBRATION AND ALIGNMENT.  REPLACED RESISTORS R518, R519, R534 AND R260	 TO INCORPORATE MOD 10.   BENCH  CHECK GOOD.					2	G	7	2 	4U				H10SW   					 
1996020900591	19960209	00591		1996	2	9	HEEA966504       	4	19960123	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				GIVES INCORRECT ALTITUDE. PERFORMED COMPLETE CALIBRATION AND ALIGNMENT.  REPAIRED.  REPLACED RESISTORS R518,R519,R534 AN	D R260 TO INCORPORATE MOD 10.  BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW    					 
1996020900592	19960209	00592		1996	2	9	HEEA966505       	4	19960123	G	3452	066106200	TRANSCEIVER     		KT76        	BELL  	206   	206L1       	1182107	SW  										COCKPIT ATC	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	50046					45173				TRANSCEIVER MUST BE RECYCLED ON FIRST FLIGHT TO SEND SIGNAL, WORKS FINE THE REST OF THE DAY. REPLACED PHOTOCELL V301 DUE	 TO WEAK REPLY LIGHT.  REPAIRED.  ALIGNED RECEIVER.  ADJUSTED POWER OUT AND FREQUENCY TO SPECS.  BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW    					 
1996020900593	19960209	00593		1996	2	9	HEEA966506       	4	19960123	G	3442	MI585200	RT UNIT         			BELL  	412   	412         	1182202	SW  										COCKPIT RADAR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				RADAR  R/T HAS BAD MODULATOR; WILL NOT SHOW ANY TARGETS.						1	G	7	2 	4U				H4SW    					 
1996020900594	19960209	00594		1996	2	9	HEEA966507       	4	19960123	G	3453	25410038	7000 CDU        			BELL  	412   	412         	1182202	SW  										COCKPIT LORAN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				CDU HAS LIGHT SEGMENTS OUT.						1	G	7	2 	4U				H4SW    					 
1996020900595	19960209	00595		1996	2	9	HEEA966508       	4	19960123	G	3444	066106103	ALTIMETER       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT RADAR	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911BR					S719				RADAR ALTIMETER PEGS OUT AFTER 15 MINUTES. SENT TO THE RADIO SHOP FOR INSPECTION AND REPAIR.						1	G	7	2 	3U				H3EU    					 
1996020900596	19960209	00596	EU  	1996	2	9	HEEA966509       	1	19960123	G	2435	230321825	STATOR          		23032027    	BOLKMS	105   	BO105S      	5626006	EU  										START/GEN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	352TT				24480	S59				STARTER GENERATOR WOULD NOT PUT OUT ANY VOLTAGE WITH THIS STATOR INSTALLED.						1	G	7	2 	3U				H3EU    					 
1996020900597	19960209	00597		1996	2	9	HEEA966510       	4	19960123	G	3422	5050010902	GYRO            		200         	SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6097Z					2820				DIRECTIONAL GYRO PRECESSES EXCESSIVELY. REPLACED WITH SERVICEABLE GYRO.						1	G	7	1 	3U				H9EU    					 
1996020900598	19960209	00598		1996	2	9	HEEA966511       	4	19960123	G	3422	5050010902	GYRO            		200         	SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				GYRO UNRELIABLE AND WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE GYRO.						1	G	7	1 	3U				H9EU    					 
1996020900599	19960209	00599	EU  	1996	2	9	HEEA966512       	1	19960123	G	3340	356H2802	POWER SUPPLY    			SNIAS 	350   	AS350B2     	8680813	EU  										ANTI COLL BEACON	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				ANTI-COLLISION LIGHT INOPERATIVE. REPLACED WITH SERVICEABLE POWER SUPPLY.						1	G	7	1 	3U				H9EU    					 
1996020900600	19960209	00600		1996	2	9	HEEA966513       	4	19960123	G	3422	5050002904	GYRO            			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT DG	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	60951					2771				DG OPERATES INTERMITTENTLY. REPLACED WITH SERVICEABLE DIRECTIONAL GYRO.						1	G	7	1 	3U				H9EU    					 
1996020900601	19960209	00601		1996	2	9	HEEA966514       	4	19960123	G	3457	0110010600	RECEIVER        		GPS165      	BRAERO	DH125 	HS125700A   	4230170	EU  										COCKPIT GPS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	125CS					NA0212				GPS NOT PICKING UP SATELLITES AND LOCKS UP WHEN ENTERING A WAYPOINT.						2	L	7	2 	4F				A3EU    					 
1996020900602	19960209	00602	SW  	1996	2	9	HEEA966515       	1	19960123	G	3212	212050207104	FLOAT BAG VALVE 			BELL  	212   	212         	1181420	SW  										RT FLOAT FWD	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FWD FLOAT BAG HAS UNBONDED INLET VALVE.						1	G	7	1 	4U				H4SW    					 
1996020900603	19960209	00603	SW  	1996	2	9	HEEA966516       	1	19960123	G	3212	212050207011	FLOAT BAG VALVE 			BELL  	212   	212         	1181420	SW  										LT FLOAT FWD	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FWD FLOAT BAG HAS UNBONDED INLET VALVE.						1	G	7	1 	4U				H4SW    					 
1996020900604	19960209	00604		1996	2	9	HEEA966517       	4	19960123	G	2312	064102300	TRANSCIEVER     			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT VHF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	117BK					7229				TRANSCEIVER RECEIVES OK, BUT DOES NOT TRANSMIT FROM EITHER STATION.						1	G	7	2 	3U				H13EU   					 
1996020900605	19960209	00605	NE  	1996	2	9	HEEA966518       	2	19960123	G	7321	0164248700	FUEL CONTROL    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ	1056 				2653				ENGINE SLOW AND HANG STARTS ON FIRST START OF DAY.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1996020900606	19960209	00606	SW  	1996	2	9	HEEA966519       	1	19960123	G	6320	212070116009	INDICATOR       			BELL  	412   	412         	1182202	SW  										XMSN OIL TEMP	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F					33073				INDICATOR STICKING AT 50 DEGREES, METER MOVEMENT BROKEN ON TEMP SIDE.						1	G	7	2 	4U				H4SW    					 
1996020900607	19960209	00607	SW  	1996	2	9	HEEA966520       	1	19960125	G	5320	206031314083S	CHANNEL         			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	MIS MFG         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41128					51134				FWD UPPER FLANGE HAS NO EDGE DISTANCE FOR RIVET INSTALLATION.						1	G	7	1 	3U				H2SW    					 
1996020900608	19960209	00608		1996	2	9	HEEA966522       	4	19960126	G	2312	021003800	OSC             			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT COMM	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	350BZ					2653				WEAK POWER AND OFF FREQUENCY.						1	G	7	1 	3U				H9EU    					 
1996020900609	19960209	00609	SW  	1996	2	9	HEEA966523       	1	19960126	G	6730	206076062003	CYLINDER        			BELL  	206   	206L1       	1182107	SW  										M/R	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5017G	13550				45228				CYLINDER LEAKING INTERNALLY AND LOOSE BEARING.						1	G	7	1 	3U				H2SW    					 
1996020900610	19960209	00610		1996	2	9	HEEA966524       	4	19960126	G	3414	8000B12	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT AIR SPD	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2246Q					45752				INDICATOR UNIT INDICATES 20 MPH LOW, OUT OF TOLERANCE.						1	G	7	1 	3U				H2SW    					 
1996020900611	19960209	00611	EU  	1996	2	9	HEEA966525       	1	19960126	G	3150		WARNING BOX     		KDW02       	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4391S					S787				WARNING BOX WARNING HORN STAYS ON BELOW 75%. SENT						1	G	7	2 	3U				H3EU    					 
1996020900612	19960209	00612	NE  	1996	2	9	HEEA966526       	2	19960126	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				TROUBLESHOT OSCILLATION 1% N1.  GOVERNOR SHAFT ROUGH.  UNIT RECEIVED INSTALLED ON CPGB-1333.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1996020900613	19960209	00613	NE  	1996	2	9	HEEA966527       	2	19960126	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				TORQUE SPLIT, TORQUE OSCILLATION.  UNIT RECEIVED INSTALLED ON CPGB-1333.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1996020900614	19960209	00614	SW  	1996	2	9	HEEA966528       	1	19960126	G	7810	212061201012	EJECTOR ASSY    			BELL  	412   	412         	1182202	SW  										RT EXH	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				EJECTOR IS CRACKED  AND HAS BROKEN RIVETS.						1	G	7	2 	4U				H4SW    					 
1996020900615	19960209	00615	SW  	1996	2	9	HEEA966529       	1	19960126	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22608					33075				TRIPLE TACH NEEDLE STICKS AND EXCESSIVE NEEDLE SPLIT.						1	G	7	2 	4U				H4SW    					 
1996020900616	19960209	00616		1996	2	9	HEEA966530       	4	19960126	G	2562		ELT             	NARCO       	ELT910      	SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31219					760230				ELT STAYS ACTIVATED.						1	G	7	2 	3U				H1NE    					 
1996020900617	19960209	00617		1996	2	9	HEEA966531       	4	19960126	G	2562		ELT             	NARCO       	ELT910      	BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2258F	2776 				33073				ELT UNIT ACTIVATES BY ITSELF IN ARMED POSITION INTERMITTENTLY.						1	G	7	2 	4U				H4SW    					 
1996020900618	19960209	00618	EU  	1996	2	9	HEEA966532       	1	19960126	G	2810	FTA017521	TANK            			BOLKMS	105   	BO105S      	5626006	EU  										MAIN FUEL	PEELING         	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	86CH					S557				MAIN FUEL TANK,PEELING INSIDE.						1	G	7	2 	3U				H3EU    					 
1996020900619	19960209	00619		1996	2	9	HEEA966533       	4	19960126	G	3416	5035P2P42	ALTIMETER       	UNITEDINST  		BELL  	412   	412         	1182202	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22608					33075				ALTIMETER READS 500 FEET HIGH.						1	G	7	2 	4U				H4SW    					 
1996020900620	19960209	00620	SW  	1996	2	9	HEEA966534       	1	19960126	G	2436	206075447007	REGULATOR       			BELL  	206   	206L1       	1182107	SW  										DC SYS	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5012V					45200				GENERATOR TURNING AS A MOTOR AT 15-20% N1 AFTER SHUTDOWN. REGULATOR MALFUNCTION.						1	G	7	1 	3U				H2SW    					 
1996020900621	19960209	00621	NE  	1996	2	9	HEEA966535       	1	19960126	G	7333	PC820101	SIGNAL CONDITION			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FUEL FLOW	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4253S	171  				760035				FUEL FLOW IND. NEEDLE PEGS OUT. SIGNAL GENERATOR MALFUNCTION.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1996020900622	19960209	00622	SW  	1996	2	9	HEEA966536       	1	19960126	G	2432	39563001	BATTERY         			BELL  	412   	412         	1182202	SW  										DC SYS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S	992  				36002				BATTERY FAILED CAPACITY TEST.						1	G	7	2 	4U				H4SW    					 
1996020900623	19960209	00623	EU  	1996	2	9	HEEA966537       	1	19960126	G	7712	G555674	TRANSDUCER      			BOLKMS	117   	BK117B1     	5626012	EU  										NR 2 ENG TORQUE	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	117BK					7229				#2 ENGINE TORQUE READS INTERMITTENT.  TRANSDUCER DEFECTIVE						1	G	7	2 	3U				H13EU   					 
1996020900624	19960209	00624	EU  	1996	2	9	HEEA966538       	1	19960126	G	3340	356H2802	POWER SUPPLY    			SNIAS 	350   	AS350B2     	8680813	EU  										BEACON	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6100U	389  				2863				BEACON FLASHES VERY SLOWLY AND DIMMLY.						1	G	7	1 	3U				H9EU    					 
1996082900327	19960829	00327	GL  	1996	8	29	HEEA967686       	2	19960822	G	7230	23033439	DAMPER SEGMENT  		23038126    						ALLSN 	250C  	250C20B     	03013	GL  					ENG COMP	BELOW SPECS     	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					CAC15233		CAE830070			RECEIVING INSPECTION REVEALED DAMPER SEGMENT LENGTH .0335 BELOW BLUE PRINT SPECS OF .542 - .544. REPLACED DISCREPANT PAR	T WITH NO CHARGE REPLACEMENT RECEIVED FROM ALLISON.										3	U			E4CE				 
1996091200220	19960912	00220		1996	9	12	HEEA967701       	1	19960829	G	7722	206375007103	INDICATOR       	MASCO       																COCKPIT TOT	MIS MARKED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR UNIT HAS WRONG RANGE MARKS ON FACEPLATE.  (RANGE MARKS REFLECT P/N 206-375-005-101)  TIME SINCE REPAIR 0:00.																			 
1996091200225	19960912	00225		1996	9	12	HEEA967706       	1	19960829	G	7722	206375006101	INDICATOR       																	COCKPIT TOT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WHEN POWER IS APPLIED WITH AN INPUT OF 29.14 M.V. (OR 700 DEGREES) NEEDLE REMAINS AT ZERO AND OVERTEMP LIGHT ILLUMINATES	.   TIME SINCE REPAIR 0:00.																		 
1996091900289	19960919	00289		1996	9	19	HEEA967765       	4	19960903	G	2312	4000098000	TRANSCEIVER     		RT3         															COCKPIT VHF	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVER INTERMITTENT AND TRANSMITS OFF FREQUENCY. SENT TO ALLIED SIGNAL AVIONICS FOR INSPECTION AND REPAIR.																			 
1996091900303	19960919	00303	GL  	1996	9	19	HEEA967779       	2	19960904	G	7250	23008054	NOZZLE          								ALLSN 	250C  	250C28      	03013	GL  					NR 1	OUT OF SPECS    	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  MEASUREMENT ON #1 NOZZLE DIMENSION (A) .019 BELOW CEB72-2103R-6 SPECS, (B) .005 BELOW BL	UEPRINT SPECS, (C) .012 BELOW BLUEPRINT SPECS.										3	U			E1GL				 
1996091900308	19960919	00308	GL  	1996	9	19	HEEA967786       	2	19960906	G	7230	23056634	GEAR            		23033193    						ALLSN 	250C  	250C30P     	03013	GL  					SPUR ADAPTER	DEFECTIVE       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					CAC91370		CAE895336			RECEIVING INSPECTION REVEALED:  SERIAL NUMBER ON SPUR GEAR DOES NOT MATCH NUMBER ON BOX. REPLACED DISCREPANT PART.											3	U			E1GL				 
1996101000777	19961010	00777		1996	10	10	HEEA967813       	1	19960910	G	7720	206075187001	INDICATOR       																	COCKPIT DUAL IND	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR IS CRACKED.  (GLASS IS CRACKED)																			 
1996101000779	19961010	00779		1996	10	10	HEEA967815       	4	19960910	G	2312	071121524	CONTROL         	KING        	KFS598      															COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										UNIT DEFAULTS TO 120.00 MHZ WHEN TURNED OFF AND ON.																			 
1996101700448	19961017	00448		1996	10	17	HEEA968006       	1	19961003	G	2140	BH1411840	PROBE           																	JET CAL HEATER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										FAILED IN OPEATION.  PROBE ASSEMBLY WON'T HEAT.																			 
1996101700470	19961017	00470		1996	10	17	HEEA968028       	1	19961003	G	7930	90321003	INDICATOR       																	COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR HAS RATTLE INSIDE UNIT.																			 
1996101700475	19961017	00475		1996	10	17	HEEA968033       	4	19961003	G	3452	6224527015	TRANSPONDER     																	COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ATC XPONDER UNIT DOES NOT MEET MANUFACTURE AND AIRWORTHINESS STANDARDS.  NUMBERS DON'T SEQUENCE CORRECTLY.  IDENT SWITCH	 LIGHT DOES NOT COME ON AND GOES OFF INTERMITTENTLY .  TEST SWITCH DOESN'T WORK AT ALL.  TIME SINCE REPAIR 0:00.																		 
1996101700481	19961017	00481		1996	10	17	HEEA968041       	4	19961003	G	3452	066106200	TRANSCEIVER     																	ATC XPONDR	INOPERATIVE     	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										INOPERATIVE FROM STOCK. REPLACED DEFECTIVE Q415 TRANSISTOR.  REPAIRED PROBLEM.  INSPECTED AND BENCH CHECK GOOD.																			 
1996101700814	19961017	00814		1996	10	17	HEEA968085       	4	19961003	G	2312	064105430	TRANSCEIVER     																	COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ALL 8' ON STANDBY FREQUENCY , FOUND 2 BURNT SURFACES MOUNT DEVICES ON BOTTOM SIDE OF BOARD.																			 
1996101700831	19961017	00831		1996	10	17	HEEA968102       	1	19961003	G	6320	212070116009	INDICATOR       	MASCO       																XMSN OIL	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PRESS NEEDLE STICKS 50 TO 80%.																			 
1996102400075	19961024	00075		1996	10	24	HEEA968178       	4	19961010	G	3444	066304400	ALTIMETER.      		KRA405      															RADAR ALT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PRECISION EQUIPMENT OUTPUT VOLTAGE BAD.  VOLTAGE FLUCTUATES IN SELF-TEST MODE USING KRA405 SWAPPED KNI416. SENT TO HELIC	OPTER SUPPORT, INC. FOR OVERHAUL.																		 
1996102400298	19961024	00298		1996	10	24	HEEA968195       	4	19961010	G	3457	13824120234	RECEIVER        	TRMNAV      																COCKPIT GPS	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										GPS RECEIVER VERY INTERMITTENT OPERATION DISPLAY VERY DIM.  WOULD NOT COMPLETE A CYCLE.																			 
1996102400306	19961024	00306		1996	10	24	HEEA968204       	4	19961010	G	3442	MI5853013	INDICATOR       		P500        															COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										AZIMUTH LINE NOT CENTERED AND DISPLAY HAS GLITCHES EVERY 2-5 MINUTES AFTER WARM UP. TIME SINCE REPAIR 0:00.																			 
1996103000007	19961030	00007	GL  	1996	10	30	HEEA968220       	2	19961011	G	7230	23039791	SPLINE ADAPTER  								ALLSN 	250C  	250C20      	03013	GL  					ENGINE	BELOW LIMITS    	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED: MEASURED .0034 BELOW MINIMUM LIMITS OF .8994 ON COUPLING'S EXTERNAL SPLINES.  SERIAL NUMB	ER 65243 AND S/N 65246 9-17-96 AND SERIAL NUMBER 64938										3	U			E4CE				 
1996102400329	19961024	00329	GL  	1996	10	24	HEEA968228       	2	19961011	G	7250	6892828	SHIELD          								ALLSN 	250C  	250C20      	03013	GL  					NR 1 NOZZLE	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  .050 OUT OF FLATNESS BETWEEN #1 NOZZLE SHIELD OUTER BAND AND INNER BAND.											3	U			E4CE				 
1996102400359	19961024	00359		1996	10	24	HEEA968259       	4	19961011	G	3451	DMED35B	INDICATOR       																	COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR INOPERATIVE UNIT. TIME SINCE REPAIR 0:00.																			 
1996112100306	19961121	00306		1996	11	21	HEEA968427       	4	19961104	G	2312	064105430	TRANSCEIVER     																	COCKPIT	INOP            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSCEIVER NO DISPLAY.																			 
1996112100311	19961121	00311		1996	11	21	HEEA968432       	4	19961104	G	2312	071121524	CONTROL         		KFS598      															COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CONTROL HAS NO DISPLAY. TIME SINCE REPAIR 0:00.																			 
1996120500224	19961205	00224	GL  	1996	12	5	HEEA968536       	2	19961121	G	7230	6851574	SCROLL ASSY     								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MIS REPAIRED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  REPAIR TO SCROLL ASSEMBLY ANTI-ICE PORT NOT FULLY WELDED AS MARKED AND DIMENSION FROM AN	TI-ICE PORT TO SPLIT LINE MEASURES .080 ABOVE BLUE PRINT SPECS (2.225)										3	U			E4CE				 
1996121200467	19961212	00467	GL  	1996	12	12	HEEA968616       	2	19961206	G	7260	23033437	GEARBOX COVER   								ALLSN 	250C  	250C20B     	03013	GL  					STUD HELICOIL	DEFECTIVE       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										UPON INSTALLATION OF STUD NOTED:  12:00 HELICOIL INSTALLED AT AN ANGLE ON GEARBOX COVER.   TIME SINCE REPAIR 0:00.											3	U			E4CE				 
1996121900388	19961219	00388		1996	12	19	HEEA968671       	4	19961211	G	3442	MI5853013	INDICATOR       	HONEYWELL   	P500        															COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										SEC SCAN SWITCH INTERMITTENT.  THIS IS THE THIRD TIME THIS UNIT IS BEING RETURNED FOR REPAIR.																			 
1997010900070	19970109	00070		1997	1	9	HEEA968792       	4	19961230	G	3444	066304400	INDICATOR       																	RADAR ALT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CHECKING INDICATOR WITH KRA405 ON SECTION 5.5.1.8 OVERALL PERFORMANCE TEST OF KRA405 MANUAL, THE PRECISION EQUIPMENT OUT	PUT VOLTAGES ARE BAD.  SWAPPING INDICATORS CURED PROBLEM.  TIME SINCE REPAIR 0:00.																		 
1996031500184	19960315	00184	NE  	1996	3	15	JYER960111       	1	19960111	G	6420	S6110334061	SPINDLE         			SKRSKY	S61   	S61A        	814210C	NE  										T/R HEAD	CRACKED         	B	S		JYER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1043T	7030 	1747 			61083				AT OVERHAUL, TAIL ROTOR SPINDLE WAS FOUND CRACKED IN AREA OF FIRST THREAD.  SIKORSKY AIRCRAFT HAS BEEN NOTIFED AND THE S	PINDLE SENT TO THEM.  (X)					2	G	7	2 	4U				H2EA    					 
1996082900374	19960829	00374	WP  	1996	8	29	JZBR12924        	2	19960801	G	7530	30717781	MANIFOLD        	ALIDSIGNAL  		AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					AIR LEAK	CRACKED         	B			JZBR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	25	500FF	6550 			99193A	P73246	P73246			CREW REPORTED RT ENGINE CANNOT MAKE TAKEOFF POWER DUE TO TEMP INDICATION.  TROUBLESHOT SYSTEM AND FOUND NO TEMPERATURE D	IFFERENCE BETWEEN NORMAL AND MANUAL MODE INDICATIONS.  BLEED VALVE OPEN AT ALL TIMES.  REPLACED BLEED VALVE, PROBLEM STI	LL EXISTED.  CHECKED HARNESS, SOLENOIDS, COMPUTER, AND BLEED VALVE SOLENOID MANIFOLD.  ALL CHECKED GOOD.  PERFORMED A FU	NCTIONAL CHECK OF THE BLEED VALVE ON THE ENGINE AND DISCOVERED A LARGE AIR LEAK IN THE MANIFOLD CAUSING THE BLEED VALVE 	TO REMAIN OPEN.  REPLACED THE MANIFOLD.  ACCOMPLISHED AN ENGINE RUN, PERFORMED ALL OPERATIONAL AND LEAK CHECKS IAW MM WI	TH NO DISCREPANCIES.  THE AIRCRAFT/ENGINE WERE RETURNED TO SERVICE.  (X)	2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1996102400001	19961024	00001	SO  	1996	10	24	JZBR13138        	1	19960828	G	5210	159AMM100771	LATCH HANDLE    			GULSTM	G1159 	G1159       	3953505	SO  										CABIN ENTRY	BROKE           	B		A	JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	720JW					178				WHILE OPENING THE DOOR FROM THE INSIDE, THE SECONDARY LATCH HANDLE BROKE AT THE LATCH SLOT AND THE RIVETS BETWEEN THE HA	NDLE-LATCH PLATE AND THE BELLCRANK WERE SHEARED.  THERE IS NO PROCEDURE IN THE MM FOR REPLACEMENT OR RIGGING OF THIS HAN	DLE.  SUBMITTER STATED THE MM SHOULD BE UPDATED TO INCLUDE THE REQUIRED INSTRUCTIONS.				2	L	7	2 	4F			RT	A12EA   					 
1996122600420	19961226	00420	SO  	1996	12	26	JZBR13247        	1	19961212	G	3240	50109331	BRAKE UNIT      			GULSTM	G1159 	G1159A      	3970109	SO  										MLG	WRONG PART      	B			JZBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	166WC					413				DURING A NORMAL BRAKE CHANGE, A PROBLEM WAS ENCOUNTERED.  A SEARCH FOR REPLACEMENT BRAKES WAS INDICATED USING THE ABS P/	N.  DURING THE COURSE OF THE SEARCH, A GULFSTREAM P/N WAS GENERATED.  IT WAS ONLY AFTER THE FACT DISCOVERED THE GULFSTRE	AM P/N WAS INCORRECT.  THIS RESULTED IN THE INSTALLATION OF A 15 DEGREE SLOTTED BRAKE WITH A ZERO DEGREE KEYED WHEEL.  D	AMAGE TO THE BRAKES HAS OCCURRED AND POSSIBLY THE WHEELS.  ALL FOUR WHEELS AND BRAKES WILL BE CHANGED W ITH SERVICEABLE 	UNITS.  CAUSE:  INCORRECT P/N BRAKES INSTALLED DUE TO WRONG P/N BEING REQUESTED.  (X)		2	L	7	2 	4F				A12EA   					 
1996122600411	19961226	00411	EA  	1996	12	26	JZBR13659        	2	19961108	G	8520		CRANKCASE       			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					NR 1 CYL	BROKEN          	B			JZBR	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	25	6896B		1540 			600919816126	L2121748A			ENGINE LOST MOST OF ITS OIL DUE TO A HOLE IN THE TOP OF THE CRANKCASE ABOVE THE CAMSHAFT LOBE FOR NR 1 CYLINDER.  SUSPEC	T CAMSHAFT FOLLOWER FAILURE WHICH WEDGED ITSELF BETWEEN THE CASE AND CAMSHAFT CAUSING CASE FAILURE.  (X)					1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1996122600528	19961226	00528	SO  	1996	12	26	JZBR13820        	1	19961212	G	2740	1159SCC21365	TORQUE TUBE     			GULSTM	G1159 	G1159       	3953505	SO  										HORIZ STAB	CHAFED          	B			JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	711RL					25				WHILE INVESTIGATING A TOILET DUMP ITEM, NOTICED THE DUMP CHUTE CHAFING ON THE HORIZONTAL STABILIZER TORQUE TUBE SHAFT LO	CATED UNDER THE LAVATORY FLOOR.  REMOVED THE SHAFT AND FOUND DAMAGE TO BE OUT OF LIMITS.  REPLACED THE TORQUE TUBE SHAFT	 WITH A NEW UNIT AND REPOSITIONED THE LAVATORY DUMP CHUTE FOR PROPER CLEARANCE.  OPERATIONAL CHECK OF SYSTEM ACCOMPLISHE	D.  ALL WORK DONE IAW THE MM.  AIRCRAFT RELEASED TO SERVICE.  (X)			2	L	7	2 	4F			RT	A12EA   					 
1997011600849	19970116	00849		1997	1	16	KQ1R279K         	4	19961216	G	2561	S2100AV8A	VEST            	SWITLIK     																CELL	LEAK            	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07					81310					CELL LEAK DISCOVERED DURING ROUTINE ANNUAL VEST INSPECTION.  INSP IAW MANUAL 25-60-33.  (X)																			 
1999092400132	19990924	00132		1999	9	24	MVH0064095       	4	19960907	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	MISREPAIRED     	H			BAQA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	63CF					6068				RECEIVED REPAIRED RT-450 SN 530.  RETURNING LOANER RT-450 SN 465.  NOT SERVICABLE DUE TO INTERMITTENT TRANSMIT.  REMOVED	 RT-450 SN 465.  RETURNED TO   INSTALLED REPAIRED UNIT RT-450 SN 530.  OP CHECK GOOD.					1	G	7	2 	3U				H10EU   					 
1999092400133	19990924	00133	EU  	1999	9	24	MVH0064096       	1	19960729	G	7712	9580113720	TRANSMITTER     			AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					TORQUE	READS LOW       	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	2380 				6068	2046			TORQUE TRANSMITTER READS LOW.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400134	19990924	00134	EU  	1999	9	24	MVH0064097       	1	19960729	G	7714	645383081	INDICATOR       			AEROSP	SA365 	SA365N      	8680669	EU  										NG TACH	STICKING        	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	5180 				6068				TACHOMETER GAUGE STICKS.						1	G	7	2 	3U				H10EU   					 
1999092400135	19990924	00135	EU  	1999	9	24	MVH0064099       	1	19960730	G	7712	9580113720	TRANSMITTER     			AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					TORQUE	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	525  				6068	2046			TORQUE TRANSMITTER SHORTED INTERNALLY.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400136	19990924	00136	EU  	1999	9	24	MVH0064100       	1	19960730	G	6210	365A11005003	BLADE           			AEROSP	SA365 	SA365N      	8680669	EU  										MAIN ROTOR	DAMAGED         	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	5246 				6068				MAIN ROTOR REMOVED FOR DAMAGE TO INBOARD LEADING EDGE.						1	G	7	2 	3U				H10EU   					 
1999092400137	19990924	00137	EU  	1999	9	24	MVH0064101       	1	19960730	G	3213	1801510001	STRUT           			AEROSP	SA365 	SA365N      	8680669	EU  										MLG	RATCHETS        	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	5266 				6068				STRUT DOES NOT EXTEND SMOOTHLY.  RATCHETS DOWN AND SOME TIMES WILL NOT EXTEND.						1	G	7	2 	3U				H10EU   					 
1999092400138	19990924	00138	EU  	1999	9	24	MVH0064102       	1	19960730	G	6210	365A11005003	BLADE           			AEROSP	SA365 	SA365N      	8680669	EU  										MAIN ROTOR	DAMAGED         	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	5246 				6068				MAIN ROTOR REMOVED FOR DAMAGE TO INBOARD LEADING EDGE.						1	G	7	2 	3U				H10EU   					 
1999092400139	19990924	00139	EU  	1999	9	24	MVH0064103       	1	19960730	G	7931	53408A	TRANSMITTER     			AEROSP	SA365 	SA365N      	8680669	EU  										ENG OIL PRESS	ERRATIC         	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				TRANSMITTER INDICATION ERRATIC.  REMOVED.						1	G	7	2 	3U				H10EU   					 
1999092400140	19990924	00140	EU  	1999	9	24	MVH0064104       	1	19960730	G	2150	M4582AE	BLOWER          			AEROSP	SA365 	SA365N      	8680669	EU  										AIR DISTRIBUTION	INOPERATIVE     	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	2060 				6068				BLOWER INOPERABLE.						1	G	7	2 	3U				H10EU   					 
1999092400141	19990924	00141		1999	9	24	MVH0064105       	4	19960730	G	3421	H140JAM	GYRO            			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	80   				6068				GYRO WILL NOT STAY.						1	G	7	2 	3U				H10EU   					 
1999092400142	19990924	00142		1999	9	24	MVH0064106       	4	19960730	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				RT 450 WILL NOT TURN ON.						1	G	7	2 	3U				H10EU   					 
1999092400143	19990924	00143		1999	9	24	MVH0064109       	4	19960730	G	3416	396005241	ENCODER         			AEROSP	SA365 	SA365N      	8680669	EU  										ALTIMETER	INACCURATE      	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				ENCODER INDICATES INACCURATELY.						1	G	7	2 	3U				H10EU   					 
1999092400144	19990924	00144		1999	9	24	MVH0064110       	4	19960731	G	2312	6221879001	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				VHF TRANSCEIVER WILL NOT COME ON.						1	G	7	2 	3U				H10EU   					 
1999092400145	19990924	00145		1999	9	24	MVH0064111       	4	19960731	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				TRANSCEIVER WILL NOT TRANSMIT.						1	G	7	2 	3U				H10EU   					 
1999092400146	19990924	00146	EU  	1999	9	24	MVH0064112       	1	19960731	G	2612	C33	DETECTOR        			AEROSP	SA365 	SA365N      	8680669	EU  										CABIN	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				DETECTOR ILLUMINATES WHEN BATTERY TURNED ON.  REPLACED AND SCRAPPED LOCALLY.						1	G	7	2 	3U				H10EU   					 
1999092400147	19990924	00147		1999	9	24	MVH0064117       	4	19960830	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				LOANER RT-450 IS STATIC IN TRANSMIT.  BLEEDING OVER ONTO OTHER RADIOS.  PROBLEM IS CONSTANT WITH INTERMITTENT BREAKS IN 	TRANSMIT.  REMOVED LOANER RT 450 SN 652.  INSTALLED LOANER SN 465.  OPS CHECK GOOD.					1	G	7	2 	3U				H10EU   					 
1999092400148	19990924	00148	NE  	1999	9	24	MVH0064119       	2	19960913	G	7210	0235237600	CHIP DETECTOR   			AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					ENGINE	LEAKING         	H			BAQA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	63CF					6068	2203			CHIP PLUG LEAKS THROUGH BODY AND ELECTRODE IS LOOSE.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400149	19990924	00149		1999	9	24	MVH0064120       	4	19960925	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	INTERMITTENT    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				RT 450 SN 530 REMOVED DUE TO INTERMITTENT TRANSMIT.   REMOVED RT 450 SN 530.  INSTALLED RT 450 LOANER FROM CORPORATE JET	S PN 400-0103-00 SN 464.  TRANSMITS AND RECEIVES GOOD.					1	G	7	2 	3U				H10EU   					 
1999092400150	19990924	00150		1999	9	24	MVH0064123       	4	19961013	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	INTERMITTENT    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				RT 450 LOANER SN 652 IS INTERMITTENT IN TRANSMIT.  REMOVED LOANER RT 450 SN 652.  REINSTALLED LOANER RT 450 SN 464.  OP 	CHECKS GOOD.					1	G	7	2 	3U				H10EU   					 
1999092400151	19990924	00151		1999	9	24	MVH0064124       	4	19961018	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	INTERMITTENT    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				RT 450 LOANER SN 652 IS INTERMITTENT IN TRANSMIT.  REMOVED LOANER RT 450 SN 652 AND REINSTALLED RT 450 SN 530.  OP CHECK	S GOOD.					1	G	7	2 	3U				H10EU   					 
1999092400152	19990924	00152	EU  	1999	9	24	MVH0064126       	1	19961023	G	6730	SC4161	SERVO           			AEROSP	SA365 	SA365N      	8680669	EU  										TAIL ROTOR	LEAKING         	H			BAQA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	63CF	509  				6068				TAIL ROTOR SERVO LEAKS AT INPUT AND OUTPUT, SERVO INPUT LEVER WORN.						1	G	7	2 	3U				H10EU   					 
1999092400153	19990924	00153		1999	9	24	MVH0064127       	4	19961024	G	2312	CH45202G	CONTROL UNIT    			AEROSP	SA365 	SA365N      	8680669	EU  										COMMUNICATIONS	INTERMITTENT    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	3596 				6068				RT 450 HAS INTERMITTIENT TRANSMIT LANE RT2.						1	G	7	2 	3U				H10EU   					 
1999092400154	19990924	00154		1999	9	24	MVH0064129       	4	19961024	G	2211	CDV85	COMPUTER        			AEROSP	SA365 	SA365N      	8680669	EU  										AUTO PILOT	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	5573 				6068				AUTOPILOT DECOUPLES, INTERMITTENT, HAS PROBLEMS HOLDING TRACK.						1	G	7	2 	3U				H10EU   					 
1999092400155	19990924	00155	EU  	1999	9	24	MVH0064140       	1	19961113	G	2435	524031B	BRUSHES         			AEROSP	SA365 	SA365N      	8680669	EU  										STARTER/GEN	WORN            	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	3790 				6068				GENERATOR BRUSHES WORN.  OVERHAULED, CHANGED BEARINGS, AND NEW BRUSHES.						1	G	7	2 	3U				H10EU   					 
1999092400156	19990924	00156	NE  	1999	9	24	MVH0064141       	2	19961116	G	7260	9560115450	MAGNETIC SEAL   			AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					STARTER DRIVE	LEAKING         	H			BAQA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	63CF	202  				6068	2203			MAG SEAL REMOVED FOR LEAKING.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400157	19990924	00157	EU  	1999	9	24	MVH0064143       	1	19961118	G	7920	0210145040	CHECK VALVE     		ARRIEL1     	AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					ENGINE OIL	LEAKING         	H			BAQA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	63CF				2106	6068	2203			REPLACED VALVE FOR EXTERNAL LEAKING SN P171B.  REMOVED VALVE SN P171B AND INSTALLED SERVICABLE VALVE , SN K575B.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400158	19990924	00158		1999	9	24	MVH0064144       	4	19961120	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				LOANER RT 450 SN 652 WILL NOT TRANSMIT.  REPLACED WITH LOANER RT 450 SN 465.						1	G	7	2 	3U				H10EU   					 
1999092400187	19990924	00187	EU  	1999	9	24	MVH0064211       	1	19960730	G	3230	894TS05NY	SWITCH          			AEROSP	SA365 	SA365N      	8680669	EU  										MLG	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	136  				6068				LANDING GEAR SWITCH INTERMITTENT, WILL NOT EXTEND OCCASIONALLY .						1	G	7	2 	3U				H10EU   					 
1999092400188	19990924	00188	EU  	1999	9	24	MVH0064212       	1	19960730	G	3270	160PS01A5A	BUTTON          			AEROSP	SA365 	SA365N      	8680669	EU  										AUX MLG	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	5266 				6068				BUTTON IS INTERMITTENT, GEAR WILL NOT EXTEND OCCASIONALLY.						1	G	7	2 	3U				H10EU   					 
1999092400189	19990924	00189	EU  	1999	9	24	MVH0064216       	1	19960730	G	6220	126892P	ROD END         			AEROSP	SA365 	SA365N      	8680669	EU  										MAIN ROTOR	WORN            	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				PART WORN EXCESSIVELY.						1	G	7	2 	3U				H10EU   					 
1999092400190	19990924	00190		1999	9	24	MVH0064217       	4	19960730	G	2312	A21815869808	SWITCH          			AEROSP	SA365 	SA365N      	8680669	EU  										TRIGGER	INTERMITTENT    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	259  				6068				SWITCH INOPERATIVE, INTERMITTENT ACTIVATION.						1	G	7	2 	3U				H10EU   					 
1999092400191	19990924	00191		1999	9	24	MVH0064218       	4	19960730	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				TRANSCEIVER WILL NOT TRANSMIT.						1	G	7	2 	3U				H10EU   					 
1999092400192	19990924	00192	EU  	1999	9	24	MVH0064219       	1	19960731	G	6320	365A32600100ME	BRUSH           			AEROSP	SA365 	SA365N      	8680669	EU  										M/R GEARBOX	DEBONDED        	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	1848 				6068				GIMBLE RING BUSHINGS DEBONDED AND WORN.						1	G	7	2 	3U				H10EU   					 
1999092400193	19990924	00193	EU  	1999	9	24	MVH0064221       	1	19960814	G	5260	14860011	ACTUATOR        			AEROSP	SA365 	SA365N      	8680669	EU  										STEP	INOPERATIVE     	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	316  				6068				ACTUATOR INOPERATIVE.						1	G	7	2 	3U				H10EU   					 
1999092400194	19990924	00194	EU  	1999	9	24	MVH0064233       	1	19961111	G	6720	360A33107001	LOBE            			AEROSP	SA365 	SA365N      	8680669	EU  										PITCH CONTROL	WORN            	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				LOBES WORN ON TAIL ROTOR PITCH.						1	G	7	2 	3U				H10EU   					 
1996080200316	19960802	00316		1996	8	2	RU3A96003        	4	19960627	G	3451		TRANSISTOR      	SIERRA      	890100011   	BEECH 	300   	300BEECH    	1152930	CE  										TACAN SYSTEM	SHORTED         	A			RU3A	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	21	70					FF5				ELECTRICAL FUMES INSIDE AIRCRAFT, MADE PRECAUTIONARY LANDING.  (M)						2	L	7	2 	4T				A24CE   					 
1996080200317	19960802	00317	CE  	1996	8	2	RU3A96004        	1	19960705	G	2121	SR1406	BLOWER MOTOR    			BEECH 	300   	300BEECH    	1152930	CE  										AUX AIR COND	FAILED          	A			RU3A	A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SW	21	81				OKC115019	FF16				THE CREW REPORTED AN ELECTRICAL BURNING SMELL IN THE CABIN SHORTLY AFTER DEPARTING THE PEORIA, ILL AIRPORT.  THEY IMMEDI	ATELY RECEIVED CLEARANCE TO THE AIRPORT AND LANDED WITHOUT INCIDENT.  MAINTENANCE FOUND THE AVIONICS EQUIPMENT CABINET A	UX AIR CONDITIONING EVAPORATOR BLOWER MOTOR WAS INOP AND SMELL OVERHEATED.  THE BLOWER MOTOR WAS REPLACED AND THE AIRCRA	FT WAS RETURNED TO SERVICE.  (M)			2	L	7	2 	4T				A24CE   					 
1996020900087	19960209	00087	NM  	1996	2	9	TWRA9603         	1	19960111	G	3350	3004185	LIGHT           			BOEING	747   	747212B     	1384886	NM  										L5 DOOR	INOPERATIVE     	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY INSPECTION, L5 MAIN ENTRY DOOR EMERGENCY LIGHT WAS FOUND INOPERATIVE.  EVAC L5 EMERGENCY DOOR LIGHT WAS REP	LACED.  OPS CHECK OK.  MM REF 33-51-00.  (X)					2	L	7	4 	4F				A20WE   					 
1996082900753	19960829	00753	NM  	1996	8	29	TWRA96208        	1	19960724	G	3350	S1356B37	LIGHT           			BOEING	747   	747212B     	1384886	NM  										CABIN	INOPERATIVE     	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186				16336	21439				DURING DAILY CHECK, FOUND SILL LIGHT L5 DOOR FORWARD INOP.  REMOVED AND REPLACED SILL LIGHT.  OPS CHECK NORMAL PER MM 33	-51-00.  (M)					2	L	7	4 	4F				A20WE   					 
1996082900754	19960829	00754	NM  	1996	8	29	TWRA96209        	1	19960724	G	3350	ML7715	BULB            			BOEING	747   	747212B     	1384886	NM  										CABIN	FAILED          	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND SEAT 56, 57 ABC EVAC LIGHTS INOP.  RELAMPED, OPS CHECK OK PER MM 33-51-00.  (M)						2	L	7	4 	4F				A20WE   					 
1996082900755	19960829	00755	NM  	1996	8	29	TWRA96210        	1	19960724	G	3350	276001	FUSE            			BOEING	747   	747212B     	1384886	NM  										CABIN	INOPERATIVE     	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND E-ZONE E-PATH BATTERY PACK DISCONNECTED DUE TO LIGHT STAYING ON ALL TIMES.  REPLACED FUSE ALL 	E-ZONE E-PATH LIGHTS.  OPS CHECK OK PER MM 33-51-00.  (M)					2	L	7	4 	4F				A20WE   					 
1996090500537	19960905	00537	NM  	1996	9	5	TWRA96242        	1	19960727	G	3350	ML7715	BULB            			BOEING	747   	747212B     	1384886	NM  										CABIN	FAILED          	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND EVAC LIGHT AT SEAT 40ABC INOP.  REPAIRED BROKEN WIRE AND RELAMPED.  OPS CHECKED OK PER MM 33-5	1-00 PG 501.  (M)					2	L	7	4 	4F				A20WE   					 
1996082900773	19960829	00773	NM  	1996	8	29	TWRA96256        	1	19960731	G	3350	ML7715	BULB            			BOEING	747   	747212B     	1384886	NM  										CABIN	FAILED          	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND EMERGENCY LIGHT INOP AT SEAT 45C.  REPLACED LAMP AND LENS ASSY.  OPS CHECKED GOOD PER MM 33-51	-00 PG 501.  (M)					2	L	7	4 	4F				A20WE   					 
1996091900846	19960919	00846	NM  	1996	9	19	TWRA96297        	1	19960824	G	3350	776005	FUSE            			BOEING	747   	747212B     	1384886	NM  										CABIN	BLOWN           	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND D-ZONE ENTIRE LEFT SIDE EVAC LIGHTS INOP BETWEEN ROWS 35ABC-45ABC.  REMOVED AND REPLACED BATTE	RY PACK FUSE PER MM 33-51-00.  OPS CHECKED NORMAL.  (M)					2	L	7	4 	4F				A20WE   					 
1996100300608	19961003	00608	NM  	1996	10	3	TWRA96303        	1	19960829	G	3350	776005	FUSE            			BOEING	747   	747212B     	1384886	NM  										CABIN	BLOWN           	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND D-ZONE LEFT SIDE EVAC LIGHT INOP.  REMOVED AND REPLACED BATTERY PACK FUSE.  OPS CHECK NORMAL P	ER MM 33-51-00, PAE 501.  (M)					2	L	7	4 	4F				A20WE   					 
1996100300609	19961003	00609	NM  	1996	10	3	TWRA96304        	1	19960829	G	3350	086861	SOCKET          			BOEING	747   	747212B     	1384886	NM  										CABIN	INOP            	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				DURING DAILY CHECK, FOUND SEAT 21C EVAC LIGHT INOP.  REPLACED SOCKET AND RELAMPED.  OPS CHECKED NORMAL AS PER MM 33-51-0	0.  (M)					2	L	7	4 	4F				A20WE   					 
1996110700715	19961107	00715	SW  	1996	11	7	UNKN0000089      	1	19961010	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	CORRODED        	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	102FW				A21429	621905				PART IS CORRODED. REPLACED WITH BLADE FROM BHT.  (X)						1	G	7	1 	4U				EXPA1G71					 
1996110700714	19961107	00714	SW  	1996	11	7	UNKN0000090      	1	19961010	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	CORRODED        	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	102FW				A21279	621905				PART IS CORRODED. RECEIVED FROM BHT AS IS - REORDERED 2ND SET FROM BHT.  (X)						1	G	7	1 	4U				EXPA1G71					 
1996110700713	19961107	00713	SW  	1996	11	7	UNKN0000091      	1	19961010	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	CORRODED        	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	102FW				A21068	621905				PART IS CORRODED.  2ND SET RECEIVED FORM BHT - REORDERED 3RD SET FROM BHT.  (X)						1	G	7	1 	4U				EXPA1G71					 
1996110700712	19961107	00712	SW  	1996	11	7	UNKN0000092      	1	19961010	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	CORRODED        	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	102FW				A21063	621905				PART IS CORRODED.  2ND SET FROM BHT - REORDERED 3RD SET FROM BHT.  (X)						1	G	7	1 	4U				EXPA1G71					 
1996110700711	19961107	00711	SW  	1996	11	7	UNKN0000093      	1	19961016	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	CORRODED        	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	102FW				A21336	621905				PART IS CORRODED.  3RD SET FROM BHT - REORDERED 4TH SET FROM BHT.						1	G	7	1 	4U				EXPA1G71					 
1996110700710	19961107	00710	SW  	1996	11	7	UNKN0000094      	1	19961016	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	CORRODED        	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	102FW				A21337	621905				PART IS CORRODED.  3RD SET FROM BHT - REORDERED 4TH SET FROM BHT.  (X)						1	G	7	1 	4U				EXPA1G71					 
1996110700708	19961107	00708	SW  	1996	11	7	UNKN0000095      	1	19961017	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	CORRODED        	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	102FW				A21233	621905				PART IS CORRODED.  4TH SET FROM BHT - REORDERED 5TH SET FROM BHT.						1	G	7	1 	4U				EXPA1G71					 
1996110700709	19961107	00709	SW  	1996	11	7	UNKN0000096      	1	19961017	G	6410	204011702121	BLADE           			BELL  	204   	UH1B        	1181410	SW  										T/R	CORRODED        	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	102FW				A21236	621905				PART IS CORRODED.  4TH SET FROM BHT - REORDERED 5TH SET FROM BHT.						1	G	7	1 	4U				EXPA1G71					 
1996082900791	19960829	00791	NM  	1996	8	29	USVA69601        	1	19960806	G	5320		STIFFENER       			BOEING	737   	737247      	138448D	NM  										BS 540	CRACKED         	A			USVA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	309VA					19614				VERTICAL STIFFENER FORWARD FACE OF CENTER FUEL TANK IS CRACKED AT UPPER FLOOR FRAME ATTACH CUP BS 540.  REPAIRED IAW MHA	2020 REV 'N/C' DATED 6-26-96 APPROVED DATA FAA FORM 8110-3.  (M)					2	L	7	2 	4F				A16WE   					 
1996082900792	19960829	00792	NM  	1996	8	29	USVA96602        	1	19960806	G	5311		FRAME           			BOEING	737   	737247      	138448D	NM  										BS 578	CRACKED         	A			USVA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	309VA					19614				CIRCUMFERENTIAL FRAME BS 578 RIGHT SIDE, 4 INCHES ABOVE CREASE BEAM, HAS CRACK EMANATING FROM HOLE FOR RECEPTACLE, WHICH	 SIDE WALL PANEL MOUNTS FROM INBOARD FACE OF FRAME RADIUS INTO WEB AREA 1 INCH CRACK.  REPAIRED IAW MHA2021 REV 'N/C' DA	TED 6-26-96 APPROVED DATA FAA FORM 8110-3.  (M)				2	L	7	2 	4F				A16WE   					 
1996082900793	19960829	00793	NM  	1996	8	29	USVA96603        	1	19960806	G	5320	652179962	FITTING         			BOEING	737   	737247      	138448D	NM  										BS 578	CRACKED         	A			USVA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	309VA					19614				MAIN CABIN FLOOR BEAM RIGHT SIDE BS 578 ATTACH ANGLE TO WEB HAS A 3.75 INCH CRACK AT WL 208 AND BBR 70.85.  INSTALLED NE	W FITTING ATTACH ANGLE, AND ALL FASTENERS IAW WITH SRM 51-30-2.  (M)					2	L	7	2 	4F				A16WE   					 
1997013000002	19970130	00002	WP  	1997	1	30	VJ1R96003        	2	19961215	G	7260	30719082	PLUG            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					OIL JET CLEAN	DETACHED        	B			VJ1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	300BS	6932 				NA0241	P76434C			ENGINE COWLING WAS OPENED TO INVESTIGATE LOSS OF OIL.  'FOUND THE TRANSFER GEARBOX OIL JET CLEAN OUT PLUG (CHAPTER 72-60	-03, FIG 1, ITEM 25) UNSEATED AND HANGING ON ITS MOUNTING STUD'.  LUBE OIL WAS VENTED OVERBOARD ONCE THE PLUG WAS UNSEAT	ED.  (X)				2	L	7	2 	4F	4	F		A3EU    	E6WE				 
1996102400363	19961024	00363	SW  	1996	10	24	W6HR9640         	1	19960930	G	6330	222331617101	ISOLATION MT    		222031602107	BELL  	222   	222U        	1182140	SW  										M/R XMSN	WORN EXCESS     	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	416MA					47526				ISOLATION MOUNTIS WORN EXCESSIVELY. ELASTOMERIC MATERIAL IS SEPERATED FROM INNER THREADED BOSS WHERE ROD END IS THREADED	 INTO.					1	G	7	2 	3U				H9SW    					 
1997032700276	19970327	00276	SW  	1997	3	27	W6HR9644         	1	19961106	G	6330	222331617101	ISOLATION MOUNT 			BELL  	222   	222U        	1182140	SW  										M/R XMSN	DEFECTIVE       	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	416MA	59   				47526				MOUNT IS DEFECTIVE.  MOUNT APPEARS TO BE "WEAK".  A/C HAD A "GROUND BOUNCE".  POSSIBLE DELAMINATION OF ELASTROMIC MATERI	AL IS APPARENT.  REPLACING THIS MOUNT WI TH "NEW" REMOVED THE GROUND BOUNCE.					1	G	7	2 	3U				H9SW    					 
1996102400754	19961024	00754	CE  	1996	10	24	WG1R583K         	1	19961001	G	2421	835563	ALTERNATOR      			CESSNA	650   	650         	2076802	CE  										NR 1 ENG AC	BEARING FAILED  	B	L		WG1R	O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	19	874G	7406 	1623 			650137				PILOT REPORTED VIBRATION COMING FROM NR 1 ENG WHICH VARIED WITH THROTTLE ALONG WITH A VOLTAGE SPIKE ON AC VOLTMETER.  AF	TER EXTENSIVE TROUBLESHOOTING, FOUND ALTERNATOR BEARINGS HAD FAILED, SHORTING OUT ALTERNATOR CONTROL UNIT, AC VOLT METER	 AND HORIZ STAB ANTI-ICE CONTROL UNIT.  ALTERNATOR ON NR 2 ENGINE FAILED 5 HRS LATER SHORTING OUT ALTERNATOR CONTROL UNI	T ALSO.  ALTERNATOR BEARINGS HAVE A SERVCIE LIFE OF 2,000 HRS.  FIRST ONE FAILED AT 1,618 HRS AND SECOND AT 1623 HRS SIN	CE OVERHAUL.  (X)		2	L	7	2 	4F				A9NM    					 
1996061300067	19960613	00067	EU  	1996	6	13	XC4R9620651      	1	19960305	G	2435	P6048233	ARMATURE        	AUXILEC     	8260121     	AEROSP	ATR72 	ATR72       		EU  										START/GEN NR 2	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			425  		1146					ARMATURE COMMUTATOR TOTAL INDICATED RUN-OUT VARIES PLUS OR MINUS 0.005 INCH.  INCONSISTENCY OF COMMUTATOR WEAR CAUSED EX	CESSIVE BRUSH WEAR.  (X)					2	H	7	2 	4T			RT