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
2003020400170	20030204	00170	GL  	2003	2	4	00065074         	3	20030114	G	6111	A1851T	BEARING         			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	PROP BLADE	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								EAA1241		CORROSION ON PROPELLER BLADE BEARINGS.						1	L	7	2 	4T	3	T	 	A31CE   	E2NE	6	C	P40EA	 
2003020400171	20030204	00171	GL  	2003	2	4	0065077          	3	20030130	G	6114		HUB             			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								902496		CORROSION ON PROPELLER HUB.						1	H	7	1 	3T	3	T	NT	A37CE   	E2NE	5	C	P60GL	 
2003020400172	20030204	00172	GL  	2003	2	4	0065202          	3	20030120	G	6114	C5152	COUNTERWEIGHT   			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	3AF34C	3GFR34C703  	GL  		CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								9611156		CORRISON ON PROPELLER COUNTERWEIGHT.						1	H	7	1 	3T	3	T	NT	A37CE   	E2NE	5	C	P60GL	 
2003020400174	20030204	00174		2003	2	4	00665098         	4	20030114	G	6122	F421Z	BEARING         																	GOVERNOR	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										GOVERNOR HAS CORROSION ON BEARING.																			 
2003040900027	20030409	00027	GL  	2003	4	9	0074382          	3	20030305	G	6110	CO83867	CLAMP           	HARTZL      		PIPER 	J3    	J3C*        	       	SO  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03					BUA26954			BUA26954		CORROSION ON CLAMP ASSEMBLY.						1	H	7	1 	3O	3	T	 	ATC660  	E2NE	6	C	P15EA	 
2003010600005	20030106	00005	CE  	2003	1	6	010203           	1	20030103	G	5510		RIB             			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	HORIZONTAL STAB	MISREPAIRED     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	6506R	8670 	2012 			U2060969	818948R	731126		HORIZONTAL STABILIZER WAS REPAIRED AT AIRCRAFT TOTAL TIME OF 6658.5. 6 EACH NEW AND IMPROVED NOSE RIBS WERE INSTALLED AN	D NUMEROUS RIVETS WERE NOT INSTALLED IN THE REPLACED RIBS.  REFERENCE SERVICE NEWSLETTER NR  87-18R1.  RIBS THAT WERE DE	TERMINED TO BE REPLACED ARE AT STATION 14.74 THRU 35.915 LT AND RT OF HORIZONTAL STABILIZER CENTER LINE.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003020400180	20030204	00180	EA  	2003	2	4	021081           	2	20030109	G	8520		CRANKCASE       			PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	TIO540U2A   	41532	EA  					ENGINE	CRACKED         	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SO	05	6902T	9831 	455  			608265046	RL23861A			ON 28 DEC 2002, AEROSTAR N6902T LANDED AT OAJ WITH NR 2 (RT) ENGINE SHUTDOWN AND PROPELLERS FEATHERED.  THE PILOT STATED	 THAT DURING FLIGHT, HE NOTICED A DROP IN OIL PRESSURE AND SHUTDOWN THE ENGINE.  PRIOR TO SHUTDOWN, THE PILOT STATED THA	T ALL OTHER INDICATIONS WERE NORMAL.  UPON EXAMINATION OF THE ENGINE, A CRACK WAS FOUND BELOW THE NR 5 CYLINDER EXTENDIN	G FORWARD TO BELOW THE NR 3 CYLINDER MIDWAY.  THE LOWER PORTION OF THE CASE WERE THE NR 5 CYLINDER ATTACHED HAD SEPARTAT	ED TO THE POINT WHERE THE LOWER MOUNTING HOLES WERE VISIBLE WITH THE CYLINDER STILL ATTACHED TO THE CASE.  INTERNAL DAMA	GE IS EXPECTED TO BE FOUND, BUT TO DATE HAS YET TO BE DETERMINED.	1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
2003040900028	20030409	00028	NM  	2003	4	9	021081F          	1	20030325	G	2710	6000050507	CONTROL ROD     			PIPER 	PA60  	PA60602P    	7106015	NM  										RT AILERON	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	6902	2437 								RT AILERON PUSH PULL TUBE CORRODED SEVERELY.  HOLE WORE THROUGH.  LOCATED BEHIND ENGINE.  RECOMMEND SPECIAL ATTENTION BE	 PAID TO THIS AREA DURING INSPECTIONS.					1	M	7	2 	3O			RT	A17WE   					 
2003020400189	20030204	00189	CE  	2003	2	4	030130           	1	20030129	G	5740	3910104001	FITTING         			HELIO 	H295  	H295        	4300802	CE  										WING	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	61JA					1286				UPPER WING ATTACH FITTING IS CRACKED.  THE CRACKS APPEAR ON THE FACE OF THE FITTINGS THAT GO AGAINST THE SPAR CARRY THRU	.  IN SOME CASES THE CRACKS CAN BE DETECTED INSIDE THE BARREL NUT BORE.  WE HAVE BEGUN CHECKING SPARE WINGS IN STORAGE A	S WELL AS FLIGHT LINE AIRCRAFT.  TO DATE WE HAVE FOUND 9 CRACKED FITTINGS.  TIMES IN SERVICE RANGE FROM 5087 TO OVER 16,	000 HOURS.   CRACKS WILL OFTEN RUN PARALLEL TO THE AXIS OF THE BARREL NUT.  SOME FITTINGS EXHIBIT A CIRCULAR BRINNELED A	REA WHERE THE FITTING CONTACTS THE CARRY THRU.  CRACKS CAN APPEAR IN THE CIRCUMFERENCE OF THE IMPRESSION OR RADIATE IN O	R OUT FROM THE CIRCUMFERENCE OF THE IMPRESSION.  SOMETIMES CORROSION IS PRESENT IN THE CRACK AREA.	1	H	7	1 	3O			 	1A8     					 
2003062500003	20030625	00003	SO  	2003	6	25	03022601         	1	20030227	G	2810	A23D0475	SOLENOID        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUEL SYSTEM	LEAKING         	C			JIKR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	01	9132Y	257  				31178				PILOT REPORTED A FUEL ODOR IN THE COCKPIT ON PREFLIGHT INSPECTION.  MAINTENANCE INSPECTED THE COCKPIT AND COMBUSTION HEA	TER AREA IN THE RIGHT SIDE OF THE THE NOSE SECTION AND FOUND THE HEATER FUEL SHUT OFF SOLENOID LEAKING FUEL FROM THE CAS	E HOUSING.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003040900029	20030409	00029	EA  	2003	4	9	030327           	2	20030327	G	7414	AB357174	POINTS          			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480G1D6   	41527	EA  					MAGNETO	LOOSE           	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	61JA	232  				1286				MAGNETO BREAKER ASSEMBLY HAS LOOSE CAM FOLLOWER.						1	H	7	1 	3O	3	O	 	1A8     	E275				 
2003061100005	20030611	00005	CE  	2003	6	11	030520           	1	20030514	G	5740	3910104322	ATTACH FITTING  			HELIO 	H295  	H295        	4300802	CE  										LT & RT WING	ELONGATED       	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	PKJAA					1436				REAR SPAR ATTACH FITTING BOLT HOLE IS ENLARGED ON BOTH WINGS.  FITTINGS ARE BEING REPLACED.						1	H	7	1 	3O			 	1A8     					 
2003061100003	20030611	00003	CE  	2003	6	11	030521           	1	20030514	G	5740	3910104001	FITTING         			HELIO 	H295  	H295        	4300802	CE  										WING	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	PKJAA					1436				UPPER WING ATTACH FITTINGS ON BOTH WINGS ARE CRACKED. THE CRACKS APPEAR ON THE FACE OF THE LEFT FITTING AND THE INSIDE C	ORNER OF THE RIGHT FITTING, THE FACES OF WHICH GO AGAINST THE SPAR CARRY THRU.  FRETTING IS PRESENT BETWEEN THE FITTING 	AND SPAR ON THE RIGHT WING. TO DATE WE HAVE FOUND 9 CRACKED FITTINGS OF 30 WINGS INSPECTED. TIMES IN SERVICE RANGE FROM 	5087 TO OVER 16,000 HOURS. CRACKS WILL OFTEN RUN PARALLEL TO THE AXIS OF THE BARREL NUT. SOME FITTINGS EXHIBIT A CIRCULA	R BRINNELED AREA WHERE THE FITTING CONTACTS THE CARRY THRU. CRACKS CAN APPEAR IN THE CIRCUMFERENCE OF THE IMPRESSION OR 	RADIATE IN OR OUT FROM THE CIRCUMFERENCE OF THE IMPRESSION. SOMETIMES CORROSION IS PRESENT IN THE CRACK AREA.	1	H	7	1 	3O			 	1A8     					 
2003091200075	20030912	00075	CE  	2003	9	12	030815           	1	20030815	G	5740	3910104001	ATTACH FITTING  			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480G1D6   	41527	EA  					WING	CRACKED         	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	60JA					1240				UPPER WING ATTACH FITTINGS ARE CRACKED. THE CRACKS APPEAR ON THE FACE OF THE FITTINGS THAT GO AGAINST THE SPAR CARRY THR	U.  IN SOME CASES THE CRACKS CAN BE DETECTED INSIDE THE BARREL NUT BORE.   3 OF THE 4 FITTINGS ON THIS PLANE ARE CRACKED	.  TIMES IN SERVICE RANGE FROM 5087 TO OVER 16,000 HOURS.  CRACKS WILL OFTEN RUN PARALLEL TO THE AXIS OF THE BARREL NUT.	  SOME FITTINGS EXHIBIT A CIRCULAR BRINNELED AREA WHERE THE FITTING CONTACTS THE CARRY THRU.  CRACKS CAN APPEAR IN THE C	IRCUMFERENCE OF THE IMPRESSION OR RADIATE IN OR OUT FROM THE CIRCUMFERENCE OF THE IMPRESSION.  SOMETIMES CORROSION IS PR	ESENT IN THE CRACK AREA.	1	H	7	1 	3O	3	O	 	1A8     	E275				 
2003102700127	20031027	00127	CE  	2003	10	27	030926A          	1	20030925	G	2897		WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BOOST PUMP	CHAFED          	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6763L					5500673				DURING INTERNAL INSPECTION OF THE FUEL BAYS FOUND FUEL PUMP WIRING HARNESSES IN BOTH WINGS WERE DAMAGED BY CHAFFING THRO	UGH THE WIRING INSULATION.  WIRING WAS CHAFFING AGAINST ALUMINUM FUEL LINES AND PUMP BODY INSIDE TANK.  CHAFFING CAUSED 	WEAR BEYOND LIMITS TO ALUMINUM FUEL LINES.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003102700128	20031027	00128	CE  	2003	10	27	030926B          	1	20030925	G	2897	1C712	WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL PUMP	CHAFED          	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4614N					5500659				DURING INTERNAL INSPECTION OF THE FUEL BAYS FOUND FUEL PUMP WIRING HARNESSES IN RIGHT WING WAS DAMAGED BY CHAFFING THROU	GH THE WIRING INSULATION.  WIRING WAS CHAFFING AGAINST ALUMINUM FUEL LINE INSIDE TANK.  CHAFFING CAUSED WEAR BEYOND LIMI	TS TO ALUMINUM FUEL LINE.  LEFT WING FUEL PUMP HARNESS HAD BEEN CHAFFING FUEL LINE ALSO.  HARNESS DID NOT HAVE DAMAGE BU	T FUEL LINE WAS WORN BEYOND LIMITS.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003102700129	20031027	00129	CE  	2003	10	27	030926C          	1	20030925	G	2897	1C712	WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL PUMP	CHAFED          	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1200N					5500681				DURING INTERNAL INSPECTION OF THE FUEL BAYS FOUND FUEL PUMP WIRING HARNESSES IN RIGHT WING WAS DAMAGED BY CHAFFING THROU	GH THE WIRING INSULATION TO BEAR WIRE.  WIRING WAS CHAFFING AGAINST ALUMINUM FUEL LINE INSIDE TANK.  CHAFFING CAUSED WEA	R BEYOND LIMITS TO ALUMINUM FUEL LINE.  LEFT WING FUEL PUMP HARNESS WAS NOT CHAFFING AGAINST ANY STRUCTURE OR TUBING.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003102700130	20031027	00130	CE  	2003	10	27	030926D          	1	20030925	G	2897	1C712	WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL PUMP	CHAFED          	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6775C					5500677				DURING INTERNAL INSPECTION OF THE FUEL BAYS FOUND FUEL PUMP WIRING HARNESSES IN RIGHT WING WAS DAMAGED BY CHAFFING THROU	GH THE WIRING INSULATION.  WIRING WAS CHAFFING AGAINST ALUMINUM FUEL LINE INSIDE TANK.  CHAFFING CAUSED WEAR BEYOND LIMI	TS TO ALUMINUM FUEL LINE.  LEFT WING FUEL PUMP HARNESS WAS CHAFFING ON MOTIVE FLOW ALUMINUM FUEL LINE AND BOTH HARNESS A	ND FUEL LINE WERE DAMAGED.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003091700018	20030917	00018	SO  	2003	9	17	031138           	1	20030729	G	3220	6330000	CONTROL ARM     			PIPER 	PA28  	PA28140     	7102802	SO  										NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	2371T	5119 	73   			287225056				FOUND NWS CONTROL BRACE CRACKED ON LT SIDE.  CAUSE DETERMINED TO BE CORROSION ON THE INTERIOR OF THE CONTROL TUBE. UPON 	INSPECTION OF THE TUBE, FOUND CORROSION ALSO FORMED ON THE RT SIDE OF THE TUBE IN THE SAME LOCATION.  ODDLY CORROSION WA	S ONLY PRESENT WITHIN A 1 INCH SPACE BETWEEN THE INBOARD WELD OUTWARD. ALSO FOUND THAT EACH SIDE OF THE CONTROL ARM HAD 	A SLIGHT BEND.  RECOMMEND PARTICULAR ATTENTION DURING INSPECTIONS.			1	L	7	1 	3O			 	2A13    					 
2003091700019	20030917	00019	SO  	2003	9	17	031139           	1	20030729	G	3220	6330000	CONTROL ARM     			PIPER 	PA28  	PA28140     	7102802	SO  										NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	9917W	2397 	29   			2823439				FOUND NWS CONTROL BRACE CRACKED ON LT SIDE.  CAUSE DETERMINED TO BE CORROSION ON THE INTERIOR OF THE CONTROL TUBE. UPON 	INSPECTION OF THE TUBE, FOUND CORROSION FORMED ON THE RT SIDE OF THE TUBE IN THE SAME LOCATION.  ODDLY CORROSION WAS ONL	Y PRESENT WITHIN A 1 INCH SPACE BETWEEN THE INBOARD WELD OUTWARD. ALSO FOUND THAT EACH SIDE OF THE CONTROL ARM HAD A SLI	GHT BEND.  RECOMMEND PARTICULAR ATTENTION DURING INSPECTIONS.			1	L	7	1 	3O			 	2A13    					 
2003123000037	20031230	00037	CE  	2003	12	30	031311           	1	20031107	G	3710	216CW	PUMP            	CONT        		CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520A      	17032	SO  					VACUUM SYS	WRONG PART      	B			W2OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	4879F	90   	20   		1110635A	U2060579	1110635A			DURING PRE-PURCHASE EVALUATION FOUND DRY VACUUM PUMP INSTALLED AT ENGINE OVERHAUL APPROX 90 HOURS AGO. ORIGINAL PUMP WAS	 WET TYPE. ALL PLUMBING FOR WET PUMP WAS UTILIZED WITH DRY PUMP INSTALLED WITH NON STANDARD FITTINGS. NO APPROVAL FOR IN	STALLATION OF DRY PUMP.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003123000039	20031230	00039		2003	12	30	031311A          	4	20031107	G	3454	05700261	BLOCK           			CESSNA	206   	U206A       	2073316	CE  										ANTENNA MOUNT	CRACKED         	B			W2OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	4879F					U2060579				DURING PRE-PURCHASE EVALUATION FOUND VOR ANTENNA ON TOP OF VERTICAL STABILIZER LOOSE. FURTHER INVESTIGATION REVEALED ANT	ENNA MOUNT BLOCK P/N 0570026-1 CRACKED AND BROKEN IN 2 PIECES.  PREVIOUS UNKNOWN PERSON HAD ATTEMPTED REPAIR OF PART WIT	H EPOXY.				1	H	7	1 	3O			 	A4CE    					 
2003123000040	20031230	00040	CE  	2003	12	30	031311B          	1	20031107	G	7810	12502591	CLAMP           			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520*      	17032	SO  					RT EXHAUST SYS	CRACKED         	B			W2OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	4879F					U2060579				DURING PRE-PURCHASE INSPECTION FOUND RT EXHAUST PIPE CLAMP CRACKED AND BROKEN AWAY FROM SUPPORT.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003032100001	20030321	00001	CE  	2003	3	21	032031           	1	20030320	G	2761	6F3058	RESTRICTOR VALVE			RKWELL	NA265 	NA26565     	7630107	CE  	ALIDSG	TFE731	TFE7313AR   	 	WP  					SPEED BRAKES	BYPASSING       	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	01	82CR	2011 				46549				MAIN ACCOMPLISHED PREFLT INSP AND THEN PILOTS PROCEEDED TO DO THEIR PREFLT INSP.  UPON NORMAL EXTENSION OF SPEED BRAKE P	ANELS, THEY RETRACTED WITH HIGH SPEED AS THOUGH SWITCHES WERE IN THE "GROUND AUTO DEPLOY" POSITION.  DISASSEMBLLY OF RES	TRICTOR VALVE SHOWED THAT IT HAD FAILED INTERNALLY EVIDENCED BY PARTIALLY CRUSHED MESH FILTERS AT EACH END AND SEPERATIO	N OF RESTRICTOR FROM CENTER DEVIDER.  THIS IS SECOND OCCURANCE ON THIS AIRCRAFT, M&D SUBMITTED AT FIRST OCCURANCE.  SUSP	ECT THAT THIS ASSEMBLY IS NOT SUBSTANTIALLY STRONG ENOUGH TO WITHSTAND INTERNAL PRESSURES.		2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2003032400002	20030324	00002	CE  	2003	3	24	032031A          	1	20030320	G	2760	6F3058	RESTRICTOR VALVE			RKWELL	NA265 	NA26565     	7630107	CE  	ALIDSG	TFE731	TFE7313AR   	 	WP  					SPOILER	BYPASSING       	B				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CE	01	82CR	2011 				46549				DURING PREFLT INSP, MAINT CREW NOTED THAT SPOILERS FULLY DEPLOYED IN LESS THAN 1 SECOND WITH SPOILER SWITCHES SET TO "IN	-FLT" MODE.  NORMAL DEPLOY TIME IN THIS MODE IS 6-10 SECONDS WHEREAS "GROUND AUTO-DEPLOY" MODE FOR LANDING IS LESS THAN 	ONE SECOND.  IN PROCESS OF TROUBLESHOOTING, IT WAS DETERMINED THAT HYD RESTRICTOR IN SPOILER SYS WAS NOT RESTRICTING FLO	W IN DEPLOY MODE BUT WILL RESTRICT IN RETRACT MODE.  FURTHER INVESTIGATION DETERMINED THAT RESTRICTOR HAD FAILED.   IT A	PPEARS THAT THE INTERNAL FILTER SCREENS IN THE RESTRICTOR DEFORM ALLOWING THE RESTRICTOR AND DIVIDER PLATES TO FLOAT BAC	K AND FORTH AND DEFORM TO THE POINT THAT RESTRICTOR AND DIVIDER PORTIONS BREAK AWAY FROM THEIR PLATES.	2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2003090200097	20030902	00097	NE  	2003	9	2	03IN170035       	2	20030621	G	8530	LW13535	CYLINDER HEAD   			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	AEIO540L1B5 	41532	NE  	HARTZL	HCC3Y	HCC3YR2     	NE  	RT ENGINE	DEPARTED        	C				E				ENGINE SHUTDOWN         				Y	E	K	ENGINE STOPPAGE           	VIBRATION/BUFFET          	FLUID LOSS                	CR	CRUISE         	1			SO	17	507JP					3262	L1864148	CK959		A/C EXPERIENCED ENG PROBLEMS APPROX 2 MINUTES AFTER INITIATING DESCENT FROM 11,500.   PILOT NOTICED VIBRATION, OBSERVED 	RT ENG FUEL FLOW FLUCTUATING.  ENRICHED FUEL MIXTURES AND TURNED ON FUEL PUMPS.  VIBR CONTINUED, PILOT MOVED RT THROTTLE	 BACK, THEN UP TO CONFIRM PROBLEM WAS WITH RT ENG.  AT THIS TIME, VIBR WORSENED FOLLOWED BY LOUD THUMP AND LARGE BANG.  	PASSENGER WITNESSED PARTS FLYING OFF RT ENG.  PILOT NOTICED  GUAGES FOR RT ENG GO TO ZERO AND THEN FEATHERED, SHUT DOWN 	ENG, ELECTED TO CONTINUE WHERE HE LANDED SAFELY.  INSP REVIELED THAT NR 5 CYL HAD SEPARATED FROM ENG CASE CAUSING DAMAGE	 TO ENG COWLING AND RT WING LE.  CYL DID STAY WITH A/C.  ENG HAD 6 NEWLY O/H CYL INSTALLED 10 FLIGHT HOURS EARLIER.	1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2003060400070	20030604	00070		2003	6	4	0411190033585    	4	20030430	G	3445	7514060	ANTENNA         			GULSTM	G1159 	GIV         	3980115	SO  										TCAS	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	768J	1881 	1881 			1119				FOUND UPPER AND LOWER TCAS ANTENNA NOT INSTALLED IAW THE STRUCTURAL REQUIREMENTS. STC ST01545AT-D INSTALLATION DRAWING S	C44 129001 , REV H.					2	L	7	2 	4F			RT	A12EA   					 
2003050700159	20030507	00159	CE  	2003	5	7	0512749          	1	20030419	G	3320	AL1235250	LAMP            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN	BURNED OUT      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	828QS					258528				END SOCKET OF CABIN INDIRECT LIGHTING FLUORESCENT LAMP TUBE NOTED AS BURNED/BLISTERED FROM OVERHEATING.  THIS CONDITION 	HAS BEEN NOTED PREVIOUSLY BY AVIONICS PERSONNEL IN OTHER AIRCRAFT.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2003091700016	20030917	00016	SO  	2003	9	17	07280305         	2	20030725	G	7414	653271	MAGNETO         			HILLER	UH12  	UH12B       	4360110	WP  	CONT  	O520  	IO520N      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	ENGINE	OVERHEATED      	B			YD5R	O				OTHER                   				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			GL	15	245C	238  				324	357302			THE OWNER/PILOT FOUND DURING GROUND OPERATION THAT THE RIGHT MAGNETO FAILED THE MAGNETO OPERATIONAL CHECK. THE MAGNETO W	AS REPLACED AND TESTED NORMAL. TWO DAYS LATER IT WAS DISCOVERED THAT THIS AIRCRAFT HAD A LT MAGNETO FAILURE SEVERAL WEEK	S EARLIER. THE RIGHT MAG WAS DISASSEMBLED AND FOUND TO BE PARTIALLY BURNED INSIDE ON THE DISTRIBUTOR GEAR ASSEMBLY. THE 	FAILED LEFT HAND MAGNETO WAS LOCATED, DISSASSEMBLED AND A SIMILAR CONDITION WAS NOTED, HOWEVER THE DAMAGE WAS NOT AS EXT	ENSIVE. THE MANUFACTURER WAS CONTACTED. THE SERVICE REP THAT ANSWERED THE PHONE SAID HE HAD SEEN THIS CONDITION BEFORE B	UT WE WOULD HAVE TO TALK TO THEIR ENGINEERING DEPARTMENT. WE ARE CURRENTLY AWAITING THEIR RESPONSE.	1	G	7	1 	3O	3	O	 	6H2     	E5CE	5	C	P25EA	 
2003031700164	20030317	00164	EU  	2003	3	17	073001           	1	20030314	G	1420	MS3126F24	CONNECTOR       			BRAERO	DH125 	BAE125800A  	1500285	EU  										ANGLE OF ATTACK	ARCED           	C				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			SW	11	244JM					258138				ANGLE OF ATTACK WILL NOT HEAT: INSPECTED CONNECTOR FS20, AND FOUND BOTH ENDS TO BE BURNT. INSPECTED BREAKER AND FOUND TO	 BE, 10AMP BREAKER, WHICH WAS TO LARGE FOR 18 GUAGE WIRE. REPLACED CONNECTOR AND ENGINEERING ISSUED A DRAWING TO ACCOMOD	ATE SYSTEM REQUIREMENTS.				2	L	7	2 	4F			RT	A3EU    					 
2003092200064	20030922	00064	NM  	2003	9	22	08010304         	1	20030813	G	2710	12537101	BEARING         			UNIVAR	108   	1083        	9230408	NM  										ZONE 500	LOOSE           	B			YD5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	747C	940  				1083747				LDC873FT AILERON WAS REMOVED FOR OTHER MAINTENANCE. WITH THE AILERON REMOVED IT WAS DISCOVERED THAT THE BEARING MOUNTED 	IN THE ROLL TRIM MOTOR ASSY. (P/N-12546-001) WAS LOOSE. THIS BEARING IS INSTALLED WITH A  LIQUID LOCKING PRODUCT AND SUB	JECTED TO A LOAD TEST PRIOR TO INSTALLATION. IT IS NOT KNOWN HOW THIS BEARING COULD HAVE COME LOOSE. IT IS VERY DIFFICUL	T TO INSPECT THIS INSTALLATION WITH THE AILERON INSTALLED. THIS BEARING SHOULD BE INSTALLED ANY TIME THE LEFT AILERON IS	 REMOVED.		1	H	7	1 	3O			 	A767    					 
2003091200046	20030912	00046	GL  	2003	9	12	0804307          	1	20030804	G	2730	14832001	MOTOR           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O520  	IO520N      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	PITCH TRIM	LOOSE           	B			YD5R	O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			GL	15	1457	169  				0547				PILOT NOTED EXCESSIVE FREE PLAY AT ELEVATOR. ELEVATOR WAS ABLE TO BE MOVED WITH LITTLE RESISTANCE  APPROX FOUR INCHES (T	WO INCHES UP AND TWO INCHES DOWN FROM TRIMMED POSITION)INVESTIGATION REVEALED THAT ARM ON PITCH TRIM MOTOR WAS LOOSE IN 	RELATIONSHIP TO PITCH TRIM MOTOR SHAFT (ASSY. P/N-14832-001).  NEW DESIGN HAS ARM (P/N-14908-001) SECURED TO SHAFT WITH 	A SINGLE SET SCREW (P/N- 51190-245). IT APPEARS THAT UPON INITAL INSTALLATION IF THE SETSCREW IN THE ARM IS NOT CENTERED	 CORRECTLY IN SHAFT RECEPTACLE TIGHTENING SETSCREW COULD GIVE AN INDICATION OF BEING "TIGHT" WHEN  SETSCREW HAS NOT PENE	TRATED COMPLETELY DOWN INTO THE SHAFT RECEPTACLE. THIS ARM/SHAFT SHOULD BE CHECKED ANY TIME "FREEPLAY" IS NOTED AT ELEVA	1	L	7	1 	3O	3	O	NT	A00009CH	E5CE	5	C	P25EA	 
2004022300030	20040223	00030	SO  	2004	2	23	1022031237WHR    	1	20031022	G	5230	1159SCB2022	DOOR SEAL       	GULSTM      		GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					ZONE 800	DEBONDED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1904W	609  			1237	1237				CREW REPORTED THAT WHEN THEY PULLED THE POWER BACK FOR DESCENT, THE CABIN ALTITUDE WOULD CLIMB. INCREASED THE POWER AND 	THE CABIN WOULD STABILIZE.  FOUND THE 1159SCB202-2 BAGGAGE DOOR SEAL BATCH NR 01-0004.  UNIT FAILED AT THE MOLD LINE WHE	RE THE INFLATION TUBE JOINS THE SEAL. APPEARS THAT THE ADHESIVE DID NOT HOLD THE SEAL TOGETHER.  THIS IS ONE OF THE NEW 	SILICON SEALS. THEY DO NOT SEEM TO BE HOLDING UP AS WELL AS THE OLD STYLE SEALS.			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2004022300029	20040223	00029	SO  	2004	2	23	102203WHR        	1	20031022	G	5230	1159SCB2022	DOOR SEAL       	GULSTM      		GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					CARGO DOOR	DEBONDED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1904W	609  			1237	1237				CREW REPORTED THAT WHEN THEY PULLED THE POWER BACK FOR DESCENT, THE CABIN ALTITUDE WOULD CLIMB. INCREASED THE POWER AND 	THE CABIN WOULD STABILIZE.  FOUND THE 1159SCB202-2 BAGGAGE DOOR SEAL BATCH NR 01-0004.  UNIT FAILED AT THE MOLD LINE WHE	RE THE INFLATION TUBE JOINS THE SEAL. APPEARS THAT THE ADHESIVE DID NOT HOLD THE SEAL TOGETHER.  THIS IS ONE OF THE NEW 	SILICON SEALS. THEY DO NOT SEEM TO BE HOLDING UP AS WELL AS THE OLD STYLE SEALS.			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003080500011	20030805	00011	EU  	2003	8	5	106476B          	1	20030521	G	6321	C632A2108102	DISC            			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					ROTOR BRAKE	FAILED          	C			SC0M	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	255SD	1068 				1102				FOUND DURING 500 HOUR INSPECTION.  INSPECTION CHECK WIGH DIAL INDICATOR REQUIRED DISASSEMBLE.  SPLINES INSPECTED AND MEA	SURED WITH PINS.  BEYOND LIMITS, PART REJECTED.  NOTE: ROTOR BRAKE DISC FREE FLOATS ON THIS SPLINE ASSEMBLY.  WEAR STEP 	ONLY IN AREA DISC RIDES.				1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2003070700210	20030707	00210	EU  	2003	7	7	106844B          	1	20030521	G	6420	C642A0402101	STRAP           			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					TAIL ROTOR HEAD	DAMAGED         	C			SC0M	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	266SD	1000 				1133				TORSION STRAP ASSY IS USED IN THE TAIL ROTOR ASSY.  FOUND DURING 500 HOUR INSPECTION/ DISASSEMBLED FOR INSPECTION.  SCOR	ING ON 2 STRAPS.  FRETTING ON NUMEROUS STRAPS, SURFACE CORROSION. (ASSEMBLY REJECTED, NEW STRAP ASSEMBLY INSTALLED)					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2003111300053	20031113	00053	CE  	2003	11	13	11032003001      	1	20031003	G	5312	24130013	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					FUSELAGE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	9390B	5460 				172RG0810				CRACKS IN LOWER LEFT BULKHEAD UNDER PILOT'S INBOARD RUDDER PEDAL TORQUE TUBE PILLOW BLOCK,  ALLOWED ABNORMAL FORWARD/AFT	 MOVEMENT OF RUDDER PEDAL TORQUE TUBE.  REPORTED TO MFG BY TELECON.  (AL03200407996)					1	H	7	1 	3O	3	O	 	3A17    	E286				 
2003111300054	20031113	00054	CE  	2003	11	13	11032003002      	1	20031003	G	5312	24130016	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										FUSELAGE	CRACKED         	M			IE8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	9390B	5460 				172RG0810				CRACKS IN UPPER LEFT BULKHEAD UNDER PILOT'S INBOARD RUDDER PEDAL TORQE TUBE PILLOW BLOCK, ALLOWED ABNORMAL FORWARD/AFT M	OVEMENT OF RUDDER PEDAL TORQE TUBE.  REPORTED TO MFG BY TELECON.					1	H	7	1 	3O			 	3A17    					 
2003123000015	20031230	00015		2003	12	30	112003           	4	20031120	G	2562	MN1300	BATTERY         	ACK         		BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6*        	52043	EA  					ELT	FAILED          	B			EVGR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	33	65JA				0322707	LM34				DURING A FUNCTION TEST OF THE ELT THE UNIT WOULD NOT TEST.  ON INVESTIGATION WE FOUND THAT ONE OF THE BATTERIES WAS FAUL	TY WITH AN (OPEN) CONDITION. WE REPLACED ALL THE BATTERIES AND THE UNIT FUNCTION TESTED PROPERLY.					1	L	7	2 	3T	3	T	 	3A20    	E2NE				 
2003123000001	20031230	00001	SO  	2003	12	30	11252003         	1	20031125	G	3230	9572402	BRACKET         			PIPER 	PA34  	PA34200     	7103405	SO  										NLG	CRACKED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NE	01	42309					347450169				NLG COLLAPSED ON LANDING, AFT END OF NOSE GEAR ACTUATOR ATTACHES TO BRACKET. THIS IS RIVETED THRU FIREWALL TO NOSE GEAR 	MOUNT FITTING. RIVETS WORKED FROM FORWARD/AFT PUSHING MOTION OF NOSE GEAR ACTUATOR, ELONGATING, THEN SHEARING OFF RIVETS	.  ACTUATOR WENT TO FULLY EXTENDED POSITION, BUT DID NOT CAUSE NOSE GEAR DRAG LINK TO GO TO OVER-CENTER POSITION, AS SHE	ARED OFF RIVETS PREVENTED IT FROM GETTING GOOD PUSH, AND OVER-CENTER ACTION OCCURING. NOSE GEAR COLLAPSED WHEN WEIGHT OF	 AC WENT ONTO NON-OVER CENTER DRAG LINK. ELONGATED AND SHEARED OFF SITUATION GOES UNDETECTED AS RIVETS ARE COVERED ON SI	DE OF TUNNEL BY MATERIAL GLUED TO TUNNEL WHERE CO-PILOTS LT FOOT WOULD NORMALLY BE.  NEED AD	1	L	7	2 	3O			 	A7SO    					 
2003031200042	20030312	00042	EA  	2003	3	12	11447            	2	20030220	G	8550	LW13383	BAFFLE          			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540A1A   	41532	EA  					OIL SUMP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	398TC	501  				3257057	L1001761A			PN LW13383 SUMP BAFFLE WAS FOUND CRACKED AT THE 6 ATTACHING SCREWS.  A FEW OF THE SCREW HOLES WERE COMPLETELY BROKE ALL 	THE WAY AROUND THE SCREW AND WASHER.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003021800049	20030218	00049	CE  	2003	2	18	1206S            	1	20030207	G	5730		SKIN PANEL      			CESSNA	501   	501         	2076603	CE  										LT & RT WING	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	501VP	8221 				5010261				DURING A PHASE 1-5 DISCOVERED CRACKS IN LT AND RT WING SKIN AT AFT OUTBOARD EDGE OF WHEEL WELL CUT OUT. LT WING CRACK WA	S .50 IN. LONG RT WING CRACK WAS 0.40 IN. LONG. REPAIRED IN ACCORDANCE WITH CESSNA REPAIR DEFINITION S-550-0264/02RD DAT	ED NOVEMBER 14, 2000.				1	L	7	2 	4F			 	A27CE   					 
2003021800050	20030218	00050	CE  	2003	2	18	1387S            	1	20030214	G	5740	2423100002	MOUNT           			LEAR  	35    	35A         	5170602	CE  										TIP TANK	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	886R	5368 				269				DICOVERED DURING INSPECTION FOUND A CRACK IN THE RT TIP TANK MOUNTING FLANGE. REPAIRED PER MFG. DRAWING.						2	L	7	2 	4F			 	A10CE   					 
2003031200043	20030312	00043	CE  	2003	3	12	1592S            	1	20030305	G	5710		STRUCTURE       			CESSNA	441   	441         	2076020	CE  										LT WING	MISREPAIRED     	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	454EA					4410054				DURING A PHASE 2, 3 & D INSPECTION, IT WAS VISUALLY DISCOVERED UPPER & LOWER RIB CAP STRUCTURE WAS MISSING AT LT WS 128.	80 AS WELL AS STRINGER SPLICES WERE NOT ATTACHED TO THE WING SKIN BETWEEN LT WS 120.0 & 148.30 & THE SKIN SPLICE USED WA	S THE WRONG MATERIAL THICKNESS.				1	L	7	2 	3T			RT	A28CE   					 
2003031200041	20030312	00041		2003	3	12	1A1              	4	20030224	G	3416	066011530101	ALTIMETER       			SNIAS 	350   	AS350B2     	8680813	EU  										TAILBOOM	CONTAMINATED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1811F					3430				HYDRAULIC FLUID LEAKING FROM THE TAIL ROTOR CONTROL SERVO ONTO THE RADAR ALTIMETER RECIEVER TRANSMITTER. THE R/T UNIT WA	S MOUNTED DIRECTLY UNDER THE TAIL ROTOR CONTROL SERVO WITH NO PROTECTION FROM FLAMABLE FLUID LEAKAGE.					1	G	7	1 	3U			 	H9EU    					 
2003123000013	20031230	00013	NE  	2003	12	30	2003006          	2	20031217	G	7200		ENGINE          			LEAR  	25    	25D         	5170514	CE  	GE    	CJ610 	CJ6108      	30006	NE  					LEFT	MALFUNCTIONED   	E				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			SO	11	947TC	9818 	3967 			233	240BSCY151A			DURING FLT AT APPROXIMATELY 2:00 AM, AIRCRAFT WAS ENROUTE WHEN THE PILOT NOTICED THAT THE LT ENGINE OIL PRESSURE WAS DEC	REASING.  THE PILOT ALSO NOTICED THAT THE LT EGT WAS CLIMBING.  THE PILOT ELECTED TO SHUT DOWN THE LT ENGINE AND RETURN 	AT THIS TIME.  NO EMERGENCY WAS DECLARED, AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  MAINTENANCE HAS BEEN DISPAT	CHED TO THE AIRCRAFT TO INVESTIGATE AT THIS TIME.			2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2003031100073	20030311	00073	CE  	2003	3	11	2003F00113       	1	20030201	G	5740	31691	ATTACH FITTING  			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  					WING STRUT	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	330MS					75095				DURING A ROUTINE SERVICE INTERNAL CUSTOMER REQUESTED THE 1000 HOUR INSPECTION DETAILED IN AIRWORTHY LIMITATIONS OF MM.  	ON ALL FOUR STRUT ATTACH FITTINGS.  BOTH FITTINGS WERE REJECTED ON LEFT WING DUE TO CHAFING ON EDGES WHERE FITTINGS PASS	 THROUGH LEADING EDGE SKIN.  FITTINGS WERE INSTALLED BY ANOTHER AGENCY AT 96 HOUR TT ACCORDING TO AC RECORDS.  GREATER A	TTENTION TO INTERFERENCE OF SKIN RELIEF WOULD PREVENT THIS.			1	H	7	1 	3O	3	O	 	A21CE   	1E10				 
2003032400035	20030324	00035	GL  	2003	3	24	2003F00151       	3	20030310	G	6114	D67132C1102	HUB             			BAG   	JETSTM	JETSTM4112  	       	EU  						ROTOL	R333	R333482F12  	GL  	PROPELLER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99		20695	3677 					922706		RECEIVED PROPELLER FOR OIL LEAK;  UPON DISASSEMBLY, FOUND CRACK ON TOP OF HUB AT NR 1 BLADE PORT; CRACK PROPAGATED FROM 	TOP OF HUB TO NR 1 BLADE SOCKET.					1	L	7	2 	4T			RT	A196    		6	C	P61GL	 
2003032400095	20030324	00095	EU  	2003	3	24	2003F00152       	1	20030310	G	2400	450235002	MASTER BOX      			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					RIGHT SIDE	FAILED          	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	02	313MS	2014 				0095				DURING A DEFUELING PROCEDURE WITH THE AIRCRAFT BATTERY DISCONNECTED AND THE GPU CONNECTED.  THE BATTERY SWITCH TURNED ON	 AND AFTER APPROXIMATELY 30 MINUTES INTO THE DEFUELING PROCEDURE THE RIGHT HAND ELECTRICAL MASTER BOX STARTED SMOKING.  	WE QUICKLY DISCONNECTED ALL ELECTRICAL POWER TO THE AIRCRAFT.  THIS OCCURANCE ALSO BLEW AN 8 AMP IN THE BATTERY MASTER B	OX AT (F2) LOCATION.			1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2003060500019	20030605	00019	CE  	2003	6	5	2003F00252       	1	20030331	G	3233	99120538	ACTUATOR        			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					RT MLG	FAILED          	D				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	13	628BS	10586	135  			5000045				RT MLG ACTUATOR COLLAPSED AND STILL INDICATED DOWN AND LOCKED.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003091900024	20030919	00024	CE  	2003	9	19	2003F00513       	1	20030627	G	2730	2655221313	BELLCRANK       			RKWELL	NA265 	NA26565     	7630107	CE  										ELEVATOR	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	800M	3840 				46541				AFTER FINDING THE LT AFT ELEVATOR BELLCRANK PN 265-5221313 FS457 CRACKED AT LOWER BEARING BOSS AREA ON A DIFFERENT NA 26	5-65 AIRCRAFT WE PERFORMED INSPECTIONS ON 5 EA.  ADDITIONAL NA 265-65 AIRCRAFT THAT WERE IN HOUSE.  THIS INSPECTION UNCO	VERED A CRACKED BELLCRANK AT THE LOCATION ON THIS AIRCRAFT.  RECOMMEND OPERATORS OF NA 265-65 MODEL AIRCRAFT PERFORM A C	LOSE VISUAL OR EDDY CURRENT INSPECTION OF THE LOWER BEARING BOSS AREA OF LT BELLCRANK PN 265-5221313 AS SOON AS POSSIBLE	.  POSSIBLE CAUSE HAS YET TO BE DETERMINED BUT THE HIGH CABLE TENSION AND THE BIAS LOADING OF THE ELEVATOR CABLES MAY BE	 A CONTRIBUTING FACTOR OR THE POSSIBLE STAKING OF THE BEARING COULD WEAKEN THE AREA AFFECTED.  MFG HAS BEEN NOTIFIED.	2	L	7	2 	4J			 	A2WE    					 
2003091900105	20030919	00105	CE  	2003	9	19	2003F00515       	1	20030804	G	3244	184F681	TIRE            			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					MLG	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	51GS	293  				5250317				SUSPECTED SUDDEN AIR LOSS BETWEEN PRE-FLIGHT INSPECTION AT HOME FBO AND LANDING AT VISITING FBO.  APPROX. 1-25 HOURS.						1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2003100600046	20031006	00046	SO  	2003	10	6	2003F00557       	1	20030827	G	2140		COMBUSTION LINER	JANITROL    		PIPER 	PA31T 	PA31T1      	7103126	SO  	PWA   	PT6   	PT6*        	52043	EA  					HEATER	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	52HL					31T8004023				DURING PRESSURE DECAY TESTS OF ELECTRO SYSTEMS JAN-AERO HEATERS, PN FR10E21-EL, WE HAVE DISCOVERED PRESSURE LEAKS IN THE	 CERAMIC COATED COMBUSTION TUBES.  THIS HAS OCCURED ON 4 SEPARATE OCCATIONS.  IT SHOULD BE NOTED THAT THE PERIODIC PRESS	URE DECAY TEST REQUIRED BY AD 96-20-07 (DOES NOT APPLY TO) HEATER SERIES B3500 WITH (CERAMIC COATED) COMBUSTION TUBES.  	ALTHOUGH THE PERIODIC PRESSURE DECAY TEST IS (NOT) REQUIRED BY AD 96-20-07 FOR CERTAIN HEATERS WITH (CERAMIC COATED) COM	BUSTION TUBES.   MM CONTINUES TO RECOMMEND PERIODIC PRESSURE DECAY TEST OF THE HEATER COMBUSTION TUBES REGARDLESS OF THE	 HEATER CONFIGURATION.	1	L	7	2 	3T	3	T	 	A8EA    	E2NE				 
2003020400215	20030204	00215	CE  	2003	2	4	2003FA0000019    	1	20030106	G	5710	085150047	BULKHEAD        			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	402CA	8800 				402B0842				INSPECTION IAW AD, A CRACK WAS FOUND IN THE RT ENGINE CANTED BULKHEAD CAP.  CRACK WAS LOCATED ON THE INBOARD SIDE OF CAP	 JUST INSIDE OF INBOARD WING LIP.  CRACK WAS APPROXIAMATELY 1.5 INCHES AND RAN CHORD WISE WITH WING.  IT WAS LOCATED IN 	THE AFT OF THE CAP WIDTH.  UPON REMOVAL OF CANTED BULKHEAD CAP, FOUND FORWARD CANTED BULKHEAD  TO BE CRACKED PERPENDICUL	AR TO THE CAP CRACK ON THE INBOARD SIDE IN THE BEND OF TOP FLANGE. THIS CRACK WAS ABOUT 1 INCH IN LENGTH.  FOUND THAT BO	TH AFT AND FORWARD BULKHEAD INBOARD SIDES HAD SEPERATED FROM INBOARD NACELLE WING RIB. FOUND THIS SAME COMBINATION ON LE	FT SIDE OF THIS SAME AIRCRAFT AND ON RIGHT SIDE OF ANOTHER.	1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003020400218	20030204	00218	CE  	2003	2	4	2003FA0000020    	1	20030106	G	5710	085150047	BULKHEAD        			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ZONE 600	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	402CA	8800 				402B0842				WHILE CONDUCTING INSPECTION IAW AD 00-01-16(D)A CRACK WAS FOUND IN THE RIGHT ENGINE CANTED BULKHEAD CAP.  CRACK WAS LOCA	TED ON THE INBOARD SIDE OF CAP JUST INSIDE OF THE INBOARD WING LIP.  CRACK WAS APPROXIAMATELY 1.5 INCHES AND RAN CHORD W	ISE WITH THE WING.  IT WAS LOCATED IN THE AFT OF THE CAP WIDTH.  UPON REMOVAL OF CANTED BULKHEAD CAP I FOUND THE FORWARD	 CANTED BULKHEAD TO BE CRACKED PERPENDICULAR TO THE CAP CRACK ON THE INBOARD SIDE IN THE BEND OF THE TOP FLANGE. THIS CR	ACK WAS ABOUT 1 INCH IN LENGTH.  I FOUND ALSO THAT BOTH THE AFT AND FORWARD BULKHEADS INBOARD SIDES HAD SEPERATED FROM T	HE INBOARD NACELLE WING RIB.	1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003020400223	20030204	00223	CE  	2003	2	4	2003FA0000021    	1	20030106	G	5710	085150047	BULKHEAD        			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ZONE 600	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	402CA	8800 				402B0842				INSPECTION IAW AD.  CRACK WAS FOUND IN RIGHT ENGINE CANTED BULKHEAD CAP.  CRACK WAS LOCATED ON INBOARD SIDE OF CAP JUST 	INSIDE OF INBOARD WING LIP.  CRACK WAS APPROXIAMATELY 1.5 INCHES AND RAN CHORD WISE WITH THE WING, IT WAS LOCATED IN THE	 AFT OF THE CAP WIDTH.  UPON REMOVAL OF CANTED BULKHEAD CAP FOUND FORWARD CANTED BULKHEAD TO BE CRACKED PERPENDICULAR TO	 CAP CRACK ON INBOARD SIDE IN BEND OF TOP FLANGE. CRACK WAS ABOUT 1 INCH IN LENGTH.  AFT AND FORWARD BULKHEADS INBOARD S	IDES HAD SEPERATED FROM INBOARD NACELLE WING RIB. FOUND THIS SAME COMBINATION ON THE LT SIDE OF THIS SAME AIRCRAFT.		1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003020400229	20030204	00229	CE  	2003	2	4	2003FA0000023    	1	20030106	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  										COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	773TP	905  	905  			BB1722				FOUND 3 INCH CRACK ACROSS LOWER,OUTSIDE CORNER OF OUTSIDE GLASS PANEL WITH SOME DELAMINATION EXTENDING 3 INCHES OUT OF S	AME CORNER. TECHNICIAN BELIEVES CONTINUAL RETORQING OF WINDSHIELD SCREWS CALLED OUT BY RAYTHEON CAUSED THE CRACK AND INC	REASES THE CHANCES OF DELAMINATION. NO OTHER AIRCRAFT THAT HE HAS SERVICED IN HIS 35 YEAR CAREER HAS HAD THIS REQUIREMEN	T AND HAS REPLACED SEVERAL KING AIR WINDSHIELDS.			1	L	7	2 	4T			 	A24CE   					 
2003020400235	20030204	00235	CE  	2003	2	4	2003FA0000025    	1	20030108	G	2710	6524113205	AILERON         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					WING	JAMMED          	B				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	27	462B					5600016				AILERON TRIM MOVED OVER 10 DEGREES IN FLIGHT WILL JAM, PILOT WILL NOT BE ABLE TO READJUST TO ZERO.						2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2003011600159	20030116	00159	WP  	2003	1	16	2003FA0000029    	1	20030101	G	3397	58643	WIRE HARNESS    			LKHEED	1011  	1011*       	       	WP  										CABIN	FAULTY          	G			AMTA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	11	1641T					293A1238				EGRESS LIGHTING AT GALLEY 72 INCH SEGMENT INOP.  REMOVED AND REPLACED TRANSITION CABLE JUMPER 72 INCH BETWEEN SEGMENT AN	D POWER CABLE.					2	L	7	3 	4F			 	A23WE   					 
2003020400241	20030204	00241	EU  	2003	2	4	2003FA0000030    	1	20030110	G	5753		VANE            			BRAERO	DH125 	HS125700A   	4230170	EU  										RT TE FLAP	CRACKED         	E			ILPA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	12OJC					257065				DURING ROUTINE INSPECTION, IT WAS FOUND THAT THE RT FLAP VANE AT THE NR 2 ATTACH POINT HAD A HAIRLINE CRACK. REPAIR WAS 	FABRICATED AND INSTALLED IAW SRM.					2	L	7	2 	4F			 	A3EU    					 
2003020400245	20030204	00245	EU  	2003	2	4	2003FA0000031    	1	20030110	G	5753		VANE            			BRAERO	DH125 	HS125700A   	4230170	EU  										RT TE FLAP	CRACKED         	E			ILPA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	12OJC					257065				DURING ROUTINE INSPECTION, IT WAS FOUND THAT THE RT FLAP VANE AT THE NR 2 ATTACH POINT HAD A HAIRLINE CRACK.  REPAIR WAS	 FABRICATED AND INSTALLED IAW SRM.					2	L	7	2 	4F			 	A3EU    					 
2003020400251	20030204	00251	CE  	2003	2	4	2003FA0000035    	1	20030115	G	2700	522277577	SKIN            			CESSNA	500   	550         	2076604	CE  										LT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01						0670				WHILE DOING A DAILY INSPECTION A 1 3/4 INCH CRACK WAS FOUND IN THE LT WING JUST ABOVE THE INBOARD FLAP BELLCRANK. WE OPE	RATE A FLEET OF 26 550 SERIES AIRCRAFT WITH A LARGE PORTION HAVING A REPAIR TO THE LT OR RT WING AT ONE POINT OR ANOTHER	. I HAVE FOUND SEVERAL WHILE WORKING AT A FBO. MANY OF MY FRIENDS ALSO CONFERM THAT THIS IS A COMMON THING TO THE FLEET.	 TALKING TO THE FACTORY THEY WANT ONE OF THERE ENGINEERS OR A DER TO HELP IN THE FIX. IT SEAMS TO ME THAT IF THIS IS A C	OMMON THING THEM WHY CAN'T THE MFG. COME UP WITH A SB AND A REPAIR KIT AS WE HAVE SEEN IN THE PAST ON OTHER LESS COSTLY 	A/C ?	1	L	7	2 	4F			 	A22CE   					 
2003020400254	20030204	00254	CE  	2003	2	4	2003FA0000036    	1	20030108	G	3230	08421022	BELLCRANK       			CESSNA	310   	T310Q       	2074244	CE  										MLG	BROKEN          	G				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SO	15	8108G	2075 				310Q1047				THE IDLER BELLCRANK FOR THE NOSE GEAR RETRACTION LINKAGE BROKE WHEN THE LANDING GEAR WAS SELECTED TO THE UP POSITION.  P	ILOT WAS UNABLE TO EXTEND THE NOSE GEAR.  UPON LANDING THE NOSE GEAR RETRACTED INTO THE WHEEL WELL.  INSPECTION REVEALED	 THAT THE IDLER BELLCRANK BROKE CAUSING THE NOSE GEAR TO BE DISCONNECTED FROM THE GEARBOX.  SUSPECT IMPROPER RIGGING OF 	THE LANDING GEAR CAUSED EXCESSIVE STRESS ON BELLCRANK.  MECHANICS NEED TO REMEMBER THAT DUE TO THE DESIGN OF THE LANDING	 GEAR SYSTEM ON TWIN ENGINE CESSNA'S, ANY ADJUSTMENTS MADE TO ANY OF THE MANY COMPONENTS OF THE LANDING GEAR EFFECTS THE	 ENTIRE SYSTEM, REQUIRING A COMPLETE RECHECK OF THE LANDING GEAR RIGGING.	1	L	7	2 	3O			 	3A10    					 
2003020400255	20030204	00255	EA  	2003	2	4	2003FA0000039    	1	20030116	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					COCKPIT	CRACKED         	G				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			GL	11	607RP					5184				THE OUTER PLY OF THE PILOT FORWARD WINDSHIELD CRACKED. THE FLIGHT WAS DISCONTINUED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003020400256	20030204	00256	NM  	2003	2	4	2003FA0000040    	1	20030121	G	5730	44305	DOUBLER         			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R3350*      	67040	EA  					LT & RT WING	CORRODED        	B			BZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	139HP	9739 				145906				FUEL INTERCONNECT ACCESS PANEL CUT OUT DOUBLER IS CRACKED AT LT AND RT PANEL NUMBERS 53L AND 53R.  LT AND RT UPPER CENTE	R WING BOX BEAM COVERS HAVE MODERATE TO MILD CORROSION ON THE UPPER HAT SECTIONS AND THE SKIN BETWEEN WING STATIONS 84.5	 TO 192 LT AND RT.  LT AND RT FORWARD UPPER SPAR CAP FROM WING STATION 84.5 TO 192 HAS MILD TO MODERATE CORROSION.  LT A	ND RT REAR UPPER SPAR CAP FROM WING STATION 84.5 TO 192 HAS MILD TO MODERATE CORROSION.			2	M	7	2 	4R	4	R	RT	A1RM    	E272				 
2003020400257	20030204	00257	NM  	2003	2	4	2003FA0000041    	1	20030121	G	5711		SPAR CAP        			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R3350*      	67040	EA  					LT & RT WING	CORRODED        	B			BZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	139HP	9739 				145906				FUEL INTERCONNECT ACCESS PANEL CUT OUT DOUBLER IS CRACKED AT LT AND RT PANEL NUMBERS 53L AND 53R.  LT AND RT UPPER CENTE	R WING BOX BEAM COVERS HAVE MODERATE TO MILD CORROSION ON THE UPPER HAT SECTIONS AND THE SKIN BETWEEN WING STATIONS 84.5	 TO 192 LT AND RT.  LT AND RT FORWARD UPPER SPAR CAP FROM WING STATION 84.5 TO 192 HAS MILD TO MODERATE CORROSION.  LT A	ND RT REAR UPPER SPAR CAP FROM WING STATION 84.5 TO 192 HAS MILD TO MODERATE CORROSION.			2	M	7	2 	4R	4	R	RT	A1RM    	E272				 
2003020300097	20030203	00097	SO  	2003	2	3	2003FA0000043    	1	20030109	G	3260	761639	SQUAT SWITCH    			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	850FS	194  				2844080				JACKED AIRCRAFT TO VERIFY SQUAT SWITCH ADJUSTMENT IAW SRM.  SQUAT SWITCH IS SUPPOSE TO ACTUATE WITHIN THE FIRST .250 INC	H OF STRUT COMPRESSION FROM FULL EXTENSION. FOUND SQUAT SWITCH TO BE ADJUSTED TO ACTUATE AT .625 INCHES.  THIS IS .375 I	NCHES OUT OF LIMITS.  THE TORQUE SEAL ON THE SQUAT SWITCH MOUNTING/ ADJUSTING HARDWARE SHOWS NO EVIDENCE OF BEING DISTUR	BED.			1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003020400258	20030204	00258	CE  	2003	2	4	2003FA0000047    	1	20030121	G	5312	07126153	BULKHEAD        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	888CH					18266884				SMALL CRACK IN AFT BULKHEAD AT STATION 209. ORIGINATING FROM UNDER THE ATTACH POINT OF RT HORIZONTAL STABILIZER, AT THE 	UPPER INBOARD CORNER.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003020400259	20030204	00259	CE  	2003	2	4	2003FA0000048    	1	20030115	G	2710	3652400019	TURNBUCKLE      	BEECH       		BEECH 	36    	36BEECH     	1151602	CE  										CONTROL CABLE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	6222V	4315 				E3				AILERON CABLE TURNBUCKLE FORWARD OF AFT SPAR BROKEN. SAFETY WIRE HOLDING CABLE TOGETHER, FOUND DURING ANNUAL INSPECTION.	 CABLE HAD BEEN CONTACTING AFT HEAT DUCT. APPEARS TO HAVE INTERNAL CORROSION FROM CONTACT WITH WIRE IN HEAT DUCT. FITTIN	G SHOW NO SIGN OF WEAR OR EXTERNAL CORROSION.				1	L	7	1 	3O			 	3A15    					 
2003020400263	20030204	00263	SW  	2003	2	4	2003FA0000049    	1	20030108	G	2750	191003	VALVE           			SWRNGN	SA226 	SA226T      	8780122	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					LT TE FLAPS	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	601JT					T319				AIRCRAFT ROLLED LT AFTER FLAPS WERE DEPLOYED FOR 30 SECONDS, INTERMITTENLY.  FOUND LT LOCK OUT VALVE DEFECTIVE. VALVE WA	S GROUND PRESSURE TESTED AND IT FAILED THE TEST. REPLACED LOCK OUT VALVE.  THIS PART NEEDS TO BE PUT ON THE REQUIRED OVE	RHAUL SCHEDULE.				2	L	7	2 	4T	3	T	RT	A5SW    	E2WE				 
2003020400264	20030204	00264		2003	2	4	2003FA0000051    	4	20030110	G	3416		ENCODER         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					COCKPIT	OUT OF ADJUST   	B			JG0R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	19	4TG					TH335				ENCODER MISSING HIGH ALTITUDE ADJUSTMENT OUT OF THE FACTORY.  THE MM REQUIRES YOU TO CALIBRATE THE ENCODER USING HIGH AL	TITUDE AND LOW ALTITUDE ADJUSTMENT POTS.					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2003020400265	20030204	00265	GL  	2003	2	4	2003FA0000052    	3	20030112	G	6110		NUT             													MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	B			UCXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15			850  					724763		DURING ROUTINE OVERHAUL OF THIS PROPELLER FOUND NR 2 THREAD IN THE NR 2 HUB SOCKET CRACKED. VISUAL/MAGNAFYING GLASS AND 	CONFIRMED WITH EDDIE CURRENT AND DYE-CHECK NDT.  FOUND THE ASSOCIATED BLADE RETENTION NUT CRACKED ON THE NR 2 THREAD AS 	WELL VIA THE SAME MEANS OF INSPECTION. THESE WERE JUST THE BEGINING OF A MINUTE CRACK AND HAD NOT PROGRESSED TO THE POIN	T OF THE PROPELLER LEAKING RED DYE OIL YET.  COULD HAVE CAUSED A COMPLETE BLADE FAILURE OF THE BLADE LEAVING THE HUB. PH	OTO ON FILE.												5	C	P3EA	 
2003020400266	20030204	00266	CE  	2003	2	4	2003FA0000054    	1	20030113	G	5312	07126153	BULKHEAD        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	888CH					18266884				SMALL CRACK IN AFT FUSELAGE BULKHEAD AT STATION 209. ORIGINATING FROM UNDER THE RIGHT HORIZONTAL STABILIZER UPPER ATTACH	 POINT.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003020500002	20030205	00002	CE  	2003	2	5	2003FA0000055    	1	20030113	G	5312	07126153	BULKHEAD        			CESSNA	182   	182Q        	2072732	CE  										FUSELAGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	888CH					18266884				SMALL CRACK IN AFT FUSELAGE BULKHEAD AT STATION 209. ORIGINATING FROM UNDER THE RT HORIZONTAL STABILIZER UPPER ATTACH PO	INT.					1	H	7	1 	3O			NT	3A13    					 
2003020500003	20030205	00003	CE  	2003	2	5	2003FA0000056    	1	20030123	G	3230	12410041	SADDLE          			CESSNA	210   	210         	2073402	CE  										MLG GEARBOX	BROKEN          	B			EG6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	9422T					57222				COMPLIANCE WITH AD 76-14-07 R2 FOUND LT MAIN GEAR SADDLE BROKEN.						1	H	7	1 	3O			RT	3A21    					 
2003020300098	20030203	00098	SO  	2003	2	3	2003FA0000057    	2	20030109	G	7414		DISTRIBUTOR BLK 								CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT  MAGNETOS AND CAUSING THEM TO MEL	T DOWN.  BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLD	ER.  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FR	OM ROCKING BACK AND FORTH.							3	O			E5CE				 
2003020300099	20030203	00099	SO  	2003	2	3	2003FA0000058    	2	20030109	G	7414		DISTRIBUTOR BLK 	SLICK       							CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	INOPERATIVE     	C			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		513  			02051452					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT	 DOWN.  BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLDE	R.  C/A:  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GE	AR FROM ROCKING BACK AND FORTH.							3	O			E5CE				 
2003020300100	20030203	00100	SO  	2003	2	3	2003FA0000059    	2	20030110	G	7414		DISTRIBUTOR BLK 	SLICK       							CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		14   			01100458					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT	 DOWN.  BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLDE	R.  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FRO	M ROCKING BACK AND FORTH.							3	O			E5CE				 
2003020300101	20030203	00101	SO  	2003	2	3	2003FA0000060    	2	20030110	G	7414		DISTRIBUTOR BLK 								CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT	 DOWN.  BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLDE	R.  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FRO	M ROCKING BACK AND FORTH.							3	O			E5CE				 
2003020300102	20030203	00102	SO  	2003	2	3	2003FA0000061    	2	20030110	G	7414		DISTRIBUTOR BLK 								CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		468  								MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT	 DOWN.  BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLDE	R.  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FRO	M ROCKING BACK AND FORTH.							3	O			E5CE				 
2003020300104	20030203	00104	SO  	2003	2	3	2003FA0000064    	2	20030108	G	7414		DISTRIBUTOR BLK 	SLICK       	            						CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					01042018					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT	 DOWN.  BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLDE	R.  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FRO	M ROCKING BACK AND FORTH.							3	O			E5CE				 
2003020300105	20030203	00105	SO  	2003	2	3	2003FA0000065    	2	20030108	G	7414		DISTRIBUTOR BLK 	SLICK       							CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					01042019					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT	 DOWN. BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLDER	.  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FROM	 ROCKING BACK AND FORTH.							3	O			E5CE				 
2003020300107	20030203	00107	CE  	2003	2	3	2003FA0000066    	1	20030103	G	5500	35405130	STRUCTURE       			BEECH 	35    	35BEECH     	1151502	CE  	CONT  	E185  	E18511      	17014	SO  					STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	80445					D45	21665D211			CRACK FOUND IN LOWER RT ATTACH BOLT HOLE FROM HOLE CENTER AT THE 2 O`CLOCK POSITION.  FOUND DURING INSPECTION FOR AD.  C	RACK LENGTH .250 INCH.					1	L	7	1 	3O	3	O	 	A777    	E246				 
2003020300109	20030203	00109	EU  	2003	2	3	2003FA0000068    	1	20030115	G	6420	109013106101	BUSHING         			AGUSTA	A109  	A109E       	0260119	EU  										T/R HEAD	LOOSE           	B			LN3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	12VW					11074				GRIP BUSHINGS WERE ROTATING INSIDE GRIPS CAUSING SCORING OF HUB.						1	G	7	2 	3U			RT	H7EU    					 
2003020300110	20030203	00110	EU  	2003	2	3	2003FA0000069    	1	20030115	G	6410	109813129101	GRIP            			AGUSTA	A109  	A109E       	0260119	EU  										BLADE GRIP	LOOSE           	B			LN3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	12VW	366  				11074				GRIP BUSHINGS WERE ROTATING INSIDE OF GRIP CAUSING GRIP INSIDE DIAMETER TO WEAR BEYOND LIMITS.						1	G	7	2 	3U			RT	H7EU    					 
2003020300112	20030203	00112	EA  	2003	2	3	2003FA0000070    	2	20030116	G	7414		BRUSHES         	SLICK       							LYC   	O540  	AEIO540D4D5 	 	EA  					MAGNETO	MISSING         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					01050130					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH WAS MISSING. 	 MFG LOOK AT REDUCING THE TOLERANCES BETWEEN THE DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PRE	VENT GEAR FROM ROCKING BACK AND FORTH.									3	O			1E4				 
2003020300113	20030203	00113		2003	2	3	2003FA0000071    	4	20030104	G	2561	FV35E3505101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED, MFG RECOMMENDED CELL PRESSURE TEST.  DOM: JULY 1990																			 
2003020300116	20030203	00116	EA  	2003	2	3	2003FA0000073    	2	20030116	G	7414		DISTRIBUTOR BLK 	SLICK       							LYC   	O540  	AEIO540D4A5 	41532	EA  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					02072354					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT	 DOWN.  BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLDE	R.  C/A:  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GE	AR FROM ROCKING BACK AND FORTH.							3	O			1E4				 
2003020300118	20030203	00118	EA  	2003	2	3	2003FA0000074    	2	20030116	G	7414		DISTRIBUTOR BLK 	SLICK       							LYC   	O540  	AEIO540D4D5 	 	EA  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					00072421					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE	 WEAR.  BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT	 DOWN.  BECAUSE THE GEAR IS WORKING SIDE TO SIDE IN BLOCK HOUSING ALLOWING THE BRUSH TO COME IN CONTACT WITH BRUSH HOLDE	R.  C/A:  REDUCING THE TOLERANCES BETWEEN DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GE	AR FROM ROCKING BACK AND FORTH.							3	O			1E4				 
2003020300119	20030203	00119	EA  	2003	2	3	2003FA0000075    	2	20030117	G	7414		DISTRIBUTOR BLK 	SLICK       							LYC   	O540  	AEIO540D4D5 	 	EA  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					00072418					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH WAS RUBBING A	ND CAUSING CARBON DUST.  RECOMMENDATION IS TO HAVE MFG LOOK AT PROCESS OF MANUFACTURING AND LOOK AT REDUCING THE TOLERAN	CES BETWEEN THE DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FROM ROCKING BACK AND F	ORTH.  FURTHER INVESTIGATION BY MFG REQUIRED TO CORRECT PROBLEMS.								3	O			1E4				 
2003020300129	20030203	00129	SW  	2003	2	3	2003FA0000082    	1	20030102	G	7930		WARNING LIGHT   			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	ACTIVATED       	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	09	4227E	6729 	6727 			45702				ENGINE MAGNETIC PLUG WARNING LIGHT CAME ON DURING FLIGHT.  PILOT LANDED AIRCRAFT AND MAINTENANCE WAS NOTIFIED.  MECHANIC	 INSPECTED MAGNETIC PLUGS AND FOUND PASTE ON UPPER ENGINE GEARBOX MAGNETIC CHIP PLUG.  MECHANIC CLEANED AND REINSTALLED 	PLUG PERFORMED MAINTENANCE IAW MM.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003020300131	20030203	00131	EA  	2003	2	3	2003FA0000084    	2	20030102	G	7261	30216018	HOUSING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					OIL PUMP	CRACKED         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	03	555AL	2702 				LJ1268				OIL PRESSURE DROPPED IN FLIGHT TO BOTTOM OF GREEN ARC.  TROUBLESHOOTING FOUND OIL PUMP HOUSING TO BE CRACKED.						1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2003020300134	20030203	00134	SO  	2003	2	3	2003FA0000085    	2	20030110	G	8530	628752	CONNECTING ROD  			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					ENGINE	BENT            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	5JA	3386 				TC942				NR 5 CYLINDER WAS REMOVED FROM RIGHT ENGINE AFTER ROUGH OPERATION AT GROUND RUN UP AND COMPRESSION LOSS.  INSPECTION REV	EALED BENT I BEAM SECTION OF CONNECTING ROD AND DAMAGE TO SKIRT OF PISTON.  FAILURE ANALYSIS DETERMINED CAUSE TO BE HYDR	OSTATIC LOCK DUE TO OVERPRIMING AT STARTUP.  NR 5 CYL OF RT ENGINE, NR 6 CYL OF LT ENGINE ARE MOST LIKELY TO HAVE THIS P	ROBLEM.  INDUCTION SYSTEM BALANCE TUBE NEEDS PROPERLY POSITIONED DRAIN FOR LT AND RT TO PREVENT THIS PROBLEM.			1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2003020300135	20030203	00135	SO  	2003	2	3	2003FA0000086    	2	20030115	G	7414	103915686	BEARING         			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					DISTRIBUTOR BLK	LOOSE           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	135Z	189  				TJ247				DURING CRUISE POWER SETTING IN FLIGHT.  RT ENGINE RPM FLUX 100-200 RPM AND MANIFOLD PRESSURE FLUX 1 INCH TO 2 INCH.  DUR	ING GROUND RUN TO TROUBLESHOOT SYSTEM ENGINE RPM WOULD SUDDENLY DROP 200-400 RPM.  AT CRUISE SETTING.  PERFORMED MAGNETO	 CHECK.  LT MAG FAILED.  BEARING IN DISTRIBUTOR BLOCK SPINNING, POSSIBLE DATE CODE ON BLOCK 01/09.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2003020300137	20030203	00137	SO  	2003	2	3	2003FA0000088    	2	20030114	G	8530		INTAKE VALVE    			CESSNA	188   	T188C       	2073012	CE  	CONT  	O520  	TSIO520T    	17040	SO  					ENGINE	LEAKING         	D			HNJG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	9614K					T18803962T	239512R			AT 470 HOURS ON REBUILT ENGINE, ALL CYLINDERS WERE REMOVE FOR INTAKE VALVE LEAKAGE. ALL VALVE SEATS WERE EASILY RECONDIT	IONED, BUT VALVES SHOWED MAJOR IDENTATION AT THE SEAT CONTACT AREA, WITH APPARENT MOVEMENT OF VALVE MATERIAL OUTWARD.					1	L	7	1 	3O	3	O	 	A9CE    	E8CE				 
2003020300138	20030203	00138	CE  	2003	2	3	2003FA0000089    	1	20030107	G	2730	NAS302665170	CONTROL CABLE   			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6*        	52043	EA  					ELEVATOR	FAILED          	B			TBWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	90ZH					LJ594				ELEVATOR TRIM CABLE FAILED IN FLIGHT WITH NO INCIDENT AT STATION 216.  CABLE BROKE AT THE ELEVATOR TRIM SERVO (SERVO: PN	 1C4696456).  TRIM SERVO HAD BEEN REPLACED ON YEAR PRIOR WITH NO NOTED DEFECTS TO THE TRIM CABLE AT THAT TIME.  STC SA14	54SW EDO AIRE MITCHELL FLIGHT DIRECTOR AUTO-PILOT SYSTEM WAS INSTALLED APRIL 3, 1972.  TIME ON FAILED PART IS 10,034.1 H	OURS.  SUSPECT CABLE HAD INTERNAL FAILURE OF STRANDS UNABLE TO SEE WHEN INSTALLED ON SERVO.  (SW15200304640)			1	L	7	2 	3T	3	T	 	3A20    	E2NE				 
2003020300139	20030203	00139		2003	2	3	2003FA0000090    	4	20030109	G	2561	CA12P0201	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOAT DEVICE FAILED MFG RECOMMENDED CELL PRESSURE TEST.  DOM JUNE 1991.																			 
2003020300140	20030203	00140		2003	2	3	2003FA0000091    	4	20030103	G	2561	CA12P201	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										FLOAT DEVICE FAILED MFG RECOMMENDED CELL PRESSURE IAW 25-60-13.  DOM: NOV 1981.																			 
2003020400001	20030204	00001	CE  	2003	2	4	2003FA0000095    	1	20030103	G	5320	04320049	BRACKET         			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235*       	41505	EA  					FUSELAGE	CRACKED         	B			LC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	8144L	4123 				A1520833				DURING AN INSPECTION FOR AD (CRACKED NUT PLATES) THE BRACKET WHICH HOLDS THE NUT PLATES WAS FOUND CRACKED ON THE UPPER R	IGHT HAND SIDE FROM THE CORNER RELIEF HOLE, INBOARD FOR APPROXIMATELY ONE INCH ALONG THE TOP BEND.  THIS CRACK IS DIRECT	LY ADJACENT TO AND JUST AFT OF THE UPPER RIGHT NUT PLATE WHICH IS ONE OF THE EIGHT NUT PLATES ADDRESSED IN THE MENTIONED	 AD, HOWEVER THE AD DOES NOT ADDRESS AN INSPECTION OF THE SUPPORTING STRUCTURE IN ANY MANNER.			1	H	7	1 	3O	3	O	 	3A19    	E223				 
2003020400152	20030204	00152	CE  	2003	2	4	2003FA0000096    	1	20030128	G	3230	50411081	BEARING RACE    			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT MLG	CRACKED         	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	05	5910M	3741 	643  			3400067				DURING INSPECTION IT WAS DISCOVERED THAT LT MLG WOULD NOT RETRACT. GEAR WAS DISASSEMBLED. BEARING INNER RACE WAS FOUND T	O BE CRACKED.					1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2003020400153	20030204	00153	WP  	2003	2	4	2003FA0000097    	2	20030124	G	7314		DRIVE SHAFT     	GARRTT      							GARRTT	TFE731	TFE73122B   	01518	WP  					FUEL PUMP	STRIPPED        	C				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			SW	11					MX498409		P89705			LT ENGINE FLAME OUT CLIMBING THROUGH 7,500 FT MSL AT 250 KTS. NO ABNORMAL INDICATIONS PRIOR. UNABLE TO RE-LIGHT. UPON RE	MOVAL OF FUEL PUMP FROM ENGINE, FOUND SHAFT SPLINES SEPARATED FROM MAIN PUMP SHAFT. REPLACED PUMP WITH OVERHAULED UNIT.										4	F			E6WE				 
2003020400154	20030204	00154	EA  	2003	2	4	2003FA0000098    	2	20030128	G	8520		CRANKSHAFT      								LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										THIS CRANKSHAFT ALONG WITH FOUR OTHERS OF SAME KIND AND AGE, HAVE EXTREMELY HEAVY GRAINULAR INDICATIONS ON JOURNALS, RAD	II, FLANGE RADIUS AND SEAL SURFACE WHEN VIEWED UNDER MAGNETIC PARTICLE INSPECTION, WET METHOD. THESE INDICATIONS ARE EXT	REMELY RARE WITH CRANKSHAFTS, COMMON ONLY INLIGHT OF SB 549, ALTHOUGH THESE PARTS ARE NOT LISTD IN THE BULLETIN.  ONE SU	CH CRANKSHAFT HAS BEEN RECERTIFIED BY OEM.								3	O			1E10				 
2003020400155	20030204	00155	EA  	2003	2	4	2003FA0000099    	2	20030128	G	8520		CRANKSHAFT      								LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										THIS CRANKSHAFT ALONG WITH FOUR OTHERS OF SAME KIND AND AGE, HAVE EXTREMELY HEAVY GRAINULAR INDICATIONS ON JOURNALS, RAD	II, FLANGE RADIUS AND SEAL SURFACE WHEN VIEWED UNDER MAGNETIC PARTICLE INSPECTION, WET METHOD. THESE INDICATIONS ARE EXT	REMELY RARE WITH CRANKSHAFTS, COMMON ONLY INLIGHT OF SB 549, ALTHOUGH THESE PARTS ARE NOT LISTD IN THE BULLETIN.  ONE SU	CH CRANKSHAFT HAS BEEN RECERTIFIED BY OEM.								3	O			1E10				 
2003020400156	20030204	00156	SW  	2003	2	4	2003FA0000100    	1	20030129	G	5310	206033210	BEAM            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUSELAGE	ELONGATED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	112TV	11436				51123				NUMEROUS RIVETS WERE FOUND WORKING LOOSE IN THE BOX BEAM DURING A 100/300/ANNUAL INSPECTION. REQUIRED REPLACEMENT OF 20 	EACH CHERRY MAXI-BOLTS, 16 EACH CHERRY MAX RIVETS. DIGITAL PICTURES WERE TAKEN TO FURTHER DESCRIBE.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003021800052	20030218	00052	SO  	2003	2	18	2003FA0000103    	2	20030123	G	7414		DISTRIBUTOR BLK 								CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	WORN            	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		502  			02040027					MAGNETO REMOVED FROM ENGINE FOR 550 HOUR INSPECTION IAW THE MAINTENANCE MANUAL.  DURING INSPECTION FOUND THAT THE CARBON	 BRUSH WAS RUBBING AND CAUSING CARBON DUST.  RECOMMENDATION IS TO HAVE MFG LOOK AT REDUCING THE TOLERANCES BETWEEN THE D	ISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FROM ROCKING BACK AND FORTH.									3	O			E5CE				 
2003021800053	20030218	00053	SO  	2003	2	18	2003FA0000104    	2	20030123	G	7414		DISTRIBUTOR BLK 	SLICK       							CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	DAMAGED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		502  			02040023					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MAINTENANCE MANUAL.  DURING INSPECTION FOUND THAT THE CARBON	 BRUSH WAS RUBBING AND CAUSING CARBON DUST.  HAVE MFG LOOK AT REDUCING THE TOLERANCES BETWEEN THE DISTRIBUTOR BLOCK AND 	THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT GEAR FROM ROCKING BACK AND FORTH.									3	O			E5CE				 
2003021800054	20030218	00054	SO  	2003	2	18	2003FA0000105    	2	20030122	G	7414		DISTRIBUTOR BLK 	SLICK       							CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	DAMAGED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		501  			01071879					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH WAS RUBBI	NG AND CAUSING CARBON DUST.  HAVE MFG LOOK AT REDUCING THE TOLERANCES BETWEEN THE DISTRIBUTOR BLOCK AND THE GEAR POST WH	ERE THEY FIT TOGETHER  TO HELP PREVENT GEAR FROM ROCKING BACK AND FORTH.									3	O			E5CE				 
2003021800055	20030218	00055	GL  	2003	2	18	2003FA0000109    	2	20030201	G	7261	R584P205	BOLT            								GE    	CF6   	CF6*        	30020	GL  					BEARING RETAINER	MISSING         	B				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	99							451304			AIRCRAFT OPERATOR REPORTED A TOTAL LOSS OF OIL PRESSURE AND QUANTITY 20 MINUTES AFTER TAKE OFF FROM LAX.  THIS RESULTED 	IN A IFSD AND AN ATB.  INVESTIGATION AT THE ENGINE REPAIR STATION REVEALED THAT ONE OF THE TWELVE RETAINING BOLTS FOR TH	E NR 7 BEARING WAS MISSING.  THE BOLT WAS FOUND IN THE BEARING SCAVENGE LINE.  THE BOLT HAD BLOCKED THE PIPE AND CAUSED 	THE ENGINE TO PUMP ALL OF THE OIL OVERBOARD.								4	F			E23EA				 
2003021800056	20030218	00056	EU  	2003	2	18	2003FA0000110    	1	20030129	G	5510	453005501	HINGE           			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZONTAL  STAB	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	400TF	4550 				279				DURING THE PERFORMANCE OF AD-89-12-08 THE LT OUTBOARD HINGE LUG WAS FOUND CRACKED.  CRACK WAS VISUAL TO THE NAKED EYE, M	ICRO FRACTURES WERE NOTED LAST 200 HOUR INSPECTION BUT WERE NOT DEFINED.  SUGGEST THAT CAUSE COULD BE DUE TO EXCESSIVE R	ADIAL AND AXIAL LOADS TRANSMITTED TO THE HINGE DURING T/R APPLICATIONS.				2	M	7	2 	4F	4	F	 	A2SW    	E6WE				 
2003021800057	20030218	00057	EU  	2003	2	18	2003FA0000111    	1	20030128	G	5510	453005501	HINGE           			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZONTAL  STAB	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	59PT	5575 				202				DURING THE PERFORMING OF AD 89-12-08, THE LT OUTBOARD HINGE LUG WAS FOUND CRACKED.  CRACK WAS VISUAL TO THE NAKED EYE.  	SUGGEST THAT CRACK CAUSE DUE TO EXCESSIVE RADIAL AND AXIAL LOADS TRANSMITTED TO THE HINGE DURING THRUST REVERSE APPLICAT	IONS AND FLIGHT INTO TURBULENT AIR.  THE RADIAL AND AXIAL LOADS CAN BE REDUCED BY ASSURING THAT THE HORIZONTAL STABILIZE	R SCISSOR SYSTEM IS INSPECTED EACH INSPECTION FOR SCISSOR WEAR AND SCISSOR BUSHING AND PIN WEAR.			2	M	7	2 	4F	4	F	 	A2SW    	E6WE				 
2003021800058	20030218	00058		2003	2	18	2003FA0000113    	4	20030116	G	2562	2020REVA	BATTERY         			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					ELT	CORRODED        	B			RJUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	399ME					18280878				SERIES 2000 AND 3000 BATTERY CORRODED FROM GASING BATTERY DISCOLORED SYTRAFOAM CASE, ALSO CAUSED DAMAGED TO ELT PLASTIC 	COVER.  DISCOVERED AT ANNUAL INSPECTION.  SUGGEST MORE FREQUENT INSPECTION.					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2003021800065	20030218	00065	EU  	2003	2	18	2003FA0000114    	1	20030113	G	2820	25PF295139A	CONDUIT         			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					FUEL CELL	CORRODED        	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	17	703TS					257031				CORROSION CAUSES PIN HOLES, FUEL LEAKS INTO CONDUIT AND LEAKS INTO BOOST PUMP WIRES.  POSSIBLE EXPLOSION OR FIRE WITH FU	EL LEAKING DIRECTLY INTO WIRES.  SUGGEST EMERGENCY INSPECTION OF ALL CONDUITS.  IN ALL SIMILAR MAKE AND MODELS THE TUBE 	CORRODES FROM THE INSIDE, WHICH IS NOT PAINTED.				2	L	7	2 	4F	4	F	 	A3EU    	E6WE				 
2003021800072	20030218	00072	CE  	2003	2	18	2003FA0000115    	1	20030127	G	2752	C1444881	CLIP            			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7313     	01518	WP  					TE FLAPS	BACKED OUT      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	720CC	1372 				45072				LEFT FLAP OUTBOARD LOWER ACTUATOR COVER PLATE FOUND DISTORTED AND BENT. UPON INVESTIGATION FOUND CIR-CLIP FOR LOWER GIMB	LE PIN MISSING. THIS MISSING CLIP ALLOWED GIMBLE PIN TO DROP DOWN. WHILE PIN WAS BACKING OUT AND DURING FLAP OPERATION D	AMAGED OCCURRED TO THE FLAP ACTUATOR COVER PLATE AND FLAP STRUCTURE.  REPLACED POWER UNIT-FLAP DRIVE. COMPLETED REPAIRS 	TO COVER PLATE AND FLAP STRUCTURE PER LEAR INSTRUCTIONS.  SUGGEST INSPECTION FOR CIR-CLIPS AT AN INCREASED INTERVAL.			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2003021800078	20030218	00078		2003	2	18	2003FA0000121    	4	20030119	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	3537B	336  				172S8827				SPINNER BULKHEAD CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800079	20030218	00079		2003	2	18	2003FA0000122    	4	20030108	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  										PROPELLER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	393SP	377  				172S8290				PROPELLER SPINNER CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800081	20030218	00081		2003	2	18	2003FA0000124    	4	20030114	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	393SP	1347 				172S8290				SPINNER AFT BULKHEAD, CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003021800119	20030218	00119	SO  	2003	2	18	2003FA0000131    	2	20030124	G	7414		DISTRIBUTOR GEAR	BENDIX      		MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  					MAGNETO	STRIPPED        	C			HJLA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	326TJ	383  			D01FA172R	290043	679119			DISTRIBUTOR GEAR, MAGNETO INOPERATIVE ON RUN-UP ON INSPECTION FOUND TEETH SHEARED IN DISTRIBUTOR GEAR-90 DEGREES.						1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2003021800120	20030218	00120	SO  	2003	2	18	2003FA0000132    	2	20030123	G	8520		CRANKSHAFT      			CESSNA	210   	210         	2073402	CE  	CONT  	O470  	IO470E      	17026	SO  					ENGINE	BROKEN          	G				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CE	01	6572X					57572	775430E			AIRCRAFT MADE EMERGENCY LANDING AFTER ENGINE FAILURE.  INVESTIGATION FOUND THAT THE ENGINE CRANKSHAFT HAD BROKEN BETWEEN	 CYLINDERS TWO AND THREE.					1	H	7	1 	3O	3	O	RT	3A21    	3E1				 
2003021800122	20030218	00122	NM  	2003	2	18	2003FA0000134    	1	20030120	G	2910	511531	HOUSING         			BOEING	737   	737*        	       	NM  										SHUTTLE VALVE	DAMAGED         	C			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					5531					PIN HOLE FROM INTERIOR OF UNIT INTO THE INSIDE OF THE MOUNTING LUG HOLE.  HIGH PRESSURE ERROSION.  (WC/ NR 171602)						2	L	7	2 	4F			RT	A16WE   					 
2003021800123	20030218	00123	NM  	2003	2	18	2003FA0000135    	1	20030128	G	2910	65446922	HOUSING         			BOEING	737   	737*        	       	NM  										HYD MODULE	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					80					HOUSING IS CRACKED IN PRIORITY PORT.  FATIGUE.  MAKE HOUSING FROM DIFFERENT MATERIAL.  ( FXS   NR 174173)						2	L	7	2 	4F			RT	A16WE   					 
2003021800126	20030218	00126	NM  	2003	2	18	2003FA0000137    	1	20030127	G	2722	69356111	SLEEVE          			BOEING	737   	737*        	       	NM  										RUDDER PCU	GOUGED          	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					1796AC					SLEEVE SURFACE IS GOUGED.  SEGEMENT RUBBED ON SLEEVE DURING OPERATION.						2	L	7	2 	4F			RT	A16WE   					 
2003021800129	20030218	00129	NE  	2003	2	18	2003FA0000138    	1	20030127	G	6210		BLADE           			SKRSKY	S64   	S64E        	8142604	NE  										MAIN ROTOR	DAMAGED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	173AC					64015				ONE OF THE TWO TRAILING EDGE STUDS THAT WAS HOLDING THE TIP END WEIGHT PACKAGE FRACTURED (TRAIL EDGE).  THE FRACTURE OCC	URED APPROX. 1/4 INCH BELOW THE LOCK RING IN THE BALANCE PLATE ASSY.  THIS CAUSED THE LEADING EDGE STUD TO DEFORM, ALLOW	ING THE WEIGHT PACKAGE TO IMPACT THE TIP CAP.  THERE WERE 1.76 LBS. SECURED ON THE TRAILING EDGE STUD.  DEFORMATION WAS 	NOTICED ON THE TIP CAP WHEN THE AIRCRAFT WAS SHUTDOWN.  THE CAP WAS REMOVED FOR REPLACEMENT, EXPOSING DAMAGE TP BOTH STU	DS AND THE TIP CAP.  THE WEIGHT PACKAGE WAS CONTAINED BY THE TIP CAP.  THE FLIGHT CREW REPORTED NO VIBRATION.		2	G	7	2 	4U			 	H4EA    					 
2003021800136	20030218	00136	CE  	2003	2	18	2003FA0000140    	1	20030113	G	5540		ATTACH FITTING  			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					RUDDER STOP	CRACKED         	B			QLSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	24DM	9874 				177RG0678				FOUND LT RUDDER STOP RIDING OVER HORN AREA.  THIS CAUSED DEFLECTION OF HORN ATTACHMENT AND CRACK.  STOP BOLTS NOT HITTIN	G HORN SQUARELY, CAUSING HORN TO RIDE UP OR DOWN UNDER STOP BOLT.  ASSURE STOP BOLTS HIT HORN SQUARELY.					1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2003021800138	20030218	00138	CE  	2003	2	18	2003FA0000141    	1	20030128	G	3233	24900022	BUSHING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					MLG ACTUATOR	UNSECURE        	B			CB9T	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5145U	984  				172RG0258				DURING 100HR INSPECTION, TECHNICIAN FOUND THE LT MLG ACTUATOR CAP BUSHING.  UNSEATED AND STICKING OUT OF THE ACTUATOR CA	P.  DURING RETRACT TEST, IT WAS FOUND THAT THE BUSHING NOW INTERFERED WITH THE BRAKE SWIVEL FITTING.  THE CAP WAS REMOVE	D AND A NEW BUSHING WAS INSTALLED IAW SEB AND SERVICE KIT.  ACCOMPLISHMENT INSTRUCTIONS 99.9 HOURS LATER, THE SAME CONDI	TION WAS FOUND AGAIN, THIS TIME IN BOTH ACTUATOR CAPS.  AGAIN, BOTH BUSHINGS WERE REPLACED.  IT IS POSSIBLE THAT THE EC1	300L ADHESIVE CALLED FOR IN SK172-151 IS NOT COMPATIBLE WITH THE GREASE OR HYDRAULIC FLUID FOUND IN THE ACTUATORS.  ALL 	PARTS WERE THOROUGHLY CLEANED PRIOR TO INSTALLATION.	1	H	7	1 	3O	3	O	 	3A17    	E286				 
2003021800140	20030218	00140	CE  	2003	2	18	2003FA0000142    	1	20030128	G	3233	2490022	BUSHING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					MLG ACTUATOR	UNSECURE        	D			CB9T	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	6220R	1091 				172RG0120				DURING 100 HOUR INSPECTION, TECHNICIAN FOUND RT MLG ACTUATOR CAP BUSHING, UNSEATED AND STICKING OUT OF THE ACTUATOR CAP.	  DURING RETRACT TEST, IT WAS FOUND THAT THE BUSHING NOW INTERFERED WITH THE BRAKE SWIVEL FITTING.  THE CAP WAS REMOVED 	AND A NEW BUSHING WAS INSTALLED IAW MFG SEB.  THE SAME CONDITION WAS FOUND AGAIN IN THE RT ACTUATOR AND THE BUSHING WAS 	REPLACED.  IT IS POSSIBLE THAT THE EC 1300L ADHESIVE CALLED FOR IN SK172-151 IS NOT COMPATIBLE WITH THE GREASE OR HYDRAU	LIC FLUID FOUND IN THE ACTUATORS.  ALL PARTS ARE CLEANED PRIOR TO INSTALLATION.		1	H	7	1 	3O	3	O	 	3A17    	E286				 
2003021800141	20030218	00141	NM  	2003	2	18	2003FA0000145    	1	20030107	G	2910	6544947	HOUSING         			BOEING	737   	737*        	       	NM  										HYD ACTUATOR	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01		41068								HOUSING CRACKED AROUND THE OUTER DIAMETER OPPOSITE THE SUPPORT MOUNT THROUGH BOLT.						2	L	7	2 	4F			RT	A16WE   					 
2003021800044	20030218	00044	NE  	2003	2	18	2003FA0000150    	2	20030209	G	7230		COMPRESSOR      								PWA   	JT8   	JT8D219     	52053	NE  					ENGINE	FOD             	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23							726974			HIGH PRESSURE COMPESSOR FOD.											4	F			E9NE				 
2003021800045	20030218	00045	CE  	2003	2	18	2003FA0000152    	1	20030211	G	3220	S217840144	HOSE            			CESSNA	210   	T210N       	2073456	CE  										NLG	RESTRICTED      	G				O				OTHER                   				S			AFFECT SYSTEMS            			LD	LANDING        	1			GL	07	210AX	2483 				21063033				THE CESSNA 210 LANDED WITH THE NOSE LANDING GEAR STILL IN THE NOSE WHEEL WELL.  UPON TROUBLESHOOTING  THE NOSE GEAR HYDR	AULC SYSTEM, FOUND ONE OF THE NOSE GEAR ACTUATOR HOSES RESTRICTED AND KINKED. CESSNA SERVICE BULLETIN SEB92-8 RELATES TO	 THE CHANGING OF CERTIAN LANDING GEAR HOSES ON AFFECTED AIRCRAFT, WITH THIS AIRCRAFT IN THE AFFECTED SERIAL NUMBERS.				1	H	7	1 	3O			 	3A21    					 
2003021800046	20030218	00046	CE  	2003	2	18	2003FA0000153    	1	20030217	G	3240		LINE            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										BRAKE SYS	MISROUTED       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11	51289					258589				DURING INSPECTION OF MLG (LT AND RT) DISCOVERED BRAKE LINES ROUTED INCORRECTLY CAUSING ONE BRAKE LINE TO CHAFE ON THE MA	IN TIRE.  SHOULD BE ROUTED IAW MAINTENANCE MANUAL 32-40-00-001.CHAFED LINES WERE REPLACED.					2	L	7	2 	4F			RT	A3EU    					 
2003021800047	20030218	00047	CE  	2003	2	18	2003FA0000154    	1	20030217	G	2597		WIRE            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										ELT	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	664AC					258566				DURING INSPECTION WITH TAIL CONE REMOVED DISCOVERED ELT WIRING HARNESS CHAFING HARD ON AFT SIDE OF NR 2 MAIN OXYGEN BOTT	LE.					2	L	7	2 	4F			RT	A3EU    					 
2003021800048	20030218	00048		2003	2	18	2003FA0000156    	4	20030217	G	6122	B210776A	GOVERNOR        			AMTR  	VANS  	RV8         	       	GL  	LYC   	O360  	O360A1A     	41514	EA  					PROPELLER	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	468JL	673  								PROPELLER WOULD CYCLE NORMALLY DURING RUN UP. AFTER TAKE OFF THE PROP WOULD BECOME UNCONTROLLABLE. RMP ONLY CONTROLLABLE	 BY THROTTLE, NOT PROPELLER CONTROL. REMOVAL AND DISASSEMBLY OF PROP GOVERNOR REVEALED THAT ALLEN SCREW HAD BACKED OUT O	F REAR OF UNIT AND WAS CAUGHT BY INTERNAL GASKET SCREEN BETWEEN UNIT AND ACCESSORY HOUSING. THIS WAS A FACTORY NEW UNIT 	WITH 673 HRS. APPEARS ALLEN SCREW WAS NOT PROPERLY TIGHTENED AT FACTORY. REINSTALLED WITH LOCK TIGHT AND TIGHTENED SECUR	ELY. HAD THERE NOT BEEN GASKET SCREEN IN PLACE, ENGINE DAMAGE OR STOPPAGE COULD OCCUR.		1	L	7	1 	3O	3	O	NT	EXPA1L71	E286				 
2003021800260	20030218	00260	SW  	2003	2	18	2003FA0000159    	1	20030130	G	7500	8961151	GASKET          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					NR 2 ENGINE	RUPTURED        	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	158WA					TC411	54192			A GASKET RUPTURED BETWEEN THE POWERPLANT AND THE BLEED AIR TUBE.  THIS ALLOWED HOT BLEED AIR TO BLOW DIRECTLY ON AN ENGI	NE FIRE DETECTOR.  THE PILOTS, FOLLOWING MFG PROCEDURES, FEATHERED THE ENGINE AND DIVERTED FOR AN UNEVENTFUL LANDING.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003021800261	20030218	00261	CE  	2003	2	18	2003FA0000160    	1	20030218	G	2435		BEARING         			RAYTHN	DH125 	HAWKER800   	7450004	CE  										STARTER GEN	FAILED          	D				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			NM	08	194JS		695  		991105	258251				STARTER-GENERATOR REAR BEARING FAILED.  (A) STARTER-GENERATOR SINCE OVERHAUL: 695.9 HOURS.						2	L	7	2 	4F			RT	A3EU    					 
2003021800262	20030218	00262	CE  	2003	2	18	2003FA0000161    	1	20030205	G	2435		BEARING         			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					STARTER GEN	FAILED          	D				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			NM	08	194JS		695  		991105	258251				STARTER-GENERATOR REAR BEARING FAILED.   (A) STARTER-GENERATOR SINCE OVERHAUL: 695.9 HOURS.  						2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2003022000001	20030220	00001	EA  	2003	2	20	2003FA0000162    	1	20030120	G	7810	C65C11073	EXHAUST PIPE    			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	CRACKED         	B			A7RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19										EXHAUST DUCT, CRACK IN BASEMETAL.  VIBRATION						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2003022000003	20030220	00003	EU  	2003	2	20	2003FA0000168    	1	20030128	G	3230	X030004000000	MANIFOLD        			GROB  	120   	G120A       	1660208	EU  										MLG	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF					85004				DURING FLIGHT THE FLIGHT CREW REPORTED THAT THE LEFT GEAR WAS SLOW TO EXTEND.  MAINTENANCE TROUBLESHOT SYSTEM AND FOUND 	LEFT EXTENSION VALVE BAD.  PARTICLES INSIDE OF VALVE WHICH PREVENTED FLUID TO FLOW UNRESTRICTED.					1	L	7	1 	3O			RT	A49CE   					 
2003022000004	20030220	00004	SO  	2003	2	20	2003FA0000169    	2	20030128	G	7414		BRUSHES         	SLICK       							CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	DIRTY           	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		500  			02040024					MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  DURING INSPECTION FOUND THAT THE CARBON BRUSH WAS RUBBING A	ND CAUSING CARBON DUST.										3	O			E5CE				 
2003031100075	20030311	00075	CE  	2003	3	11	2003FA0000172    	1	20030201	G	3244	30620	TIRE            			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	SPLIT           	B			ODAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	9525V					17280315				FOUND SPLIT IN LT MAIN TIRE ON SIDEWALL.  RECAP TIRE 6.00 X 6.  SPLIT IS APPROX 50 PERCENT RADIUS OF THE SPLIT IS TO COR	D.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031100076	20030311	00076		2003	3	11	2003FA0000175    	4	20030124	G	3416	10172001999	INDICATOR       			AMTR  	VANS  	RV8A        	05608J0	GL  	LYC   	O360  	O360A1A     	41514	EA  					ALTIMETER	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	751MB					RV8A81430				ALTIMETER PURCHASED NEW.  MAY 5, 2001 MANUFACTURE DATE.  FAILED TO PASS FRICTION PORTION OF PITOT/STATIC/XPDR.  BIANNUAL	 CHECK.  MFG CONTACTED AND IS UNAWARE OF ANY PROBLEMS WITH THIS MODEL BUT TECHNICIAN DOING STATIC TEST NOTES SEVERAL LIK	E IT HAVE FAILED SAME CHECK EARLY IN THEIR LIFETIMES.  INSTALLED IN HANGARED HOMEBUILT.  UNIT RETURNED TO MFG FOR EVALUA	TION.			1	L	7	1 	3O	3	O	NC	EXPA1L71	E286				 
2003031100077	20030311	00077	SO  	2003	3	11	2003FA0000176    	1	20030129	G	2140	A23D04	SEAL            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					FUEL REGULATOR	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	09	63954	3519 			9771374	277854085				UNIT WAS INSPECTED DURING A 100 HOUR INSPECTION USING S/B.  FUEL STAINS WERE FOUND, BAD NO FUEL, AROUND BOTH TOP AND BOT	TOM GASKETS.  UNIT WAS REMOVED FROM SERVICE.					1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2003031100078	20030311	00078	CE  	2003	3	11	2003FA0000178    	1	20030122	G	5210	551905514	MECHANISM       			CESSNA	501   	551         	2076605	CE  	PWA   	JT15  	JT15D4      	52112	NE  					PAX DOOR HANDLE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	322MA	3040 				5510378				CREW WAS UNABLE TO OPEN THE CABIN DOOR FROM INSIDE.  LINE CREW HAD TO USE EXTERNAL HANDLE TO OPEN CABIN DOOR.  THE PROBL	EM WAS THE INNER DOOR RELEASE LOWER TRIGGER, HAD BROKEN OFF AT THE TOP INNER CORNER AND FALLEN BEHIND THE TRIGGER.  CAUS	ING IT TO JAM AND NOT RELEASE THE DOOR HANDLE.				1	L	7	2 	4F	4	F	 	A27CE   	E1NE				 
2003031200047	20030312	00047	NE  	2003	3	12	2003FA0000181    	3	20030123	G	6111	6607132886	BLADE           													ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		30718	6910 					DRG172784		PROPELLER RECEIVED FOR OVERHAUL AT TEARDOWN FOUND OUTER SLEEVE WAS CRACKED ON BLADE  S/N 1140.  CRACK APPROXIMATELY 4 IN	CHES LONG.  BALDE WAS REJECTED FROM FURTHER SERVICE.															6	C	P30NE	 
2003031100080	20030311	00080		2003	3	11	2003FA0000182    	4	20030202	G	2562	AK450	ELT             																	CABIN	FAILED          	B			X3DR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	03		40   								INSTALLED NEW AK450 ON 09/01/2001.  THE ELT WAS TESTED AND FAILED TO FUNCTION.  UNIT SENT TO MFG FOR REPAIRS.																			 
2003031100081	20030311	00081	SW  	2003	3	11	2003FA0000183    	1	20030218	G	2150	7202N	BEARING         			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  					AC DRIVE	DISINTEGRATED   	B			BGSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	134MC	497  				290134	679311			DURING INSTALLATION OF AN AIR/OIL SEPARATOR, REMOVED THE AIR CONDITIONER ACCESSORY DRIVE OFF THE STARTER SHAFT TO INSTAL	L AN OIL RETURN FITTING FOR THE AIR/OIL SEPARATOR.  UPON REMOVAL OF THE ACCESSORY DRIVE HOUSING, PIECES OF THE AIR CONDI	TIONER DRIVE BEARING FELL OUT OF THE HOUSING, FURTHER EXAMINATION REVEALED TOTAL DISENTIGRATION OF CAGE FOR BALL BEARING	S.			1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2003031100083	20030311	00083	CE  	2003	3	11	2003FA0000192    	1	20030217	G	5510	083200056	BRACKET         			CESSNA	310   	310N        	2074234	CE  										STAB HINGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	721X	8161 				310N0061				UNIT WAS MANUFACTURED BY COMBINING TWO SHEETMETAL BRACKETS RIVETED TO A CASTING THAT HOLDS THE OUTBOARD ELEVATOR HINGE B	EARING.  CRACKING WAS FOUND IN BOTH THE RIGHT AND LEFT HAND ASSEMBLIES ON THE UPPER, INBOARD BEND RADIUS.  THIS CAN BE S	EEN FROM UNDERNEATH AND LOOKING THRU THE ELEVATOR/STABILIZER GAP.				1	L	7	2 	3O			 	3A10    					 
2003031100085	20030311	00085	SO  	2003	3	11	2003FA0000194    	1	20030212	G	3213	78738002	AXLE            			PIPER 	PA28  	PA28161     	7102803	SO  										MLG	CRACKED         	B			C85R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	2159H	13331				287916192				DURING ROUTINE 100 HOUR INSPECTION, BOTH LOWER AXEL STUBS (INNER PORTION OF LOWER STRUT ASSY.)  WERE FOUND CRACKED.  POS	SIBLE JUST NORMAL FATIGUE VS. HARD LANDING DAMAGE.  BOTH ARE BELIEVED TO BE ORIGINAL EQUIPMENT.  AIRCRAFT IS FLIGHT SCHO	OL TRAINING AIRCRAFT.  COULD HAVE THOUSANDS OF LANDINGS ON IT.				1	L	7	1 	3O			 	2A13    					 
2003031100086	20030311	00086	SW  	2003	3	11	2003FA0000195    	1	20030220	G	3710		SHAFT           			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					VACUUM PUMP	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	9625M					670202				NEW VACUUM PUMP SHAFT SHEARED WITH ONLY 3 HOURS OF OPERATION INSTALLED ON 04/25/2002.  BROKE ON 02/19/2003.						1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2003031100087	20030311	00087	CE  	2003	3	11	2003FA0000196    	1	20030210	G	2510	05142132	CYLINDER        			CESSNA	172   	172S        	2072439	CE  										SEAT BACK	FAILED          	B				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			GL	15	35522	1075 				172S8846				SHORTLY AFTER ROTATION SEAT BACK FAILED AND WENT TO THE RECLINED POSITION.  COMPLETE FAILURE COULD NOT BE DUPLICATED IN 	THE SHOP BUT SOME SLIPPAGE OF THE LOCKING CYLINDER WAS NOTED.					1	H	7	1 	3O			NT	3A12    					 
2003031100088	20030311	00088	CE  	2003	3	11	2003FA0000197    	1	20030212	G	3710	442CW6	PUMP            			BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720*      	41546	EA  					RT VACUUM SYS	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	46MA	239  				LD413				VACUUM PUMP FAILED UNDER NORMAL OPERATING CONDITIONS.						1	L	7	2 	3O	3	O	 	3A20    	1E15				 
2003031100090	20030311	00090	SO  	2003	3	11	2003FA0000198    	1	20030117	G	7120	MS21919WDG	CLAMP           			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE MOUNT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	173ND					2837025				CLAMP PN MS21919WD6 THAT RETAINS THE MIXTURE CONTROL CABLE TO THE ENGINE MOUNT FAILED ALLOWING CABLE TO RESTRICT THE OPE	RATION OF THE NOSE LANDING GEAR.  INSPECT SECURENESS AND ROUTING OF MIXTURE CABLE ON LIKE AIRCRAFT TO PREVERT CABLE FROM	 RESTRICTING LANDING GEAR TRAVEL.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003031100092	20030311	00092		2003	3	11	2003FA0000199    	4	20030217	G	6113	04500422	SPINNER         			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200*       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	PROPELLER	DAMAGED         	B			H9QR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	11418	143  				15075405		G16376		PROP REMOVED TO FACILITATE REPLACEMENT OF ENG CRANKSHAFT SEAL.  REMOVAL OF SPINNER, SEVERE WEAR AND FRETTING OF INNER SU	RFACE WAS NOTED WHERE FWD BULKHEAD (PN04500503) CONTACTS SPINNER.  AFTER REMOVING PROP, PROP MOUNT BOLTS WERE OVERTORQUE	D, RESULTING IN DEFORMATION OF WASHERS AND BULKHEAD.  AFT BULKHEAD (04500465) WAS CRACKED ALMOST ENTIRELY AROUND  CIRCUM	FERENCE OF BOLT CIRCLE.  PROP, AFT BULKHEAD, AND PROPELLER SPACER SHOWED EVIDENCE OF HAVING BEEN PRIED APART WITH A SCRE	WDRIVER OR SIMILAR INSTRUMENT.  MOVEMENT OF CRACKED REAR BULKHEAD HAD CAUSED FRETTING DAMAGE TO AFT FACE OF PROP HUB.  R	EQUIRED REPLACEMENT OF SPINNER, AFT BULKHEAD, AND FORWARD BULKHEAD.  PROP WAS REPAIRED AT A CERTIFIED FACILITY.	1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2003031100093	20030311	00093	GL  	2003	3	11	2003FA0000200    	1	20030103	G	3220	11799002B	BRACKET         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	154SD					1197				THE PANT BRACKETS MOVE AND ALLOW THE WHEEL PANT TO MOVE AND CRACK OR COME APART.  THE NEW WHEEL PANT BRACKETS COME WITH 	A BUSHED .2500 INCH HOLE INSTEAD OF THE NR 10 HOLE THAT IS THE SIZE NEEDED FOR THE NR 3 BOLT.  WE HAVE BEEN MAKING UP PL	ASTIC BUSHINGS THAT JUST FIT IN THE HOLES AND TAKE UP THE EXTRA SPACE AND THE NR 3 BOLT FITS INTO.  THIS HAS TAKEN CARE 	OF THE LOOSENESS OF THE BRACKET AND THE WHEEL PANT STAYS IN PLACE.  HAVEN'T HAD ANY WHEEL PANTS CRACK OR FALL OFF BEFORE	 THIS HAS BEEN DONE TO PLANES SERVICED.  THIS AC HAD LOST THE BACK HALF OF ITS WHEEL PANT ON LANDING.  OWNER HAD REPAIRE	D WHEEL PANT BEFORE WHEN BACK HALF STARTED TO COME LOOSE.  FOUND BRACKETS WOULD ROCK IF YOU TRIED TO MOVE THEM.	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003031100094	20030311	00094	SO  	2003	3	11	2003FA0000201    	2	20030205	G	8500	653688	CRANKCASE       			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	96706	322  				1116				ON AIRCRAFT, BECAUSE OF A CRACK FOUND ON ANOTHER ENGINE, DECIDED TO INSPECT AND FOUND A CRACK ON THE RIGHT FRONT SIDE OF	 THE ENGINE CASE AT THE ALTERNATOR MOUNTING FLANGE AREA.  THE CRACK STARTED ON THE ALTERNATOR REAR MOUNTING CASE THROUGH	 BOLT.  THIS CRACK IS ABOUT 2 INCHES LONG.  A REPLACEMENT ENGINE HAS BEEN ORDERED.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003031100097	20030311	00097	SO  	2003	3	11	2003FA0000202    	2	20030205	G	8500	653688	CRANKCASE       			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	907FS	1100 				1030				A SLIGHT OIL LEAK COMING FROM THE FRONT RIGHT SECTION OF THE ENGINE WAS FOUND TO BE A CRACKED CASE.  REMOVED NR 1 ALTERN	ATOR AND DYE CHECKED THE AREA.  FOUND A 6 INCH CRACK ON THE ALTERNATOR MOUNTING FLANGE STARTING ON THE ALTERNATOR MOUNTI	NG FLANGE THROUGH BOLT.  THIS ENGINE WAS REPLACED.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003031100098	20030311	00098	CE  	2003	3	11	2003FA0000203    	1	20030301	G	2913	67B025	PUMP            			PIPER 	PA23  	PA23150     	7102303	CE  	LYC   	O320  	O320*       	41508	EA  					HYD SYSTEM	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	21	211CR	4456 				23358				ONE PRESSURE LINE FAILED IN THE WING BETWEEN PUMP AND THE POWER PACK.  AFTER REPLACEMENT OF ALUMINUM LINE THE SYSTEM WAS	 SERVICED AND TESTED.  ON THE TEST HOP THE ENGINE DRIVEN PUMP FAILED AND THE PUMP CASE RUPTURED.  THE PUMP WAS REPLACED,	 THE SYSTEM RESERVICED AND GROUND CHECKS COMPLETED.  ON TEST HOP WITH THE SECOND PUMP, THE SAME FAILURE OCCURRED.  THE P	UMP RUPTURED, THE CASE SPLIT AND AFTER LOSS OF PRESSURE THE GEAR WAS EXTENDED BY HAND PUMP SUCCESSFULLY.  THE TWO PUMPS 	AND THE POWER PACK HAVE BEEN SENT TO REPAIR STATION FOR IRAN.  THIS IS ON A 1954 APACHE WITH 4456 HOURS TT.  NORMAL CONF	IGURATION IS WITH ONE ENGINE DRIVEN HYDRAULIC PUMP ON THE LEFT ENGINE.  (EMERGENCY EXTEND BY HAND PUMP OR CO2 BLO DOWN.)	1	L	7	2 	3O	3	O	RT	1A10    	E274				 
2003031100099	20030311	00099	EA  	2003	3	11	2003FA0000204    	2	20030301	G	8500		ENGINE          								LYC   	O360  	O360A4M     	41514	EA  						MAKING METAL    	G			NJ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	21							L2959536A			AT JUST FIVE HOURS AFTER MAJOR OVERHAUL, THE FLIGHT CREW REPORTED THAT THE ENGINE MADE NOISE AT LOWER RPMS METAL PARTICL	ES THAT LOOK LIKE BEARING MATERIAL WERE FOUND IN THE OIL FILTER.  AN OIL SAMPLE WAS SENT IN FOR ANALYSIS.										3	O			E286				 
2003031100100	20030311	00100	EU  	2003	3	11	2003FA0000205    	1	20030301	G	2897		WIRE            			CASA  	C212  	C212200     	2410304	EU  	GARRTT	TPE331	TPE331*     	01514	WP  					BOOST PUMP	CHAFED          	D			UATA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	287MA					287				THE WIRE PROVIDING A NEUTRAL AND POWER TO THE PUMP EXITS/ENTERS PUMP USING A SEALED AN FLARE FITTING CAUSING CHAFING TO 	OCCUR.					2	H	7	2 	4T	3	T	RT	A43EU   	E2WE				 
2003031100101	20030311	00101	CE  	2003	3	11	2003FA0000206    	1	20030121	G	5312	07126153	BULKHEAD        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	888CH					18266884				SMALL CRACK IN AFT BULKHEAD AT STA 209.  ORIGINATING FROM UNDER THE ATTACH POINT OF RIGHT HORIZONTAL STABILIZER, ATHE TH	E UPPER INBOARD CORNER.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003031100102	20030311	00102	CE  	2003	3	11	2003FA0000207    	1	20030217	G	2434	DOFF10300F	ALTERNATOR      			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	3941R					17255441				FAILURE OF THE SHAFT ON AN OVERHAULED ALTERNATOR.  THE PILOT REPORTED AN AMMETER DISCHARGED WHILE CONDUCTING A PART 61 I	NSTRUCTIONAL FLIGHT.  A PRECAUTIONARY LANDING WAS MADE AT THE NEAREST AIRPORT.  INSPECTION OF THE ELECTRICAL SYSTEM INDI	CATED A FRACTURE OF THE MAIN SHAFT OF THE GEAR DRIVEN ALTERNATOR, AFT OF THE FRONT SEAL POSSIBLY DUE TO A MANUFACTURING 	DEFECT.  NO OTHER DAMAGE WAS NOTED TO EITHER THE ACCESSORY GEARS OR THE ALTERNATOR ITSELF.  PICTURES OF THE FRACTURED SH	AFT ARE ENCLOSED.  THE UNIT WAS INSTALLED IN DECEMBER 2001 AND ACCUMULATED 328 HOURS.		1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003031100112	20030311	00112	CE  	2003	3	11	2003FA0000208    	1	20030207	G	5510	MS21044N4	NUT             			ZINAIR	CH2000	CH2000      	9950100	CE  										STAB HINGE BOLT	FAILED          	D			Y85S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	668AM					2601008				ON BOTH STABILATOR HINGE BOLTS THE NYLON LOCKNUTS BACKED OFF DUE TO THE NYLON PART OF THE NUT BECOMING DETACHED FROM THE	 NUT ITSELF.  THIS HAPPENED IN APPROXIMATELY 100 HOURS TSN.					1	L	7	1 	3O			NT	TA5CH   					 
2003031100113	20030311	00113	CE  	2003	3	11	2003FA0000209    	1	20030201	G	5510	MS21044N4	NUT             			ZINAIR	CH2000	CH2000      	9950100	CE  	LYC   	O235  	O235*       	41505	EA  					STAB HINGE BOLT	FAILED          	D			Y85S	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	649AM		100  			2601007				ON BOTH STABILATOR HNGE BOLTS THE NYLON LOCKNUTS BACKED OFF DUE TO THE NYLON PART OF THE NUT BECOMING DETACHED FROM THE 	NUT ITSELF.  THIS HAPPENED IN APPROXIMATELY 100 HOURS TSN					1	L	7	1 	3O	3	O	NT	TA5CH   	E223				 
2003031300005	20030313	00005	CE  	2003	3	13	2003FA0000211    	1	20030110	G	2730	1016100195	TORQUE TUBE     			BEECH 	1900  	1900C       	1154161	CE  										ELEVATOR	EXCESS PLAY     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17			20   							FOUND LOOSE RIVETS ON HORN ADAPTER ATTACHED TO LT ELEVATOR TORQUE TUBE PN 1016100195.						2	L	7	2 	4T			RT	A24CE   					 
2003031300006	20030313	00006	CE  	2003	3	13	2003FA0000212    	1	20030304	G	3230	AE1011888G0131	HOSE            			CESSNA	750   	750         	2076810	CE  										NLG	DETERIORATED    	B				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			SW	15	910QS	2620 				7500110				AT 19,000 FT,  NOSE GEAR TRIED TO EXTEND. HYDRAULIC PRESSURE SLAMMED GEAR BACK UP. WITHIN 30 SECONDS HYDRAULIC QUANITY O	N "A" SYSTEM RESERVOIR STARTED DROPPING. AIRCRAFT WAS SLOWED AND NORMAL GEAR EXTENSION WAS MADE. HYDRAULIC QUANITY ON A 	SYSTEM RESERVOIR WENT TO ZERO. AFTER LANDING A SYSTEM HYDRAULIC QUANITY INDICATED 10 PERCENT. TROUBLE SHOT PROBLEM TO NO	SE GEAR EXTEND HOSE LEAKING. REMOVED AND REPLACED HOSE WITH NEW. PERFORMED LANDING GEAR SWING, OPERATIONAL CHECKS, BLED 	HYDRAULIC SYSTEMS, SERVICED RESERVOIRS, AND LEAK CHECKS. ALL FOUND TO BE SATISFACTORY. RAN ENGINES AND OPERATED HYDRAULI	C SYSTEMS ON GROUND ALL FOUND TO BE SATISFACTORY.	2	L	7	2 	4J			RT	T00007WI					 
2003031300007	20030313	00007		2003	3	13	2003FA0000213    	4	20030130	G	3424	PI307	CONNECTOR       			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					GYRO	IMPROPER PART   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	172WG				980990A	17201018				CONNECTOR FROM AIRCRAFT HARNESS TO TURN COORDINATOR HAS IMPROPERLY CRIMPED PINS AND LOOSE BACKSHELL, CAUSING AUTO-PILOT 	FAILURES AND INCORRECTLY DIAGNOSED FAILURES OF TURN-COORDINATORS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031300008	20030313	00008	SO  	2003	3	13	2003FA0000214    	2	20030224	G	7414	K3823	DISTRIBUTOR BLK 								CONT  	O520  	IO520*      	17032	SO  					MAGNETO	MISMANUFACTURED 	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MAINTENANCE MANUAL.  DURING INSPECTION FOUND THAT THE CARBON	 BRUSH WAS RUBBING AND CAUSING CARBON DUST.  RECOMMENDATION IS TO HAVE MANUFACTURE LOOK AT PROCESS OF MANUFACTURING AND 	LOOK AT REDUCING THE TOLERANCES BETWEEN THE DISTRIBUTOR BLOCK AND THE GEAR POST WHERE THEY FIT TOGETHER TO HELP PREVENT 	GEAR FROM ROCKING BACK AND FORTH.  FURTHER INVESTIGATION BY MFG REQUIRED TO CORRECT PROBLEM.								3	O			E5CE				 
2003031300010	20030313	00010	CE  	2003	3	13	2003FA0000216    	1	20030307	G	2621		HARNESS         			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										FIRE BOTTLES	MISINSTALLED    	B			YK1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11						8588				CHECKED THE WIRING OF THE ENG FIRE BOTTLES IN SN 8604 BECAUSE DURING A SCHEDULED INSPECTION OF SN 8588 FOUND SQUIBS TO E	NG FIRE BOTTLES MISWIRED.  IT WAS DISCOVERED THAT IN THEIR SCENARIO, YOU WOULD SEND FIRE RETARDANT TO THE WRONG ENG (PRE	SS SHOT FOR LT ENG, AND THE RETARDANT GO TO THE RT ENG).  DURING INSPECTION OF 8604 USING MM, IT WAS DISCOVERED CONNECTO	RS GH2 (ENG 2, SHOT 2) & GJ1 (ENG 2, SHOT 1) WERE REVERSED.  RESEARCHING RAC PRINT , IT APPEARS THAT SWITCHES RR & RT HA	VE SHOT 1 & SHOT 2 LABELING REVERSED IN THE PRINT.  LABELING CONTRADICTS THE PRINT AND THE MM.  8604 WAS TESTED PER MM T	O VERIFY THEY WERE CORRECTLY MARKED AND THEN BOTTLES WERE CONNECTED CORRECTLY.	2	L	7	2 	4F			RT	A3EU    					 
2003031300011	20030313	00011	EU  	2003	3	13	2003FA0000217    	1	20030307	G	2621	30111102	CARTRIDGE       			AMD   	FALC20	FALCON200   	2730150	EU  	GARRTT	ATF3  	ATF3*       	29002	WP  					FIRE BOTTLE	DISCHARGED      	E				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	05	200WY	6520 	2    		12116A1	509				FOUND THE "AFT BAGGAGE" FIRE EXTINGUISHER CARTRIDGE DISCHARGED WITHOUT DISPENSING THE FIRE BOTTLE.						2	L	7	2 	4F	4	F	RT	A7EU    	E7WE				 
2003031300014	20030313	00014	SO  	2003	3	13	2003FA0000220    	1	20030306	G	2420	1159SCAV373509	CONVERTER       			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					AC SYSTEM	INOPERATIVE     	C				D				RETURN TO BLOCK         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			EA	25	317ML	690  				1446	1802018021			DURING TAXI FROM THE OPERATOR`S HOME BASE AND PRIOR TO A SCHEDULED DEPARTURE, THE RT AC ELECTRICAL SYSTEM FAILED. THE AI	RCRAFT RETURNED TO BASE, THE SYSTEM WAS TROUBLESHOT AND THE RT AC CONVERTER WAS FOUND TO BE FAULTY. THE UNIT WAS REPLACE	D WITH A SERVICABLE PART AND THE AIRCRAFT WAS RETURNED TO AIRWORTHY CONDITION. THIS UNIT HAS PROVEN TO BE VERY UNRELIABL	E. SINCE IT'S CONSIDERED TO BE DISPATCH CRITICAL, WE BELIEVE THAT THE FAA AND THE MANUFACTURER NEED TO FULLY INVESTIGATE	 THIS MATTER.		2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003031300015	20030313	00015	SO  	2003	3	13	2003FA0000221    	1	20030122	G	8120	9810002004	BELLOWS         			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541*    	41539	EA  					INTERCOOLER	CHAFED          	B			MYNR	O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			GL	11	66809	30   				31P7300171	R45762			INSUFFICIENT CLEARANCE, BELLOWS ARE CHAFING THROUGH, CAUSED ENGINE FAILURE ON FINAL APPROACH.  PART OF INTER COOLER INST	ALLATION, STC NR SA3801NM,					1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2003031300016	20030313	00016	CE  	2003	3	13	2003FA0000222    	1	20030303	G	3220	12430097	TRUNNION        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					NLG	BROKEN          	B			WIWR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	44EC	3686 				21063972	517810			NOSE GEAR COLLAPSED DURING TAXI, AFTER LANDING, TOOK PLACE AFT NORMAL LANDING.  COLLAR BROKE WHERE TRUNION ATTACHES TO N	OSE GEAR BARREL, PREVIOUS CRACK EXISTED.					1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003031300017	20030313	00017	CE  	2003	3	13	2003FA0000223    	1	20030219	G	5310	954200154748	CHANNEL         			BEECH 	58    	58          	1152740	CE  										FUSELAGE	MISINSTALLED    	B			CGOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	3222B	221  				TH1977				FOUND ROW OF RIVETS MISSING FROM LEFT AND RIGHT CHANNELS, FORWARD END TO ANGLE SPLICE.  CHANNELS ARE LOCATED UNDER CABIN	 FLOOR JUST BEHIND WING AFT SPAR AND SUPPORT FLOOR PANEL.  THE RIVETS ATTACH SPLICE ANGLE RUNNING UNDER AFT SPAR TIEING 	INTO FORWARD CHANNELS.  RIVET HOLES WERE PRESENT IN BOTH PIECES IN CORRECT LOCATION.  THESE RIVETS ARE PRESENT IN SIMILA	R MODELS WITH EARLIER SERIAL NUMBERS.			1	L	7	2 	3O			 	3A16    					 
2003031200001	20030312	00001	SO  	2003	3	12	2003FA0000224    	1	20030218	G	3250	63300014	HORN            	PIPER       		PIPER 	PA28  	PA28181     	7102807	SO  										NLG STEERING	BROKEN          	B				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NE	03	522BC	257  				2843461				PILOT LANDED AT GON WITH REPORTED LOSS OF RUDDER CONTROL IN FLIGHT. FURTHER INVESTIGATION REVEALED THAT NOSE LANDING GEA	R STEERING HORN ASSEMBLY TUBING HAD BROKEN ALLOWING RUDDER CABLES TO SLACK. TUBING IS 3/4 INCH OD STEEL. SUSPECT TOW LIM	ITS WERE EXCEEDED AND CRACKED STEERING HORN DURING PREVIOUS GROUND HANDLING. LIMIT BOLTS WERE NOT BENT AS USUALLY FOUND 	WHEN TURN LIMITS HAVE BEEN EXCEEDED. ASSEMBLY RETURNED TO PIPER FOR FURTHER ANALYSIS SINCE IMPROPER HEAT TREATING MAY OF	 CAUSED FAILURE.		1	L	7	1 	3O			 	2A13    					 
2003031200002	20030312	00002	SW  	2003	3	12	2003FA0000226    	1	20030219	G	5751	12341	PUSHROD         			BBAVIA	7     	7GCBC       	1220601	SW  										AILERON	LOOSE           	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01	257AC					125799				AILERON RODEND JAM NUTS FOUND LOOSE.  HAVE FOUND SIMULAR CONDITION ON PREVIOUS AIRCRAFT NEW FROM FACTORY.						1	H	7	1 	3O			NC	A759    					 
2003031200003	20030312	00003	EU  	2003	3	12	2003FA0000228    	1	20030221	G	2720	12CSN022930	RING            			LET   	L23   	L23         	1360308	EU  										RUDDER PEDAL	MISSING         	B				O				OTHER                   				C			F.O.D.                    			CR	CRUISE         	1			NM	03	438BA	95   				029016				RUDDER PEDAL LOST VERTICAL STABILTY AND THE INSTRUCTOR PILOT REPORTED THE PROBLEM TO MAINTENANCE. MAINTENANCE INSPECTED 	THE AREA AND FOUND THE SAFETY RING,WHICH HOLDS THE RUDDER PEDAL ATTACH SHAFT TO THE FUSELAGE FITTING, MISSING. AN INSPEC	TION WAS MADE TO FIND THE RING, AND DETERMINED IT WAS NOT IN THE AIRCRAFT. MAINTENANCE QUESTIONED IF IT WAS INSTALLED AT	 THE FACTORY, WHICH INITIATED A FLEET WIDE ONE TIME INSPECTION. TWO MORE AIRCRAFT WERE FOUND TO BE MISSING THE SAFETY RI	NGS.THESE ARE NEW AIRCRAFT WITH LESS THAN A HUNDRED HOURS TIME IN SERVICE.		1	K	0	0 	  			RC	G24EU   					 
2003031200004	20030312	00004	EU  	2003	3	12	2003FA0000229    	1	20030221	G	2720	12CSN022930	RING            			LET   	L23   	L23         	1360308	EU  										RUDDER PEDAL	MISSING         	B				O				OTHER                   				C			F.O.D.                    			CR	CRUISE         	1			NM	03	431BA					029013				ONE TIME FLEET INSPECTION REVEALED SAFETY RING MISSING.ONE OF THREE AIRCRAFT BELIEVED TO HAVE NOT HAD INSTALLED AT FACTO	RY.INSPECTION OF AIRCRAFT DID NOT PRODUCE MISSING PART.					1	K	0	0 	  			RC	G24EU   					 
2003031300018	20030313	00018	EU  	2003	3	13	2003FA0000230    	1	20030221	G	2720	12CSN022930	RING            			LET   	L13   	L13ACBLANIK 	       	EU  										RUDDER PEDAL	MISSING         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	421BA					028902				ONE TIME FLEET INSPECTION REVEALED SAFETY CLIP MISSING. THIS CLIP HOLDS THE SHAFT THAT ATTACHES THE RUDDER PEDAL TO THE 	FUSELAGE FITTING.ONE TIME INSPECTION INITIATED DUE TO ANOTHER AIRCRAFT IN FLEET HAVING PEDAL VERTICAL STABILTY DETERIORA	TE.				1	K	0	0 	  			 	G24EU   					 
2003031200005	20030312	00005	CE  	2003	3	12	2003FA0000232    	1	20030224	G	3210		UPLOCK BRACKET  			BEECH 	MU300 	400BEECH    	       	CE  										MLG	SHEARED         	M				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05		4778 				910080				ACFT IN PHASED INSPECTION. WHEN INSPECTORS REMOVED THE AVIONICS RACK TO TORQUE A LOOSE ATTACH FITTING BOLT ON THE RIGHT 	MLG UPLOCK FITTING, A CHECK WAS MADE OF THE OTHER ATTACH BOLTS. THE BOTTOM FORWARD ATTACH BOLT HEADS WERE FOUND SHEARED 	OFF. THE BOLT HEADS WERE FOUND ON TOP OF THE GEAR UPLOCK ASSY. THERE WAS EVIDENCE THE BOLTS HAD BEEN SHEARED FOR A LONG 	TIME. FURTHER EXAMINATION DISCOVERED THE BOLTS WERE PART NUMBER NAS1204-9 AND NOT THE REQUIRED NAS1204-8.			2	H	7	2 	4F			RT	A16SW   					 
2003031200006	20030312	00006	EA  	2003	3	12	2003FA0000234    	2	20030224	G	7322	55255	RETAINER        	PRECISION   	HA6         	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					CARBURETOR	MISINSTALLED    	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	28	575ER	331  				4496151				PILOT COMPLAINED OF STIFF THROTTLE.  FOUND THE HA-6 CARBURETOR VERY STIFF.  FOUND THE SEAL RETAINERS FOR THE THROTTLE SH	AFT, ACCELERATOR ROD AND ECONOMIZER RODS TO BE SEATED TOO DEEPLY CAUSING THE SEALS TO 'GRAB' THE SHAFTS TIGHTLY MAKING T	HROTTLE ADJUSTMENTS DIFFICULT.  MARVEL SHEBLER ADDRESSED THIS PROBLEM IN S/B A2-78 ISSUED JANUARY 1979.  HAVE FOUND A TO	TAL OF 5 FACTORY NEW CARBS WITH THIS SAME CONDITION			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003031200007	20030312	00007	SO  	2003	3	12	2003FA0000235    	2	20030224	G	8530	538304P030	PUSHROD         	CONT        							CONT  	O520  	IO520F      	17032	SO  					CYLINDER	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28			1700 				286187R			UPON DISASSEMBLING THE ENGINE FOR OVERHAUL IT WAS DISCOVERED THAT THE NR 1 CYLINDER EXHAUST PUSHROD WAS SEVERLY WORN AT 	A POINT ABOUT 4 INCHES FROM THE ROCKER ARM END.  THE WORN AREA WAS SMOOTH, CRESCENT SHAPED, ABOUT 1/2 INCH IN LENGTH, AL	MOST PENETRATING THE ENTIRE WALL THICKNESS OF THE PUSHROD.  INSPECTION OF THE PUSHROD HOUSING REVEALED A SMALL BUT SHARP	 DENT ABOUT 1/8 INCH DEEP CORRESPONDING TO AREA OF WEAR ON THE PUSHROD. IT WAS UNABLE TO DETERMINE HOW LONG THE DENT HAD	 BEEN THERE BUT IMMINENT FAILURE OF THE PUSHROD WAS VERY LIKELY.							3	O			E5CE				 
2003031200008	20030312	00008		2003	3	12	2003FA0000236    	4	20030224	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  										PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	789EP	45   				172S8135				DURING PHASE 3 INSPECTION FOUND PROPELLER SPINNER CRACKED AT BLADE CUT OUT ON ONE SIDE.  THE PROBLEM IS REOCCURRING, THI	S IS THE 5TH SPINNER REPLACEMENT ON THIS AIRCRAFT IN 1928.0 HOURS AND IS A COMMON PROBLEM ON OTHER C-172S AIRCRAFT.  CES	SNA SERVICE BULLETIN SB02-61-01 WAS ACCOMPLISHED 45.6 HOURS AGO WHICH REQUIRED ELONGATING THE MOUNTING SCREW HOLES TO AC	HIEVE A GAP OF LESS THAN 0.03 BETWEEN SPINNER AND AFT BULKHEAD.  THE MATERIAL THICKNESS OF THIS P/N SPINNER IS HALF THE 	THICKNESS OF THE OLDER CESSNA AIRCRAFT SPINNERS AND IS THE REASON FOR THE CRACKING AS IT IS NOT A PROBLEM ON THE OLDER C	ESSNA AIRCRAFT.	1	H	7	1 	3O			NT	3A12    					 
2003031200009	20030312	00009		2003	3	12	2003FA0000237    	4	20030228	G	3432	52D189	INDICATOR       			CESSNA	206   	206H        	2073301	CE  										HSI GLIDESLOPE	INOPERATIVE     	B				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			EA	21	3535T					20608151				NEW AIRCRAFT, NEW HSI 345 HRS TTAF. GLIDESLOPE INOPERATIVE, FOUND GLIDESLOPE NEEDLE RESTRAINT (FROM TRANSPORT) STILL IN 	PLACE.					1	H	7	1 	3O			RT	A4CE    					 
2003031200010	20030312	00010	SO  	2003	3	12	2003FA0000240    	1	20030301	G	2435	MZ4220R	STARTER GEN     			PIPER 	PA44  	PA44180     	7104402	SO  										ENGINE	MISMARKED       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	923ER					4496010				THIS STARTER WAS RECEIVED AS AN OVERHAULED UNIT. THE BOX AND FAA FORM 81303 INDICATED A BASIC PART NUMBER PN MZ4220, HOW	EVER THE DATA PLATE ON THE STARTER WAS MARKED MZ4222R WHICH ROTATES THE OPPOSITE DIRECTION.					1	L	7	2 	3O			 	A19S0   					 
2003031200011	20030312	00011		2003	3	12	2003FA0000243    	4	20030301	G	6113	05503671	SPINNER         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	448ER	830  				17280610	L185651A	TI046		THE PROP SPINNER ON THE 172 RS SERIES CRACKS VERY FREQUENTLY. THE CRACKS RADIATE FROM THE CUT OUT FOR THE PROP BLADES.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003031200012	20030312	00012	EA  	2003	3	12	2003FA0000244    	2	20030301	G	8500		ENGINE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  		FLUCTUATES      	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	497ER	10816	569  			17280673	L2013851A	TL054		DURING AN INSPECTION THE IDLE WAS FOUND TO BE ABOUT 900 RPM. TYPICALLY THIS IS NOT CONSIDERED TO BE A REPORTABLE EVENT, 	HOWEVER THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE REGARDING UNSTABLE IDLE/MIXT	URE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONLY DURING INSPECTION GROUND RUNS, BUT ALSO DURING OPERA	TION BETWEEN INSPECTIONS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003031200013	20030312	00013	CE  	2003	3	12	2003FA0000246    	1	20030303	G	3320	6900080000	BALLAST         			BEECH 	200   	200BEECH    	1152920	CE  										CABIN LIGHTS	BURNED OUT      	C				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	27	616GB					BB752				CABIN LIGHT C/B TRIPPED WITH ASSOCIATED ELECTRICAL ODOR IN CABIN. REMOVED ALL FLUORESCENT LIGHT POWER SUPPLIES AND FOUND	 ONE HAD SHORTED OUT AND HAD BURNED THROUGH POWER SUPPLY BALLAST CASE. CLOSE TO STARTING VELCRO ON FIR THAT HOLDS LIGHT 	POWER SUPPLY IN PLACE.RECOMMEND PERIODIC INSPECTIONS TO LOOK FOR ANY HOT SPOTS ON BALLASTS.				1	L	7	2 	4T			 	A24CE   					 
2003031200014	20030312	00014	WP  	2003	3	12	2003FA0000247    	1	20030304	G	6410	500P3100101	BLADE           			HUGHES	369   	369E        	4470707	WP  										TAIL ROTOR	BROKEN          	D				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	05	234RF	897  				0255E				WHILE IN FLIGHT , PILOT EXPERIENCE VIBRATION WITH LOSS OF TAIL ROTOR CONTROL AUTHORITY. AFTER LANDING ,INSPECTION REVEAL	ED THE BLADE PITCH HORN HAD BROKEN INTO TWO PIECES, RENDERING ONE BLADE WITH NO PITCH CONTROL.					1	G	7	1 	3U			 	H3WE    					 
2003031300019	20030313	00019	CE  	2003	3	13	2003FA0000249    	1	20030228	G	5330		SKIN            			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  					FUSELAGE	CRACKED         	B			N9VR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	52757	26   				18281165				BELLY SKIN CRACKED AT NUTPLATE FOR FAIRING AFT OF NOSE GEAR.  CAUSED BY VIBRATION OF FAIRING.  INCREASE STRUCTURE STRENG	TH INSTEAD OF USING .025 2024 USE .032 2024 T-3.					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2003031300020	20030313	00020	SO  	2003	3	13	2003FA0000250    	1	20030224	G	3310	6743604	RHEOSTAT        			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NAV LIGHTS	OVERHEATED      	B			BONR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	11562					28R7837194				PILOT REPORTED SMOKE IN THE COCKPIT CLIMBING OUT OR A NIGHT VFR FLIGHT.  INSPECTED AIRCRAFT AND FOUND NAV LIGHT / INSTRU	MENT LIGHT SWITCH / RHEOSTAT HAD OVERHEATED.  ORDERED REPLACMENT SWITCH (PN 587779) AND INSTALLED.  OPS CHECKS GOOD.  I 	HAVE SEEN THESE RHEOSTATS GET HOT BEFORE.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003031200015	20030312	00015	EA  	2003	3	12	2003FA0000252    	2	20030305	G	7322	2520626	VALVE           	PRECISION   		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL CONTROL	SCORED          	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	416ER	592  				172S9160	L3042351A			THE CREW REPORTED FLUCTUATING IDLE DURING GROUND CHECK.  THE CREW RETURNED TO THE RAMP. TYPICALLY THIS IS NOT CONSIDERED	 TO BE A REPORTABLE EVENT, HOWEVER THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE R	EGARDING UNSTABLE IDLE/MIXTURE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONLY DURING INSPECTION GROUND 	RUNS, BUT ALSO DURING OPERATION BETWEEN INSPECTIONS. A COMMON SOURCE OF PROBLEMS WITH THIS FUEL CONTROL IS THE MIXTURE V	ALVE, PN-2520626. THIS VALVE BECOMES SCORED AND THEN INACCURATE IN IT'S FUNCTION. THERE IS A PROCEDURE FOR LAPPING THIS 	VALVE'S SURFACE.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200016	20030312	00016		2003	3	12	2003FA0000254    	4	20030210	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	433ER	424  				172S9166	L3045351A			THE PROP SPINNER ON THE 172R/S SERIES CRACKS VERY FREQUENTLY. THE CRACKS RADIATE FROM THE CUT OUT FOR THE PROP BLADES.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200017	20030312	00017		2003	3	12	2003FA0000255    	4	20030210	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	433ER	424  				172S9166	L3045351A			THE PROP SPINNER ON THE 172R/S SERIES CRACKS VERY FREQUENTLY. THE CRACKS RADIATE FROM THE CUT OUT FOR THE PROP BLADES.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200018	20030312	00018	EA  	2003	3	12	2003FA0000256    	2	20030210	G	7324	63B22623	FLOW DIVIDER    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	STICKING        	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	15	409ER	475  				172S9158	L3045051A			DURING CRUISE THE CREW REPORTED AROUGH ENGINE. AFTER INSPECTING APPLICABLE SYSTEMS, THE FUEL FLOW DIVIDER WAS CHANGED AF	TER HAVING BEEN FOUND STICKING INTERNALLY.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200019	20030312	00019	EA  	2003	3	12	2003FA0000257    	2	20030210	G	7324	63B22623	FLOW DIVIDER    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	STICKING        	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	15	409ER	475  				172S9158	L3045051A			DURING CRUISE THE CREW REPORTED AROUGH ENGINE. AFTER INSPECTING APPLICABLE SYSTEMS, THE FUEL FLOW DIVIDER WAS CHANGED AF	TER HAVING BEEN FOUND STICKING INTERNALLY.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200020	20030312	00020	EA  	2003	3	12	2003FA0000258    	2	20030210	G	7324	63B22623	FLOW DIVIDER    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	STICKING        	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	15	409ER	475  				172S9158	L3045051A			DURING CRUISE THE CREW REPORTED A ROUGH ENGINE. AFTER INSPECTING APPLICABLE SYSTEMS, THE FUEL FLOW DIVIDER WAS CHANGED A	FTER HAVING BEEN FOUND STICKING INTERNALLY.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200021	20030312	00021	EA  	2003	3	12	2003FA0000259    	2	20030205	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OUT OF ADJUST   	B				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SO	15	490ER		1462 			17280633	L2786451A			THE CREW REPORTED A PARTIAL POWER LOSS DURING STALL RECOVERY. THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF A	N AIRWORTHINESS DIRECTIVE REGARDING UNSTABLE IDLE/MIXTURE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONL	Y DURING INSPECTION GROUND RUNS, BUT ALSO DURING OPERATION BETWEEN INSPECTIONS. THE IDLE SYSTEM ON THIS FUEL CONTROL UNI	T HAS ISSUES, WHERE IT REQUIRES CONSIDERABLE ADJUSTING WITHIN A RELATIVELY FEW NUMBER OF OPERATING HOURS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200022	20030312	00022	EA  	2003	3	12	2003FA0000260    	2	20030208	G	7322	2520626	VALVE           	PRECISION   	RSA5AD1     	CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360LYC*   	41514	EA  					FUEL CONTROL	SCORED          	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	405ER	444  				172S9155	L3044751A			DURING A PRE TAKE OFF IDLE CHECK THE ENGINE RAN VERY SLOW AND EVENTUALLY QUIT. THE INJECTOR SERVO WAS INSPECTED AND THE 	INTERNAL IDLE MIXTURE PLATE WAS FOUND TO BE SCORED. THERE IS A PROCEDURE FOR LAPPING THIS VALVE. IT WAS ACCOMPLISHED AND	 THE IDLE SPEED/MIXTURE WAS ADJUSTED.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200023	20030312	00023	EA  	2003	3	12	2003FA0000262    	2	20030218	G	7313	25248642	FUEL NOZZLE     			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OBSTRUCTED      	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			SO	15	456ER					17280667	L1562851A			ON TAKE OFF THE ENGINE RAN ROUGH. INVESTIGATION SHOWED THAT ONE FUEL INJECTOR NOZZLE WAS FOUND WITH AN IRREGULAR FLOW. I	T WAS REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200024	20030312	00024	EA  	2003	3	12	2003FA0000263    	2	20030219	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	420ER		1906 			17280634	L2784651A			DURING A PRE TAKE OFF IDLE CHECK, THE ENGINE QUIT. THIS ENGINE/FUEL CONTROL SYSTEM IS THE SUBJECT OF AN AIRWORTHINESS DI	RECTIVE CONCERNING UNSTABLE IDLE TENDENCIES.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031300023	20030313	00023	CE  	2003	3	13	2003FA0000264    	1	20030306	G	5520	556555026	ARM             			CESSNA	500   	500CESSNA   	2076602	CE  										ELEVATOR	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	27SF	13186	921  			5000064				DURING A PHASE 5 INSPECTION A SMALL CRACK WAS DISCOVERED NEAR THE LT UPPER NUTPLATE ON THE ELEVATOR BOBWEIGHT SUPPORT AR	M. AFTER REMOVING THE ASSEMBLY IT WAS DISCOVERED THAT THERE WERE MULTIPLE CRACKS AROUND ALL FOUR NUTPLATES. REPLACED BOT	H SUPPORT ARMS. SUSPECT METAL FATIGUE AS CAUSE OF THE CRACKING. SUGGEST THAT THIS ASSEMBLY BE REMOVED AT EACH PHASE 5 IN	SPECTION TO INSPECT FOR CRACKING.			1	L	7	2 	4F			 	A22CE   					 
2003031200025	20030312	00025	EA  	2003	3	12	2003FA0000265    	2	20030219	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  						FLUCTUATES      	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	416ER	535  				172S9160	L3042351A			THE CREW REPORTED A ROUGH IDLE DURING GROUND OPERATION. THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF AN AIRW	ORTHINESS DIRECTIVE REGARDING UNSTABLE IDLE/MIXTURE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONLY DURI	NG INSPECTION GROUND RUNS, BUT ALSO DURING OPERATION BETWEEN INSPECTIONS. THE IDLE SYSTEM ON THIS FUEL CONTROL UNIT HAS 	ISSUES, WHERE IT REQUIRES CONSIDERABLE ADJUSTING WITHIN A RELATIVELY FEW NUMBER OF OPERATING HOURS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031300024	20030313	00024	CE  	2003	3	13	2003FA0000266    	1	20030212	G	3230	24411003	PIVOT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					MLG	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6623Z	1536 				172RG0240				DURING A ROUTINE INSPECTION IT WAS NOTICED BY THE TECHNICIAN THAT THERE WAS A LARGE AMOUNT OF VERY THIN GREASE SEEPING O	UT FROM AROUND THE MAIN LANDING GEAR ACTUATOR CAPS ON BOTH THE LEFT AND RIGHT SIDES.  THE GEAR ACTUATORS AND PIVOTS WERE	 FOUND TO BE CRACKED IN THE RADIUS AT THE BOTTOM OF THE GEAR SPLINES.  TO PREVENT THIS PROBLEM IT IS SUGGESTED THAT THE 	MAIN LANDING GEAR PIVOTS BE REMOVED FROM THE AIRCRAFT AND INSPECTED EVERY 1000 HOURS.  IT IS ALSO SUGGESTED THAT THE MFG	 OF THIS PART REDESIGN THE PART OUT OF STEEL.  AD ON THE MLG PIVOT ASSEMBLIES HAD BEEN COMPLIED WITH.		1	H	7	1 	3O	3	O	 	3A17    	E286				 
2003031200026	20030312	00026	CE  	2003	3	12	2003FA0000269    	1	20030227	G	5753	0523920	ROLLER          			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					TE FLAP	DAMAGED         	D				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			GL	23		3641 				17258769	L2645527A			RT FLAP, INBOARD AFT FLAP ROLLER, FAILED AND BOUND DURING FLAP RETARCTION. THE RT OUTBOARD FLAP END CONTINUED TO RETRACT	 DEFORMING THE FLAP TO SOME EXTENT.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003031200027	20030312	00027	EA  	2003	3	12	2003FA0000270    	2	20030220	G	7313	25248642	INJECTOR        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	RESTRICTED      	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	15	433ER					172S9166	L3045351A			DURING CRUISE, THE ENGINE SPUTTERED FOR 1-2 SECONDS. THE AIRCRAFT WAS RETURNED TO HOME BASE. A THOROUGH INSPECTION OF TH	E ENGINE AND SYSTEMS WAS MADE, AND THE ONLY OBSERVABLE ITEM WAS A FUEL INJECTOR NOZZLE THAT PRODUCED A MINOR IRREGULAR F	LOW PATTERN DURING TESTING. THE NOZZLES WERE CLEANED THE AIRCRAFT WAS FLOWN WITH NO OPERATIONAL DEFECTS NOTED.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200028	20030312	00028	EA  	2003	3	12	2003FA0000271    	2	20030214	G	7313	63B22623	FLOW DIVIDER    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	STICKING        	B				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	15	482ER		1467 			17280631	L2780951A			DURING GROUND OPERATIONS, THE CREW FELT A ROUGH AND UNSTABLE IDLE. AN INSPECTION WAS MADE OFTHE ENGINE AND SYSTEMS. 2 NO	ZZLES WERE DETERMINED TO HAVE AN IRREGULAR SPRAY PATTERN. AFTER CLEANING, 1 WAS REPLACED. ALSO, THE FUEL FLOW DIVIDER WA	S FOUND TO BE STICKING INTERNALLY. IT WAS REPLACED.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200029	20030312	00029	EA  	2003	3	12	2003FA0000272    	2	20030217	G	7421	REM40E	SPARK PLUG      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FOULED          	C				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	15	437ER	483  	22   			172S8653	L2923351A			DURING STALL MANEUVERS, THE ENGINE HESITATED AND RAN ROUGH WHEN POWER WAS BROUGHT TO IDLE. AS ITEMS WERE BEING INSPECTED	, THE SPARK PLUGS WERE FOUND WITH HEAVY DEPOSITS. THE PLUGS HAD BEEN CLEANED AND TESTED ABOUT 23 HOURS PREVIOUS TO THE E	VENT. TYPICALLY, FOULED SPARK PLUGS ARE NOT A REPORTABLE INCIDENT, BUT THIS ENGINE FUEL CONTROL SYSTEM HAS BEEN THE SUBJ	ECT OF AN AIRWORTHINESS DIRECTIVE REGARDING UNSTABLE IDLE/MIXTURE ISSUES. EVEN THOUGH CONSTANT CHECKING AND ADJUSTMENT O	F THE IDLE MIXTURE/SPEED IS ACCOMPLISHED ON THIS ENGINE, IT QUITE OFTEN DEGRADES TO A VERY RICH IDLE, SHORTLY THEREAFTER	, THEREBY CAUSING SPARK PLUG AND OTHER PROBLEMS AS DESCRIBED ABOVE.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200030	20030312	00030	EA  	2003	3	12	2003FA0000273    	2	20030217	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	ERRATIC         	C				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	15	406ER		635  			172S9156	L3042951A			THE CREW REPORTED THAT THEY WERE EXPERIENCING A VERY SLOW IDLE DURING PRE TAKEOFF IDLE CHECK. IT WAS ADJUSTED. THIS ENGI	NE/FUEL CONTROL COMBINATION HAS BEEN THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE CONCERNING UNSTABLE IDLE AS WELL AS VARIO	US SERVICE BULLETINS ABOUT THE SAME SUBJECT. EVEN WITH CONTINUOUS ADJUSTMENT AND CHECKS, IT IS NOT UNCOMMON TO HAVE MANY	 WRITE UPS PERTAINING TO HIGH/LOW OR LEAN/RICH IDLE PROBLEMS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200031	20030312	00031	EA  	2003	3	12	2003FA0000274    	2	20030216	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	ERRATIC         	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	405ER		521  			172S9155	L3044751A			DURING A PRE TAKEOFF IDLE CHECK, THE ENGINE IDLED VERY SLOW AND BEGAN TO QUIT. THIS ENGINE FUEL CONTROL COMBINATION HAS 	BEEN DIFFICULT TO MAKE MAINTAIN A STABLE IDLE AND REQUIRES A SIGNIFICANT AMOUNT OF BETWEEN INSPECTION ADJUSTMENTS					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200032	20030312	00032	EA  	2003	3	12	2003FA0000275    	2	20030214	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	ERRATIC         	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	433ER		503  			172S9166	L3045351A			DURING THE PRE TAKEOFF IDLE CHECK, THE ENGINE QUIT. THE AIRCRAFT WAS RETURNED TO THE RAMP. AS IS OFTEN THE NEE, THE IDLE	 SPEED AND MIXTURE WERE ADJUSTED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200033	20030312	00033		2003	3	12	2003FA0000276    	4	20030214	G	6113	055032111	BULKHEAD        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					SPINNER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	425ER	1011 				17280646	RL805651A			THE SPINNER AFT BULKHEAD WAS FOUND CRACKED. IT WAS REPLACED WITH A NEW UNIT...						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200034	20030312	00034		2003	3	12	2003FA0000277    	4	20030211	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					SPINNER	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	408ER	965  				172S8642	L2779051A			AFT SPINNER BULKHEAD WAS FOUND CRACKED, IT WAS REPLACED WITH A NEW PART.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200035	20030312	00035	EA  	2003	3	12	2003FA0000281    	2	20030306	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	ERRATIC         	C				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	497ER		168  			17280673	L2013851A			DURING A PRE TAKEOFF IDLE CHECK, THE ENGINE RAN EXTREMELY SLOW. IT WAS ADJUSTED. THIS ENGINE/FUEL CONTROL SYSTEM HAS BEE	N THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE CONCERNING IDLE ANOMALIES.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200036	20030312	00036	EA  	2003	3	12	2003FA0000282    	2	20030306	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	ERRATIC         	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	407ER		401  			172S9157	L3045451A			DURING A PRE TAKE OFF IDLE CHECK, THE ENGINE IDLED VERY SLOWLY. IT WAS ADJUSTED. THIS ENGINE/FUEL CONTROL SYSTEM HAS BEE	N THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE REGARDING ERRATIC IDLE OPERATION.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003031200037	20030312	00037		2003	3	12	2003FA0000283    	4	20030307	G	6113	055032110	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	SPINNER	CRACKED         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	405ER					172S9155	L3044751A	VI23022		DURING INSPECTION, THE REAR SPINNER BULKHEAD WAS FOUND CRACKED. THIS IS A COMMON OCCURANCE WITH THIS PART.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003031200038	20030312	00038	SO  	2003	3	12	2003FA0000284    	1	20030311	G	2820	MS21908D6	ELBOW           			GULSTM	G1159 	GIV         	3980115	SO  										APU FUEL	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	05	1PG	1495 				1374				DURING POST FLIGHT INSPECTION RESIDUAL FUEL WAS NOTICED IN THE LEFT MAIN WHEEL WELL. WHEN SELECTING MAIN BOOST PUMP ON W	ITH APU MASTER SWITCH ON, FUEL WAS NOTICED RUNNING OUT OF THE FLEX HOSE ATTACHED TO THE APU FUEL SHUT OFF VALVE. MECHANI	C FOUND THE ALUMINUM ELBOW CRACKED. ELBOW WAS REPLACED AND LEAK CHECKED OKAY.  PAST EXPERIENCE WITH ANOTHER TYPE AIRCRAF	T HAD SIMILAR CRACKS IN ALUMINUM FITTINGS WHEN STAINLESS STEEL LINES WERE CONNECTED TO THEM. A SERVICE BULLETIN WAS ISSU	ED STATING THAT OVER TORQUE COULD CAUSE THIS CONDITION. NO WORK HAD BEEN DONE IN THIS AREA AND WAS IN THE ORIGINAL PRODU	CTION INSTALLATION.	2	L	7	2 	4F			RT	A12EA   					 
2003040900009	20030409	00009	SW  	2003	4	9	2003FA0000285    	1	20030219	G	6300	R47120252003F	GRIP            			BELL  	47    	47G3B2      	1181029	SW  										MAIN ROTOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	659CD	627  				6719				EDDY CURRENT SHOWED CRACK IN THREAD AREA OF GRIP.						1	G	7	1 	3O			 	2H3     					 
2003040900030	20030409	00030	CE  	2003	4	9	2003FA0000286    	1	20030228	G	5753	55651012	BELLCRANK       			CESSNA	501   	501         	2076603	CE  	PWA   	JD15  	JT15D1A     	 	NE  					RT IB FLAP	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	888MJ	8260 				5010446				RIGHT FLAP BELLCRANK FOLLOW-UP ROD ARM ATTACH POINT WAS CRACKED ON UPPER AND LOWER ARM.  UPON INSPECTION OF OTHER BELLCR	ANKS; FOUND THAT SPACERS WERE MISSING BETWEEN FOLLOW-UP ROD-END AND BELLCRANK FOLLOW-UP ARM.					1	L	7	2 	4F	4	F	 	A27CE   	E25EA				 
2003040900031	20030409	00031	CE  	2003	4	9	2003FA0000287    	1	20030303	G	2421	X610007	CONTACTOR       			CESSNA	172   	172S        	2072439	CE  										ALTERNATOR	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	203KS	30   				172S8856				CONTACTOR FAILS DURING USE, DUE TO IT BEING A CONTINUOUS DUTY RELAY, WAS INTERMITTENT PRIOR TO FAILURE.  (THIS IS FOR TH	E ALTERNATOR OUTPUT TO THE AIRCRAFT BATTERY BUSS.)					1	H	7	1 	3O			NT	3A12    					 
2003040900032	20030409	00032	CE  	2003	4	9	2003FA0000288    	1	20030314	G	2810		BAFFLE          			CESSNA	172   	172H        	2072424	CE  										FUEL TANK	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	4977R	12028				17256331				DURING VISUAL INSPECTION, FOUND FUEL TANK BAFFLE SPOT WELDS BROKEN LOOSE, ALLOWING BAFFLE TO MOVE AROUND FREELY INSIDE F	UEL TANK. CONDITION COULD CAUSE FUEL STARVATION DURING DECENT WITH A LOW FUEL QUANTITY, COULD CAUSE ERRONEOUS FUEL QUANT	ITY INDICATIONS DUE TO INTERFERENCE WITH TRANSMITTER FLOAT. THE FRONT FACE OF BAFFLE IS APPROX 1 INCH BEHIND FUEL TANK F	ILLER PORT. DURING REFUELING PROCESS, IF FUEL NOZZLE IS RELAXED, NOZZLE CONTACTS BAFFLE AND APPLIES EXCESSIVE PRESSURE T	O BAFFLE EVENTUALLY BREAKING SPOT WELDS LOOSE. DURING THE REFUEL PROCESS, DO NOT INSERT FUEL NOZZLE MORE THAN 3 INCHES I	NTO THE FUEL TANK. 	1	H	7	1 	3O			NT	3A12    					 
2003040900033	20030409	00033	CE  	2003	4	9	2003FA0000289    	1	20030314	G	2810		BAFFLE          			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300*       	17022	SO  					FUEL CELLS	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	4977R	12028				56331				DURING VISUAL INSPECTION, FOUND FUEL TANK BAFFLE SPOT WELDS BROKEN LOOSE, ALLOWING BAFFLE TO MOVE AROUND FREELY INSIDE F	UEL TANK. THIS CONDITION COULD CAUSE FUEL STARVATION DURING A DECENT WITH A LOW FUEL QUANTITY AND COULD CAUSE ERRONEOUS 	FUEL QUANTITY INDICATIONS DUE TO INTERFERENCE WITH TRANSMITTER FLOAT.  PROBABLE CAUSE: THE FRONT FACE OF THE BAFFLE IS A	PPROXIMATELY 1 INCH BEHIND FUEL TANK FILLER PORT.  DURING THE REFUELING PROCESS, IF THE FUEL NOZZLE IS RELAXED, THE NOZZ	LE CONTACTS THE BAFFLE AND APPLIES EXCESSIVE PRESSURE TO THE BAFFLE EVENTUALLY BREAKING THE SPOT WELDS LOOSE.  DURING TH	E REFUEL PROCESS, DO NOT INSERT FUEL NOZZLE MORE THAN 3 INCHES INTO THE FUEL TANK. 	1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003040900034	20030409	00034	CE  	2003	4	9	2003FA0000290    	1	20030314	G	2810		BAFFLE          			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300*       	17022	SO  					RT FUEL TANK	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	5134F	12773				17252909				DURING VISUAL INSPECTION, FOUND FUEL TANK BAFFLE SPOT WELDS BROKEN LOOSE, ALLOWING BAFFLE TO MOVE AROUND FREELY INSIDE F	UEL TANK. THIS CONDITION COULD CAUSE FUEL STARVATION DURING A DECENT WITH A LOW FUEL QUANTITY AND COULD CAUSE ERRONEOUS 	FUEL QUANTITY INDICATIONS DUE TO INTERFERENCE WITH TRANSMITTER FLOAT. PROBABLE CAUSE: THE FRONT FACE OF THE BAFFLE IS AP	PROXIMATELY 1 INCH BEHIND FUEL TANK FILLER PORT.DURING THE REFUELING PROCESS, IF THE FUEL NOZZLE IS RELAXED, THE NOZZLE 	CONTACTS THE BAFFLE AND APPLIES EXCESSIVE PRESSURE TO THE BAFFLE EVENTUALLY BREAKING THE SPOT WELDS LOOSE.		1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003040900035	20030409	00035	CE  	2003	4	9	2003FA0000291    	1	20030314	G	2810		BAFFLE          			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300*       	17022	SO  					RT FUEL TANK	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	5203F	12886				17253192				DURING VISUAL INSPECTION, FOUND FUEL TANK BAFFLE SPOT WELDS BROKEN LOOSE, ALLOWING BAFFLE TO MOVE AROUND FREELY INSIDE F	UEL TANK. COULD CAUSE FUEL STARVATION DURING DECENT WITH A LOW FUEL QUANTITY AND COULD CAUSE ERRONEOUS FUEL QUANTITY IND	ICATIONS DUE TO INTERFERENCE WITH TRANSMITTER FLOAT. PROBABLE CAUSE: THE FRONT FACE OF THE BAFFLE IS APPROXIMATELY 1 INC	H BEHIND FUEL TANK FILLER PORT. DURING REFUELING PROCESS, IF FUEL NOZZLE IS RELAXED, NOZZLE CONTACTS BAFFLE AND APPLIES 	EXCESSIVE PRESSURE TO BAFFLE EVENTUALLY BREAKING SPOT WELDS LOOSE. PREVENTATIVE MEASURES: DURING THE REFUEL PROCESS, DO 	NOT INSERT FUEL NOZZLE MORE THAN 3 INCHES INTO THE FUEL TANK. THIS DEFECT WAS FOUND IN 4 OUT OF 8 A/C.	1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003040900036	20030409	00036	CE  	2003	4	9	2003FA0000292    	1	20030314	G	2810		BAFFLE          			CESSNA	172   	R172E       	2072413	CE  	CONT  	IO360 	IO360*      	17025	CE  					FUEL TANK	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	7892N	14797				R1720283				DURING VISUAL INSPECTION, FOUND FUEL TANK BAFFLE SPOT WELDS BROKEN LOOSE, ALLOWING BAFFLE TO MOVE AROUND FREELY INSIDE F	UEL TANK. THIS CONDITION COULD CAUSE FUEL STARVATION DURING A DECENT WITH A LOW FUEL QUANTITY AND COULD CAUSE ERRONEOUS 	FUEL QUANTITY INDICATIONS DUE TO INTERFERENCE WITH TRANSMITTER FLOAT. PROBABLE CAUSE: FRONT FACE OF THE BAFFLE IS APPROX	IMATELY 1 INCH BEHIND FUEL TANK FILLER PORT.DURING REFUELING PROCESS, IF FUEL NOZZLE IS RELAXED, NOZZLE CONTACTS BAFFLE 	AND APPLIES EXCESSIVE PRESSURE TO BAFFLE EVENTUALLY BREAKING SPOT WELDS LOOSE. PREVENTATIVE MEASURES: DURING THE REFUEL 	PROCESS, DO NOT INSERT FUEL NOZZLE MORE THAN 3 INCHES INTO THE FUEL TANK. THIS DEFECT WAS FOUND IN 4 OUT OF 8 A/C.	1	H	7	1 	3O	3	O	 	3A17    	E1CE				 
2003040900037	20030409	00037	SW  	2003	4	9	2003FA0000293    	1	20030316	G	7120	590000509	MOUNT           			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360*       	41514	EA  					ENGINE	BROKEN          	B			NT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	78865	3432 	45   			2880	7425			DURING ANNUAL INSPECTION AND AD 75-09-08 COMPLIANCE, FOUND LOWER RT CORNER WELD JUNCTION FULLY BROKEN AND SEPARATED.  SB	 M20-175 & M20-192 HAD NOT BEEN COMPLETED, THAT WAS DESIGNED TO BE PREVENTED BY INSTALLING GUSSET AT THIS CORNER (P/N 59	0041-1).  MOUNT WAS FOR 180 HP ENGINE AND NOT UPGRADED.				1	L	7	1 	3O	3	O	 	2A3     	E286				 
2003040900038	20030409	00038	SW  	2003	4	9	2003FA0000294    	1	20030316	G	7120	590000509	MOUNT           			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					ENGINE	BROKEN          	B			NT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	9656M	3482 	45   			2880	6701			DURING CONDUCT OF ANNUAL INSPECTION AND AD 75-09-08 COMPLIANCE, FOUND LOWER RH CORNER WELD JUNCTION FULLY BROKEN AND SEP	ARATED.  SB M20-175 & M20-192 HAD NOT BEEN COMPLETED, THAT WAS DESIGNED TO PREVENT BY INSTALLING GUSSET AT THIS CORNER (	P/N 590041-1).  MOUNT WAS FOR 180 HP ENGINE AND NOT UPGRADED.				1	L	7	1 	3O	3	O	 	2A3     	E286				 
2003040900039	20030409	00039	SW  	2003	4	9	2003FA0000295    	1	20030316	G	7120	30505501	MOUNT           			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	1157P	448  				250647	290820R			DURING A SPECIAL INSPECTION, AFTER A PRIOR PROP STRIKE, FOUND THE REAR UPPER CROSSOVER TUBE OFTHE ENGINE MOUNT BENT DOWN	. DOWNLOAD BEND.  AIRCRAFT MODIFIED IAW STC SA5691NM.  REMOVED MOUNT, SENT FOR REPAIR, REINSTALLED MOUNT.					1	L	7	1 	3O	3	O	 	2A3     	E8CE				 
2003040900040	20030409	00040	SW  	2003	4	9	2003FA0000296    	1	20030316	G	7120	30505501	MOUNT           			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	DAMAGED         	B			NT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	1157P	448  				250647	290820R			DURING A SPECIAL INSPECTION, AFTER A PRIOR PROP STRIKE, FOUND THE REAR UPPER CROSSOVER TUBE OFTHE ENGINE MOUNT BENT DOWN	. DOWNLOAD BEND.  AIRCRAFT MODIFIED PER STC SA5691NM.  REMOVED MOUNT, SENT TO MFG. FOR REPAIR, REINSTALLED MOUNT.					1	L	7	1 	3O	3	O	 	2A3     	E8CE				 
2003040900041	20030409	00041	NM  	2003	4	9	2003FA0000297    	1	20030317	G	5712	41513017R	RIB             			UNIVAR	415   	A2AALON     	0540104	NM  	CONT  	C90   	C90*        	17009	SO  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5638F	2529 				A238				LIGHT SURFACE CORROSION FOUND IN BOTH STUB WINGS IN  CENTER SECTION. BOTTOM SKINS, UNDER SKIN STIFFNERS, A COUPLE SPOTS 	ON RIBS, AND BETWEEN REAR SPAR AND REAR RIB P/N 415-1307RINSPECTION WAS IN COMPLIANCE WITH AD 2002-26-02.					1	L	7	1 	3O	3	O	 	A787    	E252				 
2003040900042	20030409	00042	SW  	2003	4	9	2003FA0000299    	1	20030225	G	3230	B10006	COUPLING        			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360*       	41514	EA  					MLG MOTOR	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	111JP					690078				B100-06 RUBBER DRIVE COUPLING BETWEEN LANDING GEAR MOTOR AND TRANSMISSION, ABSORBS SHOCK WHEN LANDING GEAR REACHES ITS L	IIT, THIS IS THE ONLY CONNECTION BETWEEN TRANSMISSION AND GEAR LINKAGE, WHEN THIS PART FAILED, YOU CANNOT PERFORM ANY GE	AR EXTENSION, ELECTRICALLY OR MECHANICALLY.  RECOMMEND TO REPLACE EVERY 200 HOURS TO COINCIDE WITH 200 HOUR TRANSMISSION	 GEAR BACKLASH INSPECTION AND SB M20-190.			1	L	7	1 	3O	3	O	 	2A3     	E286				 
2003040900043	20030409	00043	SO  	2003	4	9	2003FA0000300    	1	20030222	G	3310	GS23614	LIGHT           			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540*       	41532	EA  					CABIN	BURNED OUT      	B			SL5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	2332U	25   				287911298				SPT GLOW STRIPS, INSTALLED CUSTOMER SUPPLIED ELECTROLUMINESCENT LAMPS UNDER INSTRUMENT PANEL GLARE SHIELD, WITHIN 25 HOU	RS OF AIRCRAFT OPERATION, BOTH LIGHT FAILED.  DURING INSPECTION OF THE LAMPS, TURNED POWER ON AND BOTH LAMPS SPARKED AND	 SMOKE CAME FROM AREA OF PLASTIC CONNECTORS.  REMOVED BOTH LAMPS.  BOTH FAILED IN SAME LOCATION WINT IN MINUTES AFTER IN	STALLATION.  SUGGEST THESE LAMPS NOT BE USED OR INSTALLED IN ANY AIRCRAFT UNTIL MFG CAN FIND A BETTER CONNECTOR.			1	L	7	1 	3O	3	O	 	2A13    	E295				 
2003040900044	20030409	00044	EA  	2003	4	9	2003FA0000301    	2	20030305	G	8520	IO360A3B6D	CRANKCASE       			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	NR 2 CYLINDER	CRACKED         	B			DINR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1084V		777  			241131	L2253851A	DY2456A		(STC SA4529NM 3 BLADE HARTZELL) AT 777 TSO OF THE ENGINE, THE CRANKCASE WAS FOUND CRACKED THROUGH THE NR 2 CYLINDER MOUN	TING PAD AREA AND LEAKING OIL.  THE CASE WAS NOT REPAIRABLE.  THIS IS THE 2ND TIME THIS AIRCRAFT ENGINE PROPELLER COMBIN	ATION HAS CRACKED A CASE.  PREVIOUS TSO WAS ONLY 689.				1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P25EA	 
2003040900045	20030409	00045	GL  	2003	4	9	2003FA0000302    	3	20030305	G	6110	IO360A3B6D	CASE            			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	CRACKED         	B			DINR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1084V	2370 	689  			241131	L2253851A	DY2456A		AT 689 HOUR TSO OF ENGINE AND 689 HOURS SINCE REMOVAL OF 2 BLADE PROPELLER AND INSTALLATION OF 3 BLADE PROPELLER IAW STC	.   CASE CRACKED CAUSING AN OIL LEAK.  THE CASE WAS NOT REPAIRABLE.  					1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P25EA	 
2003040900046	20030409	00046	CE  	2003	4	9	2003FA0000305    	1	20030319	G	2822	414000103	PUMP            			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					INJECTOR	SHEARED         	G				C				ABORTED TAKEOFF         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			SW	17	9486S	2539 				D8181				ENGINE QUIT DURING TAKEOFF. THE AIRCRAFT WAS SUBSTANTIALLY DAMAGED.  INVESTIGATION REVEALED A SHEARED DRIVE SHAFT FOR TH	E ENGINE DRIVEN FUEL PUMP (INJECTOR PUMP).  DISASSEMBLY REVEALED FOD (A SMALL PIECE OF WIRE) JAMMED IN THE ROTOR/VANE.  	FURTHER INVESTIGATION OF OTHER COMPONENTS OF THE AIRCRAFT FUEL SYSTEM REVEALED THAT THE LOW PRESSURE FUEL PUMP HAD FAILE	D INTERNALLY AND FRAGMENTS, INCLUDING PIECES OF THE WIRE-LIKE ROTOR PINS, HAD FLOWED TO THE INJECTOR PUMP.  NOTE: THE IN	JECTOR PUMP HAD RECENTLY BEEN REPAIRED DUE TO FAILURE CAUSED BY DAMAGED VANES/ROTOR. SUBMITTER SURMISES THAT THE LAST IN	JECTOR FAILURE WAS ALSO DUE TO FOD FROM THE SAME FAILED LOW PRESSURE PUMP.	1	L	7	1 	3O	3	O	 	3A15    	E7CE				 
2003040900047	20030409	00047	CE  	2003	4	9	2003FA0000306    	1	20030320	G	2810		BAFFLE          			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300*       	17022	SO  					FUEL CELLS	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	5241F	11723				17253322				DURING VISUAL INSPECTION, FOUND FUEL TANK BAFFLE SPOT WELDS BROKEN LOOSE, ALLOWING BAFFLE TO MOVE AROUND FREELY INSIDE F	UEL TANK. THIS CONDITION COULD CAUSE FUEL STARVATION DURING A DECENT WITH A LOW FUEL QUANTITY AND COULD CAUSE ERRONEOUS 	FUEL QUANTITY INDICATIONS DUE TO INTERFERENCE WITH THE TRANSMITTER FLOAT. PROBABLE CAUSE: THE FRONT FACE OF THE BAFFLE I	S APPROXIMATELY 1INCH BEHIND THE FUEL TANK FILLER PORT. DURING THE FUELING PROCESS, IF THE FUEL NOZZLE IS RELAXED, THE N	OZZLE CONTACTS THE BAFFLE AND APPLIES EXCESSIVE PRESSURE TO THE BAFFLE, EVENTUALLY BREAKING THE SPOT WELDS LOOSE. PREVEN	TATIVE MEASURES: DURING THE REFUELING PROCESS, DO NOT INSERT THE FUEL NOZZLE MORE THAN 3 INCHES INTO THE FUEL TANK.	1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003032400009	20030324	00009	EU  	2003	3	24	2003FA0000307    	1	20030318	G	3260	803682	PROXIMITY SWITCH			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					MLG	FAILED          	B				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SW	11	198FJ	29   				198				AFTER TAKEOFF WHEN THE GEAR HANDLE WAS PLACED UP ALL THREE GREEN LIGHTS EXTINGUISHED. A LOUD METALLIC GRINDING TYPE NOIS	E WAS NOTED AFTER SEVERAL SECONDS (10-15) THE NOISE STOPPED AND THE GREEN LIGHT FOR THE NOSE GEAR ILLUMINATED. AT THIS T	IME THE GEAR HANDLE WAS UP THE NOSE GEAR INDICATED DOWN, THE LT & RT MAIN GEAR DOORS WERE OPEN. WHEN THE GEAR HANDLE WAS	 PLACED DOWN NO ACTIVITY WAS NOTED VISUALLY OR NOISE BY THE GEAR, APPROX. 45-75 SECONDS LATER THE LT & RT MAIN GEAR DOWN	 LOCK GREEN LIGHTS ILLUMINATED AND THE RED DOOR LIGHTS EXTINGUISHED.		2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2003040900048	20030409	00048	EA  	2003	4	9	2003FA0000308    	2	20030311	G	7322	2576532	CARBURETOR      			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE	SCORED          	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	15	701ER	1142 				2844053	L2995051A			THE CREW REPORTED A ROUGH/IRREGULAR SOUND FROM THE ENGINE IN CRUISE. THE CREW RETURNED TO THE RAMP. IT IS NOT UNCOMMON F	OR THIS SITUATION TO OCCUR NOT ONLY DURING INSPECTION GROUND RUNS, BUT ALSO DURING OPERATION BETWEEN INSPECTIONS. A COMM	ON SOURCE OF PROBLEMS WITH THIS FUEL CONTROL IS THE MIXTURE VALVE. THIS VALVE BECOMES SCORED AND THEN INACURATE IN ITS F	UNCTION. THERE IS A PROCEDURE FOR LAPPING THIS VALVE SURFACE.			1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003040900049	20030409	00049	EA  	2003	4	9	2003FA0000309    	2	20030314	G	7322	25765362	CARBURETOR      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	15	432ER					17280652	L2776751A			THE CREW REPORTED A ROUGH IDLE DURING GROUND OPERATION. THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF AN AD R	EGARDING UNSTABLE IDLE/MIXTURE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONLY DURING INSPECTION GROUND 	RUNS, BUT ALSO DURING OPERATION BETWEEN INSPECTIONS. THE IDLE SYSTEM ON THIS FUEL CONTROL UNIT HAS ISSUES, WHERE IT REQU	IRES CONSIDERABLE ADJUSTING WITHIN A RELATIVELY FEW NUMBER OF OPERATING HOURS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003040900050	20030409	00050	EA  	2003	4	9	2003FA0000310    	2	20030314	G	7322	25765362	CARBURETOR      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	C				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	15	420ER					17280634	L2784651A			THE CREW REPORTED A ROUGH IDLE DURING GROUND OPERATION. THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF AN AIRW	ORTHINESS DIRECTIVE REGARDING UNSTABLE IDLE/MIXTURE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONLY DURI	NG INSPECTION GROUND RUNS, BUT ALSO DURING OPERATION BETWEEN INSPECTIONS. THE IDLE SYSTEM ON THIS FUEL CONTROL UNIT HAS 	ISSUES WHERE IT REQUIRES CONSIDERABLE ADJUSTING WITHIN A RELATIVELY FEW NUMBER OF OPERATING HOURS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003040900051	20030409	00051	EA  	2003	4	9	2003FA0000311    	2	20030317	G	7322	25765362	CARBURETOR      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	15	420ER					17280634	L2784651A			THE CREW REPORTED A ROUGH IDLE DURING GROUND OPERATION. THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF AN AIRW	ORTHINESS DIRECTIVE REGARDING UNSTABLE IDLE/MIXTURE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONLY DURI	NG INSPECTION GROUND RUNS, BUT ALSO DURING OPERATION BETWEEN INSPECTIONS. THE IDLE SYSTEM ON THIS FUEL CONTROL UNIT HAS 	ISSUES, WHERE IT REQUIRES CONSIDERABLE ADJUSTING WITHIN A RELATIVELY FEW NUMBER OF OPERATING HOURS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003040900052	20030409	00052	EA  	2003	4	9	2003FA0000312    	2	20030320	G	7322	25765362	CARBURETOR      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	444ER	1684 				172S8659	L2932851A			THE CREW REPORTED A ROUGH ENGINE DURING VARIOUS PHASES OF THE PRE-TAKE OFF RUN UP. AFTER TROUBLESHOOTING AND TESTING, TH	E FUEL CONTROL, FLOW DIVIDER AND ONE FUEL NOZZLE WERE REPLACED WITH SERVICEABLE PARTS. THIS ENGINE/FUEL CONTROL COMBINAT	ION HAS BEEN THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003040900053	20030409	00053	EA  	2003	4	9	2003FA0000313    	2	20030317	G	7322	25765362	CARBURETOR      			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	703ER					2844057	L3013951A			THE CREW REPORTED A ROUGH IDLE DURING GROUND OPERATION. THIS ENGINE/AIRCRAFT COMBINATION HAS BEEN THE SUBJECT OF AN AD R	EGARDING UNSTABLE IDLE/MIXTURE ISSUES. IT IS NOT UNCOMMON FOR THIS SITUATION TO OCCUR NOT ONLY DURING INSPECTION GROUND 	RUNS, BUT ALSO DURING OPERATION BETWEEN INSPECTIONS. THE IDLE SYSTEM ON THIS FUEL CONTROL UNIT HAS ISSUES, WHERE IT REQU	IRES CONSIDERABLE ADJUSTING WITHIN A RELATIVELY FEW NUMBER OF OPERATING HOURS.			1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003040900054	20030409	00054	CE  	2003	4	9	2003FA0000314    	1	20030320	G	3230	10138800511	CONTROL VALVE   			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  						INOPERATIVE     	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			SW	01	36GS	2579 				BB1298				DURING APPROACH TO LANDING AT ABQ THE GEAR WOULD NOT EXTEND IN NORMAL OPERATION.  LANDING GEAR HYDRAULIC POWER PACK MOTO	R WOULD RUN WHEN HANDLE IN DOWN POSITION BUT GEAR WOULD NOT MOVE.  EXTENDED GEAR WITH EMERGENCY SYSTEM.  INSTALLED NEW S	OLENOID VALVE AND GEAR OPERATED NORMALLY.				1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003040900055	20030409	00055	CE  	2003	4	9	2003FA0000315    	1	20030320	G	3246	50300010133	WHEEL           			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6*        	52043	EA  					MLG	BROKEN          	G				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	01	676J	9197 				LW179				THE INBOARD WHEEL HALF FAILED FROM ONE BOLT HOLE AND THE CRACK WALKED ALL THE WAY AROUND THE WHEEL HALF.  THE WHEEL AXLE	 NUT WAS THE ONLY THING THAT KEPT THE WHEEL ON THE AXLE.  THIS HAPPENED DURING TAXI TO TAKEOFF.					1	L	7	2 	3T	3	T	 	3A20    	E2NE				 
2003032400010	20030324	00010	EU  	2003	3	24	2003FA0000316    	1	20030318	G	3260	803682	PROXIMITY SWITCH			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					MLG	FAILED          	B				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			SW	11	198FJ	29   				198				AFTER TAKEOFF WHEN THE GEAR HANDLE WAS PLACED UP ALL THREE GREEN LIGHTS EXTINGUISHED. ALOUD METALLIC GRINDING TYPE NOISE	 WAS NOTED AFTER SEVERAL SECONDS 10-15 THE NOISE STOPPED AND THE GREEN LIGHT FOR THE NOSE GEAR ILLUMINATED. AT THIS TIME	 THE GEAR HANDLE WAS UP TH NOSE GEAR INDICATED DOWN, THE LT & RT MAIN GEAR DOORS WERE OPEN. WHEN THE GEAR HANDLE WAS PLA	CED DOWN NO ACTIVITY WAS NOTED VISUALLY OR NOISE BY THE GEAR, APPROX. 45-75 SECONDS LATER THE LT & RT MAIN GEAR DOWN LOC	K GREEN LIGHTS ILLUMINATED AND THE RED DOOR LIGHTS EXTINGUISHED.		2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2003040900056	20030409	00056	CE  	2003	4	9	2003FA0000317    	1	20030321	G	2810	0700099108	LINE            			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					FUEL SYSTEM	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	97832	12448				18267214				FUEL LINE FROM FUEL SELECTOR VALVE TO FUEL STRAINER.  RUDDER PEDALS HAD WORN A DEEP GROOVE IN FUEL LINE.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003040900057	20030409	00057	SO  	2003	4	9	2003FA0000318    	1	20030307	G	2730	31713	CONTROL CABLE   			MAULE 	M5    	M5235C      	5460135	SO  	LYC   	O540  	O540*       	41532	EA  					ELEVATOR	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	6170M	844  				7179C				FOUND ELEVATOR DOWN CABLE AT F/W BELCRANK WITH BROKEN STRAND AND WEARING AT POINT OF CONTACT.  FOUND WHILE COMPLYING WIT	H MFG SB NR 64, DURING ANNUAL INSPECTION. REPLACED CABLE WITH NEW PART.					1	H	7	1 	3O	3	O	 	3A23    	E295				 
2003040900058	20030409	00058	GL  	2003	4	9	2003FA0000319    	1	20030306	G	2510	5049074058013	SEAT BELT       			CIRRUS	SR    	SR20        	05628AJ	GL  										COCKPIT	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	06										THIS ISSUE INVOLVES SEATBELTS INSTALLED ON AIRCRAFT.  THE TENSIONER  BAR ON LAP BOLT WILL NOT HOLD TENSION ON BELTS ONCE	 TIGHTENED.  BELTS ARE LOOSENING DUE TO VIBRATION IN FLIGHT.  THE TENSION BAR IS SMOOTH, SO IT IS NOT HOLDING TENSION.  	REDESIGN TENSIONER BAR.				1	L	7	1 	3O			NT	A00009CH					 
2003040900059	20030409	00059	EA  	2003	4	9	2003FA0000320    	2	20030322	G	7322	25765362	CARBURETOR      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	C				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	497ER					17280673	L2013851A			DURING PRE TAKEOFF GROUND OPERATIONAL CHECK, THE IDLE SPEED WAS ONLY ABOUT 400 RPM.  IT WAS ADJUSTED ALONG WITH THE MIXT	URE. THIS ENGINE FUEL CONTROL COMBINATION WAS THE SUBJECT OF AN AIRWORTHINESS DIRECTIVE FOR THIS PROBLEM. THE VARIOUS OT	HER COMPONENTS OF THIS FUEL CONTROL SYSTEM ALSO HAVE RELIABILITY ISSUES RANGING FROM SCORING OF THE MIXTURE CONTROL PLAT	ES TO IMPROPER MANIFOLD VALVE OPERATION. OFTEN THE INACCURATE OPERATION OF THIS SYSTEM RESULTS IN AN EXTREMELY RICH MIXT	URE WHICH CAUSES MANY SPARK PLUG FOULING PROBLEMS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003040900060	20030409	00060	CE  	2003	4	9	2003FA0000321    	1	20030301	G	5610	101384502522	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	09	63791	814  				BB1100				CO-PILOT WINDSHIELD CRACKED DURING CRUISE.  THIS UNIT WAS INSTALLED ON 01/16/2002 AT 7294.2 TT A/F.  CURRENT INSPECTION 	REQUIREMENT CALLS FOR A WINDSHIELD SCREW TORQUE CHECK EACH 200 HOURS.  OUR EXPERIENCE HAS SHOWN THAT SOON AFTER RETORQUE	ING THE WINDSHIELD WILL FAIL.  SUGGEST THAT MFG MODIFY THE RETORQUE REQUIREMENT AT EACH 200 HOUR.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003040900064	20030409	00064	EA  	2003	4	9	2003FA0000328    	2	20030310	G	8530	70275	CYLINDER HEAD   			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	D			DZXE	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	64551					17275577	L1384439A			CYLINDER CRACKED IN EXHAUST PORT AREA OF THE HEAD.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003040900065	20030409	00065	EU  	2003	4	9	2003FA0000329    	1	20030226	G	2720		HORN            			GROB  	G103  	G103A       	1660202	EU  										ELEVATOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	1202Z	4500 				3615				ON ANNUAL INSPECTION FOUND ELEVATOR HORN LOOSE.  HORN IS BOLTED TO TWO INBOARD SOLID RIBS OF ELEVATOR.  IT IS NOW BROKEN	 LOOSE FROM THESE TWO RIBS.  THIS IS A VERY SERIOUS CONDITION, NEEDS TO BE CHECKED.  THIS AIRCRAFT IS STORED OUTSIDE.					1	K	0	0 	  			RC	G39EU   					 
2003040900066	20030409	00066	EU  	2003	4	9	2003FA0000330    	1	20030228	G	5522		SKIN            			GROB  	G103  	G103A       	1660202	EU  										LT ELEVATOR	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	1202Z	4500 				3615				ON ANNUAL INSPECTION, FOUND LEFT ELEVATOR LOWER SKIN DELAMINATED IN TWO PLACES.  TOW BLISTERS APPROXIMATELY ONE FOOT LON	G.  ELEVATOR WAS REMOVED AND SENT OUT FOR REPAIR.					1	K	0	0 	  			RC	G39EU   					 
2003040900067	20030409	00067	EU  	2003	4	9	2003FA0000331    	1	20030301	G	3210		LEG ASSY        			LET   	L13   	L13BLANIK   	1360306	EU  										MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	11	244PT	1500 				026355				LEG THAT HOLDS MLG FORK ASSEMBLY.  HAD STRAIGHT BREAK.  APPEARS TO BE FATIGUE FAILURE.  MAY HAVE BEEN CAUSED BY TAKING O	FF FROM GRASS AT ANGLE TO PAVED RUNWAY AND CONSTANT HITTING OF 2-3 INCHES NEWLY PAVED RUNWAY.  RECOMMEND TAKING OFF ON P	AVED RUNWAY, HAND PULL GLIDER OVER BUMP.				1	K	0	0 	  			 	G24EU   					 
2003040900068	20030409	00068	EA  	2003	4	9	2003FA0000332    	2	20030317	G	8550	STD1339	PLUG            			PIPER 	PA31  	PA31300     	7103104	SO  	LYC   	O540  	IO540M1A5   	41532	EA  					OIL PUMP BODY	UNDERTORQUED    	B				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SO	06	411CF	60   				31339	RL1461648A			COMPLIANCE WITH MFG SB 555, OIL PUMP BODY PLUG INSPECTION, BOTH ENGINES CHECKED AND FOUND UNDERTORQUED.  RETORQUED IAW S	B.  RETURNED TO SERVICE WITHOUT INCIDENT.  (SHOULD MAKE MANDITORY AD)					1	L	7	2 	3O	3	O	 	A20SO   	1E4				 
2003040900069	20030409	00069	EA  	2003	4	9	2003FA0000333    	2	20030327	G	7322	25765362	CARBURETOR      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INOPERATIVE     	C				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	478ER					17280623	L1635851A			DURING PRE-TAKEOFF CHECK, THE CREW REDUCED THE THROTTLE TO CHECK THE IDLE SPEED. THE ENGINE WOULD ALMOST QUIT EACH TIME 	IT WAS ATTEMPTED. THIS ENGINE/FUEL CONTROL COMBINATION REQUIRES SUBSTANTIAL ADJUST FOR A VERY FEW HOURS FLOWN.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003040900070	20030409	00070		2003	4	9	2003FA0000334    	4	20030327	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	PROPELLER	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	408ER					172S8642	L2779051A	UG23005		DURING AN INSPECTION, THE SPINNER WAS FOUND CRACKED. ALL MFG. SERVICE INFORMATION REGARDING THIS PROBLEM HAD BEEN COMPLI	ED WITH.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003040900071	20030409	00071	EA  	2003	4	9	2003FA0000335    	2	20030327	G	7322	25765362	CARBURETOR      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	404ER					172S9154	L3044651A			DURING PRE TAKEOFF IDLE CHECK, THE SPEED WAS ONLY 300-500 RPM.  THIS ENGINE/FUEL CONTROL COMBINATION REQUIRES SUBSTANTIA	L ADJUSTMENT OVER A FEW HOURS TYPICALLY.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003040900072	20030409	00072		2003	4	9	2003FA0000336    	4	20030327	G	6113	05503673	SPINNER         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	425ER					17280646	RL805651A	TL046		DURING AN INSPECTION, THE SPINNER WAS FOUND CRACKED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003040900073	20030409	00073	EA  	2003	4	9	2003FA0000337    	2	20030320	G	7322	25765362	CARBURETOR      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	472ER					17280669	L2734251A			DURING NORMAL OPERATIONS, THE ENGINE WOULD SPUTTER AND RUN VERY IRREGULARLY AT IDLE. AFTER ROUTINE IDLE SPEED/MIXTURE AD	JUSTMENT THE ENGINE RAN PROPERLY. THIS ENGINE/FUEL CONTROL COMBINATION REQUIRES ADJUSTMENT OF THE IDLE SPEED/MIXTURE MOR	E OFTEN THAN TYPICALLY REQUIRED IN THE GA TYPE AIRCRAFT.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003040900075	20030409	00075	CE  	2003	4	9	2003FA0000339    	1	20030307	G	3230	358100757	BUSHING         			BEECH 	P35   	P35         	1151530	CE  	CONT  	O470  	IO470*      	17026	SO  					WORM DRIVESHAFT	BROKEN          	B			SNSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	9603Y					D7115				THE BUSHINGS AT THE HANDLE END OF THE WORM DRIVE SHAFT WERE SEVERELY WORN AND BROKEN WHICH WOULD ALLOW THE SHAFT TO MOVE	 BACK AND FORTH AND OVER A PERIOD OF TIME THE LOCKNUT BACKED OFF FAR ENOUGH TO ALLOW THE WORM DRIVE SHAFT TO MOVE BACK A	ND FORTH A SIGNIFICANT AMOUNT WHICH WOULD CAUSE A BINDING IN THE SECTOR TO WORM GEAR CONTACT AREA.  THIS IS WHY THE MOTO	R LOCKED UP AND THE EMERGENCY GEAR SYSTEM DID NOT ALLOW THE GEAR TO BE MOVED IN EITHER DIRECTION.			1	L	7	1 	3O	3	O	RT	3A15    	E1CE				 
2003040900076	20030409	00076	EA  	2003	4	9	2003FA0000340    	2	20030307	G	8530	LW15318	CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 2	CRACKED         	B			CSLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	124FR	650  				17273814	RL729876T			ENGINE DISASSEMBLED DUE TO BIRD STRIKE.  FOUND NR 2 CYLINDER BARREL CRACKED AT JOINT OF BARREL AND HEAD.  CRACK IS APPRO	XIMATELY 2 INCHES LONG, LOCATED RADIALLY AROUND BORE.  CYLINDER SHOWS EVIDENCE OF LEAKAGE EXTERNALLY IMMEDIATELY BELOW F	INNED AREA OF HEAD.  SUGGEST CHECKING CYLINDERS FOR LEAKAGE AT INTERSECTION OF BARREL AND HEAD AT  REGULAR INSPECTION.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003040900077	20030409	00077		2003	4	9	2003FA0000341    	4	20030308	G	2561	KS9P01018	LIFE VEST       																		FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE PRESERVER FAILED.  MANUFACTURER RECOMMENDED PSI CELL TEST.  DOM:NOV 1980																			 
2003040900078	20030409	00078	EU  	2003	4	9	2003FA0000342    	1	20030319	G	3610		SHAFT           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					DRY AIR PUMP	DAMAGED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF					85002	L2802448A			DURING FLIGHT AIR PRESSURE INDICATED ZERO OUTPUT.  MAINTENANCE TECH FOUND BROKEN SHAFT ON DRY AIR PUMP.  PROBABLE CAUSE:	 VIBRATION FROM ENGINE.  C/A:  MFG TO INVESTIGATE PUTTING STIFFER LORD MOUNTS ON ENGINE FRAME TO REDUCE ENGINE VIBRATION	 TO OTHER COMPONENTS.				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003040900079	20030409	00079	EA  	2003	4	9	2003FA0000343    	2	20030220	G	7314		PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					FUEL SYSTEM	FAILED          	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	07	864AF	643  				85004	L2826348A			DURING GROUND RUN FUEL PRESSURE READINGS WERE HIGH AND UNABLE TO ADJUST PRESSURES.						1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003040900080	20030409	00080	EU  	2003	4	9	2003FA0000345    	1	20030320	G	3230	120A9491105AV	RELAY           			GROB  	120   	G120A       	1660208	EU  										MLG	DAMAGED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	867AF	395  				85007				DURING PROGRESSIVE INSPECTION FOUND BAD RELAY AND DIODES BOARD HAD OPEN ON PC BOARD BETWEEN PC BOARD AND  GEAR CONTROL R	ELAY.					1	L	7	1 	3O			RT	A49CE   					 
2003041000001	20030410	00001	EU  	2003	4	10	2003FA0000346    	1	20030317	G	3260	BAD10500	UPLOCK          			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					MLG	INOPERATIVE     	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	07	865AF					85005	L2826448A			DURING FLIGHT GEAR ON LT SIDE WOULD NOT RELEASE.  FLIGHT CREW HAD TO PREFORM EMERGENCY EXTENSION AND PULL G`S TO RELEASE	 GEAR.  TROUBLE SHOOT SYSTEM AND FOUND LEFT GEAR UPLOCK WOULD NOT RELEASE GEAR.  REPLACED UPLOCK ASSY.  RIGGING WAS OUT 	OF LIMIT.  PROBABLE CAUSE IS DESIGN OF UPLOCK ASSY INSTALLATION.  RECOMMENDATION IS TO C/W SB.				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003041000002	20030410	00002	EU  	2003	4	10	2003FA0000347    	1	20030318	G	2823	120A6229	SELECTOR VALVE  			GROB  	120   	G120A       	1660208	EU  										FUEL SYSTEM	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	692  				85001				DURING A PROGRESSIVE INSPECTION, TECH FOUND THE FUEL SELECTOR VALVE LOOSE AND HARD TO TURN.  PROBABLE CAUSE IS INTERNAL 	FAILURE.					1	L	7	1 	3O			RT	A49CE   					 
2003041000003	20030410	00003	EU  	2003	4	10	2003FA0000348    	1	20030320	G	2913	X030001B	PUMP            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					HYD SYSTEM	OVERHEATED      	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF					85007				THE HYDRAULIC PUMP CIRCUIT BREAKER KEEPS POPPING WHILE PUMP BUILDS UP PRESSURE.  NO WARNING LIGHT COMES ON TO INDICATE P	UMP IS GETTING HOT.  HOWEVER WHEN YOU TOUCH THE PUMP WITH YOUR HAND IT IS HOT.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003041000004	20030410	00004	EA  	2003	4	10	2003FA0000349    	2	20030401	G	7414	D4LN3000	MAGNETO         			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	ENGINE	LOOSE           	C				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SO	17		1950 	180  			243306	L2613451A	930320		AIRCRAFT EXPERIENCED ENGINE FAILURE AFTER TAKE-OFF, PILOT LANDED AIRCRAFT WITH MAIN LANDING GEAR RETRACTED. AIRCRAFT REC	IEVED CONSIDERABLE DAMAGE FROM LANDING. ENGINE UPPER COWLING REMOVED FOR INVESTIGATION OF ENGINE FAILURE. DURING INSPECT	ION OF ENGINE FOUND MAGNETO DISENGAGED FROM ACCESSORY CASE, ALL MOUNTING HARDWARE MISSING. REVIEW OF MAINTENANCE LOGBOOK	S REVEALED AD 96-12-07 IMPULSE COUPLING INSPECTION COMPLIED 06 APRIL, 2001. MAGNETO HAS 180.1 HRS SINCE LAST INSPECTION.	 OIL CHANGE COMPLETED 27 JANUARY, 2003.		1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2003041000007	20030410	00007	GL  	2003	4	10	2003FA0000352    	1	20030301	G	2731		TAB             			BLANCA	1419  	14193       	1220406	GL  	CONT  	O470  	IO470*      	17026	SO  					ELEVATOR TRIM	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	416MB					4225				ELEVATOR TRIM TAB  BECAME TIGHT AND HARD TO USE, AND FINALLY IT BECAME INOPERATIVE.  IT IS VERY DIFFICULT TO GET TO THIS	 PROBLEM, SINCE THE PART CONTAINING THE MOVABLE TRIM TAB IS ENCASED IN A TIGHT TUBE AND IT IS ABOVE THE OVERHEAD AND BEL	OW THE OUTER FABRIC SKIN  OF THE AIRPLANE IN THE COCKPIT AREA.				1	L	7	1 	3O	3	O	 	1A3     	E1CE				 
2003041000008	20030410	00008	GL  	2003	4	10	2003FA0000353    	1	20030301	G	2731		TAB             			BLANCA	1419  	14193       	1220406	GL  										ELEVATOR TRIM	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07										ELEVATOR TRIM TAB SYSTEM BECAME DIFFICULT TO OPERATIVE.  IT BINDS.  IT WAS DETERMINED THAT THE ORIGINAL LUBRICANT HAD CO	NGEALED IN THE LONG TRIM TAB UNIT, FROM COCKPIT TO TAIL.  THIS RESULTED IN AN NONFUNCTIONAL TRIM TAB.  THE TRIM IS ENCAS	ED INSIDE A LONG TUBE FROM COCKPIT HANDLE TO TAIL SECTION.  IT IS ATTACHED TO AND JUST UNDERNEATH THE UPPER FUSELAGE.  E	XCESSIVE FRICTION INSIDE THIS TUBE CAUSED THE PROBLEM.  LUBRICATE IS THE ANSWER.			1	L	7	1 	3O			 	1A3     					 
2003041000012	20030410	00012		2003	4	10	2003FA0000358    	4	20030328	G	2310		ANTENNA         			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					VERTICAL STAB	SEPARATED       	E			ZESA	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			EA	03	550KL	939  				5500844				THE HF ANTENNA BROKE OFF DURING FLIGHT, FROM THE VERTICAL STABILIZER TENSION UNIT.  THE ANTENNA CABLE SLAPPED AGAINST TH	E TAILCONE, CHIPPING PAINT.  NO STRUCTURAL DAMAGE FOUND.					1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2003041000013	20030410	00013	CE  	2003	4	10	2003FA0000359    	1	20030214	G	5312		FIREWALL        			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	CRACKED         	B			LC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	26499					17280730				DURING A PHASE 1 INSPECTION FOUND A CRACK IN THE FIREWALL AT THE LOWER ROW OF RIVETS ATTACHING THE BATTERY BOX TO THE FI	REWALL.   UPON REMOVAL OF BOX FOR REPAIR FOUND 2ND CRACK UNDER THE OUTBOARD VERTICAL ROW OF RANGE IN MFG SB FIREWALL INS	PECTION.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003041000014	20030410	00014	CE  	2003	4	10	2003FA0000360    	1	20030401	G	2421	E3FF103000AA	ALTERNATOR      			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	SEIZED          	D				E				ENGINE SHUTDOWN         				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			SO	09	6246B		398  			21062721	293993R			UPON FIRST START OF THE DAY A LOUD SQUEALING NOISE WAS HEARD ALONG WITH WHITE SMOKE EXITING THE COWL FLAPS AND THE PILOT	 SHUT DOWN ENGINE.  UPON REMOVING THE COWLING IT BECAME OBVIOUS THAT THE ALTERNATOR HAD SEIZED AND THAT THE BELT WAS BAD	LY BURNED. LATER EXAMINATION BY THE MECHANIC REVEALED THAT A DIODE BLOCK SCREW HAD VIBRATED LOOSE AND WEDGED BETWEEN THE	 ROTOR AND STATOR AFTER SHUT DOWN FROM THE PREVIOUS DAYS FLIGHT.			1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003041000015	20030410	00015		2003	4	10	2003FA0000361    	4	20030331	G	2562		BATTERY PACK    			BEECH 	58    	58          	1152740	CE  										ELT	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	957PC	142  				TH2023				DURING 100 HR/ANNUAL INSPECTION ELT TEST, IT WAS NOTED THAT THE ELT CASE WAS CRACKED IN THE BATTERY PORTION AND WHAT APP	EARED TO BE CORROSION WAS COMING OUT. THE BATTERY WAS SEPARATED FROM THE ELT. AT LEAST 2 OF THE 6 BATTERIES HAD LEAKED A	CID WHICH HAD EATEN INTO THE PLASTIC CASE. THE COMPLETE ELT WAS RETURNED TO THE MANUFACTURE FOR REPAIR.  NO DAMAGE WAS D	ONE TO AIRCRAFT, THE ACID NEVER CAME IN CONTACT WITH AIRFRAME COMPONENTS.  THE BATTERY PACK HAD AN EXPIRATION DATE OF JU	LY 2004, WO NR38555 WHICH WOULD MAKE IT APPROXIMATELY 9 MONTHS OLD.		1	L	7	2 	3O			 	3A16    					 
2003041000016	20030410	00016	EA  	2003	4	10	2003FA0000362    	2	20030331	G	7322	25765362	CARBURETOR      			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	418ER					172S8650	L2731951A			DURING PRE TAKEOFF RUN, THE IDLE SPEED WOULD DROP TO ABOUT 500 RPM WHEN THE THROTTLE WAS REDUCED TO THE STOP. THIS ENGIN	E FUEL CONTROL COMBINATION REQUIRES SUBSTANTIAL ADJUSTMENT TO MAINTAIN THE CORRECT IDLE SPEED/MIXTURE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003041000017	20030410	00017	CE  	2003	4	10	2003FA0000363    	1	20030313	G	5312	07126161	BULKHEAD        			CESSNA	182   	182L        	2072726	CE  											CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	42261	4078 				18258930				THE AFT FUSELAGE BULKHEAD WAS CRACKED IN THE RADIUS AT THE RUDDER STOP ATTACHMENT POINTS.						1	H	7	1 	3O			NT	3A13    					 
2003041000018	20030410	00018	NE  	2003	4	10	2003FA0000364    	2	20030403	G	7321	32447687	FUEL CONTROL    			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A60A     	52043	NE  						MALFUNCTIONED   	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	07	200EW	718  	718  			BB1163				DURING LANDING ROLLOUT, THE PILOT TRIED TO APPLY REVERSE AND THE AIRCRAFT VEERED OFF INTO THE LEFT GRASSY AREA, AND EVEN	TUALLY CAME TO REST IN THE WEST SOFT AREA.  AN ENGINE RUNUP AFTERWARDS REVEALED A DISCREPANCY IN THE RT ENGINE FUEL CONT	ROL.  IT WAS REPLACED WITH AN OVERHAULED UNIT. THE AIRCRAFT WAS TEST FLOWN SATISFACTORILY.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003041000019	20030410	00019	CE  	2003	4	10	2003FA0000365    	1	20030407	G	2121	3521000	MOTOR           	ELECTROMECH 	903840311   	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE4N	HCE4N3      	NE  	VENT BLOWER	BURNED          	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CE	05	902PL	1097 			1662	LJ1583				DURING FLIGHT, CREW HAD SMOKE IN THE CABIN.  SHUTTING OFF THE VENT BLOWER CLEARED THE SMOKE FORM THE CABIN.  AFTER REMOV	ING THE CABIN VENT BLOWER FROM THE AIRCRAFT INSPECTION OF IT FOUND THE MOTOR LOCKED UP AND THE BRUSHES BURNED UP.					1	L	7	2 	3T	3	T	RT	3A20    	E2NE	5	C	P10NE	 
2003042300001	20030423	00001	GL  	2003	4	23	2003FA0000366    	1	20030408	G	2700		ROD END         			AMTR  	AVID  	AVID*       	056121Z	GL  	ROTAX 	582   	582LC       	55555	CE  					LIFT STRUT	BROKEN          	Z				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SW	99						GFOLD				AVID AIRCRAFT LIFT STRUT, THREADED ROD-END FAILURE.  THE PILOT OF AN AVID AIRCRAFT LOST CONTROL SHORTLY AFTER TAKE-OFF A	ND THE AIRCRAFT DESCENDED INTO THE GROUND IN AN UNCOMMANDED LEFT-HAND TURN CAUSING SUBSTANTIAL DAMAGE TO THE AIRFRAME.  	THE PILOT RECALLS HEARING A SHARP CRACK SHORTLY BEFORE BECOMING AIRBORNE. THE GOVT.AAIB METALLURGIST HAS CONCLUDED THAT 	THE PORT REAR LIFT STRUT THREADED ROD-END MAY HAVE FAILED BEFORE THE IMPACT.  THIS WOULD FIT WITH THE SHARP CRACK NOISE 	AND THE ROLL TO THE LEFT.  THERE WERE NO INDICATIONS OF LONG-TERM FATIGUE OR CORROSION DAMAGE AND THE MATERIALS HARDNES	S STATE PROVED CORRECT.  HOWEVER PRE-ACCIDENT DAMAGE TO THE ROD END CANNOT BE RULED OUT.  IN PARTICULAR, THE ROD-END MAY	1	H	7	1 	  	3	I	 	EXPA1H71	EXPA3I				 
2003042800142	20030428	00142	SO  	2003	4	28	2003FA0000368    	1	20030408	G	1430		BOLT            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					VERTICAL FIN	UNDERTORQUED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	137FC	3890 				8290172				DURING ANNUAL INSPECTION FOUND VERTICAL FIN LOOSE. UPON CHECKING ATTACHMENT HARDWARE, FOUND THE FOUR BOLTS AT THE REAR S	PAR TO BE INSUFFICIENTLY TORQUED. THE SINGLE BOLT AT THE FRONT SPAR WAS TIGHT BUT WOULD NOT PREVENT SIDE TO SIDE MOVEMEN	T OF THE FIN(APPROX. 1/4 TO 1/2 INCH. THERE WAS NO RECORD OF THE VERTICAL FIN BEING REMOVED FOR MAINTENANCE AND THIS MEC	HANIC CANNOT OFFER ANY EXPLANATIONS AS TO WHY THESE BOLTS WERE NOT TIGHT.  ALL THE ATTACHING BOLTS WERE REMOVED, THE ARE	AS SURROUNDING THE BOLT HOLES INSPECTED FOR CRACKS, NEW HARDWARE INSTALLED AND RETORQUED.		1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003041000226	20030410	00226	SW  	2003	4	10	2003FA0000369    	1	20030321	G	3221	8644402	SPAR            			BELL  	206   	206B        	1181511	SW  										NLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	345F	3466 				2697				FOUND CRACK IN SPAR WEB AT NOSE GEAR SUPPORT AFT ATTACH. BOLT						1	G	7	1 	3U			 	H2SW    					 
2003041400075	20030414	00075	SO  	2003	4	14	2003FA0000370    	2	20030411	G	8530	655470A3	CYLINDER        			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520*      	17032	SO  					NR 2 & 6	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	621G		332  			TE214	816876R			CYLINDERS NR 2 AND 6 HAD LOW COMPRESSION WITH LEAKAGE PAST THE EXHAUST VALVES.  REMOVEAL AND TEARDOWN OF THE CYLINDERS R	EVEALED THE FOLLOWING:  CONDITION OF CYLINDER HEAD WAS NORMAL FOR TIME.  EXHAUST VALVES EXHIBITED EXTREME WEAR FOR TIME 	IN SERVICE.  CYLINDER BARREL EXHIBITED STEP WEAR IN THE BORE OF .003 INCH, AND PITTING.  EXHAUST VALVE GUIDES WERE WORN 	PAST SERVICE LIMITS.  HALF OF THE VALVE SPRINGS WERE OUT OF LIMITS, AND HALF WERE AT SERVICE LIMITS.  HAVE BEEN FINDING 	NUMEROUS EXAMPLES OF FACTORY NEW AND OVERHAULED CYLINDERS THAT FAIL WITH APPROX 300 HOURS SINCE NEW OR OVERHAUL.		1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2003042900064	20030429	00064	CE  	2003	4	29	2003FA0000371    	1	20030326	G	1430	AN724A	BOLT            			CESSNA	172   	172B        	2072406	CE  	CONT  	O300  	O300*       	17022	SO  					RT WING	MISINSTALLED    	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	6934X	1881 				17247834				DURING ANNUAL INSPECTION, THE RT DIRECT AILERON CABLE (PN 0510105-72) WAS FOUND TO BE CHAFFING ON THE RT WING AFT ATTACH	 BOLT THREADS AND NUT.  FURTHER INVESTIGATION REVEALED THAT BOTH THE LEFT AND RT AFT WING ATTACH BOLTS WERE INSTALLED BA	CKWARDS WITH THE THREADS FACING IN THE AFT DIRECTION.  THE EXCESSIVE LENGTH OF THE THREADED PORTION AND NUT AFT OF THE W	ING SPAR CAUSED INTERFERENCE WITH THE RT AILERON CABLE.  REPLACED THE AILERON CABLE DUE TO SEVERAL STRANDS BEING CHAFFED	 EXCESSIVELY.  REPLACED BOTH AFT WING ATTACH BOLTS AND HARDWARE.  RECORD REVIEW SHOWS THAT A/C HAD BEEN REASSEMBLED (FRO	M STORAGE) IN MAY OF 2002, AT WHICH TIME AN ANNUAL INSP WAS SIGNED OFF.	1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003042900065	20030429	00065	CE  	2003	4	29	2003FA0000372    	1	20030313	G	3246		WHEEL           			CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300*       	17022	SO  					NLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	7326T	2207 				46926				DURING ANNUAL INSP, NOSEWHEEL ASSY WAS REMOVED IN ORDER TO INSPECT THE BEARINGS FOR CONDITION.  ONE BEARING CUP WAS FOUN	D CORRODED.  WHEN LW67010 CUP WAS REMOVED FROM WHEEL HALF, TECH DISCOVERED BRG BORE SEVERELY WORN.  BEARING CUP HAD BEEN	 GLUED IN PLACE WITH REDDISH COLORED ADHESIVE COMPOUND, POSSIBLE LOCKTITE.  COMPOUND ADHERED TO WHEEL HALF AND BEARING C	UP.  WITHOUT REMOVING COMPOUND FROM WHEEL HALF, TECH PLACED A CLEAN LW67010 BEARING CUP IN WHEEL HALF.  CUP SEATED IN BO	RE WITH LIGHT HAND PRESSURE AND SPUN FREELY WITH CONSIDERABLE CLEARANCE.  A/C OWNER STATED THAT NOSEWHEEL BRGS HAD BEEN 	REPLACED LAST ANNUAL.  GLUEING THE BEARING CUP IN PLACE IS NOT AN APPROVED REPAIR.	1	H	7	1 	3O	3	O	 	3A12    	E253				 
2003042900082	20030429	00082	SO  	2003	4	29	2003FA0000373    	2	20030328	G	8530	628488	LIFTER          			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					NR 2 CYLINDER	SPALLED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	19	102KY	684  				P21000093	278764R			REMOVED NR 2 CYL FOR BLOW BY.  PULLED LIFTER ASSEMBLY TO INSPECTION CONDITION FOUND EXHAUST LIFTERBODY SPALLING.  DISASS	EMBLED ENGINE SENT CAM OUT.  CAM WAS ALSO BAD, COULD NOT BE RECONDITIONED.					1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003041400064	20030414	00064	CE  	2003	4	14	2003FA0000375    	1	20030313	G	5320	07126161	BULKHEAD        			CESSNA	182   	182L        	2072726	CE  										AFT FUSELAGE	CRACKED         	B			C3VR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	42261	4078 				18258930				THE AFT FUSELAGE BULKHEAD WAS CRACKED IN THE RADIUS AT THE RUDDER STOP ATTACHEMENT POINTS.  BLOCK RUDDER WHEN A/C IS TIE	D DOWN IN WINDY CONDITIONS.					1	H	7	1 	3O			NT	3A13    					 
2003042300045	20030423	00045	GL  	2003	4	23	2003FA0000377    	1	20030321	G	2710	12546001	MOTOR           			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					ROLL TRIM	DAMAGED         	B			FFGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	33	508JS					1170				SHAFTED IN ROLL, TRIM MOTOR ASSEMBLY SHEARED IN FLIGHT, DURING LANDING APPROACH.  THE PILOT RETAINED CONTROL AND A SAFE 	LANDING WAS ACCOMPLISHED.  NO FURTHER DAMAGE WAS FOUND DURING INSPECTION OF THE TRIM SYSTEM, AILERON AND LEFT WING.  THE	 CAUSE OF THIS FAILURE IS UNDETERMINED AT THIS TIME.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003042900123	20030429	00123	NE  	2003	4	29	2003FA0000379    	2	20030320	G	7200	SAP5999	ROLLER          								PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	FAILED          	B			CP2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15							P326888			DURING THE OVERHAUL OF THIS ENGINE NEW ROLLERS (PN 5999) WERE INSTALLED.  DURING THE TEST RUN OF THE SUBJECT ENGINE ONE 	OF THE ROLLERS FAILED.  AFTER TEAR DOWN, A HARDNESS TEST INSPECTION OF THE ROLLERS WAS CONDUCTED AND IT WAS DETERMINED T	HE ROLLER THAT FAILED, WAS CONSIDERABLY SOFTER THAN THE REMAINING ROLLERS.  (SW15200313699)									3	R			5E2				 
2003042900124	20030429	00124	SO  	2003	4	29	2003FA0000380    	1	20030217	G	5712	7847504	RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	LT WING	CRACKED         	B			NCLR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	56018	5506 				28R7335334	L1079651A	DY4614B		THE LT AND RT FORWARD TRUNNION FITTING ASSEMBLIES WERE REMOVED TO COMPLY WITH MFG (FORWARD SIDEBRACE STUD).  WHILE THE F	ITTINGS WERE REMOVED IT WAS NOTICED THAT THE LEFT AND RIGHT WING RIBS  MFG (PN 7847504 AND 05) WERE CRACKED AT THE FORWA	RD OUTBOARD FLANGE OF THE RIBS.  THIS FLANGE IS UNDER THE TRUNNION FITTING ASSEMBLY AND CANNOT BE SEEN WITHOUT REMOVAL O	F THE TRUNNION FITTING.  THIS IS THE THIRD TIME THESE CRACKED RIBS HAVE BEEN FOUND.  SUGGEST PERIODIC INSPECTION IN THIS	 AREA.		1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P25EA	 
2003042300055	20030423	00055	EA  	2003	4	23	2003FA0000381    	2	20030401	G	8530	TB2156011000	LEVER           			SOCATA	TB20  	TB21        	8680697	EU  	LYC   	O540  	TIO540*     	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE	FRETTED         	D				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	23	291GT					2091	L1071061A	DY4879B		CUSTOMER COMPLAINED OF EXCESSIVE VIBRATION.  ATTEMPTS TO BALANCE THE PROP WERE UNSUCCESSFUL.  INSPECTION REVEALED THAT T	HE EXHAUST SUPPORT (LEVER ASSY) SUPPORT BUSHINGS WERE WORN ALLOWING THE METAL PORTION TO CONTACT THE MOUNT TRANSMITTING 	THE ENGINE VIBRATION TO THE AIRFRAME.				1	L	7	1 	3O	3	O	RT	A51EU   	E14EA	5	C	P25EA	 
2003050500055	20030505	00055	SW  	2003	5	5	2003FA0000382    	1	20030210	G	1430	442615	BOLT            			GULSTM	114   	114B        	O145001	SW  	LYC   	O540  	IO540*      	41532	EA  					HORIZONTAL STAB	LOOSE           	B			GA5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	6023A	1150 				14604				DURING 100 HOUR INSPECTION, THE HORIZONTAL STABILIZER WAS FOUND LOOSE.  REMOVED DORSAL FIN, RUDDER AND ELEVATORS.  FORWA	RD ATTACH BOLTS FOR HORIZONTAL STABILIZER WERE FOUND LOOSE.  9 RIVETS ON RIGHT HAND AFT VERTICAL SUPPORT ANGLE, (PN 4426	82 WERE FOUND SHEARED.  CHECKED AND REPLACED SHEARED RIVETS.  CONTACTED DER FOR REPAIR OF SPAR ATTACH HOLES AND HARDWARE	.  REPAIRED IAW SR.  REPAIR CONSISTED OF GOING TO OVERSIZE HARDWARE FOR FRONT MOUNTING AND INSTALLING SHIM IN DOUBLER PL	ATE UNDER NUTPLATES.  THE FLOATING NUTPLATE USED IN PRODUCTION ARE REPLACED WITH FIXED NUT PLATES.  FLOATING NUTPLATES A	LLOWED STABILIZER TO MOVE TOO MUCH WITH LOOOSE BOLTS AND ELONGATED HOLES IN STABILIZER.	1	L	7	1 	3O	3	O	RT	A12SO   	1E4				 
2003042300053	20030423	00053	CE  	2003	4	23	2003FA0000383    	1	20030401	G	2510	456655	CYLINDER        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PILOT SEAT	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	3519U					172S8849	L2962951A			PRIOR TO ENGINE START, PILOT COULD NOT GET SEAT BACK TO STAY UPRIGHT.  LOCK CYLINDER WILL ALLOW SEAT BACK TO FULLY RECLI	NE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003050700194	20030507	00194	SO  	2003	5	7	2003FA0000384    	1	20030314	G	5340	67271800	BRACKET         			PIPER 	PA28  	PA28R201    	7102816	SO  										NLG ACTUATOR	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5326U	1086 				2844046				DURING A ROUTINE INSPECTION THE NOSE GEAR ACTUATOR ATTACH BRACKETT WAS FOUND LOOSE.  ALL ATTACH RIVETS AND HARDWARE WERE	 FOUND TO BE WORKING.  THE NOSE GEAR ACTUATOR ROD END CLEVIS ATTACH BOLT WAS ALSO FOUND BENT.  THE BRACKETT AND CLEVIS B	OLT WERE REPLACED.  THIS SI THE SECOND SUCH OCCURANCES IN OUR FLEET.  RECOMMEND REPLACING THE CLEVIS BOLT EVERY 100 HOUR	 AND THOROUGHLY INSPECTING THIS AREA AT EACH INSPECTION.  THE DEFECTIVE PARTS WERE SENT TO THE MANUFACTURE FOR EVALUATIO	N.		1	L	7	1 	3O			 	2A13    					 
2003050700192	20030507	00192	CE  	2003	5	7	2003FA0000385    	1	20030313	G	7810	20179110	EXHAUST PIPE    			ZINAIR	CH2000	CH2000      	9950100	CE  	LYC   	O235  	O235*       	41505	EA  					BEHIND MUFFLER	DEFECTIVE       	B			QE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	8500Z	150  				201003				THIS IS THE SECOND REPORT OF FINDING THE ABOVE COMPONENT DEFECTIVE.  THEY ARE CRACKING BEHIND THE MUFFLER SHROUD AND CAN	NOT BE SEEN WITHOUT REMOVAL OF THE SHROUD.  THIS ALLOWS EXHAUST GASES TO ENTER THE COCKPIT WHEN THE HEATER IS UTILIZED. 	 THE CRACK LENGTH IS APPROXIMATELY FIVE TO SIX INCHES.  A PICTURE OF THE CRACKED AREA WILL BE E-MAILED AS WELL.				1	L	7	1 	3O	3	O	NT	TA5CH   	E223				 
2003050700193	20030507	00193		2003	5	7	2003FA0000386    	4	20030313	G	3197	688381	SWITCH          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					INSTRUMENT PANEL	FAILED          	B			OG5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	297ND					4496078				PILOT REPORTED COMPLETE ELECTRICAL FAILURE.  DURING TROUBLESHOOTING, THE BATTERY WAS FOUND TO HAVE NO CHARGE AND THE RIG	HT ENGINE STARTER WAS STILL ENGAGED AT THE BENDIX.  FURTHER TROUBLESHOOTING FOUND THE STARTER TOGGLE SWITCH WAS STUCK IN	 THE ON POSITION FOR THE RIGHT ENGINE CAUSING THE STARTER TO REMAIN ENERGIZED AFTER ENGINE START UNTIL IT SHORTED OUT, D	RAINING THE ELECTRICAL SYSTEM TILL FAILURE.			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003041600273	20030416	00273	EU  	2003	4	16	2003FA0000387    	1	20030331	G	2434	0120468107	ALTERNATOR      			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					ENGINE	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	746  				85004				ALTERNATOR FAILED TO PROVIDE ANY OUTPUT WHILE IN USE.  SUSPECT INTERNAL FAILURE.						1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003042300054	20030423	00054	SW  	2003	4	23	2003FA0000388    	1	20030304	G	7120	206064105102	MOUNT           			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	MISMANUFACTURED 	B			ALGR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	03										WHEN CHECKING FOR FIT, ANGLE OF FITTING NOT CORRECT, WILL NOT FIT RIGHT SIDE.  BETTER QUALITY CONTROL PRIOR TO SHIPMENT.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003042300048	20030423	00048	CE  	2003	4	23	2003FA0000389    	1	20030414	G	2720		CONTROL CABLE   			CESSNA	182   	R182        	2072734	CE  										RUDDER	OUT OF RIG      	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	228HP					R18201643				WHEN THE RUDDER IS DEFLECTED TO THE FAR RIGHT, THE RIGHT RUDDER CABLE GOES SLACK AND HANGS UP UNDER THE NUT FOR THE ELEV	ATOR PULLEY CLUSTER LOCATED BY THE FUSELAGE RIGHT SIDE ACCESS PANEL.  TO PREVENT THIS A GUARD WAS SUGGESTED TO PREVENT T	HE CABLE FROM SLIPPING UNDER THE BOLT AND HANGING UP THE CONTROL CABLE.    THE CABLE TENSION WAS CHECKED AND DOUBLE CHEC	KED.  THE MECHANIC STATES THAT THIS IS NOT THE FIRST TIME HE HAS SEEN THIS PROBLEM.   			1	H	7	1 	3O			RT	3A13    					 
2003042300057	20030423	00057	SO  	2003	4	23	2003FA0000390    	1	20030407	G	3222	6705403	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NOSE STRUT	DAMAGED         	C			DF2S	C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			SW	15	355AB					4496093				AIRCRAFT WAS ON TAKEOFF ROLL WHEN AT ABOUT 79 KNOTS PILOT HEARD A LOUD POP AND SAW A PIECE OF NOSE GEAR FLY OFF THE AIRC	RAFT.  PILOT ABORTED TAKEOFF AND NOTICED A DIFFERENCE IN THE STEERING COMING BACK TO THE RAMP.  WHEN CHECKED BY MAINTENA	NCE, NOTICED THAT THE LOWER REAR SECTION OF THE NOSE TRUNNION ASSEMBLY DETACHED,  IT CAUSED THE SHIMMEY DAMPENER SHAFT T	O SHEAR AND BENT THE BRACKETS ON THE SHIMMEY DAMPENER BODY.			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003042300056	20030423	00056	CE  	2003	4	23	2003FA0000391    	1	20030331	G	2510	MM201057	LOCK            			CESSNA	172   	172R        	2072401	CE  										PILOT SEAT	MISINSTALLED    	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	15						17280433				FRONT BOLT HOLE ON THE PILOT LOCK-CYLINDER WAS INSTALLED 90 DEGREES THE WRONG DIRECTION.						1	H	7	1 	3O			NT	3A12    					 
2003041600277	20030416	00277	EU  	2003	4	16	2003FA0000392    	1	20030407	G	2710	120A4125	BEARING         			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	640  				85005				DURING PROGRESSIVE INSPECTION OF THE AIRCRAFT THERE WAS A STRANGE SOUND FROM THE AILERON SYSTEM.  FURTHER INVESTIGATION 	REVEALED THAT THE BEARING FROM THE LT AILERON ASSEMBLY WAS COMING APART.  PROBABLE CAUSE IS DESIGN OF AILERON LEVER ASSE	MBLY.  THE ANGLE AND THE AMOUNT OF USE OF THIS SYSTEM.				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003050700190	20030507	00190	SO  	2003	5	7	2003FA0000393    	1	20030205	G	2497	79412011	WIRE            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A1D     	41514	EA  					ELECTRICAL	BURNED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	9105X	2408 				2890006				AIRCRAFT ALTERNATOR ANNUNCIATOR LIGHT STAYS ON BUT AMMETER SHOWS OUTPUT.  FOUND ALTERNATOR POWER WIRE AND ANNUNCIATOR WI	RES BURNED AT DIODE ASSEMBLY.  REPLACE TERMINAL ENDS AND WIRE.  CAUSE UNKNOWN.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003042300041	20030423	00041	SO  	2003	4	23	2003FA0000402    	1	20030417	G	5743	6704212	TRUNNION        			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360A1A    	41514	EA  					RT MLG	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	3811T	8066 				28R30126				WHILE REBUSHING THE RIGHT MAIN LANDING GEAR, A VERY VISIBLE CRACK WAS FOUND IN THE SUPPORT WEB OF THE AFT TRUNNION FITTI	NG ASSEMBLY.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003042300042	20030423	00042	SO  	2003	4	23	2003FA0000403    	1	20030417	G	5743	6704212	TRUNNION        			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360A1A    	41514	EA  					ZONE 700	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	3811T	8066 				28R30126				WHILE REBUSHING THE RIGHT MAIN LANDING GEAR, A VERY VISIBLE CRACK WAS FOUND IN THE SUPPORT WEB OF THE AFT TRUNNION FITTI	NG ASSEMBLY.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003042800197	20030428	00197	CE  	2003	4	28	2003FA0000406    	1	20030410	G	3211	24411001	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	6215V	2367 				172RG0592	L2870136A	807381		FOUND CRACK IN RIGHT MAIN GEAR PIVOT ASSEMBLY AT CASTING SEAM. AIRPLANE SAT FOR 8 YEARS ON THE COAST OF FLORIDA. CORROSI	ON WAS A MAJOR FACTOR IN THIS CRACK. PLANE WAS REPAINTED AND CRACK WAS COVERED. PAINT WAS SPLITTING IN AREA. STRIPPED PA	INT AND THE CRACK APPEARED. IT WAS CRACKED ALL THE WAY THROUGH HOUSING DOWN TO GEAR LEG AND EXTENDED IN TOWARDS PIVOT 4 	INCHES.			1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003050500054	20030505	00054	CE  	2003	5	5	2003FA0000408    	1	20030414	G	2720		CONTROL CABLE   			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					RUDDER	JAMMED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	228HP					R18201643				WHEN THE RUDDER IS DEFLECTED TO THE FAR RIGHT , THE RIGHT RUDDER CABLE GOES SLACK AND HANGS UP UNDER THE NUT FOR THE ELE	VATOR PULLEY CLUSTER LOCATED BY THE FUSELAGE RIGHT SIDE ACCESS PANEL.  TO PREVENT THIS A GUARD WAS SUGGESTED TO PREVENT 	THE CABLE FROM SLIPPING UNDER THE BOLT AND JAMMING THE CONTROL CABLE.  THE MECHANIC STATES THAT THIS IS NOT THE FIRST TI	ME HE HAS SEEN THIS PROBLEM.			1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2003050700185	20030507	00185	EA  	2003	5	7	2003FA0000409    	2	20030304	G	8520	74309	BEARING         			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	8096Y	320  				32R8029005	L668561A			FOUND BEARING MATERIAL IN OIL SUCTION SCREEN.  REMOVED CYLINDERS AND FOUND CYLINDER NR 2 CONNECTING ROD BEARING FAILING 	BY LAMINATIONS PICKING LOOSE ON INSIDE DIAMETER.  THIS IS THE SAME CONDITION FOUND DURING REPLACEMENT OF ROD BEARINGS UN	DER MFG SA 59-800 WITH THE SAME MFG DATE CODE.				1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003042300049	20030423	00049	EA  	2003	4	23	2003FA0000410    	2	20030304	G	8530	SL16740A	EXHAUST VALVE   			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	8096Y	32031				32R8029005	L668561A			INVESTIGATED HEAVY OIL CONSUMPTION.  UPON DISASSEMBLY, FOUND VALVES EXCESSIVELY WORN.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003050700189	20030507	00189	EA  	2003	5	7	2003FA0000411    	2	20030304	G	8530	SL75838	VALVE GUIDE     			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	8096Y	320  				32R8029005	L668561A			INVESTIGATED HEAVY OIL CONSUMPTION.  UPON  DISASSEMBLY, FOUND VALVE GUIDES EXCESSIVE WORN.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003042300050	20030423	00050	EU  	2003	4	23	2003FA0000412    	1	20030321	G	3520	Z00N6039257260	VALVE           			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A6       	52043	EA  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	700RK	72   				253	PCEPMOO0130	HH1520		AIRCRAFT ARRIVED WITH AN OXYGEN LEAK.  THE ALTIMETRIC VALVE WAS REPLACED.  THE REPLACEMENT VALVE ALSO LEAKED.  THE THIRD	 VALVE INSTALLED DIDN`T LEAK IN THE OFF POSITION BUT WHEN THE PASSENGER OXYGEN WAS TURNED ON DEPLOYING THE  MASKS THE VA	LVE LEAKED FROM THE PRESSURE RELIEF VALVE.  THIS VALVE IS LOCATED IN THE COCKPIT ABOVE THE HEADLINER IN CLOSE PROXIMITY 	TO NUMEROUS ELECTRICAL SWITCHES.  AN OXYGEN RICH ENVIRONMENT IN THIS LOCATION COULD BE DISASTOROUS.  THIS VALVE SHOULD B	E RELOCATED TO THE CABIN TO ELEMINATE ANY HAZARDS.		1	L	7	1 	3T	3	T	RT	A60EU   	E4EA	5	C	P10NE	 
2003050700180	20030507	00180	SO  	2003	5	7	2003FA0000413    	1	20030421	G	3260	67203000	SPRING          			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360A1A    	41514	EA  					DOWNLOCK	WORN            	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	3811T	8066 				28R30126				DURING AN ANNUAL INSPECTION, IT WAS FOUND THAT BOTH MAIN LANDING GEAR DOWNLOCK SPRINGS WERE WORN 80 PERCENT OF THE WAY T	HROUGH WHERE THEY CONNECT TO THE LANDING GEAR.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003050700181	20030507	00181	GL  	2003	5	7	2003FA0000414    	2	20030414	G	7240	23030911	COMBUST CHAMBER 			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	CRACKED         	C				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			WP	07	52AZ	2170 	244  			53380				OUTER COMBUSTION CAN CRACKED 180 DEGREES AROUND FUEL NOZZLE WELD. PRIOR TO CRACK THE ENGINE WAS RATED AS A +22 MGT. THE 	ENGINE WAS -6 MGT WHEN CRACK WAS DISCOVERED. THE CRACK IS NOT VISIBLE TO THE PILOT DURING PREFLIGHT.  AN INSPECTION MIRR	OR IS REQUIRED TO SEE THE CRACK.  A CATASTROPHIC ENGINE FAILURE WITH A RESULTING FIRE WOULD HAVE OCCURED IF THE CRACK HA	D NOT BEEN DETECTED.			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003042300044	20030423	00044		2003	4	23	2003FA0000415    	4	20030421	G	6113	05503671	SPINNER         	CESSNA      		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	409ER	737  				172S9158	L3045051A			PILOT WROTE UP MISSING SCREW. UPON EXAMINATION THE SPNNER AND BULKHEAD WERE FOUND CRACKED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003042300051	20030423	00051	EA  	2003	4	23	2003FA0000416    	2	20030421	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	409ER					172S9158	L3045051A			DURING PRE TAKEOFF CHECK, THE IDLE WAS TOO LOW TO CONTINUE. THIS ENGINE/FUEL CONTROL COMBINATION REQUIRES SUBSTANTIAL AD	JUSTMENT TO MAINTAIN THE CORRECT IDLE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003042300058	20030423	00058	EA  	2003	4	23	2003FA0000417    	2	20030421	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OUT OF ADJUST   	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	456ER					17280667	L1562851A			DURING GROUND OPERATION, THE CREW NOTICED THE IDLE WAS TOO LOW TO CONTINUE THE FLIGHT. THIS ENGINE/FUEL CONTROL COMBINAT	ION REQUIRES A SIGNIFICANT AMOUNT OF ADJUSTMENT TO MAINTAIN THE CORRECT IDLE MIXTURE AND SPEED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003050700186	20030507	00186	SO  	2003	5	7	2003FA0000418    	1	20030416	G	3213	6531904	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					LT  MLG STRUT	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	83416	10263				288116160				LT MLG COLLAPSED DURING LANDING ROLLOUT.  SUBSEQUENT INVESTIGATION DISCLOSED THAT THE DRAG LINK ATTACH EARS SEPARATED FR	OM THE STRUT HOUSING.  VISUAL INSPECTION SUGGEST THAT A PRE-EXISTING CRACK IN THE OUTBOARD SCISSORS ATTACH POINT INDUCED	 SEPARATION FROM THE STRUT HOUSING.  RECOMMEND VISUAL INSPECTION OF THE MLG STRUT SCISSORS ATTACH POINTS.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003050700153	20030507	00153	CE  	2003	5	7	2003FA0000419    	1	20030422	G	5412		STRUCTURE       			ZINAIR	CH2000	CH2000      	9950100	CE  	LYC   	O235  	O235*       	41505	EA  					FIREWALL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	30ZA	734  	100  			200030				DURING INSPECTION THE UPPER HORITONTAL (Z) ON THE FIREWALL WAS FOUND CRACKED. THIS IS THE LATER REINFORCED VERSION REV. 	4. THE CRACK WAS LOCATED FROM THE HOLE WHERE THE NOSE GEAR STRUT COMES THROUGH TO THE OUTSIDE FORWARD EDGE.THE PLASTIC S	TOP UNDER THE (Z) WAS ALSO CRACKED.				1	L	7	1 	3O	3	O	NT	TA5CH   	E223				 
2003050700154	20030507	00154	CE  	2003	5	7	2003FA0000420    	1	20030422	G	5412		STRUCTURE       			ZINAIR	CH2000	CH2000      	9950100	CE  	LYC   	O235  	O235*       	41505	EA  					FIREWALL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	30ZA	734  	100  			200030				DURING INSPECTION THE UPPER HORITONTAL (Z) ON THE FIREWALL WAS FOUND CRACKED. THIS IS THE LATER REINFORCED VERSION REV. 	4. THE CRACK WAS LOCATED FROM THE HOLE WHERE THE NOSE GEAR STRUT COMES THROUGH TO THE OUTSIDE FORWARD EDGE.THE PLASTIC S	TOP UNDER THE (Z) WAS ALSO CRACKED.				1	L	7	1 	3O	3	O	NT	TA5CH   	E223				 
2003050700160	20030507	00160	EA  	2003	5	7	2003FA0000421    	2	20030422	G	7322	25765362	SERVO           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL	INACCURATE      	B				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SO	15	483ER					17280632	L2722651A			DURING FLIGHT THE CREW REPORTED A ROUGH ENGINE. SUBSEQUENTLY THE FUEL SERVO AND FLOW DEVIDER WERE CHANGED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003050600145	20030506	00145	SO  	2003	5	6	2003FA0000422    	2	20030407	G	8530	SA631475	PISTON          								CONT  	O520  	IO520F      	17032	SO  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		1707 					286490F			NR 2 AND NR 3 CYLINDER PISTON SKIRTS BROKE OFF AND FELL INTO THE OIL SUMP WHILE RUNNING AND CONTAMINATING THE ENGINE WIT	H METAL.										3	O			E5CE				 
2003050600146	20030506	00146	NM  	2003	5	6	2003FA0000423    	1	20030325	G	2910		HOSE            			AEROVD	L29   	L29         	0564310	NM  										HYD PUMP PRESS	CRACKED         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			NE	05	82674					892830				NOSE LANDING GEAR FAILED TO COMPLETELY EXTEND FOR LANDING.  INSPECTION REVEALED HYDRAULIC LEAK NEAR ENGINE COMPARTMENT. 	 FURTHER INVESTIGATION REVEALED THE HOSE WAS CRACKED NEAR THE FITTING WHERE IT ATTACHES TO THE PUMP.					1	M	7	1 	4U			RT	1M71EXPA					 
2003050600147	20030506	00147	CE  	2003	5	6	2003FA0000424    	1	20030411	G	5312	07126161	BULKHEAD        			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	2727Q					18257927				PART WAS FOUND CRACKED DURING INSPECTION REQUIRED BY AD 72-07-09.  PART WAS CRACKED AT IT HAND RUDDER CONTROL CABLE HOLE	, BETWEEN HOLE AND BULKHEAD FLANGE.  PROBABLE CAUSE IS FATIGUE.  RECOMMEND THAT CONTROL LOCK IS ALWAYS PUT IN WHEN AIRCR	AFT IS STORED OUTSIDE.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003042900127	20030429	00127	EU  	2003	4	29	2003FA0000425    	1	20030414	G	7160	F50B258700A2	INTAKE DUCT     			AMD   	FALC50	FALCON50MYST	2730106	EU  										NR 2 ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	4350M	10635				142				DURING 3C INSPECTION FOUND SEVERAL CRACKS IN THE NR 2 ENGINE INTAKE S-DUCT ASSEMBLY.  CRACKS WERE AT THE OUTER, UPPER SK	IN IN SEVERAL LOCATIONS AROUND THE UPPER ANTI-ICE BLEED AIR DUCTING ON TOP OF THE INTAKE S-DUCT ASSEMBLY.  THE ENTIRE S-	DUCT ASSEMBLY WAS REPLACED WITH NEW.  INITIAL DETERMINATION OF CAUSE OF CRACKS IS SUSPECTED TO BE METAL FATIGUE OVER TIM	E OF LIFE IN SERVICE.			2	L	7	3 	4F			 	A46EU   					 
2003042900230	20030429	00230	EU  	2003	4	29	2003FA0000426    	1	20030414	G	7160	FGFB258702D1	DUCT            			AMD   	FALC90	FALCON900EX 	2730009	EU  										NR 2 ENG INTAKE	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	890FH	707  				SC271				DURING INSPECTION NOTED PULLED RIVETS AND SPOT WELDS IN THE INTERIOR OF THE FORWARD, NR 2 ENGINE INTAKE S-DUCT ASSEMBLY.	  FORWARD S-DUCT ASSEMBLY WAS REPLACED WITH NEW.  CAUSE OF DEFECTS IS SUSPECTED TO BE OVER PRESSURIZATION OF ANTI-ICE BL	EED AIR MANIFOLD LOCATED ON TOP OF THE FORWARD S-DUCT ASSEMBLY.				2	L	7	3 	4F			RT	A46EU   					 
2003042900231	20030429	00231	SO  	2003	4	29	2003FA0000427    	1	20030325	G	7810	63726	EXHAUST STACK   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					NR 4 CYLINDER	FAILED          	G				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			EA	13	3784K					2823729				THE NR 4 CYLINDER EXHAUST RISER PULLED OUT OF THE MUFFLER DURING TAKE-OFF RESULTING IN SMOKE IN THE COCKPIT.INSULATION M	ELTED AT THE STARTER CONTACTOR AND PLACE WHERE MAIN WIRING HARNESS PASSES THROUGH THE FIRE WALL.NO FAILURE OF THE CLAMP 	OR HARDWARE WAS NOTED.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003050800007	20030508	00007	SO  	2003	5	8	2003FA0000428    	1	20030427	G	2434	2642997R	ALTERNATOR      			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE	OVERHEATED      	P				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		AP	APPROACH       	1			EA	23	2218Z		130  			28R7918117				A POOR CONNECTION BETWEEN THE OUTPUT STUD AND THE POSITIVE DIODE MOUNTING ASSEMBLY RESULTED IN EXTREME HEATING OF THE ST	UD AND MOUNTING ASSEMBLY.  THIS HEAT ALSO MELTED THE TEFLON OUTPUT STUD INSULATOR AND VAPORIZED THE DIODE LEADS.  THE DI	ODE MOUNTING ASSEMBLY IS HELD IN PLACE ONLY BY THE MOUNTING STUD AND DIODE LEADS.  THIS CAUSED THE DIODE MOUNTING ASSEMB	LY TO BECOME FREE FLOATING INSIDE THE ALTERNATOR.  THIS FAILURE MODE HAS A HIGH POTENTIAL TO CAUSE AN IN-FLIGHT FIRE IN 	THE ENGINE COMPARTMENT.		1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003050600148	20030506	00148	CE  	2003	5	6	2003FA0000429    	1	20030305	G	2820	S14956	HOSE            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL SYSTEM	FAILED          	B			FE4R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AL	03	188VE	1867 				172S8391				PILOT REPORTED FUEL LEAK AT WING ROOT AREA, RIGHT SIDE OF AIRCRAFT.  INSPECTING MECHANIC FOUND THAT WING ROOT FUEL HOSES	 WERE DETERIORATED CAUSING FUEL LEAKAGE.  HOSES LOOKED TO BE ORIGINAL INSTALLATION BUT WERE VACUUM TYPE HOSE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003050600152	20030506	00152	SO  	2003	5	6	2003FA0000430    	2	20030130	G	8530	EL649358CN	CYLINDER        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RT ENGINE	SPLIT           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	2690N	700  				414A0407	519195			STEEL BARREL SPLIT IN A SPIRAL MOTION.   CYLINDER SERIAL NR 22597-24.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003050800027	20030508	00027	CE  	2003	5	8	2003FA0000433    	1	20030331	G	8120	4066109018	TURBOCHARGER    			CESSNA	337   	P337H       	2075731	CE  	CONT  	O360  	TSIO360CB   	17025	SO  					ENGINE	MISINSTALLED    	B			WS9R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NM	07						P3370349	311020			TURBOCHARGER UNABLE TO BOOST MANIFOLD PRESSURE.  REMOVED TURBOCHARGER AND FOUND EXCESSIVE CLEARANCE BETWEEN T-WHEEL AND 	HOT SECTION HOUSING.  INCORRECT PARTS ASSEMBLED INTO A COMPLETE UNIT.  INSPECT PRODUCT PRIOR TO RELEASING TO SERVICE.					1	H	7	2 	3O	3	O	 	A6CE    	E9CE				 
2003050800118	20030508	00118	SO  	2003	5	8	2003FA0000437    	1	20030425	G	7921	B99340413	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4133D		186  			2843117				FOUND OIL LEAK ON PRE-FLIGHT INSPECTION BY STUDENT PILOT PRESSURE CHECKED OIL COOLER AND FOUND OIL COOLER LEAKING AT SEA	M ON TOP.  THIS IS A WEAK AREA ON THE OIL COOLER, COULD BE CAUSED BY VIBRATION AND NOT USING A BACK UP WRENCH WHEN INSTA	LLING OIL COOLER HOSES.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003050900096	20030509	00096	EA  	2003	5	9	2003FA0000438    	2	20030430	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360LYC*   	41514	EA  					ENGINE	INACCURATE      	B				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			SO	15	448ER					17280610	L185651A			DURING PRE TAKE OFF GROUND CHECK, THE CREW REOPORTED THE IDLE TO BE LOW. IT WAS SUBSEQUENTLY ADJUSTED. THIS ENGINE/FUEL 	CONTROL COMBINATION REQUIRES SUBSTANTIAL ADJUSTMENT TO MAINTAIN PROPER OPERATION..					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003050900105	20030509	00105	CE  	2003	5	9	2003FA0000439    	1	20030501	G	5740	351150583	FITTING         			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT WING	DEFORMED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	911ND	10508	806  			LJ774				DURING INSPECTION OF THE WING FITTINGS AND BOLTS THE RIGHT REAR WING ATTACH BOLT WAS FOUND TO BE BENT AND THE FITTING WA	S DEFORMED. IN THE MFG STRUCTURAL INSPECTION AND REPAIR MANUAL COVERS THE INSTPECTION OF THE BOLTS AND FITTING AREA.  TH	E BOLT AND A CASTING OF THE DEFORMED FITTING WAS SENT TO MFG TECH SUPPORT FOR EVAULATION. TECH RECOMMENED THE FITTING AN	D BOLT BE REPLACED.			1	L	7	2 	3T	4	T	 	3A20    	E4EA	6	C	P15EA	 
2003050900127	20030509	00127	SO  	2003	5	9	2003FA0000440    	1	20030424	G	2436	68804007	VOLT REGULATOR  			PIPER 	PA32  	PA32R301T   	7103220	SO  											DEFECTIVE       	B				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	09	902WL					3257075				WHILE UPGRADING VOLTAGE REGULATOR P/N 68804-006 TO P/N 68804-007 IAW MFG SERVICE LETTER 1049 WE HAVE HAD SEVERAL NEW REG	ULATORS THAT WOULD NOT WORK RIGHT OUT OF THE BOX.  IN THIS PARTICULAR INSTANCE THE REGULATOR OPERATIONAL CHECKED NORMAL 	DURING GROUND RUNS BUT IN FLIGHT CAUSED THE AUTO-PILOT TO FAULT.  WE RECCOMEND DOING A THOROUGH JOB OF TESTING AUTO-PILO	TS AND AVIONICS WHEN DOING THIS UPGRADE BEYOND THE SCOPE OF NORMAL GROUND CHECKS.			1	L	7	1 	3O			 	A3SO    					 
2003050900128	20030509	00128		2003	5	9	2003FA0000441    	4	20030430	G	6113	05503671	SPINNER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	407ER					172S9157	L3045451A			DURING AN INSPECTION, THE SPINNER WAS FOUND CRACKED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003050900129	20030509	00129	EA  	2003	5	9	2003FA0000442    	2	20030430	G	7421		SPARK PLUG      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FOULED          	B				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SO	15	477ER					17280622	RL234451A			THE CREW REPORTED THE ENGINE (COUGHED) ON TAKE OFF. COMPLETED AN INSPECTION ON SUSPECT ITEMS. CLEANED, TESTED AND FLOW T	ESTED ALL NOZZLES, CLEANED AND TESTED SPARK PLUGS. SEVERAL WERE FOUND MARGINALLY FOULED. THIS ENGINE/FUEL CONTROL COMBIN	ATION DOES REQUIRE SUBSTANTIAL ADJUSTMENT TO MAINTAIN PROPER IDLE SPEED/MIXTURE SETTINGS.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003060400069	20030604	00069	EA  	2003	6	4	2003FA0000443    	2	20030430	G	7322		MANIFOLD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL CONTROL	INACCURATE      	B				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	15	437ER				85010016	172S8653	L2994351A			THE PILOT REPORT A ROUGH ENGINE AT 1,000 FT. DURING SUBSEQUENT INSPECTION AND TROUBLESHOOTING, THE FUEL INJECTOR NOZZLES	 WERE CLEANED AND TESTED, THE FUEL MANIFOLD WAS REPLACED, AND THE FUEL SERVO WAS REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003050900075	20030509	00075	WP  	2003	5	9	2003FA0000444    	2	20030424	G	7230		SHROUD          								GARRTT	TFE731	TFE7314R    	01518	WP  					COMPRESSOR	FAILED          	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19		5194 					P102144			IN-FLIGHT SHUTDOWN.  SUSPECT 2ND STAGE LPC ROTOR SHROUD FAILED FROM INITIAL INSPECTION RESULTS.  DESTROYED LPC, HPC, HPT	, AND LPT.										4	F			E6WE				 
2003050900054	20030509	00054	SO  	2003	5	9	2003FA0000445    	1	20030501	G	5520	65254000	EYEBOLT         			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540*       	41532	EA  					STABILATOR TRIM	INCORRECT       	C				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	21	4335M					288411006				PART ON A/C DID NOT FIT BUSHING ASSY.  HOLE IN EYEBOLT IS TOO BIG.  ORDERED NEW PART AND HOLE WAS THE SAME.  API TECH SA	ID MFG MUST HAVE MADE BAD BATCH OF PARTS W/HOLE ID OF .315 INSTEAD OF CORRECT.286.  OUR SUPPLIER (KRN) MEASURED THEIR IN	VENTORY AND FOUND AN EYEBOLT W/CORRECT DIMENSION.				1	L	7	1 	3O	3	O	 	2A13    	E295				 
2003050900051	20030509	00051	CE  	2003	5	9	2003FA0000448    	1	20030313	G	3246	9520653	WHEEL           			CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300*       	17022	SO  					NLG	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	7326T	2207 				46926				ANNUAL INSPECTION, NOSEWHEEL ASSY WAS REMOVED IN ORDER TO INSPECT BEARINGS FOR CONDITION.  ONE BEARING CUP WAS FOUND COR	RODED.  WHEN LW67010 CUP WAS REMOVED FROM WHEEL HALF, DISCOVERED BEARING BORE SEVERELY WORN.  BEARING CUP HAD BEEN GLUED	 IN PLACE WITH A REDDISH COLORED ADHESIVE COMPOUND.  COMPOUND ADHERED TO THE WHEEL HALF AND BEARING CUP.  WITHOUT REMOVI	NG COMPOUND FROM WHEEL HALF, TECH PLACED A CLEAN LW67010 BEARING CUP IN THE WHEEL HALF.  CUP SEATED IN BORE WITH LIGHT H	AND PRESSURE AND SPUN FREELY, CONSIDERABLE CLEARANCE.  NOSEWHEEL BEARINGS HAD BEEN REPLACED AT THE LAST ANNUAL.  WHEEL H	ALF DID NOT EXHIBIT A SIMILAR CONDITION, CORROSION IN THE BEARING BORE INDICATES IT WOULD NOT BE LONG IN DEVELOPING.	1	H	7	1 	3O	3	O	 	3A12    	E253				 
2003050900049	20030509	00049	CE  	2003	5	9	2003FA0000449    	1	20030325	G	3243		MASTER CYLINDER 			CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300*       	17022	SO  					BRAKE SYSTEM	MISOVERHAULED   	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	17	7326T					46926				ANNUAL INSP, ACCESS PANELS WERE REMOVED,TO INSPECT BRAKE MASTER CYL, ASSOC FITTINGS.  MASTER CYL WERE DISCOVERED TO BE U	NAPPROVED PARTS.  CYL ASSY RESEMBLED CORRECT PART IN DESIGN, LABEL READ (TRANSMITTING PRESSURE CYLINDEY, TYPE CZD101, NO	: 153/200 DATE OF EX-FACTORY: 2000.11 MADE IN CHINA) (MISSPELLING OF (CYLINDEY) NOT A TYPO).  UNITS CONTAINED NO PROVISI	ON FOR PARKING BRAKE LEVERS.  BRAKE CYL HAD BEEN REPLACED LAST ANNUAL,  NO RECORD IN LOGS.  BRAKES WERE INOPERABLE, REQU	IRED BLEEDING.  ATTEMPTED TO SECURE ORIGINAL PARTS FROM IA WHO PERFORMED INSP, BUT UNABLE.  SUSPICIOUS OF INSTALLED COMP	ONENTS, PURCHASED SERVICEABLE UNITS, THESE WERE DISASSEMBLED, INSPECTED, RESEALED, INSTALLED IN PLACE OF CHINESE UNITS.	1	H	7	1 	3O	3	O	 	3A12    	E253				 
2003050900050	20030509	00050	SW  	2003	5	9	2003FA0000450    	1	20030501	G	5280		SKIN            			MOONEY	M20   	M20S        	5870226	SW  	CONT  	O550  	IO550*      	 	SO  	MCAULY	2A34C	2A34C*      	GL  	MLG DOOR	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	2186J					300047	679473	992960		SKIN ON RIGHT HAND GEAR DOOR SEPARATED FROM THE GEARDOOR FRAME.						1	L	7	1 	3O	3	O	RT	2A3     	E3SO	5	C	P3EA	 
2003060500020	20030605	00020	EA  	2003	6	5	2003FA0000451    	2	20030307	G	7261	26222631	COVER           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					SUMP	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	9750B	8483 				208B0100				UPON REMOVAL OF SUMP COVER, FOUND AFT EDGE CORRODED THROUGH TO PAINT SURFACE DUE TO TRAPPED WATER ERODING CHROMATE PRIME	R.  SUGGEST REMOVAL OF SUMPS AT 5000-6000 HOUR INTERVALS.					1	H	7	1 	3T	3	T	 	A37CE   	E2NE				 
2003060500022	20030605	00022	SO  	2003	6	5	2003FA0000452    	1	20030501	G	1100		PLACARD         			PIPER 	PA20  	PA20        	7102002	SO  	LYC   	O290  	O290        	41506	EA  					FUSELAGE	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4948M					20639				DURING ANNUAL INSPECTION IT WAS DISCOVERED THAT THE ORIGIONAL MFG DATA TAG WAS NOT ON THE AIRCRAFT.  USUALLY LOCATED ON 	THE FLOORBOARD NEAR THE BATTERY BOX.  A HANDMADE TAG WAS FOUND RIVETED TO THE FIREWALL.  MFG RECORDS INDICATE THAT THE C	ORRECT FUSELAGE SERIAL NR MATCHES THE LOGBOOK AND HANDMADE TAG.  A NEW TAG WILL BE ORDERED FROM MFG AT AN INFLATED PRICE	.			1	H	7	1 	3O	3	O	 	1A4     	E229				 
2003060500018	20030605	00018	SO  	2003	6	5	2003FA0000453    	1	20030509	G	2730		CONTROL CABLE   			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540*       	41532	EA  					ELEVATOR	FRAYED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	6841Z	5503 				252512				ELEVATOR UP CABLE FOUND TO HAVE NUMEROUS STRANDS BROKEN WHERE CABLE GOES THROUGH FAIRLEAD IN FUSELAGE AFT TAIL AREA NEAR	 HORIZONTAL STABILIZER LEADING EDGE / BATTERY AREA.  WAS FOUND BY FAA DURING CERTIFICATION OF 137 OPERATOR.					1	L	7	1 	3O	3	O	 	2A10    	E295				 
2003051300060	20030513	00060	CE  	2003	5	13	2003FA0000455    	1	20030501	G	7120	121322287	MOUNT BRACKET   			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540A1A   	41532	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	700HW					T20608034	L1008661A			ENGINE JUST CAME BACK FROM LYCOMING FOR SB553 AND WAS BOLTED ON AIRFRAME.  FOUND THE RT REAR LIFTING RING CRACKED 85 PER	CENT THROUGH.  CRACK HAD GRAY PAINT IN IT.  THIS COULD HAVE BROKEN WITH THE ENGINE UP IN THE AIR AND FULL ON SOMEONE OR 	THE AIRCRAFT.				1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2003051300051	20030513	00051	CE  	2003	5	13	2003FA0000456    	1	20030331	G	3233	99120538	ACTUATOR        			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					RT MLG	COLLAPSED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	628BS	10586	135  			5000045				RIGHT MAIN GEAR ACTUATOR COLLAPSED AND STILL INDICATED DOWN AND LOCKED.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003051300026	20030513	00026	SW  	2003	5	13	2003FA0000458    	1	20030308	G	5302	2703	RING            			HYNES 	B2    	B2B         	1440506	SW  	LYC   	O360  	O360*       	41514	EA  					TAILBOOM BLKHD	SEPARATED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	2238U					479				DURING ACCIDENT INVESTIGATION, FOUND TOP BULKHEAD RING SEPARATED FROM TAILBOOM PYLON.  TAIL ROTOR GEARBOX WAS STILL ATTA	CHED TO BULKHEAD RING.  BULKHEAD RING HAD SEPARATED FROM RIVET FLANGE AT TRANSITION RADIUS DUE TO EXISTING CRACKS ON THE	 LEFT AND RIGHT SIDES.  INSPECTION CAN BE ACCOMPLISHED THROUGH LIGHTENING HOLE OF BULKHEAD.				1	G	7	1 	3O	3	O	 	2H2     	E286				 
2003051300063	20030513	00063	GL  	2003	5	13	2003FA0000459    	2	20030415	G	7313	23031938	NOZZLE          								ALLSN 	250C  	250C20B     	03013	GL  					2ND STG TURBINE	DAMAGED         	B			TU3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07							CAT22870			TURBINE ASSY RECIEVED CUSTOMER REPORTED N1 RUB.  INSPECTION REVEALED THE 2ND STAGE NOZZLE DIAPHRAGM TO SEPARATED FROM TH	E 2ND STAGE NOZZLE DIAPHRAGM TO BE SEPARATED FROM THE NOZZLE ASSEMBLY.  BRAZE JOINT FAILED.  THIS ALLOW THE NOZZLE TO RU	B THE NR 1 AND NR 2 WHEELS.  THE WHEELS ARE NOW UNSERVICEABLE.  THIS NOZZLE HAS ACCUMULATED 389.4 HOURS SINCE INSTALL.  	THE TURBINE HAS 693.9 HOURS SINCE OVERHAUL.  AT 304.5 HOURS FOLLOWING THE TURBINE OVERHAUL, A LOSS OF POWER WAS EXPERIEN	CED.  THE TURBINE WAS INSPECTED. THE 2ND STAGE NOZZLE WAS IN SIMILAR IF NOT IDENTICAL CONDITION TO THE CURRENT DAMAGED U	NIT.  THIS NOZZLE HAS ACCUMULATED 389.4 HOURS SINCE INSTALLATION.    TURBINE TT: 4192.5, TSO 693, TC 5290, TCSO 700.						3	U			E4CE				 
2003051300031	20030513	00031	SO  	2003	5	13	2003FA0000461    	2	20030430	G	8500		ENGINE          			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  						MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	61EW	16   	16   			1302				AIRCRAFT ENGINE DID NOT RESPOND TO FULL THROTTLE DURING ATTEMPTED REJECTED LANDING FOLLOWING ENCOUNTER WITH SEVERE LOW A	LTITUDE TURBULENCE.  SUBSEQUENT EXAMINATION OF ENGINE AND COMPONENTS REVEALED NO ABNORMALIES.  RECOMMEND CAUTIONARY NOTE	 IN PILOT OPERATING HANDBOOK REGARDING ENGINE POWER RESPONSE DURING TURBULENCE.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003051300027	20030513	00027	SO  	2003	5	13	2003FA0000462    	1	20030312	G	3710		GASKET          	AIRBORNE    		PIPER 	PA32  	PA32301T    	7103209	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					VACUUM PUMP	UNSERVICEABLE   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	81573	826  			11AP3962	328024004				GASKET FAILED NEAR MOUNTING STUD, ALLOWING OIL UNDER PRESSURE TO EXCAPE OVERBOARD, RESULTING IN LOSS OF OIL PRESSURE AND	 SUBSEQUENT EMERGENCY OFF AIRPORT LANDING.  THE VACUUM PUMP WAS INSTALLED NEW IN DECEMBER 1998 AND HAS BEEN IN SERVICE F	OR 826.3 HOURS.  THE GASKET WAS FURNISHED NEW WITH THE VACUUM PUMP.  MODEL 215CC, S/N 11AP3962.				1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003051500001	20030515	00001	NM  	2003	5	15	2003FA0000463    	1	20030509	G	3710	CH216CW	PUMP            			LANCAR	LC40  	LC40550FG   	5150000	NM  										DRY AIR	FAILED          	B				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	05	727VP	7    				40069				DRY AIR VACUMM PUMP SHAFT SHEARD IN FLIGHT AT AROUND 7.0 HRS TOTAL TIME SINCE NEW.  THE BACK-UP PUMP MODEL NR CH216CW SE	RIAL NR C40069 ALSO FAILED BEFORE REACHING DESTINATION WITH A TOTAL AIRFRAME TIME OF 13.0 HRS.   3 PUMPS WERE NEW AND IN	STALLED DURING PRODUCTION OF THE AIRCRAFT.				1	L	7	1 	3O			RT	A00003SA					 
2003051300059	20030513	00059	CE  	2003	5	13	2003FA0000464    	1	20030512	G	3510	25F2108	BOOT            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										OXYGEN TANK	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11										OXYGEN COVER BOOTS WERE TEARING.  UPON INVESTIGATION, FOUND THE BOOTS WERE MADE OF WRONG MATERIAL AND THE MATERIAL DIDN'	T HAVE PROPER FLAME RESISTANT TREATMENT.  THE BOOTS IN QUESTION WERE MADE BY AER, A COMPANY CONTRACTED BY BRITISH AEROSP	ACE.  BOOTS WE RECEIVE BY PPA (ALSO CONTRACTED BY BRITISH AEROSPACE) ARE ALL GOOD.				2	L	7	2 	4F			RT	A3EU    					 
2003051400227	20030514	00227	CE  	2003	5	14	2003FA0000465    	1	20030430	G	3230	204303112	BELLCRANK       			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					NLG WW	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	06	52668	4355 				177RG1241				NOSE GEAR FAILED TO EXTEND ON LANDING SUBSTANTIAL DAMAGE OCCURRED.  JACKED AIRCRAFT, CYCLED GEAR TO UP POSITION WITH AFT	 LG DOORS DISCONNECTED.  ON EXTENTION, NOSE GEAR FAILED ONCE AGAIN.  MECHANICAL UPLOCK FAILED TO RELEASE.  SUSPECT OUT O	F ADJUSTMENT.				1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2003051400231	20030514	00231	GL  	2003	5	14	2003FA0000466    	2	20030403	G	7230	65278	BLADE           			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					HP TURBINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	349SF	1017 			RRL0526	5250049	1125			ON TAKEOFF, NOTICE SMALL BIRD PASS OVER NOSE AND LEFT WINDSHIELD, TAKEOFF WAS NORMAL.  DURING CLIMBOUT, 14,500 FEET, STA	RTED TO HEAR A LOUD WHINE AND VIBRATION COMING FROM LEFT ENGINE.  DIVERTED AND BROUGHT LEFT ENGINE TO FLIGHT IDLE.  DESC	ENT AND LANDING WAS NORMAL.  DURING TAXI IN, SHUTDOWN LEFT ENGINE TO PREVENT POSSIBLE DAMAGE. INITIAL INSPECTION AFTER P	ILOT REPORTED EVENT.  REVEALED EXTENSIVE HP COMPRESSOR AND TURBINE DAMAGE WITH HEAVY OIL CONTAMINATION.  CONTINUED OPERA	TION, WOULD RESULT IN TOTAL CATASTROPHIC FAILURE.		1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2003051300198	20030513	00198	SO  	2003	5	13	2003FA0000468    	2	20030423	G	8550	626739	COLLAR          								CONT  	O520  	IO520F      	17032	SO  					GOVERNOR OIL	MISALIGNED      	B				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	28							W			IN ASSEMBLING A NEW STANDARD GOVERNOR OIL TRANSFER COLLAR TO THE CRANKSHAFT IT WAS FOUND TO BIND ON THE JOURNAL.  PRIOR 	TO DISASSEMBLING THE COLLAR HALVES THE INSIDE DIAMETER WAS NOTED TO BE SMOOTH AND COLLAR TO JOURNAL CLEARANCE WITHIN NEW	 LIMITS.  ONCE THE COLLAR HAD BEEN DISASSEMBLED AND REASSEMBLED A STEP OF APPROXIMATELY .001 INCH WAS FOUND AT THE PARTI	NG SURFACES.  INSTALLING THE COLLAR ON THE CRANKSHAFT AND TORQUING IT IN PLACE CAUSED IT TO BIND IN AN INTERFERENCE FIT.	  IT APPEARS THE TWO HALVES ARE UNDER SOME TORSIONAL STRESS WHICH IS RELIEVED UPON TAKING THEM APART.  THIS NOW THE SIXT	H CONSECUTIVE COLLAR RECEIVED THAT EXHIBITS THESE CHARACTERISTICS.						3	O			E5CE				 
2003051400229	20030514	00229	EA  	2003	5	14	2003FA0000469    	2	20030409	G	7414	10157123Y	GEAR            	BENDIX      		PIPER 	PA22  	PA22108     	7102204	SO  	LYC   	O235  	O235*       	41505	EA  					LEFT MAGNETO	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	4860Z	1876 			763162	228436				THE KEEPER FOR THE MAGNETO TIMING GEAR WAS FOUND LOOSE IN THE MAG CASE.  THE KEEPER, TIMING GEAR KEY WAY AND SHAFT KEY W	AY SLOT WERE ALL FOUND WORN.  THIS WAS A 1961 ENGINE, WITH 1876 HOURS TT.  NO RECORD OF MAG MAINTENANCE COULD BE LOCATED	.  KEY PN 10-907-88-5.				1	H	7	1 	3O	3	O	 	1A6     	E223				 
2003051400235	20030514	00235	SO  	2003	5	14	2003FA0000470    	1	20030415	G	3210	402427	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					DRAG LINK	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	777RX					274728				LEFT LANDING GEAR COLLAPSED ON LANDING.  CENTER BOLT ON LEFT MAIN GEAR DRAG LINK SHEARED AND PULLED LOOSE FROM THE DRAG 	LINK REMOVING SUPPORT FROM THE LEG.  SHAPE OF THE BOLT AFTER SHEARING SUGGEST TREMENDONS LOAD, PROBABLE BAD LANDINGS BOL	T WAS TAKEN BY REP FOR TEST.  TO PREVENT REOCCURRENCE DEPEND ON WHETHER IT IS A MATERIALS FAILURE OR PILOT ERROR.				1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2003051400228	20030514	00228	CE  	2003	5	14	2003FA0000471    	1	20030513	G	2710	0510105364	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  										AILERON	CHAFED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	472ER					17280669				DURING A ROUTINE INSPECTION, THE LEFT AILERON BALANCE CABLE (P/N 0510105-364) WAS FOUND CHAFING ON A FAIRLEAD LOCATED MI	DWAY THROUGH THE FLAP WELL AREA. THE CABLE IS EXTREMELY DIFFICULT TO EXAMINE THOROUGHLY WHILE INSTALLED. A BORESCOPE CAN	 AID IN VIEWING THE AREA MORE ACCURATELY. THE BEST METHOD IS TO REMOVE THE CABLE AND PERFORM A BENDING TEST ON THE SHINY	 AREA, WHICH WILL EXPOSE ANY BROKEN WIRES. THIS OPERATOR HAS A FLEET OF APROXIMATELY 60 AIRCRAFT OF THIS MODEL, AND THIS	 PROBLEM BEGINS TO MANIFEST ITELF AS EARLY AS 1,500 HOURS TIS.		1	H	7	1 	3O			NT	3A12    					 
2003051400236	20030514	00236	CE  	2003	5	14	2003FA0000472    	1	20030513	G	2710	0510105365	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					AILERON	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	441ER					17280660	RL1192151A			DURING A ROUTINE INSPECTION, THE RIGHT AILERON BALANCE CABLE (P/N 0510105-365) WAS FOUND CHAFING ON A FAIRLEAD LOCATED M	IDWAY THROUGH THE FLAP WELL AREA. THE CABLE IS EXTREMELY DIFFICULT TO EXAMINE THOROUGHLY WHILE INSTALLED. A BORESCOPE CA	N AID IN VIEWING THE AREA MORE ACCURATELY. THE BEST METHOD IS TO REMOVE THE CABLE AND PERFORM A BENDING TEST ON THE SHIN	Y AREA, WHICH WILL EXPOSE ANY BROKEN WIRES. THIS OPERATOR HAS A FLEET OF APROXIMATELY 60 AIRCRAFT OF THIS MODEL, AND THI	S PROBLEM BEGINS TO MANIFEST ITELF AS EARLY AS 1,500 HOURS TIS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003060500059	20030605	00059	CE  	2003	6	5	2003FA0000473    	1	20030513	G	2710	0510105364	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					AILERON	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	441ER					17280660	RL1192151A			DURING A ROUTINE INSPECTION, THE LEFT AILERON BALANCE CABLE WAS FOUND CHAFING ON A FAIRLEAD LOCATED MIDWAY THROUGH THE F	LAP WELL AREA. THE CABLE IS EXTREMELY DIFFICULT TO EXAMINE THOROUGHLY WHILE INSTALLED. A BORESCOPE CAN AID IN VIEWING TH	E AREA MORE ACCURATELY. THE BEST METHOD IS TO REMOVE THE CABLE AND PERFORM A BENDING TEST ON THE SHINY AREA, WHICH WILL 	EXPOSE ANY BROKEN WIRES. THIS OPERATOR HAS A FLEET OF APROXIMATELY 60 AIRCRAFT OF THIS MODEL, AND THIS PROBLEM BEGINS TO	 MANIFEST ITELF AS EARLY AS 1,500 HOURS TIS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003060500060	20030605	00060	CE  	2003	6	5	2003FA0000474    	1	20030513	G	2710	0510105365	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					AILERON	CHAFED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	472ER					17280669	L2734251A			DURING A ROUTINE INSPECTION, THE RIGHT AILERON BALANCE CABLE WAS FOUND CHAFING ON A FAIRLEAD LOCATED MIDWAY THROUGH THE 	FLAP WELL AREA. THE CABLE IS EXTREMELY DIFFICULT TO EXAMINE THOROUGHLY WHILE INSTALLED. A BORESCOPE CAN AID IN VIEWING T	HE AREA MORE ACCURATELY. THE BEST METHOD IS TO REMOVE THE CABLE AND PERFORM A BENDING TEST ON THE SHINY AREA, WHICH WILL	 EXPOSE ANY BROKEN WIRES. THIS OPERATOR HAS A FLEET OF APROXIMATELY 60 AIRCRAFT OF THIS MODEL, AND THIS PROBLEM BEGINS T	O MANIFEST ITELF AS EARLY AS 1,500 HOURS TIS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003060500056	20030605	00056	CE  	2003	6	5	2003FA0000475    	1	20030513	G	2730	531204423	BRACKET         			CESSNA	340   	340A        	2076405	CE  										TAIL SECTION	BROKEN          	B				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	12315	2223 				340A1812				DURING ANNUAL INSPECTION,  ELEVATOR CONTROL SYS HAD EXCESSIVE FREE PLAY. FOUND BRACKETS WERE BROKEN.  THESE BRACKETS SUP	PORT ELEVATOR BELLCRANK IN TAIL SECTION.  BOTH BRACKETS WERE MISSING THREE RIVETS EACH ON THE VERTICAL ANGLE THAT ATTACH	 RESPECTIVE BRACKET TO THEIR FORWARD CHANNEL.  BOTH FORWARD TOP & LOWER TABS WERE BROKEN OFF DUE TO THREE RIVETS MISSING	 ON THE VERTICAL L SECTION.  PARTS NEVER WERE DRILLED FOR THE REQUIRED RIVETS FROM FACTORY. IF THE REAR SECTION OF THESE	 BRACKETS WERE TO BREAK OFF, YOU WOULD LOOSE COMPLETE ELEVATOR CONTROL.  THIS A/C WAS MANUFACTURED IN 1984 AND HAS COME 	THROUGH INSPECTIONS TO DATE WITH THESE RIVETS MISSING.	1	L	7	2 	3O			 	3A25    					 
2003060500058	20030605	00058	CE  	2003	6	5	2003FA0000476    	1	20030513	G	3233		ARM             			CESSNA	421   	421B        	2076014	CE  										MLG DOOR ACT	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	421KL	6551 				421B0015				RIGHT GEAR INBOARD DOOR CAME OPEN IN FLIGHT.  FOUND THE ACTUATOR ARM BROKE LOOSE AND TURNED ON ITS SHAFT. THIS ALLOW THE	 GEAR DOOR TO COME OPEN IN FLIGHT.  ONLY WARNING IS THE ADDED AIR NOISE. THE ARM IS A PRESS FIT ON THIS PART NUMBER AND 	HAS BEEN SUPERCEDED BY P/N 5045001-10 WHICH IS WELDED.  IF THIS DOOR WERE TO COME OPEN ON TAKE OFF AND THE GEAR WAS RETR	ACTED IT COULD HANG UP THE GEAR.  PILOT FOUND THIS CONDITION AFTER HE LANDED.			1	L	7	2 	3O			 	A7CE    					 
2003060500061	20030605	00061	CE  	2003	6	5	2003FA0000477    	1	20030513	G	2710	0510105362	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					AILERON	CHAFED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	472ER					17280669	L2734251A			DURING A ROUTINE INSPECTION, THE RIGHT AILERON BALANCE CABLE (P/N 0510105-362) WAS FOUND CHAFING ON A FAIRLEAD LOCATED M	IDWAY THROUGH THE FLAP WELL AREA. THE CABLE IS EXTREMELY DIFFICULT TO EXAMINE THOROUGHLY WHILE INSTALLED. A BORESCOPE CA	N AID IN VIEWING THE AREA MORE ACCURATELY. THE BEST METHOD IS TO REMOVE THE CABLE AND PERFORM A BENDING TEST ON THE SHIN	Y AREA, WHICH WILL EXPOSE ANY BROKEN WIRES. THIS OPERATOR HAS A FLEET OF APROXIMATELY 60 AIRCRAFT OF THIS MODEL, AND THI	S PROBLEM BEGINS TO MANIFEST ITELF AS EARLY AS 1,500 HOURS TIS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003060500062	20030605	00062	CE  	2003	6	5	2003FA0000478    	1	20030427	G	3222	5322012166	BOLT            			BEECH 	36    	A36         	1151604	CE  	PWA   	PT6   	PT6*        	52043	EA  					NLG	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	429P	294  	80   			E3356				DURING PILOTS PREFLIGHT, FOUND THE NUT LAYING ON THE GROUND FOR THE LOWER NOSE GEAR BOLT (532.20.12.166). THIS BOLT ATTA	CHES THE INNER SHOCK STRUT TUBE (LOWER) TO THE NOSE GEAR FORK, AND RETAINES THE INNER SLEEVE PLUG. THE BOLT WAS SHEARED 	OF FLUSH WITH THE NUT, THERE WERE SIGNS OF EXSISTING CORROSION AT THE FRACTURE LINE.				1	L	7	1 	3O	3	T	 	3A15    	E2NE				 
2003051500003	20030515	00003	CE  	2003	5	15	2003FA0000480    	1	20030512	G	2611	153831	FIRE LOOP       			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ610*      	30006	NE  					RT ENGINE	LOOSE           	E				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N			FALSE WARNING             			NR	NOT REPORTED   	1			SO	11	23RZ					164	251Y208A			FIRE DETECTION LIGHT CAME ON IN FLIGHT. REDUCED ENGINE POWER TO IDLE, AFTER 1 MINUTE SHUT DOWN ENGINE AND EXTIGUISHED BO	TH BOTTLES. ONCE ON THE GROUND ENGINE WAS INSPECTED, NO EVIDENCE OF FIRE, FOUND LOOSE CONNECTION ON FIRE LOOP.					2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2003060500064	20030605	00064	EA  	2003	6	5	2003FA0000481    	2	20030501	G	7414		BEARING         	ELECTROSYS  		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAGNETO	FAILED          	B			T22R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			WP	05	23617				C090099	2265				ENGINE WAS IN RUN UP/TEST WHEN LEFT HAND MAGNETO FAILED CHECK (DEAD MAG).  MAGNETO PROBLEM WAS INVESTIGATED AND THE FOLL	OWING CONDITION WAS NOTED.  THREE SCREWS WERE MISSING THAT ATTACH THE LOWER AND UPPER MAIN HOUSING.  TWO OF THESE SCREWS	 SEEMED TO HAVE BACKED OUT AND THE THIRD BROKE WHICH LEFT A PORTION OF THE THREADED SCREW REMAINING IN THE LOWER HOUSING	.  THERE WERE ONLY TWO REMAINING SCREWS SECURING THE TWO HOUSINGS TOGETHER WHICH HAD STARTED TO BACK OUT.  ROLLER BEARIN	G FAILED WHICH LED TO LOWER SEAL FAILURE AND DRIVE GEAR DAMAGE DUE TO SHAFT EXCESSIVE PLAY.  LOWER MAGNETO HOUSING HAS A	 TWO INCH CRACK ON THE BOTTOM SIDE LEFT OF PLASTIC INSPECTION PLUG.	1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003060500065	20030605	00065	CE  	2003	6	5	2003FA0000482    	1	20030203	G	2460	MC012A	J-BOX           			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					FIREWALL	LOOSE           	B			Z08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	465CA	3600 				17280465				FOUND THE ELECTRICAL JUNCTION BOX (J-BOX) BRACKETS LOOSE.  FURTHER INVESTIGATION REVEALED THAT THE 12 RIVETS THAT HOLD T	HE BRACKETS TO THE BOX WHERE LOOSE AND 6 OF THE 12 RIVETS THE RIVET HEADS WERE POPPING OFF, CRACKED AND FRACTURED (PHOTO	S).  IF LEFT UNATTENDED THIS COULD CAUSE THE BOX TO COME LOOSE FROM THE BRACKETS AND CAUSE POSSIBLE ELECTRICAL PROBLEMS.	  ALSO THE RIVET HEADS COMING LOOSE COULD CAUSE ARCING INSIDE THE BOX.  WAS ADVISED BY AC MFG TO REPLACE THE B-STYLE RIV	ETS WITH AD RIVETS.  NOTE:  IN ORDER TO DO THIS HAD TO DISASSEMBLE THE WHOLE BOX AND COMPONENTS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003052700116	20030527	00116	CE  	2003	5	27	2003FA0000484    	1	20030409	G	3233	12810015	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					RT MLG	CRACKED         	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9744B					172RG1007				DURING A CHECK RIDE,  THE PILOT EXAMINER REPORTED A CLUNKING NOISE AS THE GEAR WAS CYCLED.  UPON INSPECTION AND REMOVAL 	OF THE RIGHT MAIN LANDING GEAR ACTUATOR, IT WAS FOUND TO BE CRACKED ALL THE WAY ACROSS THE LARGE BORE AT THE FORWARD BOL	T HOLE.  THE SECTOR GEAR AND THE PISTON IN THE ACTUATOR WERE ALSO DAMAGED.  MFG SHOULD REDESIGN THE ACTUATOR AND GEAR PI	VOT ASSEMBLIES, MAKING IT OUT OF STEEL OR ANOTHER MATERIAL THAT MIGHT STAND UP TO THE REPEATED STRESS THAT IS PUT ON THI	S PART.  THIS IS AN ONGOING, RECURRING PROBLEM WITH THIS TYPE OF LANDING GEAR.  THIS OCCURS ON AVERAGE AROUND 2000 FLIGH	T HOURS OR SOONER AND WITHOUT WARNING.  SEB 01-2 HAD BEEN COMPLIED WITH AT TIME OF INSTALLATION.	1	H	7	1 	3O	3	O	 	3A17    	E286				 
2003060500066	20030605	00066	CE  	2003	6	5	2003FA0000485    	1	20030425	G	3233	12810013	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	RT MLG	CRACKED         	B			Z08R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	9865B	8128 				172RG1061	L2843136A			PILOT REPORTED HEARING A LOUD BANG WHEN LAND GEAR WAS RETRACTED.  A/C LANDED WITHOUT INCIDENT.  INVEST REVEALED MFG PN 1	281001-3, RT MAIN GEAR ACTR BODY CRACKED THROUGH (PHOTOS).  COMPLIED  WITH SEB AT 5741.4 HRS. A/C TT.  AD2001-06-06 HAS 	BEEN COMPLIED WITH.  FOUND CRACK STARTING WHERE LANDING GEAR CASTING ATTACHES ONTO SPOT FACE OF BODY.  COULD NOT SEE UNL	ESS ACTUATOR WAS REMOVED.  FOUND MFG PN 9882004-1 PISTON AND 9882002-2 SECTOR GEAR SHOWS SIGNS OF GEAR GALLING.  SECTOR 	GEAR WAS REPLACED 4011.0 HOURS PRIOR.  ACTUATOR BODY MAY HAVE FAILED DUE TO FATIGUE.  INSTALLED NEW ACTUATOR MFG PN 9882	015-4 AND SECTOR GEAR AS REQUIRED.  TEST RAN LANDING GEAR AND PERFORMED CHECKS AND TESTS, FOUND OK.	1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003052700128	20030527	00128	SO  	2003	5	27	2003FA0000486    	2	20030506	G	8520	65368819	CRANKCASE       			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	198AM	305  				1105	357275			TWO ONE INCH CRACKS WERE FOUND ON THE FORWARD, RT SIDE OF THE ENGINE CRANKCASE.  THE CRACKS ARE LOCATED AROUND THE FRONT	 ALTERNATOR MOUNTING BRACKET.  TOP REAR CASE THROUGH BOLT.  THIS IS THE THIRD AIRCRAFT WER ARE DOING AN ENGINE CHANGE ON	 WITH THIS DISCREPANCY.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003060500067	20030605	00067	SO  	2003	6	5	2003FA0000487    	1	20030501	G	5730		SKIN            			PIPER 	PA46  	PA46350P    	7104602	SO  										LT WING	CRACKED         	B			X0FR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9173Z		3476 			4622039				DURING ANNUAL INSPECTION, TWO CRACKS WERE FOUND ON THE LOWER LEFT WING SKIN, NEAR THE LOWER SPAR CAP, OUTBOARD OF THE MA	IN LANDING GEAR DOOR HINGE.  BOTH CRACKS WERE LOCATED NEAR THE DOUBLER, KIT NR 766-210, PREVIOUSLY INSTALLED IAW MFG SB.	  THIS AIRCRAFT HAS 4324.7 HRS TT AND 3476.3 HRS SINCE THE KIT WAS INSTALLED.  INSPECTION SHOWED NO DELAMINATION OF INNE	R DOUBLERS.  RECOMMEND INSPECTING ANNUALLY.			1	L	7	1 	3O			RT	A25SO   					 
2003060500075	20030605	00075	SO  	2003	6	5	2003FA0000488    	1	20030422	G	2701		YOKE            			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					COCKCPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	8151P	3428 				243406				DURING ANNUAL INSPECTION, OWNER REQUESTED YOKES BE CHANGED.  BOTH YOKES WERE FOUND TO BE CRACKED ON THE LOWER SIDE, THRO	UGH THE HOLE FOR THE ROLL PIN.  THE CONDITION WAS NOT VISIBLE WIGHOUT REMOVING EMBLEM AND YOKE, AS PLASTIC COATING ON YO	KE EXTERIOR HAD NOT CRACKED EVEN THOUGH ALUMINUM YOKE BENEATH WAS CRACKED FULLY THROUGH.  IF YOKES ARE REMOVED OR EMBLEM	 IS REMOVED LOOK HARD FOR CRACKS IN LINE WITH ROLL PIN HOLE.			1	L	7	1 	3O	3	O	 	1A15    	E295				 
2003060500077	20030605	00077	SO  	2003	6	5	2003FA0000489    	1	20030501	G	7921	2071011	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4A     	41514	EA  					ENGINE OIL	CRACKED         	B			VJ3R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	4133D					2843117	RL202836A			AFTER LANDING FLIGHT CREW NOTICED OIL ON SIDE OF AIRCRAFT.  MAINTENANCE INVESTIGATED AND FOUND OIL COOLER CRACKED AND LE	AKING.  CAUSE OF LEAK IS FAILURE OF OIL COOLER AT SEAMS.  RECOMMEND TO USE SOLID PIECE OIL COOLER.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003060500080	20030605	00080	CE  	2003	6	5	2003FA0000490    	1	20030429	G	7603		THROTTLE CABLE  			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL CONTROL	JAMMED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1570A	402  				CE1333	820456R			PILOT REPORTED THROTTLE WAS HARD TO MOVE.  ON FURTHER INVESTIGATION FOUND THROTTLE BUTTON WOULD JAM AND NOT RELEASE.  TH	ESE CABLES ARE PRETTY RELIABLE, AT THIS TIME, NO PROBLEM, CAUSE OR RECOMMENDATIONS TO PREVENT THIS FROM RECURRING.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003060500081	20030605	00081	SO  	2003	6	5	2003FA0000491    	1	20030505	G	3610	RA215CC	PUMP            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					PNEUMATIC SYS	BROKEN          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4130W					2843204	L2847836A			DURING FLIGHT AIRCREW REPORTED NO AIR PRESSURE.  MAINTENANCE INVESTIGATED AND FOUND DRIVE SHAFT ON AIR PUMP HAD SHEARED.	  PROBABLE CAUSE IS VANES HAD SHEAR AND JAMMED SHAFT CAUSE IT TO SHEAR.  NO RECOMMENDATIONS.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003060500082	20030605	00082	EA  	2003	6	5	2003FA0000492    	2	20030428	G	7314		SEAL            			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					FUEL PUMP	LEAKING         	B			VJ3R	O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			WP	07	863AF	893  			B4377	85003	L2802548A			FLIGHT CREW NOTICED ODOR OF FUEL DURING GROUND RUN.  TECHNICIAN TROUBLESHOOT FUEL SYSTEM AND NOTICED FUEL STAINS ON FUEL	 PUMP.  SO REPLACED FUEL PUMP.  ONCE PUMP REMOVED NOTICED GEAR SPLINE WAS WORN DASTRICALLY.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003061100001	20030611	00001	CE  	2003	6	11	2003FA0000493    	1	20030505	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					PNEUMATIC SYS	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1556A	645  				CE1318	820495R			DURING GROUND RUN UP OUTPUT OF ENGINE DRIVEN DRY AIR PUMP FAILED TO PUT OUT PROPER PRESSURE AT IDLE RPM.  RAN AIRCRAFT U	P AND AIR PRESSURE STILL LOW AT HIGHER RPM.  TESTED SYSTEM AND FOUND ENGINE DRIVEN AIR PUMP NOT WORKING PROPERLY.  BELIE	VE DRY AIR PUMP VANES ARE WORN.  NO RECOMMENDATIONS.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003060500083	20030605	00083	CE  	2003	6	5	2003FA0000494    	1	20030505	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					PNEUMATIC SYS	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5587K	297  				CE1392	825812R			DURING GROUND RUN UP OUTPUT OF ENGINE DRIVEN DRY AIR PUMP FAILED TO PUT OUT PROPER PRESSURE AT IDLE RPM.  RAN AIRCRAFT U	P AND AIR PRESSURE STILL LOW AT HIGHTER RPM TESTED SYSTEM AND FOUND ENGINE DRIVEN AIR PUMP NOT WORKING PROPERLY.  BELIEV	E DRY AIR PUMP VANES ARE WORN.  NO RECOMMEDATIONS.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003060500084	20030605	00084	CE  	2003	6	5	2003FA0000495    	1	20030505	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					PNEUMATIC SYS	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8242T					CE1610	825836R			DURING GROUND RUN UP OUTPUT OF ENGINE DRIVEN DRY AIR PUMP FAILED TO PUT OUT PROPER PRESSURE AT IDLE RPM.  RAN AIRCRAFT U	P AND AIR PRESSURE STILL LOW AT HIGHT RPM.  TESTED SYSTEM AND FOUND ENGINE DRIVEN AIR PUMP NO WORKING PROPERLY.  BELIEVE	 DRY AIR PUMP VANES ARE WORN.  HAVE NO RECOMMENDATIONS.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003060500085	20030605	00085	CE  	2003	6	5	2003FA0000496    	1	20030505	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					PNEUMATIC SYS	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5609S	414  				CE1454	825756R			DURING GROUND RUN UP OUTPUT OF ENGINE DRIVEN DRY AIR PUMP FAILED TO PUT OUT PROPER PRESSURE AT IDLE RPM.  RAN AIRCRAFT U	P AND AIR PRESSURE STILL LOW AT HIGHER RPM.  TESTED SYSTEM AND FOUND ENGINE DRIVEN AIR PUMP NO WORKING PROPERLY.  BELIEV	E DRY AIR PUMP VANES ARE WORN.  NO RECOMMENDATIONS.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003060500086	20030605	00086	EU  	2003	6	5	2003FA0000497    	1	20030503	G	3230	X03004B	VALVE           			GROB  	120   	G120A       	1660208	EU  										MLG MANIFOLD	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	802  				85004				PILOT REPORTED GEAR WAS SLOWLY TO EXTEND, OVER 1 MINUTE.  AFTER PULLING 3 G`S AT 150 KNOTS GEAR FINALLY EXTENDED DOWN AN	D LOCKED.  ON FURTHER INVESTIGATION WE FOUND NO PROBABLE CAUSE OR RECOMMENDATIONS TO PREVENT THIS FROM RECURRING.					1	L	7	1 	3O			RT	A49CE   					 
2003060500102	20030605	00102	SO  	2003	6	5	2003FA0000498    	1	20030414	G	2720	6010532	SPRING          			PIPER 	PA20  	PA20        	7102002	SO  	LYC   	O360  	O360*       	41514	EA  					RUDDER RETURN	FAILED          	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	03	4948M	903  				20639				DURING TAXI TO POSITION FOR TAKEOFF, THE RIGHT RUDDER RETURN SPRING FAILED AT THE ATTACHMENT HOOK TO THE CABLE BELLCRACK	.  THE PILOT HEARD A NOISE BUT DID NOT REALIZE THE SPRING HAD FAILED UNTIL LATE IN THE ROLLOUT.  THE FLIGHT CYCLE WAS CO	MPLETED WITHOUT EVENT.  ABOVE NORMAL RIGHT RUDDER PRESSURE WAS REQUIRED TO CORRECT YAW.  PART FAILURE APPEARS TO BE THE 	RESULT OF FATIGUE.			1	H	7	1 	3O	3	O	 	1A4     	E286				 
2003060600002	20030606	00002	EA  	2003	6	6	2003FA0000499    	2	20030417	G	7310	3011158	LOCK PLATE      								PWA   	PT6   	PT6A34      	52043	EA  					FUEL MANIFOLD	DISTORTED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17		6921 					PCE14125			LOCKPLATE WAS DISTORTED AND FAILED TO RETAIN FUEL TRANSFER TUBE IN THE FUEL MANIFOLD ADAPTER.  RESULTING, FUEL LEAK CAUS	E POWER LOSS/ EMERGENCY LANDING/ CRASH.  RECOMMEND LOCKPLATES ARE INSPECTED FOR PROPER SEATING IN TRANSFER TUBES AT 100 	HOUR ANNUAL INSPECTIONS.									4	T			E4EA				 
2003060500105	20030605	00105	EA  	2003	6	5	2003FA0000500    	2	20030403	G	7314	2B663FR	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	4093W		2402 			318152176				UPON INSPECTION OF THE ELECTRIC FUEL PUMP, HAD DISCOVERED FUEL STAINS AROUND THE TOP AND BOTTOM OF THE MOTOR HOUSING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003060500079	20030605	00079	NE  	2003	6	5	2003FA0000501    	2	20030514	G	7250	775404	BLADE           								PWA   	JT8   	JT8D217     	52053	NE  					TURBINE SECTION	CRACKED         	B			T48R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09		5935 	5935 				708409			T4 BLADE PART NUMBER 775404 KNIFE EDGES AXIAL CRACKS. (APPROXIMATELY 40 PERCENT)											4	F			E9NE				 
2003060500164	20030605	00164	SO  	2003	6	5	2003FA0000502    	2	20030501	G	8530	653816A7BP	CYLINDER        								CONT  	O200  	O200A       	17020	SO  					ROCKER SHAFTS	GALLED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25							10518A			ENGINE INSPECTED AFTER APPROXIMATELY 70 HOURS OF OPERATION ON NEW MFG ASSY.  GALLING HAD OCCURED ON THE ROCKERSHAFTS.  T	HE MFG HAD MODIFIED THE AGE OLD DESIGN TO INCLUDE LOCKING THE ROCKER SHAFT IN PLACE WITH A SET SCREW.  THE SHAFT, BEING 	UNABLE TO FLOAT AND ROTATE FOR PROPER OILING AND WEAR, GALLED.  RECOMMEND ALLOWING THE ROCKER SHAFT TO FLOAT AS IT WAS O	RIGINALLY DESIGNED TO DO. OTHER PROBLEMS ENCOUNTERED WITH THESE ASSEMBLIES INCLUDE THE BLACK CARBON/ GRAPHITE COATINGS O	N THE PISTONS FLAKING OFF AND CAUSING A POTENTIALLY BLOCKED OIL SCREEN AND SUBSEQUENT ENGINE FAILURE.							3	O			E252				 
2003060500165	20030605	00165	CE  	2003	6	5	2003FA0000503    	1	20030410	G	7120	05510231	MOUNT           			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	96573	7262 	970  			17276088	L865336A			ENGINE MOUNT WAS REMOVED FOR INSPECTION FOLLOWING PROPELLER STRIKE WITH AIRCRAFT.  AEROSPACE WELDING REPORTED MOUNT WAS 	PUSHED UP ON LOWER SECTION AND PUSHED IN ON RIGHT SIDE.  AT REMOVAL MOUNT AWAS DIFFICULT TO REMOVE FORM ATTACHMENT BOLTS	.  AFTER PROPELLER STRIKE ENGINE MOUNT SHOULD BE REMOVED FOR INSPECTION.				1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2003060500168	20030605	00168	CE  	2003	6	5	2003FA0000506    	1	20030416	G	3213	07436214	STRUT           			CESSNA	182   	182S        	2072701	CE  	PWA   	PT6   	PT6A11      	52043	NE  					MLG	DEFECTIVE       	B			QU5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	603TC					18280712				THE DIAMETER OF THE OLOE TUBE IS .0012 INCHES SMALLER THAN THE BORE OF THE FORK.  THE FORK WAS HELD ON ONLY BY THE NR5 B	OLT.  THE OLEO TUBE HAS AN UNUSUAL WEAR PATTERN OF CIRCUMFERENTIAL WEAR AND RIDGES.  IT IS BELIEVED THAT THIS OLEO WAS D	EFECTIVE FROM THE MANUFACTURER.  IT IS RECOMMENDED IXISTING AIRCRAFT BE INSPECTED FOR THIS CONDITION.  THE IMPROPER FIT 	OF THE TUBE TO THE FORK WILL EVENTUALLY CAUSE EXCESSIVE WEAR ON THE FORK AND POSSIBLE NLG FAILURE.			1	H	7	1 	3O	3	T	NT	3A13    	E4EA				 
2003060600009	20030606	00009	CE  	2003	6	6	2003FA0000507    	1	20030508	G	2434	632018	DRIVE GEAR      			CESSNA	335   	335         	2075601	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ALTERNATOR	INOPERATIVE     	B			WDAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	918AA		972  			3350048	815072R			REPORTED ALTERNATOR INOPERATIVE.  UPON REMOVAL OF ALTERNATOR FOUND ALTERNATOR DRIVE GEAR TO BE DESTROYED.  REMOVED AND I	NSPECTED OIL FILTER.  FOUND SIGNIFICANT AMOUNTS OF METAL.					1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2003060600012	20030606	00012		2003	6	6	2003FA0000508    	4	20030426	G	2561	KS9P0101HC2	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			EA	07										LIFE VEST FAILED MFG RECOMMEND CELL PRESSURE TEST IAW 25-60-1 DOM: JANUARY 1981.																			 
2003060600013	20030606	00013		2003	6	6	2003FA0000509    	4	20030428	G	2561	6A12P0201101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			EA	07										INDIVIDUAL FLOAT DEVICE FAILED MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-13.  DOM: OCT 1983.																			 
2003052700124	20030527	00124		2003	5	27	2003FA0000510    	4	20030428	G	2561	6A12P0201101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOAT DEVICE FAILED.  MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-13.  DOM:  OCT 1983.																			 
2003052700121	20030527	00121	NM  	2003	5	27	2003FA0000511    	1	20030425	G	6220	A1581	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320*       	41508	EA  					SPINDLE	ROUGH           	B			GJOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	8051M	464  				1168				ROTORCRAFT EXPERIENCED UNUSUAL VIBRATION.  REMOVED MAIN ROTOR BLADES FOUND UPON VISUAL (BY FEEL) SPINDLE BEARINGS WERE R	OUGH AND BRINELD.  FACTORY STATES THIS IS CAUSED BY MAIN ROTOR OVERSPEEDS.  IF AIRCRAFT/ROTORCAFT EXPERIENCES UNUSUAL VI	BRATION TO CHECK SPINDLE BEARINGS FOR CONDITION.				1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003060600035	20030606	00035	CE  	2003	6	6	2003FA0000512    	1	20030424	G	8012	S1991A1	SOLENOID        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	STARTER	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	737BC					17269283	L205976	731046		FOURTH INCIDENT INVOLVING THIS SAME STARTER SOLENOID INTAILING SHORTING OUT INTERNAL WINDING CAUSING STARTER TO MALFUNCT	ION.  THE FORMER THREE OCCASIONS, THE STARTER FAILED TO ROTATE (SOLENOID STUCK IN THE OPEN POSITION)  ON THIS OCCASION, 	STARTER TURNED AS SOON AS THE MASTER WAS TURNED ON ( SOLENOID STUCK IN CLOSED POSITION).  ON THIS OCCASION, THE BATTERY 	WAS NOT FULLY CHARGED AND CAUSED A HIGH CURRENT DRAW TO THE STARTER.  A DICECTEDED SOLENOID REVELED SHORTED WINDINGS.  T	HIS SWITCH WAS IN OPERATION NOT MORE THAN 6 MONTHS.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003060600042	20030606	00042	EA  	2003	6	6	2003FA0000514    	2	20030430	G	8530	LW15861	LIFTER          			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541*     	41536	EA  					CYLINDERS	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	1WA	51   				P423	L135159			LIFTERS PITTED AND MUSHROOMED.						1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2003060600052	20030606	00052	SO  	2003	6	6	2003FA0000515    	1	20030312	G	3710		GASKET          			PIPER 	PA32  	PA32301T    	7103209	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					VACUUM PUMP	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	81573	826  			11AP3962	328024004				GASKET FAILED NEAR MOUNTING STUD, ALLOWING OIL UNDER PRESSURE TO ESCAPE OVERBOARD, RESULTING IN LOSS OF OIL PRESSURE AND	 SUBSEQUENT EMERGENCY OFF AIRPORT LANDING.  THE VACUUM PUMP WAS INSTALLED NEW IN DECEMBER 1998 AND HAS BEEN IN SERVICE F	OR 826.3 HOURS.  THE GASKET WAS FURNISHED NEW WITH THE VACUUM PUMP.				1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003060500162	20030605	00162	SW  	2003	6	5	2003FA0000517    	1	20030512	G	3220	540017509	TRUSS           			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					NLG	BROKEN          	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	15	9169E	119  				290149				A/C RECEIVED STRUCTURAL DAMAGE DURING LANDING.  (THE RECORDS SHOW A NEW 540017-509 (TRUSS ASSY, NOSE GEAR, UPPER, RETRAC	T) WAS INSTALLED IN A/C AT THE TIME OF REPAIR.)  AT TOTAL TIME 211.1 A/C WAS TAKEN OUT OF SERVICE TO REPAIR STRUCTURAL P	ROBLEMS THAT CAUSED SLOWER THAN NORMAL FLIGHT.  ON THIRD TEST FLIGHT AFTER REPAIRS, NOSE GEAR COLLAPSED AT END OF LANDIN	G ROLLOUT.  INSP OF NOSE GEAR SHOWED WELDED TRUSS ASSEMBLY HAD FAILED.  TRUSS ASSY IS 4130-TUBE WELDED STRUCTURE THAT IS	 HEAT TREATED AFTER ASSY.  TWO ATTACH POINTS FOR RETRACT RODS; EACH POINT HAS TWO 4130 0.50 OD X 0.035 WALL TUBES THAT T	IE IT TO WELDED ASSY. BOTH RETRACT ROD ATTACH POINTS FAILED JUST ABOVE THE WELDS THAT TIE THE TUBES TO THE ASSY.	1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2003060500114	20030605	00114	EA  	2003	6	5	2003FA0000518    	2	20030516	G	7322	CF30766	FLOAT           	MARVELSCHEBX		PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  					CARBURETOR	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SO	03	43266				75106625	287415460	L3777227A			UPON TAKEOFF ENGINE QUIT.  UNSCHEDULED LANDING, AIRCRAFT DAMAGE WAS HEAVY.  INPSECTION OF CARBURETOR MA4SP, PART NUMBER 	10-5217, SERIAL NUMBER 75-10-6625-CFA02043, FLOAT PART NUMBER CF-30-766, FLOAT SERIAL DATE 11-01.  FLOAT SANK IN BOWL DO	 TO FLOATS SPLITTING AT SEAMS.  NO AD NOTED ON THESE FLOATS.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003060500119	20030605	00119	CE  	2003	6	5	2003FA0000519    	1	20030508	G	5751		STRUCTURE       			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6*        	52043	EA  					AILERON	DEBONDED        	B				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	788JL				881	4250202				THE AILERON IS AN ALL ALUMINUM BONDED ASSEMBLY.  THE AILERON WAS REPAIRED BY REPLACING THE AFT SKIN, USING DER APPROVED 	DATA AND WAS RETURNED TO SERVICE 11-15-2002.  ON 05-08-2003 A BOND LINE SEPARATION WAS DISCOVERED ON A SKIN EDGE.  REVIE	W OF THE REPAIR PROCESS INDICATES THAT AN EXCESSIVE AMOUNT OF TIME ELAPSED BETWEEN SKIN ETCH AND PRIMER APPLICATION.  OX	IDATION OF THE ALUMINUM SKIN RESULTED IN POOR ADHESION OF THE SKIN TO THE STRUCTURE.  REPAIR PROCESSES WERE REVIEWED TO 	INSURE THAT ALL CORE REPAIR PARTS ARE BROUGHT TO A STABLE CONDITION IF THEY ARE NOT GOING TO BE USED IMMEDIATELY.		1	L	7	2 	3T	3	T	RT	A7CE    	E2NE				 
2003061100002	20030611	00002	CE  	2003	6	11	2003FA0000520    	1	20030409	G	2710	451350393	LINKAGE         			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					LT WING AILERON	OUT OF ADJUST   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	1066H					TH1766				DURING ANNUAL INSPECTION, FOUND THE AILERON TRIM TAB LINKAGE RUBBING ON LEADING EDGE OF AILERON.  UPON INVESTIGATION AND	 CONVERSING WITH MFG TECH, FOUND THE TRIM TAB LINKAGE ARM (PN 451350393) WAS INSTALLED 180 DEGREES OUT, WITH THE SHORT E	ND HOOKED TO THE ACTUATOR LINKAGE, AND THE TRIM TAB LINKAGE ATTACHED TO THE LONG END.  LINKAGE ARM WAS REINSTALLED IN PR	OPER ORIENTATION DISCREPENCY WAS CLEARED.			1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2003061100004	20030611	00004	EA  	2003	6	11	2003FA0000521    	2	20030328	G	8550		FILTER          			GRTLKS	2T1   	2T1A2       	3910101	NM  	LYC   	O360  	AEIO360B1G6 	41514	EA  					ENGINE OIL	DAMAGED         	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	25	6018L	1485 	1    			0711	L1304351A			UPON INSTALL, OIL FILTER SCREEN WAS REMOVED TO DRAIN OIL, WAS FOUND, INSTALLED IMPROPER, WAS CRUSHED ON ONE END.  OIL FI	LTER BASE ASSY WAS REMOVED TO AID IN INSTALL OF AN OIL LINE, GASKET WAS FOUND INSTALLED BACKWARDS, PARTIAL BLOCKAGE OF O	IL PORTS.  INSTALLED FUEL SERVO, AND FOUND ARMS (MIXTURE AND THROTTLE) WERE DIFFERENT FROM ONES WE SENT, AND THROWS WERE	 DIFFERENT (NEITHER ARM INSTALLED ALLOWED STOP TO STOP MOVEMENT), ARMS HAD TO BE REPLACED.  AFTER FINAL INSTALL, READY F	OR START, BUT WOULD NOT.  TROUBLESHOOTING REVEALED FUEL MANIFOLD PLUNGER WAS STUCK CLOSED, WOULD NOT OPEN TO FUEL PRESSU	RE.  ONCE PLUNGER WAS RELEASED ENG WAS GROUND RUN AND SET UP.  ONE HOUR FLIGHT WAS MADE BEFORE THE PLUNGER SEIZED AGAIN.	1	Q	7	1 	3O	3	O	 	A18EA   	1E10				 
2003061100007	20030611	00007	CE  	2003	6	11	2003FA0000522    	1	20030501	G	2810	12000655	FUEL CELL       			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470*       	17026	SO  					LEFT WING	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	1970X					18256070				FLOATS AND FUEL CELLS.  RECEIVED NEW MFG LEFT WING FUEL CELL, MFG DATE 3/03.  INSTALLED IN AIRCRAFT,  FILLED WITH 1000LL	 AVGAS, DISCOVERED FUEL LEAK, RETURNED FUEL CELL TO MFG, FFC DISCOVERED MFG LT REAR BOTTOM CHANNEL LEAK DEFECT.  FFC REP	AIRED DEFECT AND RETURNED FUEL CELL.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003052700123	20030527	00123	EA  	2003	5	27	2003FA0000523    	2	20030521	G	8530		CYLINDER HEAD   			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	IO320*      	41508	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	64551	1494 				17275577	L1355539A			CYLINDER HEAD FOUND CRACKED FROM UPPER TO LOWER SPARK PLUG HOLES. BEING FOWARDED FOR MECHANIC AS FAX NUMBER DOES NOT WOR	K AT AFS-640. POC J. SHAPIRO 201-556-6600 EXT 230.					1	H	7	1 	3O	3	O	NT	3A12    	1E12				 
2003060600101	20030606	00101	EA  	2003	6	6	2003FA0000525    	2	20030521	G	8520	STD1211	PLUG            	LYC         		CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	O360*       	41514	EA  					CAMSHAFT	LOOSE           	B				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			WP	03	518ER	1401 				172S8922	L2992451A			WHILE PRACTICING TOUCH AND GOES, THE INSTRUCTOR NOTICED A THIN FILM OF OIL ON THE WINDSHIELD.  IT QUICKLY GOT WORSE.  MA	DE EMERGENCY LANDING.  MAINTENANCE DISCOVERED THE CRANKSHAFT PLUG HAD COME LOOSE.  OIL LEVEL WAS AT 4.5 QTS.  REPLACED C	RANK PLUG, CHECKED ENGINE BREATHER LINES (CLEAR), CLEANED AIRCRAFT, SERVICED OIL AND PUT AIRCRAFT BACK INTO SERVICE.  MF	G CONTACTED AND INFORMED OF THE INCIDENT.			1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2003061100009	20030611	00009		2003	6	11	2003FA0000527    	4	20030327	G	2562	4530421366	ELT             			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	327LJ					258490				ELT (PN 02195 MODEL 110-406) IS TRIGGERED ON WHENEVER AIRCRAFT IS WASHED, DEICED OR IN HEAVY STANDING RAIN, ELT IS MOUNT	ED AT FRAME 25, INSIDE THE TAIL CONE FAIRING ABOVE THE DATUM LINE.  POSSIBLE WATER ENTRY AREA IS THROUGH THE RUDDER SHAF	T AS IT PASSES THROUGH THE TAIL CONE FAIRING.  MM ATA23 PROVIDES NO SPECIAL INSTRUCTIONS FOR SEALING DURING INSTALLATION	.  DOCUMENT NR 570-5012 PARA 3.8 DTD 6/4/01 PROVIDES INSTRUCTION FOR SEALING THE CONNECTOR BUT NOT THE CONTAINER.  UNIT 	WAS NEVER MENT TO BE SEALED UNIT.  POSSIBLE REPAIR WOULD BE TO INSTALL A COVER FOR THE ELT.		2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2003061100011	20030611	00011	SW  	2003	6	11	2003FA0000528    	1	20030408	G	5754		SKIN            			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360*       	41514	EA  					RT WING OB LE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	52RM					1852				A/C RT WING OB LE SKIN WAS SLIGHTLY DAMAGED DURING TAXING.  ACCOMPLISHED REPAIR OF LE AND A/C RETURNED SERVICE.  IN COUR	SE OF INSP, FOUND EXTENSIVE CORROSION ON RT WING SPAR CAP STIFFNER BEHIND COPILOTS SEAT.  CORROSION WAS SO EXTENSIVE THA	T SPAR CAP STIFFNER WAS 90 PERCENT CORRODED THROUGH.  REMOVED ALL WING PANELS THAT WERE INSTALLED WITH COUNTERSUNK CHERR	Y MAX RIVETS.  CORROSION ON SPAR CAP OB OF FUEL TANK THAT COULD HAVE BEEN FOUND HAD COVERS BEEN ATTACHED WITH SCREWS AND	 EASILY REMOVABLE AND BEEN REQUIRED INSPECTION POINTS DURING ANNUAL INSPECTION.  CHERRY MAX RIVETS IN COUNTERSUNK HOLES 	ARE NEXT TO IMPOSSIBLE TO DRILL.  PINS COULD NOT BE PUNCHED OUT OR GROUND OFF TO ALLOW RIVET TO BE DRILLED.	1	L	7	1 	3O	3	O	 	2A3     	E286				 
2003061100012	20030611	00012	NM  	2003	6	11	2003FA0000529    	1	20030414	G	5714		SKIN            			LKHEED	P3A   	P3A         	5260103	NM  										WING BOX	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	925AU					151361				DURING ANNUAL (SPECIAL) INSPECTION CRACKS IN THE WING CENTER BOX PLANK NR 1 AND NR 3 WERE FOUND EMITTING FROM THE INTERN	AL WEEP HOLES LOCATED NTHE INTERNAL PLANK RISERS.  CRACK IN NR 1 PLANK, RT SIDE WAS ABOUT 3 INCHES LONG AND A 1 INCH CRA	CK IN SAME PLANK ON LEFT SIDE ABOUT 3 INCHES LONG.  ALL CRACKS RUN FORWARD AND AFT.  FATIGUE OR HARD LANDING ARE SUSPECT	ED.			2	L	7	4 	4T			RT	A32NM   					 
2003061100014	20030611	00014	CE  	2003	6	11	2003FA0000530    	1	20030515	G	3710	442CW	PUMP            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					NR 1 ENG VACUUM	INOPERATIVE     	B			NE5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	635MA		75   			402C0634				VACUUM PUMP INOPERATIVE, OVERHAULED ON 1-15-03.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003061100015	20030611	00015	CE  	2003	6	11	2003FA0000531    	1	20030515	G	3710	442CW	PUMP            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					NR 2 ENG VACUUM	INOPERATIVE     	B			NE5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	635MA		63   			402C0634				VACUUM PUMP INOPERATIVE, OVERHAULED ON 1-15-03.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003061100013	20030611	00013	SO  	2003	6	11	2003FA0000533    	1	20030522	G	2750	82905002	BELLCRANK       			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540*     	41532	EA  					TE FLAP	BROKEN          	D				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			NE	02	120FW	631  				4636134				PILOT REPORTED THAT THE AIRCRAFT ROLLED LEFT WHEN THE FLAPS WERE EXTENDED FOR LANDING REQUIRING SIGNIFICANT RIGHT AILERO	N INPUT TO COUNTERACT THIS FORCE.  PILOT RETRACTED THE FLAPS AND NOTED THE LT FLAP REMAINED DOWN APPOXIMATELY 10 DEGREES	.  PILOT COMPLETED A NORMAL LANDING.  INVESTIGATION REVEALED THAT THE LEFT FLAP BELLCRANK WAS TWISTED IN TWO AT ITS MIDP	OINT.  BELLCRANK WAS IN COMPLIANCE WITH MFG SB 1062 AND DID NOT BREAK AT A WELD.  INSPECTION OF THE RT SIDE REVEALED THA	T THE PAINT WAS BROKEN IN A TWISTING DIRECTION BUT THE BELLCRANK HAD NOT SEPARATED (YET).  BOTH BELLCRANKS WERE REPLACED	 WITH NEW PARTS.  FLAP RIGGING WAS CHECKED AND FOUND OK WITH NO BINDING IN EITHER DIRECTION NOTED.	1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2003061100116	20030611	00116	EU  	2003	6	11	2003FA0000535    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF	897  				85002				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF BEARING.  RECOMMEND DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABILITIES.				1	L	7	1 	3O			RT	A49CE   					 
2003061100117	20030611	00117	EU  	2003	6	11	2003FA0000536    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	863AF	902  				85003				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.				1	L	7	1 	3O			RT	A49CE   					 
2003061100118	20030611	00118	EU  	2003	6	11	2003FA0000537    	1	20030512	G	2700		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON CONTROL	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	802  				85004				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  PR	OBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT O	F THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABILIT	IES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100119	20030611	00119	EU  	2003	6	11	2003FA0000538    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON CONTROL	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	861AF	841  				85001				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABIL	ITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100120	20030611	00120	CE  	2003	6	11	2003FA0000539    	1	20030506	G	3710	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  										PNEUMATIC	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8173C	501  				CE1541				DURING GROUND RUN UP OUTPUT OF ENGINE DRIVEN DRY AIR PUMP FAILED TO PUT OUT PROPER PRESSURE AT IDLE RPM.  RAN AIRCRAFT U	P AND AIR PRESSURE STILL LOW AT HIGHTER RPM.  TESTED SYSTEM AND FOUND ENGINE DRIVEN AIR PUMP NOT WORKING PROPERLY.  BELI	EVE DRY AIR PUMP VANES ARE WORN.  HAVE NO RECOMMENDATION AT THIS TIME.				1	L	7	1 	3O			 	3A15    					 
2003061100121	20030611	00121	EU  	2003	6	11	2003FA0000540    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	723  				85005				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  P	ROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT 	OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABILI	TIES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100122	20030611	00122	EU  	2003	6	11	2003FA0000541    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF	459  				85007				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABIL	ITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100123	20030611	00123	EU  	2003	6	11	2003FA0000542    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	861AF	841  				85001				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF 	THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABILITIE	S.			1	L	7	1 	3O			RT	A49CE   					 
2003061100124	20030611	00124	EU  	2003	6	11	2003FA0000543    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	802  				85004				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABIL	ITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100125	20030611	00125	EU  	2003	6	11	2003FA0000544    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	802  				85004				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABIL	ITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100126	20030611	00126	EU  	2003	6	11	2003FA0000545    	1	20030512	G	2730		BEARING         			GROB  	120   	G120A       	1660208	EU  										ELEVATOR LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	863AF	902  				85003				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABIL	ITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100128	20030611	00128	EU  	2003	6	11	2003FA0000546    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF	897  				85002				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABIL	ITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100129	20030611	00129	EU  	2003	6	11	2003FA0000547    	1	20030512	G	2730		BEARING         			GROB  	120   	G120A       	1660208	EU  										ELEVATOR LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF	897  				85002				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABIL	ITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003061100130	20030611	00130	EU  	2003	6	11	2003FA0000548    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON LEVER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF	459  				85007				DURING INSPECTION FO AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER LIMITS AND LOAD HANDLING CAPABIL	ITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003062400103	20030624	00103	EU  	2003	6	24	2003FA0000549    	1	20030512	G	2720		BEARING         			GROB  	120   	G120A       	1660208	EU  										RUDDER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	802  				85004				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAIN CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003062400104	20030624	00104	EU  	2003	6	24	2003FA0000550    	1	20030512	G	2720		BEARING         			GROB  	120   	G120A       	1660208	EU  										RUDDER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	723  				85005				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003062400107	20030624	00107	EU  	2003	6	24	2003FA0000551    	1	20030512	G	2720		BEARING         			GROB  	120   	G120A       	1660208	EU  										RUDDER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	723  				85005				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL SYSTEM WHICH ALLOWS HE CONTROL ROD DEFLEC	TION TO EXCEED THE DESIGN LIMIT OF THE BEARING.  RECOMMEND A DESIGN CHANGE OR REPLACE BEARING WITH ONE THAT HAS BETTER L	IMITS AND LOAD HANDLING CAPABILITIES.			1	L	7	1 	3O			RT	A49CE   					 
2003062400108	20030624	00108	EU  	2003	6	24	2003FA0000552    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										ELEVATOR	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	723  				85005				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUR OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003062400109	20030624	00109	EU  	2003	6	24	2003FA0000553    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF	459  				85007				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003062400110	20030624	00110	EU  	2003	6	24	2003FA0000554    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON SYS	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF	459  				85007				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003062400113	20030624	00113	EU  	2003	6	24	2003FA0000555    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										AILERON	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	723  				85005				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003062500001	20030625	00001	EU  	2003	6	25	2003FA0000557    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										CONTROL SYSTEM	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF	897  				85002				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003080500001	20030805	00001	EU  	2003	8	5	2003FA0000558    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										LEVER ASSY	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	863AF	902  				85003				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.  	PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT	 OF THE BEARING.				1	L	7	1 	3O			RT	A49CE   					 
2003062500002	20030625	00002	EU  	2003	6	25	2003FA0000559    	1	20030512	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  										CONTROL SYSTEM	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF	459  				85007				DURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING.  RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003062500009	20030625	00009	SW  	2003	6	25	2003FA0000560    	1	20030519	G	6220	406310405101	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					M/R PITCH LINK	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	57HK	836  				53404				PILOT FOUND UPPER END OF BEARING ASSEMBLY LOOSE ON PRE-FLIGHT.  UPON INSPECTION BY MECHANIC FOUND THE RUBBER AROUND UPPE	R BEARING CRACKED AND BEARING CRACKED AND BEARING HOUSING HAD AXIAL PLAY.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003062500010	20030625	00010	SW  	2003	6	25	2003FA0000561    	1	20030519	G	8011	SM20ACD300A21	RELAY           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	57HK	888  				53404				PILOT REPORTED START LIGHT WOULD NOT COME ON AND AIRCRAFT WAS UNABLE TO BE STARTED.  TALKED TO PRODUCT SUPPORT AT MFG, S	TATED SOME 1K1 RELAYS WITHOUT A T STAMPED ON BOTTOM HAD A HIGH FAIL RATE.  REPLACED RELAY WITH NEW RELAY STAMPED WITH T.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003062500021	20030625	00021		2003	6	25	2003FA0000563    	4	20030516	G	2562	AK450	ELT             																	CABIN	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08										ELT FAILED FUNCTIONAL TESTS REQUIRED BY FAR 91.207.  NEW BATTERIES WERE USED FOR TEST.  UNIT PERFORMED OK AT LAST 100 HO	UR INSPECTION.  NO KNOWN DAMAGE HISTORY.																		 
2003062500023	20030625	00023	CE  	2003	6	25	2003FA0000564    	1	20030325	G	2121	26193873	FAN             			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN	SEIZED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25						078				CABIN/ CREW FAN PHYSICALLY LOCKED UP CAUSING BURNING ODOR AND SMOKE IN CABIN.  CB POPED AND RESET ONCE.  IN THE FUTURE C	REW/ CABIN FROM CB POPS RECOMMEND NOT RESETTING IN FLIGHT AS THIS IS NOT A REQUIRED FOR FLIGHT ITEM.					2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
2003062500029	20030625	00029	CE  	2003	6	25	2003FA0000565    	1	20030501	G	5312	07126161	BULKHEAD        			CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	9VP	4246 				18260376				TIME SINCE LAST AD REQUIRED INSPECTION 901.8.  ORIGINALLY INSPECTED ON 9/19/74 WITH 1246 TT, FOUND OK.  REINSPECTED AT 1	502 AND 2334.58 TT AND FOUND, OK.  ALSO INSPECTED AT 3345.1 AND FOUND AIRWORTHY.  CURRENT INSPECTION REVEALED TWO SMALL 	CRACKS .1250 AND .2500 INCH AT TOP OF RUDDER CABLE CUT-OUT AND FLANGE.  FIN SPAR BOLTS WERE TIGHT.  DYE PEN INSPECTION O	F FIN SPAR ATTACH FITTINGS REVEALED NO OTHER DAMAGE.  REPLACED BULKHEAD WITH SERVICEABLE ASSEMBLY.  GASSER BANNER TOW HI	TCH WAS INSTALLED IAW STC SA-220-50 ON 8/14/73 TT 757.0 ON THE AFT BULKHEAD TAIL SKID BOLT.  TIME OF REMOVAL IS UNKNOWN.	 AD 72-07-09.  (AL05200300898)	1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003062500024	20030625	00024	CE  	2003	6	25	2003FA0000567    	1	20030528	G	3210		HOUSING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					ACTUATOR	CRACKED         	B				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			GL	07	20SU	7164 	4    		1485	172RG0323	L2977836A			PILOT REPORTED HEARING LOUD POP.  LT MLG WAS HANGING OUT OF WHEEL WELL.  PUTTING GEAR SELECTOR IN DOWN POSITION, RT MAIN	 AND NLG EXTEND FULLY.  LT WAS STILL HANGING LOOSE. ATTEMPT TO PUMP DOWN LT WITH EMERGENCY PUMP WAS UNSUCCESSFUL.  A/C W	AS PUT INTO HANGAR AND GEAR INSPECTED.  INSP REVEALED LT MAIN GEAR ACT HAD CRACKED THROUGH FWD MOUNTING BOLT HOLE.  CRAC	K CAUSED PINION GEAR TO SEPERATE FROM RACK GEAR. THESE SEEM TO BE CRACKING AFTER COMPLING WITH AD AND MFG SB.  ACT, S/N 	5349 WAS FOUND CRACKED IN SAME LOCATION.   ACT S/N 5384 WAS FOUND CRACKED IN SAME LOCATION.   SEEMS NEW BUSHINGS THAT AR	E INSTALLED AS PART OF SB MAY BE CAUSING SOME ADDED STRESS TO ACTUATORS.	1	H	7	1 	3O	3	O	 	3A17    	E286				 
2003061100127	20030611	00127	GL  	2003	6	11	2003FA0000568    	1	20030527	G	7921	10281A	OIL COOLER      			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE OIL	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	3YH	111  				0239	686282			OIL COOLER CRACKED AT OUTBOARD FLANGE, AT BAFFLING MOUNT.  THIS IS THE TENTH OIL COOLER ON A/C THAT OUR REPAIR STATION H	AS SEEN WITH A CRACKED OIL COOLER IN THE EXACT SAME LOCATION.  MFG HAS AN OPTIONAL SB22-71-03 BAFFLE MODIFICATION THAT S	UGGESTS THAT THE BAFFLE BE MODIFIED TO PREVENT THIS PROBLEM.  MY SUGGESTION IS THAT THIS SB BE MANDATORY AND/OR TIED TO 	AN AD TO PREVENT THE OIL COOLER FROM CRACKING AND CAUSING A POSSIBLE OIL LEAK.  			1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2003062400106	20030624	00106	SO  	2003	6	24	2003FA0000569    	1	20030525	G	2497	7U1055502	WIRE            			PIPER 	PA12  	PA12        	7101202	SO  	LYC   	O145  	O145*       	41501	EA  	SNSNCH	74D	74DM        	EA  	TAIL BRACE	BROKEN          	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			WP	09		613  				122657	L3564127A			LEFT UPPER TAIL BRACE WIRE BROKE ABOUT ONE HALF IT'S LENGTH, DURING CLIMB.						1	H	7	1 	3O	3	O	 	A780    	TC199	5	N	P88614	 
2003063000045	20030630	00045	EA  	2003	6	30	2003FA0000570    	2	20030510	G	7414	10682016	DISTRIBUTOR GEAR	BENDIX      	D6LN3000    	PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	17		331  	331  		J319703GR	32R7987027	L587361A			DISTRIBUTOR GEAR ON RIGHT MAGNETO,  FAILED.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003070800110	20030708	00110	SO  	2003	7	8	2003FA0000572    	2	20030516	G	7414		DISTRIBUTOR BLK 	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	SHORTED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	6311Z	496  			01120306	CE997				MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSP IAW THE MM.  REMOVED THE REAR COVER OF MAGNETO AND FOUND A CARBON DUSTS PO	WER ON THE CAP AND AROUND THE COIL.  DIST BLOCK K3823 WAS BURNED AWAY AND EVIDENCE OF SHORTING TO THE COIL.  PROBABLE CA	USE IS THE MANUFACTURER OF THE DIST BLOCK BEARING.  MFG IS AWARE PROBLEM AND HAS CORRECTED.  HOWEVER WHAT ABOUT ALL THE 	MAGNETOS THAT HAVE NOT HAD THE BLOCKS REPLACED OR MADE IT TO THE 500 HOUR INSPECTION.  WE RECOMMEND THAT ANYONE WITH SLI	CK MAGNETOS MFG IN THE YEAR 1999-2001 HAVE THE DIST BLOCKS REPLACED TO PREVENT POSSIBLE FAILURE.		1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003080500006	20030805	00006	CE  	2003	8	5	2003FA0000573    	1	20030517	G	3710		MOTOR           			BEECH 	33    	F33A        	1151425	CE  										VACUUM PUMP	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8101C					CE1538				PILOT REPORTED STANDBY INSTRUMENT AIR PRESSURE INOPERATIVE.  ON FURTHER INVESTIGATION FOUND STAND BY VACUUM PUMP DRIVE M	OTOR FAILED.  RECOMMEND OPERATING SYSTEM AT EACH PHASE INSPECTION.					1	L	7	1 	3O			 	3A15    					 
2003080500007	20030805	00007	SO  	2003	8	5	2003FA0000574    	1	20030515	G	7921	F017641	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4144P	68   				2843121	RL3909136A			FOUND OIL LEAK ON PREFLIGHT INSPECTION BY STUDENT PILOT.  PRESSURE CHECKED OIL COOLER LEAKING AT SEAM ON TOP.  THIS IS A	 WEAK AREA ON THE OIL COOLER, COULD BE CAUSED BY VIBRATION AND NOT USING A BACK UP WRENCH WHEN INSTALLING OIL COOLER HOS	ES.  RECOMMEND FINDING A REPLACEMENT THAT IS MORE DURABLE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003070700209	20030707	00209	EU  	2003	7	7	2003FA0000576    	1	20030520	G	2121	C209690B1	FAN             			SAAB  	SF340 	SF340A      	7850100	EU  										CABIN	INOPERATIVE     	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05										FAN RETURNED FOR REPAIR, THE FAN WAS TESTED UPON ARRIVAL AND FAILED TO OPERATE.  WHEN FAN WAS DISASSEMBLED, THIS ARMATUR	E ASSY WAS FOUND TO BE NOT OF MFG DESIGN.  THE WINDINGS IN THE STATOR ASSY ARE NOT OF MFG DESIGN, THE MOTOR HOUSING HAS 	BEEN MODIFIED NOT TO MFG SPECIFICATIONS, THE FAN HOUSING HAS BEEN AND MODIFIED NOT TO MFG SPECS.  MFG OVERHAUL MANUAL DO	ES NOT ALLOW FOR  RE-WINDING  OF THE STATOR ASSY OR THE MODIFICATIONS OR REPLACEMENT OF PARTS OTHER THAN LISTED.  NOTE: 	 REPAIR STATES FAN REPAIRED AND CERTIFIED IAW MFG COMPONENT MM.		2	L	7	2 	4T			RT	A52EU   					 
2003070700196	20030707	00196	SO  	2003	7	7	2003FA0000579    	2	20030416	G	7414	10400309	IMPULSE COUPLING			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					MAGNETO	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	06	72TK					TC2267	272983R			RT ENGINE WOULD NOT DEVELOP FULL POWER.  FOUND MAGS TIMED TO 10 DEGREES ATC.  REMOVED RT AND LT MAGS, FOUND IMPULSE COUP	LER SPRINGS 10-51324 BROKEN ON BOTH MAGS.  NO REASON FOUND FOR FAILURE.  INSTALLED 2 NEW IMPULSE COUPLERS.					1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2003080500015	20030805	00015	CE  	2003	8	5	2003FA0000580    	1	20030512	G	8012	99103971	RELAY           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LT STAB WING	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	2748Y					402C0248				AIRCRAFT LOST ELECTRICAL POWER, AIRCRAFT LANDED WITHOUT INCIDENT. MECHANIC FOUND RT STARTER RELAY FAILED IN ON POSITION.	  MECHANIC CHANGED THE RELAY, RT STARTER AND AIRCRAFT BATTERY, THEN RETURNED AIRCRAFT TO SERVICE.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003080500016	20030805	00016		2003	8	5	2003FA0000581    	4	20030506	G	3457	GNS530	GPS             			CESSNA	177   	177RG       	2073709	CE  										COCKPIT	FAILED          	B			RH6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	8248G	300  				177RG0148				GPS SCREEN WENT TOTALLY BLANK.  UNIT STILL RECEIVING AND TRANSMITTING COMMUNICATION DATA.  SCREEN FAILED 2-3 MINUTES AFT	ER POWER UP.  REPORTED THAT HIGH VOLTAGE TRANSFORMER FAILED UNDER IFR FLIGHT COULD BE FATAL.					1	H	7	1 	3O			 	A20CE   					 
2003080500017	20030805	00017	CE  	2003	8	5	2003FA0000582    	1	20030319	G	2700	05131661	CONTROL WHEEL   			CESSNA	182   	182E        	2072712	CE  	CONT  	O470  	O470*       	17026	SO  					COCKPIT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	2996Y	4667 				18253996				PILOT SIDE CONTROL WHEEL FAILURE ON LANDING FLAIR.  BRAKE ON TOP LT CORNER WHERE THE HAND GRIP MEETS THE MAIN CROSS SPOK	E.  THE BRAKE IS CLEAN AND SHOWS NO SIGN OF CRACKING BEFORE THE FAILURE OCCURED.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003080500018	20030805	00018	CE  	2003	8	5	2003FA0000583    	1	20030505	G	7931	040010629	LINE            			CESSNA	140   	140         	2071602	CE  	CONT  	O200  	O200*       	17020	SO  					OIL PRESS IND	CORRODED        	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	05	73017	3861 				10222				THE OIL INDICATOR LINE WAS WORN COMPLETELY THROUGH.  THE CIRCUMSTANCES UNDER WHICH IT OCCURED, WAS DURING FLIGHT.  PROBA	BLE CAUSE:  OLD AND CORRODED.  RECOMMENDATION TO PREVENT RECURRENCE:  CLOSER INSPECTIONS OF ENGINE, AND ENGINE PARTS/ CO	MPONENTS.				1	H	7	1 	3O	3	O	NC	A768    	E252				 
2003080500021	20030805	00021	CE  	2003	8	5	2003FA0000584    	1	20030513	G	2701	S20103	BEARING         			CESSNA	206   	U206G       	2073356	CE  										YOKE GUIDE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	729					U20606151				WHILE INSPECTING THE AIRCRAFT, THE PILOTS YOKE TUBE WAS OBSERVED TO HAVE BEEN WORN DUE TO CHAFFING ON THE UNDERSIDE.  TH	E COATING ON THE YOKE GUIDE ROLLER BEARINGS HAD WORN OFF AND THE TUBE HAD WORN ABOUT .3333 OF THICKNESS OF THE TUBE.  IN	 ADDITION TO THE GUIDE BEARINGS THE YOKE TUBE PN 1260142-14 WAS REPLACED.  RECOMMEND INSPECTION OF THE BEARINGS TO PREVE	NT MORE COSTLY PARTS REPLACEMENT.			1	H	7	1 	3O			 	A4CE    					 
2003080500024	20030805	00024	CE  	2003	8	5	2003FA0000585    	1	20030510	G	5520	AN414	BOLT            			CESSNA	340   	340A        	2076405	CE  										ELEVATOR PIVOT	BENT            	B			CTUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	98585					340A0046				DURING INSPECTION DISCOVERED ELEVATOR PIVOT BOLT TO BE BENT.  REMOVED AND REPLACED BOLT WITH NEW AN4-14.  CAUSE COULD BE	 ATTRIBUTED TO GUST LOCK NOT BEING INSTALLED AND ELEVATOR MOVEMENTS WHILE AIRCRAFT ARE PARKED ON THE RAMP.					1	L	7	2 	3O			 	3A25    					 
2003080500028	20030805	00028	SO  	2003	8	5	2003FA0000586    	2	20030326	G	7414	K3823	DISTRIBUTOR GEAR			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					MAGNETO	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	82DF	450  			94100168	P21000276	513403			THIS PRESSURIZED MAGNETO WAS REMOVED AND DISASSEMBLED FOR THE 500 HOUR INSPECTION.  ALL OF THE INTERNAL HARDWARE WAS FOU	ND RUSTED. THE DISTRIBUTOR GEAR, DRIVEGEAR AND DISTRIBUTOR BLOCK WAS FOUND COVERED IN A FILM AND NOTICEABLY SOFTER THAN 	NEW EXAMPLES.  THIS IS A RESULT OF MOISTURE IONIZATION.  RECORDS CONFIRM THAT THE MOISTURE FILTER IN THE PRESSURIZATION 	LINE HAD BEEN REPLACED REGULARLY.  AD 88-25-04 ADDRESSES THIS PROBLEM IN EARLIER SERIES MAGNETOS.  SHOULD INCLUDE 6300 S	ERIES PRESSURIZED MAGNETOS.		1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003080500029	20030805	00029	SO  	2003	8	5	2003FA0000587    	2	20030326	G	7414	K3823	DISTRIBUTOR GEAR			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					MAGNETO	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	82DF				95030099	P21000276	513403			THIS PRESSURIZED MAGNETO WAS REMOVED AND DISASSEMBLED FOR THE 500 HOUR INSPECTION.  ALL THE INTERNAL HARDWARE WAS FOUND 	RUSTED.  THE DISTRIBUTOR GEAR, DRIVE GEAR AND DISTRIBUTOR BLOCK WAS FOUND COVERED IN A FILM AND NOTICEABLY SOFTER THAN N	EW EXAMPLES.  THIS IS A RESULT OF MOISTURE IONIZATION.  RECORDS CONFIRM THAT THE MOISTURE FILTER IN THE PRESSURIZATION L	INE HAD BEEN REPLACED REGULARLY AD 88-25-04 ADDRESSES THIS PROBLEM IN EARLIER SERIES MAGNETOS.  SHOULD BE AMENDED TO INC	LUDE 6300 SERIES, PRESSURIZED MAGNETOS.		1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003080500013	20030805	00013	CE  	2003	8	5	2003FA0000588    	1	20030603	G	3246	13889	BEARING CAGE    			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300*       	17022	SO  					MLG WHEEL	DETERIORATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	7145T	35   				46745				MAIN LANDING GEAR WHEEL BEARING CUPS SHOW SIGNS OF FAILURE BY PITTING.  THIS APPLIES TO BOTH INNER AND OUTER CONES ON TW	O (2) MAIN LANDING GEAR WHEELS FOR A TOTAL OF FOUR (4) FAILURES.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003080500012	20030805	00012	CE  	2003	8	5	2003FA0000589    	1	20030603	G	3246	13836	BEARING RACE    			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300*       	17022	SO  					MLG WHEEL	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	7145T	35   				46745				MAIN LANDING GEAR WHEEL BEARING CUPS SHOWS SIGNS OF FAILURE BY SCUFFING.  THIS APPLIES TO BOTH INNER AND OUTER CUPS ON T	WO (2) MAIN LANDING GEAR WHEELS FOR A TOTAL OF FOUR (4) FAILURES.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003060600001	20030606	00001	EU  	2003	6	6	2003FA0000590    	1	20030501	G	5523		WASHER          	AIMM        		AIMM  	AMT200	AMT200S     	       	EU  										TRIM ASSY	COCKED          	B				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CR	CRUISE         	1			NM	03	147XS	62   								DURING POST INSPECTION FLIGHT, PILOT WAS UNABLE TO MOVE ELEVATOR CONTROL FULL AFT.ELEVATOR CONTROL APPEARED TO BE PARTIA	LLY JAMBED. AFTER SEVERAL PULLS FULL MOVEMENT WAS ESTABLISHED AND A SAFE LANDING COMPLETED.MAINTENANCE DISCOVERED A WASH	ER ON THE TRIM SYSTEM IN FRONT OF TRIM GUIDE PN 55302/3 APPERENTLY JAMMED IN FLIGHT ON BOLT AT FORWARD END OF ROD PN 553	01.A FLEET WIDE INSPECTION OF ACADEMY AMT-200S REVEALED THREE BOLTS INSTALLED WITH THE HEADS DOWN AND NINE WITH HEADS UP	. THE AIRCRAFT WITH THE HEADS DOWN APPEAR TO CAUSE NO CONFLICT. RECOMMEND CONTACTING XIMANGO USA FOR GUIDANCE ON FIX.		1	L	7	1 	3I			NC	TG0004A 					 
2003080500030	20030805	00030		2003	8	5	2003FA0000591    	4	20030506	G	2561	KS9P0101	LIFE VEST       																	CABIN	FAILED          	B				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			EA	07										LIFE VEST FAILED, MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-1.  DOM JANUARY 1983																			 
2003080500031	20030805	00031		2003	8	5	2003FA0000592    	4	20030519	G	2561	KS9P0101	LIFE VEST       																	EMERGENCY EQUIP	FAILED          	B			KQ1R	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			EA	07										LIFE VEST FAILED.  MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-1.  DOM: JANUARY 1983																			 
2003080500032	20030805	00032		2003	8	5	2003FA0000593    	4	20030524	G	2561	KS9P0101	LIFE VEST       																	EMERGENCY EQUIP	FAILED          	B			KQ1R	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			EA	07										LIFE VEST FAILED.  MFG RECOMMENDED CELL PRESSURE TEST IAW MANUAL 25-60-1.  DOM:  MAY 1980																			 
2003080500036	20030805	00036	EA  	2003	8	5	2003FA0000594    	2	20030523	G	8530	05K23038	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	95563	137  				15285926	RL22756915			WITH 137 HOURS ON THIS ENGINE THE OIL CONSUMPTION WENT UP.  ON INSPECTION OF THE ENGINE, OIL WAS FOUND ON NR 1 AND NR 3 	CYLINDER SPARK PLUGS.  ALL FOUR CYLINDERS WERE REMOVED AND THE OIL CONTROL RINGS WERE FOUND BROKEN ON CYL NR 1 AND NR 3.	  THE CYLINDER WALLS WERE BADLY WORN AND A WEAR STEP COULD BE FELT AT THE BOTTOM TRAVEL OF THE PISTON.  THE WEAR WAS WOR	SE IN NR 1 AND NR 3 CYLINDER.  BUT WAS PRESENT ON ALL FOUR CYLINDERS.  THIS IS THE THIRD ENGINE IN FLEET FOUND IN THIS C	ONDITION IN THE PAST TWO WEEKS.  SINCE ALL CYLINDERS WERE MFG IN THE SAME TIME FRAME IT SEEMS THAT IT MIGHT BE A BAD BAT	CH OF CYLINDERS FROM THE FACTORY.  THIS ENGINE WAS REBUILT ON 2/21/03.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003080500044	20030805	00044	EA  	2003	8	5	2003FA0000595    	2	20030523	G	8530	O5K23038	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	95564					15285927	L1454115			ENG WAS REMOVED AT 353.2 HRS SMOH AND WAS SENT BACK TO MFG FOR REPAIR  DUE TO METAL IN THE OIL.  AT 779.5 HRS METAL WAS 	FOUND IN OIL SYS.  WE REPLACED ALL FOUR CYLINDERS AND CONNECTING ROD ASSY.  GROUND RUN AND TEST FLIGHT CHECKED GOOD.  AT	 981.6 HRS TSO AND 202.1 HRS  REPLACED CYLINDERS ASSY,  OIL CONSUMPTION INCRESSED.  WHEN SPARK PLUGS WERE CHECKED, OIL W	AS FOUND ON NR 1 AND NR 4 SPARK PLUGS.  REMOVED NR 1 CYLINDER AND FOUND OIL CONTROL RING BROKEN AND CYLINDER WALL BADLY 	WORN AND WEAR STEP COULD BE FELT AT BOTTOM TRAVEL OF PISTON.  REMOVED THE NR 4 CYLINDER AND FOUND TO BE WORN BUT NO BROK	EN RING.  ALL CYLINDERS WERE MFG IN SAME TIME FRAME.  IT SEEMS THAT IT MIGHT BE A BAD BATCH OF CYLINDERS FROM FACTORY.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003080500045	20030805	00045	EA  	2003	8	5	2003FA0000596    	2	20030523	G	8530	05K23038	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	95604	5237 	490  			15285935				PROBLEM WITH HIGH OIL TEMP ON TEST FLIGHT.   AT 280.3 OIL CONSUMPTION INCREASED AND ENG STARTED RUNNING ROUGH, WHEN CHEC	KING SPARK PLUGS FOUND OIL ON NR 3 CYL PLUG.  REMOVED NR 3 CYLINDER FOUND OIL CONTROL RING BROKEN, METAL IN OIL SYS.   O	N 12/27/02 REPLACED ALL 4 CYLINDERS AND CONNECTING ROD ASSY.  GROUND RUN AND TEST FLIGHT CKD GOOD.  AT 490.7 HRS SMOH AN	D 210.4 HRS SINCE WE REPLACED CYL ASSY,  OIL CONSUMPTION INCRESSED.  WHEN SPARK PLUGS WERE CHECKED, OIL WAS FOUND ON NR 	3 SPARK PLUG.  REMOVED NR 3 CYL, FOUND OIL CONTROL RING BROKEN AND CYL WALL BADLY WORN AND WEAR STEP COULD BE FELT AT BO	TTOM TRAVEL OF PISTON.  REMOVED OTHER CYL AND FOUND THEM ALL TO BE BADLY WORN.   ALL CYL WERE MFG IN SAME TIME FRAME.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003080500046	20030805	00046		2003	8	5	2003FA0000598    	4	20030515	G	3424		CONNECTOR       			CESSNA	182   	T182T       	       	CE  	LYC   	O540  	TIO540*     	41532	EA  						IMPROPER        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	529PT				2101299	T18208119				THE CONNECTOR FROM AIRCRAFT HARNESS THAT MATS TO THE TURN COORDINATOR HAS IMPROPERLY CRIMPED PINS.  THIS FAULTY CONNECTI	ON CAUSES AUTOPILOT WING ROCKING AND CAN CAUSE UNDESIRABLE ROLL RATES DURING CLIMBS.					1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2003080500048	20030805	00048	NM  	2003	8	5	2003FA0000599    	1	20030415	G	2170	NAS5213215	SLEEVE          			ISRAEL	1125  	1125        	       	NM  	GARRTT	TFE731	TFE731*     	01518	WP  					WATER SEPARATOR	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	255AL	2190 			32583	0075				CLAMP ATTACHING SLEEVE TO WATER SEPERATOR WORKED LOOSE CAUSING SLEEVE TO LEAK AT 5.0 PSI.  CREW NOTED LOSS OF COLD AIR F	LOW AND INABILITY TO MAINTAIN CABIN PRESSURE IN FULL COLD.  PRESSURIZATION WORKED NORMALLY WITH CABIN TEMPS SETTINGS ABO	VE FULL COLD.  CLAMP MAY HAVE BEEN STRESSED BY REPEATED OVER LIGHTENING.  MFG SPECIFIES 20-25 INCH POUNDS TORQUE.				2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2003080500050	20030805	00050	SW  	2003	8	5	2003FA0000600    	1	20030102	G	6320		SCAVENGE PUMP   			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					GEARBOX	INOPERATIVE     	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	09	3893U	5989 				51020				DURING BUCKET SLING TRAINING, AIRCRAFT STARTED SMOKING.  PILOT PERFORMED PRECAUTIONARY LANDING AND OVERTORQUED AIRCRAFT.	  MAINTENANCE WAS NOTIFIED AND DISPATCHED TO RETRIEVE AIRCRAFT FROM LOCATION.  AIRCRAFT ENGINE WAS INSPECTED AND FOUND T	HAT THE NR 8 SCAVENGE PUMP WAS NOT FUNCTIONING.  GEARBOX WAS REPLACED AND OVERTORQUE INSPECTION WAS PERFORMED.  AIRCRAFT	 WAS THEN RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003080500051	20030805	00051	SW  	2003	8	5	2003FA0000601    	1	20030102	G	2435	23081018	STARTER GEN     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	INOPERATIVE     	B			V9MR	A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	38885	502  				45726				GENERATOR FAILED PILOT PERFORMED CAUTIONARY LANDING.  MECHANIC INSPECTED AND REPLACED AIRCRAFT BATTERY AND STARTER GENER	ATOR.  AIRCRAFT WAS THEN RETURNED TO SERVICE.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003060600063	20030606	00063	EA  	2003	6	6	2003FA0000602    	2	20030520	G	7414		IMPULSE COUPLING	SLICK       		PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2B5    	41532	EA  					MAGNETO	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09		442  			00120999					FAILURE OF SLICK 6351, S/N 00120999, MAGNETO.  INSTALLATION DATE 7/15/01; TIME IN SERVICE SINCE NEW - 442 HRS. INSTALLED	 ON PIPER PAWNEE PA-25-235 AIRCRAFT; LYC O-540-B2B5 (I BELIEVE). IT WAS 235 HP. MODEL. FAILURE DATE 5/19/03. THE NOTED M	AGNETO FAILED DURING OPERATION, RESULTING IN DISTRUCTION OF THE MAGNETO MOUNT SYSTEM, INGESTION OF METAL COMPONENTS INTO	 THE ENGINE, DEFORMING OF THE MAG DRIVE GEAR SHAFT, MISCELLANEOUS OTHER MECHANICAL DAMAGE, AND THE DISPLACEMENT OF THE M	AG, RESULTING IN LOSS OF OIL FROM THE ENGINE.  THE MAG. APPARENTLY FAILED JUST PRIOR TO TAKE-OFF (MAG COMPONENTS WERE FO	UND ON THE RUNWAY).  THE PILOT NOTED THE ROUGH RUNNING OF THE ENGINE AND RETURNED TO THE AIRPORT AFTER A SHORT FLIGHT.	1	L	7	1 	3O	3	O	 	2A10    	E295				 
2003080500052	20030805	00052	SO  	2003	8	5	2003FA0000603    	1	20030520	G	3243	1035	MASTER CYLINDER 			MAULE 	MX7   	MX7235      	5460180	SO  	LYC   	O540  	IO540*      	41532	EA  					PARK BRAKE LEVER	INOPERATIVE     	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	114MK	1175 				10022C				SPRING AROUND MASTER CYLINDER SHAFT HUNG UP TO BURR AND DID NOT EXTEND TO HOLD THE PARKING BRAKE LEVER DOWN AGAINST TOP 	OF CYLINDER.  PREVENTING APPLICATION OF PARKING BARKE BY NATURAL MOTION OF RUDDER PEDAL IN FLIGHT.  BRAKE LOCKED DURING 	FLIGHT UNKNOWN TO PRIOR.				1	H	7	1 	3O	3	O	NC	3A23    	1E4				 
2003080500053	20030805	00053	WP  	2003	8	5	2003FA0000604    	1	20030406	G	2840	A5211	TRANSMITTER     			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320*       	41508	EA  					LOW FUEL	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	9071K	1798 				0194				LOW FUEL WARNING SYSTEM WAS INOPERATIVE: WARNING LIGHT DOES NOT ILLUMINATE WHEN FUEL IS EMPTY.  INVESTIGATION REVEALED S	YSTEM COMPONENTS OPERATIVE SATISFACTORY, BUT A (BUTT CONNECTOR) REPAIR HAD BEEN MADE ON THE WIRE FROM CIRCUIT BREAKER TO	 SYSTEM AT AN UNKNOWN DATE BY AN UNKNOWN PERSON; REPAIR WAS NOT CRIMPED PROPERLY AND WIRE INSIDE INSULATION WAS SEVERED,	 PREVENTING LIGHT FROM ILLUMINATING.  CONDITION COULD NOT BE DETECTED DURING PREFLIGHT BECAUSE THIS SN AIRCRAFT DOES NOT	 HAVE A (PRESS TO TEST) SWITCH FOR THIS SYSTEM, UNLIKE LATER MODELS WHICH DO HAVE THIS TEST SWITCH.  IN COMBINATION WITH	 INACCURATE FUEL IDICATION SYSTEM, THIS IS A DANGEROUS SITUATION.	1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003080500054	20030805	00054	WP  	2003	8	5	2003FA0000605    	1	20030406	G	2840	624600473	INDICATOR       			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320*       	41508	EA  					FUEL SYSTEM	INACCURATE      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	9071K	1798 				0194				FUEL INDICATION SYSTEM INACCURATE:  GAUGE READS .1875 FULL WHEN TANK IS EMPTY.  REPLACED TRANSMITTER WITH OVERHAULED UNI	T AND PROBLEM REMAINED THE SAME.  ACCURACY OF SYSTEM SHOULD BE VERIFIED AT EACH ANNUAL OR 100 HOUR INSPECTION.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003080500055	20030805	00055	CE  	2003	8	5	2003FA0000606    	1	20030428	G	2721	07612101	SPROCKET        			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540*     	41532	EA  					TRIM WHEEL	WORN            	B			YGJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	4218U	788  				T20608035				RUDDER TRIM SYST DID NOT SEEM TO BE RESPONDING TO INDICATED TRIM INPUT.  INSP OF RUDDER TRIM SYS, IT WAS DISCOVERED THAT	 TRIM WHEEL SPROCKETS, PN 07612101 WERE NOT SHIMMED CORRECTLY TO ALLOW FOR PROPER ENGAGEMENT OF GEAR TEETH.  TWO SPROCKE	TS ENGAGE AT 90 DEGREES TO EACH OTHER AND WERE BARELY MAKING CONTACT.  AS INCREASING TRIM LOAD WAS APPLIED SPROCKETS WOU	LD SLIP INDUCING AN UNKNOWN ERROR INTO TRIM INDICATOR.  SLIPPAGE HAD CAUSED NOTCHES TO WEAR SPROCKET TEETH ALLOWING ADDI	TIONAL SLIPPAGE TO OCCUR WHEN DECREASINGLY LESS TRIM INPUT FORCES WERE APPLIED.   TRIM SYSTEM WAS NOT PROPERLY SHIMMED D	URING MFG.  PN 0761210-1 SPROCKETS WERE REPLACED AND SHIMMED FOR PROPER ENGAGEMENT.	1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2003070800046	20030708	00046	CE  	2003	7	8	2003FA0000607    	1	20030421	G	5500	17320345	ARM             			CESSNA	177   	177         	2073704	CE  	LYC   	O320  	O320*       	41508	EA  					GUST LOCK	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	2895X					17700295				WITH GUST LOCK INSTALLED BALANCE ARM LOCKED ON DOWN STOP WHILE A/C WAS TIED DOWN IN GUSTY WIND CONDITIONS.						1	H	7	1 	3O	3	O	NT	A13CE   	E274				 
2003082600094	20030826	00094	CE  	2003	8	26	2003FA0000608    	1	20030601	G	2720		CONTROL CABLE   			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					RUDDER	LOOSE           	D				O				OTHER                   				F			FLT CONT AFFECTED         			UK	UNKNOWN        	1			NE	01	228HP					R18201643				WHEN RUDDER IS DEFLECTED TO THE FAR RIGHT, THE RIGHT RUDDER CABLE GOES SLACK AND HANGS UP UNDER THE NUT FOR THE ELEVATOR	 PULLEY CLUSTER LOCATED BY THE FUSELAGE RIGHT SIDE ACCESS PANEL.  TO PREVENT THIS, INSTALLED A SECOND NUT ON THE BOLT AN	D INSTALLED AN AN4-15 BOLT INTO THE OTHER END OF THE SECOND NUT.  THIS WAS ASSEMBLED AND TORQUED USING LOCKTITE.				1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2003082600096	20030826	00096	CE  	2003	8	26	2003FA0000609    	1	20030523	G	3246	4087A	WHEEL           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG	SEPARATED       	B			CTUR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	21	58LF					TH237				WHILE AIRCRAFT OWNER WAS TAXING AIRCRAFT, NOSE WHEEL BEAD SEAT AREA SEPARATED.  PROBABLE CAUSE COULD BE ATTRIBUTED TO A 	PREVIOUS HARD LANDING OR A DEFECT IN THE PART AT TIME OF MFG.  TO PREVENT FUTURE OCCURANCES AT TIRE REPLACEMENT MORE DIL	LIGENT INSPECTION OF THE BEAD SEAT AREA.				1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2003080500047	20030805	00047	CE  	2003	8	5	2003FA0000610    	1	20030605	G	1430	S26061	MOUNT           			CESSNA	172   	172S        	2072439	CE  										WIRE HARNESS	DEBONDED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	567JW	1752 				172S8187				ON THE NEW C-172 R AND S AIRCRAFT, THE WIRING UNDER THE CABIN FLOOR IS ATTACHED WITH TIE WRAPS TO ADHESIVE BACKED NYLON 	MOUNTS P/N S2606-1, THAT ARE ADHEARED TO THE AIRCRAFT SKIN.  DURING PHASE 3 INSPECTION ON THIS AIRCRAFT WITH 1752.3 HOUR	S, FOUR MOUNTS WERE UNATTACHED, THE ADHESIVE DEBONDED ALLOWING THE WIRING TO BE UNSECURE. AT STATION 65.33 THE REAR SEAT	 INTERCOMM WIRES WERE CHAFING ON THE TRIM CABLES.  THE UNSECURED NYLON MOUNTS WERE REPLACED WITH ADEL CLAMPS SECURED WIT	H SCREWS AND NUTS.  NYLON ADHESIVE BACKED MOUNTS SHOULD NEVER HAVE BEEN CERTIFIED TO SECURE AIRCRAFT WIRING WITHOUT THE 	USE OF ATTACH SCREWS.  ON OTHER AIRCRAFT, FINDING THE S2606-1 MOUNTS DEBONDING FROM THE AIRCRAFT SKIN. 	1	H	7	1 	3O			NT	3A12    					 
2003080500049	20030805	00049	SO  	2003	8	5	2003FA0000611    	1	20030605	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  										AILERON	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	772FT	2048 	95   			2844029				BROKEN STRANDS ON LEFT BALANCE CABLE WAS FOUND DURING NORMAL MAINTENANCE. CABLE HAS BROKEN STRANDS AT POINT WHERE CABLE 	WAS INBOARD PULLEY AT WING ROOT. PULLEYS SHOW NO SIGN OF WEAR AND TURN FREELY.  THE TOTAL TIME ON THESE CABLES WERE FROM	 1049 TO 2058. PROBABLE CAUSE BAD CABLES.				1	L	7	1 	3O			 	2A13    					 
2003082600105	20030826	00105	CE  	2003	8	26	2003FA0000612    	1	20030521	G	2140	70121	MUFFLER         			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					HEATER	BULGED          	B			CGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	48GE	597  				E3215				HEATER MUFFLER ASSY FAILED 500 HR PRESSURE TEST PERFORMED IAW MM.  UPON DISASSEMBLY, FOUND LARGE BULGES IN EXTERIOR OF M	AIN BARREL OF MUFFLER, TOWARDS ONE END.  FAILURE MODE UNDETERMINED, POSSIBLY CAUSED BY OVERHEATING.  RECOMMEND THAT PERS	ONS INSPECTING SERIES AIRCRAFT ADHERE TO MFG AIRCRAFTS RECOMMENDED DETAILED INSPECTION SCHEDULE IN ORDER TO REMOVE FAILI	NG UNITS BEFORE POSSIBLY CAUSING CARBON MONOXIDE IN CABIN OR ENGINE COMPARTMENT FIRES.			1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2003082600113	20030826	00113	EA  	2003	8	26	2003FA0000613    	2	20030506	G	7322		THROTTLE PLATE  			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CARBURETOR	WORN            	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	17	738YH				CK34866	17270338	L514276			CARBURETOR WAS LEAKING FROM ACCELERATOR PUMP SHAFT SEAL.  IN ADDITION TO  PUMP SHAFT SEAL, UNIT WAS INSPECTED AND WAS AL	SO NOTED THAT THROTTLE SHAFT AND BUSHINGS WERE WORN BEYOND LIMITS.   INSTALLED THIS CARBURETOR BACK IN OUR CUSTOMERS PLA	NE, TEST FLEW WITH NO PROBLEMS.   JUST A COUPLE OF WEEKS LATER, CUSTOMER WAS MAKING APPROACH.  HAD PULLED THROTTLE BACK 	TO IDLE A LITTLE EARLY AND DECIDED TO PUSH THROTTLE CABLE FROM THROTTLE ARM TO SEE IF PROBLEM COULD BE IN THE CABLE.  IT	 WAS NOT,  ARM ON CARBURETOR WOULD NOT MOVE.  THROTTLE PLATE MAY HAVE COME LOOSE AND CAUSE A BINDING SITUATION.  ONE SCR	EW ON PLATE WAS SLIGHTLY LOOSE, BUT EVEN WITH PLATE REMOVED THERE WAS BINDING.  SENT CARBURETOR BACK FOR REWORK.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003082600114	20030826	00114	CE  	2003	8	26	2003FA0000614    	1	20030317	G	5730	9914218	ACCESS PANEL    			CESSNA	525   	525         	2076601	CE  										WING TANK	LEAKING         	B			FCPR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	177RE	2509 				5250030				FUEL BAY ACCESS PANELS CAUSE A FUEL LEAK WHEN INSTALLED AS SPARES REPLACEMENT.  AT ALL FASTENER HOLES ON EACH DOUBLER TH	ERE IS PROTRUSION CAUSED BY THE OLD PANELS DESIGNED WITH A MILLED AREA ON BACK SIDE OF COUNTER SUNK FASTENER HOLES.  WHE	N ORIGINAL PANEL SCREWS ARE TIGHTENED IN ANCHOR NUTS HAVE PULLED DOUBLER MATERIAL INTO THE MILLED AREA OF ACCESS PANELS 	LEAVING DIMPLE LIKE PROTRUSION UP TO DEPTH OF THE MILLED AREA. BUT WHEN YOU HAVE TO INSTALL NEW ACCESS PANELS NOT HAVING	 A MILLED AREA BECAUSE THE OLDER ONES ARE NO LONGER AVAILABLE YOU END UP WITH A FUEL LEAK DUE TO THE PROTRUSION HOLDING 	THE NEW FLAT PANELS AWAY FROM THE FLAT SURFACE OF THE DOUBLER.	1	L	7	2 	4F			RT	A1WI    					 
2003070700141	20030707	00141	EU  	2003	7	7	2003FA0000615    	1	20030429	G	5320	MY2023723	STRIP           			AMD   	FALC20	FALCON20C5  	2730107	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CENTER WING	MISALIGNED      	B			JGVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	20UA	11348				91				NOTICED FUEL LEAKING FROM LT SIDE OF CENTER WING AREA.  DETERMINED ORIGIN OF LEAKAGE TO BE TWO OF THE BOLTS THAT SECURE 	REMOVABLE CENTER PLANK.  WHILE REMOVING SEALANT FROM HEAD OF BOLT 19, FROM LT SIDE, ALONG FRONT ROW OF PLANK FASTENERS, 	FOUND THAT BOLT WAS NOT PROPERLY SECURED, WOULD NOT TIGHTEN AT ALL.  REMOVED BOLT 19 FROM CENTER PLANK.  BORESCOPE INSPE	CTION REVEALED THE NUTPLATE GANG STRIP WAS OUT OF POSITION.  FOUND ADJACENT BOLT 18, WAS NOT SECURED TO NUTPLATE GANG ST	RIP EITHER.  GANG STRIP SHIFTED DURING PLANK REINSTALLATION.  THESE TWO BOLTS ARE ONLY FASTENERS AFFECTED BY IMPROPER PO	SITION OF THIS GANG STRIP.  BOLTS APPEAR TO HAVE BEEN INSTALLED WITH SEALANT ON SHANK AND OVER THE HEAD AS INSTRUCTED.	2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
2003082600177	20030826	00177	SO  	2003	8	26	2003FA0000616    	1	20030430	G	3340	MP1600	CIRCUIT BREAKER 			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235*       	41505	EA  					ANTI COLL LIGHT	DEFECTIVE       	B			YJ5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	05	4267E	6500 				3878A0515				CHANGED 2 CIRCUIT BREAKERS.  PN 454707 HIGH VOLTAGE DROP AND WOULD NOT TRIP AT 200 PERCENT RATING.  PN 454706 HIGH VOLTA	GE DROP AND TERMINALS WERE HOT ENOUGH TO BLISTER A FINGER AFTER 5 MINUTES OF OPERATION.					1	L	7	1 	3O	3	O	 	A18SO   	E223				 
2003070800062	20030708	00062	SO  	2003	7	8	2003FA0000617    	1	20030318	G	3230	7954312	BOLT            			PIPER 	PA28  	PA28180     	7102808	SO  										TORQUE LINK	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	44681					287405274				CENTER TORQUE LOCK BOLT BROKE ON TAKE OFF WHICH CAUSED THE LANDING GEAR TO FALL OFF AIRCRAFT.  THE BOLT WAS AN OLD STYLE	 BOLT THAT IS STEPPED DOWN AT THE THREADS TO .5000.  A FIX WOULD BE TO HAVE THE NEW STYLE HEAVY DUTY BOLT WHICH IS .7500	 INSTALLED IN THE TORQUE LINK.				1	L	7	1 	3O			 	2A13    					 
2003070700074	20030707	00074	NM  	2003	7	7	2003FA0000618    	1	20030610	G	5712	13017R	RIB             			UNIVAR	415   	415C        	0420302	NM  	CONT  	C85   	C8512F      	17008	SO  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	147VX					3832				AD 2002-26-02 ADMENDMENT 39-12987, MFG SERVICE BULLETIN NR 31. METHOD 1, INSPECTION HOLES IN WING CENTER SECTION. INSPEC	TED FRONT AND REAR SPARS...NO EVIDENCE OF CORROSION. DISCOVERED CORRODED RIB, RIGHT SIDE TRAILING EDGE WING WALK BOX.  R	EMOVED AND REPLACED RIB WITH NEW MANUFACTURED. CLEANED LIGHT CORROSION FROM TRAILING EDGE WING WALK OUTER SKINS, TREATED	 AREA WITH ZINC CHROMATE. TREATED WING CENTER SECTION WITH CORROSION INHIBITOR.			1	L	7	1 	3O	3	O	 	A718    	E233				 
2003082600111	20030826	00111		2003	8	26	2003FA0000619    	4	20030610	G	2562	BS2190	BATTERY         																	ELT	LEAKING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01										TWO CELLS LEAKED. DESTROYED PRINTED CIRCUIT BOARD IN ELT. DISCOVERED DURING BIENNIAL REPLACEMENT.																			 
2003082600110	20030826	00110	NM  	2003	8	26	2003FA0000620    	1	20030610	G	5712	13017R	RIB             			UNIVAR	415   	415C        	0420302	NM  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09						3832				AD NO. 2001-CE-45-4D WING CENTER SECTION INSPECTION FOR CORROSION.  SERVICE BULLETIN NO.31  USED METHOD 1, INSPECTION HO	LES IN WING WALK.  INSPECTED FRONT AND REAR SPARS.  NO EVIDENCE OF CORROSION.  FOUND CORRODED WING WALK TRAILING EDGE RI	B, RIGHT SIDE.  REMOVED AND REPLACED THIS RIB WITH NEW MANUFACTURED PART. CLEANED LIGHT CORROSION FROM TRAILING EDGE WIN	GWALK OUTER SKINS, TREATED AREA WITH ZINC CHROMATE. TREATED WING CENTER SECTION WITH CORROSION INHIBITOR. 			1	L	7	1 	3O			 	A718    					 
2003082600107	20030826	00107	SO  	2003	8	26	2003FA0000621    	2	20030609	G	8530	AEC631397STA	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	7252T	79   				E2261				6/1/02 SIX NEW ECI CYLINDER ASSY AEC631397STA INSTALLED.  11/15/02 NR 4 CYL CRACKED AFTER 171 HOURS OF SERVICE AND DAMAG	ED NR 2 CYL, BOTH OF WHICH WERE REPLACED.  2/20/03 NR 2 CYL CRACKED AFTER 79 HOURS OF SERVICE.  4/4/03 NR 4 CYL CRACKED 	AFTER 99 HOURS OF SERVICE.  6/5/03 FOUND NR 2 PISTON RING LAND AREA CRACKED AND DAMAGED SKIRT, CLOSER EXAMINATION REVEAL	ED THE PISTON HAD NOT RECEIVED SOME MACHINING OPERATIONS AND THE SKIRT HAD CONTACTED THE CONNECTING ROD OF AN ADJACENT C	YLINDER.		1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2003082700034	20030827	00034	GL  	2003	8	27	2003FA0000622    	1	20030309	G	3233	3435640101	ACTUATOR        			AMTR  	GAIR  	GLASAIRIII  	05691HK	GL  	LYC   	O540  	IO540*      	41532	EA  					NLG	SEPARATED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	307SH	1044 				3061				ACTUATOR PISTON SEPARATED AT THE ROD END BEARING THREADED AREA.  MFG SB NR 109 DATED 1-1092 RECOMMENDED INSTALLATION OF 	A THREADED REINFORCEMENT BARREL (PN 523-5627-001) BE INSTALLED TO REPLACE TO ORIGINAL BEARING JAM NUT.  THIS SB HAD BEEN	 INSTALLED AT THE TIME OF THIS INCIDENT.				1	L	7	1 	3O	3	O	RT	EXPA1L71	1E4				 
2003082700067	20030827	00067	CE  	2003	8	27	2003FA0000623    	1	20030529	G	2731	12600744	ACTUATOR        			CESSNA	414   	414A        	2075907	CE  										ELEVATOR TRIM	FAILED          	B			CWNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	XEEBC					414A0009				NEWLY OVERHAUL ELEVATOR TRIM ACTUATOR LITERALLY FELL APART AFTER INSTALL DURING TRIM OP`S CHECKS.  GROOVE PIN PN .0937 X	 .325 TYPE 3 FELL OUT OF ROLL CHAIN SPROCKET PN 0310332.  GROOVE PIN HOLES WORN IN SPROCKET AND ACTUATOR CAUSING FAILURE	.  SUSPECT FAULTY OVERHAUL PROCEDURES.				1	L	7	2 	3O			 	A7CE    					 
2003090200040	20030902	00040	SO  	2003	9	2	2003FA0000625    	2	20030506	G	8530	655469A7	PISTON          								CONT  	O520  	IO520*      	17032	SO  					CYLINDER	IMPROPER PART   	B			BSYR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07										EACH CYLINDER KIT CONTAINS PISTON (PN 654850) ON PISTON BOX IS CORRECT.  THE ACTUAL PISTON IN BOX IS (PN 654840), WHICH 	IS LOW COMPRESSION PISTON FOR TSIO520 SERIES.										3	O			E5CE				 
2003082600176	20030826	00176	GL  	2003	8	26	2003FA0000626    	2	20030509	G	7250	23055438	NOZZLE          								ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	CRACKED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17			613  		CAT90072		CAE890607S			RECEIVED THE ENGINE FOR REPAIR DUE TO HIGH OIL TEMPERATURE.  DURING INSPECTION OF THE PARTS FOUND THE WELD ON 1 OF THE 5	 TURBINE NOZZLE DIAPHRAGM RETAINING KEYS WAS CRACKED THROUGH THE CNETER FOR ALMOST ITS ENTIRE LENGTH.										3	U			E1GL				 
2003082700058	20030827	00058	CE  	2003	8	27	2003FA0000627    	1	20030616	G	5511		SPAR            			CESSNA	172   	172P        	2072436	CE  										HORIZ STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	52250	2300 				17274460				FOUND HORIZIONAL STABILIZER SPAR CRACKED AROUND CENTER LIGHTING HOLE						1	H	7	1 	3O			NT	3A12    					 
2003061700228	20030617	00228	NM  	2003	6	17	2003FA0000628    	1	20030501	G	5270		ANNUNCIATOR     			ISRAEL	1125  	1125        	       	NM  	GARRTT	TFE731	TFE7313     	01518	WP  					CABIN DOOR	FALSE INDICATION	C				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			SO	14	455SH	4902 					9612729			MAIN CABIN DOOR OPENED ON CLIMB OUT.  INSIDE DOOR LEVER HAD NOT BEEN PLACED IN SECONDARY LATCH.  THE ANNUNCIATOR PANEL L	IGHT HAD EXTINGUISHED INDICATING DOOR WAS SECURE.  GULFSTREAM AEROSPACE HAS DETERMINED THAT ANNUNCIATOR LIGHT MAY BE EXT	INGUISHED WHILE DOOR LEVER HAS NOT BEEN PLACED IN SECONDARY LATCH.				2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2003082700028	20030827	00028	SO  	2003	8	27	2003FA0000629    	2	20030606	G	8530	SA631475	PISTON          								CONT  	O520  	IO520F      	17032	SO  					ENGINE	BROKEN          	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		1490 					818805R			DISMANTELD ENGINE DUE TO METAL CONTAMINATION. FOUND NR 2 PISTON SKIRT ON BOTTOM SIDE BROKEN.											3	O			E5CE				 
2003082700029	20030827	00029	SO  	2003	8	27	2003FA0000630    	2	20030530	G	8530	SA631475	PISTON          								CONT  	O520  	IO520D      	17032	SO  					ENGINE	BROKEN          	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03							1594579D			DISMANTLED ENGINE DUE TO METAL CONTAMINATION FOUND NR 2 PISTON SKIRT BROKEN ON BOTTOM SIDE.											3	O			E5CE				 
2003070800027	20030708	00027	CE  	2003	7	8	2003FA0000631    	1	20030528	G	3710	1H525	CHECK VALVE     			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					VACCUM PUMP	LOOSE           	B			SL5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	157RD	411  				18280646				PILOT REPORTED RIGHT VACUUM PUMP WARNING LIGHT WAS ON.  DURING  TROUBLESHOOTING, DISCONNECTED HOSE FROM RIGHT SIDE OF CH	ECK VALVE MANIFOLD TO CONNECT TEST KIT AND DISCOVERED TWO MISSING RIVETS, TWO RIVETS ABOUT TO FALL OUT AND TWO LOOSE RIV	ETS ALL ON THE RIGHT SIDE OF CHECK VALVE ALLOWING VACUUM AIR TO LEK OUT BETWEEN, THE VALVE DIAPHRAM.  PROBABLE CAUSE IS 	VIBRATION FROM ENGINE , ACTING ON HOSE CONNECTED THIS END, CANNOT SEE AT THIS TIME, ANY OTHER ROUTING OF HOSE.			1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2003070800029	20030708	00029	EA  	2003	7	8	2003FA0000633    	2	20030529	G	7322	6390217	CONTROL CABLE   			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					CARBURETOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01	1599R					283845	1045536A			CONTROL CABLE BROKE, ONE INCH FROM CARBURETOR IN FLIGHT.  CARBURETOR WENT TO IDLE CUT-OFF.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003082800001	20030828	00001	SO  	2003	8	28	2003FA0000638    	1	20030611	G	2810	12J3648A	COUPLING        			GULSTM	G1159 	GIV         	3980115	SO  										LT WING	MISMANUFACTURED 	C				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			NM	09	941AM	66   				1499				LEFT WING NACA VENT PORTING FUEL ONTO GROUND AND DURING CLIMB WHEN OVER 11000 LB OF FUEL PUT INTO WING. EVENTUALLY FOUND	 MISSING O-RING P/N MS29513-337 IN OUTBOARD VENT COUPLING P/N 12J36-48A. THIS WAS REPLACED BY MFG TECHNICIANS AT OPERATO	R'S FACILITY. FUNCTIONALLY CHECKED WITH WING FULLY LOADED WITH FUEL. IT WAS OBVIOUS THAT THIS WAS CAUSED BY THE AIRFRAME	 MANUFACTURER AND WAS NOT PROPERLY TESTED.			2	L	7	2 	4F			RT	A12EA   					 
2003082700068	20030827	00068	EA  	2003	8	27	2003FA0000639    	2	20030618	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OUT OF ADJUST   	B				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	15	405ER					172S9155	L3044751A			DURING A PRE TAKEOFF ENGINE CHECK, THE ENGINE WAS IDLING AT APPROXIMATELY 1000 RPM, AND WAS ROUGH. THE FUEL CONTROL WAS 	ADJUSTED...					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003082700069	20030827	00069	EA  	2003	8	27	2003FA0000640    	2	20030525	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OUT OF ADJUST   	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	418ER					172S8650	L2731951A			DURING A PRETAKEOFF IDLE CHECK, THE IDLE WAS FOUND TOO LOW AND ROUGH. THE FUEL CONTROL WAS ADJUSTD AND THE IDLE SPEED AN	D MIXURE CONFIRMED CORRECT..					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003082700070	20030827	00070	EA  	2003	8	27	2003FA0000641    	2	20030618	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	OUT OF ADJUST   	B				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SO	15	412ER					172S8643	L2819151A			DURING A RUNUP FOR A MAINTENANCE CHECK, THE IDLE RPM AS FOUND VERY LOW. IT WAS ADJUSTED AND CHECKED. THIS IS A PROBLEM W	ITH THIS FUEL CONTROL ENGINE COMBINATION THAT OCCURS REGULARLY.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003082700074	20030827	00074	CE  	2003	8	27	2003FA0000642    	1	20030616	G	5511		SPAR            			CESSNA	172   	172P        	2072436	CE  										HORIZ STAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	100SU	14628				17275001				FOUND HORIZONTAL STABILIZER SPAR CRACKED AROUND CENTER LIGHTING HOLE.						1	H	7	1 	3O			NT	3A12    					 
2003082800004	20030828	00004	SO  	2003	8	28	2003FA0000644    	1	20030618	G	6120	83930700	ROD END         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					PROP GOVERNOR	WORN            	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SO	15	708ER	1079 				2844067	L3023651A			DURING THE FLIGHT, ON TAKEOFF, THE ENGINE RPM WAS NOT CONSISTENT. INSPECTION OF THE PROPELLER GOVERNOR CABLE ROD END, RE	VEALED EXCESSIVE WEAR AT THE CONNECTION BETWEEN THE SPHERICAL BALL AND THE SOCKET IT SNAPS INTO.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003082700065	20030827	00065	EA  	2003	8	27	2003FA0000645    	2	20030514	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	ERRATIC         	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	439ER					172S8935	L2996851A			DURING THE PRE TAKEOFF IDLE CHECK, THE IDLE RPM WAS FOUND VERY LOW. IT WAS ADJUSTED. THE IDLE MIXTURE/SPEED, ON THIS SER	VO, IS VERY ERRATIC AND UNSTABLE WITHIN A VERY FEW NUMBER OF HOURS/DAYS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003082700063	20030827	00063	EA  	2003	8	27	2003FA0000646    	2	20030516	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	ERRATIC         	C				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	501ER					172S8947	L2996051A			DURING THE PRE TAKEOFF IDLE CHECK, THE IDLE RPM WAS FOUND VERY LOW. IT WAS ADJUSTED. THE IDLE MIXTURE/SPEED, ON THIS SER	VO, IS VERY ERRATIC AND UNSTABLE WITHIN A VERY FEW NUMBER OF HOURS/DAYS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003082700064	20030827	00064	EA  	2003	8	27	2003FA0000647    	2	20030519	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	ERRATIC         	B				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SO	15	498ER					17280674				DURING THE PRE TAKEOFF IDLE CHECK, THE IDLE RPM WAS FOUND VERY LOW. IT WAS ADJUSTED. THE IDLE MIXTURE/SPEED, ON THIS SER	VO, IS VERY ERRATIC AND UNSTABLE WITHIN A VERY FEW NUMBER OF HOURS/DAYS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003090200037	20030902	00037	WP  	2003	9	2	2003FA0000648    	2	20030613	G	7200	31030351	BEARING         	ALIDSG      		GRUMAN	SA16  	G64         	       	EA  	GARRTT	TPE331	TPE3312201A 	 	WP  					TORQUE SENSOR	DISINTEGRATED   	G				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			NM	09	3629E	687  			2R2957	744B	P26058			ENGINE SHUT DOWN IN FLIGHT, AIRCRAFT LANDED IN A FIELD SUFFERED SUBSTANTIAL DAMAGE. AN ENGINE TEARDOWN WAS CONDUCTED, TH	E TORQUE SENSOR GEAR BEARING HAD FAILED, THE BEARING HAD COME APART BITS AND PIECES OF THE CAGE AND BALLS WERE FOUND IN 	THE BOTTOM OF THE GEAR BOX. VERY LITTLE EVIDENCE OF HEAT, OUTER RACES WERE STILL SHINY.				2	H	7	2 	4R	4	T	 	EXPA2H72	E3WE				 
2003090200036	20030902	00036	NM  	2003	9	2	2003FA0000649    	1	20030501	G	5270		ANNUNCIATOR     	ISRAEL      		ISRAEL	1125  	1125        	       	NM  	GARRTT	TFE731	TFE7313     	01518	WP  					DOOR LATCH	FALSE INDICATION	C				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			SO	14		4902 				017	9612729			MAIN CABIN DOOR OPENED ON CLIMB OUT.  INSIDE DOOR LEVER HAD NOT BEEN PLACED IN SECONDARY LATCH.  THE ANNUNCIATOR PANEL L	IGHT HAD EXTINGUISHED INDICATING DOOR WAS SECURE. MFG HAS DETERMINED THAT ANNUNCIATOR LIGHT MAY BE EXTINGUISHED WHILE DO	OR LEVER HAS NOT BEEN PLACED IN SECONDARY LATCH.				2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2003090200048	20030902	00048	SW  	2003	9	2	2003FA0000650    	1	20030530	G	3250	35021505	VALVE           			SWRNGN	SA227 	SA227AC     	8780603	SW  										NLG STEERING	FAILED          	D				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			GL	03	387PH					AC531				DURING THE TAKEOFF ROLL, WHILE INDICATING 40 KIAS, THE PILOT DISARMED THE NOSEWHEEL STEERING IAW THE AFM. UPON APPROACHI	NG 95 KIAS THE AIRCRAFT BEGAN TO STEER LEFT. THE PILOT PUT IN RIGHT RUDDER AND RIGHT BRAKE WITH NO EFFECT. THE TAKE OFF 	WAS ABORTED BUT THE AIRCRAFT CONTINUED LEFT DEPARTING THE RUNWAY AND CONTINUING TO TURN LEFT UNTIL IT CAME TO A STOP. UP	ON INVESTIGATION IT WAS DISCOVERED THAT THE ARMING VALVE HAD ALLOWED HYDRAULIC PRESSURE TO ENTER THE STEERING MANIFOLD A	ND PASS THROUGH THE SERVO VALVE TO THE LEFT CYLINDER OF THE ACTUATOR.		2	L	7	2 	4T			RT	A8SW    					 
2003090200051	20030902	00051	SO  	2003	9	2	2003FA0000651    	1	20030522	G	2710	62701143	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					AILERONS	BROKEN          	B			ECQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	880FT	2256 				4496033				BOTH LT AND RT FORWARD AILERON CABLES HAVE BROKEN WIRES.  AT SPOT WHERE CABLE RIDES ON INBOARD PULLEY, NEAR WING ROOT.  	PULLEY TURNS FREELY.  FOUND ON ROUTINE MAINTENANCE.  PROBABLE CAUSE MISALIGNED PULLEY FROM FACTORY.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003090200052	20030902	00052	SO  	2003	9	2	2003FA0000652    	1	20030505	G	2750	62701185	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					TE FLAP	BROKEN          	B			OG5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	295ND	2861 				4496030				DURING SCHEDULED INSPECTION FLAP OPERATION WAS FOUND TO BE DIFFICULT.  FURTHER INSPECTION FOUND FLAP CABLE HAD 4 OF 7 ST	RANDS BROKEN AT WHERE THE CABLE ENTERS THE TURNBUCKLE TERMINAL.  NO ABNORMAL SWAGING WAS NOTED ON TERMINAL.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003070700098	20030707	00098	EU  	2003	7	7	2003FA0000653    	1	20030623	G	5280		DOOR            			ISRAEL	1125  	ASTRASPX    	4500205	EU  										RT MLG	OUT OF RIG      	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	15	420CE					139				RED INTRANSIT LIGHT STAYED ON AFTER SELECTING GEAR UP.  RIGGED RT MLG INBOARD DOOR AND RIGGED RT AND LT OUTBOARD.   MLG 	DOORS IAW MM 32-10-07.   FUNCTIONAL CHECKED GOOD.					2	L	7	2 	4F			RT	A16NM   					 
2003082700073	20030827	00073	CE  	2003	8	27	2003FA0000654    	1	20030618	G	2910	651710539	LINE            			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					HYD SYSTEM	CRACKED         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	09	121L	1491 				5500896				AIRCRAFT CAME BACK FROM A TRIP LEAKING HYDRAULIC FLUID FROM THE NOSE GEAR AREA.  FOUND LINE PN 6517105-39 CRACKED AND LE	AKING HYDRAULIC FLUID.					1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2003082700030	20030827	00030	SO  	2003	8	27	2003FA0000655    	2	20030603	G	8530		INTAKE VALVE    								CONT  	O470  	O470*       	17026	SO  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03										ENGINE 561.58 SMOH, NR 5 INTAKE VALVE, CRACK IN STEM .1875 INCH FROM TOP END.  COMPLETELY AROUND.  TELEDYNE TECH REP SAI	D IT WAS NORMAL.  STELLITE TIP WELDED INTO STEM.  OTHER VALVES IN ENGINE SHOW SIGNS OF CRACK STARTING.  CLYINDERS WERE F	ACTORY NEW AT OVERHAUL.									3	O			E273				 
2003070800043	20030708	00043	CE  	2003	7	8	2003FA0000656    	1	20030602	G	3297	1SF13	WIRE            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					DOWNLOCK SWITCH	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	5403M					402B0003	812629R			DURING INSPECTION OF THE GEAR, FOUND WIRE SPLICE BROKEN.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003082700060	20030827	00060	CE  	2003	8	27	2003FA0000658    	1	20030625	G	2510	161102127	CABLE           			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					PILOT SEAT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	2083F	410  				17280671				PILOT SEAT WOULD NOT MOVE FORWARD OR AFT WHEN MOVING SEAT LOCK CONTROL. INSPECTION FOUND OUTBOARD PIN NOT DISENGANGING F	ROM SEAT RAIL. FURTHER DISASSEMBLY FOUND THE CABLE BROKEN INTERNALLY JUST ABOVE PIN RETURN SPRING. (PREVIOUS MDR DATED 6	/25/03 SHOWED INCORRECT P/N OF MC194-24)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003082700036	20030827	00036	CE  	2003	8	27	2003FA0000659    	1	20030620	G	2497	321060	TERMINAL        			BEECH 	36    	A36         	1151604	CE  										BATTERY	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	04	30764	1272 				E2382				AIRCRAFT BATTERY POSTIVE CABLE TERMINAL BROKE AT THE BATTERY POST CONNECTOR IN FLIGHT.  ALL ELECTRICAL POWER WAS DISCONN	ECTED FROM AIRCRAFT.					1	L	7	1 	3O			 	3A15    					 
2003082700072	20030827	00072	CE  	2003	8	27	2003FA0000660    	1	20030617	G	5312	07126172	BULKHEAD        			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	B			VUXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	2157R	5187 				18255357				THIS DEFECT WAS FOUND AS A RESULT OF INSPECTION REQUIRED BY AD.  THIS PART WAS REPLACED AT THIS TIME JUNE 17, 2003.  TT 	5187.97.  THIS REPORT REQUIRED BY AD PART (I).					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003082800002	20030828	00002	CE  	2003	8	28	2003FA0000661    	1	20030623	G	3234	711701	SELECTOR VALVE  			RKWELL	NA265 	NA26540     	6402608	CE  	PWA   	JT12  	JT12A6A     	52042	NE  					LT MLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	13	43W					28215				MAIN LANDING GEAR DOOR SELECTOR VALVE FAILED CAUSING MAIN GEAR FAIRING DOORS TO REMAIN OPEN.  THE LANDING GEAR UN-SAFE L	IGHT REMAINED ON WITH GEAR UP.  WITH MAIN DOOR SELECTOR VALVE FAILED, HYDRAULIC PRESSURE WAS NOT SUPPLIED TO THE NOSE ST	EERING SYSTEM.  POSSIBLE CAUSE OF VALVE FAILURE MAY BE ATTRIBUTED TO THE AGE OF THE VALVE AND THE LIGHT FLIGHT SCHEDULE 	OF THE AIRCRAFT.			2	L	7	2 	4J	4	J	 	A2WE    	1E9				 
2003082700040	20030827	00040	CE  	2003	8	27	2003FA0000662    	1	20030529	G	3233	HH55	ROD END         			BEECH 	35    	F35         	1151514	CE  	CONT  	E225  	E225*       	17015	SO  					NLG ACTUATOR	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	3363C	5151 				D4030				NOSE LANDING GEAR RETRACT/ EXTEND ROD END (PN HH55) FAILED, ALLOWING THE NOSE GEAR TO MOVE OVER CENTER AND COLLAPSE.						1	L	7	1 	3O	3	O	 	A777    	E267				 
2003090200065	20030902	00065	SO  	2003	9	2	2003FA0000663    	1	20030514	G	3220	0615400	CLIP            			PIPER 	PA22  	PA22160     	7102214	SO  	LYC   	O320  	O320A1A     	41508	EA  					TAIL SPRING	BENT            	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	25	8714D					225895				ON ROLLOUT AFTER LANDING AC GROUND LOOPED TO RIGHT.  FOUND LEFT TAILSPRING ATTACH CLIP EARS OPENED UP.   STEERING CHAIN 	DISCONNECTED.  PILOT STATED NO SHIMMY.					1	H	7	1 	3O	3	O	 	1A6     	E274				 
2003082700062	20030827	00062	EA  	2003	8	27	2003FA0000664    	2	20030604	G	8520		STUD            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 2 CYLINDER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	122FR					17273927	L805476T			TWO 38-13 STUDS BROKEN N NR 2 CYLINDER TOP.  1940 HOURS SMOH.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003082800003	20030828	00003	GL  	2003	8	28	2003FA0000665    	1	20030615	G	1430		BOLT            			AMTR  	VANS  	RV8         	       	GL  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RT MLG	SHEARED         	G				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	05		111  	111  							RV-8, N9868K, LANDED AND BEGAN ROLLOUT WHEN THE RIGHT MAIN LANDING GEAR ASSEMBLY DEPARTED AIRCRAFT. INVESTIGATION REVEAL	ED THE RIGHT MAIN LANDING GEAR LEG ATTACH BOLT SHEARED/BROKE. FAILED LANDING GEAR PARTS HAVE BEEN SENT FOR ANALYSIS.					1	L	7	1 	3O	3	O	NT	EXPA1L71	1E10	5	C	P920	 
2003090200063	20030902	00063	CE  	2003	9	2	2003FA0000668    	1	20030411	G	2434	DOFF10300B	ALTERNATOR      			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	05			6    							ALTERNATOR FAN BLADES CAME OFF.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003090200069	20030902	00069	EU  	2003	9	2	2003FA0000669    	1	20030630	G	3242	50032804	BRAKE ASSY      			AMD   	FALC50	FALCON50MYST	2730106	EU  										MLG	VIBRATION       	B			DXSR	O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			GL	15	4351M					90				THE BRAKE ASSEMBLY WAS REMOVED AFTER 5 LANDINGS AND .7 FLIGHT HOURS DUE TO A VIBRATION WHEN THE BRAKES WERE APPLIED.  TH	E ASSEMBLY FAILED BENCH CHECK, THE GRIP AND TUBE ASSEMBLIES FAILED TO RELEASE THE BRAKE DISK.					2	L	7	3 	4F			 	A46EU   					 
2003090200070	20030902	00070	EU  	2003	9	2	2003FA0000670    	1	20030630	G	3242	50032804	BRAKE ASSY      			AMD   	FALC50	FALCON50MYST	2730106	EU  										MLG	OUT OF TOLERANCE	B			DWUR	O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			EA	11	4351M					90				THE BRAKE ASSEMBLY WAS REMOVED AFTER 5 LANDINGS AND .7 FLIGHT HOURS DUE TO A VIBRATION WHEN THE BRAKES WERE APPLIED.  TH	E ASSEMBLY FAILED A BENCH CHECK, THE GRIP AND TUBE ASSEMBLIES FAILED TO RELEASE THE BRAKE DISK.					2	L	7	3 	4F			 	A46EU   					 
2003082700032	20030827	00032	EU  	2003	8	27	2003FA0000671    	1	20030630	G	3242	50032804	BRAKE ASSY      			AMD   	FALC50	FALCON50MYST	2730106	EU  										MLG	OUT OF TOLERANCE	B				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			GL	15	4351M					90				BRAKE ASSEMBLY WAS REPLACED AND AFTER 5 LANDINGS IT WAS REMOVED AND BENCH CHECKED DUE TO A WHEEL VIBRATION.  THE ASSEMBL	Y FAILED THE BENCH CHECK.  THE GAP CLEARANCE WAS TWO NARROW.  THE GRIP AND TUBE ASSEMBLIES FAILED TO RELEASE THE BRAKE A	SSEMBLY				2	L	7	3 	4F			 	A46EU   					 
2003082700033	20030827	00033	EU  	2003	8	27	2003FA0000672    	1	20030630	G	3242	50032804	BRAKE ASSY      			AMD   	FALC50	FALCON50MYST	2730106	EU  										MLG	OUT OF TOLERANCE	B				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			GL	15	4351M					90				THE BRAKE ASSEMBLY WAS REMOVED AFTER 5 LANDINGS AND .7 FLIGHT HOURS DUE TO A VIBRATION WHEN THE BRAKES WERE APPLIED.  TH	E ASSEMBLY FAILED A BENCH CHEC THE GRIP AND TUBE ASSEMBLIES FAILED TO RELEASE THE BRAKE DISK.					2	L	7	3 	4F			 	A46EU   					 
2003090200078	20030902	00078	EA  	2003	9	2	2003FA0000673    	2	20030604	G	8530	AEL6510212	CYLINDER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17										CRACKED FROM TOP SPARK PLUG HOLE AROUND OUT SIDE EX SEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003070800007	20030708	00007	EA  	2003	7	8	2003FA0000674    	2	20030605	G	8530	AEL6510241	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	4328D	996  				288416019	L1346239A			CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090200079	20030902	00079	EA  	2003	9	2	2003FA0000675    	2	20030604	G	8530		CYLINDER HEAD   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	4328D	1958 				288416019	L810539A			CYLINDER CRACKED FROM HEAD OF COMBUSTION CHAMBER EX SIDE OUT TO COOLING RING.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090200080	20030902	00080	EA  	2003	9	2	2003FA0000676    	2	20030605	G	8530	AEL6510241	CYLINDER HEAD   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17										CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090200081	20030902	00081	EA  	2003	9	2	2003FA0000677    	2	20030605	G	8530	AEL6570241	CYLINDER HEAD   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	4379V	1829 				288516010	L1346239A			CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE OF EXHAUST SEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090200082	20030902	00082	EA  	2003	9	2	2003FA0000678    	2	20030605	G	8530	AEL6510241	CYLINDER HEAD   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	4379V	569  				288516010				CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090200083	20030902	00083	EA  	2003	9	2	2003FA0000679    	2	20030604	G	8530	AEL6510241	CYLINDER HEAD   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17										CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EXHAUST SEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090200085	20030902	00085	EU  	2003	9	2	2003FA0000680    	1	20030530	G	2720	N7799233627	TURNBUCKLE      			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A64      		EA  					RUDDER CONTROL	UNSAFETIED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	459MA	97   				259	PCEPM0138			DURING THE FIRST ONE HUNDRED HOUR INSPECTION OF THIS AIRCRAFT THE AFT TURNBUCKLE FOR THE RUDDER SYSTEM, AS VIEWED THROUG	H ACCESS DOOR 311, HAD FIVE THREADS EXPOSED ON LOWER END AND FOUR THREADS EXPOSED ON UPPER END.  BOTH ENDS WERE SAFETIED	 WITH CLIPS.  CLOSE INSPECTION ON ALL TURNBUCKLES BOTH FOR EXPOSED THREADS AND PROPER SAFETIES DURING FIRST 100 HOUR INS	PECTION.			1	L	7	1 	3T	4	T	RT	A60EU   	E4EA				 
2003090200094	20030902	00094	SW  	2003	9	2	2003FA0000681    	1	20030612	G	3213	31600	AXLE            			BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320*       	41508	EA  					LT MLG	BROKEN          	D			OF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	92LB	2800 				26273				STEEL AXLE BROKE AT WELD WHILE MOVING A/C BY HAND.  NO HARD LANDINGS REPORTED.						1	H	7	1 	3O	3	O	 	A759    	E274				 
2003090200095	20030902	00095	SO  	2003	9	2	2003FA0000682    	1	20030618	G	2750	6378209	LEVER           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					FLAP LEVER	WORN            	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	38290	7352 				287716239				INSPECTION OF FLAP SYSTEM DURING ANNUAL FOUND FLAP LEVEL HANDLE ATTACH BOLT HOLE WORN.  AD96-10-03 HAD BEEN PREVIOUSLY A	CCOMPLISHED IAW SB 965.  NEEDED NEW REPLACEMENT HANDLE, BUSHING AND BOLT.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090200101	20030902	00101	SO  	2003	9	2	2003FA0000683    	1	20030619	G	7120	6711961	MOUNT           			PIPER 	PA28  	PA28RT201   	7102818	SO  										RT ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	8364N	10325				28R8118060				ENGINE MOUNT TUBE CRACKED AT TOP RIGHT ENGINE ATTACH BELOW MOUNT CUSHION.  FOUND CRACK ON 100 HOUR INSPECTION.						1	L	7	1 	3O			 	2A13    					 
2003090200102	20030902	00102	EA  	2003	9	2	2003FA0000684    	3	20030622	G	6111		STRIP           			PIPER 	J3    	J3C*        	       	SO  						SNSNCH	W72	W72GK       	EA  	PROPELLER LE	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	CFSOR		900  					T7159		AT CRUISE, PORTION OF PROP LEADING EDGE STRIP SEPARATED FROM PROP.  EMERGENCY LANDING ON LAKE ERIE SHORE.  PROP OVERHAUL	ED IN 1974.  APPROX 40 HOURS SINCE LAST ANNUAL INSPECTION.					1	H	7	1 	3O			 	ATC660  		5	N	P170	 
2003090200109	20030902	00109	SW  	2003	9	2	2003FA0000685    	1	20030505	G	6120	B24573	FORK            			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PITCH CHANGE	CRACKED         	B			IX4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09		12000	200  							PITCH CHANGE FORK WAS CRACKED, POSSIBLY DUE TO EXCESSIVE ENGINE VIBRATION.  PROPELLER HAD 200 HOURS SINCE LAST OVERHAUL.	  CUSTOMER WAS ADVISED TO HAVE PROPELLER, DYNAMICALLY BALANCED TO AVOID ANY FURTHER DAMAGE TO PROPELLER ASSEMBLY.					1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P920	 
2003090200108	20030902	00108	GL  	2003	9	2	2003FA0000686    	1	20030703	G	2720	2055450300	SUPPORT BRACKET 			DIAMON	DA20  	DA20C1      	2990001	GL  										RUDDER HINGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	932AF	180  				C0198				LOWER RUDDER HINGE/SUPPORT BRACKET CRACKED AT THE LOWER WELD.						1	L	7	1 	3O			NT	TA4CH   					 
2003090200155	20030902	00155	NM  	2003	9	2	2003FA0000688    	1	20030625	G	6710	A4372	PIN             			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320*       	41508	EA  					FLT CONTROLS	BROKEN          	B			GJOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	8051M	508  				1168				DURING OTHER MAINTENANCE INSPECTION REVEALED COLLECTIVE JACK SHAFT MOVED FORE AND AFT.  AFTER FURTHER INSPECTION, FOUND 	TAB PIN A437-2 BROKEN BETWEEN MOUNTING HOLE AND RODE END THRU HOLE.  UNKNOWN CAUSE.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003090200157	20030902	00157	SO  	2003	9	2	2003FA0000689    	1	20030603	G	3297		WIRE            			PIPER 	PA34  	PA34200T    	7103406	SO  										DOWNLOCK SWITCH	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	147FL	4731 				348170047				WIRE BROKEN OFF OF SWITCH (N/C) SHORTED TO GROUND,  POPPED GEAR CONTROL CIRCUIT BREAKER.  INSULATION ON WIRE (SPAGETTI) 	VERY BRITTLE AND WOULD NOT BEND WITH THE GEAR MOVEMENT AND BROKEN WIRE AT SOLDER CONNECTOR ON SWITCH.  LANDING GEAR NEED	S TO BE REWIRED IN ALL THREE GEAR WELLS.				1	L	7	2 	3O			 	A7SO    					 
2003090200159	20030902	00159	EU  	2003	9	2	2003FA0000690    	1	20030620	G	5510	1100211	FITTING         			AEROSP	SA316 	SA315B      	8680615	EU  										HORIZONTAL STAB	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	28	58000	448  				2639				RIGHT HAND AFT (T) FITTING BROKEN.  THIS FITTING IS ONE OF FOUR THAT ATTACHES THE HORIZONTAL STABILIZER TO THE TAILBOOM.	  NO ABNORMAL VIBRATIONS.  CAUSE UNKNOWN, NEW UNPROVEN MODIFICATIONS.  AT 448 HOURS TT THIS STABILIZER HAS THE HIGHEST T	IME ON THIS STC.  SUGGEST DAILY INSPECTION, CHANGE MATERIAL FROM ALUMINUM TO STEEL.				1	G	7	1 	4U			 	H1IN    					 
2003090200161	20030902	00161	SW  	2003	9	2	2003FA0000691    	1	20030527	G	5711	52625263	SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235*       	41505	EA  					WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	6346N	2086 				470				CRACK UNDER PLYWOOD PLATE, BOTH CRACKS FLOW THE GRAIN.						1	H	7	1 	3O	3	O	 	A759    	E223				 
2003090200162	20030902	00162	CE  	2003	9	2	2003FA0000692    	1	20030620	G	2701	26134401	BEARING         			CESSNA	208   	208         	2073702	CE  										CONROL COLLUMN	CORRODED        	B			EL6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23										ROD ASSY PN 2613440-1 LOCATED CENTER FLOOR FORWARD BY PEDESTAL FORWARD BEARING NOTED, CORRODED AND WORN TO HAVE EXCESSIV	E PLAY.  BEARING HAS GREASE FITTING BUT HARD TO GAIN ACCESS TO, ALSO NOTED, EXCESSIVE WATER ACCUMULATING IN THIS AREAS A	ND NO DRAIN HOLES NOTED.  SUGGEST DRILLING HOLES AND INCREASE LUBE AND INSPECTION OF BEARING AS THIS CONTROL ROD IS THE 	MAIN CONNECTION BETWEEN CONTROL YOKE AND ELEVATOR CABLE BELLCRANK.			1	H	7	1 	3T			NT	A37CE   					 
2003090200164	20030902	00164	GL  	2003	9	2	2003FA0000693    	3	20030622	G	6111	FL76664Q	BLADE           			CONAER	LA4   	LA4200      	5110310	NE  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	BROKEN          	B			ME4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	4GS					738		CH18101		DURING NORMAL OPERATION, A PORTION OF BLADE TIP (P-TIP) BROKE OFF.						1	H	7	1 	3O			 	1A13    		5	C	P920	 
2003090200165	20030902	00165	EA  	2003	9	2	2003FA0000694    	2	20030529	G	7414	SLICK4345	MAGNETO         			SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					ENGINE	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	103WP	5    				S1573	L2539051A			MAGNETO WAS REPLACED ON 5-27-03 WITH THIS MAGNETO.  ON 5-28-03, WHILE PERFORMING MAGNETO CHECK, LEFT MAGNETO WAS DEAD.  	VERIFIED BY REMOING PRIMARY LEAD.  CHECKED NEXT DAY AND STILL WAS NOT FUNCTION ING.  REMOVED AND REPLACED MAGNETO.					1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2003090200166	20030902	00166	EA  	2003	9	2	2003FA0000695    	2	20030531	G	7414	67542	BEARING CAGE    			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  					IMPULSE COUPLING	DISINTEGRATED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	9827P					257556146	L2280840A			DURING MAINTENANCE ACTION, FOUND LT IMPULSE COUPLING MAG GEAR ROLLER BEARING CAGE, PN LYC 67542 DISINTEGRATED AND DEPOSI	TED IN OIL SUMP.  BOTH SIDES OF ROLLER CAGE CAME LOOSE AND ROLLER BALLS BUNCHED UP INSIDE BEARING RACES.  ADDITIONAL STR	ESS OF IMPULSE MAGNETO MAY CONTRIBUTE TO DEFECT.  RT MAG ROLLER BEARING, OK.				1	L	7	1 	3O	3	O	 	2A10    	E295				 
2003090200167	20030902	00167	EA  	2003	9	2	2003FA0000696    	2	20030531	G	7414	67542	BEARING CAGE    			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  					IMPULSE COUPLING	DISINTEGRATED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	9883P	974  				257556211	L1736940A			DURING MAINTENANCE ACTION, FOUND LT IMPULSE COUPLING  MAG GEAR ROLLER BEARING CAGE, PN LYC 67452 DISINTEGRATED AND DEPOS	ITED IN OIL SUMP.  BOTH SIDES OF ROLLER CAGE CAME LOOSE AND ROLLER BALLS BUNCHED UP INSIDE BEARING RACES.  ADDITIONAL ST	RESS OF IMPULSE MAG MAY CONTRIBUTE TO DEFECT.  RT MAG ROLLER BEARING, OK.				1	L	7	1 	3O	3	O	 	2A10    	E295				 
2003090200172	20030902	00172	CE  	2003	9	2	2003FA0000697    	1	20030701	G	3233	12805042	ACTUATOR        			CESSNA	210   	210L        	2073448	CE  										MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	03	210PY	2242 				21060117				SHORTLY AFTER TAKEOFF AND PRIOR TO PERFROMING TOUCH AND GO`S, IT WAS NOTED THAT LANDING GEARS WERE NOT SAFELY DOWN AND L	OCKED. MLG'S WERE VISUALLY NOT EXTENDING PASSED FREE HANGING POSITION. SEVERAL PROCEDURES AND ATTEMPTS WERE MADE OVER TH	E FOLLOWING THREE FLIGHT HOURS WITH NO SUCCESS. AIRCRAFT LANDED GEAR UP ON RUNWAY WITH NO FIRE, INJURIES AND SUSTAINING 	ONLY MINOR DAMAGES. UPON INSPECTION, IT WAS FOUND THAT MLG UPLOCK ACTUATOR PN 1280504-2 FAILED. WHEN SELECTING EXTEND PO	SITION, IT WOULD UNLOCK THE MLG'S BUT RESTRICT PRESSURE TO FLOW THROUGH IT TO EXTEND THE MLG ACTUATORS. AIRCRAFT WAS JUS	T OUT OF ANNUAL INSPECTION WHERE THE RETRACTION SYSTEM AND EMERGENCY EXTENSION SYSTEM WAS INSPECTED FREE OF DEFECTS.	1	H	7	1 	3O			 	3A21    					 
2003090200176	20030902	00176	NM  	2003	9	2	2003FA0000698    	1	20030713	G	5712		RIB             			UNIVAR	415   	415*        	       	NM  										RT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	3595H					4220				LIGHT CORROSION FOUND ON CENTER RIB IN RT SIDE OF WING WALK WAY BETWEEN 2ND, 3RD AND 4TH LITING HOLES.   WHILE INSPECTIN	G THE CENTER SECTION IAW AD AND SB NR 31-R1 IAW METHOD NR 3 OF THE AD AND SB.  THE CORROSION WAS REMOVED AND AFFECTED AR	EAS TREATED IAW AC 43-4A CHAP. 6 PARA. 640, PARA. 641. AND SB.31-R1.  NO OTHER COROSION WAS FOUND.				1	L	7	1 	3O			 	A718    					 
2003090200170	20030902	00170	GL  	2003	9	2	2003FA0000700    	1	20030711	G	7810	DC00015B	EXHAUST PIPE    			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03		233  				C0196	806396			EXHAUST STACK FLANGE CRACKED.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2003090300017	20030903	00017	SO  	2003	9	3	2003FA0000701    	1	20030702	G	2720		TORQUE TUBE     			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A60A     	52043	NE  					RUDDER	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	2FJ	5512 				31T7620050				FOUND RUDDER TORQUE TUBE WITH CORROSION ON TUBE AND SURROUNDING ALUMINUM RIB.  FOUND DURING INSPECTION IAW SB1105.  PROB	ABLE CAUSE IS DISSIMILAR METAL CORROSION.  CLOSERER INSPECTION DURING EVENT 1 INSPECTIONS.  REPAIRS REQUIRED REPLACEMENT	 OF THE TORQUE TUBE AND TWO RIBS.				1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2003090300018	20030903	00018	SO  	2003	9	3	2003FA0000702    	1	20030620	G	1430		BOLT            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					RT MLG STRUT	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	8209E	10109				288316027				BYSTANDER POINTED OUT TO PILOT THAT RT MLG HAD FOLDED BACKWARDS.  UPON INVESTIGATION IT WAS FOUND THAT ALL 4 STRUT CYLIN	DER ATTACH BOLTS WERE SHEARED OR MISSING AT THE LOWER SPAR FLANGE ATTACH POINT.  AT 100 HR INSPECTION, CONDUCTED 86 HOUR	S PREVIOUSLY, ALL BOLTS WERE PRESENT AND GEAR DID NOT MOVE WHEN SHAKEN.  IT IS SUGGESTED THAT ALL MLG GEAR ATTACH BOLTS 	BE WRENCH CHECKED FOR PROPER TIGHTNESS AT EACH 100 HOUR INSPECTION.			1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090300015	20030903	00015	CE  	2003	9	3	2003FA0000703    	1	20030715	G	3230	51412044	SUPPORT         			CESSNA	421   	421C        	2076016	CE  										MLG	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	88586	3907 				421C0644				THE TAB ON THE SUPPORT BROKE OFF ALLOWING THE RT MAIN LANDING GEAR UPLOCK PIVOT BLOCK TO MISSALIGN. THIS COULD RESULT IN	 THE LANDING GEAR NOT LOCKING UP OR NOT RELEASING WHEN DOWN WAS SELECTED.					1	L	7	2 	3O			 	A7CE    					 
2003090300002	20030903	00002	SO  	2003	9	3	2003FA0000704    	1	20030714	G	2841	38230002	FLOAT           			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540*      	41532	EA  					FUEL QTY	WORN            	D				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			SO	11	31642	3623 				32R7885114				FUEL QUANTITY FLOAT P/N 38230-002. COMPOSITE FLOAT HAS BEEN HITTING THE UPPER BODY OF THE ASSY WHEN IN A FULL CONDITION 	AND HAS WORN .2500 INCH GROOVE ON ONE SIDE OF FLOAT AND .1875 INCH GROOVE ON THE OTHER SIDE.  GAUGE STILL OPERATED, BUT 	PARTICLES OF THE COMPOSITE FLOAT MADE IT'S WAY TO THE FUEL SCREEN. PART NEEDS MECHANICAL STOP TO PREVENT CONTACT WITH UP	PER BODY.  HAVE DIGITAL PICTURES OF FLOAT.			1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2003090300013	20030903	00013	EA  	2003	9	3	2003FA0000705    	2	20030414	G	7414		POINTS          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO	WORN            	D			QYIR	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NM	01	9892J				3120253	17273952	L493276T			ENGINE STOPPAGE DUE TO ABNORMALLY HIGH WEAR TO THE LIFTING BLOCKS OF THE CONTACT POINTS OF BOTH THE LT AND RT SIDES OF A	 COMMON MAGNETO.  BOTH CONTACT POINTS WERE REMOVED AND INSPECTED FOR BOGUS PARTS; REINSTALLED, LUBRICATED, RE-GAPPED AND	 TIMED.  THE AIRCRAFT WAS RETURNED TO SERVICE AFTER GROUND RUN.  THE MAGNETO HAS 115.5 HOURS SINCE RETURN TO SERVICE.  M	AGNETO WAS PREVIOUSLY SENT BACK FOR THE SAME ABNORMAL WEAR AFTER 225.6 HOURS IN SERVICE.  			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003090300036	20030903	00036	SO  	2003	9	3	2003FA0000707    	1	20030701	G	3222	7642603	BRACE           			PIPER 	PA28  	PA28R200    	7102811	SO  										NLG DRAG BRACE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	8991E	6500 				28R7635220				DURING 100 HR INSPECTION, DISCOVERED 1.5 INCH LONG CRACK IN RT LEG OF NOSE LANDING GEAR DRAG BRACE, 1 INCH FORWARD OF AC	TUATOR ATTACH POINT.  AREA IS HIDDEN FROM VIEW BY DOWNLOCK SWITCH ASSY.  CRACK WAS CLOSED TIGHT AND UNDETECTABLE WHEN GE	AR WAS EXTENDED DOWN.  WHEN GEAR WAS RAISED, ACTUATOR PRESSURE CAUSED CRADT TO OPEN .030-.040 INCH.  (IF MECH HAD NOT BE	EN REPLACING DOWNLOCK SWITCH, COULD HAVE POSSIBLY NOT DISCOVERED CRACK.)  DOWNLOCK SWITCH HAD A (HOME MADE) STRIKER PLAT	E AND SWITCH WAS OUT OF ADJUSTMENT.  THIS MAY HAVE LED TO EXCESSIVE STRESS OVER A PERIOD OF TIME, AT THE ACTUATOR ATTACH	 POINT.	1	L	7	1 	3O			 	2A13    					 
2003090300039	20030903	00039	CE  	2003	9	3	2003FA0000708    	1	20030701	G	2910	4532403475005	LINE            			LEAR  	45    	45LEAR      	5170805	CE  										BRAKE LINE	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	397AT	1194 				105				LINE CHAFED ON TOP OF SPOILER SHUTOFF VALVE CAUSING HYDRAULIC LEAK.  REPLACE LINE AND BLED BRAKE SYSTEM.  TIME ON PART: 	1194.9 HOURS AND 1099 LANDINGS.  INSTALLED CLAMPS WITH SPACING DISTANCE TO PREVENT RECURRANCE.  MAY NEED TO INSTALL ADDI	TIONAL CLAMPS TO ENSURE THIS WOULD NOT HAPPEN AGAIN.  NOTE: STAINLESS STEEL LINE.				2	L	7	2 	4F			RT	T00008WI					 
2003090300040	20030903	00040	CE  	2003	9	3	2003FA0000709    	1	20030325	G	3233	98820152	ACTUATOR        			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					RT MLG	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	4873S					R18201440				CRACK INDICATIONS IN THE 2.28 INCH BORE.  CRACK FOUND WHILE INSPECTING ACTUATOR IAW SB 01-2 REV 1.  RIGHT MAIN GEAR.						1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2003090300043	20030903	00043	NE  	2003	9	3	2003FA0000710    	2	20030701	G	7200	414302017	HOUSING         								LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE	CLOGGED         	B			C7GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13							LE45876			NEWLY OVERHAULED COMBUSTOR HOUSING INSTALLED ON ENGINE LE-45876, DURING REPAIR.  WHILE ASSEMBLING THE ENGINE, A HIGH AND	 UNACCEPTABLE DELTA (P) WAS CONFIRMED, WHICH INDICATED CLOGGED OIL PASSAGE AT THE NR 2 AND NR 3 BEARING BORE AREA.  FURT	HER INVESTIGATION CONFIRMED THE PROBLEM.  REPAIR WORK AT VENDOR HAS BEEN HALTED PENDING FURTHER REVIEW AND SUCCESSFUL PR	OCESS AUDITS.  NOTE: NO NONCONFORMING PARTS HAVE BEEN RELEASED TO SERVICE BY THIS FACILITY.								3	U			E5NE10				 
2003090300044	20030903	00044		2003	9	3	2003FA0000711    	4	20030701	G	8300	408112017	GEAR            								LYC   	LTS101	LTS101600A  	41560	NE  					ACCESSORY G/B	WORN            	B			C7GR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13							LE43133			NEW PART INSTALLED ON ENGINE LE-43133 DURING REPAIR.  WHILE INVESTIGATING THE CAUSE OF AGB VIBRATION, IT WAS NOTED THAT 	THE OUTPUT GEAR MENTIONED IN BLOCK 5 HAD ABNORMAL WEAR FOR A NEW PART.  THE GEAR IN QUESTION WAS REMOVED FROM THE ENGINE	 AND RETURNED TO THE OEM FOR EVALUATION/ INVESTIGATION.  IT HAS BEEN DETERMINED THAT THIS PART WAS NOT MANUFACTURED CORR	ECTLY.   AS OF 06/30/03 THERE IS A RECALL IN PROCESS BY THE MANUFACTURER OF THIS PART.								3	U			E5NE				 
2003090300054	20030903	00054	EU  	2003	9	3	2003FA0000712    	1	20030716	G	2510	A780596L	SEAT            			LET   	L23   	L23         	1360308	EU  										OPTIONAL WEIGHT	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	437BA	100  				029015				THE WEIGHTED SEATS HAVE A HANDLE WELDED ON THE LEFT REAR CORNER. WITH THE SEAT BELT FASTENED IT IS POSSIBLE TO LIMIT FUL	L LEFT RUDDER TRAVEL DUE TO THE RUDDER PEDAL JAMMING THE SEAT BELT ATTACH TAB BETWEEN THE PEDAL AND THE HANDLE. IT ONLY 	HAPPENS WITH THE OPTIONAL WEIGHTED SEAT IN THE FRONT INSTALLED.				1	K	0	0 	  			RC	G24EU   					 
2003090300051	20030903	00051		2003	9	3	2003FA0000713    	4	20030715	G	3418	XE4N024	RELAY           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  										STALL WARNING	INOPERATIVE     	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	09	524AC	250  				686				NR 1 STICK SHAKER WOULD NOT TEST. FOUND INOPERATIVE RELAY, LOCATION NO. 018K2AN2.(GULFSTREAM P/N GAR835NR1.)						2	L	7	2 	4F			RT	A12EA   					 
2003091200031	20030912	00031		2003	9	12	2003FA0000714    	4	20030715	G	6122		GOVERNOR        			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	3539S	200  				317912119				PILOT REPORTED, WENT THRU SEVERE TURBULANCE AND LOST GOVERNOR CONTROL.  ENGINE WENT TO 2575 RPM.  TROUBLESHOT UNIT, COUL	D NOT DUPLICATE, OPERATED AND CHECKED WITH PROP TACH.  OPENED ON GROUND.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003091600055	20030916	00055	EU  	2003	9	16	2003FA0000715    	1	20030708	G	5751	120A1152	HINGE           			GROB  	120   	G120A       	1660208	EU  										RT AILERON	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	946  				85001				DURING 50 HR INSPECTION THE TECH FOUND THE RETAINING CLIP COMING OUT OF BEARING.						1	L	7	1 	3O			RT	A49CE   					 
2003091200134	20030912	00134	CE  	2003	9	12	2003FA0000716    	1	20030726	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DRY AIR	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5521A	465  				CE1338	825825R			AVIONICS PERSONNEL FOUND INSTRUMENT AIR PRESSURE LOW ON GROUND RUN UP.  ON FURTHER INVESTIGATION FOUND VANES WORN ON PUM	P.  RECOMMEND PUTTING DIFFERENT TYPE OF VANES IN PUMP TO LAST LONGER.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091200137	20030912	00137	EU  	2003	9	12	2003FA0000717    	1	20030606	G	3230	X030004000000	MANIFOLD        			GROB  	120   	G120A       	1660208	EU  										FLOW CONTROL	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF	549  				85007				DURING FLIGHT THE FLIGHT CREW REPORTED THAT THE LEFT GEAR WAS SLOW TO EXTEND.  MAINTENANCE PERSONNEL TROUBLESHOT SYSTEM 	AND FOUND LEFT EXTENSION VALVE BAD.  PROBABLE CAUSE IS BELIEVED PARTICIALS INSIDE OF VALVE WHICH PREVENTED FLUID TO FLOW	 UNRESTRICTED.				1	L	7	1 	3O			RT	A49CE   					 
2003091200140	20030912	00140	EU  	2003	9	12	2003FA0000718    	1	20030608	G	2910	0332204204	RELAY           			GROB  	120   	G120A       	1660208	EU  										HYD SYSTEM	SHORTED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF					85005				WHILE PERFORMING GEAR CHECK, THE HYDRAULIC PRESSURE WOULD NOT BUILD UP.  FOUND RELAY SHORTED OUT.  RECOMMEND INSTALLING 	AN INLINE FUSE IN THE SYSTEM.  WHEN THIS RELAY FAILS, THE RELAY AND DIODES BOARD ALSO FAILS.					1	L	7	1 	3O			RT	A49CE   					 
2003091200024	20030912	00024	CE  	2003	9	12	2003FA0000719    	1	20030620	G	3610	216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					PNEUMATIC SYS	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1570A	401  				CE1333	820456R			AIR PUMP FAILED TO PROVIDE AIR PRESSURE.  RECOMMEND DIFFERENT VANES OR BETTER MATERIAL.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091200145	20030912	00145	CE  	2003	9	12	2003FA0000720    	1	20030708	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					PNEUMATIC SYS	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8252T	313  				CE1545				INSTRUMENT AIR PRESSURE BELOW LIMITS AT LOWER RPM.  GYRO WARNING LIGHT ON AT 1100 RPM.  LOW VOLUME FROM AIR PUMP.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091500020	20030915	00020	CE  	2003	9	15	2003FA0000721    	1	20030624	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  										MLG	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5582X	304  				CE1353				DURING 50 HOUR INSPECTION OF LANDING GEAR, GEAR FAILED TO EXTEND (2) TIMES.  UPON TROUBLESHOOTING GEAR SYSTEM FOUND DYNA	MIC RELAY PN SM50D7 WAS BAD.  REPLACED DYNAMIC RELAY AND CYCLED GEAR SEVERAL TIMES OPERATIONAL OF GEAR CHECKED GOOD.					1	L	7	1 	3O			 	3A15    					 
2003091500014	20030915	00014	EU  	2003	9	15	2003FA0000722    	1	20030618	G	3234		LIGHT           			GROB  	120   	G120A       	1660208	EU  										GEAR HANDLE	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF					85007				PILOT REPORTED RT GEAR LIGHT INOPERATIVE IN FLIGHT, AFTER TOUCH DOWN GEAR INDICATOR LIGHT CAME ON.  ON FURTHER INVESTIGA	TION WE BELIEVE WE HAD AN INTERMITTENT LIGHT INSIDE THE GEAR HANDLE, AFTER FOUR GEAR CYCLES THE LIGHT QUIT WORKING.					1	L	7	1 	3O			RT	A49CE   					 
2003091500016	20030915	00016	CE  	2003	9	15	2003FA0000723    	1	20030617	G	5750	12527Y6331	CONTROL CABLE   			BEECH 	33    	F33A        	1151425	CE  										LT FLAP	BROKEN          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5581T					CE1350				PILOT REPORTED WHEN SETTING FLAP SELECTOR TO 15 DEGREES, INDICATOR STAYED A (0), RIGHT FLAP EXTENDED TO 30 DEGREES AND L	EFT FLAP STAYED IN THE UP POSITION AND CIRCUIT BREAKER POPPED.  ON FURTHER INVESTIGATION FOUND THAT FLAP CABLE WAS BROKE	N WERE IT CONNECTS TO THE FLAP MOTOR.				1	L	7	1 	3O			 	3A15    					 
2003091200148	20030912	00148	CE  	2003	9	12	2003FA0000724    	1	20030617	G	3340	0107900790	POWER SUPPLY    			BEECH 	33    	F33A        	1151425	CE  										TAIL STROBE	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8268T					CE1547				TAIL STROBE WAS FOUND INOPERATIVE BY THE MECHANIC PERFORMING THE PHASE INSPECTION.  ON FURTHER INVESTIGATION FOUND THE P	OWER SUPPLY INOPERATIVE.  TIME SINCE REPAIRED 2295.					1	L	7	1 	3O			 	3A15    					 
2003091600056	20030916	00056	CE  	2003	9	16	2003FA0000725    	1	20030619	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  										MLG	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5581T	649  				CE1350				PILOT REPORTED GEAR FAILED TO RETRACT DURING FLIGHT.  TROUBLESHOOT SYSTEM, BELIEVE RELAY FAILED INTERNALLY.  RECOMMEND F	INDING A BETTER RELAY.					1	L	7	1 	3O			 	3A15    					 
2003091600057	20030916	00057	EU  	2003	9	16	2003FA0000726    	1	20030619	G	3234		HANDLE          			GROB  	120   	G120A       	1660208	EU  										MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF					85002				PILOT REPORTED LT GEAR LIGHT FLICKERED IN FLIGHT.  ON FURTHER INVESTIGATION WE BELIEVE WE HAD AN INTERMITTENT LIGHT INSI	DE THE GEAR HANDLE.  NO PROBABLE CAUSE OR RECOMMENDATION TO PREVENT THIS FROM RECURRING.					1	L	7	1 	3O			RT	A49CE   					 
2003091200100	20030912	00100	CE  	2003	9	12	2003FA0000727    	1	20030618	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DRY AIR	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8268T					CE1547	825913R			PUMP OUTPUT DECREASED AS ENGINE WARMED UP UNTIL IT BECAME UNACCEPTABLE AT LOWER RPM.  AT 1000 RPM PRESSURE DROPPED BELOW	 3 INCHES ON INDICATOR.  TESTED AIR SYSTEM FOR LEAKS AND FOUND NONE.  CHECKED REGULATOR AND MANIFOLD VALVE, REPLACED BOT	H THE SYSTEM STILL FAILED TO MAINTAIN PROPER PRESSURE.  SO REPLACED ENGINE DRIVEN AIR PUMP AND SYSTEM PASSED.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091200101	20030912	00101	SO  	2003	9	12	2003FA0000728    	1	20030604	G	7921	20710A	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4144P					2843121	RL3909136A			FOUND OIL LEAK DURING PREFLIGHT BY STUDENT PILOT.  PRESSURE CHECKED OIL COOLER AND FOUND OIL LEAK AT TOP SEAM.  THIS IS 	A WEAK AREA ON THE COOLER.  MAY BE CAUSED BY VIBRATION OR IMPROPER INSTALLATION METHODS.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091200102	20030912	00102	SO  	2003	9	12	2003FA0000729    	1	20030604	G	7921	20710A	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4142Q	1601 				2843207	RL3705736A			FOUND OIL LEAK DURING PREFLIGHT BY STUDENT PILOT.  PRESSURE CHECKED OIL COOLER AND FOUND OIL LEAK AT TOP SEAM.  THIS IS 	A WEAK AREA ON THE COOLER.  MAY BE CAUSED BY VIBRATION OR IMPROPER INSTALLATION METHODS.  REPLACEMENT WITH BETTER COOLER	.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091600058	20030916	00058	EU  	2003	9	16	2003FA0000730    	1	20030604	G	3610		SHAFT           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					DRY AIR PUMP	SHEARED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF				T35829H	85005	L2826448A			DURING FLIGHT, THE INSTRUMENT VACUUM SYSTEM FAILED.  THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTE	M REVEALED THAT THE ROTOR SHAFT HAD SHEARED.  PROBABLE CAUSE MAY BE THE ENGINE MOUNTS USED ARE TOO SOFT AND ALLOW THE EN	GINE TO VIBRATE TOO MUCH AND THIS CAUSES THE PUMP SHAFT TO SHEAR.  RECOMMEND ALTERNATIVE DRY AIR PUMP OR ALTERNATIVE ENG	INE LOAD MOUNTS.			1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003091600059	20030916	00059	EU  	2003	9	16	2003FA0000731    	1	20030613	G	7722		PROBE           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					EXHAUST EGT	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF	941  				85002	L2802448A			ON GROUND RUN-UP EGT INDICATOR FLUCTUATED 25 DEGREES.  ON FURTHER INVESTIGATION FOUND CARBON ON END OF PROBE.						1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003091600060	20030916	00060	CE  	2003	9	16	2003FA0000732    	1	20030612	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  										MLG	STICKING        	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5587K	446  				CE1392				RELAY FAILED TO FUNCTION ON THREE SEPARATE OCCASIONS CAUSING LANDING GEAR NOT TO EXTEND, PROBABLE CAUSE IS STICKING SOLE	NOID.  RELAY IS SCHEDULED FOR CHANGE EVERY 900 HOURS.  RECOMMEND CHANGING TO AN IMPROVED DESIGN RELAY.					1	L	7	1 	3O			 	3A15    					 
2003091600061	20030916	00061	CE  	2003	9	16	2003FA0000733    	1	20030613	G	2842	10238901211	TRANSDUCER      			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520*      	17032	SO  					FUEL QTY	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8173C					CE1541	825840R			PILOT REPORTED GAUGE FLUCTUATED FOR A SHORT TIME THEN WENT TO (0) FOR 15 MINUTES.  AFTER THAT GAUGE INDICATED NORMAL FUE	L FLOW, DUE TO HIGH TIME PART.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091600062	20030916	00062	CE  	2003	9	16	2003FA0000734    	1	20030616	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  										MLG	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5519A	657  				CE1337				PILOT REPORTED GEAR FAILED TO RETRACT DURING FLIGHT.  TROUBLESHOT SYSTEM, BELIEVE RELAY FAILED INTERNALLY.						1	L	7	1 	3O			 	3A15    					 
2003091500031	20030915	00031	CE  	2003	9	15	2003FA0000735    	1	20030616	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  										MLG	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8251C	32   				CE1543				PILOT REPORTED GEAR FAILED TO EXTEND DURING FLIGHT.  TROUBLESHOT SYSTEM, BELIEVE RELAY FAILED INTERNALLY.  RECOMMEND FIN	DING A BETTER RELAY.					1	L	7	1 	3O			 	3A15    					 
2003091500010	20030915	00010	CE  	2003	9	15	2003FA0000736    	1	20030616	G	3234	MS25125E3	SELECTOR        			BEECH 	33    	F33A        	1151425	CE  										MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8251C					CE1543				PILOT REPORTED GEAR SWITCH DOES NOT LOWER GEAR AT TIMES, MUST BE FIRMLY PUSHED DOWN.						1	L	7	1 	3O			 	3A15    					 
2003091200025	20030912	00025	SO  	2003	9	12	2003FA0000737    	1	20030521	G	2597		WIRE            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					OVERHEAD PANEL	BURNED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4149Y	3990 				2843128	RL1412936A			THE WIRING, CONNECTOR AND PINS IN THE PANEL ASSY OVERHEAD SWITCHES ARE MELTED AND SHORTED OUT.  THE CONNECTOR IS P5 AND 	THE WIRES ARE L1B20, L1D20, AND L3B18 WHICH GOES TO THE LANDING LIGHT SWITCH, NAV. LIGHTS SWITCH, AND THE STROBE SWITCH.	  BELIEVED THE CAUSE IS HIGHTER RESISTANCE WAS CREATED AND WITH THE AMOUNT OF CONTINUOUS CURRENT FLOW CREATED ENOUGH HEA	T TO MELT THE CONNECTORS AND BURNED THE PINS.  ECOMMENDATION IS TO US A HIGHTER AMP CONNECTOR AND PINS.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091200026	20030912	00026	SO  	2003	9	12	2003FA0000738    	2	20030530	G	7322		SHAFT           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL CONTROL	BINDING         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5581T	6    				CE1350	820457R			PILOT REPORTED HIGH CHT AND OIL TEMP IN FLIGHT.  RAN AIRCRAFT AND FOUND ENGINE RUNNING LEAN,  ATTEMPTED TO SET THE MIXTU	RE BUT WE WERE UNABLE TO.  WHEN DISCONNECTING MIXTURE CONTROL CABLE FROM FUEL CONTRO AND MOVING THE SHAFT ON FUEL CONTRO	L BY HAND, FOUND IT ROUGH AND BINDING.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091600063	20030916	00063	CE  	2003	9	16	2003FA0000739    	1	20030529	G	7430		IGNITION SWITCH 			BEECH 	33    	F33A        	1151425	CE  										CABIN	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5582X					CE1353				PILOT REPORTED NO DROP IN RPM WHILE PERFORMING MAGNETO CHECK ON GROUND RUN UP.  WHILE JIGLING THE KEY AROUND, THE PILOT 	THEN NOTICED A DROP IN RPM.  MAGNETO SWITCH IS CHECKED BEFORE TAKEOFF BY PILOTS FOR PROPER OPERATION AND AT EACH 50 HOUR	 INSPECTION MY MAINTENANCE.				1	L	7	1 	3O			 	3A15    					 
2003091500032	20030915	00032	SO  	2003	9	15	2003FA0000740    	1	20030523	G	7921		OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	4130W	507  				2843204	L2847836A			FOUND OIL LEAK ON PREEFLIGHT INSPECTION BY STUDENT PILOT.  PRESSURE CHECKED OIL COOLER AND FOUND OIL COOLER LEAKING AT S	EM ON TOP.  THIS IS A WEAK AREA ON THE OIL COOLER, COULD BE CAUSED BY VIBRATION AND NOT USING A BACK UP WRENCH WHEN INST	ALLING OIL COOLER HOSES.  RECOMMEND FINDING A REPLACEMENT THAT IS MORE DURABLE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091200027	20030912	00027	CE  	2003	9	12	2003FA0000741    	1	20030605	G	2121	152320212	MOTOR           			BEECH 	33    	F33A        	1151425	CE  										VENT BLOWER	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5587K					CE1392				DURING FLIGHT, VENT BLOWER BECAME INOPERATIVE.  TESTED SYSTEM ON GROUND AND FOUND VENT BLOWER ASSEMBLY MOTOR WAS BURNED 	OUT.  SUSPECT CAUSE IS CONTINUOUS USE OF VENT BLOWER DURING FLIGHT.  RECOMMEND INSTALLING AN INTERMITTENT SWITCH TO SHUT	 OFF VENT BLOWER WHEN LANDING GEAR IS CYCLED UP.				1	L	7	1 	3O			 	3A15    					 
2003091600064	20030916	00064	CE  	2003	9	16	2003FA0000742    	1	20030609	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					DRY AIR	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5585Y	594  				CE1389				AVIONICS PERSONNEL FOUND INSTRUMENT AIR PRESSURE LOW ON GROUND RUN UP.  ON FURTHER INVESTIGATION FOUND VANES WORN ON PUM	P.  RECOMMEND PUTTING DIFFERENT TYPE OF VANES IN PUMP TO LAST LONGER.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091600065	20030916	00065	SO  	2003	9	16	2003FA0000743    	1	20030606	G	2435	MHB4016	STARTER         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4132D	1249 				2843234	RL3707736A			PILOT REPORTED AIRCRAFT IS HARD TO START.  ON FURTHER INVESTIGATION FOUND STARTER WAS BAD.  NO RECOMMENDATION AT THIS TI	ME BECAUSE STARTER WAS HIGH TIME.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091600066	20030916	00066		2003	9	16	2003FA0000744    	4	20030605	G	2562	ELT1104	CASE            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ELT	CORRODED        	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8101C	2747 				CE1538	825785R			DURING A REPLACEMENT OF THE ELT BATTERY FOR TIME CHANGE TECHNICIAN FOUND CORROSION INSIDE BATTERY CASE.  PROBABLE CAUSE 	IS THE HEAT.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091600067	20030916	00067	SO  	2003	9	16	2003FA0000745    	1	20030605	G	7921	2071011	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	4130W		15   			2843204	L2847836A			DURING A MAINTENANCE INSPECTION OF THIS AIRCRAFT, THE OIL COOLER WAS FOUND TO BE CRACKED AROUND THE MOUNTING BOLT HOLES 	AND LEAKING FROM THE SEAM IN THAT AREA.  PROBABLE CAUSE IS VIBRATION. RECOMMEND USING A SOLID PIECE OIL COOLER.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091600068	20030916	00068	CE  	2003	9	16	2003FA0000746    	1	20030605	G	3297	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MLG	STICKING        	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	03	8251C					CE1543	825822R			DURING FLIGHT, PILOT SELECTED GEAR UP.  THE GEAR REMAINED IN THE DOWN AND LOCKED POSITION.  TROUBLESHOT SYSTEM AND FOUND	 THE DYNAMIC RELAY WAS STICKING.  PROBABLE CAUSE IS THE POINTS NOT RELEASING.  RECOMMEND THAT A DIFFERENT STYLE RELAY BE	 USED.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091600069	20030916	00069	SO  	2003	9	16	2003FA0000747    	1	20030530	G	7921		OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4161Z	219  				2843129	RL3133236A			WHILE PERFORMING MAINTENANCE ON AIRCAFT, MECHANIC DISCOVERED OIL LEAK COMING FROM THE AREA OF THE OIL COOLER.  PERFORMIN	G PRESSURE CHECK ON OIL COOLER AND FOUND OIL COOLER LEAKING AT SEAM ON TOP.  THIS IS A WEAK AREA ON THE OIL COOLER, COUL	D BE CAUSED BY VIBRATION.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091600070	20030916	00070	SO  	2003	9	16	2003FA0000748    	1	20030630	G	2434		ALTERNATOR      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	BROKEN          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4175V	665  				2843126	RL1179636A			WHILE PERFORMING PHASE INSPECTION ON ENGINE, FOUND EAR BROKEN ON ALTERNATOR.  NEED TO MAKE SURE ALTERNATOR IS SHIM MED I	N THIS AREA SO THERE IS NO STRESS ON THE EARS.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091500033	20030915	00033	SO  	2003	9	15	2003FA0000749    	1	20030604	G	2434		DIODE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ALTERNATOR	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4144P	22   			D023784	2843121	RL39091			PILOT REPORTED ALTERNATOR INOPERATIVE.  LIGHT STAYED ON AND AMP METER SHOWED 28 AMPS.  UPON FURTHER INVESTIGATION, IT WA	S FOUND THAT A DIODE HAD FAILED INSIDE THE ALTERNATOR.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091600071	20030916	00071	EU  	2003	9	16	2003FA0000750    	1	20030513	G	2711	G1204105	ACTUATOR        			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					AILERON TRIM	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF	459  				85007	RL2451848A			DURING FLIGHT, TRIM WOULD NOT STOP AND CONTINUED TO MOVE TO THE LEFT.  PROBABLE CAUSE IS INTERNAL COMPONENT FAILURE IN T	HE AILERON TRIM ACTUATOR UNIT.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003091200015	20030912	00015	SO  	2003	9	12	2003FA0000751    	2	20030529	G	7322	6299022	FUEL CONTROL    			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5581T	6    				CE1350	820457R			WAS UNABLE TO SET IDLE MIXTURE AND TOP END WAS RUNNING LEAN.  PROBABLE CAUSE IS INTERNAL FAILURE ON FUEL CONTROL.  FEELS	 AS IF BRASS IS GALLING.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091200028	20030912	00028	SO  	2003	9	12	2003FA0000752    	1	20030603	G	3610	RA215CC	PUMP            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					PNEUMATIC SYS	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4133D	250  				2843117	RL202836A			DURING GROUND RUN, ENGINE DRIVEN DRY AIR PUMP FAILED TO PUT OUT PROPER PRESSURE AT IDLE RPM.  RAN AIRCRAFT UP AND AIR PR	ESSURE STILL LOW AT HIGHER RPM.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091200029	20030912	00029	SO  	2003	9	12	2003FA0000753    	1	20030603	G	3610	RA215CC	PUMP            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					DRY AIR	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4175V					2843126	RL1179636A			DURING GROUND RUN, ENGINE DRIVEN DRY AIR PUMP FAILED TO PUT OUT PROPER PRESSURE AT IDLE RPM.  RAN AIRCRAFT UP AND AIR PR	ESSURE STILL LOW AT HIGHER RPM.  PROBABLE CAUSE IS HEAT AND VANES WEARING ON THIS DRY AIR PUMP.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091200150	20030912	00150	NE  	2003	9	12	2003FA0000754    	3	20030714	G	6110		PROPELLER       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	TIO540*     	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  		INOPERATIVE     	B			R2JR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	47RF					3261		FC8468		PROPELLER ASSY, AIRCRAFT CREW REPORTED RT PROPELLER GOES TO FEATHER ON TAXI WITH HOT OIL.  ENGINE AND PROP GOVERNOR CHAN	GED.  PROPELLER SWAPPED.  PROBLEM FOUND TO BE PROPELLER AIR CHARGE PROCEDURE WAS CHANGED IAW MFG LS.  C/W THIS SL FIXED 	PROBLEM .				1	H	7	2 	3O	3	O	 	6A1     	E14EA	5	C	P25EA	 
2003091700023	20030917	00023	GL  	2003	9	17	2003FA0000756    	3	20030711	G	6110		BEARING         													MCAULY	2A34C	2A34C50     	GL  	PROPELLER	FAILED          	B			N5PR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01			170  					710327		PROPELLER LOCKED INTO LOW PITCH TWICE.  REMOVED NR 2 BLADE TO INSPECT NR 1 BLADE BUTT.  FOUND SEVERAL BALL BEARINGS PRES	SED INTO SIDE OF INNER HUB WALL AND FERRULE.   BEARING RACE BROKEN, WITH SEVERAL SMALL PIECES IN BOTTOM OF HUB.  PROPELL	ER, HUB HAD BEEN SERVICED WITH AUTOMATIC TRANSMISSION FLUID, NOT RED DYE OIL.  PROP WAS OVERHAULED 9/25/95.														5	C	P3EA	 
2003091200022	20030912	00022	SO  	2003	9	12	2003FA0000757    	1	20030710	G	5311	3039205	FRAME           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUSELAGE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	54770					277554078				FRAME HAS SEVERE RUST PITTING ON FRAME TUBING BOTTOM LEFT AND RIGHT SIDES FORWARD OF WELDED CLUSTER.   PITTING AREA APPR	OXIMATELY 1 INCH LONG ALL AROUND TUBING.  CAUSE UNKNOWN, HOWEVER THIS IS INBOARD AND AFT OF FLAP AREA.  NOTED CONDITION 	WHEN FLOOR REMOVED FOR ANNUAL AND AD 2008-09-13 FLAP TO TUBING REPAIR NEEDED.  THIS AREA SHOULD BE CHECKED ON OTHER AIRC	RAFT.			1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2003091700025	20030917	00025	EA  	2003	9	17	2003FA0000758    	2	20030710	G	8500	A6422	SHAFT           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					ENGINE FAN	DEFECTIVE       	C				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		HO	HOVERING       	1			SO	35	122YB	413  				3309	L3842936A			FANSHAFT SHEARED, WHILE AIRCRAFT WAS IN A HOVER, CAUSING THE COOLING FAN TO DROP INTO THE SCROLL.  CAUSE UNKNOWN, BUT BE	LIEVED TO HAVE STARTED WITH A CRACK CAUSED BY A MANUFACTURING DEFECT.					1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2003091200095	20030912	00095		2003	9	12	2003FA0000759    	4	20030404	G	2564		VALVE           																	LIFE RAFT	IMPROPER PART   	D			RU3A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15										WHILE CONDUCTING PART 135 TRAINING OF LIFE RAFT DEPLOYMENT USING A SWITLIK FOUR-MAN LIFE RAFT, THE RAFT FAILED TO INFLAT	E.  IT WAS DISCOVERED THAT .020 STAINLESS STEEL SAFETY WIRE, INSTALLED ON THE BOTTLE VALVE, PREVENTED INFLATION OF THE R	AFT.  THE VALVE SHOUD HAVE BEEN SAFETIED WITH .020 SOFT COPPER SAFETY WIRE.  INVESTIGATION FOUND THAT BOTTLE HAD RECENTL	Y BEEN RECHARGED.  WE IMMEDIATELY BEGAN INSPECTING THE REST OF THE FOUR-MAN RAFTS IN OUR FLEET AND HAVE FOUND 6 BOTTLE V	ALVES THUS FAR WITH .020 STAINLESS STEEL SAFETY WIRE INSTALLED.															 
2003091200130	20030912	00130	NE  	2003	9	12	2003FA0000760    	2	20030603	G	7250	2A0847	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CORRODED        	B			KB1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03										PART RECEIVED FROM REPAIR STATION FOR FPI IAW IAE V2500A1A5 (REV 53) AND V2500D5 (REV 35), ATA 72-43-20, TASK 70-23-02-2	30-501.  PART REJECTED AT FPI FOR HOLES AND PITS ON INNER GROVE.										4	F			E311NE				 
2003091700036	20030917	00036	NE  	2003	9	17	2003FA0000761    	2	20030423	G	8530		CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2B   	 	NE  					ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			WP	01	4107Q	5657 	51   			318253008				LT ENGINE FAILED DURING CLIMBOUT AT 1500 FEET AGL, 3 MILES FROM TAKE OFF.  INSPECTION REVEALED NR 2 CYLINDER SEPARATED F	ROM CASE, A LARGE SECTION OF THE CASE WAS BROKEN OFF AT THE NR 2 POSITION AND THE CONNECTING ROD WAS SEPARATED FROM THE 	CRANKSHAFT.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003091700038	20030917	00038	CE  	2003	9	17	2003FA0000762    	1	20030616	G	2131	13035616	CONTROLLER      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN PRESSURE	MISWIRED        	B			MNGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	312NC					5500290				PX CONTROLLER REPLACED DUE TO INTERNAL FAILURE AFTER REPLACEMENT PILOT COMPLAINED ABOUT A 6000+ FOOT PER MINUTE CABIN CL	IMB RATE AND THAT THE CONTROLLER BACK LIGHTING CAME ON WHEN THROTTLES WERE REDUCED BELOW 90 PERCENT.  INSPECTION OF THE 	SYSTEM REVEALED THAT THE REPLACEMENT CONTROLLER WAS MISS-WIRED AT OVERHAUL.  REPLACED THE CONTROLLER NO FURTHER PROBLEMS	 REPORTED.   (SW05200308828)			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003091500018	20030915	00018	CE  	2003	9	15	2003FA0000763    	1	20030709	G	3240		B-NUT           			CESSNA	206   	T206H       	2073303	CE  										BRAKE LINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	2456Q	25   				T20608273				WHILE PERFORMING SB 03-53-02, FOUND 5 EA (B NUTS) CRACKED, DUE TO OVERTORQUE ON BRAKE LINES.  SEG ATTACHED IPC PAGES AND	 LOCATION OF DAMAGED (B NUTS) NUMERED 1 THRU 5.  AC TT 0025.1.  LEFT AND RIGHT BRAKES.					1	H	7	1 	3O			RT	A4CE    					 
2003091800077	20030918	00077	CE  	2003	9	18	2003FA0000765    	1	20030718	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					PNUEMATIC SYS	WORN            	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5540P	387  				CE1335	825826R			INSTRUMENT AIR SYSTEM INDICATED LOW OUTPUT ON GAUGE.  UPON FURTHER INVESTIGATION OF PNUEMATIC SYSTEM FOUND INSTRUMENT AI	R PUMP VANES WHERE WORN.  PROBABLE CAUSE IS A COMBINATION OF ENGINE HEAT AND CARBON VANE HARDNESS.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091800078	20030918	00078	SO  	2003	9	18	2003FA0000766    	1	20030715	G	7921	20710A	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	4142Q	47   				2843207	RL3705736A			FOUND OIL LEAK DURING 50 HOUR INSPECTION.  FOUND COOLER TO BE CRACKED.  RECOMMEND CHANGING TO A SOLID CAN COOLER.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091200091	20030912	00091	CE  	2003	9	12	2003FA0000767    	1	20030715	G	3610	RA216CW	PUMP            			BEECH 	33    	F33A        	1151425	CE  										DRY AIR	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	8242T	256  				CE1610				FLIGHT CREW REPORTED THAT GYRO WOULD NOT ERECT AT LOW RPM.  DISCOVERED LOW INSTRUMENT AIR PRESSURE.  REPLACED AIR PUMP A	ND SYSTEM OPS CHECKED NORMAL.  NO RECOMMENDATION AT THIS TIME.					1	L	7	1 	3O			 	3A15    					 
2003091800079	20030918	00079		2003	9	18	2003FA0000768    	4	20030801	G	6113	D7309	SPINNER         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360GB   	17025	SO  					RT ENG PROPELLER	CRACKED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	644AC	194  				3449261				PROPELLER SPINNER BULKHEAD, CRACKED.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2003091000065	20030910	00065	CE  	2003	9	10	2003FA0000770    	1	20030730	G	3710	B906	HOSE            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	3D32C	B3D32C407   	GL  	VACUUM INLET	ROTTED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01	6201T	1302 	1302 			R18201938	L2358040A	821894		VACUUM SUPPLY LINE (MFG PART NO S 5202-10) LINES FROM THE INLET FILTER TO THE INSTRUMENTS (EASTMAN HY---ON B906 REDI- PL	ASTICE LINE FELL APART WHEN TOUCHED. THIS AIRCRAFT IS AN ORIGINAL INSTALLATION AND THE SECOND WITH THIS PLASTIC INSTALLE	D.				1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	EXPP5C	 
2003091000076	20030910	00076	EU  	2003	9	10	2003FA0000771    	1	20030718	G	1410	312301901	LINE            			STBROS	SD3   	SD360300    	       	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3A     	NE  	LT ENG BLEED AIR	BROKEN          	B				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	17		22788	4896 				160032	GP35		AIRCRAFT WAS CROSSING THE NORTH ATLANTIC BETWEEN GREENLAND AND ICELAND AND ONCE THEY REACHED CRUSING ALTITUDE THE LEFT E	NGINE SHUT DOWN. THEY STARTED LOSING ALTITUDE AND WENT INTO ICELAND.  THE LEFT ENGINE BLEED AIRLINE PART NR 3123019-01 H	AS BROKEN AT THE MOUNTING POINT AT THE BOTTOM OF THE COMPRESSOR CASE.  THIS LINE TAKES COMPRESSOR AIR FROM COMPRESSOR TO	 THE BLEED AIR FILTER THEN ON TO THE FCU.  THE LOSS OF P3 AIR TO THE FCU CAUSED THE ENGINE TO ROLL BACK TO MIN FLOW AND 	THEN SHUT DOWN. WAS N-360CC NOW G-BNYI		2	H	7	2 	4T	4	T	RT	A41EU   	E26NE	6	C	P14NE	 
2003091200149	20030912	00149	NE  	2003	9	12	2003FA0000772    	2	20030724	G	7230	410126004	DIFFUSER        								LYC   	LTS101	LTS101600A3 	41560	NE  					BLEED HOLE	MISOVERHAULED   	B			C7GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13							LE43198			DIFFUSER 4-101-260-04 (SN 0062A / C301849) WAS OVERHAULED, TRACKING NR C301849-1 DATED 02/26/2003. RECEIVED DIFFUSER FRO	M CUSTOMER FOR INSTALLATION IN THEIR ENGINE. UPON INSPECTION,  DISCOVERED THAT PART WAS MISSING P3 AIR BLEED HOLE. ADDIT	IONAL DIMENSIONAL INSPECTIONS WERE PERFORMED, FOUND AT LEAST THREE DIMENSIONS TO BE OUT OF B/P REQUIREMENTS. PART WAS IN	SPECTED, OVERHAULED IAW DER ROUTING NR AMT-1926/98-25. IN SEPTEMBER OF 2000 A SUSPECT UNAPPROVED PART WAS FILED WITH  FA	A BY THIS REPAIR STATION, REF. FAA SUP CASE FILE NO. 2001-00016. ON 23 APRIL 2001, WAS NOTIFIED THAT CASE WAS INVESTIGAT	ED AND WAS CLOSED. UNDERSTANDING WAS THAT DER REPAIR WAS RESCINDED.						3	U			E5NE				 
2003091500026	20030915	00026	CE  	2003	9	15	2003FA0000774    	1	20030731	G	3230	1015801881	LINE            			BEECH 	300   	300BEECH    	1152930	CE  										HYD SYSTEM	MISMANUFACTURED 	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	07		3318 				FL65				STAINLESS STEEL HYD RETURN LINE TO THE HYD POWER PACK CAME APART AT THE POINT WHERE THE FITTING IS SWEDGED ONTO THE TUBI	NG. THIS LINE APPERARS TO NOT HAVE BEEN SWEDGED.					2	L	7	2 	4T			 	A24CE   					 
2003091800066	20030918	00066	CE  	2003	9	18	2003FA0000775    	1	20030731	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	D				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	05	9592B	13641				172RG0905				AFTER TAKE OFF TOWER REPORTED RIGHT MAIN GEAR NOT FULLY RETRACTING. AFTER A NONEVENTFULL LANDING I INSPECTED THE MAIN LA	NDING GEAR ACTUATORS AND FOUND THE RIGHT ACTUATOR TO BE SEVERLY CRACKED AND THE LEFT ACTUATOR TO HAVE HAIRLINE CRACKS. A	 FERRY PERMIT WAS FILED WHERE THEY WERE REPLACED THE FOLLOWING DAY. ACCORDING TO THE NTSB THIS AIRCRAFT HAD A SIMILAR FA	ILURE OF THE RIGHT MAIN GEAR ACTUATOR IN 1992 WHERE IT GEARED UP IN CHICAGO. THE TOTAL CYCLES ARE UNKNOWN, BUT THE PROGR	AM WANTED ME TO ENTER IT.		1	H	7	1 	3O			 	3A17    					 
2003091700112	20030917	00112	CE  	2003	9	17	2003FA0000777    	1	20030731	G	2720		TORQUE TUBE     			BBAVIA	11    	11AC        	0191102	CE  										RUDDER PEDAL	SEPARATED       	G				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			GL	23	86233					11AC37				DURING ACCIDENT INVESTIGATION, FOUND BRACKET ATTACHED TO RUDDER PEDAL TORQUE TUBE FOR ATTACHMENT OF LT RUDDER CABLE SEPA	RATED FROM TORQUE TUBE. BRACKET APPEARED TO HAVE SMALL CRACK AT REAR, APPROXIMATELY 1 INCH BELOW CABLE ATTACHMENT HOLE, 	AND DURING ACCIDENT, IT APPEARS THAT EXCESSIVE FORCE ON THE RUDDER PEDALS CAUSED THIS BRACKET TO TWIST AND SEPARATE. BEC	AUSE OF THIS FAILURE, PILOT WAS UNABLE TO RECOVER FROM GROUND LOOP.			1	H	7	1 	3O			 	A761    					 
2003091800097	20030918	00097	SO  	2003	9	18	2003FA0000778    	1	20030718	G	5340	795530100	FITTING         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A1D     	41514	EA  					COCKPIT	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	9088Q	261  				2890002				DURING AN ANNUAL INSPECTION REMOVED TRIM FROM LEFT AND RIGHT WINDSHIELD POSTS.  FOUND FOAM INSULATION IN CONTACT WITH ST	EEL FITTINGS.  PN 79553-00 AND 7955301.  FITTINGS AND ATTACHING AN3 BOLTS WERE CORRODED.  THIS IS THE SECOND INSTANCE OF	 THIS CONDITION SEVERAL TIMES BEFORE.  RECOMMEND REMOVAL OF INSULATION.  TREATMENT AND REMOVAL OF CORROSION.  REPLACE AF	FECTED HARDWARE.  APPLY ZINC CHORATE AND DINATROL AV-8 CORROSION PREVENTATIVE.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091800103	20030918	00103	SW  	2003	9	18	2003FA0000779    	1	20030624	G	5730		FABRIC          			BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320*       	41508	EA  					BOTH WINGS	ROTTED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	8642V					31375				WING FABRIC WAS FOUND TO BE ROTTED ALONG THE EDGE OF THE STRAIGHT EDGED FIBREGLASS SURFACE TAPE ON A TWO YEAR OLD FACTOR	Y COVERED WING.  THE PAINT PPG SYSTEM DELTA, SHOWS CRACKS ALONG THE EDGES OF ALL SURFACE TAPES ON THE TOP OF BOTH WINGS 	IN THE PROP ARC.  THE BAY THAT ACTUALLY FAILED SHOWED A BROWN STAIN ALONG ITS LENGTH.  AIRCRAFT IS NORMALLY HANGARED.				1	H	7	1 	3O	3	O	 	A759    	E274				 
2003091800105	20030918	00105	SW  	2003	9	18	2003FA0000780    	1	20030717	G	3233	10203	SPRING          			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					MLG ACTUATOR	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	557RM	37   				290210				PILOT WAS UNABLE TO LOWER LANDING GEAR INVESTIGATION REVEALED THAT THE SUBJECT SPRING HAD A BROKEN TANG.  RESULTING FAIL	URE OF LANDING GEAR ACTUATOR.  MOONEY SB M20-279C WAS COMPLETED 37 HOURS AGO.					1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2003091800106	20030918	00106	SO  	2003	9	18	2003FA0000781    	1	20030722	G	5340	795530001	FITTING         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					COCKPIT	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	82085	3800 				288290132				DURING AN ANNUAL INSPECTION, REMOVED TRIM FROM LEFT AND RIGHT WINDSHIELD POSTS.  FOUND FOAM INSULATION IN CONTACT WITH S	TEEL FITTINGS (PN 7955300 AND 7955301). FITTINGS AND ATTACHING BOLTS (AN3) WERE RUSTED.  HAVE FOUND SEVERAL A/C WITH THI	S PROBLEM.  RECOMMEND REMOVAL OF FOAM INSULATION TREATMENT AND REMOVAL OF CORROSION.  REPLACE AFFECTED HARDWARE.  APPLY 	ZINC CHROMATE AND DINATROL AV8 CORROSION PREVENTATIVE.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091800107	20030918	00107	SO  	2003	9	18	2003FA0000782    	1	20030710	G	7160	86245036	AIR BOX         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					RT CARBURETTOR	CRACKED         	B			OG5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	326ND	125  				4496173				DURING SCHEDULED INSPECTION, RT ENGINE CARB AIRBOX WAS FOUND TO BE CRACKED ADJACENT TO 3 OF THE 4 CARB MOUNTING HOLES.  	RESEARCH OF FLEET MECHANIC RECORDS INDICATE THIS IS THE SECOND AIRBOX IN 2 WEEKS TO BE FOUND CRACKED IN THE SAME AREA.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003091800109	20030918	00109	SO  	2003	9	18	2003FA0000783    	1	20030701	G	2710	NAS649816S	BARREL          			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  					TURNBUCKLE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	54182					187609043	L4435127A			UPON INSPECTION FOUND TURN BARREL THAT HAS GROOVE FOR CLIPS SPLIT LOCATION UPPER RT ALIRON TURNBUCKLE ONLY FOUND THESE S	TYLE TURN BARRELS THAT DONT REQUIRE SAFETY WIRE ON LATER AIRCRAFT.  FOUND THIS BEFORE AND COULD CAUSE LOSS OF AILRON CON	TROL IF BROKEN.				1	H	7	1 	3O	3	O	 	1A2     	E274				 
2003091200098	20030912	00098		2003	9	12	2003FA0000784    	4	20030613	G	2562	465510	ELT             			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					CABIN	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	201QX					240367				NEW ELT WAS INOPERATIVE.  RETURNED TO SUPPLIER.						1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2003091800111	20030918	00111	SO  	2003	9	18	2003FA0000785    	1	20030708	G	2701	410046	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A1D     	41514	EA  					CONTROL WHEEL	LOOSE           	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4141U					2843125				DURING FLEET-WIDE INSPECTION, FOUND SCREW THAT ATTACHES CONTROL WHEEL TO CONTROL SHAFT LOOSE.  RECOMMEND DIFFERENT METHO	D OF ATTACHMENT OR THE USE OF A LOCKING/ SAFETY DEVICE.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091200099	20030912	00099	SO  	2003	9	12	2003FA0000786    	1	20030709	G	2701	MS24694S59	SCREW           	PIPER       		PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					CNTRL WHEEL YOKE	UNDERSIZE       	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	289PA	1464 				2844065				THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE WAS FOUND TO BE BACKED OUT ON THE PILOTS WHEEL BY A .2500 TURN.  WHEN	 THE SCREW BACKS OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS RESULTS IN NO FLIGH	T CONTROL INPUT.  PROBABLE CAUSE OF THE SCREW BACKING OUT IS THAT THE SCREW IS TOO SHORT.  THE MS24964-S59 SCREW IS 1.09	37 INCH LONG WITH ONLY HALF A THREAD SHOWING THROUGHT THE NUTPLATE.			1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003091800112	20030918	00112	SO  	2003	9	18	2003FA0000787    	1	20030709	G	2701	MS24694S59	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CONTROL WHEEL	BACKED OUT      	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	430PA	2602 				2843488	L3222236A			THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE WAS FOUND TO BE BACKED OUT ON THE PILOTS WHEEL BY A .2500 TURN.  WHEN	 THE SCREW BACKS OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS RESULTS IN NO FLIGH	T CONTROL INPUT.  PROBABLE CAUSE OF THE SCREW BACKING OUT IS THAT THE SCREW IS TOO SHORT.  THE MS24964S59 SCREW IS 1.093	7 INCH LONG WITH ONLY HALF A THREAD SHOWING THROUGH THE NUTPLATE.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091800113	20030918	00113	SO  	2003	9	18	2003FA0000788    	1	20030709	G	2701	MS24694S59	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CONTROL WHEEL	BACKED OUT      	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	428PA	2398 				2843476	RL2983936A			THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE WAS FOUND TO BE BACKED OUT ON THE PILOTS WHEEL BY A .2500 TURN.  WHEN	 THE SCREW BACKS OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS RESULTS IN NO FLIGH	T CONTROL INPUT.  PROBABLE CAUSE OF THE SCREW BACKING OUT IS THAT THE SCREW IS TO SHORT.  THE MS24964-S59 SCREW IS 1.093	7 INCH LONG WITH ONLY HALF A THREAD SHOWING THROUGH THE NUTPLATE.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091800114	20030918	00114	SO  	2003	9	18	2003FA0000789    	1	20030709	G	2701	MS24694S59	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CONTROL WHEEL	BACKED OUT      	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	429PA	2543 				2843487	L2939636A			THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE WAS FOUND TO BE BACKED OUT ON THE PILOTS WHEEL BY A .2500 TURN.  WHEN	 THE SCREW BACKS OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS RESULTS IN NO FLIGH	T CONTROL INPUT.  PROBABLE CAUSE OF THE SCREW BACKING OUT IS THAT THE SCREW IS TOO SHORT.  THE MS24964S59 SCREW IS 1.093	7 INCH LONG WITH ONLY HALF A THREAD SHOWING THROUGH THE NUTPLATE.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091800116	20030918	00116	SO  	2003	9	18	2003FA0000790    	1	20030709	G	2701	MS24694S59	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CONTROL WHEEL	BACKED OUT      	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	928PA	3508 				2843298	L2939636A			THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE WAS FOUND TO BE BACKED OUT ON THE PILOTS WHEEL BY A .2500 TURN.  WHEN	 THE SCREW BACKS OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS RESULTS IN NO FLIGH	T CONTROL INPUT.  PROBABLE CAUSE OF THE SCREW BACKING OUT IS THAT THE SCREW IS TOO SHORT.  THE MS24964-S59 SCREW IS 1.09	37 INCH LONG WITH ONLY HALF A THREAD SHOWING THROUGH THE NUTPLATE.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091800117	20030918	00117	SO  	2003	9	18	2003FA0000791    	1	20030709	G	2701	MS24694S59	SCREW           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	CONTROL YOKE	BACKED OUT      	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	433PA	2234 				4496063	L3831536A	34792K		THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE WAS FOUND TO BE BACKED OUT ON THE PILOTS WHEEL BY A .2500 TURN.  WHEN	 THE SCREW BACKS OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS RESULTS IN NO FLIGH	T CONTROL INPUT.  PROBABLE CAUSE OF THE SCREW BACKING OUT IS THAT THE SCREW IS TOO SHORT.  THE MS24964S59 SCREW IS 1.093	7 INCH LONG WITH ONLY HALF A THREAD SHOWING THROUGH THE NUTPLATE.			1	L	7	2 	3O	3	O	 	A19S0   	E286	5	N	P4EA	 
2003091800118	20030918	00118	SO  	2003	9	18	2003FA0000792    	1	20030709	G	2701	MS24694S59	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76E*        	EA  	CONTROL WHEEL	BACKED OUT      	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	917PA	3613 				2843306		33416K		THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE WAS FOUND TO BE BACKED OUT ON BOTH THE PILOT AND COPILOTS WHEEL BY A 	.2500 TURN.  WHNE THE SCREWS BACKS OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS R	ESULTS IN NO FLIGHT CONTROL INPUT.  PROBABLE CAUSE OF THE SCREW BACKING OUT IS THAT THE SCREW IS TOO SHORT.  THE MS24964	-S59 SCREW IS 1.0937 INCH LONG WITH ONLY HALF A THREAD SHOWING THROUGH THE NUTPLATE.			1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA4	 
2003091500015	20030915	00015	SO  	2003	9	15	2003FA0000793    	1	20030709	G	2701	MS24694S59	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	CONTROL COLLUMN	BACKED OUT      	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	445PA	2134 				2843500	L3833436A	34946K		THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE WAS FOUND TO BE BACKED OUT ON BOTH THE PILOT AND CO-PILOTS WHEEL BY A	 .2500 TURN.  WHEN THE SCREW BACKS OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS R	ESULTS IN NO FLIGHT CONTROL INPUT.  PROBABLE CAUSE IS THA THE SCREW IS TOO SHORT.  THE MS24964S59 SCREW IS 1.0937 INCH L	ONG WITH ONLY HALF A THREAD SHOWING THROUGH THE NUTPLATE.			1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2003091800119	20030918	00119	SO  	2003	9	18	2003FA0000794    	1	20030709	G	2701	MS24694S59	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76E*        	EA  	CONTROL WHEEL	BACKED OUT      	B			FQAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	288PA	1802 				2843502	L2840236A	34879K		THE SCREW THAT HOLDS THE CONTROL WHEEL TO THE YOKE BACKS OUT ON BOTH THE PILOT AND COPILOTS WHEEL.  WHEN THE SCREW BACKS	 OUT ENOUGH, IT FALLS OUT ALLOWING THE WHEEL TO ROTATE FREELY AROUND THE YOKE.  THIS RESULTS IN NO FLIGHT CONTROL INPUT.	  THIS INCIDENT HAPPENED ON THIS AIRCRAFT PILOT SIDE CONTROL WHEEL FORCING THE PILOT TO MAKE AN EMERGENCY LANDING ON A D	IRT ROAD.  AFTER LANDING, THE RIGHT WING IMPACTED A TREE CAUSING SEVERE DAMAGE TO THE WING AND FUSELAGE.  PROBABLE CAUSE	 OF THE SCREW BACKING OUT IS THAT THE SCREW IS TOO SHORT.  THE MS24964S59 SCREW IS 1.0937 INCH LONG WITH ONLY HALF A THR	EAD SHOWING THROUGH THE NUTPLATE.  ADDITIONALLY, THE LOCKING FEATURE OF THE NUTPLATE HAD FAILED.	1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA4	 
2003091800120	20030918	00120	SO  	2003	9	18	2003FA0000795    	1	20030708	G	2701	410046	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360C1F     	41514	EA  					CONTROL WHEEL	LOOSE           	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4188T					2843124				DURING FLEET-WIDE INSPECTION, FOUND SCREW THAT ATTACHES CONTROL WHEEL TO CONTROL SHAFT LOOSE.  RECOMMEND DIFFERENT METHO	D OF ATTACHMENT OR THE USE OF A LOCKING/SAFETY DEVICE.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091800121	20030918	00121	SO  	2003	9	18	2003FA0000796    	1	20030708	G	2701	410046	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  										CONTROL WHEEL	LOOSE           	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4133D					2843117				DURING FLEET-WIDE INSPECTION, FOUND SCREW THAT ATTACHES CONTROL WHEEL TO CONTROL SHAFT LOOSE.  RECOMMEND DIFFERENT METHO	D OF ATTACHMENT OR THE USE OF A LOCKING/SAFETY DEVICE.					1	L	7	1 	3O			 	2A13    					 
2003091800122	20030918	00122	SO  	2003	9	18	2003FA0000797    	1	20030708	G	2701	410046	SCREW           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	IO360A1A    	41514	EA  					CONTROL WHEEL	LOOSE           	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4163W					2843127				DURING FLEET-WIDE INSPECTION, FOUND SCREW THAT ATTACHES CONTROL WHEEL TO CONTROL SHAFT LOOSE.  RECOMMEND DIFFERENT METHO	D OF ATTACHMENT OR THE USE OF A LOCKING/SAFETY DEVICE.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003091200033	20030912	00033	CE  	2003	9	12	2003FA0000798    	1	20030403	G	1430	A251392	BOLT            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PROP	IMPROPER PART   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	397SP	2371 				172S8294	RL657951A			THE PROPELLER MOUNTING BOLTS ON NEW AC MODEL SEEM TO BE TOO SHORT.  THEY DO NOT EXTRUDE AT ALL THRU THE CRANKSHAFT PRESS	ED THREADED BUSHINGS.  USUALLY THE THREADS WILL EXTRUDE 2-3 THREADS THRU THE BUSHING.  RECOMMENDATION IS TO HAVE A LONGE	R BOLT INSTALLED SO THE THREADS EXTRUDE ALL THE WAY THRU THE CRANKSHAFT BUSHINGS AT LEAST 3 THREADS.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003091800125	20030918	00125	SO  	2003	9	18	2003FA0000799    	1	20030623	G	3213		AXLE            			PIPER 	PA25  	PA25260     	7102508	SO  	LYC   	O540  	O540G1A5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	MLG	FATIGUED        	D			CDMR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	8502L	5800 				254916	L1290040	99999		AIRCRAFT LANDED ON SOFT FIELD WITH A LANDING WEIGHT OF 2850 LB.  THE MAX. CERTIFIED GROSS WT 2900 LB.  AFTER TOUCH DOWN,	  APPROX 200FT DOWN THE RUNWAY.  THE RIGHT MAIN AXLE FAILED.  THE AXLE WAS NOT ORIGINAL EQUIPMENT, LANDING GEAR UNDER ST	C SA441SW.  THE AXLE WAS MACHINED FROM A SOLID PIECE OF ALUMINUM.  THE BRAKE OCCURED AT THE TRANSITION OF THE AXLE TO TH	E MOUNTING FLANGE.  RECOMMENDATIONS: AVOID LANDING AT OR NEAR GROSS WEIGHT.  INSPECT ALL REMAINING AXLES OF THIS TYPE PR	IOR TO FURTHER FLIGHT.  CENTER BORE THE ALUMINUM SOLID AXLES AND INSERT A STEEL TUBE.  REPLACE ALL SOLID ALUMINUM AXLES 	WITH STEEL TYPE. (EA17200307288)	1	L	7	1 	3O	3	O	 	2A10    	E295	5	N	P874	 
2003091200016	20030912	00016	NE  	2003	9	12	2003FA0000800    	3	20030310	G	6111	K6523A24	BLADE           			NAMER 	F51   	F51D        	6402309	WP  	PCKARD	V1650 	V1650*      	49001	SO  	HAMSTD	24D	24D50       	NE  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	8677E					4474865		154011		UPON REMOVING FAIRINGS ON BLADE, CORROSION WAS UNDER FAIRING. PROPELLER CAME FOR AD  LONGITUDINAL CRACKS FOUND ON CAMBER	 AND FACE SIDE BLADE FAIRING.  FAIRING WAS ORIGINALLY INSTALLED IN 1940'S.  NEED TO REPLACE THEM.					1	L	7	1 	4V	4	V	 	EXPA1L71	EXP4V	6	C	P784	 
2003091200151	20030912	00151	NE  	2003	9	12	2003FA0000802    	3	20030310	G	6111	K6523A24	BLADE           	HAMSTD      		NAMER 	F51   	F51D        	6402309	WP  	PCKARD	V1650 	V1650*      	49001	SO  	HAMSTD	24D	24D50       	NE  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	8677E				154011	4474865		154011		UPON REMVING FAIRINGS ON BLADE, CORROSION WAS UNDER FAIRING.  PROPELLER CAME FOR A.D. LONGITUDINAL CRACKS FOUND ON CAMBE	R AND FACE SIDE BLADE FAIRING.  FAIRING WAS ORIGINALLY INSTALLED IN 1940'S, NEED TO REPLACE THEM.					1	L	7	1 	4V	4	V	 	EXPA1L71	EXP4V	6	C	P784	 
2003091500021	20030915	00021	GL  	2003	9	15	2003FA0000803    	1	20030615	G	5510	PN81611	BRACE           			AVIAT 	A1    	A1A         	2210405	GL  	LYC   	O360  	O360*       	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HORIZONAL STAB	SHEARED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	190BA					1447	L3654536A	CH33048		PREFLT INSPECTION FOUND THE TERMINAL HOLDING THE LT FORWARD TAIL BRACE TO THE HORIZONTAL STABILIZER TO BE SHEARED OFF.						1	H	7	1 	3O	3	O	NC	A22NM   	E286	5	C	P920	 
2003091500028	20030915	00028	SO  	2003	9	15	2003FA0000804    	1	20030806	G	7100	LW18506	FLYWHEEL        			PIPER 	PA44  	PA44180     	7104402	SO  										STARTER	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	577ER	899  				4496153				FLYWHEEL ASSEMBLY AFT BELT GROOVE FLANGE BROKEN.  FLANGE WEB AREA VERY THIN.						1	L	7	2 	3O			 	A19S0   					 
2003091700048	20030917	00048	CE  	2003	9	17	2003FA0000806    	1	20030731	G	2750	55651754CR	CONTROL CABLE   			CESSNA	500   	560CESSNA   	2076750	CE  										TE FLAP	OUT OF RIG      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	374QS	2400 	2400 			560475				DURING INSP FLAP PRESELECT CABLE P/N: 5565175-4CR, LOCATED IN COCKPIT CTR PEDESTAL, WAS FOUND BROKEN IN HALF AT SWEDGED 	BALL END.  DURING INSTALLATION OF NEW CABLE IT WAS NOTED THAT NEW CABLE COULD NOT BE RIGGED EXACTLY IAW MM DUE TO LOCATI	ON OF PRESWEDGED BALL ON CABLE.  RIGGING SYSTEM IAW MM IS SUCH THAT A PRELOAD EXISTS ON CABLE AT SWEDGED BALL END WHENEV	ER FLAPS ARE RETRACTED TO ZERO DEGREES. TRYING TO RIG OUT PROBLEM WITH CABLE TURNBUCKLES IS NOT POSSIBLE.  CONTACTED MFG	 AND DISCUSSED SITUATION.  SUSPECT THAT CABLE PRESWEDGED BALL IS BEING INSTALLED IN WRONG SPOT ON CABLE.  ALL NEW CABLES	 HAVE THE BALL SWEDGED IN SAME SPOT ACCORDING TO THE MFG.	2	L	7	2 	4F			RT	A22CE   					 
2003091700011	20030917	00011	SO  	2003	9	17	2003FA0000807    	1	20030728	G	3297	1159SCAV3856	WIRE HARNESS    			GULSTM	G1159 	GIV         	3980115	SO  										MLG	DAMAGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	941AM	114  				1499				IN TRYING TO FIT BUSHING, P/N 1159LM20156, TO INSTALL MAIN GEAR JACK ADAPTER, IT WAS FOUND THAT THE PORTION OF THE 1159S	CAV385-6 WIRE HARNESS FOR THE NR 4 WHEEL SPEED SENSOR IN TRAILING LINK OF RIGHT HAND LANDING GEAR WAS DAMAGED SUCH THAT 	BOTH CONDUCTORS ONLY HAD A FEW STRANDS OF WIRE EACH ALLOWING CIRCUIT TO BE COMPLETE. SUSPECT THAT DAMAGE WAS CAUSED PREV	IOUSLY AT SERVICE CENTER. HARNESS WAS REPLACED WITH NEW COMPONENT.			2	L	7	2 	4F			RT	A12EA   					 
2003091800100	20030918	00100	NE  	2003	9	18	2003FA0000808    	3	20030310	G	6111	K6523A24	BLADE           			NAMER 	F51   	F51D        	6402309	WP  	PCKARD	V1650 	V1650*      	49001	SO  	HAMSTD	24D	24D50       	NE  	PROPELLER	CRACKED         	B				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	8677E					4474865		154011		UPON REMOVING FAIRINGS ON BLADE, CORROSION WAS UNDERFAIRING.  PROPELLER CAME FOR AD.  LONGITUDINAL CRACKS FOUND ON CAMBE	R AND FACE SIDE BLADE FAIRING.  FAIRING WAS ORIGINALLY INSTALLED IN 1940'S.  NEED TO REPLACE THEM.					1	L	7	1 	4V	4	V	 	EXPA1L71	EXP4V	6	C	P784	 
2003091700121	20030917	00121	SO  	2003	9	17	2003FA0000809    	2	20030801	G	8530	6524517	CYLINDER        								CONT  	O550  	IO550N      	17042	SO  					ENGINE	OUT OF TOLERANCE	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		25   					686263			DURING ENGINE ASSEMBLY AFTER LIGHTING STRIKE INSPECTION IN ACCORDANCE WITH TCM SB M88-9 FOUND ALL CYLINDERS TO HAVE EXCE	SSIVE DRY LIFTER CLEARANCE.  MANUFACTURERS SPECIFICATION IS .060 TO .200 INCH., ALL CYLINDER ALL VALVES EXCEEDED .200 IN	CH CLEARANCE.									3	O			E3SO				 
2003091700117	20030917	00117	CE  	2003	9	17	2003FA0000810    	1	20030731	G	2770	256CF145	GUST LOCK       			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  										RUDDER	MISSING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11						258525				RUDDER GUST LOCK WAS MISSING FROM AIRCRAFT.						2	L	7	2 	4F			RT	A3EU    					 
2003091900019	20030919	00019	CE  	2003	9	19	2003FA0000812    	1	20030701	G	3246	130909B177	BOLT            			BEECH 	B300  	B300        	1159232	CE  										BUSHING	SEIZED          	C				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SO	13	434BW					FL109				DURING INSPECTION FOUND BOLT ON NOSE WHEEL DRAG LEG SEIZED IN BUSHING AS THE RESULT OF IMPROPER LUBRICATION.  THIS SEEMS	 TO BE DUE TO A RESENT LUBE POINT DESIGN CHANGE.  THE OLD BOLT WAS HOLLOW ALLOWING GREASE TO BE DELIVERED TO THE INNER B	USHING.  THE NEW BOLT IS SOLED WITH THE LUBE POINTS ONLY ON OUTER BUSHINGS.				2	L	7	2 	4T			RT	A24CE   					 
2003091900020	20030919	00020	CE  	2003	9	19	2003FA0000813    	1	20030701	G	3246	130909B177	BOLT            			BEECH 	B300  	B300        	1159232	CE  										BUSHING	SEIZED          	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SO	13	583AT					FL258				DURING INSPECTION FOUND BOLT ON NOSE WHEEL DRAG LEG SEIZED IN BUSHING AS THE RESULT OF IMPROPER LUBRICATION.  THIS SEEMS	 TO BE DUE TO A RESENT LUBE POINT DESIGN CHANGE.  THE OLD BOLT WAS HOLLOW ALLOWING GREASE TO BE DELIVERED TO THE INNER B	USHING.  THE NEW BOLT IS SOLID WITH THE LUBE POINTS ONLY ON OUTER BUSHINGS.				2	L	7	2 	4T			RT	A24CE   					 
2003091900021	20030919	00021	CE  	2003	9	19	2003FA0000814    	1	20030701	G	2730	11452403725	CONTROL CABLE   			BEECH 	1900  	1900D       	1154162	CE  										ELEVATOR TRIM	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	61HA					UE175				DURING A GROUND OPERATIONAL CHECK, THE ELEVATOR TRIM CABLE BROKE.  THE PART HAD 7208.0 FLIGHT HOURS AND COMPLIED WITH AD	 2003-03-18 AND SAFETY COMMUNIQUE NR 216 ON 02/17/03.					2	L	7	2 	4T			RT	A24CE   					 
2003091900023	20030919	00023	SW  	2003	9	19	2003FA0000815    	1	20030717	G	7921	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					COOLER FAN	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	702WP	296  				53543				THIS WAS THE REAR OIL COOLER FAN SHAFT BEARING.  THIS IS PART OF THE TAIL ROTOR DRIVE SYSTEM FOR THIS AIRCRAFT.  THE BEA	RING SUFFERED A COMPLETE FAILURE.  BEARING BALLS WERE FOUND ON THE AIRCRAFT OIL COOLER DECK AREA ALONG WITH PIECES OF BE	ARING CAGE.  ONE BALL FROM THE BEARING WAS FOUND LODGED IN THE OIL COOLER IMPELLAR.  THIS CONDITION WAS FOUND ON A ROUTI	NE MAINTENANCE INSPECTION AT AC TOTAL TIME 296.3.  JULY 17, 2003.  VERY LITTLE GREASE WAS FOUND ON THESE BEARING PIECES 	AND THE REMAINING RACES.  THE PROBABLE CAUSE WAS LACK OF LUBRICATION INTERVAL OR REPLACEMENT OF THIS BEARING WITH A BEAR	ING OF A  DIFFERENT DESIGN, ABLE TO WITHSTAND THE HEAT GENERATED IN THIS AREA AND STILL RETAIN ITS LUBRICATION.	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003091800139	20030918	00139	CE  	2003	9	18	2003FA0000816    	1	20030808	G	2910	S3183E1	LINE            			CESSNA	560   	560XL       	2076702	CE  										HYD SYSTEM	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	637QS	2608 				5605137				LT FLAP RETRACTION HYDRAULIC LINE, RT AND LT EMERGENCY BRAKE PNEUMATIC LINES CHAFING ON PILLOW BLOCK CLAMPS.						2	L	7	2 	4F			RT	A22CE   					 
2003091900009	20030919	00009	SO  	2003	9	19	2003FA0000817    	1	20030808	G	7160	86245836	AIR BOX         			PIPER 	PA44  	PA44180     	7104402	SO  										CARBURETOR	BROKEN          	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			WP	28	572ER	333  				4496148				PILOT REPORTED SURGING ENGINE AND LOSS OF POWER IN FLIGHT. MECHANIC FOUND DUCT ON CARB AIRBOX FROM INDUCTION FILTER COMP	LETELY BROKEN OFF. PARTIALLY BLOCKING INTAKE. REPLACED COMPLETE ASSY.					1	L	7	2 	3O			 	A19S0   					 
2003091800101	20030918	00101	EA  	2003	9	18	2003FA0000819    	2	20030731	G	7310	LW120980180	LINE            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	FUEL SYSTEM	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	15	2370F	2370 	50   			17280618	L2778551A	RE012		NR 2 CYLINDER FUEL INJECTOR LINE RUBBING ON CYLINDER COOLING FIN, CAUSING A DEEP CUT IN OUTER WALL OF FUEL INJECTOR LINE	, LEADING TO POSSIBLE ENGINE FIRE.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003091800140	20030918	00140	CE  	2003	9	18	2003FA0000820    	1	20030808	G	2520		SEAT            			CESSNA	172   	172M        	2072418	CE  										CABIN	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	12577					17262088				NUMEROUS ROLL PINS IN THE PILOT AND PASSENGER SEAT FRAME (TUBULAR) ASSEMBLIES ARE BACKING OUT, ALSO FOUND NUMEROUS ROLL 	PINS THE EXACT LENGHT AS THE DIAMETER OF THE FRAME. THEREFORE WHEN THE PIN STARTS BACKING OUT THE PIN BENDS INSIDE THE F	RAME AND BREAKS, FOUND TWO PINS IN THIS CONDITION..				1	H	7	1 	3O			NT	3A12    					 
2003091200030	20030912	00030	SO  	2003	9	12	2003FA0000821    	1	20030801	G	2597	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					OVERHEAD PANEL	BURNED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4163W	3825 				2843127	RL3705636A			DURING MAINTENANCE ON AIRCRAFT TECHNICIAN FOUND CONNECTOR P5 PINS 5 AND 6 SHOWS SIGNS OF OVERHEATING AND DISCOLORING OF 	CONNECTOR AND PINS.  THESE PINS GO TO THE NAVIGATION LIGHTS.  PROBABLE CAUSE OF OVERHEATING IS CURRENT DRAW EXCEEDING DE	SIGN OF CONNECTORS AND PINS.  RECOMMENDATION IS TO INSTALL HIGHER PERFORMANCE CONNECTORS AND PINS.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003091200129	20030912	00129	SO  	2003	9	12	2003FA0000822    	2	20030730	G	8500	631427220	VALVE           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MANIFOLD	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5581T	93   				CE1350	820457R			FLIGHT CREW REPORTED THAT THE ENGINE WOULD NOT SHUT DOWN WHEN IDLE CUT OFF WAS SELECTED.  PROBABLE CAUSE IS INTERNAL FAI	LURE, DEBRIS, FAILED DIAPHRAGM.  NO RECOMMENDATIONS AT THIS TIME.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003091500030	20030915	00030	NM  	2003	9	15	2003FA0000823    	1	20030729	G	3213	400053501	STRUT           			PIPER 	PA60  	PA60601     	7106010	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					MLG	BROKEN          	E			TZRA	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	05	600TE	6973 				610146077				TORQUE LINK ATTACH POINT ON THE RIGHT STRUT BROKE AT LANDING. THIS ALLOWED THE RIGHT MLG TIRE TO ROTATE AND PULL THE AIR	CRAFT OFF THE RUNWAY. THE RESULTING SIDE LOAD ON THE MLG CAUSED THE OVER CENTER LINK PN 400084-001, AND THE STRUT CYLIND	ER 400054-001, TO BREAK. ALSO, BOTH RIGHT SIDE MLG DOOR WERE DAMAGED ALONG WITH THE RIGHT FLAP.   THE CUFF FOR ATTACHING	 THE TORQUE LINKS  TO THE STRUT IS INSTALLED BY THE SWEAT METHOD. IN THIS CASE, THE CUFF WAS BROKEN AT THE ATTACH POINT 	FOR THE SCISSORS LINK FOR SOME TIME AND NOT NOTICED DUE TO COVERAGE OF PAINT. IT TOOK A FEW LANDINGS FOR THE SWEAT ATTAC	HMENT TO BREAK LOOSE. THE DISBONDING WAS EVIDENT BY THE DISCOLOR OF THE SWEAT SEALED AREA ON THE CUFF AND THE STRUT.	1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2003091900035	20030919	00035	NM  	2003	9	19	2003FA0000824    	1	20030811	G	5730		SKIN            			UNIVAR	415   	A2ALON      	0540102	NM  										CENTER WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	10	6620W					A110				WHILE COMPLYING WITH AD NR 2002-26-02 ON THE WING CENTER SECTION OF THIS ERCOUPE WE FOUND SEVERAL SPOTS THAT WERE WELL B	EYOND LIGHT CORROSION AND HAD PROGRESSED INTO THE EXFOLIATION STAGE. WE ENDED UP REMOVING THE BOTTOM SKIN ON THE RIGHT W	ALKWAY TO REPLACE 2 STIFFENERS BEHIND THE RIGHT REAR AUX SPAR. AND REPLACED ANOTHER 9 STIFFENERS IN THE CENTER SECTION W	ING WALK AREAS. ALL AREAS CLEANED UP, AND ARE PRIMED AND TREATED FOR CORROSION AFTER PARTS REPLACEMENT.			1	L	7	1 	3O			 	A787    					 
2003091700032	20030917	00032	EU  	2003	9	17	2003FA0000826    	1	20030729	G	6710	ASNA013735E2	BEARING         	UROCOP      		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					CYCLIC CONTROL	ROUGH           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	72HP	2663 				2717	9277			CYCLIC CONTROLS PIVOT ON THIS BEARING DURING PITCH INPUTS. BEARING WAS (CATCHING) OR (RATCHETING) CAUSING DIFFICULTY CON	TROLLING AIRCRAFT IN PITCH.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003091200103	20030912	00103	CE  	2003	9	12	2003FA0000827    	1	20030328	G	7910	BJ1000A13DO	DRAIN           			BEECH 	55    	95A55       	1152704	CE  	CONT  	O470  	IO470*      	17026	SO  					VALVE BODY	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	20JW					TC258				QUICK DRAIN FAILED, CAUSING TOTAL LOSS OF ENGINE OIL.  AFTER SHUTDOWN OF ENGINE, BROKEN OFF PART WAS FOUND.  AFTER REMOV	ING OIL PAN, ENGINE OIL WAS CHECKED AT TIME OF OIL LOSS AND HAD 4 QUARTS REMAINING, BUT WAS STILL DRAINING.					1	L	7	2 	3O	3	O	 	3A16    	E1CE				 
2003091200044	20030912	00044	EA  	2003	9	12	2003FA0000828    	2	20030709	G	8520		CONNECTING ROD  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	152AW		715  			15285977	L937915			AIRCRAFT MADE EMERGENCY LANDING.  NR 3 CONNECTING ROD BROKE, CAUSING A HOLE TO BE PUNCHED IN THE CRANKCASE AND DESTROYIN	G THE CAM FOLLOWER AREA.  CAUSE OF FAILURE HAS NOT BEEN DETERMINED.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003091900104	20030919	00104	WP  	2003	9	19	2003FA0000829    	2	20030801	G	7210	310286529	GEARBOX         			AYRES 	S2    	S2RG10      	0970217	SO  	GARRTT	TPE331	TPE331*     	01514	WP  					PROPELLER	FAILED          	G				A				UNSCHED LANDING         				J	X		WARNING INDICATION        	ENGINE FLAMEOUT           		NR	NOT REPORTED   	1			GL	15	3299A	5361 				G10117				ENGINE LOW OIL PRESSURE LIGHT ILLUMINATED, FOLLOWED BY ENGINE FAILURE AND PROPELLER FEATHER.  SUBSEQUENT EXAMINATION FOU	ND SIGNIFICANT QUANTITIES OF FERROUS METAL IN GEARBOX OIL SCREEN, LOW OIL QUANTITY AND FEROUS METAL IN ENGINE OIL TANK.					1	L	7	1 	3T	3	T	NC	A4SW    	E2WE				 
2003091000083	20030910	00083	CE  	2003	9	10	2003FA0000831    	2	20030707	G	8530	6524201048	BOLT            			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					NR 2 & 3 CYL	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	365DP	1009 				1062				WHILE PERFORMING A COMPRESSION CHECK ON THE CYLINDER FOR THE 100 HOUR INSPECTION, HAPPENED TO LOOK AT THE CYLINDER BOLTS	 AND NOTICED ONE OF THE NUTS WAS MISSING ON THE TOP FORWARD THRU BOLT ON THE NR 2 CYLINDER.  LOOKED AROUND ON THE BAFFLI	NG AND FOUND THE OTHER PIECE OF THE BOLT WITH THE NUT STILL ATTACHED.  WENT OVER TO THE NR 3 CYLINDER TO LOOK AND FOUND 	THAT THE NUT WAS MISSING ON THE THRU BOLT AFTER LOOKING AROUND THE AREA, FOUND THE NUT ON THE CYLINDER BAFFLE.  AFTER LO	OKING AT THE NUT AND THE THRU BOLT, IT APPEARS THAT THE THRU BOLT WAS OVERTORQUED AT THE FACTORY.  HAD TO REPLACE BOTH U	PPER AND LOWER THRU BOLTS.	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003091500019	20030915	00019	EA  	2003	9	15	2003FA0000834    	2	20030808	G	8530		VALVE GUIDE     			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CYLINDER	DAMAGED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	442EK	550  				1146	L2599740A			CYLINDER ASSY LOCATED AT NR 5 POSITION.  EXHAUST VALVE STUCK, UPON REMOVAL OF THE CYLINDER FROM THE ENGINE.  THE INTAKE 	VALVE LIFTER WAS ALSO FOUND TO BE DAMAGED (SHATTERED).					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003092200011	20030922	00011	SO  	2003	9	22	2003FA0000835    	1	20030728	G	2797	W20994304	WIRE            			PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360*       	41514	EA  					LT AILERON	FRAYED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	5863P					24946	L135236			REPLACED W2094304, DUE TO 4 FRAYED WIRES.  FOUND AT ANNUAL.  LOCATION , BEHIND LEFT GEAR WELL COVER WHERE CABLE COMES IN	TO WING.					1	L	7	1 	3O	3	O	 	1A15    	E286				 
2003092200012	20030922	00012	GL  	2003	9	22	2003FA0000836    	1	20030801	G	5210	MS16562224	PIN             			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					CREW DOOR	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	823AC	116  				1201				COPILOTS DOOR WOULD NOT OPEN FROM INSIDE.  OUTSIDE HANDLE WORKED OK.  UPON DISASSEMBLY, THE PIN (CROSS PIN) FOR THE PILO	TS WAS FOUND SHEARED.  SAFETY HAZARED EVIDENT.  REPLACED PIN FROM PN MS16562-224.  NO FURTHER MALFUNCTIONS AT THIS TIME.					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003091500024	20030915	00024	CE  	2003	9	15	2003FA0000837    	1	20030809	G	3340	1520010	POWER SUPPLY    			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					STROBE	MALFUNCTIONED   	B			UVJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	737XS					17269759				THIS UNIT WAS PURCHASED TO REPLACE AN EXISTING FACTORY UNIT.  UPON INSTALLATION IT WAS TESTED AND DETERMINED TO BE MALFU	NCTIONING, FLASHES ARE SPACED APPROXIMATELY 10 SECONDS APART.  MARKINGS ON THE DATA TAG OF THE POWER UNIT ARE UNCLEAR AS	 TO THE VOLTAGE.  THE TAG INDICATES 12-14 VOLTS.  THE PART UMBER IS LISTED AS CAPABLE OF 12 V OR 24 V.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003092200013	20030922	00013	EA  	2003	9	22	2003FA0000838    	2	20030813	G	8520	LW18840	CAMSHAFT        			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ENGINE	SPALLED         	B			PP4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	205N		998  			243030	L1843151A			FOUND EVIDENCE OF SEVERE SPALLING ON SEVERAL CAM LOBES.  ENGINE HAS 998.37 HOURS SINCE OVERHAUL.  CAM WAS REGROUND AT OV	ERHAUL.					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2003092200048	20030922	00048		2003	9	22	2003FA0000839    	4	20030812	G	2562	E01	ELT             			CIRRUS	SR    	SR20        	05628AJ	GL  	LYC   	O360  	IO360A1A    	41514	EA  					CABIN	FALSE ACTIVATION	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	213CD					1111				WHEN COMM 2 TRANSMITS IT ACTIVATES ELT WHICH THEN NEEDS TO BE MANUALLY SHUT OFF.  ELT HAS BEEN EXCHANGED, NO HELP.  PROX	IMITY OF NR 2 COMM ANTENNA (BOTTOM REAR MOUNT) MAY BE CAUSE OF PROBLEM.					1	L	7	1 	3O	3	O	NT	A00009CH	1E10				 
2003092200050	20030922	00050	CE  	2003	9	22	2003FA0000840    	1	20030801	G	3244	021350	TIRE            			MTSBSI	MU2   	MU2B36      	5780412	CE  										RT MLG	FAILED          	B			TUPR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	09	500PJ					668				UPON LANDING, THE TIRE DISINTEGRATED.  ASSURE THE TIRE WAS FLAT ON LANDING, DUE TO RUNWAY FOD ON TAKEOFF.						1	H	7	2 	3T			RT	A10SW   					 
2003092200051	20030922	00051	SO  	2003	9	22	2003FA0000841    	2	20030803	G	8530		CYLINDER HEAD   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	SEPARATED       	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			NE	01	2618L					414A0284	244785R			CYLINDER HEAD SEPARATED FROM THE BARREL IN CRUISE FLIGHT.  LIMIT THE USE OF CHROMED CYLINDERS TO NON TURBOCHARGED ENGINE	S.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003092200083	20030922	00083	EA  	2003	9	22	2003FA0000843    	2	20030811	G	8520		CASE HALF       			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	4053W					3240075	L411948			DURING ENGINE ANNUAL INSPECTION, FOUND 3 EA CYLINDER MOUNT THROUGH BOLTS LEAKING.  SUSPECT FRETTING CORROSION BETWEEN CA	SE HALVES.  ENGINE REMOVED FOR REPAIR.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2003092200084	20030922	00084	SO  	2003	9	22	2003FA0000844    	1	20030811	G	5730		SKIN            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUSELAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	4053W	3396 				3240075				DURING ANNUAL INSPECTION, FOUND LEFT WING INBOARD FORWARD SKIN AT ROOT WITH SPIDER CRACKS IN 2 AREAS.  ALSO FOUND WALKWA	Y SURFACE MUSHY, SUSPECT INTERNAL DAMAGE.  SUSPECT CRACKS CAUSED BY OVERSTRESS OF WINGS DURING FLIGHT.  REPAIR- IN WORK.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003092200085	20030922	00085	SO  	2003	9	22	2003FA0000845    	1	20030811	G	5730		SKIN            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  					WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	4053W					3240075				DURING ANNUAL INSPECTION, FOUND 20 STRESS CRACKS ON TOP OF BOTH WINGS ALONG BOTH LONGITUDINAL STRINGERS AFT OF MAIN SPAR	.  CRACKS RANGE FROM .250 INCH TO .750 INCH IN LENGTH, AND PROPOGATE ENTIRE LENGTH OF WINGS.  SUSPECT CRACKS CAUSED BY O	VER-STRESS OF AIRCRAFT DURING FLIGHT.  REPAIR IS IN-WORK.				1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003092200087	20030922	00087	EU  	2003	9	22	2003FA0000846    	1	20030812	G	6210	L621M1010054	BLADE           			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	312MS	2304 				0129				CRACKS FOUND IN BOTH MAIN ROTOR BLADES IN THE AREA OF THE CONTROL CUFF/ FLEXBEAM VIEWED FROM THE INSPECTION AND DRAIN HO	LES.  FLEXING BLADES UP AND DOWN YOU CAN SEE THE CRACK OPEN AND CLOSE.  ALSO YOU CAN HEAR AN AUDIBLE CLICKING SOUND.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2003092200089	20030922	00089	SO  	2003	9	22	2003FA0000847    	1	20030814	G	5711		SPAR CAP        			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					RT WING	BLISTERED       	G			GH3T	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	9753J					283868				ON INSPECTION, LARGE BLISTER WAS OBSERVED ON RIGHT WING, OB OF WING TANK FROM WING STA 95 TO STA 108.  AREA OF BLISTER W	AS APPROX 10 INCHES X 15 INCHES X 3 INCHES.  SMALL BLISTER WAS ALSO OBSERVED IB OF FUEL TANK BETWEEN WING STA 55 TO 65. 	 RIVETS WERE DRILLED OUT OF WING PNL OB OF FUEL TANK,  PANEL WAS PULLED BACK.   FUEL TANK WAS REMOVED FROM RT WING.  ON 	INSP, SEVERE CORROSION, WHICH APPEARED TO BE INTERGRANULAR, WAS SEEN IN  TOP CAP OF WING SPAR BETWEEN WING STA 97 TO 108	.  AREA WAS APPR 10 INCHES IN LENGTH, COVERED ENTIRE WIDTH OF SPAR CAP.  SPAR ABOUT .045 MATERIAL REMAINING IN  SPAR CAP	 AREA.  LESS CORROSION FOUND BETWEEN WING STATIONS 50 TO 52, 57 TO 63 AND 76 TO 84.  (WP23200307722)	1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003092200091	20030922	00091	EA  	2003	9	22	2003FA0000848    	2	20030811	G	8520	LW11754	CAMSHAFT        			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	SPALLED         	B			PP4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	3534H		750  			221437				CAMSHAFT, FOUND EVIDENCE OF SEVERE SPALLING ON SEVERAL CAM LOBES.  ENGINE HAD APPROX 750 HOURS ON A FACTORY OVERHAUL.						1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2003091200097	20030912	00097	NM  	2003	9	12	2003FA0000849    	1	20030806	G	2820		FUEL LINE       			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	C7512F      	17005	SO  					NACELLE	WRONG PART      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	2149H	239  				2772				DURING AN ANNUAL INSPECTION THE FUEL HOSES THAT ARE ROUTED FROM THE RT SIDE OF FIREWALL TO FUEL PUMP HAD BEEN SEVERLY EX	POSED TO HEAT FROM RT EXHAUST STACK CAUSING ONE HOSE TO BUBBLE UP.  THESE HOSES DID NOT HAVE FIRE SLEEVE ON THEM.  THIS 	IS AN INFLIGHT FIRE HAZARD.				1	L	7	1 	3O	3	O	 	A718    	E233				 
2003092200113	20030922	00113	EU  	2003	9	22	2003FA0000850    	1	20030811	G	2710		BEARING         			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					LT AILERON	BULGED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	865AF	904  				85005	L2826448A			DURING SPECIAL INSPECTION OF THE AIRCRAFT REVEALED THAT THE BEARING ON THE LT AILERON LEVER ASSY IS SHOWING SIGNS OF BUL	GING .  PROBABLE CAUSE IS DESIGN OF LEVER ASSY.  THE AMOUNT OF USE OF THIS SYSTEM.  REDESIGN OR REPLACE BEARING OF A HIG	HER QUALITY.				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003092200115	20030922	00115	SO  	2003	9	22	2003FA0000851    	2	20030806	G	7320	6314272A13M	VALVE           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MANIFOLD	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5581T		77   			CE1350	820457R			FLIGHT CREW REPORTED THAT THE ENGINE WOULD NOT SHUT DOWN WHEN IDLE CUT OFF WAS SELECTED.  PROBABLE CAUSE IS INTERNAL FAI	LURE, DEBRIS, FAILED DIAPHRAGM.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003092200116	20030922	00116	SO  	2003	9	22	2003FA0000852    	1	20030701	G	5711	67070003	SPAR            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					WINGS	CRACKED         	B			BX4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	75153	6703 				28R7635271				DURING REPAIRS TO BOTH WINGS FOR DAMAGED RIBS AT WING STA B9.24.  FOUND THE RT MAIN SPAR CRACKED AT WEB TO LOWER SPAR CA	P JUNCTION UNDER THE MAIN GEAR TRUSS BRACKET(PN95642-5P).  THE HORIZONTAL CRACK IS APPROX 1.5 INCH LONG, ABOUT .25 INCH 	OF THE CRACK IS PAST THE OUTBOARD END OF THE TRUSS BRACKET.  THE LOWER MOUNT HOLES IN THE SPAR CAP FOR THE TRUSS BARACKE	T ARE SLIGHTLY ELONGATED.  TRUSS BRACKET IS UNDAMAGED WITH .6250 IN STUD, REF AD 97-01-01R1 39-10864, 10-22-98.			1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003092200117	20030922	00117	CE  	2003	9	22	2003FA0000853    	1	20030804	G	5553	04310093	ATTACH FITTING  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					VERTICAL STAB	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	27	5364H					15284093				ON ANNUAL INSPECTION FOUND LEFT VERTICAL FIN ATTACH POINT OUTBOARD EAR BROKEN OFF.  ALSO FOUND A STEEL TAPERED SHIM (.01	8 TO .065) UNDER THE RIGHT THREE OF THE FOUR AFT FIN ATTACH FITTING BOLTS.  TECH SUPPORT FOUND NO REF TO ANY SUCH PART. 	 REMOVED SHIM AND REPLACED FIN ATTACH FITTING WITH SERVICABLE USED.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003092200118	20030922	00118	CE  	2003	9	22	2003FA0000854    	1	20030722	G	2820		FUEL SYS        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					CELL	CONTAMINATED    	B			SNAR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	86BR					TH1072				AIRCRAFT HAS CONTAMINANT IN FUEL SYSTEM, A WHITE GEL/PASTE SUBSTANCE THAT IS CAPABLE OF PASSING THROUGH SCREENS AND CAN 	CLOG SMALL ORIFICES SUCH AS FLOW DIVIDER BORES.  RT ENGINE FAILED ON GROUND AS A RESULT OF FLOW DIVIDER BLOCKAGE, CONTAM	INANT IS IN ENTIRE FUEL SYSTEM.				1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2003092200119	20030922	00119	CE  	2003	9	22	2003FA0000855    	1	20030804	G	2510	504516403	INERTIA REEL    			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					REAR SEAT BELT	FAILED          	B			UIVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	24547					17280796				IT HAS BEEN FOUND THAT THE REAR SEAT BELT LOWER IN REELS WILL NOT PROPERLY RETRACT UNLESS THE BELTS ARE MANUALLLY INSERT	ED/FED INTO THE REEL ASSY.  ADDITIONALLY UNLESS THE BELTS ARE FULLY RETRACTED FIRST, THEY WILL NOT EXTEND.  50 PERCENT O	F THE TIME, FACTORY NEW PART EXIBIT SAME PROBLEM.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003092200120	20030922	00120	CE  	2003	9	22	2003FA0000856    	1	20030721	G	6120	1317651F	ROD END         			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550*      	 	SO  					PROP CONTROL	WORN            	B			AWKR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	536W	220  				E3458				AIRCRAFT WAS IN FOR ITS FIRST ANNUAL INSPECTION SINCE NEW.  FOUND FORWARD PROP CONTROL ROD END WORN BEYOND SERVICEABLE L	IMITS.  PART MAY HAVE MFG DEFECT.					1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2003091200052	20030912	00052	CE  	2003	9	12	2003FA0000857    	1	20030721	G	6120	1317651F	ROD END         			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520*    	17040	SO  	BEECH	278	278*        	CE  	PROP CONTROL	WORN            	B			AWKR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	36PV	236  				EA695				AIRCRAFT WAS IN FOR ITS FIRST ANNUAL INSPECTION SINCE NEW.  FOUND FORWARD PROP CONTROL ROD END WORN BEYOND SERVICEABLE L	IMITS.  PART MAY HAVE A MFG DEFECT.					1	L	7	1 	3O	3	O	 	3A15    	E8CE	5	C	P882	 
2003091200054	20030912	00054	SO  	2003	9	12	2003FA0000858    	1	20030107	G	3220	NAS464P427	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					NLG DRAG LINK	BROKEN          	B			KRTR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	09	2088K	5942 				447995175				UPON TOUCH DOWN OF THE NOSE GEAR DURING LANDING THE NOSE GEAR COLLAPSED RESULTING IN DAMAGE TO THE NOSE OF THE AIRCRAFT,	 BOTH ENGINES AND BOTH PROPELLERS.  AFTER EXAMINATION OF THE NOSE GEAR IT WAS NOTED THAT THE CENTER DRAG LINK BOLT WAS S	HEARED IN THE CENTER AND THE DOWN LOCK HOOK WAS BROKEN IN HALF.  NOSE LANDING GEAR DOWN LOCK BUSHING REPLACEMENT.				1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2003091200011	20030912	00011	CE  	2003	9	12	2003FA0000859    	1	20030815	G	2140	D83A28	HEATER          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					CABIN	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01						TC1541				HEATER COMBUSTION TUBE CRACKED SEVERELY IN MULTIPLE LOCATIONS WHICH LIKELY INDICATES THAT CRACKS HAVE EXISTED FOR SOME T	IME.BIG PROBLEM IS THAT THERE IS NO REQUIRED PRESSURE DECAY TEST FOR THESE HEATERS. PRESSURE DECAY TESTING SUCH AS REQUI	RED FOR OTHER HEATER MODELS IAW AD 96-20-07 IS PROBABLY MOST EFFICIENT METHOD OF DETERMINING CONDITION OF COMBUSTION TUB	E.			1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2003091200012	20030912	00012	GL  	2003	9	12	2003FA0000860    	1	20030813	G	7603	A155055	THROTTLE CABLE  			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE	BROKEN          	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NM	03	922AF	320  				C0179				THROTTLE CABLE BROKE IN FLIGHT AT FULL POWER.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2003091200017	20030912	00017	EA  	2003	9	12	2003FA0000861    	2	20030818	G	8550	LW14789	DIPSTICK        								LYC   	O360  	O360A1G     	41514	EA  					OIL SYSTEM	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	3724	2600 	426  				L948136A			OIL LEVEL INDICATOR (DIP STICK) ROD BECAME LOOSE IN HOUSING (THREADED CAP) THAT HOLDS ROD IN PLACE. THIS OCCURED WHERE R	OD FITS INTO SCREW-IN PART OF DIP STICK CAP.  THIS ALLOWED ROD TO MOVE IN AN ARC OVER 1INCH IN TRAVEL OVER A RANGE OF 36	0 DEGREES (AS MEASURED AT END OF ROD OPPOSITE SCREW-IN CAP) ALLOWING ROD TO RUB AND CHAFE WHERE ROD ENTERS ENGINE CRANKC	ASE. WHEN MEASURED ROD HAD CHAFED DOWN .030 INCH.  MAIN CONCERN WOULD BE THAT ROD WOULD BREAK AT CHAFE POINT OR ROLL PIN	 WOULD WEAR AND ALLOW ROD TO FALL INTO ENGINE CASE.  UPON CHECKING OIL FILTER AND OIL SUCTION SCREEN, NO LARGE AMOUNTS O	F METAL WERE FOUND. DIP STICK LW-14789 WAS REPLACED ALONG WITH ENGINE OIL AND FILTER TO CORRECT THIS CONDITION.						3	O			E286				 
2003091200018	20030912	00018	CE  	2003	9	12	2003FA0000862    	1	20030821	G	5730	501201869	PANEL           			BEECH 	300   	B300C       	1152933	CE  										WING	DEPARTED        	B				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	07						VARIOUS				WING BOLT PANEL DEPARTED AIRCRAFT WHILE IN FLIGHT. THIS IS THE THIRD OCCURANCE ON THREE DIFFERENT AC IN APPROXIMATELY ON	E MONTH. INSPECTION REVEALED THE THE SPRING TAB HAD FAILED. RECOMMEND CLOSE INSPECTION OF THIS PANEL AT EACH PHASE INSPE	CTION.				2	L	7	2 	4T			RT	A24CE   					 
2003092300005	20030923	00005	SO  	2003	9	23	2003FA0000863    	1	20030812	G	2752	HSBG7S4	BEARING         			LKHEED	1329  	132925      	5263125	SO  	GARRTT	TFE731	TFE731*     	01518	WP  					FLAP ACTUATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	01	701JH	8343 				5230				DURING NORMAL FLAP ACTUATOR INSPECTION, FLAP SUPPORTS AT FLAP STA 19.405 WERE FOUND TO NOT ACCEPT GREASE TO THE BEARINGS	 FOR THE FLAP SUPPORT HINGE, CLOSER INSPECTION ALSO REVEALED THAT THE BEARING BALL HAD CRACKED ACROSS THE LUBRICATION HO	LE.  TWO BEARINGS WERE FOUND IN THIS CONDITION.  BEARINGS WERE REMOVED, LUBE PASSAGE CLEARED AND NEW BEARINGS WERE INSTA	LLED.			2	L	7	4 	4F	4	F	 	2A1SO   	E6WE				 
2003092200001	20030922	00001	EU  	2003	9	22	2003FA0000864    	1	20030819	G	3411		STATIC LINE     			PILATS	PC12  	PC1245      	7090551	EU  										COCKPIT	SEPARATED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	487PC					487				AT CRUISE ALTITUDE, STATIC SYSTEM LINE UNDER CABIN FLOOR BETWEEN FRAMES 32 AND 33 SEPARATED, INTRODUCING PRESSURIZED CAB	IN AIR INTO THE STATIC SYSTEM, DAMAGING PILOT AIRSPEED INDICATOR AND PILOT VERTICAL SPEED INDICATOR.  THE STATIC LINE IN	VOLVED PULLED OUT OF A TEE FITTING IN THE SYSTEM.  SUSPECTED CAUSE IS THAT THE STATIC SYSTEM LINES ARE BEING CUT TOO SHO	RT AT THE AIRCRAFT FACTORY, CAUSING UNDUE STRESS WHEN AIRCRAFT IS SUBJECTED TO PRESSURIZATION.  THIS DEFECT HAS BEEN NOT	ED ON ANOTHER AIRCRAFT OF SAME TYPE AT THIS REPAIR STATION.		1	L	7	1 	3T			RT	A78EU   					 
2003091900077	20030919	00077	SO  	2003	9	19	2003FA0000865    	1	20030813	G	7160	86245034	AIR BOX         			PIPER 	PA44  	PA44180     	7104402	SO  										ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	572ER	349  				4496148				ENGINE AIRBOX CRACKED IN THE FLANGE AREA WHERE THE CARB HEAT CABLE ATTACH BRACKET IS ATTACHED TO THE AIRBOX ASSEMBLY WIT	H TWO RIVETS.  THIS IS A CONSTANTLY CRACKING AREA ON THE AIRBOX.  MFG IS WELL AWARE OF THE PROBLEM AND HAS BROUGHT OUT A	N (IMPROVED) ASSEMBLY P/N 86245-836 WHICH IS SUPPOSED TO SOLVE THE PROBLEM.				1	L	7	2 	3O			 	A19S0   					 
2003092200002	20030922	00002	EU  	2003	9	22	2003FA0000866    	1	20030819	G	3411		STATIC LINE     			PILATS	PC12  	PC1245      	7090551	EU  										COCKPIT	SEPARATED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	487PC					487				AT CRUISE ALTITUDE, STATIC SYSTEM LINE UNDER CABIN FLOOR BETWEEN FRAMES 32 AND 33 SEPARATED, INTRODUCING PRESSURIZED CAB	IN AIR INTO THE STATIC SYSTEM, DAMAGING PILOT AIRSPEED INDICATOR AND PILOT VERTICAL SPEED INDICATOR.  THE STATIC LINE IN	VOLVED PULLED OUT OF A TEE FITTING IN THE SYSTEM.  SUSPECTED CAUSE IS THAT THE STATIC SYSTEM LINES ARE BEING CUT TOO SHO	RT AT THE AIRCRAFT FACTORY, CAUSING UNDUE STRESS WHEN AIRCRAFT IS SUBJECTED TO PRESSURIZATION.  THIS DEFECT HAS BEEN NOT	ED ON ANOTHER AIRCRAFT OF SAME TYPE AT THIS REPAIR STATION.		1	L	7	1 	3T			RT	A78EU   					 
2003092400079	20030924	00079	GL  	2003	9	24	2003FA0000867    	1	20030826	G	5346		ATTACH BOLT     			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					FIREWALL	IMPROPER PART   	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13	940CD					0259				FOUND LOWER ENGINE MOUNT TO FIREWALL BOLTS LOOSE. BOTH LOWER BOLTS WERE TO LONG AND GRIP LENGTH TO LONG.  REPLACED BOTH 	BOLTS WITH PROPER SIZE AND TORQUED TO SPECS.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2003091200045	20030912	00045	EU  	2003	9	12	2003FA0000868    	1	20030730	G	6720	AC66375	HOUSING         			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR SERVO	CRACKED         	B			QH5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	1430									TAIL ROTOR SERVO BODY, CRACKED IN LOWER FLANGE AREA.						1	G	7	1 	3U			NC	H9EU    					 
2003091200093	20030912	00093		2003	9	12	2003FA0000869    	4	20030730	G	2210	AC66375	HOUSING         			GULSTM	GV    	GULFSTREAMGV	3980116	SO  										SERVO	CRACKED         	B			QH5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	1540					580				SERVO BODY, CRACK IN LOWER FLANGE AREA.						2	L	7	2 	4F			RT	A12EA   					 
2003091200096	20030912	00096	CE  	2003	9	12	2003FA0000870    	1	20030611	G	3246	0723120	TIRE            			CESSNA	150   	152         	2071835	CE  										NLG	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	94778	258  				15285785				PILOT NOTICED A LARGE BUMP ON SIDEWALL OF TIRE.  UPON INVESTIGATION THE TUBE WAS FOUND TO BE IN GOOD CONDITION BUT TIRE 	SIDEWALL WAS VERY SOFT, ALLOWING THE TUBE TO PUSH OUTWARD.  NO OTHER DEFECTS WERE EVIDENT AND TIRE NEVER LOST AIR PRESSU	RE.  NO HARD LANDINGS WERE REPORTED.  TIRE REMOVED FROM SERVICE.				1	H	7	1 	3O			NT	3A19    					 
2003091500013	20030915	00013	EU  	2003	9	15	2003FA0000872    	1	20030814	G	5540	LN90898E4	BEARING         			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					RUDDER HINGE	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF	1073 				85002	L2802448A			DURING PRE-FLIGHT INSPECTION, FLIGHT CREW REPORTED A NOISE FROM THE RUDDER.  INSPECTION OF THE RUDDER SYSTEM REVEALED A 	FAILED BEARING IN THE BEARING SUPPORT OF THE LOWER RUDDER HINGE.  THE OUTER CASE OF THE BEARING HAD TWO PIECES BROKEN OF	F AND MISSING.  BEARING WAS RETURNED TO MANUFACTURER FOR INVESTIGATION.  RECOMMEND REPLACEMENT OF BEARINGS WITH BETTER Q	UALITY BEARINGS.			1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003092600007	20030926	00007	GL  	2003	9	26	2003FA0000873    	2	20030802	G	7532	23053176	BLEED VALVE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	INOPERATIVE     	B			EOOR	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			AL	03	511SB	710  				1090592D	CAE834299			HIGH TOT - BLEED VALVE POPPET BUSHING SLOPPY IN THE HOUSING.  REPLACED UNIT.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003092600014	20030926	00014	WP  	2003	9	26	2003FA0000874    	1	20030726	G	3246	36902900069	SKID            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C*       	 	GL  					MLG	CORRODED        	B			EOOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	511SB					1090592D				FOUND EXTENSIVE CORROSION AND LOOSE HARDWARE ON SKID TUBE ASSEMBLIES.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003091200014	20030912	00014		2003	9	12	2003FA0000875    	4	20030818	G	2561	KSD35PO723107	LIFE VEST       																	EMERGENCY EQUIP	FAILED          	B			KQ1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										LIFE VEST FAILED.  MFG RECOMMENDED CELL PRESSURE TEST.  DOM: JULY 1987																			 
2003092600016	20030926	00016		2003	9	26	2003FA0000876    	4	20030825	G	2300	GMA340	AUDIO PANEL     			AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	O360*       	41514	EA  					COCKPIT	MISWIRED        	B			HI1R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NE	05	934TE					10213				UPON HAVING AN AUDIO PANEL PARTIAL FAILURE, THE PILOT NOTED THAT THE EMERGENCY MODE DID NOT OPERATE.  THE UNIT HAD MODE 	4 INSTALLED.  IN TROUBLESHOOTING, IT WAS DETERMNED THAT THE MONO HEADSET JACKS WERE WIRED TO THE RIGHT STEREO OUTPUT INS	TEAD OF THE LEFT AS SHOWN IN THE GM4340 INSTALL MANUAL.				1	L	7	1 	3O	3	O	NT	1L71    	E286				 
2003092600019	20030926	00019	SW  	2003	9	26	2003FA0000878    	1	20030819	G	7910	206061505115	OIL TANK        			BELL  	407   	407         	1182206	SW  											CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07						53275				TANK CRACKED IN BODY NEAR VENT, ALSO APPEARS TO BE CRACKED IN APPROX OF FORMED NECK BELLOW WELD.						1	G	7	1 	3U			O	H2SW    					 
2003091000077	20030910	00077	SO  	2003	9	10	2003FA0000879    	1	20030821	G	2197	475213	WIRE            			PIPER 	PA31  	PA31350     	7103110	SO  										BLOWER MOTOR	BURNED OUT      	E				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CE	03	33JR	5694 				318052097				DURING CRUISE FLIGHT, ODOR OF SMOKE WAS NOTED COMING FROM FORWARD COMPARTMENT.  DIVERTED TO NEAREST LANDING LOCATION. LA	NDED WITHOUT INCIDENT. IT WAS NOTED THAT THE AIR CONDITIONING VENT BLOWER CB WAS TRIPPED. NO FURTHER SMELL OR SMOKE WAS 	NOTED, LANDING WAS STILL EXECUTED. UPON INSPECTION, IT WAS NOTED THAT THE RT VENT BLOWER MOTOR WIRING WAS DAMAGED AT POI	NT WHERE WIRES GO THROUGH TO THE INTERNAL MOTOR. THERE WAS NO GROMMET OR PROTECTIVE COVERING OVER WIRING TO PREVENT IT F	ROM CHAFING TO BRONZE BUSHING SURROUNDING IT. SHORT CIRCUIT TO GROUND TRIPPED BREAKER AND ISOLATED THE FAULT.  REPLACEME	NT MOTOR PN 475-213 IS IMPROVED TO HAVE A NON METALLIC GROMMET SURROUNDING WIRING THAT GOES THROUGH TO MOTOR.	1	L	7	2 	3O			 	A20SO   					 
2003091000078	20030910	00078	WP  	2003	9	10	2003FA0000881    	2	20030826	G	7320	211800260	EEC             			AMD   	FALC20	FALCONF     	2720306	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					NR 2 ENGINE	DEFECTIVE       	C				D				RETURN TO BLOCK         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			NM	09	312K	4890 				324	103149			DURING TAXI, NR 2 ENG EXPERIENCED AN UN-COMMANDED ENG SHUTDOWN. CREW OBSERVED THE ENG COMPUTER 2 CB (201E2) HAD TRIPPED.	 POWER LEVER WAS PUT IN CUT-OFF, A/C RETURNED TO RAMP. INSP OF NR 2 ENG INTAKE AND EXHAUST AREAS WAS NORMAL.  MAINT TROU	BLESHOOTING REVEALED NR 2 DIGITAL ELECTRONIC ENGINE CONTROL (DEEC) TO BE DEFECTIVE. CB COULD NOT BE RESET; IN ADDITION T	HE DEFECTIVE DEEC CAUSED EMERGENCY BATTERY (93E2) CIRCUIT BREAKER TO OPEN. THE DEFECTIVE PART WAS REPLACED WITH A SERVIC	EABLE UNIT, CIRCUIT BREAKERS WERE RESET AND DEEC WAS ADJUSTED / TESTED IAW MFG SPECIFICATIONS AND AC WAS RETURNED TO SER	VICE.  ABOVE MALFUNCTION SHOULD HAVE CAUSED ENG TO TRANSFER TO MANUAL MODE AND NOT CAUSED AN ENGINE SHUTDOWN.	2	L	7	2 	4F	4	F	 	A7EU    	E6WE				 
2003091200023	20030912	00023	CE  	2003	9	12	2003FA0000882    	1	20030519	G	5797		WIRE            			CESSNA	500   	560CESSNA   	2076750	CE  										RT TE FLAP	WORN            	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	49NS					5600116				NAV LIGHT CIRCUIT BREAKER POPPED.  TROUBLESHOT, FOUND WIRES IN RIGHT FLAP AREA HAD WORN THROUGH PROTECTIVE SLEEVE AND WI	RE INSULATION.  FOUND BARE SPOTS ON OTHER WIRES IN SAME AREA.  RECOMMEND THAT THESE AREA BE INSPECTED CLOSELY FOR INSULA	TION SLEEVE BEING WORN THROUGH.				2	L	7	2 	4F			RT	A22CE   					 
2003091000070	20030910	00070	CE  	2003	9	10	2003FA0000883    	1	20030905	G	5410	6621280103	PANEL           			CESSNA	560   	560XL       	2076702	CE  										HEATSHIELD	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	676QS	2044 				5605176				DURING INSPECTION FOUND RT WING, INBOARD LEADING EDGE BLEED AIR TUBE HEATSHIELD PANEL LOWER MOUNT FLANGE CRACKED APPROXI	MATELY HALF WAY LENGTHWISE.  THIS IS THE THIRD C-560XL THAT WE HAVE FOUND THIS CONDITION ON.  REPLACED THE PANEL WITH NE	W.				2	L	7	2 	4F			RT	A22CE   					 
2003091200021	20030912	00021	CE  	2003	9	12	2003FA0000884    	1	20030903	G	5540		BUSHING         			BBAVIA	8     	8KCAB       	2110612	CE  										RUDDER	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	330MS	838  				75095				RIGHT FORWARD RUDDER ATTACH BUSHING COTTER PIN HEAD WORN OFF BY CYCLIC CONTACT WITH FLOORBOARD. PIVOT BUSHING WAS FOUND 	MORE THAN HALF WAY OUT OF RUDDER ATTACH POINT.					1	H	7	1 	3O			 	A21CE   					 
2003091200032	20030912	00032	SW  	2003	9	12	2003FA0000885    	1	20030903	G	5411		CLAMP           			FRCHLD	SA227 	SA227CC     	3377522	SW  										ENGINE TRUSS	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05										ON AIRCRAFT ENGINE TRUSS ADEL CLAMPS FROM 3 O'CLOCK POSITION TO 9 O'CLOCK ARE SEVERLY BRITTLE AND ARE BREAKING, AND CORR	ODING THE ASSEMBLY DUE TO THE HIGH HEAT BEING GENERATED FROM THE ENGINE.					2	L	7	2 	4T			RT	A18SW   					 
2003091200019	20030912	00019	NE  	2003	9	12	2003FA0000887    	2	20030908	G	7320	109063064103	ATTACH FITTING  			AGUSTA	A109  	A109E       	0260119	EU  	PWA   	PW206 	PW206B      	0	NE  					FUEL CONTROL	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	6VZ	796  	150  			11099				ENGINE FUEL CONTROL LINKAGE ATTACHING NUT HAS BACKED OUT. THIS HAS ACCURED FIVE TIMES IN THE PAST,  ON DIFFERENT AIRFRAM	ES OPERATED. THE RESULT OF THE NUT BACKING OFF THE FUEL CONTROL ACTUATING SHAFT CAUSED A LOSS OF MANUAL CONTROL VIA THE 	POWER LEVER IN COCKPIT. THE A109E POWER CONTROL SYSTEM IS ONE OF A REDUNDENT NATURE , SO NO LOSS OF POWER WAS EXPERIENCE	D IN FLIGHT.  THESE AIRCRAFT ARE NOT OPERATED IN CIVILIAN CATAGORY, AND THIS DISCREPENCY IS OF AN ISOLATED NATURE, WHICH	 HAS BEEN CORRECTED USING UPDATED INSPECTION METHODS LOCALLY.		1	G	7	2 	3U	3	U	RT	H7EU    	E42NE				 
2003091500017	20030915	00017	CE  	2003	9	15	2003FA0000888    	1	20030908	G	2710	626010625	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT AILERON	BROKEN          	B			PAZR	O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CE	03	651EJ	4708 	59   			6500241				RT AILERON OUTBOARD FORWARD CABLE WAS FOUND BROKEN AT OUTBOARD PULLEY LOCATION. PILOT NOTICED AIRCRAFT ROLLING TO RIGHT.	 LOOKED OUT WINDOW AND FOUND RT AILERON DEFLECTED UP APPROXIMATELY 2 INCHES FROM NEUTRAL POSITION. AIRCRAFT LANDED WITHO	UT INCIDENT. UPON VISUAL INSPECTION ON GROUND BY MECHANIC, FOUND RT AILERON CABLE BROKEN. INSPECTED PULLEYS AND SURROUND	ING STRUCTURE AND FOUND SATISFACTORY. CABLE WAS REPLACED WITH A NEW CABLE AND RIGGED IAW MAINTENANCE MANUAL.			2	L	7	2 	4F			 	A9NM    					 
2003092900004	20030929	00004	EA  	2003	9	29	2003FA0000890    	2	20030521	G	8500		ENGINE          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  						MAKING METAL    	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	244HP	556  				0427	L2516940A			DURING SCHEDULED INSPECTION FOR PART 135 OPERATOR, FOUND OIL FILTER CONTAMINATED WITH METAL PARTICLES. METAL WAS IDENTIF	IED AS PROBABLE FROM CAMSHAFT. ENGINE REMOVED AND SENT TO MFG FOR REPAIR. MFG FOUND CAMSHAFT AND LIFTERS FAILED. ENGINE 	REPAIRED BY MFG AND RETURNED.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003093000050	20030930	00050	SW  	2003	9	30	2003FA0000892    	1	20030806	G	3233		NUT             			MOONEY	M20   	M20G        	5870316	SW  	LYC   	O360  	O360*       	41514	EA  					ACTUATOR	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	3680N					680034				FAILURE TO SECURE JAM NUT ALLOWED ACTUATOR TO UNTHREAD FROM ROD END BEARING.  THIS CAUSED OUT OF RIG CONDITION OF LANDIN	G GEAR AND INABILITY TO EXTEND GEAR TO DOWN AND LOCKED POSITION VIA NORMAL OR EMERGENCY.					1	L	7	1 	3O	3	O	 	2A3     	E286				 
2003091200136	20030912	00136	GL  	2003	9	12	2003FA0000893    	3	20030811	G	6140	26060141RX	INDICATOR       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A45      	52043	EA  	MCAULY	3AF34C	3GFR34C703  	GL  	PROP TACH	MALFUNCTIONED   	B			RF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	64BP	7226 				208B0604				PROPELLER RPM GAUGE INDICATED 300 RPM OVER REDLINE DURING FLIGHT.  PILOT PERFORMED PRECAUTIONARY LANDING AT FIELD OTHER 	THAN PLANNED.  FURTHER INVESTIGATION OF ENGINE AND SYSTEM: NOR TORQUE FLUCTUATUON, NO ITT FLUCTUATION, NO N FLUCTUATION,	 INDICATOR FAILURE ONLY.  REPLACED INDICATOR.  OPS CHECKED GOOD.				1	H	7	1 	3T	4	T	 	A37CE   	E4EA	5	C	P60GL	 
2003093000053	20030930	00053	CE  	2003	9	30	2003FA0000894    	1	20030721	G	3230	AN51588	SCREW           			BEECH 	55    	9555        	1152702	CE  	CONT  	O470  	IO470*      	17026	SO  					MLG BRACE ASSY	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	517DC	6350 				TC1029				SCREW BROKEN, ALLOWING TRUNNION PIN TO BACK OUT.  RETRACT BRACE BECAME LOOSE ALLOWING DOWN AND LOCK TO (UNLATCH).  WHEN 	THAT HAPPENED THE RT MAIN GEAR COLLAPSED (ON ROLL OUT) AND DAMAGED THE RIGHT FLAT, WING TIP, AND BRAKE ASSEMBLY.  PROPEL	LER STRUCK THE GROUND AS WELL.  (GK15200314901)				1	L	7	2 	3O	3	O	 	3A16    	E1CE				 
2003093000054	20030930	00054	CE  	2003	9	30	2003FA0000895    	1	20030714	G	2701	0513167200	CONTROL WHEEL   			CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470*      	17026	SO  					COCKPIT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	9794X					21058094	05131682			CONTROL WHEEL BROKE ON LT TOP .7500 INCH FROM CORNER ON LIFT OFF VX ON PILOTS SIDE.  THIS IS THE OLD SQUARE CONTOL WHEEL	 AND IS ORIGINAL PART, 40 YEARS OLD.  BROKEN CONTROL WHEEL SHATTERED, PUSH TO TALK SWITCH FASTENED TO CONTROL AT SAME LO	CATION.  CONTROL WHEEL IS WHITE PLASTIC WITH BLACK PLASTIC COATING OVER ALL SURFACES.				1	H	7	1 	3O	3	O	 	3A21    	E1CE				 
2003093000055	20030930	00055	NM  	2003	9	30	2003FA0000896    	1	20030809	G	5720	13034	BRACKET         			UNIVAR	415   	415C        	0420302	NM  	CONT  	C85   	C8512       	17008	SO  	MCAULY	1A90	1A90CF      	GL  	LT WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	87055	3970 				228	208512	8374		REMOVED AND REPLACED (2) ANGLE BRACKETS IN LT WING WALKWAY THAT WERE ATTACHED TO THE RIB.  THESE WERE FOUND CORRODED DUR	ING THE INSTALLATION OF INSPECTION PANELS BEING INSTALLED TO COMPLY WITH AD 02-26-02.  IT APPEARED WATER HAD BECOME TRAP	PED INSIDE TRAILING EDGE OF WALKBOX AND CORROSION HAD SET IN.  THE RIB WAS NOT AFFECTED.  AIRCRAFT NEEDS SMALL DRAIN HOL	E IN THIS AREA FOR DRAINAGE.			1	L	7	1 	3O	3	O	 	A718    	E233	5	N	P842	 
2003093000062	20030930	00062	SW  	2003	9	30	2003FA0000897    	1	20030702	G	3230	143331853	BRACE           			TMPSON	NAVION	NAVIONG     	6150120	SW  	CONT  	O470  	IO470*      	17026	SO  					MLG	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	2418T	2671 				NAV42418				BRACE WAS FOUND TO HAVE TWO CRACKED OUT WELD JUST BELOW UPPER WRIST.  THE FIRST CRACK PROCEEDED 150 DEGREES AROUND THE W	ELD AND THE SECOND 150 DEGREES ON THE OPPOSITE SIDE.  THE TWO CRACKS DO NOT MERGE.  THE CRACKS WERE FOUND DURING ANNUAL 	INSPECTION WITH THE NAKED EYE, A DYE PENTRATE INSPECTION CONFIRMED THE INITIAL FINDING.  UNIT WAS REMOVED FROM SERVICE.				1	L	7	1 	3O	3	O	 	A782    	E1CE				 
2003093000064	20030930	00064	CE  	2003	9	30	2003FA0000898    	1	20030828	G	2910	551701055	LINE            			CESSNA	501   	501         	2076603	CE  										HYD SYSTEM	CORRODED        	B			X6UR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	15	53BB	6650 				5010146				DURING GEAR RETRACTION AND GEAR EXTENSION, HYDRAULIC FLUID LEAKED UNDER PRESSURE.  FOUND THIS LINE CORRODED SO BADLY THA	T A HOLE HAD BEEN FORMED IN THE LINE.  THE CORROSION WAS DUE TO PREVIOUS ROUTING OF AIR CONDITIONING DUCT TY-WRAPPED TO 	THE FOUR LANDING GEAR HYDRAULIC LINES.  CONDENSATION INSIDE THE DUCT AND THE DUCT WIRE SPIRAL OF THE DUCT MAKING CONTACT	 WITH THE HYDRAULIC LINES CREATED THIS SEVERE CORROSION AND HYDRAULIC LINE FAILURE.  ALL FOUR (4) LANDING GEAR HYDRAULIC	 LINES WERE REPLACED DUE TO CORROSION.  THIS IS AN INSTALLATION PROBLEM WITH THE FREON AIR CONDITIONING SYSTEM.		1	L	7	2 	4F			 	A27CE   					 
2003093000065	20030930	00065	CE  	2003	9	30	2003FA0000899    	1	20030707	G	2820	631293	ELBOW           			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					LT ENGINE	BROKEN          	C			DYVS	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			NM	07	2655B	271  				421C0698	277163R			AT CRUISE, PILOT NOTICED A BLUE FUEL STAIN STREAMING BACK FROM THE LEFT ENGINE COOLING LOUVRES.  FOUND BROKEN 90 DEGREE 	ELBOW FITTING ON FUEL MANIFOLD VALVE INLET WAS BROKEN DUE TO VIBRATION OF ENGINE.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2003093000066	20030930	00066	GL  	2003	9	30	2003FA0000900    	3	20030812	G	6114	C514C	HUB             													MCAULY	3AF32C	3AF32C*     	GL  	PROPELLER	CRACKED         	B			F3PR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15		1400 			891104			891104		CRACK FOUND WITH ZYGLO INSPECTION DURING PROP OVERHAUL.																5	C	P22EA	 
2003093000067	20030930	00067		2003	9	30	2003FA0000901    	4	20030818	G	2562	E01	ELT             			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					CABIN	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6373C					327840081				DURING AN ACCIDENT INVESTIGATION THAT DESTROYED THIS AIRCRAFT.  IT WAS NOTED THAT THE ELT DID NOT ACTIVATE THE ELT WAS F	OUND IN THE ARMED SWITCH POSITION.  THIS AIRCRAFT HIT SEVERAL TREES AND IMPACTED THE GROUND VERY HARD.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2003093000070	20030930	00070	CE  	2003	9	30	2003FA0000902    	1	20030711	G	7820	C1560200101	MUFFLER         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ENGINE EXHAUST	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	9515B	1185 				172RG0846	L2769436A	851376		WHILE INSPECTING MUFFLER AND SHROUD IAW AD 83-14-04, A CRACK WAS FOUND AROUND A WELD ON THE AFT END OF THE CAN.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003093000073	20030930	00073	EU  	2003	9	30	2003FA0000903    	1	20030814	G	6510	N651G10V1021	BEARING         			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6*        	52043	EA  					T/R DRIVE	DISLODGED       	D			EH1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	172P	41   				14027				DURING INSPECTION TAIL ROTOR DRIVE SHAFT BEARING WAS FOUND WITH SEAL AND RETAINING RING DISLODGED FROM BEARING.  THIS BE	ARING IS CHECKED BY FLIGHT CREW.  THIS IS THE SECOND BEARING REPLACED IN 72.1 HOURS.					1	G	7	2 	3U	3	T	 	H7EU    	E2NE				 
2003093000074	20030930	00074	WP  	2003	9	30	2003FA0000904    	1	20030808	G	2560	C6284	BUCKLE          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540*       	41532	EA  					PAX SEAT BELT	CRACKED         	B			QC0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	7085U	1695 				0607				THE LT REAR PASSENGER SEAT BELT BUCKLE ASSY WAS INSPECTED DURING A 100 HOUR INSPECTION AND WAS FOUND TO BE CRACKED.  THE	 CRACK HAD DEVELOPED IN THE STAINLESS STEEL STRAP AT THE BUCKLE TO STRAP RIVIT ATTACH POINTS.  THIS STRAP IS FORMED IN A	 HORSESHOE SHAPE AROUND THE BUCKLE WITH TWO RIVETS ATTACHED TO ONLY ONE SIDE OF THE STRAP.  THIS ALLOWS MORE FLEXING OF 	THE BUCKLE DURING NORMAL OPERATION AND SUBSEQUENT CRACKING OF THE STRAP.  THIS AREA IS HIDDEN BY A PLASTIC COVER AND MUS	T BE INSPECTED CLOSELY, AS THIS  IS NOT THE FIRST BUCKLE OF THIS TYPE TO HAVE BEEN FOUND CRACKED.		1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003092600098	20030926	00098	CE  	2003	9	26	2003FA0000905    	1	20030902	G	5210	66113598	PUSHROD         			CESSNA	560   	560XL       	2076702	CE  										PAX DOOR	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07					5227	5605227				DURING A ROUTINE INSPECTION OF THE MAIN ENTRY DOOR, IT WAS DISCOVERED THAT THE DOOR OPENING / CLOSING PUSHROD WAS RUBBIN	G AGAINST THE CUT OUT IN THE DOOR STRUCTURE.					2	L	7	2 	4F			RT	A22CE   					 
2003091200010	20030912	00010	EU  	2003	9	12	2003FA0000908    	1	20030910	G	2810		FUEL TANK       			ISRAEL	1125  	ASTRASPX    	4500205	EU  										CENTER	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	09	302TS	1394 				108				FUEL LEAKING INTO THE AIRCRAFT CABIN FROM THE AIRCRAFT CENTER TANK DUE TO IMPROPER INTERNAL AND EXTERNAL SEALING AT MANU	FACTURE.  THE FUEL TANK FASTENERS APPEAR TO HAVE BEEN INSTALLED WITHOUT ADEQUATE SEALING.  RECOMMEND ACO NOTIFICATION AS	 THIS HAS BEEN AN HISTORICAL PROBLEM WITH THE ASTRA SPX.  CONDITIONS SUGGEST THAT THE SEALANT MATERIAL IS EFFECTIVE, HOW	EVER, THERE APPEARS TO BE A PROBLEM IN THE APPLICATION OF THE SEALANT AND QUALITY CONTROL.  THE FUEL TANK SEALANT WAS RE	MOVED, THE AREA CLEANED, AND RESEALED.		2	L	7	2 	4F			RT	A16NM   					 
2003091200013	20030912	00013	CE  	2003	9	12	2003FA0000909    	1	20030911	G	3246	8A080002074	CONTROL CABLE   	WIPLINEINC  		CESSNA	208   	208         	2073702	CE  										WATER RUDDER	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	912DS	104  				20800361				DURING A SCHEDULED INSPECTION FOUND THE LEFT WATER RUDDER CABLE IN EMPENNAGE WAS OFF ITS PULLEY AND CUTTING INTO THE PUL	LEY BRACKET.  THE PULLEY SAFETY PIN HAD BEEN INSTALLED IN THE BRACKETT WHILE THE CABLE WAS NOT ON THE PULLEY AT THE TIME	 OF THE FLOAT INSTALLATION.  REPLACED THE BAD BRACKET AND INSTALLED A NEW CABLE, THEN FOUND THAT THE RIGHT WATER RUDDER 	CABLE WAS MANUFACTURED TOO LONG TO COMPENSATE FOR THE INCORRECT ROUTING OF THE LEFT CABLE.  CUT THE RIGHT CABLE TO PROPE	R LENGTH AND INSTALLED A NEW CABLE END AND RIGGED WATER RUDDERS.  ALL WORK WAS PERFORMED IAW INSTRUCTION MANUALS AND DIS	CUSSIONS WITH MFG TECH SERVICE PEOPLE.	1	H	7	1 	3T			NT	A37CE   					 
2003091200035	20030912	00035	EA  	2003	9	12	2003FA0000910    	2	20030910	G	7261		SPRING          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3T*      	GL  	LT ENG OIL CAP	BACKED OUT      	B				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CL	CLIMB          	1			SW	01		20610	1348 			429	PCE40881			OIL CAP WAS NOT FULLY ENGAGED IN OIL TANK CAUSING LOSS OF APPROX 6 QUARTS OIL DURING CLIMB OUT. DISCOVERED OIL CAP UNLAT	CH ASSIST SPRING HAD DISENGAGED FROM HOLE IN CAP LATCH BAR. THIS ALLOWED OIL CAP LOCKING TAB TO LOCK WITHOUT OIL CAP FUL	LY ENGAGED IN OIL TANK. INSPECTED SIX ENGINES AND FOUND TWO CAPS WITH THIS SPRING AND FOUR WITH A SPRING DESIGN WHICH WA	S BENT OVER DURING MFG TO PREVENT DISENGAGEMENT. NO OIL CAP PN CHANGE OR SB FOUND FOR CHANGE. REPLACED BOTH OIL CAPS.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003100200068	20031002	00068	CE  	2003	10	2	2003FA0000911    	1	20030909	G	5711	052309608	SPAR            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	3517S	1075 				17281083	L2997251A	VB48036		DURING MAINTENANCE OF THE AIRCRAFT IN WHICH THE RIGHT FUEL TANK WAS OPENED UP, A CRACK WAS FOUND IN THE AFT SPAR.  THE C	RACK EXTENDS FROM WS 33.0 TO 34.375 AND IS APPROX 1.375 INCHES LONG.  THE CRACK IS LOCATED IN THE UPPER BEND RADIUS OF T	HE AFT SPAR.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003091200094	20030912	00094	EU  	2003	9	12	2003FA0000912    	1	20030814	G	2910	723552387	LINE            			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					LT BRAKE	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	809JC	11864				298				BRAKE LINE IS MADE FROM -4 ALUMINUM LINE.  CRACK STARTS .2500 INCH FROM FLARED END, AND RUNS APPROX. .3750 INCH LONG LEN	GTH OF LINE.  PROBABLE CAUSE IS FATIGUE OR LINE STRESSED, OR CORROSION.					2	M	7	2 	4F	4	F	 	A2SW    	E6WE				 
2003091500012	20030915	00012	EA  	2003	9	15	2003FA0000913    	2	20030801	G	8530	14187	EXHAUST VALVE   			STOLAM	RC3   	RC3         	3080203	NM  	FRNKLN	6A8215	6A8215*     	27030	EA  					NR 4 CYLINDER	MISSING         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	6201K					397	23433			DURING CRUISE ENGINE STARTED RUNNING.  ROUGH AND LOST POWER.  AIRCRAFT MADE EMERGENCY LANDING IN CORN FIELD.  FOUND EXHA	UST VALVE NR 4 ENGINE CYLINDER MISSING AND HOLE IN PISTON HEAD.  (.5 INCH X 2.5 INCH) HOLE.					1	H	7	1 	3O	3	O	RC	A769    	E242				 
2003100200167	20031002	00167	CE  	2003	10	2	2003FA0000914    	1	20030825	G	5320	5142003491	BRACE           			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					FUSELAGE	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	6631C					414A0038				CRACK LIKE INDICATION WHICH EXCEEDS 0.020 INCH IAW MEB 91.11 REV 1 (02/24/03)  CRACK LIKE INDICATION DETECT BY EDDY CURR	ENT INSPECTION.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003100200169	20031002	00169	GL  	2003	10	2	2003FA0000915    	3	20030825	G	6140	26060141RX	INDICATOR       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A45      	52043	EA  	HARTZL	H3B3M	HCB3M       	GL  	PROPELLER	FAILED          	B			RF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	64BP	7226 				208B0604				PROPELLER RPM INDICATED 300 RPM HIGH DURING FLIGHT.  PILOT PERFORMED PRECAUTIONARY LANDING.  NO OTHER PERIMETER FLUCTUAT	IONS.  REPLACED INDICATOR WITH NEW PART.  OPERATIONAL CHECK GOOD.					1	H	7	1 	3T	4	T	 	A37CE   	E4EA	5	C	P9NE	 
2003091500004	20030915	00004	NE  	2003	9	15	2003FA0000916    	2	20030818	G	7261	10585J	HEATER          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE OIL	CRACKED         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	01	706TA					BB1656	PCEPJ0276			TROUBLESHOT NR 2 ENGINE OIL LEAK.  FOUND A HAIRLINE CRACK NEAR UPPER INBOARD WELD OF PARTS MAIN BODY.  LOCATED JUST UNDE	R WELD AND APPROX .7500 INCH IN LENGTH.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003091500002	20030915	00002	EU  	2003	9	15	2003FA0000917    	1	20030806	G	2710	258CW2011A	CONTROL CABLE   			BRAERO	DH125 	BAE125800A  	1500285	EU  										AILERON	MISMANUFACTURED 	B			UO2R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	19	110MH					NA0425				NEW CABLE WAS .5 INCH TOO SHORT.						2	L	7	2 	4F			RT	A3EU    					 
2003091500005	20030915	00005	NE  	2003	9	15	2003FA0000918    	1	20030819	G	6320	MS8005J060E000	HOSE            			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT58*       	30011	GL  					M/R GEARBOX	CRACKED         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	13	265F					61492				AIRCRAFT WAS ENROUTE FOR REDEPLOYMENT OF FIREFIGHTING CREWS.  AIRCRAFT DEVELOPED A LARGE OIL LEAK AND MADE A PRECAUTIONA	RY LANDING.  AIRCRAFT SUSTAINED NO DAMAGE AND OCCUPANTS WERE NOT INJURED.  INVESTIGATION FOUND A MAIN TRANSMISSION OIL L	INE HAD RUPTURED AT THE POINT WHERE THE STEEL BRAIDED LINE IS SWAGED TO THE COUPLING.				2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2003091500006	20030915	00006	SO  	2003	9	15	2003FA0000919    	1	20030818	G	5753	1642400	HORN            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					LT FLAP	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	273AD	6154 				274806				DURING COMPLIANCE OF AD, THE FLAP TUBE WAS FOUND NOT TO PASS.   A NEW STEEL TUBE WS ORDERED AND IN THE REPLACEMENT PROCE	DURE THE LEFT BELLCRANK (PN 16424-00) WAS FOUND TO HAVE RUST INSIDE.  USING AN AWL TO PUSH ON THE RUSTED AREAS, IT COLLA	PSED THE WALLS.  WATER HAD COLLECTED IN THE AREA BETWEEN THE WALLS AND ROTTED THE STEEL.  NO DRAIN HOLES ARE LOCATED IN 	THAT AREA.  THE AD DOES NOT CALL FOR AN INSPECTION OF THIS PART.			1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2003091500008	20030915	00008	SO  	2003	9	15	2003FA0000920    	1	20030822	G	2497	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					OVERHEAD PANEL	BURNED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4181M					2843120	RL3909036A			DURING INSTALLATION RYAN TCAD 9900 BX SERIES WE FOUND PLUG P5 HAS SEVERAL PINS AND WIRE COATING BURNED AND MELTED.  PROB	ABLE CAUSE IS OVER CURRENT DRAW OF LANDING LIGHT AND NAV. LIGHT SYSTEM CAUSING HIGH RESISTANCE WHICH GENERATED ENOUGH HE	AT TO MELT THE PLUG AND WIRES.  RECOMMENDATION IS TO INSTALL HIGHER CAPACITY PINS TO CARRY THE LOAD OF THE CURRENT.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003100200177	20031002	00177	SO  	2003	10	2	2003FA0000921    	1	20030825	G	2497	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  										INSTRUMENT PANEL	BURNED          	B			VJ3R	O				OTHER                   				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			WP	07	4133K	4029 				2843205				DURING INSTALLATION OF RYAN TCAD 9900 BX SERIES WE FOUND PLUG P5 HAS SEVERAL PINS AND WIRE COATING BURNED AND MELTED.  P	ROBABLE CAUSE IS OVER CURRENT DRAW OF LANDING LIGHT AND NAV. LIGHT SYSTEM CAUSING HIGH RESISTANCE WHICH GENERATED ENGOUG	H HEAT TO MELT THE PLUG AND WIRES.  RECOMMENDATION IS TO INSTALL HIGHER CAPACITY PINS TO CARRY THE LOAD OF THE CURRENT.				1	L	7	1 	3O			 	2A13    					 
2003100200178	20031002	00178	SO  	2003	10	2	2003FA0000922    	1	20030825	G	2497	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  										INSTRUMENT PANEL	BURNED          	B			VJ3R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	07	4130W	4136 				2843204				DURING INSTALLATION OF RYAN TCAD 9900 BX SERIES.   WE FOUND PLUG P5 HAS SEVERAL PINS AND WIRE COATING BURNED AND MELTED.	  PROBABLE CAUSE IS OVER CURRENT DRAW OF LANDING LIGHT AND NAV LIGHT SYSTEM CAUSING HIGH RESISTANCE WHICH GENERATED ENOU	GH HEAT TO MELT THE PLUG AND WIRES.  RECOMMEND IS TO INSTALL HIGHER CAPACITY PINS TO CARRY THE LOAD OF THE CURRENT.				1	L	7	1 	3O			 	2A13    					 
2003091500009	20030915	00009	SO  	2003	9	15	2003FA0000923    	1	20030825	G	2497	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  										OVERHEAD PANEL	BURNED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4161Z	4145 				2843129				DURING INSTALLATION OF RYAN TCAD 9900 BX SERIES WE FOUND PLUG P5 HAS SEVERAL PINS AND WIRE COATING BURNED AND MELTED.  P	ROBABLE CAUSE IS OVER CURRENT DRAW OF LANDING LIGHT AND NAV. LIGHT SYSTEM CAUSING HIGH RESISTANCE WHICH GENERATED ENOUGH	 HEAT TO MELT THE PLUG AND WIRES.  RECOMMENDATION IS TO INSTALL HIGHT CAPACITY PINS TO CARRY THE LOAD OF THE CURRENT.				1	L	7	1 	3O			 	2A13    					 
2003091500003	20030915	00003	SO  	2003	9	15	2003FA0000924    	1	20030825	G	2497	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  										OVERHEAD PANEL	BURNED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4149Y	3990 				2843128				DURING INSTALLATION OF TCAD 9900 BX SERIES, FOUND PLUG P5 HAS SEVERAL PINS AND WIRE COATING BURNED AND MELTED.  PROBABLE	 CAUSE IS OVER CURRENT DRAW OF LANDING LIGHT AND NAV LIGHT SYSTEM CAUSING HIGH RESISTANCE WHICH GENERATED ENOUGH HEAT TO	 MELT THE PLUG AND WIRES.  RECOMMENDATION IS TO INSTALL HIGHER CAPACITY PINS TO CARRY THE LOAD OF THE CURRENT.				1	L	7	1 	3O			 	2A13    					 
2003091500023	20030915	00023	SO  	2003	9	15	2003FA0000925    	1	20030825	G	2497	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  										OVERHEAD PANEL	BURNED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4175V	4567 				2843126				DURING INSTALLATION OF RYAN TCAD 9900 BX SERIES,  FOUND PLUG P5 HAS SEVERAL PINS AND WIRE COATING BURNED AND MELTED.  PR	OBABLE CAUSE IS OVER CURRENT DRAW OF LANDING LIGHT AND NAV. LIGHT SYSTEM CAUSING HIGH RESISTANCE WHICH GENERATED ENOUGH 	HEAT TO MELT THE PLUG AND WIRES.   RECOMMENDATION IS TO INSTALL HIGHER CAPACITY PINS TO CARRY THE LOAD OF THE CURRENT.				1	L	7	1 	3O			 	2A13    					 
2003100200179	20031002	00179	SO  	2003	10	2	2003FA0000926    	1	20030826	G	2497	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  										COCKPIT	BURNED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9294Q	4440 				2843122				DURING INSTALLATION OF RYAN TCAD 9900 BX SERIES, FOUND PLUG P5 HAS SEVERAL PINS AND WIRE COATING BURNED AND MELTED.  PRO	BABLE CAUSE IS OVER CURRENT DRAW OF LANDING LIGHT AND NAV. LIGHT SYSTEM CAUSING HIGH RESISTANCE WHICH GENERATED ENOUGH H	EAT TO MELT THE PLUG AND WIRES.  RECOMMENDATION IS TO INSTALL HIGHER CAPACITY PINS TO CARRY THE LOAD OF THE CURRENT.				1	L	7	1 	3O			 	2A13    					 
2003091500007	20030915	00007	SO  	2003	9	15	2003FA0000928    	1	20030825	G	2497	3507201	CONNECTOR       			PIPER 	PA28  	PA28181     	7102807	SO  										OVERHEAD PANEL	BURNED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4122F	4919 				2843118				DURING INSTALLATION OF RYAN TCAD 9900 BX SERIES, WE FOUND PLUG P5 HAS SEVERAL PINS AND WIRE COATING BURNED AND MELTED.  	PROBABLE CAUSE IS OVER CURRENT DRAW OF LANDING LIGHT AND NAV. LIGHT SYSTEM CAUSING HIGH RESISTANCE WHICH GENERATED ENOUG	H HEAT TO MELT THE PLUG AND WIRES.  RECOMMENDATION IS TO INSTALL HIGHER CAPACITY PINS TO CARRY THE LOAD OF THE CURRENT.				1	L	7	1 	3O			 	2A13    					 
2003091500001	20030915	00001	SO  	2003	9	15	2003FA0000929    	2	20030913	G	7414	10885431	CAM             	BENDIX      	S6LN21      						CONT  	O300  	O300D       	17022	SO  					MAGNETO	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	4960R									DURING ANNUAL INSPECTION MAGNETO WAS REMOVED FOR 500 HR INSPECTION.  FOUND MAGNETO CAM PART NR 10-88543-1 TO BE CRACKED 	AND UNSERVICEABLE.  MAGNETO WAS FUNCTIONING NORMALY DURING ENGINE RUN UP PRIOR TO ANNUAL INSPECTION.  CRACK WAS NOT VISI	BLE UNTILL THE MAGNETO CASE WAS DISASSEMBLED.  MAGNETO HAD RECIEVED 1000 HOUR OVERHAUL APPROXIMATELY 480 HOURS PRIOR.									3	O			E253				 
2003091500022	20030915	00022	SO  	2003	9	15	2003FA0000931    	2	20030912	G	7421	URHB32E	SPARK PLUG      			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				E	D	R	VIBRATION/BUFFET          	INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      	AP	APPROACH       	1			EA	25	6827Z	151  				340A1222	509811			PILOT REPORTED ENGINE ROUGHNESS ON APPROACH AND LOSS OF RIGHT ENGINE NR 3 CYLINDER EGT INDICATION. AIRCRAFT LANDED WITH 	OUT INCIDENT. INSPECTION REVEALED NR 3 CYLINDER LOWER SPARK PLUG HAD SEPERATED INTO TWO PIECES BETWEEN THE GASKET SURFAC	E AND THE WRENCH HEX ALOWING THE CENTER ELECTRODE TO BE EJECTED FROM THE SPARK PLUG. THE COWLING SUFFERED MINOR FLAME DA	MAGE.			1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2003100600047	20031006	00047	CE  	2003	10	6	2003FA0000932    	1	20030902	G	2432	RG380E40B	BATTERY         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  					MASTER	WRONG PART      	B			E81R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	03	355TW	290  				BB521				NOTED SEALED LEAD-ACID BATTERY INSTALLED IN AIRCRAFT DURING A SCHEDULED PHASE CHECK.  ONLY DOCUMENTATION IN AIRCRAFT REC	ORDS SHOWED THAT G6381E UNSEALED TYPE LEAD ACID BATTERY SHOULD BE INSTALLED IAW STC SA1016SO.  PREVIOUS OPERATOR HAD (SW	APPED OUT) BATTERIES AT SOME POINT AND SUBSEQUENT MAINTENANCE CENTERS HAD ASSUMED BATTERY WAS A VALID INSTALLATION.  SEC	OND SUCH INSTALLATION FOUND RECENTLY.  TECHNICIANS AND REPAIR STATIONS NEED TO VERIFY LEAD ACID BATTERY IS VALID FOR THE	 STC INSTALLED IN THE AIRCRAFT.  MULTIPLE LEAD-ACID BATTERY STC`S HAVE BEEN ISSUED, HOWEVER MANY REQUIRE THE USE OF ONE 	SPECIFIC MANUFACTURERS PART NUMBER BATTERY.	1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003100600048	20031006	00048	CE  	2003	10	6	2003FA0000933    	1	20030902	G	2497	D34A22	WIRE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  					P330 CONNECTOR	MISLOCATED      	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	355TW				1025	BB521				CABIN ALTITUDE WARNING SYSTEM FAILED INITIAL TEST IAW NEW 12 MONTH INSPECTION REQUIREMENT OF MM, CHAPTER 5.  DURING SUBS	EQUENT TROUBLESHOOTING, FOUND WIRE D34A22 CONNECTED TO NC TERMINAL OF ALTITUDE SWITCH S117 INSTEAD OF C TERMINAL AS SHOW	N IN WDM 21-30-01 P.3.  EVIDENCE WIRING IN AREA DISTURBED PREVIOUSLY DURING AVIONICS MODIFICATIONS OR INTERIOR REFURBISH	MENT.			1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003100600085	20031006	00085		2003	10	6	2003FA0000934    	4	20030916	G	2210	131819TCAC420	GUIDE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ELEVATOR	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	61HA					UE175				WHILE CHECKING ELEVATOR TRIM WE FOUND INTERMITENT BINDING OF ELEVATOR TRIM WHEN MANUALLY OPERATING TO NOSE DOWN DIRECTIO	N. BINDING WAS OF SUCH THAT IT WOULD MOMENTARILY HANG BEFORE RELEASING. IT OCCURED AT PRETY MUCH THE SAME POSITION EACH 	TIME, (WHEN MOVING FROM 6 TO 3 ON THE ELEVATOR TRIM WHEEL). HEARD POPPING IN FLOOR UNDER SEAT 8A. REMOVED SEAT AND FLOOR	 PANELS AND FOUND ELEVATOR TRIM CABLE TURN BARREL HANGING UP ON THE ABOVE REFERENCED GUIDE TUBE. REMOVED AND REPLACED GU	IDE TUBE RESET CABLE TENSIONS AND SAFTIED TURN BARREL. OPERATIONALLY CHECKED SATISFACTORY.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2003100600025	20031006	00025	CE  	2003	10	6	2003FA0000935    	1	20030915	G	7714	26060131	TACHOMETER      			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	COCKPIT	DAMAGED         	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	23	1232X	71   				208B0989				TENTHS POINTER FELL OFF OF ENGINE COMPRESSOR RPM TACHOMETER INDICATOR.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003100300091	20031003	00091	CE  	2003	10	3	2003FA0000936    	1	20030915	G	5210	071100159	HINGE PIN       	CESSNA      		CESSNA	172   	172R        	2072401	CE  										PAX DOOR	SHEARED         	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NE	05	24783	515  				17281029				DOOR HELD IN PLACE BY LOWER HINGE, DOOR STOP SPRING, & PASSENGER.  INSP REVEALED UPPER HINGE PIN OF RT CABIN DOOR WAS SH	EARED COMPLETELY.  LWR HINGE PIN (P/N 0517019-12) WAS FOUND TO BE BENT, BROKEN, AND PARTIALLY INSTALLED.  LOWER HINGE & 	ADJACENT STRUCTURE WAS BENT & BROKEN. RT CABIN DOOR WINDOW SEPARATED FROM DOOR IN FLT & WAS LOST.  RT FUSELAGE WAS DAMAG	ED BEHIND AFT DOOR FRAME, AS RESULT OF CONTACT WITH DOOR OR WINDOW. HINGE PIN MATERIAL OF SHEARED UPPER HINGE PIN HAS BR	ASS COLOR.  HINGE PIN MATERIAL OF BENT LOWER HINGE PIN HAS SILVER COLOR.  UPPER HINGE PIN ON LT CABIN DOOR SHOWS SOME MI	NOR WEAR, METHOD OF INSTALLATION PREVENTS DISASSEMBLY FOR INSP.  PIN MUST BE REPLACED AFTER REMOVAL.	1	H	7	1 	3O			NT	3A12    					 
2003100600009	20031006	00009	CE  	2003	10	6	2003FA0000937    	1	20030915	G	2820	260010148	VENT LINE       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL SYSTEM	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	PKMPS	4398 				208B0656				THIS AIRCRAFT IS EQUIPPED WITH OPTIONAL INBOARD FUEL FILLER CAPS.  THE FUEL FILLER CAP ADAPTER ASSY. (P/N C156005-0105) 	HAS A SPRING LOADED FLAPPER WHICH IS DEPRESSED BY THE FUEL DISPENSING NOZZLE WHILE FILLING THE TANK.  THE FLAPPER HAS BE	EN HITTING ON THE (P/N 2600101-48) VENT LINE ASSY INSIDE THE TANK BAY AND HAS WORN THE VENT LINE APPROXIMATELY HALF WAY 	THROUGH ITS DIAMETER.  DEFECT WAS DISCOVERED BECAUSE FUEL FILLER ADAPTER WAS REMOVED FOR MAINTENANCE.			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003100900099	20031009	00099	SO  	2003	10	9	2003FA0000939    	1	20030917	G	2434		ATTACH FITTING  	PRESTOLITE  		PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					ALTERNATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	1996	80   			C111046	28R7703425	UNKNOWN			COMPONENT WAS CRACKED IN THREE PLACES, THIS IS IN THE DRIVE ATTACHMENT BASE.  (JUST FORWARD OF THE ATTACHMENT PLATE), ON	 THE WEB THAT SECURES THE ALTERNATOR.  OWNER SAID THAT HE HAD REPLACED THE ALTERNATOR 7 MONTHS AGO FOR THE SAME PROBLEM,	 CRACKED JUST AFT OF THE BASE PLATE APPROX. TIME 80 HOURS.  ALTERNATOR RETURNED TO MFG.  BELIEVE THAT PROBLEM IS A UNBAL	ANCE PROBLEM.  THE WAY THE ALTERNATOR IS MOUNTED SHOWS THAT IT IS NOT A OVER TORQUE ISSUE.			1	L	7	1 	3O	3	O	 	2A13    	E9CE				 
2003101400015	20031014	00015	SO  	2003	10	14	2003FA0000940    	1	20030918	G	2434		BEARING         			PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O320  	O320*       	41508	EA  					ALTERNATOR	OVERHEATED      	B				O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			GL	03					D071908					ALTERNATOR HARD TO ROTATE DUE TO NON-DRIVE END BEARING BEING PRESSED INTO HOUSING TOO FAR. BEARING COVER FOUND (BLUED) D	UE TOO EXCCESIVE HEAT. DRIVE PULLEY HARD TO ROTATE BY HAND. NOTE: 0 TIME SINCE OVERHAUL!					1	H	7	1 	3O	3	O	 	1A2     	E274				 
2003101000072	20031010	00072	SO  	2003	10	10	2003FA0000942    	1	20030820	G	1430		NUT             			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					CIRCUIT BREAKER	LOOSE           	B			V2AR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	9387J					283488				INSTRUMENT NUT CAME OFF VSI AND SHORTED FROM AM/FM RADIO CASE TO TOP TERMINAL OF CIRCUIT BREAKER FOR THE TURN BANK INDIC	ATOR, CAUSING WIRE FROM BUS TO CIRCUIT BREAKER TO BURN.  CHECK ALL INSTRUMENTS FOR MISSING SCREW AND REMOVE AM/FM RADIO 	FROM AIRCRAFT.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003101000073	20031010	00073	NE  	2003	10	10	2003FA0000943    	2	20030816	G	8530		CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	48395	816  				1628	21888			FOUND ALUMINUM CHIPS IN SCREEN.  INTERNAL ENGINE INSPECTION REVEALED A 5 INCH LONG CRACK IN THE NR 5 CYLINDER SKIRT.						1	Q	7	1 	3R	3	R	 	1A16    	5E2				 
2003101000075	20031010	00075		2003	10	10	2003FA0000944    	4	20030627	G	6122	A3496	SPRING          													HARTZL	HCB5M	HCB5MP3     	GL  	FEATHERING	BROKEN          	B			ME4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19								EV820		FEATHERING SPRING FOUND BROKEN INSIDE DURING DISASSEMBLY FOR OVERHAUL.																6	C	P44GL	 
2003101000081	20031010	00081	SO  	2003	10	10	2003FA0000945    	2	20030718	G	7414		BRUSHES         								CONT  	O520  	IO520*      	17032	SO  					MAGNETO	WORN            	B			CY4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		1092 			00102120					MAGNETO HAS SEVERE BRUSH WEAR.											3	O			E5CE				 
2003101400033	20031014	00033		2003	10	14	2003FA0000951    	4	20030903	G	3418	S16722	STALL WARNING   			CESSNA	177   	177RG       	2073709	CE  										LT WING	MALFUNCTIONED   	B			CRJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	35373	2557 				177RG1049				STALL WARNING SYSTEM FUNCTION TEST AT ANNUAL INSPECTION WAS CORRECT.  SYSTEM WOULD NOT OPERATE WHEN PITOT HEAT WAS SWITC	HED ON.  REMOVED STALL SWITCH AND CLEANED CORROSION FROM GROUND.  BOTH STALL WARNING AND PITOT HEAT WOULD OPERATE CORREC	TLY THEN.  PREVIOUSLY, THE STALL WARNING SYSTEM WOULD FIND A GROUND THROUGH THE PITOT HEATER VIA THE STALL WARNING HEATE	R.  WHEN THE PITOT HEAT WAS TURNED ON,  THE STALL WARNING WOULD NOT GROUND.			1	H	7	1 	3O			 	A20CE   					 
2003102200098	20031022	00098		2003	10	22	2003FA0000952    	4	20030902	G	2561	KSE35LP0723E105P	LIFE VEST       																	CELL	FAILED          	B			KQ1R	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			EA	07										LIFE VEST FAILED, MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-12.  DOM: JUNE 1998																			 
2003102200104	20031022	00104	SO  	2003	10	22	2003FA0000953    	1	20030910	G	7921	20710AR	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	4142Q					2843207	RL3705736A			DURING PREFLIGHT INSPECTION PILOT FOUND SIGNS OF AN OIL LEAK.  THE MAINTENANCE TECHNICIAN FOUND OIL LEAK ON OIL COOLER. 	 PERFORMED PRESSURE CHECK ON OIL COOLER AND FOUND BOTTOM FLANGE CRACKED.  THIS IS A WEAK ARA ON THE OIL COOLER.  RECOMME	ND FINDING A REPLACEMENT THAT IS MORE DURABLE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003102200105	20031022	00105	CE  	2003	10	22	2003FA0000954    	1	20030910	G	7333	10238901011	TRANSDUCER      			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL SYSTEM	FAILED          	B			VJ3R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	07	5585Y	146  				CE1389	825837R			FUEL FLOW WENT TO ZERO INDICATION IN FLT.  TESTS SHOWED THAT HERTZ FLUCTUATED AND READ LOWER THAN PUBLISHED SPECIFICATIO	NS.  SUSPECT INTERNAL FAILURE, PERHAPS IMPELLER IS STICKING.  NOT RECOMMENDATIONS AT THIS TIME.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003102200106	20031022	00106	SO  	2003	10	22	2003FA0000955    	1	20030909	G	7921	20710AR	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4A     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	4142Q	3699 	52   			2843207	RL3705736			DURING A MAINTENANCE INSPECTION OF THIS AIRCRAFT, THE OIL COOLER WAS FOUND TO BE CRACKED AROUND THE MOUNTING BOLT HOLES 	AND LEAKING FROM THE SEAM IN THAT AREA.  PROBABLE CAUSE IS VIBRATION.  RECOMMEND USING A SOLID PIECE OIL COOLER.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003102200107	20031022	00107	CE  	2003	10	22	2003FA0000956    	1	20030912	G	7333	10238901211	TRANSDUCER      			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL SYSTEM	INTERMITTENT    	B			VJ3R	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			WP	07	8252T	12   				CE1545	825834R			DURING TAKE OFF POWER PILOT REPORTED THAT FUEL FLOW INDUCTION WENT TO 12GPH.  UPON TROUBLESHOOTING OF THE FUEL SYSTEM MA	INTENANCE TECHNICIAN FOUND FUEL FLOW TRANSDUCER WAS INTERMITTENT.   NO RECOMMEND AT THIS TIME.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003102100278	20031021	00278	EU  	2003	10	21	2003FA0000957    	1	20030922	G	5743	A720390L	FAIRING         			LET   	L23   	L23         	1360308	EU  										WING-TIP	CRACKED         	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	438BA					029016				RADIAL CRACKS ARE BEING FOUND FLEETWIDE ON WING-TIP FAIRINGS.THERE HAVE BEEN NO COMPLETE FAILURES AT THIS TIME.  FACTORY	 ADVISES WING TIPS ARE DESIGNED TO FAIL ON SIDE LOADS TO PREVENT MAJOR DAMAGE TO WING SPAR.					1	K	0	0 	  			RC	G24EU   					 
2003102100301	20031021	00301	CE  	2003	10	21	2003FA0000958    	1	20030922	G	2150	1015552117	CLUTCH          			BEECH 	200   	B200        	1152922	CE  										AIR CON COMPRESS	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	6124A	58   			03120305ICT	BB1824				AIR CONDITIONING COMPRESSOR CLUTCH ASSY HAD FAILED AFTER 58.0 HOURS OF AIRCRAFT OPERATION. APPEARS THAT THE ELECTRIC CLU	TCH ASSY HAD BEEN ACTIVATED CONTINOUSLY AND OPERATED WHENEVER THE ENGINE WAS OPERATING.					1	L	7	2 	4T			 	A24CE   					 
2003102200077	20031022	00077	EA  	2003	10	22	2003FA0000959    	2	20030923	G	8530		CYLINDER        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT ENGINE	SEPARATED       	G				E				ENGINE SHUTDOWN         				O			OTHER                     			DE	DESCENT        	1			GL	23	439CT		627  			347250177	L884151A	AU2637		THE AIRCRAFT WAS PREPARING FOR LANDING AT ARB, PILOT REDUCED POWER.   WITHOUT WARNING, LEFT ENGINE FWD OUTBOARD CYLINDER	 SEPARATED FROM ENGINE, WAS HELD ON BY FUEL LINES AND IGNITION HARNESS. OUTBOARD UPPER ENGINE COWLING, PISTON AND ROD DE	PARTED AIRCRAFT.   LT WING LEADING EDGE AND FUEL TANK WERE PUNCTURED, CAUSING LOSS OF FUEL.   LT HORIZONTAL STABILIZER L	EADING EDGE WAS DAMAGED, POSSIBLY FROM DEPARTING COWLING.   PILOT SECURED ENGINE, MADE EMERGENCY LANDING.   NO INJURIES.			1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2003102300015	20031023	00015	CE  	2003	10	23	2003FA0000960    	1	20030905	G	7921	LW10025	OIL COOLER      			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541*     	41536	EA  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25										WE HAVE FOUND 3 OIL COOLERS IN THE PAST YEAR ON THESE AC WITH IDENTICAL CRACKS ON THE DIAGONAL SUPPORT BARS AT THE INBOA	RD WELD.  THIS LEADS TO SEPARATION OF ONE END OF THE BAR.  CAUSE OF THE CRACKS ARE NOT OBVIOUS.  WE ARE ALSO AWARE OF 2 	OTHER AC THAT HAVE EXPERIENCED IN-FLIGHT OIL COOLER FAILURES IN THE PAST YEAR.  WE DO NOT HAVE ENOUGH INFO ON PART TIMES	 OR MAINTENANCE TO FIND A COMMON LINK.			1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2003102300016	20031023	00016	NE  	2003	10	23	2003FA0000961    	2	20030905	G	8520	40350	CRANKSHAFT      			BOEING	75    	A75         	1380108	CE  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FRACTURED       	B			CP2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	806RB	10026				754000	JP206277			THE CRANKSHAFT APPEARS TO HAVE FRACTURED AT THE CRANK PIN.  SEPARATING THE CRANK PIN AND ROD ASSEMBLY FROM THE PROPELLER	 SHAFT.  THE AIRCRAFT WAS IN THE PROCESS OF BEING FERRIED CROSS COUNTRY.  THE AIRCRAFT IS USED FOR AEROBATIC PERFORMANCE	S.  (SW15200318971)				1	Q	7	1 	3R	3	R	 	A743    	5E1				 
2003102300017	20031023	00017	SO  	2003	10	23	2003FA0000962    	2	20030829	G	8530	646612	EXHAUST VALVE   			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	C7512       	17005	SO  					NR 2 CYLINDER	SEPARATED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	3182H					3807	3962612			THE FACE OF THE NR 2 CYL EXHAUST VALVE SEPARATED FROM THE STEM OF THE VALVE.  SUBSEQUENT DAMAGE TO THE POSTON AND CYLIND	ER WAS SUBSTANTIAL.  THIS FAILURE OCCURRED WHILE IN CRUISE FLIGHT.					1	L	7	1 	3O	3	O	 	A718    	E233				 
2003102300018	20031023	00018	SW  	2003	10	23	2003FA0000963    	1	20030807	G	5302	206032409001	FITTING         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					TAILBOOM	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	999AH					51046				DURING A ROUTINE INSPECTION THE UPPER LEFT HAND TAIL BOOM ATTACH FITTING WAS FOUND TO HAVE A CRACK EMANATING FROM THE FA	STENER HOLES WHICH ATTACH THE FITTING TO THE ADJACENT STRUCTURE.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003102300021	20031023	00021	SW  	2003	10	23	2003FA0000964    	1	20030909	G	5610	33036710	WINDOW          			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	208CL					11297				OPERATOR COMPLAINED OF PRESSURIZATION PROBLEM.  DURING CABIN PUMP UP, A LEAK WAS DISCOVERED AT THE RT PICTURE WINDOW.  T	HE WINDOWS OUTER PANEL WAS FOUND TO BE CRACKED.  THE CRACK LENGTH WAS DETERMINED TO BE 18 INCHES.  THE CRACK WAS LOCATED	 AT THE UPPER FASTENER HOLES.				1	H	7	2 	3T	3	T	 	2A4     	E2WE				 
2003102300022	20031023	00022	CE  	2003	10	23	2003FA0000965    	1	20030823	G	2520	7145416	SEAT FRAME      			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320*      	41508	EA  					CABIN	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	8730V	2808 				52675				2 SEAT BACK SUPPORT STRAPS BROKE ON HARD LANDING (G-METER REUD 9G) UPPER STRAP WAS A NEW BREAK AT WELD CENTER STRAP BROK	E AT REPAIR WELD FROM PREVIOUS BREAK.  CFI IN REAR SEAT SUSTAINED MINOR BACK INJURY, AIRCRAFT LT MAIN GEAR COLLAPSED RES	ULTING IN PROP STRIKE.  3-G NEGATIVE READ ON G METER IS BELIEVED TO OCCURRED WHEN AIRCRAFT SLID ON NOSE FOR 100+ FT ON A	SPHALT RUNWAY.  ALUMINUM SHEET FOR BACK SUPPORT MIGHT ALLOW BETTER LOAD DISTRIBUTION IN LIEU OF STEEL STRAPS.			1	H	7	1 	3O	3	O	 	A759    	1E12				 
2003102300024	20031023	00024	SO  	2003	10	23	2003FA0000966    	2	20030910	G	8530	SA629340	ROD BOLT        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	TSIO520BB   	17040	SO  					ENGINE	DAMAGED         	B			ZSNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	2636P					310R1649				INSTALLED (1) NEW ROD BOLT, SA 629340 LOT NR 578901, ALONG WITH NEW NUT NR SA 628109.  NUT WOULD NOT REACH SPEC. TORQUE.	  NUT WAS REMOVED TO REVEAL THREADS, DAMAGED.					1	L	7	2 	3O	3	O	 	3A10    	E8CE				 
2003102300025	20031023	00025	CE  	2003	10	23	2003FA0000967    	1	20030822	G	2720	52000083	CONTROL CABLE   			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RUDDER CONTROL	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	775RC	8143 				402C0311				LEFT RUDDER CABLE HAD CHAFED THROUGH ON THE FLEXIBLE BRAKE MASTER CYLINDER LINE.  ROUTING OF THE BRAKE LINE OVER THE RUD	DER CABLE PULLEY CAUSED THE CABLE TO FAIL BEFORE THE BRAKE FLEX LINE FAILED.  ACCESS TO EFFECTED AREA IMPOSSIBLE DUE TO 	LACK OF WORKING AREA.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003102300048	20031023	00048	CE  	2003	10	23	2003FA0000969    	1	20030908	G	3240	0500118126	LINE            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					RT MLG BRAKE	FAILED          	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AL	03	63541					17275449				DURING LANDING ROLLOUT, RT MAIN BRAKE LINE FAILED CAUSING LOSS OF BRAKE PRESSURE.  INSPECTION DETERMINED THAT BRAKE LINE	 HAD BEEN CHAFING ON FAIRING ASSEMBLY AND SIDEWALL OF RIGID LINE HAD FAILED.  SUGGEST MORE FREQUENT INSPECTIONS AND MORE	 ATTENTION TO CLEARANCES BETWEEN FAIRING AND BRAKE LINE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003102300047	20031023	00047	SO  	2003	10	23	2003FA0000970    	1	20030924	G	3230		BOLT            			PIPER 	PA32  	PA32R301    	7103218	SO  										RT MLG	BROKEN          	D				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			GL	05	9203R					3213044				WHILE PERFORMING A NON RELATED MAINTENANCE GROUND RUN, ON THE TAXI BACK TO THE HANGER A VIBRATION OCCURED FROM THE RT MA	IN LANDING GEAR. AFTER SHUT DOWN AN INSPECTION OF THE RT MAIN GEAR ASSEMBLY FOUND THE BOLT (PN 691308) HOLDING THE TWO T	ORQUE LINKS TOGETHER WAS BROKEN. THE BOLT HALVES WERE FROZEN INTO THE LINK AND WOULD NOT TURN, DUE TO INADEQUATE LUBRICA	TION. AFTER REMOVAL, THE BOLT WAS INSPECTED AND FOUND TO RUSTED OVER HALF WAY ACROSS THE DIAMETER OF THE BOLT. THE BOLT 	TIME SINCE NEW WAS 1530.7 HOURS.		1	L	7	1 	3O			 	A3SO    					 
2003102300084	20031023	00084	CE  	2003	10	23	2003FA0000972    	1	20030822	G	7810	654892	CROSSOVER TUBE  			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					RIGHT	CHAFED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	153Z	1186 				TJ322	274467R			DURING A PHASE INSPECTION, THE LEFT CROSSOVER TUBE WAS POUND CHAFED BY THE ENGINE MOUNT TRUSS (PN 102-910026-131).  THE 	CHAFING WAS APPROXIMATELY HALFWAY THROUGH THE WALL THICKNESS.  WE HAVE A SPECIAL INSPECTION TO CHECK THE HEATSHIELD FOR 	CHATING IN THIS SAME AREA, OTHERWISE THIS WOULD HAVE PROBABLY BEEN MISSED DUE TO ITS INACCESSIBILITY BEHIND THE INDUCTIO	N FILTER HOUSING, THE PART WILL BE REPLACED TO SEE IF A DIFFERENT TUBE HAS THE SAME PROBLEM.  OTHER AIRCRAFT IN THE FLEE	T WERE CHECKED WITHOUT DEFECTS NOTED.(K)		1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2003102700010	20031027	00010	EA  	2003	10	27	2003FA0000973    	1	20030106	G	6420	1885	BALL            			SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360*     	41514	EA  					T/R ZERC FITTING	MISSING         	B			OG5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	2086F	1011 				S1754				AFTER ENGAGEMENT OF ROTOR SYSTEM, TAIL ROTOR DID NOT MOVE.  INVESTIGATION FOUND BALL MISSING OUT OF ZERC, ALLOWING GREAS	E TO ESCAPE ALLOWING BUMPER TO WEAR ALLOWING SHAFT TO DECOUPLE.					1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2003102700013	20031027	00013	SO  	2003	10	27	2003FA0000974    	1	20030718	G	5751	86396004	RIB             			PIPER 	J3    	PA11        	7101102	SO  	LYC   	O360  	O360*       	41514	EA  					AILERON	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	2163N	6775 				447995222				DURING INSPECTION OF LT AILERON, FOUND ALL THREE AILERON ATTACH POINT RIBS CRACKED ADJACENT TO MOUNTING BELL CRANKS.						1	H	7	1 	3O	3	O	 	A691    	E286				 
2003102700003	20031027	00003	CE  	2003	10	27	2003FA0000975    	1	20030925	G	7603	C805975	THROTTLE CABLE  			CESSNA	500   	560CESSNA   	2076750	CE  											DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										THROTTLE CABLES FREEZING BETWEEN 6000 AND 8000 HOURS.  FWD P/NC80597-5 AND AFT P/N7-42346-1						2	L	7	2 	4F			RT	A22CE   					 
2003102300074	20031023	00074	SO  	2003	10	23	2003FA0000976    	2	20030915	G	7421	URHB32E	SPARK PLUG      			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	421GC	177  				421B0926	231527R			DURING ROUTINE 100 HR INSPECTION 4 SPARK PLUGS ON RIGHT ENGINE FOUND TO HAVE CRACKS IN THE PLUG BODY BETWEEN THE GASKET 	SURFACE AND THE WRENCH HEX.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2003102700032	20031027	00032	SO  	2003	10	27	2003FA0000977    	2	20030823	G	8530	24122	BUSHING         			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					ROCKER ARMS	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	2698J	10   	10   			15065698	635456A			EIGHT ROCKER ARM BUSHINGS SHOWED INDICATIONS OF EXCESSIVE WEAR.  THE PROBLEM WAS INDICATED AT THE FIRST OIL CHANGE (10 H	OURS) AFTER ENGINE OVERHAUL AS BRONZE PARTICLES IN THE OIL FILTER.  THE OVERHAULED ROCKER ARMS WERE INSTALLED IN NEW MFG	 CYLINDERS P/N 653816 WHICH INCLUDED NEW ROCKER SHAFTS P/N 654375. THE ROCKER ARMS WERE REMOVED AND BUSHING CLEARANCE ME	ASURED.  THE CLEARANCES VARIED FROM .005 TO .010.  MANUFACTURER'S O/H MANUAL STATES NEW CLEARANCE AS .001 TO .0025 AND T	HE SERVICE LIMIT AS .004.		1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003102700014	20031027	00014	SO  	2003	10	27	2003FA0000978    	1	20030925	G	3220	6338300	LINK ASSY       			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	9426J	3068 				283537				THE PROBLEM EXISTS WITH PN 6338300.THE ONLY DIFFERENCE WITH THE TWO PARTS IS THAT THERE IS A STIFFENER INSTALL IN THE 65	41300.  THE STIFFENER INSTALL PREVENTS THE COLLAPES OF THE BUMPER MOUNT WHICH IN TURN SPREDS THE LINK SIDE CHANNELS WHIC	H THEN CAUSES THE LINK TO CRACK.  THIS IS WHAT HAPPENED TO THE 6338300 ON ACFT 283537.   I FEEL THAT THE 6338300 SHOULD 	BE EITHER RECALLED, OR MODIFIED TO A 6541300,OR AT LEAST INSPECTED TO SEE IF THIS FAILURE EXISTS IN THE FIELD.   FAILURE	 OF THIS LINK IS A LIFE THREATENING CONDITION.		1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003102800001	20031028	00001	SO  	2003	10	28	2003FA0000981    	2	20030929	G	8520	655004	CONNECTING ROD  								CONT  	O520  	TSIO520P    	17040	SO  					ENGINE	NICKED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		130  	130  				278874			DURING ENGINE INSPECTION FOR DEBRIS IN OIL FILTER FOUND NUMBER 3 CONNECTING ROD CAP TO HAVE DEEP NICK OR GOUGE.											3	O			E8CE				 
2003102900136	20031029	00136	CE  	2003	10	29	2003FA0000982    	1	20030909	G	8010	643109	CLUTCH SPRING   			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520*      	17032	SO  					STARTER ADAPTER	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	59299				3102	21060199	295269R			CLUTCH SPRING, BROKEN.						1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2003103000003	20031030	00003	SW  	2003	10	30	2003FA0000983    	1	20030912	G	6330	2060325095	DRAG PIN        			BELL  	206   	OH58A       	1181579	SW  										TRANSMISSION	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	1082M					7221309				CRACK-LIKE INDICATION ON OUTER SIDE AND EDGE OF BORE.  CRACK-LIKE INDICATION DETECTED BY FLUORESCENT MT.						1	G	7	1 	3U			 	H2SW    					 
2003100100061	20031001	00061	CE  	2003	10	1	2003FA0000984    	1	20030929	G	3230	1VA20	SAFETY SWITCH   			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520BE   	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	MLG	DEFECTIVE       	E				A				UNSCHED LANDING         				S			AFFECT SYSTEMS            			CL	CLIMB          	1			SW	05	401TE					4010180				LANDING GERA WOULD NOT RETRACT AFTER TAKE OFF DUE TO A DEFECTIVE GEAR SAFETY SWITCH.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003100100082	20031001	00082	SO  	2003	10	1	2003FA0000987    	1	20030930	G	2597		WIRE            	NARCO       		PIPER 	PA32  	PA32RT301   	7103222	SO  										ELT BATTERY	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			116  			3257233				C/W FAR 91.207D INSPECTION FOUND ELT INOP.  OPENED ELT TO REPLACE BATTERY ASSEMBLY FOUND POWER WIRE CORRODED OFF CELL. O	THER CELLS SHOW SIGNS OF CORROSION					1	L	7	1 	3O			 	A3SO    					 
2003103000011	20031030	00011	EU  	2003	10	30	2003FA0000991    	1	20030918	G	8012	945UN01Q4AF8A	SWITCH          			UROCOP	EC155 	EC155B      	8681000	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					START	FAILED          	B			QC0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	155WH	513  				6563				DURING A TEST RUN FOLLOWING AN ENGINE CHANGE OF THE NR 1 ENGINE, THE NR 1 ENGINE FAILED TO RETURN TO IDLE WHEN THE NR 1 	START SWITCH WAS BROUGHT FROM FLIGHT TO IDLE POSITION.  SUBSEQUENT TROUBLE-SHOOTING FOUND THAT THE SWITCH WOULD ALSO FAI	L FROM IDLE TO FLIGHT POSITIONS. THIS CONDITION,  IF NOT REALIZED BY THE FLIGHT CREW, COULD RESULT IN AN UNDERPOWERED SI	NGLE ENGINE TAKE-OFF.  THIS IS NOT THE FIRST FAILURE OF THIS TYPE WITH THIS SWITCH.			1	G	7	2 	3U	3	U		H10EU   	E19EU				 
2003103000015	20031030	00015	CE  	2003	10	30	2003FA0000992    	1	20030805	G	3243	26820011	MASTER CYLINDER 			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					RT BRAKE	DAMAGED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	9750B	8641 	1989 			208B0100				RT BRAKE DRAGGING DUE TO FLUID NOT RETURNING TO RESERVOIR WHEN BRAKE WAS RELEASED, CAUSED BY OVERHEATED BRAKE CALIPER AN	D SUBSEQUENT BRAKE FIRE AND TIRE DAMAGE DURING LONG TAXI PERIOD.  RECOMMEND MASTER CYLINDERS BE OVERHAULED AT 1000 HOUR 	INTERVALS.				1	H	7	1 	3T	3	T	 	A37CE   	E2NE				 
2003103000067	20031030	00067	SO  	2003	10	30	2003FA0000993    	1	20030418	G	1430		FASTENER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					VERTICAL STAB	UNDERTORQUED    	B			UW4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	134FC	4092 				288290169	L3032436A			AIRCRAFT OWNER REQURESTED THAT WE CHECK TORQUE ON BOLTS SECURING VERTICAL FIN TO TAILCONE BULKHEAD.  FOUND ALL VERTICAL 	FIN ATTACH HARDWARE UNDER TORQUED.  INSPECTED HARDWARE AND MOUNTING HOLES.  FOUND NOT PERFECT.  REINSTALLED BOLTS AND TO	RQUED TO MFG SPECIFICATIONS.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003103000068	20031030	00068	EA  	2003	10	30	2003FA0000995    	1	20030826	G	6320	269A510351	SHAFT           			SCWZER	269   	269D        	8059501	EA  										M/R TRANSMISSION	WORN            	B			BS2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	277DT				S0028	0028				OPERATOR NOTICED CLUNK NOISE WHILE ROTATING DRIVE SYSTEM ON PREFLIGHT.  NOISE WAS FROM THE M/R TRANS.  DISASSEMBLY OF BO	LT DRIVE SYSTEM REVEALED A LOOSE UPPER PULLEY STACK UP DUG TO LOOSE AFT PINION NUT WITH ALL THE ASSOCIATING FRETTING DAM	AGE OF UPER PULLEY HUB AND BEARINGS.  M/R TRANS WAS REMOVED AND DISASSEMBLED.  PINION SHAFT BEARING RETAINER NUT WAS FOU	ND TO BE LOOSE AND THE OUTER PINION BEARINGS INNER RACE HAD BEGAN SPINNING ON THE PINION SHAFT JOURNAL.  THE UPPER PULLE	Y AFT PINION NUT HAS HISTORY OF LOOSENING AND IS CHECKED AT 100 HOR INTERVALS BUT THIS ONE HAD BEEN COMING LOOSE TOO SOO	N (80 HRS FROM LAST TORQUE) FIRST OCCUR ON THE PINION SHAFT BRG NUT PROBLEM.	1	G	7	1 	3U			0	4H12    					 
2003103000099	20031030	00099	SO  	2003	10	30	2003FA0000997    	1	20030902	G	3230	67665857002	CONTROL CABLE   			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FIREWALL	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	7527J					28R30898				ALTERNATE AIR CABLE WRAPPED AROUND NOSE GEAR WHEN RETRACTED AFTER TAKE-OFF.  ROUTING OF CABLE BOTTOM RIGHT OF FIREWALL U	P AND AROUND GEAR INDENTATION  ON FIREWALL.  IF CABLE COMES LOOSE IT WILL WRAP AROUND NOSEWHEEL TIRE.  REROUTING OF CABL	E ABOVE NOSE GEAR TO AIR BOX AND MOUNT WITH MS-21919 CLAMPS WILL ELIMINATE THIS FROM HAPPENING.  I WOULD SUGGEST PULLING	 REPORTS ON REPETITIVE PROBLEMS AND ALSO HAVING MFG ISSUE SERVICE BULLETIN ON ALTERNATE ROUTING OF THE CABLE, AWAY FROM 	THE GEAR WELL.  I WOULD APPRECIATE BEING KEPT INFORMED OF FUTURE ACTION.		1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003100300089	20031003	00089	SO  	2003	10	3	2003FA0001004    	1	20030926	G	4930	60277	BUTTON          	HAMLTN      		EMB   	135   	EMB135ER    	3260203	SO  										FILTER MODULE	CRACKED         	C			OY0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01										INDICATOR BUTTON FAILURE OCCURED ON THREE UNITS AND CRACKS CLEARLY EVIDENT ON TWO OTHERS IN SAME AREA OF BREAKAGE. ONCE 	BROKEN, A SECTION OF THE BUTTON CAN TRAVEL BEYOND THE SEALED AREA OF THE HOUSING AND HAS THE CAPABILITY OF ALLOWING A FU	EL LEAK OF UP TO 1.5 GALLONS PER MINUTE. ENGINEERING ANALYSIS INDICATES A LOW CYCLE FATIGUE SITUATION (FATIGUE CRACKS VI	SIBLE WITH A MICROSCOPE EXAM AT 7-30X). CEP PERFORMED A FEA SIMULATING THE BUTTON RESTRAINED IN THE CAP HOUSING WHICH SH	OWS THE FAILURE TO BE IN THE LOW CYCLE FATIGUE REGION FOR 7075-T6 ALUMINUM.     FUEL FILTER MODULE, PN 60500 & PN 495196	0 / SN`S: C0072, C0213, C0383, C0390, C0528	2	L	7	2 	4F			RT	T00011AT					 
2003110300059	20031103	00059	SO  	2003	11	3	2003FA0001005    	2	20030905	G	8550		ADAPTER         			BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	IO470N      	17026	SO  					OIL FILTER	WORN            	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	17	866P					CD1023				ENGINE DEVELOPED OIL LEAK, FOUND THIS ADAPTER LEAKING AT THREADS, LOCKING NUT SAFETY WAS INTACT, TORQUE DOPE WAS INTACT.	  ALL REQUIREMENTS OF AD 96-12-22 WERE MET AS PREVIOUSLY INSPECTED 18 HOURS BEFORE FAILURE.					1	L	7	1 	3O	3	O	 	3A15    	3E1				 
2003110300066	20031103	00066	EA  	2003	11	3	2003FA0001006    	2	20030829	G	8520	LW117725	CRANKSHAFT      			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	BROKEN          	B			MW2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	442AF	1173 	343  			61P063779632				CRANK BROKE ON NR 4 AND NR 6 CHEEK.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2003110300068	20031103	00068	EA  	2003	11	3	2003FA0001007    	2	20030808	G	8530	38135015	STUD            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					ENGINE CYLINDER	BROKEN          	B			MW2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	1039U		700  			347250024	L819451A			CYL STUDS BROKEN.  CYL BACKED OFF ENGINE.						1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2003110300069	20031103	00069	SO  	2003	11	3	2003FA0001008    	1	20030926	G	2821		BUTTON          			EMB   	145   	EMB145ER    	3260211	SO  										FUEL FILTER	FAILED          	B			OY0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01					C0072					INDICATOR BUTTON FAILURE OCCURRED (DETAIL PART BROKE IN HALF) ON THREE UNITS AND CRACKS CLEARLY EVIDENT ON TWO OTHERS IN	 SAME AREA OF BREAKAGE.  ONCE BROKEN, A SECTION OF THE BUTTON CAN TRAVEL BEYOND THE SEALED AREA OF THE HOUSING AND HAS T	HE CAPABILITY OF ALLOWING A FUEL LEAK OF UP TO 1.5 GALLONS PER MINUTE.  ENGINEERING ANALYSIS INDICATES A LOW CYCLE FATIG	UE SITUATION (FATIGUE CRACKS VISIBLE W/MICROSCOPE EXAMIN AT 7-30 POWER).  CEP PERFORMED A (FEA) SIMULATING THE BUTTON RE	STRAINED IN THE CAP HOUSING WHICH SHOWS THE FAILURE TO BE IN THE LOW CYCLE FATIGUE REGION FOR 7075-T6 ALUMINUM (BUTTON M	ATERIAL).  PRODUCT DELIVERED T HS 813.	2	L	7	2 	4F			RT	T00011AT					 
2003110300070	20031103	00070	CE  	2003	11	3	2003FA0001009    	1	20030924	G	3230	583800901	MOTOR           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MLG	WORN            	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1565A	535  				CE1331	820467R			PILOT REPORTED THAT LANDING GEAR WOULD NOT EXTEND.  AFTER GEAR HANDLE CYCLED TWICE GEAR CAME DOWN.  UPON TROUBLESHOOTING	 OF THE LANDING GEAR SYSTEM FOUND LANDING GEAR DYNAMIC RELAY INTERMITTENT AND LANDING GEAR MOTOR SLOW TO RETRACT AND EXT	END IAW MM.  NO RECOMMENDATIONS AT THIS TIME.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003110300071	20031103	00071	SO  	2003	11	3	2003FA0001010    	1	20030925	G	2435	MHB6016	STARTER         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4134T	60   				2843206	RL1754936A			DURING ATTEMPTED START OF AIRCRAFT ENGINE WOULD NOT START.  MAINTENANCE TECH TROUBLESHOOTING START SYSTEM FOUND THAT DC 	POWER WAS GETTING TO STARTER HOWEVER NO POWER WAS COMING OUT OF STARTER.  PROBABLE CAUSE IS AN INTERNAL FAILURE WITH THE	 STARTER.  STARTER SENT BACK TO MFG FOR ANALYSIS AND AT THIS TIME NO RECOMMENDATION TO PREVENT RECURRENCE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003110300072	20031103	00072	CE  	2003	11	3	2003FA0001011    	1	20030924	G	3230	SM50D7	RELAY           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MLG	INTERMITTENT    	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	1565A	519  				CE1331				PILOT REPORTED THAT LANDING GEAR WOULD NOT EXTEND.  AFTER GEAR HANDLE CYCLED TWICE GEAR CAME DOWN.  UPON TROUBLESHOOTING	 OF THE LANDING GEAR SYSTEM FOUND LANDING GEAR DYNAMIC RELAY INTERMITTENT.  NO RECOMMENDATIONS AT THIS TIME.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003111400018	20031114	00018	EU  	2003	11	14	2003FA0001012    	1	20030929	G	2710	120A4242	LEVER           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					AILERON	BINDING         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	865AF	937  				85005	L2826448A			DURING PRE-FLIGHT INSPECTION, FLIGHT CREW FELT BINDING ON THE AILERON SYSTEM UPON FURTHER INSPECTION FOUND BEARINGS IN A	ILERON LEVER 2 ASSY.  TO BE DAMAGED AND BINDING.  DAMAGE APPEARS TO BE CAUSED BY THE BUSHING PN 120A4435.02 IN THE FORK 	ENDS PN 120A4435.01.  IT APPEARS THAT DESIGN LIMITATIONS OF THE FLIGHT CONTROL SYSTEM EXCEEDS LIMITATIONS OF THE BEARING	S ALLOWING BUSHING TO APPLY EXCESSIVE FORCE ON BEARING DURING FULL DEFLECTION.  RECOMMEND REDESIGN OF FLIGHT CONTROL SYS	TEM OR REPLACE BEARINGS WITH NEW BEARINGS THAT HAVE GREATER LIMITS.		1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111400019	20031114	00019	EU  	2003	11	14	2003FA0001013    	1	20030929	G	2710	120A4240	LEVER           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					AILERON	BINDING         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	867AF	639  				85007	RL2451848			DURING FLEET WIDE INSPECTION, FOUND BEARINGS IN AILERON LEVER 2 ASSY.  PN 120A4242 TO BE DAMAGED AND BINDING.  DAMAGE AP	PEARS TO BE CAUSED BY THE BUSHING PN 120A4435.02 IN THE FORK ENDS PN 120A4435.01.  IT APPEARS THAT DESIGN LIMITATIONS OF	 THE BEARINGS ALLOWING BUSHING TO APPLY EXCESSIVE FORCE ON BEARING DURING FULL DEFLECTION.  RECOMMEND REDESIGN OF FLIGHT	 CONTROL SYSTEM OR REPLACE BEARINGS WITH NEW BEARINGS WITH NEW BEARINGS THAT HAVE GREATER LIMITS.			1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111400054	20031114	00054	EU  	2003	11	14	2003FA0001014    	1	20030929	G	2710	120A4242	LEVER           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					AILERON	BINDING         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	863AF	1024 				85003				DURING FLEET WIDE INSPECTION, FOUND BEARINGS IN AILERON LEVER 2 ASSY.  PN 120A-4242 TO BE DAMAGED AND BINDING.  DAMAGE A	PPEARS TO BE CAUSED BY THE BUSHING PN 120A-4435..02 IN THE FORK ENDS PN 120A4435.01.  IT APPEARS THAT DESIGN LIMITATIONS	 OF THE FLIGHT CONTROL SYSTEM EXCEEDS LIMITATION OF THE BEARINGS ALLOWING BUSHING TO APPLY EXCESSIVE FORCE ON BEARING DU	RING FULL DEFLECTION.  RECOMEND REDESIGN OF FLIGHT CONTROL SYSTEM OR REPLACE BEARINGS WITH NEW BEARINGS THAT HAVE GREATE	R LIMITS.		1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111400009	20031114	00009	EU  	2003	11	14	2003FA0001015    	1	20030929	G	2710	120A4242	LEVER           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					AILERON	BINDING         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	862AF					85002				DURING FLEET WIDE INSPECTION, FOUND BEARING IN AILERON LEVER 2 ASSY.  PN 120A-4242 TO BE DAMAGED AND BINDING.  DAMAGE AP	PEARS TO BE CAUSED BY THE BUSHING PN 120A-4435.02 IN THE FORK ENDS PN 120A4435.01.  IT APPEARS THAT DESIGN LIMITATIONS O	F THE FLIGHT CONTROL SYSTEM EXCEEDS LIMITATION OF THE BEARINGS ALLOWING BUSHING TO APPLY EXCESSIVE FORCE ON BEARING DURI	NG FULL DEFLECTION.   RECOMMEND REDESIGN OF FLIGHT CONTROL SYSTEM OR REPLACED BEARINGS WITH NEW BEARINGS THAT HAVE GREAT	ER LIMITS.		1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111400039	20031114	00039	EU  	2003	11	14	2003FA0001016    	1	20030925	G	2913		MOTOR           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					HYD PUMP UNIT	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	864AF	591  			0016	85004				DURING FLIGHT TRAINING, GEAR FAILED TO RETRACT.  MAINTENANCE TECHNICIAN FOUND THAT THE HYDRAULIC PUMP MOTOR OF THE RETRA	CT SYSTEM HAD FAILED.  PROBABLE CAUSE IS OVERHEATING OF THE HYDRAULIC PUMP MOTOR.  RECOMMENDATION IS TO MANUFACTURE TO I	NSTALL A HIGHER CAPACITY MOTOR TO OPERATE THE LANDING GEAR SYSTEM.				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111400032	20031114	00032	SO  	2003	11	14	2003FA0001017    	1	20030929	G	2434		MOUNT           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O320  	O320D3G     	41508	EA  					ALTERNATOR	BROKEN          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4161Z	365  			C121824	2843129	RL3133236A			DURNG PROGRESSIVE INSPECTION OF ENGINE FOUND LOWER ALTERNATOR MOUNTING HOLE BROKEN OFF.  PROBABLE CAUSE IS ENGINE VIBRAT	ION OR MISALIGNMENT OF ALTERNATOR ON ENGINE MOUNTING BRACKET.  RECOMMENDATINS IS TO INSTALLED AND RUBBER SHOCK MOUNT IN 	THIS AREA OR SHIMES TO ALIGN THE ALTERNATOR.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111400038	20031114	00038	GL  	2003	11	14	2003FA0001018    	2	20030905	G	7230	E230397911	COUPLING        								ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	FRETTED         	B			HDNR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03		1425 					CAE836938			COUPLING REMOVED FOR INSPECTION IAW SB T-080.  HAS SEVERE FRETTING IN AREA WHICH CONTACTS IMPELLER.  THIS PART WAS INSTA	LLED NEW IN A NEW IMPELLER.  FIT IS .0005 IN. TIGHT.										3	U			E4CE				 
2003103000008	20031030	00008	SW  	2003	10	30	2003FA0001019    	1	20030813	G	5751	M3414MPB	ROD END         			MOONEY	M20   	M20M        	5870222	SW  	LYC   	0540  	TIO540AF1B  	41532	EA  	MCAULY	3D32C	B3D32C417   	GL  	RT AILERON	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	2171Q	528  				270262	L1010161A	983600		PLANE CAME IN FOR ANNUAL. CUSTOMER REPORTED AILERON CONTROL STIFF. UPON MOVING YOKE TO CONFIRM STIFFNESS. RT AILERON ROD	 END AT AILERON BROKE. IT BROKE WHERE THREADED PORTION MEETS BEARING. REMOVED ROD END AND FOUND BEARING WAS FROZEN. ALL 	MOVEMENT WAS IN THE THREADS WHICH WEAKENED IT AND FINALLY BROKE. THE WAS NO EVIDENCE OF RUST OR ANYTHING. AIRPLANE IS KE	PT OUTSIDE AND LACK OF LUBRICANT IS SUSPECTED. OTHER SEAMED OKAY BUT WAS REPLACED ANYWAY.			1	L	7	1 	3O	3	O	RT	2A3     	E14EA	5	C	P58GL	 
2003111300083	20031113	00083	CE  	2003	11	13	2003FA0001020    	1	20031004	G	5751		CONTROL CABLE   			CESSNA	500   	550         	2076604	CE  										AILERONS	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	306CS					5500881				THE PILOTS CONTROL WHEEL EMITS A GRINDING NOISE WHEN OPERATING THE AILERONS.  FOUND THE AFT AILERON CONTROL CABLE WAS FO	UND TO BE INCORRECTLY ROUTED INSIDE THE PILOTS CONTROL COLUMN. THE CABLE TENSION WAS LOW AND THE TURNBUCKLE WAS ADJUSTED	 TO THE END OF ITS TRAVEL.				1	L	7	2 	4F			 	A22CE   					 
2003103100051	20031031	00051	NM  	2003	10	31	2003FA0001021    	1	20031003	G	5313	41513017L	RIB             			UNIVAR	415   	415C        	0420302	NM  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	10743					3254				DURING INSPECTION REQUIRED BY AD 2002-26-02 USING METHOD 1 AND METHOD 3, CORROSION WAS DISCOVERED IN THE VICINITY OF THE	 PILOT'S SIDE INBOARD RIB P/N 415-13017L THIS CORROSION CANNOT BE SEEN USING THE WING REMOVAL METHOD OF INSPECTION. HOWE	VER USING THE INSPECTION OPENING METHOD OF INSPECTION, CORROSION BEHING THE FUEL TANKS, IN THE VICINITY OF THE WING ATTA	CH FITTINGS, AND THE SPAR CAPS CANNOT BE SEEN ADEQUATELY. I FEEL THAT BOTH METHOS 1 AND 3 ARE NEEDED TO PREFORM AN ADEQU	ATE INSPECTION. THIS IS THE SECOND PLANE I HAVE DISCOVERED CORROSION THAT WAS NOT DETECTED BY WING REMOVAL ALONE.		1	L	7	1 	3O			 	A718    					 
2003103100062	20031031	00062		2003	10	31	2003FA0001022    	4	20031003	G	5301	A740224N	SPRING          			LET   	L23   	L23         	1360308	EU  										TOW RELEASE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	420BA	530  	530  			029007				PILOT REPORTED RELEASE HANDLE WOULD NOT RETRACT. MAINTENANCE FOUND UPON INSPECTION PART OF SPRING BROKEN. THREE ADDITION	AL SAILPLANES DEVELOPED THIS PROBLEM AT ABOUT SAME TIME IN SERVICE					1	K	0	0 	  			RC	G24EU   					 
2003103100052	20031031	00052	NM  	2003	10	31	2003FA0001023    	1	20031003	G	5313	41513017L	RIB             			UNIVAR	415   	415D        	0420306	NM  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2273H					2898				DURING INSPECTION REQUIRED BY AD 2002-26-02 USING METHOD 1 AND METHOD 3, CORROSION WAS DISCOVERED IN THE VICINITY OF THE	 PILOT'S SIDE INBOARD RIB P/N 415-13017L.  THIS CORROSION CANNOT BE SEEN USING THE WING REMOVAL METHOD OF INSPECTION. HO	WEVER USING THE INSPECTION OPENING METHOD OF INSPECTION, CORROSION BEING THE FUEL TANKS, IN THE VICINITY OF THE WING ATT	ACH FITTINGS, AND THE SPAR CAPS CANNOT BE SEEN ADEQUATELY.  I FEEL THAT BOTH METHODS 1 AND 3 ARE NEEDED TO PERFORM AN AD	EQUATE INSPECTION. THIS IS THE SECOND PLANE I HAVE DISCOVERED CORROSION THAT WAS NOT DETECTED BY WING REMOVAL ALONE.		1	L	7	1 	3O			 	A787    					 
2003103000069	20031030	00069	SO  	2003	10	30	2003FA0001024    	2	20031001	G	8530		CYLINDER HEAD   								CONT  	O520  	TSIO520F    	17040	SO  					ENGINE	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17										BARREL AND HEAD SEPARATION. HEAD SEPARATED BETWEEN THE THREADS AND SEAL BAND AREAS.											3	O			E8CE				 
2003103000070	20031030	00070	SO  	2003	10	30	2003FA0001025    	2	20031001	G	8530		CYLINDER HEAD   								CONT  	O520  	TSIO520F    	17040	SO  					ENGINE	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17										BARREL AND HEAD SEPARATION. HEAD SEPARATED BETWEEN THE THREADS AND SEAL BAND AREAS.											3	O			E8CE				 
2003102900110	20031029	00110	EA  	2003	10	29	2003FA0001026    	2	20030930	G	8530		CYLINDER        			CESSNA	182   	T182T       	       	CE  	LYC   	O540  	AEIO540D4A5 	41532	EA  					ENGINE	WRONG PART      	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07		245  				T18208154	L1121161A			DURING A ANNUAL INSPECTION, FOUND THE NR 1 CYLINDER TO BE INCORRECT FOR THIS INSTALLATION, INCORRECT CYLINDER INSTALLED 	MFG PRIOR TO INSTALLATION ON AIRCRAFT. CYLINDER WAS FOR SHORT REACH PLUGS, ENGINE USES LONG REACH. CYLINDER FOUND ON 2 N	D ANNUAL INSPECTION AND HAD OPERATED FOR 245 HRS.				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2003102900111	20031029	00111	EA  	2003	10	29	2003FA0001027    	2	20030930	G	8530		CYLINDER        			CESSNA	182   	T182T       	       	CE  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	WRONG PART      	C				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	07		245  				T18208154	L1121161A			DURING A ANNUAL INSPECTION, FOUND THE NR 1 CYLINDER TO BE INCORRECT FOR THIS INSTALLATION, INCORRECT CYLINDER INSTALLED 	BY MFG PRIOR TO INSTALLATION ON AIRCRAFT. CYLINDER WAS FOR SHORT REACH PLUGS, ENGINE USES LONG REACH. CYLINDER FOUND ON 	2ND ANNUAL INSPECTION AND HAD OPERATED FOR 245HRS				1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2003102900112	20031029	00112	EA  	2003	10	29	2003FA0001028    	2	20030930	G	8530		CYLINDER        			CESSNA	182   	T182T       	       	CE  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	WRONG PART      	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07		245  				T18208154	L1121161A			DURING A ANNUAL INSPECTION, FOUND THE NR 1 CYLINDER TO BE INCORRECT FOR THIS INSTALLATION, INCORRECT CYLINDER INSTALLED 	BY CESSNA OR LYCOMING PRIOR TO INSTALLATION ON AIRCRAFT. CYLINDER WAS FOR SHORT REACH PLUGS, ENGINE USES LONG REACH. CYL	INDER FOUND ON 2ND ANNUAL INSPECTION AND HAD OPERATED FOR 245HRS				1	H	7	1 	3O	3	O	NT	3A13    	E14EA				 
2003102900117	20031029	00117	GL  	2003	10	29	2003FA0001029    	1	20031001	G	5510	81611	TERMINAL        			AVIAT 	A1    	A1B         	2210406	GL  										HORIZONTAL STAB	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	2073X	574  				2073				LEFT FORWARD HORIZONTAL STABILIZER STRUT UPPER TERMINAL BROKE. BREAK OCCURED ON THE UPPER THREADED PORTION OF THE FITTIN	G.					1	H	7	1 	3O			NC	A22NM   					 
2003111400048	20031114	00048	CE  	2003	11	14	2003FA0001030    	1	20031008	G	5711	901100132	SPAR CAP        			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	MCAULY	4HFR34	4HFR34C762  	NE  	RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	502SE	10138				LJ740				DURING COMPLIANCE OF RAYTHEON AD 89-25-10, WING SPAR INSPECTION, A CRACK WAS DISCOVERED IN THE RIGHT WING LOWER WING SPA	R CAP.  					1	L	7	2 	3T	4	T	 	3A20    	E4EA	6	C	3PNE	 
2003111400053	20031114	00053	CE  	2003	11	14	2003FA0001031    	1	20031008	G	2720		CONTROL CABLE   			CESSNA	182   	182         	2072702	CE  										RUDDER	OUT OF POSITION 	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07										A SAFETY RECOMMENDATION WAS SUBMITTED IN RESPONSE TO SEVERAL INSTANCES WHERE THE RUDDER CONTROL CABLE HAD BEEN FOUND LOD	GED UNDER THE MOUNTING BOLT FOR THE ELEVATOR CONTROL CABLE PULLEY AT APPROXIMATELY STATION 156. A REVIEW OF THE INSTALLA	TION INDICATES THIS CONDITION COULD BE CAUSED BY INADVERTINTLY PUSHING THE CABLE DOWN ALLOWING IT TO BE TRAPPED WHEN MAI	NTENANCE IS BEING PERFORMED ON THE BATTERY OR AVIONICS PACKAGE WHICH ARE ALSO ACCESSED THROUGH THE STATION 156 ACCESS PA	NEL.  FAILURE TO RECHECK THE RUDDER CONTROL RIGGING FOLLOWING WORK ON THE NOSE WHEEL STEERING OR RUDDER TRIM SYSTEMS, CA	N ALSO CAUSE THE RUDDER SYSTEM TO EXHIBIT EXCESSIVE SLACK.	1	H	7	1 	3O			NT	3A13    					 
2003111300048	20031113	00048		2003	11	13	2003FA0001033    	4	20030718	G	2561	KS1235P0723103	LIFE VEST       																	EMERGENCY EQUIP	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED, MFG RECOMMEND CELL PRESSURE TEST IAW 25-60-7.  DOM: 3/1985																			 
2003111700006	20031117	00006		2003	11	17	2003FA0001034    	4	20030918	G	2561	KSD35PO723103	LIFE VEST       																	EMERGENCY EQUIP	FAILED          	B			KQ1R	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			EA	07										LIFE VEST FAILED.  MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-7.  DOM: 3/1985																			 
2003111300058	20031113	00058	CE  	2003	11	13	2003FA0001035    	1	20030920	G	3220	13889	BEARING         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					NLG	DESTROYED       	G				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			NM	07	41053					421B0419				AIRCRAFT LANDED EXITED ONTO TAXIWAY, FELT VIBRATION IN NOSE OF AIRCRAFT, FELL NOSE FIRST ONTO TAXIWAY.  THE BEARINGS IN 	NOSE WHEEL FROZE AND SHEARED AXIAL.  LANDING GEAR STRUT STRUCK GROUND AND COLLAPSED.  THE BEARING AND ROLLER RETAINER ON	 ONE SIDE HAD DISINTEGRATED AND IS MISSING.  THE OPPOSITE BEARING IS VOID OF ANY LUBRICATION.  THE BEARING EITHER WAS NO	T GREASED DURING THE LAST INSPECTION OR OUTSIDE EVENTS, SUCH AS USE OF PRESSURE WASHER TO CLEAN AIRCRAFT HAS WASHED AWAY	 THE GREASE.		1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2003111300059	20031113	00059	EU  	2003	11	13	2003FA0001036    	1	20030929	G	2710	120A4242	LEVER           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					AILERONS	BINDING         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	861AF	1052 				85001	L2802348A			DURING FLEET WIDE INSPECTION, FOUND BEARINGS IN AILERON LEVER 2 ASSY. PN 120A4242 TO BE DAMAGED AND BINDING.  DAMAGE APP	EARS TO BE CAUSED BY THE BUSHING PN 120A4435.02 IN THE FORK ENDS PN 120A4435.01.  IT APPEARS THAT DESIGN LIMITATIONS OF 	THE FLIGHT CONTROL SYSTEM EXCEEDS LIMITATIONS OF THE BEARINGS ALLOWING BUSHING TO APPLY EXCESSIVE  FORCE ON BEARING DURI	NG FULL DEFLECTION.  RECOMMEND REDESIGN OF FLIGHT CONTROL SYSTEM OR REPLACE BEARINGS WITH NEW BEARINGS THAT HAVE GREATER	 LIMITS.		1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111300049	20031113	00049	SO  	2003	11	13	2003FA0001037    	1	20030929	G	7921	20710AR	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	4133D		20   			2843117				DURING WALK AROUND OF AIRCRAFT.  MAINTENANCE TECHNICIAN FOUND OIL LEAK ON OIL COOLER.  PERFORMED PRESSURE CHECK ON OIL C	OOLER AND FOUND BOTTOM FLANGE CRACKED.  THIS IS A WEAK AREA ON THE OIL COOLER.  RECOMMEND FINDING A REPLACEMENT THAT IS 	MORE DURABLE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003111300035	20031113	00035	GL  	2003	11	13	2003FA0001038    	2	20030916	G	7321		BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					FUEL CONTROL	MALFUNCTIONED   	B				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	01	59479		2219 		85260025	1194				WHILE IN FLIGHT PILOT EXPERIENCED ENGINE HIGH SIDE GOVERNOR FAILURE.  THE PILOT WAS UNABLE TO CONTROL RISING ENGINE SPEE	D WITH THE THROTTLE.  RPM ROSE TO 115 PERCENT AND WAS SHUT DOWN BY THE PILOT.  UPON REMOVAL OF THE FUEL CONTROL, IT WAS 	NOTICED THAT THE DRIVESHAFT HAD AN EXCESSIVE AMOUNT OF RADIAL MOVEMENT, ALSO THE SHAFT SUPPORT BEARING WAS COMING APART,	 WITH THE BEARING BALLS FALLING OUT.  THIS PART HAS AN ESTABLISHED OVERHAUL PERIOD OF 2500 HOURS.  THE PART HAD 2219.4 H	OURS SINCE LAST OVERHAUL, AND HAD BEEN REPAIRED AND FUNCTIONALLY TESTED 498.3 HRS.  NOT AWARE OF THE NATURE OF THE REPAI	R.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003111700027	20031117	00027	EA  	2003	11	17	2003FA0001039    	2	20030917	G	8520	SL13212A	BEARING         			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					CONNECTING ROD	MELTED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	2664V	2    				177RG0648	L1351651A			NR 2 CYLINDER CONNECTING ROD FAILED AT THE CRANKSHAFT DUE TO OIL STARVATION AOF THE CONNECTING ROD BEARING.  POSSIBLE OI	L QUICK DRAIN VALVE OPENED IN FLIGHT AND DEPLETED ENGINE OIL SUPPLY.					1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2003111400069	20031114	00069	EU  	2003	11	14	2003FA0001040    	1	20030902	G	5302	L535A1101052	FRAME           			UROCOP	EC135 	EC135T1     	5620026	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					TAILBOOM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	522ME	1976 			R01	0144				PART CRACKED AT 90 DEGREES BEND RADIUS FROM APPROX 5 O`CLOCK POS.  TO THE 10 O`CLOCK POS.  BEFORE IT CRACKED TO THE OUTE	R SURFACE WHERE IT WAS NOTICED DURING A DAILY INSPECTION.  PROBABLE CAUSE MAY HAVE BEEN AN EARLIER GROUND BUMPING INCIDE	NT THAT CAUSED OTHER DAMAGE TO THE AIRCRAFT.  RECOMMENDATIONS TO PREVENT RECURRANCE WOULD BE TO CHOSEY INSPECTION.  THIS	 AREA AFTER ANY TAIL BUMPING INCIDENT.			1	G	7	2 	3U	3	U	 	H88EU   	E34NE				 
2003111700028	20031117	00028	NM  	2003	11	17	2003FA0001041    	1	20030807	G	5280	FGFB291300B3	DOOR            			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   	      	CFE73811B   	 	NE  					AUX MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	517PJ	1101 	793  			94				ON POSTFLIGHT INSPECTION A CRACK WAS FOUND ON AUX GEAR DOOR NEAR UPPER RT BOLT HOLE.  THERE IS NO EVIDENCE OF IMPACT BY 	A FOREIGN OBJECT.					2	K	7	3 	4F	4	F	RT	A50NM   	E44NE				 
2003111700022	20031117	00022	SO  	2003	11	17	2003FA0001042    	1	20030829	G	3820	532T1M140	RELIEF VALVE    			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					WATER HEATER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	691RC	7000 			GOS10269	1079				RELIEF VALVE IS INSTALLED ON HEATER ASSY:  FAILURE CAUSED ENTIRE WATER SYSTEM TO DRAIN INTO FUSELAGE.   THIS RELIEF VALV	E SHOULD BE PLUMBED INTO EXISTING AIRCRAFT DRAIN SYSTEM, SO WATER FLOWS OUT DRAIN MAST INSTEAD OF OUT THE FUSELAGE DRAIN	 HOLES.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003111700005	20031117	00005	SO  	2003	11	17	2003FA0001043    	1	20030903	G	2910		SHUTTLE VALVE   			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					HYD SYSTEM	LEAKING         	B				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	05	130GV					630				OXYGEN ACCESS PANEL ON RIGHT SIDE OF FUSELAGE HAD A NOTICEABLE AMOUNT OF SKYDROL-500 ACCUMALATED INSIDE THE ACCESS DOOR 	OF THE O-2 SERVICE PANEL.  IT WAS DETERMINED THAT THE FLUID WAS COMING FROM THE EMERGENCY LANDING GEAR AIR RELEASE VALVE	 VENT PORT DUE TO A LEAKING HYD/AIR SHUTTLE VALVE FROM THE LEFT HAND LANDING GEAR SIDE STAY ACTUATOR.  THIS VENT IS FORW	ARD OF THE O-2 SERVICE PANEL.  SKYDROL 500B-4 MSDS STATES - MATERIALS TO AVOID EXPOSURE TO STRONG OXIDIZING AGENTS.  WE 	ADDRESSED THIS SAME PROBLEM ON A/C G-V  S/N 584 IN AUGUST OF THIS YEAR.		2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003111300036	20031113	00036	NM  	2003	11	13	2003FA0001044    	1	20030715	G	5730	6587160	SKIN            			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D9       	52048	NE  					LWR CENTER WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	521DB					21266				DURING A C-CHECK INSPECTION, CORROSION WAS FOUND ON LOWER SURFACE OF CENTER WING, CENTER SECTION, WHICH FORMS THE UPPER 	WALL OF THE RAM AIR DUCT USED FOR COOLING OF THE AIR CONDITION SYSTEM ABOVE LEFT PLENUM CHAMBER ASS AT LBL 20 AND STIFFE	NER 5.  DURING CORROSION REMOVAL THE GROUND OUT EXCEEDED ALLOWABLE LIMITS.  REPAIRS ARE BEING ACCOMPLISHED IAW SRM.  TAT	:42266  TAC: 21515			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003111300037	20031113	00037	SO  	2003	11	13	2003FA0001046    	1	20031001	G	2810	U60750002	FUEL CAP        			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					TANK	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	5852D					224531				NEW FUEL CAP DID NOT VENT.  FUEL TANK WAS PARTIALLY COLLAPSED AND SPEWING SOUND WAS COMING FROM THE CAP.  CAP WAS TURNED	 FOR REMOVAL AND WHEN THE INDENTS RELEASED THE CAP, THE TANK POPPED BACK UP IN PLACE.  THE CAP DOES NOT SHOW ANY DEFORMA	TION OR DAMAGE, IT APPEARS NORMAL IN ALL RESPECTS.  SUGGEST A TESTING PROCEDURE BE DEVISED BEFORE THESE CAPS ARE INSTALL	ED.			1	H	7	1 	3O	3	O	 	1A6     	E274				 
2003111400005	20031114	00005	NM  	2003	11	14	2003FA0001047    	1	20030926	G	3060	P4E1184	BOOT            			PIPER 	PA60  	PA60601     	7106010	NM  	LYC   	O540  	TIO540*     	41532	EA  					PROP DEICE	LOOSE           	B			Q2AR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	45RN	50   				610056105				DEICE BOOT (FAST BOOT) DOES NOT PROPERLY ADHERE TO BLADE.						1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
2003111700024	20031117	00024	SO  	2003	11	17	2003FA0001048    	1	20030915	G	5531	1706702	SPAR            			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320*       	41508	EA  					VERTICAL STAB	CRACKED         	B			K5SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4159P	6249 				231644				DURING COMPLIANCE WITH AD 78-08-03, FOUND CRACKS IN THE UPPER HINGE REINFORCEMENT BRACKET (PN 17067-18) OF THE VERTICAL 	STABILIZER.  REMOVAL OF THE BRACKET WAS PERFORMED AND A CLOSE INSPECTION OF THE BOLT HOLES IN THE REAR SPAR FOR THE UPPE	R RUDDER HINGE CASTING REVEALED SIMILAR CRACKS THERE ALSO.				1	L	7	2 	3O	3	O	 	1A10    	E274				 
2003111400012	20031114	00012	EU  	2003	11	14	2003FA0001049    	1	20030928	G	7810	369D2860501	EXHAUST STACK   			HUGHES	369   	369FF       	4470709	EU  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	21	5841Z	1627 				0135FF	CAE900171			THE EXHAUST STACK HAD TO BE REPAIRED SEVERAL TIMES SINCE 400.0 HOURS SINCE NEW.  NOW THE AC HAS 1627.3 HOURS TT.  SERVIC	E REPORTS WAS DONE TO MFG SINCE 12-2000.  IN 3 OCCASIONS THE MFG SENT THE EXHAUST PN 369D2860501 FOR REPLACEMENT, BUT IT	 DID NOT FIT INTO THE AIRCRAFT.  IN THE MEANTIME, IT CONTINUED CRACKING AND WE CONTINUED TO REPAIR.				1	G	7	1 	3U	3	U	 	H3WE    	E1GL				 
2003111400020	20031114	00020	GL  	2003	11	14	2003FA0001050    	1	20030916	G	2432	G243	BATTERY         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					MASTER	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	14	425SJ	53   				1342	357640			THIS BATTERY BURNED A HOLE THROUGH THE FIREWALL.  NOT SURE OF CAUSE, BELIEVE THE BATTERY WAS DEFECTIVE.						1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003111400023	20031114	00023	SW  	2003	11	14	2003FA0001051    	1	20030827	G	6321	4000395	HOUSING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ROTOR BRAKE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	6181K	4301 			MAY921035	4276				DURING A 100 HOUR INSPECTION IT WAS FOUND THAT THE ROTOR BRAKE RETURN SPRING HAD WORN INTO THE HOUSING.  THE SPRINGS ON 	ALL FOUR HOUSINGS WERE COCKED AT AN ANGLE FROM TRUE CENTER, ALLOWING THE SPRING TO WEAR A GROOVE INTO THE SIDE OF THE HO	USING.  THIS GROOVE HINDERED THE SPRING ACTION TO MOVE THE PUCK EITHER IN OR OUT.  THE CONCERN IS THAT THE SPRING COULD 	BUST, OR BIND UP NOT ALLOWING THE PUCK TO MOVE BACK OFF OF THE ROTOR DISK.  THE RECOMMENDATION WOULD BE TO LENGTHEN THE 	RETURN PISTON GUIDE BORE WHERE THE PISTON RETURN PIN MOVES THRU THE HOUSING.  THIS WOULD HELP KEEP EVERYTHING IN ALIGNME	NT SO THE RETURN SPRING WILL ALWAYS MOVE STRAIGHT.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003111400034	20031114	00034	EU  	2003	11	14	2003FA0001052    	1	20030811	G	3220	8002104560	FITTING         			SOCATA	RALLYE	RALLYE235E  	8400135	EU  	LYC   	O540  	O540B4B5    	41532	EA  					NLG	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	711BZ					12936	L1859840A			NOSE WHEEL SHIMMY, GROUND HANDLING AND HARD LANDING.  THE RT FITTING PN 880.21.0.456.2 ALSO MADE FROM THE SAME MATERIAL 	AND SUBJECT TO THE SAME LOADS.					1	L	7	1 	3O	3	O	 	7A1EU   	E295				 
2003111400011	20031114	00011	SO  	2003	11	14	2003FA0001053    	1	20030902	G	7921	20710AR	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4166H		302  			2843119	RL2584436A			DURING 50 HOUR INSPECTION PHASE MAINTENANCE TECHNICIAN FOUND OIL LEAK ON OIL COOLER.  PERFORMED PRESSURE CHECK ON OIL CO	OLER AND FOUND BOTTOM FLANGE CRACKED.  THIS IS WEAK AREA ON THE OIL COOLER.  RECOMMEND FINDING REPLACEMENT THAT IS MORE 	DURABLE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003111400027	20031114	00027	CE  	2003	11	14	2003FA0001054    	1	20030903	G	2820	6314272A20	VALVE           			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL MANIFOLD	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5609S		146  			CE1454	825752R			DURING ROUTINE PHASE INSPECTION, THE MANIFOLD VALVE WAS FOUND TO BE LEAKING FUEL THROUGH THE AIR VENT.  PROBABLE CAUSE I	S INTERNAL FAILURE OF THE DIAPHRAGM.  NO RECOMMENDATION AT THIS TIME.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2003111400033	20031114	00033	SO  	2003	11	14	2003FA0001055    	1	20030421	G	7810	8743602	SHROUD          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	IO360E1A    	41514	EA  					RT ENG EXHAUST	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	266ER	126  				448195012	L39372T			THE CARB HEAT SHROUD ASSY (PN 8743602) FOR THIS AIRCRAFT SEEMS TO BE MANUFACTURED POORLY.  WE SEEM TO HAVE AN UNUSUAL FA	ILURE RATE WHERE THE FORWARD ATTACH CLAMP IS WELDED TO THE SHROUD ASSEMBLY.  WE HAVE CHANGED THIS PART 8 TIMES SINCE ENG	INE INSTALLATION FOR A DEFECT IN THIS WELDED AREA.  THE FOLLOWING IS A HISTORY TIMELINE OF HOURS AND DATES REPLACED.  NE	W 28 MAR 98 TT 0.0 HOURS, REPLACED 22 SEPT 98 TOTAL 100.0 HOURS, REPLACED.  21 JUL 01, TT 551.7 HOURS, REPLACED 22 APR 0	3, 677.7 HOURS I HAVE NO RECOMMENDED REPAIR OR DESIGN CHANGE THAT WOULD REMEDY THIS  PROBLEM. (CE03200308406)		1	L	7	2 	3O	3	O	 	A19S0   	1E10				 
2003111400028	20031114	00028	CE  	2003	11	14	2003FA0001056    	1	20030808	G	7160	1019100495	DUCT            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					ENGINE INLET	CRACKED         	B			DINR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	260G	1616 				BB1525				CRACKS ARE DEVELOPING IN LOWER DUCT SKINS (PN 101-9100495) OF THE AFT LOWER ENGINE COWLINGS.  (ENGINE INLETS, BOTH NR 1 	AND NR 2).  CRACKS IN RIVET ROW AFT OF INSPECTION PANEL (PN 101-910049-47) AND IN AFT ROW OF NUT PLATES FOR INSPECTION P	ANEL AT RETAINER/ SPLICE (PN 101-910049-9).  THIS PANEL IS AT THE HUMP IN THE INLET, IT AND THE SKIN AROUND IT ARE QUITE	 FLEXIBLE.  THE IMPACT AIR MUST BE CREATING THE FLEXING AND CRACKS.  SUPPORT AND STIFFENERS HAVE BEEN ADDED TO ARREST CR	ACK GROWTH ON OUR AIRCRAFT.		1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003111700029	20031117	00029	CE  	2003	11	17	2003FA0001057    	1	20030808	G	5321	50440012553	FLOOR PANEL     			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					ENTRY WAY	MISINSTALLED    	B			DINR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	260G	1616 				BB1525				CABIN FLOOR SKIN AT THE CABIN ENTRANCE IS TOO THIN AND FLEXIBLE.  THE SKIN FLEXES OVER A BULKHEAD THAT IS CENTERED IN TH	E ENTRANCEWAY.  A BOARDING PERSON WILL PLACE THERE FEET ON EITHER SIDE OF THIS BULKHEAD.  THIS CONSTANT FLEXING WOULD EV	ENTUALLY CRACK THE FLANGE OF THE BULKHEAD AND / OR THE FLOOR SKIN.  WORKING WITH TECH REP, WE HAVE INSTALLED A HEAVY SKI	N DOUBLER TO PREVENT FLEXING.			1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003111300082	20031113	00082	CE  	2003	11	13	2003FA0001058    	1	20030804	G	2150	1015503233	PLENUM          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					FREON EVAPORATOR	LEAKING         	B			DINR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	260G	1627 				BB1525				WATER WAS NOTED DRIPPING FROM BELLY BEACON.  AFT FREON EVAP PLENUM FOUND TO BE LEAKING.  REMOVED PLENUM, FOUND PLASTIC S	ECTION (BOX END) OF PLENUM CRACKED AND BROKEN AT ALL LOWER MOUNTING SCREW HOLES, CRACKS RADIATING FROM OF RIVET HOLES.  	PLASTIC BOX END, WHERE EVAP SITS AND BLWR ATTACHES.  REPLACED BOX END WITH NEW.  NOTED ON INSTALL OF REPAIRED PLENUM THA	T LWR FWD END OF BLWR MTNG FLANGE WAS RESTING ON A BLKHD, HOLDING BOX UP SLIGHTLY,  STRESSING LOWER MOUNTING SCREW HOLES	 OF BOX.  TRIMMED CORNER OF BLOWER MOUNT FLANGE FOR CLEARANCE.		1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003111400016	20031114	00016	CE  	2003	11	14	2003FA0001059    	1	20030916	G	3246	95439914	WHEEL           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					MLG	CRACKED         	B			QH5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	777DM					297				WHEEL HALF CRACKED ON INSIDE O-RING FLANGE.						2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2003111300081	20031113	00081	SO  	2003	11	13	2003FA0001060    	1	20030905	G	3213	65319002	STRUT           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					LT MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	80166	5620 				288216081				STRUT CRACKED AT LOWER SISSOR ATTACH POINT.  REPLACED WITH NEW FORGED PART 65489002 ASSY.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111400042	20031114	00042	EA  	2003	11	14	2003FA0001061    	2	20030725	G	7414	6351	DISTRIBUTOR BLK 			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					MAGNETO	BURNED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	3530E	584  				20608154	L2794148A			DISTRIBUTOR BLOCK AND GEAR ASSEMBLY BURNED UP.						1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2003111400015	20031114	00015	EU  	2003	11	14	2003FA0001062    	1	20030924	G	7810	369D2860501	EXHAUST STACK   			HUGHES	369   	369FF       	4470709	EU  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	21	5842Z					0137FF				THE EXHAUST STACK HAD TO BE REPAIRED SEVERAL TIMES SINCE 400.0 HOURS SINCE NEW.  NOW THE HELICOPTER HAS 1568.2 HOURS TAT	.  IN 3 OCCASIONS THE MFG SENT THE EXHAUST PIN 369D2860-501 FOR REPLACEMENT BUT IT DID NOT FIT INTO THE HELICOPTER.  IN 	MEAN TIME, PART CONTINUED CRACKING AND WE REPAIRING.				1	G	7	1 	3U	3	U	 	H3WE    	E1GL				 
2003111300045	20031113	00045	CE  	2003	11	13	2003FA0001063    	1	20031015	G	5730		SKIN            			CESSNA	310   	310         	2074202	CE  	CONT  	O470  	O470*       	17026	SO  					RIGHT WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	244S					35153				AFTER REMOVAL OF NACELLE AUX FUEL TANK, DISCOVERED A LARGE AREA OF CORROSION ON THE TOP WING SKIN. THE TANK HAD TRAPPED 	MOISTURE BETWEEN IT AND THE WING TOP OVER A PERIOD OF YEARS. THE CORROSION WAS CLEANED AND THE SKIN HAD LOST LESS THAN 1	0 PERCENT OF ITS ORIGINAL THICKNESS. THE AREA WAS CLEANED, TREATED AND PRIMED PRIOR TO REINSTALLATION OF THE TANK. THIS 	TANK WAS INSTALLED AS A PART OF THE RILEY TURBO ROCKET CONVERSION INSTALLED IN 1962.			1	L	7	2 	3O	3	O	RT	3A10    	E273				 
2003111400013	20031114	00013	GL  	2003	11	14	2003FA0001064    	1	20031002	G	6310	28132531	CLUTCH          			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360*     	41514	EA  					DRIVE BELT	WORN            	D			PNRG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	646H	4032 				1099				ON DRIVE BELT CLUTCH MECHANISM, THE SPRING HAD WORN THROUGH THE SIDE OF THE HOUSING FROM MANY HOURS OF RUBBING BACK AND 	FORTH.  THE ABOVE MENTIONED SPRING AND THE SPRING CAP WERE ALSO WORN BEYOND THE INSPECTION CRITERIA IN THE MFG MM.  AS F	AR AS WE COULD TELL FROM RESEARCHING RECORDS, THESE ARE ALL ORIGINAL PARTS WITH 4032.1 HOURS ON THEM.  PERHAPS REGULAR I	NSPECTION INTERVALS, 500 TO 1000 HOURS, WOULD CATCH A PROBLEM BEFORE IT BECOMES CATASTROPHIC.			1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2003111400010	20031114	00010	GL  	2003	11	14	2003FA0001065    	1	20031002	G	6720		CONTROL CABLE   			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360*     	41514	EA  					TAIL ROTOR	WORN            	D			PNRG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	646H					1099				BOTH REAR TAIL ROTOR CONTROLS CABLES WERE WORN WHERE THEY PASS THROUGH PLASTIC FAIR-LEADS IN AFT BULKHEAD OF TAIL BOOM. 	 BOTH WERE WORN TO 40-50 PERCENT INSP CRITERIA.  THIS IS BECOMING A CHRONIC PROBLEM AS RECORDS INDICATE THEY WERE REPLAC	ED 1 MAY 2001, AFT OF 2821.0; 15 MAR 2002, AFT OF 3159.7, 338.7 HOURS TIME IN SERVICE ON THE CABLES; 5 FEB. 2003, AFT OF	 3551.1, 391.4 HOURS TIME IN SERVICE; AND NOW, 25 SEP 2003, AFT OF 4043.9, 492.8 HOURS TIME IN SERVICE.  CONTRIBUTING FA	CTORS MAY INCLUDE THE RECOMMENDED TENSION ON THE CABLES AND THAT THE AIRCRAFT IS USED FOR AGRICULTURAL SPRAYING AND THE 	ACCUMULATION OF DIRT MAY BE ABRASIVE IN THE AREA OF THE FAIR-LEADS.  PERHAPS A KIT TO INSTALL PULLEYS IN THAT AREA.	1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2003111300077	20031113	00077	SO  	2003	11	13	2003FA0001066    	2	20030925	G	8530	652541	NUT             			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					NR 3 CYLINDER	CRACKED         	B			EHHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	188KM	340  				E3361	684654			PILOTS REPORTED LOOSE NUT ON FORWARD NUT TOP OF NR 5 CYLINDER, ON INSPECTION FOUND THAT THE STUD THIS NUT IS ON IS A THR	OUGH STUD TD NR 3 CYLINDER ON THE NR 3 CYLINDER THE NUT WAS CRACKED AND OPENED DOWN THE SIDE THUS ALLOWING THE NR 5 CYLI	NDER NUT TO BECOME LOOSE, REPLACED NUT AND TORQUE TO SPECS CALLED OUT IN SB 96-7B.				1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2003111400051	20031114	00051	SO  	2003	11	14	2003FA0001067    	1	20031003	G	2701	62839000	SPROCKET        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					CONTROL WHEEL	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	3077M	4782 				287816335				AT ANNUAL INSPECTION, FOUND BACKUP STOP PIN ON PILOT SIDE CONTROL SPROCKET TO BE DAMAGED.  FURTHER INVESTIGATION REVEALE	D THAT THE SPROCKET TOOTH LOCATED AT THE STOP PIN WAS BROKEN OUT OF THE SPROCKET.  POSSIBLE CAUSE IS STRESS FRACTURE AT 	THE WELD OF THE STOP PIN.  SPROCKET WAS REPLACED AND AILERON SYSTEM WAS RE-RIGGED IAW MM.    (NE03200401111)				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111300076	20031113	00076	CE  	2003	11	13	2003FA0001068    	1	20030924	G	7500	24540100	CLAMP           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					BLEED SUPPLY	CRACKED         	C				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			NE	03	441JK					4410197				REPORTED SMOKE IN COCKPIT UPON TAKEOFF.  A/C RETURNED IMMEDIATELY AND PERFORMED NORMAL LANDING.  INSP REVEALED A CRACKED	 V-BRAND CLAMP CONNECTING BLEED AIR SUPPLY LINES IN RT WING ROOT AREA ADJACENT TO SURFACE DEICE PRESSURE REGULATORS.  SM	OKE WAS DETERMINED TO ORIGINATE FROM A PLASTIC/VINYL HOSE INSIDE CABIN ADJACENT TO FUSELAGE SKIN WHICH HAD BURNED AND ME	LTED. SUSPECT HEAT FROM BLEED AIR SUPPLY LINES CAUSED LOCAL AREA TO CONDUCT HEAT THROUGH THE SKIN TO THE EXTENT NECESSAR	Y TO MELT THE TUBING.  INSP REVEALED NO OTHER APPARENT HEAT RELATED DAMAGE.  SUBMITTER NOTES THAT THE CRACK IN THE V-BAN	D CLAMP OCCURRED AT JUNCTION OF  BARREL BOLT, AND NO SAFETY DEVICES WERE INCORPORATED ON ANY OF CLAMPS IN AREA.	1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2003111300056	20031113	00056	CE  	2003	11	13	2003FA0001069    	1	20031009	G	3230	583800901	MOTOR           			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					MLG	INOPERATIVE     	B			TRKR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	353P	938  				TH1999				LANDING GEAR WOULD NOT EXTEND ELECTRICALLY.  EXTENDED MANUALLY-3 GREEN.  AIRCRAFT LANDED AND TAXIED TO FBO WITHOUT INCID	ENT. PLACED A/C ON JACKS AND RETRACTED GEAR-RETRACTED EXTREMELY SLOW. ON 2ND RETRACT MOTOR STARTED SMOKING. INSTALLED OV	ERHAULED MOTOR AND GEAR CYCLED WITHOUT FURTHER DEFECTS. NO EXTERNAL DAMAGE TO MOTOR. APPEARS TO BE INTERNAL FAILURE.				1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2003111400021	20031114	00021	GL  	2003	11	14	2003FA0001070    	1	20031010	G	3240	MS28775222	O-RING          	PARKERHANFIN		CIRRUS	SR    	SR22        	2130001	GL  										BRAKE ASSY	DEFORMED        	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	07	891CD	234  				0592				BRAKE ASSY O-RING DEFORMED.						1	L	7	1 	3O			NT	A00009CH					 
2003111400037	20031114	00037	SO  	2003	11	14	2003FA0001071    	1	20030905	G	3060		BOOT            	HARTZL      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PROP DEICE	DEBONDED        	B			IGAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	8131		6    			318152032				SEPARATION OF DE-ICE BOOT AFTER MAINTENANCE PERFORMED ON PROPELLER ASSY. PROBLEM OCCURRED ON LEFT AND RIGHT PROPELLERS A	FTER MAINTENANCE PERFORMED BY REPAIR STATION.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003111400049	20031114	00049	CE  	2003	11	14	2003FA0001072    	1	20031014	G	7160	BA3	FILTER ELEMENT  			BEECH 	23    	19A         	1151214	CE  										AIR INTAKE	SEPARATED       	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SW	17	7643R					MB435				ENGINE LOST POWER SHORTLY AFTER TAKEOFF. FORCED LANDING RESULTED IN SUBSTANTIAL DAMAGE TO THE AIRCRAFT. INVESTIGATION FO	UND PIECES OF THE AIR FILTER ELEMENT IN THE VENTURI OF THE CARBURETOR. THE FILTER ELEMENT HAD BEEN IMPROPERLY INSTALLED 	ALLOWING THE ENTIRE AFT END OF THE OVAL ELEMENT TO BE PINCHED BETWEEN THE FILTER SCREEN AND THE FILTER HOUSING. THIS ALL	OWED ELEMENT PIECES TO BE SEPARATED AND INGESTED INTO THE CARBURETOR.			1	L	7	1 	3O			 	A1CE    					 
2003111400063	20031114	00063	GL  	2003	11	14	2003FA0001074    	1	20031008	G	2710	10332002	HINGE           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	AILERON	DAMAGED         	H			NASA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	501NA	127  				0012	685745	FP1267B		INSP ON STOP-TO-STOP TRAVEL OF LT AILERON, NOTICED ODD DOUBLE BUMP SOUND, MVMT AT STOPS.  LT WINGTIP, AILERON WERE REMOV	ED TO FACILITATE FURTHER INSP.  IB AILERON HINGE MOVED UP AND DOWN WITH FORCE APPLIED TO IT.  VERT MVMT (0.053) WAS MEA	SURED APPROX AT BRG IN HINGE ABOUT 5 INCHES AFT OF TWO MNTING BOLTS.  TORQUE-SEAL WAS STILL ON NUTS, TORQUE WAS CHECKED 	FIRST IN TIGHTENING DIRECTION, THEN IN LOOSENING DIRECTION.  TORQUE REQUIRED TO TIGHTEN UPPER NUT WAS 75 INCH LBS, AND 5	5 INCH LBS TO LOOSEN. TORQUE REQUIRED TO TIGHTEN LOWER NUT WAS 40 INCH LBS AND 37 INCH LBS TO LOOSEN. BOLTHOLES IN AILER	ON HINGE, PULLEY BRACKET, AND FLAP HINGE WERE MEASURED FOR ELONGATION.  HOLES WERE NOT ELONGATED; LARGEST DIA FOUND WAS 	1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2003111300040	20031113	00040	SO  	2003	11	13	2003FA0001075    	1	20031009	G	5711	656015	SPAR CAP        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					RT WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	4606R	4407 				2821354				RT WING REPLACED.  EXISTING WING HAD EXFOLIATION CORROSION IN BOTTOM SPAR CAP AT INBOARD REAR OF FUEL TANK.  THERE IS NO	 ACCEPTABLE REPAIR.  CORROSION IS VISIBLE ONLY WHEN FUEL TANK IS REMOVED.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111300043	20031113	00043	NE  	2003	11	13	2003FA0001076    	2	20030925	G	7230		MODULE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENG COMPRESSOR	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	6093K	1403 	409  			2709	9564			PILOT REPORTED ENGINE WOULD NOT START AFTER FUEL STOP.  AFTER 45 MINUTES ANOTHER ATTEMPT WAS MADE.  ENGINE STARTED AND R	AN NORMALLY.  AIRCRAFT RETURNED THE FOLLOWING DAY.  DURING OTHER SCHEDULED MAINTENANCE THE AXIAL COMPRESSOR WAS TURNED B	Y HAND.  A NOTICEABLE DRAG WAS EXPERIENCED ALONG WITH A SQUEAK DURING ROTATION.  THE MODULE 02/03 ASSEMBLY WAS REMOVED F	OR RETURN TO MFG ENGINE FACILITY FOR EVALUATION AND/OR REPAIR.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003111700009	20031117	00009	GL  	2003	11	17	2003FA0001077    	3	20031010	G	6114	HCC2YR2	HUB             													HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER	CRACKED         	B			UF2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15		7552 						AU6095		PROPELLER HUB CRACKED.																5	C	P920	 
2003111400067	20031114	00067	NE  	2003	11	14	2003FA0001078    	2	20031010	G	7321	307080039	FUEL CONTROL    			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					ENGINE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	23	23FM	1966 				296	P115241			FUEL LEAKING FROM P3 VENT LINE, STATIC LEAKAGE. NO LEAKAGE PERMITTED IAW MM.						2	L	7	3 	4F	4	F	 	A46EU   	E1NM				 
2003111400068	20031114	00068	SO  	2003	11	14	2003FA0001079    	1	20031007	G	8010		GEAR            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					STARTER	DESTROYED       	B			OG5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	357ND	119  			0070987	2842185				PILOT SQUAWKED STARTER MAKING LOUD METAL GRINDING NOISE.  MECHANIC INSPECTED BURNED BENDIX GEAR HAD COME APART.  THIS IS	 THE SECOND OCCURANCE ON A SIMILAR AIRCRAFT WITH APPROXIMATELY THE SAME TIME IN SERVICE.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111700010	20031117	00010	SO  	2003	11	17	2003FA0001080    	1	20031007	G	8010		GEAR            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					STARTER	DESTROYED       	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	359ND	104  			D070992	2842187				PILOT SQUAWKED STARTER, WOULD NOT ENGAGE.  UPON MECHANIC INSPECTION FOUND BENDIX DRIVE GEAR DESTROYED.  RING GEAR WAS AL	SO DAMAGED.  SUSPECT GEAR NOT RETRACTING AFTER START.  STARTER AND RING GEAR REPLACED AIRCRAFT RETURNED TO SERVICE.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111700008	20031117	00008	SO  	2003	11	17	2003FA0001081    	1	20031009	G	2810	U60750002	FUEL CAP        			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320*       	41508	EA  					FUEL CELL	INADEQUATE      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	5852D					224531				FUEL CAP DID NOT VENT.  THE FUEL CAP WAS RETURNED TO MFG AND THEY REPORTED THE CAP TO BE VENTING PROPERLY.  MFG REPLACED	 THE CAP AND THE REPLACEMENT REFUSED TO VENT.  ON THE GROUND THERE APPEARS TO BE ADEQUATE VENTING CLEARANCE BETWEEN THE 	FILLER NECK WASHER AND THE CAP VENT HOLES.  HOWEVER, IN FLIGHT SOMETHING MOVED AND THE FILLER NECK GASKET SEALED THE VEN	T HOLES IN THE FUEL CAP.  IN SOME INSTANCES THE FILLER NECK DOES NOT EXTEND HIGH ENOUGH ABOVE THE TANK AND FILLER NECK W	ASHER TO PREVENT THIS SEALING EFFECT.  SUGGEST MODIFICATION OF THE CAP VENT HOLES TO PREVENT THIS TYPE OF BLOCKAGE.		1	H	7	1 	3O	3	O	 	1A6     	E274				 
2003111400062	20031114	00062	SO  	2003	11	14	2003FA0001082    	2	20031015	G	8530		CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	FAILED          	B				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17							1187			CYLINDER RECEIVED FOR TBO REPAIR.  CYLINDER HEAD IS CRACKED FROM TOP SPARK PLUG BOSS AROUND THE DOME AREA ON THE EXHAUST	 SIDE OF THE HEAD, ALL THE WAY TO THE LOWER SPARK PLUG BOSS. NO EVIDENCE OF COMBUSTION PRODUCTS ON THE OUTSIDE OF THE CY	LINDER HEAD SO CRACK HAS NOT PROGRESSED COMPLETELY THROUGH THE CYLINDER HEAD WALL.  PART IS REJECTED.									3	O			E5CE				 
2003111700007	20031117	00007	CE  	2003	11	17	2003FA0001083    	1	20031017	G	2434		BRUSHES         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ALTERNATOR	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	24336	574  			A146713	17280888	L2878551A	TJ054		ALTERNATOR BRUSHES EXCESSIVELY WORN FOR THE AMOUNT OF TIME ON ALTERNATOR. (3/16 IN.LONG) A NEW BRUSH IS .5 INCH LONG						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003111700016	20031117	00016	CE  	2003	11	17	2003FA0001084    	1	20031015	G	1430		RIVET           	CESSNA      		CESSNA	310   	310         	2074202	CE  	LYC   	O540  	IO540*      	41532	EA  					TORQUE TUBE	LOOSE           	B				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SO	25	244S					35153				THE RIVETS THAT ATTACH THE RUDDER TORQUE TUBE TO THE BELLCRANK ADDAPTOR PLATE BECAME LOOSE. THIS CAUSED THE RUDDER TO DE	FLECT AS MUCH AS FIVE DEGREES FROM ITS PROPER POSSITION.					1	L	7	2 	3O	3	O	RT	3A10    	1E4				 
2003111700017	20031117	00017	CE  	2003	11	17	2003FA0001085    	1	20031015	G	1430		RIVET           	CESSNA      		CESSNA	310   	310         	2074202	CE  	LYC   	O540  	IO540*      	41532	EA  					TORQUE TUBE	LOOSE           	B				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SO	25	244S					35153				THE RIVETS THAT ATTACH THE RUDDER TORQUE TUBE TO THE BELLCRANK ADDAPTOR PLATE BECAME LOOSE. THIS CAUSED THE RUDDER TO DE	FLECT AS MUCH AS FIVE DEGREES FROM ITS PROPER POSSITION.					1	L	7	2 	3O	3	O	RT	3A10    	1E4				 
2003111700025	20031117	00025	SO  	2003	11	17	2003FA0001087    	1	20031009	G	2520	9681400	SEAT            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2D     	41508	EA  	SNSNCH	74D	74DM        	EA  	CABIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	16583	4233 	6    			287325301	L3324227A	K35135		AFTER A PURCHASE OF A/C,  A/C WAS HANGERED AND PREPPED FOR INTERIOR REFURBISH. UPON INSPECTION OF LT AND RT FRONT SEATS 	BEFORE PRIMING AND REPAINTING, CRACKS FROM APPROX. 270 TO 320 DEGREES AROUND WERE DETECTED EXTENDING FROM WELDS AT SUPPO	RT BRACKETS CONNECTING UPPER TUBULARS OF SEAT FRAME. IF LEFT UNDETECTED, THE RT SEAT WOULD HAVE SEPARATED AT FRONT BRACK	ETS (SEAT FRAME SEPARATION) CAUSING FRONT PASSENGER TO FLING BKWD WITHOUT NOTICE.  LT SEAT HAD ONLY ONE CRACK, BUT WOULD	 CAUSE PRESSURE ON (ADJACENT) SEAT FRAME SUPPORT BRACKETS AND POSSIBLE SEPARATION.  GRIND OUT CRACKS AND WELD (TIG OR OX	Y/ACET GAS) BY AUTHORIZED INDIVIDUAL, OR REPLACEMENT OF SEAT FRAMES.	1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003111700026	20031117	00026	SO  	2003	11	17	2003FA0001088    	1	20031009	G	2520	9681400	SEAT            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2D     	41508	EA  	SNSNCH	74D	74DM        	EA  	CABIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	16583	4233 	6    			287325301	L3324227A	K35135		SEATS WERE REMOVED, UNUPHOLSTERED, STRIPPED OF ORIGINAL PAINT FOR REPAINTING. UPON INSP OF LT AND RT FRONT SEATS BEFORE 	PRIMING AND REPAINTING, CRACKS APPROX. 270 TO 320 DEGREES AROUND WERE DETECTED FROM WELDS AT SUPT BRKTS CONNECTING UPPER	 TUBULARS OF SEAT FRAME. RT SEAT WOULD HAVE SEPARATED AT FRONT BRKTS CAUSING FRONT PASSENGER TO FLING BKWD WITHOUT NOTIC	E.  LT SEAT HAD ONLY ONE CRACK, LT UNDETECTED MAY NOT HAVE CAUSED PILOT TO FLING BKWD BUT WOULD CAUSE PRESSURE ON OPPOSI	TE SEAT FRAME SUPPT BRKTS AND WOULD LEAD TO CRACKS.  REPAIR/ GRIND OUT CRACKS AND WELD (TIG OR OXY/ACET GAS) BY AN AUTHO	RIZED INDIVIDUAL, OR REPLACEMENT OF SEAT FRAMES. THESE PARTICULAR CRACKS WERE WELDED AND 337'S PREPARED.  	1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003111400022	20031114	00022	SW  	2003	11	14	2003FA0001089    	1	20031023	G	2571	360036	BOLT            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					BATTERY MOUNT	BURNED          	D				K				NONE                    				B	H	A	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	FLAME/FIRE                	IN	INSP/MAINT     	1			SW	17	9107G					51421				DURING A SCHEDULED INSPECTIOM FOUND PRIMARY ELECTRICAL CABLE, P6D000, IN BATTERY COMPARTMENT TO HAVE A BURNED AREA ADJAC	ENT TO RT BATTERY HOLD DOWN BOLT. MFG, STC SH297NM HAS BEEN INSTALLED ON THIS AIRCRAFT. THE BURNED AREA WAS CAUSED BY HE	AVY CONTACT OF THE PRIMARY ELECTRICAL CABLE WITH THE BATTERY HOLD DOWN BOLT. THERE IS NOT ENOUGH ROOM IN THE BATTERY COM	PARTMENT TO REROUTE THIS CABLE. DAMAGE TO SOME EXTENT ON THIS CABLE IS PREVALENT ON SEVERAL AIRCRAFT ON WHICH THIS STC H	AS BEEN INSTALLED ON. THE DESIGN OF THE BATTERY MOUNTING BRACKET IS THE CAUSE OF DAMAGE TO THE AIRCRAFT WIRING. THIS CON	DITION, IF LEFT UNRESOLVED, COULD RESULT IN SMOKE IN THE CABIN, ELECTRICAL SYSTEM FAILURE, FIRE, OR CAUSE THE BATTERY TO	1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003111300034	20031113	00034		2003	11	13	2003FA0001094    	4	20031009	G	2562	E01	ELT             			CIRRUS	SR    	SR20        	05628AJ	GL  	LYC   	O360  	IO360A1A    	41514	EA  					CABIN	FALSE ACTIVATION	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	213CD					1111				WHEN TRANSMITTING WITH NR 2 GN5430 COM RADIO, ELT IS BEING ACTIVATED, NR 2 COM ANTENNA IS LOCATED DIRECTLY BENEATH ELT L	OCATION.					1	L	7	1 	3O	3	O	NT	A00009CH	1E10				 
2003111700019	20031117	00019		2003	11	17	2003FA0001095    	4	20031009	G	2562	E01	ELT             			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					CABIN	FALSE ACTIVATION	B				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	03	416S					0020				WHEN TRANSMITTING WITH NR 2 GNS 430 COM RADIO ELT IS BEING ACTIVATED (TURNED ON)  NR 2 COM ANTENNA IS LOCATED DIRECTLY B	ENEATH ELT LOCATION.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2003111400031	20031114	00031	NE  	2003	11	14	2003FA0001096    	2	20031008	G	7230	23	MODULE          			SNIAS 	350   	AS350*      	       	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					AXIAL COMPRESSOR	SEIZED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	6088B	705  				2691	9747			PILOT REPORTED; ENGINE WOULD NOT START.  WHEN START BUTTON PUSHED, IGNITERS WOULD FIRE BUT NO NG ROTATION.  STARTER MADE	 AN (THUNK).  VOLTS WERE GOOD, SUBSEQUENT INSPECTION BY MAINTENANCE PERSONNEL DETERMINED THAT THE AXIAL COMPRESSOR HAD S	EIZED.(K)				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003111300072	20031113	00072	SO  	2003	11	13	2003FA0001097    	1	20031023	G	3340	GE4594	LAMP            			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCI3Y	HCI3YR2     	GL  	WING TIP	BURNED OUT      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	489HP					3246121	L2651048A	HK328A		THESE BULBS ARE BURNING OUT AT A RATE OF AT LEAST 50 FLIGHT HOURS AND SOMETIMES AS LOW AS 20 FLIGHT HOURS.  THE PILOT IS	 NOT LEAVING ON ALL THE TIME BUT RATHER ON LANDINGS AND TAKE OFFS.  THE TAXI LIGHT IS LAST NORMAL AMOUNTS OF TIME.					1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P33EA	 
2003111400046	20031114	00046	SO  	2003	11	14	2003FA0001098    	2	20031010	G	8530	641916CP	ROCKER BOSS     			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					NR 3 CYLINDER	FAILED          	C				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	07	45288	2531 	385  			15076825	21370971A			ON APRIL 19, FLYING BACK TO LGU, THE ENGINE SUDDENLY BEGAN VIBRATING AND LOST A LOT OF POWER. COULD NOT MAINTAIN ALTITUD	E, LANDED IN A FIELD.  MECHANIC CAME AND FOUND THAT THE ROCKER BOSSES OF CYL NR 3 HAD FAILED.  INSTALLED AN NEW CYLINDER	 ASSY AND FLEW IT BACK.  WHERE THE OTHER 3 CYLINDERS WERE REPLACED TO PREVENT RECURRENCE.  PALANE WAS UNDAMAGED.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003111400047	20031114	00047	SO  	2003	11	14	2003FA0001100    	2	20030920	G	8520	A35160A2	CONNECTING ROD  			SWFTMS	GC1B  	GC1B        	9230104	SO  	CONT  	C125  	C1252       	17011	SO  					NR 6 CYL	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	3721K					1414	183162			NR 6 CONNECTING ROD OR BEARING FAILED.(K)						1	L	7	1 	3O	3	O	NC	A766    	E236				 
2003111700020	20031117	00020	EA  	2003	11	17	2003FA0001101    	2	20031005	G	8520		ROD             			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					NR 5	DESTROYED       	B			DDER	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			WP	01	57HD	4221 	1187 			P279	L172859			ON FINAL APPROACH, LEFT ENGINE, NR 5 ROD BROKE AND BROKE CRANKCASE.						1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2003111300074	20031113	00074	SO  	2003	11	13	2003FA0001102    	1	20031008	G	7921	20710AR	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	4166H		15   			2843119	RL2584436A			DURING PREFLIGHT PILOT FOUND AN OIL LEAK IN ENGINE COMPARTMENT OF AIRCRAFT.  MAINTENANCE TECHNICIAN FOUND OIL COOLER CRA	CKED ON THE BOTTOM FLANGE AND LEAKING OIL.  THIS IS A WEAK AREA ON THE OIL COOLER.  RECOMMEND FINDING A REPLACEMENT THAT	 IS MORE DURABLE. (K)				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003111400065	20031114	00065	CE  	2003	11	14	2003FA0001104    	1	20031014	G	2751	BZ7RWT80	SWITCH          			CESSNA	340   	340A        	2076405	CE  										FLAP ACTUATOR	FAILED          	D			JQNG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	340FP	2781 				340A0298				AFTER LANDING WHILE TAXING BACK, THE PILOT RETRACTED THE FLAPS.  THE UP MICRO SWITCH FAILED TO STOP THE FLAPS AT THEIR U	P LIMIT.  BOTH CHAINS ATTACHED TO THE FLAP CABLES WERE BROKEN OR DAMAGED.  SEVERAL OPERATING RODS WERE DAMAGED AND A PUL	LEY WAS PULLED OUT OF ITS MOUNT.  IT COULD NOT BE VERIFIED THAT THE MICRO SWITCH HAD AN INTERMITTENT FAILURE.  A PROBABL	E EXPLANATION WAS THE CAM AND UP MICRO SWITCH WERE SLIGHTLY OUT OF RIG ALLOWING THE FLAP GEAR BOX TO OVER RUN.  THIS COU	LD HAVE HAPPENED THRU YEARS TO TWEAKING THE LT SWITCH TO RAISE THE FLAPS FULLY.  WE ARE GOING TO PAY CLOSER ATTENTION TO	 THE FUNCTIONING AND RIGGING OF THE FLAP SYSTEM TO TRY TO KEEP THIS FROM HAPPENING AGAIN. (K)	1	L	7	2 	3O			 	3A25    					 
2003111400024	20031114	00024	SW  	2003	11	14	2003FA0001105    	1	20030927	G	3233	41961000	WORM GEAR       	DUKES       		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	2D34C	B2D34C212   	GL  	ACTUATOR	STRIPPED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	201DP	206  			0515	240065	L1636151A	767357		LANDING GEAR UNLOCKED BUT FAILED TO RETRACT AFTER TAKEOFF.  ATTEMPS TO EXTEND GEAR TO DOWN AND LOCKED ELECTRICALLY AND M	ANUALLY WERE UNSUCCESSFUL.  GEAR COLLAPSED UPON LANDING.  INVESTIGATION REVEALED THAT THE RECENTLY REPLACED WORM AND DRI	VE GEARS INSIDE THE LANDING GEAR ACTUATOR WERE WORN AND STRIPPED.  THE GEARS WERE REMOVED AND CASE TESTED FOR HARDNESS. 	 TEST RESULTS REVELED THAT THE GEARS WERE SOFT AND BELOW MANUFACTURERS SPECS.  SUSPECT GEARS WERE IMPROPER OR NEVER HEAT	 TREATED.  (GL17200303131)  (K)		1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2003111300084	20031113	00084	SO  	2003	11	13	2003FA0001106    	1	20031004	G	3230	633062	TORQUE LINK     			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	432FL					287125219				DURING INSP OF MLG IAW SB 1131, DISCOVERED CRACK IN MLG TORQUE LINK.  FURTHER NDI REVEALED ALL (4) TORQUE LINKS CRACKED 	(PN 633062) EXACTLY AS INDICATED IN FIG 1 OF SC600.  THE TORQUE LINKS WERE NOT BEING INSPECTED IAW AD  BECAUSE THE AD CI	TES PN 6569100 OR 65691002 AS THE ONLY ONES TO BE INSPECTED.  MFG SL600 DIRECTS TORQUE LINKS TO BE INSPECTED BY AC SERIA	L NR AND BY PN (IF) TORQUE LINKS HAVE BEEN REPLACED.  AD DOES NOT COVER THE FULL SPECTRUM OF TORQUE LINKS AS THE SL INTE	NDS TO COVER.  THERE IS A DISPARITY BETWEEN THE AD AND LS AND ALL THE LINKS ARE NOT BEING INSPECTED AS THE SL ORIGINALLY	 INTENDED THEM TO BE.  REVISE AND CLARIFY THE AD.(K)	1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111300044	20031113	00044	EA  	2003	11	13	2003FA0001107    	2	20030930	G	7322	30804	FLOAT           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					CARBURETOR	OBSTRUCTED      	D			VJBS	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	09	5208D	193  			CK814912	17272451	L463476			PILOT DEPARTED HOME AIRPORT FOR INSTRUCTURAL FLIGHT WITH STUDENT.  ON TAKE OFF ROLL AT DESTINATION AIRPORT, ENGINE LOST 	POWER.  INSTRUCTOR LANDED ON PARALLEL RUNWAY WITHOUT INCIDENT.  INSTRUCTOR RESTARTED ENGINE AND PERFORMED RUN-UP SATISFA	CTORY.  A/C WAS INSPECTED WITHOUT ANY DEFECTS NOTED, AND NUMEROUS HIGH SPEED TAXI CHECKS AND TAKE OFF AND LANDINGS PERFO	RMED WITHOUT INCIDENT.  INSTRUCTOR RETURNED AIRCRAFT TO HOME AIRPORT WHERE ON NINTH SEQUENTIAL FLIGHT, ENGINE LOST PARTI	AL POWER.  A/C WAS LANDED AGAIN WITHOUT INCIDENT.  CARBURETOR WAS REMOVED AND DISASSEMBLED.  APPARENT NEW STYLE PLASTIC 	FLOAT WAS FOUND TO BE RUBBING LOWER FUEL BOWL.  THIS CAUSED THE FLOAT TO BIND AND PARTIALLY RESTRICT FUEL FLOW TO ENGINE	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003111700014	20031117	00014	GL  	2003	11	17	2003FA0001108    	1	20031023	G	7602	2276112100	CONTROL CABLE   			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FUEL MIXTURE	BROKEN          	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	03	919AF	430  				C0174				MIXTURE CONTROL CABLE BROKEN AT THE FIREWALL. THIS IS THE FIFTH ONE TO FAIL ALL AT THIS LOCATION. INSPECTION OF THE 28 A	IRCRAFT FLEET REVEALED 16 CABLES WITH A NOTICABLE KINK IN THE CABLE FELT WHEN LEVER IS ACTUATED AND HAND IS WRAPPED AROU	ND THE CABLE FORWARD OF THE FIREWALL.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2003111400040	20031114	00040	SO  	2003	11	14	2003FA0001110    	1	20031003	G	8120	LW38075	BOLT            			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					TURBOCHARGER	MISSING         	B			UXCR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	05	4184X	961  				3257200	L1075561A			THE HARDWARE ATTACHING THE TURBOCHARGER SCAVANGE SUMP TO THE TURBOCHARGER BECAME LOOSE ALLOWING LARGE QUANITY OF OIL TO 	LEAK FROM THE ENGINE OIL SYSTEM.  ONE BOLT WAS MISSING.  A FORCED LANDING WAS NECESSARY.  THIS ENGINE HAD BEEN DISASSEMB	LED, REPAIRED AND REASSEMBLED BY MFG FOR COMPLIANCE WITH AD 2002-19-03, ON 03/17/03 AT 699.6 HOURS.  WE RECOMMEND WING P	AR NR LW-38HO.25.  BOLTS WHICH HAVE DRILLED HEADS AND SECURE WITH LOCKWIRE.(K)			1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003111400029	20031114	00029	EU  	2003	11	14	2003FA0001111    	1	20031015	G	3230	0332204204	RELAY           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	AEIO540D4D5 		EA  					MLG	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	863AF	1044 				85003				FOLLOWING AN EMERGENCY GEAR EXTENSION, PERFORMED DURING A ROUTINE INSPECTION, SYSTEM WOULD NOT OPERATE.  FAULT DETERMINE	D TO BE FAILED RELAY FOR HYDRAULIC CONTROL.  PROBABLE CAUSE, TO MUCH LOAD FOR RELAY.  MANUFACTURER CONTACTED AND MANUFAC	TURER STATED THAT A SB IS UNDER DEVELOPMENT TO REPLACE THIS RELAY.(K)				1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111400055	20031114	00055	SO  	2003	11	14	2003FA0001112    	1	20030923	G	2720	4004009	TORQUE TUBE     			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  					RUDDER	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	33	59752	2687 			311182	317612010	L210368A			SB 1105, RUDDER TORQUE TUBE INSPECTION RUST AND CORROSION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003111700011	20031117	00011	CE  	2003	11	17	2003FA0001113    	1	20031023	G	8120	S19212	CLAMP           			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360*    	17025	SO  					TURBOCHARGER	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	4PF					P3370186	236147R			FRONT ENGINE TURBO EXHAUST STACK RETAINER CLAMP (TURBINE OUTLET LIP) BAND CLAMP PN S19212 STRAP PORTION FRACTURED AND EX	HAUST STACK FELL OFF AIRCRAFT ON TAKEOFF.  CLAMP MAY HAVE BEEN CRACKED, AND IT HAD NOT BEEN DETECTED BEFORE FAILURE OCCU	RRED.  CLOSER VISUAL INSPECTION SHOULD BE INITIATED, DURING ROUTINE INSPECTIONS.  OR PART SHOULD BE REPLACED AT ENGINE O	VERHAUL.(K)			1	H	7	2 	3O	3	O	 	A6CE    	E9CE				 
2003111300061	20031113	00061	SO  	2003	11	13	2003FA0001114    	1	20031008	G	3230	2101203	TUBE            			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					MLG RETRACT	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	7621E	4936 				242168				LANDING GEAR RETRACTION TUBE INBOARD ARM FRACTURED ABOVE THE ATTACHMENT POINTS FOR THE NOSE AND RIGHT MAIN AND NOSE GEAR	 COLLAPSED ON LANDING.  VISUAL INSPECTION OF THE PART INDICATED A PORTION OF THE FRACTURE COULD HAVE OCCURRED AT AN EARL	IER DATE.  CAUSE OF THE FRACTURE UNKNOWN.  THE PART IS VERY DIFFICULT TO INSPECT DUE TO THE LOCATION IN THE AIRFRAME.(K)				1	L	7	1 	3O	3	O	 	1A15    	E295				 
2003111400061	20031114	00061	SO  	2003	11	14	2003FA0001115    	1	20031017	G	3213	78738802	AXLE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					LT MLG	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	03	109GP	10410				287816287				WHILE INVESTIGATING OLEO FLUID LEAK, FOUND (3) .2500 INCH LONG CRACKS RUNNING HORIZONTALLY ACROSS THE OB FACING AREA OF 	THE LT MAIN GEAR STRUT TUBE.  CRACKS LOCATED BETWEEN 7 INCHES AND 9 INCHES UP FROM THE BASE.  CRACKS VISIBLE ONLY UPON C	OMPLETE STRUT EXTENSION WHILE ON JACKS.  THIS HOLLOW TUBE WAS FOUND TO CONTAIN FLUID, SUGGESTING IT HAS BEEN CRACKED FOR	 SOME TIME.  RECOMMEND INSPECTING THIS AREA OF LANDING GEAR ON 100 HOUR INTERVALS, ESPECIALLY ON SCHOOL AIRCRAFT WITH HI	GH CYCLES.(K)		1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111400041	20031114	00041	SO  	2003	11	14	2003FA0001116    	1	20031008	G	8120	557584	COUPLING        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					TURBO OUTLET	MISMANUFACTURED 	B			DINR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	13	65SC					277405445				EXHAUST V-BAND COUPLING NEEDED FOR TURBOCHARGER OUTLET/ TAILPIPE CONNECTION ON THIS AC.  ORIGINAL PN 555-511 WAS SUPERSE	DED BY MFG TO THE PN 557-584 WILL NOT WORK.  THE COUPLING GAP FULLY CLOSED AND BOTTOMED OUT BEFORE ADEQUATE TORQUE WAS R	EACHED.  CONTACTED MFG REP, ENGINEERING AGREED THE PN 557584 IS NOT A VALID REPLACEMENT FOR THE PN 555-511, AND RECOMMEN	DED USE OF THE ORIGINAL COUPLING.(K)			1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2003111400057	20031114	00057	GL  	2003	11	14	2003FA0001117    	3	20030925	G	6114	B65801000	ROLL PIN        			BEECH 	35    	C35BEECH    	1151508	CE  	CONT  	E225  	E2258       	17015	SO  	HARTZL	HCA2V	HCA2V204    	GL  	OIL COLLAR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	5836C	85   				D2788	36303D98R			ROLL PIN BROKE ALLOWING SLIP RING TO MOVE OUT OF POSITION CAUSING A HYDRAULIC LOCK IN PROPELLER OPERATION.  PROPELLER RE	MAINED IN LOW PITCH, HIGH RPM.  REASON FOR PIN FAILURE UNKNOWN.					1	L	7	1 	3O	3	O	 	A777    	E267	5	C	P24EA	 
2003111400058	20031114	00058	EU  	2003	11	14	2003FA0001118    	1	20031017	G	6500	109042401103	BEARING         			AGUSTA	A109  	A109        	0260109	EU  	ALLSN 	250C  	250C28      	03013	GL  					TAIL ROTOR DRIVE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	25RX					7220				DURING ROUTINE DAILY INSPECTION OF HELICOPTER USED IN EMS, MECHANIC NOTICED NR 5 TAIL ROTOR BEARING GREASE SEAL HAD SEPA	RATED FROM BEARING.  FRAGMENTS OF THE PHENOLIC BEARING CAGE WERE MISSING FROM BEARING ASSY.  MECHANIC REPORTED NO EVIDEN	CE OF RESIDUAL GREASE ON ANY OF RECOVERED PARTS.  MM CALLS FOR 1.5 MM OF GREASE EACH 300 HOUR OF OPERATION.  THIS A/C NE	XT 300 HOUR INSPECTION IS DUE IN APPROX. 30 HOURS.  PREVIOUS HISTORY ON TAIL ROTOR BEARINGS INSTALL ON THIS AC CAN INCLU	DE PROBLEMS ASSOCIATED WITH OVER SERVICING OF BEARINGS.  EXCESS GREASE CAUSES INITIAL HIGH HEAT CONDITION AND DEFORMATIO	N OF THE RUBBER GREASE SEAL.  CARE MUST BE TAKEN THAT BEARINGS MUST BE INSTALLED IAW PROCEDURES AS DESCRIBED IN MM.	1	G	7	2 	3U	3	U	 	H7EU    	E1GL				 
2003111700012	20031117	00012	SO  	2003	11	17	2003FA0001119    	2	20030919	G	8530	655771	EXHAUST VALVE   			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					NR 1 CYLINDER	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	732YK	602  				21061879				CYLINDER FAILED COMPRESSION CHECK DUE TO EXHAUST VALVE LEAKAGE.  VISUAL INSPECTION REVEALED BURNED EXHAUST VALVE WITH NO	 SIGNS OF OVER TEMP OR CARBON BUILD UP.  VALVE STEM AND GUIDE WORN BEYOND SERVICE LIMITS.  EXHAUST VALVES IN CYLINDERS 4	 AND 5 EXPERIENCE IDENTICAL FAILURES AT 247 HOURS TOTAL TIME.  PROBABLE CAUSE IS POOR QUALITY CONTROL AT ENGINE BUILD RE	SULTING IN POOR ALIGNMENT BETWEEN VALVE GUIDE AND SEAT.(K)			1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003111300057	20031113	00057	CE  	2003	11	13	2003FA0001120    	1	20030925	G	3230	504501018	TORQUE TUBE     			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	TORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	98692					402B1050	514517LT	891919		DURING A UNSCHEDULED INSPECTION, AFTER A PILOT REPORT OF THE RT LANDING GEAR NOT RETRACTING, THE MECHANIC FOUND THE RT M	AIN GEAR TORQUE TUBE BROKEN OR TORN.  IT IS SUSPECTED THAT FATIGUE COULD BE THE CAUSE.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111300067	20031113	00067	SO  	2003	11	13	2003FA0001121    	2	20030918	G	8520	1986050506	LIFTER          			CESSNA	210   	210B        	2073410	CE  	CONT  	O470  	IO470S      	17026	SO  					ENGINE	DAMAGED         	D			EAVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	9690X					21057990	109344R			DURING A SCHEDULED 50 HOUR OIL CHANGE.  STEEL WAS FOUND IN OIL SCREEN.  SUSPECTED SOURCE OF STEEL WAS COMING FROM LIFTER	S.  INSPECTED NR 5 CYLINDER LIFTERS THROUGH OIL FILLER NECK AND FOUND DAMAGED LIFTERS.  REMOVED LIFTERS FROM ENGINE.  AL	L INTAKE LIFTERS WERE DAMAGED AND 1 CNT. EXHAUST LIFTER WAS DAMAGED.  400 HOURS.  TIME IN SERVICE SINCE NEW FOR BOTH THE	 CAM AND LIFTERS.  ONE YEAR IN SERVICE.			1	H	7	1 	3O	3	O	 	3A21    	3E1				 
2003111400006	20031114	00006	EU  	2003	11	14	2003FA0001123    	1	20031021	G	3260	120A9491105AV	DIODE           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	IO540*      	41532	EA  					MLG	SHORTED         	B			VJ3R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			WP	07	863AF					85003	L2802548A			DURING FLIGHT, WHEN GEAR IS INTRANSIT, HYDRAULIC PRESSURE ANNUNCIATOR LIGHT ILLUMINATES.  CAUSE OF MALFUNCTION IS UNKNOW	N.  NO RECOMMENDATION AT THIS TIME.					1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111400008	20031114	00008	EU  	2003	11	14	2003FA0001124    	1	20031021	G	3260	120A9491105AV	RELAY           			GROB  	120   	G120A       	1660208	EU  	LYC   	O540  	IO540*      	41532	EA  					MLG	SHORTED         	B			VJ3R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			WP	07	863AF	1044 				85003	L2802548A			DURING FLIGHT, GEAR MOTOR WAS SLOW TO EXTEND LANDING GEAR.  FURTHER INVESTIGATION DETERMINED THAT EXTENSION VALVE HAD A 	RESTRICTION IN THE LINE WHICH CAUSED THE LANDING GEAR MOTOR TO REQUIRE MORE CURRENT BECAUSE OF THIS DEMAND IT CAUSED THE	 LANDING GEAR RELAY TO SHORT WHICH ALOUD THE CURRENT TO SPIKE THE RELAY AND DIODE BOARD AND SHORT IT OUT.  RECOMMENDATIO	N IS TO INSTALL A CIRCUIT PROTECTION DEVICE IN LINE BEFORE THE RELAY AND DIODE BOARD.			1	L	7	1 	3O	3	O	RT	A49CE   	1E4				 
2003111400059	20031114	00059	EA  	2003	11	14	2003FA0001125    	2	20031023	G	8520	559E	SCREW           			NAVAL 	N3N   	N3N3        	6120202	EA  	LYC   	R680  	R6809       	41540	EA  					MASTER ROD	LOOSE           	B			RAQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	44848	2623 				4477	4505			SB NR 126, 4/1/46,  HAD NOT BEEN COMPLIED WITH.  KNUCKLE PINS HAD BACKED OUT OF THE MASTER ROD AND HAD BEEN MACHING INTO	 THE CRANKSHAFT.  ENGINE WAS BEING REPAIRED FOR OTHER ISSUES WHEN THIS WAS DISCOVERED.  FAILURE WAS IMMINENT.  (SW152004	02815)(K)				1	Q	7	1 	3R	3	R	 	A2569   	E202				 
2003111400056	20031114	00056	EA  	2003	11	14	2003FA0001126    	2	20031023	G	8520	559E	SCREW           			STNSON	SR8   	SR8E        	8631416	GL  	LYC   	R680  	R68013      	41540	EA  					MASTER ROD	BROKEN          	B			RAQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	17124					9806				SB NR 126, 41.146,  HAD NOT BEEN COMPLIED WITH.  THE SAFETY WIRE LOCKING THE KNUCKLE PIN LOCKPLATE SCREWS HAD BROKEN, AL	LOWING THE KNUCKLE PINS TO BACK OUT OF THE MASTER ROD.  THE TOPS OF THE KNUCKLE PINS WERE MACHING INTO THE CAMSHAFT.  FA	ILURE WAS IMMINENT.  (SW15200402816)(K)				1	H	7	1 	3R	3	R	 	ATC609  	E202				 
2003111300065	20031113	00065	NM  	2003	11	13	2003FA0001127    	1	20031101	G	5711		SPAR CAP        			UNIVAR	415   	415C        	0420302	NM  										RT &  LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	99734	1487 								WHEN PERFORMING INSPECTION REQUIRED BY PARAGRAPH (A)OF AD94-18-04 R1 FOUND SEVERE INTERGRANULAR CORROSION IN BOTH LT AND	 RT LOWER SPAR CAPS. CORROSION WAS LOCATED 6 INCHES FROM INBOARD END OF LOWER SPAR CAP TO 18 INCHES FROM INBOARD END. CO	RROSION HAS PENETRATED THE UPPER SURFACE OF THE SPAR CAPS. THE CORROSION HAS ADVANCED TO EXFOLIATION AND LIFTING OF THE 	SURFACE HAS OCCURRED.  PITTING CORROSION HAS ALSO FOUND ON THE WING SPAR WEB IN THE AREA OF THE CORROSION ON THE SPAR CA	PS.  THE AIRCRAFT IS A 1946 MODEL AND IT APPEARS THAT THE SPARS ARE ORIGINAL.		1	L	7	1 	3O			 	A718    					 
2003111300066	20031113	00066	GL  	2003	11	13	2003FA0001128    	1	20031104	G	2140		DUCT            			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360*       	41514	EA  					HEATER	CHAFED          	P				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	37HY					2037				GROOVES WORN IN ROCKER BOX OIL RETURN TUBE.  AUXILLIARY HEAT AIR DUCT AT LOWER SIDE OF NR 1 CYL WAS RUBBING ON OIL RETUR	N TUBE.  GROOVES APPEARED TO BE 30 PERCENT TO 50 PERCENT THROUGH TUBE.  AIRPLANE WAS 2.2 HOURS TIME IN SERVICE AFTER ANN	UAL / 100 HOUR INSPECTION.  HEAT DUCT HAS TO BE CRUSHED TO FIT THIS INSTALLATION.  THERE IS INADEQUATE ISOLATION BETWEEN	 DUCT AND ENGINE CYLINDER LUBRICATING OIL RETURN TUBE.			1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2003111300075	20031113	00075	SO  	2003	11	13	2003FA0001129    	1	20031031	G	2730	MS21260S4LH	TURNBUCKLE      			PIPER 	PA32  	PA32RT300T  	7103216	SO  										ELEVATOR CABLE	CORRODED        	G				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			SO	05	39541	2633 				32R7887104				PILOT DEPARTED SMALL AIRPORT AND CLIMBED TO 1000 FT.   WHEN THE PILOT LEVELED HIS ALTITUDE, HE REALIZED THAT HE HAD LOST	 MOST ALL OF HIS ELEVATOR CONTROL.   HE PERFORMED EMERGENCY LANDING USING ELEVATOR TRIM.   UPON INVESTIGATION, FOUND THA	T A TURNBUCKLE IN AN ELEVATOR CONTROL CABLE HAD BROKEN.  THE BREAK WAS DUE TO CORROSION LOCATED BELOW THE SAFETY WIRE WR	APS. OTHER TURNBUCKLES IN THE AREA (APPROX 1 FT) WERE NOT CORRODED.  IT IS BELIEVED THAT A VENTILATION HOSE THAT WAS DIR	ECTLY ABOVE THE AFFECTED TURNBUCKLE CONTRIBUTED TO THE CORROSION BY ALLOWING CONDENSATION TO DRIP DOWN ONTO THE TURNBUCK	LE.	1	L	7	1 	3O			 	A3SO    					 
2003111300078	20031113	00078	CE  	2003	11	13	2003FA0001130    	1	20031022	G	5553	04311481	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					LT REAR FIN	CRACKED         	B			BGSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	47281	7240 				15283208				FOUND LT REAR VERTICAL FIN BRACKET CRACKED AT BASE (FITTING).						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003111300038	20031113	00038	EA  	2003	11	13	2003FA0001131    	2	20031010	G	8530	SL32000WA20P	CYLINDER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1A100	1A100*      	GL  	ENGINE	DAMAGED         	B			WW3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	5227D					17272458	L1005139A			CYLINDERS FAIL TO PASS DIFFERENTIAL COMPRESSION TEST.  NR 3 POSITION.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P918	 
2003111300079	20031113	00079	SO  	2003	11	13	2003FA0001132    	1	20031028	G	5510		CLEVIS BOLT     			PIPER 	PA36  	PA36285     	7103610	SO  	CONT  	6285  	6285A       	17038	SO  					STAB STRUT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	9942P					367560053				THE UPPER HORIZONTAL STABILIZER STRUT CLEVIS BOLT BROKE.  THE BREAK WAS IN THE THREADED SECTION.  THE AIRCRAFT TT IS 599	8 HRS. THE SAME TIME IN SERVICE FOR THIS CLEVIS BOLT.  THIS IS THE SECOND TIME HAVE FOUND A CLEVIS BOLT BROKEN IN THIS L	OCATION, ON THIS MODEL AIRCRAFT.  THIS LOCATION IS NORMALLY SO CONTAMINATED THAT A NORMAL, VISUAL INSPECTION IS NOT PRAC	TICAL.  EVEN WITH A THOROUGH CLEANING THE BREAK MIGHT NOT HAVE BEEN DETECTED.  THE BREAK HAD RUST IN A PARTIAL BREAK BEF	ORE THE FINAL FAILURE.  SUGGEST FREQUENT AND THOROUGH INSPECTIONS OR A REDESIGNED CLEVIS BOLT FOR THIS LOCATION.		1	L	7	1 	3O	3	O	 	A10SO   	E12CE				 
2003111300080	20031113	00080	NE  	2003	11	13	2003FA0001133    	2	20031023	G	7230	70BM035420	GAS GENERATOR   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	NOISY           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	853HW	6340 	521  			2741				RUBBING NOISE AFTER SHUT DOWN.  ONLY WHEN ENGINE IS HOT.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003111300051	20031113	00051	EA  	2003	11	13	2003FA0001134    	2	20031024	G	7314	200F5003	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 2 ENGINE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	05	350PC		362  			318152006	L200868A			FUEL LEAKING AT REGULATOR HOUSING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003111300055	20031113	00055	NE  	2003	11	13	2003FA0001135    	2	20031024	G	7314	200F5002	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2B   	 	NE  					NR 1 ENGINE	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	3581C					318052091	L179061A			FUEL LEAKING AT REGULATOR HOUSING, THIS IS THE NEW STYLE PUMP, AND IS NOT YET AFFECTED BY AD 2003-14-03.  WE ARE NOTING 	SIMILAR LEAKS WITH SEVERAL OF THESE PUMPS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003111400026	20031114	00026	CE  	2003	11	14	2003FA0001136    	1	20030901	G	3240		CALIPER         			CESSNA	337   	337D        	2075717	CE  	CONT  	IO360 	IO360*      	17025	CE  					MLG BRAKE	CRACKED         	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	13	85965					3371037				AIRCRAFT BEGAN TO SHAKE WHILE TAXIING, FELT LIKE SOMEONE WAS TAPPING ON THE RIGHT BRAKE PEDAL.  FLANGE AT THE BEAD CRACK	ED (ABOUT 5 INCHES LONG) AND WAS CATCHING ON BRAKE CALIPER.  NO KNOWN HARD LANDINGS.  POSSIBLE CAUSE:  WHEEL TOO SMALL F	OR AIRCRAFT.  CORROSION AND STRESS FROM 8 PLY TIRE AND 55 PSI AIR PRESSURE.  SAVING THE PART.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2003111300062	20031113	00062	CE  	2003	11	13	2003FA0001137    	1	20031101	G	5270		WARNING LIGHT   			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					CARGO DOOR	ILLUMINATED     	D				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			GL	15	93S					7500189				WHILE AT CRUISE ALTITUDE, THE CREW NOTED BAGGAGE DOOR SEAL ON LIGHT.  CREW BEGAN MAKING PREPARATIONS TO DESCEND TO A LOW	ER ALTITUDE AS REQUIRED BY AFM INSTRUCTIONS WHEN THE LIGHT (BAGGAGE DOOR SEAL) WENT OUT.  INFORMED  MFG TECH SUPPORT.  W	AITING RESOLVE.				2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2003111400035	20031114	00035	CE  	2003	11	14	2003FA0001138    	1	20031023	G	5610	4556100001V11001	WINDSHIELD      			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	FAILED          	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			GL	11	858MK	822  				141				CLIMBING THRU FL350, PILOTS WINDSHIELD SHATTERED.  OUTER GLASS LAYER SHATTERED.  822.0 HTT / 564 CYCLES (K)						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2003111300052	20031113	00052	EA  	2003	11	13	2003FA0001139    	1	20031008	G	1430		RIVET           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A60A     	52043	NE  					LOWER SPAR CAP	MISINSTALLED    	B				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	23	886EA	15319				756				SMOKING RIVETS OBSERVED AT WS122-140 PROX DURING SCHEDULED INSPECTION.  THESE RIVETS ARE CRITICAL TO WING INTEGRITY.  IT	 APPEARS THAT THE RIVETS DID NOT PROPERLY ENGAGE THE HOLE DURING OEM INSTALLATION.  SUGGEST ALL WING BOXES WITHIN 10 SER	IAL NUMBER RANGE BE CLOSELY INSPECTED FOR SAME.(K)				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2003111400036	20031114	00036	CE  	2003	11	14	2003FA0001140    	1	20031006	G	5520	05130633	BRACKET         			CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300D       	17022	SO  					ELEV BELLCRANK	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	61LV	3500 				17253899				BADLY BROKEN BRACKET WAS HELD IN PLACE BY ONLY TWO RIVETS.  TOTAL LOSS OF ELEVATOR WOULD HAVE BEEN FORTHCOMING HAD BRACK	ET NOT BEEN REPLACED.  THIS WAS DIFFICULT TO DETECT BECAUSE CONTROL FUNCTION WAS NORMAL AND IS DIFFICULT TO VIEW (BEING 	BELOW THE FLOOR).  IN ORDER TO DETECT THE PROBLEM.  ONE MUST PUT IN THE CONTROL LOCK AND CHECK ELEVATOR FOR MOVEMENT.  (	MORE THAN TWO INCHES INDICATES THE PROBLEM).  REPLACEMENT PART (05130633) IS MUCH STRONGER THAN THE ORIGINAL PART.(K)			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2003111300046	20031113	00046	SO  	2003	11	13	2003FA0001143    	1	20030909	G	3220	67054008	TRUNNION        			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG	CRACKED         	B			BJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	720KM	203  				3257300				DURING AN ANNUAL INSPECTION THE NOSE TRUNION WAS FOUND TO HAVE A CRACK APPROXIMATELY ONE INCH IN LENGTH ON THE AFT SIDE.	  GREASE WAS SEEPING FROM THE CRACK WHICH MADE IT EASILY VISIBLE.  THE CRACKED NOSE TRUNNION ASSEMBLY WAS REMOVED AND RE	PLACED WITH A NEW TRUNNION ASSEMBLY.  AT THE TIME THE CACK WAS FOUND THE AIRCRAFT HAD 203.6 TT.  THE TRUNNION HAD NOT PR	EVIOUSLY BEEN REPLACED ON THIS AIRCRAFT.			1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003111700018	20031117	00018		2003	11	17	2003FA0001144    	4	20030609	G	8300	29A21372	DRIVE ASSY      			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					ACCESSORY CASE	LEAKING         	B			BJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	15	720KM	104  				3257300	L1131061A			OIL WAS FOUND SEEPING FROM THE TURBO SCAVENGE DRIVE ASSEMBLY.  IF THE OIL WAS WIPED FROM THE PUMP IT WOULD RETURN AFTER 	JUST ONE SHORT FLIGHT.  THE OIL WAS SEEPING FROM THE SEAM WHERE BOTH HALVES OF THE DRIVE ASSEMBLY MEET.  THIS PUMP WAS R	EPLACED 22.1 HOURS PRIOR TO THIS INCIDENT FOR THE SAME REASONS.  THE DRIVE ASSEMBLY WAS REMOVED AND REPLACED WITH A NEW 	DRIVE ASSEMBLY OF THE SAME PART NUMBER.(K)			1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003111300047	20031113	00047		2003	11	13	2003FA0001145    	4	20030128	G	8300	29A21372	DRIVE SYSTEM    			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					TURBO SCAV	LEAKING         	B			BJ3R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	15	720KM	82   				3257300	L1131061A			OIL WAS FOUND SEEPING FROM THE TURBO SCAVENGE DRIVE ASSEMBLY.  IT THE OIL WAS WIPED FROM THE PUMP IT WOULD RETURN AFTER 	JUST ONE SHORT FLIGHT.  THE OIL WAS SEEPING FROM THE SEAM WHERE BOTH HALVES OF THE DRIVE ASSEMBLY MEET.  THE DRIVE ASSEM	BLY WAS REMOVED AND REPLACED WITH A NEW DRIVE ASSY.				1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003111400017	20031114	00017	SO  	2003	11	14	2003FA0001146    	1	20030929	G	8010		DRIVE GEAR      			AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	O360A4K     	41514	EA  					STARTER	INOPERATIVE     	B			IG8R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	940TE	14   				10219				WHILE ATTEMPTING TO START THE ENGINE, THE STARTER WOULD SPIN BUT WOULD NOT TURN THE ENGINE.  THE ENGINE COWL WAS REMOVED	 AND IT WAS DETERMINED THAT THE STARTER DRIVE GEAR WOULD ENGAGE THE STARTER RING GEAR BUT WOULD NOT TURN.  THE STARTER S	HAFT WOULD ROTATE INSIDE THE STARTER DRIVE GEAR.  THE STARTER WAS REMOVED AND RETURNED FOR REPAIR.(K)				1	L	7	1 	3O	3	O	NT	1L71    	E286				 
2003111400043	20031114	00043	SO  	2003	11	14	2003FA0001147    	2	20031024	G	8530		EXHAUST VALVE   			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 4 CYLINDER	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	19	421ML					421C0880	604330			DURING FLIGHT .33 OF THE EXHAUST VALVE IN THE NR 4 CYLINDER BROKE CAUSING EXTENSIVE DAMAGE TO THE PISTON AND THE CYLINDE	R HEAD.  DURING THE HIDDEN DAMAGE INSPECTION THE BROKEN VALVE WAS FOUND IN THE INTAKE PORT OF THE CYLINDER ON THE SAME C	YLINDER.  NO DAMAGE WAS FOUND IN THE REMAINING CYLINDERS OF THE TURBO CHARGER ON THE ENGINE.  NO DEFECTS NOTED IN THE OI	L FILTER.			1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2003111400066	20031114	00066	CE  	2003	11	14	2003FA0001152    	1	20031103	G	2912	206666500	SCREEN          			CESSNA	525   	525A        	2076615	CE  										HYD SYSTEM	MISSING         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	20GP	300  				525A0131				WHILE PERFORMING INSPECTION FOUND THAT IN-LINE HYDRAULIC FILTER SCREENS WERE NOT INSTALLED.  THIS IS THE SECOND OF THESE	 TYPE NEW AIRCRAFT WE HAVE FOUND MISSING THESE FILTERS SCREENS.  ORDERED FILTER SCREENS AND INSTALLED.  NOTIFIED MANUFAC	TURER THAT THESE SCREENS ARE NOT BEING INSTALLED AT THE FACTORY ON SOME AIRCRAFT.  RECOMMEND CONFIRMING THESE PART NUMBE	R HYDRAULIC SCREENS ARE INSTALLED ON NEW AIRCRAFT AT FIRST AVAILABLE INSPECTION.			1	L	7	1 	4F			RT	A1WI    					 
2003111700023	20031117	00023	WP  	2003	11	17	2003FA0001154    	2	20031104	G	7397		WIRE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					NR 2 ENGINE	LOOSE           	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	44TT	13735	640  			211	P74624C			AC WAS TAKING OFF WHEN RT FUEL COMPUTER LIGHT CAME ON AT APPROX 100 KNOTS.  PILOT ABORTED TAKE OFF. DURING TAXI BACK TO 	FBO NR 3 AND NR 4 MLG WHEEL FUSIBLE PLUGS BLEW DUE TO OVERHEATED BRAKES.  MECH INSTALLED A SPARE WHEEL AND TIRE ASSY ON 	RT MLG SO THAT AC COULD BE MOVED OFF OF TAXIWAY.  MAINT WAS DISPATCHED TO DETERMINE CAUSE OF ENG COMPUTER PROBLEM, CHANG	E NR 3, NR 4 BRAKES, WHEEL AND TIRE ASSEMBLIES. MAINT DETERMINED THAT FUEL COMPUTER LIGHT WAS CAUSED BY LOOSE WIRE TO RT	 ENGINE PT2 PROBE CONNECTOR LOCATED AT NAC.STA. 188.5 NAC. BL 100.0.  NO ANTI-SKID MALFUNCTION WAS NOTED.  AC RETURNED W	ITH NO FURTHER INCIDENTS.	2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2003111400001	20031114	00001	CE  	2003	11	14	2003FA0001156    	1	20030711	G	8011	30B3749BT	STARTER         			LEAR  	25    	25D         	5170514	CE  	GE    	CJ610 	CJ6106      	30006	NE  					ENGINE	VIBRATION       	G				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SO	17	99NJ		333  			220				WHILE IN CRUISE FLIGHT AT 370, THE FLIGHT CREW HEARD TWO FLUTTERING VIBRATION SOUNDS.  THE VIBRATION NOISES BECAME LOUDE	R AND LOUDER.  ADJUSTING THE THROTTLE ISOLATED THE VIBRATION TO THE NR 1 ENGINE.  THE PILOTS DESCENDED TO FL 250 AND SHU	T DOWN THE NR 1 ENGINE.  A SINGLE ENGINE APPROACH AND LANDING WAS MADE AT FORT LAUDERDALE INTERNATIONAL AIRPORT.  THE MA	INTENANCE DEPT TROUBLE SHOT AND DISCOVERED THAT THE NR 1 ENGINE STARTER GENERATOR HAD FAILED AND WAS THE SOURCE OF THE V	IBRATION.  THE STARTER GENERATOR WAS REPLACED AND OPERATIONALLY CHECKED AND THE AIRCRAFT WAS RETURNED TO SERVICE.		2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2003111400004	20031114	00004	SW  	2003	11	14	2003FA0001157    	1	20031101	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A65*        	17003	SO  					LT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	84670	6517 				7AC3381				ANNUAL INSPECTION.  PERFORMED AD2001-25-02R1.  NOTED CRACK ON LEFT/AFT WING SPAR.  CRACK IS ON WOOD SPAR OUTBOARD OF LIF	T STRUT ATTACH POINT.  AIRCRAFT TT 6517.08.  SPAR ORIGIN UNKNOWN.  NOTED PREVIOUS SPAR REPAIR IN DIFFERENT LOCATION DATE	D 1979.  RECOMMEND ALL APPLICABLE AIRCRAFT SPARS BE INSPECTED AS ALREADY REQUIRED BY AD.				1	H	7	1 	3O	3	O	 	A759    	E205				 
2003111400002	20031114	00002		2003	11	14	2003FA0001158    	4	20031028	G	3400	701887903014	COMPUTER        			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					COCKPIT	FAILED          	C				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	17	80A					1348				FAILED OUT OF STOCK FROM MANUFACTURER. CAUSED FMS NR 1 TO LOCKUP.  MANY DEAD KEYS ON FMS KEYBOARD.						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003111700021	20031117	00021	SO  	2003	11	17	2003FA0001159    	1	20031029	G	7500	523030	INDICATOR       			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					BLEED AIR	MISREPAIRED     	C				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	17	80J					441				EVERYTIME WE HAVE SENT ONE OF THESE UNITS TO THE MANUFACTURER, WE RECEIVE IT BACK IN AN UNSATISFACTORY WORKING CONDITION	.  THIS UNIT HAS A CABIN RATE OF CLIMB OF +50, SITTING ON THE GROUND WITH NO AIR APPLIED.(K)					2	L	7	2 	4F	4	F	 	A12EA   	E2EU				 
2003111700001	20031117	00001	CE  	2003	11	17	2003FA0001160    	1	20031027	G	2121	MB3BA1	MOTOR           			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BLOWER	BURNED OUT      	B			EYDR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	260BS		1092 			S5500080				ON 10/25/03 AT APPROXIMATELY 2200Z THE AIRCRAFT DEPARTED ITH FOR PVD WITH 2 CREW AND 5 PASSENGERS.  ON CLIMB FROM 10,000	 TO FL 190 THE FLIGHT CREW SMELLED SMOKE.  AT FIRST NO SMOKE WAS EVIDENT IN THE CABIN, THEN LIGHT SMOKE WAS DECLARED AND	 AN UNEVENTFUL LANDING WAS MADE AT HGA EIGHT MINUTES LATER.  MAINTENANCE TROUBLESHOT THE PROBLEM TO A DEFECTIVE CABIN OV	ERHEAD BLOWER ASSEMBLY.  THE MOTOR SMELLED BURNED, BUT DID NOT SHOW AND EVIDENCE OF FIRE DAMAGE.  THE 20 AMP CABIN FAN C	IRCUIT BREAKER DID NOT POP.  THE OVERHEAD BLOWER WAS MEL`D AND THE AIRCRAFT WAS RELEASED.  MFG RECOMMENDS 1200 HR OH PER	IOD FOR THIS BLOWER MOTOR. MTR HAD APPROX 1100 HRS, REDUCE OH TIME TO 1000 HOURS.(K)	1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2003111700002	20031117	00002		2003	11	17	2003FA0001161    	4	20031031	G	2210	6225734002	SERVO           			BEECH 	B300  	B300        	1159232	CE  										AILERON	BINDING         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	447TF	166  				FL364				INVESTIGATED PILOT COMPLAINT OF AILERON CONTROLS BINDING.  NOTED BINDING/BANGING TYPE SOUNDS UNDER CENTER CABIN FLOOR.  	FOUND NOISES AND BINDING NOT PRESENT WITH AILERON SERVO REMOVED FROM CAPSTAN, RETURNED WHEN AILERON SERVO REINSTALLED.  	ALSO NOTED  NOISES/BINDING NOT NOTICEABLE WITH SERVO LOOSELY FIT, NOISES/BINDING RETURNED WHEN SERVO SECURED TO CAPSTAN.	  REPLACED SERVO WITH OVERHAULED EXCHANGE UNIT, OPERATIONAL CHECKS SATISFACTORY.			2	L	7	2 	4T			RT	A24CE   					 
2003111700003	20031117	00003	CE  	2003	11	17	2003FA0001162    	1	20031107	G	3260	P634005	SWITCH          			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT MLG	INTERMITTENT    	D			RMMR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	4894C					21063658				CONDITION OCCURRED APPROX 3 TIMES UNTIL OPERATOR WOULD NOT FLY UNTIL REPAIRED.  AFTER RUN UP A LT TURN WAS NEGOTIATED, D	OWN INDICATOR LIGHT WENT (OUT) AND HORN SOUNDED.  MAINT DID INITIAL CHECK FOR BROKEN WIRES.  SUPPORTED AC, POWER APPLIED	, SHORT RUN OF GEAR PUMP & LIGHT (ON) NO HORN.  PROBLEM COULD NOT DUPLICATED. SEVERAL FLTS AND SAME FAULT WITH SAME RESU	LT.  TROUBLESHOOTING; EACH GEAR DOWN SWITCH REMOVED FROM BRKT, HAND OPERATED SEVERAL TIMES REINSTALLED.  FINAL RESULT, K	ICKING VIBRATION ON ALL GEAR (TIRES) AC ON JACKS, SQUAT SWITCH OUT OF BRACKET, RT GEAR DOWN SWITCH DUPLICATED FAULT.  RE	PLACED SWITCH, ADJUSTED, GEAR CYCLED SEVERAL TIMES, AC RETURNED TO SERVICE.	1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003111700004	20031117	00004	NE  	2003	11	17	2003FA0001163    	2	20031024	G	7230	3476	MODULE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					AXIAL COMPRESSOR	SEIZED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	6093K	1994 	23   			2709	9564			ON 17, OCT. 2003, FIRST START OF THE DAY, PILOT REPORTED ENGINE WOULD NOT START.  SUBSEQUENT INSPECTION REVEALED THAT AX	IAL COMPRESSOR WAS SEIZED.  ONLY WITH GREAT EFFORT COULD THE AXIAL COMPRESSOR BE TURNED BY HAND.  ENGINE WAS REMOVED FOR	 RETURNED TO FACILITY WHERE EVALUATION AND REPAIRS ARE TO BE ACCOMPLISHED.  MODULES 02/03 WERE INSTALLED, 24 SEPT, 2003.	  TT SINCE REPAIR WAS 23.1 HOURS.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003123000003	20031230	00003	SW  	2003	12	30	2003FA0001164    	1	20031002	G	3233	B10076	SHAFT           	DUKES       		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MLG ACTUATOR	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	201MX	94   				240266				SET OF SUBJECT GEARS WERE INSTALLED AT 4280.14 TT.  OWNER CALLED AND WAS HAVING PROBLEM WITH ACTUATOR NOT SHOWING DOWN A	ND LOCKED. TOLD HIM NOT TO FLY THE AC AND TO BRING THE ACTUATOR.   DISASSEMBLED  ACTUATOR, FOUND WORN GEAR, PN B100-76 T	O BE SO WORN THAT PINION GEAR WOULD NOT ENGAGE WORN GEAR.  ONE MORE OPERATION AND GEAR WOULD HAVE PROBABLY COLLAPSED.  T	HERE HAVE BEEN NO GEAR KITS AVAILABLE FROM MFG NOR HAS THERE BEEN ANY ACTION TO MAKE OWNER AWARE OF PROBLEM OF GEARS THA	T WERE SOLD BUT HAD NOT BEEN CARBURIZED.  SOFT GEARS EFFECT EVERY MODEL THAT USES THESE ACTUATORS BUT IT HAS HAD MOST SE	VERE EFFECT ON THIS AC.  MGF CHANGED GEAR RATIO IN THOSE ACTUATORS, CAUSING THEM TO WEAR OUT FASTER.	1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2003123000002	20031230	00002	SO  	2003	12	30	2003FA0001165    	1	20031117	G	3230	67042013	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  	HARTZL	HCC2Y	HCC2YF2     	GL  	RT MLG	BROKEN          	B				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SO	15	926ER	4911 	43   			4496016				ON LANDING, THE RT LANDING GEAR DOWN LIGHT FLICKERED. THE CREW OPTED TO SHUT DOWN ONCE OFF THE RUNWAY AND MAKE A VISUAL 	INSPECTION OF THE LANDING GEAR. THEY NOTICED THAT THE RMG WAS AT AN ODD ANGLE AND CALLED MAINTENANCE. THE MAINTENANCE CR	EW FOUND THAT THE AFT TRUNION (P/N-67042-013) WAS BROKEN IN SEVERAL LOCATIONS. ALL FLEET AIRCRAFT WERE GROUNDED AND WILL	 HAVE NEW PARTS INSTALLED.			1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920	 
2003123000096	20031230	00096	CE  	2003	12	30	2003FA0001166    	1	20031016	G	7930	53001081617	LINE            			CESSNA	340   	340CESSNA   	2076404	CE  										OIL SYSTEM	CORRODED        	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	03	69507	5534 				3400344				2 TO 3 DAYS AFTER FLIGHT, NOTICED SIGNIFICANT OIL PUDDLE FORMED UNDER FUSELAGE AT THE MAIN CABIN DOOR STATION.  UPON VIS	UAL INSPECTION, LOCATED LEAK IN FLOOR AT STATION UNDER PILOT AND CO-PILOT'S SEATS.  THE SOURCE OF THE LEAK WAS BOTH THE 	RIGHT AND LEFT OIL PRESSURE INDICATOR SUPPLY LINES (HARD LINES) BEING CORRODED AND CRACKED AS A RESULT OF LAYING AGAINST	 A CABIN AIR SCAT HOSE AS THEY WERE ROUTED IN THE BUNDLE.  THE LINES ARE APPROXIMATELY 5 FEET IN LENGTH.  APPROXIMATELY 	.5 TO .75 QUARTS OF OIL WERE REMOVED FROM THE FLOOR SECTION ADJACENT TO THE SEAT PEDESTALS.		1	L	7	2 	3O			 	3A25    					 
2003123000017	20031230	00017	EA  	2003	12	30	2003FA0001167    	2	20031028	G	8520	14H21950	OIL RING        			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					NR 3 CYLINDER	BROKEN          	B			FZPR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	11	923DH	1136 				243368	L2671551A			AIRCRAFT WAS IN FLIGHT WHEN THE PILOT NOTICED HIGH CHT TEMPS AND LOW EGT TEMPS ON NR 3 CYLINDER ON HIS JPI ENGINE ANALYZ	ER.  HE THEN NOTICED HIS OIL TEMP GO UP AND AS THE OIL PRESSURE DROPPED THE OIL TEMP THEN BEGAN TO DROP OFF.  HE THEN PU	LLED THE POWER OFF AND LANDED THE AIRCRAFT.  2-3 QUARTS OF OIL WERE STILL REMAINING IN THE ENGINE.  COMPRESSION CHECKS W	ERE NORMAL BUT NR 3 CYLINDER WAS REMOVED TO FIND THE OIL CONTROL RING PN 14H21950 TO BE BROKEN AND SEIZED INTO THE PISTO	N.  COMPRESSION RINGS WERE STILL INTACT.  CONNECTING ROD BUSHINGS WERE FINE, VISUAL INSPECTION OF INSIDE OF ENGINE ACCES	SIBLE THROUGH THE REMOVED CYLINDER OPENING APPEARED NORMAL.	1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2003123000030	20031230	00030	EA  	2003	12	30	2003FA0001168    	2	20031101	G	8520	77450	CONNECTING ROD  			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ENGINE	BROKEN          	B			AHRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	201SL					240191	L1703751AC			IT APPEARED NR 3 CONNECTING ROD FAILED DUE TO OIL STARVATION, CAUSING ROD TO BREAK AT CAP.  THE ROD THEN HIT CRANKCASE C	AUSING A HOLE IN CRANKCASE AND CAUSED THE CRANKSHAFT TO SEIZE.  WHILE REMOVING ENGINE FROM AIRCRAFT, DRAINED 2 QTS OF OI	L OUT OF OIL PAN.				1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2003123000027	20031230	00027	EA  	2003	12	30	2003FA0001169    	2	20031013	G	8500	61261516	STUD            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE CASE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	3386E					17271526	L818376T			STUD BROKEN AT CENTER, CAUSE UNKNOWN.  NO RECOMMENDATIONS.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003123000042	20031230	00042	SW  	2003	12	30	2003FA0001170    	1	20031104	G	3213		HOUSING         			GULSTM	114   	114B        	O145001	SW  	LYC   	O540  	IO540*      	41532	EA  					MLG STRUT	CORRODED        	B			SL5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	6048B	244  				14676				DURING NORMAL INSPECTION, HEAVY CORROSION WAS FOUND ON BOTH MAIN LANDING GEAR HOUSING`S UNDER AND AROUND CLAMPS SECURING	 LANDING LIGHTS AND HYDRAULIC HOSES AND TUBES.  REMOUND CLAMPS FOUND CLAMP WHERE INSTALLED PRIOR TO FINAL PAINT WITH NO 	PRIMER OR ANY CORROSION PROTECTION, CLAMPS ARE STAINLESS STEEL HOUSINGS ARE ALUMINUM.  REMOVE CLAMP AND PRIMED AND PAINT	 BETWEEN SURFACES.  NOTE: CKD SECOND AC, BOTH MAIN GEAR HOUSINGS HAVE SAME CORROSION.			1	L	7	1 	3O	3	O	RT	A12SO   	1E4				 
2003123000044	20031230	00044	SW  	2003	12	30	2003FA0001171    	1	20031104	G	3233	97200M488372C3	ACTUATOR        			GULSTM	114   	114B        	O145001	SW  	LYC   	O540  	IO540*      	41532	EA  					RT MLG	FROZEN          	B			SL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	6048B	244  				14676				DURING NORMAL INSPECTION, CYCLED LANDING GEAR.  HEARD A SQUEAL FOLLOWED BY APOP FROM THE RT MAIN LANDING GEAR, FOUND THA	T THE LANDING GEAR HYD ACTUATOR ATTACH BEARING WAS FROZEN CAUSING THE ACTUATOR HOUSINGS AROUND THE BEARING TO BREAK AND 	PULL APART.  DURING THE RETRACTION CYCLE.  RECOMMEND: INSPECTION AND LUBEING THESE AREAS AT MORE FREQUENT INTERVALS (AT 	OIL CHANGES).  NOTE:  INSPECTED LT SIDE, BEARING WAS GOOD.  INSPECTED A SECOND AC FOUND BOTH MAIN GEAR ACTUATOR BEARINGS	 FROZEN, LUBED AND WORKED FREE.		1	L	7	1 	3O	3	O	RT	A12SO   	1E4				 
2003123000093	20031230	00093	SO  	2003	12	30	2003FA0001172    	1	20031110	G	7714	SL76121	DRIVE SHAFT     			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					TACHOMETER	LOOSE           	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	9557C	2    				287816492	L798039A			THE PRESSED IN SLEEVE THAT DRIVES THE TACH CABLE CAME LOOSE AND SPINS IN THE TACH SHAFT.  RESULTS IS NO TACH INDICATION.	  SLEEVE TOO SMALL OR TACH SHAFT BORED OUT TOO MUCH, CAUSING INSUFICENT PINCH ON ASSEMBLY.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003123000043	20031230	00043	EA  	2003	12	30	2003FA0001173    	2	20031027	G	8530	72877	TAPPET          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE CYLINDER	BROKEN          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	4237D		380  			317305055	L868161A			TAPPET BODY SEPARATED AND CAUSED ENGINE TO BECOME CONTAMINATED WITH METAL.  THIS WAS RECONDITIONED TAPPET BODY.  HAVE BE	EN USING THESE TAPPETS FOR ALMOST 20 YEARS AND THIS IS THE FIRST ONE THAT HAVE HAD TO BREAK.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003123000032	20031230	00032	GL  	2003	12	30	2003FA0001174    	1	20030724	G	3510	3891350170	LINE            			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A110	 	NE  					MANIFOLD	RUPTURED        	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17	324SM	1461 	1461 			9023				OXYGEN LINE CONNECTING NR 3 CYL TO AC OXYGEN PRESS PLUMBING RUPTURED AT SWEDGE WHILE OTHER MAINT WAS BEING PERFORMED.  A	LL 4 OXYGEN CYL WERE SELECTED TO OFF BEFORE COMPLETE DEPLETION OCCURRED. AS PRECAUTION ALL REMAINING ORIGINAL PRESSURIZE	D OXYGEN SUPPLY LINES BETWEEN OXYGEN CYL AND THE OXYGEN SYS CONT PANEL WERE REPLACED WITH NEW LINES IAW AMM. ALL LINES R	EPLACED WERE VISUALLY INSP. NOTED THAT ONE OF THESE LINES HAD BEGAN TO DEVELOP BLISTER AT ONE OF CONNECTORS. A MFG ENGIN	EER WORKING THIS ISSUE REPORTED THAT LINE WITH THE BLISTER FAILED (RUPTURED) AT APPROX HALF OF THE CERTIFIED PSI RATING.	  RUPTURE OF ANY ONE OF THESE LINES ALLOW UNCONTROLLED RELEASE OF ENTIRE OXYGEN SUPPLY INTO HIGHLY ELECTRONIC ENVIRMT.	2	L	7	2 	4F	4	F	RT	T00003NY	E00057EN				 
2003123000033	20031230	00033	CE  	2003	12	30	2003FA0001175    	1	20031117	G	5711	122100511	SPAR            			CESSNA	210   	T210N       	2073456	CE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	7568N	6605 				21063235				CRACKED WING SPAR WEB AT ATTACHMENT FOR RECIPROCATING FUEL PUMP ASSOCIATED WITH FLINT WING TIP AUXILIARY FUEL SYSTEM. VI	BRATION ASSOCIATED WITH FUEL PUMP OPERATION CAUSES THIN SPAR WEB (.025 INCH) TO FLEX AND CRACK AT OUTSIDE RADIUS OF ATTA	CHMENT HARDWARE.				1	H	7	1 	3O			 	3A21    					 
2003123000036	20031230	00036	GL  	2003	12	30	2003FA0001176    	1	20030622	G	3510	3891150110	LINE            			BOMBDR	BD700 	BD7001A10   	1390006	GL  										OXYGEN SYSTEM	RUPTURED        	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17	324SM	1432 	1432 			9023				AC HAD BEEN PARKED FOR APPROX 2 WEEKS ON RAMP IN A TROPICAL CLIMATE.  WHEN FLIGHT CREW CONDUCTED THEIR PREFLIGHT INSPECT	ION, IT WAS NOTED THAT THE O2 SYS QTY WAS INDICATING 0 PSI ON EICAS AND DIRECT READING GAUGE ON EXTERIOR OF AC. SERVICIN	G OF O2 SYSTEM WAS ATTEMPTED, HOWEVER PRESSURE REMAINED AT ZERO.  UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT LINE	   INSTALLED UNDER PILOTS SIDE CONSOLE CONNECTING THE PILOTS OXYGEN MASK BOX TO OXYGEN SUPPLY WAS RUPTURED AT END FITTIN	G (HOSE HAD COME UN-SWEDGED).  A REPLACEMENT LINE WAS ORDERED FROM MFG AND INSTALLED IAW AMM.  AS PRECAUTION O2 CYLINDER	 REPLACED WITH SERVICEABLE UNITS AND O2 SYSTEM WAS PURGED IAW AMM.  AC WAS THEN RELEASED FOR SERVICE.	2	L	7	2 	4F			RT	T00003NY					 
2003122900187	20031229	00187	CE  	2003	12	29	2003FA0001177    	1	20031107	G	2121	903840311	BLOWER          			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT FLOOR	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	06	188BF	4698 				LA105				PILOT NOTIFIED MAINTENANCE FACILITY OF DEFECTIVE VENT BLOWER.  INSPECTED AND FOUND VENT BLOWER SEIZED.  REPLACED VENT BL	OWER WITH OVERHAULED PART.  SYSTEMS OPS CHECKED NORMAL.  REPLACED CURRENT LIMITER ALSO.  OVERHAUL TIME LIMIT OR MOTOR.(K	)				1	L	7	2 	4T	3	T	 	A31CE   	E2NE				 
2003123000065	20031230	00065	CE  	2003	12	30	2003FA0001178    	1	20031030	G	3240	36800111	CALIPER         			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200*       	17020	SO  					LT BRAKE	CORRODED        	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	427JW					15073873				LT BRAKE CALIPER REMOVED AND INSPECTION OF PART FOUND CORROSION AND PITTING ON CALIPER PISTON WALLS.  PISTON WAS BINDING	 WHEN MOVED.  THE PISTON WOULD NOT MOVE FREELY WITHIN CALIPER HOUSING.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003123000070	20031230	00070	NE  	2003	12	30	2003FA0001180    	3	20031027	G	6114	660714255	HUB             													ROTOL	R390	R3904123F27 	NE  	PROPELLER	CRACKED         	B			MS2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27		12226	3511 					DRG123490		PART FOUND CRACKED AT NR 2 BLADE POSITION IN RADIUS AT BEARING ABUTMENT FACE AND BEARING BORE.  PART REJECTED FROM FURTH	ER SERVICE.(K)															6	C	P31NE	 
2003123000077	20031230	00077	NE  	2003	12	30	2003FA0001181    	3	20031028	G	6111	6607132886	BLADE           													ROTOL	R389	R389*       	NE  	PROPELLER	CRACKED         	B			MS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27		19871	7462 					DR6549989		PROPELLER RECIEVED FOR OVERHAUL.  AT DISASSEMBLY AND CLEANING FOUND BLADE S/N 1139 HAD A CRACKED OUTER SLEEVE AT ROOT EN	D OF BLADE.  BLADE REJECTED FROM FURTHER SERVICE.															6	C	P30NE	 
2003123000057	20031230	00057	CE  	2003	12	30	2003FA0001182    	1	20030825	G	5540	R2700001	MOUNT           			III   	650   	650TCN      	       	CE  										RUDDER HINGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	271SA	714  				CN001				THE LOWER HINGE POINT MOUNT AS WELL AS THE REST OF THE RUDDER ASSY IS MADE OF CARBON FIBER.  THE MOUNT HAS CRACKED, DELA	MINATED, AND SEPARATED FROM RUDDER ASSY AND IS ONLY ATTACHED BY A FEW FIBERS.  THE BALL JOINT THAT CONTROLS THE RUDDER H	AS ALSO BEEN BENT AND DAMAGED.  POSSIBLE CAUSE:  OVER EXTENSION OF RUDDER ASSEMBLY.  PREVENTION:  INSTALLATION OF RUDDER	 GUST LOCKS (FOR GROUND OPS) AND THE INSTALLATION OF RUDDER CONTROL STOPS (FOR INFLIGHT OPS).(K)			1	H	7	1 	3O			NT	A41CE   					 
2003123000063	20031230	00063	EA  	2003	12	30	2003FA0001184    	2	20031007	G	8520		CONNECTING ROD  								LYC   	O540  	TIO540V2AD  	41532	EA  					NR 5 CYLINDER	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15							L8523614			FOUND NR 5 CYLINDER LT ENGINE DETACHED FROM THE CASE.  ALL CYLINDER BASE STUDS AND THE THRU BOLTS BROKEN OR PULLED OUT O	F CRANKCASE.  PIECES OF THE CRANKCASE WERE ALSO BROKEN AWAY IN THE AREA OF THE CYLINDER MOUNTING BASE.  BOTH ROD BOLTS W	ERE ALSO BROKEN AND CONNECTING ROD CAP WAS SEVERELY DISTORTED.  THE CYLINDER CONTAINED VERY MINOR DAMAGE AND NO VALVE DA	MAGE.  AIRCRAFT WAS IN NORMAL CRUISE FLIGHT WHEN OPERATOR NOTICED CYLINDER TEMP WAS COLD.  THEN REPORTED ENGINE BEGAN RU	NNING ROUGH AND SHUT IT DOWN.  PROBABLE CAUSE MY BE FAILURE OF ONE ROD END BOLT CAUSING THE FAILURE OF THE OTHER BOLT.(K	)						3	O			E14EA				 
2003122900199	20031229	00199	EA  	2003	12	29	2003FA0001185    	2	20031016	G	8530	17726	WASHER          			STNSON	10    	10B         	8632106	GL  	FRNKLN	6A4150	6A4150B3    	27024	EA  	MCAULY	1A170	1A170DM     	GL  	VALVE SPRING	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	13	8868K					1081868	13561	52849		SEVERE ENGINE ROUGHNESS OCCURRED WHILE IN FLIGHT.  AN OFF AIRPORT LANDING WAS MADE WITH NO DAMAGE TO AIRCRAFT AND NO INJ	URIES.  NR 1 CYLINDER FOUND TO HAVE NO COMPRESSION.  FOUND THAT PN 17726 VALVE SPRING WASHER HAD FAILED ALLOWING INTAKE 	VALVE TO DROP INTO CYLINDER NR 1.  ENGINE TSMOH 1106.  TIME SINCE TOP OVERHAUL 418.45.  I WAS UNABLE TO DETERMINE IF PAR	T WAS REPLACED AT MAJOR OVERHAUL OR TOP OVERHAUL. THIS REPORT IS SUBMITTED AS A CORRECTION TO THE DIFFICULTY DATE.  PREV	IOUS REPORT HAD DATE OF 11/19/2003.  ACTUAL DATE OF OCCURENCE WAS 10/16/2003.		1	H	7	1 	3O	3	O	 	A738    	E238	5	N	P857	 
2003123000025	20031230	00025	EA  	2003	12	30	2003FA0001188    	2	20031119	G	8530	17726	WASHER          			UNIVAR	108   	1081        	9230404	NM  	FRNKLN	6A4150	6A4150B3    	27024	EA  	MCAULY	1A170	1A170DM     	GL  	VALVE SPRNG	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	13	8868K					1081868	13561	52849		SEVERE ENGINE ROUGHNESS OCCURRED WHILE IN FLIGHT.  AN OFF AIRPORT LANDING WAS MADE WITH NO DAMAGE TO AIRCRAFT AND NO INJ	URIES.  NR 1 CYLINDER FOUND TO HAVE NO COMPRESSION.  FOUND THAT PN 17726 VALVE SPRING WASHER HAD FAILED ALLOWING INTAKE 	VALVE TO DROP INTO CYLINDER NR 1.  ENGINE TSMOH 1106.  TSO 418.45.  UNABLE TO DETERMINE IF PART WAS REPLACED AT MAJOR OV	ERHAUL OR TOP OVERHAUL.			1	H	7	1 	3O	3	O	 	A767    	E238	5	N	P857	 
2003123000079	20031230	00079	SW  	2003	12	30	2003FA0001189    	1	20031020	G	3230	14533107	LINK            			TMPSON	NAVION	NAVIONA     	6150104	SW  	CONT  	E185  	E185*       	17014	SO  					RT MLG	CRACKED         	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	11	4808K					NAV41808				AC MLG FAILED DURING LANDING ROLLOUT.  SCISSOR LINK ASSY HAD FRACTURED DURING THIS OPERATION CAUSING RT MAIN WHEEL TO BE	 TOE-IN.  LANDING ROLLOUT WITH WHEEL IN THIS CONFIGURATION CAUSED MAIN TRUNION TO FAIL AND GEAR TO COLLAPSE.  AN INSP OF	 AC RT MLG LINK ASSY SHOWED SIGNS OF A PREVIOUS, UNLOCATED, FRACTURE THAT PROPAGATED FROM THIS INCIDENT.  DISASSEMBLY OF	 LINKAGE WAS ACCOMPLISHED, IT WAS NOTED THAT THE SPACER AND LOWER BUSHING BLOCK INNER WALL SHOWED SIGNS OF CORROSION.  F	URTHER INSP REVILED OB AREA OF SPACER HAD NO LUBE. (REST OF SPACER HAD MINIMAL LUBRICATION) LUBE WAS REMOVED FROM BUSHIN	G BLOCK.  GREASE HAD A DISCOLORATION DUE TO HIGH USAGE AND POSSIBLE BURNING.	1	L	7	1 	3O	3	O	 	A782    	E246				 
2003122900209	20031229	00209	EA  	2003	12	29	2003FA0001190    	2	20031031	G	7310	3011849	LINE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6*        	52043	EA  					FUEL SYSTEM	FAILED          	D				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			NM	07	601PC					B225				PILOT REPORTED SMOKE IN CABIN IMMEDIATELY AFTER TAKEOFF.  LANDED IMMEDIATELY AND FOUND FUEL DRAINING FROM LEFT ENGINE.  	FOUND SEVERED FUEL LINE JUST BEHIND FORWARD B-NUT FITTING.  LINE FAILURE SEEMS TO BE A FATIGUE FRACTURE.					1	L	7	2 	3T	3	T	 	A14CE   	E2NE				 
2003123000078	20031230	00078	NE  	2003	12	30	2003FA0001191    	2	20031106	G	7310		LINE            			NAMER 	T6    	SNJ4        	6400414	GL  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	FUEL PRIMER	CHAFED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	15	7070C	1256 				8813164	10486			DURING AN ANNUAL INSPECTION, THE FUEL PRIMER LINE WAS FOUND TO BE CHAFED THROUGH AND COMPLETELY SEPARATED AT THE CLAMP O	N THE INTAKE TUBE.  THERE WAS EVIDENCE OF THIS LINE SQUIRTING FUEL ALL OVER THE ENGINE WHEN THE PRIMER IS USED.  ALL OF 	THE OTHER PRIMER LINES WERE FOUND TO BE IN ALMOST THE SAME CONDITION.  THEY WERE ALL ABOUT READY TO BREAK AT THE CLAMP A	REA.  ALL PRIMER LINES WERE REPLACED.  THIS COULD BE A POTENTIALLY DANGEROUS SITUATION, SINCE WITH THE COWLING ON THE AI	RCRAFT, THE FUEL SPRAYING ON THE ENGINE DURING PRIMING MAY NOT BE NOTICEABLE.  THE CHAFFING IS NOT READILY VISIBLE WITHO	UT CLOSELY LOOKING AT THE CLAMP AREA.  THE NEWER PRIMER LINES CAME WITH AN ANTI-CHAFE SLEEVE ON THEM.	1	L	7	1 	3R	3	R	 	A2575   	5E2	5	C	P257	 
2003122900186	20031229	00186	SO  	2003	12	29	2003FA0001193    	1	20031114	G	3246		WHEEL           			MAULE 	M4    	M4220C      	5460114	SO  	FRNKLN	6AV350	6V350*      	27043	EA  					TAIL	FAILED          	C				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			SO	15	2033U					2025C				TAILWHEEL SHIMMIED SHORTLY AFTER TOUCHDOWN, WHEN WEIGHT ON WHEELS INCREASED.  SHIMMY STOPPED FOR ABOUT A SECOND THEN RET	URNED VIOLENTLY.  DIRECTIONAL CONTROL WAS LOST WHEN RUDDER BECAME INEFFECTIVE AND A SLOW TURN TO THE RIGHT DEVELOPED (WI	ND WAS 65 DEGREE TO THE RIGHT OF RUNWAY HEADING AT 8K) FULL LEFT RUDDER AND BRAE WERE APPLIED EARLY ON BUT HAD LITTLE EF	FECT.  THE RIGHT TURN TIGHTENED UNTIL THE LEFT GEAR FAILED FROM SIDE LOAD.  DAMAGE WAS TO LEFT WING TIP, LEFT GEAR AND P	ROPELLER TIPS.  INSP OF TIRE REVEALED, OUT OF BALANCE, OUT OF ROUND AND DRY ROTTED.  UPON TEARDOWN, DISCOVERED DETENTS T	HAT LOCK STEERING WERE WORN.  THE BRONZE BUSHING IN THE VERT SHAFT WAS WORN.  (PTRS SO15200406316)	1	H	7	1 	3O	3	O	 	3A23    	E9EA				 
2003122900193	20031229	00193	SO  	2003	12	29	2003FA0001194    	1	20031202	G	2140	23D04	REGULATOR       			PIPER 	PA44  	PA44180     	7104402	SO  										FUEL PRESSURE	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	28	573ER	307  				4496149				DURING SCHEDULED INSPECTION IAW SB 107A.  FOUND HEATER FUEL PRESSURE REGULATOR LEAKING THROUGH ONE OF THE THREADED MOUNT	 HOLES.  UNIT REPLACED.					1	L	7	2 	3O			 	A19S0   					 
2003123000023	20031230	00023	SO  	2003	12	30	2003FA0001196    	1	20031028	G	7921	20710AR	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4A     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	4133D	14   	14   			2843117	RL202836A			DURING A MAINTENANCE INSPECTION OF THIS AIRCRAFT, THE OIL COOLER WAS FOUND TO BE CRACKED.  PROBABLE CAUSE IS VIBRATION. 	 RECOMMEND MANUFACTURER LOOK AT PROVIDING A SOLID PIECE OIL COOLER AS REPLACEMENT.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003123000050	20031230	00050	CE  	2003	12	30	2003FA0001197    	1	20031118	G	5500	04320049	SUPPORT BRACKET 			CESSNA	150   	152         	2071835	CE  										EMPENNAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	69254	8550 				15282586				SUPPORT BRACKET WAS FOUND TO HAVE A CRACK IN THE WELD WHILE INSPECTING NUTPLATES IAW AD.  CRACK WAS LOCATED JUST FORWARD	 OF NUTPLATE INSIDE BRACKET ABOUT .7500 INCH LONG.  WITH DYE PENETRANT INSPECTION, DYE PENETRATED COMPLETELY THROUGH WEL	D TO OUTSIDE BRACKET.  BRACKET HAS APPROXIMATELY 8550 TOTAL HOURS-NUTPLATES CHECKED OK.				1	H	7	1 	3O			NT	3A19    					 
2003123000051	20031230	00051	CE  	2003	12	30	2003FA0001198    	1	20031020	G	8011	642087A64	ADAPTER         			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					STARTER	SPLIT           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	8064N					E2578				DOWEL AT 7 O`CLOCK POSITION CAUSED (PN 655714) COVER TO SPLIT AT STUD HOLE.  DOWEL HOLE IN PN 655715A1 HOUSING WAS CUT T	OO DEEP CAUSING WSHER TO SINK INTO THE COVER INSTEAD OF BOTTOMING ON THE DOWEL.					1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2003122900207	20031229	00207	SO  	2003	12	29	2003FA0001199    	1	20030903	G	5500	1709303	FITTING         			PIPER 	PA23  	PA23        	7102302	SO  	LYC   	O320  	O320*       	41508	EA  					EMPENNAGE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	64M					23534				DISCOVERED CRACKS DURING ROUTINE INSPECTION.  AD 58-01-06 HAD BEEN COMPLIED WITH BY REPLACEMENT OF PN 1709303.						1	L	7	2 	3O	3	O	 	1A10    	E274				 
2003123000046	20031230	00046	CE  	2003	12	30	2003FA0001200    	1	20031118	G	5712	1013017	RIB             			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	IO470*      	17026	SO  					LT WING	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	29821	300  				18261233				OUTBOARD RIB OF EACH CANARD WING, CRACKED.  OUTBOARD HINGE TAB, LEFT SIDE CANARD BROKEN IN TWO.  OUTBOARD HINGE TAB OF R	T CANARD WING CRACKED.					1	H	7	1 	3O	3	O	NT	TA13    	E1CE				 
2003123000075	20031230	00075	CE  	2003	12	30	2003FA0001201    	1	20031118	G	5720	1013016	TAB             			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	IO470*      	17026	SO  					WING	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	29821	300  				18261233				OUTBOARD RIB OF EACH CANARD WING CRACKED.  OUTBOARD TAB LEFT SIDE CANARD BROKEN IN TWO.  OUTBOARD HINGE TAB OF RT CANARD	 WING CRACKED.					1	H	7	1 	3O	3	O	NT	TA13    	E1CE				 
2003122900192	20031229	00192	CE  	2003	12	29	2003FA0001203    	1	20031024	G	2497	VR600A	VOLT REGULATOR  			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELECTRICAL	BURNED          	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	13	734HL	1619 				17268866	L138376	729772		A/C ARRIVED AT SHOP AFTER EXPERIENCING SMOKE IN THE CABIN.  ELEC SYS WAS SHUT OFF (MASTER SWITCH).  INSPECTION OF ELEC S	YS SHOWED EVIDENCE OF A FIRE INSIDE OF VOLTAGE REG.  VOLTAGE REG WAS INSTALLED IAW INSTRUCTION SHEET NR PPS-2020.  THE V	OLTAGE REGULATORS INTERNAL OVER VOLTAGE RELAY FAILED.  THIS RESULTED IN AN (OVER VOLTAGE CONDITION).  FOUND MULTIPLE ELE	C UNITS (BLOWN) FROM LND LTS, FUEL QUANTITY GAUGES, BEACON FLASHER AND LAMP, TO ALL RADIOS.  THE ORIGINAL OVER VOLTAGE R	ELAY (FROM MFG) IS DISCONNECTED W/ OTHER UNIT INSTALLATION IAW ABOVE INSTRUCTIONS.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003122900195	20031229	00195	EA  	2003	12	29	2003FA0001204    	1	20031120	G	2810	C6P115731	PAD             			DHAV  	DHC6  	DHC6*       	2802606	EA  	PWA   	PT6   	PT6*        	52043	EA  					NR 5 FUEL CELL	DETERIORATED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	143Z	12818				437				REPORTED (AFT FUEL LOW) LIGHT ILLUMINATING WITH 300-400 LBS REMAINING ON GAUGE.  (SHOULD BE 110 LBS).  TROUBLESHOOTING R	EVEALED FLAPPER PAD (SEAL) WAS DETERIORATED TO THE CONSISTENCY OF A (GUMMY BEAR).  AS FUEL IS MOVED INTO THE NR 5 (ENG F	EED) TANK, BY MOTIVE FLOW SYSTEM, IT WOULD BEAK BACK OUT THROUGH THIS SEAL INTO SUBSIDIARY CELLS.  A/C UNABLE TO KEEP NR	 5 CELL FULL.  A CALL TO MFG REVEALED THIS HAS BEEN REPORTED SEVERAL TIMES WHEN A/C OPERATED IN HOT ENVIRONMENTS.  (S. A	FRICA) THIS A/C OPERATED FROM ID TO NEW MEX.  MFG CLAIMS WORKING ON DEVELOPING NEW SEAL.		1	H	7	2 	3T	3	T	 	A9EA    	E2NE				 
2003122900212	20031229	00212	CE  	2003	12	29	2003FA0001205    	1	20031202	G	2820	05560203	VENT            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					FUEL SYSTEM	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	05	734BZ	3800 				68738				FOUND FUEL LEAK RT DOOR FRAME, CAUSED BY CORROSION AND CHAFING OF FUEL VENT PIPE IN WING ROOT. INSPECTED L/S AND FOUND B	EGINNINGS OF LEAK ON THAT SIDE ALSO.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003122900206	20031229	00206	CE  	2003	12	29	2003FA0001207    	1	20031118	G	2430		PULLEY          	FORD        		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					ALTERNATOR	LOOSE           	B			E81R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	03	69042					15282455				RFD CONTROL TOWER NOTED SPARKS COMING FROM COWLING AREA.  UPON COWL REMOVAL NOTED ALTERNATOR AND ALTERNATOR PULLEY HAD B	EEN LOOSE AND WOBBLING.  ALTERNATOR HOUSING GOUGED, PULLEY SEVERELY DAMAGED FROM EXCESSIVE WOBBLING AND VIBRATION.  ROTO	R SHAFT END AND THREADS GOUGED AND SEVERELY WORN.  ALTERNATOR FORD PN DOFF 10300B.TRANSIENT AIRCRAFT, MAINTENANCE HISTOR	Y UNKNOWN.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003123000089	20031230	00089	CE  	2003	12	30	2003FA0001209    	1	20031104	G	2810	0426508910	SKIN            			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200*       	17020	SO  					LT, RT WING TANK	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	8006S					15061606				LOWER TANK SKINS CORRODED THROUGH IN STRAINER ASSEMBLY SUMP.  CORROSION NOTED IN OTHER AREAS OF TANK LOWER SURFACE CONSI	STENT WITH STANDING BEADS OF WATER.  CORROSION NOTED AROUND FUEL DRAIN VALVE PAD.  STRAINER ASSEMBLY SUMP IS LOW POINT I	N THE TANK AND HAS NO PROVISIONS FOR DRAIN.  BOTH LT AND RT TANKS AFFECTED.  AIRCRAFT INACTIVE FOR ABOUT A YEAR.(AL03200	409911)			1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003123000064	20031230	00064	CE  	2003	12	30	2003FA0001210    	1	20031112	G	2820		LINE            			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520*      	17032	SO  					FUEL SYSTEM	SWOLLEN         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	70713					18501878				FUEL LINES IN LT AND RT DOOR POSTS FOUND SWOLLEN AND POROUS.  RADIUS BEND AREA NEAR LOWER PORTION OF DOOR POST IS THE AR	EA AFFECTED.					1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2003123000090	20031230	00090	SO  	2003	12	30	2003FA0001211    	2	20031112	G	8500	IO520F	CRANKCASE       								CONT  	O520  	IO520F      	17032	SO  					BEARING BOSS	CRACKED         	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03							821524R			LT SIDE (2.4.6) CRACKED IN CENTER MAIN BEARING BOSSES IN LOWER OIL ANNALYSIS.											3	O			E5CE				 
2003123000088	20031230	00088	GL  	2003	12	30	2003FA0001215    	1	20031125	G	2420	BC4101	CASE            			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					NR 2  ALTERNATOR	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	813CD	540  				0141				ALTERNATOR CASE CRACKED AT MOUNTING FLANGE ALLOWING ALTERNATOR TO DEPART THE ACCESSORY CASE.  THE ALTERNATOR ARMATURE ST	ILL ROTATED FREELY.  PROBABLE CAUSE:  ENGINE VIBRATION, MFG REPORTED THAT THIS WAS THE 9TH ALTERNATOR TO FAIL THIS WAY.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2003123000004	20031230	00004	SO  	2003	12	30	2003FA0001216    	2	20030923	G	8540	CAM539568	GEAR            			CESSNA	182   	182B        	2072706	CE  	CONT  	O470  	O470L       	17026	SO  					STARTER ADAPTER	WORN            	B			CY4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7150E	18   				52150	670926L			TEETH TOO SHALLOW, TOOTH DEPTH WAS 0.152, NORMAL .0.180 TO 0.185.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003123000066	20031230	00066	SO  	2003	12	30	2003FA0001218    	2	20031105	G	8530	ECITIST712ACA	CYLINDER HEAD   								CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	SEPARATED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		269  					511157			CYLINDER HEAD SEPARATED FROM THE BARREL.											3	O			E8CE				 
2003123000059	20031230	00059	SO  	2003	12	30	2003FA0001219    	2	20030918	G	8500		CRANKCASE       								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		3689 	1891 				814966R			THIS ENGINE WAS RECEIVED AS CORE ENGINE.  THIS IS WHAT WE FOUND WHEN WE LIQUID PENETRANT INSPECTED IT:  CRACKED IN BEARI	NG SADDLES, LT SIDE BEARING BOSSES CENTERED.										3	O			E5CE				 
2003123000069	20031230	00069	SO  	2003	12	30	2003FA0001220    	2	20030918	G	8500	IO520F	CRANKCASE       								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03							812318R			PHASE 3 CASE, 7TH STUD.  CRACKED IN MAIN BEARING SADDLE AREA BOTH CENTER SADDLES.  I OIL ANNULUS AREA.											3	O			E5CE				 
2003123000068	20031230	00068	SO  	2003	12	30	2003FA0001221    	2	20030910	G	8500		CRANKCASE       								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03			1806 				814783R			THIS ENGINE WAS DISMANTLED, CLEANED AND LIQUID PENETRANT INSPECTED.  FOUND THIS CENTER REAR MAIN BEARING SADDLE LEFT SID	E CRACKED.  MAIN BEARING PART NR 653547.										3	O			E5CE				 
2003123000076	20031230	00076	SO  	2003	12	30	2003FA0001222    	2	20030904	G	8500	649043	CRANKCASE       								CONT  	O520  	IO520F      	17032	SO  					ENGINE	BROKEN          	B			O3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		3497 	1798 				818770R			THIS ENGINE WAS DISMANTLED FOR OVERHAUL, FOUND THE REAR CENTER MAIN BEARING SADDLE ON THE LEFT SIDE OF THE CRANKCASE IN 	A CONDITION THAT APPEARS TO BE CRUMBLING APART.										3	O			E5CE				 
2003123000021	20031230	00021	SO  	2003	12	30	2003FA0001223    	2	20030805	G	8520	SA631475	PISTON          								CONT  	O520  	IO520F      	17032	SO  					SKIRT	DESTROYED       	B			O3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03		1766 	1766 				814594R			AT DISMANTLING THIS ENGINE WE FOUND NR 5 PISTON SKIRT TO BE BROKEN AT THE RING LAND FOR THE SCRAPER RING.											3	O			E5CE				 
2003123000031	20031230	00031	NE  	2003	12	30	2003FA0001224    	2	20031006	G	7200		ENGINE          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  						FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	408EM					2434				ENGINE SHUT DOWN WITH LOUD BANG.  AIRCRAFT WAS IN LEVEL FLIGHT AT APPROX 1500 FT ABOVE GROUND.  THE CAUSE OF THE ENGINE 	FAILURE HAS NOT BEEN DETERMINED.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003123000019	20031230	00019	SW  	2003	12	30	2003FA0001225    	1	20030211	G	6520	206040439001	SHAFT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R GEARBOX	WORN            	B			QS7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	921RB	6702 	846  		ALO11974	2624				DURING ANNUAL INSPECTION, FOUND KNURLED NUT WORN BEYOND LIMIST.  UPON REMOVAL OF THE KNURLED NUT AND TAIL ROTOR BALANCE 	WHEEL FOUND THREADS ON TAIL ROTOR GEARBOX OUTPUT SHAFT, UNDER BALANCE WHEEL, EXCESSIVELY WORN AND GALLED.  CUSTOMERS PIL	OT REPORTED THAT THEY EXPERIENCED DIFFICULTY IN MAINTAINING TORQUE ON THE KNURLED NUT.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003123000018	20031230	00018	NE  	2003	12	30	2003FA0001226    	2	20031126	G	7250	400100025	NOZZLE          								LYC   	LTS101	LTS101750B1 	41560	NE  					POWER TURBINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										P/T NOZZLE SEPARATION AND CRACKED.											3	U			E5NE10				 
2003122900205	20031229	00205	EA  	2003	12	29	2003FA0001229    	2	20031205	G	7320		FUEL CONTROL    			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	OUT OF ADJUST   	D				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		LD	LANDING        	1			GL	15	21850					32R795644	L1882748A			PILOT, UPON TOUCHDOWN TO LANDING, HAD HIS ENGINE QUIT AND WOULD NOT START AND NEEDED A TOW IN.  HE ALSO FOUND THAT HE CO	ULD NOT ADVANCE HIS THROTTLE.  INSPECTED FUEL SERVO AND FOUND PIN OUT ON THE IDLE MIXTURE SETTING.  INSTALLED OLD PIN, W	ITH HAS HELD PARTICALY IN PLACE WITH THE SPRING, NEW WASHER P/N 177718 AND COTTER PIN 901200. RUN UP CHECK GOOD.				1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2003123000047	20031230	00047	SO  	2003	12	30	2003FA0001230    	2	20031205	G	8510	2224111000	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					ALTERNATOR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03		474  				C0172				ALTERNATOR BRACKET FAILED AFTER THE HEAD BROKE OFF THE AN4-5A BOLT THAT RETAINS THE BRACKET TO THE SPACER BETWEEN THE CA	SE AND BRACKET.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2003123000097	20031230	00097	CE  	2003	12	30	2003FA0001231    	1	20031210	G	3233	22430291	FITTING         			CESSNA	182   	R182        	2072734	CE  										NLG ACTUATOR	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	28	35G	4767 				R18201785				DURING ANNUAL INSPECTION FOUND THE AFT ATTACH FITTING FOR THE NOSE GEAR ACTUATOR CRACKED IN TWO PLACES.  THE CRACKS STAR	T AT THE ACTUATOR PIN BOSS AND PROGRESS UPWARD THROUGH THE FLANGE AREA TO THE EDGE OF THE FITTING.  UNABLE TO DETERMINE 	CAUSE (AGE, FATIGUE OR HARD LANDINGS).  THIS IS THE SECOND ONE FOUND IN THE FLEET(THE OTHER ONE ON S/N R18200008).  ONE 	OF THE FITTINGS HAS BEEN RETURNED TO MFG FOR THEIR EVALUATION.			1	H	7	1 	3O			RT	3A13    					 
2003123000034	20031230	00034	EA  	2003	12	30	2003FA0001232    	2	20031101	G	8530		CYLINDER        								LYC   	O235  	O235L2C     	41505	EA  					ENGINE	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99							L2028915			WHILE PERFORMING OIL AND FILTER CHANGE, CUT FILTER AND NOTICE OIL PARTICLES IN FILTER.  CALLED MFG TECH SUPPORT, IAW THE	IR REQUEST PULLED CYLINDERS.  CYLINDERS NR 1, 3, AND 4 WORN SCORED ON PISTON AND CYLINDER WALL.  ENGINE IS FACTORY OVERH	AUL W/250 SMOH.  ENGINE WAS PURCHASED IN JAN 2003.									3	O			E223				 
2003123000099	20031230	00099	SO  	2003	12	30	2003FA0001233    	1	20031112	G	7820	6871800	MUFFLER         			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE EXHAUST	DETACHED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	3580W	1769 				32473	RL1067040	CH33934B		EXHAUST TUBE ON MUFFLER, BECAME DETACHED FROM MUFFLER AND DEPARTED AIRCRAFT DURING NORMAL FLIGHT UNDER NORMAL CONDITIONS	.  RECOMMENDATIONS: CHANGE MUFFLER AT MFG RECOMMEND TIME OF 1000 HOURS OF USE.					1	L	7	1 	3O	3	O	 	A3SO    	E295	5	C	P920	 
2003123000035	20031230	00035	SO  	2003	12	30	2003FA0001234    	1	20030918	G	2742	1159SCC20033	ACTUATOR        			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					HORIZONTAL STAB	STUCK           	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	388CW					489				DURING FINAL APPROACH, FLAPS WOULD NOT EXTEND BEYOND 35 DEGREES TO THE NORMAL 39 DEGREES, NOR COULD THE FLAPS RETRACT.  	LANDING WAS UNEVENTFUL.  IT WAS LATER DISCOVERED THAT HORIZ STAB ACT (WHICH BEGINS TO MOVE HORZ STAB DOWN WHEN FLAPS GO 	BEYOND 10 DEGREES) WOULD SEIZ AND BIND AT 33-35 DEGREES.  LACK OF LUB (UNIT CAN NOT BE LUBRICATED-SEALED UNIT) SEVERE IN	TERNAL CORROSION.			2	L	7	2 	4F	4	F	 	A12EA   	E2EU				 
2003123000005	20031230	00005	NE  	2003	12	30	2003FA0001235    	2	20030809	G	7320	189111	HMU             			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					ENGINE	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										NO FUEL FLOW AT START. MANUFACTURER CLAIMS CAUSED BY DIEGME FUEL CONTAMINATION. FUEL SYSTEM CLEANED, NO EVIDENCE OF CONT	AMINATION FOUND. REPLACEMENTS UNITS INSTALLED, REPEAT OCCURRENCE 3 FLIGHT HOURS LATER. ALSO NO CONTAMINATION IN EVIDENCE	, EVEN FROM EXTENSIVE LABORATORY TESTING OF FUEL SAMPLES.  IT SEEMS THAT THESE UNITS ARE INTOLERANT OF FUEL THAT MEETS A	LL ASTM STANDARDS. AIRFRAME FILTRATION MAY BE INADEQUATE. THESE UNITS ALSO ON G200, HAWKER 1000, AND DO328JET.  WE ARE A	WARE OF NO LESS THAN 20 OTHER INCIDENTS.		2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2003123000014	20031230	00014	EU  	2003	12	30	2003FA0001236    	1	20031211	G	7830	F50B2459A2	MOUNT BRACKET   			AMD   	FALC50	FALCON50MYST	2730106	EU  										THRUST REVERSER	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	370KP	6387 				103				THRUST REVERSER CHECK VALVE MOUNT BRACKET WAS FOUND TO BE BROKEN AWAY FROM AIRCRAFT STRUCTURE.  WHEN HYDRAULIC POWER WAS	 APPLIED TO AIRCRAFT DURING MAINTENANCE THE LINE TO CHECK VALVE CRACKED AND BEGAN SPRAYING HYDRAULIC FLUID.  REPLACEMENT	 OF LINE AND MOUNT BRACKET WAS ACCOMPLISHED.  SUSPECT THAT CHECK VALVE MOUNT BRACKET BEGINS TO CRACK OVER TIME AND EVENT	UALLY BREAKS AWAY FROM AIRCRAFT STRUCTURE.  THIS IS SECOND FAILURE OF THIS MOUNT THAT WE HAVE FOUND ON THIS AC.  SUSPECT	 LINE FAILED DUE TO VIBRATION WORK HARDENING FROM NOT BEING SECURED IN PLACE.  RECOMMEND INSPECTING THIS CHECK VALVE MOU	NT AT EARLIEST CONVENIENCE TO PREVENT POSSIBLE FAILURE OF THRUST REVERSER HYDRAULIC LINE WHEN UNDER PRESSURE.	2	L	7	3 	4F			 	A46EU   					 
2003123000026	20031230	00026	SO  	2003	12	30	2003FA0001237    	1	20031111	G	3710		PUMP            			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					VACUUM SYS	DAMAGED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	5922V					32R7780378				THE VACUUM PUMPS OVERBOARD AIR LINE SHOWED SIGNS OF DAMAGED THREADS, AND WORKED OUT OF THE PUMP.  WHEN IT FELL, ITS PRES	UMED THAT IT BECAME CAUGHT IN THE NOSE GEARS DOWN LOCK MECHANISM.  ON LANDING, THE NOSE GEAR WOULD NOT FULLY EXTEND OR L	OCK, CAUSING A SAFE NOSE GEAR UP LANDING AT SMO.  (WP200404833/ INCIDENT NR IWP 23004004)				1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2003123000020	20031230	00020	SW  	2003	12	30	2003FA0001238    	1	20031201	G	2710	730048503	PUSHROD TUBE    			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360*    	17025	SO  					AILERON	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	231PF					250102				FOUND BOTH AILERON OB PUSH ROD TUBES RUSTING INTERNALLY.  IF RUST IS NOTICED ON EXTERIOR OF TUBE, IT IS ALREADY AT POINT	 OF FAILURE.  TT 5140 HRS  RECOMMEND REPLACING BOTH AILERON PUSH ROD TUBE ASSEMBLIES ON ANY AC WHICH HAVE NOT BEEN REPLA	CED IN PAST FIVE YEARS.  WATER MOISTURE COLLECTING.  (NE03200404128)				1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2003123000048	20031230	00048	EA  	2003	12	30	2003FA0001239    	2	20031205	G	8530	AEL65102NST44R	COOLING FINS    			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					ENGINE CYLINDER	BLOCKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	4922S	500  				R18201461	L2227740A			VISUAL INSPECTION REVEALED MAJORITY OF COOLING FINGS BETWEEN INTAKE AND EXHAUST PORTS BLOCKED.  VIRTUALLY NO AIR FLOW AL	LOWED TO PASS BETWEEN ALL FINS ON ALL CYLINDERS.					1	H	7	1 	3O	3	O	 	3A13    	E295				 
2003123000041	20031230	00041		2003	12	30	2003FA0001240    	4	20031202	G	2562	BP1020	BATTERY PACK    																	ELT	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	19										REPLACED THE ELT`S BATTERY PACK DURING AN ANNUAL INSPECTION.  BATTERY PACK WAS GOOD TILL JAN 2004.  THE EXTERIOR OF THE 	PACK WAS IN GOOD CONDITION.  REMOVED THE CARDBOARD COVERING AND FOUND ONE OF THE "D" CELL BATTERY`S WAS LEAKING ACID AND	 IF LEFT IN THE ELT, IT WOULD HAVE CAUSED CORROSION ON THE INTERNAL CIRCUIT BOARD OF THE ELT.  THE CAUSE OF THE LEKING B	ATTERY IS UNKNOWN, ALL THE OTHER BATTERIES IN THE PACK WERE OK.  RECOMMEND THAT WHEN AN ELT BATTERY PACK IS CHANGED, IF 	IT IS POSSIBLE, REMOVE THE PACK COVERING AND CHECK THE ACTUAL CONDITION OF THE BATTERIES.															 
2003123000012	20031230	00012	SW  	2003	12	30	2003FA0001241    	1	20031212	G	2730	110227	GUARD           			BBAVIA	8     	8GCBC       	1220803	SW  										ELEVATOR	OUT OF ADJUST   	D				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			GL	27	186AC	2843 				36994				THE CABLE GUIDE ON THE AFT PULLEY (BEFORE ATTACHING TO THE ELEVATOR BELLCRANK) WAS INSTALLED AT AN ANGLE WHICH ALLOWED T	HE CABLE TO WEAR AGAINST THE GUIDE.  TWO OF THE SEVEN STRANDS ON THE 7 X 19 CABLE WERE FOUND WORN THROUGH ON AN ANNUAL I	NSPECTION.				1	H	7	1 	3O			 	A21CE   					 
2003123000028	20031230	00028	CE  	2003	12	30	2003FA0001242    	1	20031205	G	3297		CONTACTOR       			BEECH 	18    	H18         	1151012	CE  	PWA   	R985  	R985*       	52008	NE  					MLG ACTUATOR	MALFUNCTIONED   	C				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CE	07	170LG	12523				BA666				UPON LANDING THE AIRCRAFT, THE LANDING GEAR FAILED TO EXTEND DUE TO A MALFUNCTION OF THE LANDING GEAR MOTOR CONTRACTOR. 	 PROBLEM WAS DUPLICATED WITH THE AIRCRAFT ON JACKS.  TAPPING THE CONTACTOR WITH THE LANDING GEAR SELECTOR IN THE DOWN PO	SITION WOULD OPERATE THE LANDING GEAR.  REPLACEMENT OF THE CONTACTOR CORRECTED THE GEAR MALFUNCTION.				1	L	7	2 	3R	3	R	 	A765    	5E1				 
2003123000081	20031230	00081	SO  	2003	12	30	2003FA0001243    	1	20031203	G	7921	20710AR	OIL COOLER      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			VJ3R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	4122F		7    			2843118	RL3347036A			DURING PREFLIGHT OF AIRCRAFT PILOT REPORTED OIL LEAKING FROM ENGINE.  MAINTENANCE TECHNICIAN FOUND OIL LEAK ON OIL COOLE	R.  PERFORMED PRESSURE CHECK ON OIL COOLER AND FOUND TOP FLANGE CRACKED.  THIS IS A WEAK AREA ON THE OIL COOLER.  RECOMM	END FINDING A REPLACEMENT THAT IS MORE DURABLE.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003123000082	20031230	00082	SO  	2003	12	30	2003FA0001244    	1	20031205	G	8011	MHB601	GEAR            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					STARTER	FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4163W	43   				2843127	RL2987536A			PILOT REPORTED AIRCRAFT WOULD NOT START, UPON INSPECTION FOUND BENDIX ON STARTER SHATTERED AND THE TEETH ON STARTER RING	 GALLED.  RECOMMEND RE-EVALUATE STRENGTH OF MATERIAL USED TO MANUFACTURE BENDIX.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2003122900197	20031229	00197	GL  	2003	12	29	2003FA0001245    	1	20031215	G	3510	3891150110	LINE            			BOMBDR	BD700 	BD7001A10   	1390006	GL  										OXYGEN SYSTEM	SWOLLEN         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	324SM	1567 				9023				OXYGEN SYSTEM LEAKING AT A RATE OF 3 TO 4 PERCENT OF TOTAL VOLUME IN A 24 HOUR PERIOD.  VISUAL INSPECTION OF SUSPECT LIN	E P/N 38911-5-0110 REVEALED SLIGHT BLISTERING AT THE SWEDGE AS WELL AS MISALIGNMENT OF PROTECTIVE HOSE WEBBING.  REMOVED	 AND REPLACED LINE WITH A NEW UNIT IAW AMM.  LEAK RATE DROPPED TO LESS THAN 1 PERCENT OVER 24 HOURS.  THIS LINE HAS HAD 	A HISTORY OF RUPTURING WITH 2 OCCURRENCES WITH THIS OPERATOR AND AT LEAST 8 OTHER OCCURRENCES ON OTHER MFG PRODUCTS.			2	L	7	2 	4F			RT	T00003NY					 
2003122900208	20031229	00208	NM  	2003	12	29	2003FA0001246    	1	20031216	G	2710		LINK            			LANCAR	LC40  	LC40550FG   	5150000	NM  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	AILERON	MISMANUFACTURED 	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21						40008	683385	FP1223B		WHILE RIGGING AC, USING TORQUE SPEC FROM MFG MM.  AILERON FINAL CONTROL LINK THREADS WERE DESTROYED WHILE ATTEMPTING TO 	REACH LOW END OF SPECIFIED TORQUE (REF MFG MM CHAP 27, SECT 27-10, B., STEP 9). THE MFG WAS NOTIFIED OF THIS SITUATION A	ND RESPONDED WITH:  USE SPECIFIED TORQUE FOR LINK (REF DWG LA57275900 REV B, WHICH DIFFERS FROM MM).  NEW LINK WAS ORDER	ED AND DURING TORQUING PROCEDURE, THREADS ON LINK WERE DESTROYED AGAIN. TORQUE WRENCH USED IN BOTH INSTANCES WAS CHECKED	 WITH OUR IN SHOP CHECKER AND VERIFIED TO BE WITHIN SPEC. TRIED TO CONTACT COMPANY REP BUT HAD NO RESPONSE TO OUR INQUIR	ES.	1	L	7	1 	3O	3	O	RT	A00003SA	E3SO	5	C	P25EA	 
2003123000006	20031230	00006	CE  	2003	12	30	2003FA0001247    	1	20031216	G	5533		ANGLE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					VERTICAL STAB	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	19	6WU					BB1668				TWO ANGLES THAT ARE THE FORWARD MOUNTING STRUCTURE OF THE VERTICAL STABILIZER TO THE HORIZONTAL STABILIZER HAVE 2 HOLES 	EACH WITH BOLTS THAT ATTACH THE HORIZONTAL STAB., AND 5 HOLES EACH WITH 4 LOCKBOLTS INSTALLED THAT ATTACH TO THE VERTICA	L STAB. THE TOP HOLE ON EACH ANGLE IS DRILLED THRU EACH STRUCTURAL PART EXCEPT P/N 101-640011-11 WHICH IS THE PRIMARY HO	LE OF THESE INTERCONNECTING PARTS AND THIS FASTENER WAS NEVER INSTALLED.			1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003123000094	20031230	00094	NM  	2003	12	30	2003FA0001249    	1	20031217	G	5730		SKIN            			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R3350*      	67040	EA  					LT WING	CRACKED         	F				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	139HP	9034 				145906				CRACKS EMANATING FROM THE LT AND RT MLG FORWARD LOWER CUT-OUTS IN THE CENTER WING SKIN. CRACKS RUN FORWARD FROM THE INBO	ARD CORNERS TO THE FIRST AND SECOND RIVETS.  CRACKS DO NOT CONTINUE TO THE EDGE OF SKIN.  LOCATIONS OF THE CUTOUTS ARE J	UST INBOARD OF THE NACELLE WALLS AT WING STATIONS RT 128.5, 171.5 AND LT 128.5, 171.5.				2	M	7	2 	4R	4	R	RT	A1RM    	E272				 
2003123000095	20031230	00095	NM  	2003	12	30	2003FA0001250    	1	20031217	G	5730		SKIN            			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R3350*      	67040	EA  					RT WING	CRACKED         	F				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	140HP	9966 				140443				CRACKS EMANATING FROM THE LT AND RT MLG FORWARD LOWER CUT-OUTS IN THE CENTER WING SKIN. CRACKS RUN FORWARD FROM THE INBO	ARD CORNERS TO THE FIRST AND SECOND RIVETS.  CRACKS DO NOT CONTINUE TO THE EDGE OF SKIN.  LOCATIONS OF THE CUTOUTS ARE J	UST INBOARD OF THE NACELLE WALLS AT WING STATIONS RT 128.5, 171.5 AND LT 128.5, 171.5.				2	M	7	2 	4R	4	R	RT	A1RM    	E272				 
2003123000060	20031230	00060	SO  	2003	12	30	2003FA0001251    	1	20031202	G	3233	452729	ROD END         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					NLG ACTUATOR	BROKEN          	B			OG5R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	21	804ND	1832 			199	2837004				PILOT REPORTED NOSE GEAR RETRACTED AND A THUMPING NOISE WAS NOTED, UPON WHICH THE NOSE GEAR EXTENDED AND LOCKED.  MAIN G	EAR WERE EXTENDED AND PRECAUTIONARY LANDING MADE.  INSPECTION BY MECHANIC PERSONNEL FOUND NOSE GEAR ACTUATOR ROD END HAD	 SHEARED AT THE END OF THE THREADS ON THE BEARING END.  NO OTHER DAMAGE NOTED.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2003123000074	20031230	00074	CE  	2003	12	30	2003FA0001252    	1	20031118	G	5210	071100159	PIN             			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					PILOT DOOR HINGE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	20215					17261101				DURING THE ANNUAL INSPECTION ON THIS AIRCRAFT, FOUND THE TOP PILOT DOOR HINGE PIN OVER HALF MISSING AND ONLY A SMALL POR	TION HOLDING THE HINGE TOGETHER, AM SUBMITTING THIS REPORT BECAUSE HAVE FOUND THIS PROBLEM ON MANY THIS TYPE AC HINGES I	N THE LAST FEW YEARS.  IF THE PIN FAILED COMPLETELY, THE DOOR WILL COME OFF AND MAYBE HIT THE TAIL.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003123000061	20031230	00061	SO  	2003	12	30	2003FA0001253    	2	20031208	G	8500		ENGINE          			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  						FAILED          	G				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	05	6677Y					E1594	297367R			AT CRUISE THE AIRCRAFT EXPERIENCED TOTAL POWER LOSS.  REMOVING THE ENGINE, THE TECH NOTED GEAR TEETH IN THE OIL SUMP.  E	NGINE WAS SHIPPED TO MFG FOR ANALYSIS.  NO DATA YET.					1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2003123000062	20031230	00062	CE  	2003	12	30	2003FA0001254    	1	20031126	G	2140	04530181	VALVE           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					CABIN HEAT	BROKEN          	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	03	35077	1575 				17281062				OWNER COMPLAINED OF NO HEAT IN CABIN AND CONTROL FROZEN.  FOUND FLAPPER VALVE PN NR 04530181 BROKEN AT LT SIDE HINGE NOT	 ALLOWING DOOR TO OPEN AND CONTROL SHAFT GO OVER CENTER.  REMOVED CABIN HEAT BOX AND REPLACED VALVE AND REASSEMBLED.  OP	S CHECKED OK.  PART REPLACED UNDER MFG WARRANTY.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003123000053	20031230	00053	NM  	2003	12	30	2003FA0001255    	1	20031208	G	5711		SPAR            			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	A75*        	17005	SO  					WING	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	94107	1300 				1430				LEFT FRONT SPAR SHOWS EXFOLIATION CORROSION ABOUT 12 INCHES FROM ROOT.  HAD BEEN INSPECTED AND COATED WITH PRIMER, THEN 	SIGNED OFF AS AIRWORTHY.  THIS CORROSION APPEARED TO BE 75 PERCENT THROUGH BOTTOM SPAR FLANGE.					1	L	7	1 	3O	3	O	 	A718    	E213				 
2003123000091	20031230	00091	NM  	2003	12	30	2003FA0001256    	1	20031208	G	3240		BRAKE ASSY      			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	A75*        	17005	SO  					MLG	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	94107	1300 				1430				WHEEL HALVES BADLY CORRODED, GALVANIC CORROSION WHERE STEEL KEYS ARE LOCATED IN INNER WHEEL HALF.  APPEARS TO BE FROM LO	NG TIME SETTING OUT OF USE.  OUTSIDE STORAGE APPARENTLY AFFECTED CORROSION.					1	L	7	1 	3O	3	O	 	A718    	E213				 
2003123000009	20031230	00009	SO  	2003	12	30	2003FA0001257    	2	20031208	G	8510		BEARING         			UNIVAR	415   	415C        	0420302	NM  	CONT  	C75   	C75*        	17005	SO  					ENGINE	WRONG PART      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	94107					1430	1579612			ENGINE STOPPAGE INFLIGHT, FIRST DIAGNOSIS WAS CARBURETOR PROBLEM.  SECOND STOPPAGE INDICATED A DIFFERENT PROBLEM.  TEARD	OWN OF ENGINE REVEALED A SERIES OF FRONT MAIN JOURNAL BEARING HAD BEEN INSTALLED, BLOCKING AN OIL GALLERY, CAUSING SEVER	E WEAR AND SEIZURE OF ENGINE.  CONFERRED WITH MFG TECH, CONFIRMED DIAGNOSIS AS CAUSING THIS PROBLEM.  NOTE:  THIS ENGINE	 HAD 3 STOPPAGES BETWEEN DEPARTURE AND DESTINATION,  ALL CARB ICE.			1	L	7	1 	3O	3	O	 	A718    	E233				 
2003123000083	20031230	00083	NM  	2003	12	30	2003FA0001258    	1	20031208	G	5343	41531920	MOUNT           			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	A75*        	17005	SO  					NLG STRUT	BENT            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	94107	1300 				1430				LOWER TUBES FROM LOWER NOSE STRUT MOUNT TO FIRE WALL ATTACHMENT SLIGHTLY BENT.  INSPECTION OF AIRPLANE INDICATED IT HAD 	BEEN ON ITS BACK AT SOMETINE IN THE PAST.					1	L	7	1 	3O	3	O	 	A718    	E213				 
2003123000085	20031230	00085	CE  	2003	12	30	2003FA0001259    	1	20031007	G	5312	07126103	BULKHEAD        			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540*       	41532	EA  					TAIL CONE	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	5125T	2050 				R18201818				DURING THE MFG OF THIS AC, THE OPTIONAL FACTORY OXYGEN SYS WAS INSTALLED.  IT LOOKS LIKE THIS WAS KNOWN WHEN THE TAIL CO	NE WAS BUILT AS RIVETS IN THE AREA WHERE THE OXYGEN BOTTLE BRACKETS WERE OMITTED TO PROVIDE FOR INSTALLING THE BRACKETS.	  ONCE THE BRACKETS WERE INSTALLED, THE ORIGINAL RIVET PATTERN WAS NOT PICKED UP TO THE SIDES OF THE BRACKET MOUNTING.  	THREE OF THE FOUR BRACKETS COULD HAVE AT LEAST ON THE RIVET ON EACH SIDE OF THE BRACKET ADDED.  SOME ON BOTH SIDES.  THI	S LARGE SPACING WITH NO RIVETS IN THE STRINGERS MAY HAVE LEAD TO THE CRACKING OF BOTH THE STRINGER AND THE BULKHEAD.  TH	ERE IS NO EVIDENCE THAT ANY OF THESE COMPONENTS HAVE EVER BEEN CHANGED.	1	H	7	1 	3O	3	O	 	3A13    	E295				 
2003123000084	20031230	00084	SW  	2003	12	30	2003FA0001260    	1	20031119	G	3230	2032071	CLUTCH SPRING   			MOONEY	M20   	M20S        	5870226	SW  	CONT  	O550  	IO550*      	 	SO  	MCAULY	2A34C	2A34C*      	GL  	MLG	BROKEN          	B			OF1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	2234X	178  				300001	679343	983151		IN FLIGHT, 178.3 HOURS SINCE COMPLIANCE WITH MFG SB AND MANDATORY REPLACEMENT OF NO BACK CLUTCH SPRING WITH NEW.  BOTH T	ANG ENDS BROKE OFF OF SPRING INSIDE OF LANDING GEAR ACTUATOR WHEN GEAR WAS SELECTED DOWN FOR LANDING.  ONE BROKEN TANG A	PPARENTLY JAMMED BETWEEN THE NO BACK CLUTCH SPRING AND THE NO BACK CLUTCH SPRING HOUSING MAKING EITHER ELECTRICAL OR EME	RGENCY MANUAL EXTENSION OF THE LANDING GEAR IMPOSSIBLE.  AC WAS LANDED, GEAR UP, UNEVENTFULLY BUT SUBSTANTIAL DAMAGE TO 	PROPELLER AND BOTTOM OF FUSELAGE WAS CAUSED BY CONTACT WITH RUNWAY.  INVESTIGATION UNDER WAY, OTHER REPORTS OF IDENTICAL	 FAILURES.	1	L	7	1 	3O	3	O	RT	2A3     	E3SO	5	C	P3EA	 
2003123000056	20031230	00056	CE  	2003	12	30	2003FA0001261    	1	20031128	G	7500	131823EM1360	LINE            			BEECH 	B300  	B300        	1159232	CE  										RT BLEED AIR	LEAKING         	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	447TF	199  				FL364				PILOT REPORTED RT BLEED AIR LINE FAIL ANNUNCIATOR CAME ON, CLIMBING THROUGH FL 260.  INVESTIGATED AND TROUBLESHOT IAW MM	 26-11-00.  FOUND SMALL HOLE IN BLEED AIR WARNING EVA TUBING IN FORWARD RT CABIN UNDERFLOOR AREA.  NO BLEED AIR LEAKS NO	TED ADJACENT TO AREA DURING ENGINE GROUND RUNS.  TUBING NOT CHAFED ON ADJACENT STRUCTURE OR COMPONENTS.  SPLICE-REPAIRED	 TUBING IAW MM AND RETURNED TO SERVICE.  POSSIBLE TUBING MFG DEFECT, SECOND SIMILAR OCCURRENCE NOTED IN LATE MODEL AIRCR	AFT.		2	L	7	2 	4T			RT	A24CE   					 
2003123000067	20031230	00067	GL  	2003	12	30	2003FA0001262    	1	20031120	G	2820		VENT            			AVIAT 	A1    	A1A         	2210405	GL  	LYC   	O360  	O360*       	41514	EA  					FUEL SYSTEM	OBSTRUCTED      	D			V2AR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	49349					1149				ON RUNUP,  ENGINE WOULD QUIT.  ALLOWED TO SIT APPROX 3 MINUTES, IT WOULD START AND RUN, THEN QUIT.  WHEN FUEL CAP WAS RE	MOVED A WHOOSH OF INCOMING AIR WAS HEARD.  ENGINE RAN WITH THE CAP OFF.   SUSPECT ICE BLOCKING FUEL VENT LINES INSIDE WI	NG.  AFTER OVERNIGHT IN HANGER, BOTH VENTS FREE.				1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2003122900188	20031229	00188	CE  	2003	12	29	2003FA0001263    	1	20031209	G	3260	622EN186	SQUAT SWITCH    			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					LT MLG	MISSING         	B			WC7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	431YD					5250431				PILOT REPORTED THE SQUAT SWITCH WAS INOPERATIVE.   AFTER INVESTIGATION MAINTENANCE FOUND THAT SCREW AND NUT THAT FASTEN 	THE ROLLER TO THE SWITCH PLUNGER HAD FALLEN OFF AND THE ROLLER DEPARTED THE AIRPLANE RENDERING THE SQUAT SWITCH INOPERAT	IVE.  SUGGEST A MORE POSITIVE METHOD OF ATTACHING THE ROLLER, PERHAPS A STEEL RIVET, TO PREVENT THIS FROM HAPPENING AGAI	N.			1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2003123000098	20031230	00098	CE  	2003	12	30	2003FA0001264    	1	20031125	G	5540	905241093	BRACKET         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6*        	52043	EA  					RUDDER BOOST	GOUGED          	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	439PW	842  				LJ1589				DURING SCHEDULED PHASE INSPECTION NOTED OB SIDE OF RT RUDDER BOOST BRACKET AT FS 303 GOUGED DEEPLY THROUGH BY ADJACENT C	ABLE AT AFT END.  LOCATION JUST IB OF AFT FUSELAGE ACCESS DOOR.  APPEARS BRACKET HAD BEEN INSTALLED INCORRECTLY AT MFG O	R HAD SOMEHOW BECOME BENT OVER REPLACED BRACKET WITH NEW PN 905241093 BRACKET.  AFTER BRACKET REPLACEMENT ADEQUATE CABLE	 CLEARANCE NOTED.  WOULD RECOMMEND CHAFE PROTECTION TO BE BONDED TO BRACKET TO PREVENT CABLE/BRACKET DAMAGE IN CASE OF B	RACKET BEING BENT SLIGHTLY.		1	L	7	2 	3T	3	T	RT	3A20    	E2NE				 
2003122900204	20031229	00204	SO  	2003	12	29	2003FA0001265    	1	20031111	G	3220	40336000	DRAG BRACE      			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6*        	52043	EA  					NLG	CRACKED         	B			GW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	202HC					31T7820036				DURING ROUTINE EVENT, 2 INSPECTION IT WAS DISCOVERED THE NOSE LANDING GEAR UPPER RT SIDE DRAG BRACE RETRACTION LUG ATTAC	H POINT EXHIBITED A CRACK INDICATION.  THE CRACK INDICATION WAS DISCOVERED USING (FPI).  REMOVAL OF THE NLG UPPER RT SID	E DRAG BRACE IS RECOMMENDED TO FACILITATE THE INSPECTION.  NUMEROUS CRACK INDICATIONS HAVE BEEN DETECTED ON ALL MODELS O	F AC.			1	L	7	2 	3T	3	T	 	A8EA    	E2NE				 
2003122900203	20031229	00203	CE  	2003	12	29	2003FA0001266    	1	20031126	G	2710		CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					AILERONS	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	559AM					6507107				DURING A PHASE 5 AIRFRAME INSPECTION, THE RT SIDE AILERON CABLES WERE FOUND TO BE RUBBING THE RT SPOILER ACTUATOR HYDRAU	LIC LINE.  THE DAMAGED AREAS ON THE CABLES WERE AT RT WING STA 266 ON THE AFT SIDE OF THE WING REAR SPAR.  THE PROTECTIV	E SLEEVES ON THE CABLES WERE NEARLY WORN THROUGH TO THE POINT OF STARTING TO WEAR INTO THE CABLE STRANDS.  THIS DAMAGE W	AS CAUSED DUE TO THE LOCK NUT, SECURING THE ACTUATOR HYDRAULIC LINE ELBOW, HAVING COME LOOSE ALLOWING THE HYDRAULIC LINE	 TO ROTATE AND THE B-NUTS, ON THE LINE, TO COME IN CONTACT WITH THE CABLES.  THIS HYDRAULIC LINE SHOULD BE CHECKED FREQU	ENTLY FOR SIGNS OF LOOSENING.	2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2003122900196	20031229	00196	SO  	2003	12	29	2003FA0001267    	2	20031108	G	8530	538304	PUSHROD         			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	NR 1 CYL EXHAUST	FAILED          	D			CMIS	A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	07	5497N		1071 			18267760	470501	807508		ON ROUTINE FLT PILOT HEARD A BANG AND ENGINE LOST POWER BUT CONTINUED TO RUN.  UNABLE TO MAINTAIN ALTITUDE PILOT MADE AN	 OFF AIRPORT LANDING.  FOUND EXHAUST PUSHROD BENT, WORN AND BROKEN.  REMOVED ALL CYLINDERS AND FOUND NR 1 CYLINDER INTAK	E PUSHROD BENT SLIGHTLY AND NR 5 CYLINDER EXHAUST PUSHROD BENT SEVERELY.  SUSPECT PUSHRODS WERE BENT BY BINDING OF THE V	ALVES.  THIS ENGINE WAS REMANUFACTURED ON 11-18-99 USING NEW CYLINDERS.			1	L	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003122900189	20031229	00189	SO  	2003	12	29	2003FA0001268    	1	20031125	G	8011		BUSHING         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					STARTER	FAILED          	B			WS9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	9557C				D062804	287816492	L798039A			BUSHING ON DRIVE END OF STARTER CAME OUT AFTER LESS THAN 5 HRS.  THIS WAS A NEW STARTER INSTALLED ON A NEWLY OVERHAULED 	ENGINE.  EITHER BUSHING DID NOT FIT TIGHT ENOUGH IN HOUSING OR IT WAS TOO SOFT OF MATERIAL.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003123000007	20031230	00007	CE  	2003	12	30	2003FA0001269    	1	20031208	G	5520	12604301	BEARING         			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520*      	17032	SO  					ELEVATOR	INOPERATIVE     	B			L3CR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	6490N					21063064				(ELEVATOR ARM ASSY) THE BEARING OF THE ARM CAME OFF DURING FLIGHT AND JAMMED THE ELEVATOR.						1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2003123000008	20031230	00008	SO  	2003	12	30	2003FA0001270    	1	20031202	G	5540		TORQUE TUBE     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	27329	5958 			316120	317752150				WHEN COMPLYING WITH MFG SB 1105A, RUDDER TORQUE TUBE INSPECTION, CORROSION WAS FOUND.  UPON REMOVING THE EFFECTED PARTS 	FOR REPLACEMENT, THE LARGEST AREA OF CORROSION WAS FOUND ON THE BOTTOM RIB FORWARD OF THE FRONT SPAR.  THIS AREA IS NOT 	ADDRESSED IN THE SB AS TO BE INSPECTED.  THE SB ONLY COVERS THE AREA AFT OF THE FRONT SPAR.  I FEEL THAT IN ORDER TO PER	FORM A THOROUGH INSPECTION OF THE AFFECTED AREA THE SB NEEDS TO BE REVISED TO NCORPORATE PROVISIONS FOR ACCESS TO THIS A	REA FOR INSPECTION.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003122900200	20031229	00200	EA  	2003	12	29	2003FA0001271    	2	20031202	G	8500		CRANKCASE       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE	FAILED          	D				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			EA	03	57062	3785 				3172	L1844848			DURING ROUTINE FLIGHT, LOUD NOISE WAS HEARD.  RT ENGINE WAS SHUT DOWN AND SECURED.  AFTER AN UNEVENTFUL LANDING, AN INSP	ECTION REVEALED A CATASTROPHIC CRANKCASE FAILURE AT THE NR 3 CYLINDER LOCATION HAD OCCURRED.  CYLINDER WAS COMPLETELY SE	PARATE FROM CASE.  CASE WAS CRACKED AROUND BASE STUD AREA.  CAUSE WAS DETERMINED TO BE IN THE CRANKCASE ITSELF.  ENGINE 	HAD 217 HOURS SINCE OVERHAUL AND WAS RUNNING NORMAL WITH NO PROBLEMS REPORTED.			1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2003122900213	20031229	00213	SO  	2003	12	29	2003FA0001272    	1	20031202	G	2497	587866	MASTER SWITCH   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					COCKPIT	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	27329	5950 				317752150				DURING VISUAL INSPECTION, 2 OR THE 8 EXTERNAL WIRE CONNECTIONS WERE FOUND TO BE LOOSE.  DISASSEMBLY OF THE SWITCH REVEAL	ED LOOSE INTERNAL CONNECTIONS AS WELL.  CORRECT ELECTRICAL OPERATION WAS QUESTIONABLE.  SEVERAL REPORTS OF HAVING A SPLI	T POWER BUSS WERE OBSERVED.  THIS SHOULD NOT BE.  TIME AND USE OF A NEWLY INSTALLED SWITCH WILL VERIFY IF THIS WAS THE C	AUSE OR IF OTHER PROBLEMS EXIST.  TIME ON DEFECTIVE SWITCH WAS APPROX 5950 HOURS.  RECOMMEND A THOROUGH VISUAL INSPECTIO	N BE ACCOMPLISHED AT ANNUAL.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003122900210	20031229	00210	CE  	2003	12	29	2003FA0001273    	1	20031205	G	2460	70000150	CIRCUIT BREAKER 			BEECH 	200   	B200        	1152922	CE  										COCKPIT	TRIPPED         	B				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			EA	21	87SA	8491 				BB1089				DURING CLIMB, AC RT NR 1 BUSS FEEDER 50 AMP BREAKER OPEN.  LT NR 1 BUSS FEEDER BREAKER OPENED SHORTLY AFTERWARD RESULTIN	G IN LOSS OF PILOT SIDE EFIS, MFD, AND VARIOUS OTHER SYS. CREW RETURNED TO FLIGHT ORIG POINT, LANDED WITHOUT INCIDENT. V	ISUAL INSP OF CB PANEL REVEALED NO DEFECTS. COMPLETED ELECTRICAL LOAD DISTRIBUTION INSP IAW MFG 200 SERIES MM. NO DEFECT	S SEEN, UNABLE TO DUPLICATE FAULT.  FLIGHT PERMIT OBTAINED TO MAINT. FACILITY. INSP COMPLETED WITH AC LOAD CALCULATION, 	COULD NOT DUP  FAULT.  MFG TECH CONTACTED AND INFORMED OF DIFFICULTY. MFG STATED THIS FAILURE IS NOT UNCOMMON DUE TO CB 	FATIGUE OVER TIME IN SERVICE.  REMOVED AND REPLACED BREAKERS WITH NEW, OPS CK NORMAL.  AC RETURNED TO SERVICE.	1	L	7	2 	4T			 	A24CE   					 
2003123000016	20031230	00016	EU  	2003	12	30	2003FA0001274    	1	20031219	G	5311		FRAME           			AGUSTA	A109  	A109E       	0260119	EU  										FUSELAGE	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	1YU					11130				CRACKED FRAMES AT TB/VERTICAL FIN JUNCTION.  ADDITIONALLY THE VERTICAL FIN STRUCTURE IS CRACKED AS WELL.  THIS IS THE SE	COND SHIP IN THE LAST 90 DAYS THAT HAS HAD THIS SAME DAMAGE FOUND.  THE SRM DETAILS THE INDICATIONS AND REPAIR FOR THE F	RAMES.  AUGUSTA PROVIDED DATA FOR THE VERTICAL FIN REPAIR.  THIS REPORT IS SUBMITTED IAW OUR IPM AND AS REQUIRED BY 14 C	FR 145.63.			1	G	7	2 	3U			RT	H7EU    					 
2003123000049	20031230	00049	GL  	2003	12	30	2003FA0001275    	1	20031205	G	8011	642083A10	STARTER         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	WORN            	P				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	05		96   				0374	686704			STARTER ADAPTER FAILURE.  STARTER WOULD NOT TURN ENGINE.  NO METAL CHIPS FOUND IN ENGINE OIL AT THIS TIME BUT POTENTIAL 	EXISTS WITH THIS TYPE OF FAILURE.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2003123000052	20031230	00052	CE  	2003	12	30	2003FA0001276    	1	20031219	G	2720		PULLEY          			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RUDDER	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	791QS					6507091				INITIAL INSPECTION DURING A PHASE 5 OF AFT, OB RUDDER PULLEY, FOUND PULLEY TO HAVE WEAR ON IB EDGE. FURTHER INVEST FOUND	 AFT PULLEY TO BE CHAFING ON MOUNTING BRACKETS, & BE WEARING TO A KNIFE EDGE ON THE IB EDGE. ALSO FOUND, RUDDER CABLE TO	 HAVE BROKEN STRANDS BEYOND LIMITS IAW  MM. FURTHER INVESTIGATION FOUND OB RUDDER CABLE TO BE MISALIGNED ENOUGH THAT IT 	PUT A SIDE LOAD ON AFT PULLEY, CAUSING THE PULLEY TO CHAFE ON THE PULLEY BRACKETS. IT ALSO CAUSED THE WEAR OF THE PULLEY	, AND HAD WORN THE PULLEY ENOUGH TO ALLOW IT TO CHAFE ON THE EXIT HOLE. IT APPEARED THAT SOMEONE ELSE HAD NOTICED THIS B	EFORE, UNKNOWN WHEN, AND HAD BENT THE PULLEY BRACKETS TO TRY AND KEEP THE CABLE FROM CHAFING ON THE EXIT HOLE.	2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2003123000054	20031230	00054	NM  	2003	12	30	2003FA0001277    	1	20031218	G	5730		SKIN            			LKHEED	P2V   	P2V7        	5260112	NM  	WRIGHT	R3350 	R3350*      	67040	EA  					LT WING	CRACKED         	F				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	139HP	9034 				145906				CRACKS EMANATING FROM THE LT AND RT MLG FORWARD LOWER CUTOUTS IN THE CENTER WING SKIN.  CRACKS RUN FORWARD FROM THE IB C	ORNERS TO THE FIRST AND SECOND RIVETS.  CRACKS DO NOT CONTINUE TO THE EDGE OF THE SKIN.  LOCATIONS OF THE CUTOUTS ARE JU	ST INBOARD OF THE NACELLE WALLS AT WING STATIONS RT 128.5, 171.5 AND LT 128.5,171.5.				2	M	7	2 	4R	4	R	RT	A1RM    	E272				 
2003123000055	20031230	00055	CE  	2003	12	30	2003FA0001278    	1	20031214	G	2750	51155382	BRACKET         			CESSNA	402   	402C        	207590R	CE  										TE FLAP	BROKEN          	E				L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			SW	13	442BK					402C0332				FAILURE OF RT FLAP INBOARD ACTUATING BELLCRANK BRACKET P/N 5115538-2 WHICH IN TURN CAUSED FAILURE OF FLAP BELLCRANK P/N 	0822275-55. AIRCRAFT LANDED WITHOUT INCIDENT, WITH FLAPS RETRACTED.					1	L	7	2 	3O			 	A7CE    					 
2003123000086	20031230	00086	CE  	2003	12	30	2003FA0001279    	1	20031219	G	5530		FRAME           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200*       	17020	SO  					EMPENNAGE	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	1YU					15077311				CRACKED FRAME AT TB/VERTICAL FIN SPAR JUNCTION. THIS IS THE SECOND SHIP WITH AN IDENTICAL CRACK THAT HAS BEEN SEEN IN TH	E LAST 90 DAYS.  THE MFG SRM DETAILS THE REQUIRED REPAIRS. DETECTION IS POSSIBLE USING BRIGHT LIGHT AND MIRROR, OR BY DI	RECT OBSERVATION.  ADDITIONALLY THE VERTICAL FIN STRUCTURE ON BOTH SHIPS WAS CRACKED AND REQUIRED SUBSTANTIAL REPAIR USI	NG DATA TO FABRICATE AND INSTALL DOUBLERS.			1	H	7	1 	3O	3	O	 	3A19    	E252				 
2004042700049	20040427	00049	GL  	2004	4	27	2003FA0001280    	1	20030116	G	2435	642083A10	STARTER GEN     			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  					ENGINE	FAILED          	P				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			SO	05		41   	41   							STARTER ADAPTER FAILED.  WOULD NOT TURN PROP.  NO METAL WAS FOUND IN THE ENGINE OIL THIS TIME BUT POTENTIAL EXISTS WITH 	THIS TYPE FAILURE.					1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2004021200163	20040212	00163	CE  	2004	2	12	2003FA0001281    	1	20031216	G	5320	MM67036511002	INTERCOSTAL     			LEAR  	60    	60LEAR      	5170707	CE  	GE    	CF34  	CF34*       	 	NE  					AFT CARGO BAY	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	247FX					187				RT HYDRAULIC INTERCOSTAL (LUNCHBOX PAN) IS CRACKED AT THE CASE DRAIN LINE IN THE AFT CARGO BAY AT FS 1082.   STRESS FATI	GUE AT THE RADIUS OF THE PAN.  RECOMMENDATION:  REMOVED UNSERVICEABLE LUNCH BOX PAN (PN MM670-365-002, LOCATED AND DRILL	ED NEW SERVICEABLE LUNCH BOX PAN (PN MM670-36511-002), AND INSTALLED SERVICEABLE LUNCH BOX PAN IAW CRJ SRM 51-42-21, 51-	42-06, AND THE CRJ AMM 51-23-00.  PRESSURIZATION LEAK CHECK OF THE LUNCH BOX PAN IS GOOD IAW CRJ700 AMM 21-31-00-910-801	-A01.  (EA09200401239)		2	L	7	2 	4F	4	F	RT	A10CE   	E15NE				 
2004021200186	20040212	00186	NM  	2004	2	12	2003FA0001282    	1	20031125	G	2913	123412	COVER           			BOEING	737   	737*        	       	NM  										HYD VALVE	CRACKED         	C			IU6R	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			NM	01										COVER CRACKED UPON FUNCTIONAL TESTING.  IMPROPER PROCESSING (STRESSED).    (WC/ NR 182380)						2	L	7	2 	4F			RT	A16WE   					 
2004021200187	20040212	00187	NM  	2004	2	12	2003FA0001283    	1	20031111	G	3230	6F230926	HOUSING         			BOEING	737   	737*        	       	NM  										RESTRICTOR	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01		64322			1495					BODY IS CRACKED.  MATERIAL IN THIS AREA IS WEAK.  IMPROVE DESIGN TO ADD MORE MATERIAL TO THIS AREA.  (FXS  NR 181999)						2	L	7	2 	4F			RT	A16WE   					 
2004012300071	20040123	00071	NM  	2004	1	23	2003FA0001284    	1	20031111	G	3230	66F23095	HOUSING         	CRISSAIR    		BOEING	737   	737*        	       	NM  										RESTRICTOR	CRACKED         	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01		64322			1413					BODY IS CRACKED.  MATERIAL IN THIS AREA IS WEAK.  NEED TO IMPROVE DESIGN TO ADD MORE MATERIAL TO THIS AREA.  (FXS  NR 18	1999).					2	L	7	2 	4F			RT	A16WE   					 
2004021200188	20040212	00188	NM  	2004	2	12	2003FA0001285    	1	20031111	G	3230	45035	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										VALVE	CORRODED        	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01		31926	11123		18556M					BORE IS PITTED CAUSING LEAKAGE.  MOISTURE ALLOWED THRU VENT, CORRODED UPPER BORE WEAKENING THE MATERIAL.  NEED TO IMPROV	E DESIGN TO PREVENT MOISTURE FROM REACHING BORE.  (FXS  NR 182014)					2	L	7	2 	4F			RT	A16WE   					 
2004021200189	20040212	00189	NM  	2004	2	12	2003FA0001286    	1	20031111	G	3230	45035	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										VALVE	CORRODED        	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01		31926	11123		18511M					BORE IS PITTED CAUSING LEAKAGE.  MOISTURE ALLOWED THRU VENT CORRODED UPPER BORE WEAKING THE MATERIAL.  NEED TO IMPROVE D	ESIGN TO PREVENT MOISTURE FROM REACHING BORE.  (FXS  NR 182014)					2	L	7	2 	4F			RT	A16WE   					 
2004021200190	20040212	00190	NM  	2004	2	12	2003FA0001287    	1	20031111	G	3230	45035	HOUSING         			BOEING	737   	737*        	       	NM  										VALVE	CORRODED        	B			IU6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					9002					BORE IS PITTED CAUSING LEAKAGE.  MOISTURE ALLOWED THRU VENT CORRODED UPPPER BORE WEAKING THE MATERIAL.  NEED TO IMPROVE 	DESIGN TO PREVENT MOISTURE FROM REACHING BORE.  (FXS   NR 181814)					2	L	7	2 	4F			RT	A16WE   					 
2004021200193	20040212	00193	SO  	2004	2	12	2003FA0001288    	1	20030911	G	2720		CONTROL CABLE   			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O360  	O360*       	41514	EA  					RT RUDDER	FRAYED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	390CC	650  				9944CC				RUDDER CABLE WAS FRAYED WHERE IT PASSES THROUGH THE FAIRLEADS, 5 OUT OF 7 BUNDLES WERE CUT THROUGH THE STAINLESS STEEL C	ABLE.					1	H	7	1 	3O	3	O	 	1A2     	E286				 
2004021300005	20040213	00005	CE  	2004	2	13	2003FA0001289    	1	20031229	G	3211	12116014	ATTACH FITTING  			CESSNA	206   	TU206D      	2073344	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C403   	GL  	MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		7642 	1230 			U20605485	291553R	779503		ON SCHEDULED 200 HRS VISUAL.  INSPECTION REVEALED ATTACHMENT FITTING MAIN LANDING GEAR OB CRACKED IN AREA OF REAR.  UPPE	R RADIUS, HISTORICAL RECORD REVELEAD ITS THIRD CHANGE.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL	 
2004021300007	20040213	00007	CE  	2004	2	13	2003FA0001290    	1	20031229	G	3211	12116014	ATTACH FITTING  			CESSNA	206   	TU206D      	2073344	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C403   	GL  	ZONE 100	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		7642 	1230 			U20605485	291553R	779503		ON SCHEDULED 200 HRS VISUAL, INSPECTION REVEALED ATTACHMENT FITTING MAIN LANDING GEAR OB CRACKED IN AREA OF REAR UPPER R	ADIUS, HISTORICAL RECORD REVELEAD ITS FOURTH CHANGE.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL	 
2004021300004	20040213	00004	CE  	2004	2	13	2003FA0001291    	1	20031229	G	3211	12116013	ATTACH FITTING  			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C403   	GL  	MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		7642 	1820 			U20605485	291553R	779503		ON SCHEDULED 200 HRS VISUAL INSPECTION, REVEALED ATTACHMENT FITTING MAIN LANDING GEAR OB CRACKED IN AREA OF FWD.  LOWER 	RADIUS CLOSE THE BOLT HOLE HISTORY RECORD REVELEAD ITS THIRD CHANGE.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL	 
2004021200154	20040212	00154	CE  	2004	2	12	2003FA0001292    	1	20031222	G	2520		CUSHION         			CESSNA	560   	560XL       	2076702	CE  										SEAT	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	687QS					5605187				NR 6 AND NR 8 CABIN SEATS WERE AT MAINTENANCE FACILITY FOR ROUTINE REFURBISHMENT. DURING DISASSEMBLY IT WAS FOUND THAT T	HE SEAT PAN CUSHIONS WERE MISSING.  IT APPEARS THEY HAD NEVER BEEN INSTALLED. NEW SEAT PAN CUSHIONS WERE FABRICATED AND 	INSTALLED FROM APPROPRIATELY BURN TESTED MATERIAL.				2	L	7	2 	4F			RT	A22CE   					 
2004021300013	20040213	00013	CE  	2004	2	13	2003FA0001293    	1	20031230	G	4940	A31290	SWITCH          			CESSNA	560   	560XL       	2076702	CE  										APU START	ERRATIC         	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	09	916CS	1195 				5605153				UPON SHUT DOWN OF APU AFTER ENGINE STARTS, AS THE APU SLOWED TO APPROX. 5 PERCENT THE APU STARTED ITSELF WITHOUT ANY INP	UT FROM THE CONTROL PANEL.  SUBSEQUENT SHUTDOWN ATTEMPTS RESULTED IN THE SAME RESULTS UNTIL THE FIFTH TIME, AT WHICH, TH	E MASTER SWITCH WAS TURNED OFF AS THE APU SLOWED TO 10 PERCENT.  THIS RESULTED IN A SUCCESSFUL SHUTDOWN.  THIS IS THE SE	COND THAT WE HAVE ENCOUNTERED THIS PROBLEM ON.  THE MANUFACTURER RECOMMENDED THAT WE CHANGE THE START/STOP SWITCH WHICH 	WE DID.  THIS CORRECTED THE PROBLEM FOR THE TIME BEING.  RECOMMENDED TO THE MFG THAT A SERVICE BULLETIN BE ISSUED TO CHA	NGE THE APU START/STOP SWITCH ON THIS MODEL AIRCRAFT.	2	L	7	2 	4F			RT	A22CE   					 
2004021200166	20040212	00166	CE  	2004	2	12	2003FA0001294    	1	20031218	G	2752	99105863RX	JACKSCREW       			CESSNA	208   	208         	2073702	CE  										FLAP ACTUATOR	BACKED OUT      	B				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			SW	07			114  			20800191				FLAP ACTUATOR JACKSCREW SEPARATED FROM THE ACTUATOR ASSEMBLY CAUSING FAILURE OF THE FLAP SYSTEM DURING TAKE OFF. TEAR DO	WN REVEALED THAT THE JACKSCREW RETAINING NUT HAD LOOSENED AND SEPARATED FROM THE JACKSCREW ALLOWING IT TO BE PULLED FROM	 THE ACTUATOR ASSEMBLY. RETAINING NUT HAD NO SAFETY LOCKING DEVICE INSTALLED.				1	H	7	1 	3T			NT	A37CE   					 
2004021200165	20040212	00165	CE  	2004	2	12	2003FA0001295    	1	20031218	G	2752		JACKSCREW       			CESSNA	208   	208         	2073702	CE  										FLAP ACTUATOR	BACKED OUT      	B				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			SW	07			114  			20800191				FLAP ACTUATOR JACKSCREW SEPARATED FROM THE ACTUATOR ASSEMBLY CAUSING FAILURE OF THE FLAP SYSTEM DURING TAKE OFF. TEAR DO	WN REVEALED THAT THE JACKSCREW RETAINING NUT HAD LOOSENED AND SEPARATED FROM THE JACKSCREW ALLOWING IT TO BE PULLED FROM	 THE ACTUATOR ASSEMBLY. RETAINING NUT HAD NO SAFETY LOCKING DEVICE INSTALLED.				1	H	7	1 	3T			NT	A37CE   					 
2004021200167	20040212	00167		2004	2	12	2003FA0001296    	4	20031223	G	2297		WIRE            			GULSTM	114   	114B        	O145001	SW  	LYC   	O540  	IO540*      	41532	EA  					CONNECTOR	MISROUTED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	6050Z					14660				DURING OPERATIONAL TEST OF AIRCRAFT PRIOR TO BEGINNING ANNUAL INSPECTION, FOUND WHEN RUNNING MANUAL ELECTRIC TRIM, WHILE	 PRESSING AND HOLDING DOWN TRIM INTERRUPT BUTTON, TRIM WOULD CONTINUE TO RUN THOUGH AT A MUCH SLOWER RATE. IF TRIM INTER	RUPT SWITCH WAS HELD FIRST, THEN THE MANUAL ELECTRIC TRIM ACTUATED, IT WOULD NOT RUN. (KFC-200 AUTOPILOT)  FOUND AVIONIC	S COOLING FAN GROUND WIRE WAS CONNECTED TO A JUNCTION TYING TRIM SERVO PIN C, AP COMPUTER P1 PIN N, P2 PIN Z THROUGH AUT	OPILOT DISCONNECT RELAY TO SERVO PIN A. COOLING FAN CIRCUIT BREAKER SUPPLIED VOLTAGE THROUGH THE MOTOR TO THIS CONNECTIO	N CAUSING TRIM TO RUN WHEN TRIM INTERRUPT WAS DEPRESSED.	1	L	7	1 	3O	3	O	RT	A12SO   	1E4				 
2004021300006	20040213	00006	CE  	2004	2	13	2003FA0001297    	1	20031229	G	3211	12116014	ATTACH FITTING  			CESSNA	206   	TU206D      	2073344	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C403   	GL  	ZONE 100	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		7642 	1230 			U20605485	291553R	779503		ON SCHEDULED 200 HRS VISUAL.  INSPECTION REVEALED ATTACHMENT FITTING MAIN LANDING GEAR OB CRACKED IN AREA OF REAR UPPER 	RADIUS, HISTORICAL RECORD REVELEAD ITS FOURTH CHANGE.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL	 
2004021700184	20040217	00184	GL  	2004	2	17	2003FA0001298    	2	20031201	G	7250	23055438	NOZZLE          								ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	CRACKED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17			613  				CAE890607S			RECEIVED THE ENGINE FOR REPAIR DUE TO HIGH OIL TEMPERATURE.  DURING INSPECTION OF THE PARTS FOUND THE WELD ON 1 OF THE 5	 TURBINE NOZZLE DIAPHRAGM RETAINING KEYS WAS CRACKED THROUGH THE CENTER FOR ALMOST ITS ENTIRE LENGTH.  TURBINE  TSO 613 	HOURS  (KES WO NR A03611)									3	U			E1GL				 
2004021700185	20040217	00185	SO  	2004	2	17	2003FA0001299    	1	20031124	G	2810	78012	BLADDER         			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					FUEL CELL	FAILED          	B			AKGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	05	2234B	2770 	116  			447995107				DISCOVERED FUEL LEAKING, LOWER WING LT ENGINE NACELLE.  REMOVED FUEL BLADDER AND FOUND THE LOWER IB NIPPLE CRACKED AND A	LLOWING FUEL TO LEAK.  FUEL CELL HAD BEEN REPAIRED A YEAR EARLIER.  DATE OF MFG AUGUST 1978.  INSTALLED NEW BLADDER, IT 	WAS FELT THAT THIS BLADDER HAD REACHED ITS USEFUL LIFE LIMIT.				1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2004050600081	20040506	00081	SW  	2004	5	6	2004F00092       	1	20030901	G	8120	46C19836G	TURBOCHARGER    			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE	MALFUNCTIONED   	G				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			NM	02	698R	71   				500A91019	L320248			TURBOCHARGER REPORTED BY TOWER TO BE SMOKING DURING APPROACH.  TURBOCHARGER SHIPPED TO MFG FOR INSPECTION.  PRELIMINARY 	EVALUATION: COMPRESSOR RUB.					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2004050600082	20040506	00082	SW  	2004	5	6	2004F00093       	1	20030901	G	8120	46C19836G	TURBOCHARGER    			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	FAULTY          	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	02	222LE	39   				1525187	CK4927B			TURBOCHARGER LOW IN PERFORMANCE DURING FLIGHT.  TURBOCHARGER SHIPPED TO MFG, FOR INSPECTION.  PRELIMINARY EVALUATION: CO	MPRESSOR RUB.					1	H	7	2 	3O	3	O	 	6A1     	E14EA				 
2004022300003	20040223	00003		2004	2	23	2004FA0000000    	4	20030918	G	2397	GMA340	WIRE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					AUDIO PANEL CONN	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	53215					2842170				SB 1135 DOES NOT APPLY DUE TO AIRCRAFT SERIAL NUMBER, HOWEVER, CONNECTOR WAS WIRED WITH PILOT HEADPHONES WIRE IN LOCATIO	N 31 INSTEAD OF 16.  AIRCRAFT WAS CORRECTED TO ALLOW FAILSAFE USE OF NR 1 COM.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2004012300059	20040123	00059	SO  	2004	1	23	2004FA0000001    	1	20031219	G	3250	63300014	HORN            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					NLG STEERING	BROKEN          	D			ULOV	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	13	354MR	1015 				2843315				FOUND RUDDER LOOSE, FOUND RT ARM TO NOSE WHEEL STEERING ARM BROKEN OFF.  PART APPEARED TO HAVE BEEN CRACKED FOR SOME TIM	E.  RESEARCH SHOWS WHEEL FAIRINGS REMOVED FOR REPAIR DUE TO HARD CROSSWIND LANDING 145 HOURS.  PREVIOUSLY, AND CABLE TEN	SION ADJUSTED AT LATER DATE.  SUGGEST HORN BE INSPECTED AFTER HARD LANDINGS OR EXCESS CABLE TENSION ADJUSTMENT REQUIRED.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2004022300005	20040223	00005	SO  	2004	2	23	2004FA0000002    	2	20031108	G	8530	538304	PUSHROD         			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	NR 1 CYLINDER	WORN            	D			CMIS	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	07	5497N		1071 		1265	18267760	470501	807508		ON ROUTINE FLIGHT PILOT HEARD A BANG AND ENGINE LOST POWER BUT CONTINUED TO RUN.  UNABLE TO MAINTAIN ALTITUDE, PILOT MAD	E AN OFF AIRPORT LANDING.  FOUND NR 1 EXHAUST PUSHROD BENT, WORN AND BROKEN.  REMOVED ALL CYLINDERS AND FOUND NR 1 CYLIN	DER INTAKE PUSHROD BENT SLIGHTLY AND NR 5 CYLINDER EXHAUST PUSHROD BENT SEVERELY.  SUSPECT PUSHRODS WERE BENT BY BINDING	 OF THE VALVES.  THIS ENGINE WAS REMANUFACTURED 11/18/99 USING NEW CYLINDERS.			1	L	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2004012300045	20040123	00045	CE  	2004	1	23	2004FA0000003    	1	20031112	G	2510	551900921	SEAT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	204CF					5500238				UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  	CHAIR WAS REPAIRED IAW STC ST01042WI STRUCTURAL SEAT REPAIR.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2004012300027	20040123	00027	CE  	2004	1	23	2004FA0000004    	1	20031009	G	3000	654A58	SWITCH          			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					DE ICE SYSTEM	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	440DS					RK8				MULTIPLE FAILURES OF TAIL DEICE SYSTEM.  ALWAYS GROUND TESTED GOOD.  FINALLY FLEW AIRCRAFT BACK TO MANUFACTURER FOR REPA	IR.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2004012300028	20040123	00028	EA  	2004	1	23	2004FA0000005    	2	20031002	G	8520		CAMSHAFT        			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ENGINE	SPALLED         	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	01	102LP	407  				18281121	L2791548A			ENGINE MAKING METAL, MFG DETERMINED IT TO BE CAMSHAFT/ LIFTER MATERIAL ENGINE RETURNED TO FACTORY FOR REPAIR.  THIS IS T	HE SECOND OCCURRANCE OF CAMSHAFT/ LIFTER SPALLING AND 5TH OCCURANCE OF ENGINES MAKING METAL IN A FLEET OF 5.  POSSIBLE M	ANUFACTURING AND MATERIAL PROBLEMS FROM THE MFG.				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2004012300029	20040123	00029	NM  	2004	1	23	2004FA0000006    	1	20031015	G	5753	654792327	SPAR            			BOEING	737   	737300      	1384610	NM  	GE    	CFM56 	CFM56*      	13802	NE  					LT WING TE FLAP	CRACKED         	D			SWAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	379SW				1898	26586				CRACKED AT OB AFT FLAP TRACK LOWER ATTACH HOLES.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2004022300008	20040223	00008	CE  	2004	2	23	2004FA0000007    	1	20031014	G	5610	10138402522	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	BROKEN          	C			WXHM	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	01	222KA	1384 				BB49				WHILE AT CRUISE 25,000 FT, WINDSHIELD ON LOW, INNER PANEL OF CO-PILOTS WINDOW SHATTERED.  MFG INSPECTED AND DETERMINED F	AILURE RESULT ON (CHIP PLY) FAILURE.  (NM13PLV200401669)					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2004010800053	20040108	00053	EA  	2004	1	8	2004FA0000008    	2	20031017	G	7414	35255514	MAGNETO         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	4763D					17272354				AIRCRAFT HAD PAST HISTORY OF ENGINE RUNNING RUFF AT TIMES.  AT 12 MILES OUT FROM AIRPORT, ENGINE STARTED TO RUN RUFF.  A	T 6 MILES OUT FROM AIRPORT ENGINE SHUT DOWN AND WOULD NOT START AGAIN.  THE AIRCRAFT MADE IT TO RUNWAY, OK.  CHECKED MAG	 AND FOUND BOTH CAPACITORS P LEADS SHORTED TO COVER.  COIL ALSO BAD.  BURNS ON BACK COVER SHOW THAT CAPACITOR LEADS HAVE	 BEEN ARCHING TO COVER FOR SOME TIME.  THE SPADE CLIPS ON CAPACITOR LEADS WERE LOOSE AND COULD SLIDE REARWARD TO THE POR	T WHERE ARCHED TO REAR COVER SHUTTING DOWN ENGINE OR RUNNING RUFF.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2004022300013	20040223	00013	NM  	2004	2	23	2004FA0000009    	1	20031212	G	5700		FLYING WIRE     			CHRIS 	HUSKY 	A1          	221020X	NM  	LYC   	O360  	O360A1D     	41514	EA  					TAIL UP	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	2868M	3992 				1005				UPPER LT FLYING WIRE TAIL BROKE ABOUT 6 INCHES FROM TOP ATTACH POINT.  WHILE FLYING, FLAT TYPE WIRE.						1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2004022300014	20040223	00014		2004	2	23	2004FA0000010    	4	20031206	G	2561	GA12	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOAT DEVICE FAILED, CELL PRESSURE TEST DUE TO TWO (2) SMALL PUNCTURE HOLES IN CELL.  BEYOND MFG RECOMMENDED 	REPAIR LIMITS.  DOM: FEB 1990.																		 
2004022300015	20040223	00015		2004	2	23	2004FA0000011    	4	20031121	G	2561	KSE35L8P0723E105	LIFE VEST       																	CELL	DAMAGED         	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										ONE CELL DAMAGED DUE TO HIGH IMPACT.  DAMAGE BEYOND REPAIR MANUAL LIMITS.																			 
2004022300021	20040223	00021	EA  	2004	2	23	2004FA0000014    	2	20031119	G	8550	STD91	PLUG            			PIPER 	PA46  	PA46350P    	7104602	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	LOOSE           	C			HPFR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	09	4170D					4636300	L1059461A			PLUG WAS FOUND LOOSE, BEGAN TO LEAK OIL.  CONTINUED OPERATION WOULD HAVE CAUSED PLUG TO FALL OUT RESULTING IN EXTREME OI	L LOSS.  THIS IS THE SECOND TIME THIS PLUG WAS LOOSE.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2004022300022	20040223	00022	SO  	2004	2	23	2004FA0000015    	1	20031210	G	5330	68501801	SKIN            			PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540*      	41532	EA  					FUSELAGE	CORRODED        	B			E81R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	4304W	1390 				328306029				AFTER REMOVING RT SIDE LOWER CENTER FUSELAGE EXTERIOR HAD ASSY STIFFENER AND PN 62544-01 FORWARD FAIRING TO FACILITATE O	THER REPAIRS, FOUND CONSIDERABLE CORROSION ON MOUNTING FLANGES AND ADJACENT FUSELAGE SKIN.  AREA IS SUBJECT TO ENGINE EX	HAUST AND MUD/DIRT, ETC.  TOSSED UP BY NOSEWHEEL.  HAT SECTIONS ARE NOT SEALED TO FUSELAGE SKIN, ALLOWING CORROSIVE  PRO	DUCTS TO SEEP IN OVER TIME.  SUGGEST ALL SIMILAR PA28/PA32 AIRCRAFT SHOULD HAVE 1-TIME INSPECTION AFTER 10 YEARS, HATS/S	KIN REPLACED OR REPAINTED WITH EPOXY PAINT, THEN REINSTALLED WITH 2 PART MIS-S8802 TYPE SEALANT OR SIMILAR.		1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2004022300023	20040223	00023	SO  	2004	2	23	2004FA0000016    	1	20031219	G	2722	2018500	BELLCRANK       			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER	CRACKED         	B			GFZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	801PC	5500 				244256				DURING ANNUAL INSPECTION, A CRACK WAS FOUND IN THE BELLCRANK BOLT HOLE.  ON CLOSER INSPECTION IT WAS FOUND THAT ALL FOUR	 BOLT HOLES HAD CRACKS IN VARIOUS STAGES OF PROGRESSION.  THE CRACKS BEGIN AT THE END OF THE PART AND PROCEED TOWARDS TH	E BOLT HOLE, ONLY ONE HAS MADE IT ALL THE WAY TO THE BOLT HOLE.  THE LARGEST CRACK COULD BE SEEN CLEARLY BUT THE REMAINI	NG THREE REQUIRED MAGNIFICATION.  A DYE PEN INSPECTION PRODUCED THE MOST CLEAR RESULTS.  ADDITIONALLY, AFTER THE INITIAL	 CLEANING, A CRACK WAS FOUND AT ONE OF THE HOLES FOR THE RUDDER CABLE ATTACHMENT HARDWARE.  THIS FIFTH CRACK PROGRESSES 	ALL THE WAY FROM THE HOLE TO THE OUTER EDGE.  THIS AIRCRAFT HAS SPEED MODS AND IS NOT RESTRICTED TO 203 MPH.	1	L	7	1 	3O	3	O	 	1A15    	E14EA				 
2004012300081	20040123	00081	SO  	2004	1	23	2004FA0000017    	1	20031219	G	5530	2070703	BRACKET         			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					RUDDER	CRACKED         	B			GFZR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	801PC	5500 				244256				DURING RUDDER REMOVAL FOR REQUIRED MAINTENANCE, A CRACK WAS FOUND IN MIDDLE RUDDER HINGE BRACKET MOUNTED ON THE VERTICAL	 FIN.  THE CRACK IS AT THE HINGE BEARING HOLE.  DUE TO THE LOCATION, THIS CRACK WOULD NOT HAVE BEEN VISIBLE WITHOUT REMO	VING THE RUDDER FIRST.  THIS AIRCRAFT HAS SPEED MODS AND IS NOT RESTRICTED TO 203 MPH.				1	L	7	1 	3O	3	O	 	1A15    	E14EA				 
2004022300026	20040223	00026	SO  	2004	2	23	2004FA0000018    	1	20031124	G	2823		O-RING          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					SHUTOFF VALVE	LEAKING         	B			AKGR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	05	2234B	2770 			236405	447995107				WHILE ATTEMPTING TO REPAIR A FUEL SEEPAGE PROBLEM ON THE LT ENGINE PRIMER PUMP, IT WAS DISCOVERED THAT THE FUEL SUPPLY C	OULD NOT BE SHUT OFF.  AFTER REMOVING THE FUEL FROM THE LT AND RT WINGS.  THE LT WING FUEL VALVE WAS REMOVED FROM THE SY	STEM AND DISASSEMBLED.  THE O-RINGS HAD DETERIORATED AND COME OUT OF THE RETAINING GROOVE AND WERE IN PIECES ROLL UP IN 	THE CENTER OF THE VALVE BODY.			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2004022300028	20040223	00028		2004	2	23	2004FA0000019    	4	20031231	G	3130		CONVERTER       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       	 	NE  					AFDAU	INTERMITTENT    	B			SVUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	271AT	2243 			307	273				FDAU STA LIGHT ON. CONVERTER INTERMITTENT      (WO NR 34227)						2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
2004022300046	20040223	00046	CE  	2004	2	23	2004FA0000021    	1	20031226	G	7930	639305	VERNATHERM      			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					OIL COOLER	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	732YK	650  				21061879	294273R			VERNATHERM FAILED TO BYPASS OIL COOLER WHEN OIL TEMPS LOW.						1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2004022300047	20040223	00047		2004	2	23	2004FA0000022    	4	20031231	G	2215		MOTOR           																	TRIM ACTUATOR	FAILED          	B			SVUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19		5294 			398					MOTOR FAILED SPEED OF DISPLACEMENT.  SLOW SPEED.  (WO NR 33814)																			 
2004022300055	20040223	00055	CE  	2004	2	23	2004FA0000027    	1	20031117	G	3230	583800901	MOTOR           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	FAILED          	B			FFKR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	958MC	2498 				TH552				LANDING GEAR ELECTRIC MOTOR FAILED INFLIGHT PILOT HAD TO MANUALLY EXTEND GEAR.  INSTALLED NEW MOTOR.  OPS CHECK GOOD.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2004022300062	20040223	00062	SO  	2004	2	23	2004FA0000029    	1	20031105	G	5720	62086002	STIFFENER       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  	SNSNCH	76E	76EM8       	EA  	RT WING	CRACKED         	B			FQAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	430PA	2684 				2843488	L3222236A	33529K		DURING A ROUTINE INSPECTION, A MECHANIC NOTED THE AFT STIFFING CHANNEL, PN 62086-002, CRACKED AT THE MIDDLE LIGHTENING H	OLE.  ADDITIONAL INSPECTION REVEALED NO FURTHER DAMAGE.  THE CRACKS APPEAR NEW.  THIS CRACK IS NOT TYPICAL OF THE CRACKS	 FOUND PREVIOUSLY.  THIS IS A MFG INSTALLED PART.				1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2004021700182	20040217	00182	SO  	2004	2	17	2004FA0000030    	2	20031231	G	8520		PISTON          	CONT        		BEECH 	35    	J35         	1151522	CE  	CONT  	O470  	IO470C      	17026	SO  					CYLINDER	FAILED          	G				E	B	A		ENGINE SHUTDOWN         	EMER. DESCENT           	UNSCHED LANDING         		Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	13	617Q	213  				D5670	715769C			THE PISTON IN NR 4 CYLINDER SEPARATED AT THE PISTON PIN BOSS AREA ALLOWING THE CONNECTING ROD END TO PROTRUDE THROUGH TH	E ENGINE CASE AND THE COWLING. THE CYLINDER HAD THE CERMINIL PROCESS PERFORMED ON IT IN APRIL 14,2000 BY THE ECI (ENGINE	 COMPONENT INC.).THE CYLINDER TAG SHOWS TO HAVE BEEN A COMPLETE ASSEMBLY WHEN PURCHASED.				1	L	7	1 	3O	3	O	 	3A15    	E273				 
2004012200144	20040122	00144	NM  	2004	1	22	2004FA0000038    	1	20031219	G	2730		SEAL            			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  					PITCH TRIM UNIT	LEAKING         	B			SVUR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	459PS	3736 			132	3070				CAS MISCOMPARE MESSAGE AT 25000 FT.  ALSO THE MOISTURE INDICATOR IS PINK.  (WO NR 33910)						2	H	7	2 	4T	4	T	RT	A45NM   	E20NE				 
2004022300116	20040223	00116	CE  	2004	2	23	2004FA0000049    	1	20031230	G	3233	98820041	PISTON          			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					MLG ACTUATOR	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	01	9666B					172RG0955	L2990336A			RT MAIN LANDING GEAR ACTUATOR PISTON BROKE IN TWO PIECES ON GEARED PORTION.  CAUSING RT GEAR TO FAIL TO LOCK IN DOWN POS	ITION.  RESULT WAS GEAR UP LANDING.					1	H	7	1 	3O	3	O	 	3A17    	E286				 
2004022300128	20040223	00128	CE  	2004	2	23	2004FA0000056    	1	20031120	G	2830	STCSA01110CH	O-RING          			BEECH 	33    	35B33       	1151406	CE  	CONT  	O550  	IO550B      	 	SO  					QUICK DRAIN	CRACKED         	P				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	930Q	3300 	100  			CD388				DURING A PREFLIGHT INSPECTION, PILOT IDENTIFIED SEEPAGE FROM LT WING QUICK DRAIN.  FLUSHING DID NOT REVEAL DEBRIS THAT W	OULD HAVE CAUSED LEAK, AND DID NOT ARREST LEAK.  QUICK DRAIN INSTALLED 2 YEARS PRIOR DURING FUEL CELL REPLACEMENT.  ON D	ISASSEMBLY, IDENTIFIED THAT THE O-RING WAS SEVERELY DISTRESSED, AND COVERED WITH CRACKS, PROVIDED THE CORRECT O-RINGS AS	 REPLACEMENTS.  REQUESTED TO FILE SDR, SO OWNER FILING SDR TO IDENTIFY THIS ISSUE FOR TRENDING.  NOT A FLIGHT SAFETY ISS	UE - LEAK WAS MINOR.  HOWEVER, IT APPEARS THAT THE WRONG O-RINGS WERE PROVIDED WITH QUICK DRAINS BY OEM.  PART NUMBER UN	KNOWN.	1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2004022300138	20040223	00138	SO  	2004	2	23	2004FA0000060    	1	20031224	G	5511	121C3100011	RIB             			MARSH 	S2F   	S2F3S       	3951007	SO  	GARRTT	TPE331	TPE331*     	01514	WP  					STABILIZER	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	424DF	5132 				154820				DURING A 400 HOUR INSP OF THE LT HORZ STAB, CRACKS WERE FOUND AT LE RIBS OF HORZ STAB AT STA 66.108, 80.608, AND 95.108.	  CRACKS WERE NOTED WHERE RIBS ATTACH TO THE LE SKIN.  THIS AC HAS A TT 5132.1 AND 1458.1 TT SINCE IT WAS CONVERTED TO T	URBOPROP POWERED FIRE FIGHTING AC.  THE LT HORZ SHOT DAMPER WAS REMOVED DURING TURBOPROP CONVERSION.  IT WAS ORIGINALLY 	INSTALLED TO COUNTERACT ORIGINAL RADIAL ENG INSTALLATION 3 BLADED PROP HARMONIC VIBRATION AT 2300 RPM.  IT IS BELIEVED T	HAT CRACKING COULD BE CAUSED BY VIBRATION FROM TURBO PROP INSTALLATION.  ACTUAL CAUSE OF CRACKING IS CURRENTLY BEING INV	ESTIGATED AND HAS YET TO BE DETERMINED.  LT HORZ STAB LE SKIN RIBS SHOULD BE INSP FOR CRACKS.	2	H	7	2 	4O	3	T	RT	A51NM   	E2WE				 
2004012300056	20040123	00056	GL  	2004	1	23	2004FA0000061    	2	20031223	G	8520		MASTER ROD      			BELL  	47    	47G3B1      	1181028	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	8548F					6507				CRACK-LIKE INDICATION DETECTED BETWEEN WELD AND HOLE 2 AND END OF ROD.  FLUORESCENT PENETRANT INSPECTION AND MT INSPECTI	ON USED.					1	G	7	1 	3O	3	U	 	2H3     	E4CE				 
2004022300139	20040223	00139	SW  	2004	2	23	2004FA0000062    	1	20031223	G	7120	476121711289	MOUNT           			BELL  	47    	47G3B1      	1181028	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	B			E5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	8548F					6507				CRACK-LIKE INDICATIONS DETECTED ON WELD EDGES-AREAS IDENTIFIED.  FLUORESCENT AND MT INSPECTION USED.						1	G	7	1 	3O	3	U	 	2H3     	E4CE				 
2004022300147	20040223	00147	SW  	2004	2	23	2004FA0000063    	1	20031223	G	5320	471202523	GRIP            			BELL  	47    	47G3B1      	1181028	SW  	ALLSN 	250C  	250C20      	03013	GL  					THREAD	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	8548F					6507				CRACK LIKE INDICATION DETECTED IN THREAD AREA WHICH EXCEEDS 10 PERCENT.  EDDY CURRENT INSPECTION USED.						1	G	7	1 	3O	3	U	 	2H3     	E4CE				 
2004022300154	20040223	00154	SO  	2004	2	23	2004FA0000065    	1	20031204	G	7602	ALCON93882	CONTROL CABLE   			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1D5    	41532	EA  					MIXTURE	MISROUTED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	7369P					242549	L385740			MIXTURE CONTROL CABLE SECURED AND/OR ROUTED INCORRECTLY WHEN MIXTURE CONTROL CABLE WAS REPLACED AND/OR LUBED.  WHEN THE 	CABLE CAME IN CONTACT WITH NOSE GEAR EXTENSION DURING FINAL APPROACH TO RUNWAY.  THE NOSE GEAR ASSEMBLY CAUGHT THE MIXTU	RE CONTROL CABLE SOMEWHERE BETWEEN THE FIREWALL AND CARBURETOR PULLING THE MIXTURE CONTROL CABLE DOWN.  SHUTTING OFF THE	 MIXTURE AT THE CARBURETOR WITH ENOUGH FORCE TO BRAKE THE STOP ON THE MIXTURE CONTROL ARM OF THE CARBURETOR.  CORRECTED 	BY ROUTING MIXTURE CONTROL CABLE CORRECTLY AND PERFORMING GEAR RETRACTION CHECKING OPERATION.		1	L	7	1 	3O	3	O	 	1A15    	E295				 
2004022300155	20040223	00155		2004	2	23	2004FA0000066    	4	20031228	G	2561	P0201GA12	LIFE VEST       																	CELL	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOAT DEVICE CELL TESTED AND FAILED MFG RECOMMENDED PRESSURE TEST.  DOM: OCT 1979																			 
2004022300156	20040223	00156	SW  	2004	2	23	2004FA0000067    	1	20031223	G	6320	47620991	HOUSING         			BELL  	47    	47G3B1      	1181028	SW  	ALLSN 	250C  	250C20      	03013	GL  					TRANSMISSION	CRACKED         	B			E5WR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	8548F					6507				CRACK-LIKE INDICATION DETECTED AT FLUID HOLE AREA.  FP INSPECTION USED.						1	G	7	1 	3O	3	U	 	2H3     	E4CE				 
2004022300162	20040223	00162	CE  	2004	2	23	2004FA0000069    	1	20031223	G	7810	89243	EXHAUST RISER   			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					LT ENGINE	DAMAGED         	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	11	485DS					421C0459	272250R			WHILE IN IFR FLIGHT, PILOT REPORTED LOSS OF MANIFOLD PRESSURE AND EXHAUST GAS TEMPERATURE INSTRUMENTATION READINGS.  HOW	EVER MP STABILIZED AT LOWER THAN NORMAL READINGS.  MADE PRECAUTIONARY LANDING AT CLOSEST AIRPORT, WHICH MET IFR MINIMUMS	.  TECH PRESSURE CHECKED THE EXHAUST SYSTEM AND FOUND A 2.5 INCH HOLE AT THE EXHAUST DATA PLATE ON LT INSIDE EXHAUST RIS	ER.  THIS WAS NOT VISIBLE WITHOUT MIRROR.  CAUSE WAS POSSIBLY BECAUSE OF UNEVEN HEATING AND COOLING OF PIPE UNDER THE DA	TA PLATE.  WHICH IS WELDED TO THE PIPE.  SUGGEST THAT THE DATA PLATE BE WELDED ON THE OUTSIDE OF PIPE TO BETTER INSPECT.	 OR ELIMINATE DATA PLATE AND ELECTRONICALLY ETCH INFORMATION ON TO THE RISER, AS DONE ON SOME JET ENGINE PARTS.	1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2004022300165	20040223	00165	SO  	2004	2	23	2004FA0000070    	1	20031224	G	5511	121CS100011	RIB             			MARSH 	S2F   	S2F3S       	3951007	SO  	GARRTT	TPE331	TPE331*     	01514	WP  					HORIZONTAL STAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	422DF	5151 				154817				DURING 400 HR PROGRESSIVE INSP OF THE LT HORIZ STAB, CRACKS WERE FOUND AT THE LEADING EDGE RIBS OF THE HORIZ STAB AT STA	TIONS 66.108, 80.608, AND 95.108.  CRACKS WERE NOTED WHERE THE RIBS ATTACH TO THE LEADING EDGE SKIN.  THIS AC HAS A TT 5	151.2 AND 1146.6 TIME SINCE CONVERTED TO A TURBOPROP POWERED FIRE FIGHTING AC.  THE LT HORIZ SHOT DAMPER WAS REMOVED DUR	ING TURBOPROP CONVERSION.  IT WAS ORIGINALLY INSTALLED TO COUNTERACT THE ORIGINAL RADIAL ENGINE INSTALLATION 3 BLADED PR	OP HARMONIC VIBRATION AT 2300 RPM.  CRACKING COULD BE CAUSED BY VIBRATION FROM TURBO PROP INSTALLATION.  ACTUAL CAUSE OF	 CRACKING HAS YET TO BE DETERMINED.  LT HORIZONTAL STABILIZER LE SKIN RIBS SHOULD BE INSPECTED FOR CRACKS.	2	H	7	2 	4O	3	T	RT	A51NM   	E2WE				 
2004022300170	20040223	00170	CE  	2004	2	23	2004FA0000071    	1	20031015	G	2720	505243649	ARM             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					RUDDER PEDAL	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	210CH	7523 				TH1067				PILOT WAS REMOVING RUDDER PEDAL GUST LOCK AND STATED THE TOP OF THE PEDAL (JUST FELL OFF).  PEDAL ARM HAD SEPARATED NEAR	 THE TOP END.  CROSS SECTION AREA, AT THE POINT OF SEPARATION IS AN (H) PATTERN.  A PRE-EXISTING CRACK WAS EVIDENT BY IT	S DARK COLOR AS OPPOSED TO THE BRIGHT CLEAN AREA OF THE RECENT CRACK AREA.  PRE-EXISTING CRACK COVERAGE IS APPROXIMATELY	 25 PERCENT OF THE (H) CROSS SECTION.			1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2004022300183	20040223	00183	CE  	2004	2	23	2004FA0000074    	1	20031219	G	2910	3A0900002	LINE            			CESSNA	185   	A185F       	2072821	CE  										HYD SYSTEM	CRACKED         	E				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			AL	05	6590E					18504058				12/19/03 AIRCRAFT ENCOUNTERED UNEXPECTED TURBULENT AIR, POSSIBLE WINDSHEAR. THE FORCES ACTING ON THE AIRFRAME CAUSED THI	S 3.88 INCH HYDRAULIC LINE TO FRACTURE. THE LINE CONNECTS TO A BULKHEAD ON ONE END AND TO A TEE ON THE OTHER. FROM THE T	EE, IT CONNECTS TO A LENGTHY LINE THAT RUNS THROUGH THE FORWARD SPREADER BAR. IT APPEARS TO BE THE MOVEMENT OF THE LONGE	R LINE THAT ACTED ON THE FAILED LINE CAUSING IT TO FRACTURE AT THE BULKHEAD. SUBSEQUENTLY, HYDRAULIC OIL WAS PUMPED FROM	 THE SYSTEM AS PRESSURE DROPPED AND THE PUMP ATTEMPTED TO MAINTAIN PRESSURE. TROUBLESHOOTING EFFORTS ALSO ASSISTED IN DE	PLETING THE HYDRAULIC FLUID RESERVOIR. THE AIRCRAFT LANDED WITHOUT INCIDENT ON THE GRASS ADJACENT TO THE RUNWAY.	1	H	7	1 	3O			 	3A24    					 
2004022300196	20040223	00196	CE  	2004	2	23	2004FA0000075    	1	20031214	G	8097	S15771	CONTACTOR       			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	STARTER	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	4702R	20   				R18200605	L2414236A	27025K		A NEW LIGHT WEIGHT STARTER WAS INSTALLED WHEN THE EXISTING STARTER FAILED.  THE STARTER CONTACTOR WELDS ITSELF TOGETHER 	AFTER ABOUT 15 STARTS.  2 NEW MFG CONTACTORS WERE INSTALLED AND HAD THE SAME RESULTS.  A HEAVY DUTY CONTACTOR HAS BEEN I	NSTALLED IAW MFG SERVICE BULLETIN.  THE SUSPICION IS THAT THE NEWER STARTERS DRAW SO MUCH MORE IN RUSH AMPERAGE WITH THE	 LARGER ENGINES CAUSING THE CONTACT TO WELD AND STICK.			1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2004022500022	20040225	00022	EA  	2004	2	25	2004FA0000078    	1	20031120	G	3213	C3UF811	STRUT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG FLOAT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	959PA					159	PCEPZ0016	BUA24456		LOWER END OF STRUT CRACKED BETWEEN INNER AND OUTER ATTACH LUGS (IN THE WEB) FROM BOTTOM OF STRUT UP .7500-1 INCH.  THERE	 WERE NO ABNORMAL CIRCUMSTANCES THAT CAUSED THE CRACK.  THE CRACK WAS VERY OBVIOUS, VIEW WAS UNOBSTRUCTED AND EASILY DET	ECTED DURING 100 HOUR INSP.  DO NOT THINK THERE IS ANY WAY TO PREVENT THIS KIND OF CRACK.				1	H	7	1 	3R	4	T	 	A815    	E4EA	6	C	P15EA	 
2004022500035	20040225	00035	EA  	2004	2	25	2004FA0000082    	2	20030701	G	7322	105217MP45PA	CARBURETOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	6288D		457  			17272694	L1384639A			CARBURETOR FAILED AFTER 457.6 HOURS.  ENGINE WAS INSTALLED AUG 6, 2002.  PROBABLE CAUSE OF FAILURE;  REPAIRED AS CHEAPLY	 AS POSSIBLE.  WARRANTY EXPIRED NO INSTALLATION TIME BAD ATTITUDE.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2004022500036	20040225	00036	CE  	2004	2	25	2004FA0000083    	1	20030630	G	3211	22411001	FITTING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	6464R					172RG0184	L2878136A			FITTING CRACKED ON IB SIDE.  DISCOVERED ON 100 HOUR INSPECTION.  NO RECOMMENDATION, EXCEPT, CLOSE INSPECTION, ONE TIME I	NSPECTION ANNUALLY.					1	H	7	1 	3O	3	O	 	3A17    	E286				 
2004022500037	20040225	00037	EA  	2004	2	25	2004FA0000084    	2	20030701	G	7322	105267	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	27	6439M					15284727	21906625			FUEL LEAKING AT PRODUCTION BREAK.  LACK OF QUALITY CONTROL AT OVERHAUL.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2004022500038	20040225	00038	SO  	2004	2	25	2004FA0000085    	2	20031205	G	7414		IMPULSE COUPLING	SLICK       		CESSNA	188   	T188C       	2073012	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MAGNETOR	LOOSE           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	05	9700J				96082264	T18803840T				IMPULSE COUPLING RIVET BECAME LOOSE IN HUB, ALLOWING INTERFERENCE BETWEEN PAWL AND MAGNETO HOUSING.  PAWL HAD WORN THROU	GH HOUSING, CRACKING THE MOUNTING FLANGE.					1	L	7	1 	3O	3	O	 	A9CE    	E8CE				 
2004022500039	20040225	00039	EA  	2004	2	25	2004FA0000086    	1	20031227	G	3213	190503	AXLE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					LT MLG	FLAKING         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	314FX					5372				WHEN REMOVING AND REPLACING OB BRAKE ASSEMBLY ON LT MLG.  THE AXLE WAS FOUND TO HAVE CHROME FLAKING OFF.  MFG EVALUATE.(	EA09200401322)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004022500040	20040225	00040	CE  	2004	2	25	2004FA0000087    	1	20031222	G	2400	CM358950	MASTER SWITCH   			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					COCKPIT	DESTROYED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	06	3NC	7879 				4410238				AT APPROXIMATELY FIFTY MINUTES INTO THE ONE HOUR FLIGHT, THE CREW STARTED TO NOTICE SLIGHT AVIONICS PROBLEMS ON THE COPI	LOTS SIDE.  SMOKE THEN STARTED TO EMERGE FROM THE RT AVIONICS MASTER SWITCH BREAKER.  THE CREW WAS UNABLE TO PHYSICALLY 	TURN OFF THE SWITCH.  SOON THE SMOKE STOPPED AND ALL AVIONICS POWERED BY THAT SWITCH FAILED.  THE AC LANDED WITH NO FURT	HER PROBLEMS.  MAINTENANCE REMOVED DEFECTIVE SWITCH AND DISASSEMBLE TO FIND THE MAIN WIRE FROM THE LINE SIDE HAD COME OF	F CAUSING THE POWER TO FIND ITS WAY THROUGH THE SPRING INSIDE THE SWITCH UNTIL ITS FINAL FAILURE.		1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2004022500051	20040225	00051	SO  	2004	2	25	2004FA0000089    	1	20031015	G	3244	60064PLY	TIRE            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360A1A    	41514	EA  					MLG	DEFECTIVE       	D			BSYA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	33142					28R7535126				DURING PREFLIGHT A LARGE BUBBLE WAS FOUND ON THE SIDEWALL OF THE TIRE, NEAR THE TREAD AREA.  THE BUBBLE WAS APPROX 5 INC	HES, 1 INCH WIDE, AND STUCK  ABOUT .5000 INCH.  THE TIRE WAS REFORMED TO SPECIALTY TIRE CO FOR EVALUATION.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2004022500054	20040225	00054	NM  	2004	2	25	2004FA0000090    	1	20031212	G	5720		STIFFENER       			UNIVAR	415   	415CD       	0420304	NM  	CONT  	C75   	C75*        	17005	SO  					CENTER WING	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	99780					2403	10058612R			IN COMPLIANCE WITH AD, INSPECTED WING CENTER SECTION IAW SB AND AC.  FOUND MINOR CORROSION IN RT WING CENTER SECTION ON 	FIRST STIFFENER AHEAD OF REAR SPAR IB, ITEM.  REPLACED STIFFENER.  FOUND DAMAGED STIFFENER IB FRONT OF MAIN SPAR, ITEM. 	 REPLACED STIFFENER.  REPAIRED TWO CRACKS IN BOTTOM SKIN IB BEHIND FRONT SPAR WITH PATCH 4 INCHES X 5 INCHES RIVETED, IT	EM.  REPAIRED MINOR SKIN DAMAGE TO LT GEAR OPENING WITH 3 INCHES X 4 INCH PATCH RIVETED, ITEM.  REPAIRED SMALL SKIN CRAC	K WITH 2 INCH X 2 INCH PATCH RIVETED, ITEM E.		1	L	7	1 	3O	3	O	 	A718    	E233				 
2004022500055	20040225	00055	SO  	2004	2	25	2004FA0000091    	2	20030825	G	8520		PISTON          			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	9815H	600  				18268044				THE PISTON WAS INSTALLED NEW AT TIME OF MAJOR OVERHAUL.  ONE SIDE OF PISTON SKIRT, AT LOWER SCRAPER RING BROKE AWAY AND 	BECAME SMALL CHUNKS OF ALUMINUM, AND RING PIECES IN THE OIL PAN.  THE PROBLEM WAS DETECTED BY APPROX 5 EACH.  .020 X .04	0 PIECES OF CAST ALUMINUM IN THE CUT OPEN OIL FILTER.  NO OTHER INDICATION OF A PROBLEM.  BY CHANCE AN OIL ANALYSIS HAD 	BEEN TAKEN DURING THIS SAME OIL CHANGE, THE RESULTS CAME BACK (NORMAL AND OK).			1	L	7	1 	3O	3	O	NT	3A13    	E273				 
2004022500059	20040225	00059	CE  	2004	2	25	2004FA0000096    	1	20030525	G	3220		BEARING         	CESSNA      		CESSNA	310   	310Q        	2074242	CE  										NLG	FAILED          	D				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			LD	LANDING        	1			SO	15	3310D					310Q0630				NOSE GEAR STRUT JAMMED AT NORMAL EXTENSION.  ON RETRACTION NOSE GEAR JAMS ON NOSE GEAR DOOR HINGES AND CAUSES NOSE GEAR 	BELLCRANK TO BREAK.  ACTUAL PROBLEM IS DUE TO STRUT UPPER BEARING FAILURE, BUT COULD EASILY BE MISDIAGNOSED AS A DEFECTI	VE BELLCRANK.  IT IS VERY DIFFICULT TO DETECT THIS FAILURE BEFORE FLIGHT.  I BELIEVE THAT AN AD SHOULD BE ISSUED TO CHAN	GE ALL NOSE STRUT UPPER BEARINGS AND INCLUDE A LIFE LIMIT TO THE PART.  THIS IS A SIMILAR FAILURE TO A CURRENT AD ON THI	S MODEL OF MAIN GEAR STRUT UPPER BEARING FAILURE.		1	L	7	2 	3O			 	3A10    					 
2004022500073	20040225	00073	CE  	2004	2	25	2004FA0000098    	1	20031122	G	7603	363800611	THROTTLE CABLE  			BEECH 	35    	S35         	1151532	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	INOPERATIVE     	G				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			EA	05	277RB					D7473				DURING LANDING PILOT REPORTED THAT HE COULD NOT RETARD THROTTLE.  SUSPECT BEARINGS INSIDE CABLE ARE FREEZING UP.  REMOVE	D AND REPLACED CABLE ASSY.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2004022500075	20040225	00075	CE  	2004	2	25	2004FA0000099    	1	20031221	G	2497	8824V2LA	CONTACTOR       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					RELAY	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	296SP					172S9481				RELAY, CONTACTOR FAILS UNDER LOAD ACCROSS TERMINALS.  CAUSE IS CONTACTOR NOT DESIGNED TO HANDLE CONTINOUS LOAD, (CURRENT	).  SEVERAL FAILURES NOTED IN THE PAST.  MFG WILL NOT ADDRESS THE PROBLEM.  SEVERAL OCCURRENCES NOTED IN LAST 3 YEARS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2004022500077	20040225	00077	CE  	2004	2	25	2004FA0000100    	1	20031209	G	2497	X610007	CONTACTOR       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					RELAY	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	936GW					172S9036				RELAY, CONTACTOR FAILED UNDER LOAD ACROSS TERMINALS.  CAUSE IS CONTACTOR NOT DESIGNED TO HANDLE CONTINOUS LOAD, (CURRENT	).  SEVERAL FAILURES NOTED IN PAST.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2004021700166	20040217	00166	CE  	2004	2	17	2004FA0000103    	1	20031229	G	2720	5052432626	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		15341				033				(BUNO 60981) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE RIGHT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL AS	SEMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART 	OF A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE C	RACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500064	20040225	00064	CE  	2004	2	25	2004FA0000104    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		16292				014				(BUNO 60852) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASS	EMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART O	F A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CR	ACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500070	20040225	00070	CE  	2004	2	25	2004FA0000105    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		15791				039				(BUNO 61057) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT (AS APPROPRIATE) RUDDER PEDAL ASSEMBLY ARM.  THE FAILED	 RUDDER PEDAL ASSEMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PE	RFORMED AS PART OF A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONT	H PERIOD.  THE CRACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500072	20040225	00072	CE  	2004	2	25	2004FA0000106    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		15677				047				(BUNO 61065) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT  RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL AS	SEMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART 	OF A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE C	RACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500074	20040225	00074	CE  	2004	2	25	2004FA0000107    	1	20031229	G	2720	5052432626	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17	61066	15210				048				(BUNO 61066) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE RIGHT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL AS	SEMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART 	OF A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE C	RACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500068	20040225	00068	CE  	2004	2	25	2004FA0000108    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		15664				035				(BUNO 60983) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASS	EMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART O	F A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CR	ACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500082	20040225	00082	CE  	2004	2	25	2004FA0000109    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	BROKEN          	M				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17		15341				033				(BUNO 60981)  WHILE REMOVING RUDDER CONTROL LOCK DURING PREFLIGHT, THE PILOT SIDE LEFT RUDDER PEDAL BROKE OFF.  THE FAIL	ED RUDDER PEDAL ASSEMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THIS WAS ONE OF 	SEVERAL FAILURES RESULTING IN A NAVY T-44A FLEET WIDE INSPECTION.				1	L	7	2 	3T			 	EXPA1L72					 
2004022500066	20040225	00066	CE  	2004	2	25	2004FA0000110    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	C				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		15522				017				(BUNO 60855) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASS	EMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART O	F A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CR	ACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500081	20040225	00081	CE  	2004	2	25	2004FA0000111    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		15562				038				(BUNO 60986) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASS	EMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART O	F A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CR	ACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500079	20040225	00079	CE  	2004	2	25	2004FA0000112    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		14058				055				(BUNO 61073) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASS	EMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART O	F A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CR	ACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500080	20040225	00080	CE  	2004	2	25	2004FA0000113    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17	61076	13475				058				(BUNO 61076) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASS	EMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART O	F A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CR	ACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500062	20040225	00062	CE  	2004	2	25	2004FA0000114    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	C90         	1152913	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		16868				008				(BUNO 60846) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASS	EMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART O	F A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CR	ACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.   FOR ADDITIONAL INFORMATION CONTACT LCDR	 KEITH KINTZLEY, VT-31 SAFETY OFFICER, (361) 961-3210, KEITH.KINTZLEY@NRS.NAVY.MIL OR GARY GOORIS, QUALITY ASSURANCE MAN	AGE, (361) 961-3226, GARY.GOORIS@L-3COM.COM.((	1	L	7	2 	3T			 	3A20    					 
2004022500076	20040225	00076	CE  	2004	2	25	2004FA0000115    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		12461				053				(BUNO 61071) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT  RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL AS	SEMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART 	OF A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE C	RACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500061	20040225	00061	CE  	2004	2	25	2004FA0000121    	1	20031229	G	2720	5052432626	ARM             			BEECH 	90    	C90         	1152913	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17	60844	14509				006				DYE TESTING REVEALED A CRACK IN THE PILOT SIDE RIGHT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASSEMBLY WAS MA	GNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART OF A NAVY  T-	44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CRACK FOUND ON	 THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	3A20    					 
2004022500063	20040225	00063	CE  	2004	2	25	2004FA0000123    	1	20031229	G	2720	5052432626	ARM             			BEECH 	90    	C90         	1152913	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17	60847	15948				009				(BUNO 60847) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE RT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASSEM	BLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PN).  THE TESTING WAS PERFORMED AS PART OF A NAVY  T	-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CRACK FOUND O	N THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.   FOR ADDITIONAL INFORMATION CONTACT LCDR KEITH KINT	ZLEY, VT-31 SAFETY OFFICER, (361) 961-3210, KEITH.KINTZLEY@NRS.NAVY.MIL OR GARY GOORIS, QUALITY ASSURANCE MANAGE, (361) 	961-3226, GARY.GOORIS@L-3COM.COM.	1	L	7	2 	3T			 	3A20    					 
2004022500069	20040225	00069	CE  	2004	2	25	2004FA0000124    	1	20031229	G	2720	5052432625	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	09		14829				036				(BUNO 60984) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE LEFT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL ASS	EMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART O	F A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE CR	ACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500078	20040225	00078	CE  	2004	2	25	2004FA0000125    	1	20031229	G	2720	5052432626	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	CRACKED         	M				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	17		12461				053				(BUNO 61071) DYE TESTING REVEALED A CRACK IN THE PILOT SIDE RIGHT RUDDER PEDAL ASSEMBLY ARM.  THE FAILED RUDDER PEDAL AS	SEMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THE TESTING WAS PERFORMED AS PART 	OF A NAVY  T-44A FLEET WIDE INSPECTION AFTER 4 RUDDER PEDALS FAILED DURING GROUND OPERATIONS IN A 3 MONTH PERIOD.  THE C	RACK FOUND ON THIS AIRCRAFT WAS ONE OF 16 DISCOVERED IN A FLEET OF 54 AIRCRAFT.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500084	20040225	00084	CE  	2004	2	25	2004FA0000127    	1	20031210	G	2720	5052432626	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	BROKEN          	M				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17		14459				052				(BUNO 61070) WHILE REMOVING RUDDER CONTROL LOCK DURING PREFLIGHT, THE PILOT SIDE RIGHT RUDDER PEDAL BROKE OFF.  THE FAIL	ED RUDDER PEDAL ASSEMBLY WAS MAGNESIUM, BUT WAS REPLACED WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THIS WAS ONE OF 	SEVERAL FAILURES RESULTING IN A NAVY T-44A FLEET WIDE INSPECTION.				1	L	7	2 	3T			 	EXPA1L72					 
2004022500083	20040225	00083	CE  	2004	2	25	2004FA0000128    	1	20031217	G	2720	5052432626	ARM             			BEECH 	90    	T44A        	       	CE  										RUDDER PEDAL	BROKEN          	M				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	17	60986	15562				038				(BUNO 60986) AFTER CONDUCTING STANDARD BRAKE CHECK WITH LINEMAN FOLLOWING ENGINE STARTS, THE PILOT SIDE RIGHT RUDDER PED	AL BROKE OFF AS PILOT ATTEMPTED TO SET PARKING BRAKE.  THE FAILED RUDDER PEDAL ASSEMBLY WAS MAGNESIUM, BUT WAS REPLACED 	WITH AN ALUMINUM ASSEMBLY (SAME PART NUMBER).  THIS WAS ONE OF SEVERAL FAILURES RESULTING IN A NAVY T-44A FLEET WIDE INS	PECTION.			1	L	7	2 	3T			 	EXPA1L72					 
2004022500096	20040225	00096	SO  	2004	2	25	2004FA0000131    	2	20031030	G	7414	M3050	IMPULSE COUPLING	SLICK       		BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					RT MAGNETO	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	8201T	1282 			93080059	E2838	675866			THE IMPULSE COUPLING SPRING WAS BROKEN IN 4 PIECES.  THE MAGNETO TIMING ONLY SHOWED THE RT MAGNETO TO ONLY BE OFF BY 4 D	EGREES. (EA23200404783)					1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2004022700062	20040227	00062	CE  	2004	2	27	2004FA0000141    	1	20031105	G	2910		LINE            			CESSNA	650   	650         	2076802	CE  										HYDRAULIC SYSTEM	CHAFED          	E				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			SO	19	24237					6500102				ON LANDING OF THE AIRCRAFT, THE HYDRAULIC FAN PRESSURE LINE BURST WHICH RESULTED IN LOSS OF MAIN HYDRAULIC SYSTEM FLUID.	  AIRCRAFT RAN OFF THE END OF RUNWAY 5 AT AIRPORT.  AIRCRAFT TURNED 90 DEGREES TO THE RT WHICH RESULTED IN THE LT WING T	IP TO DIG INTO THE SAND IN THE EMERGENCY RUN OFF AREA BREAKING OFF WING TIP. BOTH ENGINES INGESTED A LOT OF SAND.				2	L	7	2 	4F			 	A9NM    					 
2004022700100	20040227	00100	GL  	2004	2	27	2004FA0000145    	1	20031104	G	3230	19428030	LEG ASSY        			BLANCA	17    	1730A       	1220433	GL  										MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	6601V	2677 				30294				A CRACK HAD FORMED, PREVIOUS TO INCIDENT, AROUND THE BUSHING BOSS ON THE INBOARD END OF THE MOUNT PORTION OF THE UPPER M	AIN GEAR LEG.  THE RESULT WAS THAT THE MAIN GEAR COLLAPSED IN THE OUTBOARD DIRECTION WHILE TURNING AIRCRAFT AROUND AT TH	E END OF THE RUNWAY.  RECOMMEND THAT INSPECTION BE MADE AT CERTAIN TIME INTERVAL AND /OR IF HARD LANDING NOTED.  GEAR RE	MOVAL REQUIRED FOR INSPECTION.			1	L	7	1 	3O			 	A18CE   					 
2004021700085	20040217	00085	SO  	2004	2	17	2004FA0000147    	1	20030221	G	2140		HEATER          			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					COCKPIT	CONTAMINATED    	C				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	17	6530C					287890379				PILOT REPORTED SMOKE IN COCKPIT.  INSPECTION FOUND HYDRAULIC FLUID ON CARPET COVERING HEATER DUCT.  (EA17200405081)						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2004021100150	20040211	00150	GL  	2004	2	11	2004FA0000150    	3	20031015	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	B			R5DR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	09	431AF					18281193		020981		RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2004021100152	20040211	00152	GL  	2004	2	11	2004FA0000151    	3	20031016	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	C			R5DR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	521AF	215  				18281194		020788		RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2004021100154	20040211	00154	GL  	2004	2	11	2004FA0000152    	3	20031015	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	B			R5DR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	252AF	135  				18281185		020731		RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2004021100155	20040211	00155	GL  	2004	2	11	2004FA0000153    	3	20031015	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	B			R5DR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	372AF	215  				18281191		020833		RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2004021100157	20040211	00157	GL  	2004	2	11	2004FA0000154    	3	20031015	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	B			R5DR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	811AF	101  				18281196		020725		RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2004021100158	20040211	00158	GL  	2004	2	11	2004FA0000155    	3	20031015	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	B			R5DR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	271AF	286  				18281188		020783		RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUE THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2004021100178	20040211	00178	GL  	2004	2	11	2004FA0000156    	3	20031015	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	B			R5DR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	382AF	148  				18281192				RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2004021100179	20040211	00179	GL  	2004	2	11	2004FA0000157    	3	20031015	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	O540*       	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	B			R5DR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	251AF	151  				18281184		020738		RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TOT HE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	E295	5	C	 	 
2004021100180	20040211	00180	GL  	2004	2	11	2004FA0000158    	3	20031015	G	6110	C7409	GASKET          			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540*      	41532	EA  	MCAULY	3D36C	B3D36C431   	GL  	PROP CYLINDER	LEAKING         	B			R5DR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	522AF	152  				18281195		020742		RED DYE OIL LEAKAGE AT THE CYLINDER TO HUB ATTACH POINT.  OIL IS LEAKING PAST THE CYLINDER GASKET TO THE ATTACHING SCREW	S AND FOLLOWING THE THREADS OUT.  ADDITIONAL SEALANT NEEDS TO BE ADDED TO THE SCREWS DURING INSTALLATION AND PARTICULAR 	ATTENTION SHOULD BE GIVEN TO TORQUING THE SCREWS TO ASSURE PROPER SEATING OF THE GASKET.  (K)				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2004030100020	20040301	00020	CE  	2004	3	1	2004FA0000159    	1	20031231	G	5210	07110381	HINGE PIN       	CESSNA      		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200*       	17020	SO  					CABIN DOOR	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	714MG					15079277				DURING A 100 HOUR INSPECTION, THIS BROKEN DOOR HINGE PIN WAS FOUND.  FIND MANY OF THESE PINS BROKEN.(K) (NE01200402925)						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2004030100021	20040301	00021	CE  	2004	3	1	2004FA0000160    	1	20031204	G	6120	1317651F	ROD END         			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					PROP CONTROL	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	870JA	395  				TH2036				THREE ROD END BEARINGS WORN, ONE ON EACH PROP CONTROL AT GOVERNOR, ONE ON THROTTLE.  ONE WAS CLOSE TO FAILURE AND TO ONL	Y BEING RETAINED BY PN 100951S0632ZK LARGE AREA WASHER.					1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2004030100035	20040301	00035	GL  	2004	3	1	2004FA0000161    	2	20030902	G	7230	23039791C	COUPLING        								ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CRACKED         	B			QD5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07							CAC305250			DETECTED CRACK VIA VISUAL AND MPI INSPECTIONS DURING ROUTINE INSPECTION OF COMPRESSOR MODULE, COMPRESSOR ROTOR ASSEMBLY.	  DISASSEMBLED FOR INSPECTION OF FUTURE INSTALLATION.  NOTED HEAVY FRETTING WEAR ON COUPLING ADAPTER OD TO IMPELLER ID F	IT DIMENSION.  THE CRACK EXTENDS APPROX 60 PERCENT OF THE OUTSIDE DIAMETER OF THE PART.  THE CRACKING IS POSSIBLY DUE TO	 THE FRETTING WEAR ON THE ADAPTER OD.								3	U			E4CE				 
2004030100036	20040301	00036	GL  	2004	3	1	2004FA0000162    	2	20030902	G	7230	23039791C	COUPLING        								ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CRACKED         	B			QD5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07							CAC30525F			DETECTED CRACK VIA VISUAL AND MPI INSPECTIONS DURING ROUTINE INSPECTION OF COMPRESSOR MODULE, COMPRESSOR ROTOR ASSEMBLY.	  DISASSEMBLED FOR INSPECTION OF FUTURE INSTALLATION.  NOTED HEAVY FRETTING WEAR ON COUPLING ADAPTER OD TO IMPELLER ID F	IT DIMENSION.  THE CRACK EXTENDS APPROX 60 PERCENT OF THE OUTSIDE DIAMETER OF THE PART.  THE CRACKING IS POSSIBLY DUE TO	 THE FRETTING WEAR ON THE ADAPTER OD.								3	U			E4CE				 
2004021700087	20040217	00087	CE  	2004	2	17	2004FA0000165    	1	20030120	G	2120		DUCT            			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3315     	01514	WP  					ENVIRON SYST	MELTED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	45LU	6350 				BE8				IN LATE JAN 1999, IN FLIGHT, THE TEMPERATURE CONTROL CIRCUIT BREAKER OPENED.  AS A RESULT THE CREW EXPERIENCED AN OVERTE	MP CONDITION OF THE ENVIRONMENTAL SYSTEM.  THE ENVIRONMENTAL CONTROL WAS SELECTED OFF AND THE AIRCRAFT LANDED SAFELY.  S	UBSEQUENT INSPECTION SHOWED THAT THE ENVIRONMENTAL DUCTING UNDER THE RT CABIN FLOOR, AS WELL AS COAX CABLES FOR THE NAV 	RADIOS AND THE NR 2 COM HAD BEEN DAMAGED.  A WIRE TO THE ELECTRIC HEAT RELAY WAS FOUND DAMAGED AND MISROUTED.  ALL DAMAG	ED COMPONENTS WERE REPLACED, AND THE WIRING REPAIRED.		1	L	7	2 	4T	4	T	 	A14CE   	E4WE				 
2004021700088	20040217	00088	EA  	2004	2	17	2004FA0000166    	2	20030129	G	7314	200F5003	GARLOCK SEAL    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					FUEL PUMP	LEAKING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	101TT	18   				318252050	L262268A			THIS ENGINE DRIVEN FUEL PUMP WAS INSTALLED ON A MFG FACTORY OVERHAULED ENGINE.  FOUND ENGINE DRIVEN FUEL PUMP LEAKING FR	OM THE GARLOCK SEAL ON THE DRIVE END OF THE FUEL PUMP, LEAVING FUEL STAIN ON BOTTOM ENGINE COWL.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2004030100056	20040301	00056	EA  	2004	3	1	2004FA0000167    	2	20030122	G	7414	6351	MAGNETO         			CESSNA	182   	182T        	2072703	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ENGINE	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	214FA					18281214	L2870848A			IT APPEARS THAT THE IMPULSE COUPLING FAILED, THEREFORE SEIZING THE MAGNETO AND SHEARING GUIDE SHAFT OF RETAINER GEAR ASS	EMBLY AND BREAKING APART (INTO PIECES) THE RETAINER ASSEMBLY, ITSELF.  SENDING PIECES OF METAL INTO THE ACCESSORY CASE A	ND POSSIBLY INTO THE ENGINE, THERE ARE MARKS/IMPRESSIONS IN THE BALL BEARING SUPPORT FROM INCIDENT.  REMOVED AND REPLACE	D RT ENGINE. (RT MAGNETO)			1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2004030100059	20040301	00059	SO  	2004	3	1	2004FA0000168    	1	20030118	G	2497		WIRE            			MAULE 	MX7   	MXT7180     	5470206	SO  	LYC   	O360  	O360C1F     	41514	EA  					RT SEAT CONVERTE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	4198R	163  				14096C				CHECK LIST TELLS YOU TO REMOVE LOWER PANELS UNDER SEATS FOR INSP.  REMOVED PANELS FOR INSP AND COMPLIANCE WITH SB 64 ON 	ELEVATOR CABLES. FOUND THAT UNDER RT SEAT THERE IS CONVERTER THAT IS FOR INSTRUMENT LIGHTS.  WIRING WAS ROUTED FROM INST	RUMENT PANEL TO CONVERTER IT WAS PULLED TOO TIGHT ALLOWING 3 WIRES TO CHAFE ON 45 DEGREE SPAR BRACE.  INSULATION WAS WOR	N OFF WITH DIRECT WELDING CONTACT OF WIRES ON SPAR MEMBER.  NO CB POPPED.  EQUIP NOT WORKING IAW MM IS INSTR LIGHTS, THE	Y ARE ON BUT DO NOT DIM AS REQUIRED.  THIS CREATED FIRE WHICH MELTED SIDE KICK PANEL, BURNED INSULATION, CREATED FLAME P	ATH OF ABOUT 8 INCHES.  THIS DAMAGE COULD NOT BE SEEN WITH PANELS INSTALLED.  PILOT NEVER SMELLED SMOKE IN COCKPIT.	1	H	7	1 	3O	3	O	NC	3A23    	E286				 
2004030100070	20040301	00070	EA  	2004	3	1	2004FA0000169    	2	20031215	G	7314	LW16335	PUMP            			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					ENGINE	INOPERATIVE     	D				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	21	6756B					M2276				AIRCRAFT EXPERIENCED ENGINE FAILURE DUE TO LOSS OF FUEL PRESSURE DURING TRAINING FLIGHT.  STUDENT FAILED TO TURN ON ALTE	RNATOR SWITCH AND BATTERY POWER WAS INSUFFICIENT TO OPERATE ELECTRIC FUEL PUMP.  FAILURE OCCURRED IN VICINITY OF AIRPORT	 AND SAFE LANDING WAS EXECUTED.  DURING RUN-UP AT FULL POWER, FUEL PRESSURE WOULD DECREASE FROM NORMAL 5 PSI TO 2.5 PSI 	AND RETURNED TO NORMAL WHEN POWER REDUCED.  REMOVED PUMP AND DISASSEMBLED.  NO GLARING DEFECTS.  THE ONLY QUESTIONABLE C	ONDITION FOUND WAS THE BOTTOM CHAMBER DIAPHRAGM (WHICH PURPOSE, SUSPECT IS TO DAMPEN PULSATIONS) WAS STRETCHED AND POSSI	BLY NOT ALLOWING THE PUMP TO DRAW IN ENOUGH FUEL FOR HIGH POWER APPLICATION.	1	L	7	1 	3O	3	O	 	A1CE    	E286				 
2004030100077	20040301	00077	EU  	2004	3	1	2004FA0000174    	1	20030513	G	2560	349141012070	BUCKLE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					SEAT BELT	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	391NS	168  				3481	9772			LT OB SEATBELT BUCKLE BROKEN.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004030100078	20040301	00078	EU  	2004	3	1	2004FA0000175    	1	20030505	G	2820		COUPLER         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HEATER HOSE	SEIZED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	391NS	162  				3481				P2 HEATER HOSE SEIZED ONTO THE FITTING AT THE ENGINE.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004030100079	20040301	00079	EU  	2004	3	1	2004FA0000176    	1	20030317	G	2910	813468	SHIM            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD FILTER	MISSING         	C				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AL	05	391NS	76   				3481				HYDRAULIC FILTER BYPASS BUTTON POPPED (NO SHIMS INSTALLED).						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004030100085	20040301	00085	CE  	2004	3	1	2004FA0000177    	1	20031008	G	5711	901100132	SPAR CAP        			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	MCAULY	4HFR34	4HFR34C762  	NE  	RT WING	CRACKED         	B			FJJS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	502SE	10138				LJ740				DURING COMPLIANCE OF AD, INSPECTION, A CRACK WAS DISCOVERED IN THE LOWER WING SPAR CAP.						1	L	7	2 	3T	4	T	 	3A20    	E4EA	6	C	3PNE	 
2004021700080	20040217	00080	SO  	2004	2	17	2004FA0000179    	1	20031210	G	2140	A23D04	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					HEATER FUEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	3581C	154  				318052091				AD HAS YOU PERFORM PRESSURE LEAKAGE CHECK ON THESE HEATER FUEL PRESSURE REGULATORS.  WHEN NEW AND BEFORE INSTALLATION IN	TO AIRCRAFT.  WE FIND THAT MANY OF THESE UNITS FAIL AFTER A SHORT TIME OF USE.  THEY START LEAKING AROUND HOUSING DIAPHR	AGM AND NOTICED FUEL STAIN FROM DRAIN ON THE NOSE SECTION OF THE AIRCRAFT.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2004030100117	20040301	00117	SO  	2004	3	1	2004FA0000180    	1	20031210	G	7334	A23D04	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					FUEL SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	101TT	165  				318252050				AD HAS YOU PERFORM PRESSURE LEAKAGE CHECK ON THESE HEATER FUEL PRESSURE REGULATORS WHEN NEW AND BEFORE INSTALLATION INTO	 AIRCRAFT.  WE FIND THAT MANY OF THESE UNITS FAIL AFTER A SHORT TIME OF USE.  THE PART STARTS LEAKING AROUND HOUSING DIA	PHRAGM AND NOTICE FUEL STAIN FROM DRAIN ON THE NOSE SECTION OF THE AIRCRAFT.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2004030100111	20040301	00111	GL  	2004	3	1	2004FA0000194    	1	20031117	G	7170		DRAIN LINE      			AVIAT 	A1    	A1A         	2210405	GL  	LYC   	O360  	O360*       	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE OIL	CHAFED          	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	478DM					1450	L3657436A	CH33326B		OIL LEAK NOTED ON LOWER COWL.  DURING ANNUAL INSPECTION, NR 1 OIL DRAIN TUBE FOUND CHAFED BY CARB HEAT SCAT HOSE.  SCAT 	HOSE WAS ROUTED BETWEEN OIL DRAIN TUBE AND NR 1CYCLINDER EXHAUST STACK.					1	H	7	1 	3O	3	O	NC	A22NM   	E286	5	C	P920	 
2004030300091	20040303	00091	SW  	2004	3	3	2004FA0000200    	1	20030710	G	3233	B10076	GEAR            	DUKES       		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MLG ACTUATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	201HB	84   			0288	240209				AIRCRAFT EXPERIENCING POPPING OF THE MAIN LANDING GEAR CB ON RETRACTION AND WAS MAKING NOISE.  AIRCRAFT WAS FLOWN, GEAR 	DOWN AS A PRECAUTION.  REMOVAL AND INSPECTION OF THE GEAR ACTUATOR REVEALED AN EXCESSIVELY WORN WORM GEAR IN THE JACKSCR	EW ASSEMBLY THAT WAS BINDING WITH THE PINION GEAR CAUSING JAMMING.				1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2004030300092	20040303	00092	SW  	2004	3	3	2004FA0000201    	1	20030610	G	3233	B10076	WORM GEAR       			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MLG ACTUATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	201DD	112  			0110	240102				THIS GEAR WAS REMOVED FROM THE GEAR ACTUATOR AFTER COMPLAINTS THAT THE LANDING GEAR CIRCUIT BREAKER WAS POPPING DURING R	ETRACTION.  REPLACED THE GEARS IAW SB M20-190B EXACTLY 112.8 AIRCRAFT HOURS AGO.  THE GEAR REMOVED IS SEVERELY WORN.					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2004030400078	20040304	00078	CE  	2004	3	4	2004FA0000231    	1	20030423	G	3233	98820001	ACTUATOR        			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	MLG	CRACKED         	D			RA7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	210PF	2807 	1974 			P21000018	513932	002238		LT MLG ACTUATOR CRACKED ALLOWING ALL HYDRAULIC FLUID TO LEAK OB ON RETRACTION AFTER TAKEOFF.  COULD NOT EXTEND LANDING G	EAR WHICH RESULTED IN A GEAR UP LANDING.  NOTE, THIS ACTUATOR WAS PREVIOUSLY OVERHAULED ON 04/21/1983 AT 833 HOURS TIME 	IN SERVICE.  THERE ARE NO SIGNS OF CORROSION OR DAMAGE TO ACTUATOR.  IT SIMPLY SPLIT APPROX 3.5 INCHES LONG, LENGTH WISE	 OF THE PISTON BARREL.			1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2004030400079	20040304	00079	NM  	2004	3	4	2004FA0000233    	1	20031216	G	2741		MOTOR           	EATON       		BOEING	717   	717200      	1383700	NM  										TRIM POWER DRIVE	FOD             	D			E20R	O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			WP	23					397					FOD WITHIN MOTOR ASSEMBLY, PIECE OF ASSEMBLY TOOLING LODGED IN STATOR WINDING CAUSED FAILURE OF STATOR.						2	L	7	2 	4F			TR	A6WE    					 
2004040100157	20040401	00157	GL  	2004	4	1	2004FA0000252    	1	20031106	G	5750		AILERON         			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360*       	41514	EA  					WINGS	MISLOCATED      	B			V2AR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	354C					2119				FOUND RIVET IN AILERON LEADING EDGE HAD CAUGHT CORNER OF RIB INSTEAD OF THROUGH CENTER OF RIB.  CONDITION IN BOTH LEFT A	ND RIGHT AILERONS AT WS123.    REPAIRED CONDITION IAW MFG LETTER OF INSTRUCTION.					1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2004040100158	20040401	00158	CE  	2004	4	1	2004FA0000253    	1	20031124	G	2140		DUCT            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					HEATER	MISROUTED       	B			FE4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	792SP					172S8717				DURING A ROUTINE INSPECTION, WE FOUND THAT THE PLASTIC GLOVEBOX WAS MELTED AT THE FORWARD RIGHT SIDE.  WE FOUND THE HEAT	ER DUCTING WAS ROUTED UP AGAINST THE GLOVEBOX CAUSING THE BOX TO MELT.  REROUTED HEAT DUCTING TO PREVENT FUTURE OCCURANC	E.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2004040100159	20040401	00159	CE  	2004	4	1	2004FA0000254    	1	20031124	G	2140		DUCT            			CESSNA	172   	172S        	2072439	CE  										HEATER	MISROUTED       	B			FE4R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AL	03	35339					172S8891				DURING A ROUTINE INSPECTION, WE FOUND THAT THE PLASTIC GLOVEBOX WAS MELTED AT THE FORWARD RIGHT SIDE.  WE FOUND THAT THE	 HEATER DUCTING WAS ROUTED UP AGAINST THE GLOVE BOX CAUSING THE BOX TO MELT.  REOUTED HEAT DUCTING TO PREVENT FUTURE OCC	URANCE.				1	H	7	1 	3O			NT	3A12    					 
2004040100177	20040401	00177	SO  	2004	4	1	2004FA0000268    	1	20031126	G	2820		O-RING          			PIPER 	PA22  	PA22135     	7102206	SO  	LYC   	O290  	O290*       	41506	EA  					CHECK VALVE	WORN            	D			PS0M	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	3347A	1299 				221617				THE CHECK VALVE BETWEEN THE AUXILIARY FUEL TANK AND THE RT MAIN TANK FAILED, ALLOWING FUEL FROM THE RT MAIN TO DRAIN INT	O THE AUX TANK AND OVERFLOW FROM THE FILLER NECK.  THE PUMP AND VALVE ASSEMBLY IS INTENDED TO MOVE FUEL FROM THE AUX TAN	K TO THE RT MAIN TANK AND PREVENT REVERSE FLOW.  RECOMMEND A POSITIVE SHUT OF VALVE BETWEEN THE RIGHT MAIN TANK AND THE 	AUX TANK PUMP TO PREVENT AN IN-FLIGHT DRAINING OF FUEL FROM THE RT MAIN TANK.			1	H	7	1 	3O	3	O	 	1A6     	E229				 
2004042200151	20040422	00151	EA  	2004	4	22	2004FA0000283    	2	20030817	G	7314	154734500	PUMP            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL SYS	BURNED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	35073					17258875				PROBABLE CAUSE ENGINE COMPARTMENT FIRE OF UNDETERMINED SOURCE.  REPORT CONCERNING SEPARATION OF FUEL LINE FROM FUEL PUMP	.  ACC REPORT NR IAD02FA086.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2004050500108	20040505	00108		2004	5	5	2004FA0000299    	4	20031120	G	6122	C290D35	GOVERNOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					ENGINE	MALFUNCTIONED   	B			LW5R	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	17	9515B	5660 	1410 			172RG0846	L2774336A			WHILE ON CLIMB OUT AT 2500 RPM AND 25 INCHES, ENGINE RPM SUDDENLY WENT TO 3000 AND PILOT WAS UNABLE HAVE ANY EFFECT WITH	 PROPELLER CONTROL.  AIRCRAFT RETURNED TO AIRPORT USING THROTTLE TO CONTROL RPM.  ENGINE CONTROLS WERE ALL FOUND TO BE I	NTACT AND OPERATING NORMAL.  UNIT REMOVED AND SENT TO PROP SHOP FOR REPAIR.				1	H	7	1 	3O	3	O	 	3A17    	E286				 
2004050600077	20040506	00077	CE  	2004	5	6	2004FA0000319    	1	20031204	G	2820	1200406131	FUEL LINE       			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520*      	17032	SO  					LT WING	CORRODED        	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	07	761AN	2983 				21062103				FRONT FUEL LINE FROM LT WING TANK WAS IN CONTACT WITH FRESH AIR DUCT IN THE WING, AERO DUCT PN CEET 1.5 INCH.  THIS CAUS	ED CORROSION ON THE ALUMINUM FUEL LINE.  PROBLEM WAS FOUND WHEN FUEL STARTED LEAKING OUT OF THE WING.  REPLACED FUEL LIN	E AND FRESH AIR DUCT.  FABRICATED A STANDOFF TO PREVENT REOCCURRENCE.				1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2004050300130	20040503	00130	EU  	2004	5	3	2004FA0000326    	1	20031210	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	961SD	288  	288  			3516	9791			PILOT REPORTED DEFECT AND MAINTENANCE. STARTER/GENERATOR LIGHT CAME ON IN FLIGHT.  REPLACED STARTER/GENERATOR AND 16 AMP	 FUSE.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004050300131	20040503	00131	EU  	2004	5	3	2004FA0000327    	1	20031210	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	961SD	288  	288  			3516	9791			PILOT REPORTED DEFECT AND MAINTENANCE CORRECTIVE ACTION:  GENERATOR LIGHT CAME ON IN FLIGHT, WILL NOT RESET.  REPLACED S	TARTER/GENERATOR AND 16 AMP FUSE.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004050300142	20040503	00142	EU  	2004	5	3	2004FA0000328    	1	20031229	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	960SD	331  	331  			3501	9787			PILOT REPORTED DEFECT AND MAINTENANCE CORRECTIVE ACTION:  ON 3RD HOP, 2 MINUTES INTO FLIGHT VOLTMETER READ 23 VOLTS. NO 	GENERATOR LIGHT. SHUT DOWN FOR 10 MINUTES. CONTINUED FLIGHT FOR 3 HOURS. AT 29 VOLTS ON 4TH HOP, JUST PRIOR TO LIFT-OFF,	 GENERATOR LIGHT CAME ON AND WOULD NOT RE-SET. REPLACED STARTER/GENERATOR AND BATTERY.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004050400010	20040504	00010	EU  	2004	5	4	2004FA0000335    	1	20031022	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	962SD	291  	200  			3517	9790			PILOT REPORTED DEFECT AND MAINTENANCE CORRECTIVE ACTION:  GENERATOR WENT OFF-LINE.  REPLACED GENERATOR AND BATTERY						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004051400073	20040514	00073	SW  	2004	5	14	2004FA0000393    	1	20031227	G	2720	AN32022	COTTER PIN      			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235C1      	41505	EA  					RUDDER PEDAL	SHEARED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	53879	1554 				113676				COTTER KEY USED TO SECURE THE CLEVIS PIN BETWEEN THE RT RUDDER PEDAL AND RT BRAKE MASTER CYLINDER FAILED.  THE HEAD OR T	ANGS OF THE COTTER KEY STRIKE AN ANGLE BRACKET ON THE FIREWALL WHEN THE RUDDER PEDAL IS FULLY DEPRESSED, DEPENDING UPON 	WHICH WAY THE CLEVIS PIN HAS ROTATED.  AFTER THE COTTER KEY FALLS OUT OF THE CLEVIS PIN, THE CLEVIS PIN SEPARATES FROM T	HE RUDDER PEDAL AND BRAKE MASTER CYLINDER ASSY.  THE RUDDER PEDAL FALLS FORWARD, ALLOWING THE TOP OF THE RUDDER PEDAL TO	 COME IN CONTACT WITH THE FIREWALL WHEN DEPRESSED.  THIS RESULTS IN A LOSS OF RUDDER PEDAL TRAVEL.  THE COTTER KEY TANGS	 SHEARED AT THE CLEVIS PIN.	1	H	7	1 	3O	3	O	 	A759    	E223				 
2004052600072	20040526	00072	SO  	2004	5	26	2004FA0000412    	1	20031206	G	2510	6956800	SEAT FRAME      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	CABIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	16583	4213 				287325301	L3324227A	K35135		PILOTS TUBULAR SEAT FRAME (UPPER TUBULAR AT FWD CONNECTING BRACKETS) FOUND CRACKED AT LEAST 270 DEGREES CIRCUMFERENCE BO	TH SIDES. THIS DISCREPANCY COULD RESULT IN SEPARATION OF THE SEAT FRAME RESULTING IN PILOTS LOSS OF CONTROL OF THE AC ES	PECIALLY DURING FINAL LANDING APPROACH OR DURING TAKEOFF. REPLACEMENT OF SEAT FRAME OR WELDING OF FRAME TUBULAR WITH 30 	DEGREE TUBULAR SPLICE PATCHES WOULD RESOLVE THIS DISCREPANCY. THIS DISCREPANCY WAS ALSO FOUND BOTH SIDES ON UPPER TUBULA	R OF NON-ARTICULATING FWD RT SEAT.  NOTE: THESE DISCREPANCIES WERE FOUND DUE TO AN INTERIOR REPLACEMENT AND SEAT RE-UPHO	LSTERY. NORMAL MAINTENANCE INSPECTIONS WOULD PROBABLY NOT DETECT THESE CRACKS AS THEY ARE HIDDEN BY THE SEAT MATERIAL.	1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2004091400189	20040914	00189		2004	9	14	2004FA0000526    	4	20031224	G	6113	D7309	BULKHEAD        			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					LT PROP SPINNER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	12699					3449262				DURING ANNUAL INSPECTION, FOUND THE LT PROP SPINNER BULKHEAD CRACKED IN SEVERAL PLACES.  THE CRACKS ARE LOCATED AT JUST 	ABOUT EVERY BOLT HOLE FOR ATTACHING THE BULKHEAD TO THE PROP BULKHEAD HAD TO BE REPLACED.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2004071200026	20040712	00026	EU  	2004	7	12	2004FA0000533    	1	20031117	G	2720		CONTROL ROD     			AMD   	FALC10	FALCON10    	2730101	EU  										RUDDER	CHAFED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	707AM	6523 				159				TIP FROM AUG 03 AC 43-16A RUDDER CONTROL ROD CHAFED.  RUDDER CONTROL ROD CRANK AT FRAME NR 37.  FOUND YAW DAMPNER ATTACH	MENT PIN INSTALLED 180 DEGREE OUT.  COTTER KEY AND NUT CHAFED THE ELEVATOR SERVO HYDRAULIC LINE, NO DAMAGE TO LINE NOTED	.  ID TAG GOUGED.  CORRECTED IAW F-10 IPC 27-22-01, FIG 5 SHEET 2 OF 2.  CYCLED RUDDER FULL TRAVEL, PROPER OPERATION IND	ICATED.			2	L	7	2 	4F			 	A33EU   					 
2004091500083	20040915	00083	SO  	2004	9	15	2004FA0000582    	1	20030307	G	2820	102487	CHECK VALVE     			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					FUEL SYSTEM	STUCK           	H				O				OTHER                   				S			AFFECT SYSTEMS            			AP	APPROACH       	1			WP	23	522RF	308  				4697119	PCERM0124			CHECK VALVE, GRAVITY/SUPPLY LINE FOUND STUCK OPEN ALLOWING FUEL DISPLACEMENT FROM HEADER TANK.  AIRCRAFT INVOLVED IN FAT	AL ACCIDENT 03/07/03					1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2004091500084	20040915	00084	SO  	2004	9	15	2004FA0000583    	1	20030307	G	2820		CHECK VALVE     			PIPER 	PA46  	PA46500TP   	7104622	SO  										FUEL FLOW	MISALIGNED      	H				O				OTHER                   				S			AFFECT SYSTEMS            			AP	APPROACH       	1			WP	23	522RF	308  				4697119				HINGE PIN DISPLACED, FLAPPER DOOR MISALIGNED, ALLOWING REVERSE FUEL FLOW.  PART MARKED  99240/2S6952.						1	L	7	1 	3O			RT	A25SO   					 
2004092000123	20040920	00123	SO  	2004	9	20	2004FA0000592    	1	20030307	G	2820	102487	CHECK VALVE     			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					ZONE 600	STUCK           	D				O				OTHER                   				S			AFFECT SYSTEMS            			AP	APPROACH       	1			WP	23	522RF	308  				4697119	PCERM0124			CHECK VALVE ASSY.  GRAVITY/SUPPLY LINE FOUND STUCK OPEN ALLOWING FUEL DISPLACEMENT FROM HEADER TANK.						1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2004092000124	20040920	00124	SO  	2004	9	20	2004FA0000593    	1	20030307	G	2820	102487	CHECK VALVE     			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					ZONE 600	STUCK           	H				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			WP	23	522RF	308  				4697119	PCERM0124			CHECK VALVE ASSY. GRAVITY/SUPPLY LINE FOUND STUCK OPEN ALLOWING FUEL DISPLACEMENT FROM HEADER TANK.						1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2004090800175	20040908	00175	SO  	2004	9	8	2004FA0000611    	1	20030117	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					STABILATOR	CORRODED        	D			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	8560Y					301707				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ASLO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321).  AND THE TORQUE TUBE.  TT UNKNOWN			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2004090800169	20040908	00169	SO  	2004	9	8	2004FA0000612    	1	20030528	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					STABILATOR	CORRODED        	D			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	8660P	3705 				244106				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321).  AND THE TORQUE TUBE.  TT 3705.			1	L	7	1 	3O	3	O	 	1A15    	E14EA				 
2004090800174	20040908	00174	SO  	2004	9	8	2004FA0000613    	1	20030630	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					STABILATOR	CORRODED        	B			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	8458Y					301617				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON THE PA2	4 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33A 	THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BOLT	S:  AN24-46A (400-932), AN174-22A (402-321). AND THE TORQUE TUBE.			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2004090800172	20040908	00172	SO  	2004	9	8	2004FA0000616    	1	20030630	G	1430	AN175C33A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					STABILATOR	CORRODED        	D			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	7321Y					30365				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321).  AND THE TORQUE TUBE.			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2004090800177	20040908	00177	SO  	2004	9	8	2004FA0000617    	1	20030922	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					STABILATOR	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	8921P					244377				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321).  AND THE TORQUE TUBE.  TT 3023.			1	L	7	1 	3O	3	O	 	1A15    	E14EA				 
2004090800176	20040908	00176	SO  	2004	9	8	2004FA0000621    	1	20031111	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  					STABILATOR	CORRODED        	D			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	727DS					24276				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321).  AND THE TORQUE TUBE.			1	L	7	1 	3O	3	O	 	1A15    	E295				 
2004090800167	20040908	00167	SO  	2004	9	8	2004FA0000623    	1	20031025	G	1430	AN175C33A	BOLT            			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	TIO540*     	41532	EA  					STABILATOR	CORRODED        	D			Q76E	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	8843P	5837 				244298				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321) AND THE TORQUE TUBE.  TT 5837.			1	L	7	1 	3O	3	O	 	1A15    	E14EA				 
2004083100040	20040831	00040	SO  	2004	8	31	2004FA0000624    	1	20030117	G	1430		BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					STABILATOR	CORRODED        	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	8560Y					301707				DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION.  THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER P	A24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION.  BOTH BOLTS AN175C33	A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED.  ALSO CORRODED WERE THE FOLLOWING BO	LTS:  AN24-46A (400-932), AN174-22A (402-321) AND TORQUE TUBE.			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2005050500063	20050505	00063	SO  	2005	5	5	2005FA0000589    	1	20031210	G	8011		RING GEAR       			PIPER 	PA28  	PA28161     	7102803	SO  										STARTER	FAILED          	D				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			EA	15	149LH	76   	53   			2842192				STARTER FAILED ON AIRCRAFT WITH 76.9 HOURS TT. FAILURE DAMAGED RING GEAR, REQUIRING REPLACEMENT.						1	L	7	1 	3O				2A13    					 
2005081600214	20050816	00214	SO  	2005	8	16	2005FA0001130    	2	20030719	G	8500		SOLENOID VALVE  			CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470S      	17026	SO  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	3611Y	1544 				21058111	1028863S1			ENG BECAME ROUGH, THEN FAILED ENTIRELY.  RESTART WAS ACHIEVED, LANDING MADE.  FOLLOWING DAY ENG STARTED AND RAN NORMALLY	, UP TO FULL STATIC RPM.  ALL SUMPS WERE DRAINED, ALL FUEL FILTERS INSPECTED, ALL TANK VENTS CHECKED WITH NO EVIDENCE OF	 CONTAMINATION, BLOCKAGE, OR WATER.  FLIGHT BACK TO BASE AIRPORT WAS UNEVENTFUL.  INVESTIGATION PRODUCED NO EVIDENT CAUS	E UNTIL SOLENOID WAS REMOVED FROM VAPOR/FUEL RETURN LINE BETWEEN ENG-DRIVEN FUEL PUMP AND FUEL SELECTOR WAS CAPABLE OF S	TICKING IN CLOSED OR NEARLY-CLOSED POSITION.  THIS HAPPENED DURING ENG STARTING ON SUBJECT FLIGHT AND CAUSED A VAPOR LOC	K CONDITION TO DEVELOP.  FUEL DELIVERY TO ENG WAS INTERRUPTED WHEN ENG-DRIVEN FUEL PUMP FILLED WITH VAPOR.	1	H	7	1 	3O	3	O		3A21    	3E1				 
2006062300004	20060623	00004	SO  	2006	6	23	2006FA0000583    	1	20031031	G	2730	62701159	CONTROL CABLE   			PIPER 	PA32  	PA32RT300T  	7103216	SO  										STABILATOR	BROKEN          	G				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SO	05	39541	2633 				32R7887104				MS21260S4LH STABILATOR PRIMARY CONTROL CABLE TERMINAL END FRACTURED SHORTLY AFTER THE PILOT ROTATED AND STARTED HIS CLIM	B OUT. THE PILOT MADE AN EMERGENCY LANDING AND THE AIRCRAFT SUSTAINED SUBSTANTIAL DAMAGE TO THE PROP, ENGINE, COWLING, A	ND NOSE GEAR. THE PILOT WAS NOT INJURED. THE .040 SAFETY WIRE USED TO SAFETY THE ELEVATOR TURNBUCKLE MAINTAINED THE INTE	GRITY OF THE CONTROL SYSTEM ALLOWING THE PILOT TO MAINTAIN CONTROL UTILIZING THE TRIM AND ENGINE POWER. NTSB SAFETY RECO	MMENDATION A-01-6 THROUGH -8 DATED APRIL 16, 2001 AND SPECIAL AIRWORTHINESS ALERT BULLETIN CE-02-05R1 ADDRESS THIS PROBL	EM AND ATTRIBUTE IT TO CHLORIDE STRESS CORROSION OVER A PROLONGED CALENDAR TIME OF 18-20 YEARS.	1	L	7	1 	3O				A3SO    					 
2007013100063	20070131	00063	EU  	2007	1	31	2007FA0000087    	1	20031111	G	3411		PITOT HEAD      			FOKKER	F28   	F28MK4000   	4990810	EU  										PITOT/STATIC SYS	OBSTRUCTED      	D				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			GL	23	159AD					11227				FLIGHT NR 7, STAGE OF FLIGHT: TAKEOFF ROLL, 2ND ATTEMPT, CAPTAINS AIR SPEED INDICATOR INOPERATIVE.  REMOVED CAPTAINS AIR	SPEED INDICATOR QUICK DISCONNECTS, PURGED WITH NITROGEN, FOUND BLOCKAGE AT PITOT HEAD, REMOVED BLOCKAGE RECONNECTED QUIC	K DISCONNECTS.  OPS CHECK GOOD, ALL WORK DONE IAW AMM, CHP 34.  (K)				2	L	7	2 	4F			RT	A20EU   					 
2007013100065	20070131	00065	EU  	2007	1	31	2007FA0000088    	1	20031111	G	3411		DRAIN LINE      			FOKKER	F28   	F28MK4000   	4990810	EU  										PITOT/STATIC SYS	OBSTRUCTED      	C				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			GL	23	159AD					11227				FLIGHT NR 7, STAGE OF FLIGHT: TAKEOFF ROLL, CAPTAINS AIR SPEED INDICATOR DID NOT WORK.  REMOVED PITOT DRAIN LANE, PURGED	 WITH AIR, RECONNECTED QUICK DISCONNECT.  OPS CHECK OK IAW F28, CHP 34.  (K)					2	L	7	2 	4F			RT	A20EU   					 
2007030900042	20070309	00042	CE  	2007	3	9	2007FA0000211    	1	20030729	G	8011		BEARING         	CONT        	IO360DB     	CESSNA	172   	R172E       	2072413	CE  	CONT  	O360  	IO360DB     	17025	SO  					STARTER	NOISY           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	7884N		92   		6261973DR	R1720275	6261973DR			DURING 100 HOUR INSPECTION A NOISE WAS HEARD COMING FROM STARTER ADAPTER WHILE PROP WAS BEING PULLED THRU FOR COMPRESSIO	N CHECKS.  STARTER ADAPTER WAS REMOVED AND INSPECTED.  NO OBVIOUS DEFECTS WERE NOTED.  ASSEMBLY (635048A1) SENT OUT FOR 	EVALUATION/REPAIR AND A NEW CLUTCH SPRING BEARING WAS INSTALLED.				1	H	7	1 	3O	3	O		3A17    	E1CE				 
2007061300221	20070613	00221	CE  	2007	6	13	2007FA0000406    	1	20030611	G	7810	02R3022406	EXHAUST DUCT    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		6002 	3009 							WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND	 IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007061300226	20070613	00226	CE  	2007	6	13	2007FA0000433    	1	20030629	G	7810	02R3022406	EXHAUST DUCT    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		11669	1171 							WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND	 IN THE SKI SLOPE. EXHAUST DUCT SB HAD BEEN COMPLIED WITH 1171 HOURS PRIOR. POWER SECTION WAS REMOVED FOR REPAIR.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2007061300215	20070613	00215	CE  	2007	6	13	2007FA0000440    	1	20030514	G	7810	02R3022406	EXHAUST DUCT    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09		10498	1892 							WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND	 IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2003091900026	20030919	00026	CE  	2003	9	19	200FA0000645     	1	20030411	G	5521	50610000487	RIB             			BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					ELEVATOR	CRACKED         	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	355JS					LW257				END RIB CRACKED SEVERAL PLACES.  FWD SPAR, INBOARD END CRACKED.						1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2003122900194	20031229	00194		2003	12	29	2204             	4	20031202	G	2562	AK450	G SWITCH        			YAKLEV	YAK   	YAK52W      	05607AN	GL  										ZONE 200	WILL NOT TEST   	B			BD6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NE	05	520JE	252  				0012210				G-SWITCH FAILS TO ACTIVATE DURING TEST.						1	L	7	1 	3R			RT	EXPA1L71					 
2003123000092	20031230	00092		2003	12	30	22041            	4	20031202	G	2562	AK450	ELT             			YAKLEV	YAK   	YAK52W      	05607AN	GL  										TAILCONE	DETACHED        	B			BD6R	K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			NE	05	520JE	252  				0012210				AUXILLARY ANTENNA FELL OFF OF UNIT, WAS FOUND IN TAILCONE NEAR CONTROL SURFACE LINKAGES.						1	L	7	1 	3R			RT	EXPA1L71					 
2003111400060	20031114	00060	EU  	2003	11	14	258125           	1	20031015	G	3412	2T2D126	RELAY           			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	ARCED           	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			SW	09	802X	5233 				NA0418				PILOT REPORTED SMOKE IN COCKPIT JUST PRIOR TO LANDING.  AIRCRAFT LANDED WITHOUT HAVING TO DECLARE AN EMERGENCY.  MAINTEN	ANCE FOUND RELAY K30 IN THE TAS PROBE HEAT CIRCUIT HAD OVERHEATED DUE TO A FAILED CONNECTION ON THE POWER FEED TO THE PR	OBE HEATER.  RELAY K30 AND K25 AND K11 WERE REPLACED.  K25 AND K11 WERE REPLACED FOR PERCAUTIONARY REASONS DUE TO THE HE	AT DAMGE FROM RELAY K30.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2003082600097	20030826	00097	CE  	2003	8	26	265522130        	1	20030606	G	2730	265522130	BELLCRANK       			RKWELL	NA265 	NA265       	6402602	CE  										ELEVATOR	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	XASMQ	11964				28250				ELEVATOR BIAS BUNGEE OPERATING BELLCRANK INSPECTED AND FOUND TO HAVE MAJOR CORROSION AT ATTACHMENT FORK FOR FOR BIAS BUN	GEE TRIM TURNBUCKLE.					2	L	7	2 	4J			 	A2WE    					 
2004021300022	20040213	00022	CE  	2004	2	13	3                	1	20031230	G	1430	464P5A42	BOLT            			CESSNA	206   	TU206D      	2073344	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C403   	GL  	NLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		560  	560  			U20605485	291553R	779503		DURING THE REMOVE THE NOSE LANDING GEAR FOR ITS SERVICING AND LUBRICATION, THE TECHNICIAN DISCOVERED THE DRAG LINK REAR 	ATTACHMENT BOLT (NAS 464P5A42) WAS SHEARED.					1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
2003031300025	20030313	00025	SO  	2003	3	13	3054K            	1	20030304	G	2421	ALU306	SHAFT           	ELECTROSYS  		PIPER 	PA34  	PA34200T    	7103406	SO  										ALTERNATOR	BROKEN          	B				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	21	3054K	497  			A73067	347970102				AIRCRAFT RIGHT ALTERNATOR DROPPED OFF LINE IN FLIGHT. PILOT RETURNED TO AIRPORT WITHOUT INCIDENT. REMOVED ALTERNATOR AND	 DISCOVERED DRIVE SHAFT SHEARED. THIS AIRCRAFT HAS THE SINGLE PIECE COUPLING INSTALLED. WHEN SHAFT SHEARS WE HAVE SEEN P	IECES CONTAMINANT OIL SYSTEM AND SUBSEQUENTLY CAUSE OIL PUMP FAILURES.				1	L	7	2 	3O			 	A7SO    					 
2003091800137	20030918	00137	CE  	2003	9	18	310EE            	1	20030808	G	5320	08113031	SUPPORT BRACKET 			CESSNA	310   	310J        	2074226	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	FUSELAGE	BROKEN          	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	09	310EE	6431 				310J0001				RH LANDING GEAR COLLAPSED ON LANDING. FOUND THAT THE UPPER BELLCRANK BRACKETT P/N 0811303-1 WHICH SUPPORTS AND GUIDES TH	E RT MAIN LANDING GEAR PUSH/PULL TUBES FROM GEAR BOX TO GEAR ASSEMBLY SEPERATED FROM BULKHEAD DUE TO MOUNTING RIVET FAIL	URE. THIS SEPERATION WOULD NOT ALLOW THE RT GEAR ASSEMBLY TO STAY IN A (DOWN AND LOCKED) POSITION.				1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P5EA	 
2003092200015	20030922	00015	EU  	2003	9	22	3144032403       	1	20030324	G	6720	350A33214501	PITCH LINK      			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAIL ROTOR	WORN            	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5226R	1916 				3144	22090			TAIL ROTOR PC LINK WORN.						1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2003091700037	20030917	00037	WP  	2003	9	17	3298S            	2	20030724	G	7250		BLADE           			BRAERO	DH125 	BAE125800A  	1500285	EU  	ALIDSG	TFE731	TFE7313AR   	 	WP  					NR 2 ENGINE	MISSING         	B			WTXR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			NM	03	800VC	4299 				NA0415	P95159			3298S- AIRCRAFT EXPERIENCED VIBRATION IN FLIGHT.  NR 2 ENGINE WAS SHUTDOWN IN-FLIGHT.  AIRCRAFT ARRIVED SAFETLY.  VISUAL	 INSPECTION OF NR 2 ENGINE REVEALED A 1.0 TO 1.5 INCH PIECE OF 1EA 3RD STAGE TURBINE WHEEL BLADE WAS MISSING.  ENGINE WA	S SWAPPED WITH A LOANER AND THE DEFECTIVE ENGINE WAS SENT TO HONEYWELL.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2003091900128	20030919	00128	EU  	2003	9	19	3602081003       	1	20030810	G	2121	0500846	BLOWER MOTOR    			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					AIR CONDITIONER	DAMAGED         	E			S4WA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	820NA	306  				3602	22342			AIR CONDITIONING BLOWER POPS CIRCUIT BREAKER.						1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2003091500034	20030915	00034	CE  	2003	9	15	38850            	1	20030718	G	2913	AN9181D	FITTING         			BEECH 	18    	D18S        	1151004	CE  										HYD POWER PACK	CRACKED         	B				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			GL	09	600M					A820				AIRCRAFT GEAR STARTED TO DROP DURING FLIGHT.  FOUND TWO AN CROSS FITTINGS CRACKED.  THESE ARE MOUNTED AT THE HYDRAULIC P	OWER PACK UNDER THE PEDESTAL IN THE COCKPIT.  REPLACED FITTINGS AND ELBOWS WITH NEW.					1	L	7	2 	3R			 	A765    					 
2003091600023	20030916	00023	NM  	2003	9	16	3983             	1	20030717	G	5530	500N39507	TORQUE TUBE     			DOUG  	600N  	600N        	3027377	NM  										VERTICAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	660MC	489  	239  			RN012				PILOT NOTED DURING PREFLIGHT INSP ON RAMP, THAT THE UPPER LT VERTICAL STAB WAS BENT IN APPRX 3 INCHES AT THE TOP. VIDEO 	FOOTAGE OF THE FBO WAS REVIEWED AND IT WAS SEEN THAT THE AIRCRAFT LANDED IN THIS DAMAGE (WAS NOT CAUSED BY PERSONS OR EQ	UIPMENT ON THE GROUND).  THE VERTICAL STAB WAS REMOVED AND A CRACK RUNNING THROUGH ONE OF THE CONTROL SURFACE ATTACH HOL	ES AND 330 DEGREES AROUND THE TUBE. THE RT SIDE WAS INSPECTED IAW MD SB600N-30R1, NO DEFECTS FOUND. CRACKED PART AND EXP	ANDABLE BOLTS BEING SENT TO MFG FOR EVALUATION.  NEW TORQUE TUBE AND ATTACHING HARDWARE BEING INSTALLED.  POSSIBLE FIX W	OULD BE INTERNAL TUBE ACTING AS A SECOND LOAD PATH.	1	G	7	1 	3U			NC	H3WE    					 
2003122900211	20031229	00211	SO  	2003	12	29	39906            	1	20031125	G	2820		LINE            			PIPER 	PA34  	PA34220T    	7103420	SO  										FUEL SYSTEM	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	09	2741L	1040 				3449116				FUEL ODOR IN CABIN CAUSED US TO REMOVE SIDEWALLS TO TRACE LINES.  FOUND BOTH CROSSOVER LINES AND SCUPPERS WET WITH FUEL.	  COULD NOT GET LINES TO STOP LEAKING BY TORQUING.  DEFUELED AND DISASSEMBLED ALL FITTINGS ASSOCIATED.  CLEANED AND INSP	ECTED AND FOUND ALL TO BE OK.  NO CRACKS OR DEFORMITIES WERE NOTED.  RE-ASSEMBLED WITH CONICAL SEALS AT ALL JOINTS.  RE-	FUELED AND NO FURTHER LEAKING WAS NOTED.			1	L	7	2 	3O			 	A7SO    					 
2003091600151	20030916	00151	EU  	2003	9	16	3998             	1	20030724	G	6310	350A35109120	COUPLING        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TRANSMISSION	OVERHEATED      	B				A				UNSCHED LANDING         				B	M	J	SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 	WARNING INDICATION        	CR	CRUISE         	1			WP	05	557CB	345  				3431				DURING FLT, AIRCREW NOTED BURNING RUBBER ODOR.  DURING UNEVENTFULL, UN-PLANNED LANDING AIRCREW NOTED THE AIR-CONDITIONIN	G BELT HAD BURNED UP AND MELTED TO AIR-CONDITIONING COMPRESSOR. THIS WAS DUE TO AN SEIZED AIR-CONDITIONING COMPRESSOR. I	T IS OUR EXPERIENCE DURING A FAILURE OF THIS TYPE THE DRIVE BELT SHEARS IN HALF, PREVENTING DAMAGE TO DRIVE PULLEY. FURT	HER INSPECTION REVEALED THAT DURING FAILURE OF COMPRESSOR AND BELT, THE ENGINE TO TRANSMISSION INPUT COUPLING HAD OVER-H	EATED CAUSING WHAT APPEARS TO BE THOUSANDS OF HEAT RELATED STRESS CRACKS IN THE COUPLING. THIS OCCURED BECAUSE THE DRIVE	 BELT DID NOT SHEAR.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003032400036	20030324	00036	SO  	2003	3	24	3M1              	1	20030311	G	2497	220CC02	CONTACTOR       			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					LEFT PDB	STICKS          	B			LD2R	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			GL	15	33M	1121 				594	295312			CONTACTOR STICKS INTERMITTENLY. REPLACED CONTACTOR OPERATIONAL CHECKS NORMAL.						2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003032400037	20030324	00037	SO  	2003	3	24	3M2              	1	20030318	G	2497	220CC02	CONTACTOR       			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					LEFT PDB	FAILED          	B			LD2R	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			GL	15	33M	1124 				594	295312			CONTACTOR INTERMITTENLY FAILS TO CONNECT TO THE BUS.   REPLACED CONTACTOR.						2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003050600248	20030506	00248	SO  	2003	5	6	3M24031          	1	20030411	G	3240		ROTOR           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					BRAKE ASSY	CRACKED         	B			LD2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	23M	1499 				579	261262			BRAKE ROTOR SPLINTERING AT KEYWAY CLIPS.						2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003050600250	20030506	00250	SO  	2003	5	6	3M24032          	1	20030411	G	3240		ROTOR           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					BRAKE ASSY	CHIPPED         	B			LD2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	23M	57   				579	261262			ROTOR IS CHIPPED AT BRAKE KEYWAY CLIP.						2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003050600251	20030506	00251	SO  	2003	5	6	3M24033          	1	20030411	G	3240	1159SCL5043	ROTOR           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					BRAKE ASSY	CRACKED         	B			LD2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	23M	1499 				579	261262			ROTOR IS SPLINTERING AT KEYWAY CLIPS.						2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003060400236	20030604	00236	SO  	2003	6	4	3M25603          	1	20030506	G	3233		CLAMP           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					MLG	OUT OF POSITION 	B			LD2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	23M					579	261262			CLAMP ON RIGHT HAND MAIN GEAR SIDE BRACE ACTUATOR IS CONTACTING GEAR ACTUATION FLEX LINE. REPOSITIONED CLAMP TO CLEAR LI	NE.					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003060400237	20030604	00237	SO  	2003	6	4	3M35603          	1	20030506	G	3233		CLAMP           			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					MLG	OUT OF POSITION 	B			LD2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	33M					594	295312			CLAMP ON RIGHT HAND MAIN LANDING GEAR SIDE BRACE ACTUATOR IS CONTACTING ACTUATOR FLEX LINE.  REPOSITION CLAMP TO CLEAR L	INE.					2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003103000074	20031030	00074	SO  	2003	10	30	3M5940903        	1	20030930	G	3242	1159SCH5285	METERING VALVE  			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					NLG BRAKES	INTERMITTENT    	B			LD2R	O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			GL	15	33M	1388 	1388 			594	1129511312			BRAKES ARE VERY GRABBY WILL NOT APPLY EVENLY.						2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003103000075	20031030	00075	SO  	2003	10	30	3M59409031       	1	20030930	G	3242	1159SCH5285	METERING VALVE  			GULSTM	GV    	GULFSTREAMGV	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					BRAKES	INTERMITTENT    	B			LD2R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	15	33M	1388 	1388 			594	1129511312			METERING VALVES CAUSING GRABBY BRAKES UNABLE TO APPLY EVENLY						2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2003111400003	20031114	00003	SO  	2003	11	14	421C111003DG     	2	20031112	G	8530	654654	CYLINDER        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					ENGINE	WORN            	B			JBZR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	27	27RX	1158 				421C0404	292378R			ON ENGINE START-UP, REAR PASSENGERS NOTED GREATER THAN USUAL SMOKE EMITTED FROM EXHAUST ON NR 1 ENGINE.  THE PILOT SHUT 	DOWN AND PERFORMED A VISUAL INSPECTION OF THE ENGINE NACELLE FOR OIL AND/OR OTHER ABNORMAL CONDITIONS:  NONE NOTED.  THE	 PILOT PERFORMED ANOTHER START WITH SIMILAR RESULTS OF LIGHT SMOKE WHICH DISSAPEARED WITH INCREASED RPM.  THERE WERE NO 	UNUSUAL GAUGE INDICATIONS ON HIGH POWER RUN-UP.  MAINTENANCE WAS CALLED TO INVESTIGATE.  THE NEXT START-UP PRODUCED LITT	LE SMOKE.  A PRECAUTIONARY CYLINDER COMPRESSION CHECK REVEALED NR 1 CYLINDER TO HAVE BELOW SPEC. COMPRESSION.  THE CYLIN	DER WAS REMOVED FOR INVESTIGATION AND REVEALED WORN CYLINDER WALLS AND A STUCK OIL CONTROL RING.  THE CYLINDER/PISTON AS	1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2003021800263	20030218	00263	SW  	2003	2	18	53075            	1	20030205	G	7920	23063412	HOSE            			BELL  	407   	407         	1182206	SW  										ENGINE	CHAFED          	B			JBZA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	27	108SD	3447 				53075				THIS HOSE DETERIORATES RAPIDLY DUE TO THE FACT THAT THE HOSE IS A CORRUGATED TUBE HOUSED IN A STEEL BRAID THAT CHAFES TH	E TUBE CAUSING CHAFE DAMAGE TO THE HOSE AND SUBSEQUENT OIL LEAK.  THIS HOSE SHOULD BE REDESIGNED TO EXTEND RELIABILITY. 	 THE HOSES LAST ABOUT 2 YEARS, 1,000 HOURS.				1	G	7	1 	3U			O	H2SW    					 
2003060400047	20030604	00047	EA  	2003	6	4	5906L            	2	20030422	G	8550	1116	HOSE            			AMRGEN	AA1   	AA1         	0630610	SO  	LYC   	O320  	O320A2B     	41508	EA  					ENGINE OIL	SEPARATED       	F				B				EMER. DESCENT           				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			SW	07	5906L					AA10206	L3798627A			THE 111-6 HOSE ASSEMBLY ORIGINALLY MANUFACTURED IN 1996 BY MFG WAS OVERHAULED/REPAIRED BY UNKNOWN PERSONS ON 7-02 AS STA	TED IN OWNERS ENGINE LOG BOOK ENTRY AND STAMP IMPRESSIONS DATED ON ORIGINAL TAG.  THE ORIGINAL HOSE ASSEMBLY WAS TAKEN A	PART AND A NEW HOSE ASSEMBLED INTO THE ORIGINAL FITTINGS.  THE HOSE FITTING BLEW OFF THE 111-6 HOSE JUST AFTER TAKE OFF 	AND THE CABIN FILLED WITH SMOKE ACCORDING TO THE PILOT/OWNER.  UPON INVESTIGATION, IT APPEARS THE HOSE ASSEMBLY MAY NOT 	HAVE BEEN ASSEMBLED PROPERLY.  THE NIPPLE WAS NOT INSERTED INTO THE INSIDE DIAMETER OF THE HOSE IAW MFG.		1	L	7	1 	3O	3	O	 	A11EA   	E274				 
2003020500005	20030205	00005	SW  	2003	2	5	62691            	1	20030116	G	3244		TIRE            			GULSTM	690TP 	690D        	3970405	SW  										MLG	GROOVED         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	909HH					15035				THIS AIRCRAFT HAS CLEVELAND BRAKES INSTALLED.  THE CLEARANCE BETWEEN THE TIRE SIDEWALL AND BRAKE IN MINIMAL.  WHEN THE S	IDEWALL FLEXES DURING LANDING IT CONTACTS THE BRAKE CAUSING A 360 DEGREE GROVE IN THE TIRE SIDEWALL.  THIS DOES NOT SEEM	 TO OCCUR WITH OTHER TIRE MANUFACTURES, ONLY WITH GOODYEAR FLIGHT CUSTOM II.				1	H	7	2 	3T			 	2A4     					 
2003122900202	20031229	00202	GL  	2003	12	29	649122003        	1	20031217	G	2730		CARTRIDGE       			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					ELEVATOR	FAILED          	B				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	15	938CD					1338				ON APPROACH, PILOT DISENGAGED AUTOPILOT, FOUND ELEVATOR CONTROL TO BE STUCK IN FIXED POSITION, PITCH TRIM CONTROL WAS ST	ILL AVAILABLE BOTH UP AND DOWN. AFTER SEVERAL ATTEMPTS TO (FREE) CONTROL WITH NO SUCCESS THE PILOT "JERKED" CONTROL BACK	. CONTROL BROKE FREE ENOUGH TO PROVIDE "UP" ELEVATOR CONTROL. PILOT LANDED WITHOUT INCIDENT.  AC WAS MOVED INTO HEATED H	ANGAR WHERE INITIAL INSPECTION REVEALED ELEVATOR TO BE VERY DIFFICULT TO MOVE IN EITHER DIRECTION.  ELEVATOR WAS ABLE TO	 BE MOVED TO FULL TRAVELS IN BOTH DIRECTIONS WITH RELATIVE EASE ALTHOUGH PITCH TRIM CARTRIDGE MADE MORE "NOISE" THAN NOR	MAL. PITCH TRIM CARTRIDGE WAS REMOVED AND REPLACED WITH NEW PART. REMOVED PART WAS INSPECTED WITH NO ANOMALIES NOTED.	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2003101500019	20031015	00019		2003	10	15	8010304          	4	20031013	G	2563		LANYARD         			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PARACHUTE	MISROUTED       	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09		940  	100  			0047	686664			THE AIRCRAFT CAME INTO OUR FACILITY FOR AN ANNUAL INSPECTION. WHILE PERFORMING THE INSPECTION IT WAS NOTED THAT THE PARA	CHUTE LANYARD CABLES THAT CONNECT THE ROCKET PICK-UP COLLAR TO THE PARACHUTE WERE MISROUTED. THIS WAS MOST LIKELY DONE W	HEN ACCOMPLISHING CAPS SYSTEM MAINTENANCE. IT IS OF PARTICULAR CONCERN SINCE CABLE MISROUTING WOULD MOST LIKELY RENDER T	HE PARACHUTE INEFFECTIVE. THE CABLES WERE REROUTED IN ACCORDANCE WITH THE CIRRUS AIRFRAME PARACHUTE SYSTEM COMPONENT MAN	UAL.		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2003091500029	20030915	00029	CE  	2003	9	15	84031            	1	20030804	G	7712	31017262	TORQUE SENSOR   			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					ENGINE	MALFUNCTIONED   	B				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			NM	03	949SW					BE34	P27071			TEMP, TORQUE AND FUEL FLOW ALL DECLINED.  ENGINE WAS SECURED AND PROP FEATHERED AND AN UNEVENTFUL LANDING WAS MADE AT GJ	T.  UPON ENGINE DISASSEMBLY, THE TORQUE SENSOR SHAFT WAS FOUND SHEARED.					1	L	7	2 	4T	4	T	 	A14CE   	E2WE				 
2003070800030	20030708	00030	WP  	2003	7	8	852186           	2	20030611	G	8550	30743723	VALVE           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENGINE	FAILED          	B			ZN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	ZN3R									DE-OIL VALVE FAILED TO OPEN AND ALLOW OIL TO THE 4/5 CAVITY. THEREBY CAUSING THE NR 4 AND NR 5 BEARINGS TO SEIZE, AND TH	E ENGINE TO LOCK UP AFTER 17 MIN OF OPERATION.					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2003111400044	20031114	00044	GL  	2003	11	14	95195            	1	20031017	G	3240		CONTROL CABLE   			TCRAFT	BC    	BC12D       	8850316	GL  	CONT  	A65   	A65*        	17003	SO  					BRAKE	BROKEN          	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	09	95195					9595				LEFT BRAKE PEDAL CABLE BROKE APPROXIMATELY 10 INCHES AFT OF BRAKE PEDAL.						1	H	7	1 	3O	3	O	 	A696    	E205				 
2003111300039	20031113	00039	CE  	2003	11	13	97CW             	1	20031015	G	2897		WIRE HARNESS    	AIRBORNE    		CESSNA	500   	550         	2076604	CE  										FUEL PUMP	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	797CW	7553 			7AG141	5500232				FUEL PUMP WIRING HARNESS IS NOT SUPPORTED WITHIN THE FUEL CELL AND CHAFED ON THE FUEL LINE FROM THE PRIMARY PUMP TO THE 	CHECK VALVE INSIDE THE FUEL CELL.  THERE WAS .006 INCH DAMAGE TO THE WALL OF THE FUEL LINE AND THE PUMP HARNESS SHIELDIN	G WAS CHAFED THROUGH.  THERE WAS NO EVIDENCE OF ARCING.				1	L	7	2 	4F			 	A22CE   					 
2003111700013	20031117	00013	CE  	2003	11	17	97CW1            	1	20030926	G	2897		WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  										ZONE 600	CHAFED          	B			R3R2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	797CW	7553 	997  		7AG141	5500232				THE FUEL PUMP WIRING HARNESS IS NOT SUPPORTED WITHIN THE FUEL CELL AND CHAFED ON THE ALUMINUM FUEL LINE FROM THE PRIMARY	 PUMP TO THE CHECK VALVE INSIDE THE FUEL CELL.  THERE WAS .006 INCHES DAMAGE TO THE WALL OF THE FUEL LINE AND THE SHIELD	ING ON THE PUMP WIRING HARNESS WAS CHAFED THROUGH.  THERE WAS NO EVIDENCE OF ARCING.				1	L	7	2 	4F			 	A22CE   					 
2003050900099	20030509	00099	SW  	2003	5	9	AC2A086260       	1	20030409	G	2930		TRANSMITTER     			BELL  	430   	430         	1182150	SW  										HYD SYSTEM	FALSE INDICATION	E			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07	430CT					49089				AFTER FLIGHT IN RAIN, NR 2 HYDRAULIC PRESSURE INCREASED TO 1760 PSI AND NR 2 HYDRAULIC TEMPERATURE INCREASED TO 44 DEGRE	ES C. CLEANED WATER FROM NR 2 HYDRAULIC PRESSURE TRANSMITTER CONNECTOR PLUG.					1	G	7	2 	3U			RT	H9SW    					 
2003050900101	20030509	00101	SW  	2003	5	9	AC2A086262       	1	20030409	G	6320		CONNECTOR       			BELL  	430   	430         	1182150	SW  										GEARBOX SUMP	DAMAGED         	E			AC2A	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SO	07	430CM					49090				TRANSMISSION SUMP CHIP LITE WOULD NOT PULSE. CLEANED MOISTURE FROM SUMP CONNECTOR  PLUG.  AIRCRAFT GROUND RUN O.K.						1	G	7	2 	3U			RT	H9SW    					 
2003050900103	20030509	00103		2003	5	9	AC2A086264       	4	20030410	G	3421	430375002109	TUBE            																	EFIS	MISMANUFACTURED 	E			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07										TUBE CAME IN WITH BUTTONS IN WRONG LOCATIONS, WAS NOT INSTALLED IN AIRCRAFT. REPLACED WITH REPAIRED TUBE.																			 
2003050900097	20030509	00097	NE  	2003	5	9	AC2A086265       	2	20030410	G	7321	23072726	HYDROMECH UNIT  			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					NR 2 ENGINE	LEAKING         	E			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	430CV	3084 				49072	844078			REMOVED FOR HMU BACKLASH CHECK.  FOUND TO BE LEAKING FUEL FROM DRIVE SPLINE SEAL. REPLACED HMU.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2003051400233	20030514	00233	NE  	2003	5	14	AC2A086266       	1	20030411	G	2435	M20021	BRUSHES         			SKRSKY	S76   	S76A        	8143006	NE  										STARTER GEN	DETACHED        	E			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07	5401G	295  			5325	760137				PART IS DISBONDED. THE ATTACHING LEAD AND SPRING WEAR PLATE AND RIVET CAME APART. REPLACED ALL FOUR BRUSHES AND RAN IN B	RUSHES.					1	G	7	2 	3U			 	H1NE    					 
2003050900104	20030509	00104	SW  	2003	5	9	AC2A086267       	1	20030417	G	3340	900601	LIGHT           			BELL  	430   	430         	1182150	SW  										EXTERIOR	DEFECTIVE       	E			AC2A	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	430CT	428  				49089				PART IS DEFECTIVE. LANDING LIGHT WILL NOT ILLUMINATE. CHANGING BULB DID NOT SOLVE PROBLEM. LIGHT ASSEMBLY WAS REPLACED.						1	G	7	2 	3U			RT	H9SW    					 
2003050900098	20030509	00098	SW  	2003	5	9	AC2A086268       	1	20030417	G	3213	206323021	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07	17592	1019 				51535				PART IS CORRODED. CORROSION PITS BEYOND LIMITS. WILL COMPLETE NEW PART INFORMATION FOR THIS MMIR WHEN 592 RETURNS FROM R	E-FURB. OLD CROSSTUBE WILL BE RETURNED AT THAT TIME ALSO. PART WAS REPLACED.					1	G	7	1 	3U			 	H2SW    					 
2003061900008	20030619	00008	NE  	2003	6	19	AC2A086761       	1	20030522	G	2821	1737391	RING            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					FUEL FILTER	BROKEN          	E			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	7266F					760273				DURING FUEL FILTER CHANGE, RETAINING RING INSIDE FUEL FILTER HOUSING CAME OUT IN SEVERAL PIECES. REPLACED FILTER HOUSING	 AND RETAINING RING.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2003061900010	20030619	00010	NE  	2003	6	19	AC2A086767       	1	20030529	G	6310	7636104008103	DISC PACK       			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	5402T					760140				DISC PACK IS CRACKED. DISC PACK WAS FOUND CRACKED IN EIGHT PLACES DURING SCHEDULED INSPECTION. PART WAS REPLACED.						1	G	7	2 	3U			 	H1NE    					 
2003092600018	20030926	00018	EU  	2003	9	26	AELLCDG001       	1	20030827	G	2910	11745020V002	HYDRAULIC SYSTEM			BOLKMS	117   	BK117A3     	5626015	EU  											MISOVERHAULED   	B			VY1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19			1800 							SEVERAL COMPONENTS OF THIS TANDEM HYDRAULIC UNIT RECENTLY OVERHAULED, SEEM TO HAVE BEEN TREATED IN A WAY THAT NEITHER CO	RRESPONDS TO THE ORIGINAL DRAWINGS/SPECIFICATIONS OF THE UNIT NOR THE MBB-BK 117 REPAIR MANUAL (REM, CHAPTER 401)					1	G	7	2 	3U			 	H13EU   					 
2003020300077	20030203	00077	SW  	2003	2	3	ALGA084066       	1	20030130	G	6510	214010530101	BEARING         			BELL  	214   	214ST       	1182106	SW  										TAIL ROTOR	WORN            	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	390AL	1070 				28198				TAIL ROTOR BEARING WORN.						2	G	7	2 	4U			 	H10SW   					 
2003031800009	20030318	00009	EU  	2003	3	18	ALGA085106       	1	20030306	G	3110	B19030FB02	DISPLAY         			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					COCKPIT	DEFECTIVE       	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	523AL	610  				1262				LANE NR 1 CALCULATOR FAILURE.						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2003031800010	20030318	00010		2003	3	18	ALGA085108       	4	20030306	G	8300	E6893672	PINION GEAR     			CLARK 	1000  	1000CLARK   	2230102	SW  										GEARBOX	SPALLED         	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	PARTO	150  			CAG90222					HEAVY SPALLING ON DRIVE SIDE OF PINION GEAR TEETH CAUSING METAL IN OIL.THIS IS A REOCCURRING EVENT. VENDOR NEEDS TO UPGR	ADE THEIR QUALITY CONTROL ON GEAR MATERIAL AND FABRICATION OF GEARS.					1	Q	7	1 	3R			 	2A6     					 
2003042300069	20030423	00069	SW  	2003	4	23	ALGA085884       	1	20030401	G	6320	E6893672	PINION GEAR     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	SPALLED         	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	527AL	621  			CAG47087	53211	CAE847258			DUE TO IMPROPER MESHING OF GEARS, PINION GEAR HAD EXCESSIVE SPALLING ON GEAR TEETH. REMOVED AND REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003042300070	20030423	00070		2003	4	23	ALGA085885       	4	20030401	G	8300	E6898785	GEAR            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					PTO GEAR	DEFECTIVE       	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	527AL	621  			CAG47087	53211	CAE847258			REMOVED PTO GEAR IAW EXTEX MANDATORY BULLETIN NR T-075 REMOVED AND REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003042300071	20030423	00071	GL  	2003	4	23	ALGA085886       	2	20030401	G	7313	23008054	NOZZLE          			CLARK 	1000  	1000CLARK   	2230102	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	DISTORTED       	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										MATING SURFACE FOR SEALING PURPOSES BETWEEN NR1 & NR2 NOZZLES IS OUT OF CONCENTICITY CAUSING AIR LEAKAGE, CREATING LOW P	OWER CONDITIONS. RETURNED PART TO MFG FOR WARRANTY EXCHANGE.					1	Q	7	1 	3R	3	U	 	2A6     	E4CE				 
2003042300078	20030423	00078	SW  	2003	4	23	ALGA085888       	1	20030401	G	6220	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										ROTOR HEAD	ROUGH           	E			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	403AL	1694 				53478				MAIN ROTOR HEAD UNIVERSAL BEARING ROUGH AND RATCHETY. REMOVED IAW 407, MM.						1	G	7	1 	3U			O	H2SW    					 
2003041000228	20030410	00228	SW  	2003	4	10	ALGA085897       	1	20030402	G	7921	2660162401	IMPELLER        			BELL  	412   	412         	1182202	SW  										COOLER BLOWER	CRACKED         	E			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	XASYL				51001248	36101				IMPELLER FOUND CRACKED DURING NDI. CRACK WAS 1/4 INCH LONG EMINATING FROM BLADE TIP, IMMEDIATELY ADJACENT TO REINFORCMEN	T RING, EXTENDING STRAIGHT IN DIRECTION OF BLADE ROOT. REPLACED WITH NEW IMPELLER.					1	G	7	2 	4U			 	H4SW    					 
2003050900107	20030509	00107	SW  	2003	5	9	ALGA086243       	1	20030423	G	6220	406310405101	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	DEFECTIVE       	E			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	577AL	1012 				53247				FOUND BEARING DEFECTIVE, EXCESSIVE PLAY AND ROUGH/RATCHETING.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003050900108	20030509	00108	SW  	2003	5	9	ALGA086244       	1	20030423	G	6220	406310405101	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	WORN            	E			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	627AL	1434 				53284				FOUND BEARING TO BE WORN AND RATCHETING.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003050900109	20030509	00109	SW  	2003	5	9	ALGA086247       	1	20030423	G	6220	406310405101	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					UNIVERSAL	WORN            	E			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	587AL	1978 				53248				FOUND UNIVERSAL BEARING WORN AND ROUGH.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003052900021	20030529	00021	SW  	2003	5	29	ALGA086490       	1	20030522	G	6220	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	STICKING        	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	497AL					53172				UNIVERSAL STICKING, RATCHETY AND WORN. REMOVED AND REPLACED WITH SERVCIABLE PART.    SUBMITTED BY: PRESTON BARZARE						1	G	7	1 	3U			O	H2SW    					 
2003052900022	20030529	00022	SW  	2003	5	29	ALGA086492       	1	20030523	G	6220	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	STICKING        	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	409AL	526  				53494				UNIVERAL STICKING, RATCHETY AND WORN. REMOVED AND REPLACED WITH SERVICABLE PART.    SUBMITTED BY: PRESTON BARZARE						1	G	7	1 	3U			O	H2SW    					 
2003052800106	20030528	00106	SW  	2003	5	28	ALGA086493       	1	20030523	G	6220	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	H			ALGA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	417AL	1337 				53054				BEARING WORN AND RATCHETY.						1	G	7	1 	3U			O	H2SW    					 
2003020500026	20030205	00026	EU  	2003	2	5	AMCR200300001    	1	20030107	G	3260	1EN114N119	SQUAT SWITCH    			BRAERO	DH125 	BAE125800A  	1500285	EU  										MLG	FAILED          	B			AMCR	G	B	A		O2 MASK DEPLOYED        	EMER. DESCENT           	UNSCHED LANDING         		J			WARNING INDICATION        			CR	CRUISE         	1			GL	09	526AC	4274 				258169				AFTER 2 HOURS INTO FLIGHT AT A CRUISE ALTITUDE OF FL370, THE CABIN ALTITUDE SUDDENLY STARTED TO CLIMB AT A RAPID RATE. T	HE CABIN ALTITUDE WARNING SOUNDED, THE PAX O2 MASKS DROPPED, THE CREW IMMEDIATELY DONNED THEIR MASKS AND STARTED AN EMER	GENCY DESCENT. AFTER STABILIZING BELOW 10000 FT, THE CREW NOTICED OTHER INDICATIONS THAT LED MAINTENANCE TO THE SQUAT SW	ITCH. UPON LANDING AT THE NEAREST AIRPORT, MAINTENANCE FOUND THE LEFT SQUAT SWITCH HAD FAILED, CAUSING THE AIRPLANE TO T	HINK IT WAS ON THE GROUND, AND CAUSING THE CABIN VENTURI TO TURN ON, WHICH OPENED THE OUTFLOW VALVE.		2	L	7	2 	4F			RT	A3EU    					 
2003091700017	20030917	00017	NM  	2003	9	17	AMCR200300002    	1	20030725	G	2751	BACP30F4	PULLEY          			BOEING	727   	72717       	1384008	NM  										ZONE 600	FAILED          	B			AMCR	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			GL	09	624VA	30995				20327				UPON WING INSPECTION, FOUND RIGHT FLAP INDICATOR PULLEY SEVERELY OFFSET. FOUND THE BEARING HAD FAILED. NO INDICATION PRO	BLEMS HAD SURFACED YET. PULLEY REPLACED.					2	L	7	3 	4F			 	A3WE    					 
2003091900073	20030919	00073	GL  	2003	9	19	AMCR200300003    	1	20030812	G	5751	10332002	HINGE FITTING   			CIRRUS	SR    	SR22        	2130001	GL  										AILERON	LOOSE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	279DV	212  				0196				DURING PILOT'S PREFLIGHT, NOTICED THE RIGHT AILERON, INBOARD SIDE, HAVING EXCESSIVE PLAY. FURTHER INSPECTION REVEALED TH	AT THE TWO BOLTS (AN4-12A)HOLDING THE INBOARD AILERON HINGE AND THE OUTBOARD FLAP HINGE WERE LOOSE. THIS ALLOWED THE AIL	ERON HINGE BRACKET TO MOVE UP AND DOWN ABOUT 3/16". THE NUTS WERE TORQUE-SEAL STRIPED. MAINTENANCE RE-TORQUED THE NUTS A	ND DID A RIGGING CHECK. NO FURTHER ACTION REQUIRED. THE LEFT WING WAS INSPECTED AND THE HARDWARE WAS FOUND TO BE TIGHT.			1	L	7	1 	3O			NT	A00009CH					 
2003111400030	20031114	00030	EU  	2003	11	14	AMCR200300004    	1	20031028	G	3240	AC69784	VALVE           			BRAERO	DH125 	BAE125800A  	1500285	EU  										NLG BRAKE	LEAKING         	B			AMCR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	09	526AC	4643 				258169				CREW NOTICED THAT WHEN THEY ENGAGED THE PARKING BRAKE, A VERY LOUD SQUEALING NOISE COMING FROM THE NOSE AREA, WHICH IS T	HE LOCATION OF THE EMERGENCY PRESSURE REDUCING VALVE. CHANGED VALVE, PROBLEM SOLVED. SUSPECT INTERNAL LEAKAGE OF VALVE.					2	L	7	2 	4F			RT	A3EU    					 
2003111400025	20031114	00025	SO  	2003	11	14	AMCR200300005    	1	20031028	G	2810	79C20H	DRAIN VALVE     			GULSTM	GV    	GULFSTREAMGV	3980116	SO  										RT WING	BROKEN          	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	250DV	261  				691				DURING SUMPING OPERATION OF RT WING HOPPER, THE INTERNAL PIN BROKE, WHICH PREVENTED THE SUMP DRAIN FROM LOCKING IN FLUSH	. BY VIRTUE OF THE UNIT BEING ALL PLASTIC, THIS MAY HAVE CONTRIBUTED TO THE PREMATURE FAILURE OF VALVE.					2	L	7	2 	4F			RT	A12EA   					 
2003111300064	20031113	00064	EU  	2003	11	13	AMCR200300006    	1	20031030	G	2842	0204KTU4	PROBE           			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					FUEL QTY	INTERMITTENT    	B			AMCR	O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			GL	09	255DV	9187 				258070				AFTER TAKE-OFF, PILOT NOTICED A INTERMITTENT DROP ON THE LEFT FUEL QUANTITY GAUGE OF ABOUT 500 LBS, THEN EVERYTHING WAS 	NORMAL. ON NEXT LEG, AFTER TAKE-OFF, PILOT NOTICED THE SAME THING. INVESTIGATION UNCOVERED AN INTERMITTENT NR 4 FUEL PRO	BE IN THE LEFT WING. THE INTERMITTENT OPERATION WAS DISCOVERED ONLY AFTER EXPOSING THE PROBES, AND USING A BARFIELD BOX,	 AND THEN TAPPING ON EACH PROBE, UNTIL THE PROBLEM WAS FOUND.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2003111700015	20031117	00015	EU  	2003	11	17	AMCR200300007    	1	20031030	G	2622	898052	EXTINGUISHER    			AMD   	FALC90	FALCON900B  	2730171	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					CABIN	LEAKING         	B			AMCR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	09	522AC	3947 				148				DURING BASIC INSPECTION, TECHNICIAN FOUND THE COCKPIT FIRE EXTINGUISHER PRESSURE GAUGE TO BE READING AT VERY BOTTOM OF G	REEN RANGE. FURTHER INSPECTION REVEALED THE GAUGE TO BE LOOSE, AND SLIGHTLY TWISTING GAUGE CAUSED THE BOTTLE TO LEAK.					2	L	7	3 	4F	4	F	RT	        	E6WE				 
2003123000080	20031230	00080	EU  	2003	12	30	AMCR200300008    	1	20031118	G	2820	11590001	CONTROL VALVE   			BRAERO	DH125 	BAE125800A  	1500285	EU  										FUEL SYSTEM	LEAKING         	B			AMCR	O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			GL	09	527AC	8145 				NA0405				UPON RETURN FROM FLIGHT, MINOR FUEL LEAKAGE WAS OBSERVED ON AFT FUSELAGE. DURING FUELING, FOUND THE FUELING PRESSURE CON	TROL VALVE LEAKING. INVESTIGATION REVEALED THAT EXCESSIVE FUELING PRESSURE MAY HAVE BEEN EXCEEDED WHEN AWAY FROM BASE.  	SUGGEST OPERATORS MONITOR FBO'S FUELING TRUCKS FOR PROPER SINGLE POINT PRESSURE.  (VALVE MFG: FLIGHT REFUELING LTD.)				2	L	7	2 	4F			RT	A3EU    					 
2003120800038	20031208	00038	NM  	2003	12	8	ANCF173EE        	1	20031022	G	3213	5935348501	CYLINDER        			DOUG  	MD80  	MD83        	3023681	NM  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	632CT	9094 	9094 		SCPT1526	49632				AS RESULT OF MAGNETIC PARTICLE INSPECTION AS REQUIRED BY AVIANCA ENGINEERING ORDER 83-32-031 R4 REFERING SB MD80-32A286R	3 WAS FOUND THE SHOCK STRUT CYLINDER AT LT MLG WITH CRACKS					2	L	7	2 	4F			RT	        					 
2003021000067	20030210	00067	SO  	2003	2	10	AUS20030008      	2	20030106	G	8550	07401061	CONTROL VALVE   	CONT        	IO360HB     	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	RECIPROCATING EN	JAMMED          	W			    	K	 	 	 	NONE                    				E	K	I	VIBRATION/BUFFET          	FLUID LOSS                	FLT. ATTITUDE INST.       	NR	NOT REPORTED   	1			AU	S 	 		120  							(AUS) AFTER FIVE MINUTES OF AEROBATICS A LOW OIL PRESSURE INDICATIONWAS NOTED. GROUND CHECK FOUND THE ENGINE OIL QUANTIT	Y OK. ONREMOVAL OF THE AEROBATIC OIL SYSTEM VALVE ASSEMBLY BOTTOM PLUG A1/4IN UNC SCREW WITH ATTACHED LOCKWASHER WAS FOU	ND. SUSPECT SCREW WAS A LYCOMING ROCKER HAT SCREW. PERSONNEL/MAINTENANCE ERROR. FOD				1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2003021000068	20030210	00068	CE  	2003	2	10	AUS20030009      	1	20030103	G	3230	12805978	TUBE            	            	            	CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LANDING GEAR RET	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) LANDING GEAR ACCUMULATOR LINE CONTAINED A SMALL CORROSION PINHOLE. LOSS OF HYDRAULIC FLUID.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2003021000069	20030210	00069	CE  	2003	2	10	AUS20030011      	1	20030107	G	7602	S17773	CABLE           	LYC         	O320E2D     	CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	AMTR	C8289	C8289       	GL  	MIXTURE CONTROL	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE MIXTURE CONTROL INNER CABLE WORN.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	EXPP5N	 
2003021000070	20030210	00070	CE  	2003	2	10	AUS20030012      	1	20030102	G	5410		FIREWALL        	            	            	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	NACELLE/PYLON, M	DAMAGED         	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 	 									(AUS) PILOT REPORTED THAT THE RUDDER TRIM WAS NOT WORKING.INVESTIGATION FOUND DAMAGE TO THE FIREWALL AND SUPPORTING STRU	CTURE.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003021000071	20030210	00071	CE  	2003	2	10	AUS20030015      	1	20030104	G	6120	C2995120101	CABLE           	MCAULY      	D3A34C404   	CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	PROPELLER CONTRO	FAILED          	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			CR	CRUISE         	1			AU	S 	 									(AUS) AIRCRAFT EXPERIENCED AN UNCOMMANDED INCREASE IN PROPELLER RPM AND FAILED TO RESPOND TO FURTHER COMMANDS. INVESTIGA	TION FOUND THAT THE STAINLESS STEEL SHAFT END OF THE PROPELLER PITCH CONTROLCABLE HAD FAILED THROUGH THE THREADS LEVEL W	ITH RODEND LOCATEDNEAR THE PROPELLER GOVERNOR. SUSPECT INITIAL CRACKING WAS CAUSEDBY PREVIOUS INCORRECT RIGGING. PERSONN	EL/MAINTENANCE ERROR.			1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
2003021000072	20030210	00072	SO  	2003	2	10	AUS20030020      	2	20030110	G	8530	655771	EXHAUST VALVE   	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	RECIPROCATING EN	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO4 CYLINDER EXHAUST VALVE SEAT LEAKING. FOLLOWING VALVE REMOVALSEVERE EROSION WAS THEN FOUND ON THE NECK OF THE V	ALVE. NO5 CYLINDER EXHAUST VALVE WAS ALSO FOUND TO HAVE A SIMILAR EROSION PROBLEM. ALL OTHER VALVES WERE CHECKED AND FOU	ND TO BE IN NORMALCONDITION.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003021000073	20030210	00073	EA  	2003	2	10	AUS20030028      	2	20030113	G	8520	SL16711	BEARING         	LYC         	O320D2J     	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		887  		L1611539A					(AUS) NO4 MAIN BEARING FAILED. BEARING MATERIAL MISSING FROM BEARINGSHELL. AREA OF MISSING MATERIAL APPROXIMATELY 15MM B	Y 10MM(0.59IN BY 0.39IN). A SMALLER AREA OF BEARING MATERIAL WAS ALSO FOUND MISSING FROM NO3 MAIN BEARING SHELL. THE ARE	A OF BEARINGMATERIAL DELAMINATED/ERODED FROM NO3 BEARING IS APPROXIMATELY 7MM BY 5MM (0.275IN BY 0.196IN). THE BEARING S	URFACE CONTAINED CRACKS AND EVIDENCE THAT AJOINING AREAS OF THE BEARING SURFACE WEREDISTRESSED AND WOULD FAIL IN THE NEA	R FUTURE. METAL CONTAMINATION OF OIL SYSTEM.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003021000074	20030210	00074	EU  	2003	2	10	AUS20030029      	1	20030114	G	5730	5702010404800	WING            	            	            	MUDRY 	10    	CAP10B      	0950102	EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	WING, PLATES/SKI	FAULTY          	W			    	K	 	 	 	NONE                    				O	F	 	OTHER                     	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 	 				013					(AUS) LH AILERON INBOARD FORWARD EDGE BINDING ON TRAILING EDGE OF LOWER WING SKIN. SUSPECT MANUFACTURING ERROR.						1	L	7	1 	3O	3	O	 	A36EU   	1E10	5	N	P3EU	 
2003021000075	20030210	00075	NM  	2003	2	10	AUS20030042      	1	20030120	G	5730		SKIN            	            	            	BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		WING, PLATES/SKI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING CENTRE SECTION LOWER SKIN CORRODED AT BS 840 LBL30, WL168.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003021000076	20030210	00076	NM  	2003	2	10	AUS20030046      	1	20030120	G	5730		SKIN            	            	            	BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		WING, PLATES/SKI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING CENTRE SECTION LOWER SKIN CORRODED AT BS 800 LBL20, WL168.1.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003021000077	20030210	00077	NM  	2003	2	10	AUS20030050      	1	20030120	G	5710	6521630187	WING            	            	            	BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		WING, MAIN FRAME	DELAMINATED     	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING DELAMINATED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003021000078	20030210	00078	NM  	2003	2	10	AUS20030051      	1	20030120	G	5753	6521630187	SKIN            	            	            	BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		TRAILING EDGE FL	DELAMINATED     	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) INBOARD FORE FLAP LOWER SKIN DELAMINATED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003021000079	20030210	00079	NM  	2003	2	10	AUS20030052      	1	20030120	G	5753	6521630188	SKIN            	            	            	BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		TRAILING EDGE FL	DELAMINATED     	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) INBOARD FORE FLAP LOWER SKIN DELAMINATED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003021200036	20030212	00036	EA  	2003	2	12	AUS20030063      	2	20030116	G	8550	STD1339	SCREW           			GIPPLD	GA8   	GA8         	       	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			300  							(AUS) ENGINE OIL PUMP BODY 'ALLEN' SCREW LOOSE. FOUND DURING INSPECTION IAW LYCOMING SB/555.						1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2003032600019	20030326	00019	SO  	2003	3	26	AUS20030104      	1	20030131	G	5330	CECONITE101	FABRIC          			MAULE 	MX7   	MX7180      	5460185	SO  	LYC   	O360  	O360C1F     	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	FUSELAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE AND EMPENNAGE FABRIC COVERING FAULTY. THE 76.2MM (3IN) LINEAR STRAIGHT AND PINKED TAPES COULD BE REMOVED 	BY LIGHTLYHOLDING THE TAPE BETWEEN THUMB AND FOREFINGER AND WALKING AWAYFROM THE AIRCRAFT REMOVING THE COMPLETE FUSELAGE	 LENGTH. TAPESFROM THE TAILPLANE WERE HANGING ON THE GROUND. DOPE DISPLAYED POOR PENETRATION AND ADHESION. THE PAINT USE	D WAS EXTREMELY BRITTLE AND DID NOT APPEAR TO CONTAIN ANY ELASTIC ADDITIVE.			1	H	7	1 	3O	3	O	NC	3A23    	E286	5	C	P920	 
2003032600020	20030326	00020	SO  	2003	3	26	AUS20030105      	1	20030131	G	1430		BOLT            			MAULE 	MX7   	MX7180      	5460185	SO  	LYC   	O360  	O360C1F     	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  		WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) THE MAJORITY OF THE BOLTS USED IN THE AIRCRAFT ARE AN TYPE BOLTS WITH A DRILLED SHANK COMBINED WITH A SELF LOCKING	 NUT. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O	NC	3A23    	E286	5	C	P920	 
2003032600021	20030326	00021	SO  	2003	3	26	AUS20030107      	1	20030131	G	8011		BRUSHES         	PRESTOLITE  		MAULE 	MX7   	MX7180      	5460185	SO  	LYC   	O360  	O360C1F     	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	STARTER	WORN            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					4Y000105					(AUS) STARTER MOTOR BRUSHES WORN UNEVENLY. THE STARTER MOTOR WASREMOVED DUE TO CONTAMINATION WITH ENGINE OIL FROM A LEAK	ING CRANKSHAFT SEAL. THE UNIT WAS REMOVED AND DISASSEMBLED AND THEFOLLOWING DEFECTS WERE NOTED: BRUSHES FITTED WERE AUTO	MOTIVE PARTS AND MUCH HARDER THAN THE COMMUTATOR. THE BRUSH FACE WEAR WAS ANGLED. THE COMMUTATOR HAD BEEN DAMAGED BY THE	 HARDER BRUSHES. THE STARTER WAS CONTAMINATED EXTERNALLY AND INTERNALLY WITH OIL FROM THE LEAKING CRANKSHAFT SEAL UNAPPR	OVED PART. PERSONNEL/MAINTENANCE ERROR.		1	H	7	1 	3O	3	O	NC	3A23    	E286	5	C	P920	 
2003032600030	20030326	00030	EU  	2003	3	26	AUS20030127      	1	20030109	G	3260	J0892	CONNECTOR       			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					MLG	CORRODED        	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RT MAIN LANDING GEAR WEIGHT ON WHEELS (WOW) SWITCH JUNCTION BOX CONNECTORS J0892A AND J0892B CORRODED AND CONTAMIN	ATED.					2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2003032600032	20030326	00032	CE  	2003	3	26	AUS20030131      	1	20030113	G	7602	S29991	ROD END         			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MIXTURE CONTROL	SEPARATED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) MIXTURE CONTROL SYSTEM ROD END FAULTY.						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2003032600039	20030326	00039	NM  	2003	3	26	AUS20030176      	1	20030214	G	3150	1741010201	DISPLAY         			BOEING	737   	737800*     	       	NM  										CENTRAL WARNING	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 										(AUS) NR 1 MULTIPURPOSE CONTROL DISPLAY UNIT (MCDU) FAULTY.  INVESTIGATION FOUND AN INTERNAL SHORT CIRCUIT CAUSED BY A L	OOSE OBJECT.					2	L	7	2 	4F			RT	A16WE   					 
2003032600015	20030326	00015	NE  	2003	3	26	AUS20030226      	2	20030224	G	7200	CFM567B24	ENGINE          			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM563BUS   	13802	NE  						BIRD STRIKE     	W				O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			AU	S 			2888 							(AUS) ENGINE BIRD STRIKE. REMAINS OF BIRD FOUND INSIDE THRUST REVERSER, IDG OIL COOLER AND BOOSTER INTAKE AREA.  BOROSCO	PE INSPECTION FOUND DAMAGE TO BLADES IN THE BOOSTER AREA.  (P)					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003042300027	20030423	00027	NM  	2003	4	23	AUS20030227      	1	20030217	G	2710		CONTROL CABLE   			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	AILERONS	MISRIGGED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) FLIGHT CONTROL PROBLEMS. SUSPECT CAUSED BY AILERON CONTROL SYSTEM RIGGING. PROBLEM WAS FOUND TO BE AN INHERENT CHA	RACTERISTIC OF THIS SERIES AIRCRAFT.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003042300026	20030423	00026	EU  	2003	4	23	AUS20030243      	1	20030303	G	5347	DAN1521	FITTING         			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					SEAT/CARGO ATTAC	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NUMEROUS TIEDOWN FITTINGS LOCATED BETWEEN FRAME 24 AND FRAME 35 CONTAINED LEVEL 2 CORROSION. FOUND DURING INSPECTI	ON IAW MRBR 53-21-80.					2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2003042300004	20030423	00004	EU  	2003	4	23	AUS20030253      	1	20030303	G	5415	D5725018320000	SLEEVE          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					RT PYLON	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT PYLON SPIGOT BEARING SLEEVE PITTED AND CORRODED ON INSIDE SURFACE. FOUND DURING INSPECTION IAW J9-IA57-0824(2).						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003042300005	20030423	00005	EU  	2003	4	23	AUS20030254      	1	20030225	G	7160	1156602	FLAPPER VALVE   			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENG AIR INTAKE	SEPARATED       	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 										(AUS) CARBURETOR AIR BOX FLAPPER VALVE SEPARATED FROM SPINDLE SHAFTDUE TO WEAR.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2003042300003	20030423	00003		2003	4	23	AUS20030261      	4	20030207	G	3414	415062	INDICATOR       			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	AIRSPEED	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AIR SPEED INDICATOR (ASI) LIMITS INCORRECTLY MARKED.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2003041400077	20030414	00077	CE  	2003	4	14	AUS20030262      	1	20030224	G	3260	S13771	DOWNLOCK SWITCH 			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MLG	STICKING        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK SWITCH STUCK. RT LANDING GEAR COLLAPSED ON LANDING.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2003042900131	20030429	00131	CE  	2003	4	29	AUS20030264      	1	20030303	G	2750	14601007	CONTROL CABLE   			CESSNA	337   	337A        	2075704	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP CONTROL CABLES PN 14601007 AND PNO 14601008 CORRODED AND FRAYED.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2003042300009	20030423	00009	CE  	2003	4	23	AUS20030265      	1	20030205	G	7931	13P2002	INDICATOR       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	ENG OIL PRESSURE	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL PRESSURE GAUGE LIMITS INCORRECTLY MARKED.PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2003042300014	20030423	00014	NM  	2003	4	23	AUS20030267      	1	20030108	G	5730		SKIN            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					CENTER WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTER SECTION UPPER SKIN CONTAINED LEVEL 2 CORROSION AT SECTION 46 STN 825 RBL 13. FOUND DURING INSPECTION I	AW CPCP C53-224-05.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003042300016	20030423	00016	NE  	2003	4	23	AUS20030277      	2	20030224	G	8530	71167	EXHAUST VALVE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1        	52016	NE  	HAMSTD	23D	23D40       	NE  	ENGINE	SEPARATED       	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			921  							(AUS) ENGINE EXHAUST VALVE FAILED. VALVE HEAD SEPARATED FROM VALVE STEM CAUSING DAMAGE TO CYLINDER.						1	H	7	1 	3R	3	R	 	A815    	E143	6	C	P719	 
2003042300015	20030423	00015	NM  	2003	4	23	AUS20030292      	1	20030212	G	5320		BRACKET         			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ANGLE BRACKET LOCATED AT CARGO FLOOR LEVEL BS 720D BL 21L CONTAINED LEVEL 2 CORROSION. FOUND DURING CPCP INSPECTIO	N IAW C53-113-01.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003042900142	20030429	00142	NM  	2003	4	29	AUS20030300      	1	20030212	G	5311		FRAME           			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME LOCATED AT BS 950B BETWEEN STRINGER 27R AND STRINGER 28R CONTAINED LEVEL 2 CORROSION ON THE LOWER F	LANGE. FOUND DURING CPCP INSPECTION IAW C53-113-01.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003042300024	20030423	00024	NM  	2003	4	23	AUS20030304      	1	20030102	G	5720		STIFFENER       			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD SPAR LEADING EDGE VERTICAL STIFFENER CONTAINED LEVEL 2CORROSION LOCATED AT STN236. FOUND DURING CPCP INSPE	CTION IAW C57-562-02.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003042300031	20030423	00031	NE  	2003	4	23	AUS20030312      	2	20030227	G	7260		DRIVE SHAFT     			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE TOWER DRIVE SHAFT FAILED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003042300032	20030423	00032	CE  	2003	4	23	AUS20030313      	1	20030310	G	5521	043200121	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR SPAR CRACKED AROUND UPPER RIVET HOLE FOR HINGE BRACKET ATTACHMENT. CRACK LENGTH 30.04MM (1.183IN). CRACK 	TRAVELS INBOARD AND OUTBOARD FROM RIVET HOLE.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003050700002	20030507	00002	CE  	2003	5	7	AUS20030314      	1	20030311	G	5521	043200121	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ELEVATOR CORRODED IN AREA OF TORQUE TUBE. CAUSED BY LACK OF PRIMER DURING ASSEMBLY. INSPECTION ALSO FOUND RACKS	 FOUND EMANATING FROM UPPER AND LOWER RIVET HOLES EXTENDING TOWARDS INBOARD END OF ELEVATOR SPAR AND OUTBOARD END. UPPER	 RIVET CRACK18.9MM (0.745IN) LONG. LOWER RIVET CRACK 15.8MM (0.625IN) LONG. A CRACK WAS ALSO FOUND IN CIRCUMFERENCE OF H	OLE IN THE SPAR THAT THE ELEVATOR TRIM TAB ACTUATOR ROD PASSES THROUGH.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003050700005	20030507	00005	GL  	2003	5	7	AUS20030319      	3	20030301	G	6114	C84060	HUB             			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1873 							(AUS) PROPELLER HUB CONTAINED A RADIAL CRACK IN THE OUTBOARD END OF THE NR 1 HUB ARM AT THE HUB/PILOT TUBE JOINT. CRACK 	WAS CONFIRMEDUSING MAGNETIC PARTICLE INSPECTION (MPI). CRACK LENGTH APPROXIMATELY 25.4MM (1IN). FOUND DURING DISASSEMBLY	 AND INSPECTION FOLLOWING LIGHTNING STRIKE ON NR 3 BLADE. THE PILOT TUBE PLUGS WERE REMOVED AND NR 1 AND NR 2 HUB ARMS W	ERE FOUND TO CONTAIN APPROXIMATELY 10ML WATER IN EACH (ALONG WITH CORROSION PREVENTATIVE COMPOUND).			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003050700006	20030507	00006	EA  	2003	5	7	AUS20030320      	1	20030207	G	5753		HINGE           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEVEL 1 CORROSION WAS FOUND ON EXTERNAL SURFACES IN VARIOUS LOCATIONS. LEVEL 2 CORROSION WAS FOUND ON FLAP HINGE A	RMS,VERTICAL AND HORIZONTAL FORWARD ATTACHMENT FITTINGS. FOUND DURING INSPECTION IAW AD/DHC-6/69, LEVEL 1 AND LEVEL 2 CO	RROSION WAS FOUND AS OUTLINED IN PSM 1-GEN-5.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003050700016	20030507	00016	CE  	2003	5	7	AUS20030322      	1	20030314	G	3230	124166345	HOOK            			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	MLG DOWNLOCK	CONTAMINATED    	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK HOOK CONTAMINATED WITH DIRT WHICH PREVENTED CORRECT SEATING OF THE HOOK AND ACTIVATI	ON OF THE MICROSWITCH.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P3EA9	 
2003050700027	20030507	00027	NM  	2003	5	7	AUS20030330      	1	20030313	G	7830		STRIP           			BOEING	767   	767338      	1385151	NM  	RROYCE	RB211 	RB211524*   	 	NE  					THRUST REVERSER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT THRUST REVERSER BULLNOSE STRIP MISSING. THRUST REVERSER METALSEAL STRIP DAMAGED. DAMAGE TO NR 4 AND 9 BLOCKER D	OORS AND NR 4, 5, 6 AND 7 CASCADES.					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2003050700032	20030507	00032	EU  	2003	5	7	AUS20030336      	1	20030320	G	5311	D53113405200	FRAME           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD FRAME 1 CONTAINED LEVEL 2 CORROSION INAREA AROUND UPPER RIGHT HAND LOCATING CLIP, LEFT H	AND LOWER LOCATING CLIP AND RIGHT HAND LOWER LOCATING CLIP.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003050700034	20030507	00034	EU  	2003	5	7	AUS20030338      	1	20030321	G	5313	42L	STRINGER        			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD FUSELAGE STRINGER 44 AND STRINGER 42L LOCATED BETWEEN FRAME 28 AND FRAME 29CONTAINED LEVEL 2 CORROSION ARO	UND RIVET TAILS.					2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2003050700042	20030507	00042		2003	5	7	AUS20030341      	4	20030314	G	3442	071131900	SENSOR          	BENDIX      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	WEATHER RADAR SY	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 					3481					(AUS) WEATHER RADAR SENSOR FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003050700044	20030507	00044	CE  	2003	5	7	AUS20030343      	1	20030321	G	1430	654811	BOLT            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONNECTING ROD BOLTS CONTAINED PITTING ON GROUND SURFACES. BOLTSWERE NEW ITEMS FOR FITMENT FOLLOWING STRIP AND INS	PECTION FOR PROPELLER STRIKE.					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2003050700046	20030507	00046	SO  	2003	5	7	AUS20030345      	2	20030307	G	8520	630826	BEARING         			CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			500  							(AUS) CONNECTING ROD BIG END BEARING WORN EXCESSIVELY.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2003050700047	20030507	00047	CE  	2003	5	7	AUS20030346      	1	20030202	G	5312		BULKHEAD        			CESSNA	207   	207A        	2073604	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOORPOST BULKHEAD CRACKED AS INDICATED IN AD/C207/32.2.						1	H	7	1 	3O			 	A16CE   					 
2003050700048	20030507	00048	SO  	2003	5	7	AUS20030347      	1	20030314	G	3210	967615	LANDING GEAR    			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAINS	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT MAIN LANDING GEAR CORRODED (RUSTY).						1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2003050700049	20030507	00049	CE  	2003	5	7	AUS20030348      	1	20030319	G	7120	04135731	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE MOUNT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER LH ENGINE MOUNT BRACKET RIVETS SHEARED. SUSPECT CAUSED BY UNREPORTED HEAVY LANDING.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003050700051	20030507	00051	CE  	2003	5	7	AUS20030350      	1	20030317	G	3230		DOWNLOCK        			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RT MLG	OUT OF ADJUST   	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR FAILED TO EXTEND CORRECTLY. INVESTIGATION FOUND THE RT MAIN LANDING GEAR SWITCH AND DOWNLOCK OUT OF A	DJUSTMENT. LANDING GEAR CIRCUIT BREAKER CONTAINED A HAIRLINE CRACK.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2003050700054	20030507	00054	CE  	2003	5	7	AUS20030353      	1	20030317	G	2436	C6110010101	VOLT REGULATOR  			CESSNA	185   	185A        	2072804	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	DC SYSTEM	UNSERVICEABLE   	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) VOLTAGE REGULATOR FAULTY. VIBRATING CONTACTS WELDED CLOSED CAUSING OVER VOLTAGE WHICH DAMAGED SOME AVIONICS EQUIPM	ENT.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P25EA	 
2003050700061	20030507	00061	CE  	2003	5	7	AUS20030360      	1	20030305	G	3233	12801204	ACTUATOR        			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR DOWNLOCK ACTUATOR FAULTY. SUSPECT LEAKING INTERNALLY AS REPLACEMENT OF SEALS FIXED PROBLEM.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2003050700074	20030507	00074	CE  	2003	5	7	AUS20030366      	1	20030325	G	1430		RIVET           			CESSNA	182   	182P        	2075816	CE  										RT WING SPAR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT CONTAINED NUMEROUS DEFECTS. FOUND WHEN NEW OWNER TOOK DELIVERY. PERIODIC INSPECTION HAD BEEN CARRIED OUT 	SIX WEEKS (13HOURS) PREVIOUSLY. DEFECTS FOUND WERE: MISSING RIVETS ON THE RT WING MAIN SPAR DUE TO CORROSION. PROPELLER 	HAD 97 HTR NOT 597 AS REPORTED AND ADVISED BY PREVIOUS MRO. FIXED ELT HAD EXPIRED - NO MENTION ON CURRENT MAINTENANCE RE	LEASE.  TWO SMALL HOLES IN THE LT FUSELAGE SKIN NEAR BATTERY BOX, POSSIBLY DUE TO ELECTRICAL CONTACT. RT FUEL CAP SEALS 	UNSERVICEABLE AND CAP NOT ATTACHED TO AIRCRAFT. LT AND RT LANDING GEAR LEG FAIRINGS LOOSE ON AIRCRAFT.  THROTTLE CABLE A	TTACHMENT CLAMP MODIFIED WITH NO SUPPORTING APPROVAL DOCUMENTATION FOUND.	1	H	7	1 	3O			NT	TA13    					 
2003050700080	20030507	00080	SO  	2003	5	7	AUS20030367      	1	20030325	G	3230	7642603	LINK            			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG LINK ASSEMBLY SHEARED IN AREA LOCATEDFORWARD OF THE RH ATTACHMENT POINT.						1	L	7	1 	3O	3	O	 	2A13    	E9CE	5	C	P920	 
2003050700082	20030507	00082	EU  	2003	5	7	AUS20030370      	1	20030327	G	5753	D5755103020000	FLAP TRACK      			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING NR 4 FLAP TRACK AFT SPIGOT AND BUSH CONTAINED LEVEL 2 CORROSION. FOUND DURING INSPECTION IAW J9-IA57-0408.						2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2003050700083	20030507	00083	SO  	2003	5	7	AUS20030371      	1	20030226	G	5500	9587100	SPAR CAP        			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	STABILATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH STABILATOR LOWER SPAR CAP CORRODED.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2003050700085	20030507	00085	EA  	2003	5	7	AUS20030373      	2	20030317	G	8500	TIO540J2BD	ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  		MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL FILTER CONTAMINATED WITH SMALL BRIGHT NON-FERROUSMETAL FLAKES.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003050700087	20030507	00087	CE  	2003	5	7	AUS20030375      	1	20030312	G	5540	07606041	BAR             			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER BAR CRACKED AT BASE OF RUDDER PEDAL POST.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003050700096	20030507	00096		2003	5	7	AUS20030379      	4	20030328	G	3442	7008470912	TRANSCEIVER     			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					WEATHER RADAR	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 			10415							(AUS) WEATHER RADAR TRANSCEIVER FAILED.						2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2003050700100	20030507	00100	CE  	2003	5	7	AUS20030383      	1	20030327	G	2710		PIN             			CESSNA	172   	172N        	2072434	CE  										AILERON CONTROL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AILERON CHAIN CLEVIS BOLT SPLIT PINS MISSING AND TOP NUT LOOSE. THE AIRCRAFT HAD ONLY FLOWN FOR TWO HOURS SINCE	 THE LAST ANNUAL INSPECTION.					1	H	7	1 	3O			NT	3A12    					 
2003050700111	20030507	00111	EU  	2003	5	7	AUS20030387      	2	20030326	G	7320	737M28500011	VALVE           			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					RT ENGINE	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					571					(AUS) RT ENGINE SPAR VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003050700128	20030507	00128	SO  	2003	5	7	AUS20030395      	2	20030304	G	7314	6462121	PUMP            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE FUEL	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE DRIVEN FUEL PUMP FAULTY.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2003050700143	20030507	00143	SO  	2003	5	7	AUS20030401      	1	20030331	G	2434		ALTERNATOR      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  	AMTR	C8289	C8289       	GL  	ENGINE	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) ALTERNATOR FAILED. COMPLETE LOSS OF ELECTRICAL POWER.						1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	EXPP5N	 
2003050700144	20030507	00144	CE  	2003	5	7	AUS20030402      	1	20030402	G	3245	40135	TUBE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	TIRE	DAMAGED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LT MAIN WHEEL TIRE DEFLATED DUE TO PINCHED TUBE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003050900091	20030509	00091	EU  	2003	5	9	AUS20030403      	1	20030406	G	3610	W901B24DE	CLAMP           			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	PNEUMATIC SYS	CORRODED        	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) NR 1 ENGINE SHUT DOWN FOLLOWING LT WING OVERHEAT WARNING.INVESTIGATION FOUND THE CLAMP ATTACHED TO THE PNEUMATIC F	LOWCONTROL VALVE DOWNSTREAM FROM THE NO1 ENGINE BLEED PORT CORRODEDAND RUPTURED CAUSING EXCESSIVE AIR LEAKS.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2003050900092	20030509	00092	EA  	2003	5	9	AUS20030404      	2	20030408	G	8530	SL54002NLC	CYLINDER        								LYC   	O540  	TIO540A2B   	41532	EA  					ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CYLINDER ASSY INLET VALVE SPRING RETAINER INCORRECT PART. EXHAUST VALVE SPRING RETAINER FITTED. SIX NEW CYLINDERS 	WERESUPPLIED&IT FOUND THAT NOT ONLY DID PREVMENTIONED CYLINDER HAVE WRONG SPRING RETAINER FITTED BUT ALLCYLINDERS HAD AN	 AMOUNT OF ALUMINIUM SWARF IN THE ROCKER BOX AREA WHICH RESULTED IN HAVING TO REMOVE ALL SPRINGS&VALVES FROMCYLINDERS TO	 WASH THEM OUT. ONCE SPRINGS WERE REMVD ITFOUND THAT INCORRECT INLET LOWER SPRING SEATS HAD BEEN FITTED TO ALL CYLINDERS	 (EXHAUST LOWER SPRING SEATS HAD BEEN FITTEDINSTEAD). ON FURTHER INSPECTION IT FOUND ON ONE CYLINDER THAT THERE WAS RAIS	ED BURRS AROUND CYLINDER BASE STUD HOLES. THEREFORE BEING NARROW DECK CYLINDERS THEY HAVE HOLD DOWN PLATES FITTED.WHEN A						3	O			E14EA				 
2003050900093	20030509	00093	EU  	2003	5	9	AUS20030405      	2	20030404	G	7321		FUEL CONTROL    			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ENGINE	FAULTY          	W				O				OTHER                   				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) NR 2 ENGINE POWER MANAGEMENT CONTROL (PMC) FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003051500163	20030515	00163	EU  	2003	5	15	AUS20030407      	1	20030405	G	5610	D20543405	WINDSHIELD      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LT WINDSHIELD CRACKED. SUSPECT CAUSED BY MOISTURE INGRESS.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2003060200046	20030602	00046	SO  	2003	6	2	AUS20030412      	1	20030403	G	5711	62054	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  	AMTR	C8289	C8289       	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING REAR SPAR HEAVILY CORRODED UNDER THE REAR SPAR ATTACHMENT PLATE.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	EXPP5N	 
2003060200048	20030602	00048	EA  	2003	6	2	AUS20030414      	2	20030314	G	8520	SL74309M03	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2050 							(AUS) NR 5 CONNECTING ROD BEARING DELAMINATED. AREA OF DELAMINATION APPROXIMATELY 8MM BY 2MM (0.314IN BY 0.078IN).						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003060200055	20030602	00055	CE  	2003	6	2	AUS20030416      	1	20030410	G	2823	C2915030101	SELECTOR        			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUEL SYSTEM	WRONG PART      	W				O				OTHER                   				W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		CR	CRUISE         	1			AU	S 			5    							(AUS) FUEL SELECTOR FAULTY. INVESTIGATION FOUND THAT THE SELECTOR HAD BEEN INCORRECTLY ASSEMBLED DURING OVERHAUL 5 HOURS	 PREVIOUSLY.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2003060200071	20030602	00071	EA  	2003	6	2	AUS20030418      	2	20030401	G	8520	LW12696	CRANKCASE       			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CRANKCASE CRACKED BEYOND REPAIR AT LH CENTRE CAM JOURNAL BEARINGBASE. CRACK RUNS ACROSS THE JOURNAL SURFACE AND TH	EN DOWN FOR APPROXIMATELY 76.2MM (3IN) BEFORE TRAVELLING FOR ANOTHER 76.2MM (3IN) REARWARDS. SUMP INDUCTION TUBES LOOSE.	 THREE CYLINDERS CRACKED. SUSPECT SB/530A NOT CARRIED OUT ON CRANKSHAFT. INSIDEDIAMETER OF CRANKSHAFT CORRODED BEYOND LI	MITS.			1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL	 
2003060200072	20030602	00072	CE  	2003	6	2	AUS20030419      	1	20030411	G	7603	S122210A	CONTROL CABLE   			CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	POWER LEVER	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) THROTTLE CABLE OUTER GUIDE SEPARATED FROM SWAGED SWIVEL JOINT ALLOWING CABLE TO FAIL IN COMPRESSION.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2003060200074	20030602	00074	EU  	2003	6	2	AUS20030421      	2	20030413	G	7250		BLADE           			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TURBINE SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE HIGH PRESSURE TURBINE BLADES DAMAGED. ONE BLADE HAD MATERIAL MISSING AND TWO BLADES HAD IMPACT CRACKIN	G. FOUND DURING BOROSCOPE INSPECTION.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003060200077	20030602	00077	NM  	2003	6	2	AUS20030424      	1	20030416	G	2740		TRIM PANEL      			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					STABILIZER	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) STABILISER TRIM SYSTEM FAULTY. HORIZONTAL STABILISER MAIN TRIMACTUATOR AND HORIZONTAL STABILISER TRIM RELAY R64 RE	PLACED.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003060500013	20030605	00013	EU  	2003	6	5	AUS20030438      	1	20030421	G	4930	P93A19203	PUMP            			AIRBUS	330   	A330202     	3930316	EU  	GE    	CF6   	CF680       	30025	NE  					APU FUEL	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) APU FUEL PUMP FAILED. AFT PUMP HAD THE COVER BLOWN OFF AND FUEL IN THE ELECTRICAL WINDINGS.						2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2003060500015	20030605	00015	CE  	2003	6	5	AUS20030441      	1	20030416	G	7713		HOSE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	MANIFOLD PRESS	CRACKED         	W				O				OTHER                   				E	I		VIBRATION/BUFFET          	FLT. ATTITUDE INST.       		DE	DESCENT        	1			AU	S 										(AUS) MANIFOLD PRESSURE GAUGE HOSE CRACKED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003070700003	20030707	00003	NE  	2003	7	7	AUS20030443      	2	20030403	G	7310	430137601	MANIFOLD        			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					FUEL DIST	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE FUEL MANIFOLD LEAKING DUE TO CRACKING AT THE SOLID TUBE/RAIL LOCATED AT THE 4 O'CLOCK POSITION.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2003070700004	20030707	00004	NE  	2003	7	7	AUS20030444      	2	20030403	G	7310	430128602	MANIFOLD        			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					FUEL DIST	FAULTY          	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE REPLACEMENT FUEL MANIFOLD FAULTY. SUSPECT FLOW DIVIDER PROBLEM. MANIFOLD WAS FITTED TO REPLACE A CRACK	ED AND LEAKING MANIFOLD. SEE MDR 03/0443 FOR DEFECT.					1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2003070700005	20030707	00005	CE  	2003	7	7	AUS20030445      	1	20030414	G	7331	C6620200118	INDICATOR       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	FUEL FLOW	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE FUEL FLOW INDICATOR FAULTY.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003070700006	20030707	00006	SO  	2003	7	7	AUS20030446      	2	20030410	G	8520	646438	CRANKSHAFT      			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520B    	17040	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) CRANKSHAFT CRACKED RADIALLY IN AREA LOCATED BEHIND THE PROPELLER FLANGE. CRACK LENGTH APPROXIMATELY 50.8MM (2IN).						1	L	7	1 	3O	3	O	RT	A25SO   	E8CE	5	C	P920	 
2003070700007	20030707	00007	EA  	2003	7	7	AUS20030447      	2	20030413	G	8530		INTAKE VALVE    			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) INLET VALVE FACE BREAKING UP.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003070700008	20030707	00008	SW  	2003	7	7	AUS20030448      	1	20030425	G	6510	40734033910B	BEARING         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL ROTOR DRIVE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR DRIVESHAFT BEARING WORN AND ROUGH IN OPERATION.BEARING GREASE EXPELLED. GREASE WAS DISCOLORED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070700009	20030707	00009	WP  	2003	7	7	AUS20030449      	1	20030409	G	6720	HS105324	CONTROL CABLE   			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					TAIL ROTOR	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) TAIL ROTOR CONTROL CABLE FAILED. CABLE RUNS FROM RT PEDAL TO FIREWALL LOCATED BEHIND THE PILOT SEAT. CABLE HAD BEE	N SUBJECTEDTO HEAT SOURCE, POSSIBLY CONTACT WITH CIRCUIT BREAKER LOCATED IN CENTER TUNNEL WHEN TENSION WAS RELEASED DURI	NG MAINTENANCE. PERSONNEL/MAINTENANCE ERROR.				1	G	7	1 	3O	3	O	 	4H11    	E304				 
2003070700010	20030707	00010	EU  	2003	7	7	AUS20030450      	1	20030409	G	5713	KB574601	STRINGER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					RT CENTER WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5950 							(AUS) RT CENTER WING STRINGER CONNECTING ANGLE LOCATED AT ZONE 138 STA 16511 CONTAINED EXFOLIATION CORROSION.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2003070700014	20030707	00014	EU  	2003	7	7	AUS20030451      	2	20030420	G	7200		ENGINE          			BOEING	737   	7373Q8      	1384670	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					NR 1	VIBRATES        	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		DE	DESCENT        	1			AU	S 										(AUS) NR 1 ENGINE SURGED AND SEVERAL LOUD BANGS WERE HEARD. MAXIMUM VIBRATION RECORDED ON VIBRATION INDICATOR.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003070700016	20030707	00016	NM  	2003	7	7	AUS20030453      	1	20030430	G	3610	97918011	VALVE           			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D439	54555	NE  					PNEUMATIC SYS	FAULTY          	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) STRUT OVERHEAT WARNING. HIGH STAGE VALVES AND PYLON VALVES REPLACED. LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2003070700017	20030707	00017	CE  	2003	7	7	AUS20030454      	1	20030324	G	7921	636900RC	OIL COOLER      			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE OIL COOLER CRACKED IN AREA NEAR OIL PRESSURE MOUNTHOLE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003070700018	20030707	00018	CE  	2003	7	7	AUS20030455      	1	20030428	G	3710	216CW	PUMP            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	VACUUM SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			300  		15171					(AUS) RT ENGINE DRIVEN VACUUM PUMP FAILED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003070700019	20030707	00019	GL  	2003	7	7	AUS20030456      	1	20030419	G	3246	AN364428	NUT             			AMTR  	VANS  	RV8         	       	GL  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MLG WHEEL	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR AXLE BOLT NUT FAILED. NOSEWHEEL SEPARATED FROM AIRCRAFT.						1	L	7	1 	3O	3	O	NT	EXPA1L71	1E10	5	C	P920	 
2003070700020	20030707	00020	EU  	2003	7	7	AUS20030457      	1	20030422	G	3233		SWITCH          			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	ACTUATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			109  							(AUS) NOSE LANDING GEAR ACTUATOR FAULTY. SWITCH OUT OF ADJUSTMENT.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2003070700022	20030707	00022	EA  	2003	7	7	AUS20030459      	2	20030422	G	8520	LW13923	BUSHING         			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NR 4 CYLINDER	FAILED          	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 			582  							(AUS) NR 4 CYLINDER CONNECTING ROD FAILED.  ENGINE SEVERELY DAMAGED.  METAL CONTAMINATION OF OIL SYSTEM.   INVESTIGATION	 FOUND CONNECTING ROD LITTLE END BUSH FAILED. ALL OTHER LITTLE END BUSHES EXHIBITED SIGNS OF CRACKING AND UNUSUAL WEAR P	ATTERNS.				1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920	 
2003070700023	20030707	00023	CE  	2003	7	7	AUS20030460      	1	20030427	G	3230		BOLT            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR UPPER DRAG BRACE BENT AND FORK END OF NOSELANDING GEAR ACTUATOR SPREAD. FURTHER INVESTIGATION AL	SO FOUND THE ACTUATOR UPPER SUPPORT BEARINGS ROUGH AND UNSERVICEABLE.  SUSPECT CAUSED BY SHEARING OF THE CLEVIS BOLT WHI	CH ALLOWED THE ACTUATOR TO SEPARATE FROM THE DRAG BRACE.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003090200006	20030902	00006	NM  	2003	9	2	AUS20030461      	1	20030430	G	6310	A1902	DRIVE BELT      	ROBSIN      		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					CLUTCH MOTOR	DISTORTED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 					5880					(AUS) ENGINE TO TRANSMISSION DRIVE BELTS STRETCHED. CLUTCH MOTOR DAMAGED.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2003090200007	20030902	00007	EU  	2003	9	2	AUS20030463      	1	20030409	G	5315	BL600LBL600RBLO	FLOORBEAM       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD FUSELAGE FLOORBEAMS CONTAINED EXFOLIATION CORROSION IN AREA BELOW THE FORWARD CABIN FLOOR PANELS. CORROSIO	N WAS PRESENT AT SEVERAL FASTENER HOLES ON EACH OF THE FOUR FLOORBEAMS ATBL600L, BL600R AND BL 1127R. SUSPECT CAUSED BY 	GALLEY SPILLAGES.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2003090200008	20030902	00008	NE  	2003	9	2	AUS20030465      	2	20030430	G	7210	3030988	SEAL            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	TURBINE ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE PROPELLER SHAFT SEAL DETERIORATED AND LEAKING.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2003090200009	20030902	00009	NM  	2003	9	2	AUS20030466      	1	20030427	G	3242	21565	BRAKE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 			59   							(AUS) NR 3 MAIN WHEEL BRAKE WOULD NOT RELEASE.  DURING TAXI, THE BRAKE OVERHEATED AND THE THERMAL RELIEF PLUG IN NR 3 MA	IN WHEEL BLEW.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090200010	20030902	00010	NE  	2003	9	2	AUS20030467      	2	20030421	G	7310	3035987	LINE            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			11481							(AUS) ENGINE FUEL LINE CHAFED IN AREA OF FIREWALL SEAL.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003061700001	20030617	00001	NM  	2003	6	17	AUS20030468      	1	20030420	G	2841		INDICATOR       			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL QTY	FALSE INDICATION	W				O				OTHER                   				K	N		FLUID LOSS                	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) NR 1 FUEL GAUGE INDICATING FUEL LEAK. INSPECTION COULD FIND NO EVIDENCE OF LEAKS.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003061700002	20030617	00002	SW  	2003	6	17	AUS20030469      	1	20030501	G	3230		DRAG LINK       			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	WORN            	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			AU	S 			15490							(AUS) RT MAIN LANDING GEAR SLOW TO OPERATE. SUSPECT CAUSED BY A COMBINATION OF DOOR RIGGING AND DRAG LINK WEAR.  THE DOO	R RIGGING WAS CLOSELY EXAMINED AND THE INBOARD DOOR ADJUSTMENT WAS CONSIDERED TO BE A BIT TIGHT. THE INBOARD DOOR WAS AD	JUSTED. THE EMERGENCY EXTENSION ACTUATOR WAS REPLACED AND MINOR ADJUSTMENTS MADE TO THE RIGGING.  THE DRAG BRACE LOWER L	INK INBOARD UPPER BUSH FOUND TO BE SLIGHTLY OFF CENTER AND WAS ADJUSTED TO BE CENTRALIZED.  THE UPPER OUTBOARD DRAG LINK	 BUSHING WAS FOUND FLOATING IN THE CASTING AND WAS SECURED.  THE RT LANDING GEAR, GEAR UP AND GEAR DOWN HYDRAULIC LINES 	WERE THEN FLUSHED CLEAN.  FUNCTIONAL CHECKS WERE CARRIED OUT WITHOUT FAULT.	2	L	7	2 	4T	3	T	RT	A5SW    	E2WE	6	C	3PNE	 
2003061700003	20030617	00003	SW  	2003	6	17	AUS20030470      	1	20030502	G	5313	108771	LONGERON        			AIRTRC	AT500 	AT502       	0390303	SW  	PWA   	PT6   	PT6A15AG    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE LONGERON CRACKED IN AREA INDICATED IN SL195.						1	L	7	1 	3T	4	T	NC	A9SW    	E4EA	6	C	P15EA	 
2003061700004	20030617	00004	NM  	2003	6	17	AUS20030471      	1	20030502	G	5270	835109	CIRCUIT CARD    			BOEING	767   	767338      	1385151	NM  	RROYCE	RB211 	RB211524*   	 	NE  					DOOR WARNING SYS	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) CARGO DOOR WARNING. INVESTIGATION FOUND CARD 007 FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2003061700006	20030617	00006	SO  	2003	6	17	AUS20030473      	1	20030502	G	3221	67054003	TRUNNION        			PIPER 	PA28  	PA28R200    	7102811	SO  	CONT  	IO360 	IO360*      	17025	CE  	HARTZL	HCC2Y	HCC2YK1     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR UPPER TRUNNION CRACKED AT DRAG BRACE ATTACHMENT POINT. SUSPECT CAUSED BY EXCEEDING TURNING LIMIT	S DURING GROUND HANDLING.					1	L	7	1 	3O	3	O	 	2A13    	E1CE	5	C	P920	 
2003061700015	20030617	00015	CE  	2003	6	17	AUS20030479      	1	20030309	G	2750	14601007	CONTROL CABLE   			CESSNA	337   	M337B       	2075708	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2AF34C	D2AF34C59   	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH TRAILING EDGE FLAP CONTROL CABLE CONTAINED BROKEN STRANDS IN AREA APPROXIMATELY 25.4MM (1IN) FROM SWAGE AT BELL	CRANK END.					1	H	7	2 	3O	3	O	RT	A6CE    	E1CE	5	C	P5EA	 
2003061700017	20030617	00017	SO  	2003	6	17	AUS20030481      	1	20030507	G	7922	SL53E19600	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENG OIL TEMP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL SYSTEM THERMOSTATIC OIL COOLER BYPASS VALVE SHAFT NUTLOCK PIN SHEARED. NUT SEPARATED FROM SHAFT AND WAS	 FOUND IN THE OIL COOLER FLEX LINE. MAIN BODY CIRCLIP GROOVE SHOULDER FAILED FOR APPROXIMATELY 25 PERCENT OF CONTACT ARE	A.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003061700033	20030617	00033	CE  	2003	6	17	AUS20030485      	1	20030426	G	3246	AN515A	BOLT            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	WHEEL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1090 							(AUS) MAIN WHEEL BRAKE DISC RETAINING BOLTS (3OFF) MISSING AND FIVE BOLTS LOOSE.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2003061700034	20030617	00034	NM  	2003	6	17	AUS20030486      	1	20030430	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/XMSN	STRETCHED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE BELTS STRETCHED BEYOND LIMITS.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003061700041	20030617	00041	EU  	2003	6	17	AUS20030494      	1	20030206	G	5315		FLOORBEAM       			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLOORBEAMS CONTAINED LEVEL 2 CORROSION BETWEEN FR 64 AND FR 69.THE FOLLOWING FLOORBEAMS WERE AFFECTED:- 1) FLOORBE	AM (PN D5347217220390) FROM FR66 TO FR68 RT IN TWO AREAS AT Y1292.0 RT 2) FLOORBEAM (PN D5347218920200) ON AFT OF FR69 A	T Y1162.5 RT.				2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2003061700083	20030617	00083	NM  	2003	6	17	AUS20030501      	1	20030509	G	5270	S15	SWITCH          			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					DOOR WARNING SYS	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) MAIN CARGO DOOR AFT AUXILIARY LATCH SWITCH OUT OFADJUSTMENT.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003061700084	20030617	00084	GL  	2003	6	17	AUS20030502      	3	20030122	G	6111	106GA0	BLADE           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	DAMAGED         	W				O				OTHER                   				C			F.O.D.                    			LD	LANDING        	1			AU	S 			1913 							(AUS) PROPELLER NR 3 BLADE CONTAINED STONE DAMAGE AT THE 50 INCH STATION. BLADE LEADING EDGE CONTAINED A 6.350MM TO 12.7	MM (0.25IN TO 0.5IN) TEAR. DAMAGE EXCEEDED REPAIRABLE LIMITS.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003061700085	20030617	00085	NE  	2003	6	17	AUS20030503      	2	20030205	G	7321	32448973	FUEL CONTROL    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	FAULTY          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			1072 							(AUS) ENGINE POWER FLUCTUATIONS. SUSPECT FAULTY FCU.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003061700086	20030617	00086	GL  	2003	6	17	AUS20030504      	3	20030328	G	6111	931836	BLADE           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER BLADES (2OFF) CONTAINED DEEP SCORING ON THE CAMBER SIDE LOCATED APPROXIMATELY 76.2MM TO 127MM (3IN TO 5I	N) FROM THE TIP.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003061700088	20030617	00088	CE  	2003	6	17	AUS20030505      	1	20030327	G	2150	26012672	DRIVE SHAFT     			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	CABIN COOLING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			902  							(AUS) AIR CONDITIONING DRIVE UNIT DRIVESHAFT SPLINE WORN. OIL LEAK.CORRESPONDING SPLINE IN THE GEAROX SHAFT GEAR PNO 310	0450-01 ALSO WORN. SUSPECT CAUSED BY LACK OF LUBRICATION.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003061700089	20030617	00089	CE  	2003	6	17	AUS20030506      	1	20030108	G	2150	MRC206SZZC	BEARING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	CABIN COOLING SY	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCONDITIONING DRIVE UNIT BEARING FAILED CAUSING DRIVE BELT TO FAIL.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003061700091	20030617	00091	GL  	2003	6	17	AUS20030508      	3	20030513	G	6114	D5904C90	HUB             			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			898  							(AUS) PROPELLER HUB CRACKED IN NR 1 BLADE SOCKET.   FOUND DURING INSPECTION IAW AD/PMC/41.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003061700092	20030617	00092	NE  	2003	6	17	AUS20030509      	2	20030514	G	7320	P1018	FILTER          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) P3 FILTER FAULTY. FILTER END CAPS SEPARATED FROM FILTER ELEMENT.  SUSPECT PROBLEMS WITH GLUE USED TO HOLD END CAPS	 ON.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003061700093	20030617	00093	SO  	2003	6	17	AUS20030510      	2	20030515	G	8550	6547201	DRIVE SHAFT     			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360E   	17025	SO  	MCAULY	3AF34C	3AF34C503   	GL  	ENG OIL PUMP	FAILED          	W				O				OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			AU	S 			1066 							(AUS) ENGINE OIL PUMP DRIVESHAFT FAILED.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2003062500140	20030625	00140	EA  	2003	6	25	AUS20030513      	2	20030327	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ENGINE	CONTAMINATED    	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			AU	S 			586  							(AUS) FUEL CONTROL UNIT AIR CHAMBER CONTAMINATED WITH FUEL.  CAUSED BY OVERPRIMING.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003062500141	20030625	00141	WP  	2003	6	25	AUS20030514      	1	20030515	G	5341	2430572R	SPACER          			FLTCHR	24    	FU24AAIRPTS 	3530204	WP  	LYC   	O720  	IO720A1B    	41546	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	WING TO BODY	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING TO FUSELAGE RT SPACER FRACTURED.						1	L	7	1 	3O	3	O	 	4A12    	1E15	5	C	P25EA	 
2003062500142	20030625	00142	NM  	2003	6	25	AUS20030516      	1	20030515	G	3213	65B051308	AXLE            			BOEING	747   	747400      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING MAIN LANDING GEAR,  LT FRONT AXLE SHEARED AT BOGIE.						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2003070200061	20030702	00061	GL  	2003	7	2	AUS20030517      	3	20030519	G	6114	C58	HUB             			CESSNA	188   	A188B       	2073005	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CRACKED IN BLADE SOCKET THREADED AREA.						1	L	7	1 	3O	3	O	 	A9CE    	E5CE	5	C	P3EA	 
2003070200066	20030702	00066		2003	7	2	AUS20030518      	4	20030518	G	2310		RADIO           			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					HF COMMS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) DUAL HF SYSTEM FAILURE. ON ARRIVAL IT WAS REPORTED THAT NR 1 HF SYSTEM WANDERS OFF FREQUENCY AND BECOMES GARBLED. 	 NR 2 HF WOULD NOT TUNE TO THE FREQUENCY SELECTED. THE NR 1 SYSTEM WAS RE-RACKED AND OPERATED NORMALLY. THE NR 2 SYSTEM 	TRANSCEIVER AND COUPLER WERE REPLACED.				2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2003070200067	20030702	00067	NM  	2003	7	2	AUS20030519      	1	20030504	G	7830	D40672P	CONNECTOR       			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					THRUST REVERSER	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NR 1 ENGINE THRUST REVERSER FAULTY. SUSPECT CAUSED BY FAULTY CONNECTOR D40672P.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003070200068	20030702	00068	NM  	2003	7	2	AUS20030520      	1	20030519	G	4920	2345119059	CLAMP           			BOEING	767   	767277      	1385128	NM  	GE    	CF6   	CF680A      	30025	NE  					APU ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			32823							(AUS) APU FUEL CONTROL UNIT LOOSE ON GEARBOX DUE TO BROKEN CLAMP BOLT.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2003070200069	20030702	00069	WP  	2003	7	2	AUS20030521      	1	20030517	G	5311		FRAME           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME RT CLUSTER CRACKED.						1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2003070200070	20030702	00070	GL  	2003	7	2	AUS20030522      	1	20030512	G	5753	573100105	BRACKET         			EAGLE 	XTS   	EAGLEXTS150 	05607BZ	GL  	CONT  	O240  	IO240A      	 	SO  	MCAULY	1A135	1A135BRM    	GL  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP HINGE SUPPORT BRACKETS (PN 5731001-05 AND PN 5731001-02) CRACKED. RT INNER BRACKET FAILED AND LT INNER BRACKE	T CRACKED.					1	H	7	1 	3I	3	O	NC	A00005LA	E7SO	5	N	P842	 
2003070200071	20030702	00071	NM  	2003	7	2	AUS20030523      	1	20030514	G	6310	A1851	BRACKET         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/XMSN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION LOWER ACTUATOR BEARING MOUNT BRACKET CRACKED ON RH SIDE. CRACK RUNS THROUGH BOLT HOLE AND T	HEN FOR AN EXTRA 12.7MM (0.5IN) TOWARD THE CENTER OF THE BRACKET.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003070200072	20030702	00072	EA  	2003	7	2	AUS20030524      	2	20030429	G	8520	LW13683	BEARING         			NEWZE 	FU24  	FU24954     	6280102	WP  	LYC   	O720  	IO720A1B    	41546	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR MAIN BEARING SURFACE SEPARATED FROM BEARING SHELL.						1	L	7	1 	3O	3	O	 	A9PC    	1E15	5	C	P25EA	 
2003070200073	20030702	00073		2003	7	2	AUS20030525      	4	20030520	G	2310	8220987003	COUPLER         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					HF COMMS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HF SYSTEM UNABLE TO TRANSMIT.  RT HF SYSTEM UNABLE TO RECEIVE.   HF COUPLER FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003070200074	20030702	00074	NM  	2003	7	2	AUS20030526      	1	20030520	G	2822	6098976	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					FUEL BOOST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4654 							(AUS) NR 3 FORWARD BOOST PUMP FAILED RESISTANCE CHECK. FOUND DURING INSPECTION IAW AD/B747/173.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2003070200087	20030702	00087	NE  	2003	7	2	AUS20030527      	1	20030519	G	2913	7655009808102	PUMP            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					HYDRAULIC SYS	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 			248  							(AUS) NR 1 HYDRAULIC SYSTEM PUMP FAULTY. HYDRAULIC FLUID LOST THROUGH PUMP CASE DRAIN.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2003070200088	20030702	00088	NM  	2003	7	2	AUS20030528      	1	20030520	G	2822	6098906	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					FUEL BOOST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 FORWARD BOOST PUMP FAILED RESISTANCE CHECK. FOUND DURING INSPECTION IAW AD/B747/173.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2003070200089	20030702	00089		2003	7	2	AUS20030529      	4	20030509	G	3451	DMC632	ANTENNA         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					DME/TACAN SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HOMING SYSTEM CO-AXIAL CABLES SHORT CIRCUITING TO GROUND.   ANTENNAS OPEN CIRCUITED.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003070200090	20030702	00090	CE  	2003	7	2	AUS20030530      	1	20030520	G	2820	075062413	LINE            			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) STAINLESS STEEL FUEL PIPE LOCATED BETWEEN FUEL FILTER BOWL AND BOWL DRAIN VALVE CRACKED BENEATH (B) NUT FERRULE AT	 DRAIN VALVE END.					1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2003070200091	20030702	00091	SO  	2003	7	2	AUS20030531      	1	20030420	G	5610	1159SCB310212	WINDSHIELD      			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) COPILOTS WINDSHIELD OUTER LAYER SHATTERED.						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003070200092	20030702	00092	CE  	2003	7	2	AUS20030532      	1	20030523	G	2140	AO2060019	SOLENOID        			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2A34C	2A34C*      	GL  	HEATING SYSTEM	FAULTY          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					AO2060019					(AUS) HEATER LEAKING FUEL FROM CASE DRAIN.  INVESTIGATION FOUND THAT THE SOLENOID HAD NOT CLOSED AFTER THE HEATER WAS LA	ST USED.					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P3EA	 
2003070200094	20030702	00094	NM  	2003	7	2	AUS20030534      	1	20030522	G	2612		CONNECTOR       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					DETECTION SYSTEM	DIRTY           	W				E				ENGINE SHUTDOWN         				E	N		VIBRATION/BUFFET          	FALSE WARNING             		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE FIRE DETECTION SYSTEM FAULTY.   SUSPECT CAUSED BY DIRTY CONNECTOR.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003070200095	20030702	00095	EA  	2003	7	2	AUS20030535      	2	20030520	G	8520	LW1563185	CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAGNETO DRIVE GEAR SLEEVES INCORRECT FIT. SLEEVES SHEARED DOWELS AND REVOLVED IN CRANKCASE CAUSING METAL CONTAMINA	TION OF ENGINE OIL.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003070200096	20030702	00096	SO  	2003	7	2	AUS20030536      	1	20030414	G	3397	L430E20	WIRE            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					LIGHTS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) STROBE LIGHT WIRING LOCATED IN TAILCONE SHORTED TO SHIELDING. INVESTIGATION FOUND KAPTON POWER WIRE INSULATION CRA	CKED THROUGH TO INNER WIRES. SUSPECT CRACKING OCCURRED DUE TO LENGTH OF UNSUPPORTED WIRE, CONSTANT REMOVAL OF TAILCONE A	ND PROPERTIES OF KAPTON WIRE.				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003070200097	20030702	00097	NE  	2003	7	2	AUS20030537      	2	20030519	G	7230	CFM567B26	COMPRESSOR      			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ENGINE	CONTAMINATED    	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) FUMES IN COCKPIT.  NR 1 ENGINE FIFTH STAGE BLEED DUCT CONTAMINATED WITH ENGINE OIL.   NINTH STAGE, DUST CONTAINED 	OIL RESIDUE.  BOROSCOPE INSPECTION FOUND OIL STREAKING ON FIRST AND SECOND STAGE HPC BLADES AND STATORS.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003070200106	20030702	00106	NM  	2003	7	2	AUS20030538      	1	20030526	G	2497		WIRE HARNESS    			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					ELECTRICAL POWER	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRING LOOM W8712 LOCATED NEAR NR 1 LT DOOR BURNED AND LIGHTING CIRCUIT BREAKER TRIPPED.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2003070300026	20030703	00026	NM  	2003	7	3	AUS20030539      	1	20030520	G	4990		OIL SYSTEM      			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					APU	FAULTY          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) APU HAS EXCESSIVE OIL CONSUMPTION. SUSPECT AIR/OIL SEPARATOR.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003070300027	20030703	00027	EA  	2003	7	3	AUS20030540      	2	20030509	G	8520	LW13886	MAIN BEARING    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) METAL CONTAMINATION OF ENGINE OIL SYSTEM RESULTED IN BULK STRIP AND INSPECTION OF ENGINE. INSPECTION FOUND LOSS OF	 BEARING MATERIAL FROM THE FRONT MAIN BEARING AND DELAMINATION OF METAL FROM THE OTHER MAIN AND BIG END BEARINGS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003070300028	20030703	00028	SO  	2003	7	3	AUS20030541      	1	20030521	G	5751	62373000	DOUBLER         			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  	AMTR	C8289	C8289       	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			100  							(AUS) RT AILERON OUTBOARD HINGE DOUBLER CRACKED.  FOUND DURING INSPECTION IAW AD/PA28/16A2.						1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	EXPP5N	 
2003070300029	20030703	00029	CE  	2003	7	3	AUS20030542      	1	20030529	G	5711	0024300139	SPAR            			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CARRY THROUGH ASSEMBLY PNO 002-430013-9 CRACKED ON LOWER FACES OF FORWARD WEB PNO 002-430018-1. CRACKS ARE BE	TWEEN HUCKBOLTS AND JOIN THREE HUCK BOLTS ON EACH SIDE. CRACKS ALSO FOUND IN WEB RADIUS ON BOTH SIDES. CRACKING IS IAW M	FG SB2360 FIGURE 1. FOUND DURING INSPECTION IAW AD/36/37.				1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2003070300030	20030703	00030	EU  	2003	7	3	AUS20030543      	1	20030515	G	2750		COMPUTER        			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TE FLAPS	OUT OF TOLERANCE	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLAP COMPUTER FAULTY AND FLAP CONTROL UNIT RESOLVER OUT OF TOLERANCE.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003071800048	20030718	00048	NM  	2003	7	18	AUS20030545      	1	20030430	G	5340		ATTACH FITTING  			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME CLEATS CRACKED. SMALL CRACK IN CLEAT AT UPPER AFT FASTENER HOLE IN BS707 STRINGER 10L. FOUND DURING	 EDDY CURRENT INSPECTION.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003071800051	20030718	00051	NM  	2003	7	18	AUS20030548      	1	20030518	G	3251	8900115	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG STEERING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			10887							(AUS) NOSE WHEEL STEERING ACTUATOR FAULTY.  ACTUATOR GLAND NUT DISPLACED TO ONE SIDE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003071800052	20030718	00052	EA  	2003	7	18	AUS20030549      	2	20030516	G	7310	630193507	SEPARATOR       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	FUEL DIST	CONTAMINATED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE FUEL VAPOUR SEPARATOR BLOCKED BY PARTICLES OF UNKNOWN TYPE.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2003071800053	20030718	00053	CE  	2003	7	18	AUS20030550      	1	20030515	G	2197	B4050	HEATER          			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	AIR CONDITIONING	MISWIRED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) HEATER INCORRECTLY WIRED.  INVESTIGATION FOUND THAT THE OVERHEAT CUTOUT AND COMBUSTION PRESSURE SWITCH HAD NOT BEE	N WIRED UP.  THIS ALLOWED THE HEATER TO SOURCE FUEL AND IGNITION WITHOUT AIRFLOW AND OVERHEAT PROTECTION.					1	L	7	2 	3O	3	O	 	A29CE   	E286	5	C	P43GL	 
2003071800054	20030718	00054		2003	7	18	AUS20030551      	4	20030522	G	2562	ELT1104	ELT             																	CABIN	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELT UNITS (3 OFF) HAD CONTINUOUS TRANSMISSION IN BOTH ON AND OFF MODES.																			 
2003071800055	20030718	00055	CE  	2003	7	18	AUS20030552      	1	20030604	G	5310	571305718	WEB             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BEAM WEB CRACKED. CRACK LENGTH APPROXIMATELY 25.4MM (1IN).						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2003071800056	20030718	00056	NM  	2003	7	18	AUS20030553      	1	20030603	G	5530		HINGE           			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	VERTICAL STAB	MISLOCATED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER CENTRE HINGE FITTED IN WRONG LOCATION.  MANUFACTURING ERROR.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2003071800057	20030718	00057	NE  	2003	7	18	AUS20030554      	2	20030602	G	7230		BLADE           			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COMPRESSOR	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRST STAGE COMPRESSOR BLADES SEVERELY DAMAGED BY FOD. FOUND DURING INSPECTION IAW AD/ENG/5 A7.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003071800102	20030718	00102	EU  	2003	7	18	AUS20030555      	1	20030604	G	5730	HC573H0002000	SKIN            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT & RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT LOWER WING SKINS CORRODED IN AREA OF FUEL PUMP WATER SCAVENGE GUARDS AT RIB 15.  FOUND DURING INSPECTION	 IAW ER BA6-28-10-7 AND ISB 28-028.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003071800103	20030718	00103		2003	7	18	AUS20030556      	4	20030515	G	3457	10706	ANTENNA         			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	GPS	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) GLOBAL POSITIONING SYSTEM (GPS) ANTENNA SUSPECT FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003072100002	20030721	00002	NE  	2003	7	21	AUS20030558      	2	20030606	G	7200	200304016	ENGINE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2	BIRD INGESTION  	W				O				OTHER                   				C	J		F.O.D.                    	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) NR 2 ENGINE BIRDSTRIKE. BIRD HAD ENTERED CORE OF ENGINE. ENGINE REMOVED FOR REPAIR.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003072100007	20030721	00007	SW  	2003	7	21	AUS20030563      	1	20030610	G	5551	2743062022	ATTACH FITTING  			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER PITCH TRIM ACTUATOR RT ATTACHMENT FITTING OUTBOARD LUG CRACKED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003072100010	20030721	00010	SO  	2003	7	21	AUS20030565      	1	20030601	G	3242	21585	BRAKE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	RT MLG	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1824 							(AUS) RT INBOARD BRAKE FAULTY. INVESTIGATION FOUND TWO CRACKED ROTORS.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2003072100011	20030721	00011		2003	7	21	AUS20030566      	4	20030610	G	2564	1000107	LIFE RAFT       																	EMERG EQUIP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					082					(AUS) LIFE RAFT FOUND PARTIALLY INFLATED ON STORAGE SHELF. THIS IS A REOCCURANCE OF DEFECT REPORTED AS MDR 03/0132 WHICH	 WAS THOUGHT TO HAVE BEEN RECTIFIED.   REPAIR FACILITY BELIEVES THAT THE PROBLEM IS DUE TO FAULTY COMPONENTS IN THE CYLI	NDER VALVE OVERHAUL KITS THAT ARE SUPPLIED.																	 
2003072100014	20030721	00014	EU  	2003	7	21	AUS20030570      	1	20030607	G	2910	HC291B0059000	LINE            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) YELLOW HYDRAULIC SYSTEM QUANTITY LOW. INVESTIGATION FOUND PIPELEAKING FROM SWAGE ADJACENT TO T' PIECE CONNECTION F	OR THE YELLOW SYSTEM PRESSURE SUPPLY TO THE HP MANIFOLD.					2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003072100015	20030721	00015	EA  	2003	7	21	AUS20030571      	2	20030426	G	8500	IO540E1B5	ENGINE          			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3X	HCA3XK2     	GL  	LEFT	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			1381 							(AUS) LT ENGINE FAILED TO RESTART IN FLIGHT AFTER AN INTENTIONAL SHUTDOWN. INVESTIGATION COULD FIND NO PROBLEMS WITH THE	 ENGINE. SUSPECT CAUSED BY OVERPRIMING OF THE FUEL SYSTEM.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P913	 
2003072100016	20030721	00016	SO  	2003	7	21	AUS20030572      	1	20030520	G	3310	4773209	TRANSISTOR      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	COCKPIT LIGHTS	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) INSTRUMENT LIGHTING SOLID STATE DIMMER TRANSISTORS BLOWN DUE TO WATER INGRESS THROUGH CRACKED WINDSCREEN. ELECTRIC	AL EQUIPMENTAND LOOMS CONTAMINATED WITH WATER.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003072100017	20030721	00017	SW  	2003	7	21	AUS20030573      	1	20030604	G	2721	2742004003	ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	RUDDER TAB	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 			557  							(AUS) RUDDER TRIM TAB ACTUATOR FAULTY.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2003072100028	20030721	00028	EU  	2003	7	21	AUS20030574      	1	20030603	G	2731	DL3827M157	ACTUATOR        			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	ELEVATOR TAB	UNSERVICEABLE   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			16157							(AUS) STANDBY PITCH TRIM ACTUATOR FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL	 
2003072100038	20030721	00038	EU  	2003	7	21	AUS20030575      	1	20030604	G	5350	4995100V1	RADOME          			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	NOSE	BIRD STRIKE     	W				O				OTHER                   				C			F.O.D.                    			TO	TAKEOFF        	1			AU	S 										(AUS) BIRDSTRIKE ON SURVEILLANCE RADOME.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2003072100039	20030721	00039	EU  	2003	7	21	AUS20030576      	1	20030605	G	7797		WIRE            			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	ENGINE INDICATOR	BROKEN          	W				O				OTHER                   				E	M		VIBRATION/BUFFET          	OVER TEMP                 		CL	CLIMB          	1			AU	S 										(AUS) LT PROPELLER GEARBOX OIL TEMPERATURE INDICATION FAILED. INVESTIGATION FOUND A BROKEN WIRE TO THE TEMPERATURE SENSO	R.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2003072100040	20030721	00040		2003	7	21	AUS20030577      	4	20030508	G	3417	4083602901	MODULE          			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ADC	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) PITOT AIR DATA MODULE FAULTY.   INVESTIGATION FOUND A SMALL AMOUNT OF WATER IN THE LT AND RT PITOT SUMP DRAINS.						2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2003072100041	20030721	00041	EU  	2003	7	21	AUS20030578      	1	20030417	G	8011		MOTOR           	GE          	CF680E1     	AIRBUS	330   	A330202     	3930316	EU  	GE    	CF6   	CF680       	30025	NE  					STARTER	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE STARTER MOTOR FAILED. DAMAGE CAUSED TO ENGINE.						2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2003072100042	20030721	00042		2003	7	21	AUS20030579      	4	20030609	G	3418	9754421422	TRANSMITTER     			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STALL WARNING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0380					(AUS) ANGLE OF ATTACK (AOA) TRANSMITTER STUCK.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003072100043	20030721	00043	NM  	2003	7	21	AUS20030580      	1	20030606	G	5744	5926059510	FITTING         			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING INBOARD SPOILER MAIN ACTUATOR SUPPORT FITTING CRACKED IN THE OUTBOARD SUPPORT CHANNEL AND PASSING THROUGH 	THE SPOILER DOWNSTOP PAD FITTING REAR RIVET HOLE. FOUND DURING INSPECTION IAW MFG ALERT SB 717-57A0016.					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2003072100050	20030721	00050	CE  	2003	7	21	AUS20030581      	1	20030605	G	5313	50440014523	STRINGER        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 7 STRINGER RT SIDE CRACKED.   FOUND DURING INSPECTION IAW AD 200/55 AMDT1.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003072100055	20030721	00055	NM  	2003	7	21	AUS20030583      	1	20030604	G	3260	S106	SENSOR          			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					MLG	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) MAIN LANDING GEAR AIR SENSOR S106 FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003072100056	20030721	00056	WP  	2003	7	21	AUS20030584      	2	20030121	G	7313	3103235	NOZZLE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ENGINE	BLOCKED         	W				O				OTHER                   				E	M		VIBRATION/BUFFET          	OVER TEMP                 		NR	NOT REPORTED   	1			AU	S 			200  							(AUS) ENGINE FUEL NOZZLES PARTIALLY BLOCKED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2003090800080	20030908	00080	WP  	2003	9	8	AUS20030585      	1	20030604	G	2810	17482571	FUEL TANK       			NAMER 	F51   	P51C        	6402302	WP  	PCKARD	V1650 	V16507      	49001	SO  	HAMSTD	24D	24D50       	NE  	RT WING	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING FUEL TANK CONTAMINATED WITH RUBBER FROM DELAMINATING FUEL TANK. TANK MANUFACTURED IN SEPTEMBER 1944.						1	L	7	1 	4V	4	V	 	L113    	EXP4V	6	C	P784	 
2003072100058	20030721	00058	CE  	2003	7	21	AUS20030586      	1	20030408	G	7810	53551084	SLIP JOINT      	CONT        	TSIO520N    	CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE COLLECTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1268 		514392					(AUS) RT ENGINE EXHAUST SYSTEM SLIP COUPLING CRACKED IN AREA NEAR TRANSITION DUCT.						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2003072100059	20030721	00059	NM  	2003	7	21	AUS20030587      	1	20030523	G	3246	13889	BEARING         			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	MLG WHEEL	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT MAIN WHEEL INBOARD BEARING ASSEMBLY FAILED.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2003072100060	20030721	00060	CE  	2003	7	21	AUS20030589      	1	20030301	G	2913	202401CF	SHAFT           	CESSNA      	202401CF    	CESSNA	210   	210A        	2073408	CE  	CONT  	O470  	IO470E      	17026	SO  	HARTZL	HCA2X	HCA2XF1     	GL  	HYD PUMP	FAULTY          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PUMP DRIVE SHAFT CASE HARDENING HAD FAILED IN AREA OF KEYWAY ALLOWING KEY TO TILT AND JAM.  RESIDUAL MET	AL FROM FAILED AREA HAD DAMAGED SHAFT SEAL LEADING TO FLUID LEAKAGE.					1	H	7	1 	3O	3	O	RT	3A21    	3E1	5	C	P908	 
2003072100061	20030721	00061	CE  	2003	7	21	AUS20030590      	1	20030301	G	7820	125025113	MUFFLER         			CESSNA	210   	210A        	2073408	CE  	CONT  	O470  	IO470E      	17026	SO  	HARTZL	HCA2X	HCA2XF1     	GL  	ENGINE EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MUFFLER PIPE CRACKED FOR APPROXIMATELY 75 PERCENT OF CIRCUMFERENCE AROUND JOINT AREA. CRACK WAS HIDDEN BY EXHAU	ST CLAMPS.					1	H	7	1 	3O	3	O	RT	3A21    	3E1	5	C	P908	 
2003072100062	20030721	00062	CE  	2003	7	21	AUS20030591      	1	20030516	G	5753	052323123	FLAP TRACK      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			9762 							(AUS) LT WING FLAP TRACK CORRODED ON INNER FACE. MATERIAL THICKNESS REDUCED BY APPROXIMATELY 25 PERCNET.   TRACK IS LOCA	TED AT STN 312.75.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003072100063	20030721	00063	CE  	2003	7	21	AUS20030592      	1	20030415	G	5311	002430018N	SPAR            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SPAR WEB CONTAINED TWO CRACKS IN THE AREA OF LT UPPER WING ATTACHMENT POINT. CRACK WAS LOCATED AROUND HUCK BOLTS. 	  CRACK LENGTH 12.7MM (0.5IN).   AIRCRAFT HAD SUFFERED A WHEELS UP LANDING IN THE PAST.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2003072100073	20030721	00073	SO  	2003	7	21	AUS20030593      	1	20030513	G	5513	6524500	BRACE           			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320*       	41508	EA  	AMTR	C8289	C8289       	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER TRIM DIAGONAL BRACE CRACKED. SUSPECT BRACE WAS BENT OUT OF THE WAY FOR ACCESS. STABILIZER HI	NGE BOLTS HAD MISSING SPACER WASHERS.  PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	EXPP5N	 
2003072100078	20030721	00078	EA  	2003	7	21	AUS20030594      	2	20030523	G	7313	2541946	NOZZLE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL INJECTOR	BLOCKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			18   							(AUS) RT ENGINE NR 1 CYLINDER FUEL INJECTOR NOZZLE PARTIALLY BLOCKED BY WHAT APPEARS TO BE PLANT/VEGETABLE MATTER.   FOD	.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003072100079	20030721	00079	CE  	2003	7	21	AUS20030595      	1	20030604	G	5310	571305717	BEAM            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BEAM WEB CRACKED. CRACK LENGTH APPROXIMATELY 25.4MM (1IN).						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2003072100080	20030721	00080	NE  	2003	7	21	AUS20030596      	2	20030403	G	7230	110125004	COMPRESSOR      			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ENGINE	FOD             	W				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE VARIABLE INLET GUIDE VANES (VIGV) AND COMPRESSOR BLADES DAMAGED BY FOD.  INVESTIGATION FOUND THAT DAMAGE HA	D BEEN CAUSED BY AN OBJECT WITH A DIAMETER OF APPROXIMATELY 3.175MM TO 4.762MM(0.125IN TO 0.1875IN).  AN OBJECT OF THIS 	SIZE COULD NOT PASS THROUGH THE AIR INLET SCREEN WITHOUT CAUSING DAMAGE TO THE SCREENS.  THE INLET SCREENS CONTAINED NO 	DAMAGE.  SCREENS HAD NOT BEEN REMOVED SINCE MAINTENANCE CHECK APPROXIMATELY 26 HOURS PREVIOUSLY.			1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2003072100081	20030721	00081	CE  	2003	7	21	AUS20030597      	1	20030530	G	3213		PIN             			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	MISLOCATED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR FORK BOLT CLEVIS PIN INCORRECTLY FITTED. CLEVIS PIN WAS FITTED BACK TO FRONT AND CONTACTED WHEEL WELL	 STRUCTURE CAUSING DAMAGE TO TORQUE TUBE SUPPORT BRACKETS PN 5027002-5.   PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2003072100082	20030721	00082	CE  	2003	7	21	AUS20030598      	1	20030424	G	5711	122210523	SPAR CAP        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING SPAR CAP RIVET HEADS MISSING. INVESTIGATION FOUND THE SPAR CAP EXTENSIVELY CORRODED.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003072100083	20030721	00083	CE  	2003	7	21	AUS20030599      	1	20030325	G	3230	NAS464P5A42	BOLT            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MLG DRAGLINK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG LINK ATTACHMENT BOLT HEAD SEPARATED FROM SHANK.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003072100084	20030721	00084	EA  	2003	7	21	AUS20030600      	2	20030526	G	8550	AN9114D	ADAPTER         			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	ENGINE	SHEARED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) OIL DRAIN VALVE BROKEN OFF FLUSH WITH SURFACE OF OIL SUMP.  THREADED PORTION OF DRAIN VALVE ADAPTER STILL LOCATED 	IN SUMP.  DRAIN VALVE AND REST OF ADAPTER MISSING. LOSS OF ENGINE OIL.					1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2003072100085	20030721	00085	CE  	2003	7	21	AUS20030601      	2	20030526	G	8530	653098	CYLINDER        			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  	MCAULY	D3A36	D3A36C410   	GL  	ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			80   							(AUS) ENGINE NR 1 CYLINDER BARREL FAILED IN AREA APPROXIMATELY TWO FINS FROM TOP OF BARREL.  CYLINDER HEAD AND ATTACHED 	SECTION OF BARREL SEPARATED. SEVERE DAMAGE TO ENGINE.					1	L	7	1 	3O	3	O	 	2A3     	E9CE	5	C	P47GL	 
2003072100096	20030721	00096	SO  	2003	7	21	AUS20030603      	1	20030519	G	2916	4802800	RESERVOIR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HYD SYSTEM	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC RESERVOIR CONTAMINATED.  CONTAMINANT WAS A BLACK SLUDGE WHICH MAY INDICATE BIOLOGICAL GROWTH.   SUSPECT 	PROBLEM ORIGINATES FROM WATER LYING IN SPILL TRAY AROUND FILLER NECK.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003072100097	20030721	00097		2003	7	21	AUS20030605      	4	20030605	G	3497	9C98A22	WIRE            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NAVIGATION	WORN            	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) ALTIMETER POWER WIRING CHAFING IN AREA APPROXIMATELY 175MM(6.8IN) FROM ALTITUDE SELECT CONTROL PANEL.  WORN WIRING	 GROUNDED ON INSTRUMENT PANEL FRAMEWORK.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003072100098	20030721	00098	CE  	2003	7	21	AUS20030606      	1	20030618	G	5520	179856	ELEVATOR        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	LEFT	FOD             	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) ELEVATOR JAMMED.   INVESTIGATION FOUND A PIECE OF METAL PROTRUDING FROM THE LT ELEVATOR BALANCE HORN DIRECTLY BEHI	ND THE BALANCE WEIGHT ATTACHMENT RIB.   METAL MEASURED 12.7MM BY 57.15MM (0.5IN BY 2.25IN) WITH A THICKNESS OF 0.8128MM 	(0.032IN) AND APPEARS TO BE ALCLAD.   THE METAL CONTAINED A HOLE INTO WHICH A PK TYPE SCREW HAD BEEN INSERTED AT SOME ST	AGE.   SUSPECT METAL HAD AT ONE TIME BEEN ATTACHED TO THE ELEVATOR TIP CUFF AND HAD COME ADRIFT. FOD.			1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003072100099	20030721	00099	WP  	2003	7	21	AUS20030609      	2	20030504	G	7250	8675697	ENGINE          	GARRTT      		SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313U    	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LEFT	SEIZED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 					PO3437					(AUS) LT ENGINE SEIZED IN FLIGHT. INVESTIGATION FOUND SEVERE DAMAGE TO ALL TURBINES AND STATORS.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2003072100100	20030721	00100	CE  	2003	7	21	AUS20030610      	1	20030505	G	2750	S18193	ROD END         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	TE FLAPS	SEIZED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT FLAP ASSEMBLY PUSH/PULL ROD END BEARING SEIZED CAUSING CONTROL ROD TO SNAP.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003072100106	20030721	00106	SO  	2003	7	21	AUS20030611      	1	20030620	G	3260	4198500	BRACKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	CRACKED         	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) LT MAIN LANDING GEAR SWITCH BRACKET CRACKED RESULTING IN SWITCH OUT OF ADJUSTMENT.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003072100107	20030721	00107	CE  	2003	7	21	AUS20030612      	1	20030616	G	5311	50420013954	FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			200  							(AUS) FUSELAGE FRAME CRACKED AT FLOOR HEIGHT ON RT SIDE. FRAME IS LOCATED AT FS 207.125.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003072100108	20030721	00108	EA  	2003	7	21	AUS20030613      	2	20030606	G	7322	105217	PLUNGER         	LYC         		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					CARBURETOR	BINDING         	W				O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 					CK35050					(AUS) CARBURETOR ACCELERATOR PUMP PLUNGER BINDING IN BORE.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003072100109	20030721	00109	NM  	2003	7	21	AUS20030614      	1	20030617	G	6310	A1902	BELT            			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/XMSN	STRETCHED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE VEE BELTS STRETCHED BEYOND LIMITS.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003072100110	20030721	00110	WP  	2003	7	21	AUS20030615      	1	20030609	G	6320	269A51039	PINION GEAR     			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					M/R GEARBOX	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			36   		125194					(AUS) MAIN TRANSMISSION TAIL ROTOR DRIVESHAFT PINION FAILED IN AREA LOCATED JUST IN FRONT OF THE THREADED AREA ALLOWING 	THE TAIL ROTOR DRIVE TO SEPARATE.   AIRCRAFT STRUCK THE GROUND CAUSING EXTENSIVE DAMAGE TO THE LANDING GEAR.					1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2003072100111	20030721	00111	SO  	2003	7	21	AUS20030616      	1	20030616	G	2510	452680	INERTIA REEL    			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	COCKPIT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT INERTIA REEL MAIN SHAFT CUT THROUGH BY BELT SUPPORT ARM.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003072100112	20030721	00112	CE  	2003	7	21	AUS20030617      	1	20030402	G	2820	120040676	LINE            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL LINE CHAFED BY AILERON CABLE.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003082200097	20030822	00097	EA  	2003	8	22	AUS20030620      	2	20030616	G	8550		GASKET          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	DAMAGED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 										(AUS) ENGINE OIL FILTER INTERNAL RUBBER GASKET DAMAGED. A PIECE OF THE RUBBER GASKET WAS FOUND TO BE STUCK UNDER THE OIL	 PRESSURE RELIEF VALVE CAUSING LOSS OF OIL PRESSURE. NEW FILTER HAD BEEN FITTED APPROXIMATELY ONE HOUR PREVIOUSLY. FURTH	ER INVESTIGATION FOUNDTHE OIL LINES WERE CROSSED DURING INSTALLATION OF AIR WOLF SPIN-ON OIL FILTER MODIFICATION. ENGINE	 OIL PRESSURE FRACTURED THE FILTER HOUSING INTERNAL RUBBER CHECK VALVE ON START-UP. RUBBER PARTICLES CIRCULATED IN THE O	IL SYSTEM UNTIL ONE FRAGMENT UNSEATED THE ENGINE OIL PRESSURE REGULATING VALVE, CAUSING LOSS OF OIL PRESSURE. FRAGMENTS 	OF THE RUBBER CHECK VALVE. ERROR DUE TO CONFUSING INSTRUCTIONS IN THE DATA SENT WITH THE KIT.	1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003082200099	20030822	00099	CE  	2003	8	22	AUS20030621      	1	20030617	G	3230	12802091	PIN             			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK PIN SHEARED.						1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2003082200100	20030822	00100	EU  	2003	8	22	AUS20030622      	1	20030526	G	3213	100A703029	STRUT           			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TFE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	MLG	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR CYLINDER, SLIDING TUBE, SPHERICAL BEARING AND SPHERICAL BEARING HOUSING DAMAGED. INVESTIGATIO	N FOUND THE DAMAGE WAS CAUSED BY A LOOSE GRUB SCREW WHICH HAD COME LOOSE AND FALLEN OUT OF THE SLIDING TUBE INTO THE BOD	Y OF THE LANDING GEAR.  SUSPECT CAUSED BY INCORRECT STAKING OF THE GRUB SCREW DURING THE LAST OVERHAUL.				2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2003082200101	20030822	00101	GL  	2003	8	22	AUS20030623      	3	20030616	G	6110	B338421H	BOLT            			EMB   	110   	EMB110*     	       	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3462 							(AUS) PROPELLER COUNTERWEIGHT BOLT HEAD SHEARED. THE OTHER BOLT HEAD ALSO SHEARED WHEN THE LOCKWIRE WAS REMOVED. PROPELL	ER CAME FROM A NEW ZEALAND REGISTERED AIRCRAFT.					1	L	7	2 	4T			RT	A21SO   		6	C	P15EA	 
2003082200102	20030822	00102	NM  	2003	8	22	AUS20030624      	1	20030613	G	2822	6072101	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					FUEL BOOST	FOD             	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 AFT OVERRIDE JETTISON PUMP INGESTED PART OF THE INLET CHECK VALVE.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2003082200103	20030822	00103	CE  	2003	8	22	AUS20030625      	1	20030611	G	7722		INDICATOR       			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	EGT	FAULTY          	W				O				OTHER                   				E	M		VIBRATION/BUFFET          	OVER TEMP                 		NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE EGT SYSTEM FAULTY. EGT INDICATOR AND EGT COMPENSATOR REMOVED AND SENT FOR INVESTIGATION/REPAIR.						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2003082200105	20030822	00105	SO  	2003	8	22	AUS20030626      	1	20030620	G	3230	9529900	STUD            			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR SIDE BRACE STUD CONTAINED LONGITUDINAL MPI INDICATIONS.  FOUND DURING INSPECTION IAW AD/PA28/91 	AMDT1.					1	L	7	1 	3O	3	O	 	2A13    	E9CE	5	C	P920	 
2003082200112	20030822	00112	NE  	2003	8	22	AUS20030627      	2	20030623	G	7310	0301007720	PIPE            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					FUEL DIST	CRACKED         	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE START FUEL INJECTOR PIPE FRACTURED AT FLARE UNDER (B NUT).						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2003082200114	20030822	00114	SW  	2003	8	22	AUS20030628      	1	20030622	G	2460	ANL400	CURRENT LIMITER 			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	DC POWER	DAMAGED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) RT GENERATOR CURRENT LIMITER TERMINAL LOOSE.  POOR CONNECTION CAUSED LOCALISED HEATING OF THE CURRENT LIMITER RESU	LTING IN A BURNING SMELL.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003082200115	20030822	00115	NE  	2003	8	22	AUS20030629      	2	20030624	G	7261		O-RING          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	ENGINE	WRONG PART      	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE OIL SYSTEM CHECK VALVE O' RING JAMMED CHECK VALVE IN OPEN POSITION.  SB3178R2 DELETES THE O' RING FROM THE 	CHECK VALVE. PERSONNEL/MAINTENANCE ERROR. ENGINE SERIAL NUMBER PCE-93117.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2003082200116	20030822	00116	NE  	2003	8	22	AUS20030630      	2	20030624	G	7261		O-RING          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	ENGINE	WRONG PART      	W				K				NONE                    				E	K	W	VIBRATION/BUFFET          	FLUID LOSS                	INADEQUATE Q C            	IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL SYSTEM CHECK VALVE O' RING JAMMED CHECK VALVE IN OPEN POSITION. SB3178R2 DELETES THE O' RING FROM THE C	HECK VALVE. PERSONNEL/MAINTENANCE ERROR. ENGINE SERIAL NUMBER PCE-93183. SEEALSO MDR 03/0629 FOR SIMILAR DEFECT ON OTHER	 ENGINE OF SAME AIRCRAFT.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2003082200117	20030822	00117	CE  	2003	8	22	AUS20030631      	1	20030528	G	3230	NAS464P5A42	BOLT            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG LINK ATTACHMENT BOLT HEAD SEPARATED FROM SHANK.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003082200119	20030822	00119	NM  	2003	8	22	AUS20030632      	1	20030620	G	2431	4011769	BATTERY         			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	MASTER	OVERHEATED      	W				O				OTHER                   				H	M	J	ELECT. POWER LOSS-50 PC   	OVER TEMP                 	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			130  							(AUS) MAIN BATTERY OVERHEATED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003082200120	20030822	00120	NM  	2003	8	22	AUS20030633      	1	20030621	G	7830		FAIRING         	RROYCE      		BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					THRUST REVERSER	FAILED          	W				O				OTHER                   				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		LD	LANDING        	1			AU	S 										(AUS) RT ENGINE FAIRING FAILED.  FAIRING WAS LOCATED ON THE STRUT AT THE 6 O'CLOCK POSITION.  A SMALL AMOUNT OF DAMAGE W	AS NOTED ON SEVERAL BLOCKER DOORS AND ONE CASCADE SEGMENT.					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2003082200121	20030822	00121		2003	8	22	AUS20030634      	4	20030619	G	2565	7A144748	SLIDE           			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					PAX DOOR	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AU	S 			6197 							(AUS) DOOR NR 1 RT SLIDE RAFT FAILED.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2003082200123	20030822	00123	EU  	2003	8	22	AUS20030635      	1	20030618	G	7602	C10310UNF	BALL JOINT      	LYC         		BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MIXTURE CONTROL	BROKEN          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE MIXTURE CONTROL BALL JOINT FAILED.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2003082200124	20030822	00124	CE  	2003	8	22	AUS20030636      	1	20030612	G	3530	19900192551779	REGULATOR       			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	PORTABLE OXYGEN	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					6468287					(AUS) PORTABLE OXYGEN SYSTEM REGULATOR LEAKING PAST TEFLON SEAL.OXYGEN LEAKING FROM HIGH PRESSURE SIDE TO LOW PRESSURE S	IDE INCREASED TO OUTLET PRESSURE ABOVE THE REGULATED 50PSI. RELIEFVALVE OPENED AND LOW PRESSURE OUTLET TUBING BURST.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003082200125	20030822	00125	NM  	2003	8	22	AUS20030637      	1	20030619	G	5280		DOOR            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					MLG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR SHOCK STRUT DOOR MISSING.  DAMAGE TO A NUMBER OF HYDRAULIC LINES.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003082200126	20030822	00126		2003	8	22	AUS20030639      	4	20030601	G	3400	6229436100	SYMBOL GENERATOR			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					NAVIGATION SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) NR 1 SYMBOL GENERATOR FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003082200127	20030822	00127	NM  	2003	8	22	AUS20030640      	1	20030613	G	2612		CONNECTOR       			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					FIRE DETECTION	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE FIRE DETECTION SYSTEM FAULTY. SUSPECT FAULTY CONNECTOR.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003082200128	20030822	00128	SO  	2003	8	22	AUS20030641      	2	20030506	G	7313	811536R	INJECTOR        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	FUEL SYSTEM	BLOCKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			833  							(AUS) RT ENGINE OIL FILTER CONTAMINATED WITH METAL.  INVESTIGATION FOUND NR 5 CYLINDER INJECTOR NOZZLE WAS PARTIALLY BLO	CKED CAUSING TORCHING OF NR 5 PISTON.					1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2003082200129	20030822	00129	NM  	2003	8	22	AUS20030642      	1	20030625	G	2750	7321870018	SHUTOFF VALVE   			BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					HYD SYSTEM	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) FLAP/SLAT HYDRAULIC SHUTOFF VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2003082200130	20030822	00130		2003	8	22	AUS20030643      	4	20030610	G	2211	6224591512	COMPUTER        			BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					AUTOPILOT	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 										(AUS) LT FLIGHT CONTROL COMPUTER (FCC) FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2003082200132	20030822	00132	SW  	2003	8	22	AUS20030644      	1	20030630	G	2731	2743027041	BUSHING         			SWRNGN	SA227 	SA227AT     	8780610	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ELEVATOR TAB	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PITCH TRIM SERVO ACTUATOR LOWER ATTACHMENT POINT PIVOT BUSHING MISSING AND ATTACHMENT BOLTS WORN.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P61GL	 
2003082200133	20030822	00133	CE  	2003	8	22	AUS20030646      	1	20030626	G	8011	652406	DRIVE GEAR      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE STARTER	DAMAGED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			849  							(AUS) ENGINE STARTER DRIVE GEAR TEETH (7OFF) MISSING. INVESTIGATION ALSO FOUND CORRESPONDING CRANKSHAFT DRIVE GEAR TEETH	 DAMAGED.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003090200001	20030902	00001	NM  	2003	9	2	AUS20030648      	1	20030629	G	2497		WIRE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ELECTRICAL	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRICAL WIRING LOCATED IN THE BILGE AREA AT STA 570 IN THE FORWARD CARGO COMPARTMENT BURNED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003090200011	20030902	00011	NM  	2003	9	2	AUS20030649      	1	20030622	G	3260	189915	SENSOR          			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					RT MLG	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK SENSOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090500051	20030905	00051	CE  	2003	9	5	AUS20030650      	1	20030630	G	5711	0523315	PLATE           			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470R       	17026	SO  					WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING FRONT SPAR CAP DOUBLER PLATE CONTAINED INTERGRANULAR CORROSION.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003090500052	20030905	00052	CE  	2003	9	5	AUS20030651      	1	20030630	G	5711	122210522	ANGLE           			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470R       	17026	SO  					WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING FRONT SPAR CAP ANGLE CORRODED.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003090500053	20030905	00053	NM  	2003	9	5	AUS20030652      	1	20030428	G	5310		BEAR STRAP      			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					GALLEY DOORS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD GALLEY DOOR CRACKED. SEVEN CRACKS FOUND ON FORWARD UPPER CORNER (BEAR STRAP AND INTERNAL DOUBLER) AND ONE 	CRACK FOUND ON THE AFT UPPER CORNER (BEAR STRAP DOUBLER). FOUND DURING EDDY CURRENT INSPECTION IAW ENGINEERING INSTRUCTI	ON 737-53-14R4.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090500054	20030905	00054	CE  	2003	9	5	AUS20030653      	1	20030619	G	5511	043200156	SPAR            	CESSNA      		CESSNA	150   	A150K       	2071824	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A1500155					(AUS) STABILIZER SPAR CRACKED IN AREA AROUND ATTACHMENT BRACKET NUT PLATE. CRACK LENGTH 12.7MM (0.5 IN).						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2003090500055	20030905	00055	SO  	2003	9	5	AUS20030654      	1	20030630	G	3211	67198000	WASHER          			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					MLG	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR FORWARD TRUNNION WASHERS INCORRECT PARTS. CORRECT WASHERS HAVE A CHAMFER ON THE INTERN	AL BORE WHICH ALLOWS CLEARANCE FOR THE TRUNNION SHOULDER RADIUS. THE WASHERS FITTED DID NOT HAVE THE CHAMFER. IN THIS CA	SE THE DAMAGE WAS  MINIMAL. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2003090500056	20030905	00056	NM  	2003	9	5	AUS20030655      	1	20030630	G	2497		WIRE            			BOEING	747   	747338      	       	NM  										ELECTRICAL POWER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRICAL WIRING CHAFED AND BURNED IN AREA LOCATED ABOVE TOILET CEILING.						2	L	7	2 	4F			RT	A20WE   					 
2003090500057	20030905	00057	NE  	2003	9	5	AUS20030656      	3	20030617	G	6110		PROPELLER       			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ASSY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER REMOVED DUE TO OIL LEAK. DISASSEMBLY AND INVESTIGATION FOUND THE FOLLOWING DEFECTS;  INCORRECT LOCKING O	F BALANCE WEIGHT SCREWS. SCREWS WERE LOCKWIRED IN A MANNER THAT THE SCREWS WERE UNDOING EACH OTHER.  PN A2433 LONG BOLTS	 WERE USED INSTEAD OF PN A2432  SHORTER BOLTS. LONG BOLTS ARE USED FOR BULKHEAD MOUNT.  BULKHEAD SPACERS WERE USED TO CO	MPENSATE FOR EXTRA LENGTH. CADMIUM PLATED PN A20431 NYLOCK NUTS USED.  NO HYDRAULIC FLUID WAS USED IN PISTON.			1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2003090500058	20030905	00058	SO  	2003	9	5	AUS20030657      	1	20030618	G	3230	4198300	DOWNLOCK HOOK   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	LACK OF LUBE    	W				O				OTHER                   				W	J		INADEQUATE Q C            	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWNLOCK HOOK STIFF IN OPERATION DUE TO LACK OF LUBRICATION. SUSPECT CAUSED BY INCORRECT CLEA	NING TECHNIQUES.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003090500059	20030905	00059	SO  	2003	9	5	AUS20030658      	1	20030620	G	6120	M832481110	O-RING          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	PROP CONTROL	DAMAGED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT PROPELLER OIL TRANSFER TUBE O-RING SEAL DAMAGED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2003090500060	20030905	00060	SO  	2003	9	5	AUS20030659      	2	20030630	G	8520	530658	ROD BEARING     			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			152  							(AUS) CONNECTING ROD LITTLE END BEARING MOVED AND WORE ON PISTON. INVESTIGATION FOUND TWO MORE LITTLE END BEARINGS LOOSE	.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2003090500061	20030905	00061	SO  	2003	9	5	AUS20030660      	2	20030630	G	7313		INJECTOR        			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	ENGINE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			152  							(AUS) FUEL INJECTOR NOZZLE INCORRECTLY FITTED. TWO RUBBER SEALS AND ONE METAL WASHER FITTED INSTEAD OF THE CORRECT FIT O	F ONE RUBBER SEAL AND ONE METAL WASHER. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2003090500062	20030905	00062	NM  	2003	9	5	AUS20030661      	1	20030630	G	5730	6545407	SKIN            			BOEING	737   	73733A      	1384673	NM  										RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING UPPER SKIN LOWER SURFACE AND STIFFENERS CONTAINED LEVEL 2 CORROSION IN THE AREA OF THE RT WING VENT TANK B	ETWEEN WS557 AND WS583. FOUND DURING INSPECTION IAW A-B73-5791-51.					2	L	7	2 	4F			RT	A16WE   					 
2003090500063	20030905	00063	NM  	2003	9	5	AUS20030662      	1	20030702	G	3242	215152	BRAKE ASSY      			BOEING	747   	747438      	       	NM  										RT MLG	FIRE            	W				O				OTHER                   				A			FLAME/FIRE                			LD	LANDING        	1			AU	S 					3121					(AUS) RT WING LANDING GEAR BRAKE FIRE. NR 5F AND NR 7F BRAKES REPLACED.						2	L	7	4 	4F			RT	A20WE   					 
2003090500064	20030905	00064	NM  	2003	9	5	AUS20030663      	1	20030703	G	5711	654532525	SPAR            			BOEING	737   	73733A      	1384673	NM  										RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING AFT SPAR LOWER SECTION CONTAINED LEVEL 2 CORROSION IN AREAOF RH WING VENT TANK LOCATED BETWEEN WS557 AND W	S583. FOUND DURING INSPECTION IAW A-B73-5791-51.					2	L	7	2 	4F			RT	A16WE   					 
2003090500065	20030905	00065	CE  	2003	9	5	AUS20030664      	1	20030701	G	2750	0510105193	CONTROL CABLE   			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	TE FLAPS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) LT FORWARD FLAP CONTROL BROKEN.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003090500066	20030905	00066	WP  	2003	9	5	AUS20030665      	2	20030605	G	7230	31020224	HOUSING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SECOND STAGE COMPRESSOR HOUSING PLASMA METAL COATING SEPARATED CAUSING BLOCKAGE OF NOZZLE VANE SEGMENT COOLING AIR	 SLOTS INFIRST STAGE TURBINE NOZZLE AND METAL SPRAY DEPOSITS ON DIFFUSER VANES.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2003090500067	20030905	00067	SO  	2003	9	5	AUS20030666      	2	20030702	G	8530	653452	CYLINDER        			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	RT ENGINE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			152  							(AUS) RT ENGINE HAD TWO UNAPPROVED CYLINDERS FITTED. PN 653452 CYLINDERS ARE NOT APPROVED FOR THE GTSIO520-H MODEL CYLIN	DERS UNLESS MODIFIED. THE TWO CYLINDERS FITTED WERE NOT MODIFIED IAW APPROVED SCHEME. THE REMAINING PN 653453A4 CYLINDER	S FITTED ARE  APPROVED FOR THIS MODEL ENGINE. PERSONNEL/MAINTENANCE ERROR.  UNAPPROVED PART.				1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2003090500068	20030905	00068		2003	9	5	AUS20030667      	4	20030702	G	2565	7A141824	SLIDE           			BOEING	747   	747438      	       	NM  										NR 3	DEFLATED        	W				O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			AU	S 					GT1686					(AUS) NR 3 RT DOOR ESCAPE SLIDE DEFLATED DURING EMERGENCY EVACUATION OF AIRCRAFT FOLLOWING BRAKE FIRE.						2	L	7	4 	4F			RT	A20WE   					 
2003090500069	20030905	00069	NM  	2003	9	5	AUS20030668      	1	20030628	G	3230	11972	SOLENOID        			DHAV  	DHC8  	DHC8315     	2809010	NM  						HAMSTD	14SF	14SF15      	NE  	MLG SECT VALVE	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE SOLENOID COIL A RESISTANCE HIGH.						2	H	7	2 	4T			RT	A13NM   		6	C	P7NE	 
2003090500070	20030905	00070		2003	9	5	AUS20030669      	4	20030618	G	2210		HANDLE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AUTOPILOT SYSTEM	TRANSPOSED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT PITCH AND ROLL DISCONNECT HANDLES TRANSPOSED. THE ROLL DISCONNECT HANDLE WAS IN THE PITCH DISCONNECT HAND	LE POSITION AND THE PITCH DISCONNECT HANDLE WAS IN THE ROLL HANDLE POSITION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090500071	20030905	00071	SO  	2003	9	5	AUS20030670      	2	20030622	G	8530	639272	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 			1312 							(AUS) NR 2 CYLINDER CRACKED BETWEEN VALVES. NR 3 AND NR 4 CYLINDERS REMOVED FOR LOW COMPRESSION.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2003090500072	20030905	00072	NM  	2003	9	5	AUS20030671      	1	20030703	G	2421	31708001A	GENERATOR       			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	NR 1	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			9386 							(AUS) NR 1 AC GENERATOR FAILED. LIMITED INFORMATION PROVIDED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090500073	20030905	00073	CE  	2003	9	5	AUS20030672      	1	20030527	G	5310	VARIOUS	STRUCTURE       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR BULKHEAD BEAM EXTENSION CLEATS LOCATED AT STRINGER 5,STRINGER 7, STRINGER 8 AND STRINGER 11 CRACKED. CLEATS A	RE INSTALLED DUE TO WIDENING OF THE REAR FUSELAGE FOR STC SA2192CE.  FOUND DURING INSPECTION IAW AD/BEECH200/55 AMDT1 AN	D AD/BEECH200/21 AMDT11.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003090500074	20030905	00074	NE  	2003	9	5	AUS20030673      	2	20030629	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LEFT	FLUCTUATES      	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE TORQUE FLUCTUATING. ITT 900 DEGREES C.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003090500075	20030905	00075	EU  	2003	9	5	AUS20030674      	2	20030703	G	7320		PMC             			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					NR 2 ENGINE	FAULTY          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 ENGINE LOW POWER. SUSPECT CAUSED BY FAULTY POWER MANAGEMENT CONTROL (PMC).						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090500076	20030905	00076	SW  	2003	9	5	AUS20030675      	1	20030529	G	5310		STRUCTURE       			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	FUSELAGE	ANIMAL STRIKE   	W				O				OTHER                   				C			F.O.D.                    			LD	LANDING        	1			AU	S 										(AUS) AIRCRAFT HIT A KANGAROO DURING LANDING ROLL. INITIAL IMPACT APPEARS TO BE ON THE LT PROPELLER CAUSING SUBSTANTIAL 	DAMAGE TO THE PROPELLER. ANIMAL REMAINS WERE ALSO INGESTED INTO THE LT ENGINE. FOLLOWING THE IMPACT, THE KANGAROO WAS EJ	ECTED FORWARD AND OVER THE AIRCRAFT IMPACTING THE RT PROPELLER. ENGINEERING INSPECTION FOUND THAT THE LT PROP HAD BENT B	LADES AND THE LT ENGINE HAD INGESTED ANIMAL REMAINS. THE RT PROP AND ENGINE ARE SUSPECTED OF SUFFERING AN IMPACT AND MIN	OR FODDAMAGE TO THE ENGINE.		2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003090500077	20030905	00077	CE  	2003	9	5	AUS20030676      	1	20030328	G	5711	351100611	SPAR            			BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	IO470K      	17026	SO  	AMTR	C8289	C8289       	GL  	RT & LT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPARS PN 35110061-1 (LT) AND PN 351100612 (RT) CONTAINED EXFOLIATION CORROSION IN THE UPPER AND LOWER SPAR CA	PS.					1	L	7	1 	3O	3	O	 	3A15    	3E1	5	N	EXPP5N	 
2003090500079	20030905	00079	SO  	2003	9	5	AUS20030677      	1	20030701	G	5711		SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING MAIN SPAR WEB CRACKED. CRACK LOCATED AT THE TOP OF THE MAIN LANDING GEAR LEG ATTACHMENT AREA. CRACK LENGTH	 100MM (4IN).					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003090500080	20030905	00080	SW  	2003	9	5	AUS20030678      	1	20030704	G	3230	HMX6G	ROD END         			GULSTM	500   	500U        	0141108	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3X	HCA3XK2     	GL  	MLG	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR ACTUATOR RODEND FRACTURED AT GREASE NIPPLE HOLE.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P913	 
2003090500081	20030905	00081	NM  	2003	9	5	AUS20030679      	1	20030601	G	2781	114T642125	WASHER          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LE SLAT	MISSING         	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 5 LEADING EDGE SLAT INBOARD SENSOR TARGET MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003090500082	20030905	00082	CE  	2003	9	5	AUS20030680      	1	20030429	G	3246	MS2125005016	BOLT            			CESSNA	441   	441         	2076020	CE  										MLG WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN WHEEL HUB BOLT SHEARED.						1	L	7	2 	3T			RT	A28CE   					 
2003090500083	20030905	00083	NM  	2003	9	5	AUS20030681      	1	20030702	G	3242	215152	BRAKE           			BOEING	747   	747438      	       	NM  										MLG	FIRE            	W				O				OTHER                   				A	J		FLAME/FIRE                	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 					A0252					(AUS) RT BODY LANDING GEAR BRAKE FIRE.						2	L	7	4 	4F			RT	A20WE   					 
2003090500084	20030905	00084	SW  	2003	9	5	AUS20030682      	1	20030705	G	5210	27	SEAL            			SWRNGN	SA227 	SA227*      	       	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PAX DOOR	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) PASSENGER DOOR SEAL NOT INFLATING CORRECTLY.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
2003090500085	20030905	00085	EA  	2003	9	5	AUS20030683      	2	20030707	G	7414	1O1630052	MAGNETO         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			51   							(AUS) MAGNETO CASE SCREWS LOOSE CAUSING FRETTING BETWEEN CASE HALVES. METAL CONTAMINATION OF MAGNETO.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2003090500086	20030905	00086	SW  	2003	9	5	AUS20030684      	1	20030708	G	2910	2781032675	TUBE            			SWRNGN	SA227 	SA227*      	       	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYSTEM	LOOSE           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) HYD SYSTEM SUCTION TUBE LOOSE AT FITTING ON INBOARD NACELLE LOCATED FORWARD OF HYDRAULIC ACCUMULATOR.						2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
2003090500087	20030905	00087	NM  	2003	9	5	AUS20030685      	1	20030621	G	5310		STRUCTURE       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUSELAGE	LIGHTNING STRIKE	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AIRCRAFT LIGHTNING STRIKE. BURN MARKS AROUND RIVET HEADS AND ON SKIN. MOST DAMAGE IN AREA LOCATED NEAR STRINGER 31	P BETWEEN STN X120 AND STN X653. LH ELEVATOR OUTBOARD REAR STATIC WICK HADSIGNS OF BURNING.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090500088	20030905	00088	EU  	2003	9	5	AUS20030686      	2	20030627	G	7230		COMPRESSOR      			BOEING	737   	73733A      	1384673	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ENGINE	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE COMPRESSOR SIXTH, SEVENTH AND EIGHTH STAGES CONTAINED SUBSTANTIAL FOD DAMAGE.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090500089	20030905	00089	EU  	2003	9	5	AUS20030687      	2	20030627	G	7230	724468	BLADE           			BOEING	737   	73733A      	1384673	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ENG COMPRESSOR	FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE SEVENTH STAGE COMPRESSOR BLADES DAMAGED BY FOD.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090500090	20030905	00090	NM  	2003	9	5	AUS20030688      	1	20030707	G	2150	78279018	ACM             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CABIN COOLING SY	SEIZED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 			5821 							(AUS) CABIN AIR CYCLE MACHINE SEIZED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090500091	20030905	00091		2003	9	5	AUS20030689      	4	20030525	G	8300	3037223	CARBON SEAL     			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					LT ENG ACC GB	WORN            	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			9399 							(AUS) LT ENGINE ACCESSORY GEARBOX OIL BREATHER CARBON SEAL WORN AND LEAKING.						2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2003090500092	20030905	00092	SO  	2003	9	5	AUS20030690      	2	20030708	G	8520	655004	CONNECTING ROD  			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 CYLINDER CONNECTING ROD PN 655004 BIGEND CAP CONTACTING CAMSHAFT PN 653056 NR 2 CYLINDER EXHAUST LOBE. INSPEC	TION FOUND A SIMILAR PROBLEM WITH NR 6 CYLINDER CONNECTING ROD BIG END CAP.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2003090500093	20030905	00093	WP  	2003	9	5	AUS20030691      	1	20030703	G	5711	H36831A	SPAR            			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	DHAV	DH5220	DH5220P     	WP  	LT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING SPAR DAMAGED. LOOSE RIBS FOUND DURING PERIODIC INSPECTION WHEN SECTION OF FABRIC WAS REMVD TO CARRY OUT RI	BREPAIRS REMOVED FABRIC REVEALED NONAPPROVED REPAIR TO REAR SPAR TOP FACE & REPAIRED AREA COVERED BY PAINT. FURTHER FABR	IC REMOVAL FOUND SEVERE DAMAGE TO SPAR LOWER FLANGES AT SEVERAL LOCATIONS. AREAS OF DAMAGE WERE NOT VISIBLE FROM EXISTIN	G INSPECTION HOLE  LOCATIONS.			1	Q	7	1 	3I	3	I	 	A8EU    	A8EU	5	N	A8EU	 
2003090500094	20030905	00094	NM  	2003	9	5	AUS20030692      	1	20030502	G	5312	500N34215	BULKHEAD        			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47M     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD CRACKED AT TOP RT TAIL BOOM FITTING BRACKET.FOUND DURING INSPECTION IAW AD/HU389/108.						1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
2003090500095	20030905	00095	CE  	2003	9	5	AUS20030693      	1	20030707	G	5751	AN470AD4	RIVET           			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	AILERONS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON MASS BALANCE WEIGHT ATTACHMENT RIVETS FAULTY. APPROXIMATELY HALF OF THE RIVETS FAILED TESTING AND INSPECTI	ON IAW AD/CESSNA180/28.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P920	 
2003090500096	20030905	00096	SO  	2003	9	5	AUS20030694      	2	20030708	G	8520	35972	BOLT            			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	IO470*      	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	CONNECTING ROD	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONNECTING ROD BOLT FAULTY. LONGITUDINAL DISCONTINUITY FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/ENG/4 AMDT	8.					1	H	7	1 	3O	3	O	NT	3A13    	E1CE	5	C	P3EA	 
2003090500097	20030905	00097		2003	9	5	AUS20030695      	4	20030713	G	8300	31011447	PLANETARY GEAR  			CASA  	C212  	C212200     	2410304	EU  	GARRTT	TPE331	TPE33110    	01514	WP  					GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			217  							(AUS) ENGINE GEARBOX SUN GEAR DAMAGED WHICH IN TURN CAUSED DAMAGE TO THE PLANETARY GEARS. SUSPECT SUN GEAR INCORRECTLY H	ARDENED DURING MANUFACTURE. FOUND AS A RESULT OF SOAP SAMPLE TESTING.					2	H	7	2 	4T	4	T	RT	A43EU   	E4WE				 
2003090500098	20030905	00098	CE  	2003	9	5	AUS20030696      	1	20030708	G	3233	12810013	HOUSING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MLG ACTUATOR	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 			8674 							(AUS) RT MAIN LANDING GEAR ACTUATOR BODY SEVERELY CRACKED FROM PINION GEAR ACCESS HOLE TO THE OUTER FACE OF THE ACTUATOR	. SLIGHT CRACKING WAS ALSO FOUND FROM THE ACCESS HOLE TO THE NEEDLE BEARING HOUSING.					1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003090500099	20030905	00099	EA  	2003	9	5	AUS20030697      	2	20030616	G	8530	SL75089	PISTON          			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	O540A1D5    	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PISTON CRACKED THROUGH OIL RING LAND.						1	L	7	2 	3O	3	O	 	1A10    	E295	5	C	P9EA	 
2003090500100	20030905	00100	NM  	2003	9	5	AUS20030698      	1	20030712	G	3310	RV4NBYSD502A	RHEOSTAT        			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	BURNED OUT      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) FLIGHT COMPARTMENT LIGHTING RHEOSTAT BURNED OUT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090500102	20030905	00102	NM  	2003	9	5	AUS20030699      	1	20030711	G	2731	6355B000103	ACTUATOR        			BOEING	737   	737800*     	       	NM  										ELEVATOR TAB	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 					1511					(AUS) STABILISER TRIM ACTUATOR FAULTY. ACTUATOR MOTOR UNSERVICEABLE.						2	L	7	2 	4F			RT	A16WE   					 
2003090500109	20030905	00109	NM  	2003	9	5	AUS20030700      	1	20030704	G	3242	26123121	BRAKE           			BOEING	737   	737800*     	       	NM  										RT MLG	SEIZED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT INBOARD BRAKE SEIZED. ON  REMOVAL OF WHEEL THE BRAKE PAD WAS FOUND TO BE DISLODGED AND JAMMING THE STATORS/ROTO	RS.					2	L	7	2 	4F			RT	A16WE   					 
2003090500111	20030905	00111	NM  	2003	9	5	AUS20030701      	1	20030705	G	2910		LINE            			BOEING	767   	767383      	1385214	NM  										HYDRAULIC SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) RT ENGINE DRIVEN HYDRAULIC PUMP CASE DRAIN LINE LEAKING. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F			RT	A1NM    					 
2003090500113	20030905	00113	SO  	2003	9	5	AUS20030703      	2	20030701	G	8520	655004	CONNECTING ROD  			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1391 							(AUS) CONNECTING ROD CONTAINED A CRACK INDICATION ON THE SHANK BELOW THE LITTLE END.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2003090500114	20030905	00114	EU  	2003	9	5	AUS20030704      	1	20030712	G	5610	NP1701022	WINDSHIELD      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WINDSHIELD SHATTERED.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003090500115	20030905	00115		2003	9	5	AUS20030705      	4	20030714	G	2397		WIRE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ENTERTAIN SYS	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) PSU WIRING BURNED IN AREA ABOVE SEAT 53AB.  WIRING ARCING ON SUPPORT BRACKET.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003090500118	20030905	00118	NM  	2003	9	5	AUS20030706      	1	20030711	G	4920	380029812	APU             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					APU BAY	SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) APU FAULTY. SMOKE IN CABIN. WORKSHOP INVESTIGATION COULD FIND NO EVIDENCE OF OIL LEAK. SUSPECT OIL WAS RESIDUE FRO	M A PREVIOUS OIL LEAK.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003090500120	20030905	00120	NM  	2003	9	5	AUS20030707      	1	20030625	G	5310		DOOR FRAME      			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR FRAME CRACKED. FORWARD CORNER HAS CRACK INDICATIONS IN FIVEHOLES. AFT CORNER HAS CRACK INDICATION IN ONE HOLE	. FOUND DURINGEDDY CURRENT INSPECTION IAW QANTAS ENGINEERING INSTRUCTION733-53-14R4, BOEING SB:737-53-1116 AND CASA AD/B	737/24.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090500121	20030905	00121	SO  	2003	9	5	AUS20030708      	1	20030715	G	3230	554401	CABLE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR CABLE HAD SLIGHT BINDING. DURING INVESTIGATION OF THE BINDING PROBLEM A CRIMPED FERRULE SEPARATED FRO	M THE CABLE. CABLE WAS A NEW ITEM AND WAS BEING INSPECTED BEFORE FITMENT.CABLE IS FITTED BETWEEN LANDING GEAR SELECTOR H	ANDLE AND POWERPACK.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003090500122	20030905	00122	EA  	2003	9	5	AUS20030709      	2	20030716	G	7414	K3823	GEAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE MAGNETO DISTRIBUTOR GEAR POINTER LOOSE AND CONTACTING DISTRIBUTOR CAP AND POSTS.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003090500124	20030905	00124	NM  	2003	9	5	AUS20030710      	1	20030703	G	2731	6355B000103	ACTUATOR        			BOEING	737   	737800*     	       	NM  										ELEVATOR TAB	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) HORIZONTAL STABILISER TRIM ACTUATOR FAULTY.						2	L	7	2 	4F			RT	A16WE   					 
2003090500126	20030905	00126	EA  	2003	9	5	AUS20030711      	2	20030711	G	8530	L227667A	BUSHING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE OIL FILTER CONTAMINATED WITH FINE ALUMINIUM/BRONZE METAL PARTICLES. STRIP AND INSPECTION FOUND THAT THE 	SOURCE OF THE METAL CONTAMINATION WAS FROM THE VALVE ROCKER THRUST WASHER AREAS. SEVERAL OF THE ROCKER PEDESTAL BUSHES H	AD BEEN INSTALLED PROUD OF THE THRUST FACE AT MANUFACTURE. THIS HAS RESULTED IN THE THRUST WASHERS INITIALLY BEARING ON 	THE EDGE OF THE BUSHINGS, EVENTUALLY WEARING THEM DOWN, THEN ON TO THE ROCKER PEDESTAL THRUST FACES. SOME OF THE BUSHING	 MATERIAL RUBBED OFF DURING THIS TIME HAD LODGED BETWEEN THE THRUST WASHERS AND PEDESTALS RESULTING IN ABRASION OF THE T	HRUST FACE. PERSONNEL/MAINTENANCE ERROR.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003090500128	20030905	00128	NM  	2003	9	5	AUS20030712      	1	20030714	G	2910	AE81566J	FITTING         			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYDRAULIC SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 1 ENGINE HYDRAULIC SYSTEM FIREWALL QUICK DISCONNECT FITTING CRACKED. LOSS OF A-SYSTEM HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090500129	20030905	00129	GL  	2003	9	5	AUS20030713      	3	20030630	G	6114	D2438	HUB             			PIPER 	PA30  	PA39        	7103902	SO  	LYC   	O320  	O320*       	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			829  							(AUS) UNAPPROVED MACHINING CARRIED OUT ON PROPELLER HUB PRE-LOAD SHELF. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PROCEDUR	E.					1	L	7	2 	3O	3	O	 	A1EA    	E274	5	C	P9EA	 
2003090500130	20030905	00130	NM  	2003	9	5	AUS20030714      	1	20030715	G	2150		ODOR            			BOEING	737   	737376      	       	NM  										AIR CONDITIONING	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) FUMES WITH SLIGHT SULPHUR ODOR REPORTED BY CABIN CREW AROUND REAR GALLEY AND REAR CABIN VENTS. DURING INVESTIGATIO	N AND GROUND RUNNING THE EQUIPMENT COOLING EXHAUST FAN FAILED AND THE CIRCUIT BREAKER POPPED.					2	L	7	2 	4F			RT	A16WE   					 
2003090500131	20030905	00131	SW  	2003	9	5	AUS20030715      	1	20030715	G	2910		LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG HYD SYS	CORRODED        	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) LANDING GEAR RETRACTION SYSTEM HYDRAULIC LINE CORRODED AND LEAKING.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2003090500133	20030905	00133	CE  	2003	9	5	AUS20030716      	1	20030708	G	2710	0510105365	CABLE           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	AILERON CONTROL	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CROSSOVER CABLE LOCATED IN RT WING WORN FLAT IN AREA WHERE CABLE RUNS ON FAIR LEAD. CABLE WAS INCORRECTLY 	ROUTED. PERSONNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003090500134	20030905	00134	SO  	2003	9	5	AUS20030717      	1	20030707	G	2731	5299	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ELEVATOR TAB	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) LT AND RT HORIZONTAL STABILISER TRIM ACTUATORS JAMMED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2003090500135	20030905	00135	CE  	2003	9	5	AUS20030718      	1	20030716	G	8011	632101	GEAR            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE STARTER	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			1281 							(AUS) STARTER ADAPTER DRIVESHAFT GEAR TEETH STRIPPED.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2003090500137	20030905	00137	EA  	2003	9	5	AUS20030719      	2	20030716	G	8520	LW13521	ROD BEARING     			BNORM 	BN2   	BN2A27      	1520227	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONNECTING ROD BEARING DELAMINATED. METAL CONTAMINATION OF OIL FILTER.						1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920	 
2003090500138	20030905	00138	SO  	2003	9	5	AUS20030720      	2	20030610	G	7414	103493921	FLANGE          			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			562  							(AUS) MAGNETO FLANGE BROKEN. SUSPECT CAUSED BY OVERTENSIONING OF HOLD DOWN NUTS. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2003090500140	20030905	00140	EA  	2003	9	5	AUS20030721      	2	20030719	G	8520	LW10646	CONNECTING ROD  			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE2Y	HCE2YR1     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONNECTING ROD CONTAINED A CRACK INDICATION ADJACENT TO THE LITTLE END. LENGTH OF CRACK APPROXIMATELY 6.35MM (0.25	IN). CAP ON ANOTHER CONNECTING ROD CONTAINED CRACK INDICATION ADJACENT TO BOLT HOLE. CRACK LENGTH 3.175MM (0.125IN). CRA	CKS FOUND DURINGMAGNETIC PARTICLE INSPECTION IAW AD/ENG/4 AMDT8.				1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P9EA	 
2003090500141	20030905	00141	CE  	2003	9	5	AUS20030722      	1	20030717	G	3230	511723956	CABLE           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	MLG	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 			10369							(AUS) EMERGENCY LANDING GEAR BLOWDOWN BOTTLE ACTUATING CABLE FAULTY.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003090500143	20030905	00143	SO  	2003	9	5	AUS20030723      	2	20030717	G	8550	402C0026	VALVE           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	LT ENGINE	CONTAMINATED    	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 			10369							(AUS) LT ENGINE LOST OIL PRESSURE AND WAS SHUT DOWN. INVESTIGATION FOUND HARD CARBON PARTICLES IN THE LT ENGINE OIL PRES	SURE RELIEF VALVE.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003090500145	20030905	00145	NM  	2003	9	5	AUS20030724      	1	20030719	G	2822	7G774	PRESSURE SWITCH 			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUEL PUMP	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) RT AUXILIARY FUEL PUMP INDICATOR PRESSURE SWITCH FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090500146	20030905	00146	EU  	2003	9	5	AUS20030725      	1	20030717	G	2752	9787320307	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 			2098 							(AUS) RT TRAILING EDGE FLAP OUTER LINEAR ACTUATOR FAILED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090500148	20030905	00148	EU  	2003	9	5	AUS20030726      	1	20030717	G	2752	9787320307	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 			2182 							(AUS) LT TRAILING EDGE FLAP INNER LINEAR ACTUATOR FAILED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090500149	20030905	00149	NM  	2003	9	5	AUS20030727      	1	20030704	G	5230	6547952524	STRUCTURE       			BOEING	737   	737376      	       	NM  										CARGO DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1121					(AUS) AFT CARGO DOOR OUTER TEE STRUCTURE CRACKED IN AFT LOWER CORNER. CRACK WAS LOCATED BETWEEN TWO FASTENERS. CRACK LEN	GTH APPROXIMATELY 19.05MM (0.75IN).					2	L	7	2 	4F			RT	A16WE   					 
2003090500152	20030905	00152	WP  	2003	9	5	AUS20030728      	2	20030722	G	7510	31030791	NUT             			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENG ANTI-ICE	LOOSE           	W				O				OTHER                   				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE FIRE WARNING. THE ENGINE WAS SHUT DOWN AND THE FIRE EXTINGUISHER ACTIVATED. SUBSEQUENT INSPECTION COULD 	FIND NO EVIDENCE OF FIRE. PRELIMINARY INVESTIGATION SUGGESTS AN ENGINEANTI-ICE BLEED AIR LEAK. FURTHER INVESTIGATION FOU	ND THE NUT ON THE ENGINE ANTI-ICE BLEED AIR TUBE HAD COME LOOSE. SUSPECT DUE TO INSUFFICIENT TIGHTENING DURING MAINTENAN	CE. PERSONNEL/MAINTENANCE ERROR.			2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003090500153	20030905	00153	NM  	2003	9	5	AUS20030729      	1	20030720	G	5610	5887275505	WINDSHIELD      			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) COCKPIT CENTER WINDSHIELD CRACKED IN LOWER LT CORNER. SLIGHT BURN MARKS NOTICED ADJACENT TO THE CRACKS. SUSPECT WI	NDOW HEAT SYSTEM SHORT CIRCUIT.					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2003102000013	20031020	00013	GL  	2003	10	20	AUS20030730      	1	20030708	G	6120		PLUG            			DIAMON	DA40  	DA40        	       	GL  										PROP CONTROL	LOOSE           	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) PROPELLER PITCH CONTROL VALVE PLUG LOOSE. SUSPECT PLUG LOCKING RING BUMPED DURING EXAMINATION OF PLUG PRIOR TO FLI	GHT.					1	L	7	1 	3O			NT	A47CE   					 
2003090800001	20030908	00001	CE  	2003	9	8	AUS20030731      	1	20030723	G	3260	H111541	UPLOCK SWITCH   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LANDING GEAR POS	UNSERVICEABLE   	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK SWITCH UNSERVICEABLE.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003090800002	20030908	00002	CE  	2003	9	8	AUS20030732      	1	20030717	G	2422		INVERTER        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AC SYSTEM	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) 240 VAC INVERTER BURNED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003090800003	20030908	00003	SO  	2003	9	8	AUS20030733      	2	20030718	G	8500	TSIO520VB	ENGINE          			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	LEFT	FAILED          	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			AU	S 			1541 				402C0026			(AUS) LT ENGINE FAILED. ENGINE STARTED RUNNING ROUGH WITH ASSOCIATED VIBRATION. OIL PRESSURE AND MANIFOLD PRESSURE DROPP	ED AND ENGINE APPEARED TO BE WINDMILLING. ENGINE WAS SHUTDOWN AND PROPELLER FEATHERED.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003090800004	20030908	00004	NE  	2003	9	8	AUS20030734      	2	20030717	G	7321	0164448440	FCU             			AEROSP	AS365 	AS365N2     	8680815	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					ENGINE	CLOGGED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			503  							(AUS) FUEL CONTROL UNIT FAULTY. INVESTIGATION FOUND PRESSURE BALANCE UNIT PARTIALLY CLOGGED.						1	G	7	2 	3U	3	U	RT	H10EU   	E19EU				 
2003090800005	20030908	00005		2003	9	8	AUS20030735      	4	20030723	G	3418	285A10106	COMPUTER        			BOEING	737   	737800*     	       	NM  										STALL WARNING	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) STALL WARNING COMPUTER SUSPECT FAULTY.						2	L	7	2 	4F			RT	A16WE   					 
2003090800006	20030908	00006	NM  	2003	9	8	AUS20030736      	1	20030717	G	5311		FRAME           			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAMES CRACKED AT PSU ATTACHMENT POINTS. FOUR FRAMES ONTHE LT SIDE AND THREE FRAMES ON THE RT SIDE CRACKE	D. FOUND DURING EDDY CURRENT INSPECTION IAW EI 737-53-68R1 AND NDT TECHNIQUES E-13 AND E-18.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090800007	20030908	00007	NM  	2003	9	8	AUS20030737      	1	20030722	G	5610	141T480149	WINDOW          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					COCKPIT	CRAZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT NR 1 COCKPIT WINDOW OUTER PANE CRAZED DUE TO ELECTRICAL ARCING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003090800008	20030908	00008	NE  	2003	9	8	AUS20030738      	2	20030708	G	7320	114E6112G119	EEC             			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					LT ENGINE	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			30   							(AUS) LT ENGINE ELECTRONIC ENGINE CONTROLLER (EEC) SUSPECT FAULTY.						2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2003090800009	20030908	00009	EU  	2003	9	8	AUS20030739      	1	20030626	G	2421	503106680000	GENERATOR       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 1 GENERATOR FAILED.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003090800010	20030908	00010	NE  	2003	9	8	AUS20030740      	2	20030723	G	7200	M50	MAIN BEARING    			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE CHIP DETECTOR METAL CONTAMINATION. INVESTIGATION FOUND THE METAL TO BE M50 MATERIAL FROM THE MAIN ENGINE BE	ARINGS.					2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003090800011	20030908	00011		2003	9	8	AUS20030741      	4	20030701	G	2562	ELT1104	ELT             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CABIN	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					54513					(AUS) ELT ACTIVATED. THE AIRCRAFT WAS IN THE HANGAR AT THE TIME. THE ELT WAS UNABLE TO BE DE-ACTIVATED EXCEPT BY DISCONN	ECTING THE BATTERY.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003090800012	20030908	00012	SO  	2003	9	8	AUS20030742      	2	20030715	G	8530		CYLINDER HEAD   			BEECH 	23    	A23A        	1151208	CE  	CONT  	O346  	IO346A      	17033	SO  	SNSNCH	74DC	M74DC       	EA  	ENGINE	SEPARATED       	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 										(AUS) NR 1 CYLINDER HEAD SEPARATED AT HEAD TO BARREL JOINT.						1	L	7	1 	3O	3	O	 	A1CE    	E3CE	5	N	P88614	 
2003090800013	20030908	00013	EU  	2003	9	8	AUS20030743      	1	20030724	G	2910	3268	VALVE           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  	ROTOL	R354	R3544123F13 	NE  	HYDRAULIC SYS	FAULTY          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC SYSTEM LOW PRESSURE WARNING. NO LOSS OF FLUID.  INVESTIGATION FOUND THAT THE EMERGENCY ACCUMULATOR DUMP 	VALVE ALLOWED PRESSURE IN THE EMERGENCY AND MAIN HYDRAULIC SYSTEMS TO DROP.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL	 
2003090800014	20030908	00014	CE  	2003	9	8	AUS20030744      	1	20030530	G	3211	12941511	SADDLE          			CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520J      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR SADDLE CRACKED AND LEAKING HYDRAULIC BRAKE FLUID. FURTHER INSPECTION FOUND RT MAIN LANDING GE	AR SADDLE ALSO CRACKED.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2003090800015	20030908	00015	CE  	2003	9	8	AUS20030745      	1	20030716	G	5511	123260029	SPAR            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER FRONT SPAR CENTRE LAMINATE CRACKED. FOUND DURING INSPECTION IAW AD C21069.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2003090800016	20030908	00016	NM  	2003	9	8	AUS20030746      	1	20030715	G	3040		CONTROLLER      			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					WINDSHIELD HEAT	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) LT SIDE WINDOW OVERHEAT INDICATION. WINDOW HEAT TURNED OFF, BUT LIGHT STAYED ON. SUSPECT FAULTY & INTERMITTENT WIN	DOW HEAT CONTROLLER.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090800017	20030908	00017	NM  	2003	9	8	AUS20030747      	1	20030717	G	5230		ACTUATOR        			BOEING	747   	747438      	       	NM  										CARGO DOOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT CARGO DOOR HOOK ACTUATOR FAULTY.  ACTUATOR RUNNING OUT OFSEQUENCE.						2	L	7	4 	4F			RT	A20WE   					 
2003090800018	20030908	00018	EA  	2003	9	8	AUS20030748      	2	20030714	G	8530	LW13622	INTAKE VALVE    			BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	NR 6 CYLINDER	FAILED          	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			AU	S 										(AUS) NR 6 CYLINDER INTAKE VALVE BROKEN OFF AT UPPER PART OF VALVE STEM.  BROKEN INTAKE VALVE CAUSED EXTENSIVE DAMAGE TO	 CYLINDER.					1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2003090800019	20030908	00019	GL  	2003	9	8	AUS20030749      	3	20030701	G	6110		DOWEL PIN       			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	PROP FLANGE	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1200 							(AUS) CRANKSHAFT PROPELLER MOUNTING FLANGE PROPELLER LOCATING DOWELS INCORRECTLY FITTED. DOWELS HAVE A SLIGHT TAPER WHIC	H ALLOWS FOR A SLIP FIT INTO THE CRANKSHAFT AND AN INTERFERENCE FIT ONTO THE PROPELLER. THE DOWELS WERE INCORRECTLY FITT	ED WITH THE INTERFERENCE FIT ONTO THE CRANKSHAFT. THE INCORRECT FITMENT OFTHE DOWELS DAMAGED THE CRANKSHAFT. PERSONNEL/M	AINTENANCE ERROR.			1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003090800020	20030908	00020	CE  	2003	9	8	AUS20030750      	1	20030716	G	3246	4077	WHEEL           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	NLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					21371364					(AUS) NOSE WHEEL CORRODED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003090800021	20030908	00021	EU  	2003	9	8	AUS20030751      	1	20030722	G	3230	VARIOUS	UPLOCK SENSOR   			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	DIRTY           	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LT MLG UNSAFE LIGHT AND GEAR HANDLE WARNING LIGHT ILLUMINATED IN CRUISE AFTER 45 MINUTES IN FLIGHT. LIGHT REMAINED	 ON FOR 60 MINUTES BEFORE EXTINGUISHING 15 MINUTES PRIOR TO LANDING. BOTH LT DOOR AND GEAR UPLOCK SENSORS FOUND TO BE DI	RTY. LT DOOR UPLOCK ACTUATOR PROXIMITY CONTACT ARM FOUND LOOSE.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003090800022	20030908	00022	NE  	2003	9	8	AUS20030752      	2	20030725	G	7261	AC9718F25	FILTER          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R375	R3754123F21 	NE  	SCAVE PUMP	CONTAMINATED    	W				O				OTHER                   				K	E	J	FLUID LOSS                	VIBRATION/BUFFET          	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE ACCESSORY GEARBOX -B- SUMP SCAVENGE FILTER CONTAMINATED WITH CARBON DEPOSITS.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P17NE	 
2003090800023	20030908	00023	NE  	2003	9	8	AUS20030753      	2	20030725	G	7261	3011357	PIPE            			AIRTRC	AT500 	AT502       	0390303	SW  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 2 BEARING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3941 							(AUS) ENGINE EXTERNAL NR 2 BEARING OIL SCAVENGE LINE WORN AND LEAKING AT REAR FIRE SEAL. SEAL HAD CONTACTED PIPE WHICH H	AD CRACKED IN THE WORN AREA.					1	L	7	1 	3T	4	T	NC	A9SW    	E4EA	6	C	P15EA	 
2003090800024	20030908	00024	EA  	2003	9	8	AUS20030754      	2	20030521	G	7414	EO2FA018R	DISTRIBUTOR BLK 			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			71   							(AUS) MAGNETO DISTRIBUTOR BLOCK COLLAPSED.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003090800025	20030908	00025		2003	9	8	AUS20030755      	4	20030728	G	2561		VALVE           	EAAEROMARINE																LIFE JACKET	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					595272					(AUS) LIFE JACKET ORAL INFLATION TUBE JAMMED IN OPEN POSITION. A SECOND JACKET HAD THE SAME PROBLEM WHILE A THIRD JACKET	 FROM THE SAME BATCH DID NOT. JACKETS ARE USED ON DASH-8 AIRCRAFT.																		 
2003090800026	20030908	00026	EU  	2003	9	8	AUS20030756      	1	20030725	G	3241	AE202558	COMPUTER        			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					BRAKE ANTISKID	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) ANTI-SKID FAULT LIGHT ILLUMINATED DURING TAKEOFF ROLL. THE PROBLEM WAS FIXED BY RERACKING THE ANTI-SKID COMPUTER.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003090800027	20030908	00027	CE  	2003	9	8	AUS20030757      	1	20030730	G	5531	51310244	DOUBLER         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILISER FORWARD SPAR DOUBLER ASSEMBLY CONTAINED EXFOLIATION CORROSION.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003090800028	20030908	00028		2003	9	8	AUS20030758      	4	20030729	G	3418	906100004	COMPUTER        			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	STALL WARNING	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 1 STALL WARNING COMPUTER FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800029	20030908	00029	SW  	2003	9	8	AUS20030759      	1	20030731	G	6321	412040301101	PINION GEAR     			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR BRAKE	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 			121  							(AUS) MAIN ROTOR BRAKE QUILL PINION GEAR CRACKED FOR APPROXIMATELY 75 PERCENT ACROSS GEAR FACE. TRANSMISSION CHIP DETECT	OR ACTIVATED. INSPECTION OF CHIP DETECTOR AND FILTER FOUND NO SIGNIFICANT CONTAMINATION.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2003090800030	20030908	00030	NM  	2003	9	8	AUS20030760      	1	20030718	G	2720	2379003001	REGULATOR VALVE 			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	RUDDER CONTROL	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) RUDDER DUAL PRESSURE REGULATOR VALVE FAILED.  SUSPECT SOLENOID FAILURE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800031	20030908	00031	NM  	2003	9	8	AUS20030761      	1	20030720	G	5730		ACCESS PANEL    			BOEING	737   	737376      	       	NM  										FUEL STORAGE	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) FUEL LEAKING FROM WING AND RUNNING OVER UPPER SURFACE OF INBOARD FLAPS. INVESTIGATION FOUND THE FUEL LEAKING FROM 	THE FUEL TANK PANEL ACCESS DOOR AT LOWER WING SKIN CUTOUT NR 7404R LOCATED BETWEEN WBL 157 AND WBL 183.4. THE FUEL TANK 	CUTOUT HAD BEEN RECENTLY REPAIRED DUE TO INTERGRANNULAR CORROSION AT THE REBATE LIP. THE TANK PANEL HAD THEN BEEN REFITT	ED USING EXCESSIVE SEALANT PREVENTING THE CORRECT INSTALLATION OF THE PANEL ACCESS DOOR. PERSONNEL/MAINTENANCE ERROR.			2	L	7	2 	4F			RT	A16WE   					 
2003090800032	20030908	00032	NM  	2003	9	8	AUS20030762      	1	20030705	G	2731	AR7077M3	ACTUATOR        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ELEVATOR TAB	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U0104					(AUS) HORIZONTAL STABILISER TRIM ACTUATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090800033	20030908	00033	WP  	2003	9	8	AUS20030763      	2	20030707	G	8520		CRANKSHAFT      			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	AMTR	C8289	C8289       	GL  	ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CRANKSHAFT FAILED ULTRASONIC INSPECTION. FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/DHE/18 AMDT5.						1	Q	7	1 	3I	3	I	 	A8EU    	A8EU	5	N	EXPP5N	 
2003090800034	20030908	00034	CE  	2003	9	8	AUS20030764      	1	20030723	G	5711	00243001811	SPAR            			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CARRY THROUGH SPAR FORWARD AND AFT SPAR WEBS PN 00243001811 (FORWARD) AND PN 00243001813 (AFT) CRACKED IN LOWER RA	DIUS ON LT SIDE.					1	L	7	2 	3O			 	3A16    		5	C	P22EA	 
2003090800035	20030908	00035	SO  	2003	9	8	AUS20030765      	1	20030731	G	2752	5311281	YOKE            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					TE FLAPS ACT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT INBOARD FLAP ACTUATOR HARDWARE SEIZED DUE TO CORROSION.						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003090800036	20030908	00036	SO  	2003	9	8	AUS20030766      	1	20030731	G	2760	1159SCH2135	SWITCH          			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					DRAG CONTROL SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GROUND SPOILER PRESSURE SWITCH CONNECTOR SEPARATED FROM SWITCH HOUSING AND SHORT CIRCUITING TO GROUND. SWITCH IS L	OCATED IN LT UNDER CARRIAGE BAY.					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2003090800037	20030908	00037	WP  	2003	9	8	AUS20030767      	1	20030708	G	5710	H36831A	STRUCTURE       			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	AMTR	C8289	C8289       	GL  	RT WING	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER RT WING FAULTY. SUSPECT CAUSED BY FAULTY WORKMANSHIP WHEN REPAIRING DAMAGE AND AGED COMPONENTS. PERSONNEL/MA	INTENANCE ERROR. UNAPPROVED PART.					1	Q	7	1 	3I	3	I	 	A8EU    	A8EU	5	N	EXPP5N	 
2003090800038	20030908	00038	EA  	2003	9	8	AUS20030768      	1	20030714	G	5553	C6TFM102227	ADAPTER         			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD VERTICAL FIN ATTACHMENT BRACKET CRACKED THROUGH BOLT MOUNTING HOLE.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003090800039	20030908	00039	CE  	2003	9	8	AUS20030769      	1	20030730	G	2910	AN92440	NUT             			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	HYD SYSTEM	LOOSE           	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) SHUTTLE VALVE ELBOW FITTING JAM NUT VIBRATED LOOSE. LOSS OF FLUID.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P3EA9	 
2003090800040	20030908	00040	NM  	2003	9	8	AUS20030770      	1	20030731	G	7112	A1851	BRACKET         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENG AIR BAFFLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE COOLING SCROLL BRACKET CRACKED FROM NOTCH ON RT SIDE OF THE BRACKET TO THE BOLT HOLE THEN CONTINUING FOR AP	PROXIMATELY 12.7MM (0.5IN) PAST THE BOLT HOLE TOWARDS THE CENTER OF THE BRACKET. FOUND DURING INSPECTION IAW AD/R22/24 A	MDT1.				1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003090800041	20030908	00041	NM  	2003	9	8	AUS20030771      	1	20030717	G	5610		WINDOW          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT DECK SLIDING WINDOW 2R FAILED THE EMERGENCY RELEASE TEST.  INVESTIGATION FOUND THE CAUSE OF THE PROBLEM WAS	 EITHER LACK OF LUBRICANT OR ADJUSTMENT OF THE WINDOW.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090800042	20030908	00042	NM  	2003	9	8	AUS20030772      	1	20030730	G	2497		WIRE            			BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					AC POWER	SHORTED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE GENERATOR A' PHASE FEEDER CABLE CHAFED AND SHORT CIRCUITING TO ENGINE COWL.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2003090800043	20030908	00043	EU  	2003	9	8	AUS20030773      	1	20030804	G	3242	5002572	BRAKE DISC      			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					BRAKE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			2241 							(AUS) DURING OVERHAUL OF BRAKE UNIT IT WAS DISCOVERED THAT TWO DIFFERENT PN`S,  STATOR DISCS WERE FITTED TO THE SAME BRA	KE UNIT. DURING THE INVESTIGATION TO ASCERTAIN IF THIS SITUATION WAS ALLOWABLE IT WAS FOUND THAT PN 5002572 STAMPED ON O	NE OF THE DISCS IS THE PN FOR THE BRAKE UNIT FITTED TO THE FOKKER F28. THE CORRECT DISC PN FOR THE F50 AS STATED IN THE 	CMM IS PN 5002525. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.			2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2003090800044	20030908	00044	EU  	2003	9	8	AUS20030774      	1	20030724	G	3230	184822	HOUSING         			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	LT MLG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR RADIUS ROD BEARING HOUSING INCORRECTLY SWAGED ALLOWING BEARING TO MIGRATE APPROXIMATELY 0.381	MM(0.015IN). FOUND DURING INSPECTION IAW AD/JETSTREAM/96.					2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
2003090800045	20030908	00045	EU  	2003	9	8	AUS20030775      	1	20030731	G	2150	ES611081	MOTOR           			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	AIR CONDITIONER	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			696  							(AUS) FORWARD AIR CONDITIONER ELECTRIC MOTOR FAILED.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2003090800046	20030908	00046	CE  	2003	9	8	AUS20030776      	1	20030728	G	5740	08113509	FITTING         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	WING ATTACH	MISREPAIRED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FORWARD UPPER INBOARD WING ATTACHMENT FITTING HAD THREE BOLTS MISSING. INVESTIGATION FOUND THAT THE FITTING DOE	S NOT LINE UP WITH THE BOLT HOLES DUE TO MISALIGNMENT. FURTHER INVESTIGATION FOUND THAT THE HOLES AND THE ATTACHING CHAN	NELS HAVE BEEN DRILLED OUT BY APPROXIMATELY 0.381MM (0.015IN) TO TRY TO MAKE THE BOLTS FIT. LOOSE BOLTS ALSO FOUND ON RT	 ATTACHMENT FITTING. PERSONNEL/MAINTENANCE ERROR.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003090800047	20030908	00047	SO  	2003	9	8	AUS20030777      	1	20030801	G	3246		WHEEL           			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NLG	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE WHEEL COLLAPSED DURING LANDING.						1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2003090800048	20030908	00048	EU  	2003	9	8	AUS20030778      	1	20030802	G	7722	10151N01T100	INDICATOR       			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					ENGINE	FAILED          	W				O				OTHER                   				E	M		VIBRATION/BUFFET          	OVER TEMP                 		TO	TAKEOFF        	1			AU	S 			30368							(AUS) LT ENGINE ITT INDICATOR FAILED. ANALOG INDICATION DROPPED TO ZERO AND DIGITAL READING WAS FLUCTUATING.						2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2003090800049	20030908	00049	CE  	2003	9	8	AUS20030779      	1	20030725	G	3230	51413121	UPLOCK HOOK     			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	RT MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK HOOK CRACKED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003090800050	20030908	00050	NM  	2003	9	8	AUS20030780      	1	20030718	G	5210		LATCH           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					PAX DOOR	UNLOCKED        	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) DOOR L1 HANDLE MOVED UP CAUSING AIR NOISE DURING FLIGHT. HANDLE MOVED ON SEVERAL OCCASIONS. SUSPECT CAUSED BY INCO	RRECT RIGGING/ADJUSTMENT.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090800051	20030908	00051	EA  	2003	9	8	AUS20030781      	2	20030804	G	7313	L83868A	INJECTOR        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	OBSTRUCTED      	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					L83868A					(AUS) RT ENGINE NR 5 CYLINDER PN LW12966 HAD A BURNED PISTON. PISTON ALSO ERODED AROUND RING LANDS. COMPRESSION LEAKING 	INTO CRANKCASE AND VENTING OIL OVERBOARD VIA BREATHER. INVESTIGATION FOUND THE TORCHING CAUSED BY A PARTIALLY BLOCKED IN	JECTOR NOZZLE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003090800052	20030908	00052	EU  	2003	9	8	AUS20030782      	2	20030731	G	7250	CFM563C1	TURBINE         			BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					NR 1 ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE HPT AND LPT DAMAGED BEYOND LIMITS.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090800053	20030908	00053	CE  	2003	9	8	AUS20030783      	1	20030721	G	3233	1053840001	ACTUATOR        			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR CRACKED AND LEAKING. INVESTIGATION FOUND A CRACK IN THE CYLINDER BODY END CAP THREAD RO	OT LOCATED APPROXIMATELY THREE THREADS FROM THE SEALING CHAMFER.					1	L	7	2 	3O	3	O	 	A29CE   	E286	5	C	P43GL	 
2003090800054	20030908	00054	NM  	2003	9	8	AUS20030784      	1	20030731	G	2761	33205504	ACTUATOR        			BOEING	747   	747438      	       	NM  										NR 10 SPOILER	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			AU	S 					90V1318					(AUS) NR 10 SPOILER PANEL ACTUATOR FAILED.						2	L	7	4 	4F			RT	A20WE   					 
2003090800055	20030908	00055	NM  	2003	9	8	AUS20030785      	1	20030729	G	2822	6072101	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL BOOST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT CENTER BOOST PUMP FAILED RESISTANCE CHECK CARRIED OUT IAW AD/B747/173.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2003090800056	20030908	00056	EU  	2003	9	8	AUS20030786      	1	20030728	G	5521	NB31D088	RIB             			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR END RIB CRACKED. FOUND DURING INSPECTION IAW SB-190.						1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920	 
2003090800057	20030908	00057	NM  	2003	9	8	AUS20030787      	1	20030731	G	2750	285T004953	FSEU            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAPS	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			AU	S 										(AUS) FLAP/SLAT ELECTRONIC UNIT (FSEU) SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003090800058	20030908	00058	NE  	2003	9	8	AUS20030788      	1	20030604	G	2730	CR321443	RIVET           			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ELEVATOR CONTROL	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) ELEVATOR PUSHROD AFT END FITTING RIVETS CORRODED. END FITTING SEPARATED FROM PUSHROD CAUSING LOSS OF CONTROL CAUSI	NG DAMAGE TO AIRCRAFT DURING HEAVY LANDING.					1	H	7	1 	3O	3	O	 	1A13    	1E10	5	C	P920	 
2003090800059	20030908	00059	SO  	2003	9	8	AUS20030789      	2	20030731	G	8530	654966A	CYLINDER        			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1373 							(AUS) ENGINE CYLINDER CRACKED.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2003090800060	20030908	00060	SW  	2003	9	8	AUS20030790      	1	20030712	G	5753	422783	HINGE           			GULSTM	112   	112A        	7630302	SW  	LYC   	O360  	IO360C1D6   	41514	EA  	HARTZL	HCE2Y	HCE2YR1     	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT INBOARD TRAILING EDGE FLAP HINGE BRACKET RIVETS CORRODED AND FAILED. BRACKET WAS HELD ON BY ONLY ONE OF NINE RI	VETS WHICH ALSO FAILED WITH LITTLE EFFORT.					1	L	7	1 	3O	3	O	 	A12SO   	1E10	5	C	P9EA	 
2003090800061	20030908	00061	SW  	2003	9	8	AUS20030791      	1	20030806	G	3234	246006	SELECTOR VALVE  			SWRNGN	SA227 	SA227*      	       	SW  										MLG	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 			7225 							(AUS) LANDING GEAR SELECTOR VALVE FAILED.						2	L	7	2 	4T			RT	A5SW    					 
2003090800062	20030908	00062	SW  	2003	9	8	AUS20030792      	1	20030528	G	3233	ED12758	CLEVIS          			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	LT MLG	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2376 							(AUS) LT MAIN LANDING GEAR ACTUATOR CLEVIS FRACTURED.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2003090800063	20030908	00063	EU  	2003	9	8	AUS20030793      	1	20030807	G	1430	AN37	BOLT            			GIPPLD	GA8   	GA8         	       	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	HORIZONTAL STAB	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) HORIZONTAL STABILISER RT REAR PIVOT ATTACHMENT BOLT SHEARED.						1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2003090800064	20030908	00064	NM  	2003	9	8	AUS20030794      	1	20030530	G	3241	39353	VALVE           			BOEING	737   	737800*     	       	NM  										BRAKE ANTISKID	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR BRAKING SYSTEM ANTI-SKID VALVE FAULTY.  WORKSHOP INVESTIGATION FOUND VALVE STICKING DUE TO FAILU	RE OF SPOOL INNER MOST RUBBER SEAL WHICH WAS SEVERELY ERODED CAUSING RUBBER CONTAMINATION.					2	L	7	2 	4F			RT	A16WE   					 
2003090800065	20030908	00065	NM  	2003	9	8	AUS20030795      	1	20030730	G	5754	015T1507357	SLAT            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LEADING EDGE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NO3 LEADING EDGE SLAT INCORRECT PART. PART NUMBER OF SLAT WAS FOR A 200 MODEL AIRCRAFT INSTEAD OF FOR A 300 MODEL.	 UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003090800066	20030908	00066	CE  	2003	9	8	AUS20030796      	1	20030424	G	2612	302158	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LT ENGINE	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE FIRE WARNINGS. EXTINGUISHER DISCHARGED. NO EVIDENCE OF FIRE FOUND. FAULTY FIRE DETECTORS PN 302158 AND P	N 473275.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003090800067	20030908	00067	EA  	2003	9	8	AUS20030797      	2	20030808	G	7414	M3548	ROTOR           			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4G     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	MAGNETO	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) RT MAGNETO ROTATING MAGNETO DRIVE END SNAPPED IN AREA WHERE IT PASSES THROUGH THE REAR BEARING.						1	L	7	1 	3O	3	O	 	A1CE    	E286	5	N	P4EA	 
2003090800068	20030908	00068	SW  	2003	9	8	AUS20030798      	1	20030801	G	2897	2764034055	WIRE HARNESS    			SWRNGN	SA227 	SA227*      	       	SW  										FUEL BOOST PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BOOST PUMP WIRING HARNESS CHAFED. FOUND DURING INSPECTION IAW AD/SWSA226/88.						2	L	7	2 	4T			RT	A5SW    					 
2003090800069	20030908	00069	CE  	2003	9	8	AUS20030799      	1	20030610	G	5711	5356	SPAR            			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  	AMTR	C8289	C8289       	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING REAR SPAR CONTAINED A NUMBER OF LENGTH WISE CRACKS. FOUND DURING INSPECTION IAW AD/CHA/23.						1	H	7	1 	3O	3	O	 	A21CE   	1E10	5	N	EXPP5N	 
2003090800070	20030908	00070		2003	9	8	AUS20030800      	4	20030809	G	2211	4082260937	PANEL           			BOEING	737   	7377BX      	13844D2	NM  										AUTOPILOT COMPUT	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS)  MODE CONTROL PANEL (MCP) FAULTY. INVESTIGATION FOUND ANALOGUE SENSOR Q145 FAILED. CONNECTORS CONTAMINATED WITH ME	TAL PARTICLES.					2	L	7	2 	4F			RT	A16WE   					 
2003090800071	20030908	00071	NE  	2003	9	8	AUS20030801      	3	20030805	G	6111	BL106LA0	BLADE           			SWRNGN	SA227 	SA227*      	       	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER	ANIMAL STRIKE   	W				O				OTHER                   				C			F.O.D.                    			LD	LANDING        	1			AU	S 			1412 							(AUS) RT PROPELLER BLADE SEVERELY DAMAGED FOLLOWING WALLABY STRIKE. BLADE TIP BENT BACKWARDS ABOUT 50.8MM (2IN) FROM BLA	DE TIP.					2	L	7	2 	4T			RT	A5SW    		6	C	3PNE	 
2003090800072	20030908	00072	CE  	2003	9	8	AUS20030802      	1	20030804	G	2434	ALT9522	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	DC SYSTEM	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					D010314					(AUS) ALTERNATOR FAILED. INVESTIGATION FOUND HIGH RESISTANCE IN BRUSH BLOCK AND GLAZED BRUSHES.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2003090800073	20030908	00073	CE  	2003	9	8	AUS20030803      	1	20030708	G	2430	ALT9522	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	DC SYS	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE ALTERNATOR FAILED. INVESTIGATION FOUND HIGH RESISTANCE IN THE BRUSH BLOCK AND GLAZED BRUSHES.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2003090800074	20030908	00074	CE  	2003	9	8	AUS20030804      	1	20030515	G	2434	ALT9522	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	DC SYS	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE ALTERNATOR FAILED. INVESTIGATION FOUND HIGH RESISTANCEIN THE BRUSH BLOCK AND GLAZED BRUSHES.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2003090800075	20030908	00075	CE  	2003	9	8	AUS20030805      	1	20030515	G	2434	ALT9522	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	DC SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					D010314					(AUS) RT ENGINE ALTERNATOR FAILED. INVESTIGATION FOUND HIGH RESISTANCE IN THE BRUSH BLOCK AND GLAZED BRUSHES.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2003090800076	20030908	00076	NE  	2003	9	8	AUS20030806      	3	20030809	G	6114	R3894123F26	HUB             			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2967 							(AUS) LT PROPELLER HUB HAD TWO CRACK INDICATIONS EMANATING FROM DOWEL HOLES. FOUND DURING INSPECTION IAW AD/PR/33.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P30NE	 
2003090800077	20030908	00077	SO  	2003	9	8	AUS20030807      	1	20030805	G	1430	402377	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	FRACTURED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) MAIN LANDING GEAR TORQUE LINK BOLT FRACTURED CAUSING TORQUE LINK TO FRACTURE AS WELL.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003090800078	20030908	00078	CE  	2003	9	8	AUS20030808      	1	20030821	G	2780	1013800006	SHAFT           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	LE SLAT CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, CREW SELECTED FLAPS '0' BUT NOTED THAT PANEL NR 4 DID NOT APPEAR TO RETRACT ALL THE WAY UP.  FLIGHT 	CONTINUED TO DESTINATION AND FLAPS WERE CONFIRMED TO BE ALL UP EXCEPT NR 4 WHICH WAS HANGING DOWN BY APPROX 4 DEGREES. T	HE .5000 & .7500 PANEL PAIRS ARE PROTECTED BY A 3 TO 6 DEGREE SPLIT IN PAIR WHICH LOCKS SYSTEM, ONLY RESETTABLE ON GROUN	D. MAINT FOUND THAT  FLEXIBLE DRIVE CABLE FOR NR 4 WAS BROKEN INSIDE OF EXTERNAL COVERING. A FACTORY INSTALLED CLAMP APP	EARS TO HAVE BEEN OVERTIGHENED WHICH CAUSED A LOSS OF COVERING INTEGRITY ALLOWING MOISTURE TO ENTER CABLE SHEATH. LOW PO	RTION COLLECTED MOISTURE AND EVENTUALLY CORRODED ENOUGH TO ALLOW TORQUE TO BREAK STRANDS. MFG HAS BEEN NOTIFIED.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003090800079	20030908	00079	EA  	2003	9	8	AUS20030809      	2	20030807	G	7421	RHM38E	SPARK PLUG      			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	NR 1 CYLINDER	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 CYLINDER UPPER SPARK PLUG FAILED DUE TO CRACKED CERAMIC INSULATOR. NR 1 CYLINDER LOWER SPARK PLUG CONTAMINATE	D WITH DEBRIS FROM FAILED UPPER SPARK PLUG.					1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2003090800081	20030908	00081	NE  	2003	9	8	AUS20030810      	1	20030811	G	2497		BUSS BAR        			CONAER	LA4   	LA4250      	5110320	NE  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	DC POWER	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AVIONICS BUSS BAR CONTACTING CIRCUIT BREAKERS CAUSING CONTINUOUS POWER TO BE SUPPLIED TO THE BUSS BAR WITH THE AVI	ONICS MASTERSWITCH TURNED OFF.					1	H	7	1 	3O	3	O	 	1A13    	1E4	5	C	P33EA	 
2003090800082	20030908	00082	EA  	2003	9	8	AUS20030811      	2	20030808	G	7421	RHM38E	SPARK PLUG      			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) LOWER SPARK PLUG CENTER ELECTRODE INSULATOR CRACKED.						1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2003090800083	20030908	00083	GL  	2003	9	8	AUS20030813      	3	20030512	G	6114	D4883C55	HUB             			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			370  							(AUS) PROPELLER HUB CRACKED IN BLADE RETENTION THREADS. FOUND DURING INSPECTION IAW AD/PMC/47 AMDT1.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P5EA	 
2003090800084	20030908	00084	EU  	2003	9	8	AUS20030814      	1	20030813	G	2752	9787320307	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2004 							(AUS) FLAP LINEAR ACTUATOR FAILED BACKLASH TEST IAW AD/PC-12/13. FLAP BACKLASH 0.8128MM (0.032IN). MAXIMUM BACKLASH LIMI	T 0.508MM (0.020IN).					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090800085	20030908	00085	GL  	2003	9	8	AUS20030815      	3	20030625	G	6114	D4349C35	HUB             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			488  							(AUS) PROPELLER HUB CRACKED IN BLADE RETENTION THREADS. FOUND DURING INSPECTION IAW AD/PMC/47 AMDT1.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P21EA	 
2003090800086	20030908	00086	SW  	2003	9	8	AUS20030816      	1	20030811	G	6230	204011401125	RING            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					SWASHPLATE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1361 							(AUS) SWASHPLATE INNER RING LOOSE. INVESTIGATION FOUND GIMBAL BOLTS PNO 212-011-463-001 STEPPED AND BUSHING PNO 204-010-	496-003 MOVING IN INNER RING HOLE. HOLE HAD BEEN ENLARGED BY APPROXIMATELY 0.762MM(0.030IN). SUSPECT CAUSED BY EXCESSIVE	 USE OF SEALANT ON BOLTS DURING ASSEMBLY.				1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2003090800087	20030908	00087	EA  	2003	9	8	AUS20030817      	2	20030729	G	7210	311718001	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENG REDUCTION	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2103 							(AUS) REDUCTION GEARBOX OIL FILTER CONTAMINATED WITH FINE METAL PARTICLES.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2003090800088	20030908	00088	EU  	2003	9	8	AUS20030818      	1	20030729	G	2897		WIRE            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL BOOST PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			555  							(AUS) LT AND RT FUEL BOOST PUMP WIRING CHAFING. FOUND DURING INSPECTION IAW SB PC12/37.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090800089	20030908	00089	EU  	2003	9	8	AUS20030819      	1	20030731	G	2897		WIRE            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL BOOST PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			863  							(AUS) FUEL BOOST PUMP WIRING CHAFING. FOUND DURING INSPECTION IAW SBPC12/37.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090800090	20030908	00090	EU  	2003	9	8	AUS20030820      	1	20030806	G	2897		WIRE            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL BOOST PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3265 							(AUS) FUEL BOOST PUMP WIRING CHAFING NEAR PLUG. FOUND DURING INSPECTION IAW SB PC12/37.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090800091	20030908	00091	NM  	2003	9	8	AUS20030821      	1	20030806	G	2910	82950010109	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	CHAFED          	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) LT LIFT DUMP PRESSURE LINE CHAFED AGAINST SPOILER SELECT PRESSURE LINE DUE TO FAILURE OF GROUND SPOILER PRESSURE L	INE SUPPORT BRACKET. LOSS OF NR 1 SYSTEM HYDRAULIC FLUID.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800092	20030908	00092	CE  	2003	9	8	AUS20030822      	1	20030428	G	5531	1016400109	SPAR            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER REAR SPAR ANGLES PNO 101-640010-9 AND PN 10164001010 CONTAINED INTERGRANNULAR CORROSION. CORRO	SION ORIGINATED FROM RIVETS.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003090800093	20030908	00093	NM  	2003	9	8	AUS20030823      	1	20030812	G	3230	8400105	ACTUATOR        			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG DRAG STRUT	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG STRUT ACTUATOR FAULTY. WORKSHOP INVESTIGATION COULD NOT REPRODUCE THE FAULT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800094	20030908	00094	NM  	2003	9	8	AUS20030824      	1	20030814	G	2421	761574B	IDG             			BOEING	737   	737724      	13844BY	NM  	GE    	CFM56 	CFM567B24   	 	NE  					AC SYSTEM	FAULTY          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		LD	LANDING        	1			AU	S 			991  							(AUS) NR 2 INTEGRATED DRIVE GENERATOR (IDG) FAULTY. INVESTIGATION FOUND PHASE -A- WIRING HAD HIGH RESISTANCE.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003090800095	20030908	00095	GL  	2003	9	8	AUS20030825      	2	20030625	G	7261	6870815	LABYRINTH SEAL  			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	DETERIORATED    	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			725  							(AUS) COMPRESSOR LARGE LABYRINTH SEAL ABRADABLE COATING DEBONDED CAUSING COMPRESSOR LOCKUP.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003090800096	20030908	00096	SO  	2003	9	8	AUS20030826      	1	20030807	G	2721	666600	ARM             			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	RUDDER TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TRIM ARM CRACKED. FOUND DURING INSPECTION IAW AD/PA28/23 AMDT2.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003090800097	20030908	00097	EA  	2003	9	8	AUS20030827      	2	20030807	G	7250	40077	TURBINE WHEEL   			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			996  							(AUS) ENGINE POWER SECTION SEIZED.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003090800098	20030908	00098	NM  	2003	9	8	AUS20030828      	1	20030724	G	5711	6549469	SPAR            			BOEING	737   	737377      	       	NM  										LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING VENT BOX NR 10 STIFFENER CORRODED ON AFT FACE BETWEEN STN 557 & 583. CORROSION WAS FOUND IN 4 AREAS. 3 ARE	AS WERE LOCATED BETWEEN 100MM & 177.8MM OUTBOARD OF WS 557 & WERE APPROX 25.4MM INDIAMETER. ONE AREA LOCATED BETWEEN 304	.8MM & 381MM OUTBOARD OF WS 557 & MEASURED APPROX 100MM BY 38.1MM. LOWER SECTION OF WING REAR SPAR CONTAINED CORROSION A	T 8 FASTENER HOLES IN 254MM SPAN AT WS 583. BLEND DEPTHS WERE BETWEEN 0.0254MM & 0.1778MM VENT BOX CHANNEL CENTER FLANGE	 LOCATED BETWEEN STIFFENERS NR 9 & NR 10 AT WS 557 CONTAINED TWO AREAS OF CORROSION AT INTERSECTION WITH STRINGER 9 & 10	. 2,  CORRODED AREAS WERE APPROX 19.05MM IN DIAMETER.	2	L	7	2 	4F			RT	A16WE   					 
2003090800099	20030908	00099	NM  	2003	9	8	AUS20030829      	1	20030724	G	5711	6545407	SPAR            			BOEING	737   	737376      	       	NM  										RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING VENT BOX CORRODED. NR 10 STIFFENER AFT FACE CORRODED IN AN AREA LOCATED BETWEEN WS563 & WS 578 OVER AN ARE	A APPROX 381MM BY 63.5MM. RT WING UPPER SKIN INNER SURFACE CORRODED BETWEEN WS 557 & 583 IN AN AREA BETWEEN STIFFENER NR	 11 & WING REAR SPAR. 7 PATCHES OF CORROSION WERE FOUND VARYING BETWEEN 25.4MM (1IN) SQUARE & 177.8MM BY 76.2MM. MAX COR	ROSION DEPTH AFTER BLENDOUT RANGED FROM 0.1016MM TO 0.381MM. IN ONE 177.8MM BY 76.2MM PATCH PARTIALLY BENEATH STIFFENER 	NR 10 AT WS 566 TO WS 573 CORROSION DEPTH RANGED FROM 0.127MM TO MAX OF 11.43MM IN ONE VERY SMALL AREA. RT WING REAR SPA	R LOWER SECTION CONTAINED CORROSION LOCATED BETWEEN WS 557 & WS 583.	2	L	7	2 	4F			RT	A16WE   					 
2003090800100	20030908	00100	EU  	2003	9	8	AUS20030830      	1	20030817	G	2760	NAS16126	SEAL            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502*     	41580	EA  					DRAG CONTROL SYS	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LT GROUND SPOILER FLOW VALVE RETURN LINE CONNECTOR O-RING SEAL  LEAKING. GRADUAL LOSS OF APPROXIMATELY TEN LITRES 	OF HYDRAULIC  FLUID.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003090800101	20030908	00101	SW  	2003	9	8	AUS20030831      	1	20030818	G	3213	2751501001	CYLINDER        			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR OLEO FLAT. INVESTIGATION FOUND A FAILURE IN THE CIRCLIP GROOVE LOCATED IN THE LOWER CYLINDER 	ASSEMBLY.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003090800102	20030908	00102	EU  	2003	9	8	AUS20030832      	1	20030523	G	2510	TB1079011315	FITTING         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	COCKPIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR SEAT BELT OUTBOARD FITTINGS CONTAINED EXFOLIATION CORROSION.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2003090800103	20030908	00103	EU  	2003	9	8	AUS20030833      	1	20030525	G	5540	TB1032000111	BRACKET         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RUDDER STRUCTURE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER LOWER HINGE SUPPORT BRACKET CONTAINED EXFOLIATION CORROSION. FOUND DURING INSPECTION IAW AD TB10 31.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2003090800104	20030908	00104	EU  	2003	9	8	AUS20030834      	1	20030403	G	5711	TB2011003100	SPAR            			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING MAIN SPAR WEB CORRODED IN AREA BEHIND RIB PN TB20.11.003.100 LOCATED AT WS 660.						1	L	7	1 	3O	3	O	RT	A51EU   	1E4	5	C	P920	 
2003090800105	20030908	00105	EU  	2003	9	8	AUS20030835      	1	20030724	G	5711	TB1011011101	SPAR            			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING MAIN SPAR UPPER CAP CONTAINED CORROSION ON THE AFT FACE. RT WING LEADING EDGE INTERCOSTAL CONTAINED CORROS	ION ON THE LOWER FLANGE. FOLLOWING REMOVAL OF WINGS FOR REPAIR FURTHER CORROSION WAS FOUND ON THE TOP SURFACE OF THE LT 	AND RT MAIN SPAR UPPER CAP NEAR THE SPAR JOINT.				1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2003090800106	20030908	00106	EU  	2003	9	8	AUS20030836      	1	20030812	G	2822	480500	PUMP            			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUEL BOOST	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FUEL TRANSFER PUMP UNAPPROVED PART. PUMP HAD A LABEL ATTACHED STATING THE MANUFACTURER DOES NOT RECOMMEND USAGE	 IN AIRCRAFT  APPLICATIONS. PUMP WAS SUPPLIED FROM VENDOR UNDER THE CORRECT PN 480500 BUT WAS ACTUALLY PN 476088. FURTHE	R INCORRECT PUMPS WERE FOUND IN STOCK. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.				1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2003090800107	20030908	00107	NM  	2003	9	8	AUS20030837      	1	20030812	G	2621	4739551	CONTROL PANEL   			BOEING	737   	737800*     	       	NM  										NR 1 EXTINGUISH	MALFUNCTIONED   	W				F				ACTIVATE FIRE EXT.      				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					2897					(AUS) UNCOMMANDED OPERATION OF NR 1 AFT CARGO HOLD FIRE EXTINGUISHER. SUSPECT CAUSED BY FAULTY FIRE DETECTION AND EXTING	UISHER CONTROL PANEL.					2	L	7	2 	4F			RT	A16WE   					 
2003090800108	20030908	00108	CE  	2003	9	8	AUS20030838      	1	20030729	G	2822	5100004RX	PUMP            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	FUEL BOOST	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			711  							(AUS) FUEL BOOST PUMP FAILED. INVESTIGATION FOUND ONE VANE MISSING AND SIGNS OF ABRASION.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003090800109	20030908	00109	SO  	2003	9	8	AUS20030839      	2	20030716	G	8550	629243	HOUSING         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENG OIL PUMP	FAULTY          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 			304  							(AUS) RT ENGINE OIL PUMP HOUSING FAULTY.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2003090800110	20030908	00110	NM  	2003	9	8	AUS20030840      	1	20030818	G	2434	ALY8520R	ALTERNATOR      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					DC SYSTEM	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			1159 		AOL0871					(AUS) ALTERNATOR FAILED. INVESTIGATION FOUND BEARING AND DIODE FAILED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003090800111	20030908	00111	NM  	2003	9	8	AUS20030841      	1	20030816	G	2750	S012T236205	LINK            			BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					TE FLAPS	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT INBOARD TRAILING EDGE FLAP LINK SHEARED ON OUTBOARD HINGE. LINK IS LOCATED BETWEEN AFT FLAP AND SLAVE DRIVE BEL	LCRANK.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2003090800112	20030908	00112	CE  	2003	9	8	AUS20030842      	1	20030815	G	5510	04320041	BRACKET         			CESSNA	150   	A150K       	2071824	CE  	CONT  	O200  	O200A       	17020	SO  	AMTR	C8289	C8289       	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER BRACKET CRACKED AROUND NUT PLATES.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	EXPP5N	 
2003090800113	20030908	00113	NM  	2003	9	8	AUS20030843      	1	20030819	G	6310	V31001	LIMIT SWITCH    			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/TRANSMISS	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) ACTUATOR UP LIMIT SWITCH FAILED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003090800114	20030908	00114	EU  	2003	9	8	AUS20030844      	1	20030819	G	5711		SPAR            			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT & RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING MAIN SPARS CONTAINED SEVERE EXFOLIATION CORROSION.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2003090800115	20030908	00115	WP  	2003	9	8	AUS20030845      	1	20030820	G	5711	H35096	SPAR            			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	AMTR	C8289	C8289       	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT LOWER WING FORWARD SPAR CRACKED.						1	Q	7	1 	3I	3	I	 	A8EU    	A8EU	5	N	EXPP5N	 
2003090800116	20030908	00116	WP  	2003	9	8	AUS20030846      	1	20030820	G	5720	H35471A	STRUT           			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	AMTR	C8289	C8289       	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT REAR STRUT CORRODED INTERNALLY AT LOWER END. FOUND DURING X-RAY INSPECTION.						1	Q	7	1 	3I	3	I	 	A8EU    	A8EU	5	N	EXPP5N	 
2003090800117	20030908	00117	WP  	2003	9	8	AUS20030847      	1	20030820	G	5720	H35471A	STRUT           			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	AMTR	C8289	C8289       	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT REAR STRUT CONTAINED INTERNAL CORROSION ON THE LOWER END.  FOUND DURING X-RAY INSPECTION.						1	Q	7	1 	3I	3	I	 	A8EU    	A8EU	5	N	EXPP5N	 
2003090800118	20030908	00118	SO  	2003	9	8	AUS20030848      	1	20030813	G	2731	5299	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ELEVATOR TAB	CONTAMINATED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			1428 							(AUS) ELEVATOR TRIM TAB ACTUATORS CONTAMINATED WITH WATER FROM OVERNIGHT RAIN. WATER FROZE AT ALTITUDE AND LOCKED ELEVAT	OR TRIM.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2003090800119	20030908	00119	EU  	2003	9	8	AUS20030849      	1	20030819	G	7797		WIRE            			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	EGT INDICATOR	CHAFED          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) EGT COMPENSATOR WIRE CHAFED ON PITOT/STATIC LINE LOCATED AT STN 145 LBL 90. CAUSED BY POOR INSTALLATION DURING COM	PLIANCE WITH SB 77-JA910271. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2003090800124	20030908	00124	SW  	2003	9	8	AUS20030850      	1	20030813	G	2131		CONTROLLER      			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	CABIN PRESSURE	FLUCTUATES      	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) CABIN PRESSURISATION FLUCTUATING. INVESTIGATION CONTINUING.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003090800125	20030908	00125	NM  	2003	9	8	AUS20030851      	1	20030815	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/TRANSMISS	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE BELTS STRETCHED BEYOND LIMITS.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003090800126	20030908	00126	NM  	2003	9	8	AUS20030852      	1	20030815	G	6410	A0291	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					TAIL ROTOR BLADE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR BLADE OUTBOARD BEARING LOOSE IN HOUSING.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003090800127	20030908	00127		2003	9	8	AUS20030853      	4	20030812	G	6122	31039391	ELBOW           			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	PROP GOVERNOR	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) RT PROPELLER GOVERNOR OUTLET PRESSURE ELBOW CRACKED IN AREA ABOVE LOCKNUT.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P61GL	 
2003090800128	20030908	00128	EU  	2003	9	8	AUS20030854      	1	20030815	G	5520	TB203421102	FITTING         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR HINGE FITTING BRACKET CRACKED.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2003090800129	20030908	00129	NM  	2003	9	8	AUS20030855      	1	20030821	G	2751	H24EN1036	SWITCH          			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TE FLAPS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP 27.5 SWITCH (S294) FAULTY. FOUND DURING INSPECTION IAW AD/B727/105.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003090800131	20030908	00131	EU  	2003	9	8	AUS20030856      	1	20030814	G	2752	9787320003	PDU             			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP POWER DRIVE UNIT (PDU) FAULTY.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090800132	20030908	00132	NM  	2003	9	8	AUS20030857      	1	20030821	G	2435	23088002B	STARTER GEN     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1	FAULTY          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 STARTER-GENERATOR FAULTY.  STARTER-GENERATOR HAD ONLY JUST BEEN REPLACED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800133	20030908	00133	EU  	2003	9	8	AUS20030858      	2	20030821	G	7200		ENGINE          			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					NR 1	MALFUNCTIONED   	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			35829							(AUS) NR 1 ENGINE MOMENTARILY LOST POWER. POWER LOSS NOTED ON ENGINE GAUGES AND AIRCRAFT YAWED. NO REOCCURRENCE DURING F	LIGHT.  VIBRATION NOTICEABLE AT FLIGHT IDLE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003090800134	20030908	00134	NM  	2003	9	8	AUS20030859      	1	20030820	G	2510	3A2960007011	SEAT            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 			38704							(AUS) CAPTAINS SEAT FAILED. ROLL PINS SHEARED AT OPERATING BAR ASSEMBLIES. SUSPECT CAUSED BY FAILURE OF THE LIFT MECHANI	SM ASSEMBLY.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003090800135	20030908	00135	NM  	2003	9	8	AUS20030860      	1	20030816	G	2434	B040390	DIODE           			ROBSIN	R22   	R22MARINER  	7640115	NM  	LYC   	O320  	O320B2C     	41508	EA  					DC ALTERNATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B040390					(AUS) DC ALTERNATOR DIODE FAILED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003090800136	20030908	00136	EU  	2003	9	8	AUS20030861      	1	20030724	G	3220		LEVER           			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NLG	CORRODED        	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 					DLG0051					(AUS) NOSE LANDING GEAR WOULD NOT RETRACT.  INVESTIGATION FOUND SEVERE CORROSION IN THE FOLLOWING LOWER PLUNGER LEVER AS	SEMBLY COMPONENTS: 1. LEVER PN 2011386052. LEVER PN 2011386063. SHAFT PN 200876762					2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003090800138	20030908	00138	CE  	2003	9	8	AUS20030862      	1	20030818	G	5753	05250011	RIVET           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	TE FLAPS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FLAP INBOARD TRACK LOWER ATTACHMENT RIVETS WORKING.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003090800139	20030908	00139	CE  	2003	9	8	AUS20030863      	1	20030818	G	5753	05250011	RIVET           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	TE FLAP TRACK	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FLAP INBOARD TRACK LOWER ATTACHMENT RIVETS SHEARED. OTHER RIVETS WORKING.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003090800140	20030908	00140	NM  	2003	9	8	AUS20030864      	1	20030820	G	2435		BRUSHES         	LEARSIEGLER 		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1 STARTER GEN	WRONG PART      	W				O				OTHER                   				H	W		ELECT. POWER LOSS-50 PC   	INADEQUATE Q C            		CR	CRUISE         	1			AU	S 			122  		701					(AUS) NR 1 STARTER-GENERATOR FAILED. INVESTIGATION FOUND BRUSHES SHATTERED. SUSPECT BRUSHES WERE TOO LONG. SUSPECT UNAPP	ROVED PART.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800141	20030908	00141	NM  	2003	9	8	AUS20030865      	1	20030827	G	2761	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8106     	2809020	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	DRAG CONTROL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			24622							(AUS) LT OUTBOARD ROLL SPOILER ACTUATOR INTERNAL FAILURE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800142	20030908	00142	NM  	2003	9	8	AUS20030866      	1	20030810	G	2913	165W01020	PUMP            			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563B1US  	 	GL  					HYD SYSTEM	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					A0264					(AUS) STANDBY HYDRAULIC PUMP FAILED. PUMP RUNS BUT FAILS TO PRODUCE PRESSURE. SUSPECT FAILED SHAFT.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003090800143	20030908	00143	NM  	2003	9	8	AUS20030867      	1	20030823	G	2752	1267629	ACTUATOR        			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					TE FLAPS	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			255  							(AUS) FLAP ACTUATOR FAULTY. INVESTIGATION FOUND RECTIFIER AND PRIMARY DRIVE SOLENOID VALVE ASSEMBLY ELECTRICAL CONNECTOR	 NOT FULLY ENGAGED.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2003090800145	20030908	00145	NM  	2003	9	8	AUS20030868      	1	20030822	G	2824	24C2092	TRANSFER VALVE  			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUEL SYSTEM	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN FUEL TANK OUTBOARD PRESSURE FUELING SYSTEM SWING CHECK VALVE NOT FITTED. VALVE COUPLING, BONDING LEAD AND 	BONDING LEAD CLAMP ALSO MISSING.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003090800147	20030908	00147	NM  	2003	9	8	AUS20030869      	1	20030714	G	6310	V31001	LIMIT SWITCH    	ROBSIN      		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					ENGINE/XMSN ACT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CLUTCH ACTUATOR UP LIMIT SWITCH FAILED.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2003090800149	20030908	00149		2003	9	8	AUS20030870      	4	20030815	G	2211	4018369905	COMPUTER        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AUTOPILOT	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLIGHT DIRECTOR COMPUTER FAILED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003101700001	20031017	00001	EU  	2003	10	17	AUS20030871      	1	20030829	G	6520	330A33990320	BEARING         	UROCOP      		SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					T/R GEARBOX	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 					M305					(AUS) TAIL ROTOR GEARBOX PITCH CHANGE BEARING FAILED. PITCH CHANGESHAFT SERVO END NUT AND LOCKWASHER MISSING. SUSPECT FA	ILURE OF BEARING DUE TO CONTAMINATION BY H5606 ACTUATOR OIL CAUSING THE LUBRICATING CHARACTERISTICS OF THE SEALED BEARIN	G TO CHANGE.				2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2003101700004	20031017	00004	NM  	2003	10	17	AUS20030872      	1	20030829	G	5711		SPAR            			BOEING	737   	737377      	       	NM  										LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING VENT TANK SKIN ATTACHMENT FLANGES AND WEBS OF STIFFENERSNO9, NR 10 AND NR 11 CORRODED BEYOND LIMITS. LOWER	 SECTION OF REAR SPAR ALSO CORRODED.					2	L	7	2 	4F			RT	A16WE   					 
2003101700005	20031017	00005	NE  	2003	10	17	AUS20030873      	2	20030829	G	7260	109060166107	GASKET          			AGUSTA	A109  	A109E       	0260119	EU  	PWA   	PW206 	PW206B      	0	NE  					GEARBOX	FAILED          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) NR 2 ENGINE ACCESSORY GEARBOX COVERPLATE GASKET FAILED. LOSS OF ENGINE OIL.						1	G	7	2 	3U	3	U	RT	H7EU    	E42NE				 
2003101700006	20031017	00006	EU  	2003	10	17	AUS20030874      	1	20030828	G	5210		FRAME           			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2L PASSENGER DOOR CRACKED IN UPPER HINGE ARM ATTACHMENT BOSS.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003101700007	20031017	00007	NM  	2003	10	17	AUS20030875      	1	20030802	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					ENGINE/XMSN	STRETCHED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE BELTS STRETCHED.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2003101700008	20031017	00008	CE  	2003	10	17	AUS20030876      	1	20030826	G	5311	1014300263	FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAMES PN 1014300263 LT AND PN 10143002611 RT CRACKED.  FOUND DURING INSPECTION IAW AD/BEECH200/65 AMDT1.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003101700009	20031017	00009	NM  	2003	10	17	AUS20030877      	1	20030828	G	6510	B2243	DRIVE SHAFT     			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					TAIL ROTOR	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR DRIVESHAFT BENT.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2003101700010	20031017	00010		2003	10	17	AUS20030878      	4	20030830	G	3452	G699010	CONTROL PANEL   			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ATC TRANSPONDER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1738					(AUS) ATC TRANSPONDER CONTROL PANEL FAULTY. PANEL WAS FOUND TO BE EXCESSIVELY HOT TO TOUCH.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003101700012	20031017	00012	SO  	2003	10	17	AUS20030879      	2	20030815	G	8550	642336	REGULATOR       			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	FOD             	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 			929  							(AUS) LT ENGINE OIL PRESSURE REGULATOR CONTAMINATED WITH FOD BETWEEN PLUNGER AND SEAT.  LOSS OF ENGINE OIL PRESSURE.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2003101700013	20031017	00013	SW  	2003	10	17	AUS20030880      	1	20030830	G	2731	DL5040M6	ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ELEVATOR TAB	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7467 							(AUS) PITCH TRIM ACTUATOR ROD ENDS HAD EXCESSIVE FREE PLAY. FOUND DURING INSPECTION IAW AD/SWSA226/68A5.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2003101700014	20031017	00014	CE  	2003	10	17	AUS20030881      	1	20030901	G	5554	10563000011	HINGE           			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	RUDDER TAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER HINGE BRACKET CORRODED (RUSTED).						1	L	7	2 	3O	3	O	 	A29CE   	E286	5	C	P43GL	 
2003101700015	20031017	00015	NM  	2003	10	17	AUS20030882      	1	20030831	G	3244	B7502	TIRE            			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NR 5F TIRE TREAD SEPARATED FROM CASING. TIRE REMAINED INFLATED.  NIL DAMAGE EVIDENT TO REST OF AIRCRAFT.  SUSPECT 	CAUSED BY FAILURE OF TREAD TO BOND TO CASING DURING RETREAD.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2003101700016	20031017	00016	SW  	2003	10	17	AUS20030883      	1	20030830	G	5514	2743062913	FITTING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	H/S ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER PITCH TRIM ACTUATOR UPPER ATTACHMENT BRACKETS CRACKED ALONG LUG. FURTHER INVESTIGATION REVEA	LED THAT THERE WAS CONSIDERABLE CLEARANCE BETWEEN THE BUSHINGS AND ACTUATOR ROD ENDS WHICH RESULTED IN THE LUGS BEING ST	RESSED WHEN THE ATTACHING HARDWARE WAS TORQUED UP. COMPARISON WITH REPLACEMENT BRACKET FOUND THAT THE BUSHES INSTALLED I	N BOTH BRACKETS WERE TOO SHORT THEREFORE ALLOWING THE LUGS TO BE STRESSED INWARDS PRIOR TO CLAMPING ONTO THE ROD END. TH	IS CAUSED BOTH BRACKETS TO CRACK ALONG THE OUTBOARD LUG. FOUND DURING INSPECTION IAW AD/SWSA226/68.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2003101700017	20031017	00017	SW  	2003	10	17	AUS20030884      	1	20030827	G	2910	2781032075	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC PRESSURE LINE LOCATED IN AREA BELOW PILOTS RUDDER PEDALS CRACKED AND LEAKING. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2003101700018	20031017	00018	NM  	2003	10	17	AUS20030885      	1	20030802	G	6520	B0211	SHAFT           	ROBSIN      		ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					T/R GEARBOX	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0317					(AUS) TAIL ROTOR GEARBOX OUTPUT SHAFT BENT.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2003102000001	20031020	00001		2003	10	20	AUS20030886      	4	20030718	G	3425	4019700902	INDICATOR       			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FO ATTITUDE DIR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 			24989							(AUS) FIRST OFFICER'S ATTITUDE DIRECTOR INDICATOR (ADI) FAILED.  INVESTIGATION FOUND FAULT WAS CAUSED BY A DRY SOLDER JO	INT ON THE MULTI-LAYER FLEX CABLE CONNECTING MODULES A1-A4.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003102000002	20031020	00002	CE  	2003	10	20	AUS20030887      	1	20030901	G	7714	1143800075	INDICATOR       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE RPM	INOPERATIVE     	W				O				OTHER                   				E	I		VIBRATION/BUFFET          	FLT. ATTITUDE INST.       		NR	NOT REPORTED   	1			AU	S 			450  		8501136					(AUS) LT ENGINE PERCENT RPM INDICATOR FAULTY.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2003102000003	20031020	00003	NM  	2003	10	20	AUS20030888      	1	20030830	G	7830		THRUST REVERSER 			BOEING	767   	767338      	1385151	NM  	RROYCE	RB211 	RB211524*   	 	NE  					LT ENGINE	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) LT ENGINE THRUST REVERSER FAULTY. LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2003102000009	20031020	00009	GL  	2003	10	20	AUS20030889      	3	20030903	G	6114		INSERT          			PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	PROPELLER HUB	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE CRANKSHAFT FLANGE CRACKED AND LEAKING AROUND FACE. CRACK ORIGINATED AT DOWEL HOLE AND PROGRESSED APPROXIMAT	ELY 75 PERCENT OF THE WAY AROUND THE FLANGE.  INVESTIGATION FOUND THAT THE PROPELLER HAD BEEN MODIFIED BY THE FITMENT OF	 A STEEL INSERT IN THE MAIN BORE OF THE HUB. THE INSERT DID NOT HAVE THE REQUIRED INTERNAL CHAMFER FOR CORRECT MATING WI	TH THE PROPELLER FLANGE SO THAT WHEN THE PROPELLER BOLTS WERE TORQUED THE RESULTING BENDING LOADS CAUSED THE FLANGE TO C	RACK.  PERSONNEL /MAINTENANCE ERROR. UNAPPROVED PART.		1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2003102000010	20031020	00010	CE  	2003	10	20	AUS20030890      	1	20030821	G	2434	DOFF10300BR	ALTERNATOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  	AMTR	C8289	C8289       	GL  	DC SYSTEM	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) ALTERNATOR FAILED IN FLIGHT. LIMITED INFORMATION PROVIDED.						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	EXPP5N	 
2003102000011	20031020	00011	EA  	2003	10	20	AUS20030891      	2	20030813	G	8540	76118	SPACER          			AMTR  	VANS  	RV8         	       	GL  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	TACH DRIVE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL FILTER CONTAMINATED WITH BRONZE PARTICLES.  INVESTIGATION FOUND THE TACHOMETER DRIVESHAFT SPACER HAD CO	ME LOOSE FROM THE CAMSHAFT AND WAS WEARING ON THE SHAFT ROLL PIN.					1	L	7	1 	3O	3	O	NT	EXPA1L71	1E4	5	C	P920	 
2003102000012	20031020	00012	NE  	2003	10	20	AUS20030892      	2	20030905	G	7321	1853M56P07	HMU             			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL CONTROL	FAULTY          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) ENGINE HYDROMECHANICAL UNIT (HMU) FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003102000014	20031020	00014	CE  	2003	10	20	AUS20030893      	1	20030904	G	5741	8178610	BOLT            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	WING TO BODY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AFT UPPER WING ATTACHMENT BOLT CRACKED IN THREADED AREA.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2003102000015	20031020	00015	NM  	2003	10	20	AUS20030894      	1	20030824	G	3230	83231027001	CONNECTING ROD  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LT MAIN LANDING GEAR CONNECTING ROD BROKEN AT NECK END.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102000016	20031020	00016	NM  	2003	10	20	AUS20030895      	1	20030903	G	5730		PANEL           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					LT WING	MISINSTALLED    	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT OUTBOARD SURGE TANK ACCESS DOOR INCORRECTLY FITTED. FUEL LEAKING. DOOR WAS DAMAGED DUE TO BEING FITTED 180 DEGR	EES OUT.DOOR IS FITTED WITH ONE RAISED NUT WHICH FITS INTO ACORRESPONDING NOTCH TO PREVENT INCORRECT FITMENT. PERSONNEL/	MAINTENANCE ERROR.				2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2003102000017	20031020	00017	CE  	2003	10	20	AUS20030896      	1	20030304	G	7120		MOUNT           			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A1B    	41514	EA  	MCAULY	2D34C	2D34C9      	GL  	ENGINE	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT ENGINE MOUNTS FITTED.  MANUFACTURER'S ILLUSTRATED PARTS CATALOGUE (IPC) INDICATES INCORRECT NUMBER. CORR	ECT PART NUMBER AND INSTALLATION PROCEDURES ARE FOUND IN THE MM.  IPC INCORRECT.					1	L	7	1 	3O	3	O	 	A1CE    	1E10	5	C	P7EA	 
2003102000018	20031020	00018	NM  	2003	10	20	AUS20030897      	1	20030906	G	2761	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	DRAG CONTROL	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 			5062 							(AUS) LT OUTBOARD SPOILER ACTUATOR BODY FAILED. LOSS OF NR 2 HYDRAULIC SYSTEM FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102000019	20031020	00019	NE  	2003	10	20	AUS20030898      	2	20030908	G	7310	0311007710	LINE            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE FUEL DIST	CRACKED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 			99999							(AUS) NR 1 ENGINE FUEL INJECTOR FUEL SUPPLY PIPE CRACKED IN FLARE.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2003102000020	20031020	00020	NM  	2003	10	20	AUS20030899      	1	20030907	G	3244	324525172	TIRE            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					RT NLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) RT NOSE WHEEL TIRE BLOWN OUT. LT TIRE FAILED DUE TO OVERLOAD.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003102000021	20031020	00021	EU  	2003	10	20	AUS20030900      	1	20030908	G	5711	635	SPAR            			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING MAIN SPAR AFT LOWER WEB CONTAINED EXFOLIATION CORROSION.   CORROSION WAS MAINLY LOCATED IN AREA ADJACENT T	O MAIN LANDING GEAR LEG.					1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2003102000022	20031020	00022	EU  	2003	10	20	AUS20030901      	1	20030908	G	5711	770	SPAR            			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT & RT WINGS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING MAIN SPAR AFT LOWER WEBS CONTAINED EXFOLIATION CORROSION. CORROSION MAINLY LOCATED IN AREA ADJACENT	 TO MAIN LANDING GEAR.					1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2003102000023	20031020	00023	NM  	2003	10	20	AUS20030902      	1	20030909	G	5730	6545407	SKIN            	AAR         		BOEING	737   	737377      	       	NM  										RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING VENT TANK UPPER SKIN LOWER SURFACE CORRODED. LOWER CHORD OF REAR SPAR AND WEBS OF STIFFENERS NR 9 AND NR 1	0 ALSO CORRODED.					2	L	7	2 	4F			RT	A16WE   					 
2003102000024	20031020	00024	SW  	2003	10	20	AUS20030903      	1	20030730	G	6210	206015001115	BLADE           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					MAIN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) M/R BLADE UPPER SKIN TORN IN AREA LOCATED AT BLADE TIP IMMEDIATELY INBOARD OF TIP CAP. INSP FOUND SKIN HAD LIFTED 	IMMEDIATELY BEHIND SPAR &TORN IN SPAN WISE DIRECTION FROM TIP TO APPROX 50.8MM INBOARD OF TIP & 25.4MM AFT OF SPAR.SKIN 	& ADHESIVE HAD SEPARATED FROM THE CORE MATERIAL WITH EVIDENCE OF CORROSION UNDER THE ADHESIVE. BLADE R & FWDED TO REPAIR	 FACILITY. FURTHER INSP AT REPAIR FACILITY REVEALED OTHER AREAS OF CORROSION AND PITTING IN GRIP DOUBLERS ON LOWER SURFA	CE OF BLADE & ALSO IN AREA UNDER THE LATCH PLATES BONDED TO GRIP TANGS. PHOTOGRAPHS REVEALED CORROSION IN DOUBLERS START	ING IN MIDDLE OF BONDED JOINT & NOT EMANATING FROM MOISTURE INGRESS FROM EDGE OF JOINT AS WOULD NORMALLY BE EXPECTED.	1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003102000025	20031020	00025	GL  	2003	10	20	AUS20030904      	3	20030624	G	6114	3AF32C87JN	HUB             													MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CRACKED IN NR 3 BLADE SOCKET. CRACK LOCATED AT APPROXIMATELY 11 O'CLOCK POSITION. FOUND DURING INSPE	CTION IAWAD/PMC/41.															5	C	P22EA	 
2003102000026	20031020	00026	GL  	2003	10	20	AUS20030906      	3	20030625	G	6114	D2A34C580	HUB             													MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CRACKED AT APPROXIMATELY 12 O'CLOCK POSITION IN BOTH BLADE SOCKETS. FOUND DURING INSPECTION IAW AD/P	MC/41.															5	C	P3EA	 
2003102000027	20031020	00027	CE  	2003	10	20	AUS20030907      	1	20030908	G	3230	AN2415M	BOLT            			BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ2Y	BHCJ2YF2    	GL  	MLG	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH LANDING GEAR PUSH-PULL ROD BOLT INCORRECTLY FITTED. BOLT HEADWAS INSTALLED IN THE WRONG DIRECTION CAUSING HEAD 	TO FOUL ONINBOARD END RIB IN THE LH WHEEL WELL. CORRECT FITMENT DIRECTION OF THE BOLT WAS CLEARLY PLACARDED. PERSONNEL/M	AINTENANCEERROR.				1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P37EA	 
2003102000028	20031020	00028	NM  	2003	10	20	AUS20030908      	1	20030905	G	2710		AILERON         			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AILERON CONTROL	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 										(AUS) AILERON CONTROL SYSTEM NOTCHY' WITH A CONSIDERABLE DEAD BAND IN  THE CENTRE.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003102000029	20031020	00029	GL  	2003	10	20	AUS20030909      	3	20030802	G	6114	2A36C23CP	HUB             													MCAULY	2A36C	2A36C23     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CONTAINED CRACK INDICATIONS IN THE NR 2 BLADESOCKET AT THE 2.30 O'CLOCK AND 6 O'CLOCK POSITIONS.																5	C	P880	 
2003102000030	20031020	00030	GL  	2003	10	20	AUS20030910      	3	20030906	G	6114	3AF32C87N1	HUB             													MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CONTAINED CRACK INDICATIONS IN THE NR 2 BLADE SOCKET AT THE 1.30 O'CLOCK POSITION.																5	C	P22EA	 
2003102000031	20031020	00031	GL  	2003	10	20	AUS20030911      	3	20030606	G	6114	D2A34C58NO	HUB             													MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CONTAINED CRACK INDICATIONS IN THE NR 2 BLADE SOCKET AT THE 5.30 O'CLOCK POSITION.																5	C	P3EA	 
2003102000032	20031020	00032	CE  	2003	10	20	AUS20030912      	1	20030908	G	5310		STRUCTURE       			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	TAILBOOM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT TAILBOOM LOWER STRUCTURE CORRODED IN AREA OF ATTACHMENT TO WING STRUCTURE. CORROSION IS BOTH INTERNAL AND EXTER	NAL. RT TAILBOOM CONTAINED INTERNAL CORROSION ONLY.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2003102000033	20031020	00033	CE  	2003	10	20	AUS20030913      	1	20030905	G	5711	05230202	SPAR CAP        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING UPPER SPAR CAP ANGLE CORRODED. ANGLE IS LOCATED IN FUEL TANK BAY.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003102000034	20031020	00034	EA  	2003	10	20	AUS20030914      	2	20030902	G	8520	76220P02	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			866  							(AUS) CRANKCASE THROUGH BOLT LOCATED AT NO1 CYLINDER FORWARD LOWERPOSITION SHEARED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003102000035	20031020	00035		2003	10	20	AUS20030915      	4	20030908	G	3425	LMD5001P	RELAY           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	INTEGRATED FLIGH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3933 							(AUS) EFIS RELAY PN 3921K10 CORRODED. INVESTIGATION FOUND EXTENSIVE CORROSION THROUGHOUT THE RELAY MODULE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2003102000036	20031020	00036	NM  	2003	10	20	AUS20030916      	1	20030910	G	2824		PLUG            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TRANSFER VAVLE	LOOSE           	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) FUEL CROSSFEED VALVE PLUG LOOSE.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003102000037	20031020	00037	SW  	2003	10	20	AUS20030917      	1	20030905	G	6410	406016100119	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR BLADE CRACKED CHORDWISE FROM WATER DRAIN HOLE LOCATED AT BLADE ROOT. CRACK LENGTH APPROXIMATELY 40MM (1	.57IN).					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003102000038	20031020	00038	EA  	2003	10	20	AUS20030918      	2	20030908	G	7322	25765362	FCU             			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1137 							(AUS) FUEL CONTROL UNIT AIR CHAMBER CONTAMINATED WITH FUEL.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003102000039	20031020	00039	SW  	2003	10	20	AUS20030919      	1	20030910	G	2932	SS10127	SWITCH          			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD PRESSURE	FAULTY          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LT HYD SYS LOW PRESSURE WARNING SWITCH FAULTY.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003102000040	20031020	00040		2003	10	20	AUS20030920      	4	20030911	G	3416	28702552	ALTIMETER       			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKCPIT	FAILED          	W				O				OTHER                   				I			FLT. ATTITUDE INST.       			CL	CLIMB          	1			AU	S 			5    							(AUS) PILOTS ALTIMETER FAILED. ALTIMETER HAD BEEN INSTALLED FOR 5.4 HOURS SINCE REPAIR.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003102000041	20031020	00041	NM  	2003	10	20	AUS20030921      	1	20030911	G	5330		STRAP           			BOEING	747   	747400      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CIRCUMFERENTIAL CRACK IN SKIN PRODUCTION JOINT SPLICE STRAP ATLOCATED AT BS 2181 BETWEEN STRINGERS 1R AND 4R. CRAC	K LENGTH APPROXIMATELY 762MM (30IN).					2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2003102000042	20031020	00042	EU  	2003	10	20	AUS20030922      	1	20030910	G	3230	SA7670006123	HOSE            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502*     	41580	EA  					LT MLG	RUPTURED        	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LT MLG RETRACTION JACK FLEXIBLE HYDRAULIC HOSE RUPTURED. LOSS OF GREEN SYSTEM HYD FLUID.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003102000043	20031020	00043	CE  	2003	10	20	AUS20030923      	1	20030909	G	3233	12810013	HOUSING         			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					2428					(AUS) LANDING GEAR ACTUATOR BODY CRACKED. FOUND DURING INSPECTION IAW CESSNA SB 01-2 REV1.						1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2003102000045	20031020	00045	CE  	2003	10	20	AUS20030924      	1	20030908	G	2435	03600918	BEARING         	LUCAS       		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					STARTER-GEN	COLLAPSED       	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			812  		97249					(AUS) LT ENGINE STARTER-GENERATOR DRIVE END BEARING COLLAPSED.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003102000047	20031020	00047	CE  	2003	10	20	AUS20030925      	1	20030915	G	2933	511700712	SIGHT GLASS     			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	HYD QTY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC SYSTEM SIGHT TUBE CRACKED. LOSS OF HYDRAULIC FLUID.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003102000048	20031020	00048	CE  	2003	10	20	AUS20030927      	1	20030903	G	5343	12116013	ATTACH FITTING  			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR OUTBOARD ATTACHMENT FITTING CRACKED IN AREAOF UPPER REAR RADIUS.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003102000049	20031020	00049	SW  	2003	10	20	AUS20030928      	1	20030910	G	2770	2770066001	PLUNGER         			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GUST LOCK DAMPER	FRACTURED       	W				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) RUDDER GUST LOCK PLUNGER BROKEN INTO TWO PARTS.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003102000051	20031020	00051	EU  	2003	10	20	AUS20030929      	1	20030912	G	2424	700122490420	GCU             			BAG   	BAE146	BAE146300A  	1500267	EU  										AC GENERATOR	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 										(AUS) NR 1 GENERATOR CONTROL UNIT (GCU) FAILED.						2	H	7	4 	4F			RT	A49EU   					 
2003102000052	20031020	00052	NM  	2003	10	20	AUS20030930      	1	20030911	G	5754	114T41457	BOLT            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LE SLAT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEADING EDGE SLAT BOLT FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003102000053	20031020	00053	CE  	2003	10	20	AUS20030931      	1	20030904	G	2434	DOFF10300B	ALTERNATOR      			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	DC SYSTEM	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					A122793					(AUS) ALTERNATOR FAILED.						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL	 
2003102000054	20031020	00054	SW  	2003	10	20	AUS20030932      	1	20030910	G	2434	902014	BEARING         			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	DC GENERATOR	DISINTEGRATED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			1290 							(AUS) ALTERNATOR SLIP RING END ROLLER BEARING DISINTEGRATED. ROTORPOLED.						1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2003102000055	20031020	00055	CE  	2003	10	20	AUS20030933      	1	20030829	G	8011	NONEINIPC	SCREW           	LYC         		CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	STARTER	LOOSE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 					A112529					(AUS) STARTER MOTOR INTERMEDIATE BEARING SECURING SCREW FELL OUT ANDSHORT CIRCUITED FIELD WINDINGS.						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL	 
2003102000057	20031020	00057	CE  	2003	10	20	AUS20030934      	1	20030913	G	3297	320559	WIRE            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					MLG CONNECTOR	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR SAFETY SWITCH WIRE LOOSE AT INLINE CONNECTOR.						1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2003102000059	20031020	00059	NE  	2003	10	20	AUS20030935      	2	20030909	G	7261	120032	OIL SYSTEM      		PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	LOW             	W				O				OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE OIL SYSTEM LOW QUANTITY. TWO QUARTS OF ENGINE OIL WERE ADDED TO TOP UP OIL QUANTITY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100001	20031021	00001	NM  	2003	10	21	AUS20030936      	1	20030913	G	2720		PEDAL           			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					RUDDER CONTROL	VIBRATES        	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) MODERATE VIBRATION FELT THROUGH RUDDER PEDALS. INVESTIGATION COULD FIND NO FAULT.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003102000065	20031020	00065	GL  	2003	10	20	AUS20030937      	3	20030915	G	6114	D42145	HUB             			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	PROPELLER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1394 							(AUS) PROPELLER HUB DAMAGED IN AREA OF PRELOAD PLATE SHELF. PROPELLER HAD BEEN REMOVED AND DISMANTLED FOLLOWING GROUND S	TRIKE.					1	L	7	2 	3O	3	O	 	A29CE   	E286	5	C	P43GL	 
2003102000066	20031020	00066	EU  	2003	10	20	AUS20030938      	1	20030916	G	3213	200920604	NUT             			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR STRUT SHOCK ABSORBER GLAND NUT CRACKED.  FOUND DURING INSPECTION IAW AD/SD3-60/42.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2003102000067	20031020	00067	SW  	2003	10	20	AUS20030939      	1	20030912	G	2770	2770066001	PLUNGER         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	GUST LOCK DAMPER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER GUST LOCK ASSEMBLY PLUNGER CORRODED, BENT AND CRACKED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2003102000069	20031020	00069	GL  	2003	10	20	AUS20030940      	1	20030912	G	5310	12843003	DOOR FRAME      	AAR         	12843004    	CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENTRY DOOR FRAME PN 12843003 AND RT ENTRY DOOR FRAME PN 12843004 CRACKED IN AREA ABOVE SIDE WINDOW. CRACK LENGT	HS APPROXIMATELY 457.2MM (18IN).					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P36EA	 
2003102000070	20031020	00070	SW  	2003	10	20	AUS20030941      	1	20030915	G	2460	ANL400	CURRENT LIMITER 			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	DC POWER	MISMANUFACTURED 	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AU	S 										(AUS) CURRENT LIMITER INCORRECTLY ASSEMBLED CAUSING ARCING AT THE CONNECTION POINT. PERSONNEL/MAINTENANCE ERROR.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003102000071	20031020	00071	NM  	2003	10	20	AUS20030942      	1	20030917	G	7830		WARNING LIGHT   			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					THRUST REVERSER	INTERMITTENT    	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 2 ENGINE THRUST REVERSER UNLOCK LIGHT ILLUMINATING INTERMITTENTLY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003102000072	20031020	00072	CE  	2003	10	20	AUS20030943      	1	20030830	G	5610	10138402518	WINDSHIELD      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RT WINDSHIELD INNER PANE SHATTERED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	P60GL	 
2003102000073	20031020	00073	EU  	2003	10	20	AUS20030944      	1	20030911	G	5302	355A2305000407	SKIN            			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAILBOOM SKIN CRACKED IN AREA LOCATED AFT OF THE TAIL ROTOR GEARBOX. CRACK ORIGINATED FROM RIVET HOLE IN TAIL ROTO	R GEARBOX COWL BRACKET. CRACKED HAD EXTENDED AFT FOR APPROX 50.8MM TO 76. 2MM (2IN TO 3IN) IN AN AREA NOT NORMALLY VISIB	LE WITH VERTICAL STABILIZERS INST CRACK HAD ALSO EXTENDED FWD&DOWN APPROXIMATELY 50.8MM TO 76.2MM (2IN TO 3IN). 1ST 25.4	MM (1IN) OR SO NOT NORMALLY VISIBLE WITH TAIL ROTOR GEARBOX COWL INST LAST 25.4MM (1IN) OR SO OF CRACKIN FWD & DOWN DIRE	CTION HAD PROTUDED FROM BENEATH TAIL ROTOR GEARBOX COWL MAKING IT VISIBLE DURING DAILY INSPECTION. TAIL ROTOR GEARBOX CO	WL ATTACHMENT BRACKET HAD BEEN FRETTING ON TAILBOOM SKIN CAUSING THE 1/8IN RIVETS (3OFF) TO BECOME LOOSE. AFTMOST HOLE F	1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2003102000074	20031020	00074	CE  	2003	10	20	AUS20030945      	1	20030908	G	3213		STRUT           			CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR LEGS CORRODED.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2003102000075	20031020	00075	NM  	2003	10	20	AUS20030948      	1	20030917	G	2612		FIRE LOOP       			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					NR 1 ENGINE	FAULTY          	W				O				OTHER                   				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) NR 1 ENGINE FIRE DETECTION SYSTEM FAULTY. NR 1 ENGINE LOOP `B`  FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003102000076	20031020	00076	NE  	2003	10	20	AUS20030949      	3	20030911	G	6114	A163372	O-RING          			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	PROP HUB	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) RT PROPELLER LEAKING OIL. THE PROPELLER HAD JUST BEEN REMOVED AND REFITTED FOLLOWING REPAIR TO THE DEICE BOOT. NEW	 O-RING SEALS PN A163372 HAD BEEN FITTED AT INSTALLATION. THOROUGH INVESTIGATION COULD FIND NO REASON FOR THE LEAK.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2003102000077	20031020	00077	NM  	2003	10	20	AUS20030950      	1	20030917	G	2612		FIRE LOOP       			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					NR 1 ENGINE	FAULTY          	W				O				OTHER                   				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) NR 1 ENGINE FIRE DETECTION SYSTEM FAULTY. INVESTIGATION FOUND A HIGH RESISTANCE (2000OHMS) SENSOR IN LOOP B'.  MEL	 APPLIED BUT  DEFECT OCCURRED DURING NEXT TAKEOFF AND ON SUBSEQUENT FAULT FINDING GROUND RUN. SEE MDR 03/0948 FOR RELATE	D INCIDENT.				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003102000079	20031020	00079	EU  	2003	10	20	AUS20030952      	2	20030912	G	7200	MAKILA1A1	ENGINE          			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					NR 1	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			833  							(AUS) NR 1 ENGINE REAR BEARING CHIP DETECTOR CONTAMINATED WITH METAL.						2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2003102000080	20031020	00080	NE  	2003	10	20	AUS20030953      	2	20030710	G	7230		COMPRESSOR      			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ENGINE	FOD             	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE VIBRATION DURING START. POWER BELOW LIMITS. FOUND DURING TEST RUNS FOLLOWING CENTRIFUGAL COMPRESSOR CHANGE 	DUE TO FOD.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2003102000081	20031020	00081	EA  	2003	10	20	AUS20030954      	2	20030917	G	7322	2576535A	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CONTROL UNIT CONTAMINATED IN IMPACT DIAPHRAGM CHAMBER AND TUBES. VENTURI ALSO CONTAMINATED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003102000084	20031020	00084	EA  	2003	10	20	AUS20030955      	2	20030919	G	7414	3170	MAGNETO         			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3X	HCA3XK2     	GL  	LT ENGINE	OUT OF ADJUST   	W				O				OTHER                   				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE LOST OIL PRESSURE. INSPECTION FOUND NR 4 PISTON FAILED DUE TO DETONATION. FURTHER INVESTIGATION FOUND TH	E LT MAGNETO TIMING HAD MOVED FROM 20 DEGREES BTDC TO 35 DEGREES BTDC. MAGNETO GASKET HAD BEEN REPLACED AT PREVIOUS PERI	ODIC INSPECTION.				1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P913	 
2003102000085	20031020	00085	SO  	2003	10	20	AUS20030956      	1	20030921	G	3222	79110003	FORK            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	NLG	FRACTURED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR FORK FRACTURED. NLG COLLAPSED CAUSING PROPELLER TO DIG INTO GROUND.						1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2003102000087	20031020	00087	CE  	2003	10	20	AUS20030957      	1	20030923	G	5753		RIB             			BEECH 	76    	76          	1153005	CE  										TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT TRAILING EDGE FLAP SUPPORT RIBS CORRODED AT HINGE BRACKETS. MINOR EXTERNAL CORROSION ON FLAPS RESULTED I	N FLAPS BEING DE-SKINNED AND INSPECTED UPON WHICH THE SERIOUS INTERNAL CORROSION WAS FOUND.					1	L	7	2 	3O			 	A29CE   					 
2003102000088	20031020	00088	CE  	2003	10	20	AUS20030958      	1	20030924	G	5753		RIB             			BEECH 	76    	76          	1153005	CE  										TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT TRAILING EDGE FLAP SUPPORT RIBS CORRODED AT HINGE BRACKETS. MINOR EXTERNAL CORROSION ON FLAPS RESULTED I	N FLAPS BEING DE-SKINNED AND INSPECTED UPON WHICH THE SERIOUS INTERNAL CORROSION WAS FOUND.					1	L	7	2 	3O			 	A29CE   					 
2003102000090	20031020	00090	EU  	2003	10	20	AUS20030959      	1	20030919	G	2611	7211121100	SMOKE DETECTOR  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	E/E BAY	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) AVIONICS RACK SMOKE WARNING ACTIVATION. INVESTIGATION FOUND NOEVIDENCE OF SMOKE BUT REPLACED THE SMOKE DETECTOR AS	 APRECAUTION. SUSPECT CAUSED BY DUST CONTAMINATION OF SMOKE DETECTOR.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2003102000093	20031020	00093	NM  	2003	10	20	AUS20030960      	1	20030920	G	5532	593614318	SKIN            			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILISER TIP SKIN CRACKED IN TWO PLACES ON RT SIDE. ONE CRACK WAS APPROXIMATELY 304.8MM IN LENGTH RUNNI	NG VERTICALLY ALONG THE RIVET LINE JUST AFT OF STA YV157 APPROXIMATELY 12.7MM AFT OF HORIZONTAL STABILIZER RUB STRIP. TH	E SECOND CRACK WAS APPROXIMATELY 25.4MM IN LENGTHAND RUNS HORIZONTALLY ALONG THE LOWER EDGE OF THE SKIN. BOTH CRACKS GO 	COMPLETELY THROUGH THE SKIN AND ARE VISIBLE ON THE INSIDE OF THE STABILIZER.			2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2003102000102	20031020	00102	SO  	2003	10	20	AUS20030961      	2	20030815	G	8530	AEC631397A	CYLINDER HEAD   			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 			1101 							(AUS) ENGINE CYLINDER HEAD CRACKED.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2003102000103	20031020	00103	CE  	2003	10	20	AUS20030962      	1	20030915	G	5753	16911000045	HINGE           			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP HINGES CRACKED ON BOTH EDGES.						1	L	7	1 	3O	3	O	 	A1CE    	1E10				 
2003102000105	20031020	00105	EU  	2003	10	20	AUS20030963      	1	20030916	G	5520	5551012001	STRUCTURE       			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ELEVATOR DAMAGED. LT HINGE POINT ON HORIZONTAL STABILISER ANDTRIM ACTUATOR ALSO DAMAGED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003102000107	20031020	00107	EU  	2003	10	20	AUS20030964      	1	20030912	G	5610	1172465509	WINDOW          			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					COCKPIT	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) COPILOTS SLIDING WINDOW SEPARATED AND CONTACTED TAIL ROTOR. WINDOW HAD BEEN ACCIDENTALLY CONTACTED BY PASSENGER. C	AUSED BYCHANNEL SURROUND DISBONDING AFTER ACCIDENTAL CONTACT. EXAMINATION OF THE CHANNEL SURROUND REVEALED APPROXIMATELY	 33 PERCENT OF TOTAL LENGTH (50 PERCENT OF TOP AND BOTTOM SIDES) DISBONDED FROM MAIN WINDOW. THE CHANNEL MATERIAL APPEAR	ED STIFF AND HAD A POWDERY EXTERIOR SURFACE.			1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2003102000108	20031020	00108	EU  	2003	10	20	AUS20030965      	1	20030919	G	2611	721112211000	SMOKE DETECTOR  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	E/E BAY	CONTAMINATED    	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) AVIONICS RACK SMOKE DETECTOR ACTIVATED. INVESTIGATION COULD FIND NO EVIDENCE OF SMOKE. SUSPECT DETECTOR CONTAMINAT	ED WITH DUST.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2003102000109	20031020	00109	EU  	2003	10	20	AUS20030967      	1	20030917	G	5711	635	SPAR            			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT UPPER AFT REAR SPAR WEB CONTAINED LIGHT EXFOLIATION CORROSIONIN AREA ADJACENT TO MAIN LANDING GEAR. FOUND DURIN	G INVESTIGATION FOLLOWING CORROSION IN RT WING SPAR. SEE MDR 03/0900.					1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2003102000110	20031020	00110	EA  	2003	10	20	AUS20030968      	2	20030923	G	8520	LW16812	TAPPET          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAPPETS (8OFF) CRACKED AROUND INSIDE OF PLUNGER BODY.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003102000112	20031020	00112	SO  	2003	10	20	AUS20030969      	1	20030926	G	2140	88D951	TUBE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATER	CRACKED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			AU	S 			105  							(AUS) CABIN HEATER COMBUSTION TUBE CRACKED AND BULGING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003102000113	20031020	00113	SO  	2003	10	20	AUS20030970      	1	20030919	G	3213	4025700	TORQUE LINK     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR TORQUE LINK LUG BROKEN.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003102000114	20031020	00114	CE  	2003	10	20	AUS20030971      	1	20030829	G	2910	572700219	LINE            			CESSNA	441   	441         	2076020	CE  										HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC LINE LOCATED IN LT WING ADJACENT TO RESERVOIR CRACKED AND LEAKING.						1	L	7	2 	3T			RT	A28CE   					 
2003102000121	20031020	00121	NM  	2003	10	20	AUS20030972      	1	20030920	G	3830	26513116	DRAIN VALVE     			BOEING	737   	73733A      	1384673	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FWD LAVATORY	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD TOILET DRAIN VALVE LEAKING. FOUND DURING INSPECTION IAW AD/737/25.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003102000122	20031020	00122	SW  	2003	10	20	AUS20030973      	1	20030915	G	3233	ED12758	PIN             			GULSTM	680   	680FL       	0141608	SW  	LYC   	O720  	IO720B1B    	41546	EA  	HARTZL	HCB3Z	HCB3Z302    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR ACTUATOR CLEVIS PINS CRACKED.						1	H	7	2 	3O	3	O	 	2A4     	1E15	5	C	P907	 
2003102000124	20031020	00124	SW  	2003	10	20	AUS20030974      	1	20030815	G	3233	ED12758	PIN             			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR ACTUATOR CLEVIS PINS CRACKED.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2003102000126	20031020	00126	SW  	2003	10	20	AUS20030975      	1	20030916	G	3233	ED12758	PIN             			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR ACTUATOR CLEVIS PINS CRACKED.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2003102000127	20031020	00127	SW  	2003	10	20	AUS20030976      	1	20030903	G	3233	ED12758	PIN             			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR ACTUATOR CLEVIS PINS CRACKED.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2003102000128	20031020	00128	CE  	2003	10	20	AUS20030977      	1	20030918	G	2822	2B729	PUMP            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	FUEL BOOST	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT AND RT AUXILIARY FUEL BOOST PUMP PRESSURES BELOW REQUIRED LIMITS. ONE OF THE REPLACEMENT PUMPS ALSO HAD LOW FUE	L PRESSURE.					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2003102000130	20031020	00130	NM  	2003	10	20	AUS20030978      	1	20030921	G	2150	78279018	ACM             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CABIN COOLING	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			3998 							(AUS) AIR CYCLE MACHINE FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102000132	20031020	00132	CE  	2003	10	20	AUS20030979      	1	20030924	G	5753		RIB             			BEECH 	76    	76          	1153005	CE  										TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT TRAILING EDGE FLAP SUPPORT RIBS CORRODED AT HINGE BRACKETS. MINOR EXTERNAL CORROSION ON FLAPS RESULTED I	N FLAPS BEING DESKINNED AND INSPECTED UPON WHICH THE SERIOUS INTERNAL CORROSION WAS FOUND.					1	L	7	2 	3O			 	A29CE   					 
2003102000133	20031020	00133	CE  	2003	10	20	AUS20030980      	1	20030924	G	5753		RIB             			BEECH 	76    	76          	1153005	CE  										TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT TRAILING EDGE FLAP SUPPORT RIBS CORRODED AT HINGE BRACKETS. MINOR EXTERNAL CORROSION ON FLAPS RESULTED I	N FLAPS BEING DESKINNED AND INSPECTED UPON WHICH THE SERIOUS INTERNAL CORROSION WAS FOUND.					1	L	7	2 	3O			 	A29CE   					 
2003102000135	20031020	00135	CE  	2003	10	20	AUS20030981      	1	20030924	G	5753		RIB             			BEECH 	76    	76          	1153005	CE  										TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT TRAILING EDGE FLAP SUPPORT RIBS CORRODED AT HINGE BRACKETS. MINOR EXTERNAL CORROSION ON FLAPS RESULTED I	N FLAPS BEING DESKINNED AND INSPECTED UPON WHICH THE SERIOUS INTERNAL CORROSION WAS FOUND.					1	L	7	2 	3O			 	A29CE   					 
2003102000136	20031020	00136	CE  	2003	10	20	AUS20030982      	1	20030925	G	5753		RIB             			BEECH 	76    	76          	1153005	CE  										TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT TRAILING EDGE FLAP SUPPORT RIBS CORRODED AT HINGE BRACKETS. MINOR EXTERNAL CORROSION ON FLAPS RESULTED I	N FLAPS BEING DESKINNED AND INSPECTED UPON WHICH THE SERIOUS INTERNAL CORROSION WAS FOUND.					1	L	7	2 	3O			 	A29CE   					 
2003102000138	20031020	00138	SO  	2003	10	20	AUS20030983      	2	20030520	G	8530	SA10204	EXHAUST VALVE   			CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300B       	17022	SO  	MCAULY	1A170	1A170DM     	GL  	ENGINE	STICKING        	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			264  							(AUS) ENGINE EXHAUST VALVE STUCK OPEN. TWO OTHER VALVES ALSO STICKING.DURING RECTIFICATION FOR THE STICKING VALVES IT WA	S NOTICED THAT THE CARBURETTOR BUTTERFLY SHAFT TO BUSHING FITTING SEEMED EXCESSIVE (EXCESSIVE END FLOAT AND AXIAL WEAR).					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P857	 
2003102000139	20031020	00139	EU  	2003	10	20	AUS20030984      	1	20030922	G	5610	NP1701022	WINDSHIELD      			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 			15409							(AUS) COPILOTS B-WINDSHIELD OUTER PLY CRACKED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003102000141	20031020	00141	WP  	2003	10	20	AUS20030985      	1	20030919	G	6320		FREEWHEEL UNIT  	HUGHES      		HUGHES	269   	269A        	4470402	WP  	LYC   	O360  	HIO360B1A   	41514	EA  					M/R GEARBOX	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1265545					(AUS) FREEWHEEL UNIT LOOSE.						1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2003110600027	20031106	00027	EU  	2003	11	6	AUS20030986      	2	20030919	G	7230	1590M2P01	FAN BLADE       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1228 							(AUS) NR 2 ENGINE FAN BLADE FRACTURE SURFACE CONTAINED EVIDENCE OF FATIGUE CRACKING.  ENGINE AND FAN BLADE HAD BEEN INVO	LVED IN A BAT STRIKE AND THE ENGINE HAD BEEN REMOVED FOR WORKSHOP INSPECTION.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110600028	20031106	00028	NM  	2003	11	6	AUS20030987      	1	20030919	G	2434	23088002A	STARTER GEN     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	DC SYSTEM	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			1191 							(AUS) NR 1 DC STARTER-GENERATOR SUSPECT FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003110600029	20031106	00029	NM  	2003	11	6	AUS20030988      	1	20030919	G	2730	65C2546515	CONTROL UNIT    			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ELEVATOR	FAULTY          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) ELEVATOR FEEL AND CENTERING UNIT SPRING BROKEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110600030	20031106	00030	NM  	2003	11	6	AUS20030989      	1	20030922	G	2820	316A101045	LINE            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE FUEL FEED LINE FROM FRONT SPAR TO PYLON LEAKING.  LINE WAS WORN IN AREA OF O RING SEAL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110600031	20031106	00031	NM  	2003	11	6	AUS20030990      	1	20030921	G	5330		SKIN            			BOEING	747   	747*        	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CONTAINED SCORES AND GOUGES AT BUTT JOINTS BS2181,BS1961, BS1741, BS1480, STRINGER 4L TO STRINGER 45	.					2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2003110600032	20031106	00032	NM  	2003	11	6	AUS20030991      	1	20030923	G	2910	S332A00513	FITTING         			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYD SYSTEM	SPLIT           	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE HYDRAULIC PUMP PRESSURE LINE QUICK DISCONNECT FITTING SPLIT.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110600033	20031106	00033	WP  	2003	11	6	AUS20030992      	2	20030820	G	7260	8968085	GEAR            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TACHOMETER GEAR HAD UNAPPROVED REPAIR CARRIED OUT IN THREADED AREA. LACK OF INTERFERENCE FIT BETWEEN GEAR AND BEAR	ING PN 358272. PN 3103580-3 NR 2 IDLER GEAR HOUSING SUSPECT UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PAR	T. UNAPPROVED REPAIR.				2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003110600035	20031106	00035	NE  	2003	11	6	AUS20030993      	2	20030922	G	7530		CONTROLLER      			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211*      	54555	NE  					COMPRESSOR BLEED	FAULTY          	W				O				OTHER                   				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE STALLED. ENGINE MOVED INTO RED ZONE (115 PERCENT N1). INVESTIGATION FOUND VIGV CONTROLLER FAULTY. LT AND	 RT VIGV ACTUATORS ALSO FAULTY.					2	L	7	2 	4F	4	F	RT	A1NM    	A12EU				 
2003111000001	20031110	00001	WP  	2003	11	10	AUS20030994      	2	20030820	G	7260	3103580	HOUSING         			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GEARBOX	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE IDLER GEAR HOUSING SUSPECT UNAPPROVED PART.  HOUSING WAS A LOOSE FIT ONTO THE BACK OF THE DIAPHRAGM.  PERSO	NNEL/MAINTENANCE ERROR. UNAPPROVED PART. SEE ALSO M OR D 03/0992 FOR ADDITIONAL INFORMATION.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003110600053	20031106	00053	NM  	2003	11	6	AUS20030995      	1	20030518	G	2761	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	DRAG CONTROL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING OUTBOARD ROLL SPOILER ACTUATOR LEAKING.   INVESTIGATION FOUND ACTUATOR CRACKED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003110600174	20031106	00174	NE  	2003	11	6	AUS20030996      	2	20030918	G	7530		ACTUATOR        			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					COMPRESSOR BLEED	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE VARIABLE BLADE VALVE ACTUATORS AT THE 4 O'CLOCK AND 5 O'CLOCK POSITIONS BINDING AND INTERNAL HEXAGONAL	 DRIVES WORN.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003110700002	20031107	00002	SO  	2003	11	7	AUS20030997      	2	20030920	G	7310		HOSE            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE FUEL	LOOSE           	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 										(AUS) STRONG SMELL OF FUEL IN COCKPIT. INVESTIGATION FOUND A LOOSE HOSE NUT CONNECTION ON THE FCU AND A LOOSE HOSE ON TH	E FUEL STRAINER ASSEMBLY. PERSONNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003110700003	20031107	00003	SW  	2003	11	7	AUS20030998      	1	20030917	G	6220	206010101129	YOKE            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR HEAD	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1059 		JILM11383					(AUS) MAIN ROTOR BLADE GRIP BEARINGS CAUSED BRINELLING ON YOKE ARMS.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003110700004	20031107	00004	NM  	2003	11	7	AUS20030999      	1	20030930	G	2760	NAS16126	O-RING          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	DRAG CONTROL SYS	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) GROUND SPOILER PRESSURE LINE TO OUTBOARD GROUND ACTUATOR TEE FITTING O-RING BLEW OUT.  LOCK NUT WAS FOUND TO BE LO	OSE.  LOSS OF HYDRAULIC FLUID.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003110700005	20031107	00005	SO  	2003	11	7	AUS20031000      	1	20030930	G	5346		STRUCTURE       			PIPER 	PA36  	PA36300     	7103612	SO  	LYC   	O720  	IO720D1C    	41546	EA  	HARTZL	HCC2Y	HCC2YF1     	GL  	NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT STRUCTURE CRACKED IN TOP RT ENGINE MOUNT ATTACHMENT AREA WHEN LOOKING FORWARD.  FOUND DURING INSPECTION I	AW AD/PA36/20AMDT1.					1	L	7	1 	3O	3	O	 	A10SO   	1E15	5	C	P920	 
2003110700006	20031107	00006	NM  	2003	11	7	AUS20031001      	1	20030926	G	3010		ANTI-ICE SYSTEM 			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					RT WING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING ANTI-ICE SYSTEM OPERATING WITH ANTI-ICE SWITCH IN THE OFF POSITION.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110700007	20031107	00007	NM  	2003	11	7	AUS20031002      	1	20030928	G	3520		HOSE            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					PASSENGER OXYGEN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER SERVICE UNIT (PSU) OXYGEN HOSE SEVERED AT OXYGEN GENERATOR FITTING ON THE PSU.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110700042	20031107	00042	EA  	2003	11	7	AUS20031003      	2	20030929	G	7322	D2782	CONTROL BOX     			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					GOVERNOR	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) GOVERNOR CONTROL BOX FAILED.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003110700043	20031107	00043	NM  	2003	11	7	AUS20031004      	1	20030928	G	2424	948F4583	GCU             			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AC SYS	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			AU	S 										(AUS) APU GENERATOR CONTROL UNIT (GCU) FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110700044	20031107	00044	NM  	2003	11	7	AUS20031005      	1	20030928	G	2497		CONNECTOR       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AC POWER	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 GENERATOR DISCONNECT PLUG CONNECTOR BURNT.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110700045	20031107	00045	NM  	2003	11	7	AUS20031006      	1	20030901	G	3260		SENSOR          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) LT MAIN LANDING GEAR REAR DOOR SENSOR OUT OF ADJUSTMENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003110700046	20031107	00046	EA  	2003	11	7	AUS20031007      	2	20031001	G	7414	S6LSC204T	MAGNETO         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) MAGNETO FAULTY.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003110700047	20031107	00047	SO  	2003	11	7	AUS20031008      	2	20030917	G	7310	124F0014CR0140	HOSE            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE FUEL	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL PUMP TO FCU HOSE LOOSE AND LEAKING.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P36EA	 
2003110700048	20031107	00048	NM  	2003	11	7	AUS20031009      	1	20030928	G	5210		ROLLER          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					PAX DOOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR L1 HAD THE LATCHING ROLLERS OUTSIDE OF THE LATCHING CAM WITH THE DOOR CLOSED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110700049	20031107	00049	EU  	2003	11	7	AUS20031010      	1	20031002	G	5610	NP1701012	WINDSHIELD      			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RT WINDSCREEN (A) PANEL CRACKED IN OUTER PLY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003110700050	20031107	00050	SO  	2003	11	7	AUS20031011      	1	20030930	G	2730	PE6700255	CHAIN           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ELEVATOR CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL CHAIN BROKEN.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2003110700051	20031107	00051	NE  	2003	11	7	AUS20031012      	3	20030809	G	6111	66071326610	BLADE           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2959 							(AUS) PROPELLER BLADE BUTT CRACKED IN OUTER BLADE SLEEVE.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P30NE	 
2003110700052	20031107	00052	EU  	2003	11	7	AUS20031013      	1	20031002	G	3260	602EN556B	SWITCH          			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK SWITCH FAILED.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2003110700053	20031107	00053	NM  	2003	11	7	AUS20031014      	1	20031003	G	3213		SEAL            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					MLG STRUT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR OLEO STRUT SEALS LEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003110700054	20031107	00054	NM  	2003	11	7	AUS20031015      	1	20031002	G	2760	BACB28BA1012063	BUSHING         			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					DRAG CONTROL SYS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GROUND SPOILER BUSHES (2 OFF) MISSING FROM NUT END OF NR 1 AND NR 12 SPOILERS. THIS IS A NEW AIRCRAFT AND WAS DELI	VERED FROM THE FACTORY WITH THE BUSHINGS MISSING. MANUFACTURING ERROR.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003110700056	20031107	00056	SW  	2003	11	7	AUS20031016      	1	20031005	G	2497		WIRE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	HARNESS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CHAFED WIRES WITHIN LOOM LOCATED IN RT ENGINE NACELLE.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2003110700057	20031107	00057	NM  	2003	11	7	AUS20031017      	1	20031006	G	2121	732591C	COOLING FAN     			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AIR DISTRIBUTION	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 					2339					(AUS) FORWARD EQUIPMENT COOLING FAN FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003110700058	20031107	00058	SO  	2003	11	7	AUS20031018      	1	20031003	G	2730	710563	SPRING          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) ELEVATOR DOWN SPRING BROKEN APPROXIMATELY FIVE COILS FROM THE FORWARD ATTACHMENT MOUNTING POINTS.  INSPECTION USIN	G AN EIGHT POWER MAGNIFYING GLASS REVEALS INTERGRANNULAR CORROSION.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003110700060	20031107	00060	NM  	2003	11	7	AUS20031019      	1	20031003	G	3246	3515	BOLT            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211*      	54555	NE  					NR 2 WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 MAIN WHEEL ASSEMBLY TIE BOLT (1OFF) SHEARED AND MISSING.						2	L	7	4 	4F	4	F	RT	A20WE   	A12EU				 
2003110700074	20031107	00074	NM  	2003	11	7	AUS20031020      	1	20031003	G	2520	207810112561	SEAT BELT       			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					CABIN	FOULED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) PASSENGERS SEAT BELT LOCATED AT 11K BECAME JAMMED BETWEEN SEAT DURING FLIGHT CAUSING SKYBED' SEAT TO FAIL ELECTRIC	ALLY.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2003110700075	20031107	00075	NE  	2003	11	7	AUS20031021      	2	20031007	G	7250	BRH19759	PLUG            	RROYCE      		BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					TURBINE SECTION	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					41131191					(AUS) RT ENGINE HAD FIVE HP TURBINE STAGE 1 COVER PLATE LOCKING PLUGS PN BRH19759 AND THEIR RESPECTIVE RETAINING STRIPS 	PN BRH19728 MISSING. FOUND DURING BOROSCOPE INSPECTION IAW RR SB-BR700-72-900330.					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2003110700076	20031107	00076	NE  	2003	11	7	AUS20031022      	2	20031006	G	7250	BHR19759	PLUG            	RROYCE      		BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					TURBINE SECTION	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					41131188					(AUS) LT ENGINE HAD THREE HP TURBINE STAGE 1 COVER PLATE LOCKING PLUGS PN  BRH19759 AND THEIR RESPECTIVE RETAINING STRIP	S PN BRH19728 MISSING.  FOUND DURING BOROSCOPE INSPECTION IAW RR SB-BR700-72-900330.					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2003110700077	20031107	00077	NE  	2003	11	7	AUS20031023      	2	20031007	G	7250	BHR19729	PLUG            	RROYCE      							RROYCE	BR700 	BR700715A130	 	NE  					TURBINE SECTION	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					41131119					(AUS) ENGINE HAD FIVE HP TURBINE STAGE 1 COVER PLATE LOCKING PLUGS PN  BRH19759 AND THEIR RESPECTIVE RETAINING STRIPS PN	 BRH19728 MISSING.  FOUND DURING BOROSCOPE INSPECTION IAW RR SB-BR700-72-900330.  ENGINE WAS A SPARE UNIT AND NOT FITTED	 TO AN AIRCRAFT.									4	F			E00061EN				 
2003110700078	20031107	00078	EU  	2003	11	7	AUS20031024      	1	20031004	G	3251	AIR860021	SELECTOR VALVE  			BAG   	JETSTM	JETSTM3107  	1500215	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	STEERING UNIT	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 					LK9004521					(AUS) STEERING SELECTOR VALVE INTERNAL FAULT.						2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2003110700079	20031107	00079	EU  	2003	11	7	AUS20031026      	1	20031009	G	5610	7256100501	WINDSHIELD      			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LT WINDSHIELD CRACKED FROM BOTTOM RT SIDE. THE CRACK QUICKLY EXTENDED THE WIDTH OF THE WINDSHIELD.   INVESTIGATION	 FOUND THAT THE WINDSHIELD WAS CRACKED IN THE OUTER NON-STRUCTURAL LAYER OF GLASS.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2003110700080	20031107	00080	EU  	2003	11	7	AUS20031027      	2	20031001	G	7250		TURBINE BLADES  			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			40232							(AUS) NUMEROUS HPT BLADE CRACKS (RADIAL TIP CRACK TURNING AXIAL) WERE FOUND WITH THE POTENTIAL FOR BLADE TIP CORNER SEPA	RATION.  FOUND DURING ROUTINE BOROSCOPE INSPECTION.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110700081	20031107	00081	NE  	2003	11	7	AUS20031028      	2	20031004	G	7200		ENGINE          			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211*      	54555	NE  					RIGHT	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE FAILED TO ACHIEVE TAKEOFF POWER.  THRUST SHORTFALL REQUIRED WAS 1.73 BUT ONLY 1.71 WAS ACHIEVED WITH ASS	OCIATED EICAS MESSAGE RT ENGINE RPM LIMIT. TAKE OFF WAS ABORTED AT 110 KNOTS GROUND SPEED.					2	L	7	2 	4F	4	F	RT	A1NM    	A12EU				 
2003110700082	20031107	00082	CE  	2003	11	7	AUS20031029      	1	20030916	G	5340	642985	BRACKET         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	DC GENERATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR CAPACITOR BRACKET FAILED ALLOWING CAPACITOR TO SHORT CIRCUIT ON POSITIVE PLATE.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2003110700083	20031107	00083	EA  	2003	11	7	AUS20031030      	2	20031002	G	7200		ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	LEFT	FLUCTUATES      	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE TORQUE FLUCTUATIONS. FUEL FLOW, N1 AND ITT STABLE.  GROUND RUN CARRIED OUT.  UNABLE TO FAULT.   DEFECT N	OT CONFIRMED.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2003110700084	20031107	00084	CE  	2003	11	7	AUS20031031      	1	20030925	G	3222	AN557	BOLT            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG	SEPARATED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE WHEEL AXLE BOLT NUT SEPARATED ALLOWING AXLE CAP TO FALL OFF THE NOSE WHEEL ASSEMBLY.  DURING LANDING THE NOSE	 WHEEL CAME OUT OF THE FORK AND WEDGED UNDER THE NOSE WHEEL FAIRING.  THE NOSE WHEEL TIRE HAD BEEN CHANGED APPROXIMATELY	 10 HOURS PREVIOUSLY.				1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2003110700092	20031107	00092	GL  	2003	11	7	AUS20031032      	3	20030915	G	6114	E6605	HUB             			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			987  					772145		(AUS) PROPELLER HUB CRACKED IN AREA OF FOURTH THREAD AT THE 2 O'CLOCK POSITION. CRACK LENGTH APPROXIMATELY 25.4MM (1IN).						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2003110700093	20031107	00093	NM  	2003	11	7	AUS20031033      	1	20031004	G	2810	EC776	SEALANT         			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUEL CELL	DETERIORATED    	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 FUEL TANK LEAKING.  INVESTIGATION FOUND TANK WING TO CENTERBOX LOWER ATTACHMENT FITTING INBOARD FASTENER SEAL	ANT LIFTING.  REMOVED SEALANT FOUND TO HAVE INCLUSIONS AND VOIDS RESULTING FROM IMPROPER CLEANING AT PREVIOUS SEALANT AP	PLICATION.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003110700094	20031107	00094	SO  	2003	11	7	AUS20031034      	1	20031013	G	5514	AN17532A	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR BALANCE WEIGHT ATTACHMENT BOLTS AND ACTUATOR COLLAR ATTACHMENT BOLTS CORRODED (RUSTED). BOLT PART NUMBE	RS PN AN175-32A AND PN AN175-33A.					1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2003110700095	20031107	00095	EA  	2003	11	7	AUS20031035      	2	20031007	G	7322	2576535A	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			323  				70255902			(AUS) FUEL CONTROL UNIT IMPACT DIAPHRAGM CHAMBER CONTAMINATED WITH FUEL/OIL.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003110700096	20031107	00096	CE  	2003	11	7	AUS20031036      	1	20030925	G	5520		RIVET           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HORIZONTAL STABILIZER ELEVATOR HINGE ATTACHMENT RIVETS (3OFF) LOOSE. RIVETS WERE CHERRY-MAX TYPE.  FOUND DURING	 INSPECTION IAW AD/CESSNA400/012 AMDT3.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	3PNE	 
2003110700097	20031107	00097	NE  	2003	11	7	AUS20031037      	2	20031013	G	7261		ENGINE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  						LEAKING         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) ENGINE SHUT DOWN DUE TO TOTAL LOSS OF OIL.  DETAILED INVESTIGATION COULD FIND NO SOURCE OF LEAK.  ENGINE HAD ONLY 	BEEN FITTED THREE DAYS PREVIOUSLY FOLLOWING HSI SO WAS REMOVED AND FORWARDED TO MANUFACTURER FOR FURTHER INVESTIGATION/R	EPAIR.				2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003110700110	20031107	00110	NM  	2003	11	7	AUS20031038      	1	20031007	G	7603	T3A4	CONTROL CABLE   	RROYCE      		BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					POWER LEVER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO3 ENGINE THRUST CABLE T3A-4 WORN AT LOCATION ILES 564. FOUNDDURING INSPECTION IAW EI 743-076-0002R02 (FAA AD 200	0-05-30 AND CASA AD/B747/229).					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2003110700111	20031107	00111	NM  	2003	11	7	AUS20031039      	1	20031010	G	3244	161U00011	TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					MLG	DEFLATED        	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 			873  							(AUS) LT BODY GEAR NR 3 AFT OUTBOARD TIRE DEFLATED.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2003110700112	20031107	00112	NM  	2003	11	7	AUS20031040      	1	20031012	G	5753		PLATE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAP	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT INBOARD FLAP INBOARD SEAL PLATE SEPARATED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003110700113	20031107	00113	NM  	2003	11	7	AUS20031041      	1	20031013	G	5280		STRUCTURE       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					MLG DOOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOOR DAMAGED.  FURTHER INVESTIGATION FOUND LT MAIN LANDING GEAR BRAKE SWIVEL BRACKET AND OUTE	R DOOR ATTACHMENT FITTING LOOSE WITH TWO BOLTS SHEARED AND ANOTHER TWO BOLTS LOOSE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003111000006	20031110	00006	EU  	2003	11	10	AUS20031043      	1	20031012	G	2410	5243212137	DRIVE SHAFT     			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	SHEARED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					248471					(AUS) NR 2 GENERATOR DRIVESHAFT SHEARED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003111000007	20031110	00007	SO  	2003	11	10	AUS20031044      	1	20030930	G	2750	1642300	BELLCRANK       			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320D1A     	41508	EA  	HARTZL	HC82X	HC82XL2     	GL  	TE FLAPS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP BELLCRANK CORRODED.  FOUND DURING INSPECTION IAW AD/PA23/50.						1	L	7	2 	3O	3	O	 	1A10    	E274	5	C	P878	 
2003111000008	20031110	00008	SO  	2003	11	10	AUS20031045      	1	20030930	G	2750	1763400	TORQUE TUBE     			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320D1A     	41508	EA  	HARTZL	HC82X	HC82XL2     	GL  	TE FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP TORQUE TUBE WORN BEYOND LIMITS.  FOUND DURING INSPECTION IAWAD/PA23/89.						1	L	7	2 	3O	3	O	 	1A10    	E274	5	C	P878	 
2003111000009	20031110	00009	NM  	2003	11	10	AUS20031046      	1	20031014	G	2510		SEAT            			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					COCKPIT	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CAPTAINS SEAT VERTICAL ADJUSTMENT COLLAPSED.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003111000010	20031110	00010		2003	11	10	AUS20031047      	4	20031014	G	8300	L168468A	GEAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ACCESSORY DRIVE	BROKEN          	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE FAILED.  INVESTIGATION FOUND ACCESSORY CASE DRIVE GEARS WITH BROKEN TEETH.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003111000011	20031110	00011		2003	11	10	AUS20031048      	4	20031013	G	2370		CVR             			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT VOICE RECORDER BULK ERASE FUNCTION INOPERATIVE. FOUND DURING INSPECTION IAW AD/REC/1 REQUIREMENT 2.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2003111000012	20031110	00012	NM  	2003	11	10	AUS20031049      	1	20031013	G	2437	522778	MONITOR         			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	DC INDICATING SY	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			7891 							(AUS) DC POWER MONITOR FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003111000013	20031110	00013	NM  	2003	11	10	AUS20031050      	1	20031014	G	2120		ODOR            			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					AIR CONDITIONING	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) OIL ODOR IN CABIN.  LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003111000014	20031110	00014	EU  	2003	11	10	AUS20031051      	2	20031009	G	7230	857592	SEAL            			BOEING	737   	737*        	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			22249							(AUS) NR 1 ENGINE FORWARD STATIONARY AIR/OIL SEAL FAILED IN THE AREA OF ADHESION OF THE ABRADABLE MATERIAL TO THE SEAL A	SSEMBLY.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003111000015	20031110	00015	EA  	2003	11	10	AUS20031052      	1	20030815	G	2823	TC17300	SELECTOR VALVE  			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	FUEL SYSTEM	WRONG PART      	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		TO	TAKEOFF        	1			AU	S 										(AUS) FUEL SELECTOR VALVE INCORRECTLY ASSEMBLED.  VALVE HAD BEEN FITTED WITH SHAFT 180 DEGREES OUT OF POSITION.  PERSONN	EL/MAINTENANCE ERROR.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P28EA	 
2003111000016	20031110	00016	NM  	2003	11	10	AUS20031053      	1	20031016	G	2761	NAS161210	PACKING         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					DRAG CONTROL ACT	DISTORTED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 4 LT OUTBOARD SPOILER ACTUATOR FILTER CAP PACKING DEFORMED.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003111000017	20031110	00017	EA  	2003	11	10	AUS20031054      	2	20030924	G	8540		BUSHING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1072 							(AUS) GOVERNOR IDLE SHAFT BUSHING BROKEN AWAY AND ENTERED ENGINE LUBRICATION SYSTEM CAUSING METAL CONTAMINATION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003111000018	20031110	00018	NM  	2003	11	10	AUS20031056      	1	20031018	G	3233	NAS759011	BUSHING         			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG ACTUATOR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION ACTUATOR BUSHING MISSING. BUSHING HAD NOT BEEN FITTED DURING MANUFACTURE.  SUPPORT BR	ACKET PNO 85310340-015 DAMAGED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003111000019	20031110	00019	NM  	2003	11	10	AUS20031057      	1	20030925	G	7120	310A10415	BOLT            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1638 							(AUS) NR 2 ENGINE MOUNTING SYSTEM FORWARD MOUNT CONE BOLT CRACKED.  FOUND DURING NDT INSPECTION.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003111000020	20031110	00020	EU  	2003	11	10	AUS20031058      	2	20031017	G	7200		ENGINE          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					EGT	ERRATIC         	W				O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			46070							(AUS) NR 1 ENGINE EGT REACHED AT LEAST 1100 TO 1200 DEGREES AND WAS ERRATIC. ALL OTHER INDICATIONS NORMAL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003111000021	20031110	00021	EA  	2003	11	10	AUS20031059      	2	20030828	G	8540	13S19648	GEAR            			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	CRANKSHAFT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			448  							(AUS) CRANKSHAFT GEAR INCORRECT PART. GEAR WAS NOT COMPLETELY MESHING WITH THE OIL PUMP DRIVE GEAR. PN 13S19648 FITTED I	NSTEAD OF CORRECT PN 13S19647. SUSPECT ENGINE HAD BEEN CONVERTED FROM EITHER AN IO-540 OR TSIO-540 MODEL, BOTH OF WHICH 	USED THE FITTED GEAR. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.				1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920	 
2003111000024	20031110	00024	SO  	2003	11	10	AUS20031060      	1	20031016	G	8120	NSN	CLAMP           			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  	HARTZL	HCC3Y	HCC3YN      	GL  	TURBOCHARGER	WRONG PART      	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE EXHAUST TURBOCHARGER INTERCOOLER DUCT HOSE CLAMP INCORRECTLY TORQUED FOLLOWING MAINTENANCE.  HOSE PARTED DU	RING FLIGHT.					1	L	7	2 	3O	3	O	 	A8EA    	E19EA	5	C	P25EA	 
2003111000025	20031110	00025	EA  	2003	11	10	AUS20031061      	2	20031020	G	7420		IGNITION LEAD   			GULSTM	680   	680FLP      	0141610	SW  	LYC   	O720  	IO720B1B    	41546	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	RT ENGINE	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE NR 7 CYLINDER LOWER IGNITION LEAD DEFECTIVE AT SPARK PLUG END.						1	H	7	2 	3O	3	O	 	2A4     	1E15	5	C	P6EA	 
2003111000026	20031110	00026	EA  	2003	11	10	AUS20031062      	2	20031020	G	8540		SEAL            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	DRIVESHAFT	DAMAGED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE HYDRAULIC PUMP DRIVESHAFT SEAL DAMAGED AND LEAKING. HYDRAULIC PUMP HAD BEEN CHANGED ON THE PREVIOUS DAY.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003111000027	20031110	00027		2003	11	10	AUS20031063      	4	20031014	G	3425	4019700902	INDICATOR       			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) CAPTAINS ATTITUDE DIRECTION INDICATOR (ADI) FAILED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2003111000028	20031110	00028	GL  	2003	11	10	AUS20031064      	3	20031017	G	6114	E4715	HUB             			CESSNA	188   	A188B       	2073005	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			908  							(AUS) PROPELLER HUB CRACKED IN THREADED AREA. FOUND DURING EDDY CURRENT INSPECTION IAW AD/PMC/47 AMDT1.						1	L	7	1 	3O	3	O	 	A9CE    	E5CE	5	C	P3EA	 
2003111000029	20031110	00029	NM  	2003	11	10	AUS20031065      	1	20031022	G	2612		WARNING SYSTEM  			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FIRE DETECTION	OVERHEATED      	W				O				OTHER                   				M	B	J	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) RT WING BODY OVERHEAT LIGHT ILLUMINATED. LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003111000030	20031110	00030	NE  	2003	11	10	AUS20031066      	2	20030321	G	7200	PW123D	ENGINE          			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	RIGHT	LEAKING         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE LEAKING OIL.  OIL FUMES IN CABIN. INVESTIGATION AND BOROSCOPE INSPECTION FOUND OIL WETTING IN AREA OF IN	TERCOMPRESSOR CASE.  ENGINE REMOVED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003111000031	20031110	00031	EU  	2003	11	10	AUS20031067      	1	20031015	G	5711	58221283	SPAR CAP        			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	RTWING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING MAIN SPAR LOWER SPAR CAP CORRODED.  MICROBIOLOGICAL GROWTH FOUND ON INSIDE OF FUEL ACCESS PANELS 621BB AND	 521BB AND 521CB.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2003111000032	20031110	00032	EU  	2003	11	10	AUS20031068      	1	20031010	G	3040	59885	ARM             			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	WINDSHIELD WIPER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WINDSHIELD WIPER PIVOT ARM LUG CRACKED FROM TOP RADIUS TO ATTACHMENT PIN HOLE.  FOUND DURING INSPECTION IAW AD 	JETSTREAM 76AMDT1 AND SB 30-JA-95041.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2003111000033	20031110	00033	EU  	2003	11	10	AUS20031069      	1	20030916	G	6410	AS355A12003106	BLADE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	DEBONDED        	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			41   							(AUS) TAIL ROTOR BLADE TAB DEBONDED AND SEPARATED FROM BLADE CAUSING EXCESSIVE VIBRATION.  TAIL ROTOR BLADE TRAILING EDG	E DAMAGED.  INVESTIGATION FOUND FAILURE WAS DUE TO INCORRECT SOLVENT USED DURING TAB BONDING PROCEDURE AT OVERHAUL.  SEC	ONDARY EFFECTS OF TAB LOSS WERE TAIL ROTOR GEARBOX FAILURE DUE TO ALUMINIUM ON THEOIL AND DAMAGED TAIL ROTOR DRIVE TRAIN	.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003111000035	20031110	00035		2003	11	10	AUS20031070      	4	20030729	G	3457		GPS             			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	COCKPIT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					VARIOUS					(AUS) AGPS AND RADIO TRANSCEIVER REMOVED AND GPS/COM FITTED. AUDIO PANEL REMOVED AND A DIFFERENT ITEM FITTED. SEVERAL DE	FECTS FOUND ASSOCIATED WITH INSTALLATION. NO ENTRY IN LOG BOOK,  NO WEIGHT AND BALANCE CHANGE,  NO ELECTRICAL LOAD ANALY	SIS   NO E/O'S IN LOG BOOK    INCORRECT COAXIAL CABLE FITTED IAW INSTALLATION MANUAL   INCORRECT GPS ANTENNA IAW INSTALL	ATION MANUAL.  NO ADHERENCE TO ACCEPTABLE METHODS 8. SEVERAL INCONSISTENCIES NOW WITH RADIO SYSTEM IE. LABELING WRONG, A	BSENCE OF NOTCH FILTERS, SIDETONE ISSUES. NO EVIDENCE OF FLIGHT CHECKING (IAW CAO 108.34) OF MARKER BEACON PERSONNEL/MAI	NTENANCE ERROR. UNAPPROVED MAINTENANCE.	1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2003111000036	20031110	00036		2003	11	10	AUS20031071      	4	20030729	G	2210		CAPSULE         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	AUTOPILOT SYSTEM	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AUTOPILOT ALTITUDE HOLD CAPSULE FITTED IN A DIFFERENT POSITION TO THAT STATED BY STC. PERSONNEL/MAINTENANCE ERROR.	 INCORRECT FIT.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2003111000037	20031110	00037	NM  	2003	11	10	AUS20031072      	1	20031023	G	2450	675230450	CIRCUIT BREAKER 			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AC POWER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PACK COOLING FAN CIRCUIT BREAKER (C) PHASE TERMINAL OVERHEATED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003111000038	20031110	00038		2003	11	10	AUS20031073      	4	20030929	G	3452	007062270000	DIODE           	KING        		PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ATC TRANSPONDER	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 					6884					(AUS) TRANSPONDER DIODE FAILED. EVIDENCE OF MINOR BURNING ON CIRCUIT BOARD.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2003111000080	20031110	00080	NM  	2003	11	10	AUS20031074      	1	20031001	G	2910	731840	POWER UNIT      			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYS	FAULTY          	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 STANDBY POWER UNIT FAULTY.   SUSPECT CAUSED BY AIR IN NR 2 HYDRAULIC SYSTEM.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003111000082	20031110	00082	NM  	2003	11	10	AUS20031075      	1	20031013	G	7603	S315A10819	CABLE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					POWER LEVER	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE THRUST LEVER STIFF IN OPERATION.  INVESTIGATION FOUND INCORRECT CABLE FITTED.  CABLE WAS APPROXIMATELY 1	20MM (4.72IN)LONGER THAN THE CORRECT CABLE. FURTHER INSPECTION ALSO FOUND CABLE JAMMING ON THE INTERNAL TEFLON SURFACE. 	UNAPPROVED PART.  PERSONNEL/MAINTENANCE ERROR.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2003111000083	20031110	00083	NM  	2003	11	10	AUS20031076      	1	20031024	G	2612		FIRE DETECTOR   			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					NR 1 ENGINE	INOPERATIVE     	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 1 ENGINE FIRE DETECTOR SYSTEM INOPERATIVE.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003111000085	20031110	00085	SW  	2003	11	10	AUS20031077      	1	20031022	G	5521	440000164	RIB             			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ELEVATOR FORWARD RIB CRACKED AT TORQUE TUBE OUTBOARD MOUNTING FLANGE.  RIB CONTAINS TWO CRACKS FROM TOP AND BOT	TOM ATTACHMENT RIVETS.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2003111000087	20031110	00087	SW  	2003	11	10	AUS20031078      	1	20030912	G	5521	440000164	RIB             			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ELEVATOR FORWARD RIB CRACKED AT TORQUE TUBE OUTBOARD MOUNTING FLANGE.  RIB IS CRACKED IN TWO PLACES FROM TOP AN	D BOTTOM ATTACHMENT RIVETS.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2003111000088	20031110	00088	CE  	2003	11	10	AUS20031079      	1	20031028	G	5730	512201120	PANEL           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT LOWER WING PANEL DISBONDED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111000089	20031110	00089	CE  	2003	11	10	AUS20031080      	1	20031028	G	5730	51220031	SKIN            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LEADING EDGE SKIN DISBONDED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111000090	20031110	00090	CE  	2003	11	10	AUS20031081      	1	20031028	G	5730	512200817	PANEL           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING UPPER SKIN PANEL DISBONDED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111000091	20031110	00091	CE  	2003	11	10	AUS20031082      	1	20031028	G	5730	512200818	PANEL           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT UPPER WING PANEL SKIN DISBONDED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111000092	20031110	00092	CE  	2003	11	10	AUS20031083      	1	20031028	G	5711	512204124	SPAR CAP        			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING LOWER SPAR CAP CORRODED IN AREA IN FRONT OF AILERON.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111000094	20031110	00094	CE  	2003	11	10	AUS20031084      	1	20031028	G	5711	512204123	SPAR CAP        			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LOWER SPAR CAP CORRODED IN AREA IN FRONT OF AILERON.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111000095	20031110	00095	CE  	2003	11	10	AUS20031085      	1	20031028	G	5711	512204125	SUPPORT         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING SPAR SUPPORT CORRODED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111000097	20031110	00097	CE  	2003	11	10	AUS20031086      	1	20031028	G	5730	512201121	PANEL           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LOWER SKIN PANEL DISBONDED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003111000098	20031110	00098	SW  	2003	11	10	AUS20031087      	1	20031025	G	2131	10234010	CONTROLLER      			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	CABIN PRESSURE	FAULTY          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 			16222							(AUS) CABIN PRESSURE CONTROLLER FAULTY.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003111000099	20031110	00099	SW  	2003	11	10	AUS20031088      	1	20031022	G	5311	UNK	FRAME           			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			17536							(AUS) CABIN BELT FRAME CRACKED. FOUND DURING INSPECTION IAW SERVICE LETTER CC7-SL-036.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2003111000100	20031110	00100	CE  	2003	11	10	AUS20031089      	1	20031022	G	5741	NAS15237	BOLT            			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	LT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING UPPER FORWARD ATTACHMENT BOLT THREADS DAMAGED.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2003111000101	20031110	00101	NE  	2003	11	10	AUS20031090      	2	20031010	G	7230	110109007	COMPRESSOR      								LYC   	T53   	T5317A      	41549	NE  					TURBINE ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE COMPRESSOR SECTION CONTAINED COMPONENTS FROM AN ENGINE INVOLVED IN AN AIRCRAFT CRASH. ENGINE HAD BEEN ASSEM	BLED FROM COMPONENTS FROM FIVE DIFFERENT ENGINES. NO HISTORY CARDS WERE SUPPLIED FOR THE COMPRESSOR MODULE BUT INVESTIGA	TION FOUND THAT THE MODULE WAS FROM AN ENGINE FITTED TO AN AIRCRAFT THAT HAD CRASHED.									4	U			E17EA				 
2003111000103	20031110	00103	CE  	2003	11	10	AUS20031091      	1	20031013	G	2810	C1560030101	CAP             			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUEL STORAGE	FAULTY          	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) FUEL CAP PLASTIC SPACER FAILED ALLOWING FUEL TO VENT FROM TANK CAUSING THE FUEL CELL TO COLLAPSE.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003111000104	20031110	00104	EA  	2003	11	10	AUS20031092      	2	20031022	G	7322	25763562	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			195  							(AUS) FUEL CONTROL UNIT IMPACT AIR CHAMBER CONTAMINATED WITH FUEL.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003111000105	20031110	00105	NM  	2003	11	10	AUS20031093      	1	20031027	G	5230	AE352211	SHAFT           			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					CARGO DOOR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN CARGO DOOR FORWARD AND AFT ACTUATOR PIVOT SHAFTS SHEARED.  SECONDARY DAMAGE CAUSED TO AFT ACTUATOR MAIN SUPPO	RTS.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003111000107	20031110	00107	NM  	2003	11	10	AUS20031094      	1	20031018	G	3221		BOLT            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					NLG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION DRUM LT STOP BOLT LOOSE AND RT STOPBOLT MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2003111000108	20031110	00108	NM  	2003	11	10	AUS20031095      	1	20031027	G	3240		BRAKE ASSY      			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AUTOBRAKE SYSTEM NOT ARMING.  LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2003111000109	20031110	00109	EA  	2003	11	10	AUS20031096      	2	20031021	G	8530		EXHAUST VALVE   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	SEPARATED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) NR 4 CYLINDER EXHAUST VALVE HEAD SEPARATED FROM VALVE STEM. VALVEGUIDE LOOSE IN HEAD.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003111000119	20031110	00119	EA  	2003	11	10	AUS20031097      	2	20031015	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ENGINE	FAULTY          	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		LD	LANDING        	1			AU	S 										(AUS) FUEL CONTROL UNIT FAULTY.  WORKSHOP INVESTIGATION COULD FIND NO FAULT.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003111000120	20031110	00120	GL  	2003	11	10	AUS20031098      	3	20030923	G	6114		HUB             			CESSNA	182   	182B        	2072706	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	PROPELLER	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB FAULTY. DURING COMPLIANCE WITH AD/PMC/47 IT WAS FOUND THAT THE MOUNTING STUDS HAD BEEN INCORRECTLY S	EALED.  SILASTIC MATERIAL WAS USED FOR SEALING RATHER THAN THE CORRECT PROCEDURE AS INDICATED IN MFG SL 1993-17. THE HUB	 WAS ALSO INCORRECTLY STAMPED AS STILL BEING A GREASE FILLED HUB. PROPELLER PISTON ALSO CONTAINED A NON-APPROVED REPAIR.	 UNAPPROVED PROCEDURE. PERSONNEL/MAINTENANCE ERROR.			1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P880	 
2003111000121	20031110	00121		2003	11	10	AUS20031099      	4	20031025	G	3425	6225045202	SYMBOL GENERATOR			BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LT AND RT EFIS SYMBOL GENERATORS FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2004010600085	20040106	00085	EA  	2004	1	6	AUS20031100      	2	20031030	G	7414	DO52071	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					MAGNETO	LOOSE           	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			6    							(AUS) MAGNETO BEARING SPINNING IN HOUSING. SEE MDR 03/1101 FOR FURTHER INFORMATION.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2004010600086	20040106	00086	EA  	2004	1	6	AUS20031101      	2	20031030	G	7414	B19912E	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					MAGNETO	LOOSE           	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			164  							(AUS) MAGNETO BEARING SPINNING IN HOUSING. SEE MDR 03/1100 FOR FURTHER INFORMATION.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2004010600087	20040106	00087	SO  	2004	1	6	AUS20031102      	1	20031022	G	5343	9572402	MOUNT           			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	SEPARATED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR MOUNT BRACKET RIVETS FAILED. SUSPECT CAUSED BY HEAVY LANDING AND SUBSTANDARD RIVETING. 	PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2004010600089	20040106	00089	EU  	2004	1	6	AUS20031103      	1	20031029	G	3244	PL126	TIRE            			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	MLG	PUNCTURED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 			230  							(AUS) RT MLG TIRE PUNCTURED ON LANDING.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2004010600090	20040106	00090	EU  	2004	1	6	AUS20031104      	1	20030925	G	2822	9688411404	PUMP            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL BOOST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					85011					(AUS) RT FUEL BOOST PUMP FAILED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004010600092	20040106	00092	EU  	2004	1	6	AUS20031105      	1	20031008	G	2932	9738114306	SWITCH          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD PRESSURE	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) HYDRAULIC PRESSURE SWITCH FAILED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004010600098	20040106	00098	SW  	2004	1	6	AUS20031106      	1	20031026	G	2435	230811530	ARMATURE        	LEARSIEGLER 		BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					START GENERATOR	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 					94090					(AUS) STARTER-GENERATOR ARMATURE LOST MAGNETISM.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2004010700017	20040107	00017	EU  	2004	1	7	AUS20031107      	1	20031004	G	2434		GENERATOR       			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	DC LT & RT	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LT AND RT GENERATORS FAILED.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2004010700018	20040107	00018	CE  	2004	1	7	AUS20031108      	1	20031031	G	3260	1CH16	SWITCH          			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	MLG	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR DOWN SWITCH FAULTY.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2004010700019	20040107	00019	CE  	2004	1	7	AUS20031109      	1	20031030	G	5313	3541003868	LONGERON        			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FUSELAGE LONGERON CRACKED IN AREA APPROXIMATELY 6.35MM (0.25IN) AFT OF FIREWALL.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2004010700020	20040107	00020	CE  	2004	1	7	AUS20031110      	1	20031031	G	2912	MS28775224	O-RING          	PUROLATOR   		CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	HYD FILTER	DETERIORATED    	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					NA					(AUS) HYDRAULIC FILTER HOUSING O-RING SEAL DETERIORATED AND LEAKING.						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2004010700021	20040107	00021	SO  	2004	1	7	AUS20031111      	1	20031028	G	3213	65319004	CYLINDER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  	SNSNCH	74DM	M74DM       	EA  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR STRUT CYLINDER CRACKED IN AREA OF TORQUE LINK ATTACHMENT LUGS AS INDICATED IN MFG SB 1131.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2004010700022	20040107	00022	SO  	2004	1	7	AUS20031112      	1	20031028	G	3213	653194	CYLINDER        			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR STRUT CYLINDERS CRACKED IN AREA OF TORQUE LINK ATTACHMENT LUGS AS INDICATED IN MFG SB 	1131.					1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2004010700023	20040107	00023	NE  	2004	1	7	AUS20031113      	2	20031101	G	7323	210949	GOVERNOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TURBINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			2026 							(AUS) ENGINE OVERSPEED GOVERNOR FAULTY.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004010700052	20040107	00052	SW  	2004	1	7	AUS20031114      	1	20031024	G	5311		FRAME           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE INTERCOSTAL FRAMES CRACKED AND TORN IN AREA UNDER FLOOR. INSP FOUND FOLLOWING OTHER DEFECTS: LT AND RT BO	X BEAMS (USED FOR CENTER ISLE SEAT TRACK SUPPORT) WERE CRUMPLING AND BREAKING, CAN BE SEEN FOR MOST OF LENGTH OF BOX BEA	MS. WORSE AFFECTED AREA, WERE REAR BOX BEAMS JUST FWD OF CARGO BY AREA FLOOR BETWEEN STN435.060, STN362.271.2. MOST SIGN	IFICANT NEW PROBLEM HOWEVER, CRACKS ON INTERCOSTAL FRAMES TO MAIN HOOP FRAME ATTACHMENT. THESE WERE ALL ON LT SIDE FRAME	 AREA. 4 CRACKS ALL WAY THROUGH  INTERCOSTAL WERE FOUND IN AREA BETWEEN STN422.271, STN332.271. SOME SMALL CRACKS ON INT	ERCOSTAL FRAMES WERE FOUND ON ANOTHER 3 FRAMES ALL ON LT SIDE. SUSPECT CAUSED BY OVERLOAD OF FR8.03111424-	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2004010700053	20040107	00053		2004	1	7	AUS20031115      	4	20031103	G	3418		COMPUTER        			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	STALL WARNING	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) STALL WARNING SYSTEM FAULTY. THE FOLLOWING ITEMS WERE REPLACED:-1. FLAP POSITION INDICATOR PN 4428-150-80-10 2. RT	 STALL VANE 3. NR 2 STALL WARNING COMPUTER.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700054	20040107	00054	NM  	2004	1	7	AUS20031116      	1	20031030	G	2997		WIRE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					HYDRAULIC PUMP	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ELECTRICAL HYDRAULIC PUMP PHASE A' SPLICE DAMAGED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2004010700055	20040107	00055	NM  	2004	1	7	AUS20031117      	1	20031103	G	3244	161U00011	TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NR 6 WHEEL	PUNCTURED       	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) NR 6 WHEEL TIRE PUNCTURED.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010700056	20040107	00056	SO  	2004	1	7	AUS20031118      	1	20031029	G	1430	401269	BOLT            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	AILERON CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CONTROL COLUMN IDLER SPROCKET BOLT LOW TORQUE. SUSPECT BOLTS LOOSENED DURING RIGGING AT MANUFACTURE AND NO	T RETORQUED.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2004010700057	20040107	00057	SO  	2004	1	7	AUS20031119      	1	20031030	G	1430	401269	BOLT            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	AILERON CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CONTROL COLUMN IDLER SPROCKET BOLT LOW TORQUE. SUSPECTBOLTS LOOSENED DURING RIGGING AT MANUFACTURE AND NOT	 RETORQUED.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2004010700058	20040107	00058	SO  	2004	1	7	AUS20031120      	1	20031030	G	1430	401269	BOLT            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  	MCAULY	3AF32C	3AF32C*     	GL  	AILERON CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CONTROL COLUMN IDLER SPROCKET BOLT LOW TORQUE. SUSPECT BOLTS LOOSENED DURING RIGGING AT MANUFACTURE AND NO	T RETORQUED. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2004010700059	20040107	00059	EU  	2004	1	7	AUS20031121      	1	20031106	G	3244	40140A	TIRE            			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	NLG	DEFLATED        	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) NOSE WHEEL TIRE DEFLATED. NO DAMAGE TO WHEEL RIM. NOSE WHEEL  MUD GUARD MISSING.  INVESTIGATION FOUND THE VALVE ST	EM SHEARED FROM THE TUBE.  SUSPECT VALVE STEM FAILURE CAUSED BY FATIGUE AND AGING OF THE RUBBER AROUND THE VALVE BASE.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2004010700061	20040107	00061	NM  	2004	1	7	AUS20031122      	1	20031105	G	3411		PIVOT           			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					PITOT/STATIC SYS	OBSTRUCTED      	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FIRST OFFICERS PITOT PROBE BLOCKED BY INSECT.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2004010700068	20040107	00068	NM  	2004	1	7	AUS20031123      	1	20031104	G	2751	426EN98	SWITCH          			BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TE FLAP SWITCH S245 FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004010700069	20040107	00069	NM  	2004	1	7	AUS20031124      	1	20031104	G	3246	314801	WHEEL           			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING TIRE CHANGE MAINTENANCE ON THE WHEEL, THE NDT INSPECTION WAS NOT CARRIED OUT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700070	20040107	00070	NM  	2004	1	7	AUS20031125      	1	20031103	G	2910	65445433036	PIPE            			BOEING	737   	737376      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR UP HYDRAULIC PIPE CHAFED AND LEAKING. LOSS OF HYDRAULIC FLUID. SPRAY OF HYDRAULIC FLUID CONTAMIN	ATED E1-3 AVIONICS RACK CONNECTORS D4115P AND D4067P.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2004010700071	20040107	00071	NM  	2004	1	7	AUS20031126      	1	20031103	G	2520	201136612258	SEAT BELT       			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					CABIN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT BUCKLE PIVOT PIN SHEARED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2004010700072	20040107	00072	EU  	2004	1	7	AUS20031127      	1	20031101	G	5610	1379628C402	WINDSHIELD      			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WINDSHIELD CRACKED.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2004010700073	20040107	00073		2004	1	7	AUS20031128      	4	20031105	G	2565	D31591478	SLIDE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					R1 DOOR	TWISTED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR R1 ESCAPE SLIDE TWISTED DURING DEPLOYMENT.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004010700075	20040107	00075	EA  	2004	1	7	AUS20031129      	2	20031021	G	7414	LW13795	GEAR            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO DRIVE	DAMAGED         	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 			2170 							(AUS) ENGINE FAILED.  INITIAL INVESTIGATION REVEALED A FAILURE OF THE MAGNETO DRIVE SYSTEM. DURING AUTO ROTATION AND LAN	DING, ONE MAIN ROTOR BLADE CONTACTED THE TAILBOOM. FURTHER EXAMINATION FOUND THE CRANKSHAFT IDLER GEAR DAMAGED. SUSPECT 	CAUSED BY LOSS OF TORQUE ON THE STUD HOLDING THE CRANKSHAFT IDLER GEAR POSSIBLY CAUSED BY THREAD BEING STRIPPED DURING A	SSEMBLY.			1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004010700076	20040107	00076	NM  	2004	1	7	AUS20031130      	1	20031105	G	2597		WIRE            			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					COFFEEMAKER	SEPARATED       	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) REAR GALLEY COFFEE MAKER FAULTY. SUSPECT INTERNAL SHORT CIRCUIT IN HOTPLATE SECTION. WIRING CLAMP SCREW AND WASHER	S SEPARATED FROM HOTPLATE BASE.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2004010700077	20040107	00077	NM  	2004	1	7	AUS20031131      	1	20031106	G	2760	82950010123	TUBE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	DRAG CONTROL	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LT OB ROLL SPOILER ACTUATOR HYDRAULIC LINE CRACKED AND LEAKING ON BEND RADIUS.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012600113	20040126	00113	EU  	2004	1	26	AUS20031132      	1	20031105	G	7712	24045	PIN             			AEROSP	AS365 	AS365N2     	8680815	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TORQUEMETER	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 			564  							(AUS) ENGINE TORQUEMETER PIN FAILED.  PIN COULD NOT BE FOUND AND IT WAS SUSPECTED THAT THE PIN WAS SOMEWHERE IN THE ENGI	NE.  ENGINE WAS REMOVED FOR REPAIR.					1	G	7	2 	3U	3	U	RT	H10EU   	E00054EN				 
2004010700078	20040107	00078	NM  	2004	1	7	AUS20031133      	1	20031107	G	2720		CONTROL CABLE   			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					RUDDER	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER CONTROL SYSTEM BINDING AT RT PEDAL HALF TRAVEL.  INVESTIGATION FOUND CONTROLS BINDING ON NR 4 DRIPSHIELD LO	CATED IN FIRST CLASS CEILING AREA.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010700079	20040107	00079	NE  	2004	1	7	AUS20031134      	2	20031109	G	7230	RB211524H	COMPRESSOR      			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					LT ENGINE	DAMAGED         	W				O				OTHER                   				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		DE	DESCENT        	1			AU	S 			7866 							(AUS) LT ENGINE HAD SPARKS AND FLAMES WITH EGT APPROXIMATELY 50 DEGREES HIGHER THAN THE RT ENGINE. BOROSCOPE INSPECTION 	OF THE HPC FOUND SIGNS OF DAMAGE TO FIRST AND SECOND STAGES.					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2004010700080	20040107	00080		2004	1	7	AUS20031135      	4	20031107	G	6122	DCFS29050T3	GOVERNOR        			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	2AF34C	D2AF34C71   	GL  	PROPELLER	CRACKED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 			952  							(AUS) LT PROPELLER GOVERNOR HEAD CRACKED. LOSS OF ENGINE OIL.						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P5EA	 
2004010700090	20040107	00090	NM  	2004	1	7	AUS20031137      	1	20031111	G	2781	10608198	SWITCH          			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					KRUEGER FLAP	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NR 5 LEADING EDGE KRUEGER FLAP POSITION SWITCH FAULTY.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2004010800007	20040108	00007	EU  	2004	1	8	AUS20031138      	1	20031107	G	2897	MS154145	CIRCUIT BREAKER 			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL BOOST PUMP	BURNED OUT      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) LT INNER FUEL BOOST PUMP CIRCUIT BREAKER BURNED OUT.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2004010800048	20040108	00048	SW  	2004	1	8	AUS20031141      	1	20031030	G	6720	206001059101	CONTROL ROD     			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR CONTROL TUBE SEVERELY CORRODED IN AREA UNDER FORWARD NYLATRON SLEEVE.  INSPECTION FOUND CORROSION WAS B	EYOND LIMITS AND WAS REPLACED.  AIRCRAFT OPERATES IN A MARINE ENVIRONMENT.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004010800049	20040108	00049	GL  	2004	1	8	AUS20031142      	1	20030506	G	2572	552541	RACK            			AMTR  	VANS  	RV8         	       	GL  	CONT  	O550  	TSIO550B    	17043	SO  	MUHBR	MTV	MTV9*       	EU  	AUTOPILOT RACK	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) AUTOPILOT RACK FAULTY.  RACK WAS TOO LONG FOR COMPUTER AND THE PINS WOULD NOT MATE CORRECTLY.  RACK WAS A NEW ITEM	.					1	L	7	1 	3O	3	O	NT	EXPA1L71	E5SO	5	C	P24NE	 
2004010800050	20040108	00050	CE  	2004	1	8	AUS20031143      	1	20031016	G	2750	1460100708	CONTROL CABLE   			CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360C    	17025	SO  	MCAULY	2AF34C	D2AF34C303  	GL  	TE FLAP	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT FLAP DOWN CABLES PN 1460100-7 AND PN 1460100-8 FRAYED WITH BROKEN STRANDS AROUND BELLCRANK ACTUATOR.						1	H	7	2 	3O	3	O	 	A6CE    	E9CE	5	C	P5EA	 
2004010800051	20040108	00051	EA  	2004	1	8	AUS20031144      	2	20031107	G	8520	LW16586	TAPPET          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			200  							(AUS) TAPPET INNER BODIES CRACKED (8OFF).						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004010600012	20040106	00012	EA  	2004	1	6	AUS20031145      	2	20031106	G	8520	LW16586	TAPPET          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAPPET INNER BODIES CRACKED (8OFF).						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004010700012	20040107	00012	NE  	2004	1	7	AUS20031146      	2	20031112	G	7261	AS3216119	RING            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE OIL	MISSING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE OIL TRANSFER TUBE FORWARD AND AFT RETAINING RINGS PNOAS3216-119 MISSING. TUBE RUNS BETWEEN REDUCTION G	EARBOX AND SCAVENGE PUMP.  PERSONNEL/MAINTENANCE ERROR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700024	20040107	00024	NM  	2004	1	7	AUS20031147      	1	20031112	G	7120	65187226	FITTING         			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ENGINE MOUNT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE FORWARD SUPPORT FITTING TOP SURFACE CORRODED IN AREA BETWEEN FITTING AND UPPER STRUT SKINS. FOUND DURI	NG INSPECTION IAW AD/B727/151.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2004010800004	20040108	00004	EU  	2004	1	8	AUS20031148      	1	20031111	G	3411		PITOT TUBE      			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PITOT/STATIC SYS	CONTAMINATED    	W				O				OTHER                   				S			AFFECT SYSTEMS            			CL	CLIMB          	1			AU	S 										(AUS) PITOT/STATIC SYSTEM CONTAMINATED WITH WATER.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2004010800005	20040108	00005	NM  	2004	1	8	AUS20031149      	1	20031112	G	3244	161U00011	TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					LT MLG	DEFLATED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			921  							(AUS) LT BODY LANDING GEAR NR 4 REAR TIRE FLAT.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010800006	20040108	00006	EA  	2004	1	8	AUS20031150      	2	20031113	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	ENGINE	CONTAMINATED    	W				K				NONE                    				O	E		OTHER                     	VIBRATION/BUFFET          		IN	INSP/MAINT     	1			AU	S 										(AUS) FCU IMPACT DIAPHRAGM CHAMBER CONTAMINTED WITH FUEL/OIL.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2004010800008	20040108	00008	SO  	2004	1	8	AUS20031151      	2	20031112	G	8520	646311	PISTON          			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C506   	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) PISTON PN 646311 CRACKED IN BOSS.  PISTON PIN PN 643846 BROKEN.						1	L	7	2 	3O	3	O	 	A34CE   	E8CE	5	C	P57GL	 
2004010800046	20040108	00046	GL  	2004	1	8	AUS20031152      	2	20031024	G	7230	6890550	ROTOR           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1127 				CAE831056			(AUS) COMPRESSOR ROTOR ASSEMBLY DAMAGED BY FOD. AIRCRAFT HAD BEEN REASSEMBLED FOLLOWING PAINTING WHICH INCLUDED WORK IN 	THE COMPRESSOR PLENUM AREA.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004010800047	20040108	00047	NM  	2004	1	8	AUS20031153      	1	20031115	G	7920		B-NUT           			BOEING	737   	7377Q8      	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ENGINE OIL	LOOSE           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 2 ENGINE REAR SUMP OIL PRESSURE LINE B-NUT LOOSE.  LOOSE UNION IS LOCATED AT 6 O'CLOCK POSITION JUST OB OF THE 	ENGINE LUBRICATION UNIT.					2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2004010600013	20040106	00013	NE  	2004	1	6	AUS20031154      	2	20031111	G	8530		CYLINDER        			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) NR 12 CYLINDER FAILED. LIMITED INFORMATION PROVIDED.						2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2004010700009	20040107	00009	EU  	2004	1	7	AUS20031155      	1	20030829	G	2797		WIRE            			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	TE FLAPS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) FLAP UP MICROSWITCH WIRE BROKEN. SWITCH IS LOCATED BEHINDFLAP SELECTOR.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2004010700010	20040107	00010	NE  	2004	1	7	AUS20031156      	2	20031114	G	7310	3035987	PIPE            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE FUEL	LOOSE           	W				O				OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE FUEL PRESSURE PIPE ATTACHMENT NUT LOOSE AND LEAKING.  ATTACHMENT NUT HAD BEEN LOOSENED DURING FUEL NOZZL	E REPLACEMENT.  THE NUT HAD NOT BEEN RETORQUED OR LOCKWIRED DURING REINSTALLATION. PERSONNEL/MAINTENANCE ERROR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700011	20040107	00011	EA  	2004	1	7	AUS20031157      	2	20030827	G	8530		EXHAUST VALVE   			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2A     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	SEPARATED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) NR 2 CYLINDER EXHAUST VALVE HEAD SEPARATED FROM VALVE STEM.  ENGINE HAD BEEN SITTING IDLE FOR AT LEAST 18 MONTHS A	ND HAD JUST BEEN RETURNED TO OPERATION.					1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P9045	 
2004010700025	20040107	00025	NM  	2004	1	7	AUS20031158      	1	20031117	G	2611	473054	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CARGO BAY	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) BAGGAGE COMPARTMENT SMOKE DETECTOR FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010800002	20040108	00002	EU  	2004	1	8	AUS20031159      	1	20031116	G	2742		ACTUATOR        			AIRBUS	330   	A330202     	3930316	EU  	GE    	CF6   	CF680       	30025	NE  					HORIZONTAL STAB	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT GREASE USED ON TRIM ABLE HORIZONTAL STABILIZER ACTUATOR (THSA). AEROSHELL 22 USED INSTEAD OF CORRECT AER	OSHELL 33. USE OF INCORRECT GREASE MAKES AIRCRAFT NON COMPLIANT WITH AD/330/7.UNAPPROVED PART. PERSONNEL/MAINTENANCE ERR	OR.				2	L	7	2 	4F	4	F	RT	A46NM   	E13NE				 
2004010700114	20040107	00114	NM  	2004	1	7	AUS20031160      	1	20031003	G	5313		STRINGER        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRINGER CRACKED AT RIVET HOLE LOCATED FORWARD OF FRAME 328.  CRACK LENGTH APPROXIMATELY 0.0254MM (0.1IN). FOUND D	URING EDDY CURRENT INSPECTION.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004010800003	20040108	00003	NM  	2004	1	8	AUS20031161      	1	20031003	G	5712		RIB             			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING RIB LOCATED AT WBL 135.5 CRACKED AT LOWER CUT-OUT FOR STR 1 ON RT SIDE.  CRACK LENGTH 25.4MM (1IN).  FOUND DU	RING EDDY CURRENT INSPECTION.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004010800009	20040108	00009	EU  	2004	1	8	AUS20031162      	1	20031114	G	5610	9598110108	WINDSHIELD      			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) COPILOT'S WINDSHIELD CRACKED IN OUTER LAYER.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004010800043	20040108	00043	EA  	2004	1	8	AUS20031163      	2	20031114	G	8520	LW16586	TAPPET          								LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC LIFTERS (2 OFF) CRACKED. TAPPETS WERE NEW ITEMS.											3	O			E274				 
2004010800044	20040108	00044	EU  	2004	1	8	AUS20031164      	1	20031103	G	5711	TB2011003100	SPAR            			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT & RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3969 							(AUS) LT AND RT MAIN WING SPARS CORRODED ON REAR FACE. SPAR PN TB20-11-003-100 AND PN TB20-11-003-101.						1	L	7	1 	3O	3	O	RT	A51EU   	1E4	5	C	P920	 
2004010800045	20040108	00045	SO  	2004	1	8	AUS20031165      	1	20031023	G	2820	6390115	HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2D     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	FUEL DIST	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SUPPLY HOSE FROM TANK OUTER SECTION PERISHED.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2004010600015	20040106	00015	SO  	2004	1	6	AUS20031166      	1	20031023	G	2820	6390115	HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2D     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	AIRCRAFT FUEL	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SUPPLY HOSE FROM TANK OUTER SECTION PERISHED.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2004010700006	20040107	00006	NE  	2004	1	7	AUS20031167      	2	20031117	G	7200		ENGINE          			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NR 2	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 			13988				CW15			(AUS) NR 2 ENGINE FAILURE.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010700007	20040107	00007	SO  	2004	1	7	AUS20031168      	1	20030525	G	2820	3038	HOSE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL SYSTEM	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NA					(AUS) FUEL HOSE LOCATED BETWEEN FUEL SELECTOR AND FUEL BOWL PERISHED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004010700008	20040107	00008	SO  	2004	1	7	AUS20031169      	1	20031023	G	3240	6390117	HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2D     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	BRAKE ASSY	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT BRAKE HOSE OUTER COVERING DETERIORATED.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2004010700026	20040107	00026	SO  	2004	1	7	AUS20031170      	1	20031103	G	3213	6531904	CYLINDER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2D     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR CYLINDER CRACKED IN LOWER SECTION OF TORQUE LINK ATTACHMENT LUG.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2004010700109	20040107	00109	SO  	2004	1	7	AUS20031171      	1	20030725	G	5712	78475006	RIB             			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING RIB LOCATED AT WS 49.25 CRACKED.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2004010700110	20040107	00110	SO  	2004	1	7	AUS20031172      	1	20030725	G	5712	78475007	RIB             			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING RIB LOCATED AT WS 49.25 CRACKED.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2004010700111	20040107	00111	SW  	2004	1	7	AUS20031173      	1	20031112	G	2910	SS1009H000A110	HOSE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	BURST           	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) RT HYDRAULIC PUMP MAIN PRESSURE LINE FAILED. LOSS OF HYDRAULIC FLUID. BOTH HYDRAULIC PUMPS UNSERVICEABLE DUE TO LA	CK OF FLUID.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2004010700112	20040107	00112	SO  	2004	1	7	AUS20031174      	1	20031120	G	7810	40310010	EXHAUST PIPE    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE EXHAUST SEGMENT, HOLE IN AREA TO THE REAR OF THE TURBOCHARGER.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004010800010	20040108	00010	SO  	2004	1	8	AUS20031175      	1	20031120	G	8120	4773120000	SPRING          	GARRTT      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WASTEGATE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE TURBOCHARGER WASTEGATE OPEN, ASSIST SPRING BROKEN.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004010800037	20040108	00037	SO  	2004	1	8	AUS20031176      	2	20031119	G	8530		NUT             			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGING CYLINDER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			450  							(AUS) CYLINDER HOLDDOWN STUD NUTS MISSING OR LOOSE.  MISSING NUTS FOUND IN ENGINE COWL.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2004010800038	20040108	00038	SW  	2004	1	8	AUS20031177      	1	20031110	G	1430	NAS660427	BOLT            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK ROLLER ATTACHMENT BOLT BROKEN.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2004010600017	20040106	00017	SW  	2004	1	6	AUS20031178      	1	20031111	G	3260	602EN6026	SQUAT SWITCH    			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR SQUAT SWITCH FAILED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2004010700004	20040107	00004	CE  	2004	1	7	AUS20031179      	1	20031114	G	3244	277K081	TIRE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT MLG	DEFLATED        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR TIRE, DEFLATED DURING LANDING ROLL.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2004010700005	20040107	00005	EA  	2004	1	7	AUS20031180      	2	20031112	G	8550		OIL SYSTEM      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL SYSTEM CONTAMINATED BY UNKNOWN NON-FERROUS ITEMS.  CONTAMINATES WERE SIMILAR TO SMALL PEBBLES AND WERE 	APPROXIMATELY 5MM BY 5MM (0.196IN BY 0.196IN) IN SIZE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004010700027	20040107	00027	NM  	2004	1	7	AUS20031181      	1	20031113	G	2822	6072101	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL BOOST	OBSTRUCTED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			26529							(AUS) FORWARD OVERBOARD/JETTISON PUMP INLET HOUSING AND INLET CHECK VALVE WORN BEYOND LIMITS. AFT OVERBOARD/JETTISON PUM	P INLET CHECK VALVE DETACHED AND BLOCKING PUMP INLET.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010700101	20040107	00101	EU  	2004	1	7	AUS20031182      	1	20030715	G	2497	121972	SPLICE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AC POWER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) IDG FEEDER CABLE INLINE SPLICE WAS PRE SB-24-85-01253A. PRE MOD SPLICES PN 12197/2 WERE FITTED INSTEAD OF PN 12198	/2 SPLICES.					2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2004010700102	20040107	00102	EU  	2004	1	7	AUS20031183      	1	20031119	G	2434	ALU8421R	ALTERNATOR      			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	RIGHT	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) RT ALTERNATOR FAILED.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2004010700103	20040107	00103	CE  	2004	1	7	AUS20031184      	1	20031029	G	3243	8000016	SEAL            	CESSNA      		CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MASTER CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BRAKE MASTER CYLINDER SEAL WORN.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2004010700104	20040107	00104	EA  	2004	1	7	AUS20031185      	2	20031030	G	8530	IO360L2A	EXHAUST VALVE   			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	ENGINE	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1323 							(AUS) EXHAUST VALVES ON ALL FOUR CYLINDER BURNED.   CAUSED BY FAULTY SWAGING ON ENGINE INDUCTION PIPES WHICH ALLOWED LEA	N MIXTURE TO CYLINDERS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2004010800011	20040108	00011	NE  	2004	1	8	AUS20031186      	3	20031116	G	6111	L106LA0	BLADE           			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER	UNSERVICEABLE   	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			4190 							(AUS) LT ENGINE PROPELLER BLADE FAULTY.  LIMITED INFORMATION PROVIDED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2004010800036	20040108	00036	EU  	2004	1	8	AUS20031187      	1	20031123	G	2121	7881601	FAN             			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	AIR DISTRIBUTION	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 			24707							(AUS) LT RECIRCULATING FAN FAILED.						2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG	 
2004010600019	20040106	00019	GL  	2004	1	6	AUS20031188      	3	20031113	G	6110	660715001	PROPELLER       			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	LEFT	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 			5133 							(AUS) LT PROPELLER FAULTY. LIMITED INFORMATION PROVIDED.						2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG	 
2004010600179	20040106	00179	EU  	2004	1	6	AUS20031189      	1	20031115	G	3230	F8553048401	LINE            			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	MLG	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			2614 							(AUS) LT MAIN LANDING GEAR UP LINE FAILED. LOSS OF HYDRAULIC FLUID.						2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG	 
2004010600180	20040106	00180	NM  	2004	1	6	AUS20031190      	1	20031122	G	3397		CIRCUIT BOARD   			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	CABIN LIGHT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING INSPECTION IAW AD/DHC-8/027 THE FOLLOWING WAS OBSERVED:- 1. RT ROW 2 PSU PCB SHOWS EVIDENCE OF OVERHEATING 	AT CONNECTIONS TO Q2.2. RT ROW 4 PSU PCB SHOWS EVIDENCE OF OVERHEATING AT CONNECTIONS TO J2.3. RT ROW 8 PSU PCB SHOWS EV	IDENCE OF OVERHEATING AT CONNECTIONS TO J2.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700001	20040107	00001		2004	1	7	AUS20031191      	4	20031122	G	3421	2593996333	GYRO            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ATTITUDE	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) COPILOT TARSYN GYRO FAILED.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2004010700028	20040107	00028	SW  	2004	1	7	AUS20031192      	1	20031110	G	2752		CASE            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TE FLAP ACTUATOR	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 			11722		SC873B					(AUS) LT FLAP ACTUATOR CASE CRACKED AND LEAKING.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2004010700105	20040107	00105	SO  	2004	1	7	AUS20031193      	1	20031116	G	3241	426871	CONTROL UNIT    			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ANTISKID SYS	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 			3252 							(AUS) ANTI-SKID SYSTEM CONTROL BOX FAILED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2004010700106	20040107	00106	SO  	2004	1	7	AUS20031194      	1	20031116	G	2997	W602004022	WIRE HARNESS    			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	HYDRAULIC POWER	WORN            	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			23711							(AUS) RT HYDRAULIC SYSTEM LOOM WIRE W602-0040-22 CHAFING ON HYDRAULIC PIPE. LOOM RUNS FROM THE TOP OF THE RT REAR NACELL	E TO THE TRAILING EDGE.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2004010700107	20040107	00107	NE  	2004	1	7	AUS20031195      	2	20031123	G	7230	311489101	VALVE           			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE P2.5/P3 SWITCHING VALVE STICKING INTERMITTENTLY ALLOWING OIL VAPOUR INTO THE AIR CONDITIONING SYSTEM.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700108	20040107	00108	NE  	2004	1	7	AUS20031196      	2	20031118	G	7230	PCE123321	BEARING         			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	NR 4	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) BOROSCOPE INSPECTION OF LT ENGINE FOLLOWING FUMES IN THE AIR CONDITIONING SYSTEM FOUND OIL LEAKING IN THE NR 4 BEA	RING AREA.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010800012	20040108	00012	CE  	2004	1	8	AUS20031197      	1	20031114	G	3297	51184122	DIODE           			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	2AF34C	D2AF34C71   	GL  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR ELECTRICAL CIRCUIT DIODE FAILED.  INVESTIGATION FOUND POWER WAS BACK FEEDING FROM THE PRESS TO TEST C	IRCUIT.					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P5EA	 
2004010800039	20040108	00039	EA  	2004	1	8	AUS20031199      	2	20030916	G	7414	101630052R	MAGNETO         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			192  				L1699939			(AUS) LT MAGNETO HOUSING FAILED ALLOWING MAGNETO SHAFT TO COCK TO ONE SIDE AND SEIZE CAUSING DAMAGE TO MAGNETO DRIVE GEA	R.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2004010800040	20040108	00040	GL  	2004	1	8	AUS20031200      	1	20030921	G	5720		FLYING WIRE     			AMTR  	VANS  	RV8         	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  	AMTR	C8289	C8289       	GL  	WING	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FLYING WIRE BROKEN.  INVESTIGATION FOUND FLYING WIRES WERE UNDERSIZE. AIRCRAFT IS AMATEUR BUILT.  PERSONNEL/MAINTE	NANCE ERROR. UNAPPROVED PART.					1	L	7	1 	3O	3	I	NT	EXPA1L71	EXPE3I	5	N	EXPP5N	 
2004010800041	20040108	00041	EU  	2004	1	8	AUS20031201      	1	20031124	G	2721	9787314203	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	RUDDER TAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					343					(AUS) PITCH TRIM ACTUATOR TOP ATTACHMENT FITTING CORRODED.  SUSPECTED INTERGRANNULAR TYPE CORROSION IS CAUSING THE SURFA	CE PROTECTIVE COATING TO LIFT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004010800042	20040108	00042	CE  	2004	1	8	AUS20031202      	1	20031124	G	5711	04263071	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING SPAR ANGLE CONTAINED INTERGRANNULAR CORROSION IN AREA WHERE IT PASSES THROUGH THE FUEL TANK CAVITY.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2004010600020	20040106	00020	EA  	2004	1	6	AUS20031203      	2	20031111	G	7414	101630456R	MAGNETO         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			396  							(AUS) RT MAGNETO HOUSING SEPARATING DUE TO LOOSE RETAINING SCREWS.  INTERNAL INSPECTION ALSO FOUND THAT THE ROTATING MAG	NET HAD CONTACTED THE HOUSING CAUSING DAMAGE TO BOTH ITEMS.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2004010600176	20040106	00176	CE  	2004	1	6	AUS20031204      	1	20031117	G	2797		WIRE            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	AILERON CONTROL	LOOSE           	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) PILOT REPORTED AILERONS JAMMING AFTER TAKE OFF. THE JAMMING CONTINUED INTERMITTENTLY AND AFTER LANDING THE PILOT W	AS ABLE TO DUPLICATE THE PROBLEM. IT WAS SUSPECTED THAT A LOOSE WIRE MAY HAVE BEEN FOULING WITH THE PULLEY ON THE PILOTS	 CONTROL YOKE.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2004010600177	20040106	00177	NM  	2004	1	6	AUS20031205      	1	20031125	G	5397		WIRE HARNESS    			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					FUSELAGE	WORN            	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRING LOOM LOCATED AT BS 1000 BEHIND OVERHEAD LOCKERS CHAFED THROUGH INSULATION BLANKET AND CONTACTED FUSELAGE FR	AME CAUSING BURNING OF WIRES AND DAMAGE TO THE INSULATION BLANKET AND FRAME. AREA OF DAMAGE TO FRAME WAS APPROXIMATELY 4	.762MM BY 2.381MM(0.185IN BY 0.0937IN).				2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2004010600178	20040106	00178	WP  	2004	1	6	AUS20031206      	1	20031124	G	6210	C0162	BLADE           			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAIN ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE UPPER SKIN SUSPECT DELAMINATED. DELAMINATED AREA STARTS APPROXIMATELY 381MM (15IN) IN FROM BLADE 	TIP TO 1295.4MM (51IN) FROM THE BLADE TIP AND 63.5MM (2.5IN) IN FROM THE LEADINGEDGE. FOUND DURING INSPECTION IAW AD/R44	/18.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004010700029	20040107	00029	NM  	2004	1	7	AUS20031207      	1	20031126	G	3233		EYEBOLT         			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					MLG ACTUATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			54609							(AUS) RT WING LANDING GEAR RETRACTION ACTUATOR EYE END UNSCREWED BY APPROXIMATELY 12.7MM (0.5IN).						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010700095	20040107	00095	SO  	2004	1	7	AUS20031208      	1	20031127	G	7810	LW12437	EXHAUST DUCT    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE EXHAUST TRANSITION CRACKED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004010700096	20040107	00096	EU  	2004	1	7	AUS20031209      	2	20031126	G	7310	737M28500011	VALVE           			BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ENGINE FUEL	FAILED          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 1 ENGINE FUEL SHUTOFF VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004010800013	20040108	00013	SW  	2004	1	8	AUS20031210      	1	20031125	G	5710		STRUCTURE       			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  					RT WING	BIRD STRIKE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			14147							(AUS) RT WING LEADING EDGE DAMAGED BY BIRDSTRIKE.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
2004010800033	20040108	00033	NM  	2004	1	8	AUS20031211      	1	20031123	G	3810	DR62B	WATER HEATER    			BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					GALLEY	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) AFT GALLEY NR 1 WATER BOILER FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2004010800034	20040108	00034	NM  	2004	1	8	AUS20031212      	1	20031127	G	2910	DSC252B40124	HOSE            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			99999							(AUS) NOSE LANDING GEAR RETRACTION HOSE WALL FAILED.  LOSS OF NR 2 HYDRAULIC SYSTEM FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010600021	20040106	00021	NM  	2004	1	6	AUS20031213      	1	20031006	G	5312		BULKHEAD        			BOEING	737   	7373Q8      	1384670	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED IN WEB LOCATED AT THE TOP INBOARD CORNER OF THE LOWER LT RADAR MOUNT. CRACK LENG	TH APPROXIMATELY 9.525MM (0.375IN). FOUND DURING ULTRASONIC AND EDDY CURRENT INSPECTION IAW AD/B737/141.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004022700001	20040227	00001	GL  	2004	2	27	AUS20031214      	1	20031027	G	5102	20BHB	HOSE            			AMTR  	KAVAGH	B400        	       	GL  										PROPANE	FIRE            	W				O				OTHER                   				A			FLAME/FIRE                			CR	CRUISE         	1			AU	S 			88   							(AUS) VAPOUR PILOT LIGHT HOSE CAUGHT FIRE. DAMAGE TO HOSE MADE THE CAUSE OF THE FIRE DIFFICULT TO ASSESS BUT IT WAS SUSP	ECTED THAT THE HOSE HAD A SMALL HOLE OR SPLIT WHICH ALLOWED PROPANE GAS TO LEAK AND IGNITE.					1	B	0	0 	  				EXPA1B00					 
2004010700002	20040107	00002	WP  	2004	1	7	AUS20031215      	1	20031016	G	6720	C0311	PITCH CONTROL   			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TAIL ROTOR	ROUGH           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR PITCH CONTROL SYSTEM ROUGH IN OPERATION. FOUND DURING INSPECTION IAW AD/R44/17.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004010700003	20040107	00003	SW  	2004	1	7	AUS20031216      	1	20031126	G	2910	2781032001	TUBE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC TUBE CRACKED AND LEAKING IN BEND RADIUS.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2004010700030	20040107	00030	SO  	2004	1	7	AUS20031217      	2	20031125	G	8530	639649	ROCKER          			PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE CYLINDER	DEFORMED        	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 							BT24032			(AUS) NR 4 CYLINDER INTAKE ROCKER DEFORMED.  SUSPECT MANUFACTURING ERROR. ROCKER SHAFT RETENTION STUD BROKEN.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2004010700097	20040107	00097	CE  	2004	1	7	AUS20031218      	1	20031125	G	3233		CAP             			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			18286							(AUS) NOSE LANDING GEAR ACTUATOR END CAP CRACKED.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2004010700098	20040107	00098	NE  	2004	1	7	AUS20031219      	2	20031128	G	7200		ENGINE          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	RIGHT	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 										(AUS) DURING TAKEOFF RT ENGINE POWER WOULD NOT INCREASE TO TAKEOFF SETTINGS. THE RT ENGINE INDICATIONS REMAINED AT 85 PE	RCENT TO 90 PERCENT TORQUE AND THE RT PROPELLER WAS REPORTED TO REDUCE TO 1100 RPM.  ENGINE GROUND RUNS AND FUNCTIONAL C	HECKS COULD NOT CONFIRM OR REPRODUCE THE FAULT. AIRCRAFT HAS OPERATED FOR SEVERAL FLIGHTS WITH NO FURTHER PROBLEMS. DEFE	CT NOT CONFIRMED.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2004010700099	20040107	00099	NM  	2004	1	7	AUS20031220      	1	20031117	G	2436	GC1010245DIII	GCU             			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	DC SYSTEM	FAULTY          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 1 DC GENERATOR AND GCU SUSPECT FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700100	20040107	00100	EA  	2004	1	7	AUS20031221      	2	20031128	G	7250		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  						NOISY           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE POWER SECTION REMOVED DUE TO UNKNOWN NOISE.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2004010800014	20040108	00014	NM  	2004	1	8	AUS20031222      	1	20031119	G	2912	271T006812	FILTER          			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					HYDRAULIC SYSTEM	DAMAGED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LT HYDRAULIC FLUID DISCHARGED THROUGH DELTA (P) FITTING IN HYDRAULIC PUMP PRESSURE MODULE.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2004010800029	20040108	00029	NM  	2004	1	8	AUS20031223      	1	20031201	G	3244	445X16	TIRE            			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					LT MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LT LANDING GEAR NR 2 TIRE BLEW OUT DURING TAXI.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2004010800030	20040108	00030	EU  	2004	1	8	AUS20031224      	1	20031128	G	2932	9738114306	PRESSURE SWITCH 			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	INTERMITTENT    	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) HYDRAULIC PRESSURE SWITCH INTERMITTENT IN OPERATION.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004010800031	20040108	00031	WP  	2004	1	8	AUS20031225      	1	20031202	G	1430	NAS660531	BOLT            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					M/R SWASHPLATE	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR SWASHPLATE LOWER BOLT DAMAGED.  INVESTIGATION FOUND A FLAT SPOT ON THE BLADE SHANK.  SUSPECT MANUFACTUR	ING ERROR AS FLAT SPOT HAD BEEN CADMIUM PLATED.  FOUND DURING INSPECTION IAW AD/R44/20.					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004010800032	20040108	00032	NM  	2004	1	8	AUS20031226      	1	20031129	G	2820	20C1444	CHECK VALVE     			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL TANK	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					2176					(AUS) CENTER FUEL TANK RT BOOST PUMP DISCHARGE CHECK VALVE BODY CRACKED. CRACK LENGTH APPROXIMATELY 31.75MM (1.25IN).						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004010600022	20040106	00022	NM  	2004	1	6	AUS20031227      	1	20031126	G	7830		PLATE           			BOEING	767   	767330      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					THRUST REVERSER	SEPARATED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) NR 1 ENGINE THRUST REVERSER CASCADE VANE BLANKING PLATE SEPARATED AND ENTERED ENGINE CAUSING DAMAGE TO FAN BLADES 	(12OFF) AND ACOUSTIC PANEL.					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2004010600144	20040106	00144	NE  	2004	1	6	AUS20031228      	3	20031129	G	6111	8022531	COLLAR          			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROPELLER BLADE	SEPARATED       	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 								88362723		(AUS) NR 1 PROPELLER NR 1 BLADE COLLAR SEPARATED FROM BLADE AND STRUCK THE NO3 BLADE CAUSING IMPACT DAMAGE TO THE LEADIN	G EDGE. DEBRIS THEN STRUCK THE NR 5 LT CABIN WINDOW SURROUND STRUCTURE. INNER PANE OF THE WINDOW REMAINED INTACT.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010600146	20040106	00146	CE  	2004	1	6	AUS20031229      	1	20031124	G	5412		FIREWALL        			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	RT NACELLE	DISTORTED       	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) RT FIREWALL BUCKLED DUE TO ASSYMETRIC WASTER CONTACT DURING TAKEOFF IN GUSTY CONDITIONS. AIRCRAFT IS CONFIGURED AS	 AN AMPHIBIAN.					1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2004010600147	20040106	00147	NE  	2004	1	6	AUS20031230      	2	20030925	G	7321	0164448160	FUEL CONTROL    			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							A490B			(AUS) FUEL CONTROL UNIT FAULTY. SUSPECT FUEL TEMPERATURE SENSOR FAILED.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2004010700031	20040107	00031	EU  	2004	1	7	AUS20031231      	1	20031203	G	3260	1EN1	SWITCH          			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	MLG	CONTAMINATED    	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR SWITCHES AND OPERATING MECHANISM CONTAMINATED WITH GREASE.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2004010700094	20040107	00094	EU  	2004	1	7	AUS20031232      	1	20030917	G	6210	117150071	BLADE           			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE CRACKED IN BLADE THIMBLE RADIUS AREA. FOUND DURING REMOVAL AND INSPECTION IAW KHI KSB-117-168.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2004010800015	20040108	00015	EU  	2004	1	8	AUS20031233      	1	20030917	G	6210	117150071	BLADE           			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE CRACKED IN BLADE THIMBLE RADIUS AREA.  FOUND DURING REMOVAL AND INSPECTION IAW KHI KSB-117-168.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2004010800035	20040108	00035	NE  	2004	1	8	AUS20031234      	3	20031201	G	6111	8022532	COLLAR          	HAMSTD      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			6568 		8660457					(AUS) PROPELLER BLADE COLLAR ASSEMBLY CRACKED.  FOUND DURING FLEET-WIDE INSPECTION FOLLOWING SEPARATION OF BLADE COLLAR 	ON ANOTHER AIRCRAFT.   SEE MDR 03/1228.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010600023	20040106	00023	EU  	2004	1	6	AUS20031235      	1	20031013	G	5311	1152015	FRAME           			GROB  	G115  	G115        	       	EU  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	FUSELAGE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD FUSELAGE FRAME AND SUPPORTING CROSS BEAM FRACTURED. NOSE LANDING GEAR AFT ATTACHMENT FITTING IS ATTACHED T	O THE FRAME.					1	L	7	1 	3O	3	O	NT	A57EU   	E223	5	N	P9045	 
2004010600129	20040106	00129	NM  	2004	1	6	AUS20031236      	1	20031202	G	6320	A0061	GEARBOX         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FOLLOWING STRANGE NOISES ON RUNDOWN THE MAIN ROTOR GEARBOX WAS INSPECTED. THE MAIN ROTOR GEARBOX AND CHIP DETECTOR	 WERE FOUND TO BE CONTAMINATED WITH METAL. CHIP DETECTOR DID NOT ILLUMINATE CHIP LIGHT BUT WAS TESTED SERVICEABLE.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2004010600131	20040106	00131	NM  	2004	1	6	AUS20031237      	1	20031127	G	5311		FRAME           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME AFT CHORD HOLES (3OFF) CRACKED. AFT WEB HOLE CRACKED. FOUND DURING EDDY CURRENT INSPECTION IAW MFG 	DRAWING737R53-154-01.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004010700032	20040107	00032	NM  	2004	1	7	AUS20031238      	1	20031207	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					ENGINE/XMSN	DAMAGED         	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE BELTS JUMPED FORWARD ONE GROOVE. SUSPECT FAULTY BELTS.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2004010700086	20040107	00086	CE  	2004	1	7	AUS20031239      	1	20031202	G	5343	24130023	ATTACH FITTING  			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR ATTACHMENT FITTING CRACKED IN TWO PLACES. FITTING HAD BEEN MODIFIED IAW AD/C170/58, SEB	93-8 AND SK172-142.					1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2004010700087	20040107	00087	CE  	2004	1	7	AUS20031240      	1	20031112	G	5310		STRUCTURE       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	FUSELAGE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT STRUCTURE DETERIORATED. NUMEROUS DEFECTS FOUND DURING INSPECTION IAW AD/400/40.  MAIN LANDING GEAR ACTUAT	OR COLLAR CRACKED AT UPPER BARREL NEAR  WELD, FOUND USING MAGNETIC PARTICLE INSPECTION.  ENGINE MOUNT BEAM IB MOUNT DOUB	LER CRACKED.   LOWER CARRY THROUGH FRONT SPAR CAP PNO 5211178 CRACKED.  WING DISBOND DETECTED.   WING FRONT SPAR LUG INS	PECTION DEFECTS WERE FOUND ON ALLOWING ATTACHMENT FITTINGS PN 0822550-19, PN 0822550-20, PN0822550-21 AN D PN 0822550-22	 DEFECTS FOUND USING NON-DESTRUCTIVE TESTING METHODS.		1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2004010700088	20040107	00088	NM  	2004	1	7	AUS20031241      	1	20031127	G	2710	82700563S001	CONTROL CABLE   			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	AILERONS	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING AILERON CONTROL CABLES INCORRECTLY ROUTED AT OUTBOARD CONTROL QUADRANTS ON BOTH WINGS UNDER PANELS 	532AT AND 632AT. CABLES HAD NOT BEEN LOCATED IN THE QUADRANT GROOVE AND WERE OPERATING ON TOP OF THE QUADRANT CAUSING RU	BBING ON THE QUADRANT CAUSING WEAR. THE WEAR WAS STILL WITHIN MAINTENANCE MANUAL LIMITS WHEN FOUND. PANELS HAD NOT BEEN 	LIFTED AND WERE NOT REQUIRED TO BE LIFTED SINCE NEW. MANUFACTURING ERROR.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700089	20040107	00089	SO  	2004	1	7	AUS20031242      	1	20031207	G	7921	10717C	OIL COOLER      			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	ENGINE	SPLIT           	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) ENGINE OIL COOLER SPLIT ALONG WELD LOCATED AT THE OPPOSITE END TO THE FITTINGS. COMPLETE LOSS OF ENGINE OIL.						1	L	7	1 	3T	3	T	 	A3SW    	E2WE	6	C	P40EA	 
2004010800016	20040108	00016	NM  	2004	1	8	AUS20031243      	1	20031129	G	2731	6355B000103	MOTOR           			BOEING	737   	7377Q8      	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ELEVATOR TAB	FAILED          	W				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) STABILIZER TRIM MOTOR FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2004010800025	20040108	00025	SW  	2004	1	8	AUS20031244      	1	20031205	G	7603		POWER LEVER     			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE	INCORRECT       	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) LT ENGINE FUEL BYPASS LIGHT ILLUMINATED DURING TAKEOFF.  EXTENSIVE INVESTIGATION COULD FIND NO CAUSE FOR THE DEFEC	T. ENGINE GROUND RUNS AND POWER CHECKS WERE OK. SUSPECT CAUSED BY INCORRECTLY SET SPEED LEVER. DEFECT NOT CONFIRMED.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2004010800026	20040108	00026	SO  	2004	1	8	AUS20031245      	1	20031203	G	2435	23080013	STARTER GEN     			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	APU	UNSERVICEABLE   	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) APU STARTER-GENERATOR BRUSH COVER INSULATION NOT FITTED DURING OVERHAUL.  BRUSH LEADS SHORTED TO FRAME AND CAUSED 	DAMAGE TO THE TEST BENCH LOAD RESISTOR.  STARTER-GENERATOR HAD BEEN RETURNED FROM OVERHAUL AND WAS UNDERGOING BEDDING IN	 ON THE TEST RIG BEFORE FITMENT. PERSONNEL/MAINTENANCE ERROR.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2004010600024	20040106	00024		2004	1	6	AUS20031246      	4	20031128	G	2210	0106R2	SERVO           			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AUTOPILOT SYSTEM	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) AUTOPILOT ROLL SERVO FAULTY.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2004010600148	20040106	00148	NM  	2004	1	6	AUS20031247      	1	20031206	G	2722	65C370539	PCU             			BOEING	737   	737*        	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					RUDDER ACTUATOR	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) RUDDER PCU FAULTY CAUSING UNCOMMANDED RUDDER INPUT AFTER TOUCHDOWN. INPUT WAS TO THE RT FOR A SHORT PERIOD.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004010600163	20040106	00163	EA  	2004	1	6	AUS20031248      	2	20031201	G	7322	RSA5AD2	FCU             			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	FUEL CONTROL/REC	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1308 							(AUS) FUEL CONTROL UNIT AIR REFERENCE CHAMBER CONTAMINATED WITH FUEL.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2004010600165	20040106	00165	NE  	2004	1	6	AUS20031249      	2	20031202	G	7321	324485318	FUEL CONTROL    			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	LT ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			2486 							(AUS) LT ENGINE MECHANICAL FUEL CONTROL FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010600172	20040106	00172	CE  	2004	1	6	AUS20031250      	1	20031128	G	7120		CLAMP           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE MOUNT	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT LOWER CLAMP SPLIT ON LT SIDE.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2004010700033	20040107	00033		2004	1	7	AUS20031251      	4	20031128	G	3497		CONNECTOR       			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAGNETIC COMPASS	CORRODED        	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) COMPASS FLUX DETECTOR CONNECTOR CORRODED. SEE MDR 03/1246 FOR ASSOCIATED DEFECT.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2004010700091	20040107	00091	CE  	2004	1	7	AUS20031252      	1	20030920	G	2434	A139271	BRUSHES         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	DC ALTERNATOR	WORN            	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) ALTERNATOR BRUSHES BADLY WORN. ALTERNATOR FAILED CAUSING WIRING TO BURN AND FAILURE OF ALTERNATOR CONTROL UNIT AND	 CURRENT SENSOR AND FUSING OF THE ALTERNATOR FIELD CIRCUIT BREAKER.					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2004010700092	20040107	00092	NE  	2004	1	7	AUS20031253      	2	20031210	G	7297	430121301	WIRE HARNESS    			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					POWERPLANT	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 										(AUS) NR 1 ENGINE WIRING HARNESS FAULTY.  SUSPECT CAUSED BY WORN/DIRTY PINS IN CONNECTOR. INVESTIGATION TRACED FAULT TO 	N1 SPEED PICKUP ELECTRICAL CONNECTOR.					1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2004010700093	20040107	00093	EA  	2004	1	7	AUS20031254      	2	20031205	G	7421	REM37BY	SPARK PLUG      			GROB  	G115  	G115        	       	EU  	LYC   	O235  	O235H2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) SEVERAL SPARK PLUGS WORN/FOULED.						1	L	7	1 	3O	3	O	NT	A57EU   	E223	5	N	P9045	 
2004010800017	20040108	00017	NM  	2004	1	8	AUS20031255      	1	20031201	G	3320	17501	BALLAST         			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					SEAT 19	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) LIGHTING BALLAST LOCATED AT SEAT 19JK FAILED.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2004010800022	20040108	00022	EA  	2004	1	8	AUS20031256      	2	20031210	G	8530	74230	VALVE GUIDE     			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	LO360A1G6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	NR 1 CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 CYLINDER EXHAUST VALVE AND VALVE GUIDE WORN EXCESSIVELY.  VALVE NOT SEATING CORRECTLY.   FOUND DURING INSPECT	ION IAW AD/ENG/4 AMDT8.					1	L	7	2 	3O	3	O	 	A29CE   	1E10	5	C	P43GL	 
2004010800023	20040108	00023	SO  	2004	1	8	AUS20031257      	1	20031209	G	3230	42042	ARM             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LT MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT MAIN LANDING GEAR RETRACTION ARM BROKEN. ASSOCIATED FORK AND ROD END BENT. DAMAGE ALSO TO DOWNLOCK HOOK AND ROD	 END ASSEMBLY.  SUSPECT DOWNLOCK HOOK FAILED TO DISENGAGE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004010800024	20040108	00024	SO  	2004	1	8	AUS20031258      	1	20031130	G	5524	MS21260	STUD            			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	ELEVATOR CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ELEVATOR FORWARD CONTROL CABLE FAILED.  CABLE LOCKING STUD CORRODED.  CONTROL WHEEL HAD BEEN RESTRAINED WITH SE	AT BELT AND CABLE LOCK STUD FAILED DUE TO WIND GUSTS.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P33EA	 
2004010600025	20040106	00025	NM  	2004	1	6	AUS20031259      	1	20031205	G	3320	1167008141	CONNECTOR       			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					CABIN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					9902056827					(AUS) OVERHEAD ELECTRONICS UNIT (OEU) J1 HARNESS SEIZED AND FUSED INTO OEU CONNECTOR AT SEAT 37HJK.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010600117	20040106	00117	NE  	2004	1	6	AUS20031260      	2	20031206	G	7200		ENGINE          			BOEING	737   	73776N      	13844CH	NM  	GE    	CFM56 	CFM567B24   	 	NE  					NR 1	BIRD INGESTION  	W				C				ABORTED TAKEOFF         				E	C		VIBRATION/BUFFET          	F.O.D.                    		TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE BIRDSTRIKE. INVESTIGATION FOUND BIRD REMAINS BUT NO EVIDENCE OF DAMAGE.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2004010600119	20040106	00119	NM  	2004	1	6	AUS20031261      	1	20031018	G	5330		SKIN            			BOEING	747   	74748E      	2FOR   	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED IN UPPER FORWARD CORNER OF LOWER AFT CARGO DOOR CUTOUT FASTENER HOLE. CRACK WAS FOUND IN NR 	1 FASTENER HOLE AT THE 6 O'CLOCK POSITION WITH A LENGTH GREATER THAN 1.01MM (0.040IN). FOUND DURING INSPECTION IAW AD/B7	47/293 AND EI 747-053-017R01.				2	L	7	2 	4F	4	F	RT	A20WE   	E23EA				 
2004010600120	20040106	00120	EU  	2004	1	6	AUS20031262      	1	20031201	G	2750	7445B	VALVE           			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	T/E FLAP	FAULTY          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 					LK29					(AUS) FLAP EMERGENCY RELEASE VALVE OPERATED (POPPED).						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2004010600122	20040106	00122	EA  	2004	1	6	AUS20031263      	2	20031202	G	7322	25765362	INJECTOR        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE FUEL	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) ENGINE FUEL INJECTOR SYSTEM FAULTY.  LIMITED INFORMATION PROVIDED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2004010700037	20040107	00037	SW  	2004	1	7	AUS20031264      	1	20031214	G	2731	DL5040M6	ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ELEVATOR TAB	FAULTY          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			6510 							(AUS) ELEVATOR PITCH TRIM ACTUATOR FAULTY.  SUSPECT ACTUATOR BINDING INTERNALLY.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2004010700083	20040107	00083		2004	1	7	AUS20031265      	4	20031205	G	3416	5934PM3	ALTIMETER       			BNORM 	BN2   	BN2A21      	1520221	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	COCKPIT	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTIMETER OUT OF CALIBRATION.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2004010700084	20040107	00084	NM  	2004	1	7	AUS20031266      	1	20031205	G	3411		PIPE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					PITOT/STATIC SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AUXILIARY PITOT SYSTEM PIPE CHAFED AND LEAKING IN AREA LOCATED AT STN 1880 ABOVE SEAT 63DEFG.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010700085	20040107	00085	CE  	2004	1	7	AUS20031267      	1	20031210	G	5730		SKIN            			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	RT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FOLLOWING REMOVAL OF THE LT WING THE UPPER SKIN AND INNER RIB FLANGE WAS FOUND TO BE GROUND AWAY TO THE EXTENT THA	T THE RIVET EDGE DISTANCE WAS COMPROMISED. SOME RIVETS ALSO EXHIBIT GRINDINGMARKS. THE RT WING WAS THEN REMOVED AND INSP	ECTED AND FOUND TO BE IN A SIMILAR CONDITION. PERSONNEL/MAINTENANCE ERROR.				1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2004010800019	20040108	00019	CE  	2004	1	8	AUS20031269      	1	20031201	G	3222	AN431	BOLT            			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	NLG	BENT            	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) NLG UPPER TORQUE LINK UPPER BOLT TO STEERING COLLAR SEVERELY BENT AND ALMOST SHEARED.  INVESTIGATION ALSO FOUND TH	E STRUT UNDER EXTENDED DUE TO BEING OVERFILLED WITH OIL AND UNDER INFLATED WITH AIR.					1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2004010800020	20040108	00020	CE  	2004	1	8	AUS20031270      	1	20031215	G	3233	99101363	ACTUATOR        			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RT MLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 			68   							(AUS) RT MAIN LANDING GEAR ACTUATOR FAULTY.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2004010800021	20040108	00021	EA  	2004	1	8	AUS20031271      	2	20031117	G	7310	1776698	HOSE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	FUEL PRESSURE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) FUEL PRESSURE GAUGE SENSOR HOSE LEAKING IN AREA BEHIND INSTRUMENT PANEL.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2004010600026	20040106	00026	NM  	2004	1	6	AUS20031272      	1	20031202	G	3020		DOOR            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NR 4 NACELLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 ENGINE NACELLE ANTI-ICE PRESSURE RELIEF BLOWOUT DOOR MISSING.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010600125	20040106	00125	EU  	2004	1	6	AUS20031273      	1	20031215	G	5610		DRAIN LINE      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					WINDOW	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) DRAIN TUBE CONNECTION LOCATED BELOW WINDSCREEN FAILED ALLOWING WATER TO LEAK ONTO AND CONTAMINATE LANDING GEAR LOC	K HANDLE SOLENOID.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2004010700038	20040107	00038	SW  	2004	1	7	AUS20031274      	1	20031216	G	7500	8961153	GASKET          			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	BLEED AIR	FAILED          	W				O				OTHER                   				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE BLEED AIR LINE ATTACHMENT GASKET BLEW OUT ALLOWING HOTGAS TO BLOW ONTO ADJACENT FIRE WARNING DETECTOR.						1	H	7	2 	3T	4	T	 	2A4     	E2WE	6	C	P15EA	 
2004010700082	20040107	00082	CE  	2004	1	7	AUS20031275      	1	20031211	G	2910		VALVE           			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	HYD SYSTEM	CONTAMINATED    	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) HYDRAULIC SYSTEM UNLOADING VALVE CONTAINED DEBRIS UNDER THE VALVE SEAT CAUSING THE VALVE TO REMAIN PARTIALLY OPEN 	AND PREVENTING THE CORRECT HYDRAULIC PRESSURE FROM BEING REACHED.					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2004010800018	20040108	00018	EA  	2004	1	8	AUS20031276      	2	20031218	G	8550		SEAL            			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	OIL FILTER	DAMAGED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE OIL FILTER SEAL DAMAGED AND LEAKING.  SUSPECT SEAL DAMAGED DURING INSTALLATION.  PERSONNEL/MAINTENANCE E	RROR.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2004010800027	20040108	00027		2004	1	8	AUS20031277      	4	20031211	G	3416	40187592	COUNTER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ALTIMETER	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					77110459					(AUS) ALTITUDE INDICATOR BARO COUNTER SEIZED. FOUND DURING INSPECTION IAW AD/INST/9 AMDT6. DURING TESTING SEVERAL LIGHTI	NG LAMPS WERE FOUND TO BE BLOWN AND THE DRIVE MOTOR WAS ROUGH IN OPERATION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010800028	20040108	00028	SO  	2004	1	8	AUS20031278      	1	20031218	G	5711	62054001	SPAR            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8720 							(AUS) RT WING REAR SPAR CORRODED.  FOUND DURING INSPECTION IAW AD/PA28/40A.						1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2004010600027	20040106	00027		2004	1	6	AUS20031279      	4	20031210	G	3417	7000700975	ADC             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIR DATA COMPUTER (ADC) OUT OF CALIBRATION AT ALL ALTITUDES.  FOUND DURING INSPECTION IAW AD/INST9 AMDT6.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010600114	20040106	00114	SO  	2004	1	6	AUS20031280      	1	20031218	G	5711	62054000	SPAR            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8720 							(AUS) LT WING REAR SPAR CORRODED. FOUND DURING INSPECTION IAW AD/PA28/40A.						1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2004010600116	20040106	00116	SO  	2004	1	6	AUS20031281      	1	20031218	G	5320	6241100	CHANNEL         			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8720 							(AUS) LOWER REAR FUSELAGE CENTER CHANNEL SECTION CONTAINED DISSIMILAR METAL CORROSION ON BOTH SIDES IN AREA OF REAR SPAR	 ATTACHMENT. FOUND DURING INSPECTION IAW AD/PA28/40A AND PIPER SERVICE BULLETIN NR 977.					1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2004010700039	20040107	00039	NM  	2004	1	7	AUS20031282      	1	20031213	G	2597		WIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					CHILLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER DECK CHILLER WIRES W8599-006-10, W8599-005-10 AND W8599-006-10 CHAFED.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004010700081	20040107	00081		2004	1	7	AUS20031283      	4	20031212	G	3416	70007641	POTENTIOMETER   			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ALTIMETER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTITUDE INDICATOR POTENTIOMETER UNSERVICEABLE. FOUND DURING INSPECTION IAW AD/INST9 AMDT6. SEVERAL LIGHTING LAMPS	 ALSO FOUND TO HAVE FAILED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004032900085	20040329	00085	EU  	2004	3	29	AUS20031284      	1	20031216	G	3260	867501	SENSOR          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MLG INDICATOR	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LT LANDING GEAR UPLOCK SENSOR FAILED. SEE ALSO MDR 03/1273 FOR ASSOCIATED DEFECT.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2004032900086	20040329	00086	NE  	2004	3	29	AUS20031285      	2	20031204	G	7200		ENGINE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3	FAILED          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 3 ENGINE FAILED.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2004032900087	20040329	00087	EU  	2004	3	29	AUS20031286      	1	20031222	G	3020	S230SST	CLAMP           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ANTI ICE VALVE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			16544							(AUS) ENGINE ANTI-ICE VALVE PIPE PN 1159P41706-7 WORN AND BROKEN BY CLAMP. CLAMP WAS INCORRECT PART PN  S230SST (CORRECT	 CLAMP PN GC500BV04CTN). THE TEFLON SLEEVE ON THE CLAMP HAD WORN AWAY RESULTING IN METAL TO METAL CONTACT BETWEEN THE CL	AMP AND PIPE WHICH WAS CHAFED TO THE POINT OF FAILURE. UNAPPROVED PART.  PERSONNEL/MAINTENANCE ERROR.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2004032900088	20040329	00088	NM  	2004	3	29	AUS20031287      	1	20031206	G	7312	G726681	ELEMENT         			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	FUEL HEATER	FAULTY          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) NR 1 ENGINE FUEL HEATER THERMAL ELEMENT FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004032900089	20040329	00089	NM  	2004	3	29	AUS20031288      	1	20031218	G	2910	82970009199	PIPE            			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	UNSERVICEABLE   	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			99999							(AUS) RT MAIN LANDING GEAR HYDRAULIC UP' PIPE LEAKING.  INVESTIGATION FOUND A CRACK IN THE SIDEWALL OF THE PIPE LOCATED 	AT A BEND RADIUS. SUSPECT THE BEND RADIUS WAS DEFORMED DURING FIT AT  MANUFACTURE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004032900090	20040329	00090	NM  	2004	3	29	AUS20031289      	1	20031210	G	7697	BACC63CC1415SN	CONNECTOR       			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM567B24   	 	NE  					ENGINE CONTROLS	LOOSE           	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) ENGINE CONNECTOR D11286 NOT CONNECTED.  CONNECTOR WAS SITTING ON TOP OF THE RECEPTACLE.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2004032900091	20040329	00091	EU  	2004	3	29	AUS20031290      	1	20031214	G	2197	P3802B	WIRE            			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					AIR CONDITIONING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			17418							(AUS) FORWARD AVIONICS BAY WIRING DAMAGED.  EFIS FAN CIRCUIT BREAKER FAILED AND COULD NOT BE RESET.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2004032900092	20040329	00092	NM  	2004	3	29	AUS20031291      	1	20031215	G	2910	AN81510D	COUPLING        			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYDRAULIC SYSTEM	UNSERVICEABLE   	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 			99999							(AUS) NR 2 HYDRAULIC SYSTEM PRESSURE FILTER MANIFOLD UNION FRACTURED.  SUSPECT UNION FAILED DUE TO OVERTORQUING DURING I	NSTALLATION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004032900093	20040329	00093	NE  	2004	3	29	AUS20031292      	1	20031226	G	2612	7630607902104	FIRE DETECTOR   			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 2 ENGINE	FAULTY          	W				O				OTHER                   				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			6868 							(AUS) NR 2 ENGINE BAY FIRE DETECTOR FAULTY.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2004032900094	20040329	00094	NE  	2004	3	29	AUS20031293      	2	20031224	G	7200	200304018	ENGINE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 2 ENGINE UNCOMMANDED SHUTDOWN.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2004032900053	20040329	00053	NE  	2004	3	29	AUS20031294      	2	20031230	G	7200		ENGINE          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	RIGHT	MAKING METAL    	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE OIL SYSTEM FAULTY.   LOW OIL PRESSURE AND OIL TEMPERATURE HIGH.  INVESTIGATION FOUND A SMALL METAL SLIVE	R ON THE POWER UNIT CHIP DETECTOR WHICH HAD NOT ACTIVATED THE INDICATOR.  THE FRONT COMPRESSOR SEAL WAS ALSO FOUND TO BE	 LEAKING.  DURING ENGINE GROUND RUN THE CHIP INDICATOR ILLUMINATED AND THE DETECTOR WAS FOUND TO HAVE A NUMBER OF CONTAM	INANTS ON IT.  THE ENGINE WAS REPLACED.  SUSPECT FAILURE OF COMPRESSOR SCAVENGE PUMP.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2004032900062	20040329	00062	CE  	2004	3	29	AUS20031295      	1	20031223	G	5210	1144000301	SEAL            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	CABIN DOOR	SPLIT           	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) CABIN DOOR SEAL SPLIT ALONG TOP SECTION. LENGTH OF SPLIT APPROXIMATELY 50MM (1.96IN).						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2004032900063	20040329	00063	CE  	2004	3	29	AUS20031296      	1	20031128	G	2820	3034	HOSE            			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	FUEL SYSTEM	DETERIORATED    	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) REAR ENGINE FUEL PRESSURE HOSE LOCATED BETWEEN FIREWALL AND FUEL MANIFOLD DETERIORATED AND LEAKING ONTO LT EXHAUST	 STACK.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2004032900064	20040329	00064	NM  	2004	3	29	AUS20031297      	1	20031229	G	3260	841005	PSEU            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	RT MLG	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOOR PROXIMITY SENSE ELECTRONIC UNIT (PSEU) FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004032900065	20040329	00065	SW  	2004	3	29	AUS20031298      	1	20030926	G	3213	ED12758	CLEVIS          			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR CLEVIS CRACKED.  FOUND USING MAGNETIC PARTICLE INSPECTION AND VISUAL TECHNIQUES.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2004032900066	20040329	00066	NE  	2004	3	29	AUS20031299      	2	20031229	G	7210		GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	CONTAMINATED    	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			3322 				CPGB2272			(AUS) ENGINE COMBINING GEARBOX METAL CONTAMINATION.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2004032900067	20040329	00067	NM  	2004	3	29	AUS20031300      	1	20031217	G	3246	3006202	WHEEL           			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 			131  							(AUS) NR 1 MAIN WHEEL FAILED AT IB WHEEL RIM.  APPROXIMATELY HALF OF THE RIM (180 DEGREE ARC) HAD FAILED AND BROKEN AWAY	. TIRE DEFLATED AND ADJACENT BRAKE UNIT SUFFERED DAMAGE AT THE HOSE FITTING.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004032900068	20040329	00068	CE  	2004	3	29	AUS20031301      	1	20031229	G	3230	084012515	ROD             	CESSNA      	310R        	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C*     	GL  	MLG	FRACTURED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR AFT PUSH/PULL ROD ASSEMBLY FRACTURED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2004032900069	20040329	00069	CE  	2004	3	29	AUS20031302      	1	20031208	G	2434	ES4118	BRUSH BLOCK     			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	DC GENERATOR	WORN            	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			1469 		5112030					(AUS) ALTERNATOR GROUND BRUSH COMPLETELY WORN AWAY. SLIP RING DAMAGED BY WORN BRUSH.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004032900070	20040329	00070	CE  	2004	3	29	AUS20031303      	1	20031228	G	5311	VARIOUS	FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAMES CRACKED AT FRAME CUTOUTS.  FRAME LOCATED AT FS 286.75.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2004032900071	20040329	00071	NM  	2004	3	29	AUS20031304      	1	20031220	G	2822		IMPELLER        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					BOOST PUMP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2706 		0655					(AUS) LT CENTER AUXILIARY FUEL TANK OVERRIDE PUMP SEIZED. INVESTIGATION FOUND PART OF THE IMPELLER BROKEN AND JAMMED IN 	THE PUMP CASING.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2004032900074	20040329	00074	CE  	2004	3	29	AUS20031305      	1	20031215	G	2434	ES4118	BRUSHES         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	DC GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			125  		D052304					(AUS) ALTERNATOR GROUND BRUSH ALMOST WORN AWAY.   POSITIVE BRUSH WAS HARDLY  WORN.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2004032900075	20040329	00075	NM  	2004	3	29	AUS20031306      	1	20031230	G	5610	5893543130	WINDSHIELD      			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) FIRST OFFICERS NR 1 WINDOW CRACKED IN OUTER PANE. CRACKING APPEARS TO ORIGINATE FROM DELAMINATION AT TOP LT AREA O	F WINDOW.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004032900076	20040329	00076	NM  	2004	3	29	AUS20031307      	1	20031222	G	7830	RB211524H	THRUST REVERSER 			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE	FAULTY          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) ENGINE THRUST REVERSER FAULTY.  LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2004032900077	20040329	00077	CE  	2004	3	29	AUS20031308      	1	20031218	G	2434	ES4118	BRUSH BLOCK     			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	DC GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			237  		A032173					(AUS) ALTERNATOR BRUSHES WORN UNEVENLY.  GROUND BRUSH WORN COMPLETELY AWAY WHILE THE POSITIVE BRUSH APPEARED IN NEAR NEW	 CONDITION.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2004032900078	20040329	00078	CE  	2004	3	29	AUS20031309      	1	20031218	G	5712	0823400110	BULKHEAD        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	AMTR	C8289	C8289       	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING TIP TANK REAR ATTACHMENT BULKHEAD CRACKED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	N	EXPP5N	 
2004032900079	20040329	00079	EA  	2004	3	29	AUS20031310      	2	20031215	G	8520	SL13521	BEARING         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	CONNECTING ROD	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			376  				L1887951A			(AUS) CONNECTING ROD BIG END BEARING DELAMINATED.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2004032900080	20040329	00080	GL  	2004	3	29	AUS20031311      	2	20031227	G	7200		ENGINE          			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					NR 3	FAILED          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 3 ENGINE FAILED. SUSPECT HAIL INGESTION.						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2004032900081	20040329	00081	NE  	2004	3	29	AUS20031312      	3	20031103	G	6111	8175981	SEAL            	HAMSTD      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER BLADE	DAMAGED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					881235					(AUS) RT PROPELLER BLADE SEAL TORN ALONG OUTER SIDE. LENGTH OF TEAR APPROXIMATELY 38.1MM (1.5IN). PROPELLER HUB LEAKING 	OIL.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004032900082	20040329	00082	WP  	2004	3	29	AUS20031313      	2	20031216	G	7230	31070515	SEAL            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	COMPRESSOR	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TO	TAKEOFF        	1			AU	S 			1386 				P31229			(AUS) RT ENGINE COMPRESSOR SEAL SUSPECT FAULTY.  LEAKING OIL CAUSED SMOKE IN COCKPIT.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2004032900083	20040329	00083	EA  	2004	3	29	AUS20031314      	2	20031219	G	7322	RSA5AD1	FUEL CONTROL    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	IC235	IC235LFA7570	EA  	ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CONTROL UNIT AIR CHAMBER CONTAMINATED BY FUEL.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2004032900084	20040329	00084	NM  	2004	3	29	AUS20031315      	1	20031218	G	3411		PITOT HEAD      			BOEING	737   	7377BX      	13844D2	NM  	GE    	CFM56 	CFM567B24   	 	NE  					PITOT/STATIC SYS	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LT PITOT PROBE CONTAMINATED BY MUD FROM SUSPECTED WASP NEST.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2004032900104	20040329	00104	NM  	2004	3	29	AUS20031316      	1	20031219	G	3411		PITOT TUBE      			BOEING	737   	737800*     	       	NM  	GE    	CFM56 	CFM56*      	13802	NE  					PITOT/STATIC SYS	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LT ELEVATOR FEEL SYSTEM PITOT TUBE CONTAMINATED WITH MUD FROM WASPS.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2004032900105	20040329	00105	CE  	2004	3	29	AUS20031318      	1	20031128	G	2750	14601007	CONTROL CABLE   			CESSNA	337   	337H        	2075732	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C310  	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) IB FLAP CABLE CONTAINED BROKEN WIRES LOCATED AT TIGHT BEND AROUND THE BELLCRANK.  APPROXIMATELY 50 PERCENT OF THE 	WIRES WERE BROKEN.  INSPECTION CARRIED OUT IN RESPONSE TO MFG ALERT.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2004032900106	20040329	00106	NM  	2004	3	29	AUS20031319      	1	20031127	G	2822	609891002	PUMP            			BOEING	737   	7377Q8      	1384418	NM  	GE    	CFM56 	CFM56*      	13802	NE  					FUEL BOOST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRIC FUEL PUMP FAILED INSPECTION IAW AD/737/198/BORO.  FOUND USING BOROSCOPE AND X-RAY INSPECTION.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2004032900107	20040329	00107	CE  	2004	3	29	AUS20031320      	1	20031215	G	5320		STRAP           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EMERGENCY EXIT DOOR CUTOUT FRAME STRAP AT FS187.375 CRACKED APPROXIMATELY 50 PERCENT THROUGH.  CRACK LENGTH APPROX	IMATELY 25.4MM(1IN).					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2004032900108	20040329	00108	SO  	2004	3	29	AUS20031321      	1	20031215	G	5500		STRUCTURE       			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  	AMTR	C8289	C8289       	GL  	STABILIZER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILIZER STRUCTURE CORRODED.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	EXPP5N	 
2004042900002	20040429	00002	CE  	2004	4	29	AUS20031322      	1	20031216	G	3233	5721319	ROD             	CESSNA      		CESSNA	414   	414         	2075908	CE  										ACTUATOR	STICKING        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 			50   		231					(AUS) MAIN LANDING GEAR ACTUATOR FAULTY.  INVESTIGATION FOUND CHROME CHIPPING AWAY FROM THE EDGE OF THE LOCK GROOVE CAUS	ING THE LOCK RETAINING RING TO STICK.					1	L	7	2 	3O			RT	A7CE    					 
2004033000120	20040330	00120	SW  	2004	3	30	AUS20031323      	1	20031126	G	5414	2735112026	SKIN            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE IB NACELLE SKIN CRACKED. STRINGER AND FORMER ALSO CRACKED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2004033000121	20040330	00121	CE  	2004	3	30	AUS20031324      	1	20031218	G	2434	D0FF10300JR	ALTERNATOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	DC SYSTEM	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			1925 							(AUS) ALTERNATOR SUSPECT FAULTY. ALTERNATOR BENCH TESTED OK, BUT REPLACED DUE TO HIGH HOURS.  FAULT HAS NOT REOCCURRED S	INCE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004033000122	20040330	00122	NM  	2004	3	30	AUS20031325      	1	20031227	G	2422	S282T0044	INVERTER        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AC SYSTEM	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			AU	S 										(AUS) STANDBY INVERTER SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2004033000123	20040330	00123	NM  	2004	3	30	AUS20031326      	1	20031231	G	7830		BLOCKER DOOR    	RROYCE      		BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					THRUST REVERSER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 ENGINE THRUST REVERSER NR 1 BLOCKER DOOR BREAKING UP. A 25.4MM BY 304.8MM (1IN BY 12IN) PORTION OF ONE EDGE H	AD SEPARATED.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004033000124	20040330	00124	NM  	2004	3	30	AUS20031327      	1	20031228	G	5610		WINDOW          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					COCKPIT	OUT OF ADJUST   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) CAPTAINS NR 2 WINDOW OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2004033000132	20040330	00132	NM  	2004	3	30	AUS20031328      	1	20031230	G	3411		LINE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PITOT/STATIC SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AUXILIARY PITOT SYSTEM LEAKING.  LEAK TRACED TO PITOT LINE RUBBING ON TIE ROD BRACKET AT STN 410 RBL 50 WL300.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2004033000133	20040330	00133		2004	3	30	AUS20031329      	4	20031229	G	3431	6225221120	RECEIVER        			BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					LOCALIZER/VOR SY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			7938 		1817					(AUS) LT INSTRUMENT LANDING SYSTEM (ILS) RECEIVER FAILED.  LT ILS CIRCUIT BREAKER TRIPPED.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2004033000134	20040330	00134	CE  	2004	3	30	AUS20031330      	1	20031229	G	5522		SKIN            			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ELEVATOR RIVETS FAILED ALLOWING LOWER ELEVATOR SKIN TO BECOME LOOSE AT THE IB TRAILING EDGE.  INVESTIGATION FOU	ND SIMILAR PROBLEMS WITH THE RIVETS ALONG THE LEADING EDGE. THE RIVETS WERE .0937 INCH POP RIVETS.  INSPECTION OF THE RT	 ELEVATOR FOUND THE SAME PROBLEMS.  SUSPECT SKIN HAD BEEN REPLACED SOME YEARS AGO.				1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2004033000135	20040330	00135	CE  	2004	3	30	AUS20031331      	1	20030902	G	2910	P40791	SHUTOFF VALVE   			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					HYD SYSTEM	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE FIREWALL MOUNTED HYDRAULIC FIREWALL SHUTOFF VALVE FAULTY. VALVE WOULD NOT FULLY CLOSE WHEN THE FIRE SWIT	CH WAS  OPERATED WHICH ALLOWED HYDRAULIC FLUID TO LEAK PAST THE VALVE.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2004033000136	20040330	00136	GL  	2004	3	30	AUS20031332      	2	20031227	G	7230		BLADE           			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					COMPRESSOR	FAILED          	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CL	CLIMB          	1			AU	S 										(AUS) ENGINE VIBRATION AFTER TAKEOFF.  BOROSCOPE INSPECTION FOUND FOURTH STAGE HPC BLADE FAILED.						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2004033000137	20040330	00137	EU  	2004	3	30	AUS20031333      	1	20031215	G	5415	68120251	FITTING         			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT FITTINGS PN 68-1.2025-1 AND PN 68-1.2025-2 CRACKED AROUND RIVET HOLES.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2004033000138	20040330	00138	EU  	2004	3	30	AUS20031334      	1	20031215	G	5711	68140093	DOUBLER         			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPAR DOUBLERS PN 68-1.4009-3 AND PN 68-1.4009-4  CONTAINED A SMALL AMOUNT OF CORROSION.  DOUBLERS ARE LOCATED	 IN AREA BEHIND ENGINES AND ENGINE FIREWALLS.					1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2004033000139	20040330	00139	EU  	2004	3	30	AUS20031335      	1	20031229	G	3242	5011830	BRAKE ASSY      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 			3059 							(AUS) NR 1 BRAKE ASSEMBLY FAILED. INSPECTION FOUND THAT THE PISTONS HAD HOLED THE CARBON DISK PRESSURE PLATE CAUSING IT 	TO DELAMINATE AND THEN ALLOW THE PISTONS TO CONTACT THE FIRST ROTATING DISK R1 CAUSING SEVERE WEAR TO R1 AND THE PISTONS	.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2004033000140	20040330	00140	CE  	2004	3	30	AUS20031336      	1	20031220	G	3242	9540666	HOUSING         			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3Z	HCB3Z302    	GL  	BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR BRAKE HOUSING CRACKED ON MOUNT FLANGE.						1	L	7	2 	3R	3	R	 	A765    	5E1	5	C	P907	 
2004033000141	20040330	00141	NM  	2004	3	30	AUS20031337      	1	20031228	G	3242		PISTON          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					BRAKE	JAMMED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 FRONT MAIN BRAKE ASSEMBLY PISTON JAMMED AND ROTORS DISINTEGRATING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2004033000142	20040330	00142	EU  	2004	3	30	AUS20031338      	1	20031222	G	6510	350A34021006	DRIVE SHAFT     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					5087					(AUS) TAIL ROTOR DRIVESHAFT FORWARD SPLINED END DEBONDED AND RIVETS WORKING.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004033000144	20040330	00144	NM  	2004	3	30	AUS20031339      	1	20031227	G	3246		BOLT            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR OUTBOARD WHEEL TIE BOLT SHEARED IN THREADED SECTION.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2004033000159	20040330	00159	NM  	2004	3	30	AUS20031340      	1	20031220	G	5330		SKIN            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED AT FORWARD UPPER CORNER OF AFT CARGO DOOR CUTOUT.  FOUND DURING INSPECTION IAW EI 747-053-01	70R1 AND AD/B747/293.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2004033000160	20040330	00160	EU  	2004	3	30	AUS20031341      	1	20031222	G	3242	AHA1899	TORQUE TUBE     	DUNLOP      		BAG   	JETSTM	JETSTM4112  	       	EU  										BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					RM199					(AUS) BRAKE ASSEMBLY TORQUE TUBE CRACKED. CRACK LENGTH 3.175MM(0.125IN). FOUND DURING MAGNETIC PARTICLE INSPECTION (MPI)	.					1	L	7	2 	4T			RT	A196    					 
2004033000161	20040330	00161		2004	3	30	AUS20031342      	4	20031212	G	3410	4066192901X	DISPLAY         			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FLIGHT ENVIRONME	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRONIC DISPLAY UNIT (EDU) WAS INCORRECT PART.  MANUFACTURERS AME PLATE WAS IN RED WHICH INDICATED THAT IT WAS 	AN ENGINEERING EVALUATION UNIT. THE AIRWORTHY UNITS HAVE A BLACK NAMEPLATE. AND CARRY THE PN 4066192-901.   PERSONNEL/MA	INTENANCE ERROR.   UNAPPROVED PART.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2004033000162	20040330	00162		2004	3	30	AUS20031343      	4	20031028	G	3460	4082260937	CONTROL PANEL   			BOEING	737   	737*        	       	NM  	GE    	CFM56 	CFM567B24   	 	NE  					FLT MANAGEMENT	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) MODE CONTROL PANEL (MCP) FAILED.  INVESTIGATION FOUND THE FAULT IN U14 ON MICROPROCESSOR CCA A10.						2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003080500034	20030805	00034	SO  	2003	8	5	B30R2003003      	2	20030602	G	8530	655465A4	CYLINDER        			CESSNA	210   	T210L       	2073449	CE  	CONT  	O550  	IO550*      	 	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ENGINE	CRACKED         	B			B30R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	732JF	309  	50   			21061543	821007	A48936A		DURING ANNUAL ENGINE INSPECTION A MECHANIC NOTED BLUE FUEL STAIN IN THE AREA OF THE NR 1 CYLINDER FUEL DRAIN PORT. BLUE 	FUEL STAIN WAS REMOVED AND ENGINE FUEL SYSTEM WAS PRESSURIZED. AT THIS TIME FUEL STARTED TO DRIP FROM IN BETWEEN THE FIR	ST TWO COOLING FINS NEXT TO THE DRAIN PORT. FURTHER INSPECTION OF THE COOLING FIN AREA WITH A BORESCOPE REVEALED TWO HOL	ES IN THE CYLINDER CASTING WITH A CRACK IN BETWEEN HOLES.			1	H	7	1 	3O	3	O	 	3A21    	E3SO	5	C	P36EA	 
2003123000029	20031230	00029	EU  	2003	12	30	B30R20031120     	1	20031211	G	5414		SKIN            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					COWL DOOR	DELAMINATED     	B			B30R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204X	1378 	100  			3099	9570			DURING 100 HOUR INSPECTION, IT WAS DISCOVERED THAT THE INNER FIBERGLASS SKIN OF THE UPPER AFT SECTION OF THE ENGINE COWL	ING HAD DISBONDED FROM THE HONEYCOMB STRUCTURE OF THE COWLING. PRYROPEL INSULATION WAS TO BE INSTALLED WHILE THE AIRCRAF	T WAS IN INSPECTION AND THE COWLING WAS REMOVED TO FACILITATE THIS MAINTENANCE. REPAIRS TO BE MADE TO COWLING IAW MANUFA	CTURER'S REPAIR PROCEDURES. THEN PRYROPEL WILL BE INSTALLED IAW SOW-03-087.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003091800127	20030918	00127	CE  	2003	9	18	B30R20033010     	1	20030604	G	5520	1016200111	HINGE FITTING   			BEECH 	200   	A200        	1152921	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CORRODED        	B			B30R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074G					BC17				DURING A 14 DAY CORROSION INSP, MECH NOTED PAINT BLISTERING AROUND RIGHT ELEVATOR HINGE FITTING MOUNTING HARDWARE. REMOV	AL OF PAINT BLISTERS FROM HINGE FITTING REVEALED INTERGRANULAR CORROSION. HINGE FITTING WAS REMOVED AND CORRODED AREA WA	S CLEANED. AT THIS TIME IT WAS NOTED THAT CORROSION DAMAGE WAS BEYOND A SERVICABLE LIMIT. AT FACILITY, WE OPERATE 3 OF T	HESE AGING AIRCRAFT. WE HAVE FOUND SAME PARTS CORRODED ON MOST RECENT CORROSION INSP OF OUR 2 OTHER AIRCRAFT. THIS AIRCR	AFT WAS REPAINTED 2 YEARS AGO. DUE TO TYPE AND NATURE OF THIS CORROSION, WE ADVISE THAT OPERATORS PAY ATTENTION TO DETAI	L FOR CORROSION ON THE HORIZONTAL AND VERTICAL STABILIZERS AND THERE FLIGHT CONTROL SUFACES.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003091800128	20030918	00128	CE  	2003	9	18	B30R20033011     	1	20030604	G	5520	1016200121	HINGE BRACKET   			BEECH 	200   	A200        	1152921	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	DAMAGED         	B			B30R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074G					BC17				DURING A 14 DAY CORROSION INSPECTION, MECHANIC NOTED PAINT BLISTERING ON THE RIGHT INBOARD ELEVATOR HINGE BRACKET. REMOV	AL OF THE PAINT BLISTERS FROM HINGE BRACKET REVEALED INTERGRANULAR CORROSION. THE HINGE BRACKET WAS REMOVED AND CORRODED	 AREA WAS CLEANED. AT THIS TIME IT WAS NOTED THAT THE CORROSION DAMAGE WAS BEYOND A SERVICABLE LIMIT. AT OUR FACILITY, W	E OPERATE 3 OF THESE AGING AIRCRAFT. THIS AIRCRAFT WAS REPAINTED 2 YEARS AGO. DUE TO THE TYPE AND NATURE OF THIS CORROSI	ON, WE ADVISE THAT THE OPERATORS OF THE PAY ATTENTION TO DETAIL FOR CORROSION ON THE HORIZONTAL AND VERTICAL STABILZERS 	AND THEIR FLIGHT CONTROL SURFACES.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003111300069	20031113	00069	CE  	2003	11	13	B30R20033017     	1	20030925	G	2897	652635537	WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL PUMP	CHAFED          	B			B30R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26621					5500593				IN TROUBLESHOOTING A SUBMERGED FUEL BOOST PUMP CIRCUIT BREAKER POPPING, MAINTENANCE TECHNICIANS DISCOVERED THE FUEL BOOS	T PUMP ELECTRICAL HARNESS HAD CHAFFED THROUGH THE BUNDLE INSULATION AND WAS ARCING ON ALUMINUM FUEL LINE P/N 6526355-37 	INSIDE THE WET WING.  THE POTENTIAL FOR FUEL VAPOR IGNITION AND AN EXPLOSION.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003111300068	20031113	00068	CE  	2003	11	13	B30R20033018     	1	20030925	G	2897		WIRE            			CESSNA	500   	550         	2076604	CE  										FUEL BOOST	ARCED           	B			B30R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	03	26494					5500605				IN TROUBLESHOOTING A SUBMERGED FUEL BOOST PUMP CIRCUIT BREAKER POPPING, MAINTENANCE TECHNICIANS DISCOVERED THE FUEL BOOS	T PUMP ELECTRICAL HARNESSES HAD CHAFED THROUGH THE BUNDLE INSULATION AND WAS ARCING ON ALUMINUM FUEL LINES P/N 6526355-3	7 INSIDE BOTH THE LEFT AND RIGHT WET WING. THE POTENTIAL FOR FUEL VAPOR IGNITION COULD HAVE CAUSED AN EXPLOSION.				1	L	7	2 	4F			 	A22CE   					 
2003042800022	20030428	00022	CE  	2003	4	28	B3OR20030001     	1	20030319	G	7160	21095011	ALT AIR DOOR    			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	SEPARATED       	B			B3OR	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			SW	03	5515Y	930  				21064233	289125R			ON CLIMB OUT, ENG BEGAN TO RUN ROUGH, DROPPING 300 RPM. DURING GROUND RUN UP, MAG CHECK AT 1700 RPM SHOWED NO PROBLEM. R	UN UP TO PWR AND ENG RAN FINE, THEN DROPPED 300 RPM AND RAN ROUGH. MAINT REMOVED ALL SPARK PLUGS AND FOUND LEAD FOULED. 	CLEANED AND FIRE CHECK SPARK PLUGS. CHANGED IGN LEADS, BOTH MAGS AND ALL SPARK PLUGS, SUSPECT BURN MARKS AT LEADS TO HAR	NESS. AIR INTAKE DUCT ALTERNATE AIR DOOR WAS FOUND TO BE UNHINGED AND FOUND HINGE PIN AND DOOR LAYING IN DUCT. NO SPRING	 WAS FOUND.  ALL CYL WERE BOROSCOPED. NR 5 CYLINDER WAS FOUND TO HAVE IMPACT MARKS ON TOP OF PISTON, HEAD AND INTAKE VAL	VE SEAT. NR 5 CYL WAS REPLACED. INTAKE DOOR SPRING HAD ENTERED CYLINDER AND EXITED EXHAUST VALVE, IT WAS NEVER FOUND.	1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003043000100	20030430	00100	SO  	2003	4	30	B3OR2003002      	2	20030429	G	8550	65217122	DIPSTICK        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O550  	IO550*      	 	SO  					ZONE 400	BROKEN          	B			B3OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6621A	340  	100  			21063559	821022R			AFTER THE SECOND GROUND RUN, AND DURING A PRE-RUN CHECK FOR A THIRD GROUND RUN, A MECHANIC REMOVED THE OIL FILLER CAP/DI	PSTICK AND DISCOVERED THAT THE DIPSTICK HAD BROKEN OFF FROM THE OIL FILLER CAP. THE OIL WAS DRAINED FROM THE ENGINE, AND	 A BORESCOPE WAS USED TO DETERMINE THAT THE DIPSTICK HAD BEEN BROKEN INTO NUMEROUS PARTS.ONE PART OF THE DIPSTICK WAS RE	COVERED FROM THE OIL DRAIN HOLE AND IT WAS ABOUT ONE INCH LONG AND BENT IN A 90 DEGREE ANGLE. THE OIL FILTER WAS REMOVED	, CUT OPEN, AND THE FILTER CONTAINED A LARGE AMOUNT OF METAL FLAKES. THE OIL REMAINING IN THE FILTER CAN LOOKED LIKE MET	ALLIC PAINT.THE MECHANIC SAID HE HAD NO PROBLEM WITH INSTALLING THE OIL CAP/DIPSTICK BACK INTO THE ENGINE PRIOR TO THE S	1	H	7	1 	3O	3	O	 	3A21    	E3SO				 
2003080500037	20030805	00037	CE  	2003	8	5	B3OR2003004      	1	20030605	G	2730	1016100191	PITCH HORN      			BEECH 	200   	C12C        	1152903	CE  										ELEVATOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72476	14112	25   			BC26				DURING A 15 DAY CORROSION INSPECTION, A MECHANIC NOTICED "PAINT BUBBLING" ON THE LT ELEVATOR CONTROL PITCH HORN.  UPON F	URTHER INVESTIGATION BY SCRAPING-OFF THE PAINT BUBBLE, PITTING CORROSION WAS FOUND. AN ATTEMPT WAS MADE TO CLEAN AND TRE	AT THE PITTED AREA, BUT IT WAS FOUND THAT THE PITS WERE TOO DEEP INTO THE METAL. A NEW PITCH HORN WAS ORDERED AND THE  A	FFECTED PART WAS REPLACED.			1	L	7	2 	4T			 	A24CE   					 
2003080500039	20030805	00039	CE  	2003	8	5	B3OR2003005      	1	20030605	G	5520	1016200111	HINGE BRACKET   			BEECH 	200   	A200        	1152921	CE  										ZONE 300	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72476		35   			BC26				MECHANIC NOTICED (PAINT BUBBLING) ON LT OB ELEVATOR HINGE .UPON FURTHER INVESTIGATION BY SCRAPING-OFF THE PAINT BUBBLE, 	CORROSION WAS FOUND. AN ATTEMPT WAS MADE TO CLEAN AND TREAT AREA, BUT IT WAS FOUND THAT MORE YOU TRIED TO CLEAN CORROSIO	N, MORE METAL WAS BEING REMOVED IN  PROCESS.  FLAKING OF CORROSION WAS TOO DEEP INTO METAL OF HINGE BRACKET. A NEW HINGE	 BRACKET WAS ORDERED AND PART WAS REPLACED. HAVE FOUND IT DIFFICULT TO SPOT THESE (BUBBLED PAINT) AREAS.  WHEN AREAS ARE	 SPOTTED, WE SCRAPE-OFF SOME OF PAINT AND RESULT IS SAME, CORROSION AND FLAKING.  REPLACEMENT OF PART.  IT IS ADVISED TH	AT OPERATORS OF A/C PAY PARTICULAR ATTENTION TO ELEVATOR HINGE BRACKETS AT THEIR NEXT PERIODIC MAINTENANCE INSP.	1	L	7	2 	4T			 	A24CE   					 
2003080500040	20030805	00040	CE  	2003	8	5	B3OR2003006      	1	20030605	G	5520	1016200131	HINGE BRACKET   			BEECH 	200   	A200        	1152921	CE  										ELEVATOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7247Y		40   			BC03				MECH NOTICED (PAINT BUBBLING) ON LT AND RT, MIDDLE ELEVATOR HINGE.  FURTHER INVESTIGATION BY SCRAPEING-OFF PAINT BUBBLE,	 CORROSION WAS FOUND. ATTEMPT WAS MADE TO CLEAN AND TREAT AREA,  FOUND THAT MORE YOU TRIED TO CLEAN CORROSION, MORE META	L WAS BEING REMOVED IN PROCESS.  FLAKING, CORROSION WAS TOO DEEP INTO METAL OF HINGE BRACKET. NEW HINGE BRACKET WAS ORDE	RED AND AFFECTED PART WAS REPLACED. A/C WAS RE-PAINTED OVER TWO YEARS AGO. WE HAVE FOUND IT DIFFICULT TO SPOT THESE (BUB	BLED PAINT) AREAS.   REPLACEMENT OF AFFECTED PART. IT IS ADVISED THAT OPERATORS OF AIRCRAFT PAY PARTICULAR ATTENTION ELE	VATOR HINGE BRACKETS AT THEIR NEXT MAINT INSP.	1	L	7	2 	4T			 	A24CE   					 
2003080500041	20030805	00041	CE  	2003	8	5	B3OR2003007      	1	20030605	G	5520	1016200121	HINGE BRACKET   			BEECH 	200   	A200        	1152921	CE  										ELEVATOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72476		25   			BC26				DURING CORR INSP, MECH NOTICED "PAINT BUBBLING" ON LT, IB ELEV HINGE BRACKET. FURTHER INVESTIGATION BY SCRAPING-OFF PAIN	T BUBBLE, CORR WAS FOUND. ATTEMPT WAS MADE TO CLEAN AND TREAT AREA, BUT FOUND THAT MORE YOU CLEANED CORROSION, MORE META	L WAS BEING REMOVED IN PROCESS.  FLAKING, CORR WAS TOO DEEP INTO METAL OF HINGE BRKT.  HINGE BRKT WAS ORDERED AND AFFECT	ED PART WAS REPLACED.  A/C ARE KEPT OUTSIDE, THIS IS REASON FOR CORROSION INSP CYCLE.  A/C WAS RE-PAINTED OVER TWO YEARS	 AGO. WE HAVE FOUND IT DIFFICULT TO SPOT THESE "BUBBLED PAINT" AREAS, WHEN AREAS ARE SPOTTED, SCRAPE-OFF SOME PAINT AND 	RESULT IS SAME, CORR AND FLAKING.  RESULT IS REPLACEMENT OF AFFECTED PART. CORR FOUND ON THESE HINGE BRKT.	1	L	7	2 	4T			 	A24CE   					 
2003080500042	20030805	00042	CE  	2003	8	5	B3OR2003008      	1	20030605	G	5540	10164001413	HINGE           			BEECH 	200   	A200        	1152921	CE  										HINGE	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7247Y		40   			BC03				DURING A 15 DAY CORROSION INSP, MECH NOTICED "PAINT BUBBLEING" ON MIDDLE RUDDER HINGE BRACKET. UPON INVESTIGATION, CORRO	SION FOUND. ATTEMPT WAS MADE TO CLEAN & TREAT AREA, BUT FOUND THAT MORE METAL WAS BEING REMOVED IN THE PROCESS. FLAKING,	 CORROSION WAS TOO DEEP INTO METAL OF THE HINGE BRACKET. A NEW HINGE BRACKET WAS ORDERED AND THE AFFECTED PART WAS REPLA	CED. AS A NOTE, THE AIRCRAFT ARE KEPT OUTSIDE FOR THE MAJORITY OF THE TIME, THIS IS THE REASON FOR THE 15 DAY CORROSION 	INSPECTION CYCLE. AIRCRAFT RE-PAINTED 2 YEARS AGO.  FOUND IT DIFFICULT TO SPOT "BUBBLED PAINT" AREAS,  WHEN AREAS ARE SP	OTTED, SCRAPE-OFF SOME OF PAINT & RESULT IS SAME, CORROSION & FLAKING. RESULT IS REPLACEMENT OF AFFECTED PART.	1	L	7	2 	4T			 	A24CE   					 
2003080500043	20030805	00043	CE  	2003	8	5	B3OR2003009      	1	20030605	G	5540	10164001411	HINGE BRACKET   			BEECH 	200   	A200        	1152921	CE  										RUDDER	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7247Y		40   			BC03				MECH NOTICED (PAINT BUBBLING) ON, UPPER RUDDER HINGE BRACKET. ON INVESTIGATION, CORROSION WAS FOUND.   FLAKING, CORROSIO	N WAS TOO DEEP INTO METAL OF HINGE BRACKET.  NEW HINGE BRACKET WAS ORDERED AND AFFECTED PART WAS REPLACED.  WE HAVE FOUN	D IT DIFFICULT TO SPOT THESE (BUBBLED PAINT) AREAS, WHEN AREAS ARE SPOTTED, WE SCRAPE-OFF SOME OF PAINT AND RESULT IS SA	ME, CORROSION AND FLAKING. RESULT IS REPLACEMENT OF AFFECTED PART. IT IS ADVISED THAT OPERATORS OF A/C PAY PARTICULAR AT	TENTION TO RUDDER AND ELEVATOR HINGE BRACKETS AT THEIR NEXT PERIODIC MAINT INSPECTION. CORROSION FOUND ON THESE HINGE BR	ACKETS HAS BEEN DISCOVERED IN ADDITION TO HINGE BRACKET CORROSION.	1	L	7	2 	4T			 	A24CE   					 
2003111300070	20031113	00070	NE  	2003	11	13	B3OR20031119     	2	20031104	G	7270	310863201	DUCT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	CRACKED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26496	2481 	2481 			5500607	PCE71520			DURING A PHASE 3 AND 4 INSPECTION, IT WAS DISCOVERED THAT THE FORWARD INNER BY-PASS DUCT HAD A CRACK. THE CRACK WAS LOCA	TED AT THE 6 O'CLOCK POSITION AND WAS ABOUT AND INCH-AND-A-HALF LONG. THE DUCT WAS REMOVED AND A NEW FORWARD INNER BY-PA	SS DUCT WAS INSTALLED.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003091800126	20030918	00126	CE  	2003	9	18	B3OR20033012     	1	20030804	G	5753	1011200561	FLAP TRACK      			BEECH 	200   	A200        	1152921	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ZONE 600	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7247Y	13607	75   			BC03				DURING A 14 DAY CORROSION INSPECTION THE RIGHT HAND INBORAD FLAP TRACK WAS FOUND TO HAVE DEEP EXIFOLLIATION FLAKING CORR	OSION ON THE INBOARD SIDE OF THE TRACK.THE FLAKING WAS SEVERE ENOUGH TO CAUSE SEVERAL LAYERS OF FLAKES TO BE PRESENT. TH	E PART WAS REMOVED AND A NEW FLAP TRACK WAS INSTALLED.THIS AIRCRAFT WAS REPAINTED IN 1999, AND HAS BEEN KEPT, FOR THE MO	ST PART, OUTSIDE DUE TO LACK OF HANGER SPACE.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003091800129	20030918	00129	CE  	2003	9	18	B3OR20033013     	1	20030804	G	5753	10111001613	FLAP TRACK      			BEECH 	200   	A200        	1152921	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7247Y	13607	75   			BC03				DURING A 14 DAY CORROSION INSPECTION THE RIGHT HAND OUTBOARD FLAP TRACK WAS FOUND TO HAVE EXIFOLIATION FLAKING CORROSION	 ON THE FLAP TRACK. THE FLAKING WAS SEVERE ENOUGH TO CAUSE BUBBLING PAINT AND FLAKING METAL TO BE PRESENT. THE PART WAS 	REMOVED AND A NEW FLAP TRACK WAS INSTALLED. THIS AIRCRAFT WAS REPAINTED IN 1999, AND HAS BEEN KEPT, FOR THE MOST PART, O	UTSIDE DUE TO THE LACK OF HANGER SPACE.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003091800130	20030918	00130	CE  	2003	9	18	B3OR20033014     	1	20030804	G	5753	1011100171	FLAP TRACK      			BEECH 	200   	A200        	1152921	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7247Y	13607	75   			BC03				DURING A 14 DAY CORROSION INSPECTION THE LEFT OUTBOARD FLAP TACK WAS FOUND TO HAVE EXIFOLIATION FLAKING CORROSION ON THE	 FLAP TRACK. THE FLAKING WAS SEVERE ENOUGH TO CAUSE SEVERAL LAYERS OF FLAKING METAL TO BE PRESENT. THE PART WAS REMOVED 	AND A NEW FLAP TRACK WAS INSTALLED. THIS AIRCRAFT WAS REPAINTED IN 1999 AND, FOR THE MOST PART, HAS BEEN KEPT OUTSIDE DU	E TO LACK OF HANGER SPACE.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003091800131	20030918	00131	CE  	2003	9	18	B3OR20033015     	1	20030728	G	3213	12411023	STRUT           			CESSNA	210   	T210N       	2073456	CE  	CONT  	O550  	IO550*      	 	SO  	HARTZL	HCJ3Y	PHCJ3YR2    	GL  	RT MLG	CORRODED        	B			B3OR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6621A	5671 	50   			21063559				DURING AN ANNUAL INSPECTION, THE RT MAIN LANDING GEAR SPRING HAD BUBBLING PAINT IN THE AREA WHERE THE SPRING CONNECTS TO	 THE AXEL ASSEMBLY. THE SPRING WAS REMOVED AND THE AXEL ASSEMBLY WAS REMOVED. THE SPRING WAS FOUND TO HAVE SEVERE PITTIN	G CORROSION ON THE BOTTOM END WHERE IT ATTACHES TO THE AXEL ASSEMBLY. A NEW SPRING WAS ORDERED AND IT WAS REPLACED. IT I	S SUSPECT THAT THE SPRING BEING STEEL AND THE AXEL HOUSING BEING ALLUMINUM IT CAUSED DISSIMLER METAL CORROSION AND PITTI	NG.		1	H	7	1 	3O	3	O	 	3A21    	E3SO	5	C	P36EA	 
2003091800132	20030918	00132	CE  	2003	9	18	B3OR20033016     	1	20030728	G	3213	12411024	STRUT           			CESSNA	210   	T210N       	2073456	CE  	CONT  	O550  	IO550*      	 	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	MLG	CORRODED        	B			B3OR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6621A	5671 	50   			21063559				DURING AN ANNUAL INSPECTION, THE LEFT MAIN LANDING GEAR SPRING HAD BUBBLING PAINT IN THE AREA WHERE THE SPRING CONNECTS 	TO THE AXEL ASSEMBLY. THE SPRING WAS REMOVED AND THE AXEL ASSEMBLY WAS REMOVED. THE SPRING WAS FOUND TO HAVE SEVERE PITT	ING CORROSION ON THE BOTTOM END WHERE IT ATTACHES TO THE AXEL ASSEMBLY. A NEW SPRING WAS ORDERED AND IT WAS REPLACED. IT	 IS SUSPECT THAT THE SPRING BEING STEEL AND THE AXEL HOUSING BEING ALLUMINUM IT CAUSED DISSIMLER METAL CORROSION AND PIT	TING.		1	H	7	1 	3O	3	O	 	3A21    	E3SO	5	C	P36EA	 
2003010600144	20030106	00144		2003	1	6	BAQA082775       	4	20030103	G	3416	396005241	ENCODER         			AEROSP	SA365 	SA365N      	8680669	EU  										ALTIMETER	INACCURATE      	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	199SM					6396				ALTIMETER ENCODING INACCURATE. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H10EU   					 
2003022400017	20030224	00017	EU  	2003	2	24	BAQA084020       	1	20030122	G	6700	117132811	CONTROL ROD     			BOLKMS	117   	BK117B1     	5626012	EU  										ROTOR HEAD	WORN            	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	945ME	5952 				7235				BEARINGS WORN.  REPLACED WITH SERVICEABLE ROD.						1	G	7	2 	3U			 	H13EU   					 
2003042300074	20030423	00074	EU  	2003	4	23	BAQA084034       	1	20030127	G	5412	1176623541	FIREWALL        			BOLKMS	117   	BK117B1     	5626012	EU  										ENGINE BAY	CRACKED         	E			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	945ME	6018 				7235				FIREWALL CRACKED ON LOWER CORNER.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H13EU   					 
2003022400018	20030224	00018		2003	2	24	BAQA084038       	4	20030127	G	3442	071015190101	RADAR           			UROCOP	EC135 	EC135T1     	5620026	EU  										WX RADAR SYS	INOPERATIVE     	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	522ME	963  				0144				WEATHER RADAR INOPERATIVE.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H88EU   					 
2003022400019	20030224	00019	EU  	2003	2	24	BAQA084043       	1	20030128	G	2430	171BS1011	BATTERY         			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN	WORN            	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	117NC	391  				7517				INTERMITTENT CHARGE OF BATTERY.  NO CHARGE LIGHT ON.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			NC	H13EU   					 
2003020300086	20030203	00086	EU  	2003	2	3	BAQA084057       	1	20030130	G	6730	L673M40A1001	ACTUATOR        			UROCOP	EC135 	EC135P1     	8680990	EU  										TAIL ROTOR	LEAKING         	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	135ME	1351 				0009				LEAKING AT SPLIT LINE OF TRIANGULAR PLATE ON BOTTOM SIDE OF ACTUATOR.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			O	H88EU   					 
2003020300092	20030203	00092	EU  	2003	2	3	BAQA084063       	1	20030130	G	6410	11731743	BLADE           			BOLKMS	117   	BK117A3     	5626015	EU  										TAIL ROTOR	OUT OF BALANCE  	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	911NH					7030				BLADES WOULD NOT BALANCE.  REPLACED WITH SERVICEABLE UNITS S/N 413 AND 414.						1	G	7	2 	3U			 	H13EU   					 
2003022400021	20030224	00021	EU  	2003	2	24	BAQA084080       	1	20030204	G	6520		STUD            			BOLKMS	117   	BK117B1     	5626012	EU  										GEARBOX	LOOSE           	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	945ME	4107 				7235				STUD ON GEARBOX MOUNT IS WORKING LOOSE.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H13EU   					 
2003042300088	20030423	00088		2003	4	23	BAQA084838       	4	20030227	G	2210	117884141	CONTROL UNIT    			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101600A  	41560	NE  					CSAS	INOPERATIVE     	E			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	213AE					7219				YAW CSAS WILL NOT COME ON LINE.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2003042300046	20030423	00046		2003	4	23	BAQA085101       	4	20030306	G	3421	109290	GYRO            			BOLKMS	117   	BK117A1     	5626010	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					COCKPIT	MALFUNCTIONED   	E			BAQA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	03	300CP	2430 				7249				RATE GYRO LIGHT ILLUMINATED IN FLIGHT AND DECOUPLED. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2003041000233	20030410	00233	EU  	2003	4	10	BAQA085817       	1	20030325	G	5330	L633M2010101	MOUNT           			UROCOP	EC135 	EC135T1     	5620026	EU  										TRANSMISSION	LEAKING         	E			BAQA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	03	511ME					0143				LEAKING.  PIN NOT STICKING OUT UNDER A LOAD. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H88EU   					 
2003042300086	20030423	00086		2003	4	23	BAQA085828       	4	20030327	G	3414	C6610630106	INDICATOR       			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					AIRSPEED	OUT OF ADJUST   	E			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	560H	3178 				0017				AIRSPEED INDICATOR OUT OF CALIBRATION.  LEAK. REPLACED WITH SERVICEABLE UNIT.						2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2003050900115	20030509	00115	EU  	2003	5	9	BAQA085906       	1	20030403	G	2913	L290M20A1014	PUMP            			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					HYD SYS	LEAKING         	E			BAQA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			FS	01	601FH	231  				0069				EXCHANGE. HYDRAULIC PUMP, LEAKING. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2003042300092	20030423	00092		2003	4	23	BAQA085907       	4	20030403	G	3422	501121001	GYRO            			AGUSTA	A109  	A109E       	0260119	EU  										COCKPIT	INOPERATIVE     	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	7YL	571  				11502				VERTICAL GYRO IS INOPERABLE.  CAUSES ADI INDICATION FAILURE. REPLACED WITH SERVICEABLE UNIT.    4/8/03						1	G	7	2 	3U			RT	H7EU    					 
2003041400071	20030414	00071	EU  	2003	4	14	BAQA085911       	1	20030404	G	6520	741C000005	ACTUATOR        			BOLKMS	117   	BK117A1     	5626010	EU  										TAIL ROTOR	LEAKING         	E			BAQA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	03	300CP	2430 				7249				TAIL ROTOR ACTUATOR LEAKING.  CLEVIS WORN.  WAITING FOR UNIT TO COME IN FROM AEC.  CORE UNIT WAS OUR ASSET OFF OF 7249 S	INCE 7249 USED A RECENT REPAIRED UNIT REPAIRED FOR 7099 (NO UNIT ON 7099).  7099 NEEDED ONE IMMEDIATELY, PURCHASED ONE F	OR 7099 AS AN EXCHANGE.  7249'S CORE GOES BACK  AS AN EXCHANGE TO AEC.				1	G	7	2 	3U			 	H13EU   					 
2003042300065	20030423	00065		2003	4	23	BAQA085912       	4	20030404	G	2210	41600297006	MODULE          			UROCOP	EC135 	EC135T1     	5620026	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					TRIM ACTUATOR	FAILED          	E			BAQA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	03	533ME	472  				132				GIVING P/R SAS LIGHT AND ACTUATION W/A CORRESPONDING (P) ON PFD.  HARD CARD ENCLOSED. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U	3	U	 	H88EU   	E34NE				 
2003042300063	20030423	00063	EU  	2003	4	23	BAQA085925       	1	20030407	G	6720		SHAFT           			UROCOP	EC135 	EC135T1     	5620026	EU  										ACTUATOR	WORN            	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	511ME	136  			149	0143				INTERMITTENT YAW LIGHT AND SHAFT WORN.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H88EU   					 
2003042300080	20030423	00080	EU  	2003	4	23	BAQA085927       	1	20030407	G	6510	365A12002002	BLADE           			AEROSP	AS365 	AS365N2     	8680815	EU  										TAIL ROTOR	CRACKED         	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	915ME	2174 				6417				TAIL ROTOR BLADE HAS A CRACK NEAR CUFF.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			RT	H10EU   					 
2003042300081	20030423	00081	EU  	2003	4	23	BAQA085929       	1	20030408	G	2121	19A2772	BLOWER          			BOLKMS	117   	BK117A1     	5626010	EU  										AIR DISTRIBUTION	INOPERATIVE     	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	955ME	728  				7243				BLOWER WILL NOT COME ON. ONE CORE BEING SENT BACK. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H13EU   					 
2003042300090	20030423	00090		2003	4	23	BAQA085935       	4	20030408	G	3442	78805191703	INDICATOR       			BOLKMS	117   	BK117A1     	5626010	EU  										WX RADAR SYS	DAMAGED         	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	967LS	251  				7067				UPPER LEFT PUSH BUTTON RECESSED. REPLACED WITH SERVICEABE UNIT.						1	G	7	2 	3U			 	H13EU   					 
2003041400065	20030414	00065	EU  	2003	4	14	BAQA085938       	1	20030409	G	7722	L316M30C1003	INDICATOR       			UROCOP	EC135 	EC135P1     	8680990	EU  										TOT	INACCURATE      	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	601FH	19   				0069				NR 1 TOT READS 800 WHEN ENGINE IS COLD. NO HARD CARD AVAILABLE. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			O	H88EU   					 
2003041400055	20030414	00055	EU  	2003	4	14	BAQA085940       	1	20030409	G	5312	L713M1051101	FIREWALL        			UROCOP	EC135 	EC135T1     	5620026	EU  										FUSELAGE	CRACKED         	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	575ME	1633 				0157				FIREWALL CRACKED. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H88EU   					 
2003050900113	20030509	00113	EU  	2003	5	9	BAQA086237       	1	20030422	G	6210	L621M1010054	STUD            			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					M/R BLADE	BROKEN          	E			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	601FH	2722 				0069				WEIGHT STUD BROKE AT CUTTER KEY HOLE.  BLADE INSTALLED BUT NEVER FLOWN.  MECHANIC WENT TO ADJUST WEIGHT AND FOUND THE ST	UD BROKE.  BLADE SENT TO BE REPAIRED UNDER PO NR.  REINSTALLED RENTAL BLADE S/N 928.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2003050900117	20030509	00117	EU  	2003	5	9	BAQA086254       	1	20030424	G	2432	45043006	BATTERY         			UROCOP	EC135 	EC135T1     	5620026	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					MASTER	FAILED          	E			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	554ME	25   				0154				BATTERY UNIT FAILED SELF TEST AT INSTALLATION.  AIRCRAFT WOULD NOT CRANK-(BATTERY DISCONNECT). REPLACED WITH SERVICEABLE	 UNIT.					1	G	7	2 	3U	3	U	 	H88EU   	E34NE				 
2003050900118	20030509	00118	EU  	2003	5	9	BAQA086255       	1	20030424	G	2432	45043006	BATTERY         			UROCOP	EC135 	EC135T1     	5620026	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					MASTER	FAILED          	E			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	554ME	25   				0154				BATTERY UNIT FAILED SELF TEST AT INSTALLATION.  AIRCRAFT WOULD NOT CRANK (BATTERY DISCONNECT).  HARD CARD ENCLOSED. REPL	ACED WITH SERVICEABLE UNIT.					1	G	7	2 	3U	3	U	 	H88EU   	E34NE				 
2003060400217	20030604	00217	NE  	2003	6	4	BAQA086309       	2	20030501	G	7297	430121302	WIRE HARNESS    			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	FAILED          	B			BAQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	117UB					7062				N1 GUAGE WOULD NOT SPOOL WITH THIS HARNESS. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2003052800045	20030528	00045	EU  	2003	5	28	BAQA086332       	1	20030506	G	6220	E1T302301	ADAPTER         			AEROSP	SA365 	SA365N      	8680669	EU  										FREQUENCY	TORN            	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	199SM	667  				6396				FREQUENCY ADAPTER TORN BEYOND LIMITS.   REPLACED WITH SERVICEABLE SET.						1	G	7	2 	3U			 	H10EU   					 
2003060500152	20030605	00152		2003	6	5	BAQA086380       	4	20030512	G	3442	MI585200	RADAR           			BEECH 	100   	100BEECH    	1152916	CE  										COCKPIT	INOPERATIVE     	E			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	777GS					B241				RADAR INOPERATIVE. REPLACED WITH SERVICEABLE UNIT.						1	L	7	2 	3T			 	A14CE   					 
2003060500153	20030605	00153		2003	6	5	BAQA086396       	4	20030512	G	3442	MI585202	PEDESTAL        			BEECH 	100   	100BEECH    	1152916	CE  										ANTENNA	DAMAGED         	E			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	777GS					B241				NEGATOR SPRING. REPLACED WITH SERVICEABLE UNIT.						1	L	7	2 	3T			 	A14CE   					 
2003052800047	20030528	00047	EU  	2003	5	28	BAQA086406       	1	20030514	G	2140	JBS8803	HEATER          			UROCOP	EC135 	EC135T1     	5620026	EU  										CABIN	MALFUNCTIONED   	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	533ME	271  				132				HEATER MALFUCTIONED, TEMPERATURE WILL NOT REGULATE. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H88EU   					 
2003061700328	20030617	00328	EU  	2003	6	17	BAQA086465       	1	20030520	G	7931	5338100	TRANSDUCER      			AEROSP	AS365 	AS365N2     	8680815	EU  										OIL PRESSURE	MALFUNCTIONED   	H			BAQA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			FS	01	915ME					6417				PRESSURE DROPPED TO YELLOW AT IDLE.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			RT	H10EU   					 
2003080700122	20030807	00122	SW  	2003	8	7	BAQA086745       	1	20030527	G	2820	430201407	LINE            			BELL  	222   	222U        	1182140	SW  										FUEL SYS	LEAKING         	H			BAQA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			FS	01	223HX					47511				PUMP LEAKED FUEL BADLY FROM BOTH ENDS WHEN INSTALLED.  NEVER PUT INTO SERVICE.  8130 AND HISTORICAL RECORD CARD ENCLOSED	. REMOVED FROM ENGINE LE47204. REPLACED WITH SERVICEABLE UNIT.					1	G	7	2 	3U			 	H9SW    					 
2003061800017	20030618	00017	EU  	2003	6	18	BAQA087114       	1	20030613	G	2450	45023500	ELECTRICAL BOX  			UROCOP	EC135 	EC135P1     	8680990	EU  											INOPERATIVE     	H			BAQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	577LF	2045 				0140				AIR CONDITIONER.  INOPERATIVE.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			O	H88EU   					 
2003123000045	20031230	00045	CE  	2003	12	30	BHA01RS          	1	20031128	G	5610	10243008513	WINDOW          			BEECH 	58    	58P         	1152744	CE  										COCKPIT	DEPARTED        	B				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	04	6047S		58   			TJ37				WHILE IN FLIGHT, PILOTS LEFT SIDE WINDOW CRACKED AND DEPARTED AIRCRAFT. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.						1	L	7	2 	3O			 	A23CE   					 
2003123000038	20031230	00038		2003	12	30	BHA02RS          	4	20031128	G	8300		CASE            	GARRTT      		CASA  	C212  	C212        	2410200	EU  	GARRTT	TPE331	TPE33110    	01514	WP  					GEARBOX	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	04	117BH		838  		908169820	171	P37036			DURING ROUTINE INSPECTION, CRACK IN ACCESSORY GEARBOX WAS NOTED. CRACK WAS LOCATED AT RT SIDE ENGINE MOUNT PAD. UPON ENG	INE REMOVAL, CRACK WAS FOUND TO BE ALMOST COMPLETELY THROUGH ENGINE MOUNT PAD AREA.					2	H	7	2 	4T	4	T	 	A43EU   	E4WE				 
2004102700096	20041027	00096	CE  	2004	10	27	BJ82004F00000    	1	20031023	G	2121	50041	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  					BLOWER	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	93ZC					BB654				PILOT REPORT SMELLING SMOKE IN COCKPIT.  LANDED SAFELY.  UPON INVESTIGATION FOUND FWD EVAPORATOR MOTOR HAD A BURN SMELL.	  REPLACED, OPS CHS GOOD.  NO CHAPTER 4 OR 5 TIME ITEMS OR EVAPORATOR BLOWER ASSY OR INSPECTION OF BRUSHES.					1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2003010600032	20030106	00032	NM  	2003	1	6	BLAI200200001    	1	20030103	G	5714	41513017R	RIB             			UNIVAR	415   	415D        	0420306	NM  										CENTER WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	99997	2120 				2620				DURING REFURBISHMENT OF THE WING CENTER SECTION WING WALKWAY BOXES, AN INSPECTION WAS CONDUCTED TO COMPLY WITH AD 2002-2	6-02. LOWER SKINS OF THE WALKWAY BOXES HAD BEEN REMOVED TO PROVIDE ACCESS FOR REFURBISHMENT, THIS PROVIDED UNIMPEDED ACC	ESS TO THE ENTIRE CENTER SECTION. CORROSION WAS FOUND ON THE RIGHT SIDE INBOARD REAR FORMER RIB LOCATED BEHIND THE REAR 	SPAR. CORROSION HAD SEVERELY DAMAGED THE RIB BEYOND AC43-4A CRITERIA REQUIRING REPLACEMENT. NEW RIB WAS PURCHASED AND IN	STALLED. NO OTHER CORROSION WAS FOUND IN THE CENTER SECTION. THE ENTIRE CENTER SECTION WAS CLEANED AND PRIMED PRIOR TO R	EINSTALLATION OF LOWER SKIN.	1	L	7	1 	3O			 	A787    					 
2003111400007	20031114	00007	CE  	2003	11	14	BR549            	1	20031029	G	7603	4576101000V1700	ATTACH BOLT     			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					THROTTLE CABLE	CORRODED        	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	222MW	866  				110				UPON REPLACEMENT OF THRUST LEVER MODULE FOUND BOTH BOLTS ATTACHING THROTTLE CABLE CLEVIS TO THROTTLE MODULE CORRODED IN 	A HANK AREA WHERE BOLT PASSES THROUGH ROD END BEARINGS.  HAD TO DRIVE BOLTS OUT WITH PUNCH TO REMOVE.  UPON REMOVAL FOUN	D BOTH BOLTS DRY WITH NO VISIBLE LUBRICATION. ONE BOLT PITTED IN SHANK AREA.  ORDERED TWO NEW BOLTS FROM MANUFACTURER AN	D FOUND THAT NEITHER ORIGINAL BOLT WAS CORRECT SHANK LENGTH WHEN COMPARED WITH NEW BOLTS.			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2003111400014	20031114	00014	CE  	2003	11	14	BR550            	1	20031029	G	7603	66274010000007	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					2NDARY TRIM SYS	FAILED          	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	222MW	4    	4    			110				UNIT CAUSED FAILURE OF SECONDARY TRIM SYSTEM AFTER 4.7 HOURS OF OPERATION.						2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2003021200054	20030212	00054	CE  	2003	2	12	CA030114004      	1	20030109	G	7120	95510171	MOUNT           			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			10164								(CAN) ONE CRACK FOUND AT ONE TOP DYNAFOCAL WELD TO TUBE, FOUR CRACKS FOUND AT CROSS TUBE BETWEEN LOWER LEGS AT WELDED AR	EAS. ALL CRACKS FOUND DURING DYE-PENETRANT INSPECTION CARRIED OUT IN ACCORDANCE WITH CESSNA'S CONTINUING AIRWORTHINESS P	ROGRAM, CAP 71-20-00. MOUNT IS OLDER STYLE, LACKING WELDED FINGER-PATCH REINFORCEMENTS FOUND ON LATER MODELS AT CROSS-TU	BE WELDS. CRACKS REPAIRED AND MOUNT RETURNED TO SERVICE.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003020300031	20030203	00031	CE  	2003	2	3	CA030114006      	1	20030113	G	2133		LINE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					OUTFLOW VALVE	FROZEN          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) OUTFLOW VALVE SUCTION LINE WAS FROZEN CAUSING AIRCRAFT TO PRESSURIZE ON THE GROUND.  COULD NOT BE CONTROLLED BY CO	NTROLLER.  LINE WAS BLOWN OUT AND SYSTEM CHECKED SERVICIBLE AS PER MANUFACTURER.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003020300032	20030203	00032	SO  	2003	2	3	CA030114007      	1	20030102	G	5312	4521504	BULKHEAD        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17198								(CAN) DURING SHEDULED MAINTENANCE DISCOVERED FLEXING UNDER THE DOOR SNUBBER ATTACH BRACKET WHEN OPENING AND CLOSING THE 	CABIN DOOR. INSPECTION REVEALED CRACKING IN BULKHEAD AND SKIN AT FS 215 REPAIRS CARRIED OUT IAW REPAIR DESIGN CERTIFICAT	E C-RA02-425/D.				1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2003021200058	20030212	00058	CE  	2003	2	12	CA030115005      	1	20030115	G	5310	04118684	DOOR FRAME      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19600								(CAN) DOOR POST SKIN EXTERIOR FOUND 0.5 INCH CRACK AT THE CENTRE OF THE CURVE CUTOUT AT THE FORWARD UPPER DOOR ON THE FU	SELAGE.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003020300035	20030203	00035	CE  	2003	2	3	CA030115006      	1	20030114	G	7810	1099500001	EXHAUST STACK   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION THE ANTI ICE BOSS ON THE LT EXHAUST STACK P/N 1099500001 WAS FOUND BROKEN OFF WITH THE A	NTI ICE FLEX TUBE. THE FLEX TUBE WAS ALSO CRACKED AROUND THE THE LOWER ELBOW.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003021200064	20030212	00064	EU  	2003	2	12	CA030116006      	1	20030103	G	3242	23203500	BRAKE DISC      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DUE TO PREVIOUS BRAKE FAILURES WE NOW DISSASSEMBLE AND INSPECT THE BRAKE ASSY. AT 900 HRS. ON INSPECTION OF THIS A	SSY. WE FOUND THE INSIDE ROTOR DISK CRACKED IN 2 PLACES. WEAR PINS INDICATED BRAKE ASSY AT LESS THAN HALF LIFE.  CRACKS 	STARTED AT RELIEF HOLE AND PROCEEDED OUTWARD.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003021200066	20030212	00066	CE  	2003	2	12	CA030117001      	1	20030115	G	3710		CHECK VALVE     			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					VACUUM SYSTEM	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE VACUUM SYSTEM CHECK VALVE MANIFOLD WAS DETERMINED TO BE UNSERVICEABLE DUE TO LEAKS PAST THE CHECK VALVE DISC. 	THIS FINDING WAS DETERMINED BY FOLLOWING THE INSPECTION CRITERIA CONTAINED IN CESSNA SB02-37-04.  THE PART WAS REMOVED F	ROM SERVICE AND A REPLACEMENT PART WAS ORDERED.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003021200067	20030212	00067	CE  	2003	2	12	CA030117002      	1	20030116	G	3710		CHECK VALVE     			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					VACUUM SYSTEM	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE VACUUM SYSTEM CHECK VALVE MANIFOLD WAS DETERMINED TO BE UNSERVICEABLE DUE TO LEAKS PAST THE CHECK VALVE DISC. 	THIS FINDING WAS DETERMINED BY FOLLOWING THE INSPECTION CRITERIA CONTAINED IN CESSNA SB 02-37-04. THE PART WAS REMOVED F	ROM SERVICE AND A REPLACEMENT PART WAS ORDERED.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003020300064	20030203	00064	CE  	2003	2	3	CA030117005      	1	20030116	G	3010	130936P8D1000	LINE            	BEECH       		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					DEICE SYS	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE TUBING THAT SUPPLIES PNUEMATIC PRESSURE TO THE DEICER BOOTS WAS FOUND COLLAPSED. THIS TUBE IS LOCATED UNDER TH	E HEAT REGISTER IN THE AFT BAGGAGE COMPARTMENT.  IT APPEARS THE TUBING WAS WARM AND COLLAPSED DURING THE DEICE BOOT CYCL	E. THE HEATER DUCT SHOWS NO SIGN OF LEAKAGE. DAMAGED AREA IS 1 1/4 INCH LONG.  REF. ' FIRE AND ICE AVIATION SAFTEY, OCT 	2002 PG 25 'KING AIR HEATER DISSABLES DEICE SYSTEM FOR TURBO PROP EMPANNAGE'			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2006061200369	20060612	00369	EU  	2006	6	12	CA030117006      	1	20030116	G	2910	AE707910	HOSE            			AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     	 	NE  					HYD SYSTEM	CHAFED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			29090	29090							HYDRAULIC HOSE FOUND CHAFFED THROUGH ON ENGINE 1 GREEN HYDRAULIC SYSTEM PUMP PRESSURE TRANSDUCER. REF. 29-11-49-80A TUBE	S INSTL-HYDRAULIC, V2500, ENGINE 1, ZONE 400/ITEM 310.					2	L	7	2 	4F	4	F	RT	A28NM   	E311NE				 
2003021000084	20030210	00084	EA  	2003	2	10	CA030119002      	1	20030112	G	5610		WINDSHIELD      	PPG         	NP13932110  	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  	 		            		WINDSHIELD	                	W			    	A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA		 	22172			94144H7006					(CAN) RIGHT WINDSHIELD CRACKED DURING FLIGHT. DIVERTED FLIGHT TO HAMBURG.RIGHT WINDSHIELD REPLACED PER AMM.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003021000085	20030210	00085	NE  	2003	2	10	CA030119004      	2	20030109	G	7321	6078T55P13	FCU             	GE          	6078T55P13  	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		FCU	                	W			    	E	 	 	 	ENGINE SHUTDOWN         				X	 	 	ENGINE FLAMEOUT           			DE	DESCENT        	1			CA		 				WYG96536					(CAN) 60 MILES FROM SAVANNAH, ON DESCENT FROM FL230 TO FL110, CREW REPORTED SLOW RH ENGINE.  FLAMEOUT ON DESCENT AT 330 	KTS AT 3200 FEET/MIN DESCENT. THE INFORMATION THAT FOLLOWS WAS TAKEN FROM AIRCRAFT DEFECT LOG BEGIN QUOTE:DEFECT:  ON DE	SCENT RIGHT ENGINE FLAMED OUT, RIGHT ENG LOW OIL PRESSURE CAS MESSAGE DISPLAYED.ACTION:  REMOVED AND REPLACED #2 FCU IAW	 73-21-00.OP CK PERFORMED.NO DEFECTS NOTED.  OP & LEAK CK GOOD.  FUEL FILTER REPLACED, RIG CHECKED, TANKS SUMPED, NO DEF	ECTS NOTED.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061200370	20060612	00370	EA  	2006	6	12	CA030119007      	1	20030107	G	5610	NP1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			6898 								PERFORMED TECH FERRY FLIGHT AC FERRY FLIGHT APPROVAL AND REPLACED WINDSHIELD ACC AMM 56-11-01.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061200419	20060612	00419	NM  	2006	6	12	CA030120005      	1	20030109	G	2130	80053258	CONTROL PANEL   			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					CABIN PRESSURE	FLUCTUATES      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											AT FLIGHT LEVEL 25,000 FT, IT WAS OBSERVED CABIN PRESSURE WAS CLIMBING 1,000 FT - 2,000 FT PER MINUTE.  AIRCRAFT RETURNE	D TO BASE WITHOUT INCIDENT.  CABIN PRESSURE CONTROL PANEL REPLACED AND CHECKED SERVICEABLE IAW WITH MM 21-30-00.  NO FUR	THER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2006061200420	20060612	00420	CE  	2006	6	12	CA030120006      	1	20030116	G	2421	DOFF10300F	ALTERNATOR      			CESSNA	150   	150         	2071802	CE  	CONT  	O200  	O200A       	17020	SO  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											ON OVERHAUL OF THE ALTERNATOR THE RECTIFIER P/N ES4113, BRUSH P/N E4118, AND BEARING P/N ES4104.  ALL THESE PART NUMBERS	 ARE NON-APPROVED.  ALTERNATOR BUILD UP CARRIED OUT WITH APPROVED PARTS.					1	H	7	1 	3O	3	O	NT	3A19    	E252				 
2003021000086	20030210	00086	EU  	2003	2	10	CA030120011      	1	20030117	G	3310		WIRE            	            	            	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WIRE	                	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 									(CAN) WHILE REPLACING L.H. ALTIMETER, AN ARC/BURN MARKWAS NOTED ON THE EADI MOUNTING TRAY. WIRE # L52N-22 WAS FOUND TO H	AVE CHAFFED THROUGH.NO PROBLEMS TO THE GPWS LIGHTING HAD BEEN REPORTEDWIRE WAS REPAIRED AND LOOM RESECURED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003021300002	20030213	00002	EU  	2003	2	13	CA030121001      	1	20030116	G	3230	9738114306	PRESSURE SWITCH 			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED GEAR WOULD NOT LOCK WHEN SELECTED DOWN THE EMERGENCY HAND PUMP WAS USED TO LOCK GEAR AND INDICTION 	WORKED AND LANDING WAS UNEVENTFUL.MAINTENANCE AT THE BASE DID GEAR FUNCTIONAL TEST AND IT FUNCTIONED NORMAL, THE PRESSUR	E SWITCH CANNON PLUG WAS CLEANED.WHEN AIRCRAFT RETURNED TO BASE THE SYSTEM WAS FUNCTIONAL TESTED AGAIN AND WATER STAINS 	WERE OBSERVED IN THE HYDRAULIC AREA.ALL ELECTRICAL CONNECTORS WERE CLEANED AND TREATED WITH PRODUCT RECOMMENDED BY AIRCR	AFT MANUFACTURE.  THE PRESSURE SWITCH WAS REMOVED AND CLEANED AND FUNCTIONAL TESTED WITH NITROGEN.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003021000087	20030210	00087	CE  	2003	2	10	CA030121004      	1	20030121	G	2435	15872694	DRIVE SHAFT     	BENDIX      	66082019    	LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  	 		            		ON	SHEARED         	W			    	A	 	 	 	UNSCHED LANDING         				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA		 				1271					(CAN) WHILE ON CRUISE,A/C LOST ELECTRICAL POWER FROM THE R/H ENGINE. A/C RETURNED TO BASE. UPON INSPECTION,FOUND DRIVE S	HAFT ON DC GENERATOR HAD SHEARED.DC GENERATOR REPLACED,GROUND RUN CARRIED OUT FOUND STILL UNSERVICEABLE. UPON FUTHERTROU	BLESHOOTING FOUND CURRENT LIMITER HAD BLOWN. CURRENT LIMITER REPLACED.				2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2003021000088	20030210	00088	NM  	2003	2	10	CA030121007      	1	20030109	G	2780		BEARING         	            	            	BOEING	737   	7372T5      	1384474	NM  	PWA   	JT8   	JT8D17      	52049	NE  	 		            		AUX TRACK	                	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA		 									(CAN) LOG SNAG - ON FLAP SELECTION TO ONE UNIT, LE FLAP TRANSIT LIGHT REMAINED ON. NO. 4 SLAT REMAINED AMBER. ALL OTHERS	 GREEN. ON SELECTION OF FLAP 10, NO. 4 WENT GREEN FULL EXTEND WITH OTHER LE DEVICES.THE MAINTENANCE MECHANICS DISCOVERED	 THE NO. 4 LE SLAT OUTBOARD AUX TRACK ROLLER BEARING AND ATTACH BOLT HAD DEPARTED AND WERE FOUND IN THE LOWER PART OF TH	E L/E.THIS CAUSED THE SLAT ASSEMBLY TO SKEW UPON EXTENSION AND TRIGGER THE TRANSIT INDICATION.THE ROLLER BEARING ATTACH 	BOLT CASTELLATED NUT COTTER PIN, WAS FOUND SHEARED AND A PORTION OF THE PIN WAS FOUND IN THE AREA.THE ROLLER BEARING AND	 ATTACH BOLT WERE REPLACED AND THE SYSTEM CHECKED SERVICEABLE.	2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2003021000089	20030210	00089	CE  	2003	2	10	CA030122003      	1	20030117	G	7110	26520227	SHROUD          	CESSNA      	2652022208  	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	OUTBOARD	CRACKED         	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 									(CAN) CRACK IN LOWER RIGHT COWLING APPROXIMATELY AT STN 50 WHERE SHROUD PN 2652022-7 OUTBOARD MEETS HAT SECTION STRINGER	 REPAIRED IN ACCORDANCE WITH SIRM 51-76-00 FIG 802,  PAGE 803.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003021000091	20030210	00091	NM  	2003	2	10	CA030122006      	1	20030120	G	2910	82970010401	HYDRAULIC LINE  	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC LINE	LEAKING         	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA		 									(CAN) CREW REPORTED HYDRAULIC FLUID LEAKING FROM NO. 1 NACELLE. MAINTENACE FOUND NO.2 SYSTEM MLG DOWN PRESSURE HYDRAULIC	 LINE LEAKING.IPC REF 29-10-00 FIG.20 ITEM 25.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003021000092	20030210	00092	EA  	2003	2	10	CA030123001      	1	20030117	G	5610	NP1393226	WINDOW          	PPG         	NP1393226   	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		WINDOW	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			CA		 				00004H7000					(CAN) RH SIDE WINDOW CRACKED ON LANDING. WINDOW ASSY REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003021000093	20030210	00093	EA  	2003	2	10	CA030123002      	1	20030116	G	5610	NP1393222	WINDOW          	PPG         	NP1393222   	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		WINDOW	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			AP	APPROACH       	1			CA		 	16752			97101H4237					(CAN) SHORTLY BEFORE LANDING, THE RIGHT WINDOW CRACKED. CRACK FURTHER PROGRESS ON TOUCH DOWN. AIRPLANE FERRIED. RIGHT WI	NDOW REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2006061200422	20060612	00422	EA  	2006	6	12	CA030123005      	2	20030120	G	8530	383B	NUT             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					CYLINDER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING AIRCRAFT SCHEDULED INSPECTION EVENT, MAINTENANCE PERSONNEL FOUND A CYLINDER BASE NUT LODGED IN THE OIL PUMP SCAVE	NGE SCREEN ORIFICE.  THE NUT WAS TOO BIG IN SIZE TO BE REMOVED FROM ENGINE; THEREFORE ENGINE ACCESSORY CASE, OIL PAN AND	 THREE (3) CYLINDERS WERE REMOVED.  THE NUT WAS RETRIEVED, AND THE ENGINE WAS INSPECTED INTERNALLY.  IT WAS CONCLUDED TH	AT THE NUT WAS LEFT IN THE ENGINE BY MISTAKE BY THE OVERHAUL FACILITY.  THE ENGINE HAS A TOTAL OF 330 HRS TSO.  THE ENGI	NE WAS REASSEMBLED AND RETURNED TO SERVICE.		1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2003021000094	20030210	00094	CE  	2003	2	10	CA030123009      	1	20030120	G	5610	10138402518	WINDSHIELD      	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	OUTER PANE	CRACKED         	W			    	A	 	 	 	UNSCHED LANDING         				D	 	 	INFLIGHT SEPARATION       			CR	CRUISE         	1			CA		 									(CAN) AFTER DEPARTURE THE WINSHIELD HEAT WAS SELECTED ON AT 1500 FEET. AFTER LEVELING AT CRUISE ALTITUDE OF 16,000 FT TH	E CREW HEARD A POPPING NOISE AND NOTED THAT THE RIGHT WINDSHIELD HAD CRACKED IN THE OUTER PANE. THE CRACK WENT FROM TOP 	TO BOTTOM AND WAS APPROXIMATELY IN THE CENTER  OF THE WINDSHIELD. ABNORMAL PROCEDURES AS PER THE AFM WERE FOLLOWED AND T	HE AIRCRAFT LANDING WAS UNEVENTFUL. MAINTENANCE REPLACED THE WINDSHIELD WITH AN OVERHAULED ASSEMBLY. NO SPECIFIC CAUSE O	F THE WINDSIELD CRACKING WAS DETERMINED.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2006061200424	20060612	00424	GL  	2006	6	12	CA030124002      	2	20030122	G	7310		UNION           			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					GOVERNOR	OBSTRUCTED      	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			3    								DIFFICULTY TO START ENGINE.  UNION FITTING OBSTRUCTED WITH METALLIC PARTICLES.						1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2003021300021	20030213	00021		2003	2	13	CA030124004      	4	20030123	G	6122		SHAFT           			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6A42      	52043	NE  					PROP GOVERNOR	SHEARED         	W				E				ENGINE SHUTDOWN         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		TX	TAXI/GRND HDL  	1			CA											(CAN) AT ENGINE START UP, THE PROPELLER WOULD NOT COME OUT OF FEATHER. INSPECTION REVEALED A SHEARED CONSTANT SPEED PROP	ELLER GOVERNOR SHAFT.					1	L	7	1 	3O	4	T	RT	A25SO   	E4EA				 
2003021300024	20030213	00024	EA  	2003	2	13	CA030127004      	2	20030113	G	8520	LW15916	CRANKSHAFT      								LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L364376T			(CAN) CORROSION FOUND UNDERNEATH URETHABOND COATING APPLIED IN ACCORDANCE WITH SB 505B, SB 530A AND AD 998-02-08. URETHA	BOND COATING IS APPLIED TO PREVENT CORROSION, BUT AS IN MOST CASES, IT DID NOT.										3	O			E274				 
2003021300025	20030213	00025	CE  	2003	2	13	CA030127005      	1	20030125	G	3260	2MD31AX287	SWITCH          			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6A20      	52043	EA  					MLG SELECTOR	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH , THE LANDING GEAR WAS SELECTED DOWN, BUT THE GEAR DID NOT EXTEND. FIVE ATTEMPTS WERE MADE TO EXTEND T	HE GEAR NORMALLY AND NO JOY. THE GEAR WAS EXTENDED USING THE EMERGENCY EXTENSION SYSTEM. THE PILOT NOTED THAT IT WAS DIF	FICULT TO EXTEND.  THE EMERGENCY SERVICES WERE ACTIVATED AND A LOWFLY PAST WAS CARRIED OUT TO ENSURE THE GEAR WAS DOWN. 	 THE AIRCRAFT LANDED SUCCESSFULLY. ON INVESTIGATION, ONE OF THE SWITCHES WAS FOUND TO BE FAULTY IN THE LANDING GEAR SELE	CTOR ASSY.  THE GEAR ALSO EXTENDED NORMALLY WHEN USING THE EMERGENCY EXTENSION.  THE OAT WAS AROUND -35C.		1	L	7	2 	3T	3	T	 	3A20    	E4EA				 
2003032600052	20030326	00052	CE  	2003	3	26	CA030129001      	1	20030122	G	7713		LINE            			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					MANIFOLD	BLOCKED         	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) ON GROUND WARM UP AND RUN ALL WAS NORMAL, ON TAKEOFF RT MANIFOLD STAYED AT 28.5 INCHES, ALL OTHER INDICATIONS AND 	ENGINE FUNCTIONS NORMAL. TAKEOFF ABORTED AND AIRCRAFT RETURNED TO HANGAR. MANIFOLD LINE FOUND BLOCK IN WING SECTION BETW	EEN WING AND A/F. MOISTURE REMOVED TESTED FOUND SERVICEABLE. NOTE OUTSIDE AIR TEMP AT -29 DEGREES C AND ACFT WAS IN HANG	AR PRIOR TO FLIGHT.			1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2003021300031	20030213	00031		2003	2	13	CA030129004      	4	20030129	G	3497	RG223	COAX            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					INSTRUMENTS	UNSERVICEABLE   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN)  DURING AIRCRAFT IMPORTATION INSPECTION INTO CANADA, AVIONICS CHECKS NOTED WEAK NAVIGATION, COMMS, G/S RECEPTION. 	TROUBLESHOOTING FOUND THAT THE COAXIAL CABLE INSTALLED FOR THE ENTIRE AIRCRAFT, NAVIGATION, AND COMMUNICATIONS SYSTEMS H	AD A MANUFACTURING DEFECT FROM DAY ONE OF INSTALLATION.  THE INNER CORE OF TO CABLE DOES NOT RUN IN THE CENTER OF THE IN	SULATOR. THE CORE TOUCHES THE SHIELDING IN MULTIPLE LOCATIONS OF THE CABLE CAUSING SHORTS IN THE CABLE. INFORMATION ON C	ABLE AS FOLLOWS: M17/167-00001. MIL-C-17. 07145,  AA-4649		1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003021300032	20030213	00032	CE  	2003	2	13	CA030129005      	1	20030127	G	5751	9913000011	SKIN            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					RT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A 1.5 CENTIMETER CRACK FOUND RADIATING FROM A RIVET ON SECOND RIB FROM INBOARD EDGE AND LAST RIVET HOLE BEFORE THE	 TRAILING EDGE.  ANOTHER .5 CENTIMETER CRACK IN SKIN FOUND RADIATING FROM THE SECOND RIVET FROM THE TRAILING EDGE ON THE	 THIRD RIB.  THE CRACKS WERE DIFFICULT TO SEE BUT WERE INDICATED BY THE PAINT.THE SKIN HAD BEEN REPLACED AND HAD 870.2 H	OURS SINCE NEW.  BEECHCRAFT IS BEEN CONTACTED TO DISCUSS ANY WARRANTY OPTIONS.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003021300034	20030213	00034	CE  	2003	2	13	CA030130002      	1	20030128	G	6120	3022852	SEAL RING       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					R GEARBOX	STUCK           	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER ENGINE START, THE TORQUE READING  INDICATED APPROX 3000 FT/LBS. POWER INCREASES OR DECREASES HAD LITTLE EFFE	CT. TROUBLESHOOTING WAS PERFORMED.  A TORQUE INDICATION SYSTEM CALIBRATION TESTER WAS CONNECTED AND INDICATION WAS NORMA	L. A TEST GAUGE WAS CONNECTED TO THE TORQUEMETER OIL LINE AND CONFIRMED A HIGH READING USING THE STARTER TO SPOOL.  A SE	RVICE REP SUGGESTED THAT THE TORQUEMETER PISTON INSIDE THE RGB MAY BE HUNG UP. THIS CAN BE CAUSED BY THE TEFLON RINGS ON	 THE METER PISTON STICKING BEFORE THEY ARE WORN IN. SUGGESTED TO BLOW LOW PRESSURE AIR INTO THE OIL LINE IN THE RGB WHIL	E ROCKING THE PROP BACK AND FORTH. THIS PROCEDURE RECTIFIED THE PROBLEM AND ALL INDICATIONS HAVE BEEN NORMAL.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003021300036	20030213	00036	CE  	2003	2	13	CA030130007      	1	20030127	G	3260	1003810061	DOWNLOCK SWITCH 			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT MLG	FAILED          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) WHILE ON APPROACH THE PILOT SELECTED GEAR DOWN AND THE LT GEAR INDICATION DID NOT ILLUMINATE.  THE GEAR WAS CYCLED	 WITH NO CHANGE. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE LEFT GEAR DOWNLOCK INDICATOR SWITCH AND 	SYSTEM WAS TESTED SERVICABLE				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2006061900152	20060619	00152	EA  	2006	6	19	CA030130008      	1	20030126	G	3213	10195101	CYLINDER        			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			12455	12455							AFTER A VERY COLD OPERATION DAY, A/C TOWED TO HANGAR.  DURING INSPECTION, MECH FOUND LT MLG WITH NO CHROME PORTION VISIB	LE AND AREA WET.  LT MLG INNER CYLINDER REMOVED TO GAIN ACCESS FOR INSPECTION AND SEAL REPLACEMENT.  FOUND LWR INNER CYL	INDER WHERE LOWER BEARING SEATS SHOWING SOME CORROSION AND PITTING IAW MESSIER DOWTY MANUAL THIS AREA HAS A VERY LOW DAM	AGE TOLERANCE THAT HAS BEEN EXCEEDED.  SO OUTER CYLINDER REPLACED.  QUALITY ASSURANCE INVESTIGATION C/OUT AND FOUND THAT	 THIS GEAR ASSY HAS LESS THEN AFT OF IS TIME BEFORE O/H AND NOTHING INTO BOMBARDIER MX PROGRAM REQUIRE INSPECTION INTO T	HIS AREA OR ANY TYPE OF FLUID REPLACEMENT.  THINK THAT LOWER INNER PORTION OF MLG STRUT IS EXPOSED TO WATER (HUMIDITY) T	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003021300037	20030213	00037	EA  	2003	2	13	CA030131001      	1	20030122	G	2730	C2T29A	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ELEVATOR	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PART WAS ACTUALLY REMOVED FROM STOCK FOR INSTALLATION ON A/C, BUT WOULD NOT FIT. IT WAS TAGGED AS 'USED SERVICEABL	E'. IT APPEARS AS IF THE END LEVER HAD BEEN HOME MADE AND WELDED ON TO THE TUBE. ALSO PREVIOUSLY WORN ATTACHING HOLES HA	D BEEN '  REPAIRED' BY THE WELDING OF WASHERS TO THE LEVERS. THE MECHANIC TRYING TO INSTALL THE UNIT REJECTED IT.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003021300038	20030213	00038	EA  	2003	2	13	CA030131002      	2	20030124	G	8520	LW17031	CRANKSHAFT      								LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION FOUND UNDERNEATH URETHABOND COATING APPLIED IN ACCORDANCE WITH SB 505B, SB 530A, & AD 98-9											3	O			E274				 
2003032600056	20030326	00056	EA  	2003	3	26	CA030131006      	1	20030122	G	2730	6009230053	FEEL UNIT       			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					PITCH	ROUGH           	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) CREW STATED THAT ON TAKEOFF, EXCESSIVE FORCE ( AS COMPARED TO NORMAL TAKEOFF FORCE) WAS REQUIRED TO PULL THE YOKE 	BACK FOR TAKEOFF. CREW STATED THAT THE REQUIRED FORCE WAS SUCH THAT THEY CONSIDERED ABORTING TAKEOFF, BUT DID NOT. CREW 	ALSO NOTED THAT THE FORCE HAD A BREAKAWAY POINT, IN THAT PULLING THE YOKE BACK WAS DIFFICULT FOR A PERIOD OF TIME, THEN 	SEEMED TO SPRING FREE AND BECAME NORMAL. SUBSEQUENT TROUBLESHOOTING ON THE GROUND LED THE MAINTENACE CREW TO USE THE PIT	CH DISCONNECT MECHANISM AND ISOLATE THE PITCH FEEL SIMULATOR (PFS). IT WAS FOUND THAT THE LEFT PFS HAD SOME ROUGHNESS AN	D JERKINESS. BOTH LT AND RT PFS UNITS WERE REPLACED.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003032600059	20030326	00059	CE  	2003	3	26	CA030203004      	1	20030129	G	8011	10357487242	STARTER         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	INTERMITTENT    	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) FLIGHT CREW REPORTED THAT THE RIGHT HAND ENGINE WOULD INTERMITTENTLY 'SHUDDER'. THE FLIGHT CREW SECURED THE ENGINE	 AND THE AIRCRAFT RETURNED TO BASE UNEVENTFULLY. A DETAILED INSPECTION OF THE ENGINE AND IGNITION SYSTEM REVEALED THAT T	HE STARTING VIBRATOR WAS INTERMITTENTLY ACTIVATING. ACTIVATION OF THE STARTER VIBRATOR GROUNDS THE PRIMARY POINTS IN THE	 MAGNETOS AND UTILIZES THE SECONDARY POINTS IN THE LEFT HAND MAGNETO TO ADVANCE THE TIMING FOR STARTING. THERE HAVE BEEN	 NO FURTHER REPORTED INSTANCES OF MALFUNCTION SINCE THE STARTING VIBRATOR WAS REPLACED.		1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2003021300044	20030213	00044	CE  	2003	2	13	CA030204013      	1	20030204	G	5520	115610010125	SPLINE ADAPTER  			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					ELEVATORS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON A RECENT INSPECTION REQUESTED BY THE REGIONAL PMI IT WAS DISCOVERED THAT THE TRAILING EDGE SPLINES ON BOTH PO	RT AND STARBOARD ELEVATORS WERE CRACKED. THE ELEVATOR TRAILING EDGE SPLINES ARE PRESENTLY BEING CLOSELY MONITORED AND WI	LL BE REPLACED IN THE NEAR FUTURE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2005042700308	20050427	00308	NE  	2005	4	27	CA030204016      	1	20030128	G	3212	7625101104011	FLOAT           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					MLG	DEPLOYED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA							760065				(CAN) PRE-TAKE OFF CHECKS WERE COMPLETED FOR FLIGHT. AC WAS TURNED INTO WIND AND TAXIED FORWARD TO STRAIGHTEN OUT NOSE W	HEEL. ONCE DONE THE TOE BRAKES WERE APPLIED BY THE COPILOT AND THE PILOT BECAUSE THE AC WAS ROLLING FORWARD.  IMMEDIATEL	Y, FLOATS WERE ACTIVATED. NEITHER PILOT RECALLS PRESSING FLOAT ACTIVATION BUTTON ON EITHER CYCLIC. AC WAS THEN FLOWN WIT	H THE FLOATS ( ALL FOUR ) DEPLOYED.  THE FLOATS WERE DEFLATED AND REMOVED FROM THE AIRCRAFT.  THE FLOAT SYSTEM (4 FLOAT 	BAGS, 4 FLOAT BOTTLES AND 4 SQUIBS ) WERE REMOVED FROM ANOTHER AIRCRAFT AND INSTALLED ONTO THIS AIRCRAFT IAW THE MM.  A 	WIRING CONTINUITY CHECK OF ENTIRE FLOAT SYS WAS PERFORMED AN NO FAULT WAS FOUND. THE AIRCRAFT WAS RETURNED TO SERVICE.	1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2003021300048	20030213	00048	EU  	2003	2	13	CA030205003      	1	20030126	G	2752	952D1005	PDU             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) FLAPS FAILED TO EXTEND ON APPROACH INTO PE.  A/C LANDED AND FLAP SYSTEM INSPECTED, FLAP POWER DRIVE UNIT FOUND FAU	LTY PN 952D1005. UNIT REPLACED AND FLAP O SET CARRIED OUT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003021300049	20030213	00049	EU  	2003	2	13	CA030205005      	1	20030121	G	2752	9787320307	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FROZEN          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH,  FLAPS WERE SELECTED AND C/B FOR FLAPS POPPED. A/C LANDED AND SYSTEM WAS RESET AND TRIED AGAIN,  C/B 	POPPED AGAIN. UPON INVESTIGATION IT WAS FOUND THAT SEVERAL OF THE FLAP ACTUATORS WERE FROZEN. WHEN SYSTEM WAS WARMED EVE	RYTHING WORKED PROPERLY. ACTUATORS WERE REMOVED AND NEW ONES INSTALLED WITH IMPROVED SEALS INCORPORATED IN THEM.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003021000095	20030210	00095	EA  	2003	2	10	CA030206001      	1	20030129	G	5610	NP1393222	WINDOW          	PPG         	NP1393222   	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		WINDOW	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA		 	12304			96262H7317					(CAN) RIGHT WINDOW CRACKED ALONG WITH MESSAGE R WINDOW HEAT (C).RIGHT WINDOW AND RIGHT WINDOW HEAT CONTROLLER REPLACED A	ND AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003021300053	20030213	00053	SO  	2003	2	13	CA030206003      	1	20030129	G	2434		FIELD WIRE      	PRESTOLITE  		PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					ALTERNATOR	CHAFED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON TAKEOFF THE TWO ALTERNATOR LIGHTS CAME ON, THE PILOT RETURNED TO THE AIRPORT. THE LIGHTS EXTINGUISHED AND THEN 	HE CARRIED OUT A GROUND RUN, EVERYTHING WAS BACK TO NORMAL. A SECOND TAKEOFF WAS CARRIED OUT, THE PROBLEM RETURNED. THE 	AUXILIARY CONTROL BOX WAS GROUND CHECKED SERVICEABLE, HOWEVER, WE NOTICED THAT THE VOLTMETER WAS HIGH.  WE CARRIED OUT A	 GROUND RUN WITH AN INDEPENDENT VOLTMETER, WE DETERMINED THAT THE LT ALTERNATOR WAS CHARGING AT FULL CAPACITY (30VDC), A	ND IT WAS ENGAGING THE OVER VOLTAGE RELAY. WE DISCOVERED THAT THE NEGATIVE FIELD GROUND WAS WORN AND IT WAS TOUCHING THE	 CHARGING GROUND, CAUSING THE ALTERNATOR TO CHARGE AT ITS MAXIMUM.	1	L	7	1 	3O	3	O	RT	A20SO   	E14EA				 
2003032700191	20030327	00191	EA  	2003	3	27	CA030211003      	2	20030204	G	8530		VALVE GUIDE     	SUPAC       		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CYLINDER	STUCK           	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			CA											(CAN) IN CRUISE FLIGHT ENGINE STARTED TO RUN ROUGH AND UNABLE TO MAINTAIN POWER ABOVE 1800 RPM. PILOT LANDED WITHOUT PRO	BLEMS. ON INVESTIGATION NOTICED NR 2 CYLINDER EXHAUST VALVE STUCK OPEN ALSO NOTICED VALVE TAPPET BODY CRACKED. ENGINE WA	S REMOVED FOR REPAIR. TAPPET BODY P/N SL72877				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003032700193	20030327	00193	WP  	2003	3	27	CA030211006      	1	20030205	G	7500	369H8407	TUBE            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					BLEED AIR	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) HARD TO START ENGINE. FIRST START OF DAY, CAUSED HUNG STARTS AT 50-55 PERCENT N1. NO TOT INCREASE WHEN HEATER VALV	E OPENED. SERVICEABLE HOSE INSTALLED.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2003032700198	20030327	00198	CE  	2003	3	27	CA030211011      	1	20030204	G	5511	11562001025	RIB             			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19698			B45					(CAN) THE HORIZONTAL STABILIZER WAS REMOVED FOR ROUTINE MAINTENANCE. UPON INSPECTION OF THE LT AND RT NR 1 LEADING EDGE 	RIBS IT WAS NOTED THAT THE LT RIB WAS CRACKED ALONG LOWER FORWARD RADIUS FOR APPROXIMATELY TWO INCHES. THIS AREA IS DIFF	ICULT TO INSPECT WITH HORIZONTAL STABILIZER INSTALLED AS THE NR 1 RIB IS IN CLOSE PROXIMITY TO THE AIRCRAFT EMPENAGE AND	 BEHIND AN AIR SEAL.			1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2003032800002	20030328	00002	EA  	2003	3	28	CA030212005      	1	20030131	G	2710		SEAL            			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					RT AILERON SHAFT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) EVIDENCE OF HYDRAULIC FLUID LEAKING FROM PCU SHAFT SEAL AREA.SUSPECT LEAKING IS WORSE AT ALTITUDE ORIN EXTREME COL	D CONDITIONS.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003032800008	20030328	00008	SO  	2003	3	28	CA030214002      	1	20030128	G	1100	753690	PLACARD         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	MISMARKED       	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) ENGINE MAGNETO TIMING DIFFERS FROM ENGINE DATA PLATE VERSES AIRFRAME SERVICE MANUAL. ENGINE DATA PLATE CALLS FOR 2	0 DEGREES BTC AND THE AIRFRAME MANUAL SAYS 25 DEGREES BTC. THERE ARE SEVERAL LYCOMING SBS REGARDING ENGINE DAMAGE FROM I	NCORRECT TIMING. WE CONTACTED BOTH THE ENGINE MANUFACTURER AND THEAIRFRAME MANUFACTURER, ATTACHED IS THE REPLY FROM THE 	AIRFRAME MANUFACTURER. THEY WILL CHANGE THE S RVICE MANUAL.			1	L	7	1 	3O	3	O		A3SO    	1E4				 
2003032800013	20030328	00013	NM  	2003	3	28	CA030214007      	1	20030213	G	5210	PACMKP23SFS428	BEARING         			BOEING	757   	757236      	1384971	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					R1 CABIN DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING OPERATION OF THE DOOR R1, IT WAS NOTED THAT A SLIGHT PUSH WAS REQUIRED TO CLOSE THE DOOR. DURING A SCHEDULE	 MAINTENANCE (S-01) CHECK, MTCE FOUND THE DOOR MECHANISM CAM FOLLOWER CRANK ASSY BEARING BADLY CORRODED.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2003032800014	20030328	00014	CE  	2003	3	28	CA030214008      	1	20030212	G	3340		SWITCH          	CARLINGSWTCH		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	LANDING LIGHT	SPARKS          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) SMOKE WAS SEEN COMING FROM THE NAV LIGHT SWITCH. THE SWITCH FELL OUT AND SPARKS WERE SEEN INSIDE THEOPENING. THE S	PARKING STOPPED AFTER APPROXIMATELY 30 SECONDS. THE FAULT WAS CONFERMED BY MAINTENANC E. NO OTHER DAMAGE WAS EVIDENT. SW	ITCH IS TO BE REPLACED.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003042900143	20030429	00143	EU  	2003	4	29	CA030214011      	1	20030130	G	2997	E0052R10865NF	WIRE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					NR 2 ENGINE	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								695452			(CAN) ENGINE NR 2, HYDRAULIC FIRE SHUTOFF VALVE, CIRCUIT BREAKER 558 POPPING AND WILL NOT RESET.  INSPECTION FOUND WIRIN	G DAMAGED (P/N'S: 2912-5006, 2912-5007 AND 29-5003)(BURNT OVER 12INCHES)FROMCONNECTOR OF THE NR 2 ENGINE FIRE SHUTOFF VA	LVE (YELLOW SYSTEM), FUNCTIONAL IDENTIFICATION NUMBER: 2GD. THE WIRING WAS REPAIRED IAW AMM 20-43-10 AND THE CONNECTOR R	EPLACED IAW AMM 20-53-20. A FUNCTIONAL CHECK WAS C/OUT I.A.W. AMM 29-10-00. A FLEET CAMPAIGN WAS INITIATED.			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2003032800022	20030328	00022	CE  	2003	3	28	CA030218008      	1	20030211	G	2720	0400107104	CONTROL CABLE   			CESSNA	140   	140         	2071602	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	RUDDER	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) 2 CABLES FOUND CORRODED AND FRAYED AT FUSELAGE STA. 20.5. BOTTOM OF FORWARD LANDING GEAR BULKHEAD. DEFECT WAS FOUN	D ON CABLES BECAUSE THEY HAD TO BE REMOVED FOR MAJOR STRUCTURAL REPAIRS. THOSE CABLES RUN ON PULLIES ATTACHED TO THE BUL	KHEAD AT THE VERY BOTTOM OF THE FUSELAGE. VERY HARD TO DETECT UNLESS CABLES ARE REMOVED. FUSELAGE BOTTOM USUALLY VERY DI	RTY IN THAT AREA WHERE WATER AND MUD ACCUMULATE.			1	H	7	1 	3O	3	O	NC	A768    	E252	5	N	P918	 
2003041500007	20030415	00007	CE  	2003	4	15	CA030218009      	1	20030209	G	7921	636900	OIL COOLER      			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE OIL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WE DISCOVERED CRACKS DEVELOPING AROUND WELDS ON THE ATTACHING POINTS OF THE OIL COOLER. INSTALLATION PROCEDURE INC	LUDING TORQUE, AND ALL THE ATTACHING HARDWARE, WERE CORRECTLY FOLLOWED.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2003040100047	20030401	00047		2003	4	1	CA030218010      	4	20030213	G	6122	697072003	GOVERNOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					OVERSPEED	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) CAUTION LIGHT FOR NR 2 AC GENERATOR ON AFTER ENGINE START. CHECKLIST CONSULTED AND GENERATOR RESET WITH SUCCESS.  	AFTER TAKEOFF POWERPLANT MESSAGE ON ED, CHECKLIST CONSULTED AND NORMAL ENGINE INDICATIONS OBSERVED, FLIGHT CONTINUED TO 	NEXT BASE.  ON APPROACH, AT 500-300 FT TORQUE ON NR 2 ENGINE, STARTED TO FLUCTUATE AND A SOUND SIMILAR TO OVERSPEED GOVE	RNOR TEST WAS OBSERVED. AIRCRAFT YAW TO THE RIGHT WAS FELT, ENGINE INSTRUMENT WAS MONITORED WHILE POWER LEVER ON ENGINE 	NR 2 WAS REDUCED TO FLIGHT IDLE, POWER WAS ADDED TO THE NR 1 ENGINE. ENGINE   NR 2 WAS FEATHERED AND SHUTDOWN. AN UNEVEN	TFUL LANDING WAS PERFORMED. OVERSPEED GOVERNOR/PUMP REPLACED.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003042900144	20030429	00144		2003	4	29	CA030218011      	4	20030211	G	8300		GEARBOX         								PWA   	PT6   	PT6A41      	52043	EA  					ACCESORY	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA								8129			(CAN) ENGINE SUFFERED AN IFSD AND WAS REMOVED AND RETURNED FOR INVESTIGATION.  CUSTOMER SUSPECTED AN AGB BALL LOCK FAILU	RE.   ENGINE WAS FOUND TO HAVE SIGNIFICANT DAMAGE INSIDE THE AGB WITH MANY GEARSHAFTS & MUTILATED TEETH & INPUT DRIVE FL	ANGED BEARING COMPLETELY DESTROYED.									4	T			E4EA				 
2003040100048	20030401	00048	CE  	2003	4	1	CA030218012      	1	20030217	G	3350	TB1	TERMINAL BLOCK  			LEAR  	55    	55LEAR      	5170702	CE  	ALIDSG	TFE731	TFE7313AR   	 	WP  					EMERGENCY LIGHTS	OVERHEATED      	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MFG DESIGN FLAW, INSTRUMENT LIGHTING SYS WAS DISCOVERED WHEN NEW AIR DATA DISPLAY UNIT WAS INSTALLED FOR RVSM UPGR	ADE. SYMPTOM WAS  ADDU LIGHT WOULD GO INTO NIGHT MODE (VERY DIM) WHEN EMER BATT PACK WAS TURNED ON. PACK IS KEPT ON IN F	LIGHT TO RUN STANDBY GYRO.  PROBLEM WAS THAT IN NON-EMER MODE, EMERGENCY PACK WAS POWERING WHOLE 5 VOLT INSTRUMENT LIGHT	ING BUS VIA RELAY K2 AND CR4 ON TB1 IN CIRCUIT BOARD UR-1. 2.2 AMP DRAW THROUGH CR4 WOULD CAUSE IT TO OVERHEAT BUT IN TU	RN DROP VOLTAGE LOW ENOUGH THAT LAMP LIGHTING WAS TOO DIM TO BE NOTICED. PROBLEM WENT UN-NOTICED UNTIL RVSM MOD WAS DONE	. MFG WAS NOTIFIED OF PROBLEM, SENT WIRING MOD TO SYS.	2	L	7	2 	4F	4	F		A10CE   	E6WE				 
2003041500009	20030415	00009	CE  	2003	4	15	CA030218013      	1	20030214	G	5610	1013840252	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOTS WINDOW CRACKED IN FLIGHT						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2003041500010	20030415	00010	EU  	2003	4	15	CA030219002      	1	20030218	G	3020	5302412123	HOSE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ANTI ICE SYS	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) EXHAUST STAINING WAS NOTED COMING FROM LT INTAKE LIP DE-ICE AREA. SUBJECT HOSE (SEAL)WAS FOUND TOBE LEAKING WHERE 	THE LT PIPE COMES DOWN FROM THE EXHAUST STACK AND JOINS WITH THE LIP DEICE PART.HOSE REPLACED WITH NEW.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003041500011	20030415	00011	CE  	2003	4	15	CA030219004      	1	20030219	G	3213	504100077	PISTON          			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470VO     	17026	SO  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING COMPLETE REMOVAL AND NDT OF ALL LANDING GEAR PARTS BOTH LT & RT MAIN GEAR PISTON AND AXLE ASSEMBLIES (P/N S	 5041000-77 & 5041000-76 RESPECTIVELY) WERE FOUND CRACKED AT THE SMALLER OF THE TWO TORQUE LINK ATTACH LUGS.THE RT WAS R	EPLACED WITH A USED SERVICEABLE UNIT, HOWEVER 10 USED LT UNITS WERE TESTED AND FAILED PRIOR TO FINDING A SERVICEABLE USE	D ONE TO INSTALL.  WE FEEL FINDING A GOOD USED RT UNIT ON THE FIRST TRY WAS JUST A STROKE OF LUCK.			1	L	7	2 	3O	3	O		3A10    	3E1				 
2003041500013	20030415	00013	CE  	2003	4	15	CA030220003      	1	20030120	G	5312	10143002115	BULKHEAD        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUSELAGE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			20152	20152							(CAN) CREW REPORTED ON LAST LEG TO AIRPORT, LOW PRESSURIZATION OF 3.2 PSI. DURING TROUBLESHOOTING FOUND A CRACK FOUR INC	HES LONG ON BULKHEAD. LOCATION - CENTER OF FUSELAGE AT STATION 227.125.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2003041500004	20030415	00004	CE  	2003	4	15	CA030220004      	1	20030128	G	2780	1013800005	CONTROL CABLE   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	LE FLAPS	SHEARED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH AIRCRAFT FLAP ASYMMETRY TRIPPED. ON INSPECTION OF FLAP SYSTEM THE L/H OUTBOARD FLAP CABLE DRIVE AT MOT	OR FOUND SHEARED. NEW OUTBOARD L/H FLAP CABLE INSTALLED (P/N 101-380000-5). FLAP SYSTEM FUNCTION TEST CARRIED OUT. TESTE	D OK.				1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	STC	 
2003041500005	20030415	00005	CE  	2003	4	15	CA030220008      	1	20030220	G	2710	051010532	CONTROL CABLE   			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	TSIO520T    	17040	SO  					AILERON	FRAYED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AILERON DIRECT CABLE FRAYED AT NYLON PULLEYS IN CABIN ROOF AREA						1	H	7	1 	3O	3	O		3A24    	E8CE				 
2003041500014	20030415	00014		2003	4	15	CA030221004      	4	20030113	G	6122	8210007	GOVERNOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	INOPERATIVE     	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) ON RETURN FLIGHT PILOTS REPORT THAT RT PROPLLER RPM STAYED AT 2100. THEY WERE NOT ABLE TO GOVERN PROPELLER SPEED. 	AFTER LANDING MAINTENACE CHECKED THE SYSTEM AND DETERMINED THAT REPLACEMENT OF PROP. GOVERNOR WAS REQUIRED. AFTER REPLAC	EMENT WITH A SERVICABLE PART, FUNCTION CHECK WAS COMPLETED AND OPERATION WAS NORMAL.				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2003041500001	20030415	00001	CE  	2003	4	15	CA030221006      	1	20030218	G	5510	504400317	CHANNEL         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					HORIZONTAL STAB	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UPPER ELEVATOR CABLE P/N NAS304-34-0753 FOUND INCORRECTLY ROUTED. INSTEAD OF PASSING THROUGH THE LIGHTNING HOLES I	N AFT BOX STRUCTURE P/N50-440031-7, THE CABLE WAS ROUTED ABOVE THE STRUCTURE. THIS CAUSED THE ELEVATOR CABLE TO CUT INTO	 THE CHANNEL ASSY. WHEN FOUNDTHE CABLE HAD SAWN INTO THE EDGE OF THE CHANNEL. THE ELEVATOR BELLCRANK HAD BEEN REPLACED 8	4HRS PREVIOUSLY.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003041500002	20030415	00002	CE  	2003	4	15	CA030221007      	1	20030220	G	5520	556555026	ARM             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					COUNTER WEIGHT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ROUTINE MAINTENANCE INSPECTION OF THE CONTROL COLUMN, A CRACK WAS FOUND IN THE BOB WEIGHT ARMNEAR THE HOLE 	WHERE THE ARM IS ATTACHED TO THE ELEVATOR TORQUE TUBE. BOB WEIGHT ARM REPLACED.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2003041500006	20030415	00006	CE  	2003	4	15	CA030221009      	1	20030220	G	2435	23080025	BEARING         			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					STARTER GEN	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) AT FLIGHT LEVEL 33,000 FT A POPPING SOUND FOLLOWED BY ENGINE VIBRATIONS WAS EXPERIENCED. RT POWER LEVER RETARDED S	LOWLY AND VIBRATION LEVEL SOFTENED,BUT, STILL NOTICEABLE, ALL ENGINE PARAMETERS WERE NORMAL AND STEADY. AT 73 PERCENT ON	 DECENT THRU 29000 FT A STRONG VIBRATION BEGAN. THE RT LEVER SET TO 67 PERCENT THE VIBRATION WAS STILL NOTICEABLE. AT 9,	000 FT THE POWER LEVER WAS RETARDED TO 58 PERCENT. LANDED AND SHUTDOWN ENGINE. NR 2 STARTER GENERATOR REMOVED DUE TO BEA	RING FAILURE.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2003041500015	20030415	00015	EU  	2003	4	15	CA030224002      	1	20030224	G	2897		WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BOOST PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						B4673					(CAN) A FUEL BOOST PUMP WAS REPLACED FOR ITS SCHEDULED OVERHAUL REPLACEMENT AT 3500 HOURS.A WIRE WAS FOUND CHAFED TO BAR	E WIRE THROUGH ROUGHLY MIDWAY OF THE MANUFACTURER SUPPLIED HARNESS.  THIS COULD HAVE THE POTENTIAL TO IGNITE THE FUEL TA	NK IF SPARKS WERE PRESENT. DUE TO THE LENGTH OF WIRE, IT IS POSSIBLE FOR THE HARNESS TO RUB ON A COUPLE OF DIFFERENT PLA	CES, IE: BONDING STRAP, RIB, TOP OF PUMP. PILATUS WAS CONTACTED WITH THE PROBLEM AND WE REQUESTED A MEANS TO PROTECT THE	 HARNESS.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003041400092	20030414	00092	SO  	2003	4	14	CA030227001      	2	20030224	G	7414	6310	FLANGE          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					MAGNETO	FAILED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											(CAN) UPON PREFLIGHT RUN-UP, PILOT NOTICED RT MAGNETO ON NR 1 ENGINE WAS NOT FUNCTIONING. UPON INSPECTION BY MAINTENANCE	, THE MAGNETO WAS FOUND DETACHED FROM ENGINE WITH THE MOUNTING FLANGE BROKEN AND STILL ATTACHED TO THE ENGINE. MAGNETO W	AS REPLACED WITH NO FURTHER PROBLEMS.				1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2003041400095	20030414	00095	CE  	2003	4	14	CA030227005      	1	20030227	G	2750	14601007	CONTROL CABLE   			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360GB     	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	TE FLAPS	FRAYED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING 100 HR INSPECTION THE INBOARD RIGHT HAND FLAP CABLE WAS INSPECTED FOR WEAR IN THE AREA OF THE INBOARD FLAP 	BELLCRANK. CABLE WAS FOUND FRAYED APPROX. 1 INCH FROM CABLE END ATTACH FITTING.CABLE R EPLACED.					1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
2003041400096	20030414	00096	SO  	2003	4	14	CA030227006      	1	20030220	G	3297		WIRE HARNESS    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT MLG	DAMAGED         	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) A/C DID NOT HAVE A RIGHT GEAR DOWN & LOCKED INDICATION APPROACHING AIRPORT. SEVERAL ATTEMPTS TO RECYCLE THE GEAR H	AD NO EFFECT. ALL OTHER INDICATIONS AND GEAR OPERATION APPEARED NORMAL. A/C OVERFLEWAIRPORT FOR PRECAUTIONARY REASONS. L	ANDING WAS UNEVENTFUL. A BROKEN WIRE WAS FOUND IN THE MAIN WIRING BUNDLE ON THE RIGHT MAIN GEAR. THE WIRE COMPLETED THE 	RT GEAR DOWN & LOCKED INDICATION CIRCUIT.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2003041400097	20030414	00097	CE  	2003	4	14	CA030228001      	1	20030228	G	5510	07321014	HINGE           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	STABILIZER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ROUTINE SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE REINFORCEMENTS - STABILIZER HINGE WERE CRACKED. P	/N 0732101-4 REPLACED WITH NEW PARTS.					1	H	7	1 	3O	3	O		3A24    	E3SO	5	C	P47GL	 
2003041400100	20030414	00100	SW  	2003	4	14	CA030228004      	1	20030221	G	5312	222031506103A	FITTING         			BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON A THREE HUNDRED HOUR INSPECTION 270 BULKHEAD FITTING 222-031-506-103A WAS FOUND CRACKED. TO REPAIR INCORPORAT	ION OF TB 222U-94-72.					1	G	7	2 	3U	3	U		H9SW    	E5NE				 
2003041400101	20030414	00101	CE  	2003	4	14	CA030228007      	1	20030226	G	5312	071111224	BULKHEAD        			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION, IT WAS DICOVERED THE BULKHEAD HAD A SUBSTANDARD REPAIR AT REAR FLOAT FITTING ATTACHMENT 	BRACKETS. PREVIOUS REPAIR REMOVED TO FACILITATE NEW REPAIR. BULKHEAD WAS FOUND TO BE CRACKED BEYOND REPAIR WITH A TOTAL 	OF 4 CRACKS WITHIN A 8 INCH AREA. CRACKS WERE FOUND IN FLANGE AND WEB. AREA IS SOMEWHAT DIFFICULT TO INSPECT DUE TO FLOO	R SKIN COVERING. BULKHEAD IS BEING REPLACED WITH NEW.			1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P3EA	 
2003041400104	20030414	00104	CE  	2003	4	14	CA030228010      	1	20030221	G	7820	175400122	MUFFLER         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	EXHAUST SYS	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT MUFFLER END PLATE CRACKED BEHIND RT FORWARD EXHAUST INLET (NR 1 CYLINDER). NOT LEAKING INTO HEAT MUFFLER. BARRE	L ALSO BULGED FORWARD SIDE NEAR OUTLET (USUAL PLACE). BOTH DAMAGES MAY HAVE BEEN CAUSED BY AFTER FIRING IN MUFFLER. MUFF	LER HAS BEEN PREVIOUSLY REPAIRED ON OPPOSITE ENDPLATE. CRACK PROBABLY DUE TO METAL FATIGUE AND AGE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003041400105	20030414	00105	CE  	2003	4	14	CA030228011      	1	20030219	G	3320	PWFLC28	POWER SUPPLY    			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					CABIN	SHORTED         	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, SMOKE WAS NOTICED IN THE CABIN AREA. CABIN FIRE EXTINGUISHER WAS DISCHARGED IN GENERALAREA OF SMOKE.	 NO OPEN FLAMES WERE NOTICED. AFTER LANDING MAINTENANCE INVESTIGATED AND FOUND THAT T HE SOLID STATE POWER SUPPLY FOR AN	 OVERHEAD FLOURESCENT LIGHT HAD HAD AN INTERNAL SHORT. THERE WAS NO DAMAGE TO ADJACENT STRUCTURE INSULATION OR WIRING. P	OWER SUPPLY WAS REPLACED WITH NEW PART. SYSTEMWORKED NORMALLY.			1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2003041400107	20030414	00107	SO  	2003	4	14	CA030228015      	1	20030225	G	3230	OAS29305	POWERPACK       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MLG	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) UPON TAKEOFF FROM AIRPORT,  MLG SELECTED UP, BUT THE INTRANSIT LIGHT DID NOT GO OFF.  MLG WAS CYCLED WITH DOWN AND	 LOCKED INDICATING EACH TIME, BUT INTRANSIT REMAINING ON DURING GEAR UP SELECTION.  A FLY-BY WAS PERFORMED, NOTING THE L	T MLG DOOR OPEN, LT MLG HANGING ABOUT 45 DEGREES, AND RT MLG DOOR OPEN. A/C RETURNED TO AIRPORT, MLG WAS SELECTED DOWN W	ITH DOWN AND LOCKED INDICATIONS AND LANDED.   HYD SYS PRESSURES WERE CHECKED & FOUND TO BE WEAK, HYD POWER PACK WAS REPL	ACED WITH AN OVERHAUL UNIT, MULTIPLE GEAR SWINGS WERE PERFORMED AND THE AIRCRAFT WAS GROUND RUN AND HYD PRESSURES WERE C	HECKED SERVICEABLE.  THE AIRCRAFT SUBSEQUENTLY PERFORMED A TEST FLT WITHOUT GEAR TROUBLES.	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2003041400110	20030414	00110	EA  	2003	4	14	CA030305001      	2	20030304	G	7414	M3100	IMPULSE COUPLING			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AS A RESULT OF PREVIOUS IMPULSE COUPLING FAILURES, WE IMPLEMENTED AN IMPULSE COUPLING INSPECTION EVERY 100 HRS. UP	ON INSPECTION OF THIS IMPULSE COUPLING WE FOUND THE HUB VERY LOOSE, BOTH PAWL RIVETS LOOSE, AND THE PAWL GAPS EXCEEDED T	HE MAXIMUM ALLOWED BY SLICK SB1-98.  PAWL GAPS WERE IN EXCESS OF .170 INCH. MAX ALLOWABLE IS .150 INCH.  HAD THIS IMPULS	E COUPLING FAILED IT WOULD HAVE DAMAGED AND CONTAMINATED THE ENGINE.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003041400111	20030414	00111	EA  	2003	4	14	CA030305002      	2	20030227	G	7414	M3100	IMPULSE COUPLING	SLICK       	4372        	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						00052906					(CAN) DUE TO PREVIOUS IMPULSE COUPLING FAILURES, WE IMPLEMENTED AN IMPULSE COUPLING INSPECTION EVERY 100 HRS. THIS IMPUL	SE COUPLING WAS FOUND TO HAVE A LOOSE PAWL RIVET.  SLICK SB1-98 WAS CARRIED OUT AND THE PAWL GAPS WERE FOUND TO BE WITHI	N LIMITS, AND THE T-155 RIVET GAUGE SHOWED NO WEAR.  THE IMPULSE CO UPLING WAS REPLACED WITH A NEW ONE.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003041400114	20030414	00114	CE  	2003	4	14	CA030305005      	1	20030227	G	6123	35821511	CONNECTOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	AUTOFEATHER SYS	CRACKED         	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA			10024								(CAN) CREW REPORTED THAT AUTOFEATHER DISABLE LIGHT WOULD ILLUMINATE DURING CLIMB AND DECENT PORTIONS OF FLIGHT. MAINTENA	NCE DID NUMEROUS ATTEMPTS TO DUPLICATE WITH SYSTEM PARTS BEING REPLACED FOR TROUBLESHOOTING PURPOSES. TEST FLIGHTS WHERE	 COMPLETED WITH THE DEFECT ALSO NOT DUPLICATED. THE PRINTED CIRCUIT BOARD CONNECTOR WAS FOUND TO HAVE A HAIRLINE CRACK A	ND WAS REPLACED. THE AIRCRAFT HAS FLOWN APPROX. 7 DAYS WITHOUT REOCCURENCE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003041400117	20030414	00117	GL  	2003	4	14	CA030305008      	3	20030217	G	6111	D3A36C435A	PROPELLER       			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	BLADE ANGLES	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FACTORY NEW PROPELLER STC SA00920CH.  ONLY OBTAIN 2300 RPM STATIC, SHOULD BE 2600 RPM.  FOUND BLADE LOW END STOPS 	INCORRECTLY SET.- PROP RETURNED TO OBTAIN NEEDED 2600 RPM.  ERROR IN ENGINEERING APPROVAL AT MCCAULEY INCORRECT BLADE AN	GLES.				1	H	7	1 	3O	3	O		3A21    	3E1	5	C	P3EA	 
2003041400121	20030414	00121	CE  	2003	4	14	CA030306002      	1	20030304	G	3245	6006	TUBE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					MLG WHEEL	TORN            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) A/C LANDED AND PILOT TAXIED OFF THE RUNWAY.  20 TO 30 FEET ON TAXIWAY AND A/C BECAME IMPOSSIBLE TO TAXI. FOUND LEF	T MAIN WHEEL FLAT.WHEEL DISASEMBLED AND FOUND TUBE WITH TEAR APPROX 1/4 INCH LONG ON THECENTER OF THE TUBE ALONG THE MOL	DING RIBS.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003041400087	20030414	00087	EA  	2003	4	14	CA030306004      	1	20030228	G	5510	C2TP57	SPAR            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R98539      	52008	NE  					HORIZONTAL STAB	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) INSPECTION CARRIED OUT AS PER SB 2/47 REV 'D' AD CR-91-42.TAILPLANE SPAR FOUND CRACKED LT SIDE TOP UNDER LT PICK-U	P BRACKET C2TP159. MODS 2/436, 2/466, 2/758 HAD ALREADY BEEN INCORPORATED.AIRCRAFTTTSN 10127.3 HOURS.					1	H	7	1 	3R	3	R		A806    	5E1				 
2003040900012	20030409	00012	CE  	2003	4	9	CA030311008      	1	20030305	G	3250		BUNGEE CYLINDER 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG STEERING	FAILED          	W				O				OTHER                   				S			AFFECT SYSTEMS            			TX	TAXI/GRND HDL  	1			CA											(CAN) NOSE GEAR STEERING FAILED DURING TAXI . THE CREW EXPERIENCED A (THUMP) IN THE RUDDER / STEERING SYSTEM. AFTER THE 	(THUMP) THE CREW WAS UNABLE TO TAXI THE AIRCRAFT IN A STRAIGHT LINE. INSPECTION REVEALED THAT THE NOSE GEAR STEERING SPR	ING BUNGEE ASSEMBLY HAD FAILED. FAILURE OCURRED IN THE SPRING CLIP RETAINING SLOT AREA. SB 2220 DEALS WITH THIS ISSUE. T	HIS OPERATORSHALL INITIATE ADDITIONAL INSPECTIONS TO PREVENT REPEAT OCCURENCES.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003040900013	20030409	00013	CE  	2003	4	9	CA030311017      	1	20030307	G	5610	10138402523	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN CRUISE THE PILOTS NOTICED A CRACK APPEARED ON THE RIGHT SIDE OF THE PILOTS FRONT WINDOW. MORE CRACKS APPEARED O	N DESCENT INTO AIRPORT. ON INSPECTION THE CRACKS WERE FOUND TO BE IN THE OUTSIDE NON-STRUCTURAL GLASS. THE WINDOW WAS RE	PLACED.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003040900014	20030409	00014	CE  	2003	4	9	CA030311018      	1	20030308	G	3230	1153800025	MOTOR           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	MLG	INTERMITTENT    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LANDING GEAR STOPPED APROXIMATELY HALF WAY UP.  CIRCUIT BREAKER IN THE FLOOR HAD POPPED.  CIRCUIT BREAKER WAS RESE	T AND GEAR WAS SELECTED DOWN AND AIRCRAFT LANDED WITHOUT INCIDENT.  MOTOR WAS REPLACED AND SWINGS CARRIED OUT IAW MANUFA	CTURER.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P40EA	 
2003040900015	20030409	00015	EU  	2003	4	9	CA030312001      	1	20030221	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD PUMP	BROKEN          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) BELT BROKE BEFORE TAKE OFF.  FOUND TO HAVE BROKEN AT THE SEAM.  PULLEY AND PUMP WERE CHANGED AT THE SAME TIME AS T	HE BELT.  IT WAS NOTED THIS TIME, AS IN OTHER TIMES THAT THE BELT WAS TENSIONED TO THE MAX IN ORDER TO PUT THE PULLEY BO	LTS IN.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003040900016	20030409	00016	EU  	2003	4	9	CA030312002      	1	20030305	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD PUMP	BROKEN          	W				C				ABORTED TAKEOFF         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) AFTER THE PILOT PERFORMED HIS HYD PRESSURE TEST, (HYDRAULIC PRESSURE) LIGHT CAME ON.   ON DI THE NIGHT BEFORE AND 	ON THE DAY OF INCIDENT, THE BELT.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003040900017	20030409	00017	EU  	2003	4	9	CA030312003      	1	20030226	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					HYD PUMP	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON DESCENT FOR THE BASE, THE CAUTION HORN AS WELL AS (HYDRAULIC PRESSURE) LIGHT CAME ON.  A/C LANDED WITHOUT INCID	ENT.  UPON INSPECTION, HYDRAULIC PUMP BELT WAS FOUND BROKEN, LAYING ON THE TRANSMISSION DECK.  THE BELT WAS BROKEN AT TH	E JOINT.				1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2003040900018	20030409	00018	EA  	2003	4	9	CA030312005      	1	20030228	G	5610	NP1393325	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) FLIGHTDECK LT SIDE WINDOW CRACKED. WINDOW ASSEMBLY REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003040900019	20030409	00019	EA  	2003	4	9	CA030312006      	1	20030307	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT FL340, CO-PILOTS WINDOW CRACKED. TWO CRACKS OF AROUND 30CM IN AFT PORTION OF WINDOW. DURING APPROACH, WINDOW CR	ACK FURTHER EXTEND TOTALLY FROM FRONT TO REAR.  FOUND MIDDLE AND INNER PLY CRACKED. WINDOW REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003040900020	20030409	00020	EA  	2003	4	9	CA030312007      	1	20030308	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				K				NONE                    				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA			13433								(CAN) AIRCRAFT 7169 TAT = 13433.6 HOURS F/O SIDE WINDOW CRACKED AND ARCING ON DESCENT.  OUTER PANE CRACKED.ROAD TRIP CRE	W DESPATCHED.  REMOVED AND REPLACED RT SIDE WINDOW (ORIGINAL EQUIPMENT).  RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003040900021	20030409	00021	EA  	2003	4	9	CA030312008      	1	20030214	G	2710	600911787	CONTROL CABLE   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					AILERON	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) AILERON CONTROL JAM.  ACTION QRH ESTABLISHED THAT PILOT SIDE WAS  OPERATING CHANNEL. CONTROL ON CO-PILOT AILERON, 	FULL CONTROL FOR AILERON UP. AILERON MOTION FROM APPROX NEUTRAL AND DOWN NON EXISTENT. CONTROL ON CAPTAIN SIDE WAS FULL 	AND FREE. FOUND RT AILERON QUADRANT AT RT WHEEL WELL, LOWER CONTROL CABLE GUARD PIN LOW CLEARANCE WITH QUADRANT. DAMAGE 	AT TIP OF THAT GUARD PIN, WHICH WAS MISORIENTED, WAS STOPPING THE MOTION WHEN TRYING TO MOVE AILERON DOWN. NEW GUARD PIN	 INSTALLED IAW DWG 600-91014 AND BAPS 164-001. NO DAMAGE WAS FOUND AND INTEGRITY OF AILERON CONTROL SYS WAS CARRIED OUT 	ON THE RT SIDE, EVERYTHING CHECKED SERVICEABLE. AIRCRAFT WAS RELEASE FOR FLIGHT. NO FURTHER ACTION REQUIRED.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003040900022	20030409	00022	EA  	2003	4	9	CA030312009      	1	20030309	G	5610	NP1393211	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA			15823								(CAN) AIRCRAFT TAT = 15823.8 HOURS.FLIGHT 5788.  CAPTAIN'S SIDE WINDOW CRACKED IN CRUISE FLIGHT. DECLARED AN EMERGENCY A	ND LANDED.  REMOVED AND REPLACED SIDE WINDOW.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003042900148	20030429	00148	SO  	2003	4	29	CA030313003      	1	20030308	G	7500	5842281H5210	REGULATOR VALVE 			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) ON APPROACH, THE CREW NOTICED MULTIPLE AVIONICS FAILURES. BOTH VOR SIGNAL STRENGTHS VERY WEAK, NR 1 COMM INOP, MOS	T NAVIGATION EQUIPMENT INOP. THE PNEUMATIC PRESSURE WAS NOTED AS BEING AT 21 PSI, WHEN IT SHOULD HAVE BEEN AT 18 PSI. TH	E PNEUMATIC REGULATOR VALVE HAD FAILED. THIS FAILURE CAUSED HOT AIR TO BE RELEASED AT THE PRESSURE RELIEF VALVE WHICH IS	 LOCATED IN CLOSE PROXIMITY TO AN ANTENNA COAXIAL CABLE BUNDLE. THE HOT AIR HARDENED & DAMAGED THE CABLES, CAUSING THE A	VIONICS FAILURES MENTIONED ABOVE.		1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2003042900149	20030429	00149	SW  	2003	4	29	CA030313004      	1	20030311	G	5210	2720063907	RECEPTACLE      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15106								(CAN) DURING DOOR REPAIR, INSPECTION OF LATCHING MECH ON FUSELAGE WAS CARRIED OUT. RECEPTICLE CRACKS WERE NOTICED VISUAL	LY ON 6 OF 7 RECEPTICLES. LATCHING RECEPTICLE CONTAINS AN ECCENTRIC FITTING SITS IN RECEPTICLE TO ADJUST FOR ALIGNMENT O	F CABIN DOOR WHEN CLOSED. CRACKS IN RECEPTICLES CAN`T BE SEEN IF ECCENTRICS ARE INSTALLED.  THESE RECEPTICLES ARE ALL AL	UMINUM EXCEPT FOR NR 7 WHICH IS LOCATED AT TOP OF FUSELAGE THAT ONE IS STEEL. NR 7 RECEPTICLE ALSO DOESN`T REQUIRE AN EC	CENTRIC FITTING. RECEPTICLES WERE REMOVED FROM A A/C PREVIOUSLY REMOVED FROM SERVICE & SENT FOR NDT INSPECTION PRIOR TO 	INSTALLATION. WERE ALSO ALL CRACKED SIMILAR TO ONES REMOVED FROM AIRCRAFT.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003042900150	20030429	00150	NM  	2003	4	29	CA030313005      	1	20030226	G	2121	732591	FAN             			BOEING	767   	767383      	1385214	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					COCKPIT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) SMOKE IN COCKPIT, DISSAPATED AFTER LANDING WITH A STATUS MESSAGE 'FWD EQ EXH FAN' AND FOUND C/B H21 LWR EQUIPEMENT	 PANEL 'FWD  EXH EQUIP COOL FAN' POPPED					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2003042900151	20030429	00151		2003	4	29	CA030314001      	4	20030313	G	3417	8220372145	COMPUTER        			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					ADC	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DIS-DURING CLIMB OUT CREW NOTED CAPT/FO ALT GO BLANK. CREW ELECTED TO RETURN TO AIRPORT. NOTE ON THEWAY TO AIRPORT	 SYSTEM CAME BACK ON LINE. CREW CONTINUED TO AIRPORT TO HAVE MTX CHECK OUT SYSTEM. A/C LANDED SAFELY NO FURTHER INCIDENT	S WERE REPORTED.  FOUND NR 1 ADC COMPUTER INTERNAL FAILURE.  RAI'D THE NO.1 ADC AND OPS CHECK GOOD.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003042900152	20030429	00152	EA  	2003	4	29	CA030314002      	1	20030309	G	5610	NP139H6850	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) CREW NOTED THE CAPTAIN'S SIDE WINDOW HAD CRACKED. MAINTENANCE REMOVED AND REPLACED THE CAPTAIN'S SIDE WINDOW WITH 	SERVICEABLE UNIT.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003042900153	20030429	00153	EA  	2003	4	29	CA030314005      	1	20030212	G	3010	73010033147	LINE            			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	DE-ICE SYS	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			28861								(CAN) DURING TROUBLESHOOTING A DE-ICE SNAG, ( NR 1 ENG DE-ICE BOOT WILL NOT INFLATE ) IT WAS FOUND THAT THE DE-ICE LINE 	P/N 73010033-147 HAD BEEN CHAFFING ON A HYDRAULIC LINE. THIS LINE IS LOCATED UNDER PANEL 419AT (NR 1 ENG BATMAN PANEL). 	THE LINE IS HIDDEN UNDER NUMEROUS OTHER LINES AND IT IS VERY DIFFICULT TO SEE / NOTICE THE CHAFFING. WE HAVE CHECK AN OT	HER AIRCRAFT AND HAD TO USE A BORESCOPE TO CONFIRM IF THE LINES WERE TOUCHING EACH OTHER. THE LINE WAS REPLACED AND THE 	AIRCRAFT RETURNED TO SERVICE.SEE ATTACHED PICTURES.		2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
2003042900155	20030429	00155	CE  	2003	4	29	CA030317004      	1	20030313	G	2121	19A6002	MOTOR           			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FAN	WORN            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED DURING CRUISE A ODOUR AND NOISE IN COCKPIT. A SLIGHT AMOUNT OF SMOKE WAS NOTICED IN WINDSHIELD AREA	. PILOT PULLED CIRCUIT BREAKER FOR AVIONICS FAN AND NOISE STOPPED.PILOT RETURNED TO BASE AS PRECAUTION. SMELL DISSIPATED	 DURING RETURN TO BASE. BEARINGS ON MOTOR SHAFT FOUND TO BE WORN,CAUSING FAN TO RUB ON HOUSING.				1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
2003042900156	20030429	00156	CE  	2003	4	29	CA030317007      	1	20030311	G	5751	991300009	SKIN            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					LT AILERON	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			22426								(CAN) 1/2 INCH CRACK ON TOP SKIN OF LT AILERON FROM TRIM TAB OPENING FAR OUTBOARD CORNER TO FIRST RIVET.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003041500024	20030415	00024	CE  	2003	4	15	CA030317008      	1	20030307	G	6120	HCB4MP3	PROPELLER       			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  		FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA						FWA2327					(CAN) ON LANDING ON A CLEARED RUNWAY WITH SNOW & ICY PATCHES, SKY CLEAR & WIND CALM, PILOT HAD DIFFICULTY CONTROLLING A/	C. AS A/C SLOWED DOWN RUDDER CONTROL BECAME INEFFECTIVE CAUSING A/C TO DRIFT INTO RT SNOW BANK. UPON INVESTIGATING LT PR	OP,  FOUND IN A FINE PITCH POSITION & BLADES WERE BENT BACK 90 DEGREES FROM DIRECTION OF ROTATION. RT PROP BLADES WERE F	OUND TO BE 180 DEGREES FROM FEATHERED POSITION & WERE BENT BACK IN DIRECTION OF ROTATION.PROPS WILL BE REMOVED AND FORWA	RDED TO A PROP OVERHAUL FACILITY WHERE RT PROPELLER WILL BE DISASSEMBLED AND INSPECTED TO SEE IF AN INTERNAL FAILURE RES	ULTED IN BLADES GOING INTO THIS POSITION CAUSING THE AIRCRAFT TO LOOSE DIRECTIONAL CONTROL.	2	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P56GL	 
2003042900157	20030429	00157	CE  	2003	4	29	CA030317009      	1	20030314	G	2731	5052447413	TUBE            	BEECH       		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					CLEVIS	BROKEN          	W				A				UNSCHED LANDING         				I			FLT. ATTITUDE INST.       			CR	CRUISE         	1			CA											(CAN) AT FLIGHT LEVEL 220, FLIGHT CREW HEARD A LOUD BANG AND EXPERIENCED SIGNIFICANT AIRFRAME VIBRATION. THE A/C CLIMBED	 APPROXIMATELY 200FT BEFORE CREW WERE ABLE TO STOP ASCENT. EMERGENCY DECLARED, UNSCHEDULED LANDING CARRIED OUT. MAINTENA	NCE CREW FOUND THE LT ELEVATOR TRIM CONTROL TUBE FAILED.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003042900158	20030429	00158	CE  	2003	4	29	CA030317010      	1	20030303	G	3230	35175A	BRUSHES         			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					MLG MOTOR	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING LANDING, MLG SELECTED DOWN & NOTHING HAPPENED.  CIRCUIT BREAKER TRIPPED.  STARTED A MANUAL EMERGENCY MLG EX	TEND MANUAL MLG EXTEND HANDLE ENGAGED,  STUDENT COULDN`T MOVE ACT. AFTER SEVERAL ATTEMPTS & 2 STUDENTS MANAGED TO TURN A	CT HANDLE. AFTER 1ST TURN HANDLE BECAME EASY TO MOVE. GEAR LOWERED SUCCESSFULLY & A/C LANDED.  INSPECTION OF MLG ACT SYS	, MLG MOTOR FOUND U/S WITH ONE BAD BRUSH.  ACT WAS STIFF IN FULL UP POSITION. BOTH MOTOR & ACT REPLACED. PARTS SENT FOR 	INSPECT & REPAIR.		1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2003042900159	20030429	00159	CE  	2003	4	29	CA030318002      	1	20030317	G	2731	5061001736	TRIM TAB        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR	FRETTED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) SPECIAL INSPECTION CARRIED OUT AS PER CAMPAIGN 681-27-30-015 WHICH MANDATES INSPECTION OF THE ELEVATOR CONTROL TUB	E ATTACHMENT TO TRIM TAB.  RT TRIM TAB , BUSHING WAS FOUND NOT SEATED ALL THE WAY INTO THE TRIM TAB HORN. THE OUTBOARD S	IDE OF THE HORN HAD EXCESSIVE FRETTING FROM CONTROL ROD FORK END.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003042900160	20030429	00160	EA  	2003	4	29	CA030318009      	1	20030304	G	2730	C2T7A	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ELEVATOR	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			21878								(CAN) THE ELEVATOR TORQUE TUBE LOWER CABLE ATTACH POINT WAS FOUND TO BE ELONGATED. THE PART WAS SENT OUT TO BE REPAIRED.						1	H	7	1 	3R	3	R		A806    	5E1				 
2003042900161	20030429	00161	CE  	2003	4	29	CA030318010      	1	20030228	G	3245	6006	TUBE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MLG WHEEL	TORN            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING THE A/C STARTED TO YAW LEFT.  THE TIRE ON LT MAIN SIDE WAS FLAT AND VERY LOOSE ON THE RIM. ON LANDING T	HE BRAKES WERE NOT OVERLY USED. (PILOT REPORT)WHEEL ASSEMBLY DISASEMBLE AND FOUND TUBE WITH TEAR APPROX 1/4 INCH LONG ON	 THE CENTER OF THE TUBE ALONG MOLDING RIBS.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003041500033	20030415	00033	CE  	2003	4	15	CA030318011      	1	20030318	G	8011		DRIVE GEAR      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					STARTER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 50 HR INSPECTION, OIL FILTER ELEMENT WAS INSPECTED. STEEL PARTICLES WERE FOUND. NR  2 & 4 CYLINDERS WERE RE	MOVED FOR EXAMINATION OF CAMSHAFT & FOLLOWERS. NO FAULT FOUND. REMOVED THE TCM LIGHTWEIGHT STARTER, THE DRIVE GEAR WAS F	OUND TO BE EXCESSIVELY WORN. FURTHER INVESTIGATION REVEALED THAT BOTH MAGNETO DRIVE GEARS WERE ALSO DAMAGED. THE CAM & I	DLER GEARS WERE INSPECTED & NO DAMAGE OR WEAR WAS FOUND. I SUGGEST THAT THE STARTER GEAR WAS THE CAUSE OF THE WEAR TO TH	E MAGNETO DRIVE GEARS DUE TO METAL PARTICLES FALLING FROM THE STARTER DRIVE DOWN ONTO THE GEARS BELOW & BEING DRIVEN IN 	BETWEEN THE OTHERGEARS. IT WOULD SEEM THAT THE OTHER GEARS ARE A HARDER MATERIAL & THAT IS WHY THEY REMAINED UNDAMAG ED.	1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003042900162	20030429	00162	CE  	2003	4	29	CA030318015      	1	20030311	G	3245	65010	TUBE            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					MLG WHEEL	TORN            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) A/C LANDED WITH NO PROBLEM, TAXIED TO RAMP AND PILOT NOTICE A LOT OF DRAG ON RT MAIN HEEL DISESSEMBLED AND FOUND T	UBE WITH TWO TEARS APPROX 1/4 INCH.					1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2003042900163	20030429	00163	CE  	2003	4	29	CA030318016      	1	20030306	G	3297	1003810061	WIRE HARNESS    			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					DOWNLOCK SWITCH	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) UPON APPROACH , MLG WAS SELECTED DOWN FOR LANDING. AFTER EXTENSION IT WAS NOTED THAT THE RT MAIN WAS NOT INDICATIN	G THAT IT WAS DOWN AND LOCKED. THE GEAR WAS CYCLED SEVERAL TIMES WITH NO CHANGE IN DOWN AND LOCKED INDICATION PROBLEM. F	LT CREW PERFORMED EMERGENCY MLG EXTENSION & DECLARED AN IN-FLT EMERGENCY AND A/C WAS LANDED SAFELY. A/C WAS PLACED ON JA	CKS AND INDICATION SYSTEM INSPECTED. FAULT WAS LOCATED IN THE RT DOWNLOCK SWITCH WIRING HARNESS WHERE IT BENDS AT MLG AS	SEMBLY AND DRAG LEG INTERSECTION. A BROKEN WIRE WAS LOCATED FROM THE DOWNLOCK SWITCH AND REPAIRED. MLG SYSTEM WAS GROUND	-CHECKED SERVICEABLE WITH SEVERAL MLG EXTENSION AND RETRACTIONS, AND THE A/C WAS RELEASED FOR RETURN TO SERVICE.	1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003042900164	20030429	00164	CE  	2003	4	29	CA030318017      	1	20030316	G	2910	1013880175	HOSE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					HYD SYSTEM	CUT             	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING A WALK AROUND, THE CREW NOTICED HYDRAULIC FLUID IN THE RT MAIN GEAR AREA.MAINTENANCE FOUND THAT THE RETRACT	 LINE HAD BEEN CUT CLOSE TO THE IDENTIFICATION CLAMP. THE CUT OCCURED NEAR THE CLAMP WHICH MAY INDICATE A CYCLIC FAILURE	 WITH THE CLAMP BEING THE EDGE APPLYING PRESSURE THROUGH THE WEIGHT ON-WEIGHT OFF MOTION. THE HOSE WAS REPLACED, GEAR CY	CLED AND THE AIRCRAFT RELEASED.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2003041500038	20030415	00038	SW  	2003	4	15	CA030318019      	1	20030318	G	6220	407010105101	STUD            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					M/R HEAD	CRACKED         	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) TYPICAL CRACK FOUND AT OVERHAUL OF MAIN ROTOR HEAD.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003042900165	20030429	00165	SO  	2003	4	29	CA030319001      	1	20030317	G	3245	65010	TUBE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					MLG WHEEL	TORN            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) A/C LANDED WITH NO PROBLEM, TAXIED TO RAMP AND PILOT NOTICE A LOT OF DRAG ON RT MAIN WHEEL.  ASSEMBLY DISASSEMBLED	 AND FOUND TUBE WITH TWO TARE APPROX 1/4 INCH LONG ABOUT 6 TO 7 INCHES APART.  THE TWO TEARS ARE ALONG THE OUTBOARD DIAM	ETER OF THE TUBE.  TIRE INSPECTED FOR ANY FOREIGN OBJECTS AND NONE FOUND.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003042900166	20030429	00166	EA  	2003	4	29	CA030319004      	1	20030319	G	2820	525GG12D	FLAPPER VALVE   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL SYSTEM	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ANNUAL INPSECTION, THIS FUEL CHECK VALVE WAS REMOVED FROM AIRCRAFT FOR INSPECTION.  WE HAD TROUBLE DISMANTLING 	THE VALVE AS CORROSION HAD STARTED TO FUSE THE PARTS TOGETHER. ONCE DISMANTLED THE RUBBER SEAL ON THE INTERNAL FLAPPER V	ALVE WAS FOUND TO BE IN POOR CONDITION, AND WHEN TOUCHED WITH A SCREWDRIVER IT CRUMBLED APART. THE CURE DATE STAMPED ON 	THE OUTSIDE OF THE VALVE WAS DATED IN 1955. FAILURE OF THIS VALVE IN COULD CAUSE THE HAND WOBBLE PUMP IN THE AIRCRAFT TO	 BECOME INEFFECTIVE.		1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003041500039	20030415	00039	SO  	2003	4	15	CA030319006      	1	20030317	G	7810	557584	CLAMP           	PIPER       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					TAIL PIPE	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE MULTI SEGMENTED CLAMP WAS FOUND TO HAVE FLANGES BROKEN OFF THREE OF THE SEGMENTS. FORTUNATELY, THE REMAINING S	EGMENT HELD THE TAILPIPE IN PLACE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003042900168	20030429	00168	EA  	2003	4	29	CA030320001      	1	20030318	G	3010	73010033147	LINE            			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	DE-ICE SYS	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			32910								(CAN) AFTER FINDING THIS LINE CHAFED ON AN OTHER AIRCRAFT WE COMPLETED A SPECIAL INSPECTION.  WE FOUND THAT THE DE-ICE L	INE HAD BEEN CHAFING ON A HYDRAULIC LINE. THIS LINE IS LOCATED UNDER PANEL 419AT (NR 1 ENG BATMAN PANEL). THE LINE IS HI	DDEN UNDER NUMEROUS OTHER LINES AND IT IS VERY DIFFICULT TO SEE / NOTICE THE CHAFFING. WE HAD TO USE A BORESCOPE TO CONF	IRM IF THE LINES WERE TOUCHING EACH OTHER. THE LINE WILL BE REMOVED AND REPLACED.			2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2003042900169	20030429	00169	CE  	2003	4	29	CA030320002      	1	20030319	G	3242	1338932	STATOR          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  AIRCRAFT RETURNED FROM TRIP MARCH 17 / 03 WITH A SNAG IN THE LOGBOOK ( 2016B)- BRAKES ARE GRABBING WHEN APPLIED, 	NOTICEABLE AT LOW SPEEDS AND DURING GROUND TURNS. A/C WHEEL AND BRAKE ASSY'S REMOVED AND DISMANTLED FOR INSPECTION.BRAKE	 ASSY S/N 1649 HAD A BROKEN STATOR, BRAKE ASSY 2662 HAD STATORS WORN TO LIMITS.BOTH BRAKE ASSY WERE REPLACED AND A/C RET	URNED TO SERVICE. BRAKE ASSY'S WERE INSTALLED AT ACTT 521 7 / TOTAL  LANDINGS OF 5881. THE STATORS ON S/N 1649 HAD  TOTA	L LNDGS OF 649 PRIOR TO FAILURE.THE STATORS ON S/N 2662 HAD821 LANDINGS PRIOR TO REPLACEMENT.		1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2003041500040	20030415	00040	SO  	2003	4	15	CA030320003      	2	20030314	G	8530	641917	CYLINDER HEAD   			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACK IN ALUMINUM HEAD RUNNING UNDER TOP SPARKPLUG HOLE. CRACK DOES NOT EXTEND INTO COMBUSTION CHAMBER - NO LEAKAG	E FOUND DURING PRESSURE TEST. CYLINDER REMOVED AND REPLACED WITH RECONDITIONED UNIT.					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2003042900170	20030429	00170	CE  	2003	4	29	CA030321001      	1	20030319	G	2721		ACTUATOR        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RUDDER TRIM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE DAILY INSPECTION THE NUT SECURING THE RUDDER TRIM TABACTUATOR UPPER BOLT WAS NOTICED MISSING. THE NUT S	ECURING THE LOWER BOLT WAS LOOSE WITH NO COTTER PIN INSTALLED. 5.7 HOURS HAD ELAPSEDSINCE THE  PHASE 1 THRU 4 INSPECTION	.  THE UPPER AND LOWER BOLTS ARE NORMALLY REMOVED AT THE PHASE1 THRU 4, TO ENABLE ACTUATOR ROD LUBRICATION. THE INSTALLE	D ACTUATOR HAD A PREVIOUS MODIFIICATION WHICH INCORPORATED A GREASE FITTING, THE REQUIREMENT FOR DISSAEMBLY WAS NOT NECE	SSARY. THE AME WHO CARRIED OUT THE LUBRICATION TASK, HAD MADE A LOD BOOK ENTRY STATING THAT A INDEPENDANT CHECK WAS REQU	IRED FOR BOTH SUBJECT BOLTS, BUT, THE ENTRY HAD BEEN CROSSED OUT AND NOTED AS  'ENTERED IN ERROR' AFTER THE AME HAD NOTI	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003042900171	20030429	00171	EU  	2003	4	29	CA030321002      	1	20030320	G	2910	A27180210009000	TUBE            			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					HYD SYSTEM	DAMAGED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT HYDRAULIC RESERVOIR LOW LEVEL APPEARED ON GREEN SYSTEM.  AFTER INVESTIGATION A PIN HOLE WAS FOUND ON	 THE LT WING  SPOILER PRESSURE TUBE. TUBE ASSY WAS REPLACED AS M/M AND SYSTEM SERVICED AIRCRAFT WAS RETURNED TO SERVICE.	 CAUSE OF FAILURE IS UNKNOWN . LINE WAS ROUTED TO ENGINEERING FOR ANALYSIS .  SUSPECT INTERNAL EROSION				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2003042900172	20030429	00172	NM  	2003	4	29	CA030321003      	1	20030309	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					MLG	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF LANDING GEAR WOULD NOT RETREACT. A/C RETURN TO FIELD NLG HARNESS FOUND TO BE FAULTY, REPLACED, A/C 	SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003041500043	20030415	00043	EA  	2003	4	15	CA030321004      	2	20030320	G	7414		SHAFT           	SLICK       		BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  					MAGNETO	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						01021635					(CAN) RT ENGINE WOULD NOT START. DURING TROUBLESHOOTING THE MAGNETO WAS REPLACED. DURING THE INSPECTION OF THE MAGNETO, 	IT WAS NOTICED THAT THE MAGNETO SHAFT WAS CRACKED AT THE POINT  WHERE THE PHENOLIC CAM FOR THE POINTS IS INSERTED INTO T	HE SHAFT. ALSO EXCESSIVE WEAR WAS NOTICED ON THE CAM. WE DON'T SUSPECT THE CRACK IN THE SHAFT AFFECTED THE OPERATION OF 	THE MAGNETO EVEN WITH THE CRACK IN THE SHAFT.			1	L	7	2 	3O	3	O	 	3A16    	1E10				 
2003041500045	20030415	00045	CE  	2003	4	15	CA030321007      	1	20030321	G	5523	5061001735	BUSHING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR TRIM	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						5523					(CAN) DURING INVESTIGATION OF ELEVATOR TRIM TAB CLEVIS , BUSHINGS FOUND CORRODED AND SEIZED ON ONE SIDE/ NEW BUSHINGS AN	D BOLTS ON ORDER. A/C GROUNDED					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003041500046	20030415	00046	CE  	2003	4	15	CA030321008      	1	20030321	G	5523	5061001735	BUSHING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR TRIM	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING INVESTIGATION OF ELEVATOR TRIM TAB CLEVIS , BUSHINGS P/N 50-524024-1 FOUND LIGHTLY CORRODED AND LIGHT WEAR.	 NEW BUSHINGS AND BOLTS ON ORDER. A/C GROUNDED					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003041500047	20030415	00047	CE  	2003	4	15	CA030321009      	1	20030321	G	5523	5061001735	BUSHING         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR TRIM	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING INVESTIGATION OF ELEVATOR TRIM TAB CLEVIS , BUSHINGS P/N 50-524024-1  AND P/N 90-610010-5 FOUND LIGHTLY COR	RODED AND PARTIALY SEIZED . BOLT AND NUTWERE FOUND INSTALLED CORRECTLY WITH THE CORRECT TORQUE. NEW BUSHINGS AND BOLTS O	N ORDER. A/C GROUNDED				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003041500048	20030415	00048	CE  	2003	4	15	CA030321010      	1	20030319	G	5712	052323178	RIB             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FLAP TRACK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 200 HR INSPECTION THE INBOARD FLAP TRACK BRACKETS FOR THE CLOSING SKIN WHERE FOUND CRACKED. DURING REPLACEM	ENT OF THESE BRACKETS IT WAS DISCOVERED THAT THE LOWER CORNER OF THE RIBS WHERE ALSO CRACKED.  BOTH INBOARD AND OUTBOARD	 RIBS ON THE FELT INBOARD FLAP TRACK WHERE FOUND CRACKED AND THE INBOARD RIB ON THE RT INBOARD FLAP TRACK WAS FOUND CRAC	KED.  CRACKS MOST LIKLY CAUSED FROM REPEATED CYCLES AND OR HIGH FLAP EXTENSION SPEEDS. NOTEON THIS AIRCRAFT THE LOWER FL	AP SKINS WHERE ALSO CHANGED DURING THIS INSPECTION DUE TO CRACKS IN THETRAILING EDGE SKINS.		1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2005042700309	20050427	00309	NM  	2005	4	27	CA030321011      	1	20030226	G	2740		CONTROL UNIT    			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					RUDDER	MISOVERHAULED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UNSCHEDULED REMOVAL OF RUDDER PCU, OCCURRED ON FEB 25/26/2003 WAS IN RESPONSE TO A REQUEST FROM MATERIAL SERVICES 	BASED ON A FAA UNAPPROVED PARTS NOTIFICATION NR 2001-0089 DATED AUG 12,2002. SUSPECT PCU P/N 1U1150-3 S/N 737 WAS LISTED	 IN THE NOTIFICATION.  REMOVAL OF RUDDER PCU P/N 1U1150-3 S/N 0737 DOES CROSS REFERENCE TO FTN ZKMZP8 AND DOES INDICATE 	THAT IT WAS INSTALLED, BUT HISTORY INDICATES UNIT WAS REPAIRED ON MARCH 13,2000.   FTN HISTORY INDICATES THAT UNIT WAS I	NSTALLED ON AC ON MARCH 21, 2000 UNTIL PRESENT DATE.  FAA NOTICE INDICATES THAT SUSPECT UNITS WERE IMPROPERLY O/H  JANUA	RY 3-8 2001.  SHOP REPORT ESTABLISHED THAT PART HAD MFG CODES. PRESUMING THAT PART LISTED ON FAA LISTING HAS BE FORGED.	2	L	7	2 	4F	4	F		A16WE   	E2EA				 
2003042900174	20030429	00174	NM  	2003	4	29	CA030321013      	1	20030303	G	2435	03600923	BEARING         	LUCAS       		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	STARTER GEN	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA						1067					(CAN) GENERATOR CAUTION LIGHT ILLUMINATED DURING FLIGHT.UPON DISASSEMBLY FOUND COMMUTATOR END BEARING HAD FAILED.  BEARI	NG FELL APART DURING DISASSEMBLY.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003041500050	20030415	00050	NE  	2003	4	15	CA030324002      	3	20030317	G	6110		BEARING RACE    			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROP BLADE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PROP REMOVED DUE TO EXCESSIVE BLADE RADIAL PLUS END PLAY. UPON DISASSEMBLY 2 OPPOSING BLADE BEARING WERE FOUND TO 	BE CRACKED. HUB FORWARDED TO HARTZELL FOR EVALUATION OF DAMAGE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003041500051	20030415	00051	CE  	2003	4	15	CA030324003      	1	20030310	G	3250	59420011	BELLCRANK       			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470VO     	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION, FOUND STEERING BELLCRANK CRACKED IN RADIUS, SEVERAL LOCATIONS. NOTE: THE NEW BELLCRANK INSTALLED 	IS A HEAVIER UNIT.					1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P22EA	 
2003041500053	20030415	00053	SO  	2003	4	15	CA030324005      	1	20030320	G	5540		TORQUE TUBE     			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					RUDDER	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			12087								(CAN) DURING INSPECTION OF THE RUDDER TORQUE TUBE ASSY FOR CORROSION IAW PIPER SERVICE BULLETIN 1105 IT WAS DETERMINED T	HAT THE TORQUE TUBE HAD EXTERNAL CORROSION. THE TUBE WAS REMOVED TO ASESS THE AMOUNT OF CORROSION AND IF IT COULD BE REM	OVED AND TREATED. THE AMOUNT OF EXTERNAL SURFACE CORROSION WAS MINIMAL.THE INSIDE OF THE TORQUE TUBE WAS INSPECTED WITH 	A BOROSCOPE WHICH IS NOT CALLED FOR IN THE SERVICE BULLETIN AND WAS FOUND SEVERELY CORRODED. PIPER AIRCRAFT WAS NOTIFIED	 AND THE TORQUE TUBE WAS REPLACED WITH NEW.THE OWNER HAS POSSESION OF THE CORRODED TORQUE TUBE.		1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2003041500054	20030415	00054	EU  	2003	4	15	CA030324008      	1	20030313	G	2742		ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PITCH TRIM	SEIZED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLIGHT CREW HAD A AUTOPILOT DISCONNECT IN CRUISE FLIGHT THEY SHUT DOWN AUTOPILOT SYSTEM AND CONTINUED FLIGHT HOME.	 MAINTENANCE TESTED AUTOPILOT SYSTEM AFTER RESETTING C/B AND SYSTEM WORKED AS PER M/M.THEY THEN CARRIED OUT THE TEST ON 	THE HORIZONTAL STAB TRIM, WHEN THEY GOT TO THE PROCEDURE TO TESTTHE ALTERNATE TRIM THEY FOUND IT TO BE U/S. FURTHER INSP	ECTION REVEALED THAT THE SECONDARY MOTOR WAS SEIZED. A REPLACEMENT UNIT WAS INSTALLED AND TESTED SERVICEABLE.PITCH TRIMA	CTUATOR HAD 808.7 HR S AND 890 CYCLES. THIS IS THE SECOND FAILURE WE HAVE HAD ON THESE UNITS WITH LESS THAN 1000 HRS.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003041500055	20030415	00055	EA  	2003	4	15	CA030325005      	2	20030314	G	7414		RIVET           	SLICK       		ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					IMPULSE COUPLING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DUE TO PREVIOUS IMPULSE COUPLING FAILURES, WE HAVE IMPLEMENTED AN INSPECTION OF THE IMPULSE COUPLING EVERY 100 HOU	RS.  THIS IMPULSE COUPLING HAD A LOOSE RIVET ON ONE OF THE PAWLS. IF THE RIVET WAS TO SHEAR THERE WOULD BE SIGNIFICANT D	AMAGE TO THE ENGINE.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003041500056	20030415	00056	CE  	2003	4	15	CA030325006      	1	20030318	G	7810		BRACKET         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REGULAR INSPECTION REVEALED A CRACKED EXHAUST SUPPORT BRACKET, THE BRACKET WAS REPLACED AND AIRCRAFTWAS RETURNED T	O SERVICE					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003041500057	20030415	00057	SO  	2003	4	15	CA030325007      	2	20030312	G	8530		CYLINDER        								CONT  	O550  	IO550F      	17042	SO  					ENGINE	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ON INSPECTION OF 2 CYLINDERS, 1ST CYLINDER MEASUREMENT OF THE BARREL OF THE CYLINDER VARIES FROM 5.252' AT THE ENT	RANCE OF THE CYLINDER AND 5.255' AT THE BOTTOM. MAXIMUM LIMITS ARE 5.256 INCHES.  WE DISCOVERED A 'STEP' (SEE PHOTO) AT 	THE BOTTOM 0.008 DEEP. THIS 'STEP' WAS FORMED BY WHERE THE RINGS STOPPED THEIR TRAVEL. THE EXHAUST VALVE WAS WORN 0.005 	ON THESTEM.2ND CYLINDER - THE CYLINDER BARREL MEASUREMENT VARIED FROM 5.252 TO 5.259. WE SURPASS THE ALLOWABLE LIMITS ES	TABLISHED BY THE MANUFACTURER (5.256). THE EXHAUST VALVE WAS WORN 0.007 ON THE STEM A ND IT ALSO HAD A 0.008 'STEP' AT T	HE BOTTOM OF THE CYLINDER.						3	O			E3SO				 
2003041500058	20030415	00058	GL  	2003	4	15	CA030325012      	3	20030319	G	6140		CONNECTOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CSU	SHORTED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, PILOT REPORTED THAT NP RPM INDICATION WAS FLUCTUATING. NP WOULD DROP TO AROUND 1620 FOR A FEW SECON	DS & THEN IT WOULD RETURN TO IT'S CONSTANT SPEED RANGE OF AROUND 1700. FLUCTUATIONS LASTED FOR ABOUT 20 MINUTES. TORQUE 	& FUEL FLOW WERE CONSTANT & NO SURGING WAS FELT BY PILOT.  PILOT LANDED AT NEAREST AIRPORT. NP INDICATION SYS WAS INSPEC	TED, & RPM CONNECTOR CLEANED ON CSU. A/C WAS GROUND RUN AND NP INDICATIONS WERE NORMAL AND CONSTANT. A/C RETURNED TO BAS	E. RETURN FLT, & FURTHER INVESTIGATIONS & GROUNDS RUNS AT BASE, NP SYSTEM FUNCTIONED NORMALLY.  AFTER 22 HOURS OF FLIGHT	 OPERATION, PROBLEM HAS NOT RETURNED. BELIEVE THE PROBLEM WAS RPM CONNECTOR ON CSU, SINCE OTHER PC-12 ENGINE CONNECTORS 	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003041500059	20030415	00059	CE  	2003	4	15	CA030326001      	1	20030325	G	5523	906100105	BUSHING         	RAYTHN      		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					CONTROL ROD	SEIZED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) BUSHING INSERTED INTO ELEVATOR TRIM TAB HORNS, BOTH LT AND RT FOUND TO BE INCORRECTLY INSTALLED. BUSHING WAS NOT I	NSERTED FAR ENOUGH INTO THE HORN. THIS CAUSED THE CLEVIS FORK END TO CLAMP THE OUTER BUSHING AND HORN TAB INSTEAD OF THE	 INNER BUSHING. THE INNER BUSHING HAD TO BE DRIVEN OUT WITH A HAMMER AND PUNCH. ONCE REMOVED AND MEASURED, THE INNER BUS	HING DIMENSION WAS FOUND TO BE THE SAME SIZE AS THE OUTER BUSHING. THIS LEAVES A ZERO CLEARANCE FIT WHICH DOESNOT ALLOW 	A FREE BEARING MOVEMENT.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003041500060	20030415	00060	CE  	2003	4	15	CA030326002      	1	20030321	G	2731	50524161606	ACTUATOR        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR TRIM	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING ELEVATOR TRIM TAB FREE PLAY CHECK THE LT ELEVATOR TRIM TAB ACTUATOR WAS FOUND TO HAVE EXCESSIVE PLAY. MEASU	RED .031					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003041500061	20030415	00061	CE  	2003	4	15	CA030326003      	1	20030325	G	5523	905240241	BUSHING         			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR TRIM	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT & RT ELEVATOR TRIM HORN INNER BUSHINGS HAD TO BE DRIVEN OUT OF INNER BUSHINGS WITH HAMMER AND PUNCH. ONCE REMOV	ED & MEASURED, INNER BUSHING DIMENSION WAS FOUND TO BE THE SAME AS OUTER BUSHING INNER DIAMETER. THERE WAS NO CORROSION 	BETWEEN THE 2 BUSHINGS. THIS LEFT A 0 CLEARANCE FIT NOT ALLOWING FREE BEARING MOVEMENT. NEW OUTER & INNER BUSHINGS WERE 	RECEIVED. NEW OUTER BUSHINGS HAVE A MEASURED INNER DIAMETER .3735.  REMOVED OUTER BUSHING. ID WAS MEASURED AT .3750.   B	USHINGS HAVE BEEN INSTALLED IN ELEVATOR TRIM HORN & INNER BUSHING NOW FREELY ROTATE WITHIN OUTER BUSHING. LT BUSHING LOC	ATED IN END OF THE ELEVATOR TRIM TAB ACTUATOR ALSO REQUIRED FORCEFUL REMOVAL DUE TO CORROSION. RT SLID OUT FREELY.	1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2003041500065	20030415	00065	CE  	2003	4	15	CA030327001      	1	20030326	G	7160	9091010017	TUBE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ANTI ICE SYS	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ENGINE INTAKE ANTI-ICE TUBES REPLACED AS PER BEECH SB 71-3142. NEW TUBES FOUND CRACKED AT SECOND INSPECTION AFTER 	SB COMPLIANCE.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003041500075	20030415	00075	EA  	2003	4	15	CA030328001      	2	20030311	G	8520	LW17071	CRANKSHAFT      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION FOR AD 98-02-08 INTERNAL CORROSION. LIGHT SURFACE CORROSION WAS FOUND, WHEN LOG BOOKS CHECKED IT W	AS FOUND THAT LYCOMING HAD SIGNED OFF SB530 WHICH A COATING THAT TERMINATES INSP. LYCOMING HAS BEEN CONTACTED AND CORREC	TING THE PROBLEM.  THIS PROBLEM WAS FOUND DUE AN ERROR IN OUR TRACKING SYSTEM WHICH SHOWED AD 98-02-08 STILL AS A 5 YEAR	 INSP.  NOTE THE CORROSION FOUND DID NOT REQUIRE THE CRANKSHAFT TO BE REPLACED			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003041500086	20030415	00086	CE  	2003	4	15	CA030331003      	1	20030328	G	3245	0923150	TUBE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					WHEEL	TORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON WALK AROUND PILOT NOTICE RT MAIN TIRE FLAT. WHEEL ASSEMBLY REMOVED AND TUBE INSPECTED, TWO TEAR APPROX 1/4 INCH	 AND APPROX 7 INCHES APART FOUND ON OUTBOARD CENTER SEAM.  MICHELIN WAS CONTACTED AND THE FOUR PREVIOUS TUBES WERE SENT 	TO MICHELIN FOR MORE INSPECTION.  TIRE WAS INSPECTED FOR FOREIGN OBJECT AND NO PROBLEM FOUND.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003041500087	20030415	00087	SW  	2003	4	15	CA030331005      	1	20030331	G	2810	512681	TANK            			AIRTRC	AT802 	AT802       	0390305	SW  										FUEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION A CRACK WAS DISCOVERED ON THE FUEL HEADER TANK END PLATE. THE HEADER TANK WAS REMOVED AND REPLAC	ED WITH A NEW PART. AIRCRAFT WAS RETURNED TO SERVICE.					1	L	7	1 	3T			NC	A19SW   					 
2003041500088	20030415	00088	NE  	2003	4	15	CA030331006      	2	20030308	G	7321		LINE            			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					P3 SENSING	FROZEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN) A/C WAS COVERED IN SNOW AND ICE & REQUIRED EXTENSIVE PREHEATING.  ENGS WERE STARTED & NR 1 ENG TOOK LONGER TO LIGH	T OFF.  ONCE ALL WAS IN GREEN, A/C LIFTED OFF.  APPROX. 10 MINS INTO 1ST CYCLE,  CREW NOTICED ENGS WERE UNMATCHED. ATTEM	PTED TO MATCH THEM USING BEEPER TRIM FOR EACH ENG, UNSUCCESSFUL. ATTEMPT TO THROTTLE BACK FAILED BECAUSE THROTTLE LEVERS	 FROZEN. LOGS RELEASED & NR 1 ENG SURGED, OVERSPEED PROTECTION SHUT ENG DOWN. WITH ENG SHUTDOWN,  ABLE TO GET VERTICAL B	OUNCE UNDER CONTROL.  NR 1 ENG WAS SECURED & A/C RETURNED & LANDED.  INSPECTION OF ENG AND ITS CONTROL LINKAGES REVEALED	 ICE IN ENG P3 SENSE LINE & AN N2 BEEP MOTOR INOP. BEEP MOTOR REPLACED. ENG FCU WAS REPLACED AND ENG GROUND RUN.	2	G	7	2 	4U	4	U	 	H4EA    	E15EA				 
2003041500089	20030415	00089	SO  	2003	4	15	CA030331007      	2	20030320	G	8530		EXHAUST VALVE   			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	ENGINE	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORT OF INTERMITTENT ENGINE ROUGH RUNNING. NR 4 EXHAUST VALVE FOUND STICKY. GUIDE AND STEM CLEANED. GROUND	 RUN SATISFACTORY.					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2003041500090	20030415	00090	CE  	2003	4	15	CA030331008      	1	20030309	G	2434	DOFF10300B	ALTERNATOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			CA											(CAN) ALTERNATOR FAILURE IN FLIGHT,ELECTRICAL FAILURE						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003041500091	20030415	00091		2003	4	15	CA030331009      	4	20030331	G	2562		G SWITCH        																	ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						408797					(CAN) DURING RECERTIFICATION TESTING THE G SWITCH WAS FOUND FAILED, UNIT RETURNED TO MANUFACTURER FOR REPAIR																			 
2003041500092	20030415	00092		2003	4	15	CA030331010      	4	20030331	G	2562		G SWITCH        	POINTER     																ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						408816					(CAN) DURING ANNUAL RECERTIFICATION G SWITCH FAILED TO OPERATE - UNIT RETURNED TO MANUFACTURER FOR REPAIR.																			 
2003041500093	20030415	00093		2003	4	15	CA030331011      	4	20030331	G	2562		G SWITCH        	POINTER     																ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						408870					(CAN) DURING ANNUAL RECERTIFICATION G SWITCH FAILED TOP OPERATE - UNIT RETURNED TO MANUFACTURER FOR REPAIR																			 
2003041500094	20030415	00094	SO  	2003	4	15	CA030401001      	1	20030331	G	3210	1742002	TUBE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THREE CRACKS WERE FOUND ON THE RT MLG OUTBOARD TUBE ASSEMBLY OF THE DRAG LINK FITTING SUPPORT.  THE CRACKS ARE LOC	ATED AROUND THE LOWER MOUNTING BOLT HOLE OF THE TUBE ASSEMBLY.  AFTER REMOVAL OF THE DRAG LINK SUPPORT ASSEMBLY, THE FOR	WARD SUPPORT FITTING WAS FOUND WITH TWO CRACKS ALONG THE EACH SIDE OF THE CASTING SEAM TO THEMOUNTING BOLT HOLE.				1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2003041500095	20030415	00095		2003	4	15	CA030401003      	4	20030331	G	3422	6226163002	GYRO            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NR 2 HSI COMPASS CARD FAILES TO DISPLAY TRUE COMPASS HEADING WITH NO FLAG IN VIEW. WHEN FAILED THE NR 2 HSI COMPAS	S CARD CANNOT BE SLEWED IN EITHER SLAVE OR FREE MODES, AND IS FROZEN ON ONE BEARING. THE PAIRED CROSS SIDE RMI REMAINES 	SERVICEABLE AND CAN BE SLEWED IN BOTH FREE AND SLAVE MODE. NO WARNING FLAGS OCCUR ON ANY SYSTEM.  NR 2 HEADING SYSTEM IS	 COUPLED TO P/N 331A-3G HSI. APPARENT FAILURE IS A LACK OF 26 VAC SUPPLY FROM PIN 31 OF THE DGS-65 TO NR 2 HSI. REPLACEM	ENT OF DGS-65 GYRO CLEARS THE FAULT.THE SAFETY CONCERN IS THE LACK OF A HDG WARNING FLAG ON NR 2 HSI WHEN FAULT OCCURES.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003041500096	20030415	00096	CE  	2003	4	15	CA030401004      	1	20030401	G	5511	043200115	SPAR            			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19406								(CAN) ON INSPECTION 0432001-15 SPAR REINFORCEMENT FOUND CRACKED AFTER DISASSEMBLEY LT & RT SPARS ALSO FOUND CRACKED.  RE	ASSEMBLED WITH NEW PARTS INCLUDING NEW STYLE BRACKET. AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3O	3	O		3A19    	E252				 
2003041500098	20030415	00098		2003	4	15	CA030401008      	4	20030401	G	2562		G SWITCH        	POINTER     																ELT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						408078					(CAN) DURING ANNUAL RECERTIFICATION G SWITCH FAILED TO OPERATE - UNIT RETURNED TO MANUFACTURER FOR REPAIR																			 
2003041500099	20030415	00099		2003	4	15	CA030401009      	4	20030401	G	2562		G SWITCH        	POINTER     																ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						408884					(CAN) DURING ANNUAL RECERTIFICATION G SWITCH FAILED TO OPERATE - UNIT RETURNED TO MANUFACTURER FOR REPAIR																			 
2003041500100	20030415	00100		2003	4	15	CA030401010      	4	20030401	G	2562		G SWITCH        	POINTER     																ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						408387					(CAN) DURING ANNUAL RECERTIFICATION G SWITCH FAILED TO OPERATE - UNIT RETURNED TO MANUFACTURER FOR REPAIR																			 
2003041500101	20030415	00101		2003	4	15	CA030401011      	4	20030401	G	2562		G SWITCH        	POINTER     																ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						409263					(CAN) DURING ANNUAL RECERTIFICATION G SWITCH FAILED TO OPERATE - UNIT RETURNED TO MANUFACTURER FOR REPAIR																			 
2003061100044	20030611	00044	EA  	2003	6	11	CA030403004      	1	20030312	G	5753	601R145011	SKIN            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					TE FLAP	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10121								(CAN) CREW REPORTED (LEFT OUTBOARD FLAP UPPER PANEL HAS 6 INCH DELAMINATION). OUTBOARD FLAP UPPER SKIN FOUND TO HAVE 2 C	RACKS NEAR INBOARD END BEGINNING AT LEADING EDGE OF SKIN PANEL.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003041500104	20030415	00104	SO  	2003	4	15	CA030404002      	1	20030404	G	1430	NAS464P427	BOLT            			PIPER 	PA44  	PA44180     	7104402	SO  										NLG DRAG LINK	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CENTER NOSE GEAR DRAG LINK BOLT FOUND SHEARED BUT STILL IN PLACE DURING 100 HR. INSPECTION.						1	L	7	2 	3O			 	A19S0   					 
2003042900177	20030429	00177	SW  	2003	4	29	CA030404007      	1	20030325	G	5320	7033012	STRAP           			AIRTRC	AT400 	AT401       	0390204	SW  	ORENDA	OE600A	OE600A      	 	NE  					FUSELAGE	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UPON PERFORMING THE SCHEDULED 200 HOUR INSTALLATION INSPECTION, THE HOSE STRAP WAS FOUND TO BE BROKEN NEAR THE MOU	NTING BOLT HOLE. THE BROKEN HOSE STRAP WAS REPLACED. INVESTIGATION INTO THE CAUSE, AND FORMULATION OF CORRECTIVE ACTION 	CONTINUES. MORE DETAIL TO FOLLOW.				1	L	7	1 	3R	3	V	 	A17SW   	E0006A				 
2003050600254	20030506	00254	EA  	2003	5	6	CA030406001      	1	20030402	G	2120	92E204	CHECK VALVE     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					BULKHEAD	DAMAGED         	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CR	CRUISE         	1			CA			16373								(CAN) FLT CREW REPORTED LOSS OF PRESSURIZATION AT FL330, CABIN RATE INCREASED AT 2000/3000 FT PER MIN.EMERGENCY DESCENT 	PERFORMED PER QRH.AIRCRAFT LANDED WITHOUT FUTHER INCIDENT.MTCE FOUND A DUCT BLOWN OFF THE LEFT WATER SEPARATOR AND THE L	T BULKHEAD CHECK VALVE DAMAGED. THE DUCT WAS REINSTALLED ON THE WATER SEPARATOR, THE LH BULKHEAD CHECK VALVE WAS REPLACE	D AND AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003050700008	20030507	00008	CE  	2003	5	7	CA030407001      	1	20030402	G	3244	53716	TIRE            	MCAULY      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NLG	BLISTERED       	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING GROUND HANDLING IT WAS NOTICED THAT A CHUNK OF RUBBER FROM THE SIDE WALL OF THE NOSE WHEEL TIRE WAS MISSING	. IT SEAMED THAT THE RUBBER HAD BISTERED AND HAD BURST. NOSE WHEEL TIRE WAS REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003050700010	20030507	00010	EU  	2003	5	7	CA030407003      	1	20030227	G	2435		STARTER GEN     			BAG   	JETSTM	JETSTM3107  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	ENGINE	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER START THE GENERATOR WOULD NOT COME ON LINE. TESTING REVEALED A FAILED TERMINAL END ON THE FIELD WIRE INSIDE 	THE GENERATOR.					2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2003042900182	20030429	00182	CE  	2003	4	29	CA030407008      	1	20030403	G	3260	MS250413	SOCKET          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG INDICATOR	INTERMITTENT    	W				L				ABORTED APPROACH        				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA			11701								(CAN) FLIGHT CREW COULD NOT GET A LT GREEN GEAR LOCKED INDICATION ON APPROACH.   UPON APPROACH LT MAIN GEAR GREEN INDICA	TOR ILLUMINATED.  ALL GEAR RIGGING INSPECTED AND TESTED IAW M/M WITH NO DEFECTS NOTED.   FOUND THE LT MAIN INDICATOR LIG	HT SOCKET TO HAVE ITERMITTENT CONTACT ON PIN NR 2.   REMAINDER OF WIRE INSPECTED AND TESTED FROM INDICATOR TO DOWNLOCK S	WITCH WITH NO OTHER DEFECTS NOTED.  AIRCRAFT RELEASED PENDING SATISFACTORY TEST FLIGHT.  CREW REPORTS NO FURTHER PROBLEM	S.		1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003050700015	20030507	00015	CE  	2003	5	7	CA030408001      	1	20030403	G	3234	66710	CONTROL VALVE   			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  					LANDING GEAR	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) CESSNA 500 ON APPROACH, GEAR DID NOT EXTEND SO MANUAL GEAR EXTENSTION PROCEDURE CARRIED OUT. AIRCRAFT LANDED NORMA	LY. INSPECTED AIRCRAFT UNABLE TO DUPLICATE SNAG. SO CHANGED LANDING GEAR CONTROL VALVE AS A PRECAUTION.					1	L	7	2 	4F	4	F	 	A22CE   	E25EA				 
2003042900183	20030429	00183	CE  	2003	4	29	CA030408002      	1	20030403	G	2720	115524067	SPRING          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER RETURN	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14260								(CAN) PILOT REPORTED NOSE STEERING SEEMED SLOPPY ON TAXI AND RUDDER STIFF AFTER 70 KIAS ON TAKEOFF.  REMOVED TAILCONE AN	D FOUND BOTH RUDDER RETURN SPRINGS BROKEN WITH THE LEFT HAND SPRING BINDING ON THE ELEVATOR SUPPORT ARM.  REPLACED SPRIN	GS AND OPERATION NORMAL.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003042900184	20030429	00184	CE  	2003	4	29	CA030408004      	1	20030408	G	3020	909100991317	TUBE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ANTI-ICE SYS	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING RT ENGINE CHANGE, THE LOWER COWL WAS REMOVED AND BOTH ENGINE INTAKE ANTI-ICE FLEX TUBES WERE FOUND CRACKED.	  BOTH TUBES (P/N 90-910099-13 AND 90-910099-17) WERE CRACKED GREATER THAN 50 PERCENT OF THERE CIRCUMFERENCE. THERE WAS 	NO EVIDENCE OF ANY EXHAUST LEAK INSIDE THE COWLING. (TUBE P/N 90-910099-13) TSN110-2 HRS. P/N 90-910099-17 WAS 307.1 TSN	. BOTH TUBES HAVE BEEN REPLACED.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003050700024	20030507	00024	CE  	2003	5	7	CA030408005      	1	20030312	G	5712	05230301	RIB             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16746								(CAN) ROUTINE INSPECTION FOUND CRACKS IN LEFT NOSE RIB AT STATION 100.00 OF WING. THE RIB WAS CRACKED THROUGH LIGHTENING	 HOLE TO UPPER BEND RELIEF. RIGHT SIDE AT 100.00 WAS ALSO SHOWING CRACKS FROM RIVET HOLES AND FROM THE BEND RELIEF TOWAR	D THE LIGHTENING HOLE.BOTH RIBS WERE REPLACED. NO OTHER RIBS AFFECT ED. PLANE BELONGS TO A FLYING SCHOOL WHERE OUT OF TH	E 7 OPERATED 4 SHOWED SIGNS OF CRACKS ON BOTH OREITHER SIDE.TIME ON AIRCRAFT RANGE FROM 9500 TO 16746.1 HRS.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003042900185	20030429	00185	CE  	2003	4	29	CA030408006      	1	20030408	G	5520	115610010125	SPLINE ADAPTER  			BEECH 	100   	B100        	1152919	CE  										ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE, ELEVATORS WERE REMOVED FOR SB 2145 ON ELEVATOR TORQUE TUBE. AFTER REVIEWING SERVICE DI	FFICULTY ADVISORY AV-2003-01 FOR BEECH A100, WE FOUND SAME CRACKES ON THE RIGHT ELEVATOR ON OUR B100. AFTER DISASSEMBLE 	AT LOCAL SHEET METAL SHOP WE WERE INFORMED THAT THERE WERE 17 CRACKS AND ONE CRACK WAS COMPLETLY THROUGH THE SPLINE.THE 	TRANSPORT OFFICE WAS NOTIFIED AND THEY REQUESTED PICTURES.			1	L	7	2 	4T			 	A14CE   					 
2003050700035	20030507	00035	CE  	2003	5	7	CA030409004      	1	20030407	G	5343	24130023	FITTING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	FUSELAGE	CRACKED         	I				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED INSPECTION OF THE AIRCRAFT AND LANDING GEAR IT WAS NOTICED THAT THE FITTING WHICH ACCEPTS THE NOS	E GEAR ACTUATOR ASSEMBLY WAS CRACKED. THE TWO CRACKS WERE LOCATED JUST OUTBOARD OF THEACTUATOR MOUNTING BOSSES AND EXTEN	D BACK FROM THE FORWARD EDGE TO THE FIRST INBOARD FASTENER HOLE.THE AFFECTED PART WAS REMOVED AND REPLACED WITH A NEW PA	RT.			1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003042900186	20030429	00186	SO  	2003	4	29	CA030409005      	2	20030131	G	8520	643989	CRANKCASE       			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520AF   	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT INSPECTION A SMALL AMOUNT OF ALUMINIUM WAS FOUND IN THE OIL FILTER. CYLINDERS WERE REMOVED FROM THE ENGINE TO I	NVESTIGATE THE SOURCE OF THE FILTER CONTAMINATION. IT WAS FOUND THAT THE NR 2 MAIN BEARING HAD SHIFTED FORWARD AND WAS L	OOSE CAUSING WEAR IN THE CRANKCASE NR 2 MAIN BEARING SUPPORT.				1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2003042900187	20030429	00187	SO  	2003	4	29	CA030409006      	1	20030407	G	3220	AN721	BOLT            			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	TAILWHEEL ASSY	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GROUND CREW WAS MOVING THE AIRCRAFT ON RAMP AND RAN TAILWHEEL OF  AIRCRAFT OVER SMALL ICE RIDGE IN ORDER TO GAIN A	CCESS TO POSITION FOR PARKING. JOLT FROM THE WHEEL JUMPING ICE RIDGE RESULTED IN COLLAPSE OF THE TAILWHEEL ASSEMBLY FROM	 THE LEAF SPRING ASSEMBLY.  INSPECTION REVEALED THAT ATTACHING BOLT HAD SHEARED AND ALLOWED THIS CONDITION TO OCCUR. FUR	THER INVESTIGATION BY MAINTENANCE REVEALED THAT THE BOLT HAD LIKELY BEEN PARTIALLY SHEARED FOR SOME TIME AND GONE UNDETE	CTED HOWEVER, THE BRIEF JOLT FROM THE GROUND HANDLING INCIDENT WAS ENOUGH TO COMPLETELY SEVERE THE BOLT ITSELF. THE ROOT	 CONDITION IS DUE TO REPEATED LANDINGS IN THE FLIGHT TRAINING ENVIRONMENT WITH THIS AIRCRAFT. BOLT WAS REPLACED.	1	H	7	1 	3O	3	O	 	1A2     	E274	5	N	P88614	 
2003042900188	20030429	00188	EU  	2003	4	29	CA030409007      	1	20030407	G	2133	90231570381	OUTFLOW VALVE   			AIRBUS	320   	A320212     	3930322	EU  	CFMINT	CFM56 	CFM565A3    	 	NE  					CABIN PRESSURE	INOPERATIVE     	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ON POSITIONING FLIGHT, IN CRUISE AT 37 000, ECAM WARNING CABIN SAFETY VALVE OPEN,  FOLLOWED BY CABIN PRESSURE EXCE	SSIVE, CABIN ALTITUDE . FLIGHT CREW PERFORMED EMERGENCY DECENT AND DIVERTED. ON LANDING, OUTFLOW VALVE HAD TO BE OPENED 	MANUALLY TO DEPRESSURIZE AIRCRAFT. OUTFLOW VALVE REPLACED AND SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003050700036	20030507	00036	SO  	2003	5	7	CA030409008      	1	20030403	G	2910	1159P20518	TUBE            			GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					HYD SYSTEM	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) HUDRAULIC TUBES WERE FOUND TO BE CHAFFED BEYOND LIMITS DURING THE PYLON INTERIOR SCHEDULE INSPECTION. BOTH LEFT & 	RIGHT TUBES SHOWED DAMAGE IN NEARLY IDENTICAL SPOTS, CAUSED BYCHAFFING ON A ELECTRICALWIRE THAT HAD BEEN CLAMPPED NOT PR	OPERLY. THE WIRE SHOWED NO SIGNS OF DAMAGE. BOTH TUBES WERE REPLACED.				2	L	7	2 	4F	4	F	 	A12EA   	E2EU				 
2003050700037	20030507	00037	CE  	2003	5	7	CA030409011      	1	20030325	G	3010		PICCOLO TUBE    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) A RIGHT ENGINE INLET FOUND CRACKED WHERE INLET INTO PICOLO TUBE FOR LIP HEAT IS MOUNTED. CRACK RADIATES UPWARD ABO	UT 4 INCHES. NEW INLET INSTALLED. TEST					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003042900191	20030429	00191	SO  	2003	4	29	CA030409014      	1	20030408	G	2710	6210200	BELLCRANK       			PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND BRACKET CRACKED FOR A LENGTH OF ABOUT 2 CENTIMETERS JUST BELOW FORWARD BOLT HOLE.  DEFECT CAN ONLY BE SEEN W	ITH INSPECTION MIRROR FROM OUTBOARD INSPECTION HOLE.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003042900192	20030429	00192	SO  	2003	4	29	CA030409015      	1	20030403	G	3230		DOWNLOCK        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	MLG	STIFF           	W				O				OTHER                   				L	R		NO TEST                   	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) ONCE THE PILOT SELECTED LANDING GEAR UP, THE GEAR DID NOT RETRACT. WE DISCOVERED THAT THE DOWN LOCK MECHANISM WAS 	HARD TO MANEUVER, AFTER LUBRICATION AND CLEANING WE CARRIED OUT GEAR RETRACTION. SYSTEM SERVICEABLE.					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2003042900197	20030429	00197	CE  	2003	4	29	CA030410002      	1	20030409	G	2731	5052442034	HINGE           			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING UNSCHEDULED INSPECTION OF THE TAIL. THE ENGINEER CHECKED FOR PLAY IN THE ELEVATOR HORN BEARINGS P/N MS27645	-5.  UPON CLOSER EXAMINATION THE ENGINEER NOTICED A CRACK IN THE BEARING HOUSING AREA OF P/N 50-524420-4. AFTER REMOVAL 	OF THE BEARING FROM THE LT BEARING HOUSING P/N 50-524420-3 CORROSION WAS FOUND.  NEW PARTS WERE ORDERED TO CORRECT DEFEC	T.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003042900198	20030429	00198	CE  	2003	4	29	CA030410003      	1	20030409	G	3020	9091009913	TUBE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ANTI ICE SYS	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE COWLINGS WERE REMOVED FROM THE AIRCRAFT FOR SCHEDULED OIL CHANGE. VISUAL INSPECTION CARRIED OUT ON COWLING PRI	OR TO REINSTALLATION IDENTIFIED ONE CRACKED COWL ANTI-ICE BLEED AIR TUBE. NEW PARTS WERE INSTALLED. . A FLEET CAMPAIGN I	NSPECTION IS ONGOING, WITH INSPECTION DUE THE NEXT TIME THE COWL IS REMOVED FOR MAINTENANCE. AVERAGE PART LIFE IS LESS T	HAN 200 HRS. AFTER INSTALLATION.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003050700064	20030507	00064	CE  	2003	5	7	CA030410005      	1	20030327	G	5541	05331531	RIB             			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					RUDDER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			13866								(CAN) REPOSITIONED RUBBER AND REPLACED CRACKED RIB.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003050700066	20030507	00066	EU  	2003	5	7	CA030410007      	1	20030410	G	3260	973303311	PROXIMITY SWITCH			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF THE CREW HAD AN INTRANSITT LIGHT AND A DOWN LOCK LIGHT ON NOSE GEAR. GEAR WAS FUNCTIONING NORMALLY.	 FOUND THE NOSE GEAR DOWN LOCK PROX. SWITCH STUCK IN THE LOCK INDICATION POSITION. REPLACED SWITCH, RIGGED, FUNCTION TES	TED GEAR THROUGH SEVERAL SWINGS AND NO FURTHER DEFECTS NOTED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003050700068	20030507	00068	EA  	2003	5	7	CA030411003      	2	20030410	G	7421	URHB37E	SPARK PLUG      			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	BROKEN          	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											(CAN) SPARK PLUG SEPARATED IN HALF AND BURNT HOLE IN TOP COWLING.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P920	 
2003050700090	20030507	00090	CE  	2003	5	7	CA030414004      	1	20030411	G	5330	07133343	SKIN            			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUSELAGE SKIN PANEL UNDER REFUELING STEP NOTED HAVING A BULGE AREA UNDER TOP REAR MOUNTING BOLT AREA.  SKIN MOVEME	NT ALSO WAS EVIDENT WHEN WEIGHT WAS APPLIED TO THE STEP. DETAIL INSPECTION OF AREA FOUND BOTH THE FUSELAGE SKIN AND BULK	HEAD WHERE THE STEP IS MOUNTED HAS MULTIPLE CRACKS.				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2003050700091	20030507	00091	CE  	2003	5	7	CA030414005      	1	20030411	G	5330		SKIN            			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUSELAGE SKIN PANEL UNDER REFUELING STEPS NOTED HAVING A BULGE AREA AROUND MOUNTING BOLT.  SKIN MOVEMENT ALSO WAS 	EVIDENT WHEN WEIGHT WAS APPLIED TO THE STEP.  DETAIL INSPECTION OF AREA FOUND BOTH THE FUSELAGE SKIN AND BULKHEAD WHERE 	THE STEPS ARE MOUNTED HAS MULTIPLE CRACKS.				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2003053000100	20030530	00100	CE  	2003	5	30	CA030414006      	1	20030411	G	5312	07137879	BULKHEAD        			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUSELAGE SKIN PANEL UNDER REFUELING STEPS NOTED HAVING A BULGE AREA AROUND MOUNTING BOLT.  SKIN MOVEMENT ALSO WAS 	EVIDENT WHEN WEIGHT WAS APPLIED TO THE STEP.  DETAIL INSPECTION OF AREA FOUND BOTH THE FUSELAGE SKIN AND BULKHEAD WHERE 	THE STEP IS MOUNTED HAS MULTIPLE CRACKS.				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2003053000101	20030530	00101	EA  	2003	5	30	CA030415002      	2	20030409	G	7321	2525098	HOUSING         	HONEYWELL   							PWA   	PT6   	PT6*        	52043	EA  					FUEL CONTROL	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						A7264					(CAN) FACE OF BODY MACHINED DOWN.   WALL THICKNESS AS SHOWN IN PICTURE SHOULD BE BETWEEN .0962 FT TO .0862 FT.   FOUND A	T .0625 FT.   BODY NOT IAW OEM DRAWING REQUIREMENTS.   REWORK NOT APPROVED BY OEM.   MAIN BODY  P/N2525098, S/N 106.										3	T			E2NE				 
2003050700107	20030507	00107	NE  	2003	5	7	CA030416005      	1	20030416	G	6520	SB8208102	SEAL            			SKRSKY	S76   	S76         	8143010	NE  										T/R GEARBOX	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) NEW SEALS HAVE BEEN FOUND TO BE LEAKING FROM NEW. THESE ARE A NEW P/N RELEASED BY SIKORSKY AND SEVERAL CUSTOMER CO	MPLAINTS HAVE BEEN RECEIVED. NEW SEALS FOUND IN THE MAIN GEARBOX HAVE ALSO LEAKED UPON TEST OR SUBSEQUENT FIELD USE.					1	G	7	2 	3U			 	H1NE    					 
2003050700108	20030507	00108	CE  	2003	5	7	CA030417001      	1	20030407	G	3297		CIRCUIT BREAKER 			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON SELECTING THE LANDING GEAR UP THE LANDING GEAR MOTOR WAS UNDER EXCESSIVE STRAIN DUE TO THE LANDING GEAR GUIDE	 BEING VERY DIRTY AND THE CIRCUIT BREAKER POPPED. THE PILOT SELECTED FREE FALL ASSIST TO LOCK THE GRAR DOWN. CIRCUIT BRE	AKER WAS REPLACED, IT HAD 494.6 HOURS IN SERVICE.				1	L	7	2 	3R	3	R	 	A765    	5E1				 
2003050700119	20030507	00119	NE  	2003	5	7	CA030417009      	2	20030416	G	8520		BEARING         			DOUG  	A26   	A26BSHIELDS 	3020504	WP  	PWA   	R2800 	R280079     	52026	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING A LOCAL TRAINING FLIGHT THE RT OIL TEMP WAS NOTICED TO BE ON THE RISE.  THE OIL COOLER WAS OPENED HOWEVER T	HE TEMP CONTINUED TO RISE.  A SHORT TIME LATER THE OIL PRESSURE BEGAN TO DROP ACCOMPANIED BY BLACK SMOKE FROM EXHAUST.  	ENGINE WAS SHUT DOWN AND THE AIRCRAFT MADE A SINGLE ENGINE LANDING AT RED DEER WITHOUT INCIDENT.  THE ENGINE APPEARS TO 	HAVE A MAIN BEARING FAILURE.			2	M	7	2 	4R	4	R	 	L34     	5E8				 
2003053000107	20030530	00107	NM  	2003	5	30	CA030417011      	1	20030415	G	2710		PCU             			BOEING	737   	7372T5      	1384474	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AILERON	INOPERATIVE     	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) AFTER PUSHBACK AND START, FLAP 2 SELECTED AND HYDRAULIC SYSTEM A LOW PRESSURE ILLUMINATED AND HYD QTY GUAGE DECREA	SED TO ZERO. MAINTENANCE FOUND THE A SYSTEM AILERON POWER CONTROL UNIT (PCU) FILTER BOWL HAD FRACTURED RESULTING IN LOSS	 OF HYD PRESS/FLUID. FURTHER INFO INCLUDING THE UNIT PART NUMBER AND S/N WILL FOLLOW AFTER SHOP REPORT IS RECEIVED.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2003050700136	20030507	00136	EU  	2003	5	7	CA030421001      	1	20030416	G	3230	AE7060322	HOSE            			AIRBUS	310   	A310304     	3930339	EU  	GE    	CF6   	CF680C2A5   	 	NE  					HYD SYSTEM	RUPTURED        	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA											(CAN) ON FINAL APPROACH WHEN GEAR SELECTEDDOWNGREEN HYDRAULIC SYSTEM QUANTITY DROPPED TO NEARLY ZERO .DURING INVESTIGATI	ON FOUND THE HYDRAULIC DOWN LINE RUPTURED AT THE UPPER RIGHT HAND MAIN LANDING GEAR SWIVEL AREA. LINE WAS REPLACED AND S	YSTEM TESTED SERVICEABLE. A CAMPAIGN HAS BEEN INITIATED TO REPLACE ALL FLEX HYDRAULIC LINES AT THE UPPER MAIN LANDING GE	AR TRUNNION AREA AT NEXT A CHECK VISIT ON ALL A-310 AIRCRAFT. ALSO NEW LINES WILL BE A TIME CONTROL ITEM.			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2003050700137	20030507	00137	EA  	2003	5	7	CA030421002      	2	20030411	G	7322		SCREW           	MARVELSCHEBX		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CARBURETOR	MISSING         	W				O				OTHER                   				Y			ENGINE STOPPAGE           			LD	LANDING        	1			CA						75104001					(CAN) PILOT FIRST NOTICED PROBLEM WHEN TURNED OFF RUNWAY AFTER LANDING. REPORTED ENGINE WILL NOT CONTINUE TO RUN BELOW 1	200 RPM. MAINTENANCE FOUND IDLE MIXTURE SCREW MISSING FROM CARBURETOR. OPERATION OK WHEN PART REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003050700138	20030507	00138	CE  	2003	5	7	CA030421003      	1	20030421	G	2750	C145350	MOTOR           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FLAP SYSTEM	SEPARATED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH WHEN FLAPS WERE SELECTED FROM FLAPS 10 TO FLAPS 20 THE PILOT HEARS A LOUD BANG AND FLAPS RAPIDLY RETRA	CTED BACK TO FLAPS 10. PILOT LANDED THE AIRCRAFT IN THIS CONFIGURATION. MAINTENANCE FOUND THE FLAP TRANSMISSION TO HAVE 	BROKEN FREE OF THE STRUCTURE. AN INSPECTION WAS CARRIED OUT ON THE FLAPS & FLAP TRACKS FOR ANY ITEM THAT MAY HAVE CAUSED	 THE FLAPS TO JAM. NO FAULTS WERE FOUND.THE AIRCRAFT IS CURRENTLY OUT OF SERVICE WHILE REPAIRS ARE CARRIED OUT TO THE DA	MAGED FLAP TRANSMISSION SURPORT ASSEMBLY. MAINTENANCE HAS BEEN UNABLE TO DETERMINE WHAT CAUSED THIS FAULT. DUE TO PREVIO	US PROBLEMS WITH THE FLAP SYSTEM ON THE C208 CARAVAN MAINTENANCE SUSPECTS A FAILURE OF THE FLAP MOTOR ASSEMBLY.	1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003050700142	20030507	00142	SO  	2003	5	7	CA030421007      	1	20030420	G	2731	4536700	BEVEL GEAR      			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					ELEVATOR TRIM	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			18055								(CAN) PILOT REPORTED JAMMING ELEVATOR TRIM CONTROL BETWEEN 2 TO 4 DEGREES DOWN POSITION. THE WHEEL WOULD RELEASE IF WORK	ED BACK AND FORTH. UPON INSPECTION, ONE OF THE BEVEL GEARS INSIDE THE ELEVATOR TRIM INDICATOR BOX WAS FOUND TO HAVE TWO 	BROKEN TEETH.				1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2003052000007	20030520	00007	EU  	2003	5	20	CA030422001      	1	20030414	G	2897		WIRE            	CRANEXXXXXXX		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BOOST PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						B5091B5087					(CAN)  AIRCRAFT WAS INSPECTED DUE TO FINDINGS ON PREVIUOS AIRCRAFT IN OUR FLEET. BOTH THE LT AND RT AIRFRAME FUEL BOOST 	PUMPS WERE FOUND WITH CHAFED WIRES IN THE HARNESS.  A VERY CLOSE VISUAL INSPECTION WAS NEEDED TO FIND THE DAMAGE.PILATUS	 HAS BEEN CONTACTED AGAIN TO STRESS THE IMPORTANCE OF A RECOMENDATION TO REPAIR, EVEN IF ONLY TEMPORARY.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003052000009	20030520	00009	EU  	2003	5	20	CA030422003      	1	20030415	G	2432	TAS203	HEATER          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BATTERY	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A SECTION OF THIS HEATING ELEMENT BURNED OUT SCORCHING THE PAINT ON THE BATTERY. THE BURNED AREA ON THE ELEMENT IS	 5MM X 22CM.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003060200034	20030602	00034	CE  	2003	6	2	CA030423002      	1	20030408	G	2430	S159060L	CIRCUIT BREAKER 			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ALTERNATOR	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA			11636								(CAN) THE PILOT WAS DOING NIGHT TRAINING LOCALLY WHEN HE NOTICED THE LOW VOLTAGE INDICATOR LIT AND THE AMMETER SHOWING A	 DISCHARGE. HE FOUND THE ALTERNATOR CIRCUIT BREAKER TRIPPED.THE BREAKER WAS RESET WHICH RESULTED IN SOME SMOKE AND SPARK	S FROM UNDER THE PANEL. THE LOW VOLTAGE INDICATOR WAS STILL LIT AND THE AMMETER STILL SHOWING DISCHARGE.THE PILOT SHUT D	OWN THE ALTERNATOR SYSTEM AND RETURNED UNEVENTFULLY TO THE AIRPORT. INVESTIGATION REVEALED THE ALTERNATOR CIRCUIT BREAKE	R FAILED IN THE CLOSED POSITION.CIRCUIT BREAKER REPLACED IN ACCORDANCE WITH CESSNA SERVICE LETTER SE76-15.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003060200035	20030602	00035	NM  	2003	6	2	CA030423003      	1	20030416	G	3242	214665	BRAKE ASSY      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			24203								(CAN) BRAKE UNIT WAS INSTALLED ON AIRCRAFT FOR 233:40 SINCE ITS LAST OVERHAUL IT WAS REMOVED FROM THE AIRCRAFT ON APR 16	/03 DUE TO IT LEAKING, ONCE AT THE SHOP IT WAS STRIPPED AND CLEANED AND SENT FOR NDT WORK. THE TECHNICIAN FOUND THE NR 1	 PISTON BOSS CRACKED IN THE BOTTOM OF THE PISTON CYLINDER BORE. OUR OVERHAUL POLICY ON THE BRAKE UNITS ARE ON THE THIRD 	SHOP VISIT THE CASTING IS SENT FOR NDT TESTING THIS UNIT HAD ONLY 233 HRS SINCE THAT WAS LAST ACCOMPLISHED. BECAUSE OF T	HE LOCATION AND LENGTH OF THE CRACK IT WAS DECIDED TO SCRAP OUT THE UNIT.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003060200040	20030602	00040	CE  	2003	6	2	CA030423004      	1	20030320	G	5511	0432001646	RIB             			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LEADING EDGE RIB ASSEMBLIES ARE VERY DIFFICULT TO SEE.THE USE OF A MIRROR THROUGH THE HORIZONTAL SPAR AND RIB LIGH	TNING HOLES IS THE ONLY WAY TO SEE THE CRACKS ALONG THE TABS.I HAVE INCLUDED TWO PHOTOS. ONE OF THE PHOTOS SHOWS A NEW P	ART AND WERE THE LOCATION OF THE CRACKS HAVE BEEN(ALONG THE TABS: UPPER AND LOWER).WE BELIEVE THE RIBS ARE CRACKING DUE 	TO IMPROPER GROUND HANDLING.THE PRACTICE OF PUSHING THE AIRCRAFTS TAIL DOWN BY ITS SPAR IN ORDER TO ROTATE THE AIRCRAFT 	IN POSITION MAY BE DAMAGING THESE RIBS. BOTH RIBS WERE REPLACED WITH NEW.THE TAIL SURFACES WERE REMOVED AND REINSTALLED.		1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2003060200041	20030602	00041	SO  	2003	6	2	CA030423005      	2	20030418	G	8520	AEC648029	PISTON          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ENGINE OIL PRESSURE PROBLEMS WERE NOTICED DURING ENGINE RUN-UP.  NR 2 CYLINDER PISTON WAS F OUND CRACKED AND TH	E LOWER SKIRT OF PISTON FOUND IN OIL PAN. CYLINDERS WERE REMOVED & ENGINE INSPECTED. REMOVAL OF CYLINDERS & PISTONS REVE	ALED OTHER CRACKED PISTON SKIRTS THAT HAD NOT YET FAILED. WE SUSPECT THAT THIS IS A BAD BATCH OF PISTONS AND ANY ECI CYL	INDERS AND PISTONS ARE BEING REPLACED. THE AIRCRAFT IS STILL UNDERGOING MAINTENANCE TO INVESTIGATE THE PROBLEM WITH THES	E CYLINDERS AND PISTONS.		1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2003060200054	20030602	00054		2003	6	2	CA030423007      	4	20030417	G	2562	05118204	LANYARD         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ELT	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION IT WAS NOTICED THAT THE LANYARD CABLE WHICH LINKS THE ELT SUPPORT BRACKET TO THE ELT A	NTENNA SUPPORT BRACKET HAS ENOUGH SLACK IN ITS LENGTH THAT IT RUBS AGAINST THE FUSELAGE (EMPENNAGE) SKIN.  THE LANYARD A	PPEARS TO BE STEEL, AND THE SKIN HAS A SMALL WERE MARK ON THE INSIDE AREA MIDWAY BETWEEN THE ELT AND ANTENNA. (MONOCOQUE	 SKIN)WE INSTALLED A PIECE OF SPIRAL WRAP AROUND THE LANYARD BECAUSE WE COULD NOT REPOSITION NOR CHANGE THE LENGTH. THE 	LANYARD STILL RUBS UP AGAINST THE SKIN BUT IS NO LONGER WEARING A HOLE IN THE SKIN.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003060200066	20030602	00066	EA  	2003	6	2	CA030424005      	2	20030414	G	7414	ES1068255511	MAGNETO         			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  	MCAULY	2D34C	B2D34C208   	GL  	MAGNETO	MISOVERHAULED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) MAGNETO FAILED ON LT PORTION (DUAL MAG) ON RUN UP.  MAGNETO WAS REMOVED AND EXAMINED, BUT NO OBVIOUS DAMAGE OR FAI	LURE WAS EVIDENT.  AS THE PART ONLY HAD 72.5 HOURS SINCE ENGINE WAS OVERHAULED. REPAIRED THE MAGNETO. WHEN I RECEIVED TH	E MAGNETO BACK AFTER REPAIR, I BENCH TESTED IT AND DISCOVERED THAT THE SPARK WAS WEAK AND NOT OCCURRING AT THE PROPER TI	ME. UPON FURTHER INVESTIGATION I DISCOVERED THAT THE MAGNETO ROTOR WAS NOT TIMED CORRECTLY TO THE DISTRIBUTOR GEARS. I R	ETIMED THE MAGNETO ROTOR TO THE DISTRIBUTOR GEARS, RETESTED ON THE BENCH AND NOW THE MAGNETO FUNCTIONS PROPERLY.		1	H	7	1 	3O	3	O	 	A13CE   	E286	5	C	P7EA	 
2003070200103	20030702	00103	CE  	2003	7	2	CA030424007      	1	20030328	G	2140	H11D59	NOZZLE          	JANITROL    		BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HEATER	LEAKING         	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) HEATER UNSERVICEABLE, LEAK FOUND ON HEAD ASSY. PARTS INSTALLED, NOZZEL, GASKETS, ELEC GROUND, ELEC WASHERS, GASKET	 HEAD, IGN, IGN UNIT, VALVE, BRUSH KIT, FILTER, VENT BLOWER MOTOR O/H. HEATER, SMOKY BLACK, PARTS INSTALLED, REG VALVE, 	VALVE, IGN, EXHAUST BLK SMOKE, REMOVED HEATER FOR LEAK CHECK, NO LEAK ON COMBUSTION TUBE, REMOVE HEAD ON TUBE FOR INSP, 	FUEL NOZZLE, INSP FOR SPRAY PATTERN, NOZZLE INSTALLED.   1 GALLON, REINSTALL NOZZLE, 1 GALLON.  HEATER REINSTALLED IN A/	C, HEATER TEST, WORKING NORMALLY.		1	L	7	2 	3T	3	T	 	3A20    	E4EA	6	C	P15EA	 
2003070200104	20030702	00104	GL  	2003	7	2	CA030425004      	2	20030425	G	7230	23004538	BEARING         								ALLSN 	250C  	250C*       	 	GL  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NUT FOR NR 1 BEARING HAVE, ON SEVERAL OCCASIONS, BEEN RECEIVED NEW WITH DAMAGED BLACK NYLON (ZYTEL) MATERIAL AT TO	P OF NUT.  THERE IS THE POTENTIAL FOR LEAKS THROUGH THIS MATERIAL.  THREE RECENT SHIPMENTS (TOTALLING OVER 100 NUTS) HAV	E BEEN FOUND WITH DAMAGE TO THIS SEALING MATERIAL.									3	U			E4CE				 
2003060900163	20030609	00163	CE  	2003	6	9	CA030425005      	1	20030306	G	7797	501A	RESISTOR        			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					INDICATOR	LOOSE           	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			12598	12598							(CAN) CREW REPORTED TOTAL LOSS OF ENGINE TEMPERATURE INDICATION DURING TAXI OPERATIONS. ALL TROUBLESHOOTING PROCEDURES W	ERE FOLLOWED IN THE ENGINE AND AIRFRAME MANUFACTURER'S MAINTENANCE MANUALS. AIRFRAME WIRING HARNESS WAS CONNECTED TO MUL	TIMETER FOR TESTS. OPEN CIRCUIT WAS NOTED TO EXIST THROUGH THE BALANCE RESISTOR. INTERNAL INSPECTION OF THE RESISTOR REV	EALED A LOOSE, SOLDERED CONNECTION. SYSTEM TESTED WITHIN LIMITS. ENGINE RUNS CARRIED OUT AND SYSTEM OPERATED NORMALLY.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003060900164	20030609	00164	CE  	2003	6	9	CA030425006      	1	20030414	G	2434	DOFF10300J	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN)  WHILE AIRCRAFT WAS RETURNING TO AIRPORT, THE PILOT NOTICED AN ELECTRICAL FAILURE, AND RADIO QUIT. CONTINUED APPRO	ACH AND LANDING.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003060900165	20030609	00165	NM  	2003	6	9	CA030425010      	1	20030331	G	2897	NA	WIRE            			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					FUEL BOOST PUMP	BURNED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MAINTENANCE FOUND NR 2 MAIN AFT FUEL LOW PRESSURE LIGHT ILLUMINATED DURING OVERNIGHT MAINTENANCE. SYSTEM INSPECTED	, RELATED CIRCUIT BREAKER FOUND POPPED. AIRCRAFT RELEASED UNDER MEL 28-1-1.  MAINTENANCE REPLACED NR 2 AFT FUEL BOOST PU	MP - SYSTEM DID NOT FUNCTION CHECK SERVICEABLE. FURTHER INVESTIGATION FOUND A BROKEN AND BURNED WIRE IN THE THREE WIRE B	UNDLES GOING TO CONNECTOR D74 FROM THE AFT BOOST PUMP. THE REPORTED PROBLEM IS ADDRESSED BY SERVICE BULLETIN 737-28A1188	 RELEASED MAR. 06/03. WESTJET COMPLETED SB FEB.27/03. MAINT REPAIRED WIRING, PLUG D74 WIRE IAW MM 20-10-11. SYSTEM GROUN	D CHECKED SERVICEABLE & RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003070300034	20030703	00034	EA  	2003	7	3	CA030426001      	1	20030419	G	2133		OUTFLOW VALVE   			CNDAIR	CL600 	CL6002D24   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					CABIN PRESSURE	MALFUNCTIONED   	W				B				EMER. DESCENT           				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AIRCRAFT HAS RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT. THE CABIN ALTITUDE STARTED TO FLUCTUATE ERRACT	ICALLY AND BEGAN CLIMBING UNCONTROLLABLY. THE O2 MASK DROPPED AND COMMENCED EMERGENCY DESCENT TO MINIMUM SAFE ALTITUDE. 	THE LANDING WAS UNEVENTFUL AND ALL PASSENGERS WERE DEPLANED AT THE GATE WITHOUT FURTHER EVENT.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003060900166	20030609	00166	CE  	2003	6	9	CA030427001      	1	20030426	G	2510	05142132	LOCK            			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	SEAT CYLINDER	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) PILOT WAS PRACTICING A FORCED LANDING AND WAS ON FINAL APPROACH WITH FULL FLAPS, NO POWER AND A LOT OF TRIM TO PRO	DUCE A 70KT GLIDE. AS FULL THROTTLE WAS APPLIED AND ABORTED LANDING AT 500 FT, THERECLINABLE SEAT BACK COLLAPSED. THE PI	LOT MANAGED TO USE THE ELECTRIC TRIM TO BACK OFF THE TRIM AND REGAIN CONTROL. THE SEAT BACK WAS RECLINED BACK TO THE UPR	IGHT POSITION FOR AN UNEVENTFUL LANDING.THE PROBLEM COULD NOT BE REPEATED ON THE GROUND, INSPECTION COULD NOT REVEAL ANY	 OBVIOUS SIGN FOR THE CAUSE OF THE FAILURE. THE SEAT RECLINE CYLINDER LOCK ASSY WAS REPLACED AS A PRECAUTION.		1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2003060900167	20030609	00167	CE  	2003	6	9	CA030428004      	1	20030428	G	2160	NYLC9871	ACTUATOR        			BEECH 	100   	B100        	1152919	CE  										BLEED SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CREW WAS UNABLE TO COOL THE CABIN TEMPERATURE DURING THE FLIGHT. BOTH THE AUTO AND MANUAL MODE SYSTEM WAS USED WIT	HOUT SUCCESS. FOUND THE LT BLEED AIR BYPASS VALVE/ACTUATOR STUCK IN THE FULL HOT POSITION.UNIT REPLACED WITH AN OVERHAUL	ED UNIT AND SYSTEM TESTED OK.				1	L	7	2 	4T			 	A14CE   					 
2003060900168	20030609	00168		2003	6	9	CA030428005      	4	20030428	G	3418	9754421421	SWITCH          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AOA	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ROUGH & STICKING OPERATION OF THE VANE WAS NOTED. ASSY REPLACED WITH NEW, FUNCTION TESTS SATISFACTORY.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003060900169	20030609	00169	CE  	2003	6	9	CA030428006      	1	20030428	G	2612		FIRE LOOP       			BEECH 	100   	B100        	1152919	CE  										RT ENGINE	MALFUNCTIONED   	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB AFTER TAKE OFF, THE RT FIRE WARNING LIGHT CAME ON, THE PILOT CONDUCTED AN ENGINE SHUT DOWN AND USED T	HE FIRE BOTTLE AND RETURN TO THE MAIN BASE AS PER FLIGHT MANUAL CHECKLIST . UPON INVESTIGATION, NO FIRE WAS FOUND, ALL T	HREE FIRE SENSORS DETECTORS WERE INSPECTED, WIRING INSPECTED AND NO FAULTS WERE FOUND.  THE FIRE BOTTLE WAS RESERVICED A	ND REINSTALLED AND SYSTEM WAS TESTED PER THE MAINTENANCE MANUAL, OK.  THE FIRE WARNING WAS CAUSED BY THE EARLY MORNING S	UN LIGHT WHICH SHINED INTO COWL OPENINGS CAUSING A FALSE WARNING.		1	L	7	2 	4T			 	A14CE   					 
2003060900170	20030609	00170	CE  	2003	6	9	CA030429001      	1	20030429	G	2612	302158	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) WHILE CLIMBING THROUGH 1500 FT, LT ENGINE FIRE WARNING LIGHT ILLUMINATED INTERMITTENTLY WITH NO APPARENT SIGNS OF 	FIRE, HEAT OR CHANGE IN ENGINE PARAMETERS. THE AIRCRAFT RETURNED TO BASE FOR LANDING AND THE LIGHT EXTINGUISHED AND STAY	ED OUT ON FINAL APPROACH. INSPECTION OF FIRE DETECTION SYSTEM BY MAINTENANCE DETERMINED THAT THE LIGHT WAS SET OFF BY TH	E PRESENCE OF MOISTURE IN THE FIRE DETECTOR WIRING CONNECTOR. THE MOISTURE WAS EXPELLED AND THE SYSTEM TESTED SERVICEABL	E.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003061100052	20030611	00052	EU  	2003	6	11	CA030429002      	1	20030331	G	6230	350A37118322	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					M/R SHAFT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M1004					(CAN) COMPONENT REMOVED FOR METAL CONTAMINATION.  DURING DISASSEMBLY FOR INVESTIGATION BEARING LOCK FOUND BROKEN INTO MU	LTIPLE FRAGMENTS.  THIS CAUSED EXTENSIVE DAMAGE TO EPICYCLIC AND REDUCTION GEARBOX ASSEMBLIES.  POSSSIBLE CAUSE IS INCOR	RECT BEARING PRELOAD DURING ASSEMBLY.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003061100053	20030611	00053	SO  	2003	6	11	CA030430004      	2	20030430	G	8530	625859CP	CYLINDER        			BEECH 	35    	M35         	1151526	CE  	CONT  	O470  	IO470C      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NR 4 CYLINDER, ON INVESTIGATION DURING LEAK, DOWN TEST NOTED LOW COMPRESSION AND LEAKAGE IN EXHAUST PORT.  CYLINDE	R REMOVED AND CRACK FOUND IN EXHAUST PORT. THIS ENGINE TYPE NOTED FOR HIGH CYLINDER FAILURE RATE.  CYLINDER SCRAPPED.					1	L	7	1 	3O	3	O	 	3A15    	E273	5	C	P880	 
2003061100054	20030611	00054	CE  	2003	6	11	CA030430005      	1	20030430	G	3020	S123017	WIRE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					CARB HEAT CONTRO	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) CARB HEAT CONTROL WIRE BROKE AT PIVOT BOLT AT AIRBOX ARM. NO VISIBLE DAMAGE, BOLT MAY HAVE BEEN OVERTIGHT AND NICK	ED WIRE. NO WEAR ON CONTROL OTHERWISE, CABLE WIRE AND SHEATH ADJUSTED AND WIRE REATTACHED (EXTRA LENGTH AVAILABLE FOR AD	JUSTMENT). AIRCRAFT RETURNED TO SERVICE.FAILURE POSSIBLY DUE TO ROUGH OPERATION BY STUDENT.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003060900171	20030609	00171	CE  	2003	6	9	CA030430007      	1	20030430	G	3221	NAS755006	BUSHING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	NLG	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING THE COURSE OF COMPLIANCE WITH A ROUTINE PHASE 6 INSPECTION ON THE NLG OF THIS (A SHORT-TERM LEASE) AIRCRAFT	, MAINTENANCE FOUND NLG BEARING BLOCK WAS MISSING THE TWO BUSHINGS THAT GUIDE AND SUPPORT NLG DRAG BRACE FORK ATTACHMENT	 BOLTS.  THESE BOLTS WERE OVERTORQUED, DAMAGING FORK BEARINGS, CLIPS AND GOUGING OUT THE BEARING BLOCK BUSHING BORES. ON	 REPLACEMENT OF THE BEARING BLOCK, BOLT WAS FOUND TO BE CRACKED IN TWO PLACES. THE POSSIBILITY EXISTS OF PUSHING FORK BE	ARINGS THRU THE FORK AND INTO THE BEARING BLOCK BUSHING BORES THUS RENDERING THE FORK UNSTABLE WHICH COULD SEPARATE FROM	 THE BEARING BLOCK UNDER LOAD, AND CAUSE A NOSE GEAR COLLAPSE.	1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003060900174	20030609	00174	CE  	2003	6	9	CA030501001      	1	20030501	G	3230	MC815AS1	CONTROLLER      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MLG	STUCK           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FOLLOWING A NORMAL TAKE-OFF, GEAR WAS SELECTED UP AT WHICH TIME THE FLT CREW HEARD A LOUD GRINDING NOISE DURING TH	E FINAL PHASE OF GEAR UP CYCLE. GEAR WAS RESELECTED DOWN AND THERE WAS NO MOVEMENT OR MOTOR NOISES. FLT CREW COMPLETED A	 MANUAL GEAR EXTENSION, THREE GREEN LIGHTS OBSERVED. ANUNEVENTFUL LANDING WAS COMPLETED. FURTHER INVESTIGATION BY MAINTE	NANCE FOUND THAT LANDING GEAR MOTOR CONTROLLER HAD FAILED IN GEAR UP POSITION, NOT STOPPING WHEN THE GEAR WAS UP, ONLY S	TOPPING WHEN THE MOTOR COULD NOT LONGER MOVE THE GEAR AND POPPED ITS CIRCUIT BREAKER. MAINTENANCE REPLACEDTHE CONTROLLER	 AND COMPLETED GEAR SWINGS ALL SWINGS WERE NORMAL.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003060900177	20030609	00177	NM  	2003	6	9	CA030501004      	1	20030428	G	2910	82950010269	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) CREW REPORTED A FLUID LEAK FROM THE RT WING INBOARD SPOILER PCU. MAINTENANCE FOUND LIFT DUMP HYDRAULIC LINE FROM R	T WING SPOILER ACTUATOR LEAKING FROM A PIN HOLE AT THE MAIN ELBOW ON THE OUTBOARD PART OF THE LINE. AFTT: 32777 HRS CYCL	ES: 36996				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003052000159	20030520	00159	NM  	2003	5	20	CA030505002      	1	20030504	G	5610	NP1653114	WINDOW          			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A3    	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT FL 370 FO,S FRONT WIND SCREEN OUTER PANE SUDDENLY CRACKED. SPIDER WEB PATTERN WITH MULTITUDE FRACTURES.DECENDED	 TO FL 230. DELTA P AT 5.0. DIVERTED TO DUE FUEL. REPLACED FO,S WINDSHIELD AND WINDOW HEAT CONTROLLER AS PER AMM 56-11-1	1. WINDOW OPERATION CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003052000160	20030520	00160	NM  	2003	5	20	CA030505003      	1	20030503	G	5610	65C343482	WINDOW          			BOEING	737   	7372T7      	1384482	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) F/O,S NR 1 WINDOW OUTER (POSS MIDDLE) PANE CRACKED AT 31000 WINDOW SLOWLY DELAMINATED AND AFTER WE TURNED HEAT OFF	 WINDOW CRACKED. WINDOW REPALCED AS PER AMM.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2003052000162	20030520	00162	SO  	2003	5	20	CA030505005      	1	20030501	G	2730	41734078	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ELEVATOR	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) AFT ELEVATOR TRIM CABLE LOCATED AT AUTOPILOT SERVO SNAPPED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003050700001	20030507	00001	CE  	2003	5	7	CA030505006      	1	20030505	G	5330	1211650	SKIN            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUSELAGE	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE AIRCRAFT HAS A BLACK MATERIAL BONDED TO THE AIRCRAFT BELLY SKIN INTERIOR TO PREVENT OIL CANNING.SEVERE CORROSI	ON WAS FOUND BETWEEN THE BONDED MATERIAL AND THE SKIN. IN SOME AREAS THE CORROSION EXTENDED TO A DEPTH EQUAL TO HALF OF 	THE SKINS .032 THICKNESS. THE SKIN WAS REPLACED. OTHER SKIN AREAS ALSO REQUIRED REMOVAL OF THE BLACK MATERIAL AND REMOVA	L OF SURFACE CORROSION CARRIED OUT. A REVIEW OF THE AIRCRAFT IPC COULD NOT FIND THIS ITEM. THIS UNKNOWN BLACK MATERIAL W	AS CHECKED WITH A MULTI-METER AND FOUND TO BE CONDUCTIVE SUGGESTING THAT WITH THE PRESENCE OF MOISTURE ELECTROLYTIC CORR	OSION COULD RESULT.	1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2003060200024	20030602	00024	CE  	2003	6	2	CA030506001      	1	20030428	G	3232	50450014	ACTUATOR        			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470VO     	17026	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	MLG DOOR	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) AT 160 KTS DID NOT GET DOWN LOCKED IND ON RT MAIN. GEAR WAS SEL UP, TOP OF TRAVEL, GRINDING NOISE WAS HEARD.  GEAR	 SELECT WAS PLACED IN NEUTRAL, GEAR WAS HAND-CRANKED DOWN, A/C LANDED. RT MAIN GEAR DOOR WAS OPEN ABOUT 6 IN FROM NORMAL	 CLOSED GEAR DOWN POSITION.  WELD HOLDING GEAR DOOR ATTACH ARM TO MAIN GEAR DOOR ACT ASSY SHAFT WAS BROKEN ALLOWING ARM 	TO SLIP ON SHAFT.  DURING GEAR UP SEL, DETERMINED THAT TIRE STRUCK, RE-LOCATED ARM AND MOTOR, NOT HAVING ANY IND TO SHUT	 OFF AS LIMIT SWITCHES ARE LOCATED ON GEAR ACT, KEPT GOING CAUSING DAMAGE TO OUTPUT GEAR, GEARBOX GEAR. EXCESSIVE WIND F	ORCE WAS APPLIED TO DOOR, BREAKING WELD.  LT MAIN GEAR DOOR ACT ARM HAS BEEN REMOVED FOR NDT.	1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P36EA	 
2003053000106	20030530	00106	CE  	2003	5	30	CA030506002      	1	20030429	G	8011	MZ2399S	ARMATURE        	PRESTOLITE  		CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	STARTER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						2K000682					(CAN) UPON INITIAL START OF DAY, STARTER MADE GRINDING NOISE.UPON REMOVAL AND DISASSEMBLY OF STARTER.   IT WAS VISUALLY 	EVIDENT THE GEAR ON THE ARMATURE WAS MISSING 4 TEETH AND THE GEAR AT THE BASE OF THE BENDI X WAS MISSING ONE TOOTH.  THE	 FLYWHEEL WAS INSPECTED SERVICEABLE, THE STARTER WAS REPLACED WITH AN OVERHAUL UNIT AND THE ENG WAS GROUND RUN SATISFACT	ORY.			1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA	 
2003070700011	20030707	00011	EA  	2003	7	7	CA030506004      	1	20030413	G	2420	2CM70D6A	GENERATOR       			CNDAIR	CL215 	CL2151A10   	1900320	EA  										ELECTRICAL	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) TWO GENERATORS HAD 8130 FORMS STATING THAT GENERATORS HAD BEEN OVERHAULED AND TESTED. AFTER A GROUND GENERATOR FIR	E DURING INITIAL RUNUP ON THE FIRST UNIT, THE SECOND GENERATOR THAT HAD BEEN INSTALLED ON ANOTHER AIRCRAFT BUT NOT RUN Y	ET WAS REMOVED FOR INVESTIGATION. COMPANY OVERHAUL SHOP INSPECTED THE INTERNAL PARTS OF THE REMAINING GENERATOR AND FOUN	D EVERYTHING CLEAN EXCEPT THAT THE BRUSHES WERE BRAND NEW AND HAD NOT BEEN RUN IN AT ALL. UPON 5 MINUTES OF TESTING WITH	 A CURRENT ON TO WEARING THE BRUSHES, THE GENERATOR STARTED MAKING STRANGE NOISES AND BEGAN SMOKING. TEST WAS HALTED. GE	NERATORS SENT BACK TO SUPPLIER FOR INVESTIGATION AND CREDIT.	2	H	7	2 	4R			RT	A14EA   					 
2003082200095	20030822	00095	EA  	2003	8	22	CA030506005      	1	20030201	G	3213	1606042	TRUNNION        			CNDAIR	CL215 	CL2151A10   	1900320	EA  										MLG	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE REAR TRUNNION WAS TO BE OVERHAULED BY COMPANY. COMPANY O/H SHOP AME RECOGNIZED THAT THE CURRENT PLATING PROCES	S ON THE PART WAS INCORRECT (COPPER). THE PART WAS SENT TO PLATING COMPANY FOR NICKEL/CHROME PLATING. STRIPPING OF PART 	REVEAL ED EXCESSIVE ETCHING, PITTING, AND A PREVIOUS UNAPPROVED WELD REPAIR. PLATING COMPANY CALLED US FOR INSTRUCTIONS.	 WE ADVISED THEM TO RETURN THE PART. STORES ANDTHE OVERHAUL SHOP NOTIFIED TO DESTROY PART TO MAKE IT UNUSABLE ONCE RETUR	NED.		2	H	7	2 	4R			RT	A14EA   					 
2003070700013	20030707	00013	CE  	2003	7	7	CA030506006      	1	20030314	G	2797		WIRE            			BEECH 	95    	95          	1153402	CE  										TE FLAP MOTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AME INSTALLED THE COMPONENT (OVERHAULED JAN/02) DURING 2002-2003 WINTER MAINTENANCE. A FUNCTION CHECK OF THE U	NIT REVEALED INTERMITTENT INDICATIONS. REMOVAL OF THE UNIT REVEALED THAT THERE WAS A BROKEN WIRE INTERNALLY. A PREVIOUSL	Y UNDISCOVERED CRACK IN THE GEARBOX HOUSING WAS ALSO DETECTED. THIS UNIT HAD 0 TSO. COMPANY NOTIFIED OF POOR WORKMANSHIP	.			1	L	7	2 	3O			 	3A16    					 
2003053000110	20030530	00110	EU  	2003	5	30	CA030507003      	1	20030110	G	3150		DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA						6313					(CAN) THE CREW REPORTED ON ROUTE THAT THE DE-ICE FAIL LIGHT WAS ON BUT ALL SYSTEMS WERE WORKING PROPERLY. UPON LANDING T	HE LIGHT REMAINED ON WITH ALL SYSTEMS OFF , ONLY THE BATTERY TURNED ON.  THE BATTERYWAS CYCLED OFF THEN ON TO ATTEMPT TO	 CLEAR THE SNAG.AFTER ABOUT 2 MINUTES OF BATTERY POWER ON, SMOKE AND ELECTRICAL BURNING SMELL APPEARED.  THE BATTERY POW	ER WAS TURNED OFF AND THE BURNING DISSIPATED. MAINTENANCE FOUND THE CAWS PANEL AND CAWS COMPUTER COOKED, REPLACED BOTH U	NITS AND NO FURTHER PROBLEMS ENCOUNTERED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003053000113	20030530	00113	CE  	2003	5	30	CA030507007      	1	20030402	G	2720	505243263	PEDAL           			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					RUDDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10509								(CAN) DURING AN OPERATIONAL CHECK OF CONTROLS DURING MAINTENANCE,  LT RUDDER PEDAL FRACTURED AT ITS ATTACHMENT POINT FRO	M WEAR. OBLONG WEAR WAS NOTED IN ATTACHMENT AREA. WEAR WAS NOT READILY NOTICED DUE TO ATTACHEMENT DESIGN AND ATTACHMENT 	TO BRAKE MASTER CYLINDER. REMOVAL OF ATTACHING HARDWARE OF PEDAL NEEDED TO CHECK FOR WEAR. OTHER COMPANY B55 AIRCRAFT CH	ECKED FOR WEAR AND FOUND WORN.  PARTS REPLACED AS NECCESSARY.			1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2003053000114	20030530	00114	EU  	2003	5	30	CA030508001      	1	20030507	G	2897		WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BOOST PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DUE TO PREVIOUS FIND OF FUEL BOOST PUMP WITH A CHAFED WIRING HARNESS, THE BOOST PUMPS WERE REMOVED FOR PRECAUTIONA	RY INSPECTION.  CHAFED WIRES ON HARNESS WERE FOUND ON THERIGHT SIDE PUMP. LT PUMP WAS OLD STYLE PUMP STILL INSTALLED WIT	H HARNESS COMING OUT THE TOP OF THE PUMP.  PUMP HAD 1 848.4 HOURS PUMP WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003053000116	20030530	00116	CE  	2003	5	30	CA030508003      	1	20030506	G	3233	9981005765	ACTUATOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MLG	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ACTUATOR WAS INSTALLED AFTER HAVING OTHER GEAR PROBLEMS. WHEN GEAR WAS SELECTED UP INFLIGHT THE GEAR MOVED 1/4 OF 	THE WAY BEFORE THE CLUTCH IN THE GEARBOX BEGAN SLIPPING & CONTINUED TO SLIP UNTIL CIRCUIT BREAKER POPPED. FIRST TIME THI	S HAPPENED SUSPECTED MOTOR & CIRCUIT BREAKER BECAUSE WE DID NOT KNOW THAT THE CLUTCH WAS SLIPPING, AFTER REPLACING THE M	OTOR & CB, GEAR REPEATED SAME PROBLEM.  ON 2ND ATTEMPT, NOTED GEARBOX CLUTCH WAS SLIPPING DURING RETRACTION IN FLIGHT. D	ECIDED TO REPLACE GEARBOX. WITH GEARBOX DISCONNECTED IT WAS NOTED THAT RT GEAR ACTUATOR WAS HARDER TO TURN THAN NORMAL I	T ALSO HAD A DRY SOUNDING BACKLASH NOISE COMING FROM INPUT GEAR WHEN TORQUE TUBE IS ROCKED BACK AND FORTH.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2003053000117	20030530	00117	EA  	2003	5	30	CA030508004      	2	20030508	G	7414	M3100	RIVET           	SLICK       		ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					IMPULSE COUPLING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						98040711					(CAN) DUE TO OTHER IMPULSE COUPLING FAILURES, AT EVERY 100 HR INSPECTION, THE LT MAGNETO IS REMOVED AND THE IMPULSE COUP	LING IS INSPECTED. THIS IMPULSE COUPLING HAD A LOOSE RIVET THAT HOLDS ONE OF THE PAWLS IN PLACE.  HAD THE RIVET FAILED T	HE PAWL WOULD CONTAMINATE THE ENGINE WITH METAL. THE 100 HR INSPECTION INTERVAL WILL CONTINUE ON THE LT MAGNETO.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003053000118	20030530	00118	EU  	2003	5	30	CA030509001      	1	20030508	G	2911	9738114306	ACCUMULATOR     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)  DISCOVERED FAULT WAS WITH MLG HYD SYS PRESSURE SWITCH. REPLACED DUE TO LEAK FROM ACCUMULATOR SIDE OF HYD SYS THRO	UGH A VENT HOLE IN SIDE OF BODY OF SWITCH. THIS DEPLETES NITROGEN IN ACCUMULATOR, WITH LESS AIR IN ACCUMULATOR, LANDING 	GEAR HYDR SYS MOTOR/PUMP WOULD RUN CONSTANTLY. PRESSURE SWITCH CONTROLS RELAY THAT CONTROLS HYD MOTOR/PUMP OPERATION. RE	LAY'S OTHER CONTACTS CONTROL HYD INTERLOCK RELAY TO PREVENT OPERATION OF VAPOR CYCLE COOLING SYS & LANDING GEAR HYDR SYS	 FROM OPERATING AT SAME TIME.  NO INDICTION OF ANY DEFECT WITH LANDING GEAR SYS ,NO WARNING LIGHTS IN COCKPIT. UPON REPL	ACEMENT OF PRESSURE SWITCH AND LANDING GEAR HYD SYS RESERVICING ALL SYSTEMS OPERATED NORMALLY.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003061700044	20030617	00044	GL  	2003	6	17	CA030509002      	2	20030423	G	7210	23059576	SHIM            	ALLSN       	23035179    						ALLSN 	250C  	250C30      	03013	GL  					GEARBOX	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAG90752					(CAN) A GEARBOX WAS DISASSEMBLED FOR INSPECTION DUE TO REPORT OF LOW OIL PRESSURE.  4 OF 8 SMALL SCREWS USED TO RETAIN A	 REPAIR SHIM WERE FOUND MISSING.  THE REPAIR SHIM WAS LOCATED UNDER THE TORQUEMETER AND JOURNAL FLANGED SUPPORT.  REPAIR	 SHIM WAS LIKELY USED FOR DIMENSIONAL RESTORATION OF THE TORQUEMETER SUPPORT PAD FEATURE OF THE GEARBOX COVER.  3 OF THE	 MISSING SCREWS AND A WASHER WERE LATER FOUND  TRAPPED IN THE SCREEN OF THE SCAVENGE OIL TRANSFER TUBE AND SCREEN ASSY, 	WHICH IS LOCATED JUST UPSTREAM OF THE SCAVENGE OIL INLET OF THE OIL PUMP.THE FOURTH MISSING SCREWWAS LATER FOUND ON AN I	NTERNAL SURFACE OF THE GEARBOX COVER.						3	U			E1GL				 
2003060200025	20030602	00025	CE  	2003	6	2	CA030512001      	1	20030501	G	2750	SM50D7	RELAY           			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  					TE FLAPS	INTERMITTENT    	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) FLAPS WERE SELECTED FROM THE 15 DEGREE POSITION AND WOULD NOT MOVE UP OR DOWN.  DYNAMIC BRAKE RELAY WAS FOUND TO W	ORK IF TAPPED.  RELAY REPLACED AND AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
2003060200036	20030602	00036	WP  	2003	6	2	CA030512002      	2	20030512	G	7250	310170318	BUSHING         		310170318   						GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UPON ATTEMPTING TO INSTALL TWO BUSHINGS ON THE TORSION SHAFT FOR THE ENGINE IT WAS NOTICED THAT THE TWO BUSHINGS H	AVING THE SAME PART NUMBER HAD A DIFFERENT WALL THICKNESS AND INSIDE DIAMETER. THE SAME PART NUMBER WAS STAMPED ON EACH 	BUSHING. THE REMAINDER OF THE BUSHINGS WERE CHECKED AND A TOTAL OFTHREE BUSHINGS WERE FOUND WITH THE SAME PROBLEM (TOO T	HIN OF A WALL). BUSHINGS WERE REMOVED FROM STOCK AND PLACED IN QUARENTINE.								4	T			E4WE				 
2003060200037	20030602	00037	GL  	2003	6	2	CA030513001      	1	20030509	G	2434	654358	BRACKET         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	ALTERNATOR MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FORWARD ALTERNATOR MOUNTING BRACKET CRACKED.  THE CRACK IS LOCATED ON THE BOTTOM SIDE OF THE FORWARD ALTERNATOR MO	UNTING HOLE.					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA	 
2003060200026	20030602	00026	WP  	2003	6	2	CA030514003      	1	20030427	G	6300	C0511	ACTUATOR        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAIN ROTOR	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) MAIN ROTOR ACTUATOR ENGAGEMENT WAS OVER 90 SECONDS. ACTUATOR REMOVED AND SENT FOR OVERHAUL.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003060200028	20030602	00028	CE  	2003	6	2	CA030514004      	1	20030428	G	5312	504100491	FLANGE          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					BULKHEAD	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACK ON BULKHEAD FLANGE APPROX. .7500 LONG CRACK. NOSE COMPARTMENT AREA, NOSE WHEEL STEERING IDLER SHAFT SUPPORT 	INTERCOSTAL BULKHEAD.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003060200030	20030602	00030	EA  	2003	6	2	CA030514007      	2	20030422	G	7414	ES10384585	BREAKER POINTS  	BENDIX      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	MAGNETO	WORN            	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA						33440					(CAN) WHILE IN CRUISE AIRCRAFT EXPERIENCED A DROP IN ENGINE RPM TO APPROXIMATELY 1900 RPM. WHILE HEADING TO NEAREST AIRP	ORT, A MAGNETO CHECK DETERMINED RIGHT MAGNETO TO BE COMPLETELY DEAD. AFTER LANDING & PULLING POWER BACK, THEN ENGINE QUI	T AND COULD NOT BE RESTARTED. MAGNETO WAS REMOVED AND FOUND THAT POINTS WERE NOT OPENING AT ALL  DUE TO THE EXCESSIVE WE	AR OF THE NYLON/PLASTIC. MAGNETO REPLACED WITH SPARE AND ENGINE RAN NORMALLY.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003060200031	20030602	00031	GL  	2003	6	2	CA030514009      	3	20030424	G	6197	30600003	WIRE HARNESS    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) WHILE IN FLIGHT, THE (DE-ICE CAUTION) AMBER CAUTION LIGHT ILLUMINATED AND THE GREEN (PROP DE-ICE) WAS FLASHING. AF	TER INVESTIGATING THE PROBLEM. THE WIRE THAT WAS PROVIDING HEAT TO THE DE-ICE WAS ALREADY REPLACED.   2 BARE HEATING WIR	ES ON INTERIOR OF DE-ICER BUNDLES WERE TOUCHING CAUSING A SHORT,  THE CAUTION LIGHTS THEN WOULD ILLUMINATE. ONCE WIRE BU	NDLE (3E2360-4) WAS REPLACED, THE SYSTEM WORKED CORRECTLY.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003060200052	20030602	00052	CE  	2003	6	2	CA030514010      	1	20030510	G	2810	261601741	RESERVOIR       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) POST FLIGHT INSPECTION REVEALED FUEL DRIPPING FROM THE RESERVOIR AREA ON THE BELLY OF THE AIRCRAFT. AFTER REMOVING	 THE ACCESS PANEL FUEL WAS SEEN TO BE SEEPING FORM THE UPPER SURFACE OF THE RESERVOIR .  AFTER REMOVING THE RESERVOIR A 	SMALL CRACK WAS VISIBLE ON THE TOP SURFACE.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003060200032	20030602	00032	CE  	2003	6	2	CA030514012      	1	20030507	G	8011	Z4214	STARTER         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	BLOCKED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											(CAN) ON ENGINE START UP,  PILOT NOTICED THAT THE PROP WAS NOT TURNING. AFTER INVESTIGATION WE DISCOVERED THAT THE START	ER WAS DEFECTIVE.					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2003060200033	20030602	00033	EA  	2003	6	2	CA030514013      	2	20030425	G	8520	11F20022S3	CRANKCASE       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) DURING A 50 HOUR INSPECTION, THE ENGINEERS NOTICED AN OIL LEAK. THEY CLEANED THE ENGINE AND SPRAYED IT WITH A DEVE	LOPER. AFTER PERFORMING A GROUND RUN ON THE ENGINE, A CRACK WAS DISCOVERED IN THE CRANKCASE. THIS CRACK WAS ABOUT 6 INCH	ES LONG AND LOCATED ON THE RIGHT SIDE OF THE ENGINE, UNDER THE NR1 CYLINDER. THE ENGINE WAS REMOVED FOR REPAIR.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003061100056	20030611	00056	EA  	2003	6	11	CA030514017      	1	20030404	G	4920	38004883	APU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  						FIRE            	W				F				ACTIVATE FIRE EXT.      				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA											(CAN) APPROXIMATELY 5 MINUTES AFTER SHUTTING DOWN APU (ENGINES OFF NO GROUND POWER), DECIDED TO OPEN APU DOOR TO HELP CO	OL APU DOWN PRIOR TO LCV CHANGE.  2 MINUTES LATER, MAITNENANCE NOTICED THAT SMOKE AND FLAMES WERE COMING OUT OF THE APU 	INTAKE.  MECHANIC RUSHED TO COCKPIT, CLOSED APU DOOR AND MANUALLY DISCHARGED FIRE BOTTLE.  SHORTLY AFTER NOTICED THAT FL	AMES WERE NOW COMING OUT OF APU EXHAUST.  MAITNENANCE THEN DISCHARGED TWO PORTABLE FIRE EXTINGUISHERS INTO APU EXHAUST U	NTIL FIRE WAS EXTINGUISHED.  MAINTENANCE THEN NOTIFIED THE FIRE DEPARTMENT HOWEVER NO FURTHER ACTION WAS REQUIRED.  THE 	APU WAS REPLACED AND SENT TO MFG FOR INVESTIGATION.  NOTE: THIS APU HAD RECENTLY BEEN INSTALLED ON A/C.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003061100058	20030611	00058	NM  	2003	6	11	CA030515001      	1	20030226	G	3260	473901	DOWNLOCK SENSOR 			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG	DAMAGED         	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) NOSE GEAR UNSAFE (AMBER NLG, RED NLG & AMBER TRANSIENT LIGHT IN HANDLE) DURING CLIMB AND CRZ, MAX SPEED 210 KTS. A	FTER GEAR DOWN SELECTION, NOSE GEAR INDICATE UNSAFE, NORMAL LANDING PERFORMED AFTER ALTERNATE GEAR SELECTION AND SAFE IN	DICATING.  NOSE LANDING GEAR DOWNLOCK PROXIMITY SENSORS NR 1 AND NR 2 REPLACED . DAMAGES TO NOSE LANDING GEAR FWD DOORS 	REPAIRED. LANDING GEAR RETRACTION/EXTENSION CHECK PERFORMED WITHOUT ANY REMARKS.  CONCLUSION THE NOSE GEAR UNSAFE CONDIT	ION WAS MOST PROBABLY CAUSED DUE BREAKAGE OF THE NR 1 LOCK SENSOR WIRING.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003061100059	20030611	00059	CE  	2003	6	11	CA030515003      	1	20030509	G	2720	300433113	BELLCRANK       			CESSNA	120   	120         	2071402	CE  	CONT  	C85   	C8512F      	17008	SO  	MCAULY	1A90	1A90*       	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INVESTIGATION THE RUDDER BELLCRANK WAS FOUND CRACKED.						1	H	7	1 	3O	3	O	 	A768    	E233	5	N	P842	 
2003061100060	20030611	00060	CE  	2003	6	11	CA030515004      	1	20030514	G	2820	50921620235	TUBE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYS	GROOVED         	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) THIS AC HAS CLEVELAND BRAKE STC INSTALLED. DURING MAIN GEAR RETRACTION AND EXTENSION LT MAIN GEAR FORWARD HYD BRAK	E UNIT CONTACTED MAIN FUEL SUPPLY TUBE AND DAMAGED TUBE BY ERODING A TWO-INCH LONG BY ONE-QUARTER INCH WIDE GROOVE IN TU	BE WALL. THIS FUEL TUBE IS MAIN SUPPLY LINE FROM NACELLE TANK BOOST PUMP TO FIREWALL SHUTOFF VALVE AND APPEARED TO BE IM	PROPERLY POSITIONED FOR ADEQUATE CLEARANCE. PERFORATION OF TUBE WALL WOULD RESULT IN TOTAL FUEL LOSS FROM LT WING FROM A	 PRESSURIZED LEAK. POTENTIAL SAFETY ISSUES ARE RISK OF FIRE, LOSS OF ENGINE POWER AND POSSIBLE CONTROL DIFFICULTY RESULT	ING FROM A 1000 LB FUEL IMBALANCE. TUBE WAS REPLACED WITH A SERVICEABLE UNIT CORRECTLY POSITIONED FOR CLEARANCE.	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003070700012	20030707	00012	NE  	2003	7	7	CA030515007      	2	20030513	G	7261		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1	OVERSERVICED    	W				A				UNSCHED LANDING         				W	B		INADEQUATE Q C            	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA											(CAN)  SMOKE/FUMES DETECTED IN FLT COMPARTMENT & CABIN, TOILET SMOKE WARNING ACTIVATED, QRH DRILL ACTIONED, PAN DECLARED	, SMOKE CLEARED, RETURN, LANDED SAFELY. MAINT CARRIED OUT AN INSP & CONCLUDED THAT SMOKE/FUMES WERE RELATED TO NR 1 ENGI	NE HAVING BEEN OVERSERVICED WITH ENGINE OIL, OIL HAS BEEN OBSERVED DRIPPING FROM GANG DRAINS OF ENG & ALSO SOME WETTING 	OF NR 1 CARBON SEAL (FAN).  A/C HAS BEEN FLIGHT TESTED & ODOR OF ENGINE OIL COULD BE DETECTED IN CABIN AND COCKPIT, ESPE	CIALLY WHEN NR 1 PACK WAS UTILIZED. NO VISIBLE FUMES/SMOKE & NO ALARM TRIGGERED DURING FLIGHT TEST, MAINT PERFORMED A CO	MPRESSOR WASH & CLEANED NR 1 PACK ECS DUCTING.  A/C RETURNED TO SERVICE & HAD NO REOCCURRENCE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003061100064	20030611	00064	CE  	2003	6	11	CA030516002      	1	20030514	G	6120	640789	CIRCUIT BOARD   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	AUTOFEATHER SYS	INOPERATIVE     	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF ROLL, PILOT NOTICED THAT AUTO-FEATHER SYSTEM DID NOT ILLUMINATE TO IDENTIFY ARM  FUNCTION. PILOT I	NITIATED REJECTED TAKE-OFF, ADVISED ATC & SUBSEQUENTLY RETURNED TO AIRPORT.  MAINTENANCE WAS CONTACTED TO INSPECT AND TR	OUBLESHOOT AUTO FEATHER SYSTEM MALFUNCTION.  WE WERE INFORMED BY THE AMO THAT THE MALFUNCTION OF THE AUTO FEATHER INDICA	TION SYSTEM WAS RECTIFIED BY THE REPLACEMENT OF THE PRINTED CIRCUIT BOARD NR 119 REFERENCED AS P/N 112-364021-5. AIRCRAF	T RUNS WERE COMPLIED WITH AND THE AIRCRAFT WAS RETURNED TO SERVICE. THERE HAS BEEN NO REOCCURRENCE OF THIS DISCREPANCY.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2003071500007	20030715	00007	CE  	2003	7	15	CA030517001      	1	20030517	G	2810		FUEL CELL       			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  						CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING CREW WALK AROUND & ACTUATION WATER DRAINS, CREWS CONSISTENTLY FIND WATER EVEN IF COMPLETELY DRAINED ON PREV	IOUS FLIGHT. AIRCRAFT INSPECTED AND ALL FUELCAPS COMPLETELY RESEALED AND SEAL SEATS CLEANED. ALL FUEL BLADDERS INTERNALL	Y I NSPECTED AND FOUND MULTIPLE LARGE WRINKLES TRAPPING WATER SLUGS. ALL BLADDERS DRAINED. DURING INSPECTION IT WAS NOTE	D THAT THERE IS NO POSSIBLE WAY TO FLATTEN THE BOTTOM OF EACH BLADDER. THE BLADDERS ARE ALL PHYSICALLY LARGER THAN THE W	ING SECTIONS THAT THEY LIVE IN. RAYTHEON TECH SUPPORT NOTIFIED AND THEY RESPONDED BY TELLING US THAT ALL OF THE BARON A/	C ARE LIKE THAT. RECOMMENDED TO JUST CLEAN OUT THE WATER AND MAKE SURE FUEL CAPS SEAL PROPERLY. ALL TANKS RESEALED.	1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2003061700011	20030617	00011	CE  	2003	6	17	CA030517002      	1	20030517	G	2720		RUDDER          			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					VERTICAL STAB	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INCORPORATION OF AD 2000-20R1 (CESSNA S/B SEB01-1) RESULTS IN BINDING BETWEEN NEW STOP BOLTS AND RUDDER STRUCTURE 	DUE TO THE INCREASED SIZE OF THE STOP BOLTS.  BINDING WAS NOT APPARENT UNLESS PRESSURE WAS APPLIED TO BOTH RUDDER PEDALS	.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003060900188	20030609	00188	EA  	2003	6	9	CA030518001      	1	20030518	G	7603		GEARBOX         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					THROTTLE CONTROL	DEFECTIVE       	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) WHEN PILOT RETARDED THROTTLE AT TOP OF DESCENT, LT ENGINE FLAMED OUT. UNEVENTFUL SINGLE ENGINE LANDING. TROUBLE SH	OOTING REVEALED THROTTLE CONTROL GEARBOX DEFECTIVE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003060900189	20030609	00189	EA  	2003	6	9	CA030518002      	1	20030404	G	7603		GEARBOX         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					THROTTLE	MALFUNCTIONED   	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) THE RT ENGINE FLAMED OUT DURING DESCENT, WHEN THROTTLES WERE RETARDED TO IDLE, RT ENGINE CONTINUEDTO SPOOL DOWN ( 	TOP OF DESCENT ). TRIED RE-LIGHT ACCORDING QRH : N2 STAGNATION AT 40 PERCENT AND HIGH ITT, ABORTED ENGINE START AND PERF	ORMED UNEVENTFULL SINGLE ENGINE LANDING IN VIE.FOUND THROTTLE CONTROL GEARBOX MALFUNCTION, WITH WORN TEETH. OBSERVED SEV	ERE BACKLASH IN MOVMENT , 30 ROTATION WITHOUT OUTPUTON SHAFT, FLIGHT CREW REPORTED STICKY THROTTLE LEVER DURING FLIGHT			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082200094	20030822	00094	EA  	2003	8	22	CA030519001      	2	20030518	G	7310	LW120980100	TUBE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL MANIFOLD	BROKEN          	W				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) TUBE ASSEMBLY FOUND BROKEN AT THE INTAKE OF THE FUEL INJECTOR WHICH CAUSED LOSS OF POWER DURING CLIMB.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003053000093	20030530	00093	EU  	2003	5	30	CA030521004      	2	20030519	G	8530		INTAKE VALVE    			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  	HOFMAN	HOV352	HOV352F     	NE  	CYLINDER	SEPARATED       	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN) KATANA DA20A1 WAS ON A ROUTINE TRAINING FLIGHT WHEN THE CREW BECAME SUDDENLY AWARE OF A SIGNIFICANT ENGINE POWER L	OSS AND WERE FORCED INTO MAKING AN UNSCHEDULED LANDING IN A FARMERS FIELD. THE AIRCRAFT LANDED SAFELY AND WAS LATER DISM	ANTLED AS NECESSARY AND TRAILORED BACK TO ITS BASE OF OPERATION.  FURTHER INVESTIGATION REVEALED THAT THE NR 3 CYLINDER 	INTAKE VALVE HAD SEPARATED AND CAUSED SIGNIFICANT DAMAGE TO THE CYLINDER HEAD AND PISTON. THE VALVE ENDED UP WEDGED PERP	ENDICULAR IN ITS SEAT AND THE VALVE SPRING RETAINER WAS FOUND SEPARATED AS WELL. THE ENGINE HAS BEEN REMOVED FROM THE AI	RCRAFT FOR FURTHER ASSESSMENT AND REPAIR.	1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I	5	C	TP5BO	 
2003053000094	20030530	00094	EU  	2003	5	30	CA030521005      	1	20030518	G	3242	21600	BRAKE ASSY      			AIRBUS	A319  	A319112     	3930323	EU  	CFMINT	CFM565	CFM565B6    	13802	NE  					MLG	FIRE            	W				O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA											(CAN) FLAMES OBSERVED COMING FROM LT WHEEL OUTERSIDE BRAKE. AFTER A LONG TAXI, LOW WEIGHT, SINGLE ENG, THE BRAKE GOT TO 	440 C , AFTER PARKING AT THE GTE, FIRE WAS PUT OUT BY AC EMPL. WITH AC FIRE EXTING. REMOVED M/W & BRAKE ASSY'S. VISUAL I	NSPECTION OF LT MAIN GEAR & AXLE CARRIED OUT, NIL FAULT FOUND. AREA CLEANED  OF RESIDUAL FIRE EXT. AGENT. NEW BRAKE AND 	MAIN WHEEL INSTALLED.			2	L	7	2 	4F	4	F	RT	A28NM   	E37NE				 
2003053000095	20030530	00095	CE  	2003	5	30	CA030521006      	1	20030521	G	2750	S3782	BRACKET         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	FLAP PULLEY	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP CABLE IN LT WING AT FLAP PULLEY BRACKET FALL OF THE PULLEY BECAUSE OF THE WRONG SIZE OF PULLEY, PULLEY AND BO	LT SHOULD BE USE ON A/C S/N 185-0238 AND ON.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P25EA	 
2003053000096	20030530	00096	NE  	2003	5	30	CA030521007      	2	20030516	G	8530	114651	EXHAUST ROCKER  			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	CYLINDER	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE CREW NOTICED A SLIGHT VIBRATION IN THE LT ENGINE.  UPON LANDING A VISUAL INSPECTION WAS CARRIED 	OUT AND THE NR 11 CYLINDER WAS FOUND TO BE CRACKED FORE AND AFT ALONG THE EXHAUST ROCKER COVER, FROM THE EAR BACK TO THE	 ROCKER SHAFT.  CYLINDER WAS REPLACED WITH AN O/H UNIT AND THE ENGINE WAS GROUND RUN SERVICEABLE.				2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2003053000097	20030530	00097	CE  	2003	5	30	CA030521008      	1	20030515	G	3244	0773450	TIRE            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RT MLG	BLOWN           	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING THE RT MAIN WHEEL BLEW.  A/C WAS STOPPED SAFELY ON THE RUNWAY AND THEN TOWED OFF ONTO THE NEAREST TAXIW	AY.  AFTER THE RIM WAS INSPECTED AND THE TIRE REPLACED THE A/C WAS DISPATCHED FOR THE NEXT FLIGHT.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003061700072	20030617	00072	NE  	2003	6	17	CA030522001      	2	20030505	G	7532	HTE4500019	VALVE           			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18069	18069							(CAN) DURING THE SCHEDULE  REMOVAL OF THE ENGINE S/N 41063 THE NON-RETURN IP CHECK VALVE WAS FOUND BROKEN AT THE HINGE B	OLT. SPRING AND WASHER WAS ALSO MISSING.  VALVE WAS REPLACED AND ENGINE REPAIR SHOP WAS ADVISED.					2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2003053000098	20030530	00098	EU  	2003	5	30	CA030522002      	1	20030520	G	5240	2242277501	ACCESS DOOR     			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					OIL SYSTEM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT ARRIVED AT THE STATION WITH THE RT ENGINE OIL TANK ACCESS DOOR HALF PORTION BROKEN OFF ANDMISSING. NEW DO	OR WAS INSTALLED. FAN COWL WAS SLIGHTLY DAMAGED BY THE DOOR STRIKING. DAMAGE WAS CONSIDERED ACCEPTABLE AS PER AMM. SUSPE	CT THAT OIL TANK ACCESS DOOR WAS NOT PROPERLY CLOSED AT PREVIOUS STATION.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2003053000099	20030530	00099	EU  	2003	5	30	CA030523003      	1	20030517	G	5610	NP1653115	WINDSHIELD      			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CAPTAINS WINDSHIELD SHATTERED AT 11000 FT.   REPLACED THE WINDSHIELD AND HEAT CONTROLLER.  HEAT CONTROLLER TOTAL O	F WINDSHIELD 8477 HRS  TIME SINCE INST 203 HRS.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003070200056	20030702	00056	EA  	2003	7	2	CA030523004      	2	20030312	G	8520		CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT INSPECTION OIL LEAKAGE WAS OBSERVED FROM RIGHT ENGINE. AFTER CLEAN UP AND FURTHER INVESTIGATION A 1.25 FT CRACK	 WAS FOUND STARTING AT A CRANK CASE SEAM BOLT CLOSE TO THE STARTER AREA. AIRCRAFT WAS GROUNDED AND AN OVERHAULED ENGINE 	INSTALLED.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003070300070	20030703	00070	CE  	2003	7	3	CA030523005      	1	20030521	G	3230	50452112	FORK            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) PILOT REPORTS GEAR WOULD NOT RETRACT ON TAKE OFF.  HE ELECTED TO LEAVE DOWN FOR FLIGHT MAINTAINING PROPER SPEED.ON	 LANDING TRUCKS WERE REQUESTED BUT NO EMERGENCY DECLARED.  LANDING WAS UNEVENTFUL.  WHEN MAINTENANCE INSPECTED GEAR THEY	 FOUND ADJUSTING FORK SHEARED AT THE FIRST THREAD.  MAINTENANCE TRIED TO USE THE SAME PART OFF ANOTHER A/C WHICH WAS IN 	OUR HANGER FOR MAINTENANCE, BUT FOUND IT CRACKED IN THE SAME PLACE.  NEW PART INSTALLED RIGGED AND GEAR SWING CARRIED OU	T AND RELEASED FOR FURTHER FLIGHT.		1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003070300071	20030703	00071	EU  	2003	7	3	CA030526001      	1	20030523	G	7820		BAFFLE          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MUFFLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						L2514551A					(CAN) DUE TO FINDING A BROKEN INTERNAL BAFFLE INSIDE THE NR 1 EXHAUST SILENCER, WE INITIATED AN INTERNAL INSPECTION OF T	HE SILENCER EVERY 100 HR INSPECTION INTERVAL. THIS BAFFLE WAS FOUND TO BE COMPLETELY BROKEN.  THE EXHAUST SILENCER WAS R	EPLACED WITH A REPAIRED UNIT.  IT IS BELIEVED THAT A BACKFIRE UPON STARTUP IS THE CAUSE OF THE BAFFLE DAMAGE AND HEATING	 AND COOLING OF THE EXHAUST SYSTEM.  THE STUDENTS ARE REMINDED TO NOT OVER PRIME THE ENGINES AT START UP.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003071500009	20030715	00009	EU  	2003	7	15	CA030526003      	1	20030521	G	5312		PRESSURE PANEL  			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			37153	37153							(CAN) DURING COMPANY SPECIAL FLEET INSPECTION 13 INCH CRACK DISCOVERED IN THE WHEEL WELL UPPER PRESSURE SKIN ALONG AIRCR	AFT CENTER LINE AT EDGE OF STRINGER BETWEEN FRAME 29 TO 32. MANUFACTURER CONTACTED. DAMAGE REPAIRED AS PER BAE REPAIR IN	STRUCTION HC532H9018.				2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003071500010	20030715	00010	EU  	2003	7	15	CA030526004      	1	20030521	G	5311		PRESSURE PANEL  			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			36866	36866							(CAN) DURING COMPANY SPECIAL FLEET INSPECTION 20 INCH CRACK DISCOVERED IN THE WHEEL WELL UPPER PRESSURE SKIN ALONG AIRCR	AFT CENTER LINE AT EDGE OF STRINGER BETWEEN FRAMES 29 TO 32. MANUFACTURE CONTACTED. DAMAGE REPAIRED AS PER BAE REPAIR IN	STRU CTION HC532H9018.				2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003070200057	20030702	00057	EA  	2003	7	2	CA030526008      	1	20030521	G	3246	L812148	BEARING         			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	WHEEL	SPALLED         	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI OUT, FLT ATTENDANT REPORT SPARKS FROM NR 2 (IB LT ) MLG WHEEL ASSY.  AIRCRAFT RETURNED TO THE GATE, NE	AR GATE AREA NOTICED WHEEL HUB CAP. CREW CONFIRMS THAT DURING WALKAROUND PRIOR TO TAXI WHEEL ASSEMBLY APPREARED NORMAL A	ND HUB CAP ON WHEEL.  AFTER TAXING BACK TO GATE  NR 2 WHEEL ASSEMBLY MISSING HUB CAP , RETAINING NUT & SAFETY HARDWARE S	TILL INTACT/INSTALLED. INVESTIGATION FOUND BOTH BEARINGS FAILED P/N L812148 CODE FY AND P/N L713049 CODE JT . DUE TO THE	 SEVERE HEAT DAMAGE NOTICED TO THE BEARINGS AND MOLTEN MATERIAL, A PRESUMPTION IS MADE THAT THE WHEEL BEARINGS PROBABLY 	FAILED DURING THE PREVIOUS LANDING. WHEEL ASSEMBLY HAD 249 CYCLES SINCE LAST SHOP VISIT , BEARING TIMES UNKNOWN.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003070300054	20030703	00054	CE  	2003	7	3	CA030526010      	1	20030414	G	7722	MS3505929	SWITCH          			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					EGT LIMITER	INTERMITTENT    	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) RT ENGINE EGT LIMITER NOT WORKING, REVERTED TO MANUAL, TTL. SWITCH P/N MS35059-29 WAS FAULTY.  SWITCH P/N MS35059-	29 WAS TAKEN APART AND FOUND TO BE CONTAMINATED.  THE SWITCHES LOCATED BELOW FOUL WEATHER WINDOW WHICH MAY HAVE BEEN LT 	OPEN ON THE GROUND, OR CONTAMINATION MAY HAVE RESULTED FROM A SPILT DRINK.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2003070300055	20030703	00055	SW  	2003	7	3	CA030526011      	1	20030505	G	5511	206020120011	SPAR            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					HORIZONTAL STAB	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACK FOUND ON INBOARD PORTION OF SPAR RUNNING LONGITUDINALLY.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003070300056	20030703	00056	NE  	2003	7	3	CA030526012      	2	20030305	G	7250		ENGINE          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  						FOD             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10369								(CAN) ENGINE DOESN'T CRANK. COMPRESSOR APPEARED LOCKED. STARTER & FCU REMOVED. COMPRESSOR STILL LOCKED. WHILE TRYING TO 	ROTATE COMPRESSOR BY HAND IT EVENTUALLY FREED UP A BIT. IT WOULD ROTATE 1 AND 1/2 TURNS THEN LOCK UP. SUSPECTED FOD IN T	HE COMPRESSOR.  ENGINE WAS REMOVED. IT WOULD ROTATE FREELY IN A HORIZONTAL POSITION BUT LOCK UP IF TILTED FORWARD. MODUL	ES 2/3 WERE REMOVED & SENT FOR INSPECTION. AFTER INSPECTION COWLING & SAND FILTER INSTALLATION,   FOUND POSSIBLE EVIDENC	E OF A MISSING TIE RAP WHICH SECURED WIRING HARNESS FOR P2 SOLENOID ON SAND FILTER. TIE RAP MAY HAVE CHAFED & EVENTUALLY	 BROKE & WAS INGESTED.	1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003071500001	20030715	00001	EA  	2003	7	15	CA030527001      	3	20030521	G	6114		HUB             			BOEING	75    	A75N1       	1380134	CE  	CONT  	R670  	R670*       	17016	SO  	SNSNCH	W96JB	W96JB       	EA  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER WAS FOUND TO BE CRACKED BETWEEN LAMINATIONS, INSIDE THE INTERNAL HUB. MANUFACTURER INDICATES THIS MAY HA	VE BEEN CAUSED BY MOISTURE CONTENT FLUCTUATIONS, WHICH WOULD CAUSE INCONSISTANT PROP TORQUE SETTINGS.THERE WAS NO EVIDEN	CE OF A LOOSE PROP.  PROP WAS ALSO QUITE OLD.  REPLACED WITH NEW.				1	Q	7	1 	3R	3	R	 	A743    	E162	5	N	P170	 
2003070200058	20030702	00058	SW  	2003	7	2	CA030527005      	1	20030526	G	2110	2784142007	LINE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					BLEED AIR	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			31322								(CAN) FLIGHT CREW COMPLAINED OF PRESSURIZATION PROBLEMS. THE CABIN DIFFERENTIAL WAS LOWER THAN NORMAL. UPON INSPECTION O	F THE RT WING AIR CONDITIONING SYSTEM THE FLEXABLE ACCORDION STYLE BLEED AIR LINE FROM THE HEAT EXCHANGER/COOLING TURBIN	E ASSY WAS FOUND BROKEN IN HALF IN TWO PLACES. NO WING OVERHEAT WARNING INDICATIONS WERE WITNESSED BY THE FLIGHT CREW OR	 ANY HEAT DAMAGE FOUND IN WING. NOTHING FOUND IN OR AROUND THE AREA OF THE LINE WOULD HAVE CAUSED THE DAMAGE TO THE LINE	.WE SUSPECT THAT FATIGUE IS THE CAUSE DUE TO YEARS OF HEAT AND VIBRATION.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003070300051	20030703	00051	NE  	2003	7	3	CA030527006      	2	20030512	G	8530		SPARK PLUG      			DOUG  	B26   	B26C        	3200524	WP  	PWA   	R2800 	R280079     	52026	NE  	HAMSTD	23E	23E50       	NE  	CYLINDER HEAD	LOOSE           	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING A TEST FLIGHT AFTER AN ENGINE CHANGE THE LT ENGINE BEGAN TO RUN ROUGH AT CRUISE POWER SETTINGS. AS A PRECAU	TION, THE ENGINE WAS SHUT DOWN AND SECURED. AIRCRAFT LANDED WITHOUT INCIDENT.  INVESTIGATION FOUND ONE SPARK PLUG BECAME	 LOOSE AND BACKED OUT OF CYLINDER HEAD. ALL OTHER SPARK PLUGS FOUND TO BE SECURE. MAINTENANCE CREW BRIEFED.				2	M	7	2 	4R	4	R	 	L34     	5E8	6	C	P603	 
2003070300052	20030703	00052	EA  	2003	7	3	CA030527007      	2	20030526	G	7314		BOLT            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					FUEL PUMP	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING THE FIRST 100 HR INSPECTION THE BOLTS HOLDING THE BOTTOM COVER TO THE PUMP BODY WERE FOUND LOOSE BY SEVERAL	 TURNS.  BOLTS WERE TIGHTENED AND TORQUE SEAL WAS ADDED TO MAKE VISUAL INDICATION OF MOVEMENT. THIS INSTALLATION WOULD B	E BETTER SERVED WITH BOLTS THAT WOULD ALLOW FOR LOCKWIRE.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003071500002	20030715	00002	EU  	2003	7	15	CA030527008      	1	20030527	G	6730		SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					M/R HYD SYS	FAILED          	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN) RESISTANCE IN CYCLIC STICK LT INPUT. FLIGHT CONTROL SYSTEM INSPECTED. CYCLIC STICK FRICTION STACK UP CHECKED OK. A	LL FLIGHT CONTROLS UP TO THE SERVOS CHECK OK. M/R PITCH LINKS DISCONNECTED OK. SERVO AC 67244 SWAPPED AND PROBLEM WENT T	O OPPOSITE SIDE RT. AT GROUND IDLE SIGNIFICANT RESISTANCE FELT. RESISTANCE NOT AS SEVERE AT FLIGHT IDLE. SERVO AIR BLEED	S CHECKED OK. NEW HYD. FILTER INSTALLED. PROBLEM STILL THERE.  REPLACEMENT SERVO REQUESTED			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2003061700032	20030617	00032	EU  	2003	6	17	CA030527010      	1	20030516	G	3411	PC1245	STATIC LINE     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 SYSTEM	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS AT CRUISE FLIGHT (28,000 FT) & AUTOPILOT BEGAN TO CLIMB. AUTOPILOT WAS DISENGAGED AND AIRCRAFT LEVELE	D OFF. NR 1 ALTIMETER AND AIRSPEED BEGAN TO RAPIDLY MOVE TO ZERO. CREW DESCENDED AND LANDED AT NEXT AVAILABLE AIRPORT AS	 NR 2 SYSTEM FUNCTIONED NORMALLY. AIRCRAFT WAS FLOWN VFR BACK TO MAINTENANCE BASE WHERE NR 1 STATIC LINE WAS FOUND PULLE	D OUT OF TEE FITTING IN CABIN SIDEWALL. LINE WAS TOO SHORT AND HAD BEEN FORCED INTO PLACE. LINE REPLACED AND REINSTALLED	 AND TESTED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003070200059	20030702	00059	EA  	2003	7	2	CA030527011      	1	20030429	G	2731		PIN             			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR CONTROL	LOOSE           	W				O				OTHER                   				I			FLT. ATTITUDE INST.       			LD	LANDING        	1			CA											(CAN) PILOT REPORTED THAT HE RAN OUT OF NOSE DOWN ELEVATOR TRIM WITH FLAPS 30 DEGREES. INSPECTED FLAP TRIM INTERCONNECT 	AND FOUND NO FAULTS. INSPECTED ELEVATOR TRIM AND FOUND THAT NOSE DOWN TRIM WAS LIMITED BY A STOP IN THE COCKPIT TRIM WHE	EL. FOUND THAT PIN THAT RIDES IN GROOVE IN TRIM WHEEL & DRIVES TRIM POSITION INDICATOR HAD POPPED OUT AND INTO NEXT GROO	VE. REPOSITIONED IN APPROPRATE LOCATION & OPS CHECK OK. RERIGGED POSITION INDICATOR AND TEST FLEW AIRCRAFT, OPS NORMAL.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003070300066	20030703	00066	EU  	2003	7	3	CA030527012      	1	20030512	G	6730	SC5083	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					LT HYD SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING HYD TEST CYCLIC WENT HARD OVER LT WITHOUT CONTROL INPUT. WHEN HYD FLUID WAS WARM HARD OVER WAS LESS NOTICEA	BLE. WHEN HYD SYSTEM PRESSURE WAS DUMPED, CYCLIC WENT HARD OVER LT. HYD SERVO REPLACED, AIRCRAFT WAS RETURNED TO SERVICE	.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003070300067	20030703	00067	GL  	2003	7	3	CA030527013      	2	20030508	G	7323		DRIVE GEAR      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					GOVERNOR SHAFT	DISCONNECTED    	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) THE EXPOXY HOLDING THE SAFETY CLIP IN PLACE CAME UNBONDED, THEREFORE ALLOWING THE CLIP TO MOVE THUS ALLOWING THE D	RIVE GEAR TO DISCONNECT FROM THE SHAFT.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003070300068	20030703	00068	EU  	2003	7	3	CA030527014      	1	20030526	G	5302	1172213201	SPLICE          			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK ORIGINATING FROM TOOLING HOLE AND PROGRESSING UP VERTICAL AND ACROSS HORIZONTAL LEG OF SPLICE.  SPLICE IS LO	CATED ON LT FORWARD SECTION OF TAILBOOM ATTACH STRUCTURE.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2003070300069	20030703	00069	EU  	2003	7	3	CA030527015      	1	20030526	G	5310	1172213202	SPLICE          			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK ORIGINATING AT TOOLING HOLE AND PROGRESSING HORIZONTALY ACROSS LOWER FLANGE.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2003071500003	20030715	00003		2003	7	15	CA030527016      	4	20030506	G	3497	K22A24	WIRE HARNESS    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STALL WARING	SHORTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) STALL WARNING NR 1 C/B POPPED WITH A PUSHER CAUTION JUST AFTER TAKE-OFF.AIRCRAFT RETURNED TO BASE. C/B COULD NOT B	E RE-SET. POWER WIRE TO TORQUE TRANSDUCER  (KA22A24) FOUND SHORTED FORWARD OF THE OF THE LT EXHAUST STACK, BURNING WIRE 	AND TIE WRAP.  WIRE AND SHIELDING REPAIRED. SYTEM FUNCTION TESTED SATISFACTORY				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003061700021	20030617	00021	CE  	2003	6	17	CA030528001      	1	20030521	G	3710	212CW	PUMP            			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	VACUUM SYS	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) FAILURE OF VACUUM AIR PUMP ON DESCENT DURING UFR OPERATIONS.  VANE FAILURE, DRIVE SHEARED.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003070200060	20030702	00060	WP  	2003	7	2	CA030528002      	2	20030512	G	7200	30728001	ENGINE          			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					NR 1	BIRD INGESTION  	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			C	K	J	F.O.D.                    	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) IN CRUISE FLIGHT AT 33 K FT, DAYTIME, CLEAR SKY, NR 1 ENGINE FUEL OIL PRESSURE LIGHT FLICKERED AND FLUCTUATING OIL	 PRESSURE WAS CONFIRMED ON GUAGE. NR 1 ENGINE WAS SHUTDOWN AND AIRCRAFT DIVERTED FOR REPAIRS.  REPACED 2 FAN BLADES, COR	E INLET STATOR AND CRACKED OIL PRESSURE LINE. ENGINE BORESCOPED, GROUND RUN AND VIBRATION SURVEY C/W SATISFACTORY AND EN	GINE RETURNED TO SERVICE 2003, MAY 15. SUSPECT BIRD STRIKE OCCURRED ON PREVIOUS TAKEOFF BUT NOT NOTICED BY FLIGHT CREW.			2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2003070300036	20030703	00036	NM  	2003	7	3	CA030528003      	1	20030525	G	3234		SELECTOR VALVE  			BOEING	737   	7372T2      	1384491	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE CREW REPORTED THE NOSE GEAR DID NOT UNLOCK OR EXTEND ON THE INITIAL EXTENSION ATTEMPT. THE GEAR HA	NDLE WAS RECYCLED AND THE NOSE GEAR CAME DOWN NORMALLY.  IT WAS DECIDED TO OPERATE THE AIRCRAFT UNDER A FLIGHT PERMIT (F	ERRY PERMIT)  FOR TROUBLESHOOTING. RECTIFICATION UPON ARRIVAL INTO MAINTENANCE CONDUCTED SEVERAL GEAR SWINGS ALONG WITH 	RIGGING AND ROUTING CHECKS OF THE LANDING GEAR CONTROL SYSTEM.THE FAULT COULD NOT BE DUPLICATED. DUE TO THE HISTORY ASSO	CIATED WITH THE DEFECT, IT WAS DECIDED TO REPLACE LANDING GEAR SELECTOR VALVE FOR TROUBLESHOOTING.		2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2003071500004	20030715	00004	SW  	2003	7	15	CA030528004      	1	20030513	G	5347	206031103043	SEAT TRACK      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 8 INCH CRACK RUNNING LONGITUDINALLY IN BEND OF ANGLE. TOP FORWARD CORNER OF AFT CABIN SEAT STRUCTURE.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003071500005	20030715	00005	SW  	2003	7	15	CA030528005      	1	20030512	G	5302	206032308103S	FRAME           			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN AFT FUSELAGE FRAME.  CRACK APPROXIMATELY .3750 INCH IN LENGTH LOCATED ABOVE UPPER RT TAILBOOM ATTAC	H BOLT MOUNTING BOLT HOLE. FOUND DURING 1200 HR TAILBOOM INSPECTION AND ONLY VISIBLE WITH 10X POWER GLASS.  FRAME REPLAC	ED WITH NEW.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003071500006	20030715	00006	SW  	2003	7	15	CA030528006      	1	20030408	G	6320	206040532005	CASE            	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TRANSMISSION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BMC00527					(CAN) 1 SPLINE, ADJACENT TO 3 REWORKED SPLINES HAS SUSPECTED CRACK, IMPACT DAMAGE AND CORROSION PITTING OVER 40 PERCENT 	LENGTH OF SPLINE.  2ND ADJACENT SPLINE,  ALSO HAS SUSPECTED CRACK AND CORROSION PITTING.  CRACKS NOT IDENTIFIED ON INITI	AL OH NDI (  FPI).  UPPER CASE SCRAPPED.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003061700022	20030617	00022	CE  	2003	6	17	CA030528007      	1	20030520	G	8011	PM2401H	STARTER         			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER FAILED AFTER MINIMAL USE.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003070200062	20030702	00062	EU  	2003	7	2	CA030528010      	1	20030423	G	5312		PRESSURE PANEL  			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG WW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			32144	32144							(CAN) DURING A 'C' CHECK INSPECTION A 13 INCH CRACK DISCOVERED IN THE WHEEL WELL UPPER PRESSURE SKIN ALONG AIRCRAFT CENT	ER LINE AT EDGE OF STRINGER BETWEEN FRAMES 29 TO FRAME 32. MANUFACTURER CONTACTED. DAMAGE REPAIRED IAW MFG REPAIR INSTRU	CTION HC532H9018.				2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003070300038	20030703	00038	SO  	2003	7	3	CA030528011      	1	20030502	G	5330		SKIN            			EMB   	120   	EMB120ER    	3260203	SO  	PWA   	118   	PW118       	 	NE  	HAMSTD	14RF	14RF9       	NE  	FUSELAGE	LIGHTNING STRIKE	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			17485	17485							(CAN) DAMAGE CAUSE TO AIRCRAFT AND EQUIPMENT DUE TO LIGHTNING STRIKE. MFG RECOGNIZED THE LOWER FUSELAGE COMPOSITE PANELS	 ATTACHING THE ROTARY BEACON DO NOT HAVE ADEQUATE BONDING AND A SERVICE BULLETIN IS UNDER EVALUATION TO PROVIDE AN APPRO	PRIATE BONDING.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2003070300039	20030703	00039	CE  	2003	7	3	CA030528012      	1	20030519	G	3244	0316138	WHEEL           			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					NLG	UNBONDED        	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) AT LIFT OFF PILOT HEARD AND FELT STRONG VIBRATIONS ON THE NOSE WHEEL. HE DECLARED AN EMERGENCY AND RETURNED TO BAS	E. DURING THE INVESTIGATION FOUND NOSE WHEEL OUT OF BALANCE. NOSE WHEEL ASSY WAS STRIPPED MAY 27/03 AND FOUND BALANCE PA	TCH GLUED TO TIRE UNBONDED WHICH CAUSE THE VIBRATION, THE PATCH WEIGHT IS 1 OUNCE.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2003070300040	20030703	00040		2003	7	3	CA030528013      	4	20030527	G	2565	101656305	SLIDE           			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					LT WING	DEPLOYED        	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) LT O/H WING CHUTE WAS ACCIDENTALLY DEPLOYED BY FLT OPS DURING A TRAINING SESSION. THE CHUTE DID NOT DEPLOY COMPLET	ELY. THE LOWER SECTION OF THE CHUTE WAS PREVENTED FROM COMPLETE DEPLOYMENT BY THE IB SIDE.  CONFIRMED, OPERATOR NEVER CH	ANGED OR REMOVED THIS CHUTE, IT'S A NEW AIRCRAFT SINCE 2001 CHUTE MFR DATE 03/01 PACK DATE 06/15/01.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2003082200093	20030822	00093	NE  	2003	8	22	CA030528014      	2	20030512	G	7421	9550168760	IGNITER         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) GENERAL INFORMATION LETTER NR 02-01 (FEB18, 2002), SERVICE LETTER 2171/02/ARL1/66 (FEB12, 2002), AND SERVICE LETTE	R 2223/03/ARL/173 (APRIL02, 2003), THESE PART NUMBER IGNITERS ARE FAILING IN SERVICE, USUALLY CAUSING EXTENSIVE ENGINE D	AMAGE (WITH FIRST HAND KNOWLEDGE OF THIS).  IT IS MFG RECOMMENDATION THAT THESE IGNITERS BE REMOVED FROM SERVICE TO PREV	ENT THIS ENGINE DAMAGE FROM OCCURING, AND THEY HAVE BEEN REPLACING THEM ON WARRANTY. ON THE ENGINE LISTED ABOVE, RECEIVE	D NEW FROM MFG FEBRUARY 2003, THESE PART NUMBER IGNITERS WERE FOUND TO BE INSTALLED DURING A ROUTINE VISUAL EXAMINATION 	OF THE ENGINE TECHNICAL LOGS.  THEY WERE REMOVED PRIOR TO FURTHER FLIGHT AND RE PLACEMENT IGNITERS INSTALLED.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003072100049	20030721	00049	SO  	2003	7	21	CA030528015      	1	20030528	G	1430	MS24665143	COTTER PIN      			CURTIS	C46   	C46FAIRLIFT 	       	SO  	PWA   	R2800 	R2800*      	52026	NE  					FUSELAGE	MISMANUFACTURED 	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE COTTER PINS RECIEVED FROM AIRCRAFT PARTS INTERNATIONAL ARE FAULTY AROUND THE HEAD. THE COTTER PINS ARE MANUFAC	TURED BY WESTERN WIRE. WE RECIEVED THEM IN MARCH 2003. WHEN I CALLED THE SUPPLIER AND EXCHANGED LOT NUMBERS, HE HAD A DI	FFERENT LOT NUMBER OF COTTER PINS THAT DID THE SAME THING, BREAK AT THE LOOP.				2	L	7	2 	4R	4	R		3A2     	5E8				 
2003061700051	20030617	00051	EA  	2003	6	17	CA030529001      	2	20030430	G	8520	13F17786	CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	BROKEN          	W				E	O			ENGINE SHUTDOWN         	OTHER                   			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT,  THE RT ENGINE STOPPED. THE PILOTS TRIED TO RESTART THE ENGINE WITHOUT SUCCESS. WHILE SEARCH	ING THE CAUSE OF THE ENGINE STOPPAGE, WE DISCOVERED THAT THE VALVES WERE NOT WORKING. WE REMOVED THE ENGINE AND SENT IT 	FOR OVERHAUL, ON DISASSEMBLY THEY FOUND THE CRANKSHAFT BROKEN. ACCORDING TO THE OVERHAUL FACILITY DETONATION WOULD HAVE 	CAUSED THE CRACK. THE ENGINE WAS REPAIRED AND REINSTALLED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003061700053	20030617	00053	SO  	2003	6	17	CA030529003      	1	20030523	G	5730		STITCHING       			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  					RT WING RIBS	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RIB STICHING BROKEN MOST RIBS RT WING RECORDS. ONLY GO BACK TO 1978 NO RECORD OF REPLACEMENT AT THAT TIME. FABRIC 	TESTED GOOD. (WING RESTITCHED.)					1	H	7	1 	3O	3	O	 	1A2     	E274				 
2003070200063	20030702	00063	WP  	2003	7	2	CA030529004      	1	20030526	G	5270	H2028B	SWITCH          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					PAX DOOR	DIRTY           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE THE AFT CABIN DOOR OPEN LIGHT ILLUMINATED. AIRCRAFT RETURNED TO AIRPORT FOR INVESTIGATION. DOOR FR	AME AND SEAL CHECKED, NO DEFECT. DOOR SWITCH INSPECTED AND CLEANED. AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2003070300031	20030703	00031	EA  	2003	7	3	CA030529005      	2	20030323	G	7200		ENGINE          								PWA   	PT6   	PT6A28      	 	EA  						FAILED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CA											(CAN) ENG WAS REMOVED FROM WING AFTER A/C (ON LANDING) SKIDDED OFF END OF RUNWAY INTO MUD. ENG BEEN SENT FOR SUDDEN STOP	PAGE. ENG WAS DAMAGED IN ACCIDENT. MOST SERIOUS DAMAGE WAS FOUND IN PWR SEC BUT BROKEN FUEL PUMP MNTG FLANGE INDICATES T	HAT GG SEC HAD SOME SERIOUS LOADS/STRESS.  ENG MOSTLY PWR SEC WAS DAMAGED DURING INCIDENT.  ENERGY OF IMPACT WAS REALIZE	D ON  EXHAUST DUCT THROUGH ITS OUTER SKIN DEFORMATION WHILE OTHER POWER SEC INTERNAL COMPONENTS WERE NOT DAMAGED DESPITE	 FACT THAT PT SECTION WAS MOVED REARWARD INTO HOT SECTION. ALL POWER, HOT SECTION ELEMENTS, EXCEPT EXHAUST DUCT, WERE RE	PAIRABLE.  GG SECTION DID NOT HAVE NOTICEABLE DAMAGE ATTRIBUTED TO INCIDENT. UNSERVICEABLE PARTS WERE REPLACED.						4	T			E4EA				 
2003070300032	20030703	00032	EA  	2003	7	3	CA030529006      	2	20030323	G	7200		ENGINE          								PWA   	PT6   	PT6A28      	 	EA  						FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ENGINE WAS REMOVED FROM WING AFTER A/C (ON LANDING) SKIDDED OFF END OF RUNWAY INTO MUD. ENGINE HAS BEEN SENT FOR S	UDDEN STOPPAGE INVESTIGATION AND REPAIR. ENGINE WAS DAMAGED IN ACCIDENT. MOST SERIOUS DAMAGE WAS FOUND IN POWER SECTION 	BUT BROKEN FUEL PUMP MOUNTING FLANGE INDICATED THAT GG SECTION HAD SOME SERIOUS LOADS/STRESS. ENERGY OF IMPACT WAS REALI	ZED ON EXHAUST DUCT THROUGH ITS OUTER SKIN DEFORMATION WHILE OTHER POWER SECTION INTERNAL COMPONENTS WERE NOT DAMAGED DE	SPITE FACT PT SECTION WAS MOVED REARWARD IN TOWARDS THE HOT SECTION. ALL POWER AND HOT SECTION ELEMENTS EXCEPT EXHUAST D	UCT WERE REPAIRABLE.  ENGINE WAS REPAIRED IAW MM, LIGHT OVERHAUL SECTION.						4	T			E4EA				 
2003070300033	20030703	00033	SW  	2003	7	3	CA030530001      	1	20030526	G	6330	212030104101	LINK            	BELL        	212030104101	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					XMSN MOUNT	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) AFTER THE FLIGHT AN INSPECTION OF THE AIRCRAFT IT WAS DETERMINED THAT PART OF THE LIFT LINK HAD BROKEN OFF NEAR TH	E UPPER STAKED BEARING BOSS.  THE CAUSE OF THE BROKEN PIECE UNDETERMINED AT THIS TIME, INVESTIGATION IS ON GOING.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003070200064	20030702	00064	NM  	2003	7	2	CA030530004      	1	20030501	G	5522		SKIN            			AIRBUS	A319  	A319114     	3930350	NM  	GE    	CFM56 	CFM565A     	13802	NE  					RT ELEVATOR	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS WAS A PREVIOUS INSPECTON CALLED ON A320 FLEET.  THIS IS AN UNSCEDULED INSPECTION OF THE LT ELEVATOR SURFACE O	N THE A319.  THE INSPECTION ON THE A320 FLEET WAS 55-1024 THE ELEVATOR IN QUESTION WAS DECLARED BER (BEYOND ECONOMICAL R	EPAIR) AND HAD TO BE REPLACED.  AIRCRAFT TOTAL TIME 17,948.   NOTE: SAME AS A 320 EXCEPT THE 319 DOES NOT HAVE THE AD AP	PLIED TO IT.			2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003070300037	20030703	00037	NM  	2003	7	3	CA030530005      	1	20030528	G	2751	85711423101	BRACKET         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TORQUE SENSOR	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) AT THE END OF THE LANDING ROLL THE FLAPS WERE SELECTED UP. FLAPS TRAVELLED TO APPROX 5 DEG AND STOPPED. FLAP DRIVE	 ANNUN ILLUMINATED, FLAPS WOULD NOT MOVE UP OR DOWN. MAINT WAS DISPATCHED AND DISCOVERED SECONDARY FLAP DRIVE CABLE INTO	 LT FLAP TORQUE SENSOR, SHEARED.  LT FLAP TORQUE SENSOR BRACKET WAS FOUND BROKEN THROUGH ON TOP FOLD AND CRACKED ALONG L	OWER FOLD. SOME MINOR LOOM DAMAGE OCCURED DUE TO THRASHING OF ADRIFT DRIVE CABLE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003070200098	20030702	00098	GL  	2003	7	2	CA030530006      	3	20030526	G	6114	D4883	NUT             	MCAULY      		BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						780950					(CAN) CUSTOMER COMPLAINED OF SPINNER CRACKING. OVER HAULED BOTH PROPS AS A PRECAUTIONERY.  CHECKED PROP BEFORE DISASSEMB	LY. TRACK, ANGLES, BALANCE WITHIN SPEC. FOUND HUB CRACKED IN THREADS. MATE TO PROBLEM PROPELLER. 1 CRACKED BLADE NUT.					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2003070300024	20030703	00024	NE  	2003	7	3	CA030530010      	2	20030519	G	7321	430128807	FUEL CONTROL    			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) NO FUEL COMING OUT THE FUEL CONTROL UNIT. IT HAPPENED ON THE FIRST START ATTEMPT, IN THE MORNING. INTERNAL FAILURE	 OF FCU SUSPECTED, SINCE ALL FUEL LINES HAVE BEEN BLED FROM AIR. PREVIOUS FLIGHTS HAD NOT REVEALED ANY FLUCTUATIONS OR P	ARAMETERS PROBLEMS. FCU HAS BEEN REPLACED ON 22 MAY 2003. AND STARTS WERE AS NORMAL AS IT SHOULD. THEN, INTERNAL FCU FAI	LURE WILL HAVE TO BE INVESTIGATED BY THE OVERHAUL FACILITY OR MANUFACTURER.			1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2003070300025	20030703	00025	EA  	2003	7	3	CA030530011      	1	20030515	G	5610	601R3303311	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING THE FIRST PRODUCTION FLIGHT TEST AT 8,000 FT/250 KTS AND APPROXIMATELY 2.5 PSID IN DESCENT. THE LT SIDE WIN	DOW SHATTERED.					2	L	7	2 	4F			RT	A21EA   					 
2003070200099	20030702	00099	EU  	2003	7	2	CA030530012      	1	20030527	G	6320		GEARBOX         			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) MAIN TRANSMISSION CHIP LIGHT IN CRUISE, CHIP DETECTORS PULSED UNSUCCESSFULLY, PILOTS LANDED A/C. CHIP DETECTORS IN	SPECTED AND FOUND .1 FT  X .05 FT FERROUS CHIP WITH SEVERAL FERROUS FLAKES.  FILTERS INSPECTED, FOUND CONTAMINATED WITH 	FERROUS FLAKES. TRANSMISSION REMOVED FOR REPAIR.				1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2003070200065	20030702	00065	EA  	2003	7	2	CA030530014      	1	20030528	G	2613	GG670801021	LOOP            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					BLEED SENSING	FAILED          	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CL	CLIMB          	1			CA											(CAN) CREW EXPERIENCED A LT BLEED DUCT WARNING MSG ON CLIMB OUT THRU 23,000 FT.  LT PACK WENT OFF LINE & APPROX. 30 SECO	NDS LATER, RT PACK WENT OFF LINE.  CREW WERE UNABLE TO RESET THIS CONDITION IN AIR. AC DIVERTED. TROUBLESHOOTING, MAINT 	LT BLEED LOOP B HIGH PRESS OUTPUT(MT138) FOUND FAILED/OPEN CIRCUIT.  LT BLEED LOOP ACM (MT140) FOUND TOUCHING BLEED DUCT	 IN TWO AREAS.  A BLEED LEAK WAS FOUND BETWEEN LT ACM & PRE-COOLER. LOSS OF PRESS IS BELIEVED TO BE DUE TO LT BLEED DUCT	 WARNING WHICH REMAINED CONSTANT FOR MORE THAT 30 SECONDS RESULTING IN AUTOMATIC CLOSING OF L AND R ENGINE BLEED SOURCES	.FOLLOWING REPLACEMENT OF FAILED LOOPS & RECTIFICATION OF LEAK, AC FLT TESTED & DECLARED SERVICEABLE.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003070300022	20030703	00022	CE  	2003	7	3	CA030602001      	1	20030530	G	2752	14601007	CONTROL CABLE   			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	FLAP ACTUATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER RECEIVING SDR ALERT AL-2003-05 AN INSPECTION WAS CARRIED OUT ON OUR 337G. TWO CABLES ON BOTH SIDES WERE FOUN	D DAMAGED. THE DAMAGE WAS LOCATED EXACTLY IN THE SAME LOCATION AS MENTION IN THE ALERT IE AROUND THE SHARP BEND OF THE B	ELLCRANK. ALL CABLES HAD TO BE REMOVED TO SEE THE DAMAGE.HAD THEY NOT THE DAMAGE WOULD OF WENT UNNOTICED. BOTH SETS OF C	ABLES WERE REPLACED WITH SERVICEABLE UNITS.			1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2003070300021	20030703	00021	EU  	2003	7	3	CA030602005      	1	20030523	G	1430	LN93556X32	BOLT            		BO105       	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					HYD PACK	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLYING WITH FLEET CAMPAIGN NOTICE 351-73-20-12 IT WAS FOUND THAT THE BOLT CONNECTING THE TWO NR 2 GOVERNO	R CABLES TOO THE HYD PACK WAS TOO SHORT, ONLY ONE THREAD WAS SHOWING THROUGH THE ANCHOR NUT. A NEW BOLT WAS INSTALLED AN	D THE AIRCRAFT WAS RETURNED TO SERVICE.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003070300035	20030703	00035	CE  	2003	7	3	CA030602008      	1	20030527	G	3000	9091009913	LINE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ANTI ICE SYS	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING INSPECTION THE LT AND RT ENGINE SHORT ANTI-ICE FLEX TUBES WERE FOUND TO BE CRACKED. THERE WAS NO EVIDENCE O	F AN EXHAUST LEAK INSIDE THE COWLING. THE TUBES WERE CRACKED APPROX. HALF OF THEIR CIRCUMFERENCE. CRACKED TUBES WERE REP	LACED. LT TUBE TTSN 351 HOURS. RT TUBE TTSN 44 HOURS.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003070300008	20030703	00008	NM  	2003	7	3	CA030602010      	1	20030529	G	3240	50841	SHUTTLE VALVE   			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	BRAKE SYSTEM	BROKEN          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) NUMBER ONE BRAKE ASSY WAS LEAKING AT PISTON (DUE TO AN O-RING PROBLEM).  THE NR 1 SHUTTLE VALVE WAS NOT OPERATING 	PROPERLY CAUSING NR 2 HYDRAULIC SYSTEM QUANTITY DROP TO ZERO AND NR 1 HYD SYSTEM DROP TO 1 QUART CAUSING MANY SYSTEM FAI	LURE. THAT PROBLEM IS KNOWN BY THE MANUFACTURER AND A SB EXIST TO CORRECT THE PROBLEM. AN AD IS ALSO IN A DRAFT PROCESS.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003070300009	20030703	00009		2003	7	3	CA030603005      	4	20030602	G	2311	24700032	AUDIO PANEL     			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	UHF SYSTEM	MISINSTALLED    	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) CREW REPORTED BOTH VOR SYSTEMS WERE NOT FUNCTIONING COMPLETELY. VOR AUDIO SIGNAL COULD BE PICKED UP AND TO/FROM FL	AG WORKED. INDICATOR NEEDLES WOULD NOT DEVIATE FROM CENTER. COMPONENTS FAILED TO DETERMINE SOURCE OF PROBLEM. A/C WAS SE	NT TO FACILITY WHERE THEY DETERMINED THAT AUDIO PANEL DID NOT HAVE RELAYS INSTALLED FOR AUTOPILOT.  IT WOULD APPEAR THAT	 AUDIO PANEL WAS DIFFERENT FOR A/C  WITH FACTORY INSTALLED AUTOPILOTS.  AUDIO PANEL DOES NOT LOOK DIFFERENT FROM  FRONT,	  NO DISTINGUISHING PLACARDS TO WARN THAT UNIT IS FOR AUTOPILOT EQUIPPED MODELS ONLY. ALSO, NONE OF THE UNITS WE TRIED W	ERE SERIALIZED. RESULT WAS THAT PROPER AUDIO PANEL WAS INSTALLED FOR A/C & ALL RELATED SYSTEMS CHECKED SERVICEABLE.	1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003070300010	20030703	00010	CE  	2003	7	3	CA030603006      	1	20030529	G	3242	1338932	STATOR          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE ASSY	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) A/C WAS TAXIING TO POSITION TO PARK ON APRON WHEN IT HAD AN UNCOMMANDED BRAKING ACTION ON LT SIDE OF A/C. FLIGHT C	REW SHUT DOWN AS NORMAL AND INVESTIGATED PROBLEM. UPON VIEWING LT BRAKE, NOTICED PIECES OF BRAKE STICKING OUT AND REASON	 FOR BRAKE TO JAM.  ENG FLEW UP WITH PARTS, FOUND PIECES WERE PARTS OF IB STATOR.  BRAKE WAS CHANGED, NO OTHER DAMAGE TO	 A/C WAS NOTED. UPON INVEST OF BRAKE ASSY, IT WAS NOTED THAT IB STATOR BROKE INTO 4 PIECES. SOME PIECES HAD JAMMED BETWE	EN TORQUE PLATE ASSY,  LINING CARRIER ASSY (ROTOR), CAUSING BRAKE TO JAM AND ALSO CAUSING DAMAGE TO TORQUE PLATE ASSY.  	BRAKE UNIT WAS STAMPED WITH 'SB' INDICATING COMPLIANCE WITH SB550-32-41 AND STATOR WAS STAMPED WITH 'CHGC' AFTER PN.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003070300011	20030703	00011	CE  	2003	7	3	CA030603007      	1	20030528	G	3230	08421022	BELLCRANK       			CESSNA	310   	T310P       	2074240	CE  	CONT  	O520  	TSIO520B    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG WW	BROKEN          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) WHEN GEAR WAS SELECTED UP AFTER TAKE OFF A LOUD SNAP WAS HEARD THE RED GEAR LIGHT WAS ON. WHEN GEAR WAS SELECTED D	OWN THE 3 GREEN GEAR LIGHTS WAS OBTAINED. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. FOUND BROKEN IDLER BELLCRANK.  M	AINTENANCE IS CHECKING RIGGING AND ANY OTHER CAUSES.				1	L	7	2 	3O	3	O	 	3A10    	E8CE	5	C	P22EA	 
2003070200075	20030702	00075	SW  	2003	7	2	CA030603009      	1	20030131	G	5310	205030712037	ANGLE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK IS IN ANGLE ONLY, NOT FITTING.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003070300012	20030703	00012	SW  	2003	7	3	CA030603010      	1	20030131	G	5302	212030156047	BULKHEAD        			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAIL BOOM ATTACH BULKHEAD AT STA 243.937,  P/N 212030156047.  CRACK UNDER 1 INCH LENGTH.   BULKHEAD REPLACED WITH 	NEW.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003070300013	20030703	00013	CE  	2003	7	3	CA030603011      	1	20030529	G	2752	503801536	DRIVE GEAR      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLAP ACTUATOR	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING TRAINING FLIGHT, CREW WAS PERFORMING (TOUCH AND GO). AFTER TAKEOFF, CREW RETRACTED FLAPS AND SYS C/B POPPED	. INDICATIONS REVEALED THAT RT FLAPS HAD A STAGGER. CREW DECIDED TO DO A FLAPLESS LANDING. ON GROUND FLAP EXT REVEALED T	HAT TARGET FLAP (RT IB) REMAINED UP WHILE OTHER THREE CAME DOWN. FLAP MOTOR RAN TILL C/B POPPED. INVESTIGATION REVEALED 	THAT LOCK PIN RETAINING NUT ON 90 DEGREE DR ADAPTER, ON FLAP ACT (RT IB), FOR TARGET FLAP HAD BACKED OFF AND PIN GOT DIS	ENGAGED FROM JACK GROOVE.  90 DEGREE DR HSG MOVED AWAY FROM JACK AND ALLOWED BEVEL GEAR TO DISENGAGE. 90 DEGREE DR ADAPT	ER ON RT IB ACTUATOR WAS REPLACED. A FLEET WIDE INSPECTION WAS CARRIED OUT FOR SECURITY OF NUT IN QUESTION.	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003070300014	20030703	00014	EA  	2003	7	3	CA030603012      	1	20030602	G	2421	755469B	IDG             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					AC GENERATOR	MAKING METAL    	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) IDG 2 CAUTION MSG POSTED WHILE IN CRUISE.  LT ENGINE GENERATOR ALREADY DEFERRED.  AIRCRAFT DIVERTED, DECLARED AN E	MERGENCY AND LANDED WITHOUT FURTHER INCIDENT.  MTCE REPLACED IDG NR 2 AND OPS CHECKED SERVICEABLE.  LEFT ENGINE GENERATO	R REMAINED DEFERRED.  AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003070300018	20030703	00018		2003	7	3	CA030603013      	4	20030529	G	2215	6288713001	DOWEL PIN       			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					SERVO CONTROL	SHEARED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED THAT WHEN AUTOPILOT WAS DISCONNECTED ON APPROACH ELEVATOR CONTROL WAS VERY HEAVY. PILOT ASKED CO-PI	LOT TO CONFIRM. BOTH WERE IN AGREEMENT THAT AIRCRAFT WAS VERY HEAVY ON THE PITCH CONTROL. AN UNEVENTFUL LANDING WAS COMP	LETED WITH BOTH PILOTS FLYING AIRCRAFT DUE TO HEAVINESS OF CONTROLS.  ONCE ON GROUND, IT WAS AGAIN CONFIRMED THAT ELEVAT	OR CONTROL FELT HEAVY.  NOISE COULD BE HEARD WHEN ELEVATOR CONTROL WAS MOVED. NOISE WAS ISOLATED TO ELEVATOR AUTO PILOT 	SERVO, WITH SERVO MOTOR REMOVED CAPSTAN DRIVE GEAR DOWELS (QTY 6) WERE FOUND SHEARED. THE ELEVATOR SERVO MOUNT WAS REPLA	CED AND THE ELEVATOR CONTROL SYSTEM INSPECTION WAS COMPLETED FROM NOSE TO TAIL WITHOUT ANY OTHER ANOMALY FOUND.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003061700055	20030617	00055	EA  	2003	6	17	CA030604001      	2	20030601	G	8530		VALVE           			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	CYLINDER  HEAD	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) PILOT REPORTED HEARING A BANG DURING CLIMB, FOLLOWING BY PARTIAL POWER LOSS AND VIBRATION WAS FELT.  AN EMERGENCY 	WAS DECLARED AND AIRCRAFT RETURN FOR AN UNEVENTFUL LANDING.  INITIAL INVESTIGATION REVEALED NR 3 CYLINDER HAS A VALVE HE	AD SEPARATED AND IS STICKING OUT OF BOTTOM SPARK PLUG HOLE AREA. FURTHER DETAIL WILL BE SUBMITTED UPON ENGINE TEARDOWN.				1	H	7	1 	3O	3	O	 	A20CE   	1E10	5	C	P7EA	 
2003070200076	20030702	00076	CE  	2003	7	2	CA030604002      	1	20030520	G	7830	AE1009195G0130	HOSE            	ROHR        		CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D1      	52060	NE  					THRUST REVERSER	RUPTURED        	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						3688					(CAN) WHILE PREPARING TO REFUEL THE AIRCRAFT, PILOT NOTED A LARGE QUANTITY OF HYDRAULIC FLUID ON THE RT ENGINE/THRUST RE	VERSER AREA. THE AFT HYDRAULIC HOSE CONNECTING THE TAIL ROTOR TO THE PYLON HAD BURST AT APPROXIMATELY MID LENGTH. (THIS 	IS THE AREA WHERE THE HOSE MAKES A 90 DEGREES TURN.) THE CREW HAD NO INDICATION OF THE PROBLEM DURING LANDING AND TAXI.				2	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2003070300015	20030703	00015	CE  	2003	7	3	CA030604003      	1	20030517	G	3233	99810057652	ACTUATOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) INSPECTION OF LT MAIN LANDING GEAR ACTUATOR P3 99-810057-652 S NR 89-1002 FOLLOWING THE OCCURENCE REVEALED THAT TH	E ACME THREADS IN THE ACTUATOR WERE STRIPED. THE UNIT WAS REPLACED WITH AN OVERHAULED ACTUATOR AS WAS THE RIGHT HAND ACT	UATOR AS A PRECAUTIONARY MEASURE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003070300016	20030703	00016	CE  	2003	7	3	CA030604004      	1	20030520	G	5753	50160020	BUSHING         			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	TE FLAP	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT WAS ON A 1ST PHASE 200 HOUR INSPECTION DURING WHICH A VISUAL AND OPERATIONAL CHECK OF THE FLAPS WAS M	ADE. AT THIS TIME IT WAS NOTICE THAT THE FLAPS DID NOT OPERATE SMOOTHLY. A CLOSER LOOK AND REMOVAL OF THE FLAPS REVEALED	 THAT BUSHINGS PN 50-160020 WAS SEIZED IN BOTH INBOARD AND OUTBOARD FLAPS BOTH SIDES. THE FLAPS WERE VERY DIFFICULT TO R	EMOVE AS ALL THE HARDWARE WAS SEIZED IN THE BUSHINGS.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2003070300017	20030703	00017	NE  	2003	7	3	CA030604005      	2	20030528	G	8520	519589	INSERT          								PWA   	R2800 	CA3         	52026	NE  					ENGINE CADE	BLEW OUT        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	K	E	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	VIBRATION/BUFFET          	CR	CRUISE         	1			CA											(CAN) IN FLIGHT, NOSE CASE PLUG INSERT BLEW OUT PUMPING ENGINE OIL OVERBOARD. ENGINE WAS SMOKING AND OIL STREAMING NECES	SITATED ENGINE SHUT DOWN, PROP FEATHER, AND AIRCRAFT RETURNING TO AIRPORT. NOSE CASE REPLACED WITH A SERVICEABLE UNIT.										4	R			E231				 
2003070300006	20030703	00006	GL  	2003	7	3	CA030604006      	3	20030522	G	6111	FC84754	BLADE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	CORRODED        	W				O				OTHER                   				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER RECEIVED ON 22 MAY 2003, MODEL HC-E2YK-2B/FC847504 REMOVED FOR INSPECTION DUE TO EXCESSIVE ROTATIONAL BL	ADE MOVEMENT. A DECISION WAS MADE TO OVERHAUL THE PROPELLER. VISUAL INSPECTION ON ONE BLADE REVEALED EXCESSIVE CORROSION	 AT THE BLADE BEARING AREA. BLADE KNOB OF BLADE WAS WORN BEYOND LIMITS, BEARINGS CORRODED, PITCH CHANGE FORK AND BLOCKS 	WORN. ALL OTHER PARTS SUCH AS HUB ASSEMBLY, CYLINDER, PISTON, ETC. FOUND TO BE IN NORMAL CONDITION.  BLADE FAILURE MOST 	LIKELY WOULD HAVE OCCURRED IN THE NEAR FUTURE DUE TO  BLADE KNOB FAILURE OR CORROSION ON BLADE SHANK RADIUS AREA.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2003061700057	20030617	00057	EA  	2003	6	17	CA030604007      	2	20030526	G	7322	10S135	CARBURETOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) ACCELERATER DISCHARGE TUBE IN THE CARBURETOR VENTURI BROKE OFF, IT WAS SUCKED UPTO THE THROTTLE PLATE AND APPARENT	LY JAMMED THE THROTTLE AT 2,00 RPM. PILOT COULD NOT ADJUST POWER UP OR DOWN. THE AIRCRAFT WAS FLOWN TO THE AIRPORT, ENGI	NE WAS SHUT DOWN AND A GLIDE TO LANDING WAS EXECUTED. AFTER TOUCHDOWN ENGINESTARTED AND RAN NORMALLY. IT APPEARS THE DIS	CHARGE TUBE FELL DOWN INTO THE INTA KE AIR BOXWHEN THE ENGINE WAS SHUT DOWN DUE TO NO AIRFLOW IN THE VENTURI. THIS ALLOW	ED THE THROTTLE PLATE TO WORK NORMALLY FOR THE TAXI. THE TUBE WAS FOUND LYING IN THE AIRBOX BY THE CARB AT FLAPPER.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003070200077	20030702	00077	GL  	2003	7	2	CA030604008      	3	20030604	G	6114	A2202	BEARING         	HARTZL      												HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA									DJ11708A		(CAN) UPON DISASSEMBLIED OF THE PROPELLER IT WAS NOTED THAT ALL THREE OF THE INBOARD THRUST RACES WERE BADLY DENTED. IT 	WAS ALSO NOTED THAT THE PC ROD WAS WORN THROUGH THE HARD CHROME SURFACE.THE BEARINGS, ROD, BALLS, AND ALL THE OTHER NECE	SSARY PARTS WERE REPLACED AND THE REPAIR WAS COMPLETED. BEARINGS P/N A2202, PITCH CHANGE ROD PN B2491-4S														5	C	P33EA	 
2003070200112	20030702	00112	CE  	2003	7	2	CA030604009      	1	20030507	G	2720	505243263	RUDDER PEDAL    			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCA3V	PHCA3VF2    	GL  	COCKPIT	WORN            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER FINDING A BROKEN RUDDER PEDAL, AN INSPECTION WAS CARRIED OUT ON THE OTHER A/C.  ON ONE OF THE AIRCRAFT, THE 	ATTACHMENT POINT FOR THE RUDDER PEDAL WAS FOUND EXCESSIVELY WORN IN THE SAME LOCATION AS THE BROKEN PEDAL FOUND ON THE O	THER AIRCRAFT.  INSPECTING THIS ATTACHMENT PROPERLY CAN BE ACCOMPLISHED BY REMOVING THE ATTACHMENT HARDWARE AND INSPECTI	NG THE PIVOT POINTS. THE DESIGN OF THE RUDDER PEDAL AND ITS ATTACHEMENT TO THE BRAKE MASTER CYLINDER CAUSES THE PERSON I	NSPECTING THE PEDAL TO ASSUME THAT THERE IS NOT ANY WEAR.		1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P6EA	 
2003070200113	20030702	00113	NM  	2003	7	2	CA030605001      	1	20030521	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND LT SIDE OF FUSELAGE FORWARD UPPER CORNER OF WINDOW NR 4 AT BODY STATION 420 AND STRINGER NR 11 LT RECT	IFICATION:  HIGH FREQUENCY EDDY CURRENT CARRIED OUT IAW SRM 53-30-3 IN REPAIR AREA AT LT FUSELAGE AS 420 STR 11 LT, (NO 	CRACKS DETECTED).   SKIN REPAIRED IAW B737 SRM				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003070300007	20030703	00007	CE  	2003	7	3	CA030605003      	1	20030526	G	8011	08504691	CONTACTOR       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520MB     	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	STARTER	ARCED           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELECTRICAL SYSTEM FAILED. LT STARTER RELAY STUCK IN ON POSITION DURING START. STARTER ROTATED TILL BATTERY WAS RUN	 OUT AS IT WAS A HIGH LOAD. SERVICEABLE RELAY WAS INSTALLED, A NEW BATTERY AND OVERHAULED STARTER WERE INSTALLED, WIRING	 WAS CHECKED. PROBLEM WAS CORRECTED.				1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2003061700059	20030617	00059	EA  	2003	6	17	CA030605004      	2	20030304	G	8520		CONNECTING ROD  			BNORM 	BN2   	BN2B21      	7080221	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					NR4 CYLINDER	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CAUSE OF THE ENGINE FAILURE WOULD BE DUE TO NR 4 CONNECTING ROD BOLTS FRACTURING AT THE CRANKSHAFT JOURNAL. WI	TH THIS HAPPENING IT BECOMES DISCONNECTED & COMPLETELY DESTROYES THE CRANKCASE IN THATAREA AND PUSHES THE NR 4 CYLINDER 	OFF OF IT'S BASES PULLING AND STRIPPING ALL OF THE CYLINDER STUDS.				1	H	7	2 	3O	3	O	 	A17EU   	1E4				 
2003070200078	20030702	00078	CE  	2003	7	2	CA030605005      	1	20030526	G	7603		SPRING          			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE CONTROL	BROKEN          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLE AIRCRAFT LT ENGINE ONLY DEVELOPED 1,000 LBS TORQUE. AIRCRAFT RETURNED TO HANGAR. MAINT RAN AIRCRAF	T IN MANUAL MODE & AIRCRAFT DEVELOPED POWER. AFTER TROUBLE SHOOTING MAINTENANCE FOUND O-SPRING BROKE IN THE THROTTLE QUA	DRANT AND FELL INTO THE THROTTLE POT SENDING A FALSE READING TO THE COMPUTER LIMITING TORQUE.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2003070300002	20030703	00002	EA  	2003	7	3	CA030605006      	2	20030529	G	8520	LW15272	CRANKCASE       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) OIL LEAK DISCOVERED AT 100 HOUR INSPECTION.  NR 3 CYLINDER REMOVED UPON INSPECTION OF CRANK CASE FOUND 2 CRACKS AT	 AFT 2 STUDS OF CYLINDER NR 3. OWNER NOTIFIED, ENGINE TO BE REMOVED.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003070300003	20030703	00003	EA  	2003	7	3	CA030605007      	2	20030513	G	8530	893742C	CYLINDER        			DOUG  	DC3   	R4D8        	3021474	WP  	WRIGHT	R1820 	R182080     	67020	EA  	HAMSTD	23E	23E50       	NE  	ENGINE	PERFORATED      	W				C				ABORTED TAKEOFF         				K			FLUID LOSS                			TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT NR 1 ENGINE RAN ROUGH ON TAKEOFF.   COME BACK TO BASE ON REDUCED POWER. DIFFERENTIAL COMPRESSION CHECK IN	DICATED (0) ON NR 4 CYLINDER.  FOUND ALUMINIUM IN OILFILTER.  SUSPECT PISTON FAILURE.  REMOVED ENGINE FOR OVERHAUL.					2	L	7	2 	4R	4	R	 	6A2     	E259	6	C	P603	 
2003070300004	20030703	00004		2003	7	3	CA030605008      	4	20030524	G	6122	1A2G5	GOVERNOR        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	PROPELLER	FAILED          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) PROPELLER MOVED TO LOW RPM POSITION AS POWER WAS APPLIED FOR TAKEOFF, TAKEOFF WAS ABORTED AND AIRCRAFT TAXIED BACK	 TO DOCK. PROPELLER GOVERNOR REPLACED WITH OVERHAULED UNIT, MAIN OIL FILTER INSPECTED AND FOUND CLEAN. AIRCRAFT GROUND R	UN AND HIGH SPEED WATER RUN COMPLETED SATISFACTORY, PROPELLER FUNCTION FOUND NORMAL. REMOVED GOVERNOR INSPECTED FOR META	L CONTAMINATION, NONE FOUND. GOVERNOR SENT TO HOPE AERO PROPELLER FOR INSPECTION AND OVERHAUL.			1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2003061700060	20030617	00060	CE  	2003	6	17	CA030605009      	1	20030527	G	2910	2607003453	TUBE            			LEAR  	35    	35A         	5170602	CE  										HYD SYSTEM	LEAKING         	W				L	J			ABORTED APPROACH        	DUMP FUEL               			K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON FINAL, CREW SELECTED GEAR DOWN, GEAR UNLOCKED AND FAILED TO EXTEND, NO HYDRAULIC PRESSURE, AIRCRAFT DIVERTED TO	 QUEBEC AIRPORT, GEAR EMERGENCY EXTENDED, AIRCRAFT LANDED WITH NO FURTHER PROBLEM.FOUND LT ENGINE HYDRAULIC PUMP FUSELAG	E LINE HAD A CHAFED HOLE FROM THE END ON A SCREW HOLDING A CLAMP. LINE REPLACED SYSTEM BLEED AND SERVICE,  FOUND LT ENGI	NE HYDRAULIC PUMP FAILED, (SUSPECT RAN DRY), PUMP REPLACED, ALL HYDRAULIC SYSTEM CHECK SERVICEABLE, PRESSURE FILTER REPL	ACED. AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F			 	A10CE   					 
2003070200079	20030702	00079	WP  	2003	7	2	CA030605010      	1	20030529	G	6210	369A10045	PIN             	DOUG        		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					M/R HEAD	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						0980					(CAN) UPON POST FLIGHT INSPECTION BLADE PIN FOUND TO BE BROKEN WHERE THREAD MEETS THE PIN.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003070300005	20030703	00005		2003	7	3	CA030605011      	4	20030602	G	2562	4520130	BATTERY PACK    			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ELT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CHANGING A BATTERY PACK IN AN ELT, THE CASING WAS NOTICED TO BE CRACKED ATTHE SCREW HOLES.  IF THE BATTERIES	 HAD LEAKED THE ACID COULD LEAK ON TO THE BATTERY TRAY & THE AIRCRAFT SURROUNDING STRUCTURE.  THIS HAS HAPPENED TWICE BE	FORE.  WE HAVE AN INSPECTION INTERVAL OF 50 HRS.  ON THE BATTERY TRAY AND ELT MOUNTING.				1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920	 
2003070200108	20030702	00108	EU  	2003	7	2	CA030605012      	1	20030604	G	7603	LN93556X32	BOLT            			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20      	03013	GL  					N2 LEVER	OVERSIZED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION TO COMPLY WITH AIRCRAFT SERVICES CAMPAIGN NOTICE THE BOLT CONNECTING THE N2 CONTROL CABLES TO TH	E N2 LEVER ASSEMBLY WAS FOUND TO BE TOO LONG. THE EXTRA LENGTH HAD BEEN COMPENSATED FOR WITH THE USE OF EXTRA WASHERS UN	DER THE BOLT HEAD. INCORRECT BOLT WAS REMOVED & CORRECT BOLT INSTALLED AND TORQUE SEAL APPLIED TO THE END OF THE BOLT TO	 NUT-PLATE CONNECTION.			1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003061700062	20030617	00062	EU  	2003	6	17	CA030605013      	1	20030530	G	7603	LN93556X32	BOLT            			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					N2 LEVER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION TO COMPLY WITH AIRCRAFT SERVICES CAMPAIGN NOTICE 351-73-20-12 THE BOLT CONNECTING THE N2 CONTROL	 CABLES TO THE N2 LEVER ASSEMBLY WAS FOUND TO HAVE A LOW DRAG TORQUE IN THE NUT-PLATE.A NEW BOLT WAS INSTALLED & DRAG TO	RQUE WAS DETERMINED TO BE ACCEPTABLE.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003070200080	20030702	00080	CE  	2003	7	2	CA030605014      	1	20030604	G	2750	656517543	SWITCH          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAPS SYS	OUT OF RIG      	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE FLAP SYSTEM SECONDARY SWITCHES LOCATED IN THE AFT CABIN WERE FOUND TO BE SEVERELY OUT OF RIG. THIS ALLOWED THE	 FLAP BELL CRANKS TO OVER TRAVEL CONTACTING THE WING STRUCTURE DURING FLAP OPERATION. NO STRUCTURAL DAMAGE WAS FOUND. SY	STEM RERIGGED & CHECKED SERVICEABLE.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003070200107	20030702	00107	WP  	2003	7	2	CA030605015      	2	20030529	G	7321		FUEL CONTROL    			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENGINE	INOPERATIVE     	W				O				OTHER                   				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) WHEN TESTING MANUAL MODE (COMPUTER OFF) THERE WAS NO ENGINE POWER RESPONSE TO POWER LEVER INPUTS. FCU REPLACED, PR	OBLEM SOLVED.					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2003070200109	20030702	00109	GL  	2003	7	2	CA030605016      	3	20030527	G	6110	B1894	NUT             	HARTZL      		DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CX41					(CAN) PROP WAS REMOVED DURING ENGINE REPAIRS, NUT HOLDING PROP TO CRANKSHAFT WAS FOUND CRACKED.  NUT WAS CRACKED FROM NO	TCH FOR INSTALL/REMOVAL TOOL TO HOLE FOR LOCKING CLIP. NUT WAS REPLACED WITH OVERHAULED UNIT AND PROP WAS REINSTALED & A	IRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P28EA	 
2003061700068	20030617	00068	NE  	2003	6	17	CA030605019      	2	20030530	G	8550		ENGINE          			GRUMAV	G21   	G21A        	3951204	SO  	PWA   	R985  	R985*       	52008	NE  						MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REGULAR MAINTENANCE INSPECTION METAL WAS FOUND IN THE OIL SCREEN IN SUFFICIENT QUANTITY TO WARRANT ENGINE R	EMOVAL.					1	H	7	2 	3R	3	R	 	TC654   	5E1				 
2003070200081	20030702	00081	GL  	2003	7	2	CA030606001      	3	20030529	G	6114		BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING LAST THREE PROPELLER OVERHAULS THESE BOLTS ARE REPLACED WITH NEW AS REQUIRED. THE LAST TWO INSTALLS WERE NO	T IN COMPLIANCE WITH SL 508. THESE WERE ONLY BY CHANCE NOTICED BY THE MAINTENANCE CO-ORDINATOR (NOT AME). THE PREVIOUS O	NE WAS NOT NOTICED AND WAS RELEASED FOR SERVICE AND DESTROYED THE PROP SPINNER. THIS IS 100 PERCENT RECURRING FOR US. SP	INNER IS NOT NORMALLY INSTALLED BY PROPELLER OVERHAUL COMPANY.  RECOMMENDED AT THE NEXT 100 HR INSPECTION.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2003070200110	20030702	00110		2003	7	2	CA030606002      	4	20030529	G	2210		CLAMP           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PITCH SERVO	JAMMED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) AUTO PILOT BRIDLE CABLE CLAMP (PITCH) JAMS AGAINST EACH OTHER AT OR NEAR FULL UP (NOSE UP) CONTROL MOVEMENT. THIS 	IS A RECURRING PROBLEM. THIS HAS ALSO HAPPENED YEARS AGO WITH OLD EDO-AIR (ALTIMATIC III A/P). THESE CLAMPS ARE NEWER ST	YLE (MANDITORY BY AD) OLD CLAMPS DID NOT CAUSE PROBLEM. STEC DRAWING 76891 DOES NOT CLEARLY WARN OF THIS POTENTIAL PROBL	EM.  MFG DOES NOT WARN OF THIS PROBLEM DURING SETTING CABLE TENSION. MISSED BY (3) DUAL INSPECTIONS.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2003070200105	20030702	00105	SO  	2003	7	2	CA030606003      	1	20030530	G	2730		CABLE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PITCH SERVO	JAMMED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) AUTO PILOT PITCH SERVO BRIDLE CABLE TO ELEVATOR MAIN CONTROL CABLE CLAMPS ERRONEOUSLY INSTALLED CAUSING PITCH CONT	ROL JAMMING AT FULL ELEVATOR UP EXTENSION.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2003070200082	20030702	00082	CE  	2003	7	2	CA030606004      	1	20030605	G	2820	1200106253	LINE            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	FUEL SYSTEM	SEVERED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) DURING THE LAST OPS 4 INSPECTION, SEB 95-6, RUBBER FUEL HOSE INSPECTION AND REPLACEMENT WAS ACCOMPLISHED. SUBSEQUE	NT INSPECTION REVEILED THAT THE FUEL PRIMER LINE FROM THE MANIFOLD TO THE PRIMER T FITTING ROUTED NEAR THE ALTERNATOR PU	LLEY FOUND BROKEN IN TWO AND THE TEE FITTING CHAFED ON THE ALTERNATOR PULLEY. AIR TIME SINCE INSPECTION /MODIFICATION WA	S 19.1 HOURS. THE ABSENCE OF CLAMPS AT THE TEE  FITTING TO THE INTAKE MANIFOLD AND THE INCREASED STIFFNESS OF THE NEW LI	NES CAUSED INCREASED STRESS ON THE RIGID PRIMER LINE LEAD TO THE RIGID LINE FAILURE.  A NEW RIGID LINE AND FITTINGS WERE	 INSTALLED AND THE TEE FITTING CLAMPED AS DESCRIBED IN THE MAINTENANCE MANUAL AND IPC.	1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL	 
2003070200111	20030702	00111	CE  	2003	7	2	CA030606005      	1	20030606	G	7931		WIRE            			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	OIL PRESS XMTER	FAILED          	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) PORT ENGINE OIL PRESSURE. ON TAXI OUT, PILOTS NOTICED OIL LIGHT FLASHING. THEY SHUT DOWN THE ENGINE AND TAXIED BAC	K TO THE TERMINAL, CALLED MAINTENANCE. THEY CHECKED THE WIRES ON THE OIL PRESSURE TRANSMITTER, STARTED UP THE ENGINE AND	 ALL INDICATIONS WERE NORMAL. THEY FERRIED THE AIRCRAFT BACK, WHERE MAINTENANCE REPAIRED A WIRE TO THE OIL PRESSURE TRAN	SMITTER.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003070300019	20030703	00019	EA  	2003	7	3	CA030606006      	1	20030530	G	3010	600800398	PICCOLO TUBE    			CNDAIR	CL600 	CL600*      	       	EA  										PICCOLO TUBE	MISMARKED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE CARRYING OUT SB 600-0718 INSPECTION OF PICOLO TUBES AND DUCTS FOR CORRECT ALIGNMENT IT WAS FOUND THAT THE RT	 OUTBOARD PICCOLO TUBE BLEED HOLES WERE IMPROPERLY POSITIONED AS IDENTIFIED IN THE SB. THE PICCOLO TUBE WAS REMOVED AND 	IT WAS FOUND THAT THE TUBE HAD BEEN MANUFACTURED FOR A LT INSTALLATION AND IDENTIFIED AS A RT TUBE BY PART NUMBER AND OR	INTATION LABLE. A CORRECTLY IDENTIFIED & MANUFACTURED TUBE WAS INSTALLED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4F			RT	A21EA   					 
2003070300020	20030703	00020	EA  	2003	7	3	CA030606007      	2	20030523	G	8520	LW12163	CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS FOUND IN THRUST AREA OF CRANKSHAFT CAUSED BY EXCESSIVE END CLEARANCE OF CRANKSHAFT (IN CRANKCASE).						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003070200083	20030702	00083	EA  	2003	7	2	CA030606008      	2	20030527	G	8520	79027	CRANKSHAFT      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CRANKSHAFT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  COUNTERWEIGHT BLADE BUSHINGS AND BORE WORN (LOOSE) BEYOND REPAIRABLE LIMITS.  PROP GOVERNOR GEAR P/N 70389 HAD FA	ILED.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003070200084	20030702	00084	NE  	2003	7	2	CA030606009      	2	20030527	G	7320	3036640	FLOW DIVIDER    								PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	WRONG PART      	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA								93753			(CAN)  ENG WAS SHUTOFF IN FLT FOLLOWING HIGH T-5 OCCURRENCE. NO DAMAGE EXTERNALLY & ONLY DAMAGE FOUND INTERNALLY RUBBING	 CONTACT BETWEEN COMP TURBINE BLADE TIPS & CT SHROUD SEG.  NO EVIDENCE OF OVERTEMP, OR ANY BUILD ERRORS IN THE ENG. FLOW	 DIVIDER HAS WRONGLY IDENTIFIED BODY INSTALLED, THIS ERROR HAS CAUSED DIFFICULTIES IN STARTING AND IN FLT INCIDENT. IN-F	LT PROBLEMS OF THIS ENG CAUSED BY FLOW DIVIDER. WRONG BODY BEING INSTALLED ALLOWED OUTLET TO POUR A LOT OF FUEL THROUGH 	IT. ENG WAS POURING FUEL OUT OF THE FLOW DIVIDER, MADE ENG RUN VERY LEAN IN FUEL & NOT ABLE TO PRODUCE ENOUGH ENERGY TO 	PROPERLY ACCELERATE DURING THE START CYCLE, LEADING TO ELEVATED TEMP WITH CT BLADE TIP RUB.						4	T			E4EA				 
2003070200085	20030702	00085	CE  	2003	7	2	CA030606010      	1	20030606	G	2780		CONTROL CABLE   			CESSNA	337   	337A        	2075704	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2AF34C	D2AF34C59   	GL  	TE FLAP	FRAYED          	W				F				ACTIVATE FIRE EXT.      				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) INSPECTION OF FLAP CABLES IAW SERVICE DIFFICULTY ALERT NR AL-2003-05, FOUND THREE FRAYED CABLE ENDS, ONE AT OUTBOA	RD BELLCRANK.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2003070300041	20030703	00041	NM  	2003	7	3	CA030609001      	1	20030605	G	2612		FIRE DETECTOR   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 ENGINE	DEFECTIVE       	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) A/C WAS AT GATE, NR 2 ENGINE ALREADY RUNNING. DURING NR 1 ENGINE START FLIGHT CREW ENCOUNTERED A FIRE WARNING. THE	 CREW FIRED BOTH FIRE BOTTLES AND CONDUCTED AN EMERGENCY EVACUATION OF THE AIRCRAFT.  IT HAS BEEN DETERMINED THAT THE WA	RNING WAS OF A NUISANCE NATURE AND NO ACTUAL FIRE OCCURRED.  INITIAL INVESTIGATION CARRIED OUT BY ENGINEERS PEC FIRE LOO	P REPLACEMENT CURED DEFECT.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2003070200086	20030702	00086	EA  	2003	7	2	CA030609002      	1	20030527	G	5730	CVR67	SEAL            			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	ACCESS PANEL	SWOLLEN         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE REMOVING FUEL LIDS TO ACCESS FUEL TANKS FOR SNAG RECERTIFICATION FOLLOWING MAJOR INSPECTION, IT WAS NOTICED 	THAT THE NEW LIGHTNING SEAL P/N CVR 67 THAT WAS INSTALLED IN THE LAST WEEK OR TWO HAD SWOLLEN ALMOST 50 PERCENT LARGER T	HEN ITS NORMAL SIZE AND THE MATERIAL HAD SOFTEN FROM EXPOSURE TO JET FUEL. THE SEAL WAS ALSO DISLODGED AND HANGING OFF T	HE LADDER PLATES.  WE TESTED OUR STOCK AND FOUND THAT ONLY ONE BATCH OF THE CVR 67 IS AFFECTED BY FUEL REMOVED THIS BATC	H FROM OUR STOCK AND REPLACED THE SEAL ON THE AIRCRAFT. WE ARE ALSO GOING TO REPLACE THE SEAL ON ONE OTHER AIRCRAFT THAT	 WAS ISSUED THIS SEAL FROM THE SAME BATCH NR.	2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2003070300050	20030703	00050	EA  	2003	7	3	CA030609003      	1	20030606	G	7930	3034081	CHIP DETECTOR   			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF MAGNETIC PLUG,  A STRESS CRACK WAS FOUND AT THE BASE OF THE PLUG. UNIT WAS REMOVED FROM SERVI	CE.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003070300072	20030703	00072	CE  	2003	7	3	CA030609004      	1	20030528	G	2910	570383	PRESSURE SWITCH 			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) AIRCRAFT FLEW UNEVENTFUL. UPON TAKEOFF, THE CREW SELECTED GEAR UP. THE NOSE AND RT MAIN GEAR BEGAN TO RETRACT.  TH	E LT MAIN GEAR REMAINED DOWN AND LOCKED. CREW SELECTED GEAR DOWN AND RETURNED TO 3 GREEN.  ONCE AGAIN, CREW SELECTED GEA	R UP. GEAR DID NOT MOVE. CREW LANDED. AIRCRAFT THEN FERRIED BACK. TROUBLESHOOTING DETERMINED POWERPACK PRESSURE SWITCH H	AD FAILED OPEN. SWITCH REPLACED, LANDING GEAR FUNCTION CHECKED NORMAL.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2003071800101	20030718	00101	NE  	2003	7	18	CA030609005      	2	20030602	G	7230	586982	VALVE           			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					DUMP	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) A/C PICKED UP A 15,000 LB LOAD OF LOGS. PILOT MADE A LT PEDAL TURN TO DEPART FROM LOGGING CUT BLOCK & LOWERED COLL	ECTIVE TO DESCEND TO LOG LANDING. CREW HEAR A SWOOSH SOUND AT WHICH TIME NR 2 ENG N1 UNDER-SPEED WARNING SOUNDED & WARNI	NG LIGHTS ILLUMINATED INDICATING A SOFT STALL CONDITION. CREW EXECUTED AN IN-FLT SHUTDOWN & MOTORING OF SUBJECT ENGINE T	O PREVENT AN OVER-TEMPERATURE CONDITION. WITH NR 2 ENG SHUTDOWN PROCEDURES COMPLETED A/C CONTINUED TO LOG LANDING & RELE	ASED ITS LOAD & RETURNED TO SERVICE AREA & MADE AN UNEVENTFUL SINGLE ENG LANDING.  COMPLETE INSP OF ENG & ITS RELATED CO	NTROL LINKAGES REVEALED NOTHING ABNORMAL. ENG FUEL FILTER WAS INSPECTED FOR CONTAM.	2	G	7	2 	4U	4	U	 	H4EA    	E15EA				 
2003070300073	20030703	00073	NE  	2003	7	3	CA030609006      	2	20030607	G	8550		ENGINE          			GRUMAV	G21   	G21A        	3951204	SO  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R302    	GL  	RIGHT	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REGULARLY SCHEDULED MAINTENANCE, METAL WAS FOUND IN THE OIL SCREEN OF THE RT ENGINE IN SUFFICIENT QUANTITY 	TO NECESSITATE ENGINE REMOVAL.					1	H	7	2 	3R	3	R	 	TC654   	5E1	5	C	P28EA	 
2003070300074	20030703	00074	SO  	2003	7	3	CA030609007      	2	20030526	G	8560	4066109025	TURBOCHARGER    			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION, THE COLD SIDE OF THE TURBOCHARGER TURBINE WAS FOUND TO BE RUBBING WHEN SPUN BY HAND. THE TUR	BOCHARGER WAS REMOVED. A CRACK WAS FOUND CLOSE TO THE TAIL PIPE ATTACH FLANGE.  THE CRACK HAD SWELLED, CAUSING THE TURBO	 HOUSING TO COME INTO CONTACT WITH THE HOT-SIDE TURBINE. THE TURBO WAS REPLACED.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003070300075	20030703	00075	SO  	2003	7	3	CA030609008      	1	20030609	G	3250	AN3H7A	BOLT            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG STEERING	SHEARED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) AFTER GEAR WAS SELECTED DOWN AND THE CREW HAD THREE GREEN LIGHTS, THE PILOT NOTICED THAT THE NOSE WHEEL WAS NOT CE	NTERED. THE PILOT WAS ADVISED TO KEEP THE WEIGHT OFF OF THE NOSE WHEEL AS MUCH AS POSSIBLE AND LANDED THE AIRCRAFT SAFEL	Y WITHOUT INCIDENT. UPON INSPECTION, THE THREE AN3 BOLTS HOLDING THE STEERING ARM TO THE NOSE GEAR CYLINDER WERE FOUND T	O BE SHEARED. A 1200 HR REPLACEMENT INTERVAL HAS NOW BEEN ADDED TO THIS OPERATOR'S MAINTENANCE TRACKING SYSTEM.			1	L	7	2 	3T	4	T	 	A8EA    	E4EA	6	C	P15EA	 
2003070300076	20030703	00076	EA  	2003	7	3	CA030609009      	1	20030528	G	5523	C2T29A	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	LT ELEVATOR	BROKEN          	W				O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		CR	CRUISE         	1			CA			13672								(CAN) LT ARM WHICH CONNECTS LT ELEVATOR TRIM TAB CONTROL ROD TO TORQUE TUBE BROKEN,  COMPLETELY OFF.  NOTE: THIS ASSEMBL	Y IS OF PRE-MOD, NATURE AND PROBABLY BROKE DUE TO MISHANDLING. POST MOD ARM HAS A REINFORCING GUSSET WHICH SUBSTANTIALLY	 IMPROVES STRENGTH/RIGIDITY.				1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2003070700001	20030707	00001		2003	7	7	CA030609010      	4	20030514	G	3418	601R591541	VANE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  										AOA	OUT OF TOLERANCE	W				O				OTHER                   				L			NO TEST                   			CR	CRUISE         	1			CA											(CAN) WHILE DOING THE CLEAN STALL TEST, THE SHAKER FIRED 2 KNOTS ABOVE THE CALCULATED VALUE. THEN, WHILE SLOWING THRU 2 	KNOTS BELOW THE SHAKER, THE AIRCRAFT STARTED BUFFETING AND DEVELOPED A PRONOUNCED ROLLTO THE LEFT. THE PUSHER ACTIVATED 	3 KNOTS ABOVE THE CALCULATED VALUE, BUT THE ANGLES AT THE PUSHER SHOWED 14.5 & 14.6. AIRCRAFT RETURNED WITHOUT FURTHER O	CCURRENCES. UPON ARRIVAL, THE LT AND RT AOA VANES NUL ADJUST WERE FOUND OUT OF TOLERANCES AT 0.7/0.6 INSTEAD OF 0.8 IAW 	FTP601R2731U. VANES WERE ADJUSTED IAW FTP601R2731U AND AIRCRAFT RETURNED TO FLIGHT WITHOUT FURTHER OCCURRENCES.		2	L	7	2 	4F			RT	A21EA   					 
2003070700002	20030707	00002	SO  	2003	7	7	CA030609011      	1	20030520	G	2121		MOTOR           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FAN	ODOR            	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) THE PILOTS DETECTED A BURNING ODOR WHILE THE AIRCRAFT WAS IN DESCENT. AFTER ELIMINATING SYSTEMS, THE PILOTS CAME T	O THE CONCLUSION THAT IT WAS THE GROUND FAN. AFTER DISASSEMBLY & INSPECTION WE DID NOT FIND ANYTHING ABNORMAL. WE THINK 	THAT THE ODOR ORIGINATED FROM DUST IN THE MOTOR OF THE FAN. THE GROUND FAN WAS UTILIZED FOR THE FIRST TIME THIS SUMMER, 	ITS USE IS FOR WHEN IT IS HOT OUTSIDE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003070300042	20030703	00042	EA  	2003	7	3	CA030609012      	2	20030602	G	8530		ENGINE          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  		FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) DURING LANDING AFTER PASSING THE RUNWAY THRESHOLD ENGINE BROUGHT TO IDLE CAUSING IT TO STOP AND PROP TO WINDMILL. 	 AFTER LANDING PILOT TAXIED WITH REMAINING SPEED OFF THE RUNWAY. (RESTARTING WAS UNSUCCESSFUL).  PLANE WAS TOWED TO THE 	RAMP.  NOTE: 164 HOURS LT FOR ENGINE OVERHAUL, 2 CYLINDERS FOUND LOW COMPRESSOR, ENGINE REMOVED FOR OVERHAUL.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003070300043	20030703	00043	NE  	2003	7	3	CA030609014      	2	20030609	G	7323		SCREEN          	BENDIX      		BOLKMS	117   	BK117A1     	5626010	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					PT GOVERNOR	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						85030104					(CAN) RECEIVING INSPECTION, POST REPAIR, REVEALED A LOOSE SCREEN IN THE PG FITTING.  THIS FITTING HAD BEEN REPLACED DURI	NG THE REPAIR PROCESS.  UNIT RETURNED TO MFG REPAIR STATION.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2003070300044	20030703	00044	CE  	2003	7	3	CA030610001      	1	20030609	G	5753	6525115	RIB             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAPS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PHASE 5 INSPECTION SEVERAL FLAP RIB EXTENSIONS WERE FOUND WORN BY THE RIVETS SECURING THE FLAP TRACKS TO TH	E WING. THE CENTER HINGE INBOARD AND OUTBOARD EXTENSIONS ON THE LT FLAP AND THE INBOARD ON THE RT FLAP WERE WORN BEYOND 	LIMITS AND REPLACED. THE OTHERS WERE BLENDED IAW AIRCRAFT SERVICES AS SB -851-0082 AND RETURNED TO SERVICE.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003070300045	20030703	00045	NE  	2003	7	3	CA030610002      	1	20030605	G	6410	S611730101045	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581402    	30011	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14200								(CAN) DURING A DAILY INSPECTION A CRACK WAS FOUND IN THE INBOARD SIDE OF THE TRAILING EDGE POCKET. THE CRACK STARTED AT 	THE TRAILING EDGE AND PROPAGATED FORWARD APPROXIMATELY 70MM. (2.75 INCHES)					2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2003070300047	20030703	00047	SO  	2003	7	3	CA030610004      	1	20030603	G	3230	455180	CONDUIT         		455180      	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) RT MAIN GEAR CONDUIT FLEXIBLE OUTER SLEEVE MOVED WITH INNER CABLE EXPOSING 11.0 INCHES OF INNER CABLE. INNER CABLE	 LOOPED OUT OF EXPOSED AREA. NOW WITH CABLE BEING BENT RT GEAR COULD NOT OVER CENTER FOR DOWN AND LOCKED.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2003070300048	20030703	00048	CE  	2003	7	3	CA030610005      	1	20030606	G	2711	130909B38	BOLT            	BEECH       	1015210391  	BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	LT AILERON	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION THE TRIM TAB ACTUATOR WAS FOUND TO HAVE 2 BOLTS, P/N 130909B38, LOOSE.  THE ACTUATOR SHOWED NO IND	ICATIONS OF DAMAGE OR MALFUNCTION, TRIM TAB FREE PLAY INSPECTION WAS WELL WITHIN TOLERANCE.  BOLTS WERE TORQUED AND ANTI	 SABATOGE LAQUER WAS INSTALLED. THERE WAS NO EVIDENCE OF THE PART BEING REMOVED AND WAS MOST LIKELY THAT WAY SINCE THE A	IRCRAFT LEFT THE FACTORY.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	P10NE	 
2003070300049	20030703	00049	CE  	2003	7	3	CA030610006      	1	20030603	G	3610	1H7512	REGULATOR       			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	PNEUMATIC SYS	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PNEUMATIC REGULATOR FAILURE IN CRUISE FLIGHT OCCURRED. PILOTS HAD TWO BLEED AIR FAIL LIGHTS, LEFT AND RIGHT, AND A	LSO NOTED LOSS OF SUCTION AND PNEUMATIC PRESSURES CONFORMING LIGHT INDICATION. PILOTS RETURNED TO BASE. UPON INSPECTION 	THE REGULATOR FOUND TO HAVE TOTALLY FAILED. THIS TYPE OF REGULATOR HAS A SAFETY WHERE BY IT SHOULD REGULATE TO 20 PSI UP	ON FAILURE OF THE NORMAL 18 PSI REGULATION. THE PART WAS REPLACED WITH AN OVERHAULED UNIT, TESTED AND FOUND TO OPERATE P	ROPERLY.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	P10NE	 
2003070200100	20030702	00100	CE  	2003	7	2	CA030610007      	1	20030603	G	2752	1295210511	ACTUATOR        			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	TE FLAPS	MISINSTALLED    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLAP ACTUATOR WAS FOUND TO HAVE BEEN INSTALLED INCORRECTLY WITH LUBRICANT VENT HOLE DOWN WHICH RESULTS IN LOSS OF 	LUBRICANT.  ACTUATOR WAS REMOVED AND FOUND TO BE UNSERVICEABLE DUE TO HAVING TOO MUCH END PLAY. THE ACTUATOR WAS SENT FO	R REPAIR, RE-INSTALLED AND RIGGED.  THIS WAS CAUSED BY THE OVERHAULER NOT ASSEMBLING THE ACTUATOR CORRECTLY AND THE INST	ALLER NOT NOTICING POSITION OF THE VENT HOLE ON INSTALLATION.  THE LUBE ON THIS ACTUATOR HAD BEEN DONE 572 HOURS AND 660	 CYCLES EARLIER.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	P10NE	 
2003070200101	20030702	00101	NE  	2003	7	2	CA030610008      	2	20030610	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION IT WAS DISCOVERED THE INSULATOR HAD BROKEN FREE AND HAD SLID DOWN THE CENTER ELECTRODE ABOUT .3750. 	 COULD POSSIBLY HAVE GONE THROUGH THE GAS PATH OF ENGINE HAD IT NOT BEEN DISCOVERED.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003070200102	20030702	00102	CE  	2003	7	2	CA030610009      	1	20030606	G	5620		WINDOW          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE CABIN WINDOW INSPECTION MAINTENANCE FOUND A SMALL CRACK IN WINDOW SURROUND STRUCTURE OF A LT CABI	N WINDOW BETWEEN STA 303.25 AND 318.25. THE CRACK MEASURED O.800 INCHES IN LENGTH, PASSED 1/4 INCH PAST A FASTENER, AND 	WAS 3/4 INCH FROM THE WINDOW EDGE. THE WINDOW SURROUND STRUCTURE WAS REPAIRED IAW RRB/0 809-03 AND THE AIRCRAFT WAS RETU	RNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003070300057	20030703	00057	WP  	2003	7	3	CA030610010      	2	20030609	G	7321	8978017	FUEL CONTROL    			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UPON PERFORMING A GROUND RUN FOR AN ENGINE REPLACEMENT AND UPON THE APPLICATION OF FULL POWER THE ENGINE RESPONSE 	WAS GOOD, BUT IN ATTEMPT TO DECREASE ENGINE POWER THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUTS. IT WAS APPROXIMATELY 	30 SECOND TO A MINUTE BEFORE THE ENGINE POWER STARTED TO DECREASE TO NORMAL IDLE SPEED. INSPECTION OF ENGINE AND RIGGING	 REVEALED NO PROBLEMS. THE FUEL CONTROL UNIT WAS REPLACED AND A GROUND RUN CARRIED OUT WITHOUT THE RECURRENCE OF THE DEF	ECT.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2003070300058	20030703	00058	SW  	2003	7	3	CA030610011      	1	20030607	G	5302	20403082506	SPAR            			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19119								(CAN) ENGINEER OPENED TAIL ROTOR DRIVESHAFT COVER TO CHANGE COUPLINGS AND FOUND A CRACK HAD DEVELOPED IN THE VERTICAL FI	N SPAR. STARTING AT THE TOP LIGHTENING HOLE AND GOING LT TO THE OUTER EDGE OF THE SPARE. OUTER LT SKIN WAS ALSO CRACKED 	APPROX. SIX INCHES. TAILBOOM WAS REPLACED				1	G	7	1 	4U	4	U	 	H1SW    	E1EA				 
2003070300059	20030703	00059	EU  	2003	7	3	CA030611001      	2	20030609	G	8560	139379	LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	FITTING	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UPON RETURN OF AIRCRAFT TO BASE, MAINTENANCE FOUND OIL LEAKING FROM AROUND RT GEARBOX AREA. INVESTIGATION FOUNG TH	E OIL SUPPLY LINE FROM GEARBOX TO SUPERCHARGER HAD SHEARED OFF AT THE SUPERCHARGER. THE LINE IS A FLEXIBLE FLUID LINE AN	D THE NUT PORTION ALONG WITH THE FLARE STAYED ATTACHED TO THE SUPERCHARGER. THE BREAK OCCURED JUST BEHIND THE NUT PORTIO	N. DUE TO THE LOW OIL LEVEL NOTED IN THE GEARBOX, THE GEARBOX & SUPERCHARGER WERE REPLACED. OPERATOR WILL NOW SELF IMPOS	E A RETIREMENT LIFE TO THIS HOSE ASSEMBLY		2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899	 
2003071800100	20030718	00100	NM  	2003	7	18	CA030611002      	1	20030609	G	2710	654476114	PCU             			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AILERON	BROKEN          	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) DURING LANDING THROUGH APPROXIMATELY 60 KNOTS, AIRCRAFT EXPERIENCED A COMPLETE LOSS OF 'A' SYSTEM HYDRAULICS. (NOT	E: 'A' PUMPS ON WITH LOW PRESSURE LIGHTS ILLUMINATED - MAX 1.5 MINUTES) MAINTENANCE INSPECTION REVEALED POSITION NR 1 LO	WER AILERON PCU FILTER HOUSING COMPLETELY CRACK AROUND CIRCUMFERENCE OF HOUSING (DETACHED FROM UNIT). MAINTENANCE REPLAC	ED PCU PER MM 27-11-71, LEAK CHECK AND ADJUSTMENT TEST OF AILERON ACTUATOR COMPLETE. NO LEAKS TO REPORT.AIRCRAFT RETURNE	D TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003072100008	20030721	00008	EU  	2003	7	21	CA030611003      	1	20030610	G	7830		THRUST REVERSER 			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					NR 3 & 4 ENG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OPERATOR HAS IDENTIFIED CRACKS IN BOTH THE NR 3 AND 4 IN-BOARD THRUST REVERSER HALF, J-RINGS, ON AIRCRAFT 904. THE	 CRACKS ARE THE SUBJECT OF AD 2003-108 (B), BUT OPERATOR HAS NOT COMMENCED THE AD INSPECTION AS  IT IS ONLY DUE BEFORE 6	666 FC OR WITHIN 2166 FC FROM THE AD EFFECTIVE DATE OF MARCH 29,2003. OPERATOR IMMEDIATELY ADVISED AIRBUS OF THE FINDING	S AND AIRBUS INDICATED THAT NO APPROVED REPAIRS CURRENTLY EXIST AND THE REVERSER HALVES WILL REQUIRE REPLACEMENT. OPERAT	OR IS CURRENTLY INTHE PROCESS OF OBTAININGTWO REPLACEMENT REVERSER HALVES.		2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2003082200110	20030822	00110	SO  	2003	8	22	CA030611004      	1	20030611	G	7120	PEP6295	RING            			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					TRUNNION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10190								(CAN) TIME SHOWN ABOVE IS ENGINE TIME. PART IS OVERHAULED AT ENGINE INSTALLATION.  THE TRUNNION ASSEMBLY ATTACHED TO THE	 FORWARD ENGINE MOUNTING BEAM LINK, ATTACHING ENGINE TO AIRCRAFT, WAS RECEIVED AT RRC WITH ENGINE 8841 FOR REVISION. THE	 RING NUT LOCKING TRUNNION PEP6295 WAS FOUND CRACKED 360 DEGREE DURING THE NDT INSPECTION. THE FLANGE TRUNNION PEP 6553 	WHICH IS A SEPARATE ITEM WAS FOUND SWAGED INSIDE THE LOCKING RING NUT. INSPECTION OF  ASSEMBLY HAS DETERMINED THAT INCOR	RECT ASSEMBLY OF COMPONENTS HAS CAUSED THE COMPONENTS TO CRACK DUE TO AN OVER TORQUE APPLIED BY THE OPERATOR INSTALLING 	THE ENGINE ON THE AIRCRAFT.	2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2003082200111	20030822	00111	CE  	2003	8	22	CA030611005      	1	20030605	G	2701	16001041	SPRING          			CESSNA	188   	A188B       	2073005	CE  	CONT  	O550  	IO550D      	17042	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	CONTROL COLLUMN	BROKEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) THE SPRING (P/N 1600104-1) THAT RETRACTS THE CONTROL LOCK (P/N 1613195-1) IN FLIGHT FAILED AND ALLOWED THE CONTROL	 LOCK ASSEMBLY TO EXTEND AND SUBSEQUENTLY PARTIALLY JAM THE CONTROL STICK. THE PILOT WAS ABLE TO DISENGAGE THE LOCK ASSE	MBLY WHICH HAD JAMMED THE CONTROL STICK AND RETURNED TO BASE WITHOUT FURTHER INCIDENT.				1	L	7	1 	3O	3	O	 	A9CE    	E3SO	5	C	P25EA	 
2003070300060	20030703	00060	CE  	2003	7	3	CA030612001      	1	20030611	G	5270		SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PAX DOOR	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH, WHILE DESCENDING THROUGH 8000 FT THE CREW NOTED ILLUMINATION OF THE CABIN DOOR WARNING LIGHT. THE BLE	EDS WERE TURNED OFF AND THE CABIN DEPRESSURIZED. JUST PRIOR TO LANDING THE LIGHT EXTINGUISHED. UPON EXITING THE AIRCRAFT	, THE CREW VERIFIED THAT THE DOOR WAS INDEED IN THE CLOSED AND LOCKED POSITION AND THAT ALL VISUAL LOCK INDICATORS ON TH	E DOOR WERE SHOWING A GREEN/LOCKED INDICATION. MAINTENANCE INSPECTION DETERMINED THAT THE CABIN DOOR CLOSED SWITCH MOUNT	ED ON THE FORWARD LOWER DOOR FRAME WAS JUST BARELY BEING MADE. THE SWITCH WAS ADJUSTED FOR PROPER OVER TRAVEL AND THE DO	OR WARNING SYSTEM VERIFIED FOR CORRECT OPERATION. IN ADDITION THE DOOR LATCHING MECHANISM AND STRUCTURE WAS INSPECTED.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003071800058	20030718	00058	EU  	2003	7	18	CA030612002      	1	20030610	G	7931	11346AA	TRANSMITTER     			AMD   	FALC20	FALCON20C5  	2730107	EU  	GE    	CF700 	CF7002D2    	30010	NE  					OIL PRESSURE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON JUNE 10, 2003 DURING TAKE-OFF ROLL OF OUR FALCON 20 A/C, PILOT NOTICED A DECREASE IN OIL PRESSURE INDICATION WH	ILE ADVANCING LT ENGINE THROTTLE. PILOT INITIATED REJECTED TAKE-OFF. FLT CREW ADVISED ATC.  RETURNED TO MAINT FACILITY. 	MAINT CONFIRMED THAT OIL PRESSURE TRANSMITTER WAS DEFECTIVE. REPLACED WITH SERVICEABLE COMPONENT ACCOMPLISHED & ENG RUN 	COMPLIED WITH, ALL INDICATIONS NORMAL. A/C RELEASED,  COMPLETE CHECK FLT WAS COMPLETED SATISFACTORY WITH NO ABNORMALITIE	S.  MAINT HAS ADVISED US OF THE FOLLOWING; AFTER REMOVAL AND VISUAL INSPECTION OF DEFECTIVE OIL PRESSURE TRANSMITTER,RES	IDUAL TRACES OF THREAD TAPE USED ON AN TYPE FITTINGS WAS FOUND, WHICH CAUSED THE FALSE INDICATION.	2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2003070300061	20030703	00061	CE  	2003	7	3	CA030612003      	1	20030531	G	5520	1016100191	TORQUE TUBE     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING A SCHEDULED FLEET CAMPAIGN INSPECTION OF THE ELEVATOR TORQUE TUBE FOR ANY EVIDENCE OF CORROSION, THERE WAS 	MINOR CORROSION DETECTED ON THE LT ELEVATOR TORQUE TUBE FLANGE BETWEEN MOUNTING BOLT HOLES. THE TUBE WAS REPLACED. A SPE	CIAL INSPECTION IN ADDITION TO THE MANUFACTURERS INSPECTION PROGRAM HAS BEEN INITIATED, CALLING UP A DETAILED VISUAL OF 	THIS AREA EVERY 6 MONTHS.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003070300062	20030703	00062	EU  	2003	7	3	CA030612004      	1	20030608	G	7931		TRANSDUCER      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENG OIL PRESSURE	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE PILOT NOTICED ENG OIL PRESSURE DROP OFF TO ZERO THEN INDICATED 9 BARS ON THE PRESSURE GAU	GE. PILOT RETURNED TO POINT OF DEPARTURE. TROUBLE SHOOTING FOUND THE TRANSDUCER TO BE UNSERVICEABLE.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003070300063	20030703	00063	GL  	2003	7	3	CA030612005      	2	20030612	G	7240	23034114	CASE            			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					COMBUST CHAMBER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			12789								(CAN) ROUTINE INSPECTON AND CHANGING FUEL NOZZLE IT WAS SUSPECTED THAT THERE WAS A CRACK ALONG THE WELD WHERE THE FUEL N	OZZLE ADAPTER IS ATTATCHED TO THE END OF OUTER COMBUSTION CASE.  ON CLOSER INSPECTION IT WAS NOTED THAT THE CRACK COVERE	D OVER HALF OF THE WELDED AREA. THE CASE WAS REMOVED AND ANOTHER CASE WAS INSTALLED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003070300064	20030703	00064	GL  	2003	7	3	CA030612006      	2	20030612	G	7240	23034114	CASE            			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					COMBUST CHAMBER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AFTER INPSECTION WITH THE ENGINE RUNNING A LEAK CHECK WAS CARRIED OUT BY PLACING A HAND IN AREA OF THE FUEL NOZZLE	 AND AIR WAS FELT. THE ENGINE WAS SHUT DOWN AND A CLOSE INSPECTION WAS CARRIED OUT IN THE AREA OF WHERE THE NOZZLE ADAPT	ER PLATE IS WELDED TO THE COMBUSTION CASE. THE CRACK EXTENDED AROUND APPROXIMATLY HALF OF THE WELD.  A SERVICABLE CASE W	AS INSTALLED AND THE HELICOPTER WAS RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003070300065	20030703	00065	GL  	2003	7	3	CA030612007      	2	20030611	G	7530	2305714	CASE            	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	BROKEN          	W				E				ENGINE SHUTDOWN         				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA						CAC37734					(CAN) COMPRESSOR STALL ON START UP.  PLASTIC WAS FOUND PROTRUDING FROM START BLEED VALVE.  AFTER REMOVING BLEED VALVE, A	 1.25 X 2 X .056 INCH PIECE OF PLASTIC WAS REMOVED, WHICH WHICH APPARENTLY HAD BROKEN FREE FROM THE BLEED AIR CHAMBER TH	AT SURROUNDS THE COMPRESSOR CASE ASSY.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003071800072	20030718	00072	EA  	2003	7	18	CA030612008      	1	20030609	G	5610	601R3303312	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) CO-PILOT'S WINDOW CRACKED ON APPROACH.  WINDOW WAS REPLACED AND AIRCRAFT DECLARED SERVICEABLE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003071800074	20030718	00074	SO  	2003	7	18	CA030613001      	1	20030611	G	2752	B120344	TUBE            	MOOG        	1159SCC2121 	GULSTM	G1159 	G1159A      	3970109	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					TE FLAPS	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						98195					(CAN) AFTER REMOVING THE FLAPS TO REPAIR THE D TRACK WEB IAW AIRCRAFT SERVICE CHANGE 318B.  THE LT OUTBOARD FLAP ACTUATO	R SCREWJACK BALL RETURN TUBE COVER WAS FOUND SHEARED OFF (SUSPECT IMPROPER INSTALLATION). REPAIRED IAW CUSTOMER BULLETIN	 NR 99.				2	L	7	2 	4F	4	F	 	A12EA   	E2EU				 
2003072100018	20030721	00018	SO  	2003	7	21	CA030613003      	1	20030610	G	3244	6006	TIRE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	NLG	DAMAGED         	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL THE PILOT NOTICE A VIBRATION IN THE AIRFRAME, THEN ABORTED TAKEOFF AND TAXIED TO THE NEAREST TAXIW	AY AND NOTIFIED MAINTENANCE. UPON ARRIVAL MAINTENANCE NOTICED THE NOSE WHEEL WAS FLAT. THE NOSE WHEEL WAS DAMAGED TOO MU	CH TO BE ABLE TO DETERMINE WHAT CAUSED THE FLAT TIRE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003082200106	20030822	00106	EA  	2003	8	22	CA030613004      	1	20030611	G	2720	C2CF1777A	MOUNT           			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	RUDDER PEDAL	CRACKED         	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAKE OFF RUDDER PEDAL MOUNT ASSY PN C2CF1777A CRACKED AT BASE OF OPERATING LEVER WELD ALLOWING THE RT RUDDE	R PEDAL TO DROP TO THE FLOOR, RUDDER CONTROL WAS LOST AND THE TAKE OFF ABORTED. UPON EXAMINATION OF THE AFFECTED PARTS I	T WAS NOTED THAT THE WELD HAD SEPARATED CLEANLY FROM THE TUBE AND ALL WELD FILLER MATERIAL REMAINED ON THE OPERATING LEV	ER HALF, INDICATING POSSIBLE POOR PENETRATION OF THE ORIGINAL WELD. THIS TORQUE TUBE  IS DIFFICULT TO INSPECT AT THE WEL	D LOCATION UNLESS THE FOOT WELL PANEL IS REMOVED TO ENABLE VIEWING FROM ABOVE. TH E SUBMITTER HAS INCORPORATED A SPECIAL	 IN DETAIL INSPECTION OF THE AFFECTED PART/WELD ON A REPEATATIVE BASIS.	1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2003082200107	20030822	00107	EA  	2003	8	22	CA030613005      	1	20030605	G	5753		RIB             			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29987								(CAN) EXCESSIVE LOOSENESS BETWEEN THE TWO HALVES OF THE FLAP AT THE CENTER HINGE ARM POSITION. THE RIBS ON EITHER SIDE O	F THE HINGE ARM ARE ASSEMBLED TO THE ARM BY THE USE OF MS20470AD5-24 SOLID RIVETS.  IT WOULD APPEAR THAT THERE HAS BEEN 	SOME WORKING BETWEEN THE RIVET HEADS AND THE RIBS WHICH HAS CAUSED WEARING OF THE RIB AROUND THE RIVET HOLES.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003082200108	20030822	00108	SW  	2003	8	22	CA030613006      	1	20030307	G	6320	206040532005	CASE            	BELL        		BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TRANSMISSION	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						BMC51561					(CAN) TRANSMISSION RECEIVED FOR 1,500 HOUR INSPECTION. TOP CASE REMOVED AND 10 TEETH FROM THE INVOLUTE SPLINES WERE BROK	EN WHICH IS NOT IN ITSELF AN UNUSUAL OCCURRENCE. WHEN A NEW REPLACEMENT WAS OBTAINED FROM BELL THE LOCKWIRE HOLES FOR TH	E FILLER CAP AND CHIP PLUG HAD NOT BEEN DRILLED. A SECOND CASE WAS ACQUIRED FROM BELL AND IT WAS CORRECTLY DRILLED.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003090200002	20030902	00002	EA  	2003	9	2	CA030613007      	1	20030609	G	5511	C2TP57	SPAR            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLETED CF-91-42, SB 2/47 REV.C ON POST MOD 2/758 STABILIZER. NO CRACK WAS INITIALLY DETECTED. ALTHOUGH IT IS NO	T REQUIRED BY THE AD, BRACKETS C2TP159A AND C2TP160A WERE REMOVED FOR DETAILED VISUAL INSPECTION OF THE SPAR. THE SPAR W	AS FOUND CRACKED UNDER THE RT BRACKET (C2TP160A) APPROXIMATELY .2500 INCHES ABOVE THE TOP BRACKET BOLT HOLE. THE GUSSET 	PLATE C2TP171 WAS ALSO CRACKED DIRECTLY BEHIND THE SPAR CRACK. THESE CRACKS ARE LOCATED PARALLEL TO AND DIRECTLY IN FRON	T OF THE RADIUS OF WASHER PLATE P/N C2TP177. BOTH CRACKS ARE APPROXIMATELY .2500 - .6258 INCHES LONG.		1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2003071800059	20030718	00059	EA  	2003	7	18	CA030613008      	2	20030612	G	7261	3024566	BYPASS VALVE    			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	OIL FILTER	WORN            	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) LT ENG OIL PRESSURE DROPPED FROM NORMAL 92 P.S.I. TO APPROX 60 P.S.I.   PILOT REDUCED POWER TO 1100 LBS OF TORQUE.	 TORQUE STARTED TO FLUCTUATE AND OIL PRESS CONTINUED TO DROP TO 50 P.S.I., PILOT FEATHERED AND SHUT DOWN ENG.    DECLARI	NG AN EMERGENCY AND LANDED WITHOUT FURTHER INCIDENT. UPON INSP OF ENG, OIL WAS FOUND L EAKING OUT OF ENG INTAKE. AFTER S	OME TROUBLESHOOTING AND DISCUSSION WITH A TECH, IT WAS DECIDED TO REMOVE OIL FILTER HSG, REPLACE O RINGS AND LAP CHECK V	ALVE SEAT, ON OUTSIDE OF HSG.  AS FURTHER PRECAUTION,  MAIN OIL FILTER AND CHIP DETECTOR WERE REMOVED, INSPECTED, CLEANE	D AND REINSTALLED.  NO METAL PARTICLES WERE FOUND. ENGINE WAS TOPPED UP WITH OIL AND ENGINE RUNS COMPLETED SERVICEABLE.	1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003072100019	20030721	00019	SW  	2003	7	21	CA030613009      	1	20030525	G	6320	212040054007	CASE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					M/R GEARBOX	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11290								(CAN) WHILE CARRYING OUT A DAILY CHECK ON THE AIRCRAFT THE ENGINEER NOTICED THAT THE ONE EAR OF THE LIFT LINK SUPPORT ON	 THE TRANSMISSION SUPPORT CASE WAS BROKEN OFF.  THE TRANSMISSION SUPPORT CASE WAS REPLACED					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003090800162	20030908	00162	GL  	2003	9	8	CA030615001      	1	20030615	G	3240		CONTROL CABLE   			AMTR  	AVRO  	LANCASTER10 	       	GL  	PCKARD	224   	224         		SO  	HAMSTD	23E	23EX583     	NE  	CONTROL COLUMN	STRETCHED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT DEPARTED TAXIWAY AFTER PILOT EXPERIENCED PARTIAL BRAKE LOSS WHILE RETURNING TO THE RAMP AFTER LANDING.  D	ISCOVERED A STRETCHED PILOT'S CONTROL CABLE TO BRAKE PROPORTIONING VALVE, WHICH IN TURN LOWERED THE AIR PRESSURE AVAILAB	LE TO WHEELS.				2	H	7	4 	4V	4	V	RC	EXPA2M74	EXP4V	6	C	EXPP6C	 
2003090200003	20030902	00003	EA  	2003	9	2	CA030616001      	2	20030613	G	8500	75414	SUPPORT BRACKET 			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FUEL MANIFOLD SUPPORT BRACKET BREAKS AT BEND RADIUS-BELIEVE DUE TO STRESS INDUCED AT MANUFACTURE. BRACKET BROKE 4 	TIMES:1. AT 208.4 TTSNEACH TIME BRACKET REPLACED WITH NEW 2. AT 96.0 TTSN 3. AT 86.0 TTSN 4. AT 16.3 TTSN ON INSPECTION 	OF NEW BRACKETS WE FOUND DEEP IMPRESSIONS AT BEND RADIUS(INSIDE)FROM TOOLING- ALSO BEND IS SO SHARP THAT CRACKS ARE STAR	TING ON THE OUTSIDE OF BEND RADIUS. REPORTED FINDINGS TO SUPPLIER.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003090200004	20030902	00004	SW  	2003	9	2	CA030616002      	1	20030616	G	2752	19023	CABLE           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FLAP CONTROLS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE IS FRAYED AT UPPER ALUMINUM PULLEY.						1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2003090200005	20030902	00005	SW  	2003	9	2	CA030616003      	1	20030616	G	3220	7147061	FRAME           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TAIL SPRING	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FRAME TUBE WAS BROKEN OFF ON BOTH SIDES OF TAIL SPRING FWD ATTACH BUSHING.						1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2003071800060	20030718	00060	EA  	2003	7	18	CA030616004      	1	20030613	G	3234	574205A	SOLENOID        			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	SELECTOR VALVE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			35478			189					(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN ALL THREE GEAR STAYED UP AND LOCKED. AN EMERGENCY GEAR EXTENSION WA	S COMPLETED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE JACKED THE AIRCRAFT AND ATTEMPTED TO COMPLETE 	GEAR SWINGS WHEN THEY SELECTED GEAR UP THERE WAS NO RESPONSE. MAINTENANCE FOUND THAT THE LANDING GEAR SELECTOR VALVE SOL	ENOID DID NOT MAKE ANY NOISE WHEN THE GEAR SELECTOR WAS UP OR DOWN. THE LANDING GEAR SELECTOR VALVE SOLENOID WAS REPLACE	D AND THE GEAR SWUNG WITHOUT FURTHER INCIDENT.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2003071800061	20030718	00061	SW  	2003	7	18	CA030617001      	1	20030616	G	5302	206031329003	ATTACH FITTING  			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAJOR INSPECTION THE TAILBOOM ATTACH FITTING UPPER LT FUSELAGE SIDE WAS FOUND CRACKED AT THE UPPER AFT RIVE	T HOLE.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003071800062	20030718	00062	EU  	2003	7	18	CA030617002      	1	20030520	G	5531	350A14111925	RIB             			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION OF THE UPPER VERTICAL FIN ATTACHMENT FRAME, AME DISCOVERED RIB TO BE CRACKED.  RIB REPLA	CED AS PER REPAIR MANUAL AND A/C RETURNED TO SERVICE.					1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2003072100020	20030721	00020	SW  	2003	7	21	CA030617003      	1	20030514	G	6320		FITTING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SENT IN FOR OVERHAUL, DUE TO BEARING CHANGE NDT INSPECTION FOUND A 1 INCH CRACK AT BASE OF BEARING LUG TO BASE OF 	FRAME NEXT TO PIN.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003090800164	20030908	00164	NM  	2003	9	8	CA030618001      	1	20030613	G	5610		WINDOW          			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					COCKPIT	BIRD STRIKE     	W				C				ABORTED TAKEOFF         				C			F.O.D.                    			TO	TAKEOFF        	1			CA											(CAN) CREW REPORTS A SEAGULL STRUCK THE CO-PILOT'S R1 WINDOW AT ABOUT 100 KNOTS WHEN DEPARTED. TAKE-OFF WAS REJECTED RES	ULTING IN A 'HIGH ENERGY STOP'. AIRCRAFT TAXIED BACK TO THE RAMP WITH NO FURTHER INCIDENTS TO REPORT. MAINTENANCE INSPEC	TED THE AIRCRAFT, HIGH ENERGY STOP INSPECTION PER MM. ONE FAULT FOUND, MELTED SUBSTANCE ON NR 2 BRAKE (RUNWAY ASHPHALT) 	- MAINTENANCE R EPLACED NR 2 BRAKE ASSEMBLY.BIRD STRIKE INSPECTION COMPLETE PER MM. BIRD REMAINS REMOVED FROM R1 WINDOW 	AREA - NO FURTHER FAULTS FOUND. AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003082200098	20030822	00098	CE  	2003	8	22	CA030618002      	1	20030617	G	3246	95440263	WHEEL           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AT OVERHAUL THE INNER WHEEL HALF WAS FOUND TO BE CRACKED AT ONE CORNER RADIUS OF EACH BRAKE DISC KEYWAY. THE CRACK	S EMINATED FROM A MACHINED NOTCH IN THE RADIUS OF THE CORNERS. THE OPPOSITE CORNER OF EACH KEYWAY WAS SMOOTH.					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2003071800063	20030718	00063	NM  	2003	7	18	CA030618003      	1	20030617	G	3260	858601	PROXIMITY SENSOR			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			26210	26210							(CAN) DURING SELECTION OF GEAR DOWN ON APPROACH, THE GEAR FAILED TO EXTEND. THREE RED GEAR LIGHTS ILLUMINATED, AMBER WAR	NING LIGHT IN SELECTOR HANDLE ILLUMINATED, GEAR DOORS DID NOT OPEN.  AIRCRAFT RETURNED TO ORIGINATING AIRPORT,  ALTERNAT	E GEAR EXTENSION USED, GEAR EXTENDED AND AIRCRAFT LANDED NORMALLY.  PSEU SHOWING FAULT CODES 53 & 55 (INTERNAL CARD FAIL	URES). LANDING GEAR PROXIMITY CONTROL BOX (PSEU) REPLACED.  GEAR SWINGS CARRIED OUT . AIRCRAFT RETURNED TO SERVICE , NO 	FURTHER FAULTS.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003072100021	20030721	00021	CE  	2003	7	21	CA030618004      	1	20030616	G	3246	9544008	LINER           	GOODYEAR    		LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					KEYWAY	BENT            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						MAY772454					(CAN) ONE OF TWO MS20427-4C7 RIVETS THAT HOLD THE KEYWAY LINER ON THE INNER WHEEL HALF FAILED ALLOWING THE CENTRIFUGAL F	ORCE OF THE SPINNING WHEEL TO BEND THE LINER OUTWARD UNTIL IT CONTACTED THE LOWER TORQUE LINK, DAMAGING IT AND ALSO CUTT	ING THE SIDEWALL OF THE TIRE. A SIMILAR  INCIDENT OCCURED EARLIER ON ANOTHER LEAR 35 THAT RESULTED IN DAMAGE TO THE GEAR	 LEG. THE DAMAGED PARTS IN BOTH CASES HAD TO BE REPLACEDTHE RIVETS ARE OFTEN FOUND LOOSE AND REPLACED AT WHEEL OVERHAUL.	 A COMPANY PROCEDURE BULLETIN HAS NOW BEEN ISSUED TO INSPECT THE LINER RIVETS FOR LOOSENESS AT EACH 50 CYCLE BRAKE WEAR 	CHECK.	2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2003082100085	20030821	00085	EU  	2003	8	21	CA030618005      	1	20030613	G	2450	LHA4B6101	SWITCH          	LUCAS       	LHA4B6101   	STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					MASTER	JAMMED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) THIS SWITCH SWITCHES POWER FROM EXTERNAL TO OFF AND TO INTERNAL POWER. THE SWITCH JAMMED AND IT WAS PHYSICALLY IMP	OSSIBLE TO MOVE THE SWITCH TO THE OFF POSITION.					2	H	7	2 	4T	4	T	 	A41EU   	E4EA				 
2003082100088	20030821	00088	EU  	2003	8	21	CA030618006      	1	20030613	G	5210	500221XXX321	SPRING          			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					PAX DOOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THIS PART IS THE STRUT THAT LOCKS THE MAIN CABIN DOOR IN THE OPEN POSITION. THE INTERNAL SPRING FAILED CAUSING THE	 DOOR TO COME TO A SUDDEN STOP WHEN FULLY OPEN. THIS CAUSES STRESS ON THE LOCKING STRUT AND DOOR FRAME.					2	H	7	2 	4T	4	T	 	A41EU   	E4EA				 
2003071800064	20030718	00064	WP  	2003	7	18	CA030618007      	1	20030618	G	5511	369D23623	SPAR            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						009991878					(CAN) DURING 100 HR INSPECTION SMOKING RIVETS WERE OBSERVED ON THE BOTTOM CENTER DOUBLER OF THE HORIZONTAL STABILIZER. I	NVESTIGATION REVEALED SPAR CRACK IN WEB AND LOWER FLANGE. HORIZONTAL STAB WAS REMOVED AND SENT OUT FOR SPAR REPLACEMENT.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003072100022	20030721	00022	WP  	2003	7	21	CA030618008      	2	20030617	G	7321	8974573	BYPASS VALVE    			BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE	INTERMITTENT    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			X			ENGINE FLAMEOUT           			CL	CLIMB          	1			CA											(CAN) ON TAKE OFF,  BOTH ENGS PRODUCED NORM TAKE OFF PWR AT 400 FT AGL, CAPT CALLED FOR CLIMB PWR,  RT ENG POWER REDUCED	 TO 30 PERCENT TORQUE.   A/C RETURNED TO LAND WITH RT ENG SHUTDOWN & RT PROP FEATHERED.  MAINT RECEIVED A/C WITH RT PROP	 FEATHERED.  PROP WAS UNFEATHERED & VARIOUS FUEL CONTROL & SHUT OFF COMPONENTS CHECKED FOR PROPER OP.  NO FAULTS FOUND. 	GRD RUNS CARRIED OUT.  NO FAULTS FOUND. A FLT TEST REQUESTED & CARRIED OUT, NO FAULTS FOUND.  A/C RELEASED FOR SERVICE. 	 4 FLTS LATER, PILOT REPORTED TORQUE TEMP LIMITING SYS TEST PRODUCING ABNORMAL LARGE DROPS IN TORQUE, TEMPS & FUEL FLOW.	 SYS IS ACTIVE DURING TAKE OFF & ITS PURPOSE IS TO PREVENT DAMAGING ENG WITH EXCESSIVE TORQUES OR TEMPS.	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	3PNE	 
2003082100091	20030821	00091	NE  	2003	8	21	CA030619001      	2	20030527	G	7261	UL39099	BEARING         			BOEING	757   	757200      	1384950	NM  	RROYCE	RB211 	RB211535*   	 	NE  					NR 1 ENGINE	FRACTURED       	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			13434								(CAN) HIGH OIL CONSUMPTION AIRCRAFT N752NA, NR 1 ENGINE 31652 HAD CONSUMED APPROX. 17 QUARTS OF OIL AFTER 5.5 HR FLT FRO	M OKLAND TO MIAMI, 18 MAY 2003. ENGINE IS AT RRC FOR REPAIR, DURINGDISMANTLING OF MODULE 5, THE HP/IPT OIL VENT TUBE WAS	 FOUND FRACTURED AT WELD JOINT. ROLLS-ROYCE FRS 5585 REPLACES DAMAGED TUBE.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2003082100093	20030821	00093	CE  	2003	8	21	CA030619002      	1	20030617	G	3230	MS24171D1	RELAY           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) WHEN THE LANDING GEAR WAS SELECTED DOWN ON APPROACH THE GEAR FAILED TO EXTEND. A MANUAL EXTENSION WAS CARRIED OUT.	 MAINT JACKED THE AIRCRAFT AND SELECTEDGEAR UP AND THE GEAR AGAIN WOULD NOT MOVE. TROUBLESHOOTING FOUND THAT THE ABOVE R	ELAY WAS EXTREMELY HOT AND NOT FUNCTIONING. THE RELAY WAS REPLACED, SEVERAL GEAR SWINGS WERE CARRIED OUT AND THE AIRCRAF	T WAS RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003082100095	20030821	00095	EU  	2003	8	21	CA030619003      	1	20030617	G	3020	SM600BA	CIRCUIT BREAKER 			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  					INTAKE HEATER	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) PILOT TURNED ON MASTER SWITCH AT BEGINNING OF DAY AND GROUND HANDLERS NOTICED SMOKE COMING FROM THE RT ENGINE INTA	KE LIP HEATER. THE MASTER WAS SHUT OFF BUT EXTENSIVE DAMAGE HAD ALREADY OCCUREDTO THE INTAKE LIP HEATER. IT WAS FOUND TH	AT THE ABOVE REMOTE CONTROL CIRCUIT BREAKER HAD PERMANENTLY CLOSED CONTACTS WHICH IN TURN CAUSED THE INTAKE LIP HEAT TO 	REMAIN ON. INTAKE LIP HEATER AND CIRCUIT BREAKER WERE REPLACED AND AIRCRAFT RETURNED TO SERVICE			2	H	7	2 	4T	4	T	 	A41EU   	E4EA				 
2003082100096	20030821	00096	EA  	2003	8	21	CA030619004      	1	20030616	G	3260	N864808	PSEU            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON GEAR DOWN SELECTION, GEAR DISAGREE MESSAGE DISPLAYED. POSITION SENSOR ELECTRONICS UNIT REPLACED AND CHECKED SER	VICABLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003071800065	20030718	00065	SO  	2003	7	18	CA030619005      	1	20030612	G	3230	42042000	PIVOT           			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED INSPECTION,  A CRACK WAS FOUND ON THE INSIDE RADIUS OF THE LT MLG ACTUATOR PIVOT ARM.						1	L	7	2 	3T	4	T	 	A8EA    	E4EA	6	C	P15EA	 
2003072100023	20030721	00023	EU  	2003	7	21	CA030619006      	1	20030616	G	3250	Z4242390000	CABLE           			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					NLG STEERING	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING AN AIRCRAFT THE STUDENT PILOT NOTICED THAT THE NOSE WHEEL STEERING WAS NOT RESPONDING WITH TURNS TO 	THE RT.  MAINTENANCE WAS NOTIFIED AND IT WAS FOUND THAT THE RT NOSE GEAR STEERING CABLE WAS BROKEN AT THE AFT END OF THE	 CABLE WHERE THE ATTACH BOLT GOES THROUGH THE THIMBLE.  THE CABLE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.  IF	 THE AIRCRAFT IS NOT ROLLING WHEN NOSE WHEEL STEERING IS ACTIVATED IT PUTS STRESS ON THE NLG STEERING SYSTEM. THIS SYSTE	M DOES NOT AFFECT RUDDER MOVEMENT.		1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003082100098	20030821	00098	NM  	2003	8	21	CA030619007      	1	20030619	G	3222	8800	STRUT           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22169								(CAN) WHILE PERFORMING DEHAV TASK CARD 3220/02 VISUAL INSPECTION OF NLG ASSY GREASE FITTINGS ON NLG TRAILING ARM TO SHOC	K STRUT PISTON LINK ASSY.  FOUND GREASE FITTINGS MISSING AND LINK WORN ON DISASSEMBLY.THE FOLLOWING PARTS HAD SUSTAINED 	EXTENSIVE DAMAGE: PIN P/N 8871-1 DIAMETER HAD BEEN REDUCED ON ONE SIDE BY .151 INCHES, DIAMETER OF PIN MEASURED 1.186. L	INK ASSY LOWER BORE WORN OVAL DIMENSIONS 1.311 X 1.381.TRAILING ARM WORN BETWEEN BUSHING LUGS .162. LINK BUSHING PN 8885	-3 ONLY APPROX 1/3 REMAINED. TRAILING ARM LINK PIN BUSHINGS PN 8806-7 PITTED AND SCORED.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003071800066	20030718	00066	NM  	2003	7	18	CA030620001      	1	20030618	G	2910	82960010115	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			34525								(CAN) A HYDRAULIC LINE FROM THE NR 2 HYD SYS THAT FEEDS THE RUDDER PRESSURE REGULATOR DEVELOPED A HAIRLINE CRACK IN THE 	TAIL SECTION. . THE NR 2 SYSTEM HYDRAULIC QUANTITY DEPLETED TO BELOW MINIMUM.  AN EMERGENCY LANDING GEAR EXTENSION WAS C	ARRIED OUT AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. A FLEXIBLE HYDRAULIC LINE WAS INSTALLED TEMPORARILY AS DETA	ILED IN MAINTENANCE MANUAL CHAPTER 20-50-52. NR 2 HYDRAULIC PUMP WAS REPLACED AS A PRECAUTION, GEAR SWINGS CARRIED OUT A	ND THE AIRCRAFT RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003072100024	20030721	00024	SW  	2003	7	21	CA030620002      	1	20030618	G	5320	27200637	RECEPTACLE      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					DOOR FRAME	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23728								(CAN) WHILE CARRYING OUT SERVICE LETTER 226-SL-027, WHICH CALLS FOR INSPECTION OF THE ALL DOOR LATCH RECEPTICLES, WE FOU	ND 3 CRACKED ON PASSENGER DOOR FRAME & 2 CRACKED ON THE AFT CARGO DOOR FRAME. ONE RECEPTICAL WAS CRACKED ALMOST IN HALF 	WHILE OTHERS SMALL AND DIFFICULT TO SEE. THE ECCENTRIC BUSHING WHICH MOUNTS IN THE RECEPTICAL MUST BE REMOVED TO SEE THE	 CRACKS.  CRACKED RECEPTICLES WERE DISCOVERED IN ANOTHER METRO II IN THE FLEET THIS SERVICE LETTER IS NOT MANDATORY.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003082100101	20030821	00101	EA  	2003	8	21	CA030620003      	1	20030615	G	7110	AC35500	RING ASSEMBLY   			DHAV  	DHC3  	DHC3        	2800202	EA  	WSK   	ASZ62 	ASZ62IRM18  	 	NE  					COWL	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) NOSE COWLING PARTIALLY SEPARATED FROM ENGINE CAUSING THE TOP AND RT SEGMENTS OF COWL TO CONTACT THE PROP. AFTER LA	NDING THE COWL RING WAS INSPECTED AND 5 OF THE 9 ATTACH LUGS HAD FAILED AND 2 OF THE LUGS HAD THE VIBRATION ISOLATORS PU	LLED THROUGH. THE FAILURE OF THE LUGS WAS PROGRESSIVE IN NATURE AND SHOULD HAVE BEEN VISABLE DURING DAILY AND ROUTINE IN	SPECTIONS.			1	H	7	1 	3R	3	R	 	A815    	E10NE				 
2003082100103	20030821	00103	WP  	2003	8	21	CA030620005      	1	20030620	G	2910		VALVE           			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					HYD SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING APPROACH INTO YELLOW, HYD SYSTEM FAILURE.  MANUAL GEAR EXTENTION CARRIED OUTAND A/C LANDED WITH OUT DIFFICU	LTY.  LT GEAR BLOW BACK VALVE FOUND FAILED (CAP BURST), REPLACED IAW MM AND A/C RETURNED TO SERVICE					2	L	7	2 	4R	4	T	 	6A6     	E282				 
2003071800067	20030718	00067	NM  	2003	7	18	CA030620006      	1	20030619	G	2910		LINE            			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					HYD SYSTEM	MISINSTALLED    	W				A				UNSCHED LANDING         				W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) FLT CREW REPORTED THAT NLG UNLOCKED BUT FAILED TO RETRACT. SUBSEQUENT GEAR SELECTS WERE UNSUCCESSFUL UNTIL SPEED R	EDUCED.  GEAR DID RETRACT AT 160 KNOTS IAS,  VERY SLOW,  RETURN TO YEG. THIS ANOMALY DATES BACK TO 06/4/03, WHEN SKI ACT	UATOR ROBBED TO SERVICE ANOTHER A/C. REPLACING SKI ACTUATOR, FLEX LINES LEADING TO ACTUATOR WERE INSTALLED INCORRECTLY. 	 INSTALLATION RESULTED IN FLEXIBLE HYD LINES BECOMING CRIMPED DURING GEAR RETRACTION. CULMINATING ON 06/17/03 WHEN NLG R	EPORTED SLOW TO RETRACT.  LINES FOUND TO INSTALLED INCORRECTLY AT TIME.  LINES WERE CORRECTLY INSTALLED & AIRCRAFT DISPA	TCHED.  HOWEVER SNAG RETURNED ON JUNE 19, CAUSING AIR RETURN, MAINT UNABLE TO CONFIRM THE FAULT DURING GEAR SWINGS.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003072100025	20030721	00025	NE  	2003	7	21	CA030623001      	2	20030618	G	8530		CYLINDER        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) AFTER A SCOOPING RUN THE CREW NOTICED A 30 DROP IN THE BMEP ON THE LT ENGINE. LOAD WAS DROPPED AND A/C CLIMBED TO 	2500 FT AND EXECUTED A PRECAUTIONARY ENGINE SHUT DOWN. THE A/C FLEW TO BASE WHERE IT LANDED UNEVENTFULLY.  THE NR 5 CYLI	NDER WAS CRACKED.  CYLINDER WAS REPLACED & A/C RETURNED TO SERVICE.				2	H	7	2 	4R	4	R	RT	A14EA   	E231				 
2003082100105	20030821	00105	NM  	2003	8	21	CA030623003      	1	20030622	G	3260	841005	PSEU            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			21563								(CAN) DURING GEAR DOWN SELECTION , NO 'GREEN' INDICATION FOR NLG , GEAR CYLED,  ALTERNATE GEAR EXTENSION SELECTED. SYS R	ESET AND NORMAL GEAR DOWN SELECTED , ALTERNATE AND NORMAL GEAR INDICATION BOTH SHOWED 'GREEN' INDICATION. NORMAL LANDING	. MAINTENANCE REPLACED PSEU , GEAR SWINGS CARRIED OUT WITH NO FAULTS. AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003082100107	20030821	00107	CE  	2003	8	21	CA030623004      	1	20030613	G	3020	9091010017	DUCT            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ANTI-ICE SYSTEM	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE CARRYING OUT A COMPANY CAMPAIGN NOTICE TO INSPECT ENGINE INLET ANTI-ICE DUCTS FOR CRACKS, BOTH ENGINE SHORT 	LT DUCTS WERE FOUND CRACKED. ONE DUCT WAS CRACKED ON ONE END AND THE OTHER WAS CRACKED AT BOTH ELBOW ENDS. THE DUCTS HAD	 ACCUMULATED 191.5 HOURS SINCE INSTALLATION AS PART OF SB 71-3142. BOTH ENGINE RT LONG DUCTS HAD ALSO BEEN REPLACED SINC	E SB 71-3142 INSTALLATION. THE POST SB PARTS HAVE A HIGHER FAILURE RATE THAN THE UNITS THEY ARE REPLACING.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003071800068	20030718	00068	EA  	2003	7	18	CA030624001      	1	20030618	G	3232	NAS620434D	BOLT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG DOOR ACT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  ROLLER BEARING WITH NLG DOORS FULLY CLOSED SHOULD FALL WITHIN ITS MECHANICAL CAM-LOCK  WHEN FUNCTIONING NORMALLY.	 WHEN HYDS ARE REMOVED, RETRACT ACTUATOR WILL RELAX AND CAM-LOCKED ROLLER BEARING WILL KEEP NLG DOOR FULLY CLOSED, PREVE	NTING FROM FALLING 'OPEN'.  IF PIVOT BOLT BECOMES CORRODED AND RESTRICTS MOVEMENT OF ITS SPRING-LOADED PIVOT LEVER.  ROL	LER BEARING CAN HANG-UP AND NOT FALL INTO ITS CAM-LOCK SLOT. WHEN HYDRAULICS ARE REMOVED AND DOOR RETRACT ACTUATOR RELAX	ES, DOORS WILL DROP OPEN.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082200096	20030822	00096	NM  	2003	8	22	CA030624003      	1	20030412	G	2130	92148C010101	MODULE          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					CABIN PRESSURE	FAILED          	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, PILOT OBSERVED DIFF PRESS WENT FROM 4,5 TO 0 & RATE WENT TO A 1500 FPM DESCEND. PILOT MONITORED INST	RUMENTS CLOSELY & SHORTLY DIFF PRESS WENT BACK TO NORMAL & RATE CLIMBED NORMAL 5-600 FPM. AT ALL TIMES CABIN ALT WAS STE	ADY ON 4200 FT. LEVELING OFF AT FL 180, FELT A CLICKING IN OUR EARS & CA CALLED & SAID THEY FELT SAME WAY. STARTED A NOR	MAL DESCEND TO FL100 & CONTINUED FLT TOP CPH AT FL100.  BEFORE LEVELING OF AT FL100, A LOUD WHISTELING NOISE IN A/C.  MA	DE DESCEND INBOUND TO BASE & DECIDED TO DUMP CABIN PRESSURE ON APPROACH & LAND DEPRESSURIZED. CHECKED FOR FAULTS. FAIL T	O CABIN INDICATION MODULE RECORDED. CIM REPLACED ACCORDING AMM. CABIN PRESS TEST PERFORMED WITHOUT REMARKS.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003082100110	20030821	00110	NM  	2003	8	21	CA030624004      	1	20030506	G	3230		SQUAT SWITCH    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER LANDING GEAR WAS SELECTED UP, LANDING GEAR WAS STILL DOWN INDICATING 3 GREEN AND 3 RED LIGHTS. TRIED TO RECY	CLE THE GEAR ONCE WITHOUT SUCCESS. RETURNED FOR A NORMAL LANDING. PASSENGERS WHERE BRIEFED IN THE AIR AND ON GROUND.  HA	RNESS ASSY WOW SWITCH ON NOSE WHEEL CENTERING REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003082100116	20030821	00116	SW  	2003	8	21	CA030625001      	1	20030623	G	2913	MS219266	ELBOW           	VICKER      		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					HYD PUMP	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA						MX326593					(CAN) A HYD LEAK WAS FOUND DURING A GROUND RUN TO CHECK FOR LEAKS AFTER MINOR MAINTENANCE. THE ENGINEER NOTICED HYD FLUI	D DRIPPING FROM AN ELBOW FITTING ON THE NR 1 HYD PUMP. THE FITTING AND LINE B-NUT WERE CHECKED AND FOUND SECURE. THE FIT	TING WAS REMOVED AND UPON FURTHER INSPECTION A CRACK WAS FOUND. THE AIRCRAFT WAS REMOVED FROM SERVICE AND A REPLACEMENT 	PART ORDERED.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003082100118	20030821	00118	NM  	2003	8	21	CA030625002      	1	20030526	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG WOW	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) GEAR UP SELECTION WAS UNSUCCESSFUL. 3 GREEN & 3 RED LIGHTS AT THE SAME TIME. GEAR RECYCLED BUT WITHOUT SUCCESS. WE	 RETURNED FOR A NORMAL LANDING (NO EMERGENCY DECLARED). CABIN AND PAX BRIEFED AND DEBRIEFED. INVESTIGATION/ACTION HARNES	S ASSEMBLY WOW SWITCH ON NOSE WHEEL CENTERING REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003071800069	20030718	00069	NM  	2003	7	18	CA030625003      	1	20030519	G	3297		WIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					WOW SWITCH	SHORTED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, WOW CAUTION CAME ON AFTER SELECTING GEAR UP.  ALL OTHER INDICATIONS NORMAL. QRH PERFORMED AND A/C L	ANDED AFTER CONSULTING TCC. TROUBLESHOOTING WIRES TO LT GEAR WOW NR 2 SENSOR WAS FOUND SHORTED. SENSOR ASSEMBLY REPLACED	 ACCORDING AMM TASK 32-61-00.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003071800070	20030718	00070	CE  	2003	7	18	CA030625004      	1	20030625	G	3213	66422172	STRUT           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NLG	PUNCTURED       	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) PILOT REPORTED THAT THE NOSE OLEO WAS BOTTOMING OUT WHILE TAXING THE AIRCRAFT. WHEN ATTEMPTING TO SERVICE THE AIRS	IDE OF THE OLEO IT WAS DISCOVERED THAT OIL WAS PRESENT AT THE AIR VALVE. THE STRUT WAS DISASSEMBLED TO VERIFY IF ANY DAM	AGE HAD OCCURRED TO THE ISOLATION PISTON PACKINGS.  THE AME FOUND THAT THE METERING PIN HAD PUNCTURED THE TOP OF THE ISO	LATOR PISTON.  THE DAMAGED PARTS WERE REPLACED & THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003071800071	20030718	00071		2003	7	18	CA030625005      	4	20030610	G	3416		INDICATOR       			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ALTIMETER	INCORRECT       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STANDBY ALTIMETER WAS FOUND TO HAVE THE INCORRECT FACE INSTALLED. PART NUMBER INDICATES THE ALTIMETER IS METRIC SE	LECTABLE RANGE IS METRIC HOWEVER FACE OF ALTIMER STATES INCHES OF MERCURY RATHER THAN MILLIBARS.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003072100027	20030721	00027	SO  	2003	7	21	CA030625006      	1	20030625	G	7332	486439	TRANSMITTER     			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					FUEL PRESSURE	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING FLT,  PILOT NOTICED THE FUEL PRESSURE INDICATION DROP TO ZERO, WITHOUT ANY CHANGE IN ENGINE FUNCTION.  THE 	PILOT CUT SHORT HIS LOCAL FLT, & RETURNED TO THE AIRPORT.  THE FUEL PRESSURE TRANSDUCER WAS REPLACED WITH ANOTHER NEW TR	ANSDUCER, AND THE PRESSURE INDICATION RETURNED TO NORMAL. FURTHER TO THIS, THESE TRANSDUCERS ARE FAILING AT AN ALARMING 	RATE. EVEN A DISTRIBUTOR OF THESE PRODUCTS ADMITS THAT THEY ARE A DISPOSABLE ITEM.			1	L	7	1 	3O	3	O	 	A18SO   	E223				 
2003072100104	20030721	00104	NM  	2003	7	21	CA030625007      	1	20030618	G	2721	682015	SWITCH          			DHAV  	DHC8  	DHC8315     	2809010	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RUDDER	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) DURING CLIMB ALTITUDE PASSING 3,000 FT,  PILOT PUT RUDDER TRIM SWITCH TO A/C LT DIRECTION. HEARD STRANGE SOUND & R	UDDER TRIM CONTINUED MOVING TO A/C LT DIRECTION UNTIL FULL LT DIRECTION. TRIED TO PUT SWITCH TO RT DIRECTION BUT COULDN`	T CONTROL A/C WITH USING RUDDER TRIM SWITCH.  RUDDER TRIM WAS STILL FULL LT. PUSHED RUDDER PEDAL TO RT DIRECTION TO MAIN	TAIN A/C ATTITUDE & DECREASED AIR SPEED TO 160KT ANOTHER FLT. TOO HARD TO CONTROL A/C ATTITUDE WITH MANUAL RUDDER IN AIR	SPEED 220 KT. IN CRUSE, ATTEMPTED CIRCUIT BREAKER (RUDDER TRIM ACTUATOR) RECYCLED IAW WITH AOM , BUT CONDITION DID NOT R	ECOVER. LANDED AT DESTINATION. ROTOARY SWITCH REPLACED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003072100105	20030721	00105	NM  	2003	7	21	CA030625008      	1	20030620	G	3220	8600113	ACTUATOR        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG STEERING	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA			15728								(CAN)  PILOT COMPLAINED OF NLG WHEEL SHIMMY ON LANDING. DURING INVEST FOUND EXCESSIVE PLAY IN NLG STEERING ACTUATOR & TE	LESCOPIC LINKS.  A/C BROUGHT TO HANGER & PLACED ON JACKS.  FOUND THAT WHEN YOU MOVE NOSE WHEELS LT & RT STEERING ACTUATO	R MOVING FORE & AFT.  ATTACH BOLTS FOR CENTERING SPRING WERE ALSO LOOSE & ASSY WAS MOVING FORE & AFT.  DUE TO MOVEMENT O	F ACTUATOR,  INPUT END GLAND NUT OF ACTUATOR WOULD OPEN UP CAUSING A HYD LEAK. STEERING ACTUATOR TRANSFER TUBE REMOVED &	 FOUND DAMAGED IN CENTRE OF TUBE.  A SERVICEABLE TUBE, STEERING ACTUATOR, TELESCOPIC LINKS & CENTERING SPRING WHERE FITT	ED TO A/C.  DURING CHECKS FOUND STEERING LIMIT SWITCH U/S.  SWITCH REPLACED.  CHECKS CARRIED OUT WITH NO DEFECTS.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003082100119	20030821	00119	CE  	2003	8	21	CA030626001      	1	20030624	G	5220	651125619	SEAL            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ESCAPE HATCH	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) IN PREPARATION FOR A PHASE 5 INSPECTION MAINTENANCE TECHNICIANS HAD DIFFICULTY REMOVING THE EMERGENCY EXIT DOOR. U	PON REMOVAL IT WAS NOTED THAT THE DOOR SEAL HAD SOME FORM OF LUBRICANT ON IT THAT CAUSED THE SEAL TO STICK TO THE FRAME.	 THE AIRCRAFT MAINTENANCE MANUAL DOES NOT INDICATE ANY REQUIREMENT FOR IN SERVICE SEAL LUBRICATION. SUBSEQUENT REINSTALL	ATION AFTER CLEANING THE SEAL POSED NO DIFFICULTY.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003071800075	20030718	00075	EA  	2003	7	18	CA030626003      	2	20030613	G	8520	LW18840	CAMSHAFT        			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE WAS SENT IN FOR A PROP STRIKE INSPECTION. AFTER DISASSEMBLY THE CAMSHAFT WAS FOUND TO HAVE AN UNACCEPTA	BLE AMOUNT OF SPALLING ON THE NR 1 EXHAUST LOBE AND ON BOTH INTAKE LOBES. THE CAM AND LIFTERS WERE REPLACED WITH A MFG F	ACTORY NEW KIT.				1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2003072100029	20030721	00029	CE  	2003	7	21	CA030626004      	1	20030619	G	2435	230850041	STARTER GEN     			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ441A      	 	GL  					ENGINE	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) LT GENERATOR WENT OFF LINE IN FLIGHT. AFTER LANDING WE TRIED TO START THE LT ENGINE AND NO RESPONSE,THE LT STARTER	 GENERATOR WAS CHANGE WITH AN OVERHAUL UNIT. THE LT GENERATOR WAS DUE FOR OVERHAUL AT 2049 HOURS.					1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2003082100121	20030821	00121	EA  	2003	8	21	CA030626005      	2	20030612	G	8520	LW18840	CAMSHAFT        			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE WAS SENT FOR INSPECTION DUE TO METAL CONTAMINATION. AFTER DISASSEMBLY THE CAMSHAFT WAS FOUND TO HAVE SP	ALLING ON ALL THE LOBES, THE INTAKE LOBES BEING THE WORST. THIS SPALLING WAS THE CAUSE OF THE METAL CONTAMINATION. THE C	AMSHAFT WAS REPLACED WITH A FACTORY NEW KIT.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003082100123	20030821	00123	EA  	2003	8	21	CA030626006      	2	20030613	G	8520	LW18840	CAMSHAFT        			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE WAS SENT IN FOR CAMSHAFT CHANGE DUE TO CAMSHAFT FAILURE. THE CAMSHAFT WAS FOUND TO HAVE SEVERE WEAR ON 	THE NR 1 & 2 INTAKE LOBE. REPLACED WITH A FACTORY NEW CAMSHAFT.					1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003071800076	20030718	00076	EA  	2003	7	18	CA030626007      	2	20030612	G	8520	LW18840	CAMSHAFT        			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  	MUHBR	MTV	MTV9*       	EU  	ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE WAS SENT IN FOR INSPECTION DUE TO METAL CONTAMINATION. TWO PROBLEMS WERE DISCOVERED. FIRST, THE CONNETI	NG ROD CAPS WERE CONTACTING THE OPPOSING PISTON SKIRTS, THE CAPS WERE FOUND TO BE APPROXIMATELY .020 THICKER THAN SEVERA	L OTHERS MEASURED. THE SECOND PROBLEM FOUND WAS SPALLING ON MOST OF THE CAMSHAFT LOBES. BOTH THESE PROBLEMS CONTRIBUTED 	TO THE METAL CONTAMINATION. THE CYLINDERS, PISTONS A ND CAMSHAFT WERE ALL REPLACED WITH FACTORY NEW PARTS.			1	L	7	1 	3O	3	O	0	A76EU   	1E10	5	C	P24NE	 
2003072100030	20030721	00030	SO  	2003	7	21	CA030626008      	2	20030619	G	8520	646476	BEAM            		IO520MB     						CONT  	O520  	IO520MB     	17032	SO  					CON ROD	BENT            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE MAIN BEAM ON THE NR 2 & 6 CONNECTING RODS WERE BENT. NR 5 WAS THE MOST SEVERE. POSSIBLE CAUSE IS HYD LOCKING.											3	O			E5CE				 
2003072100092	20030721	00092	SO  	2003	7	21	CA030626009      	2	20030626	G	8530		CYLINDER HEAD   			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION FINE BRONZE PARTICLES FOUND IN OIL FILTER & SCREEN. FURTHER INVESTIGATION REVEALED ROCKER ARM BUSHIN	GS WORN. ALSO CYLINDER HEAD BOSSES WORN. THE ROCKER SHAFTS ON THESE NEW STYLE CYLINDERS ARE HELD IN PLACE WITH SET SCREW	S WHICH SEEM TO LOOSEN OFF. WE HAVE ALSO TRIED LOCTITE BUT IT SEEMS WITH NO SUCCESS. SUGGEST THAT ANY ONE WITH THESE NEW	 CYLINDERS CHECK THEM ASAP.			1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003072100093	20030721	00093	NM  	2003	7	21	CA030627001      	1	20030626	G	2710	BACC13AP6E2858	CONTROL CABLE   			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					RT INBD. AILERON	CHAFED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) DURING A ROUTINE MAINTENANCE INSPECTION, IT WAS OBSERVED THAT THE RT INBOARD AILERON CABLE ASSY WAS CHAFED AND WOR	N AT THE CABLE GUIDE. THE CABLE WAS REMOVED & NEW CABLE INSTALLED IAW MM 27-10-71. ADJUSTMENT AND FUNCTIONAL CHECK CARRI	ED OUT SERVICEABLE IAW MM 27-10-0.AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003071800077	20030718	00077	CE  	2003	7	18	CA030627002      	1	20030602	G	2510		INSULATION      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					HEADLINER	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION ON THE AIRCRAFT, THE COCKPIT HEADLINER WAS REMOVED TO ACCESS THE G-SWITCH FOR A FUNCTIONAL CH	ECK. ONCE THE HEADLINER PANEL WAS REMOVED A SECTION OF INSULATION THAT WAS NEXT TO THE MAP LIGHT FOR THE CO-PILOT WAS FO	UND SCORCHED AND BRITTLE FROM CONTACT WITH THE BACK OF THE LIGHT ASSEMBLY. THE INSULATION WAS REMOVED AND THE PANEL REIN	STALLED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003072100031	20030721	00031	CE  	2003	7	21	CA030627003      	1	20030620	G	7120		MOUNT           			CESSNA	182   	182J        	2072722	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ENGINE MOUNT CRACKED AT SUPPORT PADS. REINFORCED TO CARRY 10520 ENGINE AS PER P-PONK STC SA461NW ON JULY 96. MOUNT	 REPLACED WITH NEW MOUNT PN 4402. NO VIBRATION TO DATE.					1	H	7	1 	3O	3	O	NT	3A13    	E5CE	5	C	P21EA	 
2003072100094	20030721	00094	NE  	2003	7	21	CA030627004      	2	20030605	G	8530		EXHAUST VALVE   			DOUG  	B26   	B26C        	3200524	WP  	PWA   	R2800 	R280079     	52026	NE  					CYLINDER	FAILED          	W				E				ENGINE SHUTDOWN         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT OIL WAS NOTICED COMING FROM THE RT ENGINE. THE ENGINE WAS SHUTDOWN AND LANDED WITHOUT INCIDEN	T. MAINTENANCE FOUND THE EXHAUST VALVE ON NR 5 CYLINDER HAD FAILED.					2	M	7	2 	4R	4	R	 	L34     	5E8				 
2003072100095	20030721	00095	GL  	2003	7	21	CA030627005      	2	20030605	G	7323		GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			DE	DESCENT        	1			CA											(CAN) WHEN AIRCRAFT APPLIED POWER, GOVERNOR WOULD DROOP BUT WOULD RECOVER WITH A SLIGHT DELAY BUT WHEN AIRCRAFT DESCENDE	D AND GOVERNOR WOULD OVERSPEED IT WOULD NOT GOVERN AND DECREASE RPM AS WOULD BE NORMAL. TIME SINCE LAST REPAIR 114.8 HRS	.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003072100101	20030721	00101	SO  	2003	7	21	CA030627007      	2	20030609	G	8530	21153	SCREW           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					CYLINDER HEAD	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ROCKER SHAFT SET SCREW BECAME LOOSE AFTER 148.1 HRS OF OPERATION AND WORE THE ROCKER SHAFT BOSS IN CYLINDER HEAT M	AKING THE CYLINDER UNSERVICEABLE.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003082100128	20030821	00128	CE  	2003	8	21	CA030627010      	1	20030623	G	7810	1019100751	PLATE           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					EXHAUST SEAL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED INSPECTION, FOUND EXHAUST SEAL PLATE FROM LT ENGINE OUTBOARD EXHAUST STACK TO THE HEATED ENGINE I	NTAKE ANTI-ICE LIP WITH ONE BOLT MISSING AND THE REMAINING BOLTS LOOSE. THE RESULTING EXHAUST LEAK HAS CAUSED SOOT TO BU	ILDUP ON THE ENGINE CASES. THIS HAS CAUSED AND HIDDEN SEVERE CORROSION PITTING ON THE REDUCTION GEARBOX (RGB) CASE AND S	OME BOLTS AT ENGINE FLANGE 'B'. THIS COROSSION IS BEYOND ALLOWABLE LIMITS FOR A LOCAL FIELD REPAIR PER THE PWC ENGINE MM	 AND WILL REQUIRE REPLACEMENT OF THE RGB CASE.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003072100089	20030721	00089	SW  	2003	7	21	CA030627011      	1	20030617	G	7120	206069105101	MOUNT           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HR INSPECTION,  THE ENGINEER PERFORMING A VISUAL INSPECTION OF THE ENGINE MOUNTS FOUND A CRACK ON THE	 LOWER PORTION OF THE STRUT 1.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003072100032	20030721	00032	EA  	2003	7	21	CA030627014      	2	20030620	G	8530	71381	EXHAUST VALVE   			STOLAM	RC3   	RC3         	3080203	NM  	LYC   	O480  	GO480G2D6   	41527	EA  					NR 2 CYLINDER	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) ON INITIAL CLIMB OUT, SUDDEN VIBRATION OCCURRED. AIRCRAFT LANDED SAFELY. INVESTIGATION REVEALED FAILURE OF THE 7/1	6 INCH ZERO STEM EXHAUST VALVE IN CYLINDER NR 2.					1	H	7	1 	3O	3	O	RC	A769    	E275				 
2003072100075	20030721	00075	CE  	2003	7	21	CA030627015      	1	20030429	G	2820	05001183	LINE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					FUEL SYSTEM	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			14293								(CAN) ABOVE FUEL LINE WAS FOUND CHAFED DURING 200 HR INSPECTION.  IT WAS DETERMINED THIS WAS CAUSED FROM RUBBING ON STEE	RING ROD MOUNT.  THIS WOULD BE VERY DIFFICULT TO SEE BUT CLOSE INSPECTION SHOULD BE CARRIED OUT.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003072100076	20030721	00076	SO  	2003	7	21	CA030627016      	1	20030502	G	3230	2176000	ATTACH FITTING  			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) GEAR WOULD NO EXTEND WHEN SELECTED DOWN. EMERGENCY GEAR EXTENSION CARRIED OUT. LUG WAS FOUND BROKEN. THIS RESULTED	 IN JAMMING OF THE RETRACTION MECHANISM. THIS PART SHOULD BE INSPECTED FOR CRACKS AT INSPECTION. ALSO ATTENTION SHOULD B	E PAID TO THIS AREA AFTER HARD LANDINGS, GEAR UP LANDING OR ANY TIME THE GEAR HAS BEEN EXTENDED ABOVE ANY EXTENSION AIRS	PEED.			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2003072100077	20030721	00077	GL  	2003	7	21	CA030627017      	1	20030627	G	2730	2053840204	STOP            			DIAMON	DA20  	DA20A1      	2990000	GL  										ELEVATOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE ELEVATOR STOP WAS FOUND BROKEN OFF THE RT ELEVATOR HINGE BLOCK.  EXTENSIVE CORROSION WAS FOUND IN THE AREA OF 	THE FAILURE. THE AIRCRAFT WAS OPERATED FOR FOUR YEARS ON THE CALIFORNIA COAST.  IT IS UNCLEARIF THE SALT RICH ENVIRONMEN	T CONTRIBUTED TO THE CORROSION AND SUBSEQUENT FAILURE.				1	L	7	1 	3O			NT	TA4CH   					 
2003072100088	20030721	00088	NM  	2003	7	21	CA030627018      	1	20030627	G	2782		ACTUATOR        			BOEING	727   	72722C      	138400F	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					SLAT	FAILED          	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) 'A' SYSTEM HYDRAULIC FAILURE T/O ABORTED AND A/C RETURNED TO BLOCKS.  NR 6 SLAT ACTUATOR FOUND FAILED.REPLACED ACT	 AND A SYSTEM PUMP CASE DRAIN FILTERS INSPECTED/REPLACED. NO CONTAMINATION FOUND. AIRCRAFT RETURNED TO SERVICE.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003071800080	20030718	00080	EA  	2003	7	18	CA030628001      	1	20030626	G	2497	MS24171D1	RELAY           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELECTRICAL	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING FLT, CREW SMELLED ELECTRICAL BURNING ODOR. SYS SYSTEMATICALLY SHUT DOWN INCLUDING, AVIONICS & AIRCRAFT MAST	ER, ODOR DISSIPATED. ALL RADIOS WERE SWITCHED OFF IN AN ATTEMPT TO SECURE OPERATION OF ONE RADIO FOR COMMS.  A/C & AVION	ICS MASTER WERE SWITCHED ON WITH AN IMMEDIATE RETURN OF ODOR.  A/C AVIONICS MASTER WAS AGAIN ISOLATED & ODOR DISSIPATED.	   A/C MASTER WAS TURNED ON TO ESTABLISH BASIC A/C SYSTEMS WITH A RETURN OF ODOR. A/C RECOVERED TO MAIN MAINTENANCE BASE	 WITHOUT FURTHER INCIDENT. UPON INVESTIGATION IT WAS REVEALED THAT POWER TERMINAL OF THE NR 1 AVIONICS RELAY HAD SHORTED	 TO GROUND. AT THIS TIME THE CAUSE OF THE SHORT IS UNKNOWN.	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003071800081	20030718	00081	NM  	2003	7	18	CA030630001      	1	20030629	G	5755	MB543DDFS464	BEARING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPOILER	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			31740	31740		1205					(CAN) BEARING FOUND SEIZED DURING 'D' CHECK INSPECTION AT SUMMING LEVER WHERE FEEDBACKARM ATTACHES. THIS CAUSES THE FEED	BACK ARM TO TWIST AND BIND INCREASING FRICTIO N TO THE POINT WHERE NEAR FULL TRAVEL, THE SPOILER CLUTCH WILL DISENGAGE. 	ROLL SPOILER ACTUATOR (RT IB) REPLACED AND CHECKED, SERVICEABLE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003071800082	20030718	00082	EU  	2003	7	18	CA030630002      	1	20030630	G	2437	9755084910	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GEN 1 AMP/VOLT	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GEN 1 AMP/VOLT DISPLAY WENT BLANK. ALL OTHER GEN 1 INDICATIONS NORMAL.  ASSY REPLACED WITH SERVICEABLE UNIT.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003101700011	20031017	00011	CE  	2003	10	17	CA030702001      	1	20030626	G	1430	S346151	BOLT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					QUALITY CONTROL	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) BOLTS ORDERED FROM CESSNA AIRCRAFT COMPANY UNDER PROPRIETARY PN S346151 WERE RECEIVED AND DETERMINED TO BE INCORRE	CT. THE ORIGINAL BOLTS REMOVED FROM THE ENGINE MOUNT INSTALLATION WERE STAMPED WITH PN NAS464P864. REPLACEMENT BOLTS ORD	ERED FROM CESSNA UNDER PN S346151 WERE RECEIVED AND FOUND STAMPED WITH P/N NAS6208-64D AND PHYSICAL INSPECTION SHOWED TH	AT THEY WERE .125  LONGER THAN THE ORIGINALS. CESSNA CITATION CUSTOMER SUPPORT OFFICE WAS CONTACTED TO DETERMINE IF THE 	BOLTS WOULD BE ACCEPTABLE TO INSTALL WITH THE ADDITION OF EXTRA WASHERS. CESSNA ENGINEERS CONSULTED ENGINEERING DRAWING 	PN 6550000 AND DETERMINED THAT PN NAS464P864 WAS THE ONLY CORRECT PN. CESSNA ENGINEERING ADVISED THAT THEY WOULD CONTACT	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
2003072100033	20030721	00033	NE  	2003	7	21	CA030702002      	2	20030618	G	7321		FCU             			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN)  A/C HAD JUST DROPPED A 15,000 LB LOAD OF LOGS AT LOG LANDING IN AN UP HILL YARD. PILOT MADE A LT PEDAL TURN TO DE	PART LOG LANDING. COLLECTIVE LOWERED TO DESCEND BACK DOWN TO CUT BLOCK, NR 2 ENG N1 UNDER-SPEED WARNING SOUNDED & WITH W	ARNING LIGHTS, INDICATING SOFT STALL. CREW EXECUTED AN IN-FLIGHT SHUTDOWN & MOTORING OF ENG TO PREVENT OVER-TEMP. NR 2 E	NG SHUTDOWN COMPLET, A/C RETURNED TO SERVICE AREA & MADE A SINGLE ENG LANDING.  COMPLETE INSP OF ENG & CONTROL LINKS REV	EALED NOTHING ABNORMAL. ENG FUEL FILTER INSP FOR CONTAM,  NONE FOUND. ENG FUEL PRESSURIZING & DUMP VALVE CHANGED.  FCU A	LSO CHANGED AS A PRECAUTION. ENG RESTARTED & GROUND-RUN, ALL PARAMETERS FOUND TO BE ACCEPTABLE & A/C RELEASED FOR FLT.	2	G	7	2 	4U	4	U	 	H4EA    	E15EA				 
2003072100086	20030721	00086	CE  	2003	7	21	CA030702003      	1	20030622	G	2612	302158	FIRE DETECTOR   			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	RT ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF AIRCRAFT CLIMBED OUT, AND A RT ENGINE FIRE WARNING LIGHT CAME ON.  COULD NOT SEE SMOKE, ENGINE FUNCT	IONED NORMAL..  RETURNED TO MAINTENANCE FACILITY.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2003072100087	20030721	00087	SW  	2003	7	21	CA030702004      	1	20030626	G	6120	89741016	GOVERNOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	PROPELLER	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL LT ENGINE DID NOT PRODUCE TORQUE FOR TAKEOFF (PROP PARTIALLY CAME OFF LOCKS). ABORTED TAKEOFF.  RE	TURNED TO MAINTENANCE FACILITY.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2003072100090	20030721	00090	CE  	2003	7	21	CA030702005      	1	20030616	G	5530	04311481	FITTING         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	VERTICAL STAB	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			11807								(CAN) DURING PREFLIGHT INSPECTION PILOT NOTICED CRACK,  PARALLEL ALONG 90 DEGREES ANGLE.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2003071800083	20030718	00083	EA  	2003	7	18	CA030703001      	2	20030529	G	8550	20008A	OIL COOLER      			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) AT START AFTER LAST DAILY FLIGHT NOTED SMALL POOL OF OIL ON LANDING PAD.  ALSO NOTICED .7500 INCHES CRACK ALONG CA	STING WELD. ONLY LASTED SHORT TIME, ORDERED BRAND NEW COOLER.   WILL STROBE FAN AND TAIL ROTOR AFTER INSTALL TO CHECK FO	R VIBRATION.				1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003072100034	20030721	00034	CE  	2003	7	21	CA030703002      	1	20030620	G	7120	05510171	MOUNT           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			10212								(CAN) LOWER CROSS TUBE FOUND BROKEN AT WELD ON LT SIDE.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003072100102	20030721	00102	EU  	2003	7	21	CA030703003      	1	20030623	G	6730	SC5083	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					RT HYD SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PROBLEM RETURNED WITH AIRCRAFT. HYD HAND OVER LT DURING HYD TEST. SWAPPED LATERAL SERVO'S LT TO RT AND RT TO LT. D	URING TEST CYCLE WENT HAND OVER RT. THE OPPOSITE SERVO (LT HYDRAULIC SERVO) FROM PREVIOUS SDR WAS REPLACED. PROBLEM WENT	 AWAY. HYD SERVO IS BEING SENT TO EUROCOPTER CANADA FOR TESTING. EUROCOPTER TECH REP. FOR TESTING/TROUBLESHOOTING.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003072100103	20030721	00103	CE  	2003	7	21	CA030703004      	1	20030624	G	5697	PQ020JE004	WIRE HARNESS    			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					RT CARGO BAY	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN)  RT WINDSHIELD HEAT INOPERATIVE ON ENGINE INDICIATING AND CREW ALERT SYSTEM POPPED. SB HK062 AC POWER TO RT WINDSH	IELD. WIRE BUNDLE PQ020 AND JE004 TOUCHING AND HEAT SHRINK FAILURE CAUSING SB HK 062 TO POP.REPLACED HEAT SHRINK PROBLEM	 ELIMINATED.				2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2003072100074	20030721	00074	CE  	2003	7	21	CA030703005      	1	20030623	G	3411	IMP44PN	HOSE            			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	STATIC SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NYLON STATIC HOSE CATCHING ON LT CONTROL COLUMN UNIVERSAL JOINT ATTACH BOLT. STATIC HOSE NOT TIED OFF PROPERLY, WH	ICH RESTRICTED FORWARD MOVEMENT OF CONTROL WHEEL.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2003072100035	20030721	00035	EA  	2003	7	21	CA030703007      	2	20030625	G	8530	LW13623	PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			CA											(CAN) NR 3 CYLINDER PISTON EXPERIENCED FAILURE OF ITS ALUMINUM SIDE DURING CRUISE FLIGHT, RESULTING IN ENGINE POWER LOSS	 AND ROUGH OPERATION. PISTON FAILURE CAUSED PRESSURE FROM COMBUSTION TO ENTER THE CRANKCASE. THIS RESULTED IN THE CRANKC	ASE BECOMING PRESSURIZED FORCING THE ENGINE OIL TO BE DUMPED OVERBOARD THROUGH THE CRANKCASE BREATHER TUBE. OIL PRESSURE	 WAS EVENTUALLY LOSS RESULTING IN AN ENGINE STOPPAGE IN FLIGHT. EMERGENCY LANDING ISSUED WITH NO FURTHER DAMAGE.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003072100067	20030721	00067	CE  	2003	7	21	CA030703008      	1	20030624	G	5313	101406335	STRINGER        			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 600 HR INSPECTION REVEALED 2 CRACKED STRINGERS (NR 9 RT HYD TSB 2472 REV.II.)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2003072100068	20030721	00068	CE  	2003	7	21	CA030703009      	1	20030624	G	5412	1019100383	BULKHEAD        			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NACELLE BULKHEAD CRACKED FROM LOWER RT BOLT HOLE TO EDGE OF BULKHEAD. NEW BULKHEAD INSTALLED ON BOTH NACELLES. PRO	BLEM ATTRIBUTED TO AIRCRAFT AGE AND NUMBER OFCYCLES.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2003082100131	20030821	00131	CE  	2003	8	21	CA030703010      	1	20030627	G	5330	05411212	SKIN            			CESSNA	182   	182B        	2072706	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT IS USED FOR PARACHUTE OPERATIONS AND DOES MANY CYCLES. ON INSPECTION FOUND VISIBLE CRACK ABOUT 1 INCH LON	G AT REAR OF GEAR CUT OUT.					1	H	7	1 	3O			NT	3A13    					 
2003072100069	20030721	00069	SO  	2003	7	21	CA030703011      	2	20030410	G	8520		CRANKCASE       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING INSPECTION A CRACK WAS DISCOVERED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003072100070	20030721	00070	SO  	2003	7	21	CA030703012      	2	20030514	G	8520		CRANKCASE       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACK DISCOVERED ON THE CRANKCASE. THE CRACK WAS IN THE SAME AREA AS A PREVIOUS WELD REPAIR.THE ENGINE WAS REPAIRE	D (NEW CRANKCASE AND NEW CRANKSHAFT). DURING THE REPAIR THE COUNTERWEIGHT PINS WERE FOUND CORRODED.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003071800084	20030718	00084	EA  	2003	7	18	CA030703013      	2	20030618	G	8500	H10360D1A	ENGINE          			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NACELLE	FLAMED OUT      	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											(CAN) SUDDEN ENGINE FLAMES AND A CONTINUOUS LOSS OF SUBSTANTIAL POWER. EMERGENCY LANDING CARRIED OUT. THE ENGINE IS UNDE	R INVESTIGATION BY TSB. ADDITIONAL REPORT TO FOLLOW.					1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2003072100036	20030721	00036	EA  	2003	7	21	CA030703014      	2	20030609	G	8550	STD213	SEAL            			CESSNA	206   	T206H       	2073303	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) FOLLOWING A FLIGHT TEST THAT WAS CARRIED OUT AFTER ENGINE INSTALLATION. THE PILOT NOTICED AN EXCESSIVE OIL LEAK. T	HE ENGINE HAD RETURNED FROM OVERHAUL. FURTHER INVESTIGATION REVEALED THAT OIL SEAL WAS NOT INSTALLED. AN EMPTY SPACE WAS	 CREATED BECAUSE THAT SEAL WAS MISSING, CREATING AN EXCESSIVE OIL LEAK.				1	H	7	1 	3O	3	O	RT	A4CE    	E14EA				 
2003072100071	20030721	00071	CE  	2003	7	21	CA030703015      	1	20030618	G	3060	P5855B5W	DEICE SYSTEM    			CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  					PROP BLADE	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AFTER FLT THE PILOT NOTICED THAT THERE WAS A DE-ICE PAD MISSING ON THE LEFT PROP. WHILE WE WERE INSPECTING THE PRO	P, WE NOTICED THAT THE GLUE USED TO GLUE THE DE-ICE PAD HAD NOT DRIED OR HARDENED. THE BLADE HAD ONLY 91.1 HOURS AND IT 	ARRIVED FROM OVERHAUL. A TECHNICIAN FROM THAT OVERHAUL FACILITY ADVISED US THAT WE SHOULD ROLL ALL OTHER PROP DE-ICE PAD	S TO ENSURE THAT THEY ARE PROPERLY GLUED.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003072100072	20030721	00072	SO  	2003	7	21	CA030703016      	1	20030615	G	3230		O-RING          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AIRCRAFT JACKED UP, GEAR SWUNG. NOSE GEAR SLOWER IN RETRACTION. FOUND NOSE GEAR RAM O-RINGS FLAT. REMOVED, REPAIRE	D, REINSTALLED. AIRCRAFT OK.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003072100091	20030721	00091	SO  	2003	7	21	CA030703017      	2	20030701	G	8530	654004	EXHAUST VALVE   			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSTALLATION OF CYLINDERS AFTER OVERHAUL OF CRANKCASE THE EXHUAST VALVE IN ONE CYLINDER WAS NOTICED TO BE BAD	LY CORRODED AND ERODED AT THE NECK OF THE VALVE.ALL OTHER EXHAUST VALVES WERE INSPECTED SERVICEABLE AND THE ONE WILL BE 	REPLACED.  IT SHOULD BE NOTED THAT WHEN INSTALLED, EVEN WITH A BOROSCOPE THIS AREA CAN NOT BE INSPECTED.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003082100134	20030821	00134	EU  	2003	8	21	CA030704002      	1	20030627	G	2120	783108505	SLEEVE          			ISRAEL	1125  	ASTRASPX    	4500205	EU  										A/C DUCT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE A-CHECK A DAMAGED SLEEVE WAS FOUND ON THE AIR CONDITIONING DUCT FROM THE COOLING TURBINE TO THE WAT	ER SEPERATOR UNIT. THE DUCT HAD A 1 CM DIAMETER HOLE IN THE SIDE WALL ALLOWING THE AIR TO DUMP UNDER THE BAGGAGE FLOOR. 	NO ADDITIONAL DAMAGE TO ANYTHING IN THE AREA WAS NOTED.				2	L	7	2 	4F			RT	A16NM   					 
2003072100037	20030721	00037	CE  	2003	7	21	CA030704003      	1	20030623	G	8011		MOTOR           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					STARTER	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) ENGINE STARTER MOTOR WAS BURNED,						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2003072100051	20030721	00051	NM  	2003	7	21	CA030704004      	1	20030703	G	3340	3008375	LIGHT           			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ANTI COLLISION	FAILED          	W				A	G			UNSCHED LANDING         	O2 MASK DEPLOYED        			W			INADEQUATE Q C            			CL	CLIMB          	1			CA											(CAN) WHILE CLIMING THROUGH 23,000 FT. THEY EXPERIENCED A RAPID DEPRESSURIZATION, LOSS OF CABIN PRESSURE (O2 MASKS WERE 	DONNED BY FLT CREW). CREW MANUALLY CLOSED OUTFLOW VALVE HOWEVER AIRCRAFT WOULD NOT PRESSURIZE. CREW REQUESTED DESCENT AN	D RETURN TO BASE - NO EMERGENCY WAS DECLARED. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTION REVEALED THE UPPE	R BEACON ASSEMBLY LIGHT MISSING - NO DAMAGE IN HOLE OR AIRFRAME. ASSEMBLY REPLACED AND AIRCRAFT GROUND CHECKED SERVICEAB	LE. AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. NOTE: PART HISTORY SHOWS UPPER ANTI COLLISION LIGH	T ASSEMBLY REPLACED APRIL 17/03 DURING 'C1-3 CHECK' AT 3RD PARTY VENDOR PER NON ROUTINE FORM.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003072100052	20030721	00052	NE  	2003	7	21	CA030704006      	2	20030624	G	7250		ENGINE          								PWA   	PT6   	PT6A67D     	 	NE  						FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15655								(CAN) RUBBING SOUNDS COMING FROM POWER TURBINE AREA CAUSED BY CONTACT BETWEEN FACE OF 2ND STAGE POWER TURBINE DISK, SEAL	 & COVER OF PT SHAFT HOUSING ASSY. CONTACT AROSE BECAUSE TEE HEAD LUGS SECURING SEAL & COVER TO PT SHAFT HOUSING FRETTED	 THROUGH FLANGE RELEASING SEAL AND COVER, ALLOWING SEAL TO MOVE REARWARDS & CONTACT FACE OF PT 2 DISK. ALL OF SLOTS IN P	T SHAFT HOUSING ASSY HAVE HEAVY FRETTING WEAR, EITHER COMPLETELY THROUGH OR ALMOST COMPLETELY THROUGH FLANGE. THIS MEANS	 THAT 4 RIVETS WHICH BROKE, RELEASING TEE HEADED LUGS, FAILED TOWARDS END OF PROCESS. RIVET FAILURE WAS A RESULT OF WEAR	 & FRETTING & WAS NOT CAUSE OF IT.						4	T			E26NE				 
2003072100053	20030721	00053	NE  	2003	7	21	CA030707001      	2	20030620	G	7230		GAS GENERATOR   								PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) COMPLETE ENG OVERHAUL. AT DISASSEMBLY DISCOVERED THAT IMPELLER HAD THREE VANES WITH SECTIONS OF INDUCER DAMAGED.  	IT APPEARS THAT 3 PORTIONS OF LIBERATED MATERIAL FROM IMPELLER WERE RESULT OF IMPELLER FAILURE, PROBABLY DUE TO FATIGUE 	RESULTING FROM BLADE VIBRATION INDUCED STRESSES. MATERIAL WAS LIBERATED FROM IMPELLER ENTERED INTO THE COMBUSTION SECTIO	N OF ENGINE THROUGH THE DIFFUSER TUBES OF THE GAS GENERATOR. REMAINS OF TWO OF THREE LIBERATED PIECES WERE TRAPPED BETWE	EN SMALL EXIT DUCT & COMBUSTION LINER. ONE LIBERATED PIECE,  APPEARS TO HAVE ENTERED THROUGH COMBUSTION LINER & INTO GAS	 PATH. HP TURBINE INGESTED IMPELLER MATERIAL CAUSING HEAVY DAMAGE TO HP TURBINE BLADES.						4	F			E1NE				 
2003071800086	20030718	00086	SW  	2003	7	18	CA030707002      	1	20030707	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)TE FLAP CABLE FRAYED AT UPPER RT PULLEY.						1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2003072100064	20030721	00064	NE  	2003	7	21	CA030707004      	2	20030526	G	7200	9606080705	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DESTROYED       	W				A				UNSCHED LANDING         				J	D		WARNING INDICATION        	INFLIGHT SEPARATION       		CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS FLYING AND HAD A CHIP LIGHT. PILOT LANDED IMMEDIATELY. ON SHUT DOWNHE HEARD LOTS OF NOISE COMING FROM	 THE ENGINE. CHECKED IS CHIP PLUG AND FOUND L OTS OF METAL. AIRCRAFT WAS GROUNDED AND LEFT ON SITE. RENTAL ENGINE WAS IN	STALLED. ENGINE WAS TRANSPORTED TO TROIS-RIVIERES FOR INVESTIGATION. MODULE 4 WAS REMOVED AND REPLACED AND ENGINE REINST	ALLED.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003072100065	20030721	00065	NE  	2003	7	21	CA030707005      	2	20030706	G	7200		MODULE          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	DAMAGED         	W				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) AIRCRAFT WAS TAKING OFF AND CLIMBING. HE WAS ABOUT 40 FT INTO THE AIR AND HEARD A LOUD BANG. LANDED IMMEDIATELY. T	HE ENGINE WAS SHUT DOWN. THE AIRCRAFT WAS GROUNDED. ENGINEER SENT TO THE LOCATION FOR INVESTIGATION. THE INSPECTION REVE	AL POSSIBLE DAMAGE OF MODULE 2 AND 3.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003082100136	20030821	00136	EA  	2003	8	21	CA030707006      	1	20030701	G	2731	83963	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZONTAL STAB	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) FLIGHT CREW REPORTED ' STAB CHANNEL NR 1 FAIL' MESSAGE DURING CRUISE. RESET OK BUT FAIL MESSAGE AGAIN DURING MANUA	L TRIM. TROUBLE SHOOTING DISCOVERED MOTOR ON NR 1 HORIZONTAL STAB TRIMACTUATOR HAD FAILED. TRIM UNIT AND MOTOR CONTROL U	NIT WERE ALSO REPLACED				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003072100066	20030721	00066	SO  	2003	7	21	CA030708001      	1	20030702	G	5200		DOOR            			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					WING LOCKER	BUCKLED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA			12400								(CAN) ON DESCENT AT 8500 FT, LT WING LOCKER DOOR BUCKLED UP IN MIDDLE APPROX 4-5 INCHES, THEN CAME LOOSE FROM DOOR PIN A	ND POPPED OPEN & STARTED FLAPPING. AIRCRAFT SPEED WAS REDUCED TO 140 KTS & AIRCRAFT LANDING WAS UNEVENTFUL.  DETERMINED 	THAT WING LOCKER WAS PRESSURIZING IN FLT & WAS INCREASED ON THE DESCENT BY SPEED. IT WAS FOUND THAT THERE WERE SOME HOLE	S IN THE FORWARD END OF LOCKER & SEALEANT ON THE LOCKER SKIN SEAMES HAD DETERIORATED AND FALLEN OUT ALLOWING HIGH PRESSU	RE AIR FROM THE FLAP WELL TO ENTER THE LOCKER AREA. HOLES WERE PLUGGED & SEAMS RESEALED AND THE LOCKER WAS PRESSURE CHEC	KED FOR LEAKAGE AND FOUND SERVICEABLE.	1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2003082100138	20030821	00138		2003	8	21	CA030708002      	4	20030505	G	2210	1394T1007Z	INDICATOR       			CESSNA	441   	441         	2076020	CE  										TURN COORDINATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BEARINGS VERY NOISY AND ROUGH. BUT INSTRUMENT OPERATING NORMALLY.						1	L	7	2 	3T			RT	A28CE   					 
2003082100139	20030821	00139	CE  	2003	8	21	CA030708003      	1	20030514	G	5220	CM3838296	SEAL            			CESSNA	441   	441         	2076020	CE  										ESCAPE HATCH	CUT             	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ESCAPE HATCH LEAKING RAIN WATER WHEN AIRCRAFT SITTING ON GROUND. THE RUBBER SEAL WAS CUT BY THE LIP ON THE SEAL RE	TAINER WHICH IS LOCATED ON FUSELAGE DOOR STRIKER.					1	L	7	2 	3T			RT	A28CE   					 
2003082100142	20030821	00142	CE  	2003	8	21	CA030708004      	1	20030623	G	2823		SEAL            			CESSNA	441   	441         	2076020	CE  										VALVE ASSEMBLY	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) FIREWALL FUEL SHUT OFF VALVE FOUND TO BE LEAKING FUEL EXTERNALLY PAST HARDENED O-RING SEALS. INTERNAL LEAKAGE CAUS	ED BY INCORRECT SEALS WHICH HAD GONE SOFT LIKE PUTTY AND WERE BREAKING UP.					1	L	7	2 	3T			RT	A28CE   					 
2003082100145	20030821	00145	CE  	2003	8	21	CA030708005      	1	20030624	G	2823		O-RING          			CESSNA	441   	441         	2076020	CE  										VALVE ASSEMBLY	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) FIREWALL FUEL SHUT OFF VALVE FOUND TO BE LEAKING FUEL EXTERNALLY PAST HARDENED O-RING SEALS.  INTERNAL LEAKAGE CAU	SED BY INCORRECT SEALS WHICH HAD GONE SOFT LIKE PUTTY AND WERE BREAKING UP.					1	L	7	2 	3T			RT	A28CE   					 
2003072100044	20030721	00044	SW  	2003	7	21	CA030708007      	1	20030415	G	5610	41373	WINDOW          			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2D     	41508	EA  					COCKPIT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ONLY EXPLANATION WE HAVE FOR THIS BURNED AREA COMES FROM THE FEW TIMES THIS AIRCRAFT HAS BEEN PARKED OUTSIDE, 	OR DURING FLIGHT. IT MIGHT SOUND CRAZY, BUT SUNLIGHT MUST HIT THE GLASS AT THE RIGHT PERFECT ANGLE, BUNDLE THE LIGHT LIK	E A MAGNIFYING GLASS AND THEN HIT THE VINYL BEFORE AIRCRAFT WAS REBUILT IN 1996.				1	H	7	1 	3O	3	O	NC	A759    	E274				 
2003072100045	20030721	00045	SW  	2003	7	21	CA030708008      	1	20030501	G	6510	204040603009	HANGER ASSY     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DEFECTS FOUND DURING ROUTINE INSPECTION/LUBRICATION. PROBLEM MAY HAVE EXISTED ATPRIOR INSPECTIONS BUT NOT DISCOVER	ED. 4 INNER, 4 OUTER COUPLINGS REPLACED. CORROSION PITS/SPALLING WERE ON SEVERAL TEETH OF EACH COUPLING.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003082100146	20030821	00146	SW  	2003	8	21	CA030708009      	1	20030501	G	6400	212001053005	CONTROL ARM     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FAIRLEAD	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CONTROL TUBE AT PRIOR MAINTENANCE EVENT WAS INSTALLED BACKWARDS (180 DEGREES OUT). TUBE HAD NYLATRON SLEEVES BUT R	EVERSED POSITION CAUSED WEAR AT AFT FAIRLEAD. TUBE WORN 0.013. TUBE WALL THICKNESS IS 0.035. PART REPLACED.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003072100046	20030721	00046	SW  	2003	7	21	CA030708010      	1	20030515	G	6520	209011710005	SHAFT           	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					PITCH CHANGE	STRIPPED        	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA						AHT50649					(CAN) DURING ATTEMPTED DISASSEMBLY, WE WERE UNABLE TO REMOVE THREADED SLEEVE PN 209011719003. FOUND INCORRECT HARDWARE S	TARKUP (WASHER PN 212010714003 MISSING).  PRESUME SLEEVE BOTTOMED OUT, NUT MS14145L8 ALSO, AND HENCE THREADS STRIPPED ON	 TORQUE UP. HAD TO HACKSAW END OF SHAFT OFF TO REMOVE.  PART REPLACED.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003071800088	20030718	00088	SW  	2003	7	18	CA030708011      	1	20030515	G	6300	212060724033	TUBE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					CONTROL TUBE	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CONTROL TUBE CHAFING IS 0.017 INCH DEEP.  TUBE IS STEEL ALLOY. TUBE CHAFED FROM CONTACT WITH FIREWALL BOOT/ALUMINU	M FLANGE.  TUBE REPLACED.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003071800089	20030718	00089	SW  	2003	7	18	CA030708012      	1	20030624	G	6510	3272H	DISC PACK       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) SIGNIFICANT FRETTING AT BOLT HOLE/CLAMP UP AREA.   TWO DISKS CRACKED AT BOLT HOLE.  PART REPLACED. (FORWARD POSITI	ON)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003071800090	20030718	00090	SW  	2003	7	18	CA030708013      	1	20030701	G	2910	70012J22OW234	LINE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					HYDRAULIC SYS	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) THE PILOT REPORTED A NOISE (FROM AN UNLOADED HYDRAULIC PUMP) FOLLOWED BY THE ODOR OF HYD FLUID. HYDRAULIC PRESSURE	 ON SYSTEM NUMBER 2 DROPPED TO ZERO. THE PILOT INITIATED AN UNSCHEDULED LANDINGTO INVESTIGATE THE PROBLEM.   AFTER LANDI	NG A CHAFED HYD LINE FROM THE NUMBER 2 HYDRAULIC PUMP WAS DISCOVERED.  THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED T	O SERVICE.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003072100047	20030721	00047	NM  	2003	7	21	CA030709001      	1	20030709	G	3230	11972	SOLENOID        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	MALFUNCTIONED   	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) IN FLT DURING APPROACH, THE LANDING GEAR WAS SELECTED THE DOWN/EXTEND POSITION WITH NO SUBSEQUENT INDICATIONS THAT	 EXTENSION HAD OCCURRED. ONLY INDICATION WAS ILLUMINATION OF 3 RED, LT NOSE RT, MISMATCH ADVISORY LIGHTS ON LANDING GEAR	 SELECTOR PANEL. AFTER CONSULTING WITH ENGINEERING AN ALTERNATE EXTENSION CARRIED OUT WITH NO FURTHER INCIDENCE.  INVEST	IGATION CARRIED OUT TO DETERMINE CAUSE OF LANDING GEAR FAILURE. A RESISTANCE CHECK ON BOTH THE SOLENOIDS ON LANDING GEAR	 SELECTOR VALVE (1 FOR EXTEND & 1 FOR RETRACT COMMAND) FOUND THAT SOLENOID COIL A, HAD A RESISTANCE TWICE THAT OF TOLERA	NCE GIVEN IN CMM CH 32-30-10.  SOLENOID SELECTOR VALVE REPLACED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003072100048	20030721	00048	EA  	2003	7	21	CA030709002      	2	20030703	G	7322	193F0004D0330	SENSE LINE      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) IN CLIMB THROUGH 8,500 FT, RT ENG MANIFOLD PRESSURE DROPPED BACK TO 20 INCHES MANIFOLD PRESSURE, FROM CLIMB POWER 	SETTING OF 40 INCHES MANIFOLD PRESSURE & 2,400 RPM WITH MIXTURE FULL RICH. PILOT DID A CAUSE CHECK WITH NO RESULTS. PILO	T SECURED ENGINE & DIVERTED TO CLOSEST SUITABLE AIR FIELD. A/C LANDED WITHOUT FURTHER PROBLEMS. ON INSPECTION OF ENGINE,	 MANIFOLD SENSE LINE THAT RUNS FROM DIFFERENTIAL CONTROLLER TO MANIFOLD HAD BROKEN OFF AT DIFFERENTIAL END. THIS WOULD M	AKE ENG RUN VERY RICH AND MAKE IT LOOK LIKE ENG HAD QUIT. THIS IS A KNOWN PROBLEM AREA THAT WAS INSPECTED 20 HOURS PREVI	OUS BEFORE THE FAILURE, WITH NO FAULT DETECTED. WE ARE NOW PUTTING AN IN HOUSE 200 HR REPLACEMENT ON THIS HOSE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003082100150	20030821	00150	SW  	2003	8	21	CA030709006      	1	20030702	G	6510	327211	COUPLING        			BELL  	206   	206B        	1181511	SW  										T/R DRIVESHAFT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON DAILY INSPECTION OF AIRCRAFT FORWARD THOMAS COUPLING ATTACHMENT BOLT FOUND LOOSE.  FORWARD T/R DRIVESHAFT REMOV	ED AND DISASSEMBLED.  FORWARD DISC PACK (THOMAS COUPLING) SCRAPPED DUE TO FRETTING DAMAGE AS WELL AS ATTACHING BOLT.  AL	L HARDWARE INSPECTED FOR SERVICE ABLILITY.  ALL HARDWARE FOUND NOT TORQUE SEALED AS PER BHT TORQUE CHECK PROCEDURE. 10- 	25 HR TORQUE CHECK TO BE COMPLETED AS PER BHT MM TO INSURE BOLT TORQUE. MORE DETAILED DAILY INSPECTION SHOULD BE COMPLET	ED. PROPER MAINTENANCE PROCEDURES SHOULD BE FOLLOWED.		1	G	7	1 	3U			 	H2SW    					 
2003071800093	20030718	00093	EU  	2003	7	18	CA030709007      	1	20030628	G	6220	LB412311	THRUST BEARING  			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					SPHERICAL	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ELASTOMER SEPARATION.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003071800094	20030718	00094	WP  	2003	7	18	CA030709008      	2	20030707	G	7321		SPLINE ADAPTER  	WOODWARD    		SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					FUEL CONTROL	FAILED          	W				E				ENGINE SHUTDOWN         				X	E	J	ENGINE FLAMEOUT           	VIBRATION/BUFFET          	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			CA						2007677					(CAN) CREW STARTED ENG & NOTICED ENG WAS SLOW TO ACCELERATE TO IDLE. ONCE AT IDLE (70 PERCENT) ENGINE SLOWLY INCREASED T	O APPROXIMATLY 80 PERCENT WITHOUT INPUT FROM CREW. IN AN ATTEMPT TO REDUCE ENG POWER, WAS NO RESPONSE TO ENG CONTROL INP	UTS BY CREW. ENG SHUTDOWN & MAINT CONTACTED. UPON INSP BY MAINT, FCU DRIVE FOUND SEIZED & SHAFT SHEARED OFF. FCU REPLACE	D & ENG FUNCTION NORMAL  DURING ENG RUN. UPON REASEARCHING RECORDS ON THIS FCU, IT WAS DETERMINED THAT THIS FCU WAS REPA	IRED SEVERAL TIMES SINCE OVERHAUL. OVERHAUL WAS COMPLETED JULY 7, 2000 & REMOVED FOR REPAIR JANUARY 15, 2002 AT 1418.8 H	RS TSO & THEN AGAIN ON OCTOBER 31, 2002 AT 2168.3 HRS TSO. FAILURE OF THIS FCU OCCURED 141 HRS SINCE THE LAST REPAIR.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003082100151	20030821	00151	SO  	2003	8	21	CA030709009      	1	20030616	G	2150	4633600	CLUTCH          	YORK        		PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					AIR CONDITIONER	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE RIVETS ON THE AIR CONDITIONING CLUTCH ASSEMBLY FAILED. THIS ALLOWED TWO OF THE THREE BRACKETS THAT CONNECT THE	 OUTER RING TO THE INNER CORE, EACH ABOUT 2.25					1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2003071800095	20030718	00095	WP  	2003	7	18	CA030709010      	1	20030628	G	5340	95K0300305	ATTACH FITTING  			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUSELAGE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) EXTERNAL PLATFORM AND COUNTERWEIGHT INSTALLATION MODIFICATION OF STRUT ATTACH FITTING IS DAMAGING UPPER CORNER OF 	HELICOPTER ROOF STRUCTURE AND THUS REQUIRES INSTALLATION OF NEW HARDWARE PN 95K0300-063 & 95K0300-065.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003071800096	20030718	00096	EA  	2003	7	18	CA030710001      	2	20030410	G	8530	SA10204	EXHAUST VALVE   			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	MCAULY	1A170	1A170*      	GL  	NR 2 CYLINDER	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING A TRAINING FLIGHT POWER WAS ADVANCED, THE ENGINE LOST POWER AT THIS POINT AND STARTED TO VIBRATE. THE AIRCR	AFT IMMEDIATELY RETURNED TO THE AIRPORT AND LANDED SAFELY WITHOUT FURTHER INCIDENT. UPON INSPECTION OF THE ENGINE IT WAS	 DETERMINED THAT THE HEAD OF THE EXHAUST VALVE ON NR 2 CYLINDER HAD SEPARATED FROM THE STEM.  BECAUSE OF INTERNAL DAMAGE	 TO THE CYLINDER IT WAS CONSIDERED UNSERVICEABLE, AND A COMPLETE NEW CYLINDER ASSEMBLY PN TBN12-OCA WAS INSTALLED.  THE 	ENGINE WAS TEST RUN AND THE AIRCRAFT RETURNED TO SERVICE.		1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P857	 
2003071800097	20030718	00097	SW  	2003	7	18	CA030710002      	1	20030606	G	6410	212010750105FM	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) VOID IN S.S. LEADING EDGE STRIP OUTBOARD BLADE TIP  JUNCTION OF BLADE SKIN. VOID AREA APPROXIMATELY 0.175 INCH CHO	RDWISE X 0.375 INCH SPANWISE. BLADE REMOVED AND SENT FOR REPAIR. SN A-7719.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003071800098	20030718	00098	EA  	2003	7	18	CA030710003      	2	20030606	G	7414	106006141	MAGNETO         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) INTERMITTENT ROUGH RUNNING ENGINE IN FLIGHT. MAGNETO'S CHANGED EARLY FOR 500 HR INSPECTION. ON REMOVAL FROM ENGINE	, SUBJECT MAGNETO NOTED TO HAVE EXCESSIVE END PLAY ON GEARSHAFT. OVERHAUL VENDOR CONFIRMED END PLAY, OIL THROUGH OUT ASS	EMBLY,  BEARING BORE IN DISTRIBUTOR BLOCK HOUSING WAS OVERSIZE. CONTACT ASSEMBLY'S WORN BEYOND LIMITS.  UNIT OVERHAULED.				1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2003090800166	20030908	00166	CE  	2003	9	8	CA030710004      	1	20030709	G	5220		SEAL            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					EMERGENCY EXIT	DIRTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CAMPAIGN NOTICE 851-52-20-020 TO INSPECT THE EMERGENCY EXIT FOR STICKING CARRIED OUT. THE EMERGENCY EXIT OF AIRCRA	FT WAS INITIALLY DIFFICULT TO OPEN. THE SEAL WAS CLEANED AND INSPECTED AND FOUND SERVICEABLE. THE EMERGENCY EXIT WAS REI	NSTALLED AND FUNCTION CHECKED NORMALLY.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003082100153	20030821	00153	SW  	2003	8	21	CA030711001      	1	20030710	G	3297	120	WIRE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					RT MAIN GEAR	BROKEN          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA			23747								(CAN) ON LANDING THE RT MAIN DID NOT INDICATE GREEN SO THE PILOT DIVERTED TO A MAJOR CENTER WHERE THE TOWER CONFIRMED TH	E GEAR WAS DOWN AND HE LANDED WITHOUT INCIDENT. THE GROUND WIRE TO THE RT INBOARD ACTUATOR SWITCH WAS FOUND TO BE BROKEN	 IN THE SERVICE LOOP TO THE SWITCH. THERE WERE SIGNS THAT THE WIRE MAY HAVE BEEN PINCHED AT THE POINT OF BREAKAGE SOMETI	ME IN THE PAST.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003082100154	20030821	00154	CE  	2003	8	21	CA030711002      	1	20030623	G	5510	07126153	BULKHEAD        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			41111								(CAN) BULKHEAD WAS CRACKED UNDER ANCHOR DOUBLER AT TOP LT HORIZONTAL STABILIZER ATTACH BOLT.						1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2003082100156	20030821	00156	NE  	2003	8	21	CA030711003      	2	20030708	G	8530	127145	STUD            	PWA         		DOUG  	DC4   	C54GDC      	3021534	WP  	PWA   	R2000 	D5          	52023	NE  					CYLINDER	BROKEN          	W				E				ENGINE SHUTDOWN         				K	E		FLUID LOSS                	VIBRATION/BUFFET          		CR	CRUISE         	1			CA						SO712					(CAN) DURING CRUISE IT WAS NOTICED THAT THERE WAS A SLIGHT SHAKE AND DEVELOPED AN OIL LEAK, A PRECAUTIONARY SHUT DOWN WA	S CARRIED OUT AND PROP FEATHERED, UPON INSPECTION IT WAS FOUND THAT THE LOWERS STUDS WERE BROKEN ON THE CYLINDER ASSEMBL	Y. CURRENTLY AN INVESTIGATION INVOLVING THE OVERHAUL FACILITY IS BEING CARRIED OUT. THE STUDS WERE REPLACED ALONG WITH T	HE CYLINDER ASSEMBLY.			2	L	7	4 	4R	4	R	 	A762    	E230				 
2003082100158	20030821	00158	NE  	2003	8	21	CA030711004      	2	20030708	G	8530	127145	STUD            	PWA         		DOUG  	DC4   	C54GDC      	3021534	WP  	PWA   	R2000 	D5          	52023	NE  					CYLINDER	BROKEN          	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA						SO712					(CAN) AN OIL LEAK WAS OBSERVED IN CRUISE AND A PRECAUTIOARY SHUT DOWN WAS CARRIED OUT. UPON INSPECTION IT WAS FOUND THAT	 THE LOWER STUDS WERE BROKE, THEY WERE REPLACED ALONG WITH THE CYLINDER.					2	L	7	4 	4R	4	R	 	A762    	E230				 
2003071800099	20030718	00099	EA  	2003	7	18	CA030711005      	1	20030702	G	5740	VALC3W1005	STRUT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						3070					(CAN) DURING A ROUTINE DAILY INSPECTION A 7 INCH CRACK ON THE UPPER SURFACE OF THE LT LOWER WING STRUT IN THE TRAILING E	DGE SKIN WAS OBSERVED. 4.2 HOURS OUT OF A 100 HR INSPECTION. THE STRUT WAS GIVEN TO A DAR,  WHO IS CONDUCTING AN INVESTI	GATION. THE REPORT SHALL BE FORWARDED TO THIS SDR WHEN RECEIVED.				1	H	7	1 	3R	4	T	 	A815    	E4EA	6	C	P15EA	 
2003082100166	20030821	00166	EA  	2003	8	21	CA030713001      	1	20030629	G	2997	MS220733	CIRCUIT BREAKER 			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HYD SYSTEM	FAILED          	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING THE FIRST OFFICER NOTICED AN ODOUR AND THE CAPTAIN VERIFIED PRESENCE OF SMOKE AT CIRCUIT BREAKER PAN	EL NR 2. THE SMOKE STOPPED WHEN THE CREW REACHED OVER AND PULLED CIRCUIT BREAKER CBP2-G13.  THE PROBLEM WAS FINALLY SOLV	ED WITH THE REPLACEMENT OF CIRCUIT BREAKERS CBP2-G13 & -G14 AND HYDRAULIC RESERVOIR NR 1.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082100167	20030821	00167	EA  	2003	8	21	CA030713002      	1	20030629	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) CAPTAIN'S WINDSHIELD SHATTERED ON CLIMBOUT (RECEIVED A LT WINDSHIELD HEAT CAUTION ABOUT 15 SECONDS PRIOR TO IT SHA	TTERING).  UNEVENTFULL LANDING PERFORMED. REPLACED LT WINDSHIELD AND HEAT CONTROLLER.  AIRCRAFT RETURNED TO SERVICE.CONT	ROLLER PN 16591, SN 1660,				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082100186	20030821	00186	EA  	2003	8	21	CA030713003      	1	20030629	G	5210	601R3197411	LEVER           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) REPORTED THAT ON THE PAX DOOR BOTH THE FWD AND AFT SWIVEL LEVERS (601R3197411) HAD FAILED ALLOWING THE DOOR TO FRE	EFALL. MAINTENANCE FOUND THE SUPPORT WHEEL LEVER BENT AND THE DOOR SKIN DISTORTEDAND WITH INTERNAL STRUCTURAL DAMAGE. RE	PLACED THE SUPPORT WHEEL, BOTH SWIVEL ASSEMBLIES AND DAMAGED DOOR SIDE SKINS. AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082100189	20030821	00189	SW  	2003	8	21	CA030714001      	1	20030708	G	5751	2734027001	COUNTERWEIGHT   			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					LT AILERON	TORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23729								(CAN) PILOT DISCOVERED ON HIS POST FLIGHT WALKAROUND THAT THE LT AILERON COUNTERWIEGHTWAS HANGING DOWN ON THE INBOARD EN	D OF THE AILERON. THE AILERON WAS REMOVED AND THE BALANCE WEIGHT WAS FOUND TO HAVE TORN OUT OF THE INBOARD BOLT HOLE. TH	E DAMAGED PART OF THE WEIGHT WAS CUT OFF AND AILERON BALANCED CHECK IAW SA226TC SRM AND FOUND TO BE WITHIN LIMITS. THE B	ALANCE WEIGHTS WHERE THEN SECURED WITH PRO SEAL.THE MATERIAL FOR THE BALANCE WEIGHT IS QUITE SOFT AND TENDS TO DROOP WIT	H TIME. WE HAVE CHECKED OTHER AIRCRAFT AND FOUND SOME WEIGHTS TO BE SLIGHTLY DROOPING.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003082100190	20030821	00190	EA  	2003	8	21	CA030714002      	1	20030712	G	2421	2CM70D2	GENERATOR       			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  					ENGINE	BURNED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTING FOR A FIRE SUPPRESION MISSION, THE RT ENGINE DRIVEN GENERATOR FAILED. THE AIRCRAFT RETURNED TO BAS	E FOR MAINTENANCE. ACCESS TO THE ENGINE DRIVEN GENERATOR REVEALED A SMALL GENERATOR FIRE. A HAND HELD EXTINGUISHER WAS D	ISCHARGED PUTTING OUT THE FIRE. CAUSE OF THE FAILURE IS UNKNOWN BUT A GENERATOR BEARING FAILURE IS SUSPECTED. GENERATOR,	 WIRING HARNESS, SCAT HOSE AND FIRE SLEEVE/OIL VENT LINE DESTROYED/DAMAGED.			2	H	7	2 	4R	4	R	RT	A14EA   	E231				 
2003082100191	20030821	00191	EA  	2003	8	21	CA030715001      	2	20030714	G	7314	LW15473	PUMP            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					FUEL SYSTEM	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HR INSPECTION THE BOLTS (ON THE ENGINE DRIVEN FUEL PUMP) HOLDING THE BOTTOM COVER TO THE PUMP BODY WERE	 FOUND LOOSE.  BOLTS WERE TIGHTENED AND TORQUE SEAL WAS APPLIED TO MAKE VISUAL INDICATION OF MOVEMENT. THIS INSTALLATION	 WOULD BE BETTER SERVED WITH BOLTS THAT WOULD ALLOW LOCKWIRE. THIS IS THE SECOND TIME THAT THESE BOLTS HAVE BEEN FOUND L	OOSE AT INSPECTION. AIRCRAFT MANUFACTURER HAS BEEN CONTACTED REGARDING THIS PROBLEM.			1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2003082100192	20030821	00192		2003	8	21	CA030715002      	4	20030715	G	2215		SERVO           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					AUTOPILOT	DEFECTIVE       	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) PILOT YOKE BINDING DURING APPROACH. USING PITCH DISCONNECT HANDLE, COPILOT YOKE FELT NORMAL. FORCE FELT LIGHTER AS	 FLAPS EXTENDED. AUTOPILOT DISCONNECTED TO VERIFY A FLAP INDICATION AT A LOWER ALT & GREATER THAN NORM FORCE REQUIRED TO	 MOVE YOKE FORWARD. CONTROLS RELAXED TO FEEL CONTROLLABILITY, AN ABRASIVE NOISE HEARD. FORCE REQUIRED TO MOVE CONTROLS W	ERE LIGHTER THAN NORM. APPROACH COMPLETED. AUTOPILOT SERVO MECHANISM FOR ELEVATOR HAS BEEN REMOVED & REPLACED & A/C RETU	RNED TO SERVICE. AUTOPILOT SERVO RETURNED TO COLLINS FOR INVEST THAT REVEALED A PIECE OF ADHESIVE STUCK BETWEEN DIAPHRAG	M & GEARSHAFT. IT WAS DETERMINED THAT AN EXCESSIVE AMOUNT OF ADHESIVE DURING ASSY PROCESS OF SHAFT CAUSED INCIDENT.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003082100193	20030821	00193	NE  	2003	8	21	CA030716001      	2	20030710	G	7250	311963101	DEFLECTOR       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TURBINE SECTION	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											(CAN) TECHNICIANS FOUND CRACKED AND MISSING PIECES OF DIFFUSER DEFLECTOR SEGMENTS DURING AN ENGINE INTERNAL BORESCOPE IN	SPECTION. AFTER INVESTIGATION IT WAS FOUND THAT THE STARTER GENERATOR HAD BEEN REMOVED IN MARCH 2003 FOR CAUSING HIGH FR	EQUENCY VIBRATIONS. PRATT & WHITNEY BELIEVES THAT THE STARTER GENERATOR VIBRATION WAS THE CAUSE OF THE DAMAGE TO THE DIF	FUSER DEFLECTOR SEGMENTS.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003082100194	20030821	00194	SW  	2003	8	21	CA030716002      	1	20030716	G	2720	12364	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT RUDDER CABLES FRAYED AT FUSELAGE PULLEYS WITH RUDDER NEUTRAL.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2003082100195	20030821	00195	NM  	2003	8	21	CA030716003      	1	20030711	G	2913	65449617	HOUSING         			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					HYD PUMP	CRACKED         	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) FLIGHT CREW REPORTS ON TAXI OUT OF YVR AIRCRAFT LOST 'A' SYSTEM HYDRAULICS AND NR 1 'A' PUMP LOW PRESSURE WARNING 	LIGHT ILLUMINATED. AIRCRAFT RETURNED TO GATE UNDER ITS OWN POWER.  MAINTENANCE INSPECTION REVEALED THE NR 8 GROUND SPOIL	ER ACTUATOR PISTON HAD POPPED OUT OF HOUSING AND THE CASING WAS ENTIRELY CRACKED AROUND THE HOUSING. COMPONENT WAS REPLA	CED AND SYSTEM GROUND CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003082100196	20030821	00196	EU  	2003	8	21	CA030716004      	1	20030710	G	2822		WIRE HARNESS    	CRANEXXXXXXX		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL BOOST PUMP	NICKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						B5009A					(CAN) WHILE PERFORMING PILATUS S/B 28-011,INSPECTION OF BOOST PUMP WIRES, SOME DAMAGE IN THE FORM OF A SMALL NICK WAS NO	TED APPROX 7 INCHES FOR THE PUMP BODY. THE INSULATION APPEARED TO BE DAMAGED THROUGH TO THE CONDUCTOR. THE PUMP ASSY WAS	 REPLACED WITH AN OVERHAULED UNIT. RECORDS INDICATE THAT THESE PUMPS HAVE NEVER BEEN REMOVED AS THEY WERE MOD 'A' PUMPS 	SINCE NEW.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003082100197	20030821	00197	CE  	2003	8	21	CA030716005      	1	20030710	G	3233		ACTUATOR        			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	FRACTURED       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) RT GEAR WOULD NOT RETRACT ON TAKE OFF.AIRCRAFT RETURNED TO BLOCKS AND RT MAIN GEAR ACTUATOR RELACED. RAM WAS FRACT	URED ON THE FIRST THREAD OF RAM TO HOLD PISTON IN PLACE.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003082100198	20030821	00198	EA  	2003	8	21	CA030716006      	1	20030713	G	5740	VALC3W1005	STRUT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED TRAILING EDGE SKIN APROX 9 INCHES LONG AT LOWER END OF STRUT ON THE BOTTOM SIDE.						1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2003082100199	20030821	00199	NE  	2003	8	21	CA030716007      	2	20030625	G	7200		ENGINE          			BOEING	234   	234         	1385049	EA  	LYC   	AL5512	AL5512      	41581	NE  					NR 2	FAILED          	W				A				UNSCHED LANDING         				B	Y		SMOKE/FUMES/ODORS/SPARKS  	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CA											(CAN) LOUD BANG, SMOKE, NR 2 ENGINE STOPPED. AIRCRAFT RETURNED TO BASE SINGLE ENGINE. SMALL PIECES OF ENGINE FOUND CONTA	INED IN NACELLE THAT APPEAR TO HAVE BEEN EJECTED THROUGH BLEED BAND. ENGINE RETURNED TO OVERHAUL SHOP FOR INVESTIGATION 	AND REPAIR. THIRD THROUGH SEVENTH STAGE OF COMPRESSOR FAILED.				2	G	7	2 	4U	4	U	 	H9EA    	E4NE				 
2003082100200	20030821	00200	CE  	2003	8	21	CA030717001      	1	20030715	G	3710	1013202661	LINE            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					VACUUM REGULATOR	CHAFED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) DURING A MAINTENANCE GROUND RUN, AND FOLLOWING THE START OF THE RT ENGINE, A HISSING SOUND WAS NOTICED EMITTING FR	OM BEHIND THE INSTRUMENT PANEL. AFTER FURTHER INVESTIGATION IF WAS FOUND THAT THE INSTRUMENT AIR TUBE HAD BEEN CHAFING O	N THE UPPER CORNER OF THE RADIO RACK. THE TUBE IS USED TO JOIN THE VACUUM REGULATOR TO THE LT SIDE OF THE FORWARD BULKHE	AD TO THE MANIFOLD LOCATED IN THE COCKPIT BEHIND THE INSTRUMENT PANEL ON THE RT SIDE.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003082100201	20030821	00201	NM  	2003	8	21	CA030717002      	1	20030714	G	2910		LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION FOR MINOR HYDRAULIC LEAK FROM THE NR 2 NACELLE , SERVERAL HYDRAULIC LINES WERE REMOVED FOR INSPE	CTION . CHAFE DAMAGE WAS FOUND ON THE NR 2 NACELLE OUTBOARD MAIN LANDING GEAR FRAME , AND ON SOME STAINLESS STEEL HYDRAU	LIC LINES. ALL CHAFED LINES REPLACED WITH NEW , FRAME DAMAGE TEMPORARY REPAIRED BY BLENDING AS ALLOWED BY BOMBARDIER REP	AIR DRAWING ISSUED FOR THIS DAMAGE. AIRCRAFT REASSEMBLED AND RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003082100203	20030821	00203	CE  	2003	8	21	CA030717003      	1	20030716	G	2434	DOFF10300J	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	FAILED          	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REPORTED ELECTRICAL FAILURE DURING TAXI.  INVESTIGATION FOUND ALTERNATOR HAD A LOOSE HOUSING. ALL LOCKING TA	BS WERE SECURE ON THRU BOLTS THAT HOLD THE FORWARD AND AFT CASE HALVES TOGETHER, YET THECASE WAS CLEARLY LOOSE AND THE T	WO SECTIONS FRETTING AGAINST EACH OTHER.AS MUCH AS .125 IN. CLEARANCE WAS FOUND DESPITE APPEARANCE THAT ATTACHEMENT BOLT	S HAD BEEN LOCKED TIGHT.  ALTERNATOR EXCHANGED FOR NEW PART.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003082100204	20030821	00204	EA  	2003	8	21	CA030717004      	2	20030715	G	7311	156E00512D0240	OIL COOLER      			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT NOTICED OIL LEAKING FROM REAR COWL AREA DURING CRUISE FLT. ENGINE WAS INTENTIONALLY SHUT DOWN & SECURED WHEN	 OIL PRESSURE FLUCTUATED AND FELL TO APPROX. 50 PSI (YELLOW INDICATION STATUS). MAINTENANCE CLEANED ENGINE AND ADDED 5 Q	UARTS OIL PRIOR TO GROUND RUN. OIL LEAK SOURCE DETERMINED TO BE THE ENGINE OIL COOLER INLET HOSE. EXTERIOR INSPECTION OF	 THE HOSE SHOWED NO DISCREPANCIES. HOSE REMOVED FROM ENGINE AND FIRE SLEEVE REMOVED FOR FURTHER HOSE INSPECTION. STEEL B	RAID WAS INTACT AND SHOWED SUBTLE KINK NEAR WHERE THE INNER BEND RADI WOULD HAVE BEEN AT INSTALLATION. INTERNAL HOSE RUP	TURE LIKELY CAUSED BY INSTALLATION STRES S NOT VISIBLE UNDER FIRE SLEEVE. HOSE TTSN 390 HOURS.	1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2003082100206	20030821	00206	NE  	2003	8	21	CA030718001      	2	20030715	G	7421	AA725	IGNITER         			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				A	J		FLAME/FIRE                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) DURING START OF NR 3 ENGINE, IT WAS OBSERVED THERE WAS NO EGT. START WAS ABORTED & OBSERVED ALL PARAMETERS. MAINT 	INSPECTED AREA & REQUESTED ANOTHER START.  NR 3 ENGINE STARTED & OBSERVED RAPID EGT RISE & ENG START ABORTED.  MAINT INF	ORMED FLT DECK THAT THERE WAS A  NR 3 ENG TAIL FIRE.  FLT CREW NOTIFIED ATC.  AN AIR START UNIT WAS USED TO START A/C AS	 APU WAS INOP.  FUEL HAD DRIPPED ONTO AIR HOSE & CAUGHT FIRE.  ASU SHUTDOWN IMMEDIATELY BEFORE FLT CREW COULD CARRY OUT 	EMERGENCY PROCEDURES FOR ENG TAIL FIRE. BOTH ASU AIR HOSE & TAIL FIRE WAS EXTINGUISHED SUCCESSFULLY BY MAINT.  NR 3 ENGI	NE IGNITOR ASSY REPLACED & CHECKED SERVICEABLE IAW MM 74-00 PAGES 601-608. NO FURTHER INCIDENT.	2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003082100207	20030821	00207	CE  	2003	8	21	CA030718002      	1	20030716	G	3246	101800259	WHEEL           			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING WHEEL OVERHAUL THE NDT FACILITY DISCOVERED 3 CRACKS IN THE OUTER-HALF OF THE WHEEL ASSEMBLY. CRACKING WAS I	N THE WEB AREA BETWEEN THE BEARING BOSS AND THE BEAD SEAT FLANGE. THE INBOARD HALF WAS NOT DAMAGED. OUTBOARD WHEEL HALF 	SCRAPPED AND REPLACED WITH NEW.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003102000158	20031020	00158	WP  	2003	10	20	CA030718003      	1	20030718	G	3250		ACTUATOR        			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					NLG STEERING	MISOVERHAULED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RECIEVED ACTUATOR THROUGH OUR SUPPLIER. UPON INSTALLATION, FOUND IT BINDING.  REMOVED IT AND FOUND THAT TWO SEPERA	TE CABLES THIS UNIT HAS WERE GOING THROUGH THE SAME PULLEY WHICH LEFT THE OTHER PULLEY NOT IN USE AND BINDING THE UNIT A	S WELL AS DAMAGING THE CABLES. THE UNIT HAD A OVERHAULED TAG ON IT AND WAS SUPPOSED TO BE TESTED BUT I DON'T THINK IT CO	ULD HAVE BEEN TESTED PROPERLY GIVEN THE WAY THE CABLES WERE RUN.			2	L	7	2 	4R	4	T	 	6A6     	E282				 
2003082100208	20030821	00208	GL  	2003	8	21	CA030718004      	2	20030718	G	7250	23074538	SHAFT           			EMB   	145   	EMB145      	3260210	SO  	ALLSN 	AE300 	AE3007A     	 	GL  					LP TURBINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE CAE 312387 IS AT ROLLS ROYCE CANADA FOR REPAIR DUE TO VIBRATION. DURING INSPECTION OF THE LP TURBINE ASSEMB	LY IT WAS DISCOVERED THAT THE LP TURBINE SHAFT (23074538) HAD A SEVERE RUB AND HEAT DISCOLORATION ON THE OUTSIDE DIAMETE	R, LOC ATED IN THE AREA OF THE HP TURBINE SLEEVE (23056160) ALSO RUBBED AT FOUR LOCATION. THE SLEEVE IS ASSEMBLED INSIDE	 THE HP T/SHAFT (23069441). THIS UNUSUAL CONDITION WAS NOTED FOR THE SECOND TIME AT RRC, THE LP T/SHAFT IS A CRITICAL PA	RT.		2	L	7	2 	4F	4	F	RT	T00011AT	TE6CH				 
2003082100209	20030821	00209	EA  	2003	8	21	CA030718005      	1	20030714	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA			15617								(CAN) FLIGHT AT FL220, THE EXTERNAL PLY OF THE RT WINDOW CRACKED. THE FLIGHT CREW DID AN EMERGENCY DESCENT AND DEPLOYED 	THE OXYGEN MASK IN THE CABIN.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082100210	20030821	00210	CE  	2003	8	21	CA030721001      	1	20030716	G	2821	710C4X	DRAIN           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL FILTER	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ABOUT ONE HOUR INTO THE FLT, THE CREW NOTED THAT FUEL WAS LEAKING OUT THE LEFT AFT NACELLE FUEL DRAIN VALVE. ONCE 	ON THE GROUND INSPECTION OF THE VALVE DETERMINED THAT THE VALVE CENTER BODY HAD SEPERATED FROM THE HOUSING, RESULTING IN	 THE LEAK. THE BODY IS CRIMPED INTO THE HOUSING DURING MANUFACTURE OF THE VALVE ANDTHE CRIMP APPEARS TO HAVE FAILED. OTH	ER VALVES IN THE SYSTEM WERE INSPECTED WITH NO DEFECTS NOTED. A FLEET CAMPAIGN IS INITIATED TO REPLACE ALL THE VALVES. R	AYTHEON WAS CONTACTED AND ADVISES THAT THERE WERE PROBLEMS IN THE PAST,  WITH A BEECH COMMIQUE 97-001 AND COMM NR 38 BEI	NG ISSUED IN 1997 AND 1982 RESPECTIVELY TO REVIEW THIS ISSUE.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003082100212	20030821	00212	SW  	2003	8	21	CA030722002      	1	20030708	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TE FLAP	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE FOUND FRAYED AT THE PULLEY PN 1-2395.THE AREA TENDS TO BE A HIGH WEAR BECAUSE OF THE SIZE OF PULLEY AND IS M	ONITORED CLOSELY AT ALL INSPECTIONS.  FAILURES HAVE OCCURED IN THE PAST WITH THIS COMPANY.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2003082100213	20030821	00213	NE  	2003	8	21	CA030722003      	2	20030425	G	7261		PUMP            			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502L     	41580	NE  					RT ENGINE OIL	FLUCTUATES      	W				E				ENGINE SHUTDOWN         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE RT ENGINE OIL PRESSURE STARTED FLUCTUATING WITH HIGH VIBESMASTER CAUTION. CREW SHUT DOWN RIGHT 	ENGINE AND AN UNEVENTFUL LANDING WAS MADE. PAX CONTINUED ON CHARTERED AIRCRAFT.  POSTFLIGHT TROUBLESHOOTING REVEALED A D	EFECTIVE OIL PUMP AND METAL CONTAMINATION. THE ENGINE WAS REMOVED. A LOANER ENGINE WAS INSTALLED AND THE AIRCRAFT WAS TU	RNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2003082100214	20030821	00214	GL  	2003	8	21	CA030722004      	2	20030721	G	7323	252466715	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) PILOT WAS IN CRUISE FLIGHT & SET UP FOR HIS APPROACH FOR LANDING AND THE ENGINE DECELLED BACK TO IDLE.THE ROTOR RP	M DECAYED AND HE ENTERED AN AUTOROTATION AND LANDED WITHOUT FURTHER INCEDENT.  WHEN ON THE GROUND WE TRIED TO MOVE THE T	HROTTLE TO FULL OPEN AND THE ENGINE WOULD ALMOST QUIT.THE GOVERNOR WAS CHANGED AND THE AIRCRAFT OPERATED NORMALLY.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003090200012	20030902	00012	SW  	2003	9	2	CA030722005      	1	20030722	G	5230	27200631	BUSHING         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	RECEPTICLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33541								(CAN) DURING COMPLETION OF MFG SERVICE LETTER 226-SL-027 INSPECTION OF CABIN AND CARGO DOOR CLICK CLACK BUSHING RECEPTIC	LES FOR CRACKS, THE NR 3 CABIN DOOR RECEPTICLE WAS FOUND CRACKED IAW THE SERVICE LETTER. THE RECEPTICLE WAS REPLACED. AL	L OTHER RECEPTICLES WERE FOUND IN GOOD CONDITION.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2003090200013	20030902	00013	SW  	2003	9	2	CA030723001      	1	20030723	G	2720	12364	CABLE           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	RUDDER CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT & RT CABLES FRAYED AT CABIN PULLEYS. CABLES ARE STAINLESS STEEL AND REPLACED WITH GALVANIZED.						1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2003082100215	20030821	00215	SO  	2003	8	21	CA030723002      	1	20030722	G	3234	554401	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					MLG SELECTOR	FRAYED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) PILOT SELECTED LANDING GEAR AND NOTICED GEAR SELECTOR WAS STICKY,  HE CARRIED OUT HIS LANDING WITH NO TROUBLE.  MA	INT WAS NOTIFIED AND AFTER FURTHER INSPECTION FOUND THAT GEAR SELECTOR CABLE HAD FRAYED INTERNALLY.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003082100216	20030821	00216	EA  	2003	8	21	CA030723003      	1	20030721	G	2720	C6CFM12106	RUDDER PEDAL    			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					COCKPIT	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE CAPTAIN'S RUDDER PEDAL BROKE OFF THE AXLE WHEN APPLYING THE BRAKES TO RELEASE THE PARKING BRAKE. WHEN EXAMININ	G THE PEDAL A DARKENED AREA IN THE AREA OF THE BREAK IS VISIBLE INDICATING IT WAS PREVIOUSLY CRACKED PRIOR TO THE FAILUR	E. THE RUDDER PEDAL WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. AN EXAMINATION OF 5 OTHER AIRCRAFT IN THE FLEET S	HOWED NO DISCREPENCIES.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2003082100217	20030821	00217	CE  	2003	8	21	CA030723004      	1	20030716	G	2421	ES4145	ROTOR           			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  	MCAULY	2D34C	B2D34C202   	GL  	ALTERNATOR	WORN            	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											(CAN) ALTERNATOR WAS REMOVED AT 225.9 HRS BECAUSE OF DECREASING OUTPUT & VOLTAGE AS ELECTRICAL LOAD WAS APPLIED. ON DISA	SSEMBLY, TWO DEFECTS WERE FOUND.  THE ROTOR SHAFT BEARING JOURNAL AT THE DRIVE END WAS FOUND LOOSE TO THE BEARING BY ABO	UT .080 INCHES, ALLOWING THE ROTOR TO RUB ON THE STATOR STACKS.THE BEARING WAS ALSO SLIGHTLY WORN ON THE INSIDE BORE.ESS	ENTIALLY THE SHAFT MATERIAL WAS WORN AWAY.  OTHER DEFECT LIKELY CAUSED OUTPUT SNAG. THREE POWER OUTPUT WIRES CONNECTING 	STATOR TO RECTIFIER ASSEMBLY WERE CHAFED & HAD BEEN SHORTING AGAINST INSIDE OF REAR HOUSING. THERE WAS NO SLEEVING OR SI	LICONE ADHESIVE TO PROTECT AGAINST CHAFING.	1	H	7	1 	3O	3	O	 	A13CE   	E286	5	C	P7EA	 
2003090800167	20030908	00167	EA  	2003	9	8	CA030723005      	1	20030719	G	6123	C6NE10473	SWITCH          			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 1 ENGINE	MISINSTALLED    	W				A				UNSCHED LANDING         				W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) NR 1 ENGINE, BETA BACK-UP SYSTEM, STEADY BLUE LIGHT ILLUMINATED IN CRUISE. FAULT FOUND TO BE KLIXON SPRING PN KX5,	 DRILLED MOUNTING HOLES NOT LINING UP WITH SWITCH KX511.					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003090800169	20030908	00169	EU  	2003	9	8	CA030723006      	1	20030720	G	7830	73M200S035	WEB             			AIRBUS	330   	A330322     	3930325	EU  	PWA   	4168  	PW4168      	 	NE  					TORQUE BOX	TORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ARRIVAL, MAINTENANCE NOTICED APPROXIMATELY 18 INCHES OF METAL PROTRUDING INTO THE AIR STREAM OF NR 1 ENGINE INB	OARD THRUST REVERSER, JUST FORWARD OF THE CASCA DE VANES.  FURTHER INVESTIGATION REVEALEDTHE DAMAGE TO BE THAT THE TORQU	E-BOX FLOW WEB PANEL HAD SEPARATED FROM THE TORQUE-BOX FLOW WEB.  MFG HAVE RECOMMENDED REPLACEMENT OF FLOW WEB PANEL.				2	L	7	2 	4F	4	F	RT	A46NM   	E36NE				 
2003082100225	20030821	00225	EU  	2003	8	21	CA030724001      	1	20030707	G	2550	121433	SOLENOID        			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					CARGO HOOK	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			HO	HOVERING       	1			CA											(CAN) WHEN CARGO HOOK ELECTRICAL RELEASE IS ACTIVATED THE SYSTEM CIRCUIT BREAKER OPENS. FOUND ELECTRICAL SOLENOID INTERN	ALLY SHORTED.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003082100226	20030821	00226	EA  	2003	8	21	CA030724002      	1	20030721	G	2432	6104789	BATTERY PACK    			CNDAIR	CL601 	CL6012A12   	1900303	EA  										EMERGENCY  LIGHT	OVERHEATED      	W				O				OTHER                   				M	H		OVER TEMP                 	ELECT. POWER LOSS-50 PC   		NR	NOT REPORTED   	1			CA											(CAN) THE BATTERY ASSEMBLY FOR NR 4 EMERGENCY LIGHTING POWER SUPPLY WAS REMOVED FOR BENCH CHECK. THE ASSEMBLY WAS INSPEC	TED AND FOUND THAT THE CELL TABS HAD BEEN OVERHEATED, INSULATION HAD BEEN MELTED OFF AND THE PLASTIC ENCLOSURE WAS ALSO 	DAMAGED. AN OPERATIONAL CHECK OF THE EMERGENCY LIGHTING SYSTEM & POWER SUPPLIES WAS CARRIED OUT AND FOUND SERVICEABLE.				2	L	7	2 	4F			RT	A21AE   					 
2003082100228	20030821	00228	CE  	2003	8	21	CA030724003      	1	20030717	G	3210	681316	SEAL            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) BOTH MAIN LANDING GEAR WHEEL ASSEMBLIES WERE INSTALLED WITH THE INBOARD WHEEL BEARING SEAL INSTALLED ON THE INCORR	ECT SIDE OF THE SNAP RING. THE MAIN WHEEL INSTALLATION BUILD-UP OUT OF SEQUENCE WITH THE BUILD-UP SHOWN IN THE COMPONENT	 MAINTENANCE MANUAL.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003082100229	20030821	00229	CE  	2003	8	21	CA030724004      	1	20030717	G	2697		WIRE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					OVERHEAT DETECT	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DUCT OVERHEAT SENSOR WIRE PN W84C20 WAS FOUND BARE & BROKEN UNDER DUCT COUPLING CLAMP. THE ELECTRICAL CIRCUIT WAS 	COMPLETED THROUGH THE CLAMP AND DID NOT SHORT TO GROUND BECAUSE IT WAS ISOLATED BY THE SILICONE RUBBER COUPLING.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003082100230	20030821	00230	CE  	2003	8	21	CA030724005      	1	20030723	G	3222	66412005	AXLE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					MLG	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING A PHASE 1-5 INSPECTION OF THE MAIN LANDING GEAR THE AXLE EXPANSION PLUG PN 5514350 WAS FOUND CORRODED. UPON	 REMOVAL OF THE PLUG CORROSION WAS FOUND ON THE AXLE BORE APPROXIMATELY 1.5 INCHES FROM THE END.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003082100242	20030821	00242	CE  	2003	8	21	CA030724006      	1	20030723	G	7120	310239001	PAD             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					UPPER MOUNT	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DUE TO LEAKING GASKET AT BLEED AIR SUPPLY TUBE FOR INLET VANE ANTI-ICING THE FORWARD FACE OF THE UPPER LT ENGINE M	OUNT PAD HAS CORRODED.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003082200001	20030822	00001	SO  	2003	8	22	CA030724007      	1	20030722	G	8120		SHAFT           	GARRTT      		PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  					TURBOCHARGER	SHEARED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			A			FLAME/FIRE                			CL	CLIMB          	1			CA						YC001309					(CAN) AFTER TAKEOFF, PILOT NOTICED A LOSS OF MANIFOLD PRESS ON RT ENG. RETURNED TO AIRPORT. SAW FLAMES, SHUTDOWN & FEATH	ERED PROP. LANDING UNEVENTFUL. DURING TAXI & AFTER STOP, ENG CONTINUED TO SMOKE. DURING INSPECT, OIL COVERED EXHAUST & T	URBOCHARGER. COMPRESSOR OF TURBOCHARGER DAMAGED. BLADES BROKEN, CURLED BACK & NICKED. COMPRESSOR LOOSE IN HOUSING & DAMA	GE APPEARS TO BE CAUSED BY BLADE CONTACT. INSPECT TURBINE. TURBINE WAS MISSING, DEPARTED A/C THROUGH EXHAUST. DUE TO SHA	FT FAILURE, OIL BEING PUMPED PAST SEAL INTO INDUCTION SYS & CAUSING SMOKE, OIL BURNED IN CYLINDERS. TURBOCHARGER REMOVED	 & DISASSEMBLED FOR INSPECT. OIL PASSAGES TO BEARING WERE CLEAR.  BUSHINGS LOOK LIKE THEY PILED UP & SHAFT TWISTED.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003082200002	20030822	00002	EA  	2003	8	22	CA030725001      	1	20030414	G	5751		COUNTERWEIGHT   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					AILERON	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT AILERON BALANCE WEIGHT ARM RIVETS FOUND LOOSE						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003082200003	20030822	00003	EU  	2003	8	22	CA030725002      	1	20030724	G	3242	15907400	DISK            	CLEVELAND   		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BRAKE ASSY	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						1099					(CAN) WHILE CHANGING THE RT MAIN TIRE, THE OUTBOARD DISK WAS FOUND CRACKED. SINCE THE BRAKE WEAR INDICATORS WERE FAR FRO	M THEIR MAXIMUM LIFE INDICATION, THIS COULD BE CONSIDERED PREMATURE FAILURE. NOTE:THERE HAD BEEN A NOISE COMING FROM THE	 BRAKE DURING TOWING. THE BRAKE UNIT HAD BEEN INSPECTED WITH THE WHEEL OFF, BUT NO DEFECTS HAD BEEN NOTED. ONLY FULL DIS	ASSEMBLY OF THE BRAKE UNIT ITSELF MAY HAVE FOUND THE CRACKS EARLIER.  BRAKE UNIT WAS REPLACED WITH A SERVICEABLE UNIT			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003082200004	20030822	00004	NE  	2003	8	22	CA030725003      	2	20030708	G	7200		PLANETARY GEAR  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	FRACTURED       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			10279								(CAN) DURING CLIMB, CREW NOTED CHIP DETECTOR LIGHT ILLUMINATED. CREW RETURNED TO DEPARTURE AIRPORT. MAINTENANCE FOUND EN	GINE MAKING A GRINDING NOISE AND FELT SOME DISTRESS IN THE POWER SECTION WHEN ROTATED. ENGINE WAS REMOVED FOR INVESTIGAT	ION. DURING TEARDOWN, THE 1ST STAGE PLANETARY GEAR WAS FOUND MISSING ONE TOOTH. FURTHER SPALLING WAS FOUND ON THE SUN GE	AR. THE DAMAGED COMPONENTS ARE BEING REPLACED. ENGINE WAS 4222.0 HRS/5454 CYCLES TSO.			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003082200005	20030822	00005	SW  	2003	8	22	CA030725004      	1	20030724	G	6230	407040036107	BEARING         	BELL        		BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					M/R MAST	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						53168					(CAN) MAST REMOVED BECAUSE OF METAL CONTAMINATION, ROLLER FOUND SPALLED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003082200006	20030822	00006	NE  	2003	8	22	CA030725005      	1	20030721	G	7921	23063372	SEAL            	ALLSN       		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ACCESSORY G/B	TORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						CAG90348					(CAN) SHORTLY AFTER INSTALLATION OF A REPAIRED ENGINE (40.5 HRS TSR), OIL COOLER BLOWER SEAL FAILED CAUSING SUBSTANTIAL 	LEAK FROM ACCESSORY GEARBOX. UPON REMOVAL OF SEAL, AME DISCOVERED A TORN SEAL LIP.  IT WAS ALSO DETERMINED THAT INSTEAD 	OF ONE SPRING, (OR NONE FOR SEALS MODIFIED BY CEB 72-3260), THE SEAL CONTAINED TWO SPRINGS AROUND THE LIP. SEAL REPLACED	, A/C RETURNED TO SERVICE.			1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2003090800171	20030908	00171	EA  	2003	9	8	CA030726002      	1	20030515	G	2720	C2CF697	SPRING          			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					PEDAL ATTACH	DAMAGED         	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) SPRING PEDAL ATTACH REPLACE.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003082200010	20030822	00010	CE  	2003	8	22	CA030726006      	1	20030305	G	5751		RIVET           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  					AILERON HINGE	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LOOSE RIVETS ON BOTH WINGS AT AILERON HINGE BRACKET REPLACED.						1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2003082200011	20030822	00011	WP  	2003	8	22	CA030728001      	1	20030724	G	6210	500P2100101	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING PILOT NOTICED DEFECT IN WHITE ROTOR BLADE. BLADE FOUND CRACKED ON UNDERSIDE SKIN FROM TRAILING EDGE TO 	SPAR 17 INCHES FROM BLADE ROOT. REMAINING BLADES INSPECTED NO DEFECTS FOUND.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003090800178	20030908	00178	EU  	2003	9	8	CA030728002      	1	20030727	G	5312		PRESSURE PANEL  			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG WW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			36252	36252							(CAN) DURING GROUND PRESSURIZATION RUN FOR T/S. VISUAL INSPECTION FOUND 12 INCH CRACK IN UPPER WHEEL WELL PRESSURE SKIN 	ALONG AIRCRAFT CENTER LINE AT EDGE OF STRINGER BETWEEN FRAMES 29 TO FRAME 32. AIRCRAFT WAS PREVIOUSLY SUBJECT TO A COMPA	NY SPECIAL INSPECTION FOR THIS PROBLEM ON OTHER SIMILAR AIRCRAFT IN OPERATORS FLEET ON MAY 24/2003 AND NO REPORTED DISCR	EPANCIES FOUND. AIRCRAFT REPAIRED AS PER BAE REPAIR INSTRUCTION HC532H9018. AIRCRAFT RETURNED TO SERVICE.			2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003090800179	20030908	00179		2003	9	8	CA030728003      	4	20030728	G	3197		WIRE HARNESS    			GROB  	G115  	G115C       	1660303	EU  	LYC   	O320  	O320D1A     	41508	EA  					INSTRUMENT PANEL	FAILED          	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											(CAN) A WIRE BUNDLE BEHIND THE RT INSTRUMENT PANEL HAD CHAFED ON A SCREW SECURING A FACTORY INSTALLED BLANKING PLATE.  T	HE NUT APPEARS TO HAVE BECOME LODGED IN THE CASING SECURING THE WIRE BUNDLE ALLOWING THE SCREW TO CHAFE THROUGH THE INSU	LATION ON TWO WIRES. THE SCREW WAS OBSERVED TO FLASH WHITE AND THE INSTRUMENT PANEL SHOWS SIGNS OF HEAT DAMAGE AROUND TH	E SCREW HOLE.			1	L	7	1 	3O	3	O	NT	A57EU   	E274				 
2003090800182	20030908	00182	GL  	2003	9	8	CA030729001      	3	20030723	G	6110	C83811	CLAMP           													HARTZL	HCA3V	PHCA3VF2    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROP WAS SENT IN TO US FOR AD 2003-13-17. PROP INSPECTION WAS NOT REQUIRED BY S/N, BUT IN THE AD THEY RECOMMENDED 	THAT ANY PROP THAT HAD BEEN OVERHAULED BY T&W BE INSPECTED IAW PARAGRAPH H. UPON DISASSEMBLY & VISUAL INSPECTION OF PART	S, FOUND TWO OF C838-11 CLAMPS WERE CORRODED BEYOND REPAIR & NEEDED PLATING. ALL THREE OF A971 BEARINGS CORRODED & DENTE	D BEYOND REPAIR. B854 CYLINDER ALSO FOUND TO BE CORRODED ON INTERNAL SURFACE & NEEDS REPLACEMENT.													5	C	P6EA	 
2003082200012	20030822	00012	EA  	2003	8	22	CA030729002      	1	20030708	G	5610	NP1393212	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, RT WINDSHIELD CRACKED. RETURNED TO DEPARTURE AIRPORT.  FOLLOWING THE WINDSHIELD REPLACEMENT, THE AIR	CRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082200018	20030822	00018	NE  	2003	8	22	CA030729003      	2	20030724	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	SHUTDOWN        	W				E				ENGINE SHUTDOWN         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			CA								807603			(CAN) LT ENGINE SHUT ITSELF DOWN WITH SMALL VIB AND OIL PRESSURE WARNING. MTCE REPORTED CHIP DETECTOR WAS CONTAMINATED A	ND SOME DEBRIS WAS IN THE TAILPIPE.  FOLLOWING LT ENGINE REPLACEMENT, THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082200021	20030822	00021	EA  	2003	8	22	CA030729004      	1	20030716	G	3320	BC10065003	LIGHT           			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					CABIN	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) GALLEY LIGHTING FIXTURE OVERHEATED: NO SNAGS FOUND IN REVIEW OF SPRING & SUMMER 2003 AMTAK RECORDS WITH REFERENCE 	TO GALLEY LIGTHING FIXTURE ISSUES.  NO LIGHT FIXTURES PURCHASED OR CONSUMED DURING THE PAST 2 YEARS.  LIGHT BULB INSTALL	ED IN GALLEY LIGHTING AREA AS WELL AS ALL CABIN LIGHTING ON CRJ. LIGHTING FIXTURE FOUND ONLY IN GALLEY AREA.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003082200023	20030822	00023	SO  	2003	8	22	CA030729005      	1	20030708	G	3242	16413601	BRAKE DISC      	CLEVELAND   		MAULE 	MX7   	MX7235      	5460180	SO  										MLG WHEEL	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) BRAKE DISC BROKE AWAY AT ALL THREE MOUNTING HOLES CAUSING RT BRAKE TO FAIL IN THE TAXI MODE. AIRCRAFT VEERED OFF T	AXIWAY AND STOPPED ON GRASS. NO OTHER DAMAGE TO AIRCRAFT.   WHEEL BOLTS APPEARED TO HAVE BEEN SLIGHTLY LOOSE, SOME CHAFI	NG EVIDENT. WHEEL INSPECTED, NEW DISC AND BOLTS INSTALLED.				1	H	7	1 	3O			NC	3A23    					 
2003082200025	20030822	00025	EA  	2003	8	22	CA030729006      	2	20030726	G	8520		ROD CAP         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE PILOT NOTICED A SLIGHT VIBRATION IN LT ENGINE AND A STRANGE NOISE THEN HE NOTICED OIL COMING OUT	 OF THE ENGINE COWL. THE ENGINE WAS SHUT DOWN AND PROP FEATHERED AND THEN LANDED AT THE NEAREST AIRPORT WITH NO FURTHER 	PROBLEMS. INSPECTION OF THE ENGINE REVEILED THAT NR 1 CONNECTING ROD HAB BROKEN AND PUNCTURED THE CASE IN THREE DIFFEREN	T LOCATIONS.  WE ARE STILL WAITING TO HEAR FROM THE ENGINE SHOP FOR THE CAUSE OF THE BREAKAGE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003082200029	20030822	00029	CE  	2003	8	22	CA030729007      	1	20030723	G	2435	23047004	STARTER GEN     			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3311     	01514	WP  					ENGINE	FAILED          	W				O				OTHER                   				E	H		VIBRATION/BUFFET          	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			CA											(CAN) STARTER GENERATOR HAD INTERNAL FAILURE CAUSING AN ELECTRICAL SHORT CIRCUIT TO GROUND, CAUSING THE BUSS TIE TO LT B	USS CURRENT LIMITER TO BLOW, THUS CAUSING TO LT BUSS TO LOOSE ELECTRICAL POWER, NO PILOTS INSTRUMENTS. NO POWER TO OPERA	TE CONTROL CIRCUITS FOR FLAPS ON MLG (GEAR WAS BLOWN DOWN WITH N2). NO POWER TO OPERATE ENGINE ELECTRIC CONTROL, REVERTI	NG TO MANUAL, THUS NO REVERSE FOR LANDING.			1	L	7	2 	3T	3	T	RT	A28CE   	E3WE				 
2003082200036	20030822	00036	GL  	2003	8	22	CA030729008      	3	20030722	G	6114	A2202	BEARING         			BLANCA	17    	1731ATC     	1220437	GL  	LYC   	O540  	IO540K1E5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									DY40		(CAN) SEVERAL SMALL CRACKS WERE FOUND ALONG THE BALL TRACK OF THE INBOARD RACE OF THE A2202 BEARING. THE BEARINGS WERE R	EPLACED AND THE PROPELLER WAS OVERHAULED.					1	L	7	1 	3O	3	O	 	A18CE   	1E4	5	C	P25EA	 
2003082200038	20030822	00038	EA  	2003	8	22	CA030729009      	2	20030526	G	7322	MA45PA	CARBURETOR      			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	FAILED          	W				B				EMER. DESCENT           				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AIRCRAFT ENGINE LOST POWER IN A CLIMB, LEVELLING OUT RESTORED POWER, ANY ATTEMPT TO CLIMB RESULTED IN PARTIAL POWE	R LOSS.  AT 231.2 HOURS THE CARB WAS REMOVED AND REPAIRED. THE FLOAT BOWL THREADS WERE STRIPPED OUT, A USED SERVICEABLE 	FLOAT BOWL WAS INSTALLED. I SUSPECT THE FLOAT LEVER SETTING IS INCORRECT. IN THE PAST 2 YEARS I HAVE SENT BACK 4 MAGS, 2	 STARTERS AND ANOTHER CARBURETOR TO THIS COMPANY THAT WERE FRESH OUT OF OVERHAUL AND HAVE FAILED.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003082200041	20030822	00041	NM  	2003	8	22	CA030729010      	1	20030727	G	2612	UK	CONNECTOR       			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	CONTAMINATED    	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) FLT CREW REPORTS ON START UP, THEY HAD A FIRE WARNING FOR THE NR 2 ENG,  FIRE LIGHTS, BELLS & FIRE HANDLE LIGHT WE	RE ON. ENG SECURED BY ENG FIRE.  QRC- YSB TOWER NOTIFIED & FIRE TRUCKS WERE CALLED. CREW DISCHARGED BOTH FIRE BOTTLES, N	O EVIDENCE OF FIRE. A/C PAX DEPLANED & MAINT CALLED. MAINT INVESTIGATION CONFIRMED NO EVIDENCE OF FIRE. RT ENG FIRE DETE	CTION SYS PLACED ON MEL & FIRE BOTTLES REPLACED.  AIRCRAFT RETURNED TO SERVICE. AT NEXT RON, MAINT FOUND NR 2 ENG UPPER 	FIRE/OVERHEAT DETECTOR LOOP CONNECTORS CONTAMINATED. CONNECTORS CLEANED PER SWPM.  NO FAULTS FOUND. ENG FIRE/OVERHEAT SY	STEM TESTED PER MM.  NO FAULTS FOUND. MEL CLEARED AND AIRCRAFT RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003082200043	20030822	00043	EA  	2003	8	22	CA030729011      	2	20030714	G	7322	1041641	SCREW           			PIPER 	PA24  	PA24180     	7102402	CE  	LYC   	O360  	O360A1A     	41514	EA  					CARB FLOAT BOWL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SCREWS HOLDING FLOAT BOWL TO CARBURETOR HOUSING. ALL SCREWS LOCKED BUT ALL LOOSE IN HOUSING CAUSING CHAFING BETWEE	N BOWL, GASKET HOUSING WITH A 1/16 INCHES GAP AND ALL AROUND. DISCOVERED ON ANNUAL INSPECTION.					1	L	7	1 	3O	3	O	NT	1A15    	E286				 
2004010700050	20040107	00050	NM  	2004	1	7	CA030729012      	1	20030702	G	7603	BACC13AA3T556506	CONTROL CABLE   			BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					THRUST CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						54767					(CAN) DURING INSPECTION OF THE STATION 870 AREA AT C-CHECK IT WAS FOUND THAT THE NR 3 ENGINE THRUST CABLE WAS FRAYED TO 	THE POINT OF 1 (ONE) STRAND REMAINING.  THE CAUSE WAS IMPROPER ROUTING OF THE CABLE.  THE CABLE WAS NOT ON THE PULLEY AN	D WAS CHAFING ON THE PULLEY BRACKET.  THE PULLEY/CABLE SECURING PIN WAS IN PLACE.  THIS AREA WAS LAST ACCESSED DURING TH	E PREVIOUS CHECK.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003082200046	20030822	00046	NM  	2003	8	22	CA030729013      	1	20030702	G	5270	S586	WARNING SWITCH  			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					MLG DOOR	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) JUST PRIOR TO DESCENT THE MAIN CARGO DOOR WARNING LIGHT ILUMINATED. THE CAPTAIN MADE AN EMERGENCY DESCENT AND THE 	AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. THE MAIN CARGO DOOR WARNING SYSTEM WAS UNDER THE APPROVED MEL AT THE TIME. THE	 MEL HAD BEEN APPLIED ON A PREVIOUS LEG WHEN MAINTENANCE HAD DETERMINED THAT AS OUT OF RIG WARNING SWITCH HAD CAUSED FAL	SE WARNINGS. THE MEL HAD BEEN APPLIED IAW THE PUBLISHED INSTRUCTIONS AND THE SYSTEM WAS PLACARDED.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003102000160	20031020	00160	CE  	2003	10	20	CA030729014      	1	20030729	G	2510	08128111	SPRING          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					HEAD REST	MISMANUFACTURED 	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) MAINTENANCE TECHNICIANS WERE REPLACING A BROKEN HEADREST EXTENSION SPRING WITH A NEW PART WHEN THE NEW PART FAILED	. THE NEW SPRING SUPPLIED BY CESSNA WAS FOUND TO BE EXTREMELY BRITTLE AND WOULD BREAK IF DEFLECTED. A CALL TO CESSNA CUS	TOMER SUPPORT CONFIRMED THAT THE SPRINGS HAD BEEN MANUFACTURED INCORRECTLY.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003082200047	20030822	00047	WP  	2003	8	22	CA030729015      	2	20030605	G	7310	39423091	SWITCH          			BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					FUEL SHUTOFF	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING FLIGHT, THE ENGINE WAS UNABLE TO BE SHUT DOWN BY SELECTING ENGINE STOP BUTTON.						1	L	7	2 	3T	4	T	 	A14CE   	E2WE				 
2003082200060	20030822	00060	SW  	2003	8	22	CA030729016      	1	20030710	G	6720	500N720155	CONTROL CABLE   			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	25OC  	250C20R     	 	GL  					T/R PEDAL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT PREFLT, PILOT REPORTED A 'BINDING' AT EXTREME RT PEDAL. MAINT DISCONNECTED SECTIONS OF SYS & COULDN`T REPEAT. D	AYS LATER PILOT REPORTED SIMILAR BINDING PLUS A 'BANG' BEFORE MOVING SMOOTHLY AGAIN. DURING INVEST,  ENGINEERING FOUND B	INDING WHERE 2 CABLES JOIN TOGETHER AT TAILBOOM DISCONNECT. INNER CABLE HAS A MACHINED HEX SECTION THAT MATES WITH A HEX	 INSIDE CABLE SHEATH. AT EXTREME, PEDAL INNER HEX EXITS SHEATH HEX & IS PRELOADED, & TWISTED (10-20 INCH). WHEN PEDALS W	ERE MOVED TOWARD NEUTRAL INNER CABLE HEX ATTEMPTED TO ENTER SHEATH HEX, & BECAUSE OF A MISALIGNMENT, BOUND UP, & WHEN EN	OUGH PRESSURE EXISTED, IT WOULD SNAP INTO ALIGNMENT (CAUSING BANG & BINDING). BOTH CABLES CHANGED, RETURN TO SERVICE.	1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2003102000161	20031020	00161	CE  	2003	10	20	CA030729017      	1	20030703	G	5740	6147514435	WASHER          			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					WING FITTING	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) CAD PLATING MISSING ON 1/2 OF NEW WASHER, BOTH SIDES.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003090800183	20030908	00183	NM  	2003	9	8	CA030729018      	1	20030504	G	7160		ACTUATOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					BY-PASS DOOR	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PREFLIGHT ENGINE INTAKE BYPASS DOOR CONTROL WAS UNSERVICABLE ON RT ENGINE. STUCK IN OPEN. RELEASED ACCORDIN	G TO MEL. SYSTEMS CHECKED OK.  BY-PASS DOOR ACTUATOR WAS REPLACED THE FOLLOWING DAY.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003082200061	20030822	00061	NM  	2003	8	22	CA030729019      	1	20030531	G	2750	85711423101	BRACKET         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TORQUE SENSOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACKED (X2 PLACES) AT 1-1.5 INCHES LONG TORQUE SENSOR BRACKET PN 85711423-101. BRACKET ATTACHED TO REAR WING SPAR	 YC37.00 LT BRACKET MADE VERY LIGHT  0.040 INCHES 2024-T3AL					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003082200063	20030822	00063	SO  	2003	8	22	CA030729020      	1	20030721	G	5280	6709010	DOOR            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	MCAULY	3AF34C	3AF34C502   	GL  	MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CRACKS ON THE MAIN LANDING GEAR DOOR FLANGE. BOTH LT AND RT DOOR. DOOR IS FIBERGLASS COMPOSITE STRUCTURE. MAIN LAN	DING GEAR DOOR LT PN 67090-10 MAIN LANDING GEAR DOOR RT PN 67090-11.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2003090800185	20030908	00185	NM  	2003	9	8	CA030729021      	1	20030605	G	6120		CONTROL UNIT    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					PITCH CONTROL	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) AFTER APPLYING TAKEOFF POWER RT PROP FEATHERED TO 200 RPM. UP TRIM ON LT ENGINE, WITH PEC CAUTION ON WARNING/CAUTI	ON PANEL. TAKE OFF ABORTED AND RIGHT ENGINE SHUT DOWN. TAXIED BACK TO GATE WITH NORMAL DEBARKATION. FAULT CODES 260 AND 	236 LOGGED IN CDS. FAULT CLEAR PERFORMED. ELECTRICAL CONNECTORS CHECKED ACCORDING FIM TASK 61-20-00-810-898 WITHOUT ANY 	FINDINGS. PROPELLER CONTROL UNIT REPLACED ACCORDING AMM 61-20-11.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003090800187	20030908	00187	NM  	2003	9	8	CA030729022      	1	20030523	G	2612		FIRE LOOP       			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 1 ENGINE	DAMAGED         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) 20 MINUTES AFTER ENG SHUTDOWN, FIRE WARNING CAME ON NR 1 ENGINE. AS NO PASSENGERS WERE ONBOARD VISUAL CHECK WAS PE	RFORMED ON ENGINE & FIRE FIGHTING NOT INITIATED. WARNING WENT OFF AFTER 15 MIN.  PEC FIRE LOOP PN 10109601 REPLACED ACCO	RDING AMM. NOTE STRIP REPORTS OF FIRE LOOPS HAVE SHOWN THAT FIRE DETECTION LOOP ACTIVATION TEMP HAS DECREASED FROM NORMA	L 300 DEGREES F SETTING, AS A RESULT OF PROLONGED EXPOSURE TO A HOT ENVIRONMENT. VALUES REMOVED LOOPS RANGE FROM 216 TO 	220 DEGREES F. INVESTIGATION FROM MANUFACTURER HAS DETERMINED THAT REDUCTION IN TRIGGER TEMP, IS RESULT OF PREMATURE HYD	ROGEN OUT GASSING WITHIN INNER TUBE OF FIRE LOOP. GREATER HYDROGEN OUT GASSING, LOWER TRIGGING TEMP.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003082200067	20030822	00067	WP  	2003	8	22	CA030729023      	2	20030725	G	7320	39423091	SHUTOFF VALVE   			BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					FUEL SYSTEM	DAMAGED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THIS PART HAD PREVIOUSLY FAILED AND WAS SENT FOR REPAIR AND THEN REINSTALLED.  THE COMPONENT FAILED FOR THE SAME F	AULT AFTER ONLY 13.2 HRS OF OPERATION. THE UNIT WAS AGAIN REMOVED AND SENT FOR REPAIR AT THE SAME FACILITY UNDER WARRANT	Y.				1	L	7	2 	3T	4	T	 	A14CE   	E2WE				 
2003102000167	20031020	00167	NM  	2003	10	20	CA030729024      	1	20030714	G	2612		FIRE DETECTOR   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					RT ENGINE	FALSE ACTIVATION	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN)  17 MIN AFTER SHUTDOWN, RECEIVED A RT ENG FIRE WARNING. A/C REFUELING, CANCELLED AURAL WARNING & INSPECTED FOR FIR	E ON RT ENG. ALL NORMAL, CONTINUED TO FUEL.  AFTER 25 MIN. RECEIVED A SUGGESTION FROM TECH. OPEN COVER ON BOTH SIDES OF 	THE ENG. AFTER A COUPLE OF MINS. LIGHT OUT. FIRE WARNING MOST LIKELY CAUSED BY FAULT OF THE PEC FIRE INDICATION LOOP. ST	RIP REPORTS OF LOOPS SHOW FIRE LOOP ACTIVATION TEMP DECREASED FROM NORMAL SETTING, AS A RESULT OF PROLONGED EXPOSURE TO 	A HOT ENVIRONMENT. VALUES OF REMOVED LOOPES RANGE FROM 216 TO 220 DEGREES F. INVEST FROM MANUFACTURER DETERMINED THAT RE	DUCTION IN TRIGGER TEMP, IS RESULT OF PREMATURE HYDROGEN OUTGASSING WITHIN INNER TUBE OF FIRE LOOP.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003082200079	20030822	00079	CE  	2003	8	22	CA030729025      	1	20030724	G	2750	99524122	GEAR            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					FLAP GEARBOX	STRIPPED        	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						2515					(CAN) AFTER LANDING AND FLAPS RETRACTED CREW NOTICED THAT INBOARD FLAPS HAD RETRACTED FULLY BUT THE OUTBOARD FLAP HAD ST	UCK AT ABOUT THE APPROACH SETTING. FLAP GEARBOX/MOTOR ASSY REPLACED.  INSPECTION OF FAILED GEARBOX REVEALED NUMEROUS STR	IPPED TEETH ON ONE OF THE GEARS.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003082200080	20030822	00080	SO  	2003	8	22	CA030730001      	1	20030725	G	3210	404130405	FORK            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			10920								(CAN) WHILE INSPECTING BRAKE PADS A CRACK WAS NOTICED ON THE RT MAIN LEG CASTING AT THE AXEL RADIUS. FURTHER INSPECTION 	NOTED A 1.5 INCH CRACK IN THE RT LEG AND A 0.5 CRACK IN THE LT LEG.  BOTH MAIN LANDING GEAR LEGS REPLACED WITH SERVICEAB	LE UNITS.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003082200081	20030822	00081	SO  	2003	8	22	CA030730002      	1	20030710	G	3222	4027300	TRUNNION        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) NOSE LANDING GEAR HOUSING (TRUNNION) PIPER PN 4027300 NOTED CRACKED DURING WALK AROUND INSPECTION. APPROXIMATELY 6	 INCHES CRACK FROM RT SIDE STEERING STOP UP AND BACK ON HOUSING. THE TYPE OF CRACKING RESULTS FROM OVER STEERING OR EXCE	SSIVE PULL DURING GROUND HANDLING. THE CRACK PROBABLY PROGRESSED TO BE VISIBLE ON THE PROCEEDING LANDING.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003082200082	20030822	00082	GL  	2003	8	22	CA030730003      	1	20030721	G	7810	2500324	EXHAUST PIPE    			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912S3  	 	EU  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NOTED SLIGHT DISCOLORATION OF COWL ON ROUTINE DAILY INSPECTION, REMOVED UPPER COWL FOUND LOWER COWLING WITH SLIGHT	 BURNED AREA AROUND NR 1 CYLINDER REMOVED EXHAUST WRAP TO FIND NR 1 EXHAUST PIPE CRACKED AND BLOWN OUT. THIS IS THE 4TH 	TIME ON DIFFERENT AIRCRAFT, SAME TYPE OF ENGINE WE HAVE FOUND THIS PROBLEM OVER THE PAST 3 MONTHS.				1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2003090200014	20030902	00014	GL  	2003	9	2	CA030730004      	1	20030707	G	7810	2500324	EXHAUST PIPE    			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912S3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE ROUTINE INSPECTION, WE NOTICED SOME DISCOLORATION ON THE EXHAUST WRAP WHEN COWLS WAS REMOVED (SB 20 	78 04A). WHEN EXHAUST WRAP WAS REMOVED, IT REVEALED AN INSIDE BEND OF THE NR 1 CYLINDER AND FOUND THAT THE EXHAUST PIPE 	HAD BLOWN OUT. THIS WAS NOT OUR FIRST FINDING OVER THE PAST 3 MONTHS. WE HAVE HAD 3 OTHER AIRCRAFT WITH THE SAME IDENTIC	AL PROBLEM ON THE S3 ENGINES AT THE NR 1 CYLINDER ONLY. WE FEEL THIS PRESENTS A REAL CONCERN TO SAFETY.			1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO	 
2003090200015	20030902	00015	EU  	2003	9	2	CA030730005      	1	20030729	G	2731	Z4244120000	CABLE           			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ELEVATOR TRIM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AS A RESULT OF PREVIOUS FRAYED CABLES, SPECIAL ATTENTION IS PAID TO AREAS WHERE THE ELEVATOR TRIM CABLE PASSES THR	OUGH PULLEYS, CABLE DRUMS.  THIS CABLE HAD BROKEN STRANDS WHERE IT PASSED THOUGH THE LT AFT PULLEY.  A REPLACEMENT INTER	VAL OF THESE CABLES OF 3000 HRS WAS PUT IN PLACE TO PRECLUDE A RAPID DETERIORATION OF THESE CABLES, HOWEVER THIS CABLE H	AD ONLY 1199.2 HRS ON IT.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003090200016	20030902	00016	EA  	2003	9	2	CA030730006      	1	20030709	G	2761		PCU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ACTUATOR	ERRATIC         	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT OUT OF ROLL TRIM ON T/O, FLAP 8, IMMEDIATELY REQUIRED RIGHT CONTROL INPUT.   AUTOPILOT ALSO SHOWED RIGHT 	CONTROL INPUT. ON APP. HAND FLOWN, FLAP 45, REQD. RWD TRIM TO ALMOST FIRST HASH MARK.   REPLACED LT WING OB FLIGHT SPOIL	ER PCU DUE FLOATING/ERRATIC MOVEMENT.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003090200017	20030902	00017	EU  	2003	9	2	CA030730007      	1	20030708	G	6320	4638302024	BEARING RACE    			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	SPALLED         	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) LT INPUT ROLLER BEARING OUTER RACE SPALLING/PEELING. METAL CONTAMINATION CAUSED EXSTENSIVE DAMAGE TO OTHER INTERNA	L TRANSMISSION BEARINGS.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003090200018	20030902	00018	EA  	2003	9	2	CA030730008      	1	20030710	G	3710		BEARING         			DHAV  	DHC3  	DHC3        	2800202	EA  	WSK   	ASZ62 	ASZ62IRM18  	 	NE  	HAMSTD	23E	23E50       	NE  	VACUUM PUMP	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) BEARING FAILURE ON ACCESSORY GEARBOX VACUUM PUMP DRIVE (HOLLOW) SHAFT. THE BEARINGS (BUSHINGS) WERE FOUND SEIZED T	O THE DRIVESHAFT AND BEARING -EXCESSIVE HEAT THRU FRICTION WAS THEN CREATED AND CAUSEDTHE ALUMINUM PLUG LOCATED INSIDE T	HE SHAFT TO MELT, WHICH THEN ALLOWED THE ACCESSORY GEARBOX OIL TO BE EXHAUSTED OVERBOARD. ENGINE LOST 8 GALLONS OF OIL I	N 20 MINUTES, 3-4 MINUTES LONGER & THE ENGINE WOULD HAVE BEEN TOTALLY STARVED FOR OIL.THIS IS THE THIRD KNOWN FAILURE OF	 THIS PART IN AREA.		1	H	7	1 	3R	3	R	 	A815    	E10NE	6	C	P603	 
2003090200019	20030902	00019	EU  	2003	9	2	CA030730009      	1	20030623	G	3320	6500111	CONTACTOR       			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	BULB SOCKET	SHORTED         	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AFTER TAKEOFF FROM YTH A SLIGHT SMOKE HAZE DEVELOPED IN THE CABIN WHEN THE LIGHTS WERE TURNED ON.  A SHARP ODOR WA	S ALSO NOTICED. THE CABIN LIGHTS WERE TURNED OFF AND THE AIRCRAFT RETURNED TO YTH.  INSPECTION REVEALED THAT THE CONTACT	S HAD SHORTED AND LAMP HOLDER WAS CHARGED ON THE CABIN LIGHT AT STA 7A.  ALL OTHER LIGHTS APPEARED NORMAL. THE LIGHT FIT	TING AND TUBE AT STA 7A WIRE REPLACED AND THE LIGHTING SYSTEM TESTED NORMAL. NO REPEAT OF THE DEFECT HAS OCCURRED.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2003090200020	20030902	00020	SO  	2003	9	2	CA030730010      	1	20030716	G	3220	2075209	HOUSING         			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	MLG	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FLUID LEAK FROM HOUSING ASSEMBLY. CRACK DETECTED.						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2003090200021	20030902	00021	SO  	2003	9	2	CA030731001      	2	20030522	G	8500		ENGINE          			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  		OUT OF BALANCE  	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) ENGINE WAS REMOVED DUE TO VIBRATION.  ENGINE WAS FOUND TO BE DETUNED. NEW COUNTERWEIGHTS INSTALLED, ENGINE BALANCE	D AND RE-INSTALLED RECERTIFIED.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2003090200022	20030902	00022	CE  	2003	9	2	CA030731002      	1	20030713	G	7603		CABLE           			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	THROTTLE CONTROL	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI OF AIRCRAFT ADVANCING THROTTLE WOULD NOT INCREASE ENGINE RPM. - INVESTIGATION SHOWED THROTTLE CABLE BR	OKEN IN ENGINE COMPARTMENT BETWEEN WIRE CABLE AT BASE OF SOLID PUSH ROD ON CONTROL ASSEMBLY (THROTTLE).					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2003090200023	20030902	00023	GL  	2003	9	2	CA030731003      	2	20030704	G	7250	6886407	BLADE           	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TURBINE WHEEL	BROKEN          	W				B				EMER. DESCENT           				D	M		INFLIGHT SEPARATION       	OVER TEMP                 		CR	CRUISE         	1			CA						X140758					(CAN) IN-FLIGHT CRUISE CONFIGURATION, HIGH PITCH WHINE STARTED, TOT INCREASED FROM APPROXIMATELY 700 DEGREES C TO 760 DE	GREES C. EMERGENCY DESCENT - RUN ON LANDING AT LOCAL AIRPORT.  TEARDOWN INSPECTION TO FOLLOW (SUMMARY OF FINDINGS).  INI	TIAL VISUAL (PRE TEARDOWN) INSPECTION REVEALS ONE FRACTURED 1ST STAGE BLADE (APPROXIMATELY 65 PERCENT MISSING) AND PIECE	S MISSING FROM MANY OTHER BLADE TIPS.  LEADING EDGE OF ALL BLADES APPEAR TO BE ABRADED BY FOREIGN OBJECT (FAILED BLADE).	  NR 8 BEARING HEAT SHIELD AND 1ST STAGE NOZZLE APPEAR TO BE IN GOOD CONDITION (NO OVERTEMP).		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003090200024	20030902	00024	CE  	2003	9	2	CA030731004      	1	20030717	G	2730	051011110	PUSHROD TUBE    	CESSNA      		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ELEVATORS	STUCK           	W				D				RETURN TO BLOCK         				C	F	W	F.O.D.                    	FLT CONT AFFECTED         	INADEQUATE Q C            	TX	TAXI/GRND HDL  	1			CA											(CAN) ELEVATOR CONTROL JAMMED ON PREFLT FUNCTION TEST. COMPLETE SYSTEM INSPECTED FOR FAULT. FINDINGS: LOOSE NUT (FOD) NR	 NAS 697A6 FOUND STUCK ON TOP OF ELEVATOR PUSH ROD NR 0510111-10 AT BELLCRANK ASSEMBLY NR 0761202-50 ATTACHMENT. RESTRAI	NING ELEVATOR MOVEMENT TO THE LOWER STOP. THAT NUT WAS PROBABLY LOST ON TOP OF LOWER ELEVATOR CONTROL STOP - ELEVATOR LO	WER NR 0510146-9 AND WAS LEFT THERE UNTAKEN CARE OF AND UNDETECTED FOR YEARS THERE AFTER. THIS NUT I S OFF VERTICAL FIN 	FORWARD INSTALLATION BOLTS NR AN6-7A. LAST SUSPECTED REMOVAL AND REASSEMBLY OF VERTICAL FIN (WITH NEW NUTS) MAY 1990.  A	IRCRAFT MAINT TECH  SHOULD 'NEVER' LEAVE 'LOST' AND 'UNFOUND' HARDWARE IN AN AIRFRAME. JUST LIVE TOOLS.	1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2003090200025	20030902	00025	EA  	2003	9	2	CA030731005      	1	20030715	G	5520	60010300563	BUSHING         			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A      	30015	NE  					ELEVATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER COMPLETION OF TASK, INSPECT ELEVATOR ATTACH BOLTS, VISUAL AND NDT INSPECTION, AND DURING POST INSTALLATION/I	NDEPENDENT INSPECTION, INSPECTOR NOTICED CLICKING NOISE, FOLLOWING INVESTIGATION FOUND (LT ELEVATOR): LT ELEVATOR ATTACH	 FITTING CRACKED, DURING LT ELEVATOR REMOVAL FOUND BUSHING MISSING AT PCU TO ELEVATOR ATTACHMENT HARDWARE/OUTBOARD. ALSO	 FOUND AT INBOARD PCU (LT), BUSHING MISSING WHICH REVEALED 2 CRACKS ON LT ELEVATOR ATTACH FITTING PROPOGAGING FROM HOLE 	TOP & BOTTOM AREA. RT ELEVATOR NO DEFECT FOUND. PARTS NOT AVAILABLE AT THIS TIME, LOANER ELEVATOR TO BE INSTALLED.		2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2003090200026	20030902	00026	SO  	2003	9	2	CA030731006      	1	20030629	G	3220		LANDING GEAR    			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NOSE	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING NOSE WHEEL COLLAPSED WHILE TOWING AIRCRAFT TO HANGAR. RIGHT MAIN GEAR COLLAPSED.						1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2003090200027	20030902	00027	SO  	2003	9	2	CA030731007      	2	20030701	G	8550	6521718	DIPSTICK        			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	OIL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE DIPSTICK SEPARATED & BROKE OFF FROM THE CAP.						1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2003090200028	20030902	00028	NE  	2003	9	2	CA030731008      	2	20030708	G	8530	399353	CYLINDER HEAD   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ENGINE	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) CYLINDER HEAD OF NR 7 ASSEMBLY BROKE/SEPARATED IN CRUISE FLT. ENGINE ONLY 36.9 HOURS TTSO. METAL FATIGUE OR OIL LO	CK ON PREVIOUS ENGINE START SUSPECTED. OVERHAUL ASSEMBLY INSTALLED, GROUND RUN AND FOUND SATISFACTORY.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2003090200029	20030902	00029	EA  	2003	9	2	CA030731009      	2	20030711	G	8520	STD705	BOLT            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	IDLER GEAR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10730								(CAN) ON OVERHAUL DISASSEMBLY OF THE ENGINE, WE NOTICED THAT THE TWO BOLTS HOLDING THE IDLER GEAR SHAFT UNSCREWED AND TH	E LOCK PLATES HALF WAY ON THE BOLTS. THIS PROVOKE THE WITHDRAWAL OF THE IDLER GEAR AND CAUSED AN ENGINE SHUTDOWN. THE MA	NUFACTURER PERFORMED THE LAST OVERHAUL.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003090200030	20030902	00030	CE  	2003	9	2	CA030731010      	1	20030718	G	5530	04310093	BRACKET         	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10991								(CAN) DURING ROUTINE 200 HOUR INSPECTION THE FORWARD LT VERTICAL FIN ATTACHMENT BRACKET APPEARED TO BE CRACKED ALONG THE	 BASE EXTERNAL SURFACE WHERE IT MATES WITH THE VERTICAL TABS OF THE PART.  DISASSEMBLY REVEALED THE CRACK EXTENDED FORWA	RD AND AFT ALONG THIS DIMENSION.  THE DEFECTIVE BRACKET WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003090200031	20030902	00031	CE  	2003	9	2	CA030731011      	1	20030609	G	3240	651710917	LINE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	530   	PW535A      	 	NE  					BRAKE SYSTEM	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LT AND RT BRAKE HYD LINES WERE FOUND TO BE CHAFING ON ELEVATOR CONTROL CABLES AT F.S.178.00. THIS DISCREPANCY IS B	ELIEVED TO HAVE OCCURRED AT MANUFACTURE.  AS THIS WAS THE FIRST TIME THE FLOOR PANEL HAD BEEN REMOVED. THIS AREA IS A PL	ACE WHERE THE HYDRAULIC BRAKE LINES RUN LATERALLY ACROSS THE FLIGHT CONTROL CABLES.  THE PROBLEM WAS RECTIFIED BY REPLAC	ING BOTH LINES ASSEMBLIES AND REPOSITIONING TWO ADJACENT ADEL CLAMPS AS TO PROVIDE MAXIMUM CLEARANCE. THE GENERAL AREA I	S 1.0 FT FORWARD OF CABIN DOOR UNDER CENTER FLOORBOARD.   LT BRAKE HYD LINE P/N 6517109-17 RT BRAKE HYDRAULIC LINE P/N 6	517109-18.	2	L	7	2 	4F	4	F	RT	A22CE   	E00053EN				 
2003090200032	20030902	00032	GL  	2003	9	2	CA030731012      	2	20030727	G	7323	6870035	TUBE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GOVENOR	BROKEN          	W				B				EMER. DESCENT           				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) A/C WAS ON APROCH 1000 FT ABOVE GROUND ON A RECONNAISSANCE FLIGHT OVER A FOREST FIRE WHEN THE PILOT AND PASSENGER 	BOTH HEARD A 'POP'. THE ENGINE DECELERATED TO IDLE.  AN AUTOROTATION WAS CARRIED OUT TO A MUSKEG AREA WHERE ON TOUCHDOWN	 THE MAIN ROTOR BLADE SEVERED THE TAILBOOM.  IT WAS FOUND THAT THE PC LINE FROME THE GOVENOR TO THE FUEL CONTROL HAD BRO	KEN.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003090800211	20030908	00211	NE  	2003	9	8	CA030731013      	2	20030712	G	7250	3020159	RING            								PWA   	PT6   	PT6A114A    	52043	NE  					CT SHROUD	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE OVERHAULED IN MAY, 2001 AND RETURNED TO OPERATOR & WHO NOTED THE PERFORMANCE OF ENG HAD DETERIORATED & ENG 	WAS SENT BACK TO OVERHAULED SHOP. OVERHAUL SHOP DISCOVERED CT SHROUD SEGMENT RETAINING RING WAS NOT INSTALLED IN ITS GRO	OVE BUT HAD MOVED REARWARDS & JUMPED OVER RETAINING LIP OF THE CT SHROUD HOUSING CAUSING SOME FRETTING WEAR ON THE HOUSI	NG. THIS MOVEMENT OF RETAINING RING ELIMINATED ANY PHYSICAL IMPEDIMENT TO CT SHROUD SEGMENTS, WHICH HAD MIGRATED REARWAR	DS & LOST LOCATION. THIS CAUSED A HEAVY TIP RUB WITH CT BLADES AND ATLANTIC TURBINES ATTRIBUTES SUBSTANTIAL LOSS OF PERF	ORMANCE TO THIS RUB. CT SHROUD SEGMENTS WERE REPLACED & CT BLADES WERE WORN BELOW MINIMUM LENGTH ALSO REPLACED.						3	T			E4EA				 
2003090400128	20030904	00128	EU  	2003	9	4	CA030731015      	2	20030724	G	7210	602070009	GEARBOX         			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	RIGHT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ON CLIMBOUT THE STARBOARD GEARBOX FAILED. ENGINE WAS SHUTDOWN AND AIRCRAFT RETURNED TO YNA. AIRCRAFT WAS CHECKED B	Y AN ENGINEER AND WAS CONFIRMED GEARBOX FAILURE. THE DRIVESHAFT GD2016 S/N DR6306/65 WAS REMOVED, ENGINE CHECKED. AIRCRA	FT FERRIED BACK TO YXY BASE ON FERRY FLIGHT,  AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899	 
2003090800212	20030908	00212	EU  	2003	9	8	CA030731016      	1	20030724	G	2910		LINE            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) WHILE ENROUTE BOTH THE STARBOAD AND PORT HYDRAULIC PUMP LOW FLOW WARNING LIGHTS ILLUMINATED AND THE SYSTEM PRESSUR	E DROPPED TO ABOUT 1600-1700 PSI AND SEEMED TO STABILIZE AT THAT RANGE. AIRCRAFT WAS DIVERTED TO YXY. THE LANDING GEAR E	XTENDED NORMALLY. A LEAK WAS FOUND IN A HYDRAULIC LINE AND THE HYDRAULIC OIL LEVEL HAD DROPPED. THE HYDRAULIC LINE FROM 	THE HYDRAULIC FILTER IN LT NACELLE WAS FOUND LOOSE, LINE WAS TIGHTENED, FLUID REPLENISHED, HYDRAULIC SYSTEM BLED AND CHE	CKED, NO LEAKS.  AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	3T	4	T	 	A24EU   	A196				 
2003090800213	20030908	00213	NM  	2003	9	8	CA030731017      	1	20030729	G	2730	654476114	PCU             			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ELEVATOR	LEAKING         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) IN CRUISE, FLT CREW REPORTED AN APU FIRE INDICATION. CREW FOLLOWED CHECKLISTS, DISCHARGED APU FIRE BOTTLE, DECLARE	D AN EMERGENCY & REQUESTED CLEARANCE DIRECTLY TO YWG. APU FIRE WARNING LIGHT REMAINED ON AND CREW ADVISED OF ABNORMAL LA	NDING CONFIGURATION.  A/C LANDED WITHOUT INCIDENT, CFR CALLED OUT (NO FIRE INDICATION). AIRCRAFT TAXIED TO GATE. MAINTEN	ANCE INSPECTION REVEALED NO FIRE INDICATION. APU & APU FIRE DETECTION SYSTEM MEL'D.  AT NEXT RON, A/C INSPECTED & MAINTE	NANCE FOUND LT ELEVATOR PCU LEAKING HYD FLUID ONTO APU EXHAUST DUCTING. MAINTENANCE REPLACED PCU & GROUND CHECKED SERVIC	EABLE - NO LEAKS.  APU FIRE DETECTION SYSTEM TESTED. NO FAULTS FOUND.  A/C RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003090500001	20030905	00001	CE  	2003	9	5	CA030731018      	1	20030730	G	5497		WIRE            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  					LT NACELLE	CHAFED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKE OFF FROM FORT SMITH THE OIL PRESSURE INDICATION ON THE LT ENGINE DROPPED TO ZERO AND THE OIL PR	ESSURE LIGHT CAME ON.  A PRECAUTIONARY SHUTDOWN WAS CARRIED OUT AND THE A/C RETURNED TO FORT SMITH. ON INVESTIGATION IT 	WAS DISCOVERED THAT A WIRE BUNDLE WAS CHAFING ON THE NACELLE UPPER DOOR NEAR THE OIL PRESSURE TRANSMITTER.  THE WIRES WE	RE CHAFED RIGHT THROUGH TO BARE WIRE AND THEY SHORTED TO THE DOOR.THIS CAUSED THE OIL PRESSURE INDICATION TO DROP OFF, A	S IF THE ENGINE HAD LOST PRESSURE SUDDENLY.		1	L	7	2 	3T	3	T	 	A14CE   	E4EA				 
2003090800214	20030908	00214	EA  	2003	9	8	CA030731019      	2	20030717	G	7230	3031801	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COMPRESSOR	FRACTURED       	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) COMPRESSOR TURBINE BLADE FRACTURED CAUSING COMPLETE ENGINE FAILURE AT APPROX. 40KNOTS FORWARD AIRSPEED, PILOT CARR	IED OUT EMERGENCY LANDING.ENGINE REMOVED FOR EXAMINATION BY PWC.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003090500002	20030905	00002	SW  	2003	9	5	CA030731020      	1	20030729	G	6320	70061L275W210A	HOSE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					GEARBOX OIL	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) TRANSMISSION OIL HOSE SWOLLEN AND BLOWN APPROX.6 INCHES FROM FITTING.PILOT HAD LOW OIL PRESSURE WARNING LIGHTCOME 	ON AND CARRIED OUT PRECAUTIONARY LANDING TO INVESTIGATE. HOSE IS SUBJECT TO TENSION AND TORSION AS TRANSMISSION IS MOUNT	ED WITH LORD RUBBER MOUNTS. INVESTIGATING HOSE TSN AND CAUSE.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003090800215	20030908	00215	NM  	2003	9	8	CA030801001      	1	20030723	G	2612		FIRE DETECTOR   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 2 ENGINE	MALFUNCTIONED   	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) DURING TURN-AROUND A/C UNATTENDED FOR APPROX. 15 MINUTES.  WHEN FLIGHT CREW RETURNED TO COCKPIT,  NR 2 ENGINE FIRE	 WARNING WAS ON. PULLED TEE HANDLE.DID NOT DISCHARGE FIRE BOTTLES.  CYCLED RT CBS F2, J7, K7,  NO HELP.  DURING CALL TO 	MTX CONTROL, WARNING STOPPED. MECHANICS DISPATCHED,  NO EVIDENCE OF ACTUAL FIRE AND SYSTEM TEST NORMAL SO AIRCRAFT FERRI	ED TO BASE FOR PEC APD REPLACEMENT. SB 842603 HAS BEEN ISSUE TO ADDRESS THIS PROBLEM.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003090500021	20030905	00021	NE  	2003	9	5	CA030803001      	2	20030802	G	8500		ENGINE          			DOUG  	DC4   	C54GDC      	3021534	WP  	PWA   	R2000 	R2000*      	52023	NE  						MAKING METAL    	W				E	O			ENGINE SHUTDOWN         	OTHER                   			J	M		WARNING INDICATION        	OVER TEMP                 		CR	CRUISE         	1			CA											(CAN) THIS AIRCRAFT WAS ACTIONING A FOREST FIRE AS AN AIR TANKER AND IT WAS NOTICED THAT THE OIL PRESSURE WAS LOWER THAN	 NORMAL AND THE OIL TEMPERATURE WAS STARTING TO CLIMB FROM NORMAL. THE ENGINE WAS SHUT DOWN AND THE PROPELLER FEATHERED,	 THE AIRCRAFT RETURNED TO ITS BASE AND UPON INSPECTION IT WAS FOUND THE ENGINE WAS STIFF WHEN THE PROPELLER WAS MOVED.AL	THOUGH VERY LITTLE METAL WAS FOUND IN THE OIL SCREEN IT WAS CONSIDERED AN INTERNAL FAILURE OF UNKNOWN CAUSES AND THE ENG	INE WAS REMOVED AND REPLACED. THE ENGINE WILL BE SENT TO THE OVERHAUL FACILITY TO DETERMINE ITS NATURE.		2	L	7	4 	4R	4	R	 	A762    	5E5				 
2003090500023	20030905	00023	CE  	2003	9	5	CA030804001      	1	20030804	G	2150	11791W5635	HOSE            			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					RT ENGINE FREON	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION FOUND FREON DISCHARGE HOSE ON RT ENGINE WITH BUBBLES IN EXTERIOR RUBBER SLEEVING. NEW HOSE INSTA	LLED, AND SYSTEM SERVICED.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003090800216	20030908	00216	NM  	2003	9	8	CA030805001      	1	20030802	G	3340		LANDING LIGHT   			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					LT PYLON	FIRE            	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) DURING TROUBLESHOOTING OF AN OUTBOARD (LT HAND) LANDING LIGHT SNAG MAINTENANCENOTICED SMOKE ODOR IN THE COCKPIT AN	D THEN SEVERAL C/BS POPPED. MAINTENANCE SHUT ALL AIRCRAFT POWER DOWN. SMOKE WAS NOTICED BY MAINTENANCE COMING FROM THE L	T PYLON AREA FWD.  PYLON PANEL WAS REMOVED AND BURNED WIRING WAS DISCOVERED IN MAIN WIRE BUNDLE.  AIRCRAFT IS BEING REPA	IRED AND A FULL INVESTIGATION IS UNDERWAY.  FURTHER INFORMATION WILL FOLLOW AS IT BECOMES AVAILABLE.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003090500028	20030905	00028	SO  	2003	9	5	CA030805002      	2	20030722	G	7310		LINE            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FUEL SYS	PLUGGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT IS EQUIPPED WITH AN AFTERMARKET 6 CYLINDER EXHAUST GAS TEMPERATURE ENGINE MONITOR. DURING BREAK-IN PERIOD	 FOR FACTORY REMANUFACTURED ENGINE, NR 4 CYLINDER EGT RAN 200 DEGREES F HIGHER THAN THE OTHER FIVE CYLINDERS. TROUBLESHO	OTING EVENTUALLY FOUND A PLUGGED INJECTOR LINE TO NR 4 CYLINDER. PLUG WAS AN UNKNOWN WHITE POWDERY MATERIAL. PLUG WAS RE	MOVED, LINE CALIBRATED, ENGINE RETURNED TO SERVICE. NR 4 CYLINDER EGT NORMAL. CESSNA ENGINE GAUGES READ NORMAL BEFORE AN	D AFTER PROBLEM AND DID NOT INDICATE A PLUGGED FUEL LINE.		1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2003090800217	20030908	00217	NM  	2003	9	8	CA030805003      	1	20030722	G	5320		SUPPORT         			BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					NLG WW	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING 'C' CHECK INSPECTION, NOSE WHEEL WELL SUPPORT FOUND CRACKED BS 294 RBL 12. REPAIR CARRIED OUT AS PER SRM.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003090500047	20030905	00047	NM  	2003	9	5	CA030805004      	1	20030702	G	7603	BACC13AA3TSS6506	CONTROL CABLE   			BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					THRUST	FRAYED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						54767					(CAN) DURING INSPECTION OF THE STATION 870 AREA AT 'C' CHECK, IT WAS FOUND THAT THE NR 3 ENGINE THRUST CABLE WAS FRAYED 	TO THE POINT OF ONE (1) STRAND REMAINING. THE CAUSE WAS IMPROPER ROUTING OF THE CABLE. THE CABLE WAS NOT ON THE PULLEY A	ND WAS CHAFING ON THE PULLEY BRACKET. THE PULLEY/CABLE SECURING PIN WAS IN PLACE. THIS AREA WAS LAST ACCESSED DURING THE	 PREVIOUS 'C' CHECK.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003090500050	20030905	00050	SO  	2003	9	5	CA030805005      	1	20030725	G	3297		WIRE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					NLG	BROKEN          	W				E	L			ENGINE SHUTDOWN         	ABORTED APPROACH        			O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH THE NOSE GEAR INDICATION LIGHT WAS NOT ILLUMINATED. AFTER A FEW RETRACTIONS OF THE LANDING GEAR, THE P	ILOT PERFORMED A LOW APPROACH TO OVERSHOOT TO CONFIRM VISUALLY THAT THE GEAR WAS DOWN. A PRECAUTIONARY ENGINE OFF LANDIN	G WAS CARRIED OUT. FURTHER INSPECTION REVEALED THAT A WIRE LEADING TO THE NOSE LANDING GEAR SWITCH WAS BROKEN. THE WIRE 	WAS REPAIRED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2003090800218	20030908	00218	EU  	2003	9	8	CA030805006      	1	20030803	G	3251	C20216338203	CONTROL UNIT    			AIRBUS	320   	A320231     	3930325	EU  	IAE   	V2500 	V2500A1     	 	NE  					NLG STEERING	FAILED          	W				O				OTHER                   				Z	F		SIGNIFICANT FAILURE REPORT	FLT CONT AFFECTED         		LD	LANDING        	1			CA											(CAN) ON APPROACH, AC APPROACH STATUS REVERTED TO CAT III SINGLE WITH WHEEL PAGE SHOWING AMBER STEERING. N/W STEERING SW	ITCH CYCLED OFF THEN ON WITH INDICATIONS RETURNING TO NORMAL AND CAT III DUAL.  UPON LANDING, IDLE REVERSE WAS SELECTED(	NOISE ABATEMENT) BUT WHEN LOSS OF BRAKING WAS IDENTIFIED, MAX REVERSE WAS SELECTED AND NLG STEERING SELECTED OFF/ON BUT 	NORMAL BRAKING WAS NOT RESTORED. NWS SELECTED OFF AND ACCUMULATOR PRESSURE WAS USED TO BRING AC TO A STOP. THREE MLG TIR	ES BURST AND THE LAST ONE WAS BADLY SCUFFED. FAULT WAS IDENTIFIED AS A DUAL FAILURE OF THE BRAKING/STEERING CONTROL UNIT	 (BSCU) WHICH IS CURRENTLY BEING SENT FOR EXPERTISE. CVR AND FDR ARE BEING SENT FOR ANALYSIS.	2	L	7	2 	4F	4	F	RT	A28NM   	E311NE				 
2003090800219	20030908	00219	WP  	2003	9	8	CA030805007      	1	20030726	G	4990	GTC8598DHF	APU             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					APU BAY	FAILED          	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) APU HAD TO BE SHUTDOWN DUE TO HIGH OIL TEMPERATURE. EMERGENCY DECLARED AS ONE CSD WAS PREVIOUSLY DISCONNECTED AND 	ON MEL, APU WAS GROUND RUN, OIL LEVEL CHECKED, EVERYTHING WAS BACK TO NORMAL. AIRCRAFT RETURNED TO SERVICE. NO PROBLEM F	OR THE REST OF THE FLIGHT.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2003090400023	20030904	00023	CE  	2003	9	4	CA030805008      	1	20030513	G	3397		WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ZONE 281	CHAFED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA			16604								(CAN) TAIL FLOOD LIGHTS UNSERVICEABLE.TAIL FLOOD LIGHT LAMPS CHECKED. NO FAULT FOUND, VOLTAGE CHECKED & NONE PRESENT. LO	CATED CIRCUIT BREAKER & IT WAS FOUND TRIPPED. RESET C/B & TRIPPED RIGHT AWAY. FAULT NOW KNOWN TO BE A DEAD SHORT. SUSPEC	TING WIRING IN EMPENNAGE SECTION OF A/C. LOCATED PLUG P393 (AFT PRESSURE BULKHEAD CONNECTOR) AND FOUND THAT WIRING HAS B	EEN CHAFED BY ACTUAL BACKUP LINER. WIRING REPLACED & WIRING ENCLOSED IN SPIRAL WRAP. TAIL FLOOD LIGHTS CHECKING SERVICEA	BLE. PLUG P393 ALSO INCLUDES OTHER LIGHTING SYSTEMS & ELECTRIC ELEVATOR TRIM RELAY. NO OTHER WIRING OTHER THAN FLOOD LIG	HT WIRING AFFECTED AT THIS TIME.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003090800220	20030908	00220	NM  	2003	9	8	CA030805009      	1	20030804	G	3244	H31X97513	TIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) MULTIPLE FAILURES OF THE NR 1 & 3 MAIN WHEEL TIRES, 6 INCH LONG RUPTURES FOUND ON SIDEWALLS OF TIRES DURING A LINE	 CHECK.  TIRES STILL HELD AIR BUT INNER CORDS WERE FULLY EXPOSED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800221	20030908	00221	NM  	2003	9	8	CA030805010      	1	20030804	G	3244		TIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	RUPTURED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LARGE RUPTURE ON SIDEWALL OF TIRE FOUND AFTER LANDING OF AIRCRAFT ON THE NR 1 POSTION RECAPPED TIRE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090400034	20030904	00034	EU  	2003	9	4	CA030805011      	1	20030803	G	2497	350A62252020	WIRE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					BATTERY	DAMAGED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) JUST AFTER TAKE OFF THE PILOT & PASSENGERS NOTICED SMOKE COMING IN THE CABIN OF AIRCRAFT. PILOT OPENED DOOR TO VEN	T SMOKE OUT OF CABIN. PILOT LANDED AS SOON AS PRATICAL. AFTER LANDING INSTRUCTED PASSENGERS TO EXIT A/C, SHUT DOWN THE E	NGINE , CLOSED THE FUEL VALVE AND ELECTRICS OFF. THE PILOT GRABBED THE FIRE EXTINGUISHER AND OPENUP THE THE RT BAGGAGE C	OMPARTMENT WHERE THE FIRE WAS LOCATED. THE PILOT PULLED EVERYTHING THAT WAS ON FIRE OUTOUT OF THE BAGGAGE COMPARTMENT AN	D EXTINGUISHED THE ON FIRE ITEMS. THE FUSE HOLDER FOR THE EMERGENCY ELECTRICAL POWER CUT OFF SWITCH HAD A SHORT AGAINST 	THE BATTERY BULKHEAD.  THIS CREATED SPARKS WHICH IGNITED PAPER AND GEAR STORED IN THE BAGGAGE COMPARTMENT.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003090400035	20030904	00035	SO  	2003	9	4	CA030806001      	1	20030717	G	5712	5037707	RIB             			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					RT WING	CRACKED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) UPON GEAR RETRACTION, AFTER TAKE OFF, THE LANDING GEAR WOULD NOT LOCK UP IN THE GEAR WELL. UPON INSPECTION, THE RI	GHT MAIN GEAR ACTUATOR ATTACHMENT RIB WAS FOUND TO BE CRACKED BEHIND THE ACTUATOR BRACKET. THIS CRACK CAUSED THE RIGHT M	AIN GEAR TO HANG BELOW THE UP LOCK HOOK; PREVENTING IT TO LOCK IN THE UP POSITION.				1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2003090400039	20030904	00039	EA  	2003	9	4	CA030806002      	1	20030717	G	2910		LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYS SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ON ARRIVAL FOUND NR 1 HYD SYSTEM QTY AT 0 PERCENT. LARGE HYD LEAK NOTICED IN AFT SERVICE COMPARTMENT. FOUND LINE L	EAKING IN AFT COMPARTMENT. NEW LINE FABRICATED AND INSTALLED.SYSTEM FLUSHED. NR 1 EDP REPLACED DUE DISENTIGRATION. ALL F	OUR HYD FILTERS REPLACED. SYSTEM SERVICED AND CHECKED SERVICABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003090800222	20030908	00222	EU  	2003	9	8	CA030806003      	1	20030720	G	2720		RUDDER          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					TAIL	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING FLIGHT CONTROL CHECK AT GATE FOUND RUDDER TRAVEL STOPS SHORT OF FULL DEFLECTION TO THE LEFT.  ADJUSTED RUDD	ER MECHANICAL CONTROL IAW AMM. TESTED ARTIFICIAL FEEL AND RTL.  IAW AMM AND ALL CHECKED SERVICABLE.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003090800223	20030908	00223	NM  	2003	9	8	CA030806004      	1	20030725	G	2751	2061141	INDICATOR       			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TE FLAP	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) FLAPS WILL NOT COME UP, AIRCRAFT RETURNED TO WHITEHORSE. FLAP INDICATOR REPLACED IAW MM 27-58-41 PAGE 401. TEST CA	RRIED OUT, OPERATION CHECKED FOUND NORMAL. AIRCRAFT ENROUTE ON SCHEDULED FLIGHT.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003090800224	20030908	00224	SW  	2003	9	8	CA030806005      	1	20030729	G	2435	150SG1028	STARTER GEN     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	WORN            	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											(CAN) STARTER GEN FAILED IN FLT.  PILOT OBSERVED A GENERATOR FAIL LIGHT ON, & LANDED SAFELY. UNIT REMOVED & SENT TO AMO 	FOR INSPECTION. FOUND THE DRIVE END BEARING LINER LOOSE IN ITS CAST ENDBELL.  LOOSENESS PERMITTED  ARMATURE TO CONTACT  	STATOR, CAUSING METAL TO HEAT FROM FRICTION & COME APART, SEIZING THE GENERATOR & SHEARING THE QUILL SECTION OF THE DRIV	E SHAFT.  DRIVE END BEARING LINER IS A STEEL PART CAST INTO THE ENDBELL. IT CAME LOOSE & BEGAN TO TURN WITH THE BEARING 	& ARMATURE. THE OUTER SURFACE OF THE STEEL LINER, WHICH IS KNURLED BEFORE BEING CAST INTO THE ALUMINUM END BELL, CHEWED 	THE ENDBELL UNTIL CLEARANCE BETWEEN THE ARMATURE & THE STATOR POLES WAS ZERO.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003090800225	20030908	00225	EA  	2003	9	8	CA030806006      	1	20030806	G	3246	C2UF1761	BLOCK           	BRSTOL      		DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R98539      	52008	NE  	HAMSTD	2D	2D30        	NE  	RT FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BA2329					(CAN) FOUND BEARING BLOCK ASSY. (AFT END OF HYD. CYL.) IN RT FLOAT FOR NOSE WHEEL HAD CRACKED THROUGH CENTER ALLOWING JA	CK PICK UP BEARING TO MOVE OUT OF BLOCK ASSY AND FORCE CHANNEL ASSY OUT OF POSITION.  BLOCK ASSY APPEARED TO HAVE BEEN F	RACTURED FOR SOME TIME BEFORE COMPLETE FAILURE. FRACTURE OR CRACKS ARE NOT DETECTABLE WHEN HYD. CYL. AND BEARING BLOCK A	RE ASSEMBLED IN FLOAT.			1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2003090400048	20030904	00048	EA  	2003	9	4	CA030806007      	2	20030716	G	8520	AEL18840	LIFTER          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) METAL FOUND IN FILTER DURING INSPECTION AFTER 62.3 HOURS SINCE OVERHAUL. ENGINE DISMANTLED CAMSHAFT AND LIFTERS FA	ILED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003090800226	20030908	00226	NM  	2003	9	8	CA030806008      	1	20030712	G	2710	550030011	ACTUATOR        			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					RT AILERON	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) EICAS MSG, AILERON LOCKOUT. OCURRED AT 10,000 FT AT 250 KTS (APPROACH). RT OUTBOARD AILERON LOCKOUT ACTUATOR REPLA	CED AS PER MM CHECKS SERVICABLE					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2003090800227	20030908	00227	GL  	2003	9	8	CA030806009      	3	20030805	G	6111		BLADE           	AAR         												HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER HUB	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PROP (OVERHAULED IN NOV/2000) WAS PURCHASED AND INSTALLED ON PA31 AIRCRAFT. AT 51.6 HOURS SINCE OVERHAUL, 2 OF 3 P	ROP BLADES WERE NOTICED TO BE VERY LOOSE WHEN MANIPULATED FORE AND AFT AT THE PROP TIP.ONE BLADE IN PARTICULAR MOVED SIG	NIFICANTLY. DISCUSSIONS WITH OUR USUAL PROPELLOR OVERHAUL SHOP (NOT WHERE WE BOUGHT THE PROP) CONFIRMED THAT WE SHOULD R	EMOVE THE PROP AND SEND FOR REPAIR. THEY SURMISED THAT THE PROP NEEDED ADJUSTMENT (TIGHTENING). PROP WAS REMOVED AND SEN	T FOR REPAIR TO OUR USUAL PROP OVERHAUL FACILITY. (NOT FOR WARRANTY TO COMPANY THAT PROPWAS PURCHASED FROM). TEARDOWN RE	PORT AND FINDINGS TO BE ENTERED WHEN COMPLETED.											5	C	P33EA	 
2003090800228	20030908	00228	EU  	2003	9	8	CA030807001      	1	20030719	G	2913	2244404523	B-NUT           			AIRBUS	310   	A310        	       	EU  										CASE DRAIN LINE	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) DURING FLT, THE AIRCRAFT LOST THE B-HYDRAULIC FLUID SYSTEM.  DURING INVESTIGATION THE B-NUT WAS FOUND CRACKED ON T	HE NR 1 ENGINE DRIVEN PUMP CASE DRAIN LINE. THE LINE ASSEMBLY WAS REPLACED,  THE HYDRAULIC PUMP WAS REPLACED AS PRECAUTI	ONARY MEASURE AND THE GREEN HYDRAULIC SYSTEM FLUSHED.				2	L	7	2 	4F			RT	A35EU   					 
2003090400109	20030904	00109	EA  	2003	9	4	CA030807002      	1	20030805	G	2612	47259701	CONTROLLER      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FIRE DETECTION	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN)  A/C HAD MULTIPLE WARNINGS ON APPROACH. APU FIRE INDICATOR. (APU RUNNING DUE ONE ENG GEN ON MEL) APU AUTO SHUTDOWN	. RT & LT JET OVERHEAT MSG, LT & RT FIRE FAIL CAUTION MSG. LT WINDSHIELD HEAT IN FLT. CHGED FIRE DET CONTROLLER ALL CKS 	SERV.  CONTROLLER INSPECTED ON SITE BY MPS TECH AND NO MOISTURE, COFFEE OR CONTAMINATION FOUND. AD CF200035R1 HAD BEEN C	OMPLIED WITH. PART WILL BE FURTHER TESTED UPON ARRIVAL IN SHOP.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003090400111	20030904	00111	EA  	2003	9	4	CA030807003      	1	20030730	G	5410	22850080801	COWLING         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LT UPPER	DAMAGED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) CREW WAS NOTIFIED BY TOWER THAT THE LT UPPER ENGINE COWLING HAD COME OFF THE AIRCRAFT, AND WAS LAYING ON THE RUNWA	Y. A/C RETURNED AND LANDED THEY FOUND THE FASTENER STILL LOCKED ON THEIR DZEUS RECEPATCLE .THEY REPLACED THE DAMAGED DZE	US RECEPTACLE AND REPLACE UPPER AND LOWER COWL.NO ADDITIONAL DAMAGES ON THE STRUCTURE AND THE NACELLE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003090400112	20030904	00112	EU  	2003	9	4	CA030807004      	1	20030806	G	3233	960300110	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, WHEN THE LANDING GEAR WAS RETRACTED, THE GREEN DOWN AND LOCKED INDICATION REMAINED ON FOR THE L/H G	EAR. THE GEAR WAS CYCLED, BUT THE GEEN INDICATOR REMAINED ON. THE AIRCRAFT RETURNED TO BASE, WHERE IT WAS DETERMINED THA	T THE INTERNAL DOWN INDICATOR MICRO SWITCH WAS STAYING ON WHEN THE RAM WAS RETRACTED ON THE MLG ACTUATOR. THE ACTUATOR W	AS REPLACED, HYDRAULIC SYSTEM SERVICED, GEAR RETRACTION PREFORMED, AND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090800229	20030908	00229	EU  	2003	9	8	CA030807005      	1	20030728	G	2910	F50B765252	LINE            			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					HYD RETURN SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) SMALL LEAK WAS FOUND AFTER GROUND RUNNING AIRCRAFT HYDRAULIC SYSTEM. LEAK WAS SEEN DRIPPING ON RT INBOARD TIRE. LE	AKAGE WAS MINIMAL. UPON INVESTIGATION A TINY PIN HOLE WAS DISCOVERED AT A FAIR LEAD JUNCTION 16 INCHES OUTBOARD OF INBOA	RD FITTING - WS78 (RT WING) ON AILERON RETURN LINE NR 2 SYSTEM, PN F50B765252. PIN HOLE IS VERY SMALL AND MAY POSSIBLY C	AUSED BY CORROSION.			2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2003090800230	20030908	00230	EU  	2003	9	8	CA030807006      	1	20030801	G	2150	20388022	COOLING TURBINE 			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					COOLING FAN	FAILED          	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) POSSIBLE FAILURE OF BEARING (DEBRIS ON MAGNETIC PLUG) CAUSING SUBSEQUENT HIGH FREQUENCY VIBRATION RESULTING IN FAI	LURE OF THE FOLLOWING SUB-COMPONENTS: COOLING FAN (VANES BROKEN AND HOUSING PARTIALLY DETACHED.  HEAT EXCHANGER 178092-1	 (CRACKED AT WELDED COOLING TURBINE ATTACHMENT FLANGE).  BLEED AIR DUCT 25-8VF501-1A (SEPERATED ELBOW FITTING AT WELD JO	INT). THE DAMAGE TO THE DUCT RESULTED IN A REAR BAY OVERHEAT COCKPIT INDICATION WHEREBY THE FLIGHT CREW ALSO SHUT DOWNTH	E APU AND ENGINE BLEED VALVES AS THEY COMMENCED AN EMERGENCY DESCENT ONCE CAB IN PRESSURE WAS LOST WITH THE REFRIGERATIO	N UNIT FAILURE.	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2003090800232	20030908	00232	CE  	2003	9	8	CA030807007      	1	20030807	G	5553	07120013	FITTING         			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REMOVAL OF VERTICAL STABILIZER THE REAR DORSAL FIN ATTACH BRACKET WAS FOUND TO BE CRACKED. THE LT RADIUS HAD 	FAILED BELOW THE FASTNER ATTACHMENT.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2003090800233	20030908	00233	CE  	2003	9	8	CA030808001      	1	20030806	G	2435	03601018	BEARING         	LUCAS       		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	STARTER GEN	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						97186					(CAN) AIRCRAFT DEPARTED. DURING THE END OF CLIMB OUT THE RT (NR 2) GENERATOR ANNUNCIATOR ILLUMINATED. GENERATOR WOULD NO	T RESET, AIRCRAFT RETURNED TO AIRPORT. MAINTENANCE CHECKS CARRIED OUT NR 2 ENGINE WOULD NOT TURN ON START, GENERATOR REM	OVED, INSPECTED AND FOUND LARGE AMOUNT OF CIRCULAR MOVEMENT ON DRIVE END DUE TO BEARING FAILURE. GENERATOR REPLACED AND 	AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003090800234	20030908	00234	CE  	2003	9	8	CA030808002      	1	20030717	G	5330		SKIN            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A CRACK IN THE UPPER FUSELAGE SKIN DUE TO VIBRATION PRODUCED BY A GPS/VHF COMBINATION ANTENNA, CRACKS DEVELOPED VE	RY RAPIDLY IN SKIN & DOUBLER ALONG EDGES OF ANTENNA BASE,					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003090800236	20030908	00236	CE  	2003	9	8	CA030808003      	1	20030730	G	2913	PDLM60	CIRCUIT BREAKER 			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE331625   	 	WP  					HYD PUMP	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) THE LANDING GEAR FAILED TO RETRACT ON TAKE-OFF. THE 60 AMP HYD DRIVE MOTOR CIRCUIT BREAKER WAS FOUND TRIPPED. THE 	GEAR WAS LOWERED USING THE EMERGENCY SYSTEM AND THE AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT. THE MOTOR WAS	 BENCH CHECKED AND FOUND TO BE GOOD. THE CIRCUIT BREAKER FOR THE MOTOR WAS REPLACED AND THE SYSTEM TESTED ALL OK.				1	L	7	2 	4T	4	T	 	A14CE   	E2WE				 
2003090800241	20030908	00241	EU  	2003	9	8	CA030811001      	1	20030808	G	6320	4638202007	FREEWHEEL UNIT  			BOLKMS	105   	BO105CBS    	5626008	EU  										MAIN ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS TRANSMISSION RECEIVED FROM AN OPERATOR WITH PARTIAL DISASSEMBLY.  LT FREEWHEEL CLUTCH SHATTERED. OUTER CAGE B	ROKEN IN ONE PLACE.  INNER CAGE BROKEN IN TWO PLACES.ENERGIZING RIBBON BROKEN IN FOUR PLACES.  FOUR SPRAGS DISLODGED FRO	M CLUTCH ASSY.				1	G	7	2 	3U			NC	H3EU    					 
2003090800254	20030908	00254	WP  	2003	9	8	CA030811003      	1	20030804	G	3260		PROXIMITY SENSOR			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NLG	OUT OF RIG      	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) NOSE GEAR UNSAFE LIGHT AND AURAL WARNING ON GEAR UNSAFE AUERAL WARNING PROXIMITYTEST BITE C/OUT IAW MM 32-60-00 CO	ULD NOT DUPLICATE SNAG. RIGGING OF PROXIMITY SENSOR C/O AS PER MAINTENANCE MANUAL - NO DEFECT FOUND.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2003090800259	20030908	00259	NM  	2003	9	8	CA030811004      	1	20030806	G	3246	43667	BOLT            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG WHEEL	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE ASSEMBLING THE MAIN WHEEL, THE WHEEL BOLTS WERE TORQUED IN THE PROPER SEQUENCE AND TO PROPER TORQUE AS PER M	M, THE BOLTS WERE THENCHECKED TO VERIFY THE TORQUE AND THE NUTWOULD TURN ABOUT 1/8 OF A TURN BEFOREREACHING THE TORQUE. 	A SECOND VERIFICATION WAS COMPLETED AND THE NUT WOULD AGAINTURN 1/8 OF A TURN AND ONE OF THEM BROKE. THE TORQUE WRENCH W	AS RECHECKED FOR PROPER CALIBRATION AND FOUND SERVICEABLE. NEW BOLTS WERE ORDERED AND INSTALLED & PROBLEM RECURRED WITH 	TWO OF THE NEW BOLTS, ONE STRETCHED AND ONE BROKE. WHEEL MANUFACTURE WAS CONTACTED TO VERIFY THAT THE TORQUE IN THE MAIN	TENANCE MANUAL WAS CORRECT AND THAT THESE WERE THE CORRECT BOLTS, THEY CONFIRMED THE INFO WAS CORRECT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090800260	20030908	00260	EU  	2003	9	8	CA030811005      	1	20030804	G	2100	9738132212	SWITCH          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ECS	OVERHEATED      	W				O				OTHER                   				H	L		ELECT. POWER LOSS-50 PC   	NO TEST                   		TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF THE BREAKER OF THE ENVIRONMENTAL CONTROL SYSTEM POPPED OUT. AFTER VERIFICATION OF THE PROBLEM, AND 	DISCOVERED THAT THE SWITCH WAS BEING OVERHEATED. BUT FOUND NO TRACES OF BURN MARKS OR OVERHEATED ON THE SWITCH AFTER REM	OVAL AND A NEW SWITCH WAS BEING INSTALLED.SWITCH PN 973.81.32.212 (53183-110)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090800263	20030908	00263	CE  	2003	9	8	CA030812001      	1	20030808	G	2730	50610000546	HINGE BRACKET   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT ELEVATOR BOLT FOUND LOOSE DURING CHECK. HINGE BRACKET & BOLT EXHIBITED ABNORMAL WEAR. BOLT GROOVED .024 TO A DI	AMETER OF .225 & BRACKET HOLES ELONGATED TO .284 & .290, RESULTING IN EXCESSIVE MOVEMENT OF HINGE. INSTALATION OF BOLT I	AW MM WITH ONE AN960416L & ONE AN960416 WASHERS. IT APPEARS THAT WITH THIS INSTALATION, NUT BOTTOMED ON SHOULDER OF BOLT	. C90A MM CONTAINS A CAUTION TO THIS EFFECT (CH 27-30-00 PG 202) INDICATING PREMATURE WEAR MAY OCCUR. ALSO NOTED, BUSHIN	G OVERALL LENGTH .900, BRACKET INTERNAL BORE LENGTH .930. REPLACEMENT OF BOLT, NUT AND WASHERS, BRACKET, BUSHING AND HIN	GE BEARING, VISUAL INSPECTION OF ATTACHMENT BRACKETS, ELEVATOR BALANCING VERIFIED. NO FURTHER FAULTS FOUND.	1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003090800266	20030908	00266	SW  	2003	9	8	CA030812002      	1	20030811	G	3211	206031302269S	SUPPORT         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					CROSSTUBE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			12957								(CAN) DURING SERVICABILITY CHECK CRACKS WERE FOUND ON THE LT AFT CROSS TUBE SUPPORT P/N 206031301123 , THE RT AFT CROSS 	TUBE SUPPORT PN 206031301124 AND ON BULKHEAD PN 206031302193. ALL PARTS WILL BE CHANGED OUT.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003102000170	20031020	00170	SO  	2003	10	20	CA030812003      	2	20030812	G	8530		ROCKER          			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					CYLINDER HEAD	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON VISUAL INSPECTION OF VALVE TRAIN ASSY ON ALL FOUR CYLINDERS.  NOTED EXCESSIVE WEAR TO ROCKER ARM BOSSES, ROCKER	 ARM BUSHINGS & ROCKER SHAFTS. SHAFTS ARE ANCHORED BY SET SCREWS. FIRST INDICATION IS THAT THE LINE UP MARKS ON THE ENDS	 OF THE PINS DO NOT MATCH THE DIRECTION OF THE SET SCREW. SET SCREWS FOUND LOOSE.AT THIS POINT WE DISSMANTLED THE ASSY &	 THEN NOTED THE WEAR ON ALL OF THE OTHER PARTS.THIS IS THE THIRD OCCASION THAT THIS HAS BEEN FOUND ON OUR FLEET. TELEDYN	E CONTINENTAL IS STILL INVESTIGATING CAUSE OF PROBLEM.		1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003090900002	20030909	00002	CE  	2003	9	9	CA030812004      	1	20030731	G	8012	S19911	SOLENOID        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	STARTER	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE PILOT EXPERIENCED AN ELECTRICAL FAILURE.  UPON LANDING BACK AT BASE IT WAS DETERMINED THE STARTE	R SOLENOID WAS STUCK AND SUBSEQUENTLY THE BATTERY NEGATIVE POST MELTED. THE STARTER & MASTER RELAYS, STARTER AND BATTERY	 WERE REPLACED. THE ENTIRE ELECTRICAL SYSTEM WAS INSPECTED AND FOUND TO BE SERVICEABLE. THE ENGINE WAS GROUND RUN AND TH	E CHARGING SYSTEM FOUND TO BE OPERATING NORMALLY.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003090900003	20030909	00003	CE  	2003	9	9	CA030812005      	1	20030807	G	3242	215286	STATOR          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE ASSY	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						0511					(CAN) STATOR BROKEN ON LT BRAKE ASSY. ACCORDING TO THE WEAR INDICATORS, THERE WAS APPROX. 150-200 CYCLES OF BRAKE LIFE R	EMAINING.PROBLEM DESCRIPTION WOULD PROBABLY BE PREMATURE BRAKE FAILURE. THE LT WHEEL ASSY WAS ALSO REPLACED. INSPECTION 	OF THE RT BRAKE ASSY. ALSO SHOWED SIGNS OF STATOR CRACKING.THE RT BRAKE ASSY WAS ALSO REPLACED. SN REMOVED 0733.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003090900004	20030909	00004	EA  	2003	9	9	CA030813002      	2	20030808	G	8530	75089	PISTON          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DEFECTIVE PART FOUND DURING A TOP OVERHAUL AT 1785.8 HOURS (ENGINE TIME).  THIS ENGINE CYLINDERS HAD NEVER BEEN RE	MOVED SINCE LYCOMING OVERHAUL.  PERTINENT INFORMATION:  CRACK IN PROGRESS, 3/4 INCH LONG.  WE CAN OBSERVE POROSITY IN TH	E MATERIAL AT THE CRACK LOCATION.  PART KEPT FOR INVESTIGATION.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003090900005	20030909	00005	NM  	2003	9	9	CA030813003      	1	20030810	G	2750	652661433	TRANSMISSION    			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					TE FLAP	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO I/B T/E FLAPS WOULD NOT EXTEND IN NORMAL OR MANUAL MODE. POST LANDING INSPECTION DETERMINED NR 4 FL	AP TRANSMISSION (I/B, I/B) WAS UNSERVICEABLE. THE UNIT WAS REPLACED THE FLAP SYSTEM RIG CHECKED AND FUNCTION TESTED. AIR	CRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003090900006	20030909	00006	NM  	2003	9	9	CA030813004      	1	20030810	G	2750	652661433	TRANSMISSION    			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					TE FLAP	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO I/B T/E FLAPS WOULD NOT EXTEND IN NORMAL OR MANUAL MODE. POST LANDING INSPECTION DETERMINED NR 4 FL	AP TRANSMISSION (I/B, I/B) WAS UNSERVICEABLE. THE UNIT WAS REPLACED THE FLAP SYSTEM RIG CHECKED AND FUNCTION TESTED. AIR	CRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2003090900007	20030909	00007	CE  	2003	9	9	CA030813005      	1	20030808	G	2910	MS28893C6	RELIEF VALVE    			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					HYD SYSTEM	LEAKING         	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) THE LANDING GEAR HAD A SERIES OF 2 FAILURES WHERE THE 60 AMP BREAKER TRIPPED AS THE MLG WAS RETRACTING & WOULD NOT	 RESET THEREBY FORCING THE CREW TO LOWER THE GEAR WITH THE EMERGENCY SYS & RETURN TO BASE. THE FAILURE COULD NOT BE DUPL	ICATED WHEN THE GEAR WAS SWUNG BY MAINT. THE HYD DRIVE MOTOR WAS BENCH CHECKED OK & BREAKER REPLACED. A THIRD INCIDENT W	HERE BREAKER TRIPPED WHILE THE A/C WAS STILL ON THE RAMP PROMPTED MAINT TO CARRY OUT A FULL 1000 HR SYS INSPECTION DURIN	G WHICH THE THERMAL RELIEF VALVE WAS DISCOVERED TO OPEN AT RANDOM CAUSING THE HYD PUMP TO CYCLE RAPIDLY UNTIL CIRCUIT HE	ATED UP & THE BREAKER TRIPPED. IT WAS REPALCED WITH AN OVERHAULED VALVE AND THE A/C RETURNED TO SERVICE.	1	L	7	2 	4T	4	T	 	A14CE   	E2WE				 
2003112600059	20031126	00059	NE  	2003	11	26	CA03081300A      	2	20030813	G	8520	15373	PISTON          			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	S3H1        	52016	NE  					ENGINE	DAMAGED         	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) AT INSPECTION, A VERY SMALL AMOUNT OF FERROUS MATERIAL FOUND IN PRESSURE FILTER. ADDITIONAL INSPECTION FOUND A PIS	TON WITH BROKEN TOP COMPRESSION RING. INSPECTION OF OTHER PISTONS FOUND THEM TO HAVE BEEN WORN BEYOND LIMITS IN THE TOP 	RING GROOVE WIDTH.  WORN PISTONS WERE REPLACED WITH NEW.				1	L	7	1 	3R	3	R		EXPA1L71	E143				 
2003110600001	20031106	00001	NE  	2003	11	6	CA030813AAA      	2	20030813	G	8530	15373	PISTON          			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	S3H1        	52016	NE  					ENGINE	DAMAGED         	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) AT INSPECTION, A VERY SMALL AMOUNT OF FERROUS MATERIAL FOUND IN PRESSURE FILTER.ADDITIONAL INSPECTION FOUND A PIST	ON WITH BROKEN TOP COMPRESSION RING.INSPECTION OF OTHER PISTONS FOUND THEM TO HAVE BEEN WORN BEYOND LIMITS IN THE TOP RI	NGGROOVE WIDTH.  WORN PISTONS WERE REPLACED WITH NEW.				1	L	7	1 	3R	3	R	 	EXPA1L71	E143				 
2003090900008	20030909	00008		2003	9	9	CA030814001      	4	20030813	G	3418		HEATER          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AOA SENSOR	INTERMITTENT    	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						0068					(CAN) PILOT REPORTED THAT AMBER 'AOA DEICE' LAMP ILLUMINATED INTERMITTENTLLY ON ANNUNCIATOR PANEL. CLOSE INSPECTION OF A	OA DEICE SYSTEM WITH CONTINUITY TESTER INDICATED FLUCTUATION IN METER READINGS WHEN NOSE CONE OF SUSPECTED AOA WAS HEATE	D AND COOLED. AOA TRANSMITTER REPLACED WITH SERVICEABLE SPARE . DEFECT ELIMINATED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003090900009	20030909	00009	SW  	2003	9	9	CA030814002      	1	20030814	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STAINLESS STEEL CABLE, RT FLAP CABLE FRAYED AT PULLEY WHEN FLAPS SELECTED DOWN.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2003090900010	20030909	00010	SW  	2003	9	9	CA030814003      	1	20030814	G	2720	12364	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLES ARE STAINLESS STEEL. LT AND RT CABLES FRAYED AT CABIN PULLEY IN NEUTRAL POSTION.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2003090900011	20030909	00011	SW  	2003	9	9	CA030815001      	1	20030809	G	7120		MOUNT           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE 100 HR INSPECTION, A SMALL RUST LINE WAS DETECTED ON THE UPPER LT MOUNT LOCATION AT THE WELD.  FURTHER 	INSPECTION WITH 10 POWER MAGNIFYING GLASS DETERMINED THAT THE AREA WAS CRACKED 1/2 INCH.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2003090900012	20030909	00012	EU  	2003	9	9	CA030817001      	1	20030808	G	2710	RZ1241	SPRING          			GROB  	G115  	G115C       	1660303	EU  	LYC   	O320  	O320D1A     	41508	EA  					AILERONS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE TOWING THE AIRCRAFT TO ITS PARKING SPOT, A BANG WAS HEARD.  THE AILERONS DEFLECTED FULL SCALE LT. THE AILERO	N AND RUDDER WERE NO LONGER INTERCONNECTED. ONE OF THE SPRINGS WAS FOUND TO HAVE BROKEN OFF AT THE ATTACHMENT POINT.  WH	ILE REPLACING THE SPRING THE OTHER SPRING WAS FOUND TO BE SUBSTANTIALLY WEAKER THAN THE NEW SPRING.  BOTH SPRINGS WERE R	EPLACED IN ACCORDANCE WITH THE MANUFACTURER'S DIRECTIVES.			1	L	7	1 	3O	3	O	NT	A57EU   	E274				 
2003090900013	20030909	00013	SO  	2003	9	9	CA030818001      	2	20030815	G	8530	AEC648029	PISTON          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON DOING A CYLINDER INSPECTION IT WAS NOTICED THAT THE COMPRESSION ON THE NR 4 CYLINDER WAS LOW. REMOVAL OF THE 	CYLINDER REVEALED A PISTON SKIRT LAYING IN OIL SUMP WHICH HAD COME FROM THE NR 5 CYLINDER. THESE PISTON SKIRTS BREAKING 	OFF HAVE CREATED 2 INFLT ENGINE FAILURES WITHIN THE LAST YEAR AND A HALF FOR PERIMETER. THE PROBLEM WAS IDENTIFIED AS PO	OR HEAT TREATMENT BY  THE MANUFACTURER 'ECI'. NO AIRWORTHINESS DIRECTIVE HAS BEEN ISSUED FOR THIS PROBLEM AS OF YET. ALL	 THE PISTONS INVOLVED HAD A CASTING NUMBER OF '04' STAMPED ON THE INSIDE OF THE PISTON. 3 ECI CYLINDER ASSEMBLIES WERE R	EPLACED ON THIS ENGINE TO AVOID ANY FUTURE FAILURES.	1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2003090900014	20030909	00014	SW  	2003	9	9	CA030818002      	1	20030818	G	2497	GS550	STUD            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GROUND	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN AREA INSPECT, MECHANIC NOTICED THAT GROUND STUD & WIRE FOR GROUND POWER RECEPTICLE APPEARED BURNED. ON I	NVEST FOUND CONNECTION LOOSE & FUSELAGE LUG, GROUND STUD & WIRE TERMINAL BURNED & OVERHEATED. ACCORDING TO PARTS LIST IN	 WIRING MANUAL GROUND STUD INCORRECTLY ASSEMBLED. STUD WAS LAST ASSEMBLED WHEN A/C WAS BUILT. STUD BOLT SHOULD BE AN AN6	-10 BUT WAS A-5 & WAS MISSING SOME WASHERS THAT ARE CALLED OUT IN PARTS LIST & WIRING MANUAL.			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2003090900015	20030909	00015	NE  	2003	9	9	CA030818003      	2	20030814	G	7532		BLEED VALVE     			CESSNA	500   	550         	2076604	CE  	PWA   	530   	PW530A      	 	NE  					COMPRESSOR	MALFUNCTIONED   	W				O				OTHER                   				W	R	J	INADEQUATE Q C            	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	AP	APPROACH       	1			CA											(CAN) RT ENGINE SURGES UPON DECELERATING THRU 70 PERCENT, SECONDARY ORIFICE ON BLEED OFF VALVE TORQUE MOTOR INSPECTED AN	D CLEANED. P3 AIR SEPERATOR INSPECTED AND CLEANED ASPER PRATT AND WHITNEY. BLEED OFF VALVES SWAPPED (RT TO LT). ENGINE G	ROUND RAN , NO FAULT COULD BE DUPLICATED.				1	L	7	2 	4F	4	F	 	A22CE   	E00053EN				 
2003090900016	20030909	00016	GL  	2003	9	9	CA030818004      	3	20030816	G	6110	57A24041	PITCH STOP      			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	PROP CYLINDER	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF THE PROP, MAINTENANCE ATTEMPTED TO REMOVE THE SPINNER BUT COULDN'T BECAUSE THE LOW PITCH STOP	 THREADS WERE STRIPPED, WHERE THE SPINNER ATTACHES TO THE LOW PITCH STOP. THE LOW PITCH STOP HAD TO BE REMOVED FROM THE 	P ROPELLER SO THE SPINNER COULD BE REMOVED. IT WAS ALSO NOTED THAT THE HOLE IN THEFRONT OF THE SPINNER FOR THE LOW PITCH	 STOP WAS ENLARGED ALLOWING THE SPINNER T O WOBBLE SLIGHTLY DURING OPERATION CAUSING THE SPINNER AND SPINNER BULKHEAD TO	 CRACK. THE PROPELLER, LOW PITCH STOP AND SPINNER AND BULKHEAD ASSEMBLY WERE REPLACED.		1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P920	 
2003090900017	20030909	00017	NE  	2003	9	9	CA030818005      	2	20030818	G	8530		EXHAUST VALVE   			DOUG  	B26   	B26C        	3200524	WP  	PWA   	R2800 	R280079     	52026	NE  					NR 3 CYLINDER	FAILED          	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO WHITE SMOKE WAS OBSERVED EXITING THE LT INBOARD EXHAUST STACK. THE ENGINE WAS SHUT DOWN AND SECURED	, THE A/C LANDED WITHOUT INCIDENT. UPON INVESTIGATION THE NR 3 CYL. EXHAUST VALVE STEM HAD SEVERED AND WAS INGESTED INTO	 THE CYL. OIL SCREENS WERE CHECKED AND CYL. CHANGED A/C RETURNED TO SERVICE.				2	M	7	2 	4R	4	R	 	L34     	5E8				 
2003090900018	20030909	00018		2003	9	9	CA030819001      	4	20030813	G	2210	30513126	SERVO           			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					YAW	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE-OFF ROLL, OUT OF EXETER AND A COUPLE OF TIMES IN FLT, CREW REPORTED RUDDER KICKED, FOLLOWED BY A BANK 	OF 10 DEGREES. THE YAW AUTOPILOT ACTUATOR WAS REPLACED AND THE SYSTEM WAS CONFIRMED SERVICEABLE AFTER A VERIFICATION FLT	.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2003090900019	20030909	00019	EA  	2003	9	9	CA030819002      	2	20030814	G	7230	T102401	BLADE           								PWA   	PT6   	PT6A27      	52043	EA  					GAS GENERATOR	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ENGINE WAS SHUTDOWN IN CRUISE DUE TO TORQUE INDICATION DROPPING OFF AND ITT CLIMBING TO 6900C.  DISMANTLE INVESTIG	ATION HAS REVEALED THAT CT DISK ASSEMBLY EXHIBITED ONE FRACTURED CT BLADE AT THE ROOT OF THE AIRFOIL OR BLADE PLATFORM. 	THE FRACTURED AIRFOIL WAS LODGED BETWEEN THE CT SHROUD SEGMENTS AND CT BLADE TIPS. SEVERE RUBBING OF CT BLADE TIPS WAS E	VIDENT. COMPRESSOR ALSO SUFFERED HEAVY RUBBING DAMAGE. ROOT CAUSE IS STILL BEING ANALYSED.								4	T			E4EA				 
2003090900020	20030909	00020	NM  	2003	9	9	CA030819003      	1	20030810	G	2913		PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYD SYSTEM	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT NR 2 ENG HYD PUMP  CAUTION ON. FLIGHT CONTINUED TO DESTINATION AND LANDING WAS UNEVENTFUL. METAL FOU	ND IN CASE DRAIN FILTER. EDP REPLACED AND LINES FLUSHED. ALL NR 2 HYD FILTER ELEMENTS REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003090900030	20030909	00030	EU  	2003	9	9	CA030820001      	1	20030816	G	3246		WHEEL           			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					MLG SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) AFTER TAKE OFF UNABLE TO CLOSE GEAR DOOR TO CLOSE AIRCRAFT RETURN TO GATE,  FOUND BOTH CENTER GEAR WHEEL AT RIM,  	CENTER GEAR DOORS DAMAGED					2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2003090900031	20030909	00031	NM  	2003	9	9	CA030820002      	1	20030818	G	2121		FAN             			BOEING	747   	747433      	       	NM  	PWA   	4056  	PW4056      	 	NE  					CABIN	SMOKE           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) SMOKE IN CABIN, AIRCRAFT DIVERTED INTO ICELAND SUSPECT RE-CIRCULATING FAN INVESTIGATION UNDER WAY						2	L	7	4 	4F	4	F	RT	A20WE   	E24NE				 
2003090900032	20030909	00032	NM  	2003	9	9	CA030820003      	1	20030817	G	2761	65449617	ACTUATOR        	BOEING      		BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					DRAG CONTROL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						1531					(CAN) UPON ROUTINE PRE-FLIGHT WALK AROUND INSPECTION, ENGINEER DISCOVERED TRACES OF FLUID UNDER THE RT WING O/B FLAP TRA	CK FAIRINGS.  FLAPS WERE BROUGHT DOWN AND SPEED PANELS RAISED. ENGINEER DISCOVERED NR 8 GRD SPOILER ACTUATOR COVERED IN 	HYD FLUID. AFTER PRESSURIZING THE HYD SYS, THE SPOILER PANELS WERE CYCLED A FEW TIMES. A SMALL LEAK WAS LOCATED IN THE M	IDDLE OF THE ACTUATOR CYL, BUT ONLY LEAKED ON THE WAY FROM EXTEND TO RETRACT POSITION.  THE SPOILERS WERE KEPT CYCLING T	O TRY TO LOCATE THE EXACT POSITION OF THE LEAK, AFTER ABOUT 6 CYCLES, THE CYL SUDDENLY CRACKED WITH A LOUD BANG FROM THE	 TOP TO THE BOTTOM OF THE CYL RELEASING APPROX 1 GAL OF FLUID IN ABOUT 15 SECONDS. A NEW ACTUATOR WAS ORDERED.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003090900041	20030909	00041	NM  	2003	9	9	CA030825001      	1	20030720	G	2612	10109601	FIRE LOOP       			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 1 ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) AIRCRAFT OPERATING DEMO FLIGHTS FOR CUSTOMER UNDER CANADIAN REGISTRATION WITH BOMBARDIER CREW. AFTER LAST DEMO FLI	GHT DURING PASSENGER DEPLANING THE NR 1 FIRE WARNING ACTIVATED. CREW FIRED ONE BOTTLE (AFT) AND THE FIRE WARNING STOPPED	 NO EVACUATION NECESSARY. ENGINE WAS ALREADY SHUTDOWN. WARNING WAS DETERMINED TO BE A NUISANCE AS PER Q400 ISAR 2003-05 	ITEM 3  'NUISANCE PEC FIRE LOOP INDICATION' 40 HRS TSN ON LOOP.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003090900044	20030909	00044	SW  	2003	9	9	CA030825002      	1	20030815	G	2720		PEDAL           	BLANCA      		BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TOE BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AME WAS DOING A QUICK VISUAL OF THE COCKPIT AREA BEFORE THE AIRCRAFT WAS TO LEAVE FOR THE DAYS FLIGHT, WHEN HE NOT	ICED A CRACKED ON THE FACE OF THE PEDAL. ON FURTHER INPECTION OF THE PEDAL IT WAS DISCOVERED THAT THE CRACK CONTINUED AR	OUND THE BACK ON INTO ONE OF THE MAIN ATTACH POINTS.				1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2003090900047	20030909	00047	NM  	2003	9	9	CA030825003      	1	20030821	G	3220	89607	BOSS            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG CENTER MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REINSTALLATION OF THE NOSE LANDING GEAR CENTERING MECHANISM A CRACK WAS NOTICED IN THE MAIN BODY BEHIND THE	 MOUNTING BOSS OF THE CENTRING MECHANISM, THE CRACK AS 3/4 INCH IN LENGTH. THE LOCATION OF THE CRACK DOES NOT ALLOW IT T	O BE VISIBLE WITH OUT REMOVING THE CENTERING MECHANISM.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003090900049	20030909	00049	EA  	2003	9	9	CA030825005      	2	20030719	G	7322	233615	FLOAT VALVE     	PRECISION   		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	CARBURETOR	FAILED          	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) FLOAT VALVE AND SEAT ASSEMBLY FOUND TO BE STICKING IN THE OPEN POSITION CAUSING A HIGH FUEL LEVEL IN THE FLOAT CHA	MBER. THEREFORE GIVING A RICH MIXTURE IN THE IDLE RANGE CAUSING ENGINE TO STALL IN IDLE RANGE AND ROLL-OUT ON RUNWAY. TO	 CORRECT THIS CONDITION, FLOAT VALVE POLISHED ND REASSEMBLED AND HAS BEEN RUNNING GOOD EVER SINCE.				1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003090900051	20030909	00051	SW  	2003	9	9	CA030825006      	1	20030721	G	2551		SPRAY BOOM      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					EXTERIOR	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) THE RT SPRAY BOOM FAILED AND FLEW UP INTO THE MAIN ROTOR BLADES. THE PILOT KEPT CONTROL OF THE AIRCRAFT AND LANDED	 SAFELY AT THE AIRPORT. UPON INVESTIGATION WE DETERMINED THAT THE TWO MAJOR FACTORS CAUSING THE INCIDENT WERE: THE BOOM 	HAD A WELDED JOINT HALF WAY OUT ON THE RT SIDE (BROKE AT THE WELD). THE BOOM HAD AN AIRFOIL SHAPE CAUSING IT TO FLY UP I	NTO MAIN ROTOR BLADES.  WE CONFIRMED THAT NONE OF OUR AIRCRAFT HAVE THE AIRFOIL SHAPE BOOMS (THIS AC WAS THE ONLY ONE). 	 WE REPLACED XX'S BOOMS WITH SIMPLEX ROUND SHAPED BOOMS. WE ALSO CONFIRMED THAT OUR AIRCRAFT DO NOT HAVE ANY WELDED JOIN	TS ON THE BOOMS.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003090900053	20030909	00053	CE  	2003	9	9	CA030825007      	1	20030818	G	2797		WIRE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CONTROL WHEEL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING REASSEMBLY CONTROL WHEEL, A TECHNICIAN DISCOVERED TWO BARE WIRES HIDDEN INSIDE THE CONTROL WHEEL ASSY. THE 	BARE WIRES COULD BE PARTIALLY SEEN FROM A SMALL OPENING IN THE FRONT SIDE OF THE CONTROL WHEEL PAD. AFTER DISMOUNTING TH	E CONTROL WHEEL ASSEMBLY AND REMOVING ITS ASSOCIATED PARTS (WHEEL FRONT AND AFT COVER, BEARING AND SHAFT), IT BECAME POS	SIBLE TO PERFORM A CLOSER INSPECTION OF THE WIRES. THE WIRES ARE BUNDLED UP AND ROUTED INSIDE A SMALL SHAFT USED FOR HOL	DING THE CONTROL WHEEL TOGETHER. TWO SCREWS ATTACHED THE SHAFT TO THE CONTROL WHEEL. FURTHER INVESTIGATION OF THE ASSEMB	LY REVEALED THAT THE WIRES WERE FORCIBLY DAMAGED BY THE TWO SCREWS DURING PERIODIC MAINTENANCE.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003112600071	20031126	00071	SW  	2003	11	26	CA030825008      	1	20030726	G	5302	212030161001	ATTACH FITTING  			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAILBOOM	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA			13319								(CAN) DURING CRUISE FLIGHT THE CREW FELT A (POP) ON THE AIRCRAFT WITH NO OTHER INDICATIONS. NO WARNING LIGHTS, NO CONTRO	L OR HANDLING PROBLEMS. AFTER LANDING, THE ENGINEER CARRIED OUT HIS ROUTINE (BEFORE FLIGHT) INSPECTION.  LOOKING AT THE 	TAILBOOM TO FUSELAGE ATTACH FITTINGS, HE FOUND THE FITTING P/N 212-030-161-001 BROKEN IN HALF. DETAILED INSPECTION AFTER	 REMOVING THE TAILBOOM FOUND THE UPPER LT CAP ANGLE P/N 212-030-191-001 UNDER THE UPPER ATTACHMENT FITTING CRACKED.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003090900056	20030909	00056	WP  	2003	9	9	CA030825009      	1	20030809	G	1430	528075	BOLT            	MENASCO     	528400      	CVAC  	580   	580         	2422806	WP  	ALLSN 	501D  	501D13      	03004	GL  					MLG STRUT	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) UPON LANDING AT YCG THE FLT CREW EXPERIENCED A SEVERE SHIMMY FROM THE LANDING GEAR. THE AIRCRAFT WAS BROUGHT TO A 	STOP ON THE RUNWAY WITHOUT THE USE OF BRAKES. THE CREW WAS INFORMED BY RADIO THAT THE RT MLG WAS NOT TRACKING STRAIGHT. 	AFTER ENSURING THERE WAS NO FIRE THE AIRCRAFT WAS TAXIED TO THE TANKER BASE. IT WAS DETERMINED THAT THE RT MLG TORQUE LI	NK BOLT HAD BROKEN CAUSING THE WHEEL ASSY TO ROTATE THROUGH 180 DEGREES SEVERING THE BRAKE LINES. SEVERAL BRAKE CALIPER 	RETAINING BOLTS WERE ALSO FOUND SEVERED. THERE WAS SOME MINOR DAMAGE TO THE TORQUE LINK. NO PARTS WERE FOUND ON WHEN THE	 RUNWAY WAS CHECKED. THE AIRCRAFT WAS INSPECTED, REPAIRED AND RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	        	E282				 
2003090900057	20030909	00057	CE  	2003	9	9	CA030825010      	1	20030818	G	2824	15507A	SEAL            	ITT         		CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					FUEL VALVE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						L04635					(CAN) LT CROSSFEED VALVE WAS FOUND TO BE LEAKING (WEEPING FUEL PAST SEALS THAT FAILED. PN 15507A HAD TURNED TO A SOFT PU	TTY LIKE SUBSTANCE, MS29513011 0-RINGS HAD GONE HARD.  NOTE: THIS VALVE DID NOT APPEAR TO HAVE BEEN REPLACED, HENCE APPR	OXIMATELY 20 YEARS SERVICE, 5300 HRS.				1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2003090900059	20030909	00059	CE  	2003	9	9	CA030825011      	1	20030715	G	2460		DIODE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	DC POWER	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) A/C ON APPROACH, TURNED RECOG LIGHT ON, LOST INTERCOM, NR 2 RADIO, COULD NOT EXTEND LAND GEAR.  EMER EXTENSION CAR	RIED OUT.  AC LANDED WITHOUT FURTHER INCIDENT. MAINT FOUND NR 2 DUAL FED BUS RT DIODE FAILED AND A LOOSE BUS WIRE NR 2 D	UAL FED BUS. DIODE REPLACED AND WIRE TIGHTENED. PERFORMED GEAR FUNCTION CHECKS AFTER EMER EXT. GROUND CHECKS CARRIED OUT	. INTERCOM, NR 2 RADIO AND LANDING GEAR FUNCTION NORMALLY. AC RETURNED TO SERVICE. THERE WAS A FEEDER DIODE INSPECTION C	ARRIED OUT AT LAST PHASE 3 INSPECTION DATED 13 JUNE 2003.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2003090900061	20030909	00061	CE  	2003	9	9	CA030825012      	1	20030810	G	3230	AE3660120G0230	HOSE            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	RUPTURED        	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) TIME ON HOSE UNKNOWN ALTHOUGH DATA PLATE ON IT INDICATES 13 YEARS OLD.  LANDING GEAR WAS SELECTED UP AND ONLY 2 MA	IN GREEN LIGHTS CAME ON.  THERE WAS ALSO A STRONG ODRO OF HYD FLUID.  PILOT SELECTED DOWN AND THE NOSE GEAR LIGHT DID NO	T COME ON.  PILOT THEN HAND PUMPED THE GEAR DOWN AND GOT 3 GREEN LIGHTS.  AIRCRAFT RETURNED TO BASE AND MAINTENANCE REPL	ACED THE NOSE GEAR RETRACT LINE.  GEAR SWINGS CHECKED SERVICEABLE.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003090900063	20030909	00063	SW  	2003	9	9	CA030825013      	1	20030811	G	3251	2719087009	ACTUATOR        		AIRTIGHT    	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG STEERING	LOOSE           	W				D				RETURN TO BLOCK         				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA											(CAN) TOTAL TIME UNKNOWN, NOT TRACKED, PILOT STARTED TO TAXI AND REPORTED BAD VIBRATION WITH THE NOSE STEERING ON OR OFF	.  THE INTERNAL PART OF THE STEERING ACTUATOR COULD BE MOVED BY HAND.  STEERING ACTUATOR WAS REMOVED, SYSTEM FLUSHED OUT	 AND SERVICEABLE STEERING ACTUATOR INSTALLED.  SYSTEM WAS RETURNED TO SERVICE.				2	L	7	2 	4T	3	T	RT	A8SW    	E2WE	6	C	3PNE	 
2003090900064	20030909	00064	CE  	2003	9	9	CA030825014      	1	20030821	G	2780	1013800006	SHAFT           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	LE SLAT CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, CREW SELECTED FLAPS '0' BUT NOTED THAT PANEL NR 4 DID NOT APPEAR TO RETRACT ALL THE WAY UP.  FLIGHT 	CONTINUED TO DESTINATION AND FLAPS WERE CONFIRMED TO BE ALL UP EXCEPT NR 4 WHICH WAS HANGING DOWN BY APPROX 4 DEGREES. T	HE .5000 & .7500 PANEL PAIRS ARE PROTECTED BY A 3 TO 6 DEGREE SPLIT IN PAIR WHICH LOCKS SYSTEM, ONLY RESETTABLE ON GROUN	D. MAINT FOUND THAT  FLEXIBLE DRIVE CABLE FOR NR 4 WAS BROKEN INSIDE OF EXTERNAL COVERING. A FACTORY INSTALLED CLAMP APP	EARS TO HAVE BEEN OVERTIGHENED WHICH CAUSED A LOSS OF COVERING INTEGRITY ALLOWING MOISTURE TO ENTER CABLE SHEATH. LOW PO	RTION COLLECTED MOISTURE AND EVENTUALLY CORRODED ENOUGH TO ALLOW TORQUE TO BREAK STRANDS. MFG HAS BEEN NOTIFIED.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003090900065	20030909	00065	CE  	2003	9	9	CA030825015      	1	20030824	G	2425	1143800331	INDICATOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	AC VOLT METER	SHORTED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			12568								(CAN) DURING CURISE FLIGHT, CREW NOTED ELECTRICAL ODOR AND SMOKE IN COCKPIT AREA. THE AIRCRAFT RETURNED TO ORIGINAL DEPA	RTURE LOCATION. THE DURATION OF THE SMOKE/SMELL WAS VERY BRIEF.  MAINTENANCE REPLACED THE AC VOLTMETER INDICATOR WHICH A	PPEARS TO HAVE SHORTED INTERNALLY.  THE UNIT HAS BEEN SENT FOR INVESTIGATION AND A STRIP HAS BEEN REQUESTED FOR FURTHER 	FOLLOWUP.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003090900067	20030909	00067		2003	9	9	CA030825016      	4	20030716	G	8300	6014T81G28	GEARBOX         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ACCESSORY	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA								807537			(CAN) LT FUEL PUMP  AND LT SCAV EJECTOR CAUTION MESSAGES WERE POSTED AND LT ENGINE FUEL PRESSURE WENT TO ZERO CAUSING TH	E LT ENGINE TO SHUT DOWN.  NO N2 ROTATION WHEN STARTER MOTORED.  REPLACED ENGINE QEC ASSEMBLY.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003090900069	20030909	00069	EA  	2003	9	9	CA030825017      	1	20030815	G	5610	NP1393221	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24190								(CAN) LT SIDE WINDOW WAS FOUND DELAMINATED. THERE IS NO POST OR PRE SB CONFIGURE FOR THE WINDOW.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003090900071	20030909	00071	CE  	2003	9	9	CA030826001      	1	20030728	G	5230	85355041	DOOR            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	WING LOCKER	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) DURING DESCENT OUT OF FL270 AND DESCENDING THRU FL240 THE LT WING LOCKER OPENED IN FLIGHT. AIRCRAFT LANDED WITHOUT	 INCIDENT. WING LOCKER INSPECTED FOR DAMAGE, NO DAMAGED NOTED. TWO LOCKING LATCHES WERE STILL IN THE CLOSED POSITION. AI	RCRAFT RETURNED TO BASE. MAINT FURTHER INSPECTED LATCHING SYSTEM, NO FAULTS NOTED. KEY LOCK WAS NOT USED AT TIME OF FLIG	HT. COMPANY PROCEDURE WILL CHANGE TO USEKEY LOCK ON WING LOCKERS.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2003090900072	20030909	00072	SO  	2003	9	9	CA030826002      	1	20030812	G	2821	100871002	STRAINER        	PIPER       		PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320B2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	GASCOLATOR	STRIPPED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING INSPECTION OF THE FUEL GASCOLATOR AT THE ANNUAL, THE STUD FOR THE SAFETY NUT WAS FOUND TO BE STRIPPED. THE 	GASCOLATOR BALE WAS REPLACED WITH A NEW PART AS A RECTIFICATION TO THE PROBLEM.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003090900074	20030909	00074	CE  	2003	9	9	CA030826003      	1	20030808	G	2810	56181065	PLATE           			CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					FUEL CELL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			11516								(CAN) DURING A NR 3 INSPECTION, A FUEL STAIN WAS NOTICED AROUND THE RT NAVIGATION LIGHTCOVER. THE COVER WAS REMOVED AND 	A CRACK WAS FOUND ON THE FORWARD FUEL TANK PLATE. THE CRACK WAS UNDER THE LOWER STROBE LIGHT BRACKET, CAUSING FUEL TO LE	AK INTO THE STROBE LIGHT/NAV LIGHT AREA.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2003090900075	20030909	00075	SW  	2003	9	9	CA030826004      	1	20030817	G	6340	32005023	PLATE           			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					MOUNTING	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) LOOSE CONNECTOR MOUNTING PLATE.  INSTALLED SERVICEABLE UNIT TSO 0:0.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003090900077	20030909	00077	NE  	2003	9	9	CA030826006      	2	20030825	G	7200		ENGINE          			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					NR 4	OVERHEATED      	W				F	E			ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         			M	E	J	OVER TEMP                 	VIBRATION/BUFFET          	WARNING INDICATION        	CL	CLIMB          	1			CA			26815					741670			(CAN) CLIMBING THROUGH FL130, NR 4 ENGINE STALLED AND HIGH TEMPS.  A/C RETURNED HNL WITH ENG SHUT DOWN AND FIRE BOTTLES 	BLOWN. ENG HAD 17,536 HRS SINCE SHOP VISIT AND 2,068 CYCLES SINCE SHOP VISIT					2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2003090900079	20030909	00079		2003	9	9	CA030826007      	4	20030824	G	3140	066040211113	SYMBOL GENERATOR			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA											(CAN) NR 1 SYMBOL GENERATOR FOR THE CAPTAIN'S ELECTRONIC FLIGHT INSTRUMENTS CAUSED BOTH UPPER AND LOWER CATHODE RAY DISP	LAY TUBES TO FAIL ON THE CAPTAIN'S SIDE. UPPER AND LOWER CRT'S ON THE CAPTAIN'S SIDE WOULD INTERMITTENTLY GO INTO SELF T	EST, AND WOULD ONLY SHOW 'SELF TEST' ON THE SCREENS OR BE COMPLETELY BLANK, NO FLIGHTDATA WAS AVAILABLE. NR 1 AND 2 SYMB	OL GENERATORS WERE SWAPPED AND THE FAILURE FOLLOWED TO THE NR 2 (CO-PILOT) SIDE SYMBOL GENERATORS WERE RETURNED TO THEIR	 ORIGINAL LOCATION. NR 1 SYMBOL GENERATOR WAS REPLACED AND RECONFIGURED IN ACCORDANCE WITH THE MAINTENANCE MANUAL. SYSTE	M OPERATED NORMAL.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003110600123	20031106	00123		2003	11	6	CA030826008      	4	20030826	G	2562		BATTERY         	ACK         																ELT	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) TWO ELTS, THE AK-450 AND THE  E-01, ARE APPROVED TO USE ALKALINE BATTERIES.  AT PRESENT, WE ARE ABLE TO PURCHASE C	OMMERCIALLY  BATTERIES WITH THE EXPIRATION DATE YEAR 2010.  OTHER ELT MANUFACTURERS THAT USE SIMILAR BATTERIES HAVE A MA	NDATORY REPLACEMENT CYCLE OF 2 YEARS.  WE HAVE ENCOUNTERED CORROSION DAMAGE ON ELTS THAT HAD BATTERIES INSTALLED LONGER 	THAN 2 YEARS. IT MAY BE ADVISABLE TO INFORM THE INDUSTRY TO REPLACE THE BATTERIES WITHIN A 2 YEAR PERIOD, REGARDLESS OF 	THE MANUFACTURER'S  PROPOSED EXPIRATION DATE.															 
2003090900080	20030909	00080	GL  	2003	9	9	CA030826009      	3	20030818	G	6111		BLADE           													MCAULY	1A100	1A100MCM    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) EXTRA WORK TO REMOVE CORROSION FROM PROPELLER CAMBER FACE.																5	N	P918	 
2003090900082	20030909	00082	SW  	2003	9	9	CA030826010      	1	20030808	G	2497	RCR326820JM	RESISTOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					POTENTIOMETER	BURNED          	W				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA											(CAN) DURING NORMAL LEVEL CRUISE SMOKE & FUMES SEEN ESCAPING OVERHEAD ELECTRICAL PANEL.  AIRCRAFT LANDED AND SHUTDOWN.  	SMOKE DISAPPEARED AND ALL SYSTEMS FOUND FUNCTIONAL EXCEPT INSTRUMENT LIGHTS.  INSTRUMENT LIGHTS BREAKER PULLED AND DEACT	IVATED.  UPON INSPECTION OF OVERHEAD PANEL, RESISTOR FOR INSTRUMENT LIGHTS FOUND CHAFED THROUGH TO ANOTHER WIRE CAUSING 	RESISTOR TO SHORT OUT AND BURN.  BETTER CARE IN INSTALLATION OF PARTS, PROPER SHEATHING AND BUNDLE LOCATING.			1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003090900083	20030909	00083	NE  	2003	9	9	CA030826011      	2	20030806	G	8530	356995	CYLINDER        			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT WAS ORBITING THE FIRE WHEN THE FLIGHT CREW HEARD A BACKFIRE FROM THE NR 4 ENGINE. THE ENGINE WAS SHUT	 DOWN AND THE PROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED TO BASE. MAINTENANCE CREWS FOUND THE NR 2 CYLINDER WAS CRAC	KED AT THE EXHAUST EAR. THE CYLINDER WAS REPLACED WITH A SERVICEABLE ASSEMBLY. THE ENGINE WAS GROUND RUN AND LEAK CHECKE	D SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	4 	4R	4	R	 	6A4     	E264	6	C	P871	 
2003090900084	20030909	00084	NE  	2003	9	9	CA030826012      	2	20030729	G	8530	356996	CYLINDER        			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	LOOSE           	W				E				ENGINE SHUTDOWN         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE FLIGHT CREW NOTICED NR 1 ENGINE WAS BACKFIRING. THE ENGINE WAS SHUT DOWN AND THE PROPELLER WAS F	EATHERED. THE AIRCRAFT RETURNED TO BASE. MAINTENANCE CREWS FOUND THE INTAKE INSERT ON NR 11 CYLINDER WAS LOOSE. THE CYLI	NDER WAS REPLACED WITH A SERVICEABLE ASSEMBLY. THE ENGINE WAS GROUND RUN AND LEAK CHECKED SERVICEABLE. THE AIRRAFT WAS R	ETURNED TO SERVICE.			2	L	7	4 	4R	4	R	 	6A4     	E264	6	C	P871	 
2003090900085	20030909	00085	WP  	2003	9	9	CA030826013      	1	20030731	G	2612	351005	CONNECTOR       			CVAC  	580   	580         	2422806	WP  	ALLSN 	501D  	501D13      	03004	GL  					FIRE DETECTOR	BROKEN          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE FLIGHT CREW RECEIVED A FIRE WARNING INDICATION FOR THE ZONE 1 AREA OF THE RT ENGINE. THE LOAD WA	S JETTISONED, THE 'E' HANDLE WAS PULLED ON THE RT ENGINE AND THE AIRCRAFT RETURNED TO LOON RIVER. UPON INVESTIGATION THE	 CONNECTOR WAS FOUND BROKEN CAUSING THE FALSE INDICATION. THE CONNECTOR WAS REPLACED, THE SYSTEM WAS FUNCTION CHECKED SE	RVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	        	E282				 
2003090900087	20030909	00087	EA  	2003	9	9	CA030826014      	2	20030825	G	8500		ENGINE          			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE PILOT NOTED NR 2 ENGINE WAS BACK FIRING AND SMOKE WAS VISIBLE. THE ENGINE WAS SHUT DOWN AND THE P	ROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED TO YWL. UPON INVESTIGATION THE MAINTENANCE CREW NOTED THAT THE MAIN OIL SC	REEN WAS CONTAMINATED WITH ALUMINUM AND STEEL. THE ENGINE IS BEING REPLACED WITH A SERVICEABLE UNIT. THE PROPELLER AND D	OME WILL BE DRAINED AND FLUSHED PRIOR TO BEING REINSTALLED. THE ENGINE WILL BE GROUND RUN AND LEAK CHECKED PRIOR TO THE 	AIRCRAFT BEING RELEASED TO SERVICE.		2	H	7	2 	4R	4	R	 	A25WE   	E259	6	C	P8879	 
2003090900089	20030909	00089	WP  	2003	9	9	CA030826015      	1	20030818	G	2421	696233B	CSD             			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					AC SYSTEM	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				M			OVER TEMP                 			CR	CRUISE         	1			CA						5061					(CAN) THE AIRCRAFT TOOK OFF FROM CANCUN AND THE CSD TEMPERATURE ON THE RT ENGINE WAS APPROACHING CAUTION SO THE PILOT DE	CIDED TO DISCONNECT THE CSD AND, DUE TO THE AIRCRAFT APU ON MEL, DECLARE AN EMERGENCY AND LANDED IN FLL. MAINTENANCE IN 	FLL CHECKED THE CSD OIL LEVEL AND FILTER DIFFERENTIAL PRESSURE INDICATOR. NO DEFECT FOUND, AIRCRAFT RETURNED TO SERVICE.	 FLIGHT TO YUL NO PROBLEM EXCEPT CSD TEMPERATURE IN YELLOW BAND. CSD WAS REPLACED AS A PRECAUTION IN YYZ.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2003090900090	20030909	00090	NM  	2003	9	9	CA030826016      	1	20030820	G	5280	59423782	HINGE BRACKET   			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG DOOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) CRACK FOUND ON MAIN LANDING GEAR INNER DOOR ATTACH BRACKET FOR PUSH ROD. DOOR REMOVED AND OPERATED ON CDL 32-10-4.	 DOOR RECEIVED AND WILL BE INSTALLED.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102000174	20031020	00174	EA  	2003	10	20	CA030826017      	2	20030813	G	7250		ENGINE          								PWA   	PT6   	PT6A28      	 	EA  					NACELLE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE CONTINUED TO BE OPERATED FOR APPROXIMATELY ONE HOUR BEFORE SEIZING TO A STOP, AFTER A 'LOW OIL LEVEL' INDIC	ATOR ILLUMINATED IN THE COCKPIT. ENGINE WAS REMOVED AND SHIPPED TO REPAIR STATION TO REVIEW ENGINE AND DETERMINE REQUIRE	D WORKSCOPE.  ATLANTIC TURBINES BELIEVES THAT THE EXCESSIVE HEAT GENERATED FROM THE LACK OF OIL BEING SUPPLIED TO THE LU	BRICATED COMPONENTS CAUSED THE 1ST STAGE CARRIER ASSEMBLY TO SEIZE. NO DAMAGE WAS FOUND IN THE ENGINE THAT WOULD CAUSE A	 MAJOR OIL LOSS.							4	T			E4EA				 
2003090900094	20030909	00094	NE  	2003	9	9	CA030826018      	2	20030813	G	7250		TURBINE BLADES  			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NR 2 ENGINE	SHINGLED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ROUTINE SERVICE CHECK FOUND NR 2 ENGINE NOZZLE ASSY CRACKED APPROX 3/4 OF THE WAY AROUND. NO NOTICABLE VIBRATIO	NS. UPON REMOVAL OF NOZZLE ASSY NOTICED SOME TURBINE BLADES SHINGLED. ENGINE HAD BEEN INSTALLED NOV 2002.  ENGINE REMOVE	D FOR SHOP INVESTIGATION. ENG SER 731399 TOTAL HRS 28,672 TOTAL CYCLES 10,342 TIME SINCE INSTALLED 1,847 AND CYCLES 833				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003090900095	20030909	00095	NE  	2003	9	9	CA030826019      	2	20030813	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ROUTINE INSPECTION BOTH ENGINE IGNITERS WERE FOUND TO HAVE LOOSE CENTER ELECTRODES.  IN LIGHT OF RECENT TURBOME	CA SERVICE LETTERS REGARDING IGNITERS (N/A TO THIS PN THOUGH) IT WAS DEEMED NECESSARY TO REPLACE THEM TO PREVENT POSSIBL	E ENGINE DAMAGE CAUSED BY AN ELECTRODE DETACHING AND FODDING THE ENGINE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003102000177	20031020	00177	CE  	2003	10	20	CA030827001      	1	20030821	G	5320	26111441	SUPPORT         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FLAP ACTUATOR	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			18416	18416							(CAN) ON APPROACH, FLAPS WERE SELECTED TO 30 DEGREES.  FLAP INDICATION WAS SHOWING 20 DEGREES & AIRSPEED CONFIRMED FLAPS	 WERE INOPERATIVE. FLAP MOTOR CIRCUIT BREAKER WAS POPPED & STANDBY FLAP MOTOR WAS TRIED WITH NO RESULTS.  A SUCCESSFUL L	ANDING WAS MADE & FLAPS WERE FOUND STUCK IN THE 20 DEGREE POSITION.  INSPECTION REVEALED FLAP ACTUATOR SUPPORT ASSY TORN	 & CRACKED.  TRANSMISSION HAD TWISTED SUPPORT ASSY & JAMMED.  ATTEMPTED USE OF ALTERNATE FLAP MOTOR BY CREW HAD SHEARED 	DRIVE COUPLING.  MM CALLS UP AN INSPECTION OF FLAP SUPPORT ASSY EACH 400 HRS.   SUPPORT ASSY APPEARED TO HAVE NUMEROUS C	RACKS PRESENT PRIOR TO BREAKING POINT,  LEADING TO INCREASED STRESS & UNSUPPORTABLE LOAD.	1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003090900096	20030909	00096	SO  	2003	9	9	CA030827002      	2	20030825	G	8530	654004	EXHAUST VALVE   			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	ERODED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING THE BOROSCOPE INSPECTION OF THE ON-CONDITION PROGRAM, SPECIAL EFFORT WAS MADE TO INSPECT THE EXHAUST VALVE 	AS WE HAD FOUND A PREVIOUS VALVE OF THE SAME PART NUMBER IN POOR CONDITION.  THE NR 2 CYLINDER EXHAUST VALVE WAS FOUND S	EVERELY ERODED 1/3 TO 1/2 OF THE WAY ACROSS THE DIAMETER OF THE VALVE STEM WHERE THE STEMOF THE VALVE MEETS THE HEAD OF 	THE VALVE.  THE PROBLEM APPEARS TO BE A METALLURGICAL PROBLEM OR A DEFECT IN THE MANUFACTURE OF THE VALVE.  THE VALVE WI	LL BE REPLACED NEW.  ALL OTHER ASPECTS OF THE ENGINE WERE INSPECTED FOR A CAUSE OF THIS PROBLEM AND NONE WERE EVIDENT.		1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003090900099	20030909	00099	NM  	2003	9	9	CA030827003      	1	20030825	G	3244		TIRE            			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					MLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ON ROTATION NR 2 TIRE BLEW RECAP OFF. FLASH OF LIGHT SEEN FROM FLT DECK, LOUD BANG AND RUBBER ODOR IN C/P. RETURNE	D TO YYZ. ON ARRIVAL FOUND RECAP MISSING AND TIRE STILL INFLATED. CREW REPORTED NR 1 ENG VIBS UP TO 1.7 UPON INSPECTION 	FOUND DAMAGE TO SOME FAN BLADES ON NR 1 ENG.   A/C HANGERED FOR INSPECTION AND OVERWIEGHT LANDING CHECK. TIRE HAD BEEN I	NSTALLED MAY 02 2003.  ASSY HAD HAD TWO RECAPS			2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2003090900101	20030909	00101	CE  	2003	9	9	CA030827004      	1	20030818	G	3245	600X6	TUBE            			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520D      	17032	SO  					NLG TIRE	PINCHED         	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING, THE PILOT EXPERIENCED A SHIMMY IN THE AIRFRAME WHILE TAKING OFF THE RUNWAY. THE PILOT STOPPED AND S	HUTDOWN THE AIRCRAFT. THE NOSE WHEEL WAS FOUND TO BE FLAT. MAINTENANCE PERSONNEL REPLACED NOSE WHEEL ASSEMBLY WITH SERVI	CEABLE UNIT. THE FLAT NOSE WHEEL ASSEMBLY WAS DISASSEMBLED AND THE TUBE WAS FOUND PINCHED ALONG ITS CENTRE LINE ADJACENT	 TO THE TIRE CENTRE LINE. IT APPEARS THAT THE BALANCE WEIGHT ATTACHED INSIDE THE TIRE WAS WHAT CAUSED THE TUBE FAILURE.			1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2003090900102	20030909	00102	NE  	2003	9	9	CA030827006      	2	20030819	G	7200		ENGINE          			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  						FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AC WAS INVOLVED IN FIREFIGHTING OPERATIONS. AFTER PICKING UP LOAD OF WATER WITH A 95 PERCENT TORQUE SETTING AC BEG	AN A CLIMB. 5 SECONDS INTO CLIMB AT 95 PERCENT TORQUE PILOTS HEARD WHAT WAS DESCRIBED AS A COMPRESSOR STALL AND FELT A S	LIGHT KICK IN AIRFRAME. THE NR 1 TORQUE DROPPED TO 20 PERCENT AND FLUCTUATED MOMENTARILY. PILOT THEN REDUCED POWER AND L	OWERED BUCKET BACK INTO WATER. ALL INDICATIONS WERE NORMAL.  AC THEN RETURNED TO SERVICE LANDING.  NR 1 ENGINE HAS BEEN 	REMOVED AND REPLACED.  BOTH FREEWHEEL UNITS HAVE BEEN REMOVED AND REPLACED.  CAUSE OF THE MOMENTARY POWER LOSS, UNKNOWN.	 FREEWHEEL UNITS WILL BE BROUGHT TO OUR OVERHAUL FACILITY FOR A DOCUMENTED TEARDOWN AND INSPECTION.	2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2003090900103	20030909	00103	CE  	2003	9	9	CA030827007      	1	20030819	G	7810	NH100089740	CLAMP           			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	EXHAUST PIPE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A NR 4 INSPECTION, THE V-BAND CLAMP ATTACHING THE EXHAUST TAIL PIPE TO THE TURBOCHARGER, WAS FOUND BROKEN. 	THE CLAMP WAS BROKEN IN HALF. THE ONLY THING HOLDING THE TAIL PIPE ON WAS A SUPPORTING HOSE TYPE CLAMP MOUNTED HALF WAY 	DOWN THE PIPE. THE BROKEN CLAMP WAS REPLACED.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2003090900104	20030909	00104		2003	9	9	CA030827008      	4	20030813	G	2565	69492111	NUT PLATE       			BOEING	727   	727251      	138408H	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					GIRT BAR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) L-2 DOOR ESCAPE SLIDE GIRT BAR FORWARD FLOOR FITTING NUT PLATE ASSY MISSING, UNDER FLOOR PANEL. THIS NUT PLATE REE	NFORCED THE GIRT BAR FITTING ATTACHMENT TO THE FLOOR. IN CASE OF CHUTE DEPLOYEMENT, THE LOAD IN THE SLIDE WOULD PULL ON 	THE ATTACH FITTING AND COULD PULL ON THE FLOOR PANEL, LEAVING THE CHUTE ATTACHED BY ONLY ONE FITTING.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003090900106	20030909	00106	EA  	2003	9	9	CA030827009      	2	20030630	G	8530	SL11795	VALVE SPRING    			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  BOTH EXHAUST VALVE SPRING BROKEN, NR 1 CYLINDER.    NEW SPRINGS INSTALLED ALL CYLINDER.  RAN OK, SLIGHT INCREASE 	IN EXHAUST GAS TEMPERATURE NR 1 RPBE.					1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2003090900107	20030909	00107	SO  	2003	9	9	CA030827010      	1	20030821	G	5520	7C103053	HORN            			GULSTM	GA7   	GA7         	3960401	SO  	LYC   	O320  	O320D1D     	41508	EA  	HARTZL	HCF2Y	HCF2Y*      	GL  	ELEVATOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			14673								(CAN) LT ELEVATOR HORN ASSEMBLY WAS FOUND TO BE CRACKED.						1	L	7	2 	3O	3	O	 	A17SO   	E274	5	C	P27EA	 
2003090900108	20030909	00108	NM  	2003	9	9	CA030827011      	1	20030813	G	2740	MS202204	PULLEY          			BOEING	727   	727251      	138408H	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					STAB TRIM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSPECTING THE TAIL AREA (C-CHECK), IT WAS NOTICED THAT THE RT STABILIZER TRIM CABLE WAS TRAVELLING VERY CLO	SE TO THE PULLEY HOLDING BRACKET. FURTHER INVESTIGATION REVEALED ONE MORE RT CABLE PULLEY WORN AND TWO OTHERS WORN OUT O	N THE LT CABLE.  CABLES TENSION TEST WAS CARRIED OUT AND BOTH CABLES TENSION VALUE WERE FIVE LBS BELOW THE MINIMUM SPECI	FIED MANUFACTURER TENSION LIMIT.  ALL FOUR PULLEYS WERE REPLACED, SYSTEM RIGGED AND NORMAL FUNCTION RESUMED IAW MM.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003090900110	20030909	00110	NM  	2003	9	9	CA030827012      	1	20030813	G	5753	66147195	BOLT            			BOEING	727   	727251      	138408H	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					TE FLAP ROLLER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION FOUND RT INBOARD FLAP 2ND INBOARD TRACK, FORWARD ROLLER BOLTS (2) ASSY MISSING.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003102000179	20031020	00179	CE  	2003	10	20	CA030827013      	1	20030827	G	3080	1013800159	HOSE            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					BRAKE DEICE SYS	DETERIORATED    	W				K	K			NONE                    	NONE                    			O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BRAKE DE-ICE HOSE WAS FOUND TO BE BLOCKED DUE TO DETERIORATION OF THE INSIDE OF HOSE.  THE UPPER FLEXIBLE HOSE WAS	 FOUND TO PASS SHOP AIR THROUGH AN AIR NOZZLE BUT WAS NOT FOUND TO PASS THE VOLUME SUPPLIED BY THE ENGINE BLEED AIR. THE	 LARGE VOLUME OF AIR BLOCKED THE INSIDE OF THE HOSE COMPLETELY AND WOULD NOT ALLOW THE LT BRAKE TO BE DE-ICED.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2003102000180	20031020	00180	SW  	2003	10	20	CA030828001      	1	20030820	G	2910	70012F000X204	HOSE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					HYD SYSTEM	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING FLIGHT THE PILOT NOTICED A LOSS OF HYD PRESSURE ON NR 1 HYDRAULIC SYSTEM. THE SYSTEM WAS DEACTIVATED AND TH	E PILOT RETURNED TO BASE.  AFTER LANDING, SYSTEM NR 1 WAS INSPECTED AND A HYD PRESSURE HOSE WAS FOUND RUPTURED. THE HOSE	 ASSEMBLY WAS REPLACED AND THE SYSTEM SERVICEABILITY CHECKS WERE COMPLETED.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003090900111	20030909	00111	SO  	2003	9	9	CA030828002      	2	20030820	G	8530		EXHAUST VALVE   			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O550  	TSIO550C    		SO  					CYLINDER HEAD	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRUISING AT 25,000 FT, MANIFOLD PRESS DROPPED BY 5 INCHES, DID NOT RECOVER UNTIL BELOW 10,000 FT. MAINT CHECKS ON 	GROUND DETERMINED NO (ZERO) COMPRESS ON NR 6 CYL UPON REMOVAL OF CYL EXHAUST VALVE WAS DISCOVERED TO HAVE .2500 OF VALVE	 FACE MISSING. PIECE OF VALVE WAS FOUND LODGED IN LT TURBOCHARGER CAUSING WHEEL DAMAGE. EXAM OF ENG CASE REVEALED A 4 IN	CH CRACK ON MAIN JOURNAL BETWEEN CYL 4 AND 6.   NOTE: 137 HRS PRIOR TO THIS INCIDENT, MAINT FACILITY HAD NOTED SMALL CRA	CK IN ENG CASE BETWEEN CYL 4 AND 6, LOG BOOK. NOTATION READS 'SEALED SMALL CRACK IN LT CRANKCASE BETWEEN CYLINDER NR 4 A	ND NR 6 BELOW 7TH. STUD CRACK TO BE MONITERED AT SCHEDULED INSP'.	1	L	7	1 	3O	3	O	RT	A25SO   	E5SO				 
2003090900113	20030909	00113	EA  	2003	9	9	CA030828003      	2	20030813	G	7414		IMPULSE COUPLING	BENDIX      		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					MAGNETO	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						877086					(CAN) ENGINE FAILED TO START. THE LT MAGNETO IMPULSE COUPLING SEIZED. MAGNETO REMOVED FOR REPAIR.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003090900115	20030909	00115	CE  	2003	9	9	CA030828004      	1	20030821	G	7330	811015	INDICATOR       			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FUEL QTY	ARCED           	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REPORTS (SNAG VERIFIED LATER) LT FUEL QUANTITY INDICATOR FLUCTUATES BETWEEN 1000 & 1400 LBS. (FREQUENCY OF N	EEDLE FLUCTUATION RENDERS NEEDLE A BLUR). INSPECTION OF INDICATOR REVEALED WATER MARKS ON LOWER FORWARD FACE OF INDICATO	R AND ON REAR OF INDICATOR EVIDENCE OF WATER DRIPPING WAS APPARENT. SUSPECT WATER DRIPPING IN ON FUEL PANEL WHEN WINDOW 	OPENED AFTER A RAIN.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003090900117	20030909	00117	NE  	2003	9	9	CA030828005      	2	20030822	G	7250	3028601	BLADE           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TURBINE SECTION	FRACTURED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) PILOTS NOTICED SLIGHTLY HIGHER ITT TEMP ON RT ENG A SLIGHT RISE IN N2 SPEEDS. TEMP AND N2 INDICATIONS, AS WELL AS 	ALL OTHER INDICATIONS WHERE NOTED TO BE WELL WITHIN NORMAL OPERATING PARAMETERS.ON FINAL INTO CALGARY AIRPORT WHILE POWE	RING BACK A SLIGHT VIBRATION WAS NOTED BY PIC.PILOT LANDED WITH BOTH ENGINES RUNNING.ONCE SHUTDOWN, PILOT INVESTIGATED B	OTH ENGINES BY VISUALLY LOOKING IN INTAKES AND EXHAUSTS.  PILOT NOTICED SEVERAL SMALL PARTICLES OF METAL INSIDE EXHAUST 	DUCT ON RT ENG.  HOT SECTION OF RT ENG REMOVED FOR INVESTIGATION. HIGH PRESSURE TURBINE BLADES FOUND SEVERELY DAMAGED (3	 OR MORE BLADE TIPS MISSING AND/OR TIPS CURLED OVER).  ENGINE REMOVED FROM AIRFRAME FOR INVEST.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003090900118	20030909	00118	EA  	2003	9	9	CA030828006      	2	20030820	G	8520	LW10346	CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	SHEARED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			CA											(CAN) PILOT DEPARTED NORWAY HOUSE FOR WINNIPEG. AFTER REACHING CRUSE ALTITUDE THE L/H ENGINE RAN ROUGH FOR A SHORT PERIO	D OF TIME THEN FEATHERED ON ITS OWN AND SHUT DOWN. THE PILOT RETURNED TO NORWAY HOUSE AND LANDED UNEVENTFULLY. ON THE GR	OUND IT WAS DETERMINED THAT WHEN THE PROPELLER WAS TURNED THROUGH BY HAND THAT PISTONS IN CYLINDERS 6,5,4, & 3 WERE NOT 	MOVING. THE LT ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED WITH OUT FURTHER INCIDENT. INVESTIGATION OF THE FAILED ENGI	NE IS ON-GOING. PRELIMINARY INVESTIGATION SHOWS THAT THE CRANKSHAFT SHEARED IN 2 PLACES CAUSING EXTENSIVE DAMAGE.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003101700002	20031017	00002	EA  	2003	10	17	CA030829001      	1	20030821	G	3212	C2UF1085	STRUT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	LT FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT FLOAT MAIN FORWARD STRUT FOUND CRACKED AT TOP ATTACHMENT LUG DURING AIRCRAFT REFUELING, GROUNDED,  AWAITING NEW	 STRUT.					1	H	7	1 	3R	3	R	 	A815    	5E2	6	C	P719	 
2003090900119	20030909	00119	GL  	2003	9	9	CA030829002      	2	20030822	G	7250	23031937	NOZZLE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHILE TROUBLESHOOTING AN ENGINE THAT WAS RUNNING HOTTER THAN NORMAL, WE PRFORMED A HOT SECTION INSPECTION AND FOUN	D THE 1ST STAGE NOZZLE CRACKED 90 DEGREES AROUND THE INNER RIM. IF THE CRACK HAD NOT BEEN FOUND, A TURBINE FAILURE MAY H	AVE OCCURRED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003102000005	20031020	00005	NM  	2003	10	20	CA030902002      	1	20030825	G	2421		CIRCUIT BOARD   			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					3 PHASE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT REPORTS SHORTLY AFTER TAKE OFF ROTATION, NUMEROUS THREE PHASE CIRCUIT BREAKERS (2 AND 3 THRUST REVERSER, 	GASPER FAN AND PANEL INSTRUMENT INDICATOR NR 1 DC) POPPED CAUSING LOSS OF SEVERAL SYSTEMS AND ANNUNCIATIONS. NR 2					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102000006	20031020	00006		2003	10	20	CA030902003      	4	20030808	G	3417	8220372436	ADC             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	DEFECTIVE       	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA											(CAN) AN ABORTED TAKE OFF ROLL OCCURED AT 100 KTS IAS FOR A 20 KTS SPLIT BETWEEN PILOT AND CO-PILOT INDICATED AIRSPEED. 	 LT 60 KTS - RT 60 KTS, LT 70 KTS = RT 80 KTS, LT 100 KTS = RT 120 KTS.  AIR DATA COMPUTER NR 1 REPLACED WITH A SERVICEA	BLE UNIT IAW AMM.  SYSTEM CHECKED AND FOUND SERVICEABLE.  DEFECTIVE UNIT RETURNED TO VENDOR.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003102000007	20031020	00007	EA  	2003	10	20	CA030903001      	2	20030817	G	8520		CASE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) PILOT REPORTED ENGINE OIL ON NR 1 COWL WHEN COWL WAS REMOVED IT WAS NOTICED THAT THERE WAS OIL ON TOP OF THE NR 6 	CYL.  HOLD DOWN STUDS. AFTER THE ENGINE WAS CLEANED IT WAS GROUND RUN AND THE OIL APEARED TO BE COMING FROM AROUND THE S	TUD BUT AFT ER FURTHER INSPECTION AND PAINT REMOVAL THERE WAS A HAIRLINE CRACK APPROX. 1.5 INCHES IN LENGTH.THE ENGINE W	AS REMOVED AND A NEW CASE WAS INSTALLED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003102000008	20031020	00008	EU  	2003	10	20	CA030903002      	1	20030901	G	2910	10546649	MANIFOLD        	BOLKMS      	10545028    	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					VALVE BODY	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA						052235					(CAN) THE INDICATOR LIGHT FOR THE NR 1 HYD SYS WILL NOT EXTINGUISH WHEN POWERED BY THE HYDRAULIC CART NOR WILL THE RESER	VOIR DRAIN INTO THE HYDRAULIC CART. (SUSPECT THE TEST SCREW ORIFICE IN THE VALVE BODY IS PLUGGED). THE HYDRAULIC POWER P	ACK ASSEMBLY WAS REPLACED AND GROUND CHECKED SERVICEABLE. THE SUSPECT ASSEMBLY WAS SENT FOR REPAIR.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003102000182	20031020	00182	EA  	2003	10	20	CA030903003      	2	20030717	G	7230	3023401	BLADE           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COMPRESSOR	FAILED          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) RT ENGINE SHUTDOWN DUE TO LOW TORQUE 10 PSI AND RISING T5 SHUTDOWN AT 690 DEGREES C.  PILOT WAS IN CRUISE ABOUT 9 	MINS AFTER TAKEOFF FROM GJOA HAVEN. AIRCRAFT RETURNED TO GJOA HAVEN AND PERFORMED AN UNEVENTFUL LANDING.  MAINTENANCE DI	SCOVERED A FUEL LINE BETWEEN START CONTROL AND FCU WAS BROKEN.  INTAKE SCREEN WAS REMOVED TO GAIN ACCESS TO COMPRESSOR I	NLET.  COMPRESSOR WAS DETERMINED TO BE SEIZED.  ENGINE WAS SUBSEQUENTLY REMOVED AND SENT TO STANDARD AERO FOR EXAMINATIO	N.  IT WAS DETERMINED THAT THE CT DISC HAD A BLADE FAILURE CAUSING AN INTERNAL ENGINE VIBRATION WHICH CAUSED THE FUEL LI	NE TO CRACK AND CAUSED FAILURE OF THE ENGINE MAIN BEARINGS.	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003102000183	20031020	00183	CE  	2003	10	20	CA030903004      	1	20030820	G	2810		LINE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL CELL	BLOCKED         	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) AIRCRAFT HAD LT ENGINE SHUTDOWN IN FLIGHT. AFTER EXTENSIVE TROUBLESHOOTING FOUND THAT AN INTERNAL PATCH ON FUEL BL	ADDER HAD COME OFF AND BLOCKED THE LINE TO NACELLE TANK.  ALL TANKS WERE INSPECTED AND 2 OTHER TANKS HAD INTERNAL PATCHE	S.  FUEL CELL REPAIRER TOLD US THAT INTERNAL PATCHES ARE COMMON PRACTICE.  WE HAVE INSTITUTED AN INSPECTION OF ALL BLADD	ER MACHINES TO DOCUMENT PATCHED TANKS AND PUT THEM ON A 12 MONTH INSPECTION.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003102000185	20031020	00185	WP  	2003	10	20	CA030903005      	1	20030818	G	6520	369D25146	BEARING         			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20R2    	 	GL  					M/R TRANSMISSION	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AS DESCRIBED ABOVE ROLLER BEARING PN 369D25146 INNER RACE FAILURE. IN THIS CASE THIS FAILURE WAS DETECTED BY THE A	IRCRAFTS WARNING SYSTEM. THE AIRCRAFT WAS FOR CED TO MAKE AN UNSCHEDULED LANDING. THE FAILURE OF THIS P/N BEARING HAS BE	EN SEEN ON MORE THAN ONE OCCASION.  THIS PROBLEM NEEDS TO BE REVIEWED BY THE MANUFACTURER AND A CHECK OF THE BEARINGS TO	LERANCE ETC. BEFORE A MORE SERIOUS INCIDENT OCCURS.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003102000186	20031020	00186	EA  	2003	10	20	CA030903006      	1	20030827	G	2731	6009230165	ACTUATOR        			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					PITCH TRIM	FAILED          	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ATTEMPT TO TRIM  AIRCRAFT NOSE UP OR NOSE DOWN CAUSED BOTH PITCH TRIM CHANNELS TO INDICATE (OFF).  THUS HORIZONTAL	 PITCH TRIM SYSTEM DE-ACTIVATED.					2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2003102000193	20031020	00193	SO  	2003	10	20	CA030903007      	2	20030812	G	7310	6524323A1M	VALVE           			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	RT ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) PN 6524323A1M (FLOW DIVIDED) LEAKING FUEL AFTER ENGINE SHUT DOWN/NEW PART INSTALLED.						1	L	7	2 	3O	3	O	 	A23CE   	E8CE	5	C	P25EA	 
2003102000195	20031020	00195	EA  	2003	10	20	CA030903008      	1	20030705	G	2810	21564075	FUEL CELL       			CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT WING	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) FUEL LEAKING FROM RT WING FROM FRONT SPAR IN FRONT OF FUEL CELL NR 6 FUEL CELLS NR 6,7,8 REMOVED FROM A/C TO INSPE	CT FOR LEAKS.  NR 6, NR 7 FUEL CELL PRESSURE TESTED AND FOUND SERVICEABLE. NR 8 FUEL CELL PRESURE TESTED AND A HOLE WAS 	FOUND AT THE BOTTOM OF THE CELL.  NR 8 FUEL CELL PN 21564075 SN 72846 REMOVED AND CELL REPLACED. A/C REFUELED AND NO LEA	KS DETECTED OVERNIGHT. A/C RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2003102000196	20031020	00196	SW  	2003	10	20	CA030903009      	1	20030813	G	5302	206031329103	ATTACH FITTING  			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON SCHEDULED 100 HR INSPECTION, VISUAL INSPECTION OF TAILBOOM ATTACH FITTINGS.  UPPER LT AIRFRAME FITTING FOUND CR	ACKED.  UPON FURTHER INVESTIGATION AFT AIRFRAME BULKHEAD FOUND CRACKED AT UPPER LT LOCATON.   SUSPECTED CAUSE LONG IDLE 	TIMES AT 60 PERCENT  N1 AND HEAVY SLING LOADS.   MANUFACTURING DEFECTS POSSIBLY A FACTOR ALSO.   SHORTEN IDLE TIMES TO O	NLY NECESSARY COOL DOWN AND WARM UP TIMES.   WHEN IDLING FOR PERIODS OF TIME, USE 70 PERCENT N1.			1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003102100002	20031021	00002	EA  	2003	10	21	CA030903010      	1	20030812	G	2810	215640024	FUEL CELL       			CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION OF RT WING FUEL LEAKING FROM SPAR AREA IN FRON OF CELL NR 6 ON OUTBOARD SIDE OF ENGINE NACELLE.  N	R 7 FUEL BLADDER SN 72863 PN 215-64002-4 FROM HOLE IN THE BOTTOM OF THE BLADDER CELL REPLACED, A/C REFUELED,  LEAK CHECK	ED OK.  A/C RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2003102000197	20031020	00197	EA  	2003	10	20	CA030903011      	1	20030826	G	2810	21564002	FUEL CELL       			CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF*       	NE  	RT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FUEL LEAK DETECTED RT WING.  CELL NR S POSITION 1,2,3,4,5, REMOVED FOR TESTING.CELLS NR 1,2 TESTED OK AND REINSTAL	LED CELL NR 3 PN 21564002-4 S NR 72862 TESTED DEFECTIVE AND REPLACED. CELL NR 4 PN 21564002 S NR 72826 TESTED DEFECTIVE 	AND REPLACED. CELL NR 5 PN 21564002-6 S NR  72856 TESTED DEFECTIVE AND REPLACED. CELL NR 6 PN 21564002 SN  72848 TESTED 	DEFECTIVE AND REPLACED. A/C GROUND RUN AND LEAKED CHECK SERVICABLE.			2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2003102000198	20031020	00198	EA  	2003	10	20	CA030903012      	1	20030804	G	2810	215640024	FUEL CELL       			CNDAIR	CL215 	CL2156B11415	       	EA  										RIGHT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) RT FUEL CELL POSITION NR 7 REPLACED PN 215640024, SN 72562 REMOVED AND FOUND LEAKING.  CELL REPLACED A/C REFUELED 	AND LEAK TESTED OK. A/C RETURNED TO SERVICE.					2	H	7	2 	4T			RT	A14EA   					 
2003102000199	20031020	00199	EA  	2003	10	20	CA030903013      	1	20030828	G	2810	215640024	FUEL CELL       			CNDAIR	CL215 	CL2156B11415	       	EA  										LEFT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION LT WING WAS FOUND LEAKING. FUEL CELLS POSITION NR 4,  PN 215-640024,  SN 82119 TESTED DEFECTIVE AN	D REPLACED.POSITION NR 7,  PN 21564002 SN 72478 TESTED DEFECTIVE AND REPLACED.POSITION NR 8 PN 21564075 SN 75337 TESTED 	DEFECTIVE AND REPLACED.  REFUELED GROUND CHECKED SERVICEABLE.				2	H	7	2 	4T			RT	A14EA   					 
2003102000200	20031020	00200	WP  	2003	10	20	CA030903014      	1	20030823	G	2131		CONTROLLER      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					CABIN PRESSURE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) ON DEPARTURE YYZ, HAD A PRESSURE (PRESSURIZATION) BUMP, GAGES CHECKED NORMAL THROUGH 1000 FEET, HAD A CABIN ALT OF	 1000 FT. DIFFERENTIAL, PRESSURE OF 2.0 PSI. QRH FOLLOWED AND LANDED BACK TO YYZ.   A/C PRESSURIZED TO 8 PSI ON GROUND I	N MANUAL MODE, NO FAULT FOUND. MEL RAISED AND CLEARED BY THE ACCOMPLISHMENT OF BITE TEST ON BOTH CABIN PRESSURE CONTROLL	ERS, NIL FAULT FOUND.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2003102000201	20031020	00201	WP  	2003	10	20	CA030903015      	1	20030825	G	5241		SEAL            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					AFT GALLEY DOOR	FAILED          	W				B	I			EMER. DESCENT           	CABIN DEPRESSURIZATION  			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB FROM YQX, CABIN ALT. WAS ANNUNCIATED WITH MASTER WARNING. FLOW LITEWAS ON PRESSURE CONTROLLER. EMERGE	NCY DESXENT INITIATED AND LANDED BACK TO YQX.  AFT GALLEY DOOR ANNUNCIATED BRIEFLY DURING DESCENT.   AFT SERVICE DOOR SE	AL AND LATCHES CHECKED, DOOR CYCLED, AIRCRAFT PRESSURIZED ON GROUND AND NO LEAK NOTED, ANNUNCIATOR LIGHT OUT. AIRCRAFT R	ELEASED FOR FLIGHT.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2003102000202	20031020	00202	EA  	2003	10	20	CA030903016      	1	20030414	G	2810	21564002	FUEL CELL       			CNDAIR	CL215 	CL2156B11415	       	EA  										LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING WINTER MAINTENANCE IT WAS DISCOVERED THAT A/C HAD SOME AMOUNTS OF FUEL LEAKING FROM WINGS. 6 CELLS IN ALL W	ERE FOUND LEAKING ON THE LT WING.					2	H	7	2 	4T			RT	A14EA   					 
2003102000203	20031020	00203	SW  	2003	10	20	CA030903017      	1	20030824	G	2897	PT02E82P	CONNECTOR       			SWRNGN	SA226 	SA226TC     	8780404	SW  										RT BOOST PUMP	BURNED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) PILOT'S SELECTED RT MAIN BOOST PUMP ON AND CIRCUIT BREAKER POPPED. CIRCUIT BREAKER POPPED AGAIN AND WAS LEFT ALONE	 FOR REMAINDER OF FLIGHT. THE BOOST PUMP WAS REMOVED AND FOUND THAT THE CONNECTOR ON THE PUMP AND THE AIRFRAME WIRING HA	D SHORTED INTERNALLY. CONNECTOR AND BOOST PUMP WAS REPLACED.				2	L	7	2 	4T			RT	A8SW    					 
2003102000204	20031020	00204	NM  	2003	10	20	CA030904001      	1	20030831	G	2434	11521062	STARTER GEN     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 1	FAILED          	W				O				OTHER                   				B	O		SMOKE/FUMES/ODORS/SPARKS  	OTHER                     		AP	APPROACH       	1			CA											(CAN) NR 1 DC STARTER- GENERATOR SHAFT SHEARED ON APPROACH.  PASSENGERS NOTICED SPARKS COMING FROM THE NACELLE.  THE INT	ENSE HEAT DISCOLOURED AND BLISTERED THE PAINT AND WARPED THE COMPOSITE AROUND THE GENERATOR EXHAUST OUTLET.  STARTER-GEN	ERATOR REPLACED, COWL REPLACED.  A/C RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003102000205	20031020	00205	NM  	2003	10	20	CA030904002      	1	20030824	G	5280	83231027001	CONNECTING ROD  			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FWD MLG DOOR	BROKEN          	W				O				OTHER                   				J	O		WARNING INDICATION        	OTHER                     		CR	CRUISE         	1			CA			27532								(CAN) LT MLG DOOR LIGHT ILLUMINATED IN FLIGHT. CREW WITNESSED FWD MLG DOOR WAS OPEN. LANDING COMPLETED WITHOUT INCIDENT.	 UPON INSPECTION BY ENGINEERING IT WAS FOUND THAT THE FWD MLG DOOR CONNECTING ROD ASSY HAD SHEARED. THE CONNECTING ROD W	AS REPLACED AND AN OPERATION CHECK PERFOR MED ON THE MLG SYSTEM.  AIRCRAFT WAS RELEASED BACK INTO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102000211	20031020	00211	NE  	2003	10	20	CA030904003      	2	20030728	G	8520	10992	LINK            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					ENGINE	BROKEN          	W				A				UNSCHED LANDING         				P	Y		NO WARNING INDICATION     	ENGINE STOPPAGE           		CR	CRUISE         	1			CA											(CAN) THE AIRCRAFT WAS IN CRUISE FLT WHEN THE ENGINE ABRUPTLY FAILED. THE AIRCRAFT CARRIED OUT AN UNSCHEDULED LANDING. M	AINTENANCE DISCOVERED A BROKEN LINK ROD AND THE ENGINE WAS REPLACED.					1	H	7	1 	3R	3	R	 	A815    	E142				 
2003102000212	20031020	00212	EA  	2003	10	20	CA030904004      	1	20030814	G	3211	TBC6U11373	BLOCK           			DHAV  	DHC6  	DHC6        	2802606	EA  										MLG	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) REBOUND BLOCKS FOUND TO HAVE WRONG THREAD. BLOCKS CAN BE REPAIRED. REPAIR FOUND TO BE MINOR. PAPER TRAIL FOLLOWED 	TO EXACT POINT DEFECT OCCURRED. ALL BLOCKS, BY S/N LOCATED. A FIELD REPAIR AND SB CURRENTLY BEING DEVELOPED. WILL BE ISS	UED TO CUSTOMERS WITH THE SN'S LISTED. PROCESS SHEETS AND INSPECTION CRITERIA CHANGED TO PREVENT REOCCURRENCE.				1	H	7	2 	3T			RT	A9EA    					 
2003102000214	20031020	00214	EA  	2003	10	20	CA030904005      	1	20030814	G	3211	TBC6U11373	BLOCK           			DHAV  	DHC6  	DHC6        	2802606	EA  										MLG	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) REBOUND BLOCKS FOUND TO HAVE WRONG THREAD. BLOCKS CAN BE REPAIRED. REPAIR FOUND TO BE MINOR. PAPER TRAIL FOLLOWED 	TO EXACT POINT DEFECT OCCURRED. ALL BLOCKS, BY S/N LOCATED. A FIELD REPAIR AND SB CURRENTLY BEING DEVELOPED. WILL BE ISS	UED TO CUSTOMERS WITH THE SN'S LISTED. PROCESS SHEETS AND INSPECTION CRITERIA CHANGED TO PREVENT REOCCURRENCE.				1	H	7	2 	3T			RT	A9EA    					 
2003102000257	20031020	00257	NM  	2003	10	20	CA030905001      	1	20030902	G	2740	6355B000103	ACTUATOR        			BOEING	737   	737*        	       	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					STAB TRIM	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) CREW REPORTED AT CRUISE, STAB OUT OF TRIM WARNING LIGHT ILLUMINATED. CREW FOLLOWED NON NORMAL CHECKLIST. THEY WERE	 UNABLE TO RE-CONNECT AUTO PILOT IN EITHER 'A' OR 'B' COMMAND. A/C WOULD NOT RESPOND TO MAIN ELECTRIC TRIM. CREW RESORTE	D TO MANUAL TRIM. CREW CONTACTED MCC AND WERE INSTRUCTED TO PULL ASSOCIATED CIRCUIT BREAKERS FOR MAIN ELECTRIC TRIM (NO 	CHANGE).  A/C LANDED UNEVENTFULLY, NO EMERGENCY WAS DECLARED.  MAINT INSP DISCOVERED MAIN ELECTRIC MOTOR HAD FAILED. POW	ER WAS AVAILABLE TO MOTOR. WHEN MOTOR WAS REMOVED FROM THE GEARBOX,  TRIM WHEELS WERE FREE TO TURN. MAINTENANCE REPLACED	 STAB TRIM MOTOR, SYSTEM GROUND CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.	2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2003102000227	20031020	00227	EA  	2003	10	20	CA030905002      	1	20030903	G	2120	601R9500115305	ODOR            			CNDAIR	CL600 	CL6002B19   	1900309	EA  										ECS SYSTEM	DETECTED        	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) WHILE CLIMBING TO FLIGHT LEVEL 360 THE CREW NOTICED A VERY STRONG ODOR INDICATIVE OF EITHER AN ECS SYSTEM OVERHEAT	ING OR ELECTRICAL FIRE. THE ECS & ELECTRICAL SYNOPTIC PAGES SHOWED NO ANOMALIES.  THE ODOR INCREASED IN INTENSITY AND TH	E CREW DECLARED AN EMERGENCY,  THEN PROCEEDED WITH A HIGH SPEED DESCENT.  THE ODOR SIGNIFICANTLY DECREASED AT LOWER ALTI	TUDES AND THE AIRCRAFT LANDED WITHOUT FURTHER OCCURENCES.  UPON SHUT DOWN, THE CAPTAIN & FIRE CHIEF OPENED THE AFT EQUIP	MENT BAY AND EXPERIENCED THE SAME ODOR THAT WAS PRESENT DURING THE FLIGHT,  BUT ONLY STRONGER.  AFTER THE ECS SYSTEM WAS	 TESTED PER FTP 601R2103 WITH NO FAULT FOUND. THE WATER SEPARATOR BAGS WERE VERIFIED FOR CONTAMINATION AND NONE FOUND.	2	L	7	2 	4F			RT	A21EA   					 
2003102000228	20031020	00228	NE  	2003	10	20	CA030905003      	2	20030803	G	8520		ENGINE          			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					NACELLE	FAILED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE AIRCRAFT WAS IN CRUISE FLIGHT A LOUD BANG WAS HEARD. THE PILOT CARRIED OUT AN UNSCHEDULED LANDING. THE AIRCRAF	T WAS CHECKED BY MAINTENANCE AND THE OIL SCREEN WAS FOUND TO HAVE METAL PARTICLES. THE AIRCRAFT WAS FLOWN TO A MAINTENAN	CE FACILITY WHERE THE ENGINE WAS REPLACED.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003102000230	20031020	00230	CE  	2003	10	20	CA030905004      	1	20030830	G	3234	1013841377	SELECTOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) AIRCRAFT WENT ON LOCAL FLIGHT, WHEN GEAR SELECTED DOWN ON PREPARATION FOR LANDING GEAR DID NOT GO DOWN, CREW MANUA	LLY PUMPED GEAR DOWN AND RECEIVED 3 GREEN INDICATION. AFTER LANDING, AIRCRAFT WAS PLACED ON JACKS AND GEAR SWINGS CARRIE	D OUT. GEAR FUNCTIONED CORRECTLY ON FIRST 7 RETRACTION/EXTENSION CYCLES. ON EIGHTH EXTENSION GEAR DID NOT START TO EXTEN	D. GEAR HANDLE 'JIGGLED' IN DOWN POSITION AND GEAR OPERATED AT THIS POINT.NEW SELECTOR ASSEMBLY INSTALLED GEAR RE-SWING 	NUMEROUS TIMES AND FOUND TO OPERATE NORMALLY.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003102000231	20031020	00231		2003	10	20	CA030905005      	4	20030905	G	3416		ALTIMETER       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	STUCK           	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA											(CAN) DURING A PITOT/STATIC CHECK,, IT WAS FOUND THAT THE BAROMETRIC SCALE, ON THE CAPTAIN'S ENCODING ALTIMETER, WOULD N	OT MOVE WITH THE ADJUSTMENT KNOB. ALTIMETER POINTERS WOULD MOVE WHEN BAROMETRIC ADJUSTER WAS TURNED, HOWEVER THE SCALE I	NDICATING THE PRESSURE ADJUSTED TO, WOULD NOT MOVE. ALTIMETER REPLACED, PITOT/STATIC SYSTEM TESTED SERVICEABLE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003102000232	20031020	00232		2003	10	20	CA030905006      	4	20030905	G	3425	066031252500	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EFIS	BROKEN          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) CAPTAIN'S LOWER ELECTRONIC FLIGHT INSTRUMENT DISPLAY UNIT, (CATHODE RAY TUBE), WOULD FADE TO UNREADABLE LEVEL, DUR	ING LONG OPERATIONS. LOWER DISPLAY UNIT GIVE HSI AND COMPASS/GPS NAVIGATION INFORMATION WHICH WOULD BE LOST AFTER A FADE	 OUT. UNIT WOULD FUNCTION AGAIN AFTER A POWER SHUT DOWN AND UNIT WAS ALLOWED TO COOL. EFIS DISPLAY UNIT REPLACED AND SYS	TEM OPERATED NORMALLY.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003102000233	20031020	00233	WP  	2003	10	20	CA030905007      	1	20030827	G	5241		DOOR            			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					GALLEY	NOT CLOSED      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB FROM YYZ, 'CABIN ALT' WARNING LIGHT ON DUE TO 'AFT GALLEY DOOR OPEN'. QRH PROCEDURES CARRIED OUT AND 	AIRCRAFT LANDED BACK TO YYZ.  GALLEY DOOR FOUND IMPROPERLY CLOSED BY MAINTENANCE.  SEAL CLEANED AND AIRCRAFT PRESSURIZED	 ON GROUND, NO LEAK FOUND AND NO DOOR WARNING INDICATION.  TEST C/OUT IAW MM REF. 21-50-00.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004012600090	20040126	00090	EU  	2004	1	26	CA030905008      	1	20030902	G	3246	AH42883	WHEEL           			STBROS	SC7   	SC7SERIES3  	8100512	EU  	GARRTT	TPE331	TPE3312201A 	 	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	DAMAGED         	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF THE CREW HEARD A LOUD NOISE UPON SETTING MAX POWER.  AN IMMEDIATE REJECTED TAKEOFF WAS CARRIED OUT, DIR	ECTIONAL CONTROL WAS MAINTAINED, AND THE AIRCRAFT WAS STOPPED ON THE RUNWAY.  IB WHEEL HALF PN/AH 42883, S/N 994 AND CAL	IPER SUSTAINED DAMAGE.  ALTHOUGH THE WHEEL HALF IS NOT SUSPECTED THE CAUSE OF THIS REPORT, THE MFG SUGGESTS 12 MONTH OVE	RHAUL PERIODS ON WHEEL ASSEMBLY. THIS WHEEL HALF WAS NDT INSPECTED SEPT 17, 2002.			1	H	7	2 	3T	4	T	NT	A15EU   	E3WE	6	C	P15EA	 
2003102000234	20031020	00234	EU  	2003	10	20	CA030908001      	1	20030829	G	3260	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) THE AIRCRAFT WAS ON APPROACH AND THE NOSE GEAR GREEN LIGHT DID NOT COME ON, BOTH MAINS INDICATED GREEN.THE GEAR WA	S EXTENDED MANUALLY WITH THE HAND PUMP AND A N UNEVENTFUL LANDING CARRIED OUT. MAINTENANCE FOUND THE HYDRAULIC POWERPACK	 WAS NOT RUNNING DUE TO AN UNSERVICEABLE MOTOR RELAY R601.  THE RELAY WAS REPLACED AND THE SYSTEM FUNCTIONED PROPERLY. T	HE 974.09.26.112 RELAY IN QUESTION HAS BEEN FAILING IN THE PAST.  THIS IS THE 3RD INSTANCE THE SAME PART NUMBER RELAY HA	S FAILED, EITHER OPEN OR CLOSE. ONE PRIOR TO THIS FAILED OPEN AND WOULD NOT ALLOW THE PUMP TO RUN, AND THE ONE PRIOR TO 	THAT FAILED CLOSED AND THE PUMP RAN CONTINUOUSLY. PILATUS HAS BEEN NOTIFIED VIA A DEFECT REPORT.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003102000237	20031020	00237	SO  	2003	10	20	CA030908002      	1	20030902	G	2910	1771703	LINE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER TAXIIING THE AIRCRAFT FOR MAINTENANCE WE NOTICED HYDRAULIC FLUID ON THE FLOOR UNDER THE RT WING ROOT.  AFTER	 REMOVING THE BELLY PANEL FOR INSPECTION THE LEAK WAS FOUND TO BE LOCATED ABOUT 20 INCHES AFT OF THE LEADING EDGE OF THE	 RT WING WHERE THE LANDING GEAR HYDRAULIC EXTENSION LINE PN 1771703 IS CROSSED BY THE AILERON CABLE. INSUFFICIENT CLEARA	NCE BETWEEN THE HYDRAULIC LINE AND CABLE APPEAR TO HAVE ALLOWED FOR THE CABLE TO CHAFE THROUGH THE HYDRAULIC LINE. CLOSE	 CONSIDERATION WHILE INSPECTING THIS AREA SHOULD BE CARRIED OUT.		1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2003102000238	20031020	00238	NE  	2003	10	20	CA030908003      	2	20030828	G	8520		ENGINE          			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  						SEIZED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE SEIZED. INFLIGHT EMERGENCY UDE AT 1200 FT ASL. AIRCRAFT LANDED UNDAMAGED ON FLOATS.  OIL TANK LEVEL CONFIRM	ED AT 5 QAL. CAUSE UNKNOWN AT THIS TIME.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003102000240	20031020	00240	CE  	2003	10	20	CA030908004      	1	20030810	G	2420	1100718	ALTERNATOR      			BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HC92W	HC92WK2     	GL  	ENGINE	FAILED          	W				O				OTHER                   				H	H		ELECT. POWER LOSS-50 PC   	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA											(CAN) NOTICED NO CHARGE,  MINIMIZED ELECTRICAL LOAD TURNED OFF ALTERNATORS RESET ON CHANGED RELAY LT TO RT.  NO CHARGE T	URNED MASTER OFF, 25 MILES FROM AIRPORT, TURNED MASTER ON AND 1 RADIO GOT ATIS AND CALLED TOWER LOST ALL POWER, CALLED T	OWER ON CELL DID A MANUAL GEAR EXTENSION AND FLY BY TOWER TO CONFIRM GEAR DOWN THEN JOINED CIRCUT AND LANDED.				1	L	7	2 	3O	3	O	 	3A16    	1E10	5	C	P16EA	 
2003102000242	20031020	00242	CE  	2003	10	20	CA030908005      	1	20030826	G	2434	E54118	BRUSHES         	CESSNA      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ALTERNATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						8010181					(CAN) PREMATURELY WORN FIELD BRUSHES, SHORTED FIELD CIRCUIT FAILING ALTERNATOR, VOLTAGE REGULATOR AND OVERVOLTAGE SENSOR	.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003102000245	20031020	00245	EA  	2003	10	20	CA030908007      	1	20030903	G	2435	BC09100	BEARING         	LUCAS       		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	STARTER-GEN	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CL	CLIMB          	1			CA						1510					(CAN) TWO MIN AFTER TAKEOFF THE  NR 3 DC STARTER-GEN FAILED, THE GENERATING SYSTEM WAS SHUTDOWN. MAINTENANCE FOUND THAT 	THE STARTER MODE FUNCTIONING OK. AFTER TROUBLESHOOTING THE STARTER-GENERATOR WAS REPLACED DUE TO HEAVY BRUSH WEAR AND TH	E BEARING WAS FAILING. THIS UNIT HAD 1385.9 HRS SINCE BEARING CHECK / BRUSH REPLACEMENT.				2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2003102000247	20031020	00247	EA  	2003	10	20	CA030908008      	1	20030903	G	2435	BC09101	SHAFT           	LUCAS       		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	STARTER-GEN	SHEARED         	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA						1372					(CAN) SHORTLY AFTER TAKEOFF THE NR 3 DC GEN LIGHT CAME ON, THE SYSTEM WAS DEACTIVATED. AFTER ABOUT FIVE MINUTES THE NR 3	 DC GEN HOT LIGHT CAME ON FOR ABOUT 20 SECONDS. FOR TROUBLESHOOTING WE ATTEMPTED TO START THE NR 3 ENG, WHICH KNOCKED TH	E GROUND POWER UNIT OFF LINE AND BURNED OUT THE GROUND POWER LIMITER. DURING THE REMOVAL OF THE STARTER-GEN WE FOUND THE	 STARTER DISCOLOURED FROM THE HEAT AND WHEN THE STARTER WAS PULLED AWAY FROM THE ENG, THE SHAFT PULLED OUT OF IT. THE ST	ATOR HAD SHEARED OFF OF THE SHAFT.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2004010800001	20040108	00001	EA  	2004	1	8	CA030908009      	1	20030827	G	7500	C6VW10263	DUCT            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BLEED AIR	DAMAGED         	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) RT BLEED AIRS LINE RUPTURED IN THE BRADED FLEX AREA. THE BLEED AIR THEN MELTED THE WIRE BUNDLE RUNNING FROM THE EN	GINE INTO THE WING. THE ONLY INDICATION WAS THAT THE BETA BACKUP SYSTEM MALFUNCTIONED. ALL THE WIRES EXCEPT FOUR HAD DAM	AGE WHEN REMOVED.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003102000248	20031020	00248	CE  	2003	10	20	CA030908010      	1	20030827	G	7922	723747	RELIEF VALVE    	STWARNER    		BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					OIL COOLER	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA						2769					(CAN) LT ENGINE OIL TEMP WENT INTO THE YELLOW ON CLIMB OUT. PILOT DID A PRECAUTIONARY SHUTDOWN OF THE ENGINE AND RETURNE	D TO THE AIRPORT.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003102000250	20031020	00250	EA  	2003	10	20	CA030909001      	2	20030831	G	8530	CON008046305	CYLINDER HEAD   			GRUMAV	S2    	TS2A        	3951110	SO  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	ENGINE	SEPARATED       	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED THAT THE LT ENGINE WAS RUNNING ROUGH. DURING INVESTIGATION BY MAINTENANCE CREW IT WAS DISCOVERED TH	AT BOTH NR 2 AND NR 8 CYLINDER HEADS WERE SEPERATING FROM THE BARREL. ONE CYLINDER HAD A SLIGHT OIL LEAK EVIDENT AND THE	 OTHER AN AIR COULD BE FELT IN THE AREA OF SEPERATION. THE CYLINDERS WERE REPLACED WITH SERVICEABLE ASSEMBLIES AND THE A	IRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4O	4	R	RT	EXPA2H72	E259	6	C	P8879	 
2003102000251	20031020	00251	SW  	2003	10	20	CA030909002      	1	20030907	G	2913	MS28775314	O-RING          			AIRTRC	AT802 	AT802A      	0390308	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  					MLG	TORN            	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT 1 HYDRAULIC PUMP LIGHT ILLUMINATED INDICATING LOW HYDRAULIC FLUID LEVEL. THE LANDING GEAR WAS EXTEND	ED NORMALLY AND THE AIRCRAFT RETURNED TO THE AIRPORT FOR A NORMAL LANDING. DURING INVESTIGATION THE MAINTENANCE CREW FOU	ND A HYDRAULIC LEAK IN THE RT FLOAT MLG. THE O-RING WAS REPLACED AND A GEAR RETRACTIONTEST WAS COMPLETED. THE AIRCRAFT W	AS RETURNED TO SERVICE.			1	L	7	1 	3T	4	T	NC	A19SW   	E4EA				 
2003102000253	20031020	00253	CE  	2003	10	20	CA030909003      	1	20030808	G	3242	215286	STATOR          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT BRAKE ASSY	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) STATOR BROKEN ON RT BRAKE ASSY.  IN REFERENCE TO A PREVIOUS SDR CA20030812005 SUBMITTED FOR ALT BRAKE FAILURE ON S	AME A/C, THE RT BRAKE WAS REMOVED FOR CLOSER INSPECTION DURING AN UNRELATED PHASE INSPECTION.THE R/H BRAKE WAS ALSO FOUN	DTO HAVE A BROKEN / CRACKED STATOR WHICH MAY HAVE LED TO ANOTHER PREMATURE BRAKE FAILURE.THE BRAKE ASSY WAS REMOVED AND 	TAGGED UNSERVICEABLE.BRAKE PN 215286, S/N0753R. THIS BRAKE WAS APPROX. INTO ITS LIFE.  ACCORDING TO THE WEAR INDICATORS 	ON THE BRAKE ASSY, THERE WAS 150-200 CYCLES REMAINING ON THE BRAKE.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003102000259	20031020	00259	CE  	2003	10	20	CA030910001      	1	20030903	G	2612	99120363	FIRE LOOP       			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT ENGINE	CHAFED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE FIRE DETECTION SENSOR LOOP ON THE LT ENGINE WAS FOUND CHAFING ON THE REAR TOP BRACKET (SUPPORT AFT OF ENGINE C	OVER) DURING PHASE 1,2,3, & 4 INSPECTION. THE LOOP RESISTANCE MEASURED BEYOND LIMITS AND WAS REPLACED. WEAR DAMAGE ON TH	E BRACKET WAS REPAIRED AS PER AC43131B.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003102000261	20031020	00261	EA  	2003	10	20	CA030910002      	1	20030905	G	5230	HSP115P0941400	PIN             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					CARGO DOOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THROUGH 15,000 FT CARGO DOOR CAUTION MESSAGE CAME ON. PRESSURIZATION NORMAL. PIN FOUND SHEARED ON LAT	CH TO STOW DOOR HANDLE. PIN REPLACED CHECKS SERVICABLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003102000262	20031020	00262	NE  	2003	10	20	CA030910003      	2	20030904	G	7200		ENGINE          			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  						FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) THE ENGINE HAS BEEN REMOVED FOR TEARDOWN TO DETERMINE THE CAUSE OF THE PROBLEM.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102000263	20031020	00263	SW  	2003	10	20	CA030910004      	1	20030717	G	5320	205030163095	SPAR CAP        			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					ENGINE BAY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE DOING A ROUTINE INSPECTION, A 15 INCH CRACK WAS FOUND IN THE ENGINE DECK AT ITS FORWARD END UNDER THE TRANSM	ISSION TAIL ROTOR OUTPUT AREA. FURTHER INVESTIGATION WAS CARRIED OUT AND FOUND THAT THE SPAR CAP WAS CRACKED. UPON DISSA	MBLY FOR THE CAP REPLACEMENT A 13' CRACK WAS FOUND IN THE WALL PN 205030169411. TH E SPAR CAP AND ENGINE DECK ASSY'S WER	E REPLACED WITH NEW PARTS AND THE WALL ASSY WAS REPAIRED AS PER A BELL HELICOPTER APPROVED REPAIR SCHEME. THE REPAIR WAS	 CARRIED OUT BY A APPROPRIATLY RATED AMO.		1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2003102000264	20031020	00264	NM  	2003	10	20	CA030910005      	1	20030902	G	2612	87858201	CONNECTOR       	KIDDE       		BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					UPPER FIRE LOOP	WEAK            	W				F	E			ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         			N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA						3236					(CAN) BOTH THE UPPER FIRE LOOP AND CONNECTOR RESISTANCE VALUES WERE BEYOND LIMITS. BOTH WERE REPLACED.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102000281	20031020	00281	NM  	2003	10	20	CA030910006      	1	20030902	G	2612	87858201	CONNECTOR       	KIDDE       		BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					UPPER FIRE LOOP	WEAK            	W				F	E			ACTIVATE FIRE EXT.      	ENGINE SHUTDOWN         			N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA						3236					(CAN) BOTH THE UPPER FIRE LOOP AND CONNECTOR RESISTANCE VALUES WERE BEYOND LIMITS. BOTH WERE REPLACED.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102000286	20031020	00286	EU  	2003	10	20	CA030910007      	1	20030815	G	2910	SC5083	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYD SYSTEM	UNSERVICEABLE   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING GRD CHECKS AT IDLE & FLIGHT IDLE,  CYCLIC CONTROL MOVING UNCOMMANDED LT & FORWARD.  CYCLIC CONTROL WOULD CO	NTACT  STOP, AFTER 1-2 SECONDS IT COULD BE BROUGHT BACK TO CENTER POSITION & APPEARED NORMAL.  MOVEMENT COULD BE DUPLICA	TED ON SUBSEQUENT RUNS, FORWARD & LT UNCOMMANDED & WITH SUBSTANTIAL FORCE REQUIRED TO HOLD CYCLIC IN NEUTRAL POSITION. A	FTER TROUBLESHOOTING & WITH STAFF PRESENT,  IT WAS DETERMINED ONE LATERAL HYD SERVO WAS CAUSING LT FWD MOVEMENT ON CYCLI	C CONTROL. BOTH LATERAL SERVO'S REPLACED WITH REPAIRED UNITS. THIS CAUSED AN AFT & RT MOVEMENT ON CYCLIC.  FINAL FIX WAS	 TO REPLACE RT SERVO ONLY & REINSTALL ORIGINAL LT SERVO. SUBSEQUENT RUNS ACHIEVED NO UNCOMMANDED MOVEMENTS LT OR RT.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003102000287	20031020	00287	NE  	2003	10	20	CA030910008      	2	20030814	G	7250	70BM055420	MODULE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ENGINE MAKING METAL INVESTICATION LED US TO BELIEVE METAL COMING FROM MO5 MODULE. REPLACED MODULE AND NO LONGER MA	KING METAL.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003102000289	20031020	00289	CE  	2003	10	20	CA030910009      	1	20030908	G	3233	508202085	ACTUATOR        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  					NLG	NOISY           	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) DURING LANDING GEAR EXTENSION THE NOSE GEAR ACTUATOR MADE A LOAD SCREECH NOISE. THE ACTUATOR WAS REPLACED AND THE 	GEAR SWINGS PERFORMED NORMALLY.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003102000291	20031020	00291	EU  	2003	10	20	CA030910010      	1	20030812	G	6510	350A35105901	FLEX COUPLING   			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					T/R DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION,  A SMALL MARK, SLITE DENT WAS FOUND ON THE OUTER DISC OF THE FLEX COUPLING FURTHER INVE	STIGATION FOUND THAT THIS DENT HAD SET UP A STRESS RISER IN WHICH HAD CAUSED THE DISC TO CRACK THE COUPLING WAS REPLACED	 WITH NEW PARTS AND RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003102000296	20031020	00296	EU  	2003	10	20	CA030911001      	1	20030910	G	2710	31055150	SERVO           			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2*    	 	GL  					AILERON	JAMMED          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI ,THE ECAM MESSAGE  AILERON BLUE SYSTEM JAM CAME ON UPON THE FLIGHT CONTROL CHECK BY THE FLIGHT CREW. P	ROCEDURE PERFORMED AS PER CHECK LIST AND THE AIRCRAFT RETURNED TO THE GATE DUE TO HARD DEFLECTION OF CONTROL WHEEL AND U	NABLE TO DETERMINE MOVEMENT OF RT AILERON. TROUBLE SHOOTING CONFIRMED THE RT AILERON SERVO AT FAULT. SERVO ASSY WAS REPL	ACED AND THE AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENT. UNIT ROUTED TO THE VENDOR FOR STRIP REPORT.			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2003102000299	20031020	00299	EU  	2003	10	20	CA030911002      	1	20030911	G	2910	AC67244	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					HYDRAULIC	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PILOT CONDUCTED PREFLIGHT CHECK AND ON AIRCRAFT RUN UP COMPLIED WITH THE INTENT OF AD CF 200315R1. DURING THE TEST	 UPON DEPLETION OF THE HYDRAULIC SYSTEM ACCUMULATORS, CYCLIC MOVED TO THE LT FWD QUADRANT UNCOMMANDED. THE TEST WAS REPE	ATED 12 TIMES AT BOTH GROUND AND FLIGHT IDLE AND EVERY CHECK CONCLUDED IN THE SAME UNCOMMANDED CYCLIC MOVEMENT. RT LATER	AL SERVO WAS ISOLATED AS BEING THE CAUSE OF THE UNCOMMANDED CYCLIC MOVEMENT AND REPLACED. THE AD WAS AGAIN PERFORMED AND	 THE A/C CONTROLS AND HYDRAULIC SYSTEM FUNCTIONED NORMALLY.		1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003102000300	20031020	00300	NE  	2003	10	20	CA030911003      	2	20030730	G	8530		PUSHROD TUBE    			DOUG  	A26   	A26CSHIELDS 	3020506	WP  	PWA   	R2800 	R280079     	52026	NE  					RT ENGINE	CHAFED          	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT AFTER BOMB RUN OIL NOTICED ON NACELL OF RT ENGINE. PRECAUTIONARY ENGINE SHUT DOWN COMPLETED, A/C LAND	ED WITHOUT INCIDENT.BREASEWAY FOUND TO HAVE CHAFED SMALL HOLE IN CYLINDER NUMBER 15 EX. PUSH ROD TUBE. PUSH ROD TUBE REP	LACED BREASEWAY SECURED AND A/C RETURNED TO SERVICE.				2	M	7	2 	4R	4	R	 	L34     	5E8				 
2003102100003	20031021	00003	SO  	2003	10	21	CA030911004      	1	20030819	G	5744	89W121CSM100121	HINGE           			GRUMAV	S2    	S2F         	3951006	SO  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	LT AILERON	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AIRCRAFT PERFORMED FIREBOMBING MISSION. UPON RETURN, THE PILOT COMPLAINED OF FLUTTER IN THE CONTROLS. INITIAL INSP	ECTION REVEALED NO DAMAGE. FURTHER IN-DEPTH DETAILED INSPECTION REVEALED A BROKEN LT WING INBOARD AILERON HINGE. DUE TO 	THE CONDITION OF THE HINGE, IT WAS DETERMINED TO HAVE HAPPENED SOME TIME BEFORE. BECAUSE IT COULD NOT BE DETERMINED WHEN	 THE FAILURE OCCURRED, BOTH HINGES WERE REPLACED DUE TO POTENTIAL STRESS THE BREAKAGE APPLIED ON THE UNDAMAGED HINGE. TH	E AILERON HINGES WERE NDT'ED 315.9 HOURS PREVIOUS DURING THE AIRCRAFT'S AIRFRAME EXTENSION PROGRAM.		2	H	7	2 	4O	4	R	RT	EXPA2H72	E259	6	C	P8879	 
2003102100004	20031021	00004	CE  	2003	10	21	CA030912001      	1	20030908	G	7120	121343317	MOUNT           			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS IN RADIUS OF ENGINE MOUNT SUPPORT						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2003102100005	20031021	00005	WP  	2003	10	21	CA030912002      	1	20030813	G	6210		PIN             	DOUG        		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0098848032					(CAN) PIN FAILURE, SHEARED AT TOP THREAD OF THREADED SHANK FOR ADJUSTER NUT. CHIEF ENGINEERS COMMENTS: THIS IS THE SECON	D PIN TO SHEAR ON THIS AIRCRAFT, SEEMS BOTH PINS WERE MANUFACTURED ATABOUT THE SAME TIME.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003102100006	20031021	00006		2003	10	21	CA030912003      	4	20030728	G	8300	107010101	GEAR            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ACCESSORY G/B	FAILED          	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) A/C PERFORMING NORMAL APPROACH. DURING FINAL, A LIGHT WHINING SOUND HEARD AS POWER APPLIED. AS POWER INCREASED, SO	UND INCREASED. AT APPROX 8 FT FROM TOUCHDOWN, ENG STOPPED, & CHIP CAUTION LIGHT ILLUMINATED. CONTROL MAINTAINED HELICOPT	ER LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED ENG OIL LOW. MAG CHIP DETECTOR REMOVED & FOUND SILVER METAL PARTICLES	. OIL FROM GEARBOX COLLECTED & FOUND TO CONTAINED SILVER & BLACK METAL PARTICLES UP TO 1/16  IN DIAMETER. ENGINE REMOVED	 FROM SERVICE & RENTAL ENGINE INSTALLED. A/C RETURNED TO SERVICE. FAILED ENG SENT IN FOR EVAL & REPAIR. PRELIMINARY INVE	ST REVEALED ACCESSORY DRIVEN GEAR FAILED & BROKE IN TWO. PRIMARY REASON FOR GEAR FAILURE UNDER INVESTIGATION BY NTSB.	1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2003102100007	20031021	00007	SO  	2003	10	21	CA030912004      	1	20030907	G	3232	89H10528	ACTUATOR        			GRUMAV	S2    	S2F         	3951006	SO  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	MLG DOOR	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AIRCRAFT DEPARTED ENROUTE TO A FIRE. PILOT OF ANOTHER AIRCRAFT IN THE GROUP NOTICED RT MLG DID NOT FULLY RETRACT A	ND GEAR DOORS DID NOT CLOSE. THE GEAR WAS CYCLED BUT NO CHANGE SO AIRCRAFT FLEW AND LANDED WITHOUT INCIDENT. MAINTENANCE	 CREW REPLACED THE MLG DOOR ACTUATOR, A GEAR SWING WAS COMPLETED AND THE AIRCRAFT WAS RETURNED TO SERVICE.				2	H	7	2 	4O	4	R	RT	EXPA2H72	E259	6	C	P8879	 
2003102100008	20031021	00008	SO  	2003	10	21	CA030912005      	1	20030909	G	2913	1213HBG310A	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					HYD SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING OPERATIONAL CHECK OF HYDRAULIC SYSTEM FOUND RT HYDRAULIC PUMP LANDING GEAR SELECTION HANDLE WON'T RETURN TO	 NEUTRAL POSITION WITHIN POINTED IN MM PERIOD OF TIME ( THREE TO NINE ) SECONDS. THE PUMP WAS IN SERVICE FOR 177.3 HRS S	INCE NEW.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003102100009	20031021	00009	SW  	2003	10	21	CA030915001      	1	20030908	G	6310	CL422501	CAGE            	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					SPRAG CASE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BLA2684					(CAN) SPRAG CAGE CRACKED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003102100010	20031021	00010	CE  	2003	10	21	CA030915002      	1	20030912	G	2750	26620185	TUBE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TE FLAP CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ROD CONNECTING THE LT AND RT FLAP BELLCRANKS WAS FOUND WORN WHERE IT PASSES OVER THE PASSENGER READING LIGHT M	OUNTING BRACKET ON THE LT SIDE OF THE CABIN. TWO WEAR MARKS WERE NOTED. THE WEAR CORRESPONDING TO THE FLAP UP POSITION W	AS THE DEEPEST WITH THE SECOND ONE AT BEING AT THE FULL DOWN FLAP SETTING. THE FLAP SYSTEM WAS DETERMINED TO BE INSTALLE	D AND RIGGED CORRECTLY BUT POSITIONING OF THE READING LIGHT BRACKET CAUSED INSUFFICIENT CLEARANCE			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003102100011	20031021	00011	EA  	2003	10	21	CA030915003      	1	20030714	G	5521	C2TE37ND	SPAR            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT & RT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT ELEVATOR FRONT SPAR UPPER ATTACH HOLES FOR CENTER HINGE POSITION HAS A SMALL CRACKS AROUND THE UPPER AN3	 BOLT HOLE.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003102100012	20031021	00012	EA  	2003	10	21	CA030915004      	1	20030807	G	5521	C2TE37ND	SPAR            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT ELEVATOR FRONT SPAR UPPER ATTACH HOLE FOR CENTRE HINGE POSITION HAS A SMALL CRACK(S) AROUND THE UPPER AN	3 BOLT HOLE.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003102100013	20031021	00013	EA  	2003	10	21	CA030915005      	1	20030807	G	5521	C2TE37ND	SPAR            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT ELEVATOR FRONT SPAR UPPER ATTACH HOLE FOR CENTRE HINGE HAS A SMALL RADIAL CRACK AROUNG THE UPPER AN3 BOLT HOLE.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003102100014	20031021	00014	CE  	2003	10	21	CA030915006      	1	20030905	G	5711	05233151	SPAR            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT WING FORWARD UPPER SPAR PLATE HAS SEVERAL AREAS OF EXHALATION. PART REPLACED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003102100015	20031021	00015	EA  	2003	10	21	CA030915007      	1	20030913	G	5280	CC67010520	DOOR            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					MLG	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) THE RT MLG DOOR WAS FOUND MISSING ON POST FLIGHT INSPECTION. DAMAGE WAS FOUND ON THE FUSELAGE, RT INBOARD FLAP AND	 WING LOWER SKIN. REPAIR SCHEM WILL BE GIVEN F OR THE FUSELAGE AND THE FLAP.					2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003102100016	20031021	00016	SW  	2003	10	21	CA030915008      	1	20030907	G	6310	205040176101	BOOT            	BELL        		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					M/R DRIVE	TORN            	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA						A202038					(CAN) DURING THE INSPECTION AFTER THE LAST FLIGHT OF THE DAY, THE ENGINEER INSPECTED THE MAIN DRIVESHAFT BOOTS FOR LEAKA	GE. THERE WAS NO VISUAL SIGN OF A GREASE LEAKAGE. AS THE ENGINEER PUT HIS HAND UNDER THE, ENGINE SIDE,  DRIVESHAFT COUPL	ING, HE FELT A BUILT UP OF GREASE IN THE PARTICLE SEPARATOR BOOT TUNNEL. THE DRIVESHAFT WAS REMOVED AND THE INSPECTION O	F THE BOOT REVEALED THAT THE RUBBER OF THE BOOT HAD SEPARATED APPROXIMATELY 80 PERCENT CIRCUMFERENTIAL FROM ITS METAL RI	NG. THE DRIVESHAFT WAS REPLACED.		1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2003102100017	20031021	00017	EA  	2003	10	21	CA030915009      	2	20030904	G	7314	025323101	PUMP            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUEL SYSTEM	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WHILE CLIMBING AFTER TAKEOFF, NOTICED LOSS OF TORQUE AND OIL PRESSURE. SECURED THE LT ENGINE. FAILURE TROUBLE SHOT	 TO LOSS OF FUEL FLOW. HIGH PRESSURE FUEL PUMP AND FUEL CONTROL UNIT REMOVED AND EXAMINED. FOUND THE INPUT GEAR OF THE P	UMP HAD STRIPPED SPLINES AND REPLACED HIGH PRESSURE FUEL PUMP WITH OVERHAULED UNIT AND REASSEMBLED ENGINE. ENGINE GROUND	 RUN SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. TEAR DOWN REPORT ON FAILED UNIT WILL BE REQUESTED FROM OVERHAUL SHOP.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003102100018	20031021	00018	CE  	2003	10	21	CA030915010      	1	20030908	G	7120	121343317	MOUNT           			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS IN RADIUS OF ENGINE MOUNT SUPPORT.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003102100019	20031021	00019	EU  	2003	10	21	CA030915011      	1	20030909	G	5312	07125033	BULKHEAD        			REIMS 	182   	F182Q       	7530302	EU  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION, TAIL INSPECTED, STA 124.0 FOUND BULKHEAD CRACKED IN CORNER.  REPLACED WITH NEW. DURING R	EPLACEMENT FOUND ALSO BULKHEAD P/N 0712511 ON STA 140.0 CRACKED ON LT CORNER. REPLACED WITH NEW. POSSIBLE HARD LANDING D	AMAGE.				1	H	7	1 	3O	3	O	 	A42EU   	E273	5	C	P3EA	 
2003102100020	20031021	00020	SW  	2003	10	21	CA030915012      	1	20030910	G	7600	410MV	COMPARATOR      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					DROOP	DAMAGED         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) PILOT REPORTED DROOP IN RPM AT TAKEOFF. FLEW TO BASE WITH NO PROBLEM. CHANGED OUT GOVERNOR. COULD NOT RIG CONTROLS	 AS PER MAINTENANCE MANUAL. INVESTIGATION RESULTED IN FINDING INOPERATIVE DROOP COMPENSATOR DUE TO SHEARED RIVET. RIVET 	REPLACED, CONTROLS RIGGED. OPS NORMAL.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003102100021	20031021	00021	SW  	2003	10	21	CA030915013      	1	20030912	G	5302	H20503281177	PANEL           	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAILBOOM	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						00298					(CAN) THIS WAS FOUND ON A DAILY INSPECTION.  THE TAILBOOM HELICOMB PANEL WAS DELAMINATED JUST AFT OF THE BAGGAGE COMPART	MENT.  THIS AIRCRAFT WAS ON FIRES, DOING LOTS OF HOVERING WHICH MAY HAVE CONTRIBUTED TO THE DELAMINATION DUE TO HOT EXHA	UST HITTING IT.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003110600003	20031106	00003	SO  	2003	11	6	CA030916002      	2	20030915	G	7414	6320	POINTS          	SLICK       		CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	CONTACT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						99101361					(CAN) POINT ASSEMBLY CONTACT ARM FAILED.						1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2003102100022	20031021	00022	NE  	2003	10	21	CA030916003      	2	20030829	G	7300		ENGINE          			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502L     	41580	NE  					LEFT	SHUTDOWN        	W				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL390, THE LT ENGINE ROLLED BACK AND SHUTDOWN.  AN EMERGENCY WAS DECLARED.  AT 10,000 FT. AN IN-F	LIGHT WINDMILL START WAS SUCCESSFULLY ACCOMPLISHED.  ALL ENGINE PARAMETERS WERE NORMAL PRIOR TO THE EVENT, AND ALSO FOR 	THE REMAINDER OF THE FLIGHT AFTER IT WAS RESTARTED. SUBSEQUENT MAINTENANCE PERFORMED AFTER LANDING REVEALED NO ANOMOLIES	.  ALL FILTERS, SUMPS, AND CHIP DETECTORS WERE INSPECTED AND WERE ALL FOUND TO BE NORMAL.  THE FCU WAS REPLACED AS A PRE	CAUTION.		2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2003102100023	20031021	00023	GL  	2003	10	21	CA030918001      	2	20030908	G	7250	MS9732019	WASHER          	ALLSN       		BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE ASSYTURB	MISSING         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA						24175					(CAN) AFTER INSTALLATION OF TURBINE ASSEMBLY ON ENGINE, GROUND RUNS WERE BEING DONE. OIL WAS NOTICED LEAKING EXCESSIVELY	 FROM THE NR 6 & 7 OIL PRESSURE TEE FITTING. UPON DISASSEMBLY OF FITTING, IT WAS NOTICED THAT THE CRUSH WASHER PN MS9372	019 WAS MISSING BETWEEN OIL STRUT AND TURBINE CASE. TURBINE TSO WAS 0.0 HOURS.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2003102100024	20031021	00024	CE  	2003	10	21	CA030918002      	1	20030828	G	2710		BEARING         			CESSNA	177   	177         	2073704	CE  	LYC   	O360  	O360A3A     	41514	EA  					AILERON CONTROL	BRINELLED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SNAPPING NOISE HEARD WHEN AILERON MOVED. BEARING AREAS ON CONTROL TUBES FRONT OF FIREWALL FOUND SEVERELY BRINELLED	.					1	H	7	1 	3O	3	O	NT	A13CE   	E286				 
2003102100025	20031021	00025	EU  	2003	10	21	CA030918003      	1	20030908	G	2915		CONTROLLER      	SAMM        		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					REGULATOR	STUCK           	W				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA						311					(CAN) HYDRAULIC SELECTED OFF. HYDRAULICS TOOK 35 SECONDS TO TURN OFF. SUSPECT SLIDER STICKING OPEN. REPLACED HYDRAULIC C	ONTROLLER (REGULATOR) WITH SERVICEABLE UNIT. TEST NORMAL.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003102100026	20031021	00026	SO  	2003	10	21	CA030918004      	1	20030916	G	3221	67054003	TRUNNION        	PIPER       		PIPER 	PA44  	PA44180     	7104402	SO  										DRAG LINK	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, CREW DETECTED A LATERAL CRACK IN THE NOSE GEAR TRUNNION ASSEMBLY WHERE THE DRAG LINK	 ASSEMBLY ATTACHES TO THE NOSE GEAR TRUNNION. PART REMOVED AND REPLACED WITH NEW ASSEMBLY.					1	L	7	2 	3O			 	A19S0   					 
2005042700311	20050427	00311	CE  	2005	4	27	CA030918005      	1	20030917	G	2421	99105922	ALTERNATOR      			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE ATTEMPTING TO REPLACE THE STAND-BY ALTERNATOR IT WAS DISCOVERED THAT THE ELECTRICAL CONNECTION WOULD NOT ENG	AGE INTO THE SOCKET PROVIDED IN THE ALTERNATOR BECAUSE THE SOCKET WAS OVERFILLED WITH EPOXY RESIN.  ATTEMPTS WERE MADE T	O CLEAR THE EXCESS RESIN BUT IT WAS FEARED THAT DAMAGE TO THE ALTERNATOR WOULD RESULT. THE MFG HAS BEEN RECENTLY TAKEN O	VER BY A NEW OWNER AND SINCE THIS TAKEOVER THIS IS THE SECOND TIME WE HAVE COME ACROSS THIS PROBLEM. THE UNIT WAS RETURN	ED TO THE VENDOR FOR REPLACEMENT.		1	H	7	1 	3T	3	T		A37CE   	E4EA	5	C	P60GL	 
2003102100036	20031021	00036	NE  	2003	10	21	CA030918006      	1	20030731	G	3212	7625102701101	ROD END         	SKRSKY      		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					EXPLOSIVE LINK	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						5125					(CAN) UPON RETURN FROM A ROUTINE FLIGHT, IT WAS NOTED THAT THE RT EXPLOSIVE LINK ROD END WAS SHEARED. EXPLOSIVE LINK REP	LACED WITH SERVICEABLE PART, A/C RETURNED TO SERVICE.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2003102100038	20031021	00038	NM  	2003	10	21	CA030918007      	1	20030916	G	5330		SKIN            			BOEING	737   	7372Q9      	138448M	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE DAILY CHECKS A CRACK WAS FOUND ON THE EXTERIOR FUSELAGE AT STN 935-937 STRINGER 24L. CRACK WAS REPA	IRED IAW SRM 53-30-3 FIG 48 SHEET 29 DETAIL VI. ACFT TIMES 58839.13 ACFT CYCLES 55678.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2005042700310	20050427	00310	NM  	2005	4	27	CA030918008      	1	20030911	G	3220	BACB30GE	BOLT            			BOEING	737   	737*        	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NLG	IMPROPER PART   	W				L				ABORTED APPROACH        				W	D	J	INADEQUATE Q C            	INFLIGHT SEPARATION       	WARNING INDICATION        	DE	DESCENT        	1			CA											(CAN) NOSE LANDING GEAR LOCK ACTUATOR LOWER ATTACH BOLT SHEARED, ALLOWING ACTUATOR TO FAIL. BOLT IDENTIFIED AS AN UNAPPR	OVED PART. THIS BOLT WAS NOT INSTALLED BY THIS OPERATOR.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2003102100048	20031021	00048	EA  	2003	10	21	CA030918009      	1	20030916	G	2822		DIAPHRAGM       			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					WOBBLE PUMP	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			10300								(CAN) ON INSPECTION THE WOBBLE PUMP WAS FOUND TO BE LEAKING FUEL FROM THE DIAPHRAGM SEAL AREA DURING A SYSTEM PRESSURE T	EST. THE OVERHAUL FACILITY CONFIRMED THAT THE SEAL AND O-RINGS WERE OLD AND IN NEED OFREPLACEMENT.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003102100050	20031021	00050	WP  	2003	10	21	CA030918010      	1	20030918	G	6320	369D25416	BEARING         	DOUG        		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R TRANSMISSION	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA						0022220405					(CAN) TAIL ROTOR O/P PINION ROLLER BEARING CRACKED AND SPALLED.  SPUN ON T/R O/P PINION ROLLER BEARING JOURNAL. JOURNAL 	NOW UNDERSIZE					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003102100051	20031021	00051	EU  	2003	10	21	CA030918011      	1	20030918	G	6220	350A31190703	STARFLEX        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MAIN ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE BEFORE THE FRIST FLIGHT (BFF) INSPECTION, THE PILOT FOUND THE STARFLEX ARM END BUSHING DEBONDED AND DIS	PLACED OUTBOARD BY APPROXIMATELY 3/8 OF AN INCH. UPON DISASSEMBLY OF THE M/R HEAD THE FREQUENCY ADAPTER PN EIT-3023-01 I	NNERBORE WAS FOUND TO BE DAMAGED BY BUSHING AND RETAINING BOLT MIGRATION OUTBOARD.DURING THE PREVIOUS DAYS FLYING, THE P	ILOT NOTICED A SLIGHT DIFFERENCE IN THE HELICOPTERS VIBRATORY LEVEL.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003102100057	20031021	00057	NE  	2003	10	21	CA030918012      	1	20030916	G	2430		GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE	OUT OF ADJUST   	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) DURING TRAINING, INFLIGHT ENGINE SHUTDOWN AND RESTART PROCEDURES WERE BEING DEMONSTRATED. WHEN START WAS ATTEMPTED	 THE THE OVERSPEED SYSTEM TRIPPED AND PREVENTED THE RESTART. TROUBLESHOOTING INDICATES THAT A OUTPUT VOLTAGE OF 28.55 VD	C FROM THE OPERATING ENGINE GENERATOR WILL TRIP THE OVERSPEED SYSTEM AND PREVENT STARTING. ADJUSTMENT OF THE OUTPUT VOLT	AGE TO 28.5 VDC HAS CORRECTED THIS PROBLEM.			1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2003102100059	20031021	00059	WP  	2003	10	21	CA030919002      	1	20030915	G	6210	369A10045	PIN             	HUGHES      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						0098846211					(CAN) WHEN PIN WAS OPENED TO REMOVE MAIN ROTOR BLADE PIN FELL APART. IT WAS NOTED PIN WAS SHEARED OFF WHERE LAST THREAD 	WAS CUT.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003102100067	20031021	00067		2003	10	21	CA030919003      	4	20030907	G	3450		CONTROL PANEL   			BOEING	767   	767375      	1385217	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					TCAS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) A/C HAD A DUAL ATC FAILURE AFTER DEPARTURE LHR. UK ATC WOULD NOT LET THE A/C PROCEED SO RETURNED TO LHR. OVERWEIGH	T LANDING CHECK CARRIED OUT. ATC CONTROL PANEL CHANGED AND NO FURTHER FAULT					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2003102100068	20031021	00068	EA  	2003	10	21	CA030921001      	1	20030912	G	5610	NP13932110	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AIRCRAFT HAS RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT.  RT WINDSHIELD INNER PLY CRACKED WHILE EN-ROUT	E FROM ORD TO AUS.  THE AIRCRAFT WAS FERRIED TO ORD FOR THE WINDSHIELD REPLACEMENT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003102100074	20031021	00074	EA  	2003	10	21	CA030922002      	1	20030803	G	2710		PCU             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	JAMMED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, THE CREW RECEIVED A 'OB SPOILERON' CAUTION AND 'OB FLIGHT SPOILER' CAUTION MESSAGES.THE MDC REPORT	ED THE LT OUTBOARD MFS PCU JAM.  CREW DECLARED AN EMERGENCY AND LANDED SAFELY WITH NO OTHER INCIDENTS REPORTED.  FOLLOWI	NG REPLACEMENT OF THE LT OUTBOARD MFS POWER CONTROLLER, THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003102100076	20031021	00076		2003	10	21	CA030922003      	4	20030918	G	2210	8220044001	CONTROL PANEL   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					AUTOPILOT	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON AUTOPILOT DISCONNECT ON APPROACH ELEVATORS WERE STUCK AND HAD TO OVERPOWER TO REGAIN CONTROL.FLT DID NOT ENTE	R ANY VISIBLE MOISTURE DURING FLT.  A/C LANDED NORMALLY. PANEL REPLACED (FCP)AS PER AMM 22-11-07-400-801 AND ALL OPERATE	S NORMALLY.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003102100079	20031021	00079	EA  	2003	10	21	CA030922004      	2	20030922	G	8530		STUD            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 2 NACELLE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HR. INSPECTION THE NR 2 ENGINE COWL WAS REMOVED. WHEN THE COWL WAS LOWERED TWO NUTS WITH HALF THE STUDS	 FELL OUT ONE 3/8 INCH AND ONE 1/2 INCH. AFTER FURTHER INSPECTION IT WAS NOTICED THAT THE NR 2 CYL HOLD DOWN STUDS ON TH	E LOWER HALF OF THE CYL WAS MISSING. WHEN THE CYL. WAS REMOVED IT WAS NOTED THAT THE CYL HAD A LARGE CRACK BETWEEN THE T	OP SPARK PLUG HOLE TO THE EXHAUST VALVE. THE PARTS HAVE BEEN SENT OFF TO TSB TO DETERMINE THE REASON FOR BREAKAGE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003102100081	20031021	00081	NM  	2003	10	21	CA030922005      	1	20030905	G	5610	07802	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			22757	22757							(CAN) DURING CRUISE FLIGHT AT 25,000 FT THE LT WINDSHIELD STARTED ARCING WITH SUBSEQUENT SHATTERING OF THE WINDSHIELD OU	TER PLY. AIRCRAFT REQUESTED ALOWER ALTITUDE TO DESEND BELOW ICING CONDITIONS , AND CONTINUED TO DESTINATION. MAINTENANCE	 REPLACED WINDSHIELD ASSEMBLY AND AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100082	20031021	00082	NM  	2003	10	21	CA030923001      	1	20030905	G	7931	ST1042	TRANSMITTER     			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					OIL PRESSURE	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) ON START UP NR 2 ENGINE OIL PRESSURE WOULD NOT COME UP. START ABORTED AND ENGINES SHUT DOWN.FOUND NR 2 ENGINE OIL 	PRESSURE TRANSMITTER PN ST1042 TO BE UNRELIABLE AT TIMES. TRANSMITTER REPLACED AND ALL INDICATIONS NORMAL. AIRCRAFT RELE	ASED RETURN TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102100083	20031021	00083	GL  	2003	10	21	CA030923002      	3	20030918	G	6114	D7015	HUB             			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	MISOVERHAULED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HUB UNIT BLADE SOCKET NR 2, EXPANSION PLUG HOLES DRILLED TOO DEEP BY THE PREVIOUS OVERHAUL.  HUB UNIT REPLACED.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2003102100085	20031021	00085	GL  	2003	10	21	CA030923003      	3	20030918	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER BLADES MEASURED WHEN RECEIVED IN SHOP. BLADES FOUND TO BE BELOW MIN. WIDTH AND THICKNESS. BLADES REPLACE	D.					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2003102100086	20031021	00086	GL  	2003	10	21	CA030923004      	3	20030918	G	6111	S82NC55	BLADE           			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BLADES MEASURED WHEN RECEIVED IN SHOP, FOUND BLADE WIDTH TO BE BELOW MIN. ALLOWABLE.  BLADES REPLACED.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2003102100087	20031021	00087	GL  	2003	10	21	CA030923005      	2	20030914	G	7230		BEARING         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					COMPRESSOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) NR 1 ENGINE BEARING FAILED, CHIP LIGHT NOTIFIED PILOT. AIRCRAFT WAS IN CRUISE FLIGHT. UPON INVESTIGATION THE BEARI	NG CAGE AND BALLS WERE NO LONGER CONTAINED BETWEEN THE INNER AND OUTER RACES. THE IMPELLER WAS ALLOWED TO TILT AND AS A 	RESULT RUBBED A GROOVE INTO THE COMPRESSOR HOUSING. COMPRESSOR ASSEMBLY WAS REPLACED WITH SERVICEABLE UNIT. AIRCRAFT WAS	 GROUND RUN AND RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003102100097	20031021	00097	EA  	2003	10	21	CA030923006      	2	20030917	G	7210		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  						FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			15537								(CAN) ENG SHUTDOWN IN FLT WHEN OIL PRESSURE DROPPED BELOW 75 PSI. REMOVED FOR INVEST. ENG FOUND TO HAVE 3 SOURCES OF OIL	 LOSS, PRINCIPAL ONE IS THOUGHT TO HAVE RESULTED IN RAPID OIL LOSS & MAIN PRESSURE PUMP OIL STARVATION, AN OIL GALLERY P	ORT ON RGB ACCESSORY G/B WHICH HAD A STRIPPED THREAD & BLANKING PLUG MISSING. THERE WAS NO EVIDENCE IN ENG OF ANY DAMAGE	 CAUSED BY LACK OF LUBE & PROMPT ENG SHUTDOWN PREVENTED SIGNIFICANT DAMAGE. ENG FOUND TO HAVE BALL BEARING ON ALTERNATOR	 DRIVE SHAFT FAILED, CAUSING SHAFT TO LOSE LOCATION & ALLOW OIL LEAKAGE AT SEAL. PROPSHAFT OIL SEAL RUNNER & NR 7 BEARIN	G INNER RACE HAD BOTH SPUN ON PROP SHAFT CAUSING SIGNIFICANT MATERIAL LOSS TO ALL 3 PARTS & AN OIL LEAKAGE PATH.						4	T			E4EA				 
2003102100098	20031021	00098	NM  	2003	10	21	CA030923007      	1	20030919	G	5753	654642821	FLAP TRACK      			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING AD 2002-05-07 (BOEING SB737-57A1249), THE RT SIDE FLAP TRACK POSITION NR 7 WAS FOUND CRACKED. TRA	CK WAS REPLACED.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102100100	20031021	00100	NM  	2003	10	21	CA030923008      	1	20030919	G	5312		BEAM            			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			65308								(CAN) WHILE PERFORMING SB 737-53A1173 (INSPECTION OF THE VERTICAL BEAMS AT STATION 178 PRESSURE BULKHEAD) THE FOLLOWING 	DEFECTS WERE FOUND, VERTICAL BEAM WEB CRACKED AT BS178 RBL 5.7 WL 1832-VERTICAL BEAM WEB CRACKED AT BS 178 RBL 17.1 WL 2	30 BOTH CRACKS WERE REPAIRED AS PER BOEING 737 SRM.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102100101	20031021	00101	NM  	2003	10	21	CA030923009      	1	20030919	G	5330		SKIN            			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			65308								(CAN) WHILE LOOKING AT FUSELAGE ON THE LT SIDE,THE TECHNICIAN WAS QUESTIONNING WHAT SEEM TO BE A SCRATCH MARK. AFTER FUR	THER INVESTIGATION AND INTERIOR LINING REMOVAL,IT WAS DISCOVERED THAT THE SCRATCH WASINDEED A CRACK IN THE FUSELAGE LOCA	TED AT FUSELAGE STA 771, BETWEN STRINGER 16L AND 17L.THE CRACK WAS 2 INCHES LONG,BETWEEN STA 771 AND STA 773 ABOVE FLOOR	 LEVEL. CRACK WAS REPAIRED USING 737 SRM.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102100102	20031021	00102	SW  	2003	10	21	CA030923010      	1	20030912	G	6420	204011722005	YOKE            			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					TAIL ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAIL ROTOR HUB ASSY WAS SENT FOR OVERHAUL. YOKE WAS SENT FOR NDT AS PART OF O/H AND WAS FOUND TO BE CRACKED.						1	G	7	1 	4U	4	U	 	H1SW    	E1EA				 
2003102100106	20031021	00106	NE  	2003	10	21	CA030923011      	2	20030812	G	8530	12081	STUD            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					CYLINDER BASE	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ALL NR 6 HOLD DOWN STUDS FOUND BROKEN.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2003102100107	20031021	00107	CE  	2003	10	21	CA030924001      	1	20030922	G	5210	1144000301	SEAL            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					PAX DOOR	DETACHED        	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) SEAL BECAME DETACHED FROM RETAINER AT UPPER AFT CORNER OF AIRSTAIR DOOR CAUSING RAPID DEPRESSURIZATION OF AIRCRAFT	 IN FLIGHT.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003102100108	20031021	00108	EU  	2003	10	21	CA030924002      	1	20030924	G	3260	9733033111	PROXIMITY SWITCH			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AFTER TAKE OFF THE SYSTEMS RELATED TO THE RT PROXIMITY SWITCH STARTED TO FLASH. THE AIRCRAFT RETURNED TO BASE.  TH	E AIRCRAFT WAS PUT ON JACKS AND THE WIRING WAS INSPECTED. THERE WERE NO DEFECTS FOUND AND THE SNAG COULD NOT BE DUPLICAT	ED. AS THE AIRCRAFT HAD FLOWN THROUGH HEAVY RAIN THE DAY BEFORE ALL THE CONNECTORS WERE CLEANED AND RESEALED. THE PROXIM	ITY SWITCHES WERE SWAPPED FROM LT TO RT TO SEE IF THE SNAG WOULD FOLLOW. THE AIRCRAFT WAS TEST FLOWN AND THE SNAG DID NO	T RETURN. THE AIRCRAFT WAS RETURNED TO SERVICE. SDR TO BE CLOSED IN 1 WEEKIF THE ARE NO MOVE OCCURANCES.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003102100109	20031021	00109	NM  	2003	10	21	CA030924003      	1	20030906	G	2761	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPOILER	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			35059								(CAN) THE AIRCRAFT EXPERIENCED A FLIGHT TURNBACK DUE TO TOTAL LOSS OF HYDRAULIC FLUID FROM THE NR 2 HYDRAULIC SYSTEM. BE	CAUSE OF THE FLUID LOSS AN EMERGENCY EXTENSION OF THE LANDING GEAR HAD TO BE CARRIED OUT PRIOR TO LANDING. THE CAUSE OF 	THE FLUID LOSS WAS DUE TO A CATASTROPHIC FRACTURE FAILURE OF LT HAND OUTBOARD SPOILER ACTUATOR METAL BODY, ALLOWING THE 	WHOLE CONTENT OF THE NR 2 HYD SYSTEM TO BE RELIEVED THROUGH THE ACTUATOR BODY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100111	20031021	00111	EA  	2003	10	21	CA030924004      	2	20030910	G	7532	54009494	BLEED VALVE     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN FLIGHT SHUTDOWN DUE FADEC CAUTION LIGHT CREW SHUT THE ENGINE DOWN, FADEC FAULT CODE WAS 912. A FAULTY P2.2 BLEE	D VALVE WAS IDENTIFIED VALVE. 2.2 BLEED VALVE REPLACED AND AIRCRAFT WAS DECLARED SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003102100112	20031021	00112	EA  	2003	10	21	CA030924005      	2	20030919	G	8530	381369679	STUD            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					NR 5 CYLINDER	BROKEN          	W				E				ENGINE SHUTDOWN         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) LT ENGINE CYLINDER NR 5 CYLINDER BASE STUDS SHEARED OFF IN CASE. STUDS APPEAR TO HAVE BEEN CRACKED INSIDE CASE ARE	A.  POSSIBLY FROM OVER TORQUEING.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2003102100114	20031021	00114	CE  	2003	10	21	CA030924006      	1	20030905	G	2823	662820010003	SHUTOFF VALVE   			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					FUEL SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN LT ENGINE FUEL SHUTOFF VALVE WAS SELECTED CLOSED AND AIRFRAME POWER WAS SELECTED OFF,  NOISE WAS HEARD COMING	 FROM THE VALVE.  IT WAS DISCOVERED THAT THECURRENT WAS NOT CUT OFF WHEN THE VALVE WASCLOSED.REPLACED SHUTOFF VALVE.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2003102100117	20031021	00117	WP  	2003	10	21	CA030925001      	2	20030408	G	7250	3060690	BLADE           			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					LPT3	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) FAILURE OF LPT3 BLADE. THESE BLADES WERE INSTALLED AT TIME OF MANUFACTURE. BASED ON EXPERIENCE FROM OTHER EVENTS, 	SEPARATIONS OF THE LPT 3 BLADE HAVE BEEN TRACED TO EXCESSIVE MECHANICAL ADJUSTMENT DONE DURING TIME OF MANUFACTURE. WHIL	E THIS IS A COMMON PRACTICE IN THE AEROSPACE CASTING INDUSTRY, THE GEOMETRY OF THIS BLADE MAKES IT SENSITIVE TO THIS PRO	CESS. THE FRACTURE APPEARS AS A STRESS RUPTURE FRACTURE MODE. IN AN EFFORT TO REDUCE ADDITIONAL FAILURES, HONEYWELL ISSU	ED SERVICE BULLETIN TFE731-3686 TO REQUIRE EDDY CURRENT AND FLUORESCENT PENETRANT INSPECTION OF AT MPI OR TIME OF TURBIN	E ACCESS.	2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2003101700003	20031017	00003	NM  	2003	10	17	CA030925002      	1	20030905	G	2910	82920010307	LINE            			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	RUPTURED        	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI-OUT, FUSELAGE HYD LINE RUPTURED AT A POINT OVERHEAD ROW 4 - 5 (CA. FS X 407.7 + 2) JUST FORWARD OF THE	 PRESSURE FITTING AND BELOW THE 90 DEGREE BEND ROUTING THE LINE DOWNWARD.  7 PASSENGERS WERE ON BOARD (1 PASSENGER AND 1	 FA WERE TAKEN TO HOSPITAL FOR TREATMENT). THE HYDRAULIC LINE WAS REPLACED.  DURING THE SUBSEQUENT PRESSURE CHECK, THE A	DJACENT LINE (P/N 82920010263 / NLG RETRACT) WAS FOUND TO BE SEEPING AT THE BULKHEAD PRESSURE FITTING SWAGE. THE OPERATO	R HAS EXPRESSED THEIR INTENT TO VISUALLY INSPECT THEIR FLEET FOR LEAKAGE IN THIS AREA.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100121	20031021	00121	CE  	2003	10	21	CA030925003      	1	20030921	G	2750	26600111	CONTROL ROD     			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18574	18574							(CAN) WHILE CARRYING OUT A PHASE INSPECTION, THE CONTROL COLUMN CONNECTING TUBE WAS FOUND CRACKED.  THE CRACK WAS LOCATE	D AT ONE OF THE ATTACHMENT BOLT HOLES TO THE KNUCKLE FITTING.  THE CRACK EMANATED FROM THE BOLT HOLE CLOSEST TO THE END 	OF THE TUBE, TO THE END OF THE TUBE.  A NEW TUBE WAS INSTALLED IN THE AIRCRAFT AND RETURNED TO SERVICE.  2 OTHER AIRCRAF	T IN OUR FLEET WERE INSPECTED WITH NO DEFECTS FOUND.			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2003102100124	20031021	00124	CE  	2003	10	21	CA030925004      	1	20030923	G	2161	2297009	SOLENOID VALVE  			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	RT ENGINE	SHORTED         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE, THE 5 AMPS CIRCUIT BREAKER (CABIN TEMP) TRIPPED.  CREW RESET ONE TIME AND TRIPPED AGAIN.  UPON IN	VESTIGATION FOUND RT AMBIENT SOLENOID SHUTOFF VALVE SHORTED CAUSING CIRCIUT BREAKER TO TRIPPED. SOLENOID VALVE REPLACED 	WITH NEW AND SYSTEM GROUND TESTED OK IAW M/M.				1	L	7	2 	4T	4	T	 	A14CE   	E2WE	6	C	P40EA	 
2003102100125	20031021	00125	CE  	2003	10	21	CA030925005      	1	20030916	G	3240	30162	PAD             			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	BRAKE ASSY	LOOSE           	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) DURING LANDING THE AIRCRAFT WAS PULLING TO THE LEFT SIDE OF THE RUNWAY.  UPON APPLICATION OF THE BRAKE ON THE LEFT	 SIDE AIRCRAFT STARED TO VIBRATE.  THE BRAKE WAS ALSO NOTED TO BE SOFT AND INEFFECTIVE.  MAINTENANCE INSPECTED IT AND FO	UND THE LT OUTBOARD BRAKE WEAR PADS BECAME DISLODGED AND DAMAGED THE BRAKE ASSEMBLY AND THE WHEEL HALF. THE WEAR PADS AR	E RIVETED ON AND IT APPEARS THAT A RIVET LET GO AND STARTED A CHAIN REACTION BREAKING ALL THE OTHER RIVETS LETTING THE W	EAR PAD MOVE AND DAMAGE THE OTHER PARTS.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2003102100127	20031021	00127	GL  	2003	10	21	CA030925006      	3	20030901	G	6197	KX5116	SWITCH          			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP RESET	SHORTED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING FROM DOCK, NR 1 ENGINE DID NOT RESPOND TO (REVERSE) COMMAND BUT POWERED UP TO FORWARD MODE. FOUND WI	RING WRAP INTERFERED WITH PROP RESET SWITCH IN OVERHEAD POWER LEVER QUADRANT. MODIFICATION WAS COMPLETED IAW DHC-6-100, 	MOD6/1912 (INSTALLATION OF SPARK IGNITION).				1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2003102100130	20031021	00130	NM  	2003	10	21	CA030926001      	1	20030911	G	2910	82970010477	LINE            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING THIS FLIGHT WE EXPERIENCED A HYDRAULIC FAILURE OF THE NR 2 HYDRAULIC SYSTEM NUMBER . AFTER THE LANDING, THE	 INSPECTION REVEALED A CRACKED ENGINE DRIVEN PUMP FEED PRESSURE TUBE.MOD 8Q100820 WAS INTRODUCED TO IMPROVE THE RELIABIL	ITY OF THE TUBES BY CHANGING THE MATERIAL FROM ALUMINIUM TO STAINLESS STEEL, AND TO INTRODUCE MACHINED FLARED END FITTIN	GS IN LIEU OF THE FORMED FLARED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100132	20031021	00132	SO  	2003	10	21	CA030926002      	1	20030922	G	3250	70933003	SHAFT           			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG STEERING	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT REPORTED LACK OF NOSE WHEEL STEERING CONTROL. UPON INSPECTION, THE NOSE WHEEL STEERING SHAFT WAS FOUND CRACK	ED LONGITUDINALLY BETWEEN BOLT HOLES.					1	L	7	2 	4T	4	T	 	A23SO   	E4EA	6	C	P15EA	 
2003102100135	20031021	00135	EA  	2003	10	21	CA030926003      	2	20030917	G	7414	67542	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	LT MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ENGINE, LT MAGNETO-ENGINE HOURS: 1230.5 SN. L-8588-48. DAMAGE WAS DISCOVERED DURING 100 HOUR INSPECTION. REMOVA	L OF ONE LT MAGNETO WAS REQUIRED TO COMPLETE A MAGNETO INSPECTION. WHEN MAGNETO WAS REMOVED MAGNETO GEAR RETAINER ASSY A	ND BEARING PULLED OUT OF THE ENG TOGETHER WITH DRIVE COUPLING YET AGAIN . UPON FURTHER INSP NO DAMAGE TO GEAR RETAINER A	SSY AND BEARING WAS FOUND AND ASSY WAS REPLACED WITH NEW AND REINSTALLED. ALSO BEARING RECESS WAS INSP AND MEASURED TO B	E WITH-IN LIMITS AND CHECKED OK.		1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2003102100137	20031021	00137	SO  	2003	10	21	CA030926004      	1	20030813	G	2823	3085600	CONTROL CABLE   	PIPER       		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	FUEL SELECTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE TESTING OPERATION OF LT FUEL SELECTOR CONTROL NOTICED THAT THE LT SIDE WAS MOVING VERY EASY.  FURTHER INSPEC	TION FOUND THAT THE INNER CABLE HAD BROKEN LEAVING THE FUEL VALVE IN AN UNKNOWN POSITION. CABLE WAS REPLACED WITH NEW.					1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2003102100139	20031021	00139	SO  	2003	10	21	CA030926005      	1	20030819	G	3230	1742003	DRAG LINK       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LT GEAR LEG SUPPORT BRACE AT THE REAR ATTACHEMENT FITTING WAS CRACKED COMPLETELY TO THE BOLT HOLE.  PART WAS R	EMOVED AND WAS WELD REPAIRED. IT WAS SENT FOR NDT TOGETHER WITH RIGHT DRAG LINK AND DRAG LINK CASTING AND PASSED. PARTS 	WERE RE-INSTALLED CHECKS OK NO OTHER LOCAL DAMAGE WAS DETECTED.				1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2003102100141	20031021	00141	NE  	2003	10	21	CA030926006      	2	20030520	G	7321		CAP             	WOODWARD    		BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL CONTROL	FRACTURED       	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						A34702					(CAN) FUEL DRIPPED FROM THE AFCU AND ENTERED THE CABIN OF THE AIRCRAFT. POST FLIGHT TROUBLESHOOTING IDENTIFIED A MAJOR L	EAK FROM THE ALUMINUM CAP PLUG ON THE SIDE OF THE AFCU. EXAMINATION HAS IDENTIFED THAT THE FRACTURE IS DUE TO LCF. THE E	XACT TOTAL TIME OF THE CAP IS NOT KNOWN, BUT IS ESTIMATED AT +2,000 HOURS.				1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2003102100142	20031021	00142	CE  	2003	10	21	CA030928001      	1	20030927	G	3510	1145600585	LINE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	OXYGEN SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13726	13726							(CAN) WHEN TRYING TO SERVICE OXYGEN SYSTEM ONLY THE LT BOTTLE WOULD FILL AND A LOUD LEAK COULD BE HEARD.  AFTER INVESTIG	ATION BY MAINTENANCE THE FILLER INTERCONNECT LINE  WAS FOUND TO BE CRACKED WHERE IT ATTACHES TO THE RT BOTTLE. THE LINE 	WAS REPLACED AND LEAK TESTED SERVICABLE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003102100143	20031021	00143	CE  	2003	10	21	CA030928002      	1	20030914	G	2750	0512128	PULLEY BRACKET  			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	TE FLAPS	DETACHED        	W				O				OTHER                   				O	I		OTHER                     	FLT. ATTITUDE INST.       		AP	APPROACH       	1			CA											(CAN) ON FINAL APPROACH TO LAND THE AIRCRAFT WAS BUFFETED BY A GUST OF WIND AT WHICH TIME THE LT FLAP PARTIALLY RETRACTE	D. THE AIRCRAFT MADE AN UNEVENTFULL LANDING AND DURING INVESTIGATION BY MAINTENANCE THE LT FLAP PULLEY BRACKET WAS FOUND	 DETACHED FROM THE AIRFRAME. IT WAS REPLACED AND THE SYSTEM WAS TESTED AND FOUND OPERATING NORMALLY.				1	H	7	1 	3O	3	O	 	3A24    	E3SO	5	C	P47GL	 
2003102100144	20031021	00144	NE  	2003	10	21	CA030929001      	2	20030914	G	7200		ENGINE          			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					NR 1	BURNED          	W				F				ACTIVATE FIRE EXT.      				A	J		FLAME/FIRE                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ENG FIRE ON A/C 796 NR 1 POS.  A/C WAS FULLY LOADED WITH PASS. DURING ENG START RECEIVED A FIRE IND ON NR 1 ENG, F	IRST BTL WAS RELEASED, FIRE IND RE-APPEARED, SECOND BTL RELEASED. NO FURTHER FIRE IND WERE RECEIVED.  PAX EXITED A/C AND	 NO EMER EVACUATION WAS DECLARED. ENG AT RRC FOR INVEST,  INSP REVEALED SIGNIFICANT DAMAGE TO ACOUSTIC LINING, MANY MELT	ED WIRES. FUEL SYS ON ENG 13245 WAS PRESSURIZED ON TEST CELL W/ENG STATIC TO VERIFY FOR LEAKS, NO LEAKS OBSERVED. DRY AN	D WET MTR CYCLES WERE CARRIED OUT, NO LEAKS OBSERVED. FUEL DRAIN TANK WAS EMPTIED PRIOR TO WET CRANK, THERE WAS EVIDENCE	 OF FUEL DRAIN I.E. MANIFOLD DRAINING PROPERLY. EEC WILL BE SENT TO VENDOR FOR NON VOLATILE MEMORY DOWNLOAD/CHECK.	2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2003102100145	20031021	00145	NE  	2003	10	21	CA030929002      	2	20030918	G	7314	1143880425	PUMP            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					FUEL SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				B	K	J	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) CREW NOTICED A FUEL ODOR IN AIRCRAFT AT ALTITUDE AND A PASSENGER NOTIFIED THAT FLUID APPEARED TO BE COMING FROM CO	WL AREA THAT NORMALLY PROVIDES EXHAUST AIR FROM THE STARTER GENERATOR. THE AIRCRAFT DIVERTED TO THE CLOSEST AIRPORT. MAI	NTENANCE FOUND THE RT ENGINE LOW PRESSURE FUEL PUMP WAS LEAKING FUEL. THE PUMP WAS REPLACED AND THE AIRCRAFT CONTINUED. 	THE PUMP STRIP FOUND THAT A GASKET BETWEEN THE REGULATOR AND THE MAIN BODY WAS BLOWN OUT OF POSITION ALLOWING FUEL LEAKA	GE.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2003102100146	20031021	00146	NE  	2003	10	21	CA030929003      	2	20030919	G	7314	1143880425	PUMP            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					FUEL SYSTEM	LEAKING         	W				O				OTHER                   				B	K	J	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) SIMILIAR TO A PREVIOUS SDR ON THE RT SIDE ON SEPT 18, 2003, THE LT HAND LOW PRESSURE FUEL PUMP BEGAN LEAKING IN FL	IGHT ALLOWING ODOR AND FUEL ESCAPE FROMTHE AIRCRAFT. MAINTENANCE AGAIN REPLACED THE PUMP AND THE STRIP SHOWED THE SAME G	ASKET BLOW OUT ALLOWING FOR FUEL TO ESCAPE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2003102100147	20031021	00147	EU  	2003	10	21	CA030929004      	1	20030926	G	3250		STEERING SYS    			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					NLG	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) AFTER TOUCH DOWN APROX 80 KNOTS THE NOSE GEAR STEERING WHEEL AUTOMATILLY WHEN TO A FULL LEFT TURN COMMAND. THE AIR	CRAFT DEPARTED THE RUNWAY TO THE LT AND CAME TO A REST AT APROX 90 DEGREES TO THE RUNWAY IN THE SOIL AREA NEXT TO RUNWAY	. THE RT WING TIP STRUCK THE GROUND AT APROX 20 KNOTS IN THE SOIL AREA DAMAGE WAS OBSERVED IN THE NOSE GEAR AREA AND ALS	O THE RIGHT TIP AREA.			2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2003102100154	20031021	00154	NM  	2003	10	21	CA030929006      	1	20030928	G	2761	654456110	ACTUATOR        			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					SPOILER	MALFUNCTIONED   	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT THE AIRCRAFT EXPERIENCED A TOTAL LOSS OF HYDRAULIC SYSTEM A FLUID. AIRCRAFT TURNED BACK TO YUL AND LA	NDED WITHOUT INCIDENT.  THE NR 3 SPOILER ACTUATOR WAS FOUND TO BE THE CAUSE OF THE FLUID LEAK.ACTUATOR REPLACED AND AIRC	RAFT RETURNED TO SERVICE. A SHOP REPORT HAS BEEN REQUESTED FOR THE ACTUATOR UNIT.  WILL ADD MORE INFO WHEN AVAILABLE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003102100155	20031021	00155	NE  	2003	10	21	CA030930001      	2	20030925	G	7220	80337035003	BREATHER TUBE   			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  	HARTZL	HCE5N	HCE5N3      	GL  	RT ENGINE	KINKED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											(CAN) THE AIRCRAFT WAS WORKED ON FOR HOT ENVIRONMENTAL ODOR. THE ENVIRONMENTAL SYSTEM WAS CHECKED OVER AND THE DUCT WORK	 WAS CHECKED WITH A BORESCOPE.  PILOTS REPORTED THE ODOR WAS BACK WITH SMOKE WHEN THE POWERED UPTHE ENGINES.THE ENGINE C	OWLS WERE REMOVED AND OIL WAS FOUND IN THE BLEED AIRVALVE OF THE RIGHT ENGINE.THE ENGINE BREATHER LINE WAS FOUND KINKED 	AND BADLY RESTRICTED CAUSING NR 1 BEARING CAVITY TO FLOOD.  THE LINE WAS REPLACED COMPRESSOR WASH CARRIED OUT,  ENGINE G	ROUND RUNS AND TEST FLIGHT WAS SATISFACTORY.		1	H	7	2 	3O	4	T	RT	A59EU   	E26NE	5	C	PZONE	 
2003110700009	20031107	00009	EU  	2003	11	7	CA030930002      	1	20030929	G	2150	1879009	ODOR            	AIRESRCH    		AIRBUS	310   	A310300     	3930305	EU  										HEAT EXCHANGER	DETECTED        	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA											(CAN) FLIGHT CREW REPORTED AN ELECTRICAL BURNING ODOR IN THE CABIN ON APPROACH WITH GEAR SELECTED DOWN.DURING GROUND TES	T , THE PROBLEM WAS TRACED TO THE RT AIR CONDITIONING PACK .THE HEAT EXCHANGER HAD BEEN REPLACED ON THE PREVIOUS FLIGHT 	AND WAS FRESHLY O/H AND PAINTED. THE COELESER BAG WAS REPLACED AND THE AIR CONDITIONING PACK WAS OPERATED AND CHECKED SE	RVICEABLE.			2	L	7	2 	4F			RT	A35EU   					 
2003102100157	20031021	00157	NM  	2003	10	21	CA030930003      	1	20030827	G	2710		ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ROLL SPOILER	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			24621								(CAN) DURING SCHEDULED MAINTENANCE AN OPERATIONAL CHECK OF THE ROLL SYSTEM DISCONNECT WAS PERFORMED IAW MFG MRB TASK 276	0/02. IT WAS DISCOVERED THAT AILERON TRAVEL WAS RESTRICTED AT THE FULL LT WING DOWN SELECTION CAUSING THE ROLL SYSTEM DI	SCONNECT CLUTCH TO DISENGAGE AT FULL TRAVEL AND SUBSEQUENTLY ILLUMINATING THE ASSOCIATED CAUTION LIGHT. FURTHER INVESTIG	ATION DETERMINED THAT THE LT OUTBOARD ROLL SPOILER ACTUATOR HAD AN INTERNAL FAILURE CAUSING RESTRICTED TRAVEL DURING EXT	ENSION OF ROLL SPOILER.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100158	20031021	00158	NM  	2003	10	21	CA030930004      	1	20030518	G	2761	A44700009	ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ROLL SPOILER	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			30561								(CAN) ROLL SPOILER ACTUATOR SERIAL NUMBER 0963 FOUND TO BE LEAKING AFTER ENGINEERS PERFORMED TROUBLESHOOTING FOR A HYDRA	ULIC LEAK ON LT WING. THE ACTUATOR WAS SUBSEQUENTLY REMOVED FROM THE AIRCRAFT AND SENT FOR  REPAIR. THE REPAIR AGENCY RE	PORT FINDING A CRACK IN THE ACTUATOR HOUSING, AND THE ASSY WAS RETURNED TO THE OPERATOR FOR SCRAP. THIS ACTUATOR HAS NOW	 BEEN FORWARDED TO THE AT SB FOR INSPECTION AND REPORT.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100159	20031021	00159	SW  	2003	10	21	CA030930005      	1	20030824	G	6330	BSH16ATC32	BEARING         	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					PIN ASSY	UNSTAKED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BEARING IN PIN ASSEMBLY BECAME UNSTAKED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003102100160	20031021	00160	GL  	2003	10	21	CA030930006      	2	20030827	G	7230	6895803	SCROLL          	ALLSN       		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAC70614					(CAN) DURING INSPECTION A CRACK WAS FOUND IN THE COMPRESSOR SCROLL.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003102100161	20031021	00161	CE  	2003	10	21	CA030930007      	1	20030821	G	2730	05341221	BELLCRANK       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ELEVATOR CONTROL	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) THE ELEVATOR BELLCRANK MAIN BEARING WAS FOUND SPINING LOOSE INSIDE THE BELLCRANK ASSEMBLY. THE BELLCRANK WAS WORN 	OUT BY THE OUTER PORTION OF THE BEARING. THE BEARING IS A PRESSED FIT, AND CANNOT BE REPLACED.  THE ENTIRE ELEVATOR BELL	CRANK ASSEMBLY HAD TO BE REPLACED WITH NEW.  CABLE TENSIONS WERE INSPECTED AND FOUND TO BE NORMAL.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003102100162	20031021	00162	CE  	2003	10	21	CA030930008      	1	20030924	G	7820	175400114	MUFFLER         			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	LEAKING         	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT NOTICED CO DETECTOR INDICATING MONOXIDE IN CABIN AND COULD DETECT EXHAUST ODOR. CABIN HEAT SHUT OFF AND VENT	S OPENED AND UNSCHEDULED LANDING CARRIED OUT AT ERICKSON, MB.  MUFFLER WAS REPLACED BY AME WITH OVERHAUL ACORN WELDING U	NIT AND FURTHER FLIGHT WAS UNEVENTFUL. PRESSURE TESTING OR REMOVED MUFFLER DETECTED TINY LEAK AT EXHAUST EXIT BAFFLE, NO	T LEAKING INTO HEAT MUFFLER. NO LEAKAGE DETECTED INTO MUFFLER AREA, BUT SOOT WAS PRESENT IN MUFFLER. SUSPECT LEAKAGE OCC	URS AT ELEVATED TEMPERATURES. AIRCRAFT WAS CURRENT WITH CF-90-03R2 HEAT MUFFLER INSPECTION.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003102100163	20031021	00163	CE  	2003	10	21	CA030930009      	1	20030919	G	3340	C6220010201	WIRE            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	WING TIP	BURNED          	W				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			CA											(CAN) THE NAV. LIGHT CIRCUIT BREAKER/SWITCH WOULD TRIP INSTANTLY WHEN SELECTED ON.  ALSO THE AMMETTER WOULD SPIKE TO 20+	 AMPS FOR A MICRO-SECOND. I DEAD SHORT WAS DETECTED IN THE NAV LIGHT CIRCUIT.  FURTHER INSPECTION REVEALED THAT, WITHIN 	THE LT WINGTIP THE LT NAV LIGHT WIRE HAD WORN INTO THE BONDING STRAP OF THE LT STROBE LIGHT AND FUSED TOGETHER.  THE WIR	E CONNECTED TO THE BASE OF THE NAV LIGHT SOCKET HAD ALSO SUFFERED HEAT DAMAGE FROM THE DEAD SHORT.  BOTH WIRE SEGMENTS W	ERE REPLACED WITH NEW.  AND RE-ROUTED. SYSTEM TESTED CHECKS OK.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2003102100164	20031021	00164	SW  	2003	10	21	CA030930010      	1	20030915	G	6510	AN1747A	BOLT            	BELL        		BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					THOMAS COUPLING	STRIPPED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ON THOMAS COUPLING TORQUE CHECK TWO BOLTS FOUND LOOSE. ON INVESTIGATION OF BOLTS, THREADS FOUND TO BE STRIPPED OFF	 ON LOWER END.  ALL OTHER BOLTS ON FORWARD DRIVESHAFT INSPECTED FOR SERVICEABILITY.  BOLT REPLACED NEW AND TORQUED.  CAU	SE OF DIFFICULT MIGHT HAVE BEEN BOLTS UNDER TORQUED/OVER TORQUED.  BETTER INSPECTION OF BOLTS WHEN REMOVING AND INSTALLI	NG HARDWARE.  COMPLY WITH 10-25 HOURS TORQUE CHECK INSPECTION IAW MANUFACTURER.			1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003102100165	20031021	00165		2003	10	21	CA030930011      	4	20030819	G	2562		ANTENNA         	AMERIKING   		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	ELT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						465776					(CAN) ANTENNA SEPARATED AT ANTENNA WIRE TO BASE CONNECTION.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003102100166	20031021	00166		2003	10	21	CA030930012      	4	20030818	G	2562		ANTENNA         	AMERIKING   		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	ELT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						465777					(CAN) GLUE JOINT FAILED AND ALLOWING ANTENNA TO SEPARATE FROM BASE NUT.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2003102100167	20031021	00167	EA  	2003	10	21	CA030930013      	1	20030930	G	2820	601R6227221	TUBE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					FUEL INJECTOR	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AMJOR INSPECTION (C-CHECK AND 96 MTH INSP.) A FUEL TUBE ASSEMBLY IN CENTER TANK WAS DISCOVERED WITH EVIDENC	E OF ARCING.  FURTHER INSPECTION REVEALED ADJACENT PART (STIFFENER PN 60010011193) HAD ALSO SIMILAR EVIDENCE OF ARCING. 	TUBE ASSEMBLY WAS REINSTALLED TEMPORARILY TO TAKE MEASUREMENTS. THE ACTUAL DISTANCE BETWEEN STIFFENER AND FUEL TUBE IS A	PPROXIMATELY .250 INCH IAW OEM SPECIFICATIONS. DAMAGE ON TUBE IS 0.300 X 0.370  WITH A DEPTH OF 0.010 DAMAGE ON STIFFENE	R IS 0.300 X 0.350 WITH A DEPTH 0.030 ALL COMPONENTS: TUBE, CLAMPS, SLEEVES, ETC HAVE BEEN QUARANTINED. OEM HAS BEEN ADV	ISED OF SITUATION.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003102100168	20031021	00168	WP  	2003	10	21	CA030930014      	1	20030930	G	2822		HOUSING         			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					PUMP	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						7470					(CAN) THIS FUEL PUMP WAS INSTALLED TO REPLACED A TIME (X) FUEL PUMP, AFTER MANY ATTEMPS TO REPAIRED A FUEL LEAK,THE TECH	 DISCOVERED A CRACK IN THE PUMP HOUSING.THE CRACK FOUND LOCATED AT THE BOLTS FLANGE ATTACHMENT.  THE PUMP WAS O/H IN NOV	/02 THIS PUMP WAS REPLACED AGAIN AND THE AIRCRAFT RETURN TO SERVICE.				2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2003102100169	20031021	00169	EA  	2003	10	21	CA030930015      	1	20030929	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) LT SIDE WINDOW CRACKED DURING DESCENT INTO NAS.   AIRCRAFT WAS FERRIED FOR SIDE WINDOW REPLACEMENT.						2	L	7	2 	4F			RT	A21EA   					 
2003102100170	20031021	00170	EA  	2003	10	21	CA030930016      	1	20030813	G	2420	1K4XD	TRU             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AT CRUISE ALT ADG DEPLOYED, AC1 AUTO TRANSFER MSG DISPLAYED. SMOKE IN COCKPIT.  NR 1 TRU FAILED.  FOLLOWED QRH.  D	IVERTED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003102100171	20031021	00171	EA  	2003	10	21	CA031001000      	1	20030904	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, LT WINDSHIELD CRACKED.  OLD STYLE WINDSHIELD						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003102100172	20031021	00172	EA  	2003	10	21	CA031001001      	1	20030813	G	5610	NP1393226	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			10906								(CAN) RT WINDSHIELD INNER LAYER CRACKED DURING FLIGHT. AIRPLANE FERRIED. RT WINDSHIELD REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003102100173	20031021	00173	EA  	2003	10	21	CA031001002      	1	20030518	G	5610	NP1393226	WINDSHIELD      			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) RT COCKPIT WINDOW CRACKED DURING DESCENT AT 18000 FT. AIRPLANE FERRIED FOR WINDOW REPLACEMENT.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003102100174	20031021	00174	EA  	2003	10	21	CA031001003      	1	20030508	G	5710	NP13932110	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) IN CRUISE,  AT FL 300 THE INNER PLY OF THE RT WINDOW CRACKED. THE QRH WAS APPLIED AND THE FLT CONTINUED WITHOUT FU	RTHER INCIDENT. THE AIRCRAFT WAS FERRIED WHERE THE WINDOW WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004010700060	20040107	00060	CE  	2004	1	7	CA031001004      	1	20030924	G	2810		FUEL TANK       			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					AFT MIDDLE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSPECTING THE INSIDE OF THE BLADDER TANKS FOR LOOSE PATCHES BECAUSE OF LOOSE PATCHES FOUND ON ANOTHER AIRCR	AFT.  MAINTENANCE FOUND A BABY SLEEPER INSIDE AFT MIDDLE FUEL TANK.  THIS AIRCRAFT CAME INTO THE FLEET 3 YEARS AGO AND A	S THIS COMPANY DOES NOT USE OLD CLOTHS AS RAGS IT HAS BEEN IN THE AIRCRAFT FOR SOME TIME.  OBVIOUSLY THERE WAS NO CLOSEU	P INSPECTION DONE BEFORE. THE PANEL WENT ON AFTER MAINTENANCE LAST TIME.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003102100175	20031021	00175	SO  	2003	10	21	CA031001005      	2	20030926	G	8530	AEC631397SNA	CYLINDER HEAD   			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINE	SEPARATED       	W				B				EMER. DESCENT           				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											(CAN) IN FLIGHT SEPARATION OF CYLINDER HEAD (POSITION NR 2), VIBRATION AND LOST OF POWER.  CYLINDER PREVIOUSLY INSTALLED	 MAY 23/03, AIRCRAFT TIME 3792.1 HOURS AND ACCUMULATED 119.4 HOURS OF FLIGHT AT TIME OF SEPARATION.  CYLINDER REPLACED W	ITH SA ME MODEL AND MFG.				1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2003102100176	20031021	00176	SW  	2003	10	21	CA031001006      	1	20030825	G	5340	212030154001	FITTING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11367								(CAN) PART REMOVED FROM SERVICE.NEW PART INSTALLED.						1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2003102100177	20031021	00177	SW  	2003	10	21	CA031001007      	1	20030824	G	6340	2060763731	TACHOMETER      			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					MAIN ROTOR	WORN            	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) DURING GROUND RUN PILOT EXPERIENCED LOSS OF HYDRAULIC POWER TO THE FLIGHT CONTROLS.  THE MAIN ROTOR TACHOMETER WAS	 REMOVED.  THE INTERNAL SPLINES OF THE TACH WERE WORN ALLOWING THE HYD PUMP SPLINES NOT TO ENGAGE.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003102100178	20031021	00178	GL  	2003	10	21	CA031001008      	2	20030910	G	7250	23038160	BEARING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					NR 5	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT PILOT REPORTED AN ENGINE CHIP WARNING LIGHT.  DURING SERVICEABILITY CHECK 2ND CHIP LIGHT REPORTED. T	HE ENGINE WAS DISASSEMBLED. THE TURBINE SECTION OF THE ENGINE, IN THE NR 5 BEARING AREA THE SNAP RING AND SPACER WERE UN	SEATED AND RESTING ON THE POWER TURBINE SHAFTING. FURTHER INSPECTION REVEALED THAT A BALL OF THE NR 5 BEARING WAS MISSIN	G. THE TURBINE FORWARDED TO AN OVERHAUL FACILITY.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003102100179	20031021	00179	CE  	2003	10	21	CA031001009      	1	20030923	G	2750	14601007	CONTROL CABLE   			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	TE FLAPS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A SPECIAL INSPECTION WAS INITIATED TO COMPLY WITH REMOVAL AND INSPECTION OF FLAP CONTROL CABLES THAT ARE CONNECTED	 TO THE INBOARD FLAP BELLCRANK. CABLE P/N 1460 100-7 AND 1460100-8 WERE BOTH FOUND TO HAVE SEVERAL BROKEN STRANDS AND RE	QUIRED REPLACEMENT. SERVICE DIFFICULTY ALERT AL2003-05 REFERS TO THIS PROBLEM.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2003102100180	20031021	00180	CE  	2003	10	21	CA031001010      	1	20030923	G	2750	14601007	CONTROL CABLE   			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C310  	GL  	TE FLAPS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A SPECIAL INSPECTION WAS INITIATED TO COMPLY WITH REMOVAL AND INSPECTION OF FLAP CONTROL CABLES THAT ARE CONNECTED	 TO THE INBOARD FLAP BELLCRANK. CABLE PN 14601007 AND 14601008 WERE BOTH FOUND TO HAVE SEVERAL BROKEN STRANDS AND REQUIR	ED REPLACEMENT SERVICE DIFFICULTY ALERT AL 2003-05 REFERS TO THIS PROBLEM.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2003102100181	20031021	00181	NM  	2003	10	21	CA031002001      	1	20030821	G	2435	23088002B	STARTER GEN     			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING TAKE OFF ROLL, NR 1 DC GEN CAUTION LIGHT ILLUMIN CAUSING LOSS OF ASSOC SYS AND CIRCUITS TO THAT PWR BUS.  C	REW CYCLED NR 1 DC GEN SWITCH OFF THEN ON TO RESET SYS BUT CAUTION LIGHT CONTINUED TO FLASH CAUSING VARIOUS SYS TO DROP 	OFF LINE. DC STARTER GENERATOR HAD BEEN INSTALLED PREVIOUS NIGHT DURING LINE CHECK AND ENGINE GROUND RUN FUNCTIONAL CHEC	K WAS CARRIED OUT WITH NIL DEFECTS EVIDENT.  UNSERVICEABLE DC START GENERATOR WAS REPLACED AND A/C WAS GROUND RUN AND CH	ECKED SERVICEABLE. STRIP REPORT CONFIRMED THAT STATOR WIRE (COLOR YELLOW) PIN E WITHIN ENCLOSURE WAS FRAYED RESULTING IN	 SHORT TO SPEED SENSOR WIRE (COLOR WHITE) PIN H.  START GENERATOR WAS REPAIRED AND TESTED SERVICEABLE IAW CMM 24-30-20.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100182	20031021	00182	NM  	2003	10	21	CA031002002      	1	20030930	G	2913	6617302	SHAFT           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					E/D PUMP	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLIGHT CREW REPORT LANDING, TAXI IN AND ENGINE SHUT ALL NORMAL. AFTER NR 2 ENGINE START, NR 2 ENG HYD PUMP CAUTION	 LIGHT REMAINED ON AND SYSTEM PRESSURE DIDN'T INCREASE.  METAL FILINGS WERE FOUND IN THE HYDRAULIC FILTER. NR 2 EDP SHAF	T FOUND SHEARED. TECHNICIANS CARRY OUT THE APPLICABLE AMM SYSTEM FLUSHINGS PRIOR TO RETURNING A/ C TO SERVICE . ALSO PLE	ASE REFER TO TR 29054 TASK 29-1000617807 CARRIED OUT FLUSHING OF THE NR 1 AND NR 2 HYDRAULIC SYSTEM SUCTION LINES AFTER 	THE EDP FAILURE AND TR 29-056, TASK 291000617809 AND FLUSHING OF THE HEAT EXCHANGER'S TUBES OF THE NR 2 HYDRAULIC SYSTEM	 AFTER AN EDP OR PTU FAILURE.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2004012600091	20040126	00091	CE  	2004	1	26	CA031002003      	1	20031001	G	2710	2300003231	CABLE           			LEAR  	35    	35LEAR      	5170600	CE  										CONTROL COLUMN	MISROUTED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING A DUAL FLIGHT CONTROL INSPECTION,( ON A SCHEDULED AILERON CONTROL CABLE REPLACEMENT).  FOUND CABLE MIS-ROUT	ED INSIDE THE CONTROL COLUMN ASSY BOROSCOPE INSPECTION CONFIRMED THE CABLE WAS NOT ROUTED THROUGH THE CABLE GUIDE. CABLE	 WAS RE-ROUTED.				2	L	7	2 	4F			 	A10CE   					 
2003102100183	20031021	00183	NM  	2003	10	21	CA031002004      	1	20030930	G	7931		PUMP            			BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					ENGINE OIL	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) A/C WAS ENROUTE FROM YYZ TO FCO AND WHILE OVER YQB HAD A NR 1 ENG LOW OIL PRESSURE WARNING. CREW SHUTDOWN NR 1 ENG	 AND DIVERTED TO YUL. APPEARS TO BE MAIN OIL PUMP FAILURE. METAL HAS BEEN FOUND IN GEARBOX. ENGINE CHANGE UNDERWAY.					2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2003102100184	20031021	00184	EA  	2003	10	21	CA031002005      	2	20030930	G	8520	13B27121B	CRANKSHAFT      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRANKSHAFT FAILED SB 505. AFTER REMOVAL OF PROTECTIVE COATING, CRANKSHAFT FOUND CORRODED. ALSO AREA FOUND TO HAVE 	BEEN MACHINED TO LARGEST DIAMETER PERMITTED BY SB 505. THIS IS ONE OF MANY FOUND DURING OVERHAUL, SB 530 DOES NOT SEEM T	O BE WORKING.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2003102100185	20031021	00185	SO  	2003	10	21	CA031002006      	1	20030924	G	2140	94E423	SWITCH          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HEATER	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHEN ACCOMPLISHING A O/H ON THE HEATER WE FOUND THE DIFFERENTIAL PRESS SW STUCK IN THE CLOSED POSITION. THIS IS TH	E FOURTH SWITCH FOUND DEFECTIVE IN OUR O/H SHOP. THE SUPPOSEDLY NEW IMPROVED SWITCH MFG HAS PRODUCED IS NO BETTER THAN T	HE OLD SWITCH THAT IT REPLACES.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003102100186	20031021	00186	EU  	2003	10	21	CA031003001      	1	20031003	G	2910	10546641	MANIFOLD        			BOLKMS	117   	BK117A1     	5626010	EU  										HYD SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED INSPECTION OF THE HYDRAULIC UNIT A CRACK WAS FOUND IN THE SYSTEM 1 VALVE BODY MANIFOLD.  THE CR	ACK ORIGINATES FROM A BLANKING PLUG AND PROGRESSES OUTWARDS APPROXIMATELY 11 MM.  NO LEAK OF HYDRAULIC FLUID APPARENT.  	THIS UNIT WAS RECEIVED FOR INSPECTION FROM A US CUSTOMER.  UNIT TOTAL TIME IS 8935.5 HOURS.  MANIFOLD TIME NOT KNOWN.				1	G	7	2 	3U			 	H13EU   					 
2003102100187	20031021	00187	NM  	2003	10	21	CA031003002      	1	20030929	G	2710		BUSHING         			BOEING	767   	767333      	1385301	NM  	PWA   	4060  	PW4060      	52119	NE  					AILERON CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROLLING AILERON BEYOND 3 UNITS ON CONTROL COLUMN BINDING FELT.  WHEEL VERY SLOW TO RETURN TO NORMAL. NOT AS STIFF 	WITH INPUT TO THE LEFT.  WHEEL WOULD NOT RETURN TO NEUTRAL ON ITS OWN.  FOUND INBOARD DROOP QUADRANT SIEZED.  (CROSS SHA	FT) ON INSPECTION OF REMOVED UNIT , FOUND BEARING SIEZED AND BUSHING MIGRATED.  UNIT P/N 251T1602-6 UNIT REPLACED AND AI	LERON SYSTEM NORMAL.			2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2003102100188	20031021	00188	NM  	2003	10	21	CA031003003      	1	20030427	G	5250		LOCK            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT DOOR	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, DISCOVERED HANDLE FOR FLT DECK DOOR DEADBOLT MISSING & PILOTS WERE LOCKED IN THE COCKPIT. CREW LATE	R BELIEVED AIRCRAFT VIBRATION UNSCREWED HANDLE & IT FELL TO FLOOR. AN EFFORT TO UNHINGE DOOR MADE BY CAPTAIN & FLT ATTEN	DANT. CREW UNABLE TO RELEASE LOWER HINGES OR TO RESET ANY OF HINGES AS DOOR HAD POPPED OUT & JAMMED. UPON ARRIVAL, CAPTA	IN CLIMBED OUT THROUGH EMERGENCY HATCH, MAINT CALLED OUT, DOOR REINSTALLED, ELECTRICAL PORTION OF DEADBOLT SYS DISABLED 	& SYS DEFERRED. UPON INVEST DISCOVERED 5 REPORTED CASES OF BENT/BROKEN DEADBOLT HANDLES. DUE TO FLT CREWS FORCING HANDLE	. CREATED AN IN-HOUSE TASK 5250/01X FOR THE INSPECT CHECK OF THE EMERGENCY DOOR HINGE DISENGAGEMENT SYS.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003102100189	20031021	00189	EA  	2003	10	21	CA031004001      	2	20031003	G	7314	RG9080J7AM	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN)  ENGINE DRIVEN FUEL PUMP IN SERVICE 100.1 HRS SINCE NEW. ON ENGINE RUN UP WOULD NOT SUPPLY RATED FUEL PRESSURE.  O	N IDLE PRESSURE 29 PSI.  THERE IS ANOTHER PROBLEM WITH THOSE PUMPS RG9080J7A-OUTLET AND INLET FITTING OFTHE PUMP ARE HIG	H PROFILE AND DIMENSION IN BETWEEN THE FITTINGS IS ABOUT 6 INCHES.  BUT TO INSTALL PUMP THIS DIMENSION SHOULD BE NO MORE	 THAN 5 INCHES OTHERWISE ENGINE MOUNT WOULD NOT ALLOW TO INSTALL PUMP TO ITS PLACE. YOU HAVE TO CHANGE ONE OF FITTINGS E	VERY TIME INCREASING POSSIBILITY TO GET INTERNAL STRUCTURE DAMAGED.  IT LOOKS LIKE THE PUMP WAS NOT DESIGNED FOR THIS EN	GINE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003102100190	20031021	00190	SW  	2003	10	21	CA031005001      	1	20031001	G	2460	023470000	BATTERY         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ELT	FAILED          	W				D				RETURN TO BLOCK         				H	W		ELECT. POWER LOSS-50 PC   	INADEQUATE Q C            		TX	TAXI/GRND HDL  	1			CA											(CAN) RECURRING DEFECT ON BATTERY (2BT1 - DESIGNATORS IAW ELECTRICAL DRAWING) ON LINE FAULT.  BATTERY REMOVED AND INSPEC	TED.  VOLTAGE AND CURRENT DRAW SATISFACTORY ON BENCH.  VISUAL INSPECTION REVEALED LOOSE RETAINING NUT ON ONE TERMINAL CA	USING INTERNAL ARCING AT HIGH AMPERAGE DRAW.  FURTHER INVESTIGATION OF COMPLETE BATTERY CIRCUIT ALSO REVEALED DAMAGED (O	VERHEAT) WIRES (P17A22 AND P18A22N) AT BATTERY SWITCH(2S1) PROBABLE CAUSE EFFECT OF DIODE (2CR1) PREVIOUSLY FOUND DEFECT	IVE.   ALL BATTERY TERMINALS TORQUED, NEW WIRES FABRICATED, MARKED AND INSTALLED.		1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003102100191	20031021	00191	SO  	2003	10	21	CA031006001      	1	20030929	G	3233	1959500004	ACTUATOR        			EMB   	120   	EMB120ER    	3260203	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	MLG	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			17943	17943							(CAN) AFTER TAKE OFF, PILOT SELECTED GEAR UP, HAD A RED LIGHT INDICATION ON RT MAIN LANDING GEAR.  PILOT DECIDED TO RETU	RN TO BASE, GEAR WAS SELECTED DOWN WITH 3 GREEN LIGHTS.AIRCRAFT WAS PUT ON JACKS, 3 RETRACTIONS TEST CARRIED OUT, UNABLE	 TO DUPLICATE THE RETRACTION PROBLEM.  GEAR VISUALLY INSPECTED FOUND PLAY ON RT RETRACTION ACTUATOR.   ACTUATOR REMOVED 	AND FOUND ROD END WORN OUT WITH EXCESSIVE PLAY. (.125 INCH OF PLAY FWD AND AFT) NEW ROD END INSTALLED AND SYSTEM CHECK S	ERVICEABLE. THE ACTUATOR TBO IS 18000 CYCLES. NO OTHER INSPECTIONS OR TASK CARDS ARE CALLED FOR THIS SPECIFIC ACTUATOR.		2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2003102100192	20031021	00192	SW  	2003	10	21	CA031006002      	1	20031006	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TE FLAPS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT FLAP CABLE FRAYED AT WING ROOT PULLEY AT FLAP FULL DOWN POSITION.						1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2003102100193	20031021	00193		2003	10	21	CA031006003      	4	20030909	G	3457	AIS20035	SWITCHING UNIT  	COLLINS     		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	GPS	FAILED          	W				O				OTHER                   				P			NO WARNING INDICATION     			CR	CRUISE         	1			CA											(CAN) REPORTED FAULTY NR2 RMI COMPASS BEARING, ADF INDICATION ON RMI NR1, NR2 BOTH NEEDLES WITH NO FLAGS. WHEN BOTH RMI 	S HAVE NEEDLES NR1, NR2 SELECTED TO NAV  COMPASS INDICATION ON NR 2 RMI FREEZES NON IT S CURRENT HEADING. NR 2 RMI COMPA	SS CANNOT BE SLAVED WITH NR 1 HEADING SWITCH IN MANUAL OR FREE MODES, NO HEADING FLAG IS DISPLAYED ON NR 2 RMI. STORM SC	OPE ALSO DISPLAYS  FAULTY HDG INFO AND IS NOT FLAGGED.  RMI NEEDLES SELECTED TO ADF,  NR 1 & 2 NEEDLES INDICATE 180 DEGR	EES OFF TRUE ADF BEARING. THE RMI, ADF NEEDLES DO NOT DEFLECT IN TEST MODE. EHSI, ADF NEEDLE INDICATES NORMALLY AND DEFL	ECTSIN TEST. THE ADF AUDIO IS RECEIVED NORMALLY. REPLACING THE GPS SWITCHING UNIT PN AIS200-35 CLEARS ALL FAULTS.	1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003102100194	20031021	00194	CE  	2003	10	21	CA031006004      	1	20030929	G	5521	50610000415	RIB             			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REMOVAL OF LOOSE SKIN RIVETS (AFT OF BALANCE WEIGHT, OUTBOARD OF HINGE), AN ENLARGED HOLE WAS OBSERVED WITH A	PPARENT CRACKING OF THE UNDERLYING RIB.  UPON FURTHER INVESTIGATION, RIB P/N 50-610000-415 WAS FOUND CRACKED ALONG THE B	END RADIUS IN 3 OUT OF 4 CORNERS. C/A REQUIRED REPLACEMENT OF THE LOWER SKIN, RIB ASSEMBLY, LOOSE RIVETS, AND PAINTING A	ND BALANCING OF THE ELEVATOR ASSEMBLY.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003102100197	20031021	00197	EA  	2003	10	21	CA031006005      	1	20030925	G	2751	601R930301	TRANSMITTER     			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAP POSITION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAPS FAILED AT 42 DEGREES ON LEFT FLAP (HAD 45 DEG ON RT FLAP) FOUND TO BE THE FLAP POSITION TRANSMITTER AT FAULT	.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003102100198	20031021	00198	EA  	2003	10	21	CA031006006      	2	20030925	G	7510	9091010017	ANTI-ICE SYSTEM 			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	INTAKE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE ENGINE ANTI-ICE INTAKE TUBE HAS BEEN REPLACED TWICE SINCE SERVICE BULLETIN 71-3142 WAS INCORPORATED. OTHER SIM	ILAR FAILURES HAVE BEEN DOCUMENTED ON THIS AIRCRAFT.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2003111000022	20031110	00022		2003	11	10	CA031006007      	4	20031006	G	2561	WARL8A	LIGHT           																	LIFE JACKET	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) EASTERN AERO MARINE LIFE JACKET P/N P0723E105P WERE SENT FOR OVERHAUL AND RECERTIFICATION. 100 PERCENT OF THE JACK	ETS RETURNED WITH FAILED WATER ACTIVATED LIFE JACKET LIGHT ASSEMBLIES. THESE UNITS WERE ONLY 2 YEARS OLD, MANUFACTURED I	N AUGUST/2001. THE LIFE JACKET LIGHT ASSEMBLIES WERE MANUFACTURED BY PROSAR TECHNOLOGIES INC. OF DEERFIELD BEACH, FLA. T	HE PART NUMBER OF THE DEFECTIVE UNIT IS WARL-8A. ALL WATER ACTIVATED LIGHT ASSEMBLIES WERE REPLACED AT OVERHAUL AND THE 	LIFE JACKETS WERE RE-INSTALLED BACK INTO THE AIRCRAFT. IN SPEAKING WITH THE OVERHAUL FACILITY, THEY CONFIRMED THAT IT IS	 VERY COMMON FOR THESE UNITS TO FAIL AT OVERHAUL INSPECTION.														 
2003102100205	20031021	00205	SW  	2003	10	21	CA031006008      	1	20031002	G	3250		WIRE            			SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN2     	GL  	NLG STEERING	DAMAGED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) FLT LANDING, ONCE DECELERATED TO 60 KNOTS NOSE WHEEL STEERING WAS ARMED, RESULTING IN AN UN-COMANDED FULL AUTHORIT	Y LT TURN CAUSING A/C TO LEAVE RUNWAY.  A/C WAS TAXIED OUT ON IT OWN POWER, AFTER INSP FERRIED ON FLIGHT PERMIT FOR MORE	 STRUCTURAL INSP AND REPAIR OF NOSE WHEEL STEERING SYS.  NO STRUCTURAL DAMAGE WAS FOUND. TEST AND INSP OF NOSE WHEEL STE	ERING SYS REVEALED TINY SINGLE STRAND OF WIRE INSIDE THE HARNESS SIDE OF CONNECTOR FOR THE SERVO VALVE.  STRAND OF WIRE 	WAS REMOVED, SYS TESTED AND A/C RETURNED TO SERVICE.COMPANY POLICY OF THE USE OF NOSE WHEEL STEERING HAS BEEN CHANGED TO	: UNLESS EXTENUATION CIRCUMSTANCES THE USE OF NOSE WHEEL STEERING IS LIMITED TO SPEEDS UNDER10 KNOTS.	2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P15EA	 
2003111000023	20031110	00023	NE  	2003	11	10	CA031006009      	2	20031003	G	7320	ETPU10002C	CONTROL UNIT    			BOEING	757   	757256      	1384925	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					TPU	WILL NOT TEST   	W				D				RETURN TO BLOCK         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				30880							(CAN)   LT ENGINE FLAMED OUT ON WHILE TAXIING IN. EICAS MSG 'LT ENG LP PUMP'.  TROUBLESHOOT PER FIM 75-32-00 BITE CODE 9	0 ON THE TRANSIENT PRESSURE UNIT LED TO ITS REPLACEMENT. DURING ENGINE RUN N3 WAS NOTED TO BE ON LOWER END OF LIMIT PER 	MM71-00-00 FIG.517A. FUEL FLOW GOVERNOR REPLACED.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2003102100206	20031021	00206	GL  	2003	10	21	CA031007001      	1	20030923	G	7120	MS213061C	WASHER          			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ENGINE MOUNT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INVEST OF CLUNKING SOUND COMING FROM NOSE AREA OF DA20-C1 , FOUND THAT LT LWR ENG MNT TO FIREWALL ATTACH BOLT WAS 	UNDER TORQUE (5 FT LBS VS. 15 FT LBS). MNT HAD APPROX. 60 THOU END PLAY,WAS SOURCE OF  CLUNKING SOUND. RT MNT WAS ALSO U	NDER TORQUE AT ABOUT 5 FT LBS.  ALL OF THE MS21306-1C WASHERS UNDER THE HEAD OF THESE BOLTS HAD BEEN DISHED IN. UPPER EN	G MNT TO FIRE WALL BOLTS ON A/C WERE REMOVED AND FOUND MS21306-1C WASHERS UNDER BOLT HEAD WERE ALSO DISHED IN.  MS21306-	1C WASHERS HAVE ID OF AN-7 WASHER ON AN ENG MNT BOLT THAT IS AN AN-6.  A/C WAS CHECKED AND FOUND ALL WASHERS TO BE DAMAG	E UPPER AND LOWER WITH THE LOWER SHOWING MORE WEAR.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2003102100210	20031021	00210	EU  	2003	10	21	CA031007002      	2	20031003	G	7322		SEAL            			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					FUEL CONTROL	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) APPROXIMATELY ONE HOUR AFTER DEPARTING THE CREW OBSERVED A FINE SPRAY COMING FROM NR 2 OUTBOARD NACELLE DRAIN. THE	 AIRCRAFT RETURNED TO YFB. TROUBLE SHOOTING DETERMINED THAT THE FCU SEAL HAD FAILED. THE UNIT WAS REPLACED , THE AIRCRAF	T GROUND RUN RETURNED TO SERVICE.				2	L	7	2 	3T	4	T	 	A24EU   	A196				 
2003102100212	20031021	00212	CE  	2003	10	21	CA031007004      	1	20031003	G	3230	1145802283	CLEVIS          			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					EMER GEAR EXT	OUT OF RIG      	W				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			CA											(CAN) WHILE ON A TRAINING FLIGHT AND DEMONTRATING AN EMERGENCY GEAR EXTENSION, THE GEAR WAS UNABLE TO BE RETRACTED AFTER	 EMERGENCY EXTENSION. THE A/C LANDED SAFELY AND WAS PULLED INTO THE HANGAR AND PLACED ON JACKS. MAINTENANCE FOUND THAT T	HE THICK CARPET PREVENTED THE HANDLE FROM RESETING THE BYPASS VALVE. THIS PREVENTED THE GEAR FROM RETRACTING. THE SYSTYE	M WOULD WORK CORRECTLY ONLY AFTER FOECEFULLY PRESSING THE HANDLE INTO THE CARPET BEFORE ENGAGING THE STOW CLIP. THE CLEV	IS WASADJUSTED SO THAT THE BYPASS VALVE RESETS BEFORE THE HANDLE REACHES THE CARPET AND STOW CLIP.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2003111000034	20031110	00034	CE  	2003	11	10	CA031008001      	1	20031007	G	2620	1199111992	SWITCH          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					EXTINGUISHER	SEPARATED       	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			16822								(CAN) RECENTLY BEECH ADDED  FIRE EXTINGUISHER ACTIVATION CHECK TO PHASE 2 INSPECTION, UPON COMPLETION THIS INSPECTION, F	OUND BOTH LT AND RT FAILED TEST. WITH FURTHER INVESTIGATION WE FOUND THE BACK PART OF THE SWITCHES HAD FALLEN OFF. SWITC	H IS A 2 PART SWITCH.  PART YOU SEE IN THE COCKPIT IS A LIGHT TO INDICATE AN ENGINE FIRE WHICH YOU PUSH TO EXTINGUISH A 	FIRE.  THIS PART OF THE SWITCH SENDS A SIGNAL TO SQUIB. PUSHED INDICATING PART OF SWITCH, PUSHES ON ACTIVATION PART OF S	WITCH WITCH WILL FIRE SQUIB. THE ACTIVATION PART OF SWITCH IS ATTACHED TO THE BACK OF INDICATION PART WITH CLASPS. CLASP	S HAD FAILED ALLOWING ACTIVATION PART OF SWITCH TO FALL OFF OF THE INDICATION PART LEAVING THE SYSTEM FULLY DISABLED.	1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003102100214	20031021	00214	NE  	2003	10	21	CA031008002      	3	20031008	G	6111	70242	RETAINER        			CNDAIR	CL215 	CL2151A10   	1900320	EA  						HAMSTD	43E	43E60       	NE  	PROPELLER BLADE	FAILED          	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) THE PROPELLER WAS REMOVED AND DISASSEMBLED FROM THE RT SIDE OF A CL 215 FOR SHIPMENT TO AN OVERHAUL FACILITY WHEN 	IT WAS DISCOVERED THAT NR 1 BLADE RETAINER ASSY WAS CRACKED AND SEVERAL ROLLERS WERE DESTROYED. UPON A CLOSER INSPECTION	 THE OTHER TWO BLADES HAD SIMILAR DAMAGE BUT NOT TO THE SEVERE DEGREE THAT NR 1 HAD. THE PROP FORWARD BARREL HALF P/N 52	1463-1 ALSO HAD SOME MINOR DAMAGE. THE PROP ASSY WAS FORWARD TO THE OVERHAUL FACILITY FOR ACCESSMENT.			2	H	7	2 	4R			RT	A14EA   		6	C	P871	 
2003102100217	20031021	00217	EU  	2003	10	21	CA031008003      	2	20031006	G	7322	861115	DIAPHRAGM       	ROTAX       		DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  					CARBURETOR	SWOLLEN         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA						980074					(CAN) WHEN THE CARB WAS DISASSEMBLED THE DIAPHRAGM WAS FOUND TO HAVE SWOLLEN AND WAS BUBBLED UP WHEN INSTALLED IN THE CA	RBURETOR. THE AIRCRAFT OPERATES PRIMARILY ON UNLEADED MOGAS WITH OCCASIONAL USE OF 100LL AVGAS.					1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2003102100219	20031021	00219	EU  	2003	10	21	CA031008004      	2	20031006	G	7322	861115	DIAPHRAGM       	ROTAX       		DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  					CARBURETOR	SWOLLEN         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA						980137					(CAN) WHEN THE CARBURETOR WAS DISASSEMBLED THE DIAPHRAGM WAS FOUND TO BE SWOLLEN AND WHEN INSTALLED IN THE CARBURETOR IT	 DID NOT SEAT PROPERLY. THE AIRCRAFT IS OPERATED PRIMARILY ON UNLEADED MOGAS WITH OCCASIONAL USE OF 100LL AVGAS.					1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN				 
2003102100220	20031021	00220	EA  	2003	10	21	CA031008005      	2	20030827	G	7597	C6VW10263	LINE            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					BLEED AIR	BURST           	W				A				UNSCHED LANDING         				S			AFFECT SYSTEMS            			CR	CRUISE         	1			CA			30215								(CAN) THE PILOTS HAD THE BETA BACKUP SYSTEM ON THE RT ENGINE FAIL IN FLIGHT. IT WAS DISCOVERED BY THE ENGINEER THAT THE 	BLEED AIR LINE HAD RUPTURED IN THE BRADED AREA WHERE IT LEAVES THE ENGINE COMPARTMENT AND GOES INTO THE WING. THE WIRE B	UNDLE SUSTAINED DAMAGED BY THE BLEED AIR, WHICH RESULTED IN THE HARNESS SHORTING OUT CAUSING THE BETA LIGHT FAILURE. THE	 LINE WAS ORIGINAL AND WAS CORRODED FROM THE IN SIDE OUT.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2003111000124	20031110	00124	EA  	2003	11	10	CA031009001      	2	20031006	G	7414	M3100	IMPULSE COUPLING	SLICK       	4372        	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					MAGNETO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						98040711					(CAN) DUE TO PREVIOUS IMPULSE COUPLING FAILURES, THE MAGNETO IMPULSE COUPLING IS INSPECTED EVERY 100 HOURS OF OPERATION.	THIS MAGNETO WAS REMOVED FOR A 500 HOUR INSPECTION AND THE HUB WAS FOUND TO BE VERY LOOSE.THIS COUPLING HAD ONLY 93.1 HO	URS TSN.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2003111000125	20031110	00125	CE  	2003	11	10	CA031009002      	1	20031004	G	5610	10138402522	WINDSHIELD      			BEECH 	B300  	B300B350C   	       	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT CRUISE ALTITUDE RIGHT HAND WINDSHIELD INNER PLY SHATTERED IN FLIGHT. PART WASREPLACED PRIOR TO NEXT FLIGHT.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003102100221	20031021	00221	CE  	2003	10	21	CA031009003      	1	20031007	G	7922	1584653	CONTROL VALVE   			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENGINE OIL TEMP	ERRATIC         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ENGINE OIL TEMPERATURE WITH FLUCTUATION ON LT ENGINE IN FLIGHT, IN RESPECT WITH THROTTLE LEVER. TEMPERATURE CONTRO	L VALVE REPLACED WITH NEW UNIT, GROUND POWER CHECK CARRIED OUT SATISFACTORY					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2003111000126	20031110	00126	CE  	2003	11	10	CA031010001      	1	20031002	G	5711	1181200291	SPAR CAP        	RAYTHN      		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16961	16961							(CAN) A CRACK WAS FOUND IN THE RT LOWER SPAR CAP HORIZONTAL FLANGE AT STATION 117.0 BL.THE CRACK EXTENDED FROM THE RIVET	 HOLE AFT TO THE EDGE OF THE FLANGE, AND FORWARD JUST SHY OF THE FLANGE RADIUS (OF THE VERTICAL LEG).THE CRACK WAS NOTIC	ED ON A PREFLIGHT INSPECTION BY MAINTENANCE PERSONNEL.  THE MANUFACTURER WAS CONTACTED AND AN APPROVED REPAIR INITIATED 	TO SPLICE IN A NEW PIECE OF THE LOWER CAP.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003102100222	20031021	00222	GL  	2003	10	21	CA031010002      	2	20030924	G	7250	6893647	LABYRINTH SEAL  			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) SEVERAL CHIP LIGHTS WERE EXPERIENCED DURING OPERATION WHICH PROMPTED THE REMOVALOF ENGINE. MAGNETIC PARTICLES WERE	 NOTED ON THE UPPER GEARBOX CHIP DETECTOR. UPON FLUSHING THE TURBINE NR 8 BEARING AREA FERROUS PARTICLES AND SILVER FLAK	ES WERE FOUND. UPON DISASSEMBLY, THE TURBINE AFT LABYRINTH STATIONARY SEAL WAS FOUND TO HAVE ITS SILVER PLATED ID SEPARA	TED AS A RING. THE ROTATING SEAL WAS NOTED TO HAVE THE OIL SLINGER MACHINED OFF FROM CONTACT WEAR. THE FAILURE AND ASSOC	IATED REPAIR PROCESSES FOR THIS PART ARE UNDER REVIEW.		1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2003111000128	20031110	00128	CE  	2003	11	10	CA031013001      	1	20031013	G	5751	122008515	BALANCE WEIGHT  			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION IT WAS DISCOVERED THAT THERE WERE SMALL HAIRLINE CRACKS (HORIZONTAL) AT THE THREE MOST OUTBOARD MA	SS BALLANCE WEIGHT ATTACH SCREW LOCATIONS. ONE INCH IN LENGTH.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2003111000129	20031110	00129	SO  	2003	11	10	CA031014001      	1	20030425	G	2520		FRAME           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					CABIN SEAT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THIS FORWARD CABIN SEAT AND SOME SEATS IN OTHER SAME MODEL. DUE TO THEIR AGE, HAVE WEAKENED AND CRACKED AT WELDED 	JOINTS. THE MOST COMMON LOCATON HAS BEEN THE WELDED JOINT BETWEEN THE SEAT CUSHION FRAME AND THE 'S' BEND SUPPORT TUBE. 	THE OPPOSITE END OF THIS SUPPORT TUBE IS ALSO WELDED TO THE SEATLOWER TUBULAR FRAMEWORK WHICH IS STRONG ENOUGH NOT TO CR	ACK. ALTHOUGH THE SEATISSTILL STYRONG ENOUGH TO BEAR THE WEIGHT OF THE PILOT/PASSENGER EVEN WITH BOTHTHE LEFT AND RIGHT 	SUPPORT TUBE FAILURE, THE DANGER IS AS FOLLOWS:WITH BOTH SUPPORT TUBES FAILED, IF THE PILOT WOULD LEANBACK WITH ENOUGH R	EARWARD FORCE ON THE SEAT BACK, THE SEAT WILL DISENGAGE FROM THE SEAT TRACKS INADVERTENTLY AND SLIDE BACK.	1	L	7	1 	3O	3	O		2A13    	E274				 
2003111000131	20031110	00131	SO  	2003	11	10	CA031014002      	1	20030612	G	2750	400673	BOLT            	PIPER       		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					FLAP HANDLE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AB2311					(CAN) IN SPITE OF REPLACEMENT OF CLEVIS BOLT (AN23-11) AND BUSHING (63900-174) IN COMPLIANCE WITH AD 96-10-03, PIPER SER	VICE BULLETIN 965, EXCESSIVE WEAR AND ELONGATION OF BUSHING HOLE WAS DISCOVERED. ALTHOUGH AD 96-10-03 DOES NOT REQUIRE A	 RECURRENT INSPECTION OF THE BUSHING INSTALLATION. THIS DISCREPANCY WAS FOUND AT THE TIME OF ROUTINE MAINTENANCE EVENT, 	ALTHOUGH A RECURRENT INSPECTION IS NOT REQUIRED BY AD 96-10-03, IT WOULD BE PRUDENT TO INSPECT THIS AREA PERIODICALLY.			1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111000132	20031110	00132	EA  	2003	11	10	CA031014003      	2	20030925	G	8520	LW11775	PLUG            			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	O540A1C5    	41532	EA  					PISTON PIN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  END PLUG IN QUESTION WAS WORN AWAY TO NO MORE THAN .030 OF AN INCH. AT WHICH POINT THE STEEL WRIST PIN WOULD HAVE	 BEEN WEARING HARDON THE CYLINDER WALL, IF THE ALUMINUM PIN WORE ANYMORE. ALSO NOTED, THE WRIST PIN MOVED ALL THE WAY OV	ER TOTHE WORN SIDE. THIS CREATED A SITUATION WHERE THE PISTON, ON ONE SIDE HAS A COM PLETE STEEL WRIST PIN INSIDE. THE O	THER SIDE HAD ONLY ABOUT 3/4 OF WRIST PIN INTHE PISTON HOLE. THIS HAS APPEARED TO CREATE A 'HOT' SPOT ON THE SIDE WITH N	O W RIST PIN IN IT. THE PISTON IS BURNED. THIS ALSO HAPPENED TO BE THE EXHAUST SIDE OF THE CYLINDER. THE CYLINDER HEAD I	TSELF LOOKS LIKE IT WAS OVER HEATED AND THE HEAD LOOKS CRACKED. THESE PINS WERE INSTALLED IN 1993.	1	H	7	1 	3O	3	O	 	A7EA    	E295				 
2003111000133	20031110	00133	EA  	2003	11	10	CA031014004      	2	20030925	G	8530		EXHAUST VALVE   			FOUND 	FBA   	FBA2C       	3640102	EA  	LYC   	O540  	O540A1C5    	41532	EA  					ENGINE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) EXHAUST VALVE IS BURNED, CRACKED IN TWO PLACES, RADIAL FROM CENTRE. SIDES OF VALVE ARE CHIPPED AND MISSING PIECES.	 FACE OF ROCKER ARM THAT CONTACTS TOP OF EXHAUST VALVE IS BADLY WORN AWAY. THE HARDENEDFACE IS COMPLETELY GONE AND ARM O	F ROCKER ASSEMBLY WAS RIDING ON VALVE SPRING RETAINER WASHER. VALVE RETAINER WASHER ISCRACKED THROUGH IN THREE PLACES. R	OCKER ARMS ARE OF SAME CONFIGURATION. SHOULDBE ONE OF EACH TWO DIFFERENT STYLES. CYLINDER NR 4 HAS TWO ROCKER ARMS OF SA	ME CONFIGURATION, BUT OPPOSITE TO NR 2. ROCKER ARMS WERE NOT INSTALLED CORRECTLY.		1	H	7	1 	3O	3	O	 	A7EA    	E295				 
2003111000134	20031110	00134	EA  	2003	11	10	CA031014005      	1	20031003	G	2750	C3CF1709	CONTROL ROD     			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16887								(CAN) DURING ROUTINE INSPECTION THE FLAP CONTROL ROD (TUNING FORK) WAS FOUND TO HAVE A .70 INCH CRACK RUNNING LENGTHWISE	 FROM THE THREADED END OF THE ROD.					1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2003111000135	20031110	00135	NE  	2003	11	10	CA031014006      	2	20031012	G	7230	ALF502R5	FAN BLADE       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA			30678	30678							(CAN) WHEN CLIMBING THROUGH 1200 FT AFTER TAKEOFF, BIRDSTRIKE WAS NOTED AND NR 2 ENGINE VIBRATION CLIMBED TO 1.0. AIRCRA	FT RETURNED FOR NORMAL LANDING. MAINTENANCE INSPECTION FOUND BENT AND TORN BLADES ON THE NR 2 ENGINE MAIN FAN. BIRD FEAT	HERS AND OTHER RESIDUE NOTED INSIDE ENGINE AND OVER WINGS FLAPS ETC. AIRFRAME CLEANED AND INSPECTED WITH NO DAMAGE FOUND	, NR 2 ENGINE REMOVED FROM SERVICE & REPLACED WITH SERVICEABLE SPARE. AIRCRAFT RETURNED TO SERVICE.			2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2003111000136	20031110	00136	EA  	2003	11	10	CA031014007      	1	20031014	G	5410	22850081141	DOOR            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LT NACELLE	MISSING         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) A/C TAXIED TO GATE AFTER LANDING. THE LOWER LEFT FIXED COWL DOOR WAS MISSING FROM AIRCRAFT.  SEVERAL MOMENTS LATER	 THE COWL WAS FOUND OUT ON TAXI WAY AND RECOVERED BY AIRPORT AUTHORITIES.A NUMBER OF CAMLOC FASTENERS WERE FOUND IN COWL	.THE REMAINDER OF FASTENERS WERE STILL ATTACHED TO COWL SUPPORT ON ENGINE.  ADDITIONAL DAMAGE TO COVER ASSY P/N 228-5915	4-801 AND PANEL ASSY P/N 228-50082-811 WAS ALSO SUSTAINED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003111000137	20031110	00137	EA  	2003	11	10	CA031014008      	1	20030904	G	3220		LANDING GEAR    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NOSE	MALFUNCTIONED   	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED NOSE GEAR NOT DOWN AND LOCKED.  TOWER COULD NOT VERIFY NOSE GEAR DOWN.  COMPANY AIRCRAFT DID A FLY 	BY AND VERIFIED NOSE GEAR DOORS OPEN BUT NOSE GEAR NOT DOWN AND LOCKED.  AIRCRAFT WAS RUNNING LOW ON FUEL.CREW DECLARED 	EMERGENCY AND LANDED WITH THE NOSE GEAR NOT FULLY EXTENDED. CREW REPORTED THEY FOLLOWED QRH PROCEDURES FOR GEAR DOWN DIS	AGREE.AIRCRAFT TEMPORARILY REPAIRED AND FERRIED FOR PERMANENT REPAIRS.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003111000138	20031110	00138	SW  	2003	11	10	CA031015001      	1	20031013	G	2497	AN44AWGN405	TERMINAL        	BELL        		BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					POWER CABLE	DETACHED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						NS					(CAN) THE P56A4 POWER CABLE WAS DETACHED FROM THE CRIMPED AN-4 4AWG N-40-50 ELECTRICAL LUG.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2003111000139	20031110	00139	EA  	2003	11	10	CA031015002      	1	20031013	G	2913	848847	PUMP            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) HYD NR 2 QUANTITY DROPPED STEADILY DURING FLT. AT LANDING HAD NR 2 QTY AT 25 PERCENT DECLARED EMERGENCY AND LANDED	 NORMALLY IN ALBANY. PUMP CHANGED, SYSTEM FLUSHED AND FILTERS CHANGED ALL NOW NORMAL					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003110600002	20031106	00002	NM  	2003	11	6	CA031015003      	1	20031007	G	3231	6546059	LINK            			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG DOOR	BROKEN          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) A LOUD BANG WAS HEARD UPON GEAR RETRACTION. ONCE GEAR WAS RETRACTED A STRONG VIBRATION WAS FELT.  WHEN GEAR EXTENT	ED, VIBRATION WENT AWAY. RETURNED TO YYC FOR A NORMAL LANDING. RT NOSE LANDING GEAR DOOR DOG LINK FOUND BROKEN. LINK REP	LACED, SWING CARRIED OUT AND ALL RETURNED TO NORMAL.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003110600004	20031106	00004	NM  	2003	11	6	CA031015004      	1	20031011	G	3320	325070	BALLAST         			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					CABIN LIGHTS	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) A STRONG ELECTRICAL ODOR WAS PRESENT OVER MID WING AREA. PRODUCED A BURNING WIRE ODOR.  A LIGHT BALLAST WAS FOUND 	TO BE AT FAULT.  BALLAST, FLUORESCENT LIGHT ASSY AND BULB REPLACED AND ALL CHECKS NORMAL.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003110600006	20031106	00006		2003	11	6	CA031015005      	4	20031010	G	2330	J5500	CONTROL BOX     			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					VIDEO SYSTEM CON	SMOKE           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) VIDEO TRANSCOM POWER BOX WAS SMOKING ON GROUND.  NO OTHER DAMAGE FOUND.  UNIT REPLACED AND ALL CHECKS NORMAL						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003110600007	20031106	00007	SW  	2003	11	6	CA031015006      	1	20030929	G	2822	1C2710FR	CARTRIDGE       	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					BOOST PUMP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL BOOST PUMP STOPPED PUMPING.  PUMP CHANGED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003110600009	20031106	00009	GL  	2003	11	6	CA031015007      	3	20031010	G	6110	5262163312	O-RING          	MCAULY      												MCAULY	2A34C	2A34C66     	GL  	PROP CYLINDER	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						733167					(CAN) CUSTOMER COMPLAINED OF RED OIL IN HIS ENGINE OIL. THE PROPELLER WAS SENT IN OFR REPAIR, AND IT WAS DETERMINED THAT	 THE CYLINDER WAS BADLY WORN INTERNALLY AND THAT THE SEAL WAS ALSO BADLY WORN.  THIS ALLOWED RED OIL FROM INSIDE THE HUB	 TO ENTER THE OIL SYSTEM.   A NEW SEAL AND CYLINDER WERE INSTALLED, THE PROPELLER WAS ASSEMBLED, AND LOCKED.														5	C	P3EA	 
2003110600010	20031106	00010	GL  	2003	11	6	CA031015008      	3	20031002	G	6114	1A105SCM7154	HUB             													MCAULY	1A105	1A105*      	GL  	PROPELLER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UPON O/H OF THIS FIXED PITCH PROP, FOUND AN INCLUSION IN HUB AREA THAT MEASURED ABOUT 1 INCH IN TOTAL LENGTH.  GRO	UND ABOUT 0.030 OUT OF IT AND IT SEEMED TO GET LARGER IN SIZE. SENT MFG AN EMAIL ABOUT IT, REPLIED THAT IT APPEARED TO B	E A FORGING LAP IN MATERIAL, PROP WAS THEREFORE SCRAP. THEY INFORMED US THAT WARRANTY WOULD NOT BE CONSIDERED BECAUSE SB	 137W HAD NOT BEEN FOLLOWED. THIS SB SAYS THAT PROP REQUIRES OVERHAUL 72 MONTHS OR 2000 HRS. THIS PROP WAS INSTALLED IN 	THE 70S, AND HAS NEVER SEEN AN OVERHAUL. IF THIS PROP HAD BEEN INSPECTED AS REQUIRED BY THE FACTORY, CUSTOMER WOULD HAVE	 BEEN COVERED UNDER WARRANTY, NOT TO MENTION  PROBLEMS THAT COULD HAVE A RISEN IF THIS PROGRESSED INTO A CRACK.											5	N	P918	 
2003110600015	20031106	00015	CE  	2003	11	6	CA031015009      	1	20031006	G	2720	04115262	BAR             	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RUDDER PEDAL	CRACKED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) LOSS OF LT RUDDER CONTROL IN FLIGHT. LT RUDDER TORQUE TUBE BAR FOUND CRACKED AND DEFORMED WHERE THE 'TEE' IS WELDE	D TO THE BAR.  LT RUDDER PEDAL ON THE RT. (AIRCRAFT BEING FLOWN FROM RT SEAT) CRACK 2 INCHES LONG, FROM END OF PIPE, ARO	UND HEAT AFFECTED ZONE OF THE WELD, CONTINUING FOR .7500 INCH ALONG PIPE (INBOARD).  AIRCRAFT LANDED SAFELY AT DESTINATI	ON AIRPORT (CYBW).			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2003110600016	20031106	00016	CE  	2003	11	6	CA031015010      	1	20030929	G	5510	07126153	BULKHEAD        			CESSNA	182   	182L        	2072726	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RIVETS LOOSE AT TOP OF ANCHOR DOUBLERS ON BOTH SIDES AND CRACK STARTING ON RIVET ON LEFT SIDE DOUBLER FOR ANCHOR N	UT TO RECEIVE HORIZONTAL  STAB FRONT ATTACH BOLTS.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2003110600017	20031106	00017	EA  	2003	11	6	CA031015011      	2	20030926	G	7414	ES10384585	POINTS          	BENDIX      	04RN3000    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	MAGNETO	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						G01JA047					(CAN) AT ROUTINE INSPECTION, THE MAGNETO TO ENGINE TIMING WAS FOUND TO BE CONSIDERABLY OFF (ABOUT 5 DEG OFF).  THE MAGNE	TO WAS REMOVED AND FOUND THAT THE E-GAP AND POINT OPENING WERE WAY OFF. THE POINTS ONLY HAD 100 HOURS ON THEM AND THE PL	ASTIC/NYLON FOOT WAS WEARING SO THAT THE POINT GAP WAS GETTING SMALLER AND SMALLER. ( HAD A C172 DO A PRECAUTIONARY LAND	ING IN MAY 03 DUE TO ENGINE PROBLEM WHICH TURNED OUT TO BE MAGNETO POINTS NOT OPENING AT ALL.)			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003110600018	20031106	00018	CE  	2003	11	6	CA031015012      	1	20030925	G	5711	042640032	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RT WING	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RT WING AFT SPAR FOUND CRACKED AT AFT WING ATTACH POINT.  1 INCH CRACK LOCATED FROM INBOARD END OF AFT SPAR P/N 04	26400-32 JUST BELOW SPAR REINFORCEMENT CRACK EXTENDS ALONG THE LENGTH OF THE SPAR 1 INCH.  WING REMOVED FOR REPAIR.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003110600019	20031106	00019	EU  	2003	11	6	CA031015013      	1	20030925	G	6520	350A33020005	GEARBOX         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					TAIL ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PILOT HAD AN TGB CHIP LIGHT INFLIGHT.  LANDED AT HIS BASE FOR THE ENGINEER TO CHECK IT OUT. THEY FOUND A LOT OF A 	DARK GRAY SLUDGY SUBSTANCE WHICH PUT THE CHIP LIGHT ON. THEY DRAINED THE GEARBOX ANDDID A GROUND RUN FOR ABOUT .5 HOUR A	ND FOUND NOTHING (NO METAL).  WE REPLACED THE GEARBOX WITH A NEW OVERHAULED ONE AND SENT THIS GEARBOX FOR REPAIR OR OVER	HAUL.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003110600020	20031106	00020	CE  	2003	11	6	CA031015014      	1	20031002	G	5512	12120031	DOUBLER         			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	BULKHEAD	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) HORIZONTAL ATTACHMENT POINT DOUBLER FORWARD RT CRACKED AT TOP NUTPLATE RIVET.  DOUBLER REPLACED WITH NEW.  AREA IN	SPECTED. NO OTHER FAULTS FOUND.  CAUSE IMPROPER GROUND HANDLING (SPECULATION).					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2004010600028	20040106	00028	EA  	2004	1	6	CA031015015      	1	20031009	G	3242	213293	BRAKE ASSY      			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	MLG	LEAKING         	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) BRAKE WAS SENT TO SHOP FOR WARRANTY REPAIR. SNAGGED AS LEAKING FROM PIN ON OCT 02, 2002. THE UNIT WAS REPAIRED AND	 RETURNED. BRAKE WAS INSTALLED ON 13 AUG 03, IT WORKED FOR 132.1 HOURS AND THEN STARTED TO LEAK FROM ONE OF THE PISTONS.	 THIS IS NOT THE FIRST BRAKE THAT WE HAVE SENT IN FOR WARRANTY REPAIR, AND IS ONLY THE LATEST EXAMPLE. IT IS STARTING TO	 CAUSE SOME CONCERN WITH REGARDS TO THE REPAIR FACILITY.			2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2003110600021	20031106	00021	EA  	2003	11	6	CA031015016      	2	20030924	G	8520	61151	SHAFT           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	CRANKCASE	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) CRANKSHAFT IDLER GEAR SHAFT P/N 61151 FOUND LOOSE AT ENGINE DISASSEMBLY.  2 BOLTS STD-705 UNLOOKED, BACK OFF 2C3 T	HREADS. LOCKPLATE 73817 NOT BENT FAR ENOUGH ONBOLT HEAD.  THIS ENGINE WAS REBUILT.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2003110600022	20031106	00022	NE  	2003	11	6	CA031015017      	2	20031011	G	8530	399353	CYLINDER HEAD   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CYLINDER HEAD CRACKED 360DEG FROM CYLINDER (BARREL PN 47517)						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2004010600029	20040106	00029	NM  	2004	1	6	CA031015018      	1	20031002	G	3020	4100S0283	HEATER          			BOMBDR	DHC8  	DHC8402     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	INTAKE	SHORTED         	W				O				OTHER                   				M	B	H	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	DE	DESCENT        	1			CA											(CAN) 1ST -NR 1 ENG HEATER ELEMENT UNSERVICEABLE, NO LIGHT INTO BY-PASS DOOR SWITCH, AND ENG ADAPTER HTR NR 1 CAUTION LI	GHT, C/B INTAKE LIP ENG NR 1 POP-OUT. FOUND BOTH ELEMENT OF NR 1 INTAKE HTR (SHORTED). NO FAULT FOUND INTO AC (CDS).  HT	R ELEMENT REPLACED. 2ND - DURING APPROACH, CREW NOTICE A STRONG ELEC BURN SMELL INTO  CABIN. NR 1 ENG INTAKE LIP HTR C/B	 POP-OUT, CAUTION LIGHT ENG ADAPTER HTR SMELL ORIGIN IDENTIFIED BY PILOTS, FIREMEN ASST REQUESTED BEFORE LANDING. AC LAN	D SAFELY. FOUND ENG AIR INTAKE ADAPTER HTR  SHORTED, BURNED. THIS TIME CDS FAULT CODE FOUND 'TMU 3 FAIL', TMU P/N 4100S0	18-06 REPLACED, S/N 0214 (AERAZUR). COMPLETE SYSTEM TESTED 'S'.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2003110600023	20031106	00023	GL  	2003	11	6	CA031015019      	2	20030911	G	7250	23038160	TURBINE         			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					N1	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER ENGINE WAS SHUTDOWN A RUBBING NOISE WAS HARD COMING FROM THE N1 TURBINE WHEELS.  IT WAS CONFIRMED BY MOTORIN	G THE ENGINE AFTER SHUTDOWN. TURBINE WAS REPLACED AND SENT TO AN APPROVED REPAIR FACILITY.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003110600024	20031106	00024	EU  	2003	11	6	CA031015020      	1	20031013	G	2810	7583552	SPACER          			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					FUEL TANK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SENDER REMOVED FOR CLEANING TANK, AND NOTICED SEVERAL BRIDGE SPACERS HAD EITHER BROKEN OR LOOSE RIVETS.						1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2003110600026	20031106	00026	SW  	2003	11	6	CA031015021      	1	20031015	G	5230	2720063907	RECEPTACLE      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	CARGO DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19836								(CAN) DISCOVERED CARGO DOOR (KLICK-KLACK) RECEPTACLE CRACKED WHILE COMPLYING WITH SERVICE LETTER 226-SL-027, WHICH DEALS	 WITH THIS PROBLEM.  DISCOVERED BY REMOVING ECCENTRIC BUSHING, AND IT WAS IMMEDIATELY VISIBLE. PART WAS CRACKED THROUGH 	FROM THE CENTER OF THE HOLE TO THE EDGE OF THE BRACKET. THE REST OF THE AIRCRAFT WAS INSPECTED, FOUND NO DEFECTS. AS THI	S WAS THE FIRST OF THE COMPANY FLEET TO BE INSPECTED, AND THE LOWEST TIME, MAINTENANCE WILL COMPLETE THE REST OF THE FLE	ET AS SOON AS POSSIBLE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2003110600059	20031106	00059	EA  	2003	11	6	CA031016001      	2	20031015	G	7310	3011857	LINE            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYS	RUPTURED        	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) WHILE CARRYING OUT MAINTENANCE IN THE ACCESSORY SECTION AREA OF THE LT ENGINE (PT6A-34) A STRONG FUEL SMELL WAS NO	TICED BY MAINTENANCE.  A FURTHER INVESTIGATION REVEALED THAT WITH THE AIRFRAME FUEL BOOST PUMPS SELECTED ON THAT THERE W	AS FUEL SPRAYING FROM A RIGID LINE (FUEL PRESSURE) CONNECTING THE START CONTROL UNIT AND THE FUEL CONTROL UNIT.  THE RUP	TURE WAS FOUND TO BE AT THE END OF THE LINE ADJACENT TO THE FITTING. THE LINE CAN BE FOUND IN MFG PT6A-34 IPC73-10-03 FI	GURE 1 ITEM 20 (LINE P/N 3011857). THE LINE WAS REPLACED, LEAK CHECK ED, AND THE AIRCRAFT WAS RETURNED TO SERVICE.  INCL	UDED IS AN ILLUSTRATION FROM THE IPC WITH THE AFFECTED LINE IDENTIFIED.	1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2003110600062	20031106	00062	CE  	2003	11	6	CA031016002      	1	20031016	G	3230	ADNE5323	ROD END         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON GEAR RETRACTION ON OUR BEECH 58, A BANG WAS HEARD AND FLIGHT CREW NOTICED THE NOSE GEAR PARTIALLY RETRACTED. AI	RCRAFT LANDED AND NOSE GEAR COLLAPSED. DAM AGE TO AIRCRAFT WAS THE FOLLOWING: LT AND RT PROPELLERS BENT,  NOSE GEAR DOOR	S DAMAGED, HEATER EXHAUST STACK DAMAGED, PITOT TUBE DAMAGED.  AFTER JACKING AIRCRAFT WE FOUND THE FORWARD ROD END ON THE	 RETRACT ARM TO HAVE BROKEN AROUND THE BEARING HOUSING  ROD END PART NUMBER ADNE5-323.  AIRCRAFT TOTAL TIME:7064.0  BEAR	ING DOES NOT APPEAR TO HAVE SEIZED AS IT IS STILL FREE ON THE ATTACHING BOLT.		1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2003110600087	20031106	00087		2003	11	6	CA031016003      	4	20031005	G	6122	3032125	LINE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			AP	APPROACH       	1			CA						32507					(CAN) ON APPROACH INTO SEATTLE THE RT ENGINE POWER DECREASED SLOWLY ON ITS OWN. THE CREW SHUTDOWN AND SECURED THE ENGINE	. THE AIRCRAFT LANDED UNEVENTFULLY AND WAS TOWED FROM THE RAMP.  DURING INVESTIGATION BY MAINTENANCE IT WAS FOUND THAT T	HE ENGINE WOULD ACTUALLY IDLE BUT AT MIN FLOW.  THE PY AND P3 LINES WHERE REMOVED AND BY PRESSURE TESTING REVEALED A CRA	CK JUST FORWARD OF THE AFT B NUT. CRACK WAS RUNNING HALFWAY AROUND THE CIRCUMFERENCE OF THE TUBE.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2003110600088	20031106	00088	NM  	2003	11	6	CA031017001      	1	20030929	G	2420		GENERATOR       			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	AC SYS	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) AN OPERATOR HAS REPORTED THAT DURING THE TROUBLESHOOTING OF AN AIRCRAFT THAT HAD EXPERIENCED A DUAL AC GENERATOR F	AILURE, FINDING THAT THE CAUSE TO BE TWO AC FEEDER CABLES (2421-10003G12C-1, 2421-20003F12C-1) SHORTED TO ONE OF THE BRA	CKETS ALONG THE LOWER TRAILING EDGE OF THE WING. THE BRACKET WAS FOUND TO BE MISSING IT S BONDED CATERPILLAR GROMMET. TH	ESE GROMMETS PROVIDE PROTECTION TO THE WIRING FROM THE BRACKETS SHARP EDGES. SERVICE LETTER DH8-SL-24-010 TO BE ISSUED T	O PROVIDE INSPECTION CRITERIA AND REPAIR PRACTICES TO PREVENT WIRE CHAFING IN THE TRAILING EDGE AREA INBOARD OF THE NACE	LLE, WING STATION NUMBER YW 47.5 TO YW132.70.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003110600089	20031106	00089	EA  	2003	11	6	CA031017002      	1	20031013	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT SIDE WINDOW SHATTERED IN FLIGHT. (EXTERNAL) NO CHANGE TO PRESSURIZATION.  LT WINDOW CHANGED AND NO FURTHER FAUL	TS.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003110600090	20031106	00090	EA  	2003	11	6	CA031017003      	1	20031015	G	5270		SWITCH          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					DOOR WARNING SYS	DIRTY           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) PAX DOOR WARNING AT FL200. DOOR RIGGING CARRIED OUT IAW AMM 52-11-02. NOTE: A/C HAD TWO PREVIOUS SNAGS. BIT CHECK 	FAULTED S47 AT WHICH TIME SWITCH WAS CLEANED AND LUBED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003110600093	20031106	00093	GL  	2003	11	6	CA031017004      	2	20031004	G	7321	23070108	FUEL CONTROL    			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	250C  	250C20R2    	 	GL  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE295410			(CAN) AFTER LANDING, THROTTLE WAS SNAP ROLLED TO IDLE. N2 WAS NR IMMEDIATELY INCREASED TO 105 PERCENT AND STABILIZED. EN	GINE WAS SHUT DOWN BY ROLLING THROTTLE TO CUT OFF. NOTE: ENGINE WAS DUE FOR HOT SECTION, SO RENTAL WAS INSTALLE4D. SUSPE	CT ENGINE, FCU AND GOVERNOR SENT TO REPAIR STATION FOR TEST CELL AND RECERTIFICATION, AND TO SEE IF THEY COULD REPRODUCE	 THE PROBLEM.			1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2003110600094	20031106	00094	NM  	2003	11	6	CA031017005      	1	20031017	G	3350	6050251	BATTERY PACK    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					EMERGENCY LIGHT	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) DURING TROUBLE SHOOTING OF A CONTINUOUS POPPING OF CIRCUIT BREAKER G3 (EMERG LTS) HAS BEEN REPORTED. INVESTIGATION	 SHOWED BURNED WIRING AT EMERGENCY LIGHT POWER SUPPLY BOX EPS4, FROM CONNECTOR 3351-P6.  THERE WAS SIGNS OF AN INTERNAL 	SHORT INSIDE BATTERY PACK.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003110600097	20031106	00097	SW  	2003	11	6	CA031017006      	1	20031010	G	2120		SMOKE           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	CABIN	DETECTED        	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			23562	23562							(CAN) PILOT REPORTED SMOKE IN CABIN WHEN BATTERY MASTER WAS TURNED ON. ODOR WAS CONFIRMED BY MAINTENANCE.  ALL ELECTRICA	L INSTRUMENTS, INDICATORS & AVIONICS WERE INSPECTED ON THE CAPTAINS SIDE.  GLARESHIELD AND CAPTAINS SEAT WERE REMOVED AN	D WIRING INSPECTED.  NO DEFECTS WERE FOUND.  AIRCRAFT WAS REASSEMBLED AND GROUND CHECKS CARRIED OUT WITH NO FAULTS PRESE	NT.  AIRCRAFT RETURNED TO SERVICE AND NO ADDITIONAL DEFECTS HAVE BEEN REPORTED TO DATE IN REGARDS TO THIS INCIDENT.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2003110600098	20031106	00098	CE  	2003	11	6	CA031017007      	1	20031006	G	5610	1013840251	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	FAILED          	W				I				CABIN DEPRESSURIZATION  				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) CO-PILOTS WINDSHIELD INNER PANE COMPLETELY SHATTERED IN FLIGHT.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2003110600099	20031106	00099	CE  	2003	11	6	CA031017008      	1	20031017	G	5753		SKIN            			CESSNA	500   	550         	2076604	CE  										TE FLAP	DAMAGED         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN)FLAP HAS BEEN REPAIRED ON TWO AREAS ALONG  LE.  RETURNED AFTER SEVERAL FLIGHTS WITH MAJOR DISBOND BETWEEN CARBON SK	IN PLIES AND FOAM CORE ON LOWER SKIN AT TE EXTENDING FROM IB CLOSE OUT RIB 60' SPAN WISE AND 13' FWD IN CHORD WISE DIREC	TION. SOLID LAMINATE TE SKIN HAS ALSO DELAMINATED AT TE 13-3/4' SPAN WISE FROM CLOSE OUT RIB.  UPON EXAMINATION OF FLAP,	 CRACKING HAS ALSO BEEN OBSERVED AT LE  IN LOCATION OF FILLET WHERE LE PROFILE MEETS FWD IB ROLLER LUG.  CRACKING OF PAI	NT ON LE OF IB ACTUATOR LUG AT BOND LINE IS ALSO VISIBLE.  HOLES IN ACTUATOR MOUNT FOR RETAINING PIN HAVE BEEN OVERSIZED	 AND ELONGATED. CONTINUING TO EVALUATE THE FULL EXTENT OF DAMAGE.  LIKELY CAUSE OF DAMAGE HAS NOT YET BEEN DETERMINED.	1	L	7	2 	4F			 	A22CE   					 
2003110600100	20031106	00100	CE  	2003	11	6	CA031017009      	1	20031017	G	2820		CHECK VALVE     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUEL SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER PILOTS HAD DEPLANED PASSENGERS AND BAGGAGE AT A SCHEDULED STOP THEY NOTICED FUEL COMING OUT OF THE FUEL VENT	.  MAINTENANCE TOWED THE A/C TO THE HANGER AND DEFUELED THE A/C.  THEY FOUND THAT THE ONEWAY VALVE GOING TO THE AUX TANK	, SOMETHING HOLDING THE FLAPPER OFF THE SEAT LETING FUEL GO TO THE AUX TANK OVER FILLINGIT MAKING IT DRAIN ON THE GROUND	. VALVE CLEANED AND CHECKED AND INSTALLED LINES WERE CHECKED FOR CONTAMINATION AND NONE FOUND.  A/C WAS RETURNED TO SERV	ICE.		1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003110600102	20031106	00102		2003	11	6	CA031017010      	4	20031017	G	2562	400010	ELT             																	CABIN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL RECERTIFICATION OF THE ELT IT WAS DISCOVERED THAT THE UNIT HAD NO MEASURABLE TRANSMIT POWER.  UNIT W	AS RETURNED TO THE MANUFACTURER FOR REPAIR.																		 
2003110600103	20031106	00103	EA  	2003	11	6	CA031020001      	1	20030919	G	3230		SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	LEAKING         	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) THE PILOT REPORTED UPON APPROACH, THE MLG DID NOT EXTEND AND THE DISAGREE MSG APPEARED. A SECOND ATTEMPT PRODUCED 	THE SAME RESULTS. THE LANDING GEAR WAS SUCCESSFULLY EXTENDED MANUALLY IAW EMERGENCY PROCEDURE.  THE AIRCRAFT RETURNED TO	 SERVICE FOLLOWING REPLACEMENT OF THE FOLLOWING PARTS.   MLG SELECTOR VALVE, P/N 750005000, S/N 0828  MLG PRIORITY VALVE	, P/N 4619-3, S/N 1157 NLG PRIORIY VALVE, P/N 4622,S/N 1172  NOTE: DURING INSPECTION/TROUBLESHOOTING OF THE AIRCRAFT BY 	THE MECANIC, EVIDENCE OF HEAVY HYD LEAKAGE WAS FOUND AT THE MLG SELECTOR VALVE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003110600104	20031106	00104	EA  	2003	11	6	CA031020002      	1	20030928	G	4900	WE38007703	APU             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					APU BAY	SMOKE           	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) DURING THE TAKE OFF ROLL, THE SMOKE AFT LAV WARNING MESSAGE BECAME EVIDENT. THE LAVATORY SMOKE ALARM WAS GOING OFF	 AND THERE WAS A PRESENCE OF SOME SMOKE ACCORDING TO THE FLIGHT ATTENDANT. MAINTENANCE PERFORMED SOME TROUBLESHOOTING AN	D IN COMBINATION WITH THE HISTORICAL ASSOCIATION OF THIS ANOMALY WITH A MALFUNCTION IN THE APU ELECTED TO PLACE THE APU 	ON MEL.  THE AIRCRAFT RETURNED TO SERVICE.  LATER THE APU WAS REPLACED AND THE MEL WAS REMOVED.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2003110600109	20031106	00109	EA  	2003	11	6	CA031020003      	1	20031019	G	5270		SENSOR          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) AFTER T/O UNABLE TO PRESSURIZE ABOVE 1.5 PSI. PASSENGER LATCH WARNING ON DOOR SYNOPTIC PAGE WITH ASSOCIATED (OB CO	OL) CAUTION EICAS MESSAGE AND (IB COOL) EICAS STATUS MESSAGE WITH PASS DOOR OPEN.  REPLACED OUTER DOOR HANDLE LOCKED SEN	SOR.  ALL CHECKS NORMAL.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003110600110	20031106	00110	NM  	2003	11	6	CA031020004      	1	20031018	G	3231	709121	PRIORITY VALVE  		709121      	BOEING	767   	7673Y0      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					MLG DOOR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						00100					(CAN) BEFORE LANDING (GEAR DISAGREE) MSG CAME ON AND NOSE GEAR WOULD NOT EXTEND.  ALTEXTENSION USED AND GEAR DOWN AND LO	CKED.  REPLACED NOSE GEAR PRIORITY VALVE AND GEAR SWING CARRIED OUT AND ALL NORMAL.					2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2003110600111	20031106	00111	NM  	2003	11	6	CA031020005      	1	20031016	G	2120		ODOR            			BOEING	747   	747475      	       	NM  	GE    	CF6   	CF680C2B2   	30025	NE  					CABIN	DETECTED        	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) AFTER T/O THRU 8,000 FT HAD A STRONG ODOR OF SMOKE IN C/P CABIN.  THE ODOR WAS SULPHERUS AND NOT ELECTRICAL. TURNE	D OFF RECERC AND GASPER FANS AND ODOR DISSAPPEARED.  FLT CONTINUED TO DESTINATION AND NO FURTHER FAULT.					2	L	7	4 	4F	4	F	RT	A20WE   	E13NE				 
2003110600112	20031106	00112	NE  	2003	11	6	CA031020006      	2	20031020	G	7314	1143890425	PUMP            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LP FUEL	LEAKING         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			CA											(CAN) CREW ARRIVED AT TERMINAL AND UPON SHUTDOWN WERE ALERTED TO FUEL COMING FROM RIGHT COWL.  MAINTENANCE FOUND LOW PRE	SSURE FUEL PUMP HAD BLOWN OUT GASKET BETWEEN MAIN BODY AND THE REGULATOR ASSEMBLY.  PUMP WAS REPLACED AND THE AIRCRAFT R	ETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003110600119	20031106	00119	CE  	2003	11	6	CA031020007      	1	20031010	G	2424	DGR3	CONTROL UNIT    			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ALTERNATOR	SHORTED         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) ACU SHORTED INTERNALLY CAUSING ALTERNATOR TO RUN UNCONTROLLED WHILE IN FLIGHT.  PROBLEM RESULTED IN SMOKE IN COCKP	IT WITH ALL RADIOS AND INSTRUMENTS THAT ARE ELECTRICAL TO TAKE TO MUCH POWER AND DESTROYED THEM ALL INTERNALLY.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2003110600120	20031106	00120	EU  	2003	11	6	CA031020008      	1	20031016	G	5246	5711012353	STRUT           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	OIL COOLER DOOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, IT WAS NOTED THAT THE ATTACHMENT HOLE FOR THE OIL COOLER DOOR STRUT WAS SEVERLY WORN.  THE STRU	T WAS REPLACED WITH NEW.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003110600121	20031106	00121	CE  	2003	11	6	CA031020009      	1	20031001	G	8011		BRUSHES         	LUCAS       		CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					STARTER GEN	WORN            	W				K				NONE                    				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA						96291					(CAN) LT ENGINE WOULD NOT ROTATE ON START.  INSPECTION OF THE STARTER GENERATOR DETERMINED THAT THE BRUSHES WERE EXCESSI	VELY WORN.  THE ASSEMBLY ONLY HAD 139.5 HOURS SINCE OVERHAUL.					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2003110600122	20031106	00122	CE  	2003	11	6	CA031020010      	1	20031006	G	2435		BEARING         	LUCAS       		CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					STARTER GEN	WORN            	W				K				NONE                    				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						969					(CAN) NR 2 GENERATOR WENT OFF LINE DURING TAXI TO THE RAMP. WOULD NOT RESET. MAINTENANCE DETERMINED THAT THE GENERATOR W	AS DEFECTIVE. THERE WAS PLAY IN THE SHAFT BEARING GS CAUSING REJECTION OF THE UNIT. REPORT FROM THE OVERHAUL SHOP CONFIR	MED A BEARING FAILURE INSIDE THE ASSEMBLY. UNIT HAD ONLY 164 HOURS SINCE OVERHAUL.				1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2003110600126	20031106	00126	WP  	2003	11	6	CA031020011      	2	20031016	G	7250	310166811	CASE            			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	COMBUST SECTION	CRACKED         	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			11374								(CAN) A/C WAS APPROACHING AIRPORT WITH INTENTIONS TO LAND.  RT ENG BETA LIGHT ON WITH OTHER ABNORMAL ENG INDICATIONS.  A	 MISSED APPROACH INITIATED.  RT ENGINE WOULD ONLY GENERATE 70 PERCENT TORQUE AND TEMPS AND FUEL FLOW WERE HIGH.  PILOT I	N COMMAND RETURNED TO YELLOWKNIFE AFTER CONSULTATION WITH MAINT.  A/C LANDED NORMALLY.  ON INVESTIGATION THE RT ENGINE W	AS FOUND TO HAVE A CRACKED COMBUSTION CASE.  CRACK APPEARS TO ORIGINATE AT WELD SURROUNDING FWD PLENUM DRAIN FITTING.  C	RACK TRAVELED A THIRD OF WAY AROUND FITTING, THEN PROGRESSED AFT FOR THREE INCHES.  CRACK BRANCHED AND PORTION OF CASE F	ELL AWAY, CAUSING AIR LOSS THAT WAS RESPONSIBLE FOR SYMPTOMS OBSERVED ON FLIGHT DECK.  ENGINE WAS REMOVED FOR REPAIR.	2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL	 
2003110600129	20031106	00129	NM  	2003	11	6	CA031021001      	1	20031015	G	3820	3051110137	HEAT TAPE       			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					WATER SYS	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WATER LINE P/N 10-61998-310 OUTER WOVEN COVERING BURNED THROUGH AND PLASTIC INNER CORE PARTIALLY BURNED.  ALL FOUR	 WIRE STRANDS WERE BURNED THROUGH ON THE HEATER TAPE. IN SECTION 45H20 LINE AND HEATER TAPE REPLACED.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2003110600131	20031106	00131	EU  	2003	11	6	CA031021002      	1	20030926	G	2897	E0437DL20	WIRE            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUEL SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A MTCE PREP VISIT FOR RETURNING THE A/C BACK TO LESSOR , MTCE IDENTIFIED A PROBLEM WITH NR 2 ENGINE LP VALV	E DURING THE OPERATIONAL TEST OF THE VALVE IAW TASK 28-24-00-790-003.  FURTHER TROUBLESHOOTING IDENTIFIED WIRE DL-20-AE-	FR-F, SPEC MIL-W-25038/3, 18' BACK FROM FACTORY SPLICE 4010VS, CONTAMINATED AND BRITTLE WITH EVIDENCE OF DECOLORIZATION.	  ON FURTHER EVALUATION, THE WIRE WAS FOUND TO BE CORRODED. WIRE NR 2824-4543 WAS REPLACED AND INSTALLED FROM 4010VS TO 	4008VS IAW MFG ELECTRICAL STANDARDS PRACTICE MANUAL. OPERATIONAL TEST OF NR 2 ENGINE LP VALVE WAS COMPLETED SATISFACTORY	. AIRCRAFT TOTAL TIME:39,434, LDG 14,870	2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003110600132	20031106	00132	NE  	2003	11	6	CA031021003      	2	20031015	G	7321	V319	SWITCH          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	ENGINE	STUCK           	W				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			CL	CLIMB          	1			CA											(CAN) ENGINE EXPERIENCED TORQUE SURGE DURING CLIMBOUT. ENGINE WAS SHUT DOWN IN FLIGHT.  PRELIMINARY INFO STATES THAT TQ 	DID NOT EXCEED 120 PERCENT.  PLA BETA LOCKOUT SWITCH 6141-S4 FOUND STUCK.  SWITCH HAS BEEN REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003110600133	20031106	00133	EA  	2003	11	6	CA031021004      	2	20031010	G	8500		ENGINE          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LEFT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE THE LT ENGINE LOST POWER FOR APPROXIMATELY 5 MINUTES, THEN RESTARTED. THE ONLY INDICATION WAS A LOSS OF 	M.P. TO 20' AND A YAW TO THE LEFT. THE LT PROP WAS FEATHERED BUT CONTINUED TO ROTATE SO THE PILOT FELT THE ENGINE WAS ST	ILL RUNNING AND UNFEATHERED THE PROP AT WHICH TIME SHORTLY AFTER THE ENGINE REGAINED POWER.  IN THE PROCESS OF TROUBLESH	OOTING, THE FUEL WAS SELECTED TO INBOARDS FROM OUTBOARDS.  A COMPLETE INSPECTION OF THE TURBO CHARGER, INDUCTION SYSTEM 	AND FUEL DELIVERY SYSTEM WAS CARRIED OUT ALONG WITH SAMPLES OF FUEL FROM THE TANKS AND NO PROBLEM COULD BE FOUND. THE AI	RCRAFT WAS TEST FLOWN FOR 30 MIN WITH NO FURTHER PROBLEMS.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2003110600135	20031106	00135	CE  	2003	11	6	CA031021005      	1	20030516	G	5511		SPAR            			CESSNA	175   	175         	2072502	CE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	HORIZONTAL STAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DISCOVERED A BREAK IN THE STABILIZER SPAR DURING AN ANNUAL INSPECTION.						1	H	7	1 	3O	3	O	NT	3A17    	E286	5	C	P920	 
2003110600143	20031106	00143	EU  	2003	11	6	CA031021006      	1	20031014	G	2597	224695	TRANSFORMER     			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					PSM	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE CABIN CREW REPORTED AN ELECTRICAL BURNING ODOR IN CABIN AT ROW 13.  THE LIGHTS WERE EXTINGUISHE	D AND THE ODOR DISAPPEARED AFTER 15 MINUTES.  MAINTENANCE FOUND THE TRANSFORMER AT ROW 14 ABC SMELLED BURNED.  THE PASSE	NGER SERVICE MODULE AT ROW 14 ABC WAS REPLACED AND THE SYSTEM WAS TESTED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2004012600108	20040126	00108	WP  	2004	1	26	CA031021007      	1	20031002	G	2820	S4913808AS12722	LEVER           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LT ENGINE FUEL	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			14725								(CAN) LT ENGINE DID NOT START.  NO FUEL FLOW.  MAINTENANCE FOUND FUEL VALVE CONTROL CABLE BROKEN AT LT AFT FUSELAGE SECT	ION.  A FLEET CAMPAIGN WILL BE PERFORMED.  AWAITING RESULT.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2003110600144	20031106	00144	SO  	2003	11	6	CA031021008      	2	20031015	G	8530	628488	CAM FOLLOWER    			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCA3V	PHCA3VF2    	GL  	LT ENG NR 5 CYL	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INVESTIGATING PROBLEM OF LEAKING EXHAUST VALVE CYLINDER NR 6.   A CHECK OF THE VISABLE CAMSHAFT INDICATED SE	VERE SPALLING ON CAM FOLLOWER FOR NR 5 CYLINDER.  CHECK OF OIL SCREEN SHOWED NO METAL. CHECK OF OIL SCREEN WELL REVEALED	 METAL.  AIRCRAFT HAS BEEN INACTIVE DURING THE PREVIOUS 9 MONTHS. STORED IN A HEATED HANGAR.				1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P6EA	 
2003110600147	20031106	00147	EU  	2003	11	6	CA031021010      	1	20031020	G	8011		STARTER GEN     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER WOULD NOT COME ON LINE WHEN START BUTTON PUSHED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003110600148	20031106	00148	NM  	2003	11	6	CA031021011      	1	20030720	G	3260		PROXIMITY SENSOR			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) LANDING GEAR FAILURE, AFTER TAKE-OFF GEAR UP SELECTED.  NOSE DOOR ADVISORY LIGHT CAME ON FOR ABOUT 30 SEC AND OFF.	  ON AGAIN FOR 1 MIN AND SO ON. RETURNED BACK TO BASE.  LIGHT OFF BEFORE LANDING. INVESTIGATION/ACTION NOSE LANDING GEAR	 DOOR CLOSED PROXIMITY SENSOR REPLACED IAW AMM 32-61-06.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003110600150	20031106	00150	SW  	2003	11	6	CA031021012      	1	20031010	G	6510	2060403459	HANGER ASSY     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 1200 HR INSPECTION AFT OIL COOLER BEARING HANGER WAS FOUND TO BE CRACKED AT THE 1200 O'CLOCK POSITION.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003110600151	20031106	00151	EA  	2003	11	6	CA031022001      	1	20031002	G	2760	M633741	BALL JOINT      			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					SPOILER	SEPARATED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) PRIOR TO TOUCHDOWN THE AIRCRAFT ROLLED TO THE RT.  FLIGHT SPOILERS WERE SELECTED, BOTH EXTENDED AT FIRST THEN THE 	LT SPOILER SUDDENLY RETRACTED TO THE '0' POSITION AS A RESULT OF THIS THE AIRCRAFT IMMEDIATELY ROLLED TO THE RT. THE PIL	OT CORRECTED THE CONDITION BY TURNING THE CONTROL WHEEL TO THE LEFT. ON GROUND, MAINTENANCE INSPECTED THE SPOILER SYSTEM	 AND IT WAS NOTICED THAT THE BALL JOINT ON THE SPOILER CABLE HAD SEPARATED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003110700001	20031107	00001	NM  	2003	11	7	CA031022002      	1	20030723	G	3241	6007047	TRANSDUCER      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					WHEEL SPEED	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) WHEN LANDING THE BRAKES HAD ALMOST NO EFFECT, ONLY AT VERY SLOW SPEEDS DID THE BRAKES SEEM TO WORK A LITTLE AND ON	LY WITH VERY HARD APPLICATION ON THE BRAKE PEDALS.  RESULT WAS A VERY LONG LANDING, BUT WITH PLENTY TO SPARE.  INVESTIGA	TION/ACTION, HYD SYSTEM NR 1 BLED IAW AMM 29-10-00. BRAKE TEST PERFORMED. THESE ACTIONS DID NOT SOLVE THE PROBLEM. THE P	ROBLEM HAVE RE-OCCURRED.  THIS TIME BOTH HYD SYSTEM 1 AND 2 WERE BLED. ALL BRAKES BLED AND THEN TAXI AND BRAKE TEST PERF	ORMED W/O SUCCESS. DURING A MORE THOROUGH INSPECTION OF WHEEL SPEED TRANSDUCERS, A MECHANICAL RESISTANCE WAS NOTED ON WH	EEL SPEED TRANSDUCERS POS 2,3 AND 4.  WHEEL SPEED TRANSDUCERS REPLACED ACC AMM 32-46-11.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2004010700074	20040107	00074	NM  	2004	1	7	CA031022003      	1	20031020	G	5313		STRINGER        			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TIE CLIP INSPECTION IAW SB 737-53-1085, FOUR CRACKS WERE FOUND ON STRINGER 10R AT STN 807, 827, 847, AND 86	7. ALL CRACKS WILL BE REPAIRED IAW SRM 53-10-3PG 15, FIG 2, ( SHEET 7). ACFT TIMES 56965.51. ACFT CYCLES 53441.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003110600153	20031106	00153	EA  	2003	11	6	CA031022004      	1	20031011	G	3246	9543077	WHEEL           		9543077     	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					RIM	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA						74196					(CAN) ON THE LANDING ROLL, A BANG WAS HEARD AND THEN THE AIRCRAFT LEANED AND TURNED TOTHE RIGHT A BIT.  THE CO-PILOT OBS	ERVED THE RIGHT MAIN TIRE WAS FLAT.  THE A/C WAS SHUT DOWN AND PASSENGERS AND CARGO WERE OFF-LOADED. A PIECE OF THE WHEE	L RIM WAS FOUND 100 METERS BEHIND THE AIRCRAFT.  MAINTENANCE WAS DISPATCHED AND THE AIRCRAFT REPAIRED AND RETURNED TO SE	RVICE.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2003110600156	20031106	00156	EU  	2003	11	6	CA031022005      	1	20030817	G	2435	23085024	BEARING         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STARTER GEN	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) FRONT BEARING FAILED IN FLIGHT AND PILOTS REPORTED VIBRATION/RUMBLE FROM ENGINE.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003110600173	20031106	00173	CE  	2003	11	6	CA031022006      	1	20031021	G	5522	10061004217	COUNTERWEIGHT   	BEECH       	1156100102  	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					LT ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14478								(CAN) ON PRE-FLIGHT INSPECTION, THE LT ELEVATOR WAS MOVED AND A RATTLING NOISE WAS HEARD.FURTHER INSPECTION REVEALED THE	 INBOARD BALANCE WEIGHT, OUTBOARD BALANCE WEIGHT SUPPORT WAS LOOSE. THE THREE ATTACHING BOLTS PN AN174-6 WERE FOUND BACK	EDOUT APPROX. 1/8 INCH.  THE ELEVATOR SKIN HAD TO BE DE-RIVETED TO ACCESS THESE BOLTS.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2004012600111	20040126	00111	NM  	2004	1	26	CA031022007      	1	20031017	G	3233	NAS759011	BUSHING         			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) RELEASED IN-SERVICE ACTIVITY REPORT2003-09. AN ARTICLE IN THIS REPORT REFERENCED A SITUATION DURING MANUFACTURE OF	 SOME AC, BUSHING PN: NAS75-9-011 WAS OMITTED FROM ASSEMBLE PROCESS OF THE NOSE LANDING GEAR RETRACTION ACTUATOR INTO AI	RCRAFT. ALL OF OUR FLEET AIRCRAFT WERE SUBJECTED TO INSPECTION IAW THE INFORMATION PROVIDED IN THE IN-SERVICE ACTIVITY R	EPORT AND AS A RESULT OF THE INSPECTIONS ONE OF OUR A/C WAS FOUND TO HAVE THE BUSHING, AS DESCRIBED, OMITTED DURING ASSE	MBLE.  DUE TO THE MISSING BUSHING SUPPORT BRACKET PN: 85310340-015 WAS FOUND TO BE DAMAGED. NO OTHER DAMAGE WAS IDENTIFI	ED IN THE WHEEL WELL.  THE DAMAGED SUPPORT BRACKET WAS CHANGED ALONG WITH A NEW BUSHING AND ATTACH BOLT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003110600176	20031106	00176	CE  	2003	11	6	CA031022008      	1	20030925	G	5540	11564000035	HINGE           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					RUDDER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14388								(CAN) DURING VERTICLE STAB. DE-ICE BOOT REPLACEMENT, IT WAS NOTED THAT THREE OF THE SIX JO-BOLT FASTENERS THAT ATTACH TH	E UPPER RUDDER HINGE BRACKET TO THE SPAR WERE LOOSE.THESE FASTENERS WERE REPLACED WITH NEW.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003110600178	20031106	00178	EU  	2003	11	6	CA031022009      	1	20031021	G	2752	9787320003	DRIVE UNIT      			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) FLAPS FAILED TO FULLY RETRACT AND FLAP WARNING LIGHTS CAME ON.FOUND THE FLAP POWER DRIVE UNIT HAD FAILED INTERNALL	Y AND WOULD NOT DRIVE THE FLAPS. PDU REPLACED AND FLAPS RIGGED AS PER THE MAINTENANCE MANUAL. FLAP SYSTEM OPERATED SERVI	CEABLE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003110600179	20031106	00179	SO  	2003	11	6	CA031022010      	1	20031003	G	5711		SPAR            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					DRAG LINK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED AT BOLT HOLES AT SPAR ATTACHMENT.						1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2003110700008	20031107	00008	CE  	2003	11	7	CA031022011      	1	20031012	G	3233	S24266	BEARING         			CESSNA	177   	177RG       	2073709	CE  										MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) PILOT WAS COMING INTO LAND SELECTED GEAR DOWN. HEARD LOUD BANG FROM REAR OF A/C AND GOT NO GREEN DOWN LIGHT INDICA	TION. ABORTED APPROACH & TRIED SEVERAL TIMES TO GET GEAR DOWN, NO SUCCESS. PUT GEAR HANDLE DOWN & DID FLY-BY. TOWER REPO	RTED HE HAD NOSE GEAR DOWN BUT MAIN GEAR WAS PARTIALLY DOWN. PILOT ELECTED TO DO LANDING ON GRASS BESIDE RUNWAY. LANDED 	SUCESSFULLY LITTLE DAMAGE TO AIRCRAFT. NLG WAS DOWN & LOCKED. A/C LIFTED UP AND GEAR WAS LOCKED DOWN. AIRCRAFT WAS PUT O	N JACKS AT HANGER. FLOOR WAS LIFTED & FOUND ROD END ATTACHING MLG ACTUATOR TO MLG LINKAGE BROKEN, PART HAD BROKEN OFF GO	T UNDERNEATH LINKAGE &STOPPED GEAR FROM LOCKING DOWN. ROD END REPLACED & GEAR SWING COMPLETED WITH NO PROBLEMS.	1	H	7	1 	3O			 	A20CE   					 
2003110700010	20031107	00010		2003	11	7	CA031023001      	4	20031022	G	2211	6229815704	CIRCUIT CARD    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					ACTUATOR	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA						111					(CAN) IN CRUISE THE RUDDER MOVED WITH NO INPUT CAUSING YAW. THE MOVEMENT WAS INTERMITTENT ALWAYS RETURNING TO NEUTRAL. R	EPLACED FCC CARD AND YAW DAMPER ACTUATOR, CHECKS SERVICABLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012600092	20040126	00092	NM  	2004	1	26	CA031023002      	1	20031022	G	2751	2061121	INDICATOR       			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					TE FLAPS	STICKING        	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) ON CLIMB, RT OB FLAP STOPPED AT 3 DEGREES. A FLAP ASYMMETRY CONDITION OBSERVED.  AIRCRAFT RETURNED TO BASE WITHOUT	 INCIDENT. OB FLAP INDICATOR REPLACED IAW MM 27-52-21 AND FUNCTIONALLY TESTED SERVICEABLE.  NO FURTHER INCIDENT ON SUBSE	QUENT FLIGHT.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2003110700011	20031107	00011	CE  	2003	11	7	CA031023003      	1	20031012	G	3233	S24266	BEARING         			CESSNA	177   	177RG       	2073709	CE  										MLG ACTUATOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH FOR LANDING PILOT SELECTED GEAR DOWN ANDHEARD A LOUD BANG FROM BEHIND HIM RECIEVING NO GREEN DOWN LIGH	T THE PILOT ABORTED HIS LANDING. HE CIRCLED THE AIRPORT AND TRIED NUMEROUS TIMES TO GET HIS GEAR DOWN. FINALLY HE SELECT	ED GEAR DOWN AND DID A FLY BY OF THE TOWER. TOWER PERSONNEL SAW TOLD HIM THAT HIS NOSE GEAR WAS DOWN BUT HIS MAIN GEAR W	AS JUST HANGING THERE. PILOT LANDED ON GRASS BESIDE RUNWAY AND LANDED SAFELY. THE NOSE GEAR WAS LOCKED DOWN BUT THE MAIN	 GEAR WAS NOT.THE FLOOR WAS LIFTED AND DISCOVERED THAT THE MAIN GEAR ACTUATOR ROD EN D THAT IS ATTACHED TO THE GEAR HAD 	BROKEN AND THE BROKEN PIECE HAD FALLEN INTO THE GEAR BELLCRANK AND JAMMED STOPPING THE GEAR FROM LOCKING DOWN CORRECTLY.	1	H	7	1 	3O			 	A20CE   					 
2004010500112	20040105	00112	NM  	2004	1	5	CA031023005      	1	20031020	G	3260	464505	DOWNLOCK SENSOR 			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					RT MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) WHEN SELECTING GEAR DOWN DURING APPROACH RIGHT MAIN LANDING INDICATED UNSAFE. GO-AROUND PERFORMED AND MALFUNCTION 	CHECKLIST CONSULTED AND PERFORMED FOR ALTERNATE GEAR EXTENSION. ALTERNATE GEAR INDICATION SHOWED 3 GREEN LIGHTS, BUT NOR	MAL LANDING GEAR INDICATION STILL SHOWED RIGHT MAIN GEAR UNSAFE. PASSENGERS SEATED AROUND PROPELLERS RESEATED FOR PAX CO	MFORT REASONS. NORMAL LANDING PERFORMED WITH FIRE AND RESCUE ON STANDBY.SAFETY PIN INSTALLED AFTER SHUTDOWN. PASSENGERS 	DEBRIEFED IN AIRCRAFT AND PAX OFFERED ADDITIONAL DEBRIEFING.R/H MLG DOWNLOCK SENSOR REPLACED. AIRCRAFT RETURNED TO SERVI	CE.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003110700012	20031107	00012	EU  	2003	11	7	CA031023006      	1	20031022	G	2752	9787320308	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAP	BINDING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE EXTENDING THE FLAPS FOR LUBRICATING, A CHATTERING NOISE WAS HEARD, FOLLOWED BY A FLAP FAILURE. INVESTIGATION	 REVEALED THE L/H INBOARD AND RT OUTBOARD FLAP ACTUATORS TO BE EXTREMLY HOT AND BINDING. THE ACTUATORS WERE REPLACED AND	 RIGGED, AND THE AIRCRAFT RETURNED TO SERVICE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003110700013	20031107	00013	SW  	2003	11	7	CA031023007      	1	20031019	G	6510	407040339101	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL ROTOR	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT HAD TAKEN OFF. SHORTLY THEREAFTER HEARD A THUMP FROM THE REAR FOLLOWED BY VIBRATION. ON REACHING FINAL DESTI	NATION INSPECTION REVEALED NR 5 TR DRIVE SHAFT BEARING 407-040-339-101 FAILED.OVERHEAT EVIDENCE ON THE HANGAR AND DAMAGE	 SUSTAINED TO THE RELATED DRIVE SHAFT SEGEMENT AS A RESULT OF WOBBLING WITHIN THE HANGAR. 3 BALLS STILL IN THE BEARING R	ACE  AND 6 LODGED IN THE TAIL ROTOR GEARBOX FAIRING.			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003110700014	20031107	00014	NM  	2003	11	7	CA031023008      	1	20031010	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8402     	       	NM  	PWC   	150   	PW150A      	 	EA  					HYD SYS	LEAKING         	W				H				DEACTIVATE SYST/CIRCUITS				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) DURING DESCENT FLIGHT CREW REPORT LT HYRAULIC SYSTEM PRESSURE GOING DOWN AND CONFIRM HYD.  LEAK COMMING FROM LT NA	CELLE. FLAP EXTENSION CUTOUT BUT VERY SLOW. A/C LANDED OK. LT ENGINE DRIVE HYDRAULIC PUMP FOUND LEAKING AT PUMP INTERFAC	E (SPLIT LINE). NEW PUMP INSTALLED, HYD SYSTEM FLUSHED AND RESERVOIR SERVICED, CASE DRAIN,  PRESSURE AND RETURN FILTER I	NSPECTED AND REPLACED . A/C RETURN TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2003110700015	20031107	00015	EU  	2003	11	7	CA031024001      	1	20031022	G	5320		ATTACH FITTING  			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					MAINT LADDER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) THE LT UPPER ATTACH PLATE OF THE MAINTENANCE LADDER,  LOCATED IN THE AFT SECTIONOF THE AIRCRAFT, HAS FAILED (FATIG	UE CRACK ) BRINGING THE RELEASED POST TO 0.87 5 INCH FROM THE RUDDER INPUT ROD. EVENTUAL FAILURE OF THE RT UPPER ATTACH 	PLATE COULD POSSIBLY BRING THE LADDER IN CONTACT WITH THE RUDDER INPUT ROD.AIBUS INDUSTRIE WAS ADVISED AND WILL PROVIDE 	A REPAIR SCHEME.			2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2003110700016	20031107	00016	NE  	2003	11	7	CA031024002      	2	20031023	G	7200		ENGINE          			AIRBUS	A319  	A319114     	3930350	NM  	CFMINT	CFM56 	CFM565A3    	 	NE  					LEFT	OVERSPEED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	M	J	INADEQUATE Q C            	OVER TEMP                 	WARNING INDICATION        	CL	CLIMB          	1			CA			19143								(CAN) WHILE CLIMBING OUT BETWEEN 10,000 AND 11,000 FT THERE WAS AN OVERSPEED ON THE LEFT ENGINE FOLLOWED BY EGT GOING OF	F THE CLOCK. ENGINE SHUT DOWN AND RETURNED TO LAX. ENGINE CHANGE UNDERWAY. WILL AWAIT ENGINE REPORT WHEN RETURNED TO SHO	P.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2003110700019	20031107	00019		2003	11	7	CA031024003      	4	20031022	G	3417	8220372154	ADC             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) ON DEPARTURE AT 2000 FT THE SPEED BUG WENT FROM 200 KTS TO 40 KTS UN COMMANDED AT THE SAME TIME THE 'STALL FAIL MS	G' ON FOR 30 SEC. PURGED NR 1 AND 2 PITOT LINES AND CHANGED ADC NR 1.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003110700062	20031107	00062	SW  	2003	11	7	CA031024004      	1	20031023	G	7920	GT331	OIL FILTER      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					RT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED OIL SAMPLE ON THE RT ENGINE THE OIL FILTER REMOVED WAS NOTEDTO BE DAMAGED AT THE RADIUS OF THE 	MOUNTING FLANGE. THIS IS THE OIL FILTER THAT IS INCLUDED IN THE WEAR CHECK CANADA INC. P/N GT-331 OIL SAMPLE KITS.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003110700063	20031107	00063	SW  	2003	11	7	CA031024005      	1	20031023	G	7920	GT331	OIL FILTER      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					RT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON PILOT PREFLIGHT INSPECTION IT WAS DISCOVERED THE RT ENGINE OIL FILTER BYPASS WAS POPPED, THE OIL FILTER WAS REP	LACED, AND OIL SAMPLE TAKEN.  IT WAS NOTED THE THE REMOVED OIL FILTER WAS DAMAGED WITH MATERIAL MISSING FROM THE FLANGE.	  WE BELIEVE THE FILTER WAS PLUGGED FROM THE MISSING MATERIAL OF THE FLANGE AFTER ENTERING THE OIL PUMP.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003110700064	20031107	00064	SW  	2003	11	7	CA031024006      	1	20031023	G	7920	GT331	OIL FILTER      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					LT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE OIL FILTER BYPASS PIN WAS FOUND POPPED ON THE LT ENGINE.THE OIL FILTER WAS REPLACED AND OIL SAMPLE TAKEN. DAMA	GE TO THE REMOVED OIL SAMPLE WAS NOTED. THE MOUNTING FLANGE OF THE FILTER WAS MISSING FROM THE RADIUS INWARD. THE OIL FI	LTER IS INCLUDED IN THE WEAR CHECK CANADA INC. P/N GT-331 OIL SAMPLE KITS.THE FILTER WAS BELIEVED TO BE PLUGGED FROM THE	 MISSING MATERIAL OF THE OIL FILTER AFTER ENTERING THE OIL PUMP.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2003110700066	20031107	00066	NE  	2003	11	7	CA031024007      	2	20031021	G	7310	30607591	PUMP            			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ASTRA SPX SN 079 EXPERIENCED A STRIPPED FUEL LINE FITTING ON THE RT ENGINE MOTIVE FLOW PUMP INLET PORT. FOUND DURI	NG THE ENGINEER'S MORNING POST-FLIGHT INSPECTION, 21 OCT 2003. THE AIRCRAFT EXPERIENCED HEAVY TURBULENCE THE PREVIOUS NI	GHT,THOUGH THIS IS NOT CONSIDERED THE CAUSE OF THE FAILURE, IT MAY HAVE CONTRIBUTED TO THE FINALITY OF IT. FUEL PUMP REP	LACED AND AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2003110700067	20031107	00067	NE  	2003	11	7	CA031027001      	2	20031024	G	7310	EM4843	SHUTOFF VALVE   			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6A66      	52043	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ENGINE COWLS WERE REMOVED FOR 150 HOUR INSPECTION AND A SMALL AMOUNT OF FUEL WAS FOUND IN THE BOTTOM RIGHT COW	L.  WHEN THE RT FUEL BOOST PUMP WAS TURNED ON TO LOCATE THE SOURCE FUEL WAS OBSERVED DRIPPING AT ABOUT 1 DROP PER 2 SECO	NDSFROM THE RT ENGINE FIREWALL SHUTOFF VALVE. THE LEAK WAS FROM THE ACTUATOR END NOT THE MAIN BODY. FAA AD 2003-17-03 HA	D BEEN COMLIED WITH THE VALVE HAD BEEN MODIFIED AS PER ELECTROMECH SB 484-3AB.			1	H	7	2 	3O	4	T	RT	A59EU   	E26NE				 
2003110700070	20031107	00070	NM  	2003	11	7	CA031027002      	1	20031022	G	5512		PANEL           			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					HORIZONTAL STAB	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT HORIZONTAL STABILIZER LOWER TRAILING EDGE ACCESS PANELS AFT SUPPORT BEAMS MISSING 7 HORIZONTAL ATTACH BOLTS BAS	ED ON THE CONDITION OF THE AREA IN WHICH THE DISCREPANCIES WERE FOUND AND THEFACT THAT THE ACFT WAS ON A M01 CHECK INDIC	ATES THAT THE ACFT WAS RECEIVED FROM THE FACTORY IN THIS CONDITION.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2004012600114	20040126	00114	NM  	2004	1	26	CA031027003      	1	20031024	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SMALL CRACK (APPROX..5000 INCH). FOUND IN OUTER SKIN AT STR.14L,BETWEEN BS 824 ANDBS828. CRACK REPAIRED IAW REV87,	SRM 53-30-3 FIG48 DETAIL XIV SHEET12.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003110700072	20031107	00072	CE  	2003	11	7	CA031027004      	1	20031009	G	6120		CONTROLLER      			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) TAKE-OFF WAS REJECTED IN YXY DUE TO AUTO FEATHER FAILING TO ARM ON THE RIGHT SIDE A/C GROUND RUN TESTED-NORMAL-NO 	FAULT FOUND A/C RELEASED FOR RETURN TO SERVICE					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003112600072	20031126	00072	NM  	2003	11	26	CA031027005      	1	20031025	G	2910		MODULE          			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					A-HYD SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) ON DECENT NR1 A SYS LOW PRESSURE LIGHT ILLUMINATED. SHORTLY, NR 2 A SYS LOW PRESSURE LIGHT ILLUM. CREW ACCOMPLISHE	D QRH FOR LOSS OF SYS A. EMERGENCY DECLARED & LANDED. MAINT CHECKED SERVICEABLE HYD SYS RES STANDPIPE & PRESSURE. ENG RA	N AND HYD PRESSURE SERVICEABLE AT 3000 PSI. MAINT SUSPECTED PRESSURE RELIEF VALVE IN A SYS PRESSURE MODULE TO BE AT FAUL	T. A SYS PRESSURE MODULE REPLACED AND GROUND RUNS SATISFACTORY.  AC RELEASED FOR SERVICE. TO PERFORM A FULL INSP AND FUN	CTION OF RESERVOIR AIR PRESSURE SYS TO ENSURE FAULT WAS NOT CAUSED BY CAVITATING PUMPS DUE TO HEAD PRESSURE LOSS.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2003110700073	20031107	00073	CE  	2003	11	7	CA031027006      	1	20031017	G	3221	51420025	DRAG BRACE      			CESSNA	441   	441         	2076020	CE  										NLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHEN COMPLYING WITH CESSNA SERVICE BULLETIN CQB91-9 FOUND CRACK AT RAM ATTACH LUG. REPLACED DRAG BRACE.						1	L	7	2 	3T			RT	A28CE   					 
2003110700085	20031107	00085	CE  	2003	11	7	CA031027007      	1	20031001	G	5511	04320016	RIB             			CESSNA	150   	150K        	2071822	CE  	CONT  	O200  	O200A       	17020	SO  					HORIZONTAL STAB	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WHEN REPLACING THE LT LEADING EDGE HORIZONTAL STABILIZER SKIN PN 0432001-16 DUE TO IT BEING DENTED. IT WAS FOUND T	HAT BOTH INBOARD NOSE RIB ASSEMBLIES WERE CRACKED. THEY WERE REPLACED WITH NEW FACTORY PART PN 0432001-6 RT AND PN 04320	01-46 LT.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2003110700086	20031107	00086	CE  	2003	11	7	CA031027008      	1	20031011	G	2731	335240253	SHAFT           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ELEVATOR DRIVE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELECTRIC TRIM (ELEVATOR) DRIVE SHAFT SHEARED. THIS CAUSED ONE CAPSTAND TO OPERATE AND THE OTHER TO MOVE FREELY ON 	ITS OWN. THIS MOVEMENT CAUSED THE BRIDAL CABLES TO UNWIND AND CREATE RESTRICTION. THE TRIM WAS RESTRICTED FROM GOING NOS	E DOWN. MANUAL MOVEMENT OF THE TRIM WAS ALSO RESTRICTED.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2003110700087	20031107	00087	NM  	2003	11	7	CA031028001      	1	20031028	G	2720		ROD END         			BOEING	767   	767333      	1385301	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					RUDDER CONTROL	UNSAFETIED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) RT ELEVATOR LOST MOTION DEVICE TO ELEVATOR CONTROL ROD END AT LOST MOTION DEVICE NOT IN SAFETY.  ROUTINE INSPECTIO	N DURING A M01 CHECK FOUND THE ROD END WAS NOT IN SAFETY. LOCKWIRE COULD BE INSERTED THROUGH THE INSPECTION HOLE. THE WI	TNESS SEAL FROM THE FACTORY WAS ALSO INTACT. REF IPC 27-31-53-02 SHT 1 ITEM 40 & 45 AND AMM 27-31-00 SHT 3 FIG 3. AIRCRA	T TOTAL TIME: 9,414HRS/1,352CYC			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2003122900191	20031229	00191		2003	12	29	CA031028002      	4	20031011	G	3497	S10711	TUBE            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	PITOT	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION OF THE AIRFRAME IT WAS FOUND THAT THE SECTION OF PITOT TUBE IN THE WING NEAR THE PITOT	 TUBE ASSEMBLY WAS FOUND MELTED. THE REASON FOR THIS CONDITION WAS DETERMINED TO BE INTERFERENCE ON THE TUBE BY THE WIRI	NG FROM THE PITOT HEATER ELEMENT. THERE WAS NO PREVIOUS REPORT BY THE CREW INDICATING ANY RELATED SYSTEMS FAILURE HOWEVE	R AT THE TIME OF INSPECTION IT WAS DEFINITELY FOUND TO BE DEFECTIVE. THE LINE WAS REPLACED AND ROUTING VERIFIED AS NOT T	O INTERFERE WITH WIRING AGAIN. AIRCRAFT TOTAL TIME WAS 11770.		1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2003110700088	20031107	00088	CE  	2003	11	7	CA031028003      	1	20031028	G	3230	1158100283	PINION GEAR     			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING GEAR SWING LT HAND MAIN LANDING GEAR WAS SHUTTERING ON RETRACTION.  REMOVED ACTUATOR AND REPLACED WITH OVER	HAULED PART.TOOK ACTUATOR TO OVER HAUL FACILITY AND DISASSEMBLED AND DISCOVERED DEFECT.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2003110700089	20031107	00089	SO  	2003	11	7	CA031028004      	1	20031016	G	2424	756055	VOLT REGULATOR  			PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320D2A     	41508	EA  						FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) VOLTAGE REGULATOR FAILED AND ALSO CAUSED DAMAGE TO THE ALTERNATOR DIODES. THE ALTERNATOR DIODES WERE REPLACED, AND	 THE VOLTAGE REGULATOR REPLACED WITH A NEW VR200A UNIT. CHARGING SYSTEM TESTED OK.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003112600105	20031126	00105	EU  	2003	11	26	CA031028005      	1	20031026	G	5280		DOOR            			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					LT MLG	DETACHED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) AT 30,000 FT. ON DESCENT AT 300KIAS A SHUDDER  WAS FELT ON AIRCRAFT. ALL GEAR INDICATION WAS NORMAL. LANDING GEAR 	LOWERED FOR LANDING ALL GREEN LIGHTS NO RED LIGHT IN HANDLE. LANDED NORMALLY, AT CHALKSIT WAS OBSERVED LT OUTBOARD GEAR 	DOOR WAS SEPERATED FROM HINGE.				2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2003112600106	20031126	00106	CE  	2003	11	26	CA031028006      	1	20031027	G	3244	178K431	TIRE            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					MLG	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PRE-FLIGHT INSPECTION BY CREW, THE CAPTAIN NOTICED NR 2 TIRE HAS THE THREAD SEPARATED FROM THE ASSY. THE WH	EEL ASSY WAS REPLACED WITH A REPAIRED UNIT,  AIRCRAFT RETURN TO SERVICE.					2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2003123000100	20031230	00100	NM  	2003	12	30	CA031028007      	1	20031021	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IAW  MM-7200-03-00640 DATED OCT.21 03. FILLET SEAL WAS REMOVED AT THE LOWER EDGE OF THE LAP JOINTS AT STRINGERS S4	,S10 AND S14, BOTH LT AND RT SIDE. CLOSE VISUAL INSPECTION CARRIED OUT AND SCRIBE MARKS FOUND ON S4,S10 ANDS14, BOTH LT 	AND RT SIDES.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2004012600080	20040126	00080	SO  	2004	1	26	CA031028008      	1	20031027	G	2822	421136	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										FUEL BOOST	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING THE WALK AROUND THE PILOT NOTICED FUEL LEAKING FROM ONE OF THE PANELS UNDER THE AIRCRAFT.  MAINTENANCE WAS 	NOTIFIED AND INVESTIGATION REVEALED THAT THE ELECTRIC FUEL BOOST PUMP WAS LEAKING FROM THE PRESSURE REGULATOR ADJUSTMENT	.  PUMP WAS REPLACE WITH A SERVICEABLE UNIT AND THE AIRCRAFT RETURNED TO SERVICE. THE PUMP IN QUESTION HAD RECENTLY BEEN	 OVERHAULED AND HAD ONLY BEEN IN OPERATION FOR 28.1 HOURS.			1	L	7	2 	3O			 	A20SO   					 
2003110700090	20031107	00090	EA  	2003	11	7	CA031028009      	2	20030702	G	7200		COMPRESSOR      			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FAILED          	W				E	F	A		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	UNSCHED LANDING         		X	A	J	ENGINE FLAMEOUT           	FLAME/FIRE                	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) ENGINE FAILURE, ENGINE FIRE, FIRE EXTINGUISHED. - AIRCRAFT LANDED SINGLE ENGINE.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2003110700091	20031107	00091	EA  	2003	11	7	CA031028010      	2	20031015	G	8530		PISTON          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) PILOT FELT A VIBRATION IN THE A/C. CARRIED OUT A PRECAUTIONARY LANDING, DURING WHICH HE NOTICED A LACK OF POWER. O	N INSPECTION IT WAS DISCOVERD THAT NR 5 PISTON HAD FAILED.					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004010600030	20040106	00030	EA  	2004	1	6	CA031029001      	1	20031026	G	2910	601R7514771	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING APPROACH TO EWR UNABLE TO LOWER LANDING GEAR. HAD HYD 3 LOW PRESSURE WARNING. HYD LEVEL 'O' MANUAL GEAR EXT	ENSION PERFORMED '3 GREEN' FOUND LEAK COMING FROM 3A PUMP PRESSURE HOSE. PUMP AND HOSE REPLACED, LEAK AND OPERATION NORM	AL.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2003110700118	20031107	00118	EA  	2003	11	7	CA031029002      	1	20031028	G	7920	3033315	OIL FILTER      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					EXTERNAL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE OIL FILTER CHANGE, THE NEW FILTER WAS VISUALLY INSPECTED AND FOUND TO HAVE 2 WIRE THREADS PROTRUD	ING FROM THE FILTER. THE ORIGINAL FILTERS WERE VISUALLY INSPECTED AND WERE FOUND TO BEIN THE SAME CONDITION. REFERENCING	 OUR STORES, WE ESTABLISHED THAT THE SUSPECT FILTERS WERE PURCHASED FROM PACE ENTERPRISES IN MARCH 2003 AND WERE FROM BA	TCH NR 0552. ALL FILTERS PURCHASED FROM THAT P ERIOD, REGARDLESS OF BATCH NR WERE VISUALLY INSPECTED, EITHER FROM STOCK 	ORFROM AIRCRAFT AND IT WAS FOUND THAT THE ABNORMALITY WAS LIMITED TO THOSE FROM BATCH NR 0552. THE DISTRIBUTOR WAS INFOR	MED AND THE SUSPECT PARTS RETURNED.	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2004010600031	20040106	00031		2004	1	6	CA031029003      	4	20031027	G	3420		BULB            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ANNUNCIATOR	BURNED OUT      	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) (HDG) ANNUNCIATOR LIGHT INOP. BULBS ARE NOT FIELD REPLACEABLE, THEREFORE A SERVICEABLE CONTROLLER WAS INSTALLED.  	THERE IS 2 OTHER SOURCES OF THE HDG ANNUNCIATOR IN THE EFIS SYSTEM.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2003111000002	20031110	00002	NM  	2003	11	10	CA031029004      	1	20031023	G	2761		CASE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ACTUATOR	CRACKED         	W				O				OTHER                   				F	K	J	FLT CONT AFFECTED         	FLUID LOSS                	WARNING INDICATION        	LD	LANDING        	1			CA			31515	31515		0965					(CAN) LT NR 1 OUTBOARD SPOILER WOULD NOT DEPLOY ON TOUCH DOWN. NR 1 OUTBOARD ACTUATOR CASING FOUND CRACKED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003111000003	20031110	00003	WP  	2003	11	10	CA031029005      	1	20031029	G	5311	C0201	FRAME           			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					FUSELAGE	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CLAMP FROM MR GEARBOX COOLING HOSE FOUND WEARING INTO FRAME. WORN ALMOST COMPLETELY THROUGH FRAME.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004010600071	20040106	00071	CE  	2004	1	6	CA031029006      	1	20031022	G	2820	050042355	LINE            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL SYSTEM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSP, TECH WAS FOCUSED ON STEERING ARM INSTALLATION AND NOTICED THAT RT STEERING ARM WAS CHAFING ON	 FUEL LINE. SECTION OF FUEL LINE AFFECTED RUNS FROM UNION FITTING NEAR  FUEL SELECTOR TO FUEL STRAINER BOWL LOCATED AT F	IREWALL. REASON FOR THE CHAFING CONDITION WAS APPARENTLY DUE TO THE FUEL LINE INSTALLATION HAVING BEEN DISTORTED. THE CO	NTOUR OF THE LINE WAS ORIGINALLY DESIGNED TO AVOID ANY CONTACT WITH OTHER MOVING PARTS. SOMEHOW THAT CONTOUR HAD BEEN CO	MPROMISED ALLOWING CONTACT FROM THE MOVING STEERING ARM. THE EXTENT OF WEAR HAD PROGRESSED TO THE POINT OF ABOUT 90 PERC	ENT THROUGH THE WALL THICKNESS OF THE LINE.  THE LINE WAS REMOVED FROM SERVICE AND REPLACED WITH A NEW PART.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004012600071	20040126	00071	SW  	2004	1	26	CA031029007      	1	20031029	G	7120	10048512	PIN             	BELL        		BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE MOUNT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SPECIAL INSPECTION OF ENGINE MOUNT LEGS, INTRODUCED ON OPERATOR'S  A/C, LOWER PINS P/N 100-048-5-12 WERE FO	UND TO BE SEVERELY CORRODED.  ONE OF THE PINS, SEE ATTACHED PHOTO WAS SEVERED.  VARYING DEGREE OF CORROSION WAS ALSO OBS	ERVED ON ID OF THE MOUNT LEGS.  SOME LEGS WERE REJECTED UPON PRELIMINARY INSPECTION.  OPERATOR HAS INTRODUCED MANDATORY 	3-YEAR CORROSION INSPECTION OF ENGINE MOUNT LEGS, REQUIRING REMOVAL OF PINS AND DISASSEMBLY OF LEGS.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004012600072	20040126	00072	CE  	2004	1	26	CA031029008      	1	20031029	G	2430	51538001A	GCU             			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	DC SYSTEM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			11182	11182							(CAN) A/C DEPARTED AND SHORTLY AFTER TAKEOFF THE LT GENERATOR FELL OFFLINE. IT COULD NOT BE RESET SO THE CREW ELECTED TO	 RETURN TO THE AIRPORT. THRU TROUBLESHOOTING BY MAINTENANCE THE LT GENERATOR CONTROL UNIT WAS FOUND AT FAULT. IT WAS REP	LACED AND TESTED SERVICABLE.  ON A SIDE NOTE BOTH LT AND RT FUEL FLOW INDICATORS WHERE DAMAGED WHEN THE GCU FAILED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2003111000004	20031110	00004	NM  	2003	11	10	CA031030001      	1	20031028	G	2133	10604954	OUTFLOW VALVE   			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					CABIN PRESSURE	FAILED          	W				G	A			O2 MASK DEPLOYED        	UNSCHED LANDING         			W			INADEQUATE Q C            			CL	CLIMB          	1			CA											(CAN) A/C EXPERIENCED LOSS OF PRESSURIZATION ON CLIMB OUT. CREW DISCOVERED RT PACK INOPERATIVE. A/C LANDED AT COMPANY MA	INTENANCE FACILITY WHERE THE RT FWD PACK VALVE WAS REPLACED AND A/C RETURNED TO SERVICE.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2004010600099	20040106	00099	SO  	2004	1	6	CA031030002      	2	20031029	G	7414	10400615B	CONDENSER       			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550N      	17042	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	MAGNETO	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FOUND MAGNETO IS ALIVE WITH MAGNETO SWITCHED OFF.  CONDENSOR IS OPEN CIRCUIT INTERNALLY.						1	L	7	1 	3O	3	O	NT	A00009CH	E3SO	5	C	P36EA	 
2004010600101	20040106	00101	GL  	2004	1	6	CA031030003      	1	20031029	G	7120	AN817A	BOLT            			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  	HARTZL	HCJ2Y	BHCJ2YF1    	GL  	ENGINE MOUNT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOTTOM TWO ENGINE MOUNT TO FIREWALL ATTACHMENT BOLTS FOUND WITH TORQUE MARKING MISALIGNED.  BOLTS REQUIRED ONE TUR	N IN ORDER TO BRING TORQUE BACK TO SPEC.					1	L	7	1 	3O	3	O	NT	A00009CH	E1CE	5	C	P37EA	 
2003111000005	20031110	00005	NM  	2003	11	10	CA031030004      	1	20031023	G	2750	734382D	TORQUE TUBE     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAP	GROOVED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE IT WAS DISCOVERED THAT THE R/H WING FLAP PRIMARY TORQUE TUBE AT APPROX. WING STN YW 325.00 WAS 	DEEPLY GROOVED. GROOVE WAS AT ABOUT THE MIDLENGTH OF THE TUBE AROUND ITS CIRCUMFERENCE. TUBE HAD BEEN WEARING ON A NEARB	Y ELECTRICAL BUNDLE 'P' CLAMP.TORQUE TUBE REPLACED AND CLAMP ADJUSTED TO GIVE ADEQUATE CLEARANCE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012000023	20040120	00023	EA  	2004	1	20	CA031030005      	1	20030913	G	2910	DSC252B4012	LINE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	DRAG STRUT	FAILED          	W				L				ABORTED APPROACH        				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING ILS APPROACH, CAPT CALLED FOR LANDING GEAR TO BE LOWERED 'NR 2 HYD PRESSCAUTION LIGHT CAME ON FOLLOWED BY L	ANDING GEAR UNSAFE LIGHTS. APPROACH DISCONTI NUED, A/C ORBITED UNDER RADAR CONTROL TO EAST OF AIRFIELD. EMERGENCY CHECK 	LISTCONSULTED. NR 2 HYD. FAILURE DRILL CARRIED OUT AND LANDING GEAR LOWERED USINGSTANDBY SYSTEM. PAN PAN DECLARED. NR 2 	HYD QUANTITY FELL TO ZERO (EXPECTED). PASS ENGERS KEPT INFORMED THROUGH OUT EVENT. A/C LANDED WITHOUT FURTHER INCIDENT. 	INVESTIGATION FOUND THAT THE CAUSE WAS THE NLG DRAG STRUT ACTUATOR FLEXI PIPE FRACTURING P/NO DSC252B4-0124 AND THE PTU 	PRESSURE PIPE P/N 829400010-159 AND SUBSEQUENTLY FAILING, POSSIBLY DUE TO LOAD AND THE INFREQUENT USE OF THE PX PIPE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012600089	20040126	00089	EA  	2004	1	26	CA031030006      	1	20031024	G	5610	601R330334	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) FOS SIDE WINDOW CRACKED WHILE IN CRUISE.  EMERGENCY DECLARED, AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDEN	T.  AIRCRAFT RETURNED TO SERVICE FOLLOWING THE WINDOW REPLACEMENT. (SEE ALSO: US NR 2003121000202)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004010600103	20040106	00103	NE  	2004	1	6	CA031030007      	2	20031025	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	FAILED          	W				E				ENGINE SHUTDOWN         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) LOUD BANG AT 3000 FT AND LT ENGINE SHUT DOWN.  AIRCRAFT LANDED IN TLH WITHOUT FURTHER INCIDENT.  LT ENGINE REPLACE	D, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004010600173	20040106	00173	EU  	2004	1	6	CA031031001      	1	20031030	G	5610		SEAL            	PPG         		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDSCREEN	DELAMINATED     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						98355H5908					(CAN) DURING THE PRESSURIZATION SYSTEM TEST AIR LEAKAGE WAS NOTED COMING FROM AROUND THE MAIN WINDSCREENS.  UPON REMOVAL	 OF THE WINDSCREEN THE SEAL THAT IS ATTACHED TO THE WINDSCREEN WAS FOUND TO BE DELAMINATING. NO FIELD REPAIR IS AVAILABL	E SO THE WINDSCREEN WAS REPLACED WITH A NEW UNIT.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004010700016	20040107	00016	EU  	2004	1	7	CA031031002      	1	20031030	G	5610		SEAL            	PPG         		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	WINDSCREEN	DELAMINATED     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						98329H3985					(CAN) DURING THE PRESSURIZATION SYSTEM TEST IT WAS NOTED THERE WAS AIR LEAKAGE AROUND THE MAIN WINDSCREENS. UPON REMOVAL	 OF THE WINDSCREEN THE SEAL ATTACHED TO THE WINDSCREEN WAS FOUND TO BE DELAMINATING. THERE IS NO FIELD REPAIR AVAILABLE 	SO THEWINDSCREEN WAS REPLACED WITH A NEW UNIT.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012100001	20040121	00001	GL  	2004	1	21	CA031031003      	1	20031024	G	3240	AE2463509E02	LINE            			DHAV  	DH82  	DH82        	2801000	GL  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	BRAKE	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) AFTER ENGINE SHUT DOWN AND CHECKS COMPLETED, ATC CALLED TO SAY THAT SMOKE WAS COMING FROM LT BRAKES AND THAT THE F	IRE SERVICE WAS ON ITS WAY. F.D. AND PILOT VERIFIED HYDRAULIC FLUID ON THE GROUND IN THE WHEELS AREA. THE SMOKE DECLARED	 BY ATC WAS MORE LIKE A FINE STREAM OR VAPOR, CLEARLY CAUSED BY HYDRAULIC FLUID SPRAYING FROM A RUPTURED PIPE OVER THE W	ARM BRAKES. INVESTIGATION BY ENGINEERS FOUND FLEXIBLE HYDRAULIC PIPE PN AE2463509E0230 SN 71867 TO NR 1 BRAKE UNIT WAS L	EAKING, IPC REFERENCE 32-10-20 FIG 32 ITEM 20.		1	Q	7	1 	3I	4	T		EXPA1Q71	E20NE	6	C	P7NE	 
2004012600067	20040126	00067	NM  	2004	1	26	CA031031004      	1	20031028	G	2497	AA4N103	CONTACTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	STARTER GEN	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON SHUTDOWN OF THE RT ENGINE, THE CREW NOTICED THE RT PROPELLER CONTINUED TO ROTATE. THE CREW TURNED OFF ALL POWER	 ON THE AIRCRAFT AND THE PROPELLER STOPED ROTATING.  INVESTIGATION SHOWED CONTACTOR 2431-K2(P/N A-A4N103) WAS STUCK IN T	HE CLOSED POSITION.  CONTACTOR WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.  (STARTER/GENERATOR ALSO REPLACED AS PRECA	UTION)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012600068	20040126	00068	CE  	2004	1	26	CA031031005      	1	20031029	G	5524	043200171	HINGE           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RT ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ELEVATOR OB HINGE ASSY BOLT HOLE IS WORN AND OBLONGED IN SHAPE AS WELL AS THE HINGES INNER FACES ARE GROOVED FR	OM BUSHING.  NOTE THAT BUSHING IS NOT SE IZED IN THE BEARING ASSY ON THE ADJOINING HORIZONTAL STAB HINGE.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2004012600069	20040126	00069	GL  	2004	1	26	CA031031006      	2	20030612	G	7323	23065123	GOVERNOR        			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					DROOP COMP	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) NR DROOPING TO 97 WITHOUT RECOVERY UNDER POWER AND OVER SPEEDING TO 107 WHEN POWER REDUCED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004010700034	20040107	00034	WP  	2004	1	7	CA031031007      	1	20030606	G	6210		PIN             	DOUG        		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0098849059					(CAN) ON DI FOUND PIN .1250 OF AN INCH ABOVE LEAD/LAG LINK WHILE PREPARING TO INSTALL PIN INTO LEAD/LAG LINK.  UPON UNLA	TCHING OF CLIP OFF BOTTOM PORTION OF PIN, LOWER PORTION OF PIN WAS FOUND SHEARED OFF ABOUT .7500 INCH FROM BOTTOM. REMOV	AL OF PIN REVEALED POSSIBLE CRACK STARTING OFF THREADED PORTION OF PIN.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004010700035	20040107	00035	EU  	2004	1	7	CA031031008      	1	20030605	G	6730		BEARING         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ROTOR SERVO	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						DN124					(CAN) ON THE DAILY INSPECTION, THE BEARING WAS FOUND LOOSE IN THE HOUSING( MOVEMENT AXIALLY ) BECAUSE OF STAKING FAILURE	. FURTHERMORE, WITH THE FREEDOM OF THE BEARING TO MOVE AXIALLY PLUS THE RADIAL STRESSES IMPOSED, THE SLEEVE BETWEEN THE 	BEARING OUTER RACE AND ITS HOUSING STARTED TO BREAK UP.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004010700036	20040107	00036	EU  	2004	1	7	CA031031009      	1	20030613	G	7170		DRAIN VALVE     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ENGINE SHUTDOWN, A SINGLE POP SOUND IS HEARD AT THE EXHAUST AREA. FURTHER INVESTIGATION DETERMINE THE DRAIN / O	VERSPEED VALVE TO BE THE CAUSE.  A SMALL JET BENEATH THE T-FITTING WAS FOUND TO BE MISSING.  THE DRAIN/ OVERSPEED VALVE 	HAD JUST BEEN REPLACED DUE TO 10 YEAR CALENDAR LIFE				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004010700044	20040107	00044	CE  	2004	1	7	CA031031010      	1	20031030	G	5410	10191004911	DUCT            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DISCOVERED COWL DUCT CRACKING DURING ROUTINE MAINTENANCE INSPECTION. MFG HAS PREVIOUSLY IDENTIFIED THIS PROBLEM AN	D DESIGNED A FIELD REPAIR TO RECTIFY IT.   INCORPORATED FIELD REPAIR FR-KA-00038 TO BOTH ENGINE COWLS.   DUCT PN 101-910	049-12 ALSO AFFECTED IN SAME MANNER.   SIMILAR REPAIRS CONDUCTED TO ALL OTHER COMPANY B200 COWLINGS.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2004010700045	20040107	00045	EA  	2004	1	7	CA031103001      	1	20031030	G	5297	601R5800511	WIRE HARNESS    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					CARGO DOOR	PINCHED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) CLIMBING THRU 10,000 FT CREW RECEIVED PASS AND SERVICE DOOR FLASHING RED.  DURING APPROACH CARGO INDICATION AS WEL	L. AT GATE FOUND CB DOOR INDICATOR POPPED. ON INVESTIGATION FOUND SERVICE DOOR HARNESS PINCHED IN DOOR. F.M.R. ISSUED TO	 CHECK OTHER A/C IN FLEET FOR CORRECT INSTALATION.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012100002	20040121	00002	NM  	2004	1	21	CA031103002      	1	20031030	G	2120	32167441	ISOLATION VALVE 			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AIR DISTRIBUTION	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, IT WAS OBSERVED THAT CABIN PRESSURE WAS NOT CONSISTENT WITH FLIGHT LEVEL. AIRCRAFT RETURNED TO BASE 	WITHOUT INCIDENT. AIRCRAFT WAS DISPATCHED UND ER MEL 21-01-01 WITH RT PACK INOP FLYING AT AN ALTITUDE OF FL 25,000 FT. T	HE ISOLATION VALVE WAS HARD FAULTED.  NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2004012600073	20040126	00073	NM  	2004	1	26	CA031103003      	1	20031101	G	2120	AP500219101	DUCT            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	CABIN AIR	DAMAGED         	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) AN OPERATOR EXPERIENCED A RAPID DECOMPRESSION AT 22000FT, CAUSING AN EMERGENCY DESCENT WITH AT LEAST ONE PASSENGER	 THAT LOST CONSCIOUSNESS. MAINTENANCE FOUND A BLOWN DUCT IN THE ECS COMPARTMENT P/N AP500219-101 THE DUCT IS DAMAGED AND	 WILL REQUIRE REPLACEMENT.  OPERATOR STATED THAT THE DUCT BLEW AT THE SEAM (GLUED EDGES). REF. IPC 21-22-16-01-065. ALSO	 THE FIRST TWO OVERHEAD BINS ON THE RT SIDE ALSO RECEIVED COSMETIC DAMAGE, THE LAMINATE DEBONDED FROM THE BIN.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004012600074	20040126	00074	SO  	2004	1	26	CA031103004      	2	20031031	G	8530	654286	EXHAUST VALVE   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE	BROKEN          	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW REPORTED A MINOR ENGINE VIBRATION AND HIGH NR 2 CYLINDER EGT AS WELL AS ERRATIC CHT INDICATIONS.  	EXAMINATION FOUND THAT DUE TO FAULTY INFORMATION FROM THE MULTI PROBE SYSTEM THE OBSERVED INFORMATION ACTUALLY REFLECTED	 NR 6 CYLINDER OPERATION.   NR 6 CYLINDER WAS REMOVED AND THE EXHAUST VALVE WAS FOUND BROKEN IN THE SEAT AREA. THE ASSEM	BLY WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	H	7	1 	3O	3	O	 	A4CE    	E3SO	5	C	P47GL	 
2004012600093	20040126	00093	EA  	2004	1	26	CA031103005      	2	20031007	G	7200		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  						LIGHTNING STRIKE	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			27101								(CAN) AC WAS HIT BY LIGHTNING STRIKE. REVIEWED ENG ON GROUND AND RESIDUAL MAGNETISM WAS FOUND ON PROP SHAFT.  IT WAS CON	FIRMED THAT ENG DID SUFFER FROM LIGHTNING STRIKE, PARTS FOUND WITH HIGH MAGNETISM ON THEM.  PRESENCE OF ARCING ON FRONT 	RED GB MAIN BEARINGS ARE TYPICAL RESULTS FROM LIGHTNING STIKES. ONE 1ST STG PLANET GEARS WAS FOUND WITH SPALLING ON ONE 	GEAR TOOTH.  DETERMINED THAT THIS DAMAGE DID NOT COME FROM LIGHTNING STRIKE. NO OTHER MATING GEAR WAS FOUND WITH MATCHIN	G DAM. THAT WOULD BE PRESENT IF SPALLING FROM AN ELEC DISCHARGE ARC.  DAMAGE INDICATES IMPACT ON TIP OF TOOTH CAUSING MA	TERIAL DISPLACEMENT TOWARDS SPALLED SIDE. DISPLACEMENT INCREASED SURFACE STRESS CAUSING SURFACE TO FRACTURE AND SPALL.						4	T			E4EA				 
2004012600106	20040126	00106	SW  	2004	1	26	CA031103006      	1	20031028	G	6410	206016201131	BLADE           			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	OVERSIZED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CHAMFERS 44 DEG 30 INCHES - 45 DEG 30 INCHES (2 PLACES) X .395 - .415 DIMENSION ARE ACTUALLY OVERSIZE TO .450. BLA	DES CAN BE REWORKED BY RE-MACHINING THE CHAMFERS TO THE REQUIRED DIMENSION.  THE CHAMFERS ARE LOCATED AT THE ROOT END OF	 THE BLADE WHERE IT MATES WITH THE PITCH HORN 206-011-809.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004010700062	20040107	00062	EU  	2004	1	7	CA031104001      	1	20031025	G	2720	NAS62038	BOLT            	SAAB        	7255700511  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					RUDDER STOP	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) THE PILOT REPORTED A RUDDER TRAVEL PROBLEM AND TEMPORARY STIFFNESS AT END OF TRAVEL. AFTER INVESTIGATION FROM MAIN	TENANCE, FOUND LEFT RUDDER STOP PAD ATTACHING BOLT CAME LOOSE AND BROKE. AREA INSPECTED AND BOLT REPLACED. REFERENCE IPC	 55-50-00-02 ITEM 535				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
2004031500025	20040315	00025	CE  	2004	3	15	CA031104002      	1	20031027	G	2842	S33311	TRANSMITTER     			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1C235	1C235LFA    	GL  	FUEL QTY	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON COMPLIANCE OF THE FUEL QTY INDICATORS PERFORMANCE TEST (ANNUAL ITEM), IT WAS NOTED THAT THE LT WING TRANSMITT	ER DID NOT GO QUITE TO ZERO.  (INDICATED SLIGHTLY ABOVE THE '0' READING ON THE GAUGE)  FURTHER INSPECTION REVEALED THAT 	THE TRANSMITTER ARM WAS RESTING ON A STRINGER INSIDE THE TANK.  IT WAS DETERMINED THAT THE TRANSMITTER  INSTALLED IN THE	 LT WING WAS THE CORRECT PART NUMBER FOR THE RT WING.  INSTALLED THE CORRECT SENDING UNIT, SYSTEM FUNCTIONS NORMALLY.  T	HIS AIRCRAFT WAS DELIVERED FROM THE FACTORY WITH THIS INSTALLATION.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P12EA	 
2004012600078	20040126	00078	SW  	2004	1	26	CA031104003      	1	20031104	G	5350	407030609101	CASTING         			BELL  	407   	407         	1182206	SW  										FUSELAGE	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON DISASSEMBLY OF THE AIRCRAFT FOR REPAIR, THE PART WAS FOUND NOT TO BE ATTACHED TO IT'S MATING FAIRING AS REQUIRE	D.  THE RIVETS WERE PULLED BETWEEN THE ATTACHING PARTS AND NOT THROUGH THE CASTING.					1	G	7	1 	3U			O	H2SW    					 
2004012600094	20040126	00094	NE  	2004	1	26	CA031104004      	2	20031101	G	7261	208313801	GEARBOX         			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 4 ENGINE	WORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA								LFO5567A			(CAN) DURING CLIMB , RED MASTER WARNING , RED NR 4 OIL PX WARNING, NR 4 OIL PX GUAGE IN RED.  CREW ELECTED TO SHUTDOWN N	R 4 ENGINE.  AIRCRAFT RETURNED TO DEPARTING AIRPORT FOR NORMAL LANDING.  INSPECTION FOUND OIL PUMP DRIVE GEAR IN GEARBOX	 SPLINES WORN, ALONG WITH WEAR ON OIL PUMP SHAFT RESULTING IN OIL PUMP NOT BEING DRIVEN.  NR 4 ENGINE REMOVED AND REPLAC	ED WITH SERVICEABLE SPARE.			2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2004012600105	20040126	00105	EA  	2004	1	26	CA031105001      	1	20031028	G	5250	CDSP10154	LOCK            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON GROUND CREW UNABLE TO OPEN FLIGHT DECK DOOR. DOOR UNHINGED TO ALLOW EXIT FROM C/P.  A/C FERRIED BACK FOR REPAIR	S.  AFTER DISASSEMBLY AN INTERNAL PART WAS FOUND BROKEN.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004010700113	20040107	00113		2004	1	7	CA031105002      	4	20031103	G	3425	7003974722	COMPUTER        			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	COCKPIT	SHORTED         	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB SMOKE APPEARED IN COCKPIT. SIMULTANEOUSLY, AUTOPILOT AURAL WARNING WAS HEARD. AUTOPILOT STAYED ENGAGE	D. FLIGHT CREW PUT SMOKE HOOD ON AND ABORTED FLIGHT. AIRCRAFT RETURNED TO BASE. EXHAUSTIVE INSPECTION OF ALL EQUIPMENT I	N COCKPIT DID NOT REVEAL ANY VISUAL SIGNS OF FIRE. IT WAS NOTICED THAT THERE FLIGHT GUIDANCE COMPUTER HAD STRONG BURNT O	DOR BUT HAD NO EXTERNAL OVERHEAT /FIRE DAMAGE. THE RT FLIGHT GUIDANCE COMPUTER WAS REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010700115	20040107	00115	WP  	2004	1	7	CA031105003      	2	20031103	G	7200		ENGINE          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					LEFT	SURGES          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) UPON DEPARTURE/CLIMB PHASE OF FLIGHT, LT ENGINE CHIP DETECTOR LIGHT CAME ON STEADY. FLIGHT CREW MONITORED GAUGES A	ND NOTICED  LT OIL PRESSURE GAUGE HAD EXCEEDED RED LINE LIMIT. SHORTLYAFTER ENGINE POWER BEGAN TO SURGE. LT POWER LEVER 	WAS REDUCED IN SMALL INCREMENTS AND INTIALLY EASED SURGING. AFTER SHORT BREIFING TO PASSENGERS, ENGINE SURGING RETURNED 	AND WAS WORSENING, DECISION WAS THEN MADE TO SHUT-DOWN ENGINE. FLIGHT CREW DECIDED THAT THE MOST ADEQUATE PLACE TO LAND 	THE AIRCRAFT WAS ISLAND LAKE, MANITOBA. THE APPROACH AND LANDING WERE UNEVENTFU L. THE ENGINE WAS REPLACED BY MAINTENANC	E AND BROUGHT BACK TO WINNIPEG FOR TEAR DOWN AND ANALYSIS. MORE INFORMATION TO FOLLOW ONCE TEAR DOWN IS COMPLETE.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2004012600115	20040126	00115	CE  	2004	1	26	CA031105004      	1	20031105	G	7603	3011543	LEVER           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE CONROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION OF THE REVERSING LEVER GUIDE PIN BRACKET FOR WEAR DURING AN ENGINE BUILD UP IT WAS NOTICED THAT TH	E BRACKET PLATE THAT THE GUIDE PIN IS WELDED TO WAS CRACKED. THE CRACK WAS ADJACENT TO THE PIN WELD AND ON THE FORWARD S	IDE OF THE PLATE. TOTAL FAILURE OF THE PLATE WOULD CAUSE THE PIN TO DISLODGE ALLOWING THE BETA ARM TO ROTATE OUT OF THE 	PROPELLER REVERSING ARM SLIP RING. SEE PT6A-27/2 8 ILLUSTRATED PARTS MANUAL CHAPTER 76-10-00 FIGURE 2 ITEM 390			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2003112600073	20031126	00073	SW  	2003	11	26	CA031105005      	1	20030922	G	6520	427034851101	SUPPORT         			BELL  	427   	427         	1182207	SW  	PWC   	PW207 	PW207D      	 	NE  					T/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOREIGN OPERATOR NOTICED, DURING WALK AROUND, A ROUTINE MAINTENANCE CRACK ON THE TAIL ROTOR GEAR BOX/VERTICAL FIN 	SUPPORT ASSEMBLY.  PART HAD 310 HOURS SINCE NEW. PART HAS BEEN REMOVED AND SENT FOR INVESTIGATION.					1	G	7	1 	3U	3	U	 	R00001RC	E42NE				 
2003112600084	20031126	00084	NM  	2003	11	26	CA031105006      	1	20030728	G	6120	697070212	BUSS BAR        		697071234   	BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 6 BLADE	SHORTED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA						NA					(CAN) DURING CRUISE THE AC GEN NR 2 CAUTION LIGHT CAME ON TOGETHER WITH (PROP DEICE) CAUTION LIGHT. GEN AND PROP DEICE R	ESET ACC. TO QRH. AFTER APPROX. 5-10 SEC. BOTH (AC GEN NR 1) AND (AC GEN NR 2) CAUTION LIGHTS CAME ON WITH ASSOCIATED BU	S FAULT CAUTION LIGHTS. 2ND ATTEMPT TO RESET GEN NOT TRIED. DESCENT STARTED TO LEAVE ICING COND. AFTER QRH CHECKLIST COM	PLETED. NORMAL LANDING WITHOUT AC PWR.  INVESTIGATION/ACTION TROUBLESHOOTING IDENTIFIED THE FAULT TO BE BUSS BARS P/N 69	7070212 AND 697070213 ON BLADE NO 6. THE BUS BARS HAD APPARENTLY BEEN LOOSE AND IN CONTACT WITH EACH OTHER, THERE BY CAU	SING A SHORT BETWEEN THE PHASES OF AC POWER.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2003112600085	20031126	00085	EU  	2003	11	26	CA031106001      	1	20031105	G	2752	697511007	ACTUATOR        			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					TE FLAP	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON APPROACH ECAM FLAP FAULT, FLAPS WOULD NOT EXTEND. CARRIED OUT FLAPLESS LANDING.   WITH SLATS AT 2 FOUND WATER I	N NR 2 RT FLAP INPUT GEARBOX ROTARY ACTUATOR.  DRAINED ACTUATOR AND REPLACED FLUID, ALL CKS NORMAL. MPD TASK TO CHANGE F	LUID IS CALLED FOR AT C4. A/C PRESENTLY 190 DAYS BEFORE C3 IS DUE.				1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2003112600087	20031126	00087	NM  	2003	11	26	CA031106003      	1	20031015	G	5740	20001201	ATTACH FITTING  			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL ISPECTION OF WING TO FUSELAGE ATTACH FITTINGS IAW MFG SB 600-136, THE LT AFT FITTING WAS FOUND TO BE	 CRACKED. ALL OTHER AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO FURTHER DEFECTS NOTED. THE AIRCRAFT WILL BE REPAIRED PR	IOR TO BEING RELEASED FOR SERVICE.				1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2003112600088	20031126	00088	NM  	2003	11	26	CA031106004      	1	20031106	G	2731	82700550001	CONTROL CABLE   			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HORIZONTAL STAB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE HEAVY CHECK AT THE YHZ BASE THE FOLLOWING HAS BEEN DISCOVERED. THE ELEVATOR TRIM CHAINS IN THE HORIZONT	AL STAB HAVE BEEN FOUND TO HAVE SEVERAL CRACKS IN THE LINKS. ONE OF THE CHAINS FELL APART DURING MAINTENANCE IN THE AREA	. IPCREFERENCE 27-38-00 FIG 20 ITEM 170. THE CHAIN/CABLE ASSEMBLY HAS BEEN REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2003123000101	20031230	00101	EA  	2003	12	30	CA031106005      	1	20031015	G	5711		SPAR CAP        			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	CWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ACCOMPLISHMENT OF AD CF-92-26R1, THE ULTRASONIC INSPECTION WAS BEING COMPLETED IAW SB 215-A454. CRACKS WERE	 DETECTED ON THE LOWER RT AND LOWER LT SPAR CAPS. THE AIRCRAFT WILL BE REPAIRED IAW MFG REO PRIOR TO BEING TO RETURNED T	O SERVICE.				2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2003123000102	20031230	00102	EA  	2003	12	30	CA031106006      	1	20031024	G	5230	85230448001	LINK            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	CARGO DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING GROUND HANDLING WHILE CLOSING THE CARGO DOOR THE LINK ASSEMBLY BROKE CAUSING THE HANDLE FREE TO TURN.  RAMP	 CREW WAS NOT ABLE TO LOCK THE DOOR USING THE HANDLE.  THE LINK WAS FOUND BROKEN AT THE LOWER SECTION EYE END.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010500103	20040105	00103	WP  	2004	1	5	CA031106007      	1	20031029	G	4920		CASE            	GARRTT      		DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					APU GEARBOX	SHEARED         	W				F				ACTIVATE FIRE EXT.      				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						P3009					(CAN) APU FIRE WARNING DURING APU START (AUTO SHUTDOWN). MAINTENANCE FOUND THE APU GEARBOX CASE SHEARED, THE TURBINE PLE	NUM TWISTED AND TURBINE WHEEL DISK DISINTEGRATED. AWAITING REPORT FROM MFG.  APU ASSEMBLY REPLACED.					2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004010500114	20040105	00114	EA  	2004	1	5	CA031106008      	1	20031015	G	5340	21531033800	FITTING         			CNDAIR	CL215 	CL2151A10   	1900320	EA  						HAMSTD	43E	43E60       	NE  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ACCOMPLISHMENT OF AD CF97-07R2,THE WING TO FUSELAGE FITTINGS WERE BEING INSPECTED IAW SB 215-A476. DURING T	HE INSPECTION THE RT FORWARD OUTBOARD ANGLE OF THE WING TO FUSELAGE FITTING WAS FOUND CRACKED. THE AIRCRAFT WILL BE REPA	IRED IAW MFG REPAIR ENGINEERING ORDER PRIOR TO BEING RETURNED TO SERVICE.				2	H	7	2 	4R			RT	A14EA   		6	C	P871	 
2004010500115	20040105	00115	NM  	2004	1	5	CA031106009      	1	20030803	G	2435	11521062	STARTER GEN     			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) STARTER GENERATOR FAILURE DURING CRUISE DC GEN NR 2 CAUTION LIGHT CAME ON.  RESET ACCORDING TO QRH WITHOUT SUCCESS	. AFTER 30 MINUTES, FLIGHT WHEN DESCEND WAS INITIATED AT A LOWER POWER SETTING RESET WAS PERFORMED WITH SUCCESS. OK FOR 	REST OF FLIGHT. INVESTIGATION/ACTION TROUBLESHOOTING SHOWED A FAULTY STARTER-GENERATOR WHICH WAS REPLACED. THE FAULT WAS	 CONFIRMED AT THE SHOP.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2004010500118	20040105	00118	SW  	2004	1	5	CA031106010      	1	20031103	G	5530	41000885	CHANNEL         			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING X-RAY INSPECTION OF THE VERTICAL STABILIZER A CRACK APPROXIMATELY .7500 INCH LONG WAS NOTED ON P/N 410008-8	5 CHANNEL LOCATED IN THE LOWER SECTION OF THE VERTICAL STABILIZER. THIS PART IS LOCATED IN THE AREA SUBJECT TO AD 95-13-	02. THE CRACK IS RUNNING ALONG THE RT VERTICAL FLANGE OF THE CHANNEL AND STARTS AT THE CORNER RELIEF. THE AIRCRAFT HAD B	EEN MODIFIED IAW SB 218 PT 2. THE AIRCRAFT WILL BE REPAIRED PRIOR TO RETURNING TO SERVICE.			1	H	7	2 	3T	4	T	 	2A4     	E2WE	6	C	P15EA	 
2004010500119	20040105	00119		2004	1	5	CA031106011      	4	20030818	G	2210	C18112AA	ACTUATOR        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					YAW DAMPER	FAILED          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE OFF ROLL YAW DAMPER-DISENGAGED. TAKEOFF ABORTED AND TCC CONTACTED. THE PROBLEM WAS LOCALIZED TO THE YA	W DAMPER ACTUATOR WHICH WAS REPLACED. THE FAULT WAS LATER CONFIRMED TO BETHE LINEAR POTENTIOMETER AT THE SHOP.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2004010500120	20040105	00120	SW  	2004	1	5	CA031106012      	1	20031103	G	5530	41000885	CHANNEL         			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLETING A X-RAY INSPECTION ON THE VERTICAL STABILIZER, A CRACK WAS NOTED ON THE RT VERTICAL FLANGE OF THE	 CHANNEL. THE CRACK IS APPROXIMATELY .6250 INCH IN LENGTH.  IT IS LOCATED IN THE AREA COVERED BY AD95-13-02. THE AIRCRAF	T HAD BEEN MODIFIED IAW SB218 PT2.THE AIRCRAFT WILL BE REPAIRED PRIOR TO BEING RETURNED TO SERVICE.				1	H	7	2 	3T	4	T	 	2A4     	E4WE	6	C	P15EA	 
2004012100003	20040121	00003	SW  	2004	1	21	CA031106013      	1	20031103	G	5531	41000823	SPAR            	AEROCD      		GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING X-RAY INSPECTION OF THE VERTICAL STABILIZER, A CRACK WAS NOTED ON THE CENTER SPAR FLANGE LOCATED 2 FASTENER	S UP FROM THE EXTERNAL DOUBLER APEX. THE CRACKIS APPROXIMATELY 5/8 - 3/4 INCH IN LENGTH AND RUNS 90 DEGREES TO THE FLANG	E. A CRA CK APPROXIMATELY 1INCH IN LENGTH WAS DETECTED ON CHANNEL P/N 410008-85. THIS CRACK RUNS VERTICALLY UP THE RIGHT	 HAND FLANGE. THIS AREA IS COVERED BY AD 95-13-02. THE AIRCRAFT HAD BEEN MODIFIED IAW SB 208 PT2.			1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2004012100004	20040121	00004	NM  	2004	1	21	CA031107003      	1	20030821	G	3150	4100S01806	TMU             			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					COCKPIT	FAILED          	W				O				OTHER                   				S			AFFECT SYSTEMS            			CR	CRUISE         	1			CA											(CAN) MULTIPLE CAUTIONS, DURING CRUISE AT FL240 THE FOLLOWING CAUTIONS APPEARED AND STAYED ON DURING THE REST OF THE FLI	GHT: PUSHER SYS FAIL, PITOT HEAT NR 2, ENG ADPT HEAT NR 2, DEICE TIMER. QRH CONSULTED AND MANUAL FLYING PERFORMED ACCORD	INGLY. NORMAL LANDING COMPLETED.  CONTACTOR K2 IN RT AC CONTACTOR BOX WAS REPLACED, BUT THE FAULT WAS STILL PRESENT ON N	EXT FLT. THE PROBLEM WAS IDENTIFIED AS THE TIMER AND MONITOR UNIT (TMU) IN THE DE-ICING SYSTEM.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2004010600072	20040106	00072	WP  	2004	1	6	CA031107004      	1	20031103	G	6210	369A10045	ATTACH FITTING  			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) BROKEN PIN WAS FOUND ON 100 HOUR INSPECTION. LOCATION WAS AT THE JUNCTION OF SHANK AND THREADS.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004010600073	20040106	00073	SO  	2004	1	6	CA031107005      	2	20030911	G	8530		GUIDE           	CONT        		CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200FM     	GL  	INTAKE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						6931701					(CAN) OTHER CYLINDERS INSTALLED ON THIS ENGINE DID NOT HAVE THE INTAKE GUIDE SEALS INSTALLED.  (SHORTER GUIDES REQUIRES 	SEALS, WHILE LONGER GUIDES DO NOT REQUIRE SEALS.)  THE INTAKE SPRINGS WERE REMOVED TO MEASURE THE GUIDE TO SEE IF THE SE	ALS WERE REQUIRED FOR INSTALLATION.  ONCE THE SPRINGS WERE REMOVED, IT WAS NOTED THAT THE GUIDE COULD ROCK FROM SIDE TO 	SIDE.  THE CYLINDER IS BEING RETURNED TO FOR WARRANTY. THE CYLINDER WAS REPAIRED UNDER THEIR WO NR 69317-01.			1	H	7	1 	3O	3	O	 	5A5     	E269	5	N	P874	 
2004012100005	20040121	00005	SO  	2004	1	21	CA031107006      	2	20030911	G	8530	UK	GUIDE           	CONT        		CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  					CYLINDER INTAKE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						6931701					(CAN) DURING INSPECTION, IT WAS NOTED THAT THE INTAKE GUIDES WERE LEAKING OIL.THE SPRINGS WERE REMOVED TO MEASURE THE GU	IDE HEIGHTS.THERE ARE NOW SHORTER GUIDES THAT REQUIRE THE INSTALLATION OF A SEAL.  SOME OF THESE SEALS WERE NOT INSTALLE	D ON A BATCH OF CYLINDERS.WE WERE GOING TO MEASURE THE GUIDE HEIGHTS TO SEE IF THE SEALS WERE MISSING.IT WAS AT THIS TIM	E IT WAS NOTED THAT THE GUIDE ON NR 6 CYLINDER WAS LOOSE.			1	H	7	1 	3O	3	O	 	5A5     	E269				 
2004010600074	20040106	00074		2004	1	6	CA031107007      	4	20030823	G	3160	C12432AA05	PROCESSOR       			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	ELEVATOR FEEL	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) MULTIPLE CAUTIONS, DURING CRUISE FL180 (ELEVATOR FEEL) CAUTION LIGHT ON. THEREAFTER (AVIONICS) AND (PROP DEICE) CA	UTION LIGHT ON. ON ED IOP2 CAUTION LIGHT. QRH CONSULTED AND PRIORITY LANDING (STBY 1). PERFORMED.  AFTER THIS OCCURRENCE	 THE NR 2 INPUT, OUTPUT PROCESSOR WAS REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004010600075	20040106	00075	SO  	2004	1	6	CA031107008      	2	20030911	G	8530		GUIDE           	CONT        		CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200FM     	GL  	INTAKE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						6931701					(CAN) DURING INSPECTION, IT WAS NOTED THAT THE INTAKE GUIDES WERE LEAKING OIL. THE SPRINGS WERE REMOVED TO MEASURE THE G	UIDE HEIGHTS. THERE ARE NOW SHORTER GUIDES THAT REQUIRE THE INSTALLATION OF A SEAL. SOME OF THESE SEALS WERE NOT INSTALL	ED ON A BATCH OF CYLINDERS.  WE WERE GOING TO MEASURE THE GUIDE HEIGHTS TO SEE IF THE SEALS WERE MISSING.  IT WAS AT THI	S TIME IT WAS NOTED THAT THE GUIDE ON NR 6 CYLINDER WAS LOOSE. THE CYLINDER WAS REMOVED AND SENT FOR WARRANTY CONSIDERAT	ION.		1	H	7	1 	3O	3	O	 	5A5     	E269	5	N	P874	 
2004010600076	20040106	00076	NM  	2004	1	6	CA031107009      	1	20030920	G	2421	11522184	GENERATOR       			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NR 2 AC	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) AC GENERATOR FAILURE, AC NR 2 GEN CAUTION LIGHT CAME ON FEW SECONDS AFTER TAKE OFF POWER SET FOR TAKE OFF. TAKE OF	F ABORTED AND AIRCRAFT WAS TAXIED BACK.  INVESTIGATION/ACTION TROUBLESHOOTING SHOWED THAT THE AC GENERATOR WAS FAILING. 	THE GENERATOR WAS REPLACED. NO FURTHER FAULT REPORTED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004010600081	20040106	00081	EA  	2004	1	6	CA031107010      	1	20031029	G	2910	601R7528657	LINE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) NR 2 HYDRAULIC SYSTEM LEAKING. QUANITY READS ZERO. MAINTENANCE FOUND RESERVOIR FILL TUBE ASSEMBLY FOR NR 2 SYSTEM 	IN REAR EQUIPMENT BAY CRACKED ABOUT ONE INCH FROM FILL ADAPTER PORT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004010600107	20040106	00107	EA  	2004	1	6	CA031107011      	1	20031102	G	2913	N6521123	PUMP            			CNDAIR	CL600 	CL6002D24   	1390016	EA  	GE    	CF34  	CF343B1     	 	NE  					HYD SYSTEM	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	M	J	FLUID LOSS                	OVER TEMP                 	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) AFTER T/O, CREW NOTICED ENG NOISES WERE ROUGH.  AUDIO CK AT AFT BLKHD IND RT ENG.  NO ABNORMAL IND, AT 15,000 FT D	URING PRESS CHECKS, HYD 2LO PRESS AMBER MSG POSTED ON AND OFF.  ENG FLOW LINE WAS GREEN/AMBER ON AND OFF, 2800 PSI.  QTY	 WAS NML, TEMP OF 47 DEG C, HYD NR 1 TEMP WAS AT 11 DEGREES C.  THRUST WAS REDUCED TO IDLE ON RT ENG, HYD PRESS DROPPING	 TO 2600 PSI,  TEMP INCREASING. CREW PERFORMED ENG SHUT DOWN, QTY DROPPED TO ZERO, ROUGH ENG NOISE DISAPPEARED.  A/C LAN	DED W/O INCIDENT.  HYD FLUID WAS LEAKING FROM BELLY NEAR AFT EQUIP BAY.  FOUND PRES LINE FROM ENG DRIVEN PUMP WITH CRACK	 INSIDE ELBOW WHICH CAUSED IND AND DEPLETED SYS OF FLUID.  INDICATES PUMP IS AT FAULT AND CAUSED VIB CRACKING LINE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012100006	20040121	00006		2004	1	21	CA031107012      	4	20031103	G	2562	ELT910	ELT             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TAIL	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN)  ELT TEST WAS PERFORMED.  THE REMOTE SWITCH IN THE COCKPIT WAS USED TO TEST THE ELT FUNCTION.  WHEN THE ELT WAS AC	IVATED THEN TURNED OFF, THE ELT CONTINUED TO TRANSMIT.  FLIGHT SERVICES WAS NOTIFIED AS TO THE PROBLEM. THE SWITCH ON TH	E ELT WAS TURNED OFF AND THE ELT CONTINUED TO TRANSMIT. THE ANT ENNA WAS DISCONNECTED TO LIMIT THE TRANSMISSION SIGNAL. 	THE ELT WAS REMOVED FROM THE AIRCRAFT AND TAKEN TO A LOCAL AVIONICS SHOP. THEY CONFIRMED THAT THE ELT WA S STILL TRANSMI	TTING. THE ELT WAS OPENED UP AND THE BATTERY WAS DISCONNECTED. ELT RECERTIFIED SEP.  05, 2003 BATTERY DUE AUG. 11, 2005 	INSTALLED IN C-XX SEP.11, 2003 A/F HRS. AT INSTALL 2958.6 A/F HRS. AT FAILURE 3100.2 TOTAL TIME IN AIRCRAFT 141.6 HRS.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004021700097	20040217	00097	NM  	2004	2	17	CA031107013      	1	20031106	G	2435	23088002B	STARTER GEN     			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			18380								(CAN) DUAL DC GENERATOR FAILURE, NR1 GENERATOR FOUND BURNED.  NORMAL ENG START, BEFORE TAXI, COMPLETE ELECTRICAL FAILURE	, QRH PROCEDURES UNSUCCESSFUL.  ENGINES SHUT DOWN, DURING DISEMBARKATION OBSERVED WHITE SMOKE FROM NR1 ENGINE, FIRE BRIG	ADE ARRIVED, NO DANGER TO CREW OR PASSENGERS.  FOUND NR1 DC STARTER GEN BURNED. NR1 STARTER GEN AND CONTACTOR 2431K1 REP	LACED.  GROUND RUN PERFORMED, NR2 DC GEN CAUTION LIGHT ON, NOT RESETABLE.  NR2 STARTER GEN AND CONTACTOR 2431K2 REPLACED	.  NORMAL OPERATION, AIRCRAFT BACK IN SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004010600110	20040106	00110	CE  	2004	1	6	CA031107014      	1	20031106	G	5610	5042006935	WINDSHIELD      			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	BROKEN          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOTS REPORTED THAT WHILE CRUISING AT 23 000 FT THEY A HEARD CRACKLING SOUND.  SOON AFTER THEY DETECTED THIS SOUN	D, THE INTERIOR PANE OF THE LEFT  WINDSHIELD SHATTERED.  HEAT WAS NOT IN USE, AND THE AMBIENT TEMPERATURE WAS -30 C.  TH	E PILOTS IMMEDIATELY REDUCED PRESSURE AND DECENDED TO 10 000 FT, THEN RETURNED TO AMO FOR MAINTENANCE.				1	L	7	2 	3T	4	T	 	3A20    	E4EA	6	C	P15EA	 
2004010600111	20040106	00111	SW  	2004	1	6	CA031107015      	1	20031107	G	5510	AN4730A	EYEBOLT         			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION THE HORIZONTAL STAB STRUT ATTACH EYEBOLTS WERE REMOVED FOR INSPECTION. DURING MPI THERE W	AS A CRACK OF APPROXIMATELY .3125 INCH IN LENGTH NOTED AT THE RADIUS.  ALL OTHER AIRCRAFT IN OUR FLEET WILL BE INSPECTED	. THE EYEBOLTS WILL BE REPLACED WITH NEW PRIOR TO THE AIRCRAFT BEING RETURNED TO SERVICE. I WOULD LIKE TO SUGGEST THAT A	LL OPERATORS OF THIS AIRCRAFT TYPE INSPECT THE EYEBOLTS FOR CRACK INDICATIONS.			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2004010600112	20040106	00112	SW  	2004	1	6	CA031107016      	1	20031107	G	5510	AN4730A	EYEBOLT         			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCB5M	HCB5MA3     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MPI INSPECTION OF THE HORIZONTAL STABILIZER STRUT ATTACH EYEBOLTS, A CRACK APPROXIMATELY .1875 INCH IN LENG	TH WAS NOTED. ALL EYEBOLTS WILL BE REPLACED PRIOR TO THE AIRCRAFT BEING RETURNED TO SERVICE.					1	L	7	1 	3T	3	T	NC	A19SW   	E2NE	6	C	P44GL	 
2004012600060	20040126	00060	EA  	2004	1	26	CA031107017      	1	20031107	G	5340	215260533	LEVER           			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	UPLOCK ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 'C' CHECK OF THE WATER SYSTEM A MPI INSPECTION WAS COMPLETED ON THE WATERDOOR UPLOCK ACTUATING LEVER MOUNTI	NG LUG. A CRACK WAS NOTED ON THE MOUNTING FLANGE. THE CRACK IS APPROXIMATELY .5000 INCH IN LENGTH. THE PART WILL BE REPL	ACED WITH A SERVICEABLE UNIT.				2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
2004012600061	20040126	00061	NM  	2004	1	26	CA031109001      	1	20031106	G	3230	69600892	SPRING          			BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) UPON DEPARTURE FROM THE NOSE LANDING GEAR FAILED TO LOCK UP.  AFTER SELECTING GEAR HANDLE TO NEUTRAL POSITION THE 	NOSE GEAR FELL OUT OF THE NOSE WHEEL WELL.  SEVERAL SUBSEQUENT GEAR UP SELECTIONS WERE UNSUCCESSFUL. THE AIRCRAFT RETURN	ED AND MADE AN UNEVENTFUL LANDING.  RECERTIFICATION THE AC WAS DISPATCHED IAW FERRY FLIGHT PERMIT.  MAINTENANCE DISCOVER	ED THAT ONE OF THE NOSE GEAR SKI SPRINGS HAD FAILED THEREBY INTERFERING WITH THE RETRACTION OF THE SKI AND IN TURN PREVE	NTING THE NOSE GEAR FROM LOCKING UP.  THE SKI SPRING WAS REPLACED AND GEAR SWUNG WITH NO FURTHER FAULT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2004010600174	20040106	00174	NM  	2004	1	6	CA031110001      	1	20031109	G	3233	65B0150422	ACTUATOR        			BOEING	747   	747433      	       	NM  	PWA   	4056  	PW4056      	 	NE  					MLG	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA						0569					(CAN) AFTER T/O, UNABLE TO RETRACT GEAR.  GEAR TILT MSG ON EICAS AND RT BODY GEAR TILT INDICATION.  FLT RETURNED TO FRA 	AT 38,000 KG OVERWEIGHT.  ACTUATOR AND FLEX LINE BORROWED AND INSTALLED, ALL CKS NORMAL.  O/W LANDING CHECK CARRIED OUT.					2	L	7	4 	4F	4	F	RT	A20WE   	E24NE				 
2004031500077	20040315	00077	SW  	2004	3	15	CA031110002      	1	20031107	G	6420		BUSHING         	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR HEAD	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						AHW50066					(CAN) TWO PITCH HORNS WERE IN FOR REPAIR, ONE HAD BUSHINGS IN HOLES AND BOTH HAD ODD SERIAL NUMBERS.  WE CONTACTED OEM A	ND THEY SAID THAT THE BUSHED HOLES WOULD NOT BE APPROVED BY THEM.   AS FOR THE SERIAL NUMBERS, ONE COULD NOT BE CONFIRNE	D AS BEING MADE BY MFG AND THE OTHER SERIAL NUMBER WAS SOLD TO THE VENEZUELA MILITARY AND IT IS POSSIBLE FOR IT TO MAKE 	ITS WAY BACK TO THE COMMERCIAL MARKET. WE ARE HOLDING THE PARTS PENDING FURTHER INVESTIGATION.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2004010700013	20040107	00013	NE  	2004	1	7	CA031110003      	2	20031107	G	7261		ENGINE          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	RIGHT	LEAKING         	W				O				OTHER                   				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	AP	APPROACH       	1			CA								PS0163			(CAN) DURING APPROACH AND LANDING, CREW NOTED BURNING ODOR AND LIGHT SMOKE IN CABIN. LAVATORY SMOKE DETECTOR TRIPPED AND	 RIGHT ENGINE OIL PRESSURE BEGAN TO DROP. LANDING AND ROLL WAS COMPLETED SO THE EGNINE WAS SECURED AT THE GATE. SEVERAL 	QUARTS OF OIL WERE EXHAUSTED OUT THRU THE COMPRESSOR INLET ONTO THE RAMP.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2004010700014	20040107	00014	SW  	2004	1	7	CA031110004      	1	20031029	G	3230	1114174S0135	HOSE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	LEAKING         	W				L				ABORTED APPROACH        				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) UPON DESCENT, CREW SELECTED GEAR DOWN.  RT GEAR INDICATED ONLY (IN TRANSIT).  CREW DID A FLY BY AND TOWER CONFIRME	D THAT THE GEAR WAS NOT DOWN. THE CREW CLIMBED OUT, SELECTED THE EMERGENCY GEAR SYSTEM, AND THE GEAR EXTENDED NORMALLY. 	 THEY DID ANOTHER FLY BY, AND TOWER CONFIRMED ALL 3 GEAR WERE DOWN, AND THEY HAD 3 GREEN LIGHTS INDICATED. MAINTENANCE I	NSPECTED THE AIRCRAFT, DETERMINED THAT MAIN GEAR DOWN HOSE HAD FAILED (SEVERE LEAK) CAUSING A LOSS OF PRESSURE TO THE NO	RMAL GEAR DOWN ACTUATOR.  MAINTENANCE REPLACED THE HOSE, CONDUCTED GEAR SWINGS, AND INSPECTED THE GEAR SYSTEM FOR ANY FU	RTHER ANOMALIES.  HYDRAULIC FLUID WAS REPLENISHED, AND THE AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER DIFFICULTIES.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2004012600062	20040126	00062	NE  	2004	1	26	CA031110006      	1	20030803	G	6220	S161026005	PISTON ROD      	SKRSKY      	S161026000  	SKRSKY	S58T  	S58ET       	8141803	NE  	PWA   	PT6T  	PT6T3       	52045	EA  					DAMPER ASSY	SEVERED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA						41585					(CAN) ON AIRCRAFT APPROACH FOR LANDING, AIRFRAME VIBRATION WAS FELT.  UPON LANDING AIRCRAFT WAS GROUND ROCKING.  REDUCTI	ON OF ENGINE THROTTLES INCREASED GROUND ROCK AND AIRFRAME VIBRATION. THROTTLES SHUT-OFF AND ROTOR BRAKE APPLIED, UPON BR	AKING M/R BLADE SWEPT FORWARD.  INVESTIGATION FOUND M/R DAMPER PISTON ROD SEVERED AT THREADED PORTION.  DAMPER PISTON RO	D SENT OUT FOR METALLURGY TESTING.			2	G	7	2 	4U	4	U	 	1H11    	E22EA				 
2004012600063	20040126	00063	EA  	2004	1	26	CA031110007      	2	20030901	G	7250		BLADE           			SKRSKY	S58T  	S58ET       	8141803	NE  	PWA   	PT6T  	PT6T3       	52045	EA  					TURBINE SECTION	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) THE AIRCRAFT WAS ENGAGED IN FIRE FIGHTING DUTIES WHEN ENGINE VIBRATION WAS FELT.  ALL AIRCRAFT SYSTEMS WERE IN NOR	MAL, OPERATIONAL AND PERFORMANCE LIMITS.  SUBSEQUENT TROUBLESHOOTING OF THE POWER SECTION WAS COMPLETED AND THE POWER SE	CTION WAS REMOVED FROM THE AIRCRAFT FOR FURTHER INVESTIGATION.  PRELIMINARY TEARDOWN FOUND THAT COMPRESSOR TURBINE WHEEL	 HAD THREE PARTIAL BLADES MISSING.  ONE BLADE WAS MISSING HALF OF ITS LENGTH AND TWO OTHERS MISSING APPROXIMATELY .1250 	INCH FROM THE TIP OF THE BLADES.  THE POWER SECTION IS CURRENTLY AT AN ENGINE OVERHAUL SHOP FOR FURTHER INVESTIGATION.  	INVESTIGATION REPORTS ARE CURRENTLY PENDING.	2	G	7	2 	4U	4	U	 	1H11    	E22EA				 
2004010700040	20040107	00040	EA  	2004	1	7	CA031110008      	1	20031101	G	3510	6044441011	CONTROLLER      			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX OXYGEN	BURNED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											(CAN)AFTER T/O, CREW NOTICED OVERHEATING ELECTRONIC SMELL, SMALL AMOUNT OF SMOKE FROM PASSENGER'S OXY CNTL PANEL. CREW D	IVERTED AC, HEADED BACK TO AIRPORT OF ORIGIN.  LIGHT DIMMER ASSY (PS1LN) WIRE LN15C22 FEEDING 5 VAC TO OXYGEN CTRL PANEL	 (P/N 6044441011, WIRED DURING COMPLETION PHASE) FOR INTEGRAL LIGHT WAS CONNECTED TO HIGH VOLTAGE (HV) POST, THUS FEEDIN	G 115 VAC FROM CBP2-C12 (BUSS 2) DIRECTLY TO INTEGRAL LIGHTING.  THIS RESULTED IN SHORT CIRCUIT INTERNALLY TO INTEGRAL L	IGHTING FACEPLATE BURNING FUSE (OVER CURRENT) IN LIGHTING CIRCUIT DIM. SYS WAS SERVICEABLE UPON CONNECTING WIRE LN15C22 	TO LV2 POST OF PS1L, IAW WIRING DIAGRAM, REPLACING PASS OXYGEN CTRL PANEL AND THE PS1L'S FUSE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004010700041	20040107	00041	NE  	2004	1	7	CA031113001      	2	20031014	G	7200		ENGINE          			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					RIGHT	SHUTDOWN        	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA								35102			(CAN) DURING CRUISE AT FL 390, THE RT ENGINE SHUTDOWN. THE CREW REPORTED ALL ENGINE PARAMETERS WERE NORMAL AT THE TIME A	ND NO MESSAGES OR CAUTIONS WERE POSTED. THE CREW DECENDED AND PERFORMED A SUCCESSFUL WINDMILL RELIGHT AT 10,000 FT.   FO	LLOWED BY AN UNEVENTFUL LANDING.  THE FOLLOWING MAINTENANCE ACTIONS WERE PERFORMED ON THE RT ENGINE:  PERFORMED FLAME-OU	T INSPECTION, INSPECTED FUEL FILTER AND A/C TANKS FOR WATER. BOROSCOPED ENGINE. INSPECTED RIGGING OF VSVS AND FEEDBACK C	ABLE. INSPECTED OIL FILTER, INSTALLED AND INSPECTED MAGNETIC CHIP DETECTORS. PERFORMED EXTENSIVE ENGINE RUNS AND POWER A	SSURANCE CHECK. NO ABNORMALITIES NOTED. AIRCRAFT FLOWN FOR FURTHER TROUBLESHOOTING.	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2004010700042	20040107	00042	EA  	2004	1	7	CA031113002      	2	20030812	G	8550	S19515	DRAIN VALVE     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	OIL SUMP	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) AFTER DRAINING ENGINE OIL  DURING A 100 HOUR INSPECTION, THE VALVE WAS CLOSED. UPON CLOSING THE VALVE, IT CAME APA	RT. NO ABNORMAL AMOUNT OF FORCE WAS APPLIED. THE VALVE IS SPRING LOADED CLOSED. IF THIS WERE TO HAPPEN IN FLIGHT ALL OIL	 COULDBE LOST AT A RAPID RATE. THE VALVE WAS REPLACED WITH A DIFFERENT STYLE OF UNIT. ALL THESE VALVES SHOULD BE REMOVED	 FROM SERVICE.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2004010700043	20040107	00043	NM  	2004	1	7	CA031113003      	1	20031109	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			60021								(CAN) 2 INCH CRACK AT S 17R BETWEEN BS 727B AND BS 747 ON RT AFT SIDE OF FUSELAGE.  CRACK REPAIRED IAW MFG SRM 53-30-3 F	IG 48 PROCEDURE IV AND VII.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2004012600064	20040126	00064	SW  	2004	1	26	CA031113004      	1	20031113	G	5751	250000283	SPAR            			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION A CRACK WAS NOTED ON THE AILERON SPAR AT IB HINGE FITTING ATTACH POINT.  THE CRACK IS APP	ROXIMATELY .5000 INCH IN LENGTH, AND STARTS AT THE IB END OF THE SPAR AND IS RUNNING SPAN WISE APPROXIMATELY .1250 INCH 	BELOW THE IB LOWER FITTING ATTACH HOLE.  WE WILL BE INSPECTING THE REST OF OUR FLEET.  THE AILERON WILL BE REPAIRED PRIO	R TO THE AIRCRAFT BEING RETURNED TO SERVICE.			1	H	7	2 	3T	4	T	 	2A4     	E2WE	6	C	P15EA	 
2004012600075	20040126	00075	CE  	2004	1	26	CA031113005      	1	20031110	G	5551	12320131	FITTING         			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING GROUND HANDLING, HOR. STAB. FOUND TO HAVE FREEPLAY ON RT SIDE.  UPON FURTHER INSP, THE RT FWD ATTACH FITTIN	G WAS FOUND TO BE CRACKED.  ALL OTHER EMPANAGE FITTINGS AND ATTACH POINTS WERE INSPECTED FOR LOOSENESS AND CONDITION.  A	LL AREAS FOUND SERVICEABLE. THE FITTING WAS REPLACED AND STABILIZERS WERE RE-INSTALLED.  PRIOR TO DETECTION OF CRACKED F	ITTING, PILOT'S HAD NO REPORTS OF VIBRATION OR UNUSUAL FLIGHT CHARACTERISTICS.  AFTER MAINTENANCE WAS C/O, AIRCRAFT WAS 	RETURNED TO SERVICE.		1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2004012600076	20040126	00076	NE  	2004	1	26	CA031113006      	2	20031110	G	7310	0301007710	LINE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					FUEL SYSTEM	BROKEN          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								9547			(CAN) THE PILOT EXPERIENCED A SLOW SLUGGISH START.  ON INVESTIGATION HE FOUND FUEL ON THE DECK AND DOWN THE LT SIDE OF T	HE ENGINE.  HE FOUND THE LT START INJECTOR FUEL SUPPLY LINE CRACKED NEAR THE FLARE AT THE POINT WHERE IT IS ATTACHED TO 	THE INJECTOR. THE LINE WAS REPLACED.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004012600077	20040126	00077	CE  	2004	1	26	CA031113007      	1	20031112	G	2730	62342051	TORQUE TUBE     			CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					ELEVATOR	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PHASE 5 INSPECTION A TASK INVOLVE THE REMOVAL OF THE AFT VERTICAL FIN TOP FAIRING, TO INSPECTED INSIDE TH	IS AREA.  MAINTENANCE PERSONNEL FOUND THE TWO ELEVATOR TORQUE TUBES WERE CHAFED.  MAINTENANCE PERSONNEL MAINTENANCE DEPA	RTMENT SENT THE PART TO MFG FOR REPAIR. THE DAMAGE WAS BEYOND LIMITS.				2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2004012600095	20040126	00095	CE  	2004	1	26	CA031113008      	1	20031113	G	2710	6260102439	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  	GARRTT	TPE731	TFE7313C    	 	WP  					SPOILER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULE INSPECTION ON RT WING OB FLIGHT SPOILER. THE OB RT SPOILER ACTUATING CABLE (FOR THE FLT SPOILER 	ACTUATOR) WAS FOUND FRAYED UNDER A PULLEY ASSY.					2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2004010700046	20040107	00046	NE  	2004	1	7	CA031113009      	2	20031110	G	7200		ENGINE          			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					NR 4	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) ON FLT FROM YYZ TO DELLI, 3HRS INTO FLT, NR 4 ENG ROLLED BACK TO 75 PERCENT N1 THEN RECOVERED APROX 1,500 NM FROM 	DESTINATION.  LATER ENG OIL FILTER CLOGGED LT CAME ON THEN ENG REDUCED TO 67 PERCENT FOR REST OF FLT. DURING DESCENT NR 	4 ENG SHUTDOWN. ENGINE, MANPOWER AND EQUIPMENT ENROUTE FOR ENG CHANGE.				2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2004012600112	20040126	00112	EU  	2004	1	26	CA031113010      	1	20031016	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 500 HR INSPECTION, PERFORMED A TAIL ROTOR SPAR INSP WITH DISASSEMBLY AS REQUIRED BY AD.1D(3).  FOUND A LA	RGE PIECE OF SPAR SEPARATED ON EDGE IN LONGITUDINAL DIRECTION APPROX. 8 MM IN WIDTH AND 2 MM THICK. SEPARATION EXTENDS F	ROM REINFORCED ATTACHMENT SECTION DOWN TO THE BLADE ROOT. THE TAIL ROTOR WAS REPLACED.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2004010700047	20040107	00047	WP  	2004	1	7	CA031113012      	2	20031109	G	7261	GT331	OIL FILTER      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					LT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE OIL FILTER BYPASS PIN WAS FOUND POPPED ON THE LT ENGINE.  THE OIL FILTER WAS REPLACED AND OIL SAMPLE TAKEN.  D	AMAGE TO THE REMOVED OIL SAMPLE WAS NOTED. THE MOUNTING FLANGE OF THE FILTER WAS MISSING FROM THE RADIUS INWARD. THE OIL	 FILTER IS INCLUDED IN THE WEAR CHECK P/N GT-331 OIL SAMPLE KITS.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2005042700312	20050427	00312	EU  	2005	4	27	CA031113013      	1	20031106	G	3246	1388920629	BEARING RACE    			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	NLG WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						JAN911074					(CAN) AIRCRAFT ON LANDING FELT A VERY STRONG SHIMMY AT THE NOSE, THE PILOTS DID THEIR INVESTIGATION AND ONE OF THE NOSE 	WHEEL BEARINGS WAS COMPLETELY BROKEN AND THE WHEEL WAS LOOSE ON THE AXLE. TECHNICIAN WAS SENT TO REPLACE BOTH NWA'S.  AF	TER INVESTIGATION, LOOSE HUB BOLTS WERE FOUND AND AT BUILD UP PROCEDURE THE OPTIONAL SB340-32-34 IS NOW IMPLEMENTED MAND	ATORY.  THE BEARING CLEANING PROCEDURE WAS REVIEWED AND A NOTICE OF NO PRESSURE WASHING OF WHEEL AREAS WAS ALSO GIVEN AN	D THE SB 50 06227-32-01 (IB SEAL IMPROVEMENT WILL BE PROGRESSIVELY IMPLEMENTED.		2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2004012600104	20040126	00104	CE  	2004	1	26	CA031113014      	1	20031111	G	2710	666000164	CONTROL CABLE   			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					AILERON CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) PILOT REPORTED CONTROL FELT DIFFERENT DURING LANDING. MAINT FOUND RT WING AILERON CABLE ASSY WING UP, BROKEN.  CAB	LE AND PULLEYS ARE ORIGINAL HAVE NOT BEEN REPLACED.  CABLE BROKE AT AFT PULLEY AT WS53.07, BRAKE WAS NOT POLISHED.  PREL	IMINARY INSPECTION REVEALED  FOLLOWING: PULLEY ATTACH BOLT PN AN4H15A WAS ROCKING IN AFT BRACKET PN 66603194.  BOLT HAS 	EVIDENCE OF PLATING WORN OFF, SUSPECT BOTTOM AREA.  AFT PULLEY BRACKET BOLTHOLE ELONGATED TO .3 INCH.  PULLEY PN S3784 H	AD ONLY ONE SMALL SPOT THAT WAS RUFF.  SIDES OF PULLEY HAD POLISHED AFT PULLEY BRACKET.  PULLEY BEARING ROTATES OK.  NO 	EVIDENCE OF CABLE CHAFING ANYTHING, CABLE MISS ROUTING OR PULLEY BINDING.	2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2004012600065	20040126	00065	EA  	2004	1	26	CA031114001      	1	20031106	G	2820	T99A378603	EJECTOR         			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  						CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL WAS TRANSFERRING FROM THE RT TANK TO THE CENTER TANK.  THE TRANSFER WAS NOTICED WHILE THE A/C WAS ON GROUND. 	 INVESTIGATION REVEALED THAT THE RT PRIMARY EJECTOR WAS CRACKED AND THE FUEL WAS LEAKING FROM THE EJECTOR TO THE CENTER 	TANK.  THE EJECTOR WAS REPLACED AND A/C RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012600066	20040126	00066	EA  	2004	1	26	CA031114002      	1	20031104	G	5610	NP13932110	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			20077								CA031114004(CAN) THE RT WINDSHIELD CRACKED AFTER TAKE OFF.  THE WINDSHIELD WAS A PRE SERVICE BULLETIN.  THE WINDSHIELD W	AS REPLACED AND A/C IS BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012600096	20040126	00096		2004	1	26	CA031114004      	4	20031104	G	2397		WIRE HARNESS    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	AUDIO SELECOTR	CHAFED          	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA											(CAN) A/C DEPARTED, AFTER TAKEOFF, CREW EXPERIENCED A COMMUNICATIONS FAILURE. CREW SQUAKED 7600 & RETURNED FOR LANDING. 	MAINT TROUBLESHOT COMMUNICATIONS SYS.  NR 1 COMM FAILED, REPLACED COMM WITH SERVICEABLE VHF UNIT, COMM NR 1 OPERATING NO	RMAL. AWAITING STRIP REPORT.  NR 2 VHF COMM - WIRE CHAFED (NR 2 COMM 'MIC KEY' WIRE) BETWEEN NR 2 VHF COMM & NR 1 AUDIO 	SELECTOR. CHAFED WIRE GOING TO GROUND. REPAIRED WIRE & CHECKED NR 2 COMM SYS. OPERATING NORMAL.  HF - FOUND LOOSE HF PIN	 IN NR 1 AUDIO SELECTOR, ADJUSTED PIN LOCKING MECHANISM AND RE-INSTALLED. HF STILL HAD TUNING PROBLEM. INSTALLED SERVICE	ABLE HF REC/EXC AND HF AMP. GROUND TUNING ACCOMPLISHED. D) GROUND CHECKS OF RADIOS CARRIED OUT.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2004010700048	20040107	00048	EA  	2004	1	7	CA031114005      	2	20031104	G	8520		THRU BOLT       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	LEAKING         	W				O				OTHER                   				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) SMOKE IN CABIN.  OIL LEAK ON FRONT OF ENGINE, LEADKED OIL DOWN BAFFLE TO HEAT MUFF INLET.  OIL DRIPPED INSIDE HOT 	MUFFLER CREATING SMOKE.  2 FORWARD CRANK CASE THROUGH BOLTS FOUND LEAKING.   REPAIRS ARE NOT COMPLETED YET, 4 NOV. 03.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004012600070	20040126	00070	WP  	2004	1	26	CA031114006      	1	20031103	G	3610	321417611	REGULATOR       			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					DOOR SEAL	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, FLOW LIGHT (PRESS) COME ON, UNABLE TO STABILIZE, ACFT LANDED BACK.  FOUND AFT GALLEY DOOR SEAL NOT P	ROPERLY SEATED.  DURING SECOND CLIMB, SAME FLOW LIGHT CAME ON WITH BOTH AIRCRAFT PACKS BETWEEN 0-2 PSI  ACFT LANDED BACK	 AND ACFT FERRIED TO BASE.  LT PNEUMATIC PILOT PRESSURE REGULATOR REPLACED ALSO RT PRESSURE REGULATOR VALVE REPLACED AND	 RT AIR CONDITIONING PILOT PRESSURE REGULATOR REPLACED.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004012600079	20040126	00079	EU  	2004	1	26	CA031114007      	1	20031016	G	2897		CONNECTOR       			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					FUEL PUMP	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) WHILE THE AIRCRAFT WAS IN CRUISE FLIGHT, A BURNING ODOR WAS NOTICED IN THE CABIN. THE PILOT LANDED THE AIRCRAFT UN	EVENTFULLY. THE BURNING ODOR WAS TRACED TO THE OVERHEAD LT FUEL PUMP SWITCH.  WHEN THE OVERHEAD PANELS WERE REMOVED A BU	RNED PUMP SWITCH CONNECTOR WAS SEEN.  CONNECTOR WAS REPLACED. THE RT SIDE WAS ALSO CHECKED AND IT WAS NOTED THAT THE CON	NECTOR IS SHOWING SIGNS OF OVER HEAT.  TWO SEPARATE D.C. BUSES, PUMP SWITCHES AND PUMPS AFFECTED.			1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2004012600097	20040126	00097	EA  	2004	1	26	CA031114008      	1	20031114	G	2721		THRUST BEARING  			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SPRING TAB WAS STIFF, IT WAS LUBED AND WORKED NORMAL. ON SCHEDULED WINTER MAINTENANCE INSPECTION BEARING WAS FOUND	 TO BE WORN PAST LIMITS.					2	H	7	2 	4R	4	R	RT	A14EA   	E231	6	C	P871	 
2004012600087	20040126	00087	SW  	2004	1	26	CA031114009      	1	20031114	G	5751	250000283	SPAR            			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AS A FOLLOW UP INSPECTION ON THE REST OF OUR FLEET FOLLOWING THE DISCOVERY OF THE CRACKED AILERON SPAR ON OUR AIRC	RAFT, THE LT AILERON SPAR WAS FOUND CRACKED ON THIS AIRCRAFT.  THE CRACKS ARE ALL LOCATED IN THE SAME AREA AS PREVIOUSLY	 REPORTED AND ARE APPROXIMATELY .5000 INCH IN LENGTH. THE IB AILERON RIBS ON THE LT AILERONS WERE ALSO FOUND CRACKED. TH	E CRACKS ON THE RIBS WERE APPROXIMATELY .5000 INCH IN LENGTH.  I WOULD LIKE TO SUGGEST THAT ALL OPERATORS OF THIS AIRCRA	FT TYPE DO AN INSPECTION OF THEIR AIRCRAFT. WE INSPECTED THE RT AILERONS BUT FOUND NO DAMAGE. THE AIRCRAFT WILL BE REPAI	RED PRIOR TO BEING RETURNED TO SERVICE.	1	H	7	2 	3T	4	T	 	2A4     	E2WE	6	C	P15EA	 
2004012600081	20040126	00081	NE  	2004	1	26	CA031117001      	2	20031109	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) MFG HAS RECEIVED A REPORT WHICH WE FEEL IS A REPORTABLE EVENT. AFTER TAKE OFF HEARD LOUD BANG AND VIBRATION FROM R	T ENGINE.  ENGINE SHUTDOWN.  RETURNED TO AIRPORT.  ENGINE SUFFERED INTERNAL FAILURE.  ENGINE REPLACED, AIRCRAFT RETURNED	 TO SERVICE. NOTE: TIME SINCE LAST BOROSCOPE  666.5 HRS,  552 CYCLES.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004010700049	20040107	00049	NM  	2004	1	7	CA031117002      	1	20031111	G	5330		SKIN            			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 3 INCH CRACK IN FUSELAGE SKIN AFT OF REAR WING TO BODY FAIRING TOP OF 18L BETWEEN BS 747 - BS 767.  REPAIRED SRM I	AW 53-30-3 FIG 48 (SHEET 33) DETAIL XI, REF PROCEDURE IV AND VII. AIRCRAFT TIME 56,88:17CYCLES52,484 C					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2004012600088	20040126	00088	NM  	2004	1	26	CA031117003      	1	20031111	G	5330		SKIN            			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 2.34 CRACK IN FUSELAGE TOP OF S18L BETWEEN BS 727A AND BS 727B.  REPAIRED IAW SRM 53-30-3,FIG 48, SHEET 33, DETAIL	 XI REFERENCE PROCEDURE IV AND VII.  AIRCRAFT TIME 56,880:17 CYCLES52,484 C					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2004010700051	20040107	00051	NM  	2004	1	7	CA031117004      	1	20031113	G	5330		SKIN            			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48876								(CAN) THE AIRCRAFT WAS ON A (C CHECK. UPON INSPECTION OF THE FUSELAGE, A QUESTIONABLE SCRATCH WAS FOUND AT STATION BS 70	0 STRINGER NR 1.  PAINT WAS STRIPPED AND NDT INSPECTION CARRIED OUT. A CRACK OF HALF INCH LONG WAS DISCOVERED. THE FUSEL	AGE WAS REPAIRED IAW SRM.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2004012600109	20040126	00109	SW  	2004	1	26	CA031117005      	1	20031031	G	7120	206062101013	LEG ASSY        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DENTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11003								(CAN) DURING ENGINE COMPRESSOR CHANGE (SCHEDULED), 6 ENGINE LEGS WERE SENT OUT TO BE STRIPPED, NDT ED, AND REPAINTED. DU	RING STRIPPING STAGE IT WAS NOTED THAT P/N 206-062-101-014 HAD A SMALL DENT ON IT (ABOUT 4 =FROM TOP). IT WAS FOUND TO B	E BEYOND MFG LIMITATION FOR REPAIR. DENT HAS APPEARANCE OF BEING CAUSED BY MECHANICAL DAMAGE AT SOME POINT IN TIME. DURI	NG NDT INSPECTION OF WAS FOUND TO HAVE A SMALL PIN HOLE ABOUT 2 FROM THE TOP. IT WAS NOTED THAT THERE WERE 2 SMALL MARKS	 ON EITHER SIDE OF PIN HOLE THAT LOOK LIKE A LOCKWIRE TWIST.  IT APPEARS THAT A LOCKWIRE TWIST FROM ENGINE MOUNT HAS CON	TACTED THE ENGINE LEG AT SOME POINT IN TIME. THERE IS NO REQUIREMENT FROM MFG TO NDT ENGINE LEGS.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004012600110	20040126	00110	SW  	2004	1	26	CA031117006      	1	20031031	G	7120	206062111101	MOUNT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11003								(CAN) DURING AN ENGINE COMPRESSOR CHANGE (SCHEDULED), THE 3 ENGINE MOUNTS P/N 206-062-111-101 WERE SENT OUT TO BE STRIPP	ED, NDT , AND REPAINTED. DURING THE NDT STAGE THERE WERE CRACK INDICATIONS FOUND ON 2 OF THE MOUNTS ALONG THE TREADED PO	RTION.  THE SUBJECT MOUNTS WERE REPLACED WITH NEW ASSY S. THERE IS NO REQUIREMENT FROM THE MANUFACTURER TO NDT THE ENGIN	E MOUNTS.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004031500115	20040315	00115	EU  	2004	3	15	CA031117007      	1	20031110	G	3310	8623	LAMP            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	COCKPIT	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) TRANSFORMER IS DESIGNED TO STEP DOWN 115 VAC SUPPLY VOLTAGE TO A MAX OF 5 VAC REQUIRED BY REST OF CIRCUITRY.  OUTP	UT WIRES FROM ABOVE MENTIONED TRANSFORMER ARE INCREASED IN GAUGE SIZE TO 16 AWG, SO THAT IN  EVENT OF A GROUND FAULT TRA	NSFORMER OUTPUT WIRING WOULD HAVE SUFFICIENT ELECTRICAL CURRENT CAPACITY TO TRIP CB AND PROTECT OVER ALL CIRCUIT INTEGRI	TY.  DUE TO A DESIGN OVERSIGHT, ONE OF TWO TRANSFORMER OUTPUT WIRES SELECTED WAS OF INSUFFICIENT SIZE, 24 AWG. THEREFORE	, ANY GROUND FAULTED COMPONENT PRESENT ON ITS ASSOCIATED LIGHTING BUSS IE:  LAMP MODULE, CAUSED THIS WIRE TO ACT LIKE AN	 ELECTRICAL HEATING ELEMENT.  THIS CAUSED A SERIOUS FIRE HAZARD SITUATION, DUE TO EXCESSIVE CURRENT FLOW WITHIN CIRCUIT.	2	H	7	2 	4T	4	T	 	A41EU   	E4EA	6	C	P44GL	 
2004012600103	20040126	00103	EU  	2004	1	26	CA031117008      	1	20031110	G	3150	8623	LAMP            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65AR    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	FUEL TOTALIZER	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) PILOT NOTED ELEC BURNING ODOR.  CREW DISENGAGED AC ELEC MASTER.  FOUND TRANS & WIRING  WARM TO TOUCH.  WIRES MELTI	NG A PLASTIC ABRASION SHIELD. DAMAGE DETECTED IN WIRING WITH TRANS & WIRES WITHIN SAME BUNDLE. TRANS DISCONNECTED FROM C	IRCUIT & CHECKED.  DAMAGED WIRING & ABRASION SHIELD WERE REPAIRED & TRANS REINSTALLED.  MAINT PERFORMED A LIGHTING CHECK	 & REPLACED A LINE LAMP MODULE INSTALLED IN  FUEL TOTALIZER DISPLAY. LAMP ASSY HAD A MFG DEFECT. DEFECT SHORT CIRCUITED 	LIGHTING BUSS. RESULTED IN EXCESS CURRENT PRESENT WITHIN SYS, CAUSING TRANS & ASSOC WIRES TO OVERHEAT. CONCLUDED THAT TH	E FAULTY BULB INITIATED PROBLEM A POSSIBLE FLAW IN CIRCUITS WIRING CAUSED WIRING FAILURE. DEFECTIVE CIRCUIT.	2	H	7	2 	4T	4	T	 	A41EU   	E4EA	6	C	P44GL	 
2004012600099	20040126	00099	CE  	2004	1	26	CA031117010      	1	20031112	G	5280		DOOR            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					MLG	MISMANUFACTURED 	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) WHEN LANDING GEAR WAS SELECTED UP THE RED INTRANSITE LIGHT WOULD NOT GO OUT. THE A/C WAS PLACED ON JACKS AND FOUND	 THE RT GEAR DOOR WAS TOO TIGHT NOT ALLOWING THE GEAR TO LOCK UP AND TURN THE INTRANSITE LIGHT OUT.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2004012600101	20040126	00101	SO  	2004	1	26	CA031117012      	1	20031116	G	3297		WIRE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) ON THE LANDING APPROACH GEAR WAS SELECTED DOWN.  THE LT GEAR LIGHT WOULD NOT COME ON.  A FLY PAST WAS DONE AND MTC	E CONFIRMED THE GEAR WAS DOWN. THE C/B WAS PULLED AND GEAR WAS SELECTED DOWN TO HYD LOCK THE GEAR DOWN.  LANDING WAS MAD	E AND FOUND A BROKEN WIRE ON THE GEAR SWITCH. REPAIRED WIRE AND RETURNED TO SERVICE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004012600102	20040126	00102	WP  	2004	1	26	CA031117013      	1	20031114	G	6220	369A1228901	STOP            	DOUG        		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					DROOP	UNSERVICEABLE   	W				O				OTHER                   				F	D		FLT CONT AFFECTED         	INFLIGHT SEPARATION       		NR	NOT REPORTED   	1			CA						2472					(CAN) PILOT REPORTED M/R HUB ASSY STIFF TO FLAP DURING DAILY INSPECTION. UPON INVESTIGATING THE DROOP STOP ASSY  WAS FOU	ND THAT THE ROLL PINS (P/N NAS561C5-14) THAT HOLD THE T-HEAD (P/N 369A1229-3) TO THE PLUNGER (P/N 369A1240-3) HAD WORKED	 THERE WAY OUT ON 3 ASSY'S. THE ROLL PINS DAMAGED THE PLUNGERS AS WELL AS THE BEARINGS (P/N 369A1237) IN WHICH THE PLUNG	ERS RIDE IN ON THE 3 LOCATIONS WHEN THEY CAME OUT.  ALL THREE PLUNGERS AND BEARINGS REQUIRED REPLACEMENT AND ALL ROLL PI	NS REPLACED WITH NEW. M/R HUB ASSY HAS TO BE REMOVED FOR THE REPLACEMENT AND RE-INSTALLED.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004012600082	20040126	00082	CE  	2004	1	26	CA031117014      	1	20031113	G	5260	1015141439	CABLE           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	AIRSTAIR  LATCH	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF CABIN DOOR CAM LOCK LATCHES, THE DOOR LATCHING CABLE WAS FOUND TO HAVE HALF TO THREE QUARTERS	 OF THE CABLE STRANDS BROKEN.  IF THIS CABLE WOULD HAVE BROKEN COMPLETELY IT COULD HAVE CAUSED ONE COMPLETE SIDE OF DOOR	 TO BECOME UNLATCHED DURING FLIGHT.  THESE CABLES HAVE AN 8000-CYCLE LIFE AND ONLY LASTED 2814 CYCLES.  THE CABLES WERE 	REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2004012600083	20040126	00083	NM  	2004	1	26	CA031117015      	1	20031113	G	3000	AS323710	FASTENER        			BOEING	737   	73776N      	13844CH	NM  	CFMINT	CFM567	CFM567B22   	13802	NE  					MANIFOLD	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						NA					(CAN) REGULAR SCHEDULE MAINTENANCE INSPECTION.  MAINTENANCE ENGINEER FOUND NR 1 AND NR 2 ENGINE THERMAL ANTI ICE MANIFOL	D FOR NOSE COWL BOLTS BACKING OUT WHILE CONDUCTING MFG TASK CARD NR 36-020-01-00 (FUNCTION CHECK PRECOOLER CONTROL VALVE	, WING TAI SOLENOID).  COMPANY ISSUED FLEET INSPECTION FOR LOOSE FASTENERS.  SEVERAL AIRCRAFT FOUND WITH LOOSE BOLTS. IN	SPECTED AND CORRECTED THROUGH COMPANY SPECIAL MAINTENANCE ITEM INSPECTION. REFERENCE:  POWERPLANT BUILD UP MANUAL, FIGUR	E 13-1, 12 O'CLOCK STRUT INSTALLATION, 71-00-02, PAGES 1-4.		2	L	7	2 	4F	4	F	RT	A16WE   	E00055EN				 
2004012600084	20040126	00084	EU  	2004	1	26	CA031118001      	1	20031117	G	2612	9751210099	CLAMP           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FIRE DETECTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FIRE DETECTION SYSTEM ON ENGINE, QUICK RELEASE CLAMPS WHICH HOLD ISOLATORS AND FIRE LOOP IN PLACE FOUND WORN. CAUS	ED FIRE LOOP TO BECOME UNSECURE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012600085	20040126	00085	EU  	2004	1	26	CA031118002      	1	20031116	G	2530		MODULE          			AIRBUS	320   	A320212     	3930322	EU  	CFMINT	CFM56 	CFM565A3    	 	NE  					COFFEEMAKER	BURNED          	W				A				UNSCHED LANDING         				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA											(CAN) AIRCRAFT DIVERTED DUE TO SMOKE/BURNING ODOR IN FWD GALLEY.  FAULT WAS DETERMINED TO BE THE NR 2 COFFEEMAKER AND WA	S REMOVED.  FURTHER INVESTIGATION OF COFFEEMAKER REVEALED A LOOSE TERMINAL NUT ON POWER MODULE ASSEMBLY.  THIS CAUSED TH	E TERMINAL TO HEAT UP AND IN TURN MELTED/BURNED INSULATION ON TERMINAL LUG.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2004012600086	20040126	00086	EU  	2004	1	26	CA031118003      	1	20031117	G	3251		CASTING         			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	YOKE	BROKEN          	W				O				OTHER                   				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		LD	LANDING        	1			CA											(CAN) AFTER LANDING, THE AIRCRAFT FELT A SHIMMY VIBRATION.  AT THE GATE THE PILOT NOTICED A BROKEN PIECE MISSING OFF THE	 NOSE STEERING COLLAR YOKE ASSY. AFTER INVESTIGATION THE PART INSTALLED IS PRE SB32-099 WHICH CALLS FOR REGULAR INSPECTI	ON DUE TO THAT SAME REASON AS NAMED ABOVE. AT THIS MOMENT THIS IS NOT A MANDATORY SB OR AD.  WE WILL BE IMPLEMENTING THE	 SB WITH THE NEW PN 3931074101 AS PART OF OUR FLEET RELIABILITY PROGRAM.			2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2004012700016	20040127	00016	NE  	2004	1	27	CA031118004      	2	20031102	G	7200		ENGINE          			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502L     	41580	NE  					RIGHT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) APPROX 20 MIN AFTER TAKE-OFF, THE CREW NOTICED A HIGH VIBE INDICATION ON THE RT ENGINE. THEY THROTTLED BACK TO IDL	E WITH NO CHANGE IN VIBES. THE CREW ELECTED TO SHUTDOWN THE ENGINE AND RETURN TO THEIR POINT OF DEPARTURE, WHERE THEY MA	DE AN UNEVENTFUL LANDING.  SUBSEQUENT CHECKS REVEALED CHIPS IN THE CHIP DETECTORS AND SOME RESISTANCE WHEN ROTATING THE 	FAN BY HAND. THE ENGINE WAS REMOVED AND A LOANER INSTALLED.			2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2004012700017	20040127	00017	EA  	2004	1	27	CA031118005      	2	20031103	G	7220	1099100299	DUCT            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DETECTED IN UPPER FORWARD AREA OF THE INLET DUCT EXTENDING FORWARD AND 1 AFT OF THE OUTBOARD RIVET ROW OF TH	E INLET LIP.  THIS EXCEEDED THE SR-KA-00011 LIMITS, REQUIRING DUCT REPLACEMENT.  WHEN DISASSEMBLING THE COWL FOR DUCT RE	PLACEMENT IT WAS NOTED THAT THE INLET ANTI-ICE TUBES WERE CRACKED WHERE THEY ATTACH TO THE INLET LIP (PN 109-910049-1) A	ND REQUIRED REPAIR BY WELDING BEFORE REASSEMBLY, SEE SRM 54-00-04, PG 201.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2004012700018	20040127	00018	CE  	2004	1	27	CA031118006      	1	20031112	G	2730	5052441029	BELLCRANK       			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	INTERFERENCE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE FORWARD ELEVATOR BELLCRANK, CABLE LOCK TAB, WAS FOUND TO BE INTERFERING WITH THE LANDING GEAR MOTOR RELAY OUTB	OARD MOUNTING BOLT, PREVENTING THE BELLCRANK FROM CONTACTING ITS MAX NOSE UP STOP (ELEVATOR SECONDARY STOPS). THE RELAY 	MOUNTING BOLT WAS EXCESSIVELY LONG, AND MOUNTED HEAD REARWARD SUCH THAT ITS ASSOCIATED NUT/WASHER WAS CATCHING ON THE CA	BLE LOCK TAB INSTALLED ON THE ELEVATOR BELLCRANK. THIS IS THE SAME CONDITION THAT WAS DISCOVERED ON ASSOCIATED SDR 20030	416002.		1	L	7	2 	3T	4	T	 	3A20    	E4EA	6	C	P15EA	 
2004010700063	20040107	00063	EU  	2004	1	7	CA031118007      	1	20031114	G	2422	MGH182100	INVERTER        			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	NR 2	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) NR 2 INVERTER FAILED ON ROUTE TO VANCOUVER.  A/C LANDED WITHOUT INCIDENT.  NR 2 INVERTER WAS REPLACED, TESTED SERV	ICEABLE, A/C RETURNED TO SERVICE.					2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899	 
2004010700064	20040107	00064	NM  	2004	1	7	CA031118008      	1	20031110	G	3246	315731	WHEEL           			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  					NR 4	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE NR 4  MAINWHEEL WAS IN FOR A TIRE CHANGE. AFTER THE WHEEL WAS STRIPPED DOWN AND CLEANED, A LARGE CRACK WAS FOU	ND IN THE INNER BEARING HOUSING,  RUNNING APPROX. 4 INCHES VERTICALLY DOWN THE TUBEWELL SIDE OF THE WHEEL FROM THE BEARI	NG HOUSING.  SECOND CRACK SUBSEQUENTLY FOUND.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2004021700195	20040217	00195	GL  	2004	2	17	CA031118009      	1	20031025	G	2741	VF465F11	RELAY           			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	ELEVATOR TRIM	STUCK           	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) TRIM WAS STUCK IN NOSE UP. TRIM INDICATOR WAS NOT SHOWING FULL UP (ONE LIGHT FROM FULL UP IND), WHEN TRIM WAS SELE	CTED BY EITHER TRIM SWITCHES THERE WAS NO RESPONSE.  FOLLOWING MFG EMER PROCEDURES CHECK CB, (IN) AS THE TRIM MOVED TO F	ULL UP INDICATION AND WOULD NO LONGER MOVE. EMER PROCEDURES INDICATE THAT HIGHER FORCES CAN BE EXPECTED AND TO LAND AT N	EAREST SUITABLE AIRPORT.  STUCK TRIM DID NOT PREVENT FULL DEFLECTION OF ELEVATOR CONTROL OTHER THAN HIGHER FORCES REQUIR	ED. AFTER SEVERAL HOURS IT WAS PINNED DOWN THAT TRIM SWITCHES WERE WIRED THROUGH TWO RELAYS. FOUND THAT DOWN RELAY WOULD	 STICK WHEN TRIM WAS SELECTED IN FULL UP POSITION.  REPLACED BOTH RELAYS AND THEN UNABLE TO FAIL SYS.	1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2004012700019	20040127	00019	WP  	2004	1	27	CA031118010      	1	20030808	G	2435	150SG1028	LINER           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					STARTER GEN	LOOSE           	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA						4947					(CAN) VIBRATION SNAG.  STARTER GENERATOR REPLACED.  OVERHAUL SHOP FOUND THE STEEL BEARING LINER IN THE DRIVE END ENDBELL	 HAD BROKEN LOOSE FROM ITS CASTING AND WORE DOWN THE ALUMINUM ENDBELL.  THE LINER IS CURLED ON THE OUTSIDE, AND THE ROUG	H SURFACE CHEWED THE ENDBELL SUFFICIENTLY TO ALLOW THE ARMATURE TO RUB ON THE STATOR POLES, CAUSING LOSS OF DIAMETER OF 	BOTH PARTS, RENDERING THE ARMATURE AND STATOR SCRAP.  THE DRIVE SHAFT DID NOT SHEAR, AND WAS NOT DAMAGED (MPI DONE).  SE	RVICE BULLETIN SB150SG106 WAS FOUND COMPLIED WITH, THAT SB INSTALLS A DOWEL PIN TO LOCK THE LINER TO THE ENDBELL IN CASE	 IT SHOULD COME LOOSE.	1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004012700020	20040127	00020	NM  	2004	1	27	CA031118011      	1	20031020	G	5552	65174305	RIB             			BOEING	727   	72722C      	138400F	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ACCOMPLISHMENT OF AD 2002-12-13 AND ENGINEERING ORDER 7-5510-7-5001PT1 INSPECTION OF THE ELEVATOR HINGE SUP	PORT RIBS FOR CRACKS IN THE FLANGES ON AIRCRAFT WITH KNOWN 7079-T6 MATERIALS.  A CRACK WAS FOUND IN A NON-TYPICAL AREA N	OT COVERED BY THE AD OR THE EO.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2004012700021	20040127	00021	EA  	2004	1	27	CA031118012      	1	20031115	G	3230	16600103	UPLOCK          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) CREW HAD TO CYCLE THE GEAR HANDLE TWICE TO GET THE NOSE GEAR TO COME DOWN.  REMOVED AND REPLACED THE UPLOCK ASSY. 	 AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012700022	20040127	00022	EA  	2004	1	27	CA031118013      	1	20031116	G	5610	NP1393229	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN)  THE FIRST OFFICER'S SIDE WINDOW SHATTERED AS THE AIRCRAFT DESCENDED OF 41,000 FT.  THERE WERE NO REPORTED PROBLEM	S AFTER THIS OCCURRENCE. MAINTENANCE REPLACED THE DAMAGED SIDE WINDOW AND THE AIRCRAFT RETURNED TO SERVICE.  (SEE ALSO: 	US NR 2003121700181)				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012700023	20040127	00023	NM  	2004	1	27	CA031119001      	1	20031107	G	6220	A1581	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					M/R HEAD	ROUGH           	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED MAIN ROTOR SYSTEM ROUGH INTERMITTENT.  INSPECTED BY AME, SPINDLE BEARINGS FOUND ROUGH. SENT FOR REP	AIR.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2004012700024	20040127	00024	EA  	2004	1	27	CA031119002      	2	20031113	G	7323	25241673	GOVERNOR        			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 1 ENGINE	FAILED          	W				O				OTHER                   				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			CA											(CAN) NR 1 ENGINE POWER SURGING PRIOR TO LANDING, AFTER LANDING ENGINE FLAME OUT OCCURED.						1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2004010700065	20040107	00065	SO  	2004	1	7	CA031119003      	2	20031113	G	7322		CARBURETOR      			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	ICED            	W				B				EMER. DESCENT           				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			CA											(CAN) DEPARTING, CLIMBED UP TO CRUISING ALTITUDE OF 4,500 FT, STARTED DESCENT BY REDUCING POWER FROM 2,500 RPM TO APPROX	 2,350 RPM. TEMP WAS -2 AND DEWPOINT -9 FOR 6,000 FT. GOT DOWN TO 3,500, LEVELED OFF, WENT TO ADD POWER FOR CRUISE, ENG 	SPUTTERED, WENT TO IDLE, THEN BACK TO FULL RPMS AND CONTINUED, FORCING SHALLOW DESCENT. PULLED ON CARB HEAT MIX FULL RIC	H, CKD FUEL VALVE, PRIMER, MAGS, OIL TEMP, OIL PRESS,  CKD OK. REACHING 500 FT AGL, POWER DID NOT REGAIN SO COMMITTED TO	 FORCED APPROACH BY SHUTTING DOWN ENG. AC TOUCH DOWN IN FIELD AND CAME TO A ROLLING STOP, NO DAMAGE.  RCMP WERE DISPATCH	ED. GROUND PERSONNEL PULLED COWL OFF, INSP ENG, FUEL SYS, DID RUN-UP, DETERMINED CARB ICE WAS PROBLEM.	1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2004012700025	20040127	00025	CE  	2004	1	27	CA031119004      	1	20031030	G	8120	12509291	COUPLING        	GARRETTLTD  		CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360CB   	17025	SO  	MCAULY	2AF34C	D2AF34C303  	GL  	TURBOCHARGER	SEPARATED       	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA						BAO06000					(CAN) COUPLING SEPARATED FROM TURBOCHARGER COMPRESSOR HOUSING CAUSING INDUCTION LEAK AND RESULTING POWER LOSS.						1	H	7	2 	3O	3	O	 	A6CE    	E9CE	5	C	P5EA	 
2004012700026	20040127	00026	SW  	2004	1	27	CA031119005      	1	20031023	G	6310	206040222005	SHAFT           	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FREEWHEEL UNIT	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						B12165					(CAN) FREEWHEEL SENT FOR OVERHAUL.  NEW INNER SHAFT REQUIRED.  INNER SHAFT PURCHASED NEW AND INSTALLED WITH NEW SEALS.  	FREEWHEEL INSTALLED ONTO AIRCRAFT FOR 24.3 HOURS THEN REMOVED FORWARD SEAL LEAKING.  FREEWHEEL ASSEMBLY RETURNED TO OVER	HAUL SHOP FOR SEAL WARRANTY, SEAL REPLACED.  FREEWHEEL RE-INSTALLED AND REMOVED ONCE AGAIN FORWARD SEAL LEAKING.   ASSEM	BLY DISASSEMBLED AND INSPECTED.  INNER SHAFT FOUND TO BE OUT OF ROUND OR BENT CAUSING SEAL TO LEAK.  SHAFT TAGGED UNSERV	ICEABLE AND RETURNED TO MANUFACTURER FOR INSPECTION.  NEW SHAFT INSTALLED INTO FREEWHEEL ASSEMBLY AND CONFIRMED STRAIGHT	.  QUALITY CONTROL OF NEW PARTS BETTER CONTROLLED AT MANUFACTURER.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004012700027	20040127	00027	NM  	2004	1	27	CA031119006      	1	20031116	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			61732								(CAN) 2 INCH CRACK FOUND BELOW S17L BETWEEN BS 749 - 751. CRACK REPARED IAW SRM CHAPTER53-30-3, FIG 48, DETAIL XI.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2004010700066	20040107	00066	EU  	2004	1	7	CA031119007      	1	20031119	G	3242	AN52765	BRAKE           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	RT MLG	DRAGGING        	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											(CAN) RIGHT BRAKE DRAGGED ON TAKEOFF OUT OF YXY A/C RETURNED TO GATE WITH NO INCIDENTS. NR 3 BRAKE REPLACED.						2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899	 
2004012700028	20040127	00028	SO  	2004	1	27	CA031119008      	1	20031117	G	3610	442CW6	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PNEUMATIC SYS	INOPERATIVE     	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) AT RT ENGINE RUN UP FOUND LIGHT PNEUMATIC SOURCE MALFUNCTION STAYING ON TILL 2000 RPM.  AFTER TROUBLESHOOTING FOUN	D THE PUMP PN 442CW-6 WOULD NOT DELIVER RATED PNEUMATIC PRESSURE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004012700029	20040127	00029		2004	1	27	CA031119009      	4	20031119	G	2562	1104	ELT             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					CABIN	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ARTEX ELT MODEL ELT 110-4 P/N 453-0150 WAS WIRED INCORRECTLY- THE ELT WOULD ONLY ACTIVATE BY PANEL SWITCH OR THE S	WITCH ON THE ELT.  FOR THE ELT TO BE OPERATED IN AUTOMATIC MODE A JUMPER WIRE BETWEEN PINS 5 AND 8 OF MOLEX TRAY CONNECT	OR NEEDS TO BE INSTALLED. ON THIS A/C THE JUMPER WIRE WAS MISSING. THERE IS A CAUTION DECAL BESIDE THE PANEL SWITCH ABSE	NCE OF LIGHT DURING FIRST 3 SECONDS OF TEST INDICATES POSSIBLE G-SWITCH FAILURE.   IN INSTRUCTIONS STEP 4, IT IS VERY IM	PORTANT THAT LIGHT COME ON DURING THE FIRST FEW SECONDS OF TEST.  IF THE LIGHT FAILS TO COME ON IMMEDIATELY CHECK PINS 5	 AND 8 OF THE ELT UNIT MOLEX CONNECTOR TO MAKE SURE THAT THEY ARE JUMPERED PROPERLY.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004012700030	20040127	00030	SW  	2004	1	27	CA031120001      	1	20030505	G	6730	C4264269	ACTUATOR        	RONSON      		BELL  	206   	206L4       	1182110	SW  										HYD SERVO	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						RH4578A					(CAN) WHILE SERVICING THE HYDRAULIC ACTUATORS BY HELICOPTER ACCESSORY SERVICE IT WAS NOTICED THAT BOTH CYCLIC AND THE CO	LLECTIVE ACTUATOR EXTENSIONS WERE BENT LATERALLY ON THE LONGITUDINAL AXIS.  NO ACCIDENT OR INCIDENT REPORTED ON THE SUBJ	ECT HELICOPTER.				1	G	7	1 	3U			NC	H2SW    					 
2004012700031	20040127	00031	EU  	2004	1	27	CA031120002      	1	20031118	G	2435	3022376	SEAL            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	STARTER GEN	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UPON RETURNING TO BASE, IT WAS NOTICED THAT OIL WAS COMING OUT OF THE STARTER GEN COOLING VENT. THE STARTER GEN SE	AL (P/N 3022376) WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012700032	20040127	00032	EU  	2004	1	27	CA031120003      	1	20031118	G	2430	9882115103	GCU             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 GENERATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) JUST BEFORE SHUTDOWN, IT WAS NOTED THAT THE GEN 2 CAWS LIGHT WOULD COME ON INDICATING GEN 2 FAILURE. THE GENERATOR	 CONTROL UNIT P/N 988.21.15.103 WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012700033	20040127	00033	EU  	2004	1	27	CA031120004      	1	20031030	G	2742	9787314202	ACTUATOR        			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HORIZONTAL TRIM	INOPERATIVE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) DURING LEVEL FLIGHT, THE CREW ATTEMPTED TO INITIATE A SLOW DESCENT USING HORIZONTAL STAB PITCH TRIM AND NOTICED IT	 WAS INOPERATIVE. THEY TRIED TO USE THE SECONDARY (ALTERNATE) TRIM FUNCTION AND NOTICED IT WAS ALSO INOPERATIVE. THEY PE	RFORMED APPROPRIATE CHECK LIST FUNCTIONS AND FINISHED FLIGHT WITHOUT USE OF PITCH TRIM WITHOUT INCIDENT. WHEN TROUBLESHO	OTING THE SYSTEM WE COULD HEAR THE MOTORS ON BOTH PRIMARY AND ALTERNATE SYSTEMS WHEN ACTIVATED BUT NO MOVEMENT WAS NOTIC	ED. THE REST OF THE SYS WAS OK SO WE CONCLUDED THAT PITCH TRIM ACTUATOR WAS FAULTY AND HAD FAILED INTERNALLY. THE ACTUAT	OR WAS REPLACED AND THE SYSTEM RESUMED BEING AIRWORTHY.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012700034	20040127	00034	WP  	2004	1	27	CA031120005      	1	20031107	G	2730	S4913801CS38808	CONTROL CABLE   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					ELEVATOR	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING 'C' CHECK, MAINTENANCE FOUND THE LT ELEVATOR UP AND DOWN CABLE TWISTED ONE FULL TURN TOGETHER BETWEEN VERTI	CAL STABILIZER CABLE RETAINER (IPC 27-30-00 FIG 4A ITEM C) AND HORIZONTAL STABILIZER PULLEYS (IPC 27-30-00 FIG 5B ITEM M	). CABLE STRANDS FOUND WORN TO APPROXIMATELY 50 PERCENT.  BOTH CABLES REPLACED.  IT WAS FOUND THAT THE VERTICAL STABILIZ	ER ASSEMBLY WAS REMOVED AND REINSTALLED BY THE PREVIOUS OPERATOR.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004012700035	20040127	00035	CE  	2004	1	27	CA031120006      	1	20031120	G	5230		LATCH           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CARGO DOOR	UNSECURE        	W				A				UNSCHED LANDING         				W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) NOTICED BAGGAGE DOOR LITE ON AFTER TAKEOFF,  RETURNED TO BASE FOUND LATCH UNDONE.  LATCH CLOSED.   AIRCRAFT RETURN	ED TO SERVICE.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2004012700036	20040127	00036	EU  	2004	1	27	CA031120007      	1	20031120	G	6220	704A3363320851	SPHERICAL STOP  			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MAIN ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A WORN SPHERICAL STOP WAS CHANGED DUE TO DEBOND.  WITH THE ONE STOP CHANGED AND THE ROTORS TURNING AT FULL RPM ON 	THE GROUND AND HYDRAULIC SYSTEM TURNED 'OFF' THE CYCLIC STICK MOVED VIA ROTOR HEAD FEED BACK. TO DETERMINE THE CAUSE OF 	THE FEED BACK , THE TWO OTHER STOPS WERE CHANGED SO THAT WE WOULD HAVE STOPS WITH THE SAME ELASTOMERIC QUALITIES.  THE P	ROBLEM OF THE FEED BACK WITH HYDRAULICS OFF WENT AWAY.  MFG ALLOWS ONE STOP OF THE SAME PART NUMBER TO BE CHANGED OUT, B	UT IN THIS CASE WE HAD A PROBLEM.		1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004012700037	20040127	00037	NE  	2004	1	27	CA031120008      	1	20031025	G	7921	0401272820	DUCT            			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENG OIL COOLER	SEPARATED       	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING NORMAL DAILY TREND CHECK, PILOT NOTICED GRADUAL INCREASE IN ENG OIL TEMP ON NR 2 AND REPORTED TO THE ENGINE	ER.  INSPECTION CARRIED OUT ON THE NR 2 OIL COOLER DUCT INSTALLATION IN WHICH THE FLEXIBLE DUCT LOCATED BELOW THE BLOWER	 ON THE INSIDE OF THE AIRFRAME WAS FOUND TO HAVE SEPERATED INTERNALLY AND PARTIALLY COLLAPSED. THE DUCT WAS CHANGED OUT 	AND OIL TEMP WENT BACK TO NORMAL. DUCT HAD BEEN INSTALLED ON 11MAY 2003.THIS IS THE SECOND OCCURRENCE OF FAILURE OF THIS	 PART.(REFER ALSO I2002-192)		1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2004012700038	20040127	00038	WP  	2004	1	27	CA031120009      	1	20031113	G	5610	5887275505	WINDSHIELD      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, EXCESSIVE NOISE CAME FROM CENTER WINDSHIELD.  AIRCRAFT LANDED BACK TO DEPARTURE.  THE CENTER WINDSHI	ELD WAS PREVIOUSLY REPLACED. MAINTENANCE FOUND SCREW TORQUE NOT PROPERLY SETTED.  WINDSHIELD RETORQUED AND RESEALED IAW 	AMM AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004010700067	20040107	00067	GL  	2004	1	7	CA031120010      	2	20031104	G	7321	23070609	FUEL CONTROL    			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			51490								(CAN) PILOT RETURNING TO BASE NOTICED RAPID TORQUE GAUGE FLUCTUATION BETWEEN 5 PERCENT TO 10 PERCENT, OCCURRING MOSTLY A	T AROUND 85 PERCENT TORQUE.  LATER PILOT AND AME CONDUCTING TEST FLIGHT TO CONFIRM PROBLEM NOTICED SLIGHT ENGINE SURGING	 NOTICEABLE ONLY BY ENGINE SOUND, NO OTHER GAUGES INDICATED ANY PROBLEM.  AFTER EXTENSIVE TROUBLESHOOTING, IT WAS FOUND 	THAT THE FUEL CONTROL UNIT WAS CAUSING THE TORQUE FLUCTUATION.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004021700196	20040217	00196	EA  	2004	2	17	CA031120011      	2	20031113	G	7230		BLADE           								PWA   	PT6   	PT6*        	52043	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15958								(CAN) DAMAGE TO PT COMPONENTS IS SUBSTANTIAL AND MOST ARE CONSIDERED SCRAP. DAMAGE INCLUDES LG NR OF PT2 BLADES (3115863	-01) FRACTURED AT BLADE ROOT AND AT PT SHAFT HSG ASSY WHICH HAS MNT FLANGE SEPARATED FROM MAIN BODY OF HSG.  ALL COMPONE	NTS EXCEPT GB ARE SCRAP.  AN INTERSTAGE AIR SEAL FAILURE WHERE PART OF ROTATING SEAL FATIGUES AND BREAKS AWAY AND JAMS U	P  PT2 AIRSEAL CAUSING INNER SEAL TO BE TORN FROM PT2 STATOR AND PIECES INGESTED INTO PT1,  PT2 ROTORS CAUSING BLADES TO	 FRACTURE, WITH OUT OF BALANCE CAUSING PT SHAFT HSG TO FRACTURE WITH MASSIVE DAMAGE RESULTING, PT SHAFT HSG FAILURE, CON	SIDERED THAT A PRIMARY FAILURE. FRACTURE AROUND HSG JUST AT FLANGE CORNER RADIUS WAS VERY UNIFORM ALL AROUND.						3	T			E2NE				 
2004012700039	20040127	00039	EA  	2004	1	27	CA031120012      	1	20031119	G	3242	95503774	BRAKE ASSY      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	FROZEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE AIRCRAFT WAS OPERATING OUT OF A REMOTE STRIP.  UPON BACK-TRACK AND TURN-AROUND FOR TAKE-OFF, THE A/C ENCOUNTER	ED DEEP SNOW AT THE END OF THE STRIP.  NORMAL TAKE-OFF PROCEDURES WERE C/O.  UPON LANDING AT YVQ, PILOTS EXPERIENCED ABR	UPT DECELLERATION. THE A/C CAME TO A STOP ON THE RUNWAY SHORTLY AFTER TOUCHDOWN.  MAINTENANCE WAS DISPATCHED TO MEET THE	 A/C ON THE RUNWAY TO LOOK INTO THE PROBLEM. ICE BUILD UP WAS FOUND IN BOTH MAIN GEAR BRAKE ASSY. AFTER MELTING THE ICE 	WITH METHYL HYDRATE, THE A/C WAS ABLE TO TAXI OFF RUNWAY. INSPECTION WAS C/O ON MAIN GEAR AND BRAKE ASSEMBLIES FOR ANY A	BNORMALITIES. NO DEFECTS FOUND. BRAKES WERE CHECKED SERVICEABLE AND A/C RETURNED TO SERVICE.	1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2004012700040	20040127	00040	EU  	2004	1	27	CA031121001      	1	20031118	G	5713		STRINGER        			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33599								(CAN) DURING A ROUTINE SCHEDULED MAINTENANCE, A SMALL CRACK ON STRINGER 8 JUST IB OF WS251.3 RT WING WAS FOUND.  A TEMPO	RARY/PERMANENT REPAIR SCHEME WAS OBTAINED.  A PERMANENT REPAIR WAS CARRIED OUT IAW BARA/748/6591/03-MJC WASH S/N 000397.					2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899	 
2004012700041	20040127	00041	CE  	2004	1	27	CA031121002      	1	20031119	G	7830	20200081	IDLER LINK      	ROHR        		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					THRUST REVERSER	BROKEN          	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		LD	LANDING        	1			CA						466					(CAN) LT ENGINE THRUST REVERSER, LOWER DOOR, INBOARD AFT, IDLER LINK ASSY BROKEN AROUND THE BEARING SUPPORT BOSS. IDLER 	LINK FOUND JAMMED IN THRUST REVERSER STRUCTURE CAUSING THRUST REVERSER TO REMAIN CLOSED AND LOCKED WHEN SELECTED TO DEPL	OY ON LANDING. IT IS LIKELY THIS HAPPENED ON THE PREVIOUS LANDING AND UPON STOWING THE T/R JAMMED IN A CLOSED AND LOCKED	 POSITION.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2004012700042	20040127	00042	SW  	2004	1	27	CA031121003      	1	20031113	G	3250	21525	SPRING          			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235K2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	TAIL STEERING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BROKEN TAILWHEEL SPRING DISCOVERED DURING GROUND HANDLING. HOOK HAD BROKEN OFF ONE END. BREAK APPEARED TO HAVE STA	RTED AT BEND WHERE HOOK IS FORMED FROM SPRING COIL.					1	H	7	1 	3O	3	O	 	A759    	E223	5	N	P9045	 
2004012700043	20040127	00043	SO  	2004	1	27	CA031121004      	1	20031120	G	3232		SHAFT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ACTUATOR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING POST FLIGHT WALK AROUND THE PILOT NOTICED THE IB GEAR DOOR WAS IN THE DOWN POSITION,  AFTER FURTHER INSPECT	ION IT WAS NOTICED THAT THE GEAR DOOR ACUATOR PISTON SHAFT WHERE IT IS THREADED HAD SNAPPED OFF.  THERE WAS NO OTHER DAM	AGE TO THE A/C.  AFTER FURTHER INSPECTION THERE APPEARED TO BE A OLD CRACK APPROX HALFWAY THROUGH THE SHAFT WHICH WOULD 	NOT BE NOTICABLE DURING ROUTINE INSPECTIONS.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004012700044	20040127	00044	NM  	2004	1	27	CA031124001      	1	20030911	G	3320	404830	SOCKET          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	CABIN LIGHT	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) CEILING LIGHT, SHORT CIRCUIT.  UPON ENTERING AIRCRAFT, THE CABIN ATTENDANT SMELLED SMOKE AROUND ROW 20 AND AFT.  P	ILOT CONFIRMED THE SMELL OF SMOKE AND SAW VISIBLE SMOKE FROM AROUND ROW 20 SEAT AC AND TURNED OFF ALL ELECTRICITY AND TH	E SMOKE STOPPED.  MAINTENANCE WAS CALLED FOR ASSISTANCE.  INVESTIGATION/ACTION TROUBLESHOOTING SHOWED AN OVERHEATED LAMP	 HOLDER PN 404830 AT POSITION 20. THE LAMP HOLDER WAS REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004012700045	20040127	00045	WP  	2004	1	27	CA031124002      	1	20031121	G	6710	369A7304	SUPPORT BRACKET 			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COLLECTIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A SCHEDULED 100 HR INSP, A CRACKED WAS FOUND ON THE UPPER BEARING CAP THAT SUPPORTS THE IB END OF THE COLLECTIV	E JACKSHAFT.  AFTER REMOVAL, IT WAS NOTED THAT THE CRACK HAD NOT YET GONE FULLY THRU THE MATERIAL. THE ASSY WAS REPLACED	 WITH A SERVICEABLE UNIT AND AIRCRAFT RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004012700046	20040127	00046	SW  	2004	1	27	CA031124003      	1	20030401	G	3246		SKID            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING FLIGHT OPERATION THE SKID GEAR (SUPPLEMENTAL TYPE CERTIFICATE HIGH SKID WITH FLIGHT STEP CONFIGURATION) WAS	 FOUND WITH 14 INCHES BROKEN.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004012700047	20040127	00047	SW  	2004	1	27	CA031124004      	1	20031121	G	7920		PIN             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCE4N	HCE4N3      	NE  	OIL FILTER	POPPED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE OIL FILTER BYPASS PIN WAS FOUND POPPED ON THE LT ENGINE.  THE OIL FILTER WAS REPLACED.  DAMAGE TO THE REMOVED 	OIL SAMPLE WAS NOTED.  THE MOUNTING FLANGE OF THE FILTER WAS MISSING FROM THE RADIUS INWARD. THE OIL FILTER P/N 3001436-	1 IS INCLUDED IN THE WEAR CHECK. P/N GT331 OIL SAMPLE KITS.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	5	C	P10NE	 
2004012700048	20040127	00048	CE  	2004	1	27	CA031125001      	1	20031117	G	3297		WIRE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					MLG	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA											(CAN) IN APPROACH FLIGHT CREW CANNOT EXTEND THE GEAR NORMALLY. EMERGENCY BLOW DOWN SYSTEM ACTIVATED(EMERGENCY EXTENSION)	.  MAINTENANCE FOUND WIRE TO DIODE CR105(LOCATED ON RT INSTRUMENT PANEL NEAR EMERGENCY BATTERY SWITCH) BROKEN OFF.  WIRE	 RECONNECTED TO DIODE CR105.  GEAR SWING FUNCTIONAL CHECK COMPLETED. AIRCRAFT RETURN TO SERVICE.				2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2004012700049	20040127	00049		2004	1	27	CA031125002      	4	20030911	G	3420	42000332501	COMPUTER        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	AHRS	MALFUNCTIONED   	W				O				OTHER                   				P			NO WARNING INDICATION     			CL	CLIMB          	1			CA											(CAN) AHRS NR 1 AND AP FAILURE: DURING CLIMB TROUGH FL 190 (FOR FL 230), SPEED 221, CLEAN CONFIG AND PITCH 5 DEGREE NOSE	 UP.  ELEVATOR FEEL CAUTION LIGHT CAME ON AND PFD/MFD ON LT SIDE LOST ALL INDICATIONS.  WE LEVELED OFF AT FL 200 AND SPE	ED CAME BACK TO MAX 200, CHANGE AP OVER TO RT PILOT AND CONDUCTED MANUAL FLYING FOR THE REST OF THE FLIGHT.  ADC NR 1 WA	S CHANGED FROM NORMAL TO NR 2. RETURNED TO BASE (REST OF THE FLIGHT UNEVENTFUL).  INVESTIGATION/ACTION: AFTER ARRIVAL TO	 BASE, THE AHRS WAS REPLACED. THE FAULT WAS LATER CONFIRMED AT SHOP.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005042700313	20050427	00313	EU  	2005	4	27	CA031125003      	1	20031124	G	5320	25W26110200	BRACKET         			ISRAEL	1125  	ASTRASPX    	4500205	EU  	GARRTT	TFE731	TFE73140    	29001	NE  					LT WHEEL WELL	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PROBLEM WAS FOUND ON LT SIDE GEAR DOOR STOP.  BRACKET WAS INSTALLED BY AIRCRAFT MFG IN THE WRONG POSITION AND WRON	G PN IAW MFG IPC BRACKET WAS CHANGED AND DOOR RIGGED IAW MM AND WORKED OK.					2	L	7	2 	4F	4	F	RT	A16NM   	E1NM				 
2004012700050	20040127	00050	WP  	2004	1	27	CA031125004      	2	20031124	G	7200		ENGINE          			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					RIGHT	MALFUNCTIONED   	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) A/C CLIMBING THROUGH 10K, RT ENGINE SPOOLED DOWN.  STILL TROUBLESHOOTING.						2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2004012700051	20040127	00051	EU  	2004	1	27	CA031126001      	1	20031114	G	2820	3510541	LINE            			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) REFERENCE AIRCRAFT SB 351 054 AIRFRAME FUEL FILTER SUBSTITUTION.  FUEL LINE PN 351-054-1 LEAKS THROUGH THE STAINLE	SS STEEL BRAIDED CASING OF THE LINE. MAINTENANCE SUSPECTS THE LINE HAS DETERIORATED WITH AGE. THE LINE WAS MANUFACTURED 	IN 1994 AND HAS ACCUMULATED NINE YEARS IN SERVICE.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2004012700052	20040127	00052	NE  	2004	1	27	CA031126002      	2	20031101	G	7250		TURBINE WHEEL   			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					NR 2 ENGINE	OVERHEATED      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA								13247			(CAN) AIRCRAFT 478  NR 2 ENGINE, FLIGHT 376 LIH-HNL. DURING CLIMB AT 10,000 FT, NR 2 ENGINE EXPERIENCED A LOUD BOOM AND 	OVERHEATED TO 1093 DEGREES.  ENGINE WAS SHUTDOWN. AIRCRAFT MADE NORMAL SINGLE ENGINE LANDING.  MCD WAS CHECKED AND FOUND	 CLEAN.  FAN ROTOR WAS SPUN AND BUMPS IN THE ROTATION COULD BE FELT. INSPECTION OF THE TAILPIPE REVEALED METAL PARTICLES	.  ENGINE JUST ARRIVED NOV 25 ATRRC FOR INVESTIGATION OF FAILURE.			2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2004012700053	20040127	00053	SW  	2004	1	27	CA031126003      	1	20031126	G	6310	406040509101	CAP             			BELL  	407   	407         	1182206	SW  										FREEWHEEL ASSY	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FREEWHEEL ASSEMBLIES WERE DISOVERED TO HAVE A MISSING MACHINING FEATURE ON THEIR CAPS 509-101, .188.						1	G	7	1 	3U			O	H2SW    					 
2004012700054	20040127	00054	CE  	2004	1	27	CA031126004      	1	20031122	G	3213	11581000654	STRUT           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A PILOT REPORTING THE RT MAIN GEAR OLEO WAS LOW, MAINTENANCE ATTEMPTED TO INFLATE THE OLEO WITH NITROGEN. TH	E NITROGEN IMMEDIATELY STARTED TO LEAK FROM A LARGE CRACK AROUND THE UPPER TORQUE KNEEBOSS ON THE BRACE ASSEMBLY. THE CR	ACK WAS APPROXIMATELY 6 INCHES IN LENGTH STARTING AT THE BOTTOM OF THE BRACE ASSEMBLY, GOING UP THE RADIUS ON THE LT SID	E OF THE BOSS AND TURNING AND CROSSING OVER THE TOP OF THE BOSS. THIS GEAR HAD 277 CYCLES SINCE INSPECTION.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	3PNE	 
2004012700055	20040127	00055	SW  	2004	1	27	CA031126005      	1	20031126	G	6310	406040509101	CAP             			BELL  	206   	206L4       	1182110	SW  										FREEWHEEL ASSY	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FREEWHEEL ASSEMBLIES WERE DISCOVERED TO HAVE A MISSING MACHINING FEATURE ON THEIR CAPS 509-101, .188						1	G	7	1 	3U			NC	H2SW    					 
2004012700056	20040127	00056	CE  	2004	1	27	CA031126006      	1	20031029	G	5343	07900066	ATTACH FITTING  			CESSNA	180   	180G        	2072616	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT P/N 0790006-6 WAS BROKEN DUE TO INTERGRANULAR CORROSION.  FLO	OR AND ADJACENT STRUCTURES DRILLED APART TO FACILITATE CHANGING THE BRACKET.  REASSEMBLED USING EXISTING RIVET SIZE AND 	PATTERN AS ORIGINAL.				1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2004012700057	20040127	00057	SW  	2004	1	27	CA031126007      	1	20031124	G	5302	206031329001	ATTACH FITTING  			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15731								(CAN) CRACK LOCATED AT UPPER LT TAILBOOM ATTACHMENT FITTING (AIRFRAME SIDE), P/N 206031329001. CRACK EXTENDS BETWEEN FIR	ST SET OF RIVETS FORWARD OF ATTACHMENT BOLT HOLE, AS WELL AS ABOVE UPPER RIVET TO THE TOP EDGE OF THE FITTING.  CRACK FO	UND DURING A 100/300 HR INSPECTION. SUBJECT PART TO BE REPLACED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004012700058	20040127	00058	CE  	2004	1	27	CA031126008      	1	20031125	G	3213	11581000654	STRUT           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER FINDING THE RT MAIN GEAR BRACE CRACKED WE INSPECTED THE LT GEAR AND FOUND A SMALL CRACK AT THE UPPER END OF 	THE RADIUS OF THE UPPER TORQUE KNEEBOSS. LIQUID PENETRANT WAS REQUIRED TO CONFIRM THE CRACK. IT STARTED AT THE TOP OF RA	DIUS AND TRAVELED DOWNWARDS ABOUT 1.5 INCHES.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	3PNE	 
2004012700059	20040127	00059	WP  	2004	1	27	CA031126009      	1	20031124	G	6410	369A10045	PIN             			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20R2    	 	GL  					M/R BLADE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BLADE PIN FOUND TO BE BROKEN WHERE THREAD MEETS THE PIN.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004012700060	20040127	00060	CE  	2004	1	27	CA031126010      	1	20031107	G	2131		CONTROLLER      			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					CABIN PRESSURE	MALFUNCTIONED   	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE AT AN ALTITUDE IN EXCESS OF FL 40 AFTER ALTITUDE CHANGES DOWN AND UP IN EXCESS OF 1000 FEET THE PRESSURI	ZATION CONTROLLER FAILED TO  MAINTAIN CABIN PRESSURIZATION.  AN EMERGENCY DESCENT WAS INITIATED AND PASSENGER OXYGEN MAS	KS DEPLOYED. THE PRESSURIZATION CONTROL WAS ABLE TO BE RESET PRIOR TO LANDING. INVESTIGATION FOUND THAT THIS WAS A KNOWN	 PROBLEM WITH THIS AIRCRAFT AND WAS ADDRESSED BY AD WIRE 21-004. MFG HAS JUST LATELY RELEASED S/B 45-21-13 WHICH HAS BEE	N INSTALLED IN THIS AIRCRAFT AND CONFIRMED TO HAVE CORRECTED THIS PROBLEM.		2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2004012700061	20040127	00061	NM  	2004	1	27	CA031126011      	1	20031120	G	5753		SKIN            			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48876								(CAN) WHILE PERFORMING A (C CHECK), CORROSION WAS FOUND ON THE LT IB FLAP AT WBL 124.  AFTER PAINT REMOVING IT WAS DISCO	VERED THAT A CRACK OF .5000 INCH LONG WAS BENEATH THE PAINT. CRACK REPAIR IAW SRM.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2004012700062	20040127	00062	NM  	2004	1	27	CA031126012      	1	20031112	G	5330		SKIN            			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	LIGHTNING STRIKE	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48876								(CAN) WHILE PERFORMING A (C CHECK) IT WAS FOUND THAT THE AIRPLANE HAD BEEN HIT BY LIGHTING. POINT OF ENTRY WAS AT NOSE D	OOR AND EXIT POINT AT RT ELEVATOR TAB.  REPAIR HAD TO BE CARRIED OUT BETWEEN BS 196 TO 203, BS 219 TO 235 , FORWARD OF N	OSE LDG FS 188, NOSE DOOR AND RT ELEVATOR TAB.  NO DAMAGE TO RADIO. CARRY OUT MFG LIGHTING STRIKE PROCEDURE IAW MM.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2004012700063	20040127	00063	CE  	2004	1	27	CA031127001      	1	20031125	G	3210	508103327	BRACE           	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER FINDING TWO OTHER GEAR BRACES CRACKED (SDR 20031126008, 20031126004) WE INSPECTED THE LT GEAR AND FOUND A PO	SSIBLE CRACK AT THE UPPER END OF THE RADIUS OF THE UPPER TORQUE KNEEBOSS. LIQUID PENETRANT WAS REQUIRED TO CONFIRM THE C	RACK. IT STARTED AT THE TOP OF RADIUS AND TRAVELED DOWNWARD TO THE END OF THE GEAR BRACE. THE GEAR WAS REPLACED AND THE 	AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	3PNE	 
2004012700064	20040127	00064	CE  	2004	1	27	CA031127002      	1	20031127	G	3242	9550634	KEY             	GOODYEAR    		LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					TORQUE TUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						JAN8175					(CAN) DURING A BRAKE ASSY OVERHAUL IAW MM,  FOUND TORQUE TUBE KEY CRACKED. WE EXPERIENCE THIS TWICE SINCE LAST MONTH. TH	E TORQUE TUBE HOLD THE STATIONARY DISK IN PLACE. TORQUE TUBE REPLACED.					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2004012700065	20040127	00065	CE  	2004	1	27	CA031127003      	1	20031125	G	5711	0001102501	ATTACH FITTING  	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	MCAULY	4HFR34	4HFR34C652  	NE  	WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19436								(CAN) DURING AN UNSCHEDULED INSPECTION A SMALL CRACK WAS FOUND IN THE UPPER FORWARD WING ATTACH FITTING, THE CRACK WAS A	PPROXIMATELY .0625 OF AN INCH LONG STARTING AT THE TOOLING HOLE HEADING TOWARD THE TUB.  THE AIRCRAFT IS GROUNDED WAITIN	G FOR WING SPAR REPLACEMENT.  THE CRACK IS VERY HARD TO SEE, IF YOU LOOK AT THE 3RD PICTURE, TAKEN THOUGHT A MAGNIFYING 	GLASS YOU WILL SEE A FINE BLACK LINE LEAVING THE HOLE AT 7 O CLOCK THIS IS THE CRACK.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	3PNE	 
2004012700066	20040127	00066	NE  	2004	1	27	CA031127004      	2	20031117	G	7421	9550175400	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								4251			(CAN) DURING 100 HOUR INSPECTION IT WAS FOUND THAT THE CERAMIC INSIDE THE IGNITORS X 2 WERE LOOSE AND RATTLING AROUND IN	SIDE THE IGNITERS. IGNITERS WERE MANUFACTURED BY CHAMPION PN CH34745.  IGNITERS REPLACED. UNSERVICEABLE IGNITERS SENT TO	 MFG FOR REPLACEMENT.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2004012700067	20040127	00067	CE  	2004	1	27	CA031127005      	1	20031118	G	5320	07136713	ANGLE           			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	CABIN FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABIN FLOOR ON RT SIDE.  DISCOVERED FLOOR HAD MOVED DOWN.  ON INVESTIGATION FOUND THE LT AND RT TUNNEL ANGLES BROK	EN AND CRACKED. REMOVED BOTH ANGLES PN 07136713 AND -4, PARTS WERE NOT MADE BY MFG.   NO RECORD OF A REPAIR FOUND IN TEC	HNICAL LOGS.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2004012700068	20040127	00068	EU  	2004	1	27	CA031127006      	2	20031120	G	7532	EU13933	PLATE           								RROYCE	TAY   	TAY6118     	 	EU  					BLEED VALVE	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A REQUEST CAME FROM MFG TO VERIFY A POSSIBLE MANUFACTURING PROBLEM ON PLATE EU13933.  MFG FOUND THEIR STOCK OF EU1	3933 WRONGLY MANUFACTURED. RADIUS OF PLATE WAS MACHINED ON WRONG SIDE OF PLATE BY MANUFACTURER IN SPAIN.  HAVING NO RADI	US IN CORRECT AREA COULD CAUSE A POTENTIAL STRESS TO THE TAY HP COMPRESSOR BLEED VALVE STRAP WHICH COULD CAUSE A POTENTI	AL FAILURE OF BLEED VALVE. DEFECTIVE PLATES HAVE BEEN REMOVED FROM USAGE AN PLACED IN QUARANTINE AND PROBLEM REPORTED TO	 MFG IAW THEIR REQUEST. MFG ARE PRESENTLY INVESTIGATING PROBLEM AND POTENTIAL SAFETY HAZARD. MEANWHILE MFG INSTALLING US	ED SERVICEABLE PLATE UNDER TECHNICAL VARIANCES FROM MFG. CONTAINMENT ACTIONS ARE PRESENTLY UNDERGOING BY MFGS.						4	F			E25NE				 
2004012700069	20040127	00069	EA  	2004	1	27	CA031127007      	1	20031125	G	2823	TC173007	SELECTOR        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	FUEL SYSTEM	CORRODED        	W				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) THE PILOT REPORTED THAT THE FUEL SELECTOR WAS HARD TO MOVE. ON INSPECTION THE STEEL DETENT PLATE LOCATED ON THE SE	LECTOR, BEHIND THE CABLE DRUM WAS FOUND TO BE CORRODED. THE VALVE WAS REMOVED FOR OVERHAUL.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P28EA	 
2004012700070	20040127	00070	EA  	2004	1	27	CA031127009      	1	20031125	G	2820	C2P1107	LINE            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	FUEL SELECTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A FUEL SELECTOR CHANGE INTERGRANULAR CORROSION WAS NOTED ON THE FUEL LINE ELBOW.  CORRODED PART REPLACED WI	TH NEW UNIT.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P28EA	 
2004012700071	20040127	00071	EU  	2004	1	27	CA031127010      	1	20031118	G	2910	704A336900004	DRIVE BELT      			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYS SYSTEM	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON RECEIPT OF INFORMATION REGARDING BELT CONDITION,  BELT WAS REMOVED FROM THE AIRCRAFT AND INSPECTED.  DELAMINA	TION OF TOP FABRIC 100 PERCENT OF WIDTH TO A DEPTH OF 2-3 MILLIMETERS.  EDGES SHOWED CRACKS IN RUBBER, VISIBLE WITH 10X 	GLASS. LIFE OF PART 600 HOURS.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2004012700072	20040127	00072	CE  	2004	1	27	CA031127011      	1	20031125	G	5312	08130225	BULKHEAD        			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470VO     	17026	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE 100 HOUR INSPECTION PLAY WAS NOTICED IN THE NOSE GEAR AREA.  UPON INSPECTION THE LT NOSE SECTION BULKHE	AD WAS FOUND TO BE CRACKED VERTICALLY THROUGH THE CENTER OF THE LIGHTENING HOLE.  DOUBLER PATCHES WERE INSTALLED AND RIV	ETED INTO PLACE AND THE NOSE GEAR WAS AGAIN INSPECTED FOR PLAY.				1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P36EA	 
2005042700314	20050427	00314	EA  	2005	4	27	CA031127012      	1	20031119	G	2750	5912577	TORQUE SHAFT    			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					TE FLAPS	DISCONNECTED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) THIS AIRCRAFT WAS ON ITS FIRST FLIGHT AFTER A C-CHECK HAD BEEN CARRIED OUT. THE FLAP SYSTEM HAD EXPERIENCED SEVERA	L PROBLEMS AFTER THE CHECK AND PRIOR TO THIS FLIGHT. TORQUE SHAFTS AND BPSUS HAD BEEN REPLACED DURING THE C-CHECK AND TH	ERE HAD BEEN MECHANICAL MIS-RIG PROBLEMS WHEN RETURNING TO SERVICEABILITY. SUBSEQUENT TO THE FAILURE INBOUND AIRPORT, IT	 WAS DISCOVERED THAT THE LT WING TORQUE SHAFT HAD BECOME DISCONNECTED FROM THE ADJACENT SPLINE DRIVE.  WHEN THE SHAFT HA	D BEEN INSTALLED, THE BOLT HAD NOT BEEN SECURED THROUGH THE SPLINE DRIVE.  THE SHAFT WAS SECURED PROPERLY, SYSTEM CHECKE	D AND THE AIRCRAFT RETURNED TO SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012700073	20040127	00073	EA  	2004	1	27	CA031127013      	1	20031126	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) CAPT'S SIDE WINDOW SHATTERED AT FL240.  AIRCRAFT FERRIED.  WINDOW REPLACED, AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012700074	20040127	00074	NE  	2004	1	27	CA031127014      	2	20031101	G	7200		ENGINE          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					RIGHT	LIGHTNING STRIKE	W				O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING DESCENT, AROUND 7000 FT, AIRCRAFT HIT BY LIGHTNING STRIKE ON THE RT SIDE OF THE COCKPIT.  AT THE SAME TIME,	 MESSAGER ENG FLAMEOUT (C) POSTED ON EICAS.  THE RT ENGINE PARAMETERS ROLLED BACK, AFTER A FEW SECONDS THE PARAMETERS CA	ME BACK TO NORMAL AND THE ENGINE OPERATED NORMALLY.  AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  ON THE GROUND, THE INSPE	CTION REVEALED THAT THE ENTRY POINT OF THE LIGHTNING STRIKE WAS ON THE RIGHT FORWARD NLG DOOR.  THE EXIT POINT WAS ON TH	E HORIZONTAL STAB TRAILING EDGE.  NO DEFECTS WERE FOUND ON THE ENGINE.  THE QAR DISK WAS REMOVED FOR ANALYSIS WHICH CONF	IRMED THE ENGINE FLAMEOUT WITH N2 PARAMETER GOING BELOW IDLE FOR A FEW SECONDS.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012700075	20040127	00075	EA  	2004	1	27	CA031127015      	1	20031124	G	3234	555405	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH WHEN SELECTING GEAR DOWN RECEIVED NOSE DOOR AURAL AND GEAR DOWN DISAGREE.  MISSED APPROACH AND RAN CHE	CKLIST.  SELECTED GEAR UP TO MODERATE FLIGHT CONDITIONS.  NEXT APPROACH SAME THING HAPPENED.  THIS TIME USED MANUAL GEAR	 RELEASE.  GEAR INDICATED DOWN AND LOCKED.  NLG SELECTOR VALVE FOUND LEAKING AND ELECTRICAL CONNECTOR COMPLETED SATURATE	D INTERNALLY WITH HYD FLUID. REPLACED NLG SELECTOR VALVE AND OPS OK.  AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012700076	20040127	00076	EU  	2004	1	27	CA031128001      	1	20031118	G	7120	601741	BEARING         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ISOLATION MOUNT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PERIODIC 100-HOUR INSPECTION A VIBRATION ISOLATOR BEARING WAS FOUND ROUGH.  UPON DISASSEMBLY, DAMAGE WAS FO	UND ON THE INNER AND OUTER RACES OF THE BEARING DUE TO LACK OF LUBRICATION.  METAL PARTICLE PASTE WAS EVIDENT IN THE BEA	RING AREA.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2004021700197	20040217	00197	EA  	2004	2	17	CA031128002      	2	20031117	G	7261		CHIP DETECTOR   								PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ENG WAS REMOVED AFTER COMPRESSOR SEIZURE AND OIL LOSS DUE TO A BROKEN CHIP DETECTOR.  CONFIRMED COMPRESSOR SEIZED.	 FOUND THAT NR 1 BRG HAD COLLAPSED DUE TO OIL STARVATION.  NR 1 BRG FAILURE RESULTED IN HIGH LEVEL OF HEAT GENERATION, L	OSS OF COMPRESSOR LOCATION, AS RESULT OF BRG DETERIORATION, CAUSING EXTENSIVE ROTATING TO STATIC PARTS RUBBING.  COMPRES	SOR DAMAGE WILL REQUIRE REPLACEMENT OF DAMAGED PARTS. MELTING METAL FROM COMPRESSOR SPACERS, FLOWING MELTED METAL PARTIC	LES THRU DIFFUSER TUBES DEPOSITING ON INSIDE OF GG CASE AND FACE OF EXHAUST DUCT.  NR 1 BRG DETERIORATION ALSO CAUSED CT	 AXIAL MOVEMENT RESULT IN BLADE PLATFORMS RUBBING CT VANE. SPALLING DAMAGE CAN BE RESULT OF INADEQUATE LUBRICATION.						4	T			E4EA				 
2004012700077	20040127	00077	SW  	2004	1	27	CA031128003      	1	20031127	G	3397	186187192	WIRE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	STROBE LIGHTS	MISROUTED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING COMPANY STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), FABRIC WAS REMOVED FROM THE WINGS.  ON INSPECTION 	OF THE WIRES, IT WAS DISCOVERED THAT THE POWER WIRES FOR THE NAV AND STROBE LIGHTS WERE INCORRECTLY ROUTED ALLOWING THE 	WIRES TO RUB ON A RIB.  FURTHER INSPECTION FOUND THAT THESE WIRES WERE NOT SUPPORTED OVER A COMPRESSION STRUT ALLOWING T	HE WIRE TO RUB IN THIS AREA.  ON INSPECTION OF THE WIRE ROUTING DOWN THE LEADING EDGE NOW INCLUDING THE STALL WARNING WI	RES, 2 GROMMETS ON THE NOSE RIBS WERE FOUND DETERIORATED AND SPLIT ALLOWING WIRES TO RUB ON THE NOSE RIBS.  2 OTHER GROM	METS WERE FOUND PARTIALLY SPLIT AND DETERIORATING.	1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012700078	20040127	00078	SW  	2004	1	27	CA031128005      	1	20031128	G	5753	21583	MOUNT           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON THE COMPANY STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), FLAP MOUNT (LEFT WING ROOT POSITION) WAS INSPECTED	 AND CRACKS WERE FOUND ON THE MOUNTING FACE BOTTOM BOLT HOLE.					1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012700079	20040127	00079	SW  	2004	1	27	CA031128006      	1	20031128	G	2120	212073111001	PLENUM          			BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					CABIN AIR	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WATER ENTERED IN PLENUM CHAMBER OF CABIN AIR INTAKE OVERFLOWED ONTO CEILING INSULATION CAUSING ELECTRICAL ARCING.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2004012700080	20040127	00080	NM  	2004	1	27	CA031128007      	1	20031127	G	3211	104451	SPRING          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION, FOUND RT SPRING ASSY ON THE LT GEAR WHICH THE PROX. SWITCH IS CONNECTED TO, BROKEN.  THE BRAKE WA	S NOT ON A LUG, IT WAS RIGHT IN THE COILS. THIS SPRING WAS INSTALLED ON A PRE MOD STAB STAY ASSY. PRE S/B 8-32-148, OR D	HC8-32-86.THIS CAUSED THE PROX SENSOR TO SEE A NEAR/FAR CONDITION INTERMITTENTLY.  THIS CAUSED THE GEAR LIGHT TO CYCLE B	ETWEEN GREEN AND RED.  RECTIFICATION: MLG SIDE STAY REMOVED AND SPRING ASSY REPLACED.  OPERATION CHECKED SERVICEABLE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012700081	20040127	00081	EA  	2004	1	27	CA031201001      	1	20031115	G	2420		RELAY           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					GENERATOR	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) FLAPS FAIL, CAUTION MESSAGE POSTED AND SLATS FAIL, CAUTION MSG POSTED ON ADG (AIR DRIVEN GENERATOR) POWER, UNABLE 	TO MOVE FLAPS.  AFTER POWER WAS RESTORED, SLATS HALFSPEED AND FLAPS HALFSPEED STATUS MSG WERE POSTED AND DISAPPEARED AFT	ER LANDING.  RELAY HAS BEEN CYCLED AND RETESTED IAW OUR FLIGHT TEST PROCEDURE NR S670-242301 PARA. 8.1.6 AND 8.1.7. SLAT	S AND FLAPS FOUND SERVICEABLE IAW FTP S670-275001. SUBSEQUENT FLIGHT TESTING BEING SUCCESSFUL.  CURRENTLY, ENGINEERING I	S UNDER INVESTIGATION FOR A SIMILAR ISSUE WITH ANOTHER AC 10118 WHERE NO ACCESS BUS POWER WAS AVAILABLE ON ADG POWER DUR	ING A FLIGHT TEST AND AFTER POWER RESTORATION, EVERYTHING CAME BACK NORMAL. THE SECOND ATTEMPT ON ADG WAS SUCCESSFUL.	2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012700082	20040127	00082	SW  	2004	1	27	CA031201002      	1	20031201	G	3397	33	WIRE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	NAV LIGHTS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NAV WIRE IN LT WING FOUND ATTACHED WITH MASKING TAPE TO COMPRESSION TUBE.  WIRE WAS CHAFING ON TUBE AND EXPOSED WI	RE CAUSING SHORT AGAINST COMPRESSION TUBE, BLOWING FUSE.					1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012700083	20040127	00083	SW  	2004	1	27	CA031201003      	1	20031201	G	3397	33	WIRE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  	MCAULY	1A200	1A200*      	GL  	NAV LIGHTS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NAV WIRE IN LT WING FOUND ATTACHED WITH MASKING TAPE TO COMPRESSION TUBE. WIRE WAS CHAFING ON TUBE AND EXPOSED WIR	E CAUSING SHORT AGAINST COMPRESSION TUBE, BLOWING FUSE.					1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012700084	20040127	00084	SW  	2004	1	27	CA031201004      	1	20031201	G	3397	3359	WIRE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	NAV LIGHTS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NAV WIRE IN LT WING FOUND ATTACHED WITH MASKING TAPE TO 2ND AND 3RD COMPRESSION TUBES FROM OB, AND RT WING FOUND A	TTACHED WITH MASKING TAPE TO 3RD (FROM OB) COMPRESSION TUBE.  WIRES CHAFFING ON TUBE AND EXPOSED WIRE CAUSING SHORT AGAI	NST COMPRESSION TUBE, BLOWING FUSE.				1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012700085	20040127	00085	SO  	2004	1	27	CA031201005      	1	20031127	G	8120		BEARING         	GARRETTLTD  	LW1268985   	PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	TURBOCHARGER	FAILED          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA						ZIO14456					(CAN) AFTER TAKEOFF ENGINE MANIFOLD PRESS DROPPED TO 23 INCHES, THE PILOT TURNED AND LANDED BACK AT AIRPORT. MANTENANCE 	FOUND THE TURBO BEARINGS FAILED. ENGINE WAS FLUSHED AND NEW FILTER AND OIL INSTALLED WITH THE TURBO BEING REPLACED. A/C 	WAS GROUND RUN AND TEST FLOWN FILTER WAS CHECKED FOR METAL AND INSIGNIFICANT AMOUNTS WERE FOUND. ANOTHER FILTER WAS INST	ALLED AND A/C RETURNED TO SERVICE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004012700086	20040127	00086	WP  	2004	1	27	CA031201006      	1	20031123	G	2150	39613011	CONTROL VALVE   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					LT PACK FLOW	INOPERATIVE     	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FLOW LITE ILLUMINATED ON CLIMB, CABIN CONTINUED TO DEPRESSOR AND AFT GALLEY DOOR LIGHT ILLUMINATED PRIOR TO DESCEN	T.  AIRCRAFT LANDED BACK TO YYZ.  MAINTENANCE FOUND LT PACK FLOW CONTROL VALVE INOPERATIVE.  FLOW CONTROL VALVE REPLACED	 AND SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004012700087	20040127	00087	SO  	2004	1	27	CA031201007      	1	20031127	G	3260	6720300	SPRING          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	MLG DOWNLOCK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A WALK AROUND BEFORE FLIGHT, AN INSTRUCTOR AND STUDENT PILOT NOTICED THAT THE RT MAIN LANDING GEAR DOWNLOCK	 SPRING WAS BROKEN.  THIS SPRING IS TO KEEP THE DOWNLOCK MECHANISM IN PLACE.  UPON FURTHER INVESTIGATION BY MAINTENANCE 	THE STUDENT WHO FLEW THE AIRCRAFT LAST NOTED THAT THE LANDING GEAR HYDRAULIC PUMP WOULD COME ON AND OFF WHILE TAXIING TH	E AIRCRAFT, INDICATING THAT THE BRACKET WAS LIFTING OFF OF THE DOWNLOCK SWITCH ENOUGH TO TURN THE PUMP ON.  IF THE AIRCR	AFT WAS MOVED BY TOW BAR WITH THE POWER OFF THE PUMP WOULD NOT KICK ON TO KEEP THE GEAR DOWN AND LOCKED AND THERE WOULD 	BE A POSSIBILITY OF THE MAIN GEAR COLLAPSING.	1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920	 
2004012700088	20040127	00088	SO  	2004	1	27	CA031201008      	1	20031127	G	3211	6720300	SPRING          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	MLG DOWNLOCK	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON DISCOVERY OF A BROKEN DOWNLOCK SPRING THE LT DOWNLOCK SPRING WAS INSPECTED AND IT WAS FOUND TO BE WORN ON THE	 LOWER END ON THE CURVED PART OF THE SPRING WHERE IT HOOKS ONTO THE TRUNION.  THIS SPRING KEEPS THE DOWNLOCK HOOKS IN PL	ACE.  IF IT BREAKS THE ONLY THING KEEPING THE MAIN GEAR LOCKED IS THE HYDRAULIC PUMP.  IF POWER TO THE AIRCRAFT IS REMOV	ED ANY GROUND HANDLING OF THE AIRCRAFT COULD  POSSIBLY CAUSE THE GEAR TO COLLAPSE.			1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920	 
2004012700089	20040127	00089	EU  	2004	1	27	CA031201009      	1	20031126	G	2750	Z4243300014	SPRING          			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					LT TE FLAP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION THE LT FLAP CONTROL LEVER UPLOCK SPRING WAS FOUND TO BE BROKEN.  THIS SPRING KEEPS PRE	SSURE ON THE UPLOCK HOOK THAT HOLDS THE FLAP I N THE UP POSITION.  THERE ARE ALSO SPRINGS THAT ASSIST IN KEEPING THE FLA	P IN THE UP POSITION, BUT THEY DO NOT LOCK IT, ONLY THE HOOK LOCKS THE FLAP.  WITH THIS SPRING BEING BROKEN THERE IS NO 	POSITIVE PRESSURE ON THE HOOK.  IF THE PILOT DOES HIS WALK AROUND WITH THE FLAPS EXTENDED THIS DEFECT WOULD GO UNNOTICED	.		1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2004012700090	20040127	00090	WP  	2004	1	27	CA031202001      	1	20031125	G	7120	6252220928	WASHER          			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					ENGINE MOUNT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE INSTALLATION, COULD NOT TORQUE ENGINE MOUNT YOKE BOLT P/N 3935739-1 IAW MM SECTION 20-10-14 PAGE 201	. UNABLE TO COMPRESS, THE INNER PLI WASHER RING OF PLI WASHER SET P/N PL120-117-8. THESE PLI WASHERS WERE PROVIDED FROM 	FOLLOWING SUPPLIERS:  THE ALTERNATE PLY WASHER P/N 62522-20-92-8 SHOWN IN THE IPC 71-20-00 PURCHASED FROM MFG WAS USED A	ND INSTALLED IAW AMM 20-10-14 PAGE 201.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004021700198	20040217	00198	NE  	2004	2	17	CA031202002      	3	20031129	G	6111	802253180225	COLLAR          	HAMSTD      		DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	PROP BLADE	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			10648								(CAN) DURING TAKEOFF ROLL NR1 PROP, NR 4 BLADE COLLAR P/N 802253-1, -2 SEPARATED FROM PROP BLADE AND STRUCK NR2 BLADE CA	USING IMPACT DAMAGE TO ITS LE NICKEL SHEATH.  DEBRIS IMPACTED ONTO LT ROW 5 CABIN WINDOW CAUSING A HOLE IN OUTER PANE AN	D DAMAGE TO WINDOW FRAME.  INNER PANE OF WINDOW WAS NOT IMPACTED AND REMAINED INTACT. AC PERFORMED AN UNSCHEDULED LANDIN	G.  SMALL SECTION OF COLLAR WAS ABLE TO BE RECOVERED FROM RUNWAY. FAILURE MAY BE DUE TO COLLAR CRACKING AND/OR FAILURE O	F ADHESIVE USED TO SECURE COLLAR TO PROPELLER BLADE.  MFG HAS BEEN INVOLVED WITH THE INVESTIGATION AND FOLLOWING WAS OBT	AINED FROM LOCAL HS FIELD SUPPORT REPRESENTATIVE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012700091	20040127	00091		2004	1	27	CA031202003      	4	20031129	G	2562	4530150	TRANSPONDER     			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ELT	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CA)  WAS NOTIFIED THAT SEARCH AND RESCUE WAS RECEIVING AN ELT RESPONSE FROM A COMPANY AIRCRAFT.  INSPECTED AND IT WAS D	ETERMINED THIS AIRCRAFT WAS AT FAULT.  THE UNIT WAS DISCONNECTED AND A FURTHER INSPECTION FOUND WATER LOCATED AROUND THE	 RECEPTACLE AND CONNECTOR.  THE ELT WAS CONFIRMED. NO FURTHER ACTION WAS TAKEN BY RESPONDING AUTHORITIES.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2004012700092	20040127	00092		2004	1	27	CA031202004      	4	20031201	G	3414		GYRO            			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					ADG SYSTEM	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) NAV NR 1 LOST ALL DATA FOLLOWING ADG DROP ON PILOT PFD. WHEN ADG AUTO DEPLOYED, PILOT PFD BLANKED COMPLETELY FOR A	 MOMENT, THEN SPEED TAPE CAME BACK, NUMEROUS REDFLAGS ANNUNCIATED UNTIL POWER WAS TRANSFERRED AND IRS NR 1 RE-ALIGNED IN	 ATT. MODE . ALSO STAB FAULT- STATUS MESSAGE POSTED AFTER ADG DROP AND UNABLE TO RESET.  THE SYSTEM HAS BEEN VERIFIED AN	D RETESTED ON GROUND WITHOUT ANY DEFECT DISCOVERED.  ANOTHER TEST FLIGHT WITH ADG DROP WAS ATTEMPTED WITHOUT ANY OCCURRE	NCE. MFG ENGINEERING IS INVESTIGATING THE SOURCE OF PROBLEM.		2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004021700199	20040217	00199	EU  	2004	2	17	CA031202005      	1	20031201	G	2597		WIRE            			AIRBUS	A321  	A321211     	3930370	EU  	IAE   	V2530 	V2530A5     	 	NE  					BUFFET/GALLEYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WIRE DAMAGE IN COMPARTMENT 2411, DAMAGED OVEN WIRES IN GALLEY 5,  COMPARTMENT 2408.  WIRES FOR ALL OVENS IN GALLEY	 5 ARE COLLECTED TOGETHER AND ROUTED THROUGH THIS COMPARTMENT 2408.  O/NIGHT CREWS PERFORM AN OVEN FIT CHECK IN COMPARTM	ENT 2411 WITH SIMULATED 0.5 INCH THICK X 3 INCH LONG X 1 INCH WIDE RUBSTRIP MOUNTED TO SIDE WALL OF THIS COMPT JUST IN F	RONT OF WIRE BUNDLE IN THIS COMPT.  BECAUSE IN LATEST PROPOSED REVISION OF MFG SB THEY ARE PROPOSING TO INSTALL RUB STRI	PS IN BOTH COMPARTMENTS 2408 AND 2411. ONLY VALIDATED THE RUBSTIP FIT CHECK IN COMPARTMENT 2408, WHERE PROBLEMS ARE OCCU	RRING.	2	L	7	2 	4F	4	F	RT	A28NM   	E40NE				 
2004012700093	20040127	00093	NM  	2004	1	27	CA031202006      	1	20031127	G	5620	85323917001	WINDOW          			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	CABIN	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, MODERATE RIME ICE WAS REPORTED AT FL 180 (-18C), WE STARTED ACCUMULATING ICE, REQUESTED A DESCENT T	O FL 160. IN DESCENT, STARTED GETTING SOME PROP VIBRATION, 1050 RPM WAS SET TO AID SHEDDING. ACCUMULATION WAS MODERATE B	OOTS EASILY KEEPING UP, SET ON SLOW, PROPS SET ON BELOW -10C.  AFTER 5 TO 10 MINUTES FA CALLED, ADVISED WINDOW, SEAT 2E 	EITHER HAD CRACK IN IT OR A STREAK OF ICE ACROSS IT. PILOT CHECKED PRESSURIZATION, IT SHOWED NO INDICATIONS OF A LEAK. T	HERE WAS A PLEXIGLASS COVER ON OUTSIDE OF WINDOW THAT HAD A CRACK IN IT NOT ACTUAL WINDOW, SINCE ICE STRIKES ARE COMMON 	THERE AND FUSELAGE IS BEEFED UP.  AFTER CHECKING ON THE GROUND IT WAS OBVIOUS IT WAS THE WINDOW.  MAINTENANCE NOTIFIED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012700094	20040127	00094	SW  	2004	1	27	CA031203001      	1	20031202	G	3221	71470209L	TUBE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	LT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) VERTICAL FRAME TUBE JUST ABOVE AND ATTACHING TO MLG TRUSS FITTING BROKEN JUST ABOVE WELD AT MLG FITTING.CRACK TRAV	ELS COMPLETELY AROUND AND SECOND CRACK GOES VERTICAL 2 INCHES FROM FIRST LOWER CRACK, THEN AROUND THE TUBE AGAIN APPROX 	75 PERCENT.				1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012700095	20040127	00095	SW  	2004	1	27	CA031203002      	1	20031202	G	5710	4149641497	SUPPORT         			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					FUEL TANK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL TANK SUPPORT BRACKETS CRACKED AT ENDS DIRECTLY OFF OF WELDS.  5 OUT OF 6 BRACKETS CRACKED IN LT WING AND ONLY	 1 FOUND CRACKED IN RT WING.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2004012700096	20040127	00096	SW  	2004	1	27	CA031203003      	1	20031202	G	5710	4149641497	SUPPORT         			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FUEL TANK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL TANK SUPPORT BRACKETS FOUND CRACKED AT ENDS DIRECTLY OFF OF WELDS. 3 IB BRACKETS CRACKED IN RT WING NONE IN L	T WING.  NUMBER OF CRACKS VARY FROM 2 TO ALL 4 POINTS OF EACH BRACKET.					1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012700097	20040127	00097	NE  	2004	1	27	CA031203004      	2	20031130	G	7200		ENGINE          			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 1	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	E	J	SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          	WARNING INDICATION        	CL	CLIMB          	1			CA			57181					702874			(CAN) FLIGHT ENROUTE, FLIGHT CREW REPORTED INCREASED VIBRATIONS COMING FROM NR 1 ENGINE AND SPARKS REPORTED ON VISUAL IN	SPECTION. CREW SHUTDOWN ENGINE AND DECLARED AN EMERGENCY. AIRCRAFT RETURNED AND LANDED WITHOUT FURTHER INCIDENT.  ENGINE	 CHANGE BEING CONDUCTED AND ENGINE TO BE SENT TO OVERHAUL FACILITY FOR INVESTIGATION.  WILL FOLLOW UP WITH RESULTS OF OV	ERHAUL.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2004012700098	20040127	00098	EA  	2004	1	27	CA031203005      	2	20031119	G	8550	O320A2B	LINE            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2B     	41508	EA  	MCAULY	1C172	1C172AGM    	GL  	OIL PRESS	LOOSE           	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT REPORTED LOW OIL PRESSURE AND SMOKE. LANDED OFF AIRPORT TO MINIMIZE POSSIBLE DAMAGE TO ENGINE. NO LOSS OF PO	WER. INSPECTION REVEALED A LOOSE OIL PRESSURE LINE AT ENGINE. THE TECHNICAL RECORDS SHOWED NO INDICATION OF WORK BEING C	ARRIED OUT IN THAT AREA. THE LINE WAS REMOVED AND INSPECTED NO DAMAGE WAS FOUND. RE-INSTALLATION AND CLEANING OF THE ENG	INE COMPARTMENT WAS CARRIED OUT.  BOTH OIL FILTER AND SUCTION SCREEN REMOVED AND INSPECTED NO PROBLEM FOUND. ENGINE FILL	ED WITH AEROSHELL 15W50 AND GROUND RUN CARRIED OUT NO LEAKS AIRCRAFT RETURNED TO SERVICE. SUBSEQUENT OIL FILTER AND SUCT	ION SCREEN INSPECTION CARRIED OUT TWICE IN 10 HRS WITH NO PROBLEM FOUND.	1	H	7	1 	3O	3	O	NC	A759    	E274	5	N	P910	 
2004012700099	20040127	00099	GL  	2004	1	27	CA031203006      	1	20031114	G	2730	AN3165	NUT             			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	PUSH PULL ROD	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							C0234				(CAN) DURING 100 HR INSPECTION THE ROD END JAM NUT OF THE ELEVATOR PUSH PULL ROD P/N 22-2730-02-00 WAS FOUND LOOSE. THE 	OPPOSITE ATTACHMENT OF THE PUSH PULL ROD IS SUCH THAT THERE IS NO POSSIBILITY OF THE ROD END TURNING IN THE TUBE THEREFO	RE THERE WAS NO LOSS OF RIGGING. JAM NUT WAS TIGHTENED AND AIRCRAFT RETURN TO SERVICE.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2004012700100	20040127	00100	CE  	2004	1	27	CA031203007      	1	20031130	G	1430	817851223	BOLT            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT WING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A SIRM INSP OF THE WING BOLTS THE RT FWD UPPER WING BOLT SHOWED REJECTIONABLE INDICATIONS. THE BOLT WAS REPLACE	D AND A/C RETURNED TO SERVICE.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2004012700101	20040127	00101	CE  	2004	1	27	CA031203008      	1	20031130	G	1430	817851223	BOLT            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT WING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSP OF A/C AT SIRM INSP FOUND REJECTIONABLE INDICATIONS ON THE FORWARD UPPER RT WING BOLT. REPLACED AND A/C RE	TURNED TO SERVICE. PART WAS 9 YEARS OLD.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2004012700102	20040127	00102	CE  	2004	1	27	CA031203009      	1	20031130	G	1430		BOLT            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT WING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON DOING A SIRM WING BOLT INSP THE FWD UPPER RT WING BOLT SHOWED REJECTIONABLE INDICATIONS. BOLT WAS CHANGED AND R	ETURNED TO SERVICE. BOLT LIFE WAS 9YEARS.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2004012700103	20040127	00103	CE  	2004	1	27	CA031203010      	1	20031203	G	3310	2K40F3	RESISTOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT LIGHT	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA			12387								(CAN) ON APPROACH CREW NOTICED SMOKE COMING FROM UNDER THE CAPTAINS INSTRUMENT PANEL. AFTER A UNEVENTFUL LANDING AND INS	PECTION OF THE WIRING UNDER THE CAPTAINS INSTRUMENT PANEL WAS CARRIED OUT. FOUND THAT CABIN FLUORESCENT LIGHTING RESISTO	R BURNED UP CAUSING THE SMOKE IN THE FLIGHT DECK. SYSTEM INOPERATIVE AND REPLACEMENT PART ORDERED. GROUND RUNS CARRIED O	UT. NO FURTHER FAULTS FOUND.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2004012700104	20040127	00104		2004	1	27	CA031204001      	4	20031121	G	3425		SYMBOL GENERATOR			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					FLT COMPUTER	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) CAPTAIN EADI AND EHSI WENT BLANK TWICE DURING  DESCENT AND APPROACH. EACH TIME THEY STAYED OFF FOR ABOUT 5-10 SECO	NDS, THEN CAME BACK ON. SYMBOL GENERATOR NR 1 SWAPPED WITH NR 2 AND COULD NOT DUPLICATE SNAG ON GROUND. AIRCRAFT DISPATC	HED SERVICEABLE. SUSPECT PROBLEM RELATED WITH BAD VENTILATION. FOUND HSI AND ADI SCREEN PACKED WITH DUST.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004012700105	20040127	00105	NM  	2004	1	27	CA031204002      	1	20030820	G	5752	85740011101	MOUNT           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPRING TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33039	33039							(CAN) WHILE THE AILERON WAS IN THE SHOP FOR REPAIR OF DAMAGE UNRELATED TO THIS INCIDENT, CRACKS WERE DISCOVERED ON THE R	T AILERONS SPAR WEB AND DOUBLER BEHIND THE THE SPRING TAB MOUNTING BRACKET P/N 85740011-101.  THE FINDINGS WERE REPORTED	 TO MFG AND RD8-57-1433 ISSUE 5 WAS ISSUED FOR THE REPAIR, IT CALLS FOR THE AILERON FRONT SPAR WEB TO BE REPLACED/SPLICE	D AS WELL AS A DOUBLER ADDED TO THE SPAR BETWEEN STATION YW 430.7 AND YW 437.9.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004021700200	20040217	00200		2004	2	17	CA031204003      	4	20031029	G	3120	73910193001	CLOCK           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) AC HAD INTERMITTENT WOW CAUTION LIGHT COMING ON IN DIFFERENT STAGES OF FLIGHT. TROUBLESHOOTING INDICATED THAT FAUL	T WAS A WIRING DEFECT.  AFTER HOURS OF INSTALLING NEW WIRING TO SENSOR THAT PSEU INDICATED FAULT ON AC WAS RETURNED TO S	ERVICE ONLY TO RETURN.  EXPLAINED THAT WHEN CLOCK WAS COLD IT WOULD EMIT A ROGUE EMI SIGNAL INTO AC ELECTRICAL SYS THUS 	CAUSING PSEU TO INDICATE A FAULT WITH A WOW SENSOR ON AC.  OFFENDING PART WAS IDENTIFIED AND REPLACED WITH NO REOCCURREN	CE OF PROBLEM ON AC.  OFFENDING PART WAS 8 VDC INPUT VOLTAGE REGULATOR P/N 340T 8.   IT WAS REPLACED AND THE CLOCKED CHE	CKED TO ALL FACTORY SPECS AND RECERTIFIED.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012700106	20040127	00106	CE  	2004	1	27	CA031205001      	1	20031204	G	5610	10138402524	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCE4N	HCE4N3      	NE  	COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE FLIGHT THE PILOT HEARD A 'CLAP' AND THEN NOTICED A CRACK IN THE RT WINDSHIELD. THE AIRCRAFT RETURN	ED TO BASE. INSPECTION DETERMINED CRACK TO BE IN THE EXTERIOR PANE, LIKELY ORIGINATING FROM A SMALL STONE BRUISE. WINDSH	IELD TO BE REPLACED.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	P10NE	 
2004012700107	20040127	00107	EA  	2004	1	27	CA031205002      	2	20031204	G	7297		CONNECTOR       			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WIRE HARNESS	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) WHEN REDUCING POWER FOR DESCENT THE PILOT NOTICED A NORMAL REDUCTION IN TORQUE INDICATION, THEN AS POWER FURTHER R	EDUCED THE TORQUE INDICATION WOULD CLIMB TO REDLINE VALUES. NO OTHER ENGINE PARAMETERS OR AIRCRAFT BEHAVIOR AGREED WITH 	THIS INDICATION AND THROUGH CONSULTATION WITH MAINTENANCE PERSONNEL ON THE GROUND, THE DESCENT AND LANDING CONTINUED UNE	VENTFULLY. INSPECTION DISCOVERED TWO BROKEN WIRES (PINS D AND B)  WHERE THEY ENTER CONNECTOR CONNECTION E232. THIS WIRIN	G HARNESS MAKES A 180 DEGREE BEND JUST PRIOR TO ENTERING THE PLUG. AIRCRAFT TTSN 1763		1	L	7	2 	3T	4	T	 	A8EA    	E4EA	6	C	P15EA	 
2004012700108	20040127	00108	EA  	2004	1	27	CA031205003      	1	20031201	G	5730		SKIN            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF341A      	 	NE  					LT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING FTP STALLS, BUFFET WAS EXPERIENCED JUST PRIOR TO PUSHER ACTIVATION FOR BOTH THE CLEAN AND F20 STALLS.  ADDI	TIONALLY A MILD LT WING DROP WAS EXPERIENCED ON THE F20 STALL. AFTER LANDING, SEALANT WAS OBSERVED TO HAVE SPREAD OUT OF	 THE LT WING LEADING EDGE JOINTS (CHORDWISE) AND HAD FLOWED BACK ONTO THE WING SURFACE. MEASURES HAVE BEEN TAKEN TO INCL	UDE AN INSPECTION TO BE CARRIED OUT WALK AROUND OF PILOT AND TECHNICIAN TO VERIFY INSTALLATION OF SEALANT AT CRITICAL AR	EAS.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012700109	20040127	00109	NE  	2004	1	27	CA031205004      	2	20031128	G	7421	SC2036	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								4299			(CAN) ON REMOVAL OF IGNITORS ON ENGINE S/N 4299, IT WAS OBSERVED THAT THE LT IGNITOR HAD LOST IT'S CORE (IGNITOR P/N SC2	036). A BORESCOPE INSPECTION REVEALED THERE WAS SUBSTANTIAL DAMAGE TO THE 1ST STAGE TURBINE BLADES (7 BLADES DAMAGED). T	HE ENGINE WAS REMOVED FROM SERVICE AND MODULE 2/3 SENT TO ACRO IN VANCOUVER FORASSESSMENT.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004012700110	20040127	00110	CE  	2004	1	27	CA031205005      	1	20031201	G	2497		WIRE HARNESS    			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ALTERNATOR	BURNED          	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT NOTICED HIGH VOLTAGE LIGHT- ELECTRICS TURNED OFF - RETURNED TO BASE. CONTACT WITH TOWER BY CELL PHONE.- ON I	NSPECTION AT AMO FACILITY IT WAS LEARNED THAT THE WIRING HARNESS TO THE ALTERNATOR FAILED/SHORTED OUT.- REPAIRS TO THE H	ARNESS WAS MADE AND THE AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004012700111	20040127	00111	EA  	2004	1	27	CA031205007      	1	20031201	G	5710	C3W255	STRUT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17743								(CAN) WING STRUT WAS REMOVED TO INSPECT/REPAIR SLOPPY STRUT ATACHMENT CONDITION.  UPON REMOVING STRUT ASSEMBLY, LUG FACE	S (FORWARD/AFT) FOUND CORRODED.   REF. PSM 1-3-3 FIG 2-1 (DHC-3 REPAIR MANUAL).					1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2004012700112	20040127	00112	EA  	2004	1	27	CA031205008      	1	20031201	G	5740	C3W10433	ATTACH FITTING  	DHAV        		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	WING STRUT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						233					(CAN) FRETTING EXFOLIATION CORROSION ON LINK ATTACH LUG (1 ONLY).						1	H	7	1 	3R	3	R	 	A815    	E142	6	C	P719	 
2004012700113	20040127	00113	WP  	2004	1	27	CA031205009      	1	20031205	G	5302		MOUNT           	ROBSIN      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					AFT ANTENNA	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0379					(CAN) DURING INSPECTION AFT GPS ANTENNA SEALENT WAS NOTICED TO BE CRACKED AND THE ANTENNA WAS LOOSE.  UPON REMOVING THE 	ANTENNA, 3.5 INCH CRACKED WAS FOUND ON THE TAILCONE SKIN.  THE CRACK DID NOT ORIGINATE FROM ANY OF THE MANUFACTURED RIVE	T OR SCREW HOLES.  IT COULD NOT BE DETERMINED IF THE ANTENNA HAD BEEN PULLED ON AS THERE WAS NO DAMAGE TO THE ANTENNA OR	 BENDING OF THE TAILCONE SKIN.  PICTURES HAVE BEEN FORWARDED TO TRANSPORT  MAINTENANCE AND MANUFACTURER. THE TAILCONE HA	S BEEN SENT TO THE MANUFACTURER FOR INSPECTION AND REPAIR.		1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004012700114	20040127	00114	NE  	2004	1	27	CA031205010      	2	20031201	G	7250	3020159	SHROUD          								PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SECTION	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								A00086EW			(CAN) AFTER LIGHTNING STRIKE THE ENGINE WAS REMOVED FOR MAJOR REPAIR.  WHEN THE ENGINE WAS SPLIT THE TECHNICIAN NOTICED 	A DISLODGED COMPRESSOR TURBINE SHROUD SEGMENT,  RETAINING RING.  THE SEGMENTS DROPPED AND CAUSED COMPRESSOR TURBINE BLAD	E TIP RUBS. THIS PROBLEM HAS BEEN DOCUMENTED ON AT LEAST 5 OTHER ENGINES THAT THE AUTHOR IS AWARE OF.  MFG HAS ISSUED P/	N 3110741-02 RETAINING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 3248 (41/42, 45 SERIES) TO PREVENT THE COLLAPSE 	OF THE RETAINING RING.  THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MODELS SUCH AS THE  114A ENGINE MODEL TO ALL	OW THE MORE ROBUST RETAINING RING TO BE USED.						3	T			E4EA				 
2004012700115	20040127	00115	NE  	2004	1	27	CA031205011      	2	20031201	G	7250	3020159	RETAINER        								PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SECTION	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								A00021X9			(CAN) DEGRADED ENGINE PERFORMANCE (HIGH ITT/LOW NG) LEAD TO HOT SECTION MAINTENANCE BY CUSTOMER.  THE COMPRESSOR TURBINE	 SHROUD SEGMENT RETAINING RING HAD BECOME LOOSE. THE SEGMENTS WERE LOOSE AND CAUSED COMPRESSOR TURBINE BLADE TIP RUBS. T	HIS PROBLEM HAS BEEN DOCUMENTED ON AT LEAST 5 OTHER ENGINES THAT THE AUTHOR IS AWARE OF.  MFG HAS ISSUED P/N 3110741-02 	RETAINING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 3248 (41/42, 45 SERIES) TO PREVENT THE COLLAPSE OF THE RETAIN	ING RING.  THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MODELS SUCH AS THE  114A ENGINE MODEL TO ALLOW THE MORE R	OBUST RETAINING RING TO BE USED.						3	T			E4EA				 
2004012700116	20040127	00116	NE  	2004	1	27	CA031205012      	2	20031201	G	7250	3020159	RETAINER        								PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SECTION	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DEGRADED ENGINE PERFORMANCE (ITT LIMITED) LEAD TO HOT SECTION MAINTENANCE. A DISLODGED COMPRESSOR TURBINE SHROUD S	EGMENT-RETAINING RING WAS FOUND.  THE SEGMENTS WERE LOOSE, SHIFTED AND CAUSED COMPRESSOR TURBINE BLADE TIP RUBS. THIS PR	OBLEM HAS BEEN DOCUMENTED ON AT LEAST 5 OTHER ENGINES THAT THE AUTHOR IS AWARE OF.  MFG HAS ISSUED P/N 3110741-02 RETAIN	ING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 3248 (41/42, 45 SERIES) TO PREVENT THE COLLAPSE OF THE RETAINING RI	NG.  THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MODELS SUCH AS THE  114A ENGINE MODEL TO ALLOW THE MORE ROBUST 	RETAINING RING TO BE USED.						3	T			E4EA				 
2004012700117	20040127	00117	NE  	2004	1	27	CA031205013      	2	20031201	G	7250	3020159	RETAINER        								PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SECTION	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER HOT SECTION INSPECTION THE ENGINE WAS RUNNING HOT.  WHEN THE ENGINE WAS SPLIT THE TECHNICIAN NOTICED THE COM	PRESSOR TURBINE SHROUD SEGMENT RETAINING RING HAD FALLEN BEHIND THE VANE.  THE SEGMENTS MOVED AND CAUSED COMPRESSOR TURB	INE BLADE TIP RUBS. THIS PROBLEM HAS BEEN DOCUMENTED ON AT LEAST 5 OTHER ENGINES THAT THE AUTHOR IS AWARE OF.  MFG HAS I	SSUED P/N 3110741-02 RETAINING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 3248 (41/42, 45 SERIES) TO PREVENT THE C	OLLAPSE OF THE RETAINING RING.  THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MODELS SUCH AS THE 114A ENGINE MODEL	 TO ALLOW THE MORE ROBUST RETAINING RING TO BE USED.						3	T			E4EA				 
2004012700118	20040127	00118	NE  	2004	1	27	CA031205014      	2	20031202	G	7314	1143890425	PUMP            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	FUEL PRESS	LEAKING         	W				O				OTHER                   				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		NR	NOT REPORTED   	1			CA											(CAN) CREW NOTED THAT FUEL WAS LEAKING FROM THE RT ENGINE COWL.  MAINTENANCE FOUND THAT THE LOW PRESSURE FUEL PUMP HAD B	LOWN OUT THE GASKET BETWEEN THE MAIN BODY AND THE REGULATOR ASSEMBLY ALLOWING FUEL UNDER PRESSURE TO ESCAPE. THE PUMP WA	S REPLACED AND THE AIRCRAFT RELEASED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2004012700119	20040127	00119	SO  	2004	1	27	CA031205015      	1	20031202	G	3230		UPLOCK          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	MLG	FROZEN          	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) LANDING GEAR UPLOCK FROZEN.  WOULD NOT RELEASE TO LOWER GEAR.   A MANUAL GEAR EXTENSION WAS COMPLETED.  AIRCRAFT G	EAR INSPECTED AND RE-LUBRICATED.  FLIGHTS SINCE THEN HAVE BEEN SATISFACTORY.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2004012700120	20040127	00120	SO  	2004	1	27	CA031205016      	1	20031130	G	3260		BULB            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	MLG INDICATOR	LOOSE           	W				L				ABORTED APPROACH        				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) NO RT LANDING GEAR DOWN AND LOCKED INDICATION.  SOURCE CONFIRMED TO BE A LOOSE LIGHT BULB SOCKET.   NO OTHER ACTIO	N TAKEN.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2004012700121	20040127	00121		2004	1	27	CA031208001      	4	20031204	G	3413	7040	INDICATOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LEFT VSI	INOPERATIVE     	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) LT VSI WAS NOTED TO READ UP TO 250 FPM HIGH AS COMPARED TO THE RT AND PRESELECT SETTING.  IT WAS NOTED TO READ ZER	O IN LEVEL FLIGHT.  VSI REPLACED WITH SERVICEABLE UNIT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012700122	20040127	00122	EU  	2004	1	27	CA031208002      	1	20031204	G	5230	5523512071	CABLE           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CARGO DOOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CABLE USED TO LOWER THE CARGO DOOR WAS FOUND TO HAVE A BROKEN STRAND.  CABLE WAS REPLACED WITH NEW.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012700123	20040127	00123	EU  	2004	1	27	CA031208003      	1	20031203	G	3297	9740926112	RELAY           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE-OFF, LANDING GEAR WOULD NOT FULLY RETRACT.  NOSE GEAR CAME PARTWAY UP ONLY.  GEAR WAS SELCTED DOWN AND 	LOCKED AND AC RETURNED TO BASE. HYD RELAY 947.09.26.112 WAS REPLACED, GEAR SWINGS CARRIED OUT AND AC RETURNED TO SERVICE	.  EVENING BEFORE, CREWS HAD COMPLAINED OF GEAR BEING SLOW.  MAINT WAS INVESTIGATING AND IN PROCESS GEAR WOULD NOT RETRA	CT WHILE ON JACKS, A DIRTY CONNECTOR WAS TO HYD CONTROL RELAY 947.09.26 .112.  CONNECTOR WAS CLEANED AND  SYS OPERATED N	ORMALLY THROUGHOUT GEAR SWINGS.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012700124	20040127	00124	NM  	2004	1	27	CA031208004      	1	20031201	G	2130	32194211	CONTROL VALVE   			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					CABIN PRESSURE	MALFUNCTIONED   	W				G				O2 MASK DEPLOYED        				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT THROUGH 25,000 FT. FLIGHT CREW REPORTED, DUCT OVERHEAT ON RT PACK. COULD NOT CONTROL TEMPERATURE WITH	 RT PACK ON.  AIRCRAFT LOST ALL PRESSURIZATION AT ABOUT 25,000 FT. AND COULD NOT CONTROL CABIN PRESSURE IN MANUAL. CREW 	CONTACTED ATC AND CONDUCTED RAPID DESCENT DOWN TO 9,000 FT. CREW COULD NOT RESTORE PRESSURIZATION, SO THEY RETURNED.  WH	EN AIRCRAFT LEVELLED OFF AT 9,000 FT. CAPTAIN WAS INFORMED OXYGEN MASKS HAD DROPPED DOWN IN THE CABIN.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2004012700125	20040127	00125	NE  	2004	1	27	CA031208005      	2	20031201	G	7250	3020159	RETAINER        								PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SECTION	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE CUSTOMER EXPERIENCED A NEGATIVE SHIFT IN PERFORMANCE AND INCREASED ITT.  THE HOT SECTION WAS INSPECTED. THE CT	 SHROUD SEGMENTS HAD SHIFTED AND THE CT BLADES WERE RUBBED. THIS PROBLEM HAS BEEN DOCUMENTED ON AT LEAST 5 OTHER ENGINES	 THAT THE AUTHOR IS AWARE OF.  PWA HAS ISSUED P/N 3110741-02 RETAINING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 	3248 (41/42, 45 SERIES) TO PREVENT THE COLLAPSE OF THE RETAINING RING. THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGI	NE MODELS SUCH AS THE114A ENGINE MODEL TO ALLOW THE MORE ROBUST RETAINING RING TO BE USED.							3	T			E4EA				 
2004012700126	20040127	00126	EU  	2004	1	27	CA031208006      	1	20031206	G	2750	5275212133	LINK            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAP CONTROL	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT AFT LINK PART NUMBER 527.52.12.133 AT CENTER FLAP POSITION FOUND BENT. FLAP FAIRINGS WERE REMOVED AND ALL LINKA	GES INSPECTED.  NO OTHER FAULTS FOUND. RT FLAP INSPECTED, NO FAULTS FOUND.  BOTH RT FLAP FLEX DRIVE CABLES INSPECTED, NO	 FAULTS FOUND. SUSPECT FOD ICE/SLUSH FROM RUNWAY FILLED FAIRING AND FROZE. WHEN FLAPS WERE SELECTED IT INTERFERED WITH A	FT LINKAGE CAUSING IT TO BEND.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012700127	20040127	00127	WP  	2004	1	27	CA031208007      	1	20031128	G	3080	39271012	AUGMENT VALVE   			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					RIGHT	FAILED          	W				A				UNSCHED LANDING         				J	M		WARNING INDICATION        	OVER TEMP                 		CL	CLIMB          	1			CA						3798					(CAN) RT ICE PROTECTION TEMPERATURE HIGH ILLUMINATED IN CLIMB. AIRCRAFT LANDED. MAINTENANCE REPLACED THE RT AUGMENTATION	 VALVE P/N 392710-2, S/N 3798 AND THE RT ICE ANTICIPATORS P/N 129110-2-1, S/N P118 AND P/N 129112-1-1, S/N N4216. SYSTEM	 WAS SERVICEABLE FOLLOWING THESE ACTIONS.				2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004012700128	20040127	00128	NE  	2004	1	27	CA031208008      	1	20031208	G	6320	6135345133	BEARING         	SKRSKY      	613520600   	SKRSKY	S61   	S61NM       	8142710	NE  										M/R GEARBOX	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						65659					(CAN) BRG IS ONE OF FOUR BABBITT BRS LOCATED IN INPUT HOUSING AND COVER OF MGB.  BRG IN QUESTION IS LOCATED IN THE INPUT	 COVER IN THE NR 1 POSITION. THIS GB WAS BEING TEST RUN BY MFG AC, TEN MINUTES IN TO RUN TEST STAND SHUT DOWN BECAUSE OF	 AN OVERTEMP ON SUBJECT BRG.  INVESTIGATION REVEALED THAT IT WAS DUE TO OIL STARVATION THAT WAS DUE TO THE OIL GALLERY I	N BRG BEING LOCATED INCORRECTLY. OIL HOLE WAS LOCATED APPROX. 45 DEG OUT. THIS RESULTED IN NO OIL FLOW TO JOURNAL ON HIG	H SPEED INPUT THAT RUNS IN IT. ORIENTATION OF BEARING WAS LOCATED CORRECTLY, THERE IS A PIN CUT OUT ON THE FLANGE OF BEA	RING TO PRECLUDE THIS POSSIBILITY.	2	G	7	2 	4U			 	1H15    					 
2004012700129	20040127	00129	NE  	2004	1	27	CA031209001      	2	20030810	G	7320	CASC501	REGULATOR       			FOKKER	F27   	F27MK100    	4990617	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					FUEL FLOW	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) NR 2 ENGINE FAILED TO ACCELERATE AT ALTITUDE DURING ALPHA FLOOR PROTECTION TEST. (AIRCRAFT SLOWS TO MINIMUM SPEED.	 AUTO THROTTLE SHOULD KICK IN AND ACCELERATE AIRCRAFT.) INVESTIGATION OF THE CASC501 FUEL FLOW REGULATOR FROM THIS ENGIN	E SHOWED THAT IT HAD BEEN SET TO DELIVER LOWER THAN REQUIRED FUEL FLOW BECAUSE IT WAS TESTED WITH A GD501 FUEL PUMP INST	EAD OF A GD500 FUEL PUMP AS SPECIFIED.  A REVIEW OF R AND O RECORDS HAS SHOWN THAT 7 OTHER REGULATORS ARE AT RISK BECAUS	E OF THE SAME ERROR.		2	H	7	2 	4T	4	F	 	A817    	E25NE				 
2004012700130	20040127	00130	NE  	2004	1	27	CA031209002      	1	20031209	G	6310	6135020459102	BUSHING         	SKRSKY      		SKRSKY	S61   	S61NM       	8142710	NE  										FREEWHEEL UNIT	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) THE SUBJECT BUSHING INSIDE DIAMETER WAS NOT WITHIN DRAWING LIMITS. DRAWING LIMITS ARE 2.533 - 2.536. ACTUAL WAS 2.	532. THIS BUSHING WOULD NOT FIT ON TO THE SHAFT. IT WAS SUPPLIED AS NEW.					2	G	7	2 	4U			 	1H15    					 
2004012700131	20040127	00131	SW  	2004	1	27	CA031209003      	1	20031202	G	2810		BLADDER         	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CELL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WHEN FUEL TANK FILLED TO MAXIMUM CAPACITY A DRIP WOULD SHOW ON THE BELLY OF THE AIRCRAFT NEAR THE FUEL CAVITY DRAI	N HOLE.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004012700132	20040127	00132	SW  	2004	1	27	CA031209004      	1	20031208	G	4940	980871103P261	PRESSURE SWITCH 			SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	APU	CRACKED         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI IN FROM THE LAST FLIGHT OF THE DAY, THE CREW NOTICED THE OIL PRESSURE LIGHT ILLUMINATED. THE GAUGE CONFIRM	ED THE INDICATION.  THE CREW SHUT THE ENGINE DOWN.  ON ARRIVAL AT THE RAMP, A SUBSTANTIAL AMOUNT OF OIL WAS FOUND LEAKIN	G FROM THE COWL. MAINTENANCE WAS NOTIFIED, AND TRACED THE PROBLEM TO A THE AUTO IGNITION PRESSURE SWITCH INSTALLED ON TH	E TORQUE PRESSURE MANIFOLD.  THE SWITCH WAS INSTALLED AS PART OF AD 2002-01-16.  PART TOTAL TIME WAS 580 HOURS SINCE NEW	.  A SERVICEABLE SWITCH WAS INSTALLED AND GROUND RUN CARRIED OUT SERVICEABLE.		2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P15EA	 
2004012700133	20040127	00133	CE  	2004	1	27	CA031209005      	1	20031208	G	3297		DOWNLOCK SWITCH 			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	BROKEN          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) LT MAIN LANDING GEAR NOT INDICATING DOWN AND LOCKED ON APPROACH.  AIRCRAFT RETURNED TO BASE.  BROKEN WIRE ON DOWN 	SWITCH FOUND AND REPAIRED.  GEAR SWING CARRIED OUT NORMAL FOR TYPE. AIRCRAFT RELEASED FOR RETURN TO SERVICE					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2004012700134	20040127	00134	EU  	2004	1	27	CA031210001      	1	20031208	G	2133	9631411001	SOLENOID        	HONEYWELL   		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	OUTFLOW VALVE	STUCK           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						118B0244					(CAN) AIRCRAFT WOULD NOT PRESSURIZE AFTER TAKE OFF. RETURNED TO BASE AND IT WAS FOUND SAFTEY VALVE WAS OPEN. THE REASON 	WAS THE SOLENIOD VALVE WAS STUCK IT WAS REMOVED AND CLEANED INSTALLED AND TESTED. GROUND RUNS WERE CONDUCTED AND PRESSUR	IZATION WAS FUNCTIONAL TESTED AND FOUND SERVICABLE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004012700135	20040127	00135	SO  	2004	1	27	CA031210002      	2	20031208	G	8530	646657A2	CYLINDER        			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C*     	GL  	ENGINE	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA								270746R			(CAN) ON APPROACH TO LANDING RT ENGINE STARTED TO RUN ROUGH. PILOT LANDED WITHOUT INCIDENT. AIRCRAFT WAS BROUGHT INTO TH	E HANGER AND A DP TEST WAS CONDUCTED ON THE ENGINE AND NR 6 CYLINDER WAS FOUND TO BE CRACKED FROM THE TOP SPARK PLUG HOL	E ALL THE WAY AROUND TO THE LOWER SPARK PLUG HOLE. CYLINDER WAS REMOVED AND NO OTHER DAMAGE WAS NOTED.				1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2004012700136	20040127	00136	EA  	2004	1	27	CA031210003      	2	20031206	G	7250	3022797	OIL RUNNER      			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	TURBINE SECTION	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			23583					86031			(CAN) DURING THE UNSCHEDULED REMOVAL OF NR 2 PROP DUE TO OIL LEAKING FROM THE PROP SHAFT, IT WAS NOTICED THAT THE PROP S	HAFT OIL RUNNER (PART OF THE POWER SECTION) WOULD ROTATE WITHOUT THE PROP SHAFT MOVING. INFORMED US THAT THIS IS AN INDI	CATION THAT BEARING RETAINING NUT ASSY (NUT P/N 3022710) MAY HAVE LOOSENED UP. THE POWER SECTION WAS REMOVED AND SENT FO	R REPAIR.			2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2004012700137	20040127	00137	NE  	2004	1	27	CA031210004      	2	20031201	G	7250	3020159	RETAINER        								PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SECTION	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								A00086EW			(CAN) DURING A SCHEDULED HOT SECTION INSPECTION THE TECHNICIAN FOUND SHIFTED CT SHROUD SEGMENTS. THE RETAINING RING HAD 	RELAXED IN SERVICE AND MOVED OUT OF THE RING GROOVE. THIS PROBLEM HAS BEEN DOCUMENTED ON AT LEAST 5 OTHER ENGINES THAT T	HE AUTHOR IS AWARE OF.  MFG HAS ISSUED P/N 3110741-02 RETAINING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 3248 (4	1, 42, 45 SERIES) TO PREVENT THE COLLAPSE OF THE RETAINING RING.  THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MO	DELS SUCH AS THE 114A ENGINE MODEL TO ALLOW THE MORE ROBUST RETAINING RING TO BE USED.							3	T			E4EA				 
2004012700138	20040127	00138	SW  	2004	1	27	CA031210005      	1	20031208	G	5510		ATTACH FITTING  			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MA3     	GL  	HORIZIONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION THE RT HORIZONTAL STABILIZER AUX FIN WAS FOUND TO BE LOOSE. UPON INVESTIGATION BY MAINTEN	ANCE PERSONNEL THE FORWARD STABILZER BRACE AND AUX FIN ATTACH PLATE P/N 30653-2 WAS FOUND CRACKED COMPLETELY THROUGH AND	 AFT STABILIZER BRACE AND THE AUX FIN ATTACH PLATE WAS CRACKED APPROXIMATELY 1 INCH.  THE CRACKS STARTED AT THE RADIUS O	F EACH PLATE. THE ATTACH PLATES WERE REPLACED WITH NEW PARTS.			1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2004012700139	20040127	00139	EA  	2004	1	27	CA031210006      	1	20031209	G	5511	21523107821	RIB             			CNDAIR	CL215 	CL2151A10   	1900320	EA  	PWA   	R1340 	AWASP       	52016	NE  	HAMSTD	43E	43E60       	NE  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION IT WAS NOTED THAT THE INBOARD RIB P/N 215-23107-821 WAS CRACKED ON THE UPPER FLANGE. THE 	REMAINING AIRCRAFT IN THE FLEET WERE INSPECTED AND ALL 3 HAD CRACKS ON THE SAME RIB. THE CRACKS VARIED IN LENGTH FROM 1 	INCH TO APPROXIMATELY 4 INCH. THE TAT'S WERE 3545.3, 3274.8 AND 2919.5.				2	H	7	2 	4R	3	R	RT	A14EA   	ATC14	6	C	P871	 
2004031500026	20040315	00026	WP  	2004	3	15	CA031210007      	1	20030129	G	6520	369A53525	BEARING RACE    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					CLUTCH	INCORRECT       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						HT8920					(CAN) AT 300 HR. INSPECTION IT WAS NOTED THE OUTER RACE DID NOT HAVE A P/N, S/N OR A HEAT TREATMENT NR ETCHED ON IT. THI	S WAS NOTED ON THE AD COMPLIANCE RECORD ALSO (BUT USED ANYWAY). MD HELICOPTERS SERVICE ENGINEERING WAS CONTACTED AND WE 	WERE INFORMED THAT IAW NOTES NR 19 AND 20 OF DRAWING THE PART MUST BE SERIALIZED AND IT WAS RECOMMENDED TO REMOVE FROM S	ERVICE (FAX LETTER ON FILE).			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004012700140	20040127	00140	EA  	2004	1	27	CA031210008      	2	20031210	G	7397		CONNECTOR       	BELL        		BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					PRESSURE SWITCH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DIAPHRAGM BROKEN AND LEAKING AROUND PINS ON ELECTRICAL HARNESS.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2004031500027	20040315	00027	WP  	2004	3	15	CA031210009      	1	20030129	G	6500	369D25102	HOUSING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					T/R COVER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1094					(CAN) AT REMOVAL OF TRANSMISSION FROM AIRFRAME A SUSPECTED CRACK IN THE T/R O/P COVER AT THE OIL PRESSURE SENDING UNIT W	AS NOTED. THIS AREA WAS PAINT STRIPPED AND THE AREA WAS NOT ONLY CRACKED IT HAD ALSO BEEN STOP DRILLED, FILLED WITH EPOX	Y AND PAINTED. THIS IS NOT A REPAIRABLE ITEM. IT WAS ALSO NOTED THE TOP COVER HAD A BOLT MISSING. THE CUSTOMER WAS NOTIF	IED AND THEN NOTIFIED THE REPAIR FACILITY THAT OVERHAUL THIS UNIT NOV.19/01 AND REPAIRED JULY 8/02. THEY REPLACED THE HO	USING FEB.26/03.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004012600116	20040126	00116	CE  	2004	1	26	CA031211001      	1	20031209	G	2820	040031158	LINE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	FUEL SYSTEM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL LINE HAD A ROUGH LOOK TO THE SURFACE. THE FUEL LINE WAS ACCESSED BY REMOVING CENTER CONSOLE COVER AND PEELING	 BACK CARPET.  CLOSER EXAMINATION OF LINE REVEALED CORROSION PITS AND RESIDUE THAT WAS DETERMINED TO BE CAUSED BY THE FU	EL LINE CONTACT WITH MOISTURE SOAKED CARPET.  LINE IS ROUTED UP FROM FLOOR THROUGH A CUT-OUT AND CLAMPED FURTHER UP WHER	E IT CONNECTS TO A UNION FITTING. THIS IS ON RT SIDE OF CONSOLE AND ADJACENT TO WHERE INSTRUCTORS LT FOOT WOULD BE RESTI	NG. MOISTURE FROM HIS/ HERFOOTWEAR IS ABSORBED INTO CARPET AND RESTS ALONG FUEL LINE WHERE IT EXITS FLOOR.  LINE WAS REM	OVED AND REP LACED WITH A NEW PART.  CONSOLE WILL BE REINSTALLED WITH EDGE OF CARPET RESTING OVER BASE OF CONSOLE.	1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2004012600117	20040126	00117	NM  	2004	1	26	CA031211002      	1	20031207	G	2910	659603	SOLENOID VALVE  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	SEPARATED       	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			30959	19335							(CAN) DURING CLIMB CREW REPORTED LOSS OF NR 2 HYD FLUID. NR 2 HYD ISO VALVE CAUTION LIGHT ILLUMINATED.  NR 2 HYD QUANTIT	Y GAUGE SHOWING DECLINE. AIRCRAFT RETURNED TO ORIGINATING AIRPORT, ALTERNATE GEAR EXTENSION USED, NORMAL LANDING.  MAINT	ENANCE FOUND NR 2 HYD FLIGHT SPOILER VALVE CAP HAD SEPARATED, ALLOWING LOSS OF HYD FLUID. VARIOUS PARTS LOCATED IN THE N	ACELLE. CAP SHOULD BE SECURED TO VALVE BODY WITH 4 SCREW/STUDS, 3 STUDS REMAINED IN BODY, ONE MISSING. 2 HEADS STILL LOC	KWIRED TOGETHER LOCATED IN NACELLE, REMAINING ATTACHMENT PARTS NOT LOCATED. VALVE REPLACED WITH SERVICEABLE UNIT, FUNCTI	ON, LEAK CHECKED. AIRCRAFT RETURNED TO SERVICE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012600118	20040126	00118	NE  	2004	1	26	CA031211003      	3	20031201	G	6111	8022532	COLLAR          	HAMSTD      		DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROP BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									8660457		(CAN) DURING A FLEET INSPECTION OF PROPELLER BLADES TO CHECK INTEGRITY AND CONDITION OF THE BLADE CUFFS. AS A RESULT OF 	THE INSPECTIONS, ONE COLLAR ASSY WAS FOUND TO BE CRACKED, HOWEVER, STILL SECURELY ATTACHED. THE BLADE ASSY WAS REMOVED F	ROM SERVICE AND HAS BEEN SENT FOR REPAIR. MFG HAS BEEN INFORMED OF FINDINGS.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012600119	20040126	00119	EA  	2004	1	26	CA031211004      	1	20031204	G	7920	5085T10G01	TUBE            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					HEAT EXCHANGER	CHAFED          	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) DURING TROUBLESHOOTING OF POSSIBLE OIL LEAK ON NR 1 ENGINE, MAINTENANCE FOUND OIL LINE FROM HEAT EXCHANGER TO LUBE	 SCAVENGE PUMP DEEPLY CHAFED ON FLANGE OF A AND B SUMP SUPPLY LINE.  LINE REPLACED. A AND B SUMP SUPPLY LINE REPOSITIONE	D AND ADDITIONAL CLAMPING INSTALLED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012600120	20040126	00120	NE  	2004	1	26	CA031211005      	2	20031207	G	7532	311269001	PIPE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	BLEED VALVE	CRACKED         	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF NR 1 ENGINE FUEL FLOW INDICATING 150 LBS HIGHER THAN NR 2 ENGINE. ON NR 1 ENGINE MAINTENANCE FOUND P3 V	ENTURI TUBE WITH CRACKS JUST ABOVE FLANGE THAT HAD JOINED TOGETHER TO PUSH OUT PART OF THE WALL OF THE TUBE TO CREATE A 	HOLE. TUBE WAS REPLACED.  ENGINE TSN: 24434 TSO: 4853 CSN: 34845 CSO: 6528				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012600121	20040126	00121	NE  	2004	1	26	CA031212001      	1	20031202	G	6220	S611520107	RECEPTACLE      			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					M/R HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) POCKETS 20,21,22 FOUND CRACKED SPAN WISE ON UNDER SIDE OF POCKET. AFTER REMOVAL OF POCKET FROM THE BLADE, IT WAS F	OUND THAT THE POCKETS WERE NOT BONDED TO THE BACK FACE OF THE SPAR. THIS ALLOWED THE POCKETS TO WORK UP AND DOWN CAUSING	 THE SURFACE CRACKS.				2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2004012600122	20040126	00122	NM  	2004	1	26	CA031212002      	1	20031127	G	2710	82700563S001	CONTROL CABLE   			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	AILERON SYSTEM	MISRIGGED       	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA											(CAN) AILERON CTRL CABLES FOUND TO BE INCORRECTLY ROUTED AT OB CNTL QUADRANTS ON BOTH WINGS, UNDER ACCESS PANELS 532AT A	ND 632AT.  IT WAS ONLY DUE TO OTHER AILERON MAINT THAT PANELS 532AT, 632AT WERE LIFTED TO FACILITATE RIGGING CHECKS.  IN	CORRECT ROUTING ISSUE, CABLES IN QUESTION HAD NOT BEEN LOCATED IN QUADRANT GROOVE AS REQUIRED HENCE WERE OPERATING ON TO	P OF QUADRANT RESULTING IN RUBBING ON QUADRANT. ALTHOUGH CABLES HAD BEEN RUBBING ON QUADRANT THEY HAD NOT GENERATED WEAR	 OUTSIDE OF MM LIMITS, ONCE RIGGED THEY HAVE REMAINED IN SERVICE. IN ADDITION, HAD AILERONS NOT BEEN CHANGED, PANELS WOU	LD NOT HAVE BEEN LIFTED AT THIS VISIT. DEFECT DISCOVERED IS BELIEVED TO HAVE BEEN IN A/C SINCE MANUFACTURE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012600123	20040126	00123	SW  	2004	1	26	CA031212003      	1	20031203	G	5302	206032409001P	FITTING         			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE 100 HR INSPECTION TO AIRCRAFT, THE LT UPPER TAILBOOM ATTACHMENT FITTING WAS FOUND CRACKED. CRACK AP	PEARED TO BE BETWEEN AND EXTENDED BELOW THE TWO FORWARD MOST ATTACHING RIVETS. NO INDICATION OF CRACK WAS NOTED ON PREVI	OUS INSPECTION. TAILBOOM WAS REMOVED FROM AIRCRAFT, SENT TO APPROVED REPAIR FACILITY, FITTING REPLACED AND TAILBOOM PLAC	ED BACK IN SERVICE.			1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2004012600124	20040126	00124	NM  	2004	1	26	CA031212004      	1	20031209	G	2710		CONTROL CABLE   			BOEING	727   	727243      	138408D	NM  	PWA   	JT8   	JT8D15      	52051	NE  					AILERON SYSTEM	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			48876								(CAN) CONTROL WHEEL VERY STIFF WHEN DEFLECTED LT AND SLOW TO RETURN ON RT DEFLECTION. LOST MOTION CABLES ADJUSTED IAW MM	 27-10-0 AILERON INPUT PUSHROD ADJUSTED IAW MM 27-10-0CENTERING PUSHROD ADJUSTED A PER MM 27-10-0 SPOILER MIXER CONTROL 	ROD ADJUSTED MM 27-61-0 SPRING CARTRIDGE ROD ADJUSTED IAW MM 27-10-0 AILERON SPOILER FUNCTIONAL CHECK CARRIED OUT AND FO	UND OK IAW MM 27-10-0 AND 27-60-0.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2004030200001	20040302	00001	CE  	2004	3	2	CA031212005      	1	20031212	G	5510	04320049	BRACKET         	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22758								(CAN) AN INSPECTION WAS PERFORMED TO THE BRACKET AT THE REAR OF THE HORIZONTAL STABILIZER IN PREPARATION FOR COMPLIANCE 	WITH CESSNA SERVICE BULLETIN 03-6.ONCE THE STABILIZER AND BRACKET WERE REMOVED FROM THE AIRCRAFT, A CLOSE VISUAL EXAMINA	TION REVEALED A CRACK MEASURING ABOUT 1/2 INCH IN LENGTH RUNNING ALONG THE WELD ADJACENT TO ONE OF THE INSTALLED NUTPLAT	ES. THE BRACKET WAS REMOVED FROM SERVICE AND A REPLACEMENT BRACKET WAS PLACED ON ORDER FROM THE MANUFACTURER.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2004012700001	20040127	00001	EA  	2004	1	27	CA031212006      	1	20031210	G	6240	269A46193	DRIVE ASSY      			SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					ROTOR TACH	CORRODED        	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED LOST ROTOR TACH INDICATION. ROTOR DRIVE CABLE WAS REMOVED FROM ITS OUTER SHEATH FOR INSPECTION AND 	WAS FOUND SNAPPED IN TWO JUST BEFORE IT ENTERS INTO THE TRANSMISSION. IT WAS REMOVED PREVIOUSLY DUE TO REPORT THAT ROTOR	 NEEDLE WAS BOUNCING. IT WAS INSPECTED AND RELUBED AND NO INDICATION OF DEFECTS WERE REPORTED. IT WAS THEN REINSTALLED. 	WHEN IT WAS INSPECTED THE SECOND TIME AFTER FAILURE, IT WAS NOTED THAT IT HAD BEEN CORRODING FROM THE INSIDE OUT.			1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2004012700002	20040127	00002	EA  	2004	1	27	CA031214001      	1	20031202	G	5610	NP13932210	WINDOW          			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) RT SIDE WINDOW CRACKED DURING DESCENT. WINDOW REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012700003	20040127	00003	NE  	2004	1	27	CA031214002      	2	20031123	G	7320	4120T01P02	FMU             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					FUEL CONTROL	DEFECTIVE       	W				O				OTHER                   				W			INADEQUATE Q C            			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THERE WAS A L FADEC FAULT 1 STATUS MESSAGE.  LT FUEL FLOW DROPPED FROM 890 KG/HR TO 670 KG/HR LT N1 I	NCREASED TO 98 PERCENT, LT ENG FLAMEOUT CAUTION AND CONTIGNITION STATUS MESSAGES APPEARED.  MESSAGES THEN DISAPPEARED AN	D ENGINE RETURNED TO NORMAL.  FDR ANALYSIS REVEALED THAT THE ENGINE DID NOT FLAME OUT. IAW MFG RECOMMENDATION THE FMU (F	UEL METERING UNIT) HAS BEEN REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012700004	20040127	00004	EA  	2004	1	27	CA031215001      	2	20031029	G	8530	73772	COOLING JET     	AAR         		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	CYLINDER	SEPARATED       	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA								L58061			(CAN) PISTON COOLING JET BACKED OUT OF HOLE. BOUNCED AROUND INSIDE OF ENGINE BEFORE THE CRANKSHAFT PUSHED IT THROUGH THE	 TOP OF THE CASE					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004012700005	20040127	00005	CE  	2004	1	27	CA031215002      	1	20031210	G	2700	0510105325	CONTROL CABLE   			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  		FRAYED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CABLE INSPECTION REVILED WEAR & FRAYING AT THE POINT WERE THE CABLE CHANGES DIRECTION ENTERING THE FUSELAGE.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2004012700006	20040127	00006	NE  	2004	1	27	CA031216001      	2	20031212	G	7320	4120T01P02	FMU             			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					FUEL CONTROL	DEFECTIVE       	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			CR	CRUISE         	1			CA											(CAN) DURING CRUISE THE CREW SAW THE RT ENGINE EGT CLIMBING, THE CREW SHUT DOWN THE ENGINE. EGT HAD REACHED 936DEG FOR 1	0.9 SECS. THE AIRCRAFT LANDED WITHOUT FURTHER PROBLEM. THE FUEL METERING UNIT (FMU) WAS REPLACED AND THE AIRCRAFT RETURN	ED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004012700007	20040127	00007	CE  	2004	1	27	CA031216003      	1	20031117	G	7120	05131329	BRACKET         			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	ENG MNT ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE MOUNT TO FIREWALL 1/B  LT LOWER CHANNEL BRACKET FOUND CRACKED. REPLACED WITH NEW.						1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA	 
2004012700008	20040127	00008		2004	1	27	CA031216004      	4	20031212	G	2200		CONTROL UNIT    			CVAC  	580   	580         	2422806	WP  	ALLSN 	501D  	501D13D     	03004	GL  					AILERON	JAMMED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) ON FLT,  AUTO-PILOT WAS UNABLE TO CHANGE AC DIRECTION,  AUTO-PILOT WAS DISCONNECTED AND CREW DISCOVER THAT THEY WE	RE UNABLE TO MOVE AILERON CONTROL WHEEL. THEY MOVED TRIM AND SUDDENLY AILERON CONTROL WHEEL TURNED, CONTROL WHEEL DID NO	T JAM AGAIN. AFTER ARRIVAL, INVESTIGATION REVEALED THAT LT AILERON CONTROL (FUSELAGE) PRESSURE SEAL WAS COATED WITH A .7	500 INCH COAT OF ICE.  ICE WAS MELTED AND WATER DRYED. WE DISCOVERED THAT ONE CARGO CONTAINER WAS LOADED WITH SMALL AMOU	NT OF SNOW, WHICH MELTED AND DRIPPED UNDER FLOOR ON CONTROL CABLES ON THE LT SIDE. WE SEALED FLOOR PANEL 5 FEET FORWARD 	AND AFT OF CONTROL CABLES. AN INSP WAS CARRIED OUT FOR TWO FOLLOWING FLIGHTS AND NO ICE OR WATER WHERE FOUND IN AREA.	2	L	7	2 	4T	4	T	RT	        	E282				 
2004021700201	20040217	00201	NE  	2004	2	17	CA031216005      	2	20031211	G	7310	82820127101	TUBE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			37521					PCE120367			(CAN) TEARDOWN OF ENGINE FOR A HOT SECTION INSP.  FROM A/C NR 2 POS,  ENGINEER DISCOVERED STAINLESS STEEL TUBE ASSY, ENG	INE WASTE FUEL RETURN LINE P/N 82820127-101, CHAFFED. THE IPC, PSM 1-8-4, REF IS 71-70-00 FIG 10 ITEM NR 245 MM, PSM 1-8	-10, REF IS 71-00-02 FOR COMPONENT IN QUESTION. FOUND THAT IT WAS RUBBING AGAINST AFT FIREWALL INSTALLATION LOWER SECTIO	N AT STN XN.107.18,P/N 85411444-101 IPC REF IS 54-10-00 FIG 5 ITEM NR70.  FIX FOR THIS IS FUEL RETURN LINE NEEDS TO BE P	OSITIONED IN A MANNER THAT BOTH SECTIONS OF LINE ARE IN SAME HORIZONTAL PLANE, SHOULD BE AS CLOSE TO CASE DRAIN FITTING 	AS POSSIBLE.  IF THERE ARE ANY LINES FOUND WITH CHAFFING DAMAGE,WILL BE CHANGED OUT DEPENDING ON THE SEVERITY.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004012700009	20040127	00009	GL  	2004	1	27	CA031216006      	1	20031116	G	3240	GW41571253	CONTROL UNIT    			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					MLG BRAKES	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			CA											(CAN) AFTER TAKE OFF, (BRAKE FAULT) AND (GND LIFT DUMP) ADVISORY CAS MESSAGE WERE POSTED UPON GEAR RETRACTION AND REMAIN	 POSTED THROUGHOUT THE FLIGHT.  ON TOUCHED DOWN, THE PILOT NOTICED THAT THERE WAS NO DECELERATION FELT WHEN APPLYING THE	 PEDALS.  THE THRUST REVERSERS AND EMERGENCY BRAKE WERE USED TO STOP THE AIRCRAFT.  TROUBLESHOOTING REVEALED THAT THE BR	AKE CONTROL UNIT (BCU) WAS SHOWING AN (INTERNAL FAILURE).  THE BCU WAS REPLACED, THE SYSTEM TESTED FULLY OPERATIONAL AND	 THE AIRCRAFT WAS RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
2004012700010	20040127	00010	NE  	2004	1	27	CA031216007      	2	20031216	G	7310	0301007720	LINE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					ENGINE FUEL	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								9631			(CAN) PILOT ATTEMPTED A START AND THE ENGINE FAILED TO ACCELERATE.  INITIAL T4 INDICATION WAS VERY LOW AND THE T4 DID NO	T INCREASE AS THE THROTTLE WAS MOVED FORWARD DURING THE STARTING SEQUENCE.  THE PILOT ABORTED THE START. UPON INSPECTION	 THE PILOT NOTICED FUEL LEAKING FROM THE ENGINE OVERBOARD DRAIN.  THE PILOT LIFTED THE ENGINE COWLING AND TRACED THE FUE	L LEAKAGE TO THE RT FUEL INJECTOR PIPE. THE PIPE FAILED BEHIND THE FLARE AT THE INJECTOR JUNCTION.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004012700011	20040127	00011	SW  	2004	1	27	CA031217001      	1	20031215	G	2750	21903	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FLAP HANDLE	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE COMPANIES STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), THE FLAP CABLE ATTACHED TO THE FLAP HANDLE W	AS FOUND FRAYED AS IT STARTS TO ENTER AND TURN AROUND THE SECTOR (P/N 3-1128).  THERE WAS NO INDICATION OF FRAYING UNTIL	 THE CABLE WAS REMOVED AND INSPECTED.  IT WAS ESTIMATED THAT THE CABLE WAS FRAYED 70 PERCENT.				1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2004012700012	20040127	00012	EA  	2004	1	27	CA031217002      	2	20031216	G	8520	ST203	RING            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	PISTONS	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA								RL1657939			(CAN) REPORTED ENGINE BACKFIRING AT LOW RPM. CARRIED OUT COMPRESSION TEST ON ALL FOUR CYLINDERS. COMPRESSIONS WERE AS FO	LLOWS, NR 1 70/80, NR 2, 72/80, NR 3, 60/80, NR 4, 74/80.  REMOVED NR 3 CYLINDER AND FOUND MARKS IN CYLINDER AND RINGS W	ERE EXCESSIVELY SHARPENED FOR ONLY 51.  2HRS TT. THROUGH CONVERSATION WITH THE ENGINE SHOP THEY HAVE FIGURED THE RINGS F	AILED. ALL FOUR CYLINDERS ARE BEING REMOVED AND REPLACED WITH DIFFERENT RINGS AND COMPLETE CYLINDER ASSY. THIS SDR IS AL	SO BEING FORWARDED TO THE ENGINE SHOP AND WOULD SUSPECT IT BEING PASSED ON TO THE FAA ALONG WITH THERE OWN PARTS FAILURE	 NOTIFICATION SYSTEM.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004012700013	20040127	00013	NE  	2004	1	27	CA031217003      	2	20031213	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) THRUST LOSS RT ENGINE ON CLIMB ACCOMPANIED BY VIB ICON.  QRH CARRIED OUT, ENGINE SECURED, WAITING FOR REPORT.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012700014	20040127	00014	NE  	2004	1	27	CA031217004      	2	20031216	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  						MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) LOUD BANG, N1 VIB, N2 VIB AND ITT MAX TEMP NEEDLE PEGGED.  ENGINE SHUT DOWN.  AWAITING REPORT.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012700015	20040127	00015	EA  	2004	1	27	CA031217005      	1	20031206	G	4920		ENGINE          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) APU ENGINE FAILED FOUND MOST OF THE EXHAUST TURBINE ON RAMP,  AWAITING REPORT.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012700141	20040127	00141	NM  	2004	1	27	CA031217006      	1	20030829	G	3297	461651	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG	SHORTED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) UPON LANDING PILOT GOT IB ANTI SKID CAUTION LIGHT ON FOR APPROX. 5 SEC. AFTER LANDING. CAUTION LIGHT THEN DISAPPEA	RED. WHEN PARKED PILOT FOUND RT MAIN INNER TIRE TO BE TOTALLY BLOWN. PAX TOLD US THAT THEY SAW A TIRE THAT NEVER HAD ANY	 ROTATION AND EXPLODED SHORTLY AFTER LANDING ROLL WAS STARTED. WHEELS NR 3 AND NR 4 REPLACED IAW AMM 32-41-01. AIRCRAFT 	WAS THEN RELEASED FOR FLIGHT IAW MEL 32-40-2. DURING FURTHER TROUBLESHOOTING WIRES TO RT IB/OB WHEEL SPEED TRANSDUCERS F	OUND SHORTED TO GROUND. WIRES REPLACED AND SYSTEM TESTED IAW AMM 32-46-00.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004012700142	20040127	00142		2004	1	27	CA031217007      	4	20031210	G	2297		WIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	AUTOPILOT SYSTEM	CHAFED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) MULTIPLE FAIL MESSAGES, YD NOT CENTER, AIR DATA FAIL AND ATT DATA FAIL. FOUND CHAFED DATA BUSS WIRES BEHIND MFD2 C	AUSED BY 3428-P1-A3 CONNECTOR BACKSHELL.  SPLICE REPAIRED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004021700202	20040217	00202	CE  	2004	2	17	CA031217008      	1	20031209	G	2520	5045164038088	RESTRAINT       			CESSNA	182   	T182T       	2072738	CE  	LYC   	O540  	TIO540AK1A  		EA  	MCAULY	3D36C	B3D36C424   	GL  	PAX CABIN	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION IT WAS NOTICED THAT BOTH REAR SEAT RESTRAINT SYSTEM INERTIA REELS WOULD INTERMITTENTLY LOCK AND 	NOT ALLOW BELT TO EXTEND. IT WAS DECIDED THAT IF RESTRAINTS WERE RELEASED IN FLIGHT IT MAY NOT BE POSSIBLE TO REFASTEN T	HEM SO BOTH UNITS WERE REPLACED. PARTS WILL BE RETURNED TO THE MANUFACTURER AS THE AIRCRAFT IS STILL ON WARRANTY.  OUR M	FG TECH. SUPPORT PERSON WAS ADVISED OF THIS PART DEFECT.			1	H	7	1 	3O	3	O	NT	3A13    		5	C	P58GL	 
2004021700203	20040217	00203	NM  	2004	2	17	CA031218001      	1	20031217	G	3231	10605801	SEQUENCE VALVE  			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG DOOR	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) JUST AS AC STARTED TO TAXI CREW NOTED LOSS OF ALL HYD FLUID IN SYSTEM A. A/C SHUT DOWN AND PUSHED BACK INTO PARKIN	G SPOT.  LEAK DETERMINED TO BE COMING FROM THE RT MLG DOOR SEQUENCE VALVE.  BODY OF VALVE FOUND SPLIT.  A/C UNLOADED, VA	LVE CHANGED, GEAR SWINGS CARRIED OUT AND A/C RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2004021700204	20040217	00204	NM  	2004	2	17	CA031218002      	1	20031216	G	6120	697073001A	PITCH CONTROL   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROPELLER	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				E	W		VIBRATION/BUFFET          	INADEQUATE Q C            		CR	CRUISE         	1			CA											(CAN) EVERY 20 SECONDS IN FLIGHT, PROP SPEED DROPS BY 10 RPM AND ALL OTHER ENGINE PARAMETERS ALSO DROP. CREW COULD FEEL 	THE DROP IN POWER, NOT AN INDICATION PROBLEM. FADEC WAS REPLACED, ON GROUND HIGH POWER RUNS NO DEFECT NOTICED. TAKE-OFF 	WAS FINE, BUT ON CLIMB, PARAMETER FLUCTUATIONS RESURFACED EVERY 20 SECS. NR 1 ENGINE SHUTDOWN AND AIRCRAFT RETURNED TO B	ACK BASE. PCU CHANGED AND CHECK FLIGHT WAS SUCCESSFUL, AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004021700205	20040217	00205	CE  	2004	2	17	CA031218003      	1	20031129	G	5210		LATCH           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	PAX DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER COMPLETING FLIGHT AND TAXIING THE PILOT WAS UNABLE TO OPEN THE AIRSTAIR DOOR TO DISEMBARK PASSENGERS. THEY W	ERE REQUIRED TO EXIT THE AIRPLANE USING THE OVER WING EMERGENCY EXIT.  BEFORE MAINTENANCE PERSONNEL WERE ABLE TO ARRIVE 	ON THE SCENE THE PILOT HAD MANAGED TO OPEN THE AIRSTAIR DOOR BY USING A SCREWDRIVER TO RELEASE THE DOOR CAM MECHANISMS. 	MAINTENANCE INVESTIGATED AND FOUND THAT THE INTERNAL DOOR CABLE HAD BROKEN AND THEREFORE THE DOOR COULD NOT BE OPENED NO	RMALLY.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2004031500075	20040315	00075	EA  	2004	3	15	CA031218004      	1	20031217	G	2731	C3CF4187	ROD             			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	ELEVATOR TAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROD HAS BEEN DISCOVERED TO BE WORN.						1	H	7	1 	3R	3	R	 	A815    	E142	6	C	P719	 
2004021700206	20040217	00206	NM  	2004	2	17	CA031218005      	1	20031204	G	3070		RIBBON HEATER   			BOEING	767   	767233      	1385113	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					WATER LINE	BURNED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) DURING THE CURRENT MAINT VISIT ON VA704 A BURNED HEATER TAPE HAS BEEN DISCOVERED. THE 7.1 FOOT LONG DRAIN LINE ELE	MENT IS THE HEATER B193 (COX P/N 3051-01 MODEL 110-7.1-71) LOCATED AT BSTA 1560, WL 174, RBL 62. IN THIS CASE, HEATER AN	D PROTECTIVE TAPE EXHIBITS HEAT DAMAGE ALONG ITS ENTIRE LENGTH.  NOTE THAT ADJACENT INSULATION BLANKET MATERIAL ON BULKH	EAD ALSO EXHIBITS HEAT DAMAGE. REF /L/INDICATES THAT THE REF /F/ RELEASE WITH NON-ESSENTIAL HEATER DEACTIVATION INSTRUCT	IONS IS STILL SEVERAL MONTHS AWAY. QUITE ANXIOUS TO DETERMINE WHICH LINES MAY BE DEACTIVATED.		2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2004021700207	20040217	00207	EA  	2004	2	17	CA031218006      	1	20031217	G	2731	C3CF4187	ROD             			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	STABILATOR	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE ROD HAS FOUND TO BE A PROBLEM IN THIS TYPE OF A/C SHOULD BE INSPECTED IN CONJUNCTION WITH THE STABILATOR TRIM 	JACK AT 400 HRS.					1	H	7	1 	3R	3	R	 	A815    	E142	6	C	P719	 
2004021700208	20040217	00208	EU  	2004	2	17	CA031218007      	1	20031217	G	7997	K11A24NK10A24	WIRE            	DEUTSCH     		PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CHIP DETECTOR	FRAYED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) INTERMITTENT CHIP LIGHT IN FLIGHT. THE INSULATION CRACKED RADIALLY IN RUBBER AT STRAIN RELIEF, THE FRAYING OF THE 	WIRES CAUSED THEM TO TOUCH INTERMITTENTLY CAUSING THE CHIP LIGHT TO FLICKER. WIRE INSULATION REPAIRED.  A/C RETURNED TO 	SERVICE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004021700209	20040217	00209	NM  	2004	2	17	CA031218008      	1	20031212	G	5753	69378535	FITTING         			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FLAP TRACK	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON WALK AROUND, MAINTENANCE FOUND THE RT OB FOREFLAP OB LINK BROKEN. MAINTENANCE REPLACED THE FOREFLAP AND AIRCRAF	T RETURNED TO SERVICE. CAUSE UNKNOWN. WILL UPDATE IF ADDITIONAL INFORMATION AVAILABLE.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2004031500079	20040315	00079	CE  	2004	3	15	CA031219001      	1	20031217	G	5511	0432001646	RIB             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE STABILIZER WAS REMOVED FROM THE AIRCRAFT TO PERFORM OTHER UNRELATED REPAIRS WHEN IT WAS DISCOVERED THAT BOTH O	F THE IB LEADING EDGE NOSE RIBS WERE CRACKED.  THE CRACKS APPEAR ON THE FLANGE ADJACENT TO THE MOST AFT ATTACHING TABS. 	 CRACKS WERE FOUND TO BE .1250 TO .2500 INCH IN LENGTH AND FOUND AT THE TOP AND BOTTOM POSITIONS.  WITH THE STABILIZER O	FF WE REPLACED BOTH RIBS WITH NEW PARTS. THIS DEFECT SEEMS TO BE A COMMON FINDING FOR OPERATORS OF 152 SERIES AIRCRAFT.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2004031500080	20040315	00080	GL  	2004	3	15	CA031222001      	1	20031217	G	3246	3006202	WHEEL           			DHAV  	DH82  	DH82        	2801000	GL  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	MLG	FRACTURED       	W				D				RETURN TO BLOCK         				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA			24258								(CAN) TAXIING FOR TAKE-OFF WHEN THE OB WHEEL OF THE LT MLG SUFFERED A STRUCTURAL FRACTURE.  DURING THE TAXI, THE FLIGHT 	CREW HEARD A LOUD BANG FROM THE AIRCRAFT, AND DIRECTLY FOLLOWING, THE AIR TRAFFIC CONTROL RADIOED THE CREW TO ADVISE THA	T THERE WERE SIGNS OF SMOKE EMANATING FROM THE LT  OF THE AIRCRAFT.				1	Q	7	1 	3I	4	T	 	EXPA1Q71	E20NE	6	C	P7NE	 
2004021700210	20040217	00210	NM  	2004	2	17	CA031222002      	1	20031219	G	2751		SKIN            			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15A     	52051	NE  					AILERON	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING LOADING OF CARGO, THE DOLLY AND CONTAINER UNLATCHED AND ROLLED UNDER THE LT WING SCORING THE PAINT AND CREA	SING THE LT OB AILERON LOWER SURFACE.  THE RESULTING DAMAGE FOUND 2 CREASES ON THE AILERON WITH 1 AT 14 INCHES LONG AND 	THE OTHER AT 7 INCHES LONG.  ANOTHER CREASE WAS NOTED ON THE ACCESS PANEL AT 14 INCHES LONG.  THE DAMAGES WERE ASSESSED 	AND WERE FOUND WITHIN LIMITS IAW SRM 57-50-5.  NO PROBLEMS DURING SUBSEQUENT FLIGHT.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2004021800001	20040218	00001	WP  	2004	2	18	CA031222003      	1	20031021	G	6520	369D25430	GEAR            	HUGHES      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0065					(CAN) UNIT RECEIVED TO INSPECT FOR REPORTED METAL GEN. (9 PREVIOUS REPORTS) REPAIRED BY FACILITY FAA REPAIR STATION 6 TI	ME (10 BEARINGS REPLACED) THEN OH.  LAST REPORT WAS 104.6 HRS. AFTER OH, WHEN IT WAS OPENED THE INTERIOR HAD A THICK SLU	DGE THROUGHOUT.  I/P AND O/P SPACERS FOUND SPINNING AND /OR DAMAGED.  O/P GEAR WAS BROKEN AT ALIGNMENT BEARING JOURNAL (	ALIGNMENT BEARING STILL ON BROKEN PIECE)			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004021800002	20040218	00002	WP  	2004	2	18	CA031222004      	1	20031112	G	6320	369A535051	CLUTCH          			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UNIT RECEIVED TO REINSPECT AFTER CUSTOMER REPORTED OIL LEAK FROM CLUTCH, (NEAR TO DRY) TO FACILITY FAA REPAIR STAT	ION (THEY O/H THIS UNIT 88 HRS AGO).  THIS FACILITY REPORTED TO THE CUSTOMER THAT THEY CHANGED THE SEAL, AND THAT WAS AL	L THAT WAS NEEDED.  CUSTOMER RECEIVED UNIT AND NOTICED THE OIL IN THE CLUTCH WAS STILL BLACK THEY SHIPPED IT TO OUR FACI	LITY.  UPON RECEIPT,  REMAINING OIL WAS DRAINED (THICK BLACK AND FULL OF METAL PARTICLES), UNIT DISASSEMBLED.  BOTH LARG	E AND SMALL OIL BEARINGS WERE FOUND PITTED AND SPALLED, REQUIRED REPLACEMENT.  ALSO THE OUTER RACE SPLINES WERE NOTIBLY 	WORN (MEASURED AT 1.3050 INCH.  MDHI COMPONENT O/H MANUEL LIMIT IS 1.3054 INCH), IT ALSO REQUIRED REPLACEMENT.	1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004021800003	20040218	00003	WP  	2004	2	18	CA031222005      	1	20031118	G	6520	369D25400	GEARBOX         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UNIT RECEIVED TO INSPECT FOR REPORTED METAL GENERATION. THE FOLLOWING WAS FOUND AT DISASSEMBLY. I/P GEAR 369D25434	 U/S DUE TO SEVERE CORROSION PITS, O/P GEAR 369D 25430 ALSO PITTED BUT POLISHABLE. THE DUPLEX BEARINGS 369D25420 HAD NO 	CLAMP UP(.001-.003 INCH REQUIRED), THEY SPUN IN THE RETAINER 369D25409. ALSO THE O/P ALIGN . BEARING 369D25419 WAS LOOSE	 IN ITS' RETAINER (SPINNING). THIS UNIT WAS O/H THEN REPAIRED FOR METAL GEN. 3 TIMES BY REPAIR FACILITY FAA STATION.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004031500081	20040315	00081		2004	3	15	CA031222006      	4	20031215	G	8300		GEARBOX         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					ACCESSORY	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		DE	DESCENT        	1			CA			10813								(CAN) ON DESCENT FROM 310 TO 290, NR 1 ENGINE ABRUPTLY SHUT DOWN WITH A LOUD VIBRATION NOISE. 20 MINUTES OUT, NR 1 ENGIN	E SHUT DOWN OWN IT'S OWN WITH A LOUD VIBRATION. ENGINE WAS SECURED AND THE AC LANDED WITHOUT INCIDENT. MAINTENANCE INSPE	CTED THE AIRCRAFT AND FOUND NO OBVIOUS PROBLEMS. ATTEMPTED TO START. DID NOT SEE A RISE IN NR 2, ENGINE WOULD NOT START.	 MUCH METAL FOUND IN FILTERS.  ACCESSORY GEAR BOX WAS NOT SPINNING.  ENGINE REMOVED AND REPLACED. GEAR BOX INPUT'S ROTAT	E, BUT NO ACCESSORY GEARS TURN.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004021800004	20040218	00004		2004	2	18	CA031223001      	4	20031210	G	3460	6225798022	CONTROL PANEL   	COLLINS     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	FMC	ODOR            	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA			10833			4236					(CAN) ON FINAL APPROACH THE CREW SMELLED A STRANGE ODOR IN COCKPIT. INVESTIGATION BY MAINTENANCE REVEALED THAT THE ODOR 	CAME FROM NR 1 FLIGHT CONTROL PANEL.  IT WAS REPLACED ALONG WITH THE NR 1 FLIGHT COMPUTER WITH NO FURTHER REOCCURRENCES.	  BOTH UNITS WHERE FORWARDED TO REPAIR SHOP AND THEN FURTHER TO ORIGINAL MANUFACTURER.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2004021800005	20040218	00005	EA  	2004	2	18	CA031223003      	1	20031222	G	2421	AE2132MK6	SHAFT           	LUCAS       		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	AC GENERATOR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33338			2028					(CAN) AFTER FLIGHT MAINTENANCE NOTICED AN OIL LEAK FROM THE NR 2 NACELLE, FURTHER INVESTIGATION FOUND THE NR 2 AC GENERA	TOR SHAFT SHEARED. THE FLIGHT CREW HAD NOT NOTICED ANY FAILURES SINCE IN THE NORMAL OPERATION MODE THIS AC GEN IS IN STA	NDBY AND ONLY WORKS IF AN OTHER GEN FAILS. THE GEN WAS REMOVED AND THE AIRCRAFT RETURNED TO SERVICE.				2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2004031500096	20040315	00096	WP  	2004	3	15	CA031223004      	1	20031021	G	6520	369D25400	GEARBOX         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UNIT RECEIVED AFTER REPORT OF METAL GENERATION (UNIT INSPECTED AND REPORTED NO DEFECTS AND RETURNED).  CUSTOMER WA	S NOT PLEASED AS THEY HAVE REPORTED METAL GEN.  IN THIS UNIT 5 TIMES PREVIOUS GEARBOX WAS NOT INSTALLED ON A/C IT WAS SH	IPPED TO OUR FACILITY FOR A 2ND OPINION.  PICTURES WERE TAKEN AT DISASSEMBLY AND THE FOLLOWING WAS FOUND:  BOTH I/P AND 	O/P SPACER WERE DAMAGED FROM SPINNING, PREVIOUS REMOVALS, THE LARGE I/P BEARING WAS PITTED.  PARTS REPLACED WERE SHOWN T	O AIRWORTHINESS INSPECTOR.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004031500097	20040315	00097	WP  	2004	3	15	CA031223005      	1	20031212	G	6520	369D25434	GEAR            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					T/R GEARBOX	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						HD1007					(CAN) CUSTOMER REPORTED METAL GEN. 51.2 HRS AFTER LAST REPAIR. REQUESTED THE RETURN OF THIS UNIT, AFTER DISASSEMBLY IT W	AS NOTED THE I/P SPACER WAS WORN AGAIN, AN O/H DIMENSION CHECK (NOT REQUIRED AT THIS TIME) WAS CARRIED OUT AND THE I/P B	EARING JOURNAL IS BELOW DIMENSION. AS THIS UNIT HAS BEEN REPAIRED 6 TIMES SINCE O/H WAS CARRIED OUT. THE I/P GEAR IS SUS	PECTED FOR BEING UNDER DIM FOR SOME TIME. THE GEAR HAS BEEN SENT TO AN APPROVED FACILITY TO CARRY OUT THE NICKEL PLATING	 REQUIRED.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004022300002	20040223	00002	EU  	2004	2	23	CA031223006      	2	20031219	G	8530	922230	SOCKET          	BOMBDR      		DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912F3  	 	EU  	HOFMAN	HOV352	HOV352F     	NE  	CYLINDER HEAD	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) A CRACKED DEVELOPED AROUND APPROX. .5000 THE CIRCUMFERENCE OF THE SOCKET ABOUT .2500 INCH BEYOND THE TREADS. THE L	OCATION OF THE CRACK IS APPROX. COINCIDENTAL WITH THE START OF THE BEND IN THE SOCKET. COOLANT WAS NOTED LEAKING FROM TH	E CRACK.				1	L	7	1 	3O	3	O	NT	TA4CH   	E00051EN	5	C	TP5BO	 
2006061200425	20060612	00425	EU  	2006	6	12	CA031224001      	1	20031216	G	2697		WIRE HARNESS    			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					SMOKE DETECTOR	CHAFED          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											F/A NOTICED SPARK FROM OXYGEN PNL.  A/C REMAINED IN SERV SEVERAL DAYS.  UPON INSPECT, WIRE BUNDLE DIRECTLY ABOVE LAV "E"	 SMOKE DETECT FOUND CHAFFED ON SMOKE DETECT.  INSPECT FOUND ROUTING OF WIRE BUNDLE WITH LITTLE CLEARANCE BETWEEN BUNDLE 	AND DETECTOR AND REPEAT OF INCIDENT WITH MORE SERIOUS CONSEQUENCES COULD BE LIKELY.  WIRED BUNDLE RECEIVES IT'S POWER FR	OM 2000 C/B PANEL AND SUPPLIES PWR TO AFT CARGO LOADING SYS, AFT DRAIN MAST AND VARIOUS RIBBON HEATERS, ETC.  FEW A/C WE	RE INSPECTED 401, 408, 410, 219, 224 HERE.  NO A/C HAD WIRE BUNDLE TOUCHING SMOKE DETECTOR.  HOWEVER, DISTANCE BETWEEN B	UNDLE AND SMOKE DETECTOR IS NEVER SAME.  NOTICED FLEXIBLE EXTRACT DUCT IS NEVER INSTALLED SAME WAY.	2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2005011200001	20050112	00001	WP  	2005	1	12	CA031224002      	2	20031223	G	7210	8679225	CASE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					PLANETARY GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				17040							(CAN) ACRFT RETURNED WITH A LOW OIL PRESS. ON RESEARCHING ENG TRENDS, OIL PRESS HAD BEEN STEADILY DECLINING FOR APPROX A	 MONTH AT 1-2 PSI A DAY. PROBLEM WASN`T NOTICED BY FLT CREW UNTIL A SUBSTANTIAL DROP ON DAY OF INCIDENT. OIL PRESSURE WO	ULD ONLY DROP ON A HIGHER POWER SETTING. MX REPLACED SEVERAL ENG OIL REGULATING COMPONENTS IN AN ATTEMPT TO REPAIR PROBL	EM. DURING RUN-UP AT HIGH POWER OIL PRESS LOW & TORQUE BEGAN TO FLUCTUATE. A FEW OPS TESTS ACCOMPLISHED TO ISOLATE PROBL	EM. ENG PROBLEM DIFFICULT TO DIAGNOSE. AS PRECAUTION REDUCTION GEAR CASE DISASSEMBLED FOR INSPECT OF OIL SYS. DURING DIS	ASSEMBLY, FOUND PLANETARY GEAR SYS CARRIER CRACKED AROUND ENTIRE CIRCUMFERENCE. SUSPECT THAT DAMAGE WAS CAUSED BY AN OVE	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2004031500111	20040315	00111	EA  	2004	3	15	CA031224003      	2	20031124	G	7200	3028004	ENGINE          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  						MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE40252			(CAN) ENGINE S/N PCE40252 WAS SENT FOR METAL IN OIL. ENGINE WAS DISSASSEMBLED AND IT WAS FOUND THAT THE NR 2 BEARING ROL	LER CAGE SILVER PLATE HAD FLAKED OFF.  MFG HAS A SIL NR PT6A-106 ON THIS CONDITION. THIS ENGINE WAS REPAIRED IAW MFG LAT	EST SPECIFICATIONS AND RETURNED TO SERVICE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2004031500112	20040315	00112		2004	3	15	CA031229001      	4	20031228	G	3197	HJ2A20	WIRE            			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					INSTRU PANEL	BURNED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) WIRE NR HJ2A20 CHAFED AGAINST MOUNT FOR KMD850 MFD DISPLAY. ECU SELECTED TO ON AND BURNING ODOR NOTICED, ECU SELEC	TED TO OFF AND CB WAS NOTED POPPED. SIX WIRES DAMAGED AS A RESULT OF EXCESSIVE HEAT. DAMAGED SECTION OF WIRE REMOVED AND	 REPAIRED. THREE OTHER WIRES REPAIRED FOR CHAFING IN AN UNRELATED POSITION.				1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2004031500121	20040315	00121	EA  	2004	3	15	CA040102003      	1	20031112	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) LT WINDSHIELD ARCING IN LT CORNER AND PROPAGATING OUTWARDS. UPON LANDING, FOUND LT WINDSHIELD WAS ALSO CRACKED. RE	PLACED LT WINDSHIELD.  WINDSHIELD REPLACED. AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004031500123	20040315	00123	CE  	2004	3	15	CA040103002      	1	20031205	G	2435	M230881320	BRUSHES         	LEARSIEGLER 		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	STARTER GEN	WORN            	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						96189					(CAN) COULD NOT GET LT GENERATOR ON LINE. MAINTENANCE REPLACED STARTER GENERATOR BRUSH INSPECTION ON REMOVED UNIT SHOWED	 EXCESSIVE WEAR.  ONLY 755.9 HRS SINCE NEW. STARTER GEN OH 1500 HRS. BRUSH INSP EVERY 400 HRS. NORMAL BRUSH LIFE 2200 HR	S BUT ALWAYS REPLACED AT O/H.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2004031500124	20040315	00124	CE  	2004	3	15	CA040103003      	1	20031114	G	2435	M230881320	BRUSHES         	LEARSIEGLER 		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	STARTER GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						96188					(CAN) DURING ROUTINE BRUSH CHECK, BRUSHES FOUND BELOW MINIMUM LIMIT. STARTER GEN REPLACED. STARTER GEN O/H 1500 HRS NORM	AL BRUSH LIFE 2200 HRS ALWAYS REPLACED AT OH.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2004031500125	20040315	00125	CE  	2004	3	15	CA040103004      	1	20031205	G	2435	M230881320	BRUSHES         	LEARSIEGLER 		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	STARTER GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						96199					(CAN) DURING ROUTINE BRUSH INSPECTION,  MAINTENANCE FOUND STARTER GEN BRUSHES BELOW MINIMUM LIMITS. STARTER GEN REPLACED	.  NORMAL BRUSH LIFE 2200 HRS STARTER GEN OH 1500 HRS. BRUSHES ALWAYS REPLACED AT OH.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2004031500142	20040315	00142	SO  	2004	3	15	CA040105002      	1	20030817	G	2913		SHAFT           	AIRBORNE    		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD PUMP	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA						3437					(CAN) AFTER LANDING THE PILOT SHUTDOWN THE RT ENGINE SO HE COULD CHECK THE LT HYDRAULIC PUMP WHICH HE DID BY PUTTING THE	 GEAR HANDLE DOWN, GEAR HANDLE DID NOT COME BACK TO NEUTRAL. MAINTENANCE REMOVED THE HYDRAULIC PUMP AND FOUND THE SHAFT 	SHEARED, ORDERED AN OVERHAUL AND INSTALLED BEFORE NEXT FLT.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004031500143	20040315	00143	EU  	2004	3	15	CA040105003      	1	20031116	G	5310	137978C5	DOOR FRAME      	BAG         		BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	PAX DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23564			712					(CAN) DURING ROUTINE INSPECTION, A .1250 INCH CRACK WAS FOUND IN THE CABIN DOOR FRAME AT THE UPPER FORWARD DRAW BOLT. TH	ROUGH CONTACT WITH MFG AND OTHER LOCAL VENDORS, IT WAS DETERMINED TO BE MORE COST EFFECTIVE TO REPLACE THE ENTIRE DOOR A	SSEMBLY RATHER THAN JUST THE FRAME.   AS THIS CRACK WAS DISCOVERED BY MAINTENANCE CREW DURING A GROUND INSPECTION. THE D	OOR WAS REPLACED AND DEFECT RECTIFIED WITHOUT ANY INCIDENT.			2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2004031500144	20040315	00144	CE  	2004	3	15	CA040105004      	1	20031216	G	3213	519400113	STRUT           			CESSNA	421   	421A        	2076012	CE  	CONT  	O520  	GTSIO520D   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) LT MAIN LANDING GEAR COLLAPSED UPON TOUCH-DOWN WITH ALL 3 GREEN LIGHTS ON.  FOUND DOWN LOCK ARM  BROKEN AWAY FROM 	LUG ON TOP END OF STRUT. LOCK ARM NORMALLY HOLDS SIDE BRACE IN PLACE AND ACTUATES DOWN SWITCH. REPLACED COMPLETE MAIN LA	NDING GEAR ASSEMBLY AND RETRACT MECHANISM WITH SERVICEABLE COMPONENTS.				1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2004031500145	20040315	00145	EU  	2004	3	15	CA040105005      	1	20031205	G	7170	MY20515108003	DRAIN LINE      			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					ENGINE	CHAFED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA								2454427			(CAN) NR 2 ENGINE FIRE WARNING MOMENTARILY SOUNDED ON TAKEOFF.  UPON INVESTIGATION THE EP CAN DRAIN LINE WAS FOUND WITH 	A HOLE IN IT, DUE TO THE STAINLESS STEEL OIL TORCH VENT LINE CHAFING AGAINST THE ALUMINUM DRAIN LINE. ENGINE INSPECTED F	OR DAMAGE, DAMAGED DRAIN LINE REPLACED.  FIRE SYSTEM FUNCTION TESTED AND ENGINE GROUND RUN COMPLETED, AIRCRAFT RETURNED 	TO SERVICE.  QUALITY BULLETIN ISSUED TO MAINTENANCE BASES FOR INSPECTION OF ALL E.P. CAN DRAIN LINES AND REPLACEMENT OF 	ANY DAMAGED LINES OR PORTS FOUND.		2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2004031500146	20040315	00146	NM  	2004	3	15	CA040105006      	1	20031218	G	3230		CABLE           			DHAV  	DHC8  	DHC8301     	1386003	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NLG RELEASE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17222								(CAN) AN OPERATOR REPORTED FINDING A BROKEN NLG ALTERNATE RELEASE CABLE AT THE TEE HANDLE DURING OVERNIGHT SERVICING. CA	BLE REPLACED AND A/C RETURNED TO SERVICE. SB 8-32-146 HAS NOT BEEN COMPLETED ON THIS A/C, WHICH ADDRESSES THIS ISSUE. RE	LATED ISAR 96-07.  AD PENDING.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2004031500147	20040315	00147	CE  	2004	3	15	CA040105007      	1	20031203	G	2700	0510105325	CONTROL CABLE   			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  		FRAYED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CABLE INSPECTION REVEALED WEAR AT THE POINT WHERE THE CABLE CHANGES DIRECTION ENTERING THE FUSELAGE.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2004031500166	20040315	00166	SO  	2004	3	15	CA040106003      	1	20031219	G	3700		SHAFT           	AIRBORNE    		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	DRY AIR PUMP	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						22633					(CAN) DURING THE LAST FLIGHT OF THE DAY THE LT INDICATOR LIGHT ON THE INSTRUMENT PANEL CAME ON, INDICATING THAT THE VACU	UM PUMP HAD FAILED.  AFTER LANDING,  MAINTENANCE FOUND THAT THE SHAFT HAD BROKEN. RECEIVED OH PUMP NEXT MORNING INSTALLE	D, GROUND RUN NO FAULTS FOUND.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004031500167	20040315	00167	CE  	2004	3	15	CA040106004      	1	20031219	G	5610	71286	WINDOW          			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O320  	IO320E1A    	41508	EA  	HARTZL	HCC2Y	HCC2YL1     	GL  	COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) TOP WINDOW (SKY LIGHT) SHATTERED AND BROKE AWAY AFTER LEVELLING OFF FROM DOING A CUBAN EIGHT.						1	H	7	1 	3O	3	O	 	A21CE   	1E12	5	C	P920	 
2004031500168	20040315	00168	SO  	2004	3	15	CA040106005      	1	20031209	G	3260	4195200	DOWNLOCK        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	MLG	INOPERATIVE     	W				L				ABORTED APPROACH        				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) AIRCRAFT WAS PREPARING TO LAND, PILOT SELECTED GEAR DOWN, ONLY THE NOSE AND RT GEAR HAD A LOCK INDICATION, UNSAFE 	GEAR INDICATION.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2004031500181	20040315	00181	SO  	2004	3	15	CA040106006      	1	20031231	G	6123		LATCH           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									DJ8460A		(CAN) ON ENGINE SHUT DOWN RT PROP WENT TO FEATHER. ENGINE WAS GROUND RUN AND MAX RPM WAS ONLY 1900. MAINTENANCE REPLACED	 PROPELLER AND RETURNED AC TO SERVICE. PROP BLADE LATCHES ARE PRESUMED TO BE THE PROBLEM. PROP IS BEING SENT TO REPAIR S	HOP.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004031500182	20040315	00182	SO  	2004	3	15	CA040106007      	2	20031121	G	7414	10790206	MAGNETO         			CESSNA	337   	337C        	2075712	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C61   	GL  	ENGINE	DAMAGED         	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) FRONT ENGINE WOULD NOT RUN WHEN LT SETTING WAS SELECTED DURING GROUND RUN UP. IT WAS LATER DISCOVERED THAT THE LT 	MAGNETO NOISE SUPRESSOR WAS ALSO DEFECTIVE, P/N A293.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2004031500184	20040315	00184	GL  	2004	3	15	CA040106009      	3	20031229	G	6114	C130195	CLAMP           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED CLAMP NOT DISCOVERED UNTIL THE OVERHAUL.  PART MPI INSPECTED IAW ASTM-E-1444 WHEN FOUND.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2004031500185	20040315	00185	GL  	2004	3	15	CA040106010      	3	20031229	G	6114	A1851T	BEARING RACE    			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BEARING RACE CRACKED, DISCOVERED AT OVERHAUL, DURING THE NDT PROCESS.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2004031500187	20040315	00187	WP  	2004	3	15	CA040107001      	1	20031126	G	7830	M6335421	BALL JOINT      			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					THRUST REVERSER	WORN            	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) THRUST REVERSER FOLLOW-UP CABLE FOUND DETACHED. BALL JOINT CONNECTED TO ROD FOUND DISMANTLED FROM ITS JOINT SHELL.						2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004032500030	20040325	00030	EA  	2004	3	25	CA040107003      	2	20031216	G	7414	10400405	DISTRIBUTOR GEAR	BENDIX      		PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAGNETO	BROKEN          	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA						A32562					(CAN) 20 TEETH BROKEN OFF DISTRIBUTOR GEAR ASSEMBLY AND THE DISTRIBUTOR GEAR ELECTRODE BROKEN OFF. FOLLOWING INSTRUCTION	S OF MFG SB 658 FOR CORRECT PRACTICES FOR MAGNETO INSTALLATION ON ENGINE WILL ELEMINATE THE PROBLEM.					1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2004032500031	20040325	00031	EA  	2004	3	25	CA040107004      	2	20031222	G	7414	10400405	DISTRIBUTOR GEAR	BENDIX      		PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAGNETO	BROKEN          	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						A32562					(CAN) 8 TEETH BROKEN OFF DISTRIBUTOR GEAR ASSEMBLY. A GEAR HOLDING TOOL WAS USE FOR THE MAGNETO INSTALLATION ON ENGINE N	OT RECOMMENDED IAW MFG MSB NR 528 AND MFG SB 658.					1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2004032500032	20040325	00032	CE  	2004	3	25	CA040107005      	1	20031219	G	7312	10585	HEATER          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	OIL/FUEL	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) OIL PRESSURE ANNUNCIATOR ILLUMINATED FOLLOWED BY OIL PRESSURE FLUCTUATIONS. CREW THEN SHUT ENGINE DOWN AND LANDED 	WITH NO FURTHER PROBLEMS. UPON INSPECTION BY MAINTENANCE IT WAS CLEAR THAT THERE WAS AN EXCESSIVE OIL LEAK AND LOW OIL L	EVEL. THIS WAS THE CAUSE OF THE FLUCTUATIONS IN THE OIL PRESSURE.  FURTHER INSPECTION REVEALED THAT A CRACK IN THE OIL T	O FUEL HEATER CAUSED THE EXCESSIVE OIL LEAK. THE CRACK WAS LOCATED AT A WELD IN THE SEAM AREA. THE ENGINE WAS INSPECTED 	IAW MFG MM 72-00-00 PAGE643.   OIL TO FUEL HEATER WAS REPLACED AND SEVERAL GROUND RUNS WERE CARRIED OUT.   ENGINE WAS FO	UND TO BE OPERATING WITHIN DESIRED SERVICEABLE LIMITS AND AIRCRAFT WAS RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2004032500033	20040325	00033	NE  	2004	3	25	CA040107006      	2	20031201	G	7250	3020159	RETAINER        	PWA         							PWA   	PT6   	PT6A114A    	52043	NE  					TURBINE SECTION	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						9Y415					(CAN) THE HOT SECTION WAS GIVEN A SCHEDULED BORESCOPE INSPECTION.  A COMPRESSOR TURBINE SHROUD SEGMENT HAD SHIFTED SLIGH	TLY.  THE RETAINING RING HAD COME OUT OF THE GROOVE. THIS PROBLEM HAS BEEN DOCUMENTED ON OTHER ENGINES.  MFG HAS ISSUED 	P/N 3110741-02 RETAINING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 3248 (41/42, 45 SERIES) TO PREVENT THE COLLAPS	E OF THE RETAINING RING. THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MODELS.								3	T			E4EA				 
2004032500034	20040325	00034	NE  	2004	3	25	CA040107007      	2	20031230	G	7250	3020159	RETAINER        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TURBINE SECTION	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE HOT SECTION WAS REPAIRED TO CORRECT DEGRADED PERFORMANCE.  THE RETAINING RING HAD POPPED OUT OF THE RING GROOV	E AND A CT SHROUD SEGMENT HAD SHIFTED. THIS PROBLEM HAS BEEN DOCUMENTED ON  OTHER ENGINES.  MFG HAS ISSUED P/N 3110741-0	2 RETAINING RING ON SB 13121 (60A, 61, 62, 65 SERIES) AND SB 3248 (41/42, 45 SERIES) TO PREVENT THE COLLAPSE OF THE RETA	INING RING.  THE LATTER SB HAS NOT BEEN ISSUED ON SMALLER ENGINE MODELS SUCH AS THE114A ENGINE MODEL TO ALLOW THE MORE R	OBUST RETAINING RING TO BE USED.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2004032500041	20040325	00041	EU  	2004	3	25	CA040108001      	1	20031118	G	2435		BRUSHES         	LUCAS       		BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	STARTER GEN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				257  		TA5344					(CAN) BRUSH PIGTAILS WERE FOUND TO BE BADLY FRAYED,  BRUSHES WERE DAMAGED. RETURNED UNIT FOR EVALUATION. ARMATURE FAILED	, COMMUTATOR BARS LIFTED CAUSING DESTRUCTION OF BRUSHES AND DAMAGE TO 4 BRUSH SPRINGS. ARMATURE WAS SERVICEABLE AT TIME 	OF PREVIOUS O/H. CAUSE OF FAILURE UNDETERMINED. O/H REQUIRED AND INSTALLATION OF STANDARD OEM BRUSHES RECOMMENDED. MIRAJ	 MILLENNIUM BRUSHES THAT WERE INSTALLED ON THE UNIT WERE SUSPECTED OF CAUSING EXCESSIVE HEAT BUILD UP, SUGGESTED THAT IM	PROPER SEATING OF ANY TYPE OF BRUSH WILL CAUSE OVERHEATING.  ASSURED THAT THEIR BRUSHES WOULD NOT GENERATE EXCESSIVE HEA	T IF INSTALLED CORRECTLY. UNIT INSTALLED TO REPLACE THIS ONE FAILED AFTER 42.6 HRS.	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2004032500044	20040325	00044	NE  	2004	3	25	CA040108004      	2	20031215	G	7230	0292152880	TAB             								TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					COMPRESSOR	CRACKED         	W				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			CA								9646			(CAN) ON AN OCCURRENCE TEARDOWN OF ENGINE, BETWEEN MODULE 2 AND MODULE 3, THE TECHNICIANS DISCOVERED A TAB BRIDGE CRACKE	D AND WAS INGESTED INTO THE ENGINE SUBSEQUENTLY CAUSING DAMAGE TO THE CENTRIFUGAL COMPRESSOR,  WHICH WAS REPLACED.										3	U			E19EU				 
2004032500045	20040325	00045	GL  	2004	3	25	CA040108005      	1	20031231	G	5610	2056000902	SPRING          			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  	HOFMAN	HOV352	HOV352F     	NE  	CANOPY HOOKS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LT CANOPY SPRING CLIPS BROKE OFF AT BOTH ENDS OF THE CANOPY SPRING SIMULTANEOUSLY.  THE ENERGY RELEASED DURING	 THE FAILURE WAS SUFFICIENT TO ALLOW ONE OF THE CLIPS TO TRAVEL THE WIDTH OF THE COCKPIT AND STRIKE THE RT SEAT OCCUPANT	 IN THE REAR OF THE HEAD. THERE HAVE BEEN NUMEROUS FAILURES OF CANOPY SPRINGS NOTED IN THE PAST.  IN ALL PREVIOUS CASES 	ONLY ONE OF THE CLIPS FAILED.  IN THE CASE OF A SINGLE-CLIP FAILURE BOTH THE SPRING AND THE BROKEN CLIP HAVE REMAINED AT	TACHED TO THE AIRFRAME.  THIS IS THE FIRST INSTANCE OF A SIMULTANEOUS FAILURE OF BOTH ENDS.  IT IS ALSO THE FIRST INSTAN	CE IN WHICH AN AIRCRAFT OCCUPANT WAS STRUCK BY A PIECE OF THE FAILED SPRING.	1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I	5	C	TP5BO	 
2004032500047	20040325	00047	EA  	2004	3	25	CA040109001      	1	20031216	G	2750	601R930507	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN) TE FLAPS FAILED ON THREE OCCASIONS. AFTER EXTENSIVE TROUBLESHOOTING THE FLAP ELECTRONIC UNIT WAS AT FAULT AND LT B	PSU WAS REPLACED. TEST FLIGHT SUCCESSFUL.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004032500048	20040325	00048	EA  	2004	3	25	CA040109002      	1	20031214	G	5270		SENSOR          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					DOOR WARNING SYS	OUT OF RIG      	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) ON DEC.14 DURING CLIMB 8500 MSL - (PAX DR LATCH CAUTION). A/C LEVELED OFF AT 12000 WITH PRESSURIZATION OK, CAUTION	 THEN UPGRADED TEICAS CAUTION MSG:  PAX DR LATCH: ON DEC.15 WHILE CLIMBING THROUGH 14,000 FT WITH CAB DIFF OF 5.5 PSI.  	RETURN LEG MESSAGE REAPPEARED. PRESSURE NORMAL.  CLIMBED TO 280.  PRESS DIFF. WAS 8.0.PRESSURE NORMAL (PASSENGER DOOR) A	FTER TROUBLESHOOTING FOUND SENSORS 46, 47 OUT OF RIG.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004032500053	20040325	00053	EU  	2004	3	25	CA040109005      	1	20031214	G	2435	23079005	BRUSHES         	LUCAS       		BAG   	JETSTM	JETSTM3212  	1500217	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	STARTER GEN	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			42   			1826					(CAN) AFTER PREVIOUS STARTER GEN FAILED.  IT WAS REMOVED BECAUSE IT FAILED TO ROTATE  ENGINE DURING START. REMOVED BRUSH	 COVER AND FOUND ONE OF BRUSH LEADS MELTED AND SMALL PIECES OF METAL FALLING OUT OF THE UNIT. TOOK PICTURES, SENT IT TO 	A THIRD PARTY FOR EVALUATION.  DISASSEMBLED THE UNIT AND FOUND NR4 BRAIDED LEAD FROM STATOR TO BRUSH HAD NOT BEEN CONNEC	TED.  SOLE CONTACT WAS WITH BACK OF SCREW ON NR 4 BRUSH ASSEMBLY. IT WAS ABLE TO PASS TESTS BECAUSE OF CONTACT WITH BACK	 OF BRUSH ASSY. DURING SERVICE, WIRE EVENTUALLY VIBRATED AWAY FROM SCREW OR SIMPLY NOT ENOUGH CURRENT WAS ABLE TO FLOW T	HROUGH THAT CONNECTION.  RESULT WAS A HEAT BUILD UP IN LEADS TO OPPOSITE BRUSH WITH EVENTUAL FAILURE.	2	L	7	2 	4T	4	T	RT	BA15CAA 	E4WE	6	C	P61GL	 
2004032500064	20040325	00064	NM  	2004	3	25	CA040109008      	1	20030909	G	6120	697073001A	PITCH CONTROL   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROPELLER	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE GROUND START, THE FLT CREW GOT A POWER PLANT ADVISORY LIGHT ON THE ENGINE DISPLAY UNIT. POWER PLANT 	ADVISORY DISAPPEARED AFTER RESET PROCEDURE CARRIED OUT IAW TCC REQUEST.  THE CENTRAL DIAGNOSTIC SYSTEM (CDS) WAS INTERRO	GATED AND REVEALED THAT FAULT CODE 224 GBE SWITCH STUCK OFF ON LT SIDE HAD TRIGGERED THE POWERPLANT ADVISORY ONED. PCU P	LUGS P20 AND P24 WERE CHECKED IAW FIM WITHOUT REMARKS.  PCU WAS REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032500070	20040325	00070	NM  	2004	3	25	CA040112002      	1	20030904	G	2750	C1486561	PRESSURE SWITCH 			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	TE FLAPS	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO BASE, FLAPS 5 WAS SELECTED AND FLAP POWER CAUTION LIGHT CAME ON IMMEDIATELY, QRH WAS CONSULTED AND 	SYSTEM RESET SUCCESSFULLY ACCORDINGLY. NORMAL LANDING PREFORMED WITH FLAP 15, NEXT CREW BRIEFED AND TCC CONTACTED.  INVE	STIGATION/ACTION THE CENTRAL DIAGNOSTIC SYSTEM (CDS) WAS INTERROGATED WITHOUT FINDINGS. DUE TO A NUMBER OF PREVIOUS LOG 	REMARKS REGARDING FLAP POWER, ESPECIALLY LOG REMARK L109 MENTIONING (HYDRAULIC PRESSURE LOSS), IT WAS DECIDED TO REPLACE	 THE FLAP POWER UNIT (FPU).  CONCLUSION, NO SIMILAR PROBLEMS HAVE BEEN EXPERIENCED SINCE THE ABOVE INCIDENT AND IT IS CO	NCLUDED THAT A FAULTY PRESSURE SWITCH ON THE FPU CAUSED THE INCIDENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032500095	20040325	00095	EU  	2004	3	25	CA040113003      	1	20031208	G	2730	F50B273517	CONTROL ROD     			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					ELEVATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C CHECK INSPECTION, ELEVATOR PUSH/PULL CONTROL ROD WAS FOUND WITH A WEAR MARK OF 1.37 LONG, .34  WIDE AND .	0125 DEEP.  THE WEAR MARK WAS CAUSED BY INTERFERENCE WITH A GEAR TYPE CLAMP ON AN ECS DUCT UNDER THE AFT CABIN VANITY.  	THE GEAR/SCREW PORTION OF THE CLAMP WAS POSITIONED AGAINST THE TUBE.  LOOSENING THE CLAMP AND ROTATING IT SO SCREW/GEAR 	PORTION WAS AT 12 O`CLOCK POSITION RECTIFIED THE INTERFERENCE PROBLEM. CONTROL ROD WAS REPLACED WITH NEW UNIT.			2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2004071200157	20040712	00157	GL  	2004	7	12	CA040113011      	2	20031201	G	7210	6858647	DRIVE ASSY      	ALLSN       		CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  	HAMSTD	54H	54H60       	NE  	ALTERNATOR	STRIPPED        	W				E				ENGINE SHUTDOWN         				J	Z	Y	WARNING INDICATION        	SIGNIFICANT FAILURE REPORT	ENGINE STOPPAGE           	CR	CRUISE         	1			CA			1416 			CAG600774					(CAN) AFTER PROPS WENT OUT OF SYNC, ENG DRIVEN COMP LOW OIL LIGHT ILLUMINATED.  EDC DISCONNECT WAS SELECTED, FLUCTUATING	 GB OIL PRESSURE WAS OBSERVED. PRESS FLICKERED FROM 200 PSI TO 120 PSI ABOUT EVERY 5 SECONDS. SHUTDOWN CARRIED OUT, AC R	ETURNED TO BASE OEI. TEARDOWN, PRELIMINARY REPORT INDICATES STRIPPED SPLINES ON ALTERNATOR DR SHAFT ASSY, ALTERNATOR DR 	SHAFT NUT FOUND LOOSE, REAR BRG ALTERNATOR DR ASSY FOUND LOOSE DURING DISMANTLING. INCIDENT OCCURED 35.6 HOURS AFTER NOS	E CASE WAS REPAIRED FOR EXCESSIVE (.025') RADIAL PLAY OF PROP SHAFT, DURING INVESTIGATION FOR OIL TRANSFER FROM EDC TO R	EDUCTION GB. EXCESS RADIAL PLAY WAS DISCOVERED WHILE CHANGING PROP SHAFT SEAL FOR OIL LEAKAGE FROM FRONT OF NOSE CASE.	2	L	7	2 	4R	4	T	 	6A6     	E282	6	C	P906	 
2004032500136	20040325	00136	EU  	2004	3	25	CA040114001      	1	20031208	G	3300	3640126	MODULE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					LIGHT DIMMER	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) WATER INGRESS AND HUMIDITY FROM AIR VENTS AND DOOR SEAL LEAK.   LEADS TO CORROSION AND SUBSEQUENT FAILURE OF THE W	ARNING LIGHTS, DIMMING MODULE LOCATED BEHIND THE INSTRUMENT PANEL.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2004032900054	20040329	00054	NM  	2004	3	29	CA040114006      	1	20031111	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG	INOPERATIVE     	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER T/O CREW WERE UNABLE TO SELECT GEAR UP. WITH GEAR SELECTOR IN UP POSITION THEY HAD NO YELLOW DOOR LIGHTS AND	 STILL 3 GREENS AND 3 REDS AND LEVER TRANSIT LIGHT. THEY SELECTED LEVER DOWN, BRIEFED CREW AND PAX AND RETURNED TO BASE 	FOR NORMAL LANDING.  INVESTIGATION/ACTION THE UNABILITY TO RETRACT LANDING GEARS WAS CAUSED DUE BREAKAGE OF THE NOSE WHE	EL CENTERING PROXIMITY SENSOR WIRES.  NOSE WHEEL CENTERING SENSOR REPLACED IAW AMM 32-61-00.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032900055	20040329	00055	NM  	2004	3	29	CA040114007      	1	20031214	G	3297	471515	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	MLG	INOPERATIVE     	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, CREW WAS UNABLE TO GET LANDING GEAR UP.  WHEN MOVING HANDLE NO AMBER LIGHT ONLY GREEN AND RED LIGHT	S.  RETURNED TO BASE FOR LANDING.  THE INABILITY TO RETRACT LANDING GEAR  WAS CAUSED DUE BREAKAGE OF THE NOSE WHEEL CENT	ERING PROXIMITY SENSOR WIRES. NOSE WHEEL CENTERING SENSOR REPLACED IAW AMM 32-61-00.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032900056	20040329	00056	WP  	2004	3	29	CA040114008      	1	20031202	G	6420	D0621	ROTOR HEAD      			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TAIL ROTOR	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON RECEIPT OF AD2003-24-51 HELICOPTER WAS INSPECTED FOR THE SUSPECT NAS6605-31BOLTS. EVEN THOUGH THE R44 S/N WAS	 NOT LISTED IN THE AD OR ROBINSON HELICOPTER SERVICE BULLETIN 51 THE T/R HUB NAS6605-31BOLTS WERE FOUND TO HAVE THE VEND	OR IDENTIFICATION MARKING 01D0. THE BOLTS WERE REPLACED AND THE A/C RETURNED TO SERVICE.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004032900057	20040329	00057	NM  	2004	3	29	CA040114009      	1	20031214	G	3297		WIRE            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROX SWITCH	BROKEN          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) GEAR DOORS WOULD NOT CLOSED AFTER GEAR UP SELECTION.  RETURNED TO BASE FOR NORMA LANDING.  INVESTIGATION/ACTION TH	E UNABILITY TO RETRACT LANDING GEARS WAS CAUSED DUE BREAKAGE OF THE NOSE WHEEL CENTERING PROXIMITY SENSOR WIRES. NOSE WH	EEL CENTERING SENSOR REPLACED IAW AMM 32-61-00.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032900058	20040329	00058	NM  	2004	3	29	CA040114010      	1	20031219	G	3297	464505	WIRE HARNESS    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	RT MLG DOWNLOCK	DAMAGED         	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) WHEN CREW SELECTED GEAR DOWN, NO GREEN LIGHT INDICATION, THEY GOT UNSAFE AND DOOR LIGHT INDICATION ON LT SIDE, GO 	AROUND, RECYCLING WITH SAME RESULT. ALTERNATE GEAR EXTENSION ACCORDING TO QRH WITH SUCCESSFUL RESULT. LANDING WAS NORMAL	. PSEU CHECKED FOR FAULTS.  LGD LK1 FAULT FOUND.   LT GEAR DOWNLOCK HARNESS REPLACED IAW AMM 32-61-06. OPERATIONAL TEST 	PERFORMED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032900061	20040329	00061	NE  	2004	3	29	CA040115004      	2	20031228	G	8530		CYLINDER HEAD   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA											(CAN) HEAD TO BARREL SEPARATION AT THE END OF THE THREADED PORTION OF THE STEEL BARREL. REMOTE AMO HIRED TO REPLACE CYLI	NDER ASSEMBLY NOTED THAT THE FAILURE WAS A TYPICAL METAL FATIGUE FAILURE.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P28EA	 
2004032900101	20040329	00101	CE  	2004	3	29	CA040115006      	1	20031209	G	2720	7173	SOLENOID        			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER BOOST	STICKING        	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) DURING LOWERING OF THE LANDING GEAR, UNSCHEDULED YAW WAS NOTICED BY THE CREW AND UPON LANDING, THE AIRCRAFT WAS DI	FFICULT TO TAXI. THE RUDDER SYSTEM RECEIVES THE INPUT FROM THE RUDDER BOOST SOLENOID.  AS THEY ARE LOCATED IN AN UNHEATE	D AREA OF THE AIRCRAFT, THE MOISTURE IN THE COLD AND HUMID INSTRUMENT AIR SUPPLY TENDS TO FREEZE THE SOLENOID AND STICK.	  WHEN THE SOLENOID STICKS OPEN, THE MOST COMMON SYMPTOM IS HEAVY RUDDER INPUT, WHILE TAXIING. THUS THE PILOT HAD DIFFIC	ULTY ON THE GROUND.  THE SOLENOID WAS REPLACED, GROUND RUN CARRIED OUT AND THE AIRCRAFT WAS RELEASED TO SERVICE.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2004042900099	20040429	00099	GL  	2004	4	29	CA040122007      	3	20031118	G	6114	C6760	SPRING          			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	PROP FEATHERING	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) PROPELLER SPRING FAILED INSPECTION.  MPI PROCEDURE WAS ACCOMPLISHED AND CRACK INDICATIONS WERE FOUND IN SEVERAL AR	EAS.  PROPELLER WAS REMOVED PRE-MATURELY DUE TO LIGHTNING STRIKE.  SPRING WAS NEW FROM MFG AND INSTALLED FOR ONLY 636.4 	HRS FROM THE PREVIOUS OVERHAUL. SPRING WAS SENT TO MFG FOR EVALUATION, IT WAS FOUND WITH SEVERAL CRACK INDICATIONS.  SPR	ING REMOVED FROM SERVICE.   WARRANTEE SPRING WAS PROVIDED FROM MFG.  CRACKS HAVE BEEN FOUND IN OTHER SPRINGS DURING ROUT	INE OVERHAUL INSPECTIONS.  NO CRACK INDICATION ALLOWED IN THE SPRING.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2004042900101	20040429	00101	EA  	2004	4	29	CA040123002      	1	20031220	G	7110	A33721	STRUT           			CNDAIR	CL604 	CL604       	1900301	EA  	GE    	CF34  	CF343B1     	 	NE  					CORE COWL	UNSECURE        	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, THE CREW NOTED THAT LT ENGINE THROTTLE COULD NOT BE RETARDED FROM 92 PERCENT.  CREW ELECTED	 TO SHUT ENGINE DOWN WITH FIRE/PUSH PBA.  A/C MADE AN UNEVENTFUL LANDING.  SUBSEQUENT INSPECTION REVEALED THAT THE CORE 	COWL SUPPORT STRUT HAD NOT BEEN PROPERLY SECURED IN CORE COWL WITH SNAP RETAINER AND LOCKPIN AFTER LAST ACCESS.  WHEN TH	E STRUT FELL BACK DOWN ON THE ENGINE, IT FOULED AND APPARENTLY RESTRICTED MOVEMENT OF THE THROTTLE CONTROL BOX LINKAGE T	O THE FUEL CONTROL.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004031500019	20040315	00019	NE  	2004	3	15	CA040123010      	2	20031227	G	7320	6047T774P11	FUEL CONTROL    			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					LT ENGINE	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) AT CRUISE ALTITUDE, DURING DESCENT, CREW WERE UNABLE TO RETARD POWER ON THE LT ENGINE THROTTLE. A FEW ATTEMPTS TO 	REDUCE POWER WERE MADE WITH NO CHANGE. THE CREW MANUALLY SHUTDOWN THE ENGINE AND MADE AN UNEVENTFUL LANDING. SUBSEQUENT 	TROUBLESHOOTING TRACED THE PROBLEM TO THE FUEL CONTROL UNIT. THE FCU WAS REPLACED AND THE A/C RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004031500036	20040315	00036	EA  	2004	3	15	CA040127003      	1	20031001	G	2750	C3CF1709	CONTROL ARM     			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  	HAMSTD	23D	23D40       	NE  	LT TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS LT FLAP COANTROL ARM WAS FOUND CRACKED DURING AN INSPECTION.  THE CRACK WAS 188 MM/0.7 INCH RUNNING LENGTHWIS	E FROM THE THREADED END OF THE ROD ENDING AT THE INSPECTION HOLE. THIS PART WAS REPLACED WITH A NEW UNIT.					1	H	7	1 	3R	3	R	 	A815    	E142	6	C	P719	 
2004031500037	20040315	00037	EA  	2004	3	15	CA040127004      	2	20031217	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	RT ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ENGINE, NR 5 CYLINDER FAILED COMPRESSION TEST. UPON REMOVAL, CYLINDER INTERIOR AND UNDERSIDE OF PISTON HEAD FOU	ND TO HAVE SOME TYPE OF BROWNISH SURFACE COATING ON THEM.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2004031500055	20040315	00055	EA  	2004	3	15	CA040127012      	2	20031202	G	8530		EXHAUST VALVE   			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA								L4533127A			(CAN) NR 3 CYLINDER EXHAUST VALVE WAS INGESTED BY ENGINE AND EXPELLED OUT THE EXHAUST, CAUSING EXTENSIVE DAMAGE TO ENGIN	E AND METAL CONTAMINATION.  ENGINE REMOVED FOR OVERHAUL.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004031500056	20040315	00056	SO  	2004	3	15	CA040127013      	2	20031216	G	7314	6533512	PUMP            			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	FUEL SYSTEM	FAILED          	W				A				UNSCHED LANDING         				Y	K	J	ENGINE STOPPAGE           	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) ENGINE DRIVEN FUEL PUMP P/N 653351-2 FAILED DUE TO THE SEAL BETWEEN THE FUEL PUMP AND THE FUEL PUMP DRIVE. ALLOWIN	G THE FUEL PRESSURE TO DROP AND ENGINE SHUT DOWN FOR LACK OF FUEL. THE FUEL PASSED THROUGH THE FUEL PUMP DRIVE DRAIN & O	VER BOARD THE AIRCRAFT.				1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2004031500057	20040315	00057	NE  	2004	3	15	CA040127014      	2	20031228	G	7322		PUMP            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					FUEL CONTROL	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA						5ADS1907					(CAN) WHILE HELICOPTER WAS CONDUCTING AERIAL LIFT WORK THE PILOT NOTED THE ENGINE FUEL PUMP LIGHT CAME ON. HE RETURNED T	O THE STAGING AREA AND LANDED UNEVENTFULLY.  THROUGH TROUBLESHOOTING ON THE GROUND IT WAS DISCOVERED THAT ONE ELEMENT OF	 A DUAL ELEMENT PUMP FAILED.  LIKELY CAUSE IS THE FAILURE OF THE INTERNAL DRIVE SPLINE, A KNOWN PROBLEM WITH -93 FUEL CO	NTROLS.			1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2004031500076	20040315	00076	WP  	2004	3	15	CA040127022      	1	20031223	G	6520	369D25401	HOUSING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					T/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						HD1007					(CAN)  ALTHOUGH NOT REQUIRED AT THIS TIME, DUE TO THE ABNORMAL WEAR ON THE IP GEAR LARGE BEARING JOURNAL THE HOUSING WAS	 SENT OUT FOR ALIGNMENT AND NDT INSPECTION. THE RESULTS WERE RECEIVED RECENTLY FROM TRANSPORT APPROVAL FACILITY THAT THE	 GEARBOX HOUSING WAS FOUND CRACKED IN THE O/P ALIGNMENT BEARING AREA.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004031500094	20040315	00094	NE  	2004	3	15	CA040128006      	2	20031228	G	7322	85634	PUMP            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					FUEL CONTROL	WORN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA						5ADS1907					(CAN) FUEL CONTROL P/N 1-170-240-93, S/N 5ADS1907 WAS RECEIVED DUE TO DAMAGED MAIN DRIVE SHAFT SPLINE. DISASSEMBLED AND 	INSPECTED FCU AND FOUND DAMAGED PUMP ASSEMBLY.  RECORD OF INSPECTION IAW SB73-39.  FCU S  91 AND  93 HAVE TIP SEAL PUMP,	 AND THEY CAN BE INSTALLED ON FOLLOWING ENGINE TYPES: T5313B, T5317A, T5317A-1 AND T5317B.  INVESTIGATED TWO TIP SEAL PU	MP AND MAIN DRIVESHAFT FAILURE ON FCU  FITTED WITH TIP SEAL PUMPS. FAILURE OF THESE PARTS LEADS TO LOSS OF FUEL SUPPLY T	O FCU, BOTH AUTOMATIC AND EMERGENCY SUPPLY, CAUSING ENGINE FLAMEOUT. IN BOTH CASES THE FCU S  INVESTIGATED HAD TSO IN TH	E MID LIFE RANGE.  WAITING FOR FURTHER CLARIFICATION AND GUIDANCE FROM THE MFG.	1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2004031500107	20040315	00107	EU  	2004	3	15	CA040129005      	1	20031208	G	2913	704A33690004	PUMP            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	BROKEN          	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING SLINGING OF SURVEY EQUIPMENT (SO CALLED 'MAG BIRD').  HYDRAULIC FAILURE OCCURRED.  PILOT DROPPED OFF SURVEY	 EQUIPMENT AND MADE  UNSCHEDULED LANDING. THE A/C SUSTAINED NO DAMAGE.  HYDRAULIC PUMP DRIVEBELT FOUND BROKEN. BELT REPL	ACED, A/C RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2004031500109	20040315	00109	CE  	2004	3	15	CA040129007      	1	20031210	G	5520	1015241099	BRACKET         	BEECH       		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BALLAST WEIGHT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELEVATOR FORWARD BALLAST WEIGHT STOP BRACKET AND BOLT FOUND BENT APPROXIMATELY 80 DEGREES FROM ITS ORIGINALLY INST	ALLED POSITION. DENTS ON WEIGHT FACE INDICATE STOP BOLT AND BRACKET ASSEMBLY WAS SUBJECTED TO SEVERAL SEVERE CONTROL MOV	EMENTS OF THE AIRCRAFT ELEVATOR CONTROL SYSTEM.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2004031500139	20040315	00139	WP  	2004	3	15	CA040202002      	1	20031228	G	3260	833703	PROXIMITY SENSOR			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D219     	52053	NE  					NLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED AND RED NOSE GEAR LIGHT ON WITH GEAR HANDLE UP. AIRCRAFT LANDED BACK.  NLG UP LOCK PROXIMITY SEN	SOR P/N 8-337-03 REPLACED ALSO RELAY R2-262 REPLACED AS PRECAUTIONARY. AIRCRAFT DISPATCHED SERVICEABLE. SAME DEFECT REOC	CURS AT DEPARTURE. AIRCRAFT LANDED BACK.  NOSEGEAR OLEO FOUND FLAT. OLEO HAS BEEN SERVICED AND SYSTEM CHECKED SERVICEABL	E.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
2004032500060	20040325	00060	NM  	2004	3	25	CA040204001      	1	20030906	G	5610	80260005	WINDSHIELD      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R320	CR3204123F1 	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) LT FRONT WINDOW CRACKED AT FL 230 SPEED 240 KTS. (WINDOW HEAT ON) DESCEND TO FL 100, REDUCED SPEED TO 200 KTS, AND	 DIFF. PRESS TO 3,0 PSI.  INVESTIGATION/ACTION, LT FRONT WINDSHIELD, S/N: 419 REPLACED. THE MFG HAS INVESTIGATED, BUT CO	ULD NOT IDENTIFY THE CAUSE OF THE CRACK AS BEING MANUFACTURING OR HANDLING RELATED.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P5NE	 
2004032500061	20040325	00061	NM  	2004	3	25	CA040204002      	1	20031119	G	2913	6617302	PUMP            			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	SEIZED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE A/C LOST HYDRAULIC PUMP NR 1. QRH CONSULTED AND FOLLOWED BY ACTIVATING STBY PUMP.  PRESSURE RESTORED	 TO NR 1 ONE SYSTEM.  RETURNED TO BASE AND MADE A UNEVENTFUL LANDING.  INVESTIGATION/ACTION, ENGINE DRIVEN PUMP (EDP) FO	UND SEIZED AND CONSEQUENTLY REPLACED ACC AMM 29-11-01. HYDRAULIC SYSTEM NR 1 FLUSHED AND BLEED ACC AMM 29-10-00.   HYD S	YSTEM NR 1, PRESSURE, RETURN AND CASE DRAIN FILTERS REPLACED.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032500072	20040325	00072	NM  	2004	3	25	CA040204003      	1	20031020	G	5610	80260006	WINDSHIELD      			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) RT WINDSHIELD CRACKED AT FL230.  SPEED REDUCED AND DESCEND DOWN TO FL100. QRH PERFORMED.  SPEED AT MAX CRUISE AND 	MAX DIFF PRESSURE AT TIME OF THE CRACKING. RT WINDSHIELD REPLACED IAW AMM 56-10-01-400-801. THE MFG HAS INVESTIGATED THE	 WINDSHIELD AND FOUND A SCRATCH UNDER THE MOLDED EDGE SEAL AT CRACK INITIATION. THE SCRATCH IS A RESULT OF HANDLING PRIO	R TO DELIVERY AND BEFORE INSTALLATION OF THE MOLDED EDGE SEAL AT MANUFACTURE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032500085	20040325	00085	NM  	2004	3	25	CA040204004      	1	20031121	G	2910	9752565	RELIEF VALVE    			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA						NA					(CAN) PILOT BECAME AWARE OF HYD. QT. 20-30 PERCENT, AND HYD NR 1 ISO VALVE CAUTION LIGHT. PRESSURE WAS AT THIS TIME OK. 	AFTER 5 MIN. QT. DROPPED TO 0 PERCENT. THIS CAUSED NEW CAUTION LIGHTS, AND QT. IN SYST. NR 1 TO INCREASE TO 50-60 PERCEN	T. COMPLETED ABNORMAL CHECKLIST FOR FLAPLESS LANDING. SINCE WE HAD QT. 50-60 PERCENT IN NR 1 SYS, AND PRESSURE FLUCTUATI	NG, DECIDED TO TRY FLAPS 5. REACHED 3 DEGREES & STOPPED. NORMAL FLAPLESS LANDING PERFORMED.  AFTER SERVICING NR 1 HYD SY	STEM , HYD FLUID WAS FOUND POURING FROM HYD BALANCE RELIEF VALVE DRAIN PORT TUBE. HYD BALANCED RELIEF VALVE REPLACED ACC	 AMM 29-11-51. LEAK CHECK OF HYD SYSTEM NR 1 PERFORMED WITHOUT ANY REMARKS.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004050300233	20040503	00233	NE  	2004	5	3	CA040204006      	2	20030911	G	7320	117024093	FUEL CONTROL    			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					ENGINE	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENGINE STOPPED IN-FLIGHT.						1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2004032500087	20040325	00087	NM  	2004	3	25	CA040204008      	1	20031112	G	6120	697073001A	PITCH CONTROL   			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PROPELLER	INOPERATIVE     	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA											(CAN) ENGINE INDICATING POWERPLANT MESSAGE ON ED DURING TAKEOFF ROLL. T/O ABORTED AND RETURNED TO GATE FOR TECHNICAL INV	ESTIGATION. THE CENTRAL DIAGNOSTIC SYSTEM (CDS) WAS INTERROGATED AND REVEALED THE PRESENCE OF FAULT CODE 224 ON LT ENGIN	E (THE GBE SWITCH STAYS IN THE CLOSED POSITION). THE PITCH CONTROL UNIT (PCU) WAS THEN REPLACED IAW TASK 61-20-11 AND AN	 ENGINE TEST RUN PERFORMED, REF. AMM TASK 71-00-00-868-805.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004032500103	20040325	00103	EA  	2004	3	25	CA040204013      	1	20030226	G	3310	2LA00691307	LIGHT           			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					COCKPIT	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) CREW REPORTED SMOKE/SPARKS FROM CO-PILOTS FLOOD LIGHTS ON SIDE PANEL BELOW BASE OF WINDSHIELD WITH BURN MARKS ON P	LASTIC AREA AT BASE OF W/S AND SIDE WINDOW. REMOVED AND REPLACED F/OS MIDDLE FLOOD LIGHT ASSY IAW AMM 33-11-03 AND OPS C	HECKED SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004032600002	20040326	00002	EA  	2004	3	26	CA040208001      	1	20031124	G	2760	5120011	CONTROL UNIT    			CNDAIR	CL600 	CL6002C10   	1390015	EA  	GE    	CF34  	CF348C1     		NE  					SPOILERS	DEFECTIVE       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, IB FLT SPOILER CAUTION MESSAGE GOT POSTED AND RT IB FLIGHT SPOILER FULLY DEPLOYED.  DECLARED AN EMER	GENCY AND LANDED.  RT IB MULTI FUNCTION SPOILER PCU WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. NOTE: DFDR ANALYS	IS INDICATED THAT THE RT INBOARD MFS DID DEPLOY.  THIS DFDR DOWNLOAD WILL BE PROVIDED TO MFG FOR REVIEW.				2	L	7	2 	4F	4	F	RT	A21EA   	EOOO63EN				 
2004050700052	20040507	00052	GL  	2004	5	7	CA040210007      	3	20030310	G	6111	D3A34C403B	BLADE           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	PROPELLER	SCORED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER SHUT-DOWN, PILOT NOTICED ONE PROPELLER BLADE ROOT SNAP RING HAD POPPED OUT OF ITS LOCATION DURING PREVIOUS F	LIGHT.  IN DOING SO, IT DAMAGED THE BLADE ROOT BY SCORING SURFACE.  PROPELLER REMOVED AND SENT FOR REPAIR AT PROPELLER S	HOP.				1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2004031500072	20040315	00072	WP  	2004	3	15	CA040217006      	1	20031106	G	7810	D3181	HEAT SHIELD     			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TAIL PIPE	DEPARTED        	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) PART DEPARTED HELICOPTER WHILE IN FLIGHT. DUE TO LOCATION OF DESCRIBED PART, IF (WHEN) PART LEAVES AIRCRAFT IN FLI	GHT IT IS QUITE PROBABLE PART WILL COME INTO CONTACT WITH TAIL ROTOR.  PART HAS NOT BEEN LOCATED SINCE DEPARTURE. PART H	AS NOT BEEN REPLACED DUE TO CONCERNS FOR FLIGHT SAFETY.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2004031500073	20040315	00073	SW  	2004	3	15	CA040217007      	1	20031114	G	3246	206050246102	SKID            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SKID TUBE PARTIALLY DISASSEMBLED TO INVESTIGATE ELONGATED HOLE. SIGNIFICANT CORROSION FOUND UNDER 206-050-132-1 DO	UBLER. DAMAGE IN NO-REPAIR AREA. SKID TUBE REPLACED.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2004031500082	20040315	00082	SW  	2004	3	15	CA040217010      	1	20031118	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					MAIN ROTOR	SCORED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN ROTOR BLADE BOLT EXTREMELY DIFFICULT TO REMOVE FROM BOTH BLADES/MAIN ROTOR HUB. BOLTS, BLADE BUSHINGS AND MAI	N ROTOR GRIPS ALL HAD HEAVY SCORING. CAUSE UNKNOWN.  BOLTS SCRAPPED. BUSHINGS REPLACED IN MAIN ROTOR BLADE AT APPROVED F	ACILITY, AND MAIN ROTOR GRIPS SCRAPPED DUE TO LOW TIME REMAINING. (HUB REMOVED DUE TO TX , TT STRAPS.) 206-011-132-009 M	/R GRIP S/N A1-02662 AND A1-02325206-015-001-107 M/R BLADE S/N A-3341 AND A-3262 206-011-135-5  BLADE BOLT S/N CH1625 AN	D CH1632.		1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2004031500083	20040315	00083	SW  	2004	3	15	CA040217011      	1	20031128	G	6410	222016001131	BLADE           			BELL  	230   	230         	1182149	SW  										TAIL ROTOR	DAMAGED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) DURING ROUTINE FLIGHT,  A 6.5 INCH PIECE OF DOUBLER BROKE OFF FROM THE BLADE, CAUSING VIBRATIONS.						1	G	7	2 	3U			NC	H9SW    					 
2004031500105	20040315	00105	WP  	2004	3	15	CA040219004      	2	20031231	G	7200	TFE7315BR	ENGINE          			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					LT & RT	MISRIGGED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) FOUND BOTH ENGINES HOOKED UP THE WRONG WAY.  INSPECTED AND CORRECTED IAW SB 26-3610.  ENGINE, TFE731-5BRS/N P10753	0 RFE-731-5BR  S/N P107531.  DUAL-HEAD ENGINE FIRE EXTINGUISHER HOOKED UP IN REVERSE AND COULD RESULT IN A FIRE EXTINGUI	SHER BOTTLE BEING DISCHARGED INTO THE WRONG ENGINE NACELLE.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2004031500155	20040315	00155	EU  	2004	3	15	CA040223004      	1	20030813	G	6320	350A32392301	DRIVE SHAFT     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					OIL PUMP	BROKEN          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						M1968					(CAN) AFTER FIRST START OF THE DAY THE TRANSMISSION OIL PRESSURE LIGHT NEVER WENT OFF.  ENGINE WAS SHUT DOWN TO INVESTIG	ATE THE SOURCE OF THE PROBLEM.  IT WAS FOUND THAT THE NEWLY OVERHAUL OIL PUMP WAS NOT DELIVERING ANY PRESSURE.  ON REMOV	AL OF MAIN TRANSMISSION AND OIL PUMP ASSEMBLY, THE DRIVE PINION SHAFT OF OIL PUMP WAS FOUND BROKEN IN TWO PIECES.  NOTE 	THAT THE AIRCRAFT FLEW THE DAY BEFORE WITH NO PROBLEM AT ALL.  CONCLUSION OF THE OVERHAUL FACILITIES STATE THAT THE SHAF	T FAILED IN A TORSIONAL MODE OF INSTANTANEOUS OVERLOAD.  DAMAGE FOUND ON THE PINION GEAR TEETH INDICATE THAT AN OBJECT P	ASSSED THROUGH THE MESH OF THE PUMP AND JAMMED OFF THE INTERMESHING OIL PUMP GEAR.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2004031500178	20040315	00178	EA  	2004	3	15	CA040225006      	2	20030930	G	7322	25242192R	FLOW DIVIDER    			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1B235	1B235BFA    	GL  	FUEL SYSTEM	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) THE AIRCRAFT SAT FOR APPROXIMATELY 7 YEARS.  AFTER A POWER LOSS IN FLIGHT, SUBSEQUENT INSPECTION OF THE INJECTOR N	OZZLES (TO FIND CONTAMINATION PRESENT) THE FUEL SYSTEM WAS SENT FOR REPAIR.  IT WAS GREEN-TAGGED AS REPAIRED. PROBLEM ST	ILL PRESENT, WENT BACK,  WAS BENCH-CHECKED AND PASSED. PROBLEM STILL NOT FIXED, SENT BACK, GREEN-TAGGED AGAIN, PROBLEM S	TILL PRESENT.   FINALLY, WE OPENED ONE OF THE UNUSED PORTS AND THE ATTACHED PHOTOS SHOW THE CONTAMINATION THAT WAS FOUND	. A NEW (OVERHAULED) FLOW DIVIDER WAS PURCHASED AND INSTALLED.  PROBLEM HAS NOT RETURNED.		1	L	7	1 	3O	3	O	 	A1CE    	1E10	5	N	P12EA	 
2004031500179	20040315	00179	EA  	2004	3	15	CA040225007      	1	20030714	G	5520	C3TE37ND	HINGE           			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT ELEVATOR FRONT SPAR P/N C2-TE-37ND UPPER ATTACH HOLES (NR 10) FOR CENTER HINGE POSITION HAS SMALL CRACK(	S) AROUND THE UPPER AN3 BOLT HOLE.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2004050300249	20040503	00249	GL  	2004	5	3	CA040227004      	2	20031116	G	7250	6898663	TURBINE WHEEL   			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					3RD STG BLADES	FAILED          	W				O				OTHER                   				T			ENGINE CASE PENETRATION   			CR	CRUISE         	1			CA											(CAN) 3RD TURBINE STAGE WHEEL BLADES SHED IN FLIGHT.  PART TIME SINCE NEW : 2852 HOURS.  PILOT IDENTIFIED FLIGHT PROBLEM	 AND LANDED IN AUTOROTATION.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2004050300250	20040503	00250	GL  	2004	5	3	CA040227005      	2	20031201	G	7250	6898663	TURBINE WHEEL   			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					3RD STG BLADES	FAILED          	W				O				OTHER                   				T			ENGINE CASE PENETRATION   			CR	CRUISE         	1			CA											(CAN) M 407 HELICOPTER HAD 3RD STAGE TURBINE WHEEL FAILURE IN FLIGHT.   AIRCRAFT CRASHED.  TURBINE WHEEL PART TIME 1144 	HOURS SINCE NEW.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2004050300263	20040503	00263	NE  	2004	5	3	CA040301002      	2	20030817	G	7230		COMPRESSOR      			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE AIRCRAFT DEPARTED A STAGING AREA, SHORTLY AFTER TAKEOFF, THE AIRCRAFT HAD AN ENGINE FAILURE AND CRASHED IN TAL	L TREES. THE PILOT WAS THE ONLY OCCUPANT AND WAS KILLED ON IMPACT. THE ENGINE WAS RECEIVED FROM OVERHAUL AND INSTALLED 1	8 HOURS PRIOR TO THE ACCIDENT. THE NTSB HAS CONFIRMED THAT THE COMPRESSOR ASSEMBLY SUFFERED A SUDDEN AND CATASTROPHIC FA	ILURE. THEY HAVE NOT YET DETERMINED THE EXACT CAUSE OF THIS FAILURE.			1	G	7	1 	4U	4	U	 	H1SW    	E1EA				 
2004050700036	20040507	00036	NM  	2004	5	7	CA040305003      	1	20031218	G	3250	481505	MANIFOLD        			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	NLG STEERING	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) NOSE STEERING CAUTION CAME ON DURING TAXI. VACATED RWY WITH HELP OF BRAKES AND FOOT STEERING. TOWED TO RAMP AND OF	F-LOADED PAX THERE.  SEVERAL UNSUCCESSFUL RESETS PERFORMED. INVESTIGATION/ACTION, STEERING CONTROL UNIT CHECKED FOR FAUL	T CODES. FAULT CODES EHVS AND SOVC PRESENT.  STEERING MANIFOLD REPLACED IAW AMM 32-51-16.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004050700039	20040507	00039	EA  	2004	5	7	CA040306001      	1	20031129	G	2140	601R950681	DUCT            			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1 A/C PACK	DETACHED        	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) THE A/C WAS DISPATCHED WITH PACK NR 1 INOPERATIVE IAW MEL.  AFTER T/O, WHEN TRANSFERRING THE BLEED AIR FROM APU TO	 THE ENGINES,  CABIN ALT CAUTION INDICATION CAME ON ON THE EICAS. THE CREW BEGAN TO FOLLOW QRH PROCEDURE AND, SUDDENLY, 	 CABIN ALT  WARNING INDICATION CAME ON ON THE EICAS.  THE CREW BEGAN AN EMERGENCY DESCENT AND THEY RETURNED TO THE DEPAR	TURE AIRPORT. A/C LANDED UNEVENTFULLY.  DUCT FROM PRECOOLER TO PRIMARY HEAT EXCHANGER IN PACK NR 2 WAS FOUND MISS ATTACH	ED AT PRIMARY HEAT EXCHANGER SIDE.  DUCT REPOSITIONED.  AMM TASK NR 2 AMM NR 21-31-00-710-801 CARRIED OUT. A/C RELEASED 	INTO SERVICE.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004050700046	20040507	00046	EA  	2004	5	7	CA040307001      	1	20031217	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) CAPTAINS WINDSHIELD CRACKED IN FLIGHT.  AC DIVERTED TO AND LANDED WITHOUT FURTHER INCIDENT.  INSPECTED CAPTAINS WI	NDSHIELD AND FOUND DAMAGE TO OUTER PLY.  AC FERRIED FOR REPAIR.  WINDSHIELD REMOVED, REPLACED AND LEAK CHECK PERFORMED. 	 AC RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004040500012	20040405	00012	CE  	2004	4	5	CA040310006      	1	20030918	G	7120	05510171	MOUNT           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10065	10065							(CAN) A WELD WAS DISCOVERED CRACKED IN THE LOWER PART OF THE ENGINE SUPPORT.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2004041300009	20040413	00009	NE  	2004	4	13	CA040315006      	2	20030827	G	7323	43012354	GOVERNOR        			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					OVERSPEED	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) MAIN ROTOR RPM WAS FOUND TO OSCILLATE DURING CRUISE FLIGHT AND SOMETIMES DROOP DOWN -5 RPM NR.   REPLACING FUEL CO	NTROL UNIT, FUEL PUMP AND GOVERNOR DID NOT HELP THE PROBLEM.   REPLACING THE OVERSPEED GOVERNOR ELIMINATED ALL SYMPTOMS.					1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2004041300010	20040413	00010	EU  	2004	4	13	CA040315007      	1	20030911	G	7720	406100807	LINK            			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					FLOW FENCE	BROKEN          	W				A				UNSCHED LANDING         				M			OVER TEMP                 			CR	CRUISE         	1			CA											(CAN) DURING NORMAL CRUISE FLIGHT, THE PILOT NOTICED A SUDDEN SHARP RISE IN T4 (TOT) STILL WITHIN LIMITS.   AFTER RETURN	ING TO BASE, ONE OF THE LINKS CONTROLLING THE FLOW FENCE WAS FOUND TO BE BROKEN.					1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2004071900072	20040719	00072	NE  	2004	7	19	CA040316005      	2	20031206	G	7200		ENGINE          			CNDAIR	CL600 	CL600*      	       	EA  	LYC   	ALF502	ALF502L     	41580	NE  						FOD             	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			CA											(CAN) CREW REPORTED ENGINE VIBRATION DURING DESCENT.  SUBSEQUENT TROUBLESHOOTING ON THE GROUND CONFIRMED THE VIBRATION O	N DURING ENGINE DECELERATION.  FOD DAMAGE WAS DISCOVERED IN THE ENGINE CORE AND HOT SECTION.  THE ENGINE WAS REPAIRED AN	D THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2004041600036	20040416	00036	NM  	2004	4	16	CA040323004      	1	20031203	G	2760		SWITCH          			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	PRESSURE CONTROL	INOPERATIVE     	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, REACHING 185 KTS CREW GOT AN OB SPOILER CAUTION LIGHT AT 4000 FT. REDUCING BELOW 185 CAUTION LIGHT D	ISAPPEARED, AND CAME BACK AT 185 KTS. CONFIRMED CHECKLIST ITEMS.  KEPT SPEED BELOW 200 AND RETURNED BACK TO BASE FOR A N	ORMAL LANDING.  INVESTIGATION/ACTION THE PRESSURE CONTROL SWITCH ON THE OB SPOILER DUMP VALVE WAS REPLACED IAW AMM 27-61	-28.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2004041600037	20040416	00037	NM  	2004	4	16	CA040324006      	1	20031211	G	5260	85217051101	GOOSENECK ASSY  			BOMBDR	DHC8  	DHC8400     	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R408	CR4086123F17	EU  	AIRSTAIR DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OPERATORS HAVE REPORTED FINDING FOUR AIRSTAIR DOOR GOOSENECKS CRACKED / BROKEN IN THE FORWARD POSITION.  IT WAS AL	SO FOUND ON TWO AIRCRAFT THAT THE FASTENERS WERE CORRODED AT THE DOOR PIVOT POINT.  A FLEET CAMPAIGN TO INSPECT AND LUBE	 THESE FASTENERS IS BEING CARRIED OUT. NOTE, MANUFACTURER OF THE DOOR AND THE GOOSENECK IS MHI.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P17BO	 
2005011300020	20050113	00020	CE  	2005	1	13	CA040325001      	1	20030920	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					COCKPIT	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA											(CAN) INNER PLY ON CAPTAINS WINDSHIELD INSTANTLY SHATTERED AT APPROXIMATELY 28,000 FT, CAUSING THE CREW TO COMMENCE AN E	MERGENCY DESCENT AND LANDING. WEATHER WAS FAIR AT THE TIME AND THERE WAS NO WINDSHIELD HEAT ON.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2004070900087	20040709	00087	GL  	2004	7	9	CA040405003      	1	20031217	G	2730		CARTRIDGE       			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360ES     		SO  					ELEVATOR	FAILED          	B				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	15	938CD					1338				ON APPROACH, PILOT DISENGAGED AUTOPILOT, FOUND ELEVATOR CONTROL TO BE STUCK IN FIXED POSITION, PITCH TRIM CONTROL WAS ST	ILL AVAILABLE BOTH UP AND DOWN. AFTER SEVERAL ATTEMPTS TO (FREE) CONTROL WITH NO SUCCESS THE PILOT "JERKED" CONTROL BACK	. CONTROL BROKE FREE ENOUGH TO PROVIDE "UP" ELEVATOR CONTROL. PILOT LANDED WITHOUT INCIDENT.  AC WAS MOVED INTO HEATED H	ANGAR WHERE INITIAL INSPECTION REVEALED ELEVATOR TO BE VERY DIFFICULT TO MOVE IN EITHER DIRECTION.  ELEVATOR WAS ABLE TO	 BE MOVED TO FULL TRAVELS IN BOTH DIRECTIONS WITH RELATIVE EASE ALTHOUGH PITCH TRIM CARTRIDGE MADE MORE "NOISE" THAN NOR	MAL. PITCH TRIM CARTRIDGE WAS REMOVED AND REPLACED WITH NEW PART. REMOVED PART WAS INSPECTED WITH NO ANOMALIES NOTED.	1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2004071200202	20040712	00202	GL  	2004	7	12	CA040407012      	3	20030326	G	6114		HUB             	MCAULY      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						R777080					(CAN) PROPELLER FOUND CRACKED AT BOLT HOLES WHILE COMPLYING WITH AD 2003-12-05.  PROPELLER WAS PREVIOUSLY NOT CRACKED WH	ILE COMPLYING WITH AD 97-06-16 (PREVIOUS VERSION OF 2003-12-05).  TWO RADIAL 1/2 INCH CRACKS AROUND TWO BOLT HOLES WERE 	LOCATED WITH LPI AND VISIBLE WITH 10X MAGNIFIER.  REMOVED PROP FROM SERVICE.  SIMILAR PROP PREVIOUSLY REMOVED FROM SERVI	CE ON ANOTHER COMPANY C-152.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2004080500099	20040805	00099	WP  	2004	8	5	CA040413004      	1	20030813	G	6210		BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PIN FAILURE,  SHEARED AT TOP THREAD OF THREADED SHANK FOR ADJUSTER NUT.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2004080500100	20040805	00100	EA  	2004	8	5	CA040413005      	2	20030906	G	7250		TURBINE WHEEL   			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR 2 ENGINE	DAMAGED         	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA								CPPS61014			(CAN) WHEN THROTTLES WERE ROLLED TO IDLE FOR COOL DOWN A LOW GROWL WAS HEARD AT IDLE. ENGINES WERE SPUN UP TO 100 PERCEN	T AND GROWL WENT AWAY.  BOTH ENGINES WERE BROUGHT BACK TO IDLE AND NOISE WAS HEARD AGAIN.  ENGINES WERE SPOOLED UP SEPAR	ATELY AND PROBLEM WAS ISOLATED TO NR 2 ENGINE.  ENGINEER WAS NOTIFIED.  DURING BOROSCOPE INSPECTION OF NR 2 ENGINE IT WA	S DISCOVERED THAT PORTIONS OF 7 BLADES WERE MISSING.  POWER SECTION REMOVED DUE TO CT WHEEL DISTRESS.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2004080600006	20040806	00006	EU  	2004	8	6	CA040414005      	1	20030921	G	2821		FILTER          			AEROSP	ATR72 	ATR72201    	8680943	EU  	PWA   	PW120 	PW124B      	 	NE  					FUEL PUMP	CONTAMINATED    	W				E				ENGINE SHUTDOWN         				E	M		VIBRATION/BUFFET          	OVER TEMP                 		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, ENGINE ITT ROSE AND ENGINE WAS UNRESPONSIVE TO TLA INPUT. ENGINE WAS SHUT DOWN AND AN UNEVENTFUL SIN	GLE ENGINE LANDING WAS MADE. POST EVENT EXAMINATION SHOWED THAT METERING VALVE OF THE HMU WAS JAMMED BY A PIECE OF EPOXY	 MATERIAL. BORE (DOWNSTREAM) SURFACE OF FUEL FILTER SHOWED AN LARGE DEPOSIT OF EPOXY, WHICH APPARENTLY WAS AN EXCESS OVE	RFLOW OF MATERIAL USED TO SECURE END CAPS TO BARREL OF FILTER.  FURTHER INVESTIGATION BY THE SUPPLIER OF THE PUMP ASSEMB	LY HAS SHOWN THAT INCIDENT FILTER, WHILE MARKED TO BE VERY SIMILAR TO THAT OF SUPPLIER, WAS NOT, IN FACT, MADE BY SUPPLI	ER.  SUPPLIER HAVE ISSUED INSTRUCTIONS TO FIELD TO INSPECT PW100 FILTERS FOR POSSIBLE PRESENCE OF EPOXY IN BORE OF UNIT.	2	H	7	2 	4T	4	T	RT	A53EU   	E2ONE				 
2005022300147	20050223	00147	CE  	2005	2	23	CA040423002      	1	20030305	G	5312		BULKHEAD        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											DURING A SCHEDULED INSPECTION OF THE REAR PRESSURE BULKHEAD A LOCALIZED AREA OF PITTING CORROSION WAS DISCOVERED AROUND 	THE BULKHEAD FITTING FOR THE RELIEF TUBE CONNECTION.  THE AREA WAS CLEANED AND INSPECTED AND AN APPROVED DOUBLER REPAIR 	CARRIED OUT.  THE BULKHEAD FITTING ASSEMBLY WAS REPLACED WITH NEW TO PREVENT THE POSSIBILITY OF ANY FURTHER LEAKAGE.  AL	L OTHER AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO DEFECTS NOTED.			1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
2004080500066	20040805	00066	CE  	2004	8	5	CA040503004      	1	20030213	G	3246	95440263	WHEEL           			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE TIRE CHANGE, NDT REVEALED SEVERAL CRACKS AROUND THE FLANGE IN THE AREAS WHERE THE BRAKE ASSEMBLY SL	IDES INTO THE WHEEL HALF. WHEEL HALF REMOVED FROM SERVICE.					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2005022400009	20050224	00009	NE  	2005	2	24	CA040504007      	2	20030919	G	8530	AE92181	CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					EXHAUST PORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											CYLINDER WAS CRACKED FROM SPARK PLUG HOLE TO SPARK PLUG HOLE ON THE EXHAUST SIDE.  THE CRACK HAD OPENED UP TO A SIGNIFIC	ANT SIZE HOLE MAKING THE EXHAUST VALVE VISIBLE FROM BETWEEN THE FINS.  THE LEAKING EXHAUST GASES HAD BURNED AWAY A PORTI	ON OF THE FINS AROUND THE OPENING.				1	H	7	1 	3R	3	R		A815    	5E2				 
2005022400011	20050224	00011	CE  	2005	2	24	CA040506001      	1	20031121	G	5511	07326031	SPAR            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											REMOVED HORIZONTAL STABILIZER.  REAR SPAR REINFORCEMENT PART NUMBER 0732603-1 CHANGED.  AFT ATTACHEMNT POINT REINFORCEME	NT BRACKET RT PART NUMBER 0732101-4 REPLACED WITH NEW.  ADJACENT RIVETS REPLACED.  SERVICE KIT SK185-27 INSTALLED TO FAC	ILITATE SCREW JACK REMOVAL.  LT TRIM JACK REMOVED.  NEW SCREW PART NUMBER 0712500-11 INSTALLED.  TRIM JACK REINSTALLED. 	 RIGGED AND SAFETIED AS PER CESSNA MANUAL.			1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
2005030800026	20050308	00026	EU  	2005	3	8	CA040528004      	1	20031023	G	6310	330A32600000	FREEWHEEL UNIT  			SNIAS 	SA330 	SA330J      	8680612	EU  	TMECA 	TURMO4	TURMO4C     	60008	EU  					M/R GEARBOX	FAILED          	W				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			CA											ON START UP, ROTORS BEGAN TURNING.  A LOUD BANG HEARD.  START ABORTED.  INSPECTION REVEALED T/R SHAFT SEGMENT TWISTED AT	 NR 5 SHAFT.  FREEWHEEL SLIPPED MOMENTARILY AND RE-ENGAGED.  TRANSMISSION SENT TO FRANCE FOR DISASSEMBLY.  SPRING IN FRE	EWHEEL FOUND BROKEN.  ENGINE INSPECTED BY MANUFACTURE.  ALL SHAFTING REPLACED.  GEARBOXES IN T/R SYSTEM INSPECTED, FUSEL	AGE AND T/BOOM VISUALLY AND NDT INSPECTED, HEAD AND M/R BLADES INSPECTED (VISUALLY & NDT).  TRANSMISSION, MOUNTS VISUALL	Y AND NDT INSPECTED.  ALIGNMENT CHECKS OF A/F AND ENGINE MOUNTS CONDUCTED.		2	G	7	2 	4U	4	U		H4EU    	E10EU				 
2005030800036	20050308	00036	SW  	2005	3	8	CA040531005      	1	20031203	G	6230	214010404111	SUPPORT         			BELL  	214   	214B1       	1182105	SW  	LYC   	T55   	T5508D      	41555	NE  					SWASHPLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A1900242					DURING AN INSPECTION CHECK ON THE SWASH PLATE THE FRICTION WAS NOTED AS VERY TIGHT.  UPON DISASSEMBLY, IT WAS FOUND THAT	 ONE OF THE FOUR BEARINGS RIDING ON THE SUPPORT HAD LOST IT'S 'COATING' ENTIRELY. THE RESULTING METAL/METAL CONTACT WORE	 INTO THE SUPPORT, CAUSING THE FRICTION TO STIFFEN.  THE SUPPORT AND ALL FOUR BEARINGS WERE SUBSEQUENTLY SCRAPPED.				2	G	7	1 	4U	4	U		H6SW    	E4NE				 
2004072900041	20040729	00041	NE  	2004	7	29	CA040602009      	2	20030530	G	8530	356995	CYLINDER        			DOUG  	DC6   	DC6B        	3021712	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			DE	DESCENT        	1			CA								P35500			(CAN) DURING DESCENT, NR 2 ENGINE BACKFIRED, THE FLIGHT CREW MOVED THE MIXTURE TO RICH, THE ENGINE STABILIZED FOR 2 MINU	TES. THE ENGINE BACKFIRED AGAIN AND THE ENGINE WAS SHUT DOWN AND THE PROPELLER WAS FEATHERED. THE AIRCRAFT LANDED WITHOU	T INCIDENT. UPON INVESTIGATION BY MAINTENANCE IT WAS NOTED THAT THE EXHAUST EAR ON CYLINDER NR 18 WAS CRACKED. THE CYLIN	DER WAS REPLACED, THE ENGINE WAS GROUND RUN AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	4 	4R	4	R	 	6A4     	E264	6	C	P871	 
2004072900083	20040729	00083	CE  	2004	7	29	CA040604005      	1	20030522	G	5412		BULKHEAD        			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	LT NACELLE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED ENGINE CHANGE THE LT CANTED BULKHEAD ASSEMBLY  ENGINE MOUNT STRUCTURE WAS FOUND TO HAVE BEEN DA	MAGED BY EXHAUST GASES. THE INDIVIDUAL PARTS REQUIRING REPLACEMENT ARE AS FOLLOWS. 0851500-47 CAP0851500-39 CHANNEL 0851	601-201 WEB FORWARD 0851601-27 WEB AFT.  THE IPC DOES NOT GIVE A ASSEMBLY OR PN FOR THE CANTED BULKHEAD ITSELF.				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P25EA	 
2004072900010	20040729	00010	SO  	2004	7	29	CA040622003      	2	20030925	G	8520		CRANKCASE       			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CRANKCASE WAS DISCOVERED CRACKED NEAR OIL CAP LOCATION. CRANKCASE REPLACED.						1	H	7	1 	3O	3	O	NT	3A13    	3E1	5	C	P3EA	 
2004101800051	20041018	00051	EU  	2004	10	18	CA040806008      	1	20030830	G	6320	350A32108203	PLANETARY GEAR  			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					EPI CYCLIC	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M1538					(CAN) EPI CYCLIC WAS MAKING METAL.  SOURCE WAS THE PLANET GEAR INNER RACE WAS SPALLING AND MAKING METAL.						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
2004101300107	20041013	00107	SW  	2004	10	13	CA040817001      	1	20031205	G	2820	6859177	LINE            			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		AP	APPROACH       	1			CA											(CAN) FOUND A CRACK ON FLARE OF FCU SUPPLY LINE FROM FUEL PUMP.  REPLACED LINE ON SITE WITH REMOVED SERVICEABLE UNIT FRO	M ANOTHER AIRCRAFT.  LEAK CHECK C/O AND AIRCRAFT RETURNED TO SERVICE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2004101800031	20041018	00031	EU  	2004	10	18	CA040827007      	1	20031204	G	2700	27529030	MOTOR           			AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					VALVE	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						10106					(CAN) THE AIRCRAFT HAD BEEN THROUGH A MAJOR INSPECTION AT CONTRACTOR 4 MONTHS PREVIOUS. THE VALVE HAD BEEN REMOVED FOR A	CCESS TO OTHER AREAS. THE PILOT REPORTED CIRCUIT BREAKER POPPED DURING TAXI. PILOT RETURNED TO HANGAR. INVESTIGATION FOU	ND RODS CONNECTED TO VALVES WERE MISRIGGED, RESULTING IN JAMMING OF RODS, RESULTING IN OVERLOADING OF MOTOR, CAUSING CIR	CUIT BREAKER TO POP. VALVE ASSEMBLY REPLACED, RODS RIGGED IAW MM, FUNCTION CHECKED NORMAL.			2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2005030300149	20050303	00149		2005	3	3	CA040902008      	4	20031020	G	3457	CI2480100	ANTENNA         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					GPS DATA	VIBRATION       	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA											A/C ORIGINALLY EQUIPPED WITH ANTENNA MOD CI4510-700 IAW LSTC NR C-LSA02-377/D.  ANTENNA LATER RECALLED BY MANUFACTURER. 	REPLACEMENT ANTENNA MOD CI2480-100.  DURING FLT, REPLACEMENT ANTENNA VIBRATED LOUD ENOUGH TO BE HEARD IN COCKPIT. ANTENN	A REMOVED.    INSTALLED SAME ANTENNA IN SAME LOCATION. ON 2 OTHER BEECH 200'S WITH NO VIBRATION NOTICED. OPERATORS HAVE 	BEEN KEPT ADVISED OF SITUATION WITH OTHER A/C. SPECS SHEET FOR CI2480-100 ANTENNA  STATED 350KTS TAS MAX & A CEILING OF 	55,000'. SPECS SHEET FOR CI2480-100 ANTENNA TODAY STATES 210KTS IAS MAX AT 10,000' & CEILING OF 20,000 FT. ANTENNA MANUF	ACTURER WILL BE CONTACTED FOR CLARIFICATION.	1	L	7	2 	4T	4	T		A24CE   	E4EA				 
2004111000061	20041110	00061	SW  	2004	11	10	CA041001001      	1	20030922	G	2913	8505141	DRIVE GEAR      	PARKERHANFIN		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TACH DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BD01509					(CAN) DURING A NORMAL O/H OF THE PUMP ASSY MPI INSP OF THE DRIVEN GEAR FOUND A CRACK ON THE TACH DRIVE END OF THE SHAFT.	  THE CRACK WAS IN THE CORNER OF THE SQUARE DRIVE.  PUMP GEARS REPLACED.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005012400016	20050124	00016	SW  	2005	1	24	CA041005003      	1	20030409	G	2197		WIRE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HEATER	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA							2656				(CAN) CASEY HEATER BLOWER MOTOR CIRCUIT BREAKER TRIPPED TWICE DURING THE FIRST 2 HOURS OF USE AFTER MOTOR OVERHAUL. INSP	ECTION REVEALED THAT THE CASEY HEATER POWER WIRE BETWEEN THE CB SWITCH AND THE CAPACITOR WAS 16 GAUGE. THE CASEY INSTALL	ATION INSTRUCTIONS CALL FOR 10 GAUGE WIRE. REPLACED 16 GAUGE WIRE WITH 10 GAUGE WIRE. INSTALLED NEW 35 AMP CIRCUIT BREAK	ER DUE TO AGE. INSTALLED PANEL AMP  METER BETWEEN COB AND BLOWER AND RAN FAN TO VERIFY AMP DRAW.  AMP DRAW DETERMINED TO	 BE 43 AMPS AT START UP AND 23 AMPS CONTINUOUS. SYSTEM OPERATING NORMAL.		1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2005020100076	20050201	00076	NM  	2005	2	1	CA041201004      	1	20031129	G	5330		SKIN            			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TWO INCH CRACK WAS FOUND ON OUTER FUSELAGE BETWEEN STA 727A, 727B AT STR. 16L. FUSELAGE CRACK REPAIRED IAW SRM 53-	30-3 FIG.48 SHEET 34 DETAIL XII. TIMES- 59472:22 CYCLES- 54285.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2006070500176	20060705	00176	EA  	2006	7	5	CA060206011      	2	20030523	G	8520		PISTON RING     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	NR 6 CYLINDER	SEIZED          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				2193 							(CAN) AIRCRAFT WAS AIRBORNE FOR APPROXIMATELY 10 MINUTES WHEN ENGINE OIL TEMPERATURE OBSERVED HIGHER THAN USUAL. ENGINE 	SEEMED TO RUN ROUGH, AIRCRAFT RETURNED TO AIRPORT AND LANDED WITHOUT INCIDENT. UPON INSPECTION FOUND NR 6 CYLINDER IN AN	 ALMOST SEIZED CONDITION. RINGS WERE SEIZED TO PISTON. CYLINDER ASSEMBLY REMOVED FROM SERVICE AND NEW ASSEMBLY INSTALLED	. GROUND RUNS COMPLETED NO FURTHER FAULTS NOTED. (TC NR 20060206011)			1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2003061700231	20030617	00231	EU  	2003	6	17	CCHA087050       	1	20030609	G	6330	L633M2010101	MOUNT           			UROCOP	EC135 	EC135T1     	5620026	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					GEARBOX	FAILED          	H			CCHA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	911CK	1386 				0138	30169			ARIS MOUNT FAILED INSPECTION. REPLACED ARIS MOUNT						1	G	7	2 	3U	3	U	 	H88EU   	E34NE				 
2003042900067	20030429	00067		2003	4	29	CDFROTW1         	4	20030425	G	2562	452013002	BATTERY         	ARTEX       	100HM       	BELL  	204   	UH1H        	1181407	SW  										ELT	LEAKING         	B			CF0R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	497DF				64677	11533				AT REMOVAL OF ELT BATTERY AT POSTED REMOVAL DATE IT WAS DISCOVERED THE BATTERY PACK HAD LEAKED AND CORRODED COMPONENTS W	ITHIN THE CASE.  THERE WAS ALSO A CRACK NOTED ON THE BATTERY CASE WHICH APPEARS TO BE CAUSED BY OVER HEAT OR OVER PRESSU	RE.  THE ELT IS CHECKED EVERY 100 HRS AND APPEARED TO BE WORKING CORRECTLY.  THE MANUFACTURER WAS NOTIFIED OF THE PROBLE	M.  NO CAUSE HAS BEEN DETERMINED.			1	G	7	1 	4U			 	EXPA1G71					 
2003020500027	20030205	00027	CE  	2003	2	5	CE03SDRM0001     	1	20030121	G	2520	3034242ABS	SEAT BACK       			LEAR  	60    	60LEAR      	5170707	CE  										CABIN	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03		2410 				175				AIRCRAFT ARRIVED AT REPAIR STATION WITH DISCREPANCY INDICATING THAT A PASSENGER SEAT BACK WAS BROKEN.  PRELIMINARY INSPE	CTION FOUND SEAT BACK CRACKED ALONG ENTIRE LOWER LENGTH AT THE 8 HOLES USED FOR ATTACHMENT OF UPHOLSTERY.  SENT SEAT BAC	K TO ERDA WHO INDICATED THAT THE HOLES FOR THE UPHOLSTERY ATTACHMENT IS AN UNAUTHORIZED ALTERATION PERFORMED BY WHOEVER 	COVERED THE SEAT.  THE HOLES ARE NOT SUPPOSED TO BE THERE.  INSPECTED 3 OTHER LEARJET MODEL 60 SEATS AND FOUND THE SAME 	HOLES.  FINDINGS WERE DISCOVERED AT JETCORP, CRS DELR158D.		2	L	7	2 	4F			RT	A10CE   					 
2004030100131	20040301	00131	WP  	2004	3	1	CHI2741          	1	20030805	G	6210	369D21100516A	BLADE           			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	CRACKED         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		3340 								WHILE PERFORMING OFF AC INSPECTION OF MAIN ROTOR BLADE, UTILIZING EDDY CURRENT, DISCOVERED ONE CRACK EMANATING FROM FIRS	T LIGHTING HOLE AT APPROX STA 36.5 IN (C) CHANNEL.  SECTION BLADE TO VERIFY EDDY CURRENT FINDINGS.  CRACK EXTENDS FROM I	D OF LIGHTING HOLE UP TO START OF BEND RADIUS.  AC PARKED STATIC WITHOUT OR IMPROPER  BLADE TIE DOWNS DURING GUSTING WIN	DS OR AROUND OTHER OPERATING AC.  EXCESSIVE TENSION ON BLADE TIE DOWNS.  MANUFACTURE DEFECT OR PRACTICES.  (K)			1	G	7	1 	3U			 	H3WE    					 
2003090200120	20030902	00120	NE  	2003	9	2	CNQ8200360111    	2	20030707	G	7200	PW525A	ENGINE          			CESSNA	560   	560XL       	2076702	CE  	PWA   	545   	PW545A      	 	NE  					RIGHT	BURNED          	B				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	15	2HB					5605222	DB0454			RT ENGINE OIL PRESSURE DROPPED ON CLIMBOUT. ALSO HAD A 10 PERCENT POWER LOSS.  PILOT SHUT DOWN ENGINE.  FOUND ENGINE HAD	 A FIRE MELTING PARTS OF ENGINE.					2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2003080500035	20030805	00035	CE  	2003	8	5	CSE001           	2	20030605	G	7414	6224	MAGNETO         			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  	MCAULY	2A34C	2A34C*      	GL  	ENGINE	MISREPAIRED     	B			NUVY	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	35	90BE					251143				ENGINE WILL NOT RUN ON LEFT MAGNETO. INSPECTION IN THE WORKSHOP REVEALED THAT THE WOODRUFF DRIVE KEY BETWEEN THE DRIVE S	HAFT AND DRIVE COUPLING WAS MISSING.					1	L	7	1 	3O	3	O	 	2A3     	E9CE	5	C	P3EA	 
2003012400013	20030124	00013	NM  	2003	1	24	DHL2003755002    	1	20030123	G	3260		LIGHT           			BOEING	727   	727225      	1384077	NM  												A			DHLA	K	O			NONE                    	OTHER                   			O			OTHER                     			AP	APPROACH       	1			SO	01	755DH					21857				1)  WHEN LANDING GEAR WAS SELECTED DOWN, LEFT MAIN GREEN LIGHT FAILED TO ILLUMINATE. SECONDARY MAIN GREEN LIGHTS WERE IL	LUMINATED. CYCLING LIGHTS DIMMER SWITCH GOT ALL GEAR LIGHTS WORKING.	2)  REMOVED AND REPLACED KORRY LIGHT ASSEMBLY IAW B	727 M/M 33-10-51 (LT GEAR). SYSTEM OPS CHECKED GOOD ON DUMMY RETRACTION IAW B727 M/M 32-30-00.				2	L	7	3 	4F			 	A3WE    					 
2003090200049	20030902	00049	CE  	2003	9	2	DXTA2003MD001    	1	20030620	G	4910	66506502	DUCT            			CESSNA	560   	560XL       	2076702	CE  										APU	MISALIGNED      	B			DXTA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	608QS	240  				5605308				INSTALLATION OF NEW UPGRADED APU STARTER/GENERATOR P/N 9912499-29 IN LIEU P/N 9912499-22, REF: CE-560XL IPC 80-11-00 FIG	 01 ITEM NR 1 AND NR 1A. THE NEW STARTER/GENERATOR END BELL IS 1INCH LONGER WHICH CAUSES A MISALIGNMENT IN THE INLET COO	LING DUCT, AND HAND WORKING FOR INSTALLATION FOR ALIGNMENT PUTS STRESS ON 4EA. METAL TABS THAT ATTACHS DUCT TO THE INLET	 PANEL 			2	L	7	2 	4F			RT	A22CE   					 
2003090300130	20030903	00130	WP  	2003	9	3	E27R1730A        	2	20030725	G	7200	31017262	TORQUE SENSOR   			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					ENGINE	OUT OF POSITION 	B				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			X	F		ENGINE FLAMEOUT           	FLT CONT AFFECTED         		CR	CRUISE         	1			WP	07	441SB	4700 				4410301	P77688			TORQUE SENSOR MATCHED CAM TENSION NUT FOUND TO BE LOOSE CAUSING LOSS OF FUEL PUMP DRIVE AND IN-FLIGHT FLAME OUT.  ENGINE	 TIMES ARE APPROX.					1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2003090300026	20030903	00026	EA  	2003	9	3	EA01             	2	20030716	G	7414	1068255511	MAGNETO         			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	01	1084B		200  			243266				ENGINE FAILED IN FLIGHT.  AIRCRAFT LANDED IN FIELD WITHOUT INCIDENT.  INVESTIGATION REVEALED THAT THE DUAL MAGNETO HAD F	AILED FROM BOTH SET OF POINTS NOT OPENING.  200 HRS ON MAGNETO SINCE OVERHAUL.  POINTS ADJUSTED BY  MECHANIC AT 100 HRS 	SINCE OVERHAUL WITHOUT REMOVING FROM ENGINE.  MAGNETO REMOVED, POINTS SET IAW MM, MAGNETO OPERATION SATISFACTORY ON TEST	 BENCH AND REINSTALLED ON ENGINE.			1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2003060600045	20030606	00045	GL  	2003	6	6	EA332003B0364    	3	20030311	G	6114	FP311A	PROPELLER       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	HUB	OVERSERVICED    	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	33	756MS	1488 				U20604205	564849	FP311A		GREASING PROP FOUND GREASE DID NOT COME OUT AFT ZERK FITTING HOLE ON SAME BLADE.  AFT/TRAILING EDGE ZERKS WERE REMOVED. 	 RATHER IT CAME OUT ANOTHER AFT GREASE ZERK FITTING HOLE.  PROP WAS REMOVED AND SENT TO PROP SHOP WHO UPON DISASSEMBLY F	OUND PROP HUB WAS COMPLETELY FILLED WITH GREASE.  IT WAS NOTED ON DISASSY THERE IS NO SEAL IN AREA WHERE GREASE GOES.  S	EAL OCCURES BY A METAL TO METAL CONTACT OF SUFACES.  TRACTOR PROP AFT GREASE ZERK.  NO MORE THAN 1 OZ (APPROX 6 PUMPS OF	 A MANUAL GREASE GUN) IS TO BE PUT IN FITTING OR UNTIL IT COMES OUT AFT ZERK HOLE.  MFG SAYS PUTTING GREASE IN FWD FITTI	NG ON TRACTOR PROP WILL (REDUCE POSSIBILITY OF GREASE BYPASSING BEARING AREA AND ENTERING HUB CAVITY.	1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P36EA	 
2003050900106	20030509	00106	CE  	2003	5	9	EAE00103         	1	20030417	G	2910	2607024324	LINE            			LEAR  	35    	35A         	5170602	CE  										HYD SYSTEM	CRACKED         	E			E18A	O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			GL	23	610GA					35A073				LOST HYDRAULIC PRESSURE WHEN LANDING GEAR WAS EXTENDED. NO BRAKES AVAILABLE UPON LANDING. DRAG CHUTE DEPLOYED TO STOP AI	RCRAFT.					2	L	7	2 	4F			 	A10CE   					 
2003050900094	20030509	00094		2003	5	9	EC3R200300001    	4	20030424	G	2330	145111	CONTROLLER      			GULSTM	GV    	GV          	3980116	SO  										ENTERTAIN SYS	CORRODED        	B			EC3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05						515				DURING A ROUTINE SCHEDULED INSPECTION, PASSENGER CABIN ENTERTAINMENT SYSTEM CONTROLLER P/N 1451-1-1 AND 1-1-2 COMPONENTS	 WERE BEING REPLACED DUE TO CUSTOMER REQUEST, PRIOR TO INSTALLATION A BENCH CHECK WAS PERFORMED ON UNITS AND THE UNITS F	AILED TEST. UPON OPENING THE COVER OF THE UNITS FOR INSPECTION, CORROSION WAS NOTED ON THE INSIDE OF THE UNIT DUE TO THE	 INTERNAL 12 VOLT GELPACK BATTERY LEAKING, CORRODING INTERNAL IC COMPONENTS.  UNITS INSTALLED IN THE AIRCRAFT EXHIBITED 	SIGNS OF CORROSION ALSO. UNITS CAN BE INSTALLED AT VARIOUS LOCATIONS WITHIN THE PASSENGER CABIN AND MAY BE INSTALLED ON 	VARIOUS OTHER MODEL AIRCRAFT.	2	L	7	2 	4F			RT	A12EA   					 
2003050900112	20030509	00112	CE  	2003	5	9	EC3R200300002    	1	20030425	G	2520	613132421	STUD            			CESSNA	172   	172A        	2072404	CE  										SEAT	CRACKED         	B			EC3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	142H					47245				DURING AN UNSCHEDULED INSPECTION IT WAS NOTED THAT THE PASSENGER SEAT ATTACHMENT STUD WAS CRACKED AT THE LOBE. A REPLACE	MENT STUD WAS PROCURED AND INSTALLED AND UPON TORQUING THIS STUD TO THE SPECIFIED VALUE IT ALSO CRACKED. A RANDOM INSPEC	TION OF OTHER G-IV AIRCRAFT AT THIS FACILITY REVEALED CRACKED SEAT STUDS AS WELL. A TOTAL OF TWELVE (12) SEAT STUDS WERE	 FOUND TO BE CRACKED IN THIS SPECIFIC AIRCRAFT.			1	H	7	1 	3O			 	3A12    					 
2003123000087	20031230	00087	CE  	2003	12	30	ENHA200320002    	1	20031212	G	5412	1019100383	BULKHEAD        			BEECH 	200   	200BEECH    	1152920	CE  										RT NACELLE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90PB	12272				BB125				RT NACELLE WAS WEARING AND CRACKING AT CONTACT WITH RT AFT LOWER COWL.  REPLACED BULKHEAD.						1	L	7	2 	4T			 	A24CE   					 
2003123000024	20031230	00024	CE  	2003	12	30	ENHA20032002A    	1	20031217	G	5412	1019100383	BULKHEAD        			BEECH 	200   	200BEECH    	1152920	CE  										RT NACELLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90PB	12272				BB125				RT NACELLE WAS WEARING AND CRACKING AT CONTACT WITH RT AFT LOWER COWL. REPLACED BULKHEAD						1	L	7	2 	4T			 	A24CE   					 
2003111700094	20031117	00094	GL  	2003	11	17	EOO2003F00003    	2	20030913	G	7323	23065121	SHAFT           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GOVERNOR	SEIZED          	B			EOOR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AL	03	CGPHC		869  			180257D				PILOT COMPLAINED OF AN ERRATIC GOV.  FOUND THROTTLE SHAFT SEIZED.  REPLACED UNIT.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003011500143	20030115	00143		2003	1	15	ERAA082930       	4	20030102	G	3442	40008330208	INDICATOR       			SKRSKY	S61   	S61N        	8142104	NE  										COCKPIT	INTERMITTENT    	H			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01		1056 								RADAR UNIT BLINKS ON & OFF.  FOUND RADAR UNIT TO BE INTERMITTANT.  RADAR UNIT HAD MAJOR WATER DAMAGE. REPAIRED TRACES, R	EMOVED CORROSION AND TESTED.					2	G	7	2 	4U			 	1H15    					 
2003042300073	20030423	00073	NE  	2003	4	23	ERAA085141       	1	20030212	G	6210	6117020201067	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  										MAIN ROTOR	DAMAGED         	H			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01		4301 								MAIN ROTOR BLADE HAS BLACK BIM.  SENT FOR REPAIR.  INSPECTED IAW SRM SA 4045-31E CHAPTER / SECTION 65-10-01 REV 5.  PERF	ORMED 2 DAY LEAK CHECK IAW SER 50908; REPLACED BIM TRANSDUCER AND REINSTALLED BIM; RECHARGED SPAR IAW S-61N MM SA4045-80	 REV MARCH 1, 1978 AT 4301.3.				2	G	7	2 	4U			 	1H15    					 
2003052800033	20030528	00033	SW  	2003	5	28	ERAA086443       	1	20030425	G	6510	212040600005	HANGER ASSY     			BELL  	412   	412         	1182202	SW  										T/R DRIVE	VIBRATION       	H			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	169EH	12002				33064				HANGER ASSY HAS HIGH FREQUENCY VIBRATION.  COUPLING AND BEARING HANGER WERE PAINTED WITH PRIMER.  NO DEFECTS NOTED FOR V	IBRATION. DISASSEMBLED, STRIPPED PRIMER FROM COUPLINGS, CLEANED & VISUALLY INSPECTED ALL PARTS.  HAD COUPLING CAD PLATIN	G TOUCHED UP.  REASSEMBLED IAW 412 CR&O INSTALLING NEW SEAL & ALL SERVICEABLE PARTS.  PURGED BEARING WITH MOBIL 28 GREAS	E & REPACKED FLEX COUPLING WITH GREASE DATED 9-20-01.			1	G	7	2 	4U			 	H4SW    					 
2003070100085	20030701	00085	EU  	2003	7	1	ERAA087074       	1	20030514	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	CRACKED         	H			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	294EH	13186				S675				TAILROTOR ASSY HAS CRACKED INNER SLEEVE BUSHING, CONTROL LEVER CLOSE TOLERANCE BOLT WORN. ACTION TAKEN:  C/W  PRELIMINAR	Y INSPECTION AND FOUND INNER SLEEVE BUSHING CRACKED.  DISSASSEMBLED, REMOVED PAINT,  PRIMER AND VISUALLY INSPECTED ALL P	ARTS.  INSTALLED NEW RING, NEW BUSHINGS IN BLADE GRIPS AND INNER SLEEVE BUSHINGS.  MACHINE AND NDT INNER SLEEVE BUSHINGS	.  SEE NDT TEST.  INSTALLED NEW CLOSE TOLERANCE BOLT AND BUSHING INCONTROL LEVERS, NEW GRIP SEALS, C/W 1200 HR / 2400 HR	 6 YR INSPECTION ON TAILROTOR.  COMPLIED WITH  300 HR/ 2400 HR BLADE INSPECTION.  REASSEMBLED TAILROTOR WITH NEW WASHERS	, NUTS.  STATIC BALANCED.  INSPECTION IAW MM CHAP 33, 34, 101 TABLE 101-10.1 &107  TT 13186.1  TSI -0-.	1	G	7	2 	3U			 	H3EU    					 
2003070100086	20030701	00086	EU  	2003	7	1	ERAA087075       	1	20030514	G	3212	D24873102	FLOAT           			BOLKMS	105   	BO105S      	5626006	EU  										MLG	WORN            	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01		6354 								RT FLOAT ASSY IS DUE 6 MONTH INSPECTION.  FLOAT ASSY HAS WORN FLOAT COVER, LEAKING BAG.   6 MONTH INSPECTION COMPLIED WI	TH AND REPLACED COVER AND BAG.   AD AND SB COMPLIED WITH:  ERA AAIP, AIR CRUISER M/M AND SB'S 120-81-3, 120-81-4, 120-82	-4, 120-84-1, 802-25-1, 802-25-2.				1	G	7	2 	3U			 	H3EU    					 
2003070100087	20030701	00087	EU  	2003	7	1	ERAA087076       	1	20030514	G	3212	D24873101	CHECK VALVE     			BOLKMS	105   	BO105S      	5626006	EU  										LT FLOAT ASSY	INOPERATIVE     	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	294EH	11470				S675				LT FLOAT ASSY DUE 6 MONTH INSPECTION, HAS BAD CHECK VALVE.   CA:  COMPLIED WITH 6 MONTH INSPECTION. COMPLIED WITH AAIP, 	AIR CRUISER M/M AND 120-81-3, 120-/1-4, 120-82-4. 120-84-1, 802-25-1, 802-25-2.					1	G	7	2 	3U			 	H3EU    					 
2003070100088	20030701	00088	EU  	2003	7	1	ERAA087077       	1	20030514	G	3212	D24762102	FLOAT           			BOLKMS	105   	BO105S      	5626006	EU  										MLG	LEAKING         	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	149EH	252  				S705				FLOAT BAG LEAKS AT SEAMS.   PATCHED 4 PIN HOLES AND TESTED.						1	G	7	2 	3U			 	H3EU    					 
2003070100089	20030701	00089	EU  	2003	7	1	ERAA087078       	1	20030514	G	3212	D24873102	FLOAT           			BOLKMS	105   	BO105S      	5626006	EU  										MLG	LEAKING         	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	129EH					580				RT FLOAT ASSY DUE 18 MONTH INSPECTION.   18 MONTH INSPECTION COMPLIED WITH AND REPAIRED LEAKS.  COMPLIED WITH AAIP, AIR 	CRUISER M/M SB'S 120-81-3, 120-81-4, 120-82-4, 120-84-1, 802-25-1, 802-25-2.					1	G	7	2 	3U			 	H3EU    					 
2003070100090	20030701	00090	EU  	2003	7	1	ERAA087079       	1	20030515	G	6520	4619002003	GEARBOX         			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	MAKING METAL    	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	130EH	11727				558				GEARBOX MAKING METAL.  FOUND GEAR SET HAS PITTING ON TEETH, SCRAPPED GEAR SET, FOUND PITTING ON TAPERED ROLLER BEARINGS 	OUTER RACES.  OVERHAULED GEARBOX ASSY IAW REM 304 AND SB BO-105-30-109.  COMPLIED WITH SB BO-105-30-109, INSTALLED NEW P	INION AND BEVEL GEAR, ALL NEW BEARINGS, SEALS AND PACKINGS.  ADJUSTED BACKLASH, DISTANCE AND PATTERNS AS REQUIRED.  COMP	LIED WITH SB BO-105-30-109, ASB BO-105-30-111.			1	G	7	2 	3U			 	H3EU    					 
2003070100091	20030701	00091	EU  	2003	7	1	ERAA087080       	1	20030515	G	6420	10531714	ROTOR HEAD      			BOLKMS	105   	BO105A      	       	EU  										TAIL ROTOR	CRACKED         	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	291EH	13361				S842				INNER SLEEVE BUSHING CRACKED.  PITCH CHANGE BUSHINGS WORN.   DISASSEMBLED FOR INSPECTIONS PERFORMED VISUAL AND NDT INSPE	CTIONS AS REQUIRED REPAIRED WORN, DAMAGED AND CORRODED PARTS.  COMPLIED WITH 1200HR / 6 YEAR INSPECTGION ON HUB.  300 AN	D 2400 HR BLADE INSPECTONS DONE.   REASSEMBLED, TORQUED AND SAFETIED AS REQUIRED.  INSTALLED 2 SERVICEABLE BLADES AND ST	ATIC BALANCED.  INSPECTED AND REPAIRED IAW BO105-REM301, MM CH 3334,101 AND 107.  TT 13361.3			1	G	7	2 	3U			 	H3EU    					 
2003070100092	20030701	00092	EU  	2003	7	1	ERAA087081       	1	20030515	G	3212	D24762102	FLOAT           			BOLKMS	105   	BO105S      	5626006	EU  										MLG	FAILED          	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	125EH	981  				S562				THIS INFO FOR FAA SDR.  RT FLOAT BAG HAS A HOLE AROUND TOP OFF VALVE.  C/A:  REPLACE 2 EA TOP OFF VALVES, REPLACED 1 EA 	PATCH, C/W 6 AND 18 MONTH INSPECTIONS.					1	G	7	2 	3U			 	H3EU    					 
2003070100093	20030701	00093	SW  	2003	7	1	ERAA087082       	1	20030515	G	6730	212076004101	SERVO           			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	VIBRATION       	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	418EH	8482 				33032				TAIL ROTOR SERVO HAS HIGH FREQ BUZZ IN TAIL ROTOR PEDALS WITH HYD SYSTEM TURNED ON.   HAS CYLINDER WEAR, INTERNAL LEAKAG	E ON PILOT VALVES REPLACED CYLINDER AND PILOT VALVES TESTED IAW CMM.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2003070100140	20030701	00140	SW  	2003	7	1	ERAA087083       	1	20030515	G	6410		BLADE           			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	DAMAGED         	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	164EH	2484 			HB394	33004				TAIL ROTOR ASSY HAS HOLE IN BLADE TIP.  TAIL ROTOR BLADE SN A-9675 HAS VOID AT TIP.   REMOVED BLADES FROM YOKE ASSY.  IN	STALLED SERVICEABLE BLADE SN A-10483 AND TOUCHED UP PAINT ON BLADE SN 9724.  CHECKED TRUNNION CENTERING AND PURGE LUBED 	.  ASSEMBLED AND BALANCED IAW BHT-412-CR&O CH 64.				1	G	7	2 	4U			 	H4SW    					 
2003070100141	20030701	00141	SW  	2003	7	1	ERAA087084       	1	20030515	G	6410		BLADE           			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	DAMAGED         	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	164EH	1553 				33004				THIS INFO FOR FAA SDR.  HOLE IN BLADE TIP AND FEATHERING BEARINGS LOOSE.  PITCH HORN BUSHINGS MISSING.  FEATHERING BEARI	NGS WORN AND BLADE HAD VOID AT TIP.  TRUNNION BEARINGS HAD SOME ROUGHNESS. ACTION TAKEN:  DISASSEMBLED, CLEANED &  VISUA	LLY INSPECTED PARTS.  REASSEMBLED IAW 412-CR&O INSTALLING SERVICEABLE BLADE, NEW TRUNNION ORGS & SEALS, NEW PITCH HORN B	USHINGS, MARVEL BALANCED, TORQUED AND SAFTIES IAW 412-CR&O CH 64.  COMPLIED WITH TB 412-95-134.			1	G	7	2 	4U			 	H4SW    					 
2003070100142	20030701	00142	SW  	2003	7	1	ERAA087085       	1	20030515	G	6220		SPINDLE         			BELL  	412   	412         	1182202	SW  										M/R HEAD	DAMAGED         	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	169EH	15608			AAD00017M	33064				THIS INFO FOR FAA SDR.  M/R HEAD DUE ERA SPINDLE INSPECTION.  SINDLE SN A-356 HAD THREAD DAMAGE BEYOND LIMITS IAW 412-CR	 AND 0 CH. 62 (SCRAPPED)  C/A:  REMOVED SPINDLES AND VISUALLY INSPECTED ALL PARTS.  C/W ERA SPINDLE INSPECTION AND TB 41	2-03-190.  INSPECTED AND REASSEMBLED IAW 412-CR AND O CH 62 AND TB 412-03-190.  PURGE LUBED ARM AND CLEVIS ASSEMBLY WITH	 OBIL 28 GREASE.  REASSEMBLED WITH ORIGINAL SERVICEABLE BOLTS.  COMPLIED WITH TB 412-03-190 ERA 412 SPINDLE INSPECTION.			1	G	7	2 	4U			 	H4SW    					 
2003070100143	20030701	00143	GL  	2003	7	1	ERAA087086       	2	20030516	G	7321	252464430NH	FUEL CONTROL    			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	SURGES          	E			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	292EH	13364				562				ENGINE SURGES AT HIGH POWER SETTINGS.   REPAIRED AND TESTED IAW MFG OHM FORM 15-602E.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2004020500101	20040205	00101	CE  	2004	2	5	EWG2003F00001    	1	20031103	G	2797		WIRE            			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					SPEED BRAKES	CHAFED          	B			EWGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	92ND					5250186				PILOT REPORTS (SPEED BRAKE) CIRCUIT BREAKER POPS EVERY TIME SPEED BRAKES EXTEND MANUALLY OR IN AUTO MODE  PROBLEM WAS IS	OLATED TO A CHAFED WIRE BETWEEN PIN 5 AND PIN X AT CONNECTORS JR004 AND PS003.  THE WIRE WAS ARCING AGAINST THE RT ENGIN	E MOTIVE FLOW LINE PN 631600052 LOCATED BEHIND ACCESS PANEL 192CR CAUSING A PIN HOLE AND SUBSEQUENTLY A FUEL LEAK AGGRAV	ATING THE DANGER.  THE WIRE IN QUESTION IS ROUTED IN A BUNDLE AROUND THE FUEL SUPPLY LINE TO THE ENGINE AND THE MOTIVE F	LOW LINE.  THE WIRE WAS REPAIRED IAW WM AND SECURED AWAY FROM ANY OTHER ADJACENT STRUCTURE OR TUBING.  MOTIVE FLOW LINE 	REPLACED.	1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2003091200118	20030912	00118	GL  	2003	9	12	FCPR200300011    	3	20030811	G	6111		SEPARATOR       			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	3A32C	D3A32C*     	GL  	NR 3 BLADE	LEAKING         	B			FCPR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	09	5004E	25   				50304				FOUND 1 BALL BEARING MISSING FROM BLADE NR 3, PN A1634-9, SEPARATOR PN B5223.						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P21EA	 
2003082600104	20030826	00104		2003	8	26	FCPR20030010     	4	20030506	G	2210	KFC325	AUTOPILOT SYS   			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A6       	52043	EA  					COCKPIT	MALFUNCTIONED   	B			FCPR	O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NM	09	700PX	48   				249				PILOT REPORTED THAT WHILE FLYING IN IMC CONDITIONS WITH AUTO PILOT ENGAGED IN HEADING MODE, HE COMMANDED A COURSE CHANGE	 AND THE AUTOPILOT PERFORMED A TURN IN THE OPPOSITE DIRECTION.  CONDUCTED AT P-STATIC TEST AND FOUND SEVERAL STATIC WICK	S NOT BONDED CORRECTLY, ALSO  FOUND THAT WHEN HIGH VOLTAGE APPLIED TO THE PROPELLER THE AUTOPILOT WOULD TURN ITSELF ON A	ND RANDOMLY GO INTO DIFFERENT MODES.  THE AUTOPILOT AND AIRFRAME MANUFACTURES HAVE BEEN CONTACTED.			1	L	7	1 	3T	3	T	RT	A60EU   	E4EA				 
2003031300113	20030313	00113	CE  	2003	3	13	FJC3869          	1	20030224	G	2810	10092007117	ADAPTER         			BEECH 	200   	200BEECH    	1152920	CE  										FUEL CELLE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	553R	9400 				BB589				WHILE PERFORMING MAINTENANCE TO REPAIR A FUEL LEAK THE TECHNICIAN NOTICED CORROSION ON DEFUEL ADAPTER PLATE IN NACELLE T	ANK. FURTHER INVESTIGATION FOUND SIGNIFICANT CORROSION ON DEFUEL ADAPTER PLATE ASSY. THIS PLATE ALSO SUPPORTS THE BOTTOM	 PORTION OF THE NACELLE FUEL PROBE. SECTION 28-40 OF THE KING AIR MM COVERS THE RECURRING 30 MONTH INSPECTION OF THE NAC	ELLE FUEL PROBE FOR CORROSION AND CONTAMINATS. THIS PORTION OF THE PLATE ASSY. IS DIFFICULT TO SEE. MOISTURE IN THE LOW 	PART OF THE NACELLE TANK CAUSED CORROSION.		1	L	7	2 	4T			 	A24CE   					 
2003042900046	20030429	00046	CE  	2003	4	29	FJC4285          	1	20030411	G	2730	AN414	BOLT            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ELE BELLCRANK	BENT            	B			CTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	234PS	3469 				340A0368				DURING INSPECTION OF THE ELEVATOR SYSTEM THE TECHNICIAN DISCOVERED THE ELEVATOR BELLCRANK BOLT BENT.  WE HAVE FOUND SEVE	RAL BENT IN OUR FLEET, AND WOULD SUGGEST THAT ALL OPERATORS HAVE THE BOLT AND BEARING INSPECTED AS SOON AS POSSIBLE.					1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2003042300173	20030423	00173	CE  	2003	4	23	FLTICE0303002    	1	20030318	G	3010	CT464	CONTROL PANEL   			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					COCKPIT	ERRATIC         	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	03	77CF					21062679				CPS-OWNER FOUND THAT THE TKS QUANTITY INDICATOR FLUCTUATES IN FLIGHT FROM 9.8 TO LOWER LEVELS. THIS PROBLEM IS INTERMITT	ENT. REPLACED QUANTITY INDICATOR.					1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003082600100	20030826	00100	WP  	2003	8	26	FRISBY03003      	1	20030327	G	2910	41022021	HOUSING         			DOUG  	DC9   	DC982       	3022082	WP  										HYD SYSTEM	CRACKED         	B			UFHR	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			SO	05	ISMEV				627	49669				AFTER TAKEOFF FLIGHT NR IG81 I-SMEV (MSN 49669) HAD FLIGHT INTERRUPTION, DIVERTED AFTER HYD SYST MALFUNCTION.  LANDING G	EAR WAS RETRACTED, NLG REMAINED EXTENDED WITH (RED) LIGHT (ON), LT AND RT HYD SYST PRESS WAS (0) PSI, AND (L/R HYD PRESS	) ADV ON EOAP.  ABNORMAL PROCEDURE WAS CARRIED OUT, SOON AS TRANSFER PUMP WAS SWITCHED (OFF), HYD PRESSURE CAME BACK AND	 NLG RETRACTED.  LT HYD OIL QUANTITY WAS 3 QUARTS,WITH (AMBER) LIGHT (ON).  ANALYSIS INDICATED LOSS OF PRESS IN BOTH HYD	 SYS WAS DUE TO FAILURE OF PTU, P/N 4100310-6, S/N 627, SO PTU WAS REMOVED FOR REPAIR. INSP REVEALED DRAIN PORT HSG., P/	N 4102202-1 WAS CRACKED COMPLETELY AROUND CIRCUMFERENCE.  PTU WAS SUBJECT OF PREVIOUS SB AND AD AND INCIDENT RPT 016/03.	2	L	7	2 	4F			 	A6WE    					 
2004022300035	20040223	00035		2004	2	23	GARMINGTX327     	4	20031215	G	3452	0110049000	TRANSPONDER     			PIPER 	PA44  	PA44180     	7104402	SO  										ATC SYSTEM	FALSE INDICATION	D				O				OTHER                   				H	J	S	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        	AFFECT SYSTEMS            	AP	APPROACH       	1			EA	27	633TA	1174 	341  			4496052				LANDING GEAR FAILED TO RETRACT CAUSING DC BUS LOW VOLTAGE WARNING LIGHT TO FLASH ON AND OFF THREE TIMES UNTIL GEAR LOCKE	D UP.  UPON SUBSEQUENT A.D.I.Z. REENTRY, TRANSPONDER SET TO 0440 AS PROVIDED BY ATC.  TRANSPONDER DISPLAYED 0440 BUT TRA	NSMITTED 1200.  AIRCRAFT PROPERLY ENTERED ADIZ IAW NOTAM PROCEDURES. ATC FILED PILOT DEVIATION REPORT TO FAA FOR FAILURE	 TO SQUAWK 0440.   NOTE: REVERSE CURSOR NOT SEEN BY EITHER PILOT.			1	L	7	2 	3O			 	A19S0   					 
2003020300093	20030203	00093	GL  	2003	2	3	HDNA084070       	2	20030131	G	7230	23057142	CASE            			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CRACKED         	H			HDNA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	915SH					S340	CAE830496			ONE 4TH STAGE COMPRESSOR STATOR VANE BROKE OFF SEVERELY DAMAGING THE 4TH & 5TH STAGE COMPRESSOR BLADES WITH SUBSEQUENT C	OMPRESSOR STALLING AND LOW ENGINE POWER.					1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
2003042300075	20030423	00075	EU  	2003	4	23	HE66085914       	1	20030407	G	6330	L633M2010101	MOUNT           			UROCOP	EC135 	EC135T1     	5620026	EU  										GEARBOX	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			FS	01	135CR	763  				0164				GEARBOX MOUNT LEAKING,  REPLACED.						1	G	7	2 	3U			 	H88EU   					 
2003042300072	20030423	00072	EU  	2003	4	23	HE66085916       	1	20030407	G	6330	L633M2010101	MOUNT           			UROCOP	EC135 	EC135T1     	5620026	EU  										GEARBOX	DEFECTIVE       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	135CR	763  				0164				GEARBOX MOUNT LEAKING REPLACED						1	G	7	2 	3U			 	H88EU   					 
2003041400074	20030414	00074		2003	4	14	HE66085919       	4	20030407	G	2210	41600297006	MODULE          			UROCOP	EC135 	EC135T1     	5620026	EU  										TRIM ACTUATOR	DEFECTIVE       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	135CR					0164				AFTER INSTALLING THIS MODULE WE WERE HAVING TRIM ACTUATOR FAILURES AND AUTO PILOT WOULD NOT PASS BIT.  REINSTALLED OLD M	ODULE.					1	G	7	2 	3U			 	H88EU   					 
2003042300064	20030423	00064	EU  	2003	4	23	HE66085949       	1	20030411	G	6330	L633M2010105	MOUNT           			UROCOP	EC135 	EC135T1     	5620026	EU  										GEARBOX	FAILED          	H			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	135CR					0164				AIRCRAFT BECAME ROUGH IN FLIGHT INSPECTED MOUNTS AND NOTICED THEY FAILED						1	G	7	2 	3U			 	H88EU   					 
2003011600056	20030116	00056		2003	1	16	HEEA083015       	4	20030106	G	2312	N0001552	CONNECTOR       			BELL  	206   	206L1       	1182107	SW  										VHF ANTENNA	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3905B					45598				BNC CONNECTOR WILL NOT LOCK ALL THE WAY DOWN ON VHF ANTENNA.						1	G	7	1 	3U			 	H2SW    					 
2003011600215	20030116	00215	SW  	2003	1	16	HEEA083127       	1	20030108	G	6420		BEARING         			BELL  	206   	206L3       	1182108	SW  										DRIVE LINK	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3207Q					51540				TAIL ROTOR HEAD DRIVE LINK HAS WORN BEARINGS. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003011700011	20030117	00011	SW  	2003	1	17	HEEA083156       	1	20030108	G	6220		BEARING         			BELL  	206   	206B3       	1181506	SW  										LINK ASSY	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2268V				CT3097	3605				MAIN ROTOR HEAD LINK HAS A WORN BEARING. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003012100051	20030121	00051	SW  	2003	1	21	HEEA083253       	1	20030108	G	3212	206073926107	RELIEF VALVE    			BELL  	206   	206L3       	1182108	SW  										EMERGENCY FLOATS	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3207Q					51540				EMERGENCY FLOAT RELIEF VALVE LEAKING. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003012100103	20030121	00103	SW  	2003	1	21	HEEA083288       	1	20030109	G	7720	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TOT	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31077					51520				TOT INDICATOR INOPERATIVE. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003012100177	20030121	00177	GL  	2003	1	21	HEEA083327       	2	20030109	G	7321	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X	6971 				51552				FUEL CONTROL UNIT PRODUCING INTERMITTENT START. UNABLE TO VERIFY DIFFICULTY REPORTED.  NO DISCREPANICES NOTED.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003012100243	20030121	00243	SW  	2003	1	21	HEEA083362       	1	20030109	G	7910	4369	CAP             			BELL  	206   	206L3       	1182108	SW  										OIL TANK	DEFECTIVE       	E			HEEA	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	03	31077					51520				OIL TANK CAP AND ADAPTER DOES NOT FIT PROPERLY. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2003012700268	20030127	00268	SW  	2003	1	27	HEEA083743       	1	20030115	G	7712	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										TORQUE INDICATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				DROPS TO ZERO OR PEGS OUT INTERMITTENTLY IN CRUISE FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2003012800032	20030128	00032	GL  	2003	1	28	HEEA083785       	2	20030115	G	7200	23064570	LINER           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				ENGINE HOWL AT 63-70 PERCENT N1. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E4CE				 
2003012800033	20030128	00033	SW  	2003	1	28	HEEA083786       	1	20030115	G	7797	23065805	HARNESS         			BELL  	407   	407         	1182206	SW  										ENG INDICATING	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				HARNESS HAS HIGH RESISTANCE SHORT PIN C AND D AT TOP. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2003012800046	20030128	00046	GL  	2003	1	28	HEEA083799       	2	20030115	G	7320	23072725	HYDROMECH UNIT  			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH	3907 				53393				HMU HAS SPLINE WEAR AND UNABLE TO BLEED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E4CE				 
2003012800106	20030128	00106	SW  	2003	1	28	HEEA083850       	1	20030116	G	6230		BEARING         			BELL  	407   	407         	1182206	SW  										ROD ASSY	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH				HBFS17	53398				MAIN ROTOR HAS WORN BEARING ON ROD ASSY.						1	G	7	1 	3U			O	H2SW    					 
2003022400051	20030224	00051	NE  	2003	2	24	HEEA084172       	1	20030212	G	3243	7625001101102	MASTER CYLINDER 			SKRSKY	S76   	S76A        	8143006	NE  										BRAKE SYS	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	4253S					760035				PILOT RT MASTER CYLINDER LEAKS.						1	G	7	2 	3U			 	H1NE    					 
2003022400063	20030224	00063	NE  	2003	2	24	HEEA084184       	1	20030212	G	5246	A29261	BRACKET         			SKRSKY	S76   	S76A        	8143006	NE  										ACCESS DOOR	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546G					760076				RT TRANSMISSION ACCESS DOOR STRUT UPPER ATTACH BRACKET BROKEN. SCRAPPED.						1	G	7	2 	3U			 	H1NE    					 
2003022400076	20030224	00076	NE  	2003	2	24	HEEA084197       	1	20030213	G	7714	54487129110	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C*       	 	GL  					ENGINE N1	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4253S					760035				LIGHT INTERMITTENT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U	3	U	 	H1NE    	E4CE				 
2003022400078	20030224	00078	NE  	2003	2	24	HEEA084199       	1	20030213	G	6320	7635109011105	BEVEL GEAR      			SKRSKY	S76   	S76A        	8143006	NE  										M/R GEARBOX	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22342	970  			A08100268	760096				MAIN ROTOR BEVEL GEAR HAS HEAVY FROSTING AND PITTING - GEAR WAS LOAD TESTED AND ACCEPTED PRIOR BY SIKORSKY PER SO NR DF 	624-0001 ON APRIL 18, 2001. TO BE SENT TO VENDOR.					1	G	7	2 	3U			 	H1NE    					 
2003022400110	20030224	00110	SW  	2003	2	24	HEEA084225       	1	20030120	G	2510	407070620149	PANEL           			BELL  	407   	407         	1182206	SW  										SEAT	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH					53461				SEAT PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2003022400111	20030224	00111	SW  	2003	2	24	HEEA084226       	1	20030120	G	5320	407070620150	TRIM PANEL      			BELL  	407   	407         	1182206	SW  										INTERIOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH					53396				INTERIOR TRIM PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2003022700102	20030227	00102	SW  	2003	2	27	HEEA084406       	1	20030212	G	2420	SM20ACD300A21	CONTACTOR       			BELL  	407   	407         	1182206	SW  										ELECTRICAL	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				CAUSING START/AUTO RELIGHT CAUTION LIGHTS TO NOT ILLUMINATE.						1	G	7	1 	3U			O	H2SW    					 
2003022700104	20030227	00104	SW  	2003	2	27	HEEA084408       	1	20030212	G	2420	SM20ACD300A21	CONTACTOR       			BELL  	407   	407         	1182206	SW  										ELECTRICAL	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	490PH					53378				GENERATOR TAKES SEVERAL SECONDS TO GO OFFLINE WHEN SWITCH IS TURNED OFF.						1	G	7	1 	3U			O	H2SW    					 
2003022700115	20030227	00115	SW  	2003	2	27	HEEA084421       	1	20030212	G	6510	222044003101	HANGER ASSY     			BELL  	222   	222U        	1182140	SW  										TAIL ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6992					47521				RUST INSIDE SPLINED ADAPTER; BEARING SEAL DAMAGED; AND HANGER SUPPORT CRACKED ON BOTTOM. REPLACED BEARING 222344606-101 	DUE TO SEAL DAMAGED.  REPLACED HANGER DUE TO CRACKED.  REPAIRED.					1	G	7	2 	3U			 	H9SW    					 
2003022700116	20030227	00116	SW  	2003	2	27	HEEA084422       	1	20030212	G	6510	222044003101	HANGER ASSY     			BELL  	222   	222U        	1182140	SW  										TAIL ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6992					47521				RUST INSIDE SPLINED ADAPTER; BEARING SEAL DAMAGED; AND HANGER SUPPORT CRACKED ON BOTTOM. REPLACED BEARING DUE TO SEAL DA	MAGED.  REPLACED HANGER DUE TO CRACKED.  REPLACED SHAFT DUE TO CORROSION.  REPAIRED.					1	G	7	2 	3U			 	H9SW    					 
2003022700119	20030227	00119	SW  	2003	2	27	HEEA084425       	1	20030212	G	3340	930500251	SEARCH LIGHT    			BELL  	230   	230         	1182149	SW  										EXTERIOR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911RC					23037				SEARCH LIGHT DOES NOT RETRACT ALL THE TIME.						1	G	7	2 	3U			NC	H9SW    					 
2003030400103	20030304	00103		2003	3	4	HEEA084605       	4	20030214	G	3442	MI585200	INDICATOR       			BELL  	412   	412         	1182202	SW  										WX RADAR SYS	WEAK            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				WEATHER RADAR PAINTS WEAK RETURNS. FOUND RECEIVER SENSITIVITY WEAK.  ADJUSTED TO SPECS. BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2003030500040	20030305	00040		2003	3	5	HEEA084622       	4	20030214	G	3445	80511400003	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										WX RADAR SYS	MALFUNCTIONED   	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				AIR COLLISION AVOIDANCE SYSTEM SHOWS RS232 NR 2 FAIL - ERROR CODE 13 AT STARTUP. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003030500060	20030305	00060		2003	3	5	HEEA084642       	4	20030214	G	3454	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				VHF NAVIGATION RECEIVER INOPERATIVE. POWER SUPPLY VOLTAGES ARE BAD.  REPLACED BURNED RESISTORS R791, R792, R793 AND R794	.  ALSO REPLACED IC I101, TRANSISTOR Q718, Q719 AND Q103.  REPAIRED PROBLEM.   BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2003030500063	20030305	00063		2003	3	5	HEEA084645       	4	20030214	G	3454	071107600	AMPLIFIER       			BELL  	412   	412         	1182202	SW  										VOR SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2258F					33073				NR 2 KDA CONNECTOR FROZE ON BOX. FOUND UNIT EXCESSIVELY CORRODED.  CLEANED CORROSION AND REPLACED 18 HEADER PINS DUE TO 	CORROSION.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2003030500066	20030305	00066		2003	3	5	HEEA084649       	4	20030212	G	2312		POTENTIOMETER   			BOLKMS	105   	BO105S      	5626006	EU  										AUDIO PANEL	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3071K					S859				AUDIO PANEL CONTROL UNIT VOLUME IS SENSITIVE. FOUND FACEPLATE INSERT, VOLUME POTENTIOMETER S101, AND TRANSFER SWITCH S10	2 BAD.  REPLACED.  BENCH CHECK GOOD.					1	G	7	2 	3U			 	H3EU    					 
2003030600001	20030306	00001		2003	3	6	HEEA084713       	4	20030217	G	3455	071121004	CONTROL BOX     			BELL  	412   	412         	1182202	SW  										COCKPIT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				ADF CONTROL BOX DAMAGED, CAN'T CHANGE FREQUENCY. FOUND DISPLAY DS302, PHOTOCELL V301, PHOTOCELL LENS BAD AND SWITCH SPOO	L NOT PROPERLY ALIGNED WITH SWITCH S304.  REPLACED DISPLAY, PHOTOCELL, PHOTOCELL LENS AND ALIGNED SWITCH.  REPAIRED.  BE	NCH CHECK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2003030600017	20030306	00017		2003	3	6	HEEA084730       	4	20030217	G	2340	A3016R	MIXER BOX       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				ICS MIXER BOX HAS NO SOUND. FOUND ICS AUDIO INTERMITTENTLY CUTTING OUT.  CLEANED REAR CONNECTOR AND S1 SWITCHES.  RESOLD	ERED WIRES TO CIRCUIT BOARD AND R72 VOLUME CONTROL.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2003030600019	20030306	00019		2003	3	6	HEEA084732       	4	20030217	G	2340		SWITCH          			BELL  	412   	412         	1182202	SW  										INTERPHONE BOX	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K				21497	36001				NR 2 COMM SWITCH IS LOOSE. FOUND LIGHT PANEL AND SELECTOR KNOB BAD, SWITCH S1 NOISY AND SWITCH S2 LOOSE.  CLEANED SWITCH	 S1, TIGHTENED SWITCH S2, REPLACED SELECTOR KNOB AND LIGHT PANEL.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2003030600122	20030306	00122	SW  	2003	3	6	HEEA084824       	1	20030221	G	6220	412310400103	ROD BEARING     			BELL  	412   	412         	1182202	SW  										M/R HEAD	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22347					36005				MAIN ROTOR HEAD HAS A WORN ROD BEARING. REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2003030700163	20030307	00163		2003	3	7	HEEA084907       	4	20030228	G	3421	7660002113103	GYRO            			SKRSKY	S76   	S76A        	8143006	NE  										VERTICAL	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	764P					760276				IMPACT INDICATOR ON VERTICAL GYRO WAS RED, INDICATING EXCESSIVE IMPACT. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2003031100040	20030311	00040	SW  	2003	3	11	HEEA085056       	1	20030228	G	3212	206050248113	FLOAT           			BELL  	206   	206L3       	1182108	SW  										MLG	LEAKING         	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	6160Y					51609				DURING PRESSURE TESTING FLOAT BAG LEAKED THROUGH AFT SEAM.						1	G	7	1 	3U			 	H2SW    					 
2003052900051	20030529	00051	NE  	2003	5	29	HEEA086506       	2	20030521	G	7314	0292858180	VALVE           			AEROSP	AS355 	AS355*      	       	EU  	TMECA 	ARRIEL	ARRIEL1B2   	60030	NE  					FUEL PUMP	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	971AE					3230	22118			FUEL PUMP METERING VALVE IS LEAKING FROM SEAL DRAIN.						1	G	7	2 	3U	3	U	 	H11EU   	E19EU				 
2003052900070	20030529	00070	NE  	2003	5	29	HEEA086512       	1	20030521	G	2497		WIRE            			SKRSKY	S76   	S76A        	8143006	NE  										STARTER GEN	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546K				1204	760082				NR 2 GENERTOR WILL NOT COME ON LINE.  INSPECTED BY ACCESSORY SHOP AND FOUND STATOR LEAD WIRE TO BRUSH BOX BROKEN OFF.  A	LSO FOUND BRUSHES CHIPPED. SENT TO NAASCO NORTHEAST FOR WARRANTY REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2003052900071	20030529	00071	NE  	2003	5	29	HEEA086513       	1	20030521	G	2435		ARMATURE        			SKRSKY	S76   	S76A        	8143006	NE  										STARTER GEN	NOISY           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5435V				808	760158				ARMATURE MAKING NOISE. TESTED OK - NO PROBLEM FOUND.						1	G	7	2 	3U			 	H1NE    					 
2003052900090	20030529	00090		2003	5	29	HEEA086522       	4	20030521	G	3421	7660002113103	GYRO            			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911MJ					760231				GYRO INTERMITTENTLY CAUSES ADI TO ERECT TO 45 DEGREE BANK AND ALSO INTERMITTENTLY CAUSES ADI TO TUMBLE. SENT TO B.F. GOO	DRICH AEROSPACE FOR WARRANTY REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2003052900091	20030529	00091		2003	5	29	HEEA086523       	4	20030521	G	2215	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	760PH	6850 				760078				AFCS ACTUATOR INOPERATIVE.  INSPECTED BY ACCESSORY SHOP AND FOUND UNIT NOT RESPONDING TO TEST, NO POWER COMING FROM UNIT	.					1	G	7	2 	3U			 	H1NE    					 
2003052900093	20030529	00093	NE  	2003	5	29	HEEA086525       	2	20030521	G	7261	9560137520	MAGNETIC SEAL   			AEROSP	AS355 	AS355*      	       	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  						LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	974AE					2653	9586			ENGINE MAGNETIC SEAL LEAKING.						1	G	7	2 	3U	3	U	 	H11EU   	E19EU				 
2003053000035	20030530	00035		2003	5	30	HEEA086541       	4	20030522	G	2312	071121524	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	762P					760060				VHF SYSTEM CONTROL UNIT IS UNREADABLE. IN SHOP REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2003053000036	20030530	00036		2003	5	30	HEEA086542       	4	20030522	G	3455	071121815	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										ADF SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	762P					760060				ADF CONTROL UNIT IS UNREADABLE. IN SHOP REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2003060900203	20030609	00203		2003	6	9	HEEA086576       	4	20030522	G	3442	MI585200	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										WX RADAR SYS	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4253S					760035				NO DISPLAY MAP AND WEATHER MODE. SHOP REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2003052800084	20030528	00084	SW  	2003	5	28	HEEA086598       	1	20030521	G	6321	209040177101	ADAPTER         			BELL  	412   	412         	1182202	SW  										ROTOR BRAKE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				CORROSION AND WORN. SENT TO H-S TOOL & PARTS FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003052800085	20030528	00085	SW  	2003	5	28	HEEA086599       	1	20030521	G	2844	209062003001	SWITCH          			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	107X					33113				SWITCH LEAKING - RIVETS ARE LOOSE. SCRAPPED.						1	G	7	2 	4U			 	H4SW    					 
2003052800087	20030528	00087	SW  	2003	5	28	HEEA086601       	1	20030521	G	7921		BEARING         			BELL  	412   	412         	1182202	SW  										OIL COOLER	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z				51003838	36019				BEARING SPINS IN HOUSING; MAKING MUD. REPLACED BEARING 9104-NPP DUE TO WORN; BEARING W202PP DUE TO WORN.  REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2003052800088	20030528	00088	SW  	2003	5	28	HEEA086602       	1	20030521	G	7921	209062502101	OIL COOLER      			BELL  	412   	412         	1182202	SW  										ENGINE OIL	VIBRATES        	E			HEEA	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	03	142PH					33150				HIGH VIBRATION. REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2003052800089	20030528	00089	SW  	2003	5	28	HEEA086603       	1	20030521	G	2620		GAUGE           			BELL  	412   	412         	1182202	SW  										EXTINGUISHER	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z				23776B1	36019				CORROSION ON PRESSURE GAUGE. REPLACED PRESSURE GAUGE 2725-709 DUE TO CORROSION.  REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2003052800091	20030528	00091	SW  	2003	5	28	HEEA086604       	1	20030521	G	2437	209070264003	AMMETER         			BELL  	412   	412         	1182202	SW  										COCKPIT	STICKS          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				NR 2 SIDE STICKS WHEN GEN IS BROUGHT ON LINE.						1	G	7	2 	4U			 	H4SW    					 
2003052800103	20030528	00103	SW  	2003	5	28	HEEA086612       	1	20030521	G	7810	212061210001	DUCT            			BELL  	412   	412         	1182202	SW  										EXHAUST STACK	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				EXHAUST STACK DUCT HAS LARGE CRACKS. REPLACED.						1	G	7	2 	4U			 	H4SW    					 
2003052900023	20030529	00023	SW  	2003	5	29	HEEA086621       	1	20030521	G	2432	30126002	BATTERY         			BELL  	412   	412         	1182202	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				WENT TO ZERO VOLTS BEFORE START. REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2003052900024	20030529	00024	SW  	2003	5	29	HEEA086622       	1	20030521	G	2611	302319	SMOKE DETECTOR  			BELL  	412   	412         	1182202	SW  										CABIN	WILL NOT TEST   	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	21498					36003				SMOKE DETECTOR WILL NOT TEST WITH SMOKE.						1	G	7	2 	4U			 	H4SW    					 
2003052900028	20030529	00028	SW  	2003	5	29	HEEA086626       	1	20030521	G	6220		BEARING         			BELL  	412   	412         	1182202	SW  										M/R HEAD	WEAK            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	800Y	9289 			A469	33134				MAIN ROTOR HEAD BEARINGS WEAK. REPLACED DAMPER SET 412010145105 ( 2 EA), S/N LK3098 AND LK3109 DUE TO SEPARATING AND DRO	OP RESTRAINT NAS6607-D21 (4 EA) DUE TO WORN.  REPAIRED.					1	G	7	2 	4U			 	H4SW    					 
2003052900047	20030529	00047	SW  	2003	5	29	HEEA086638       	1	20030521	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DEBONDED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22347	14633				36005				LOWER FRETTING PADS IS UNBONDED, THE TRAILING EDGE POCKET AT THE ROOT HAS WATER TRAPPED INSIDE. SENT TO ROTOR BLADES, IN	C. FOR INSPECTION AND REPAIR.					1	G	7	2 	4U			 	H4SW    					 
2003052900050	20030529	00050	SW  	2003	5	29	HEEA086641       	1	20030521	G	3212	412050013113	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				EMERGENCY FLOAT LEAKING.						1	G	7	2 	4U			 	H4SW    					 
2003052900061	20030529	00061		2003	5	29	HEEA086648       	4	20030521	G	3421	504001790116	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	PRECESSES       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21498					36003				PRECESS TO RIGHT AFTER ONE HOUR OF FLIGHT. REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2003052900062	20030529	00062	SW  	2003	5	29	HEEA086649       	1	20030521	G	2435	51509002R	GENERATOR       			BELL  	412   	412         	1182202	SW  										NR 1	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				#1 GENERATOR NEEDS TO BE RESET BEFORE IT WILL GO ON LINE. SENT TO MASCO FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003052900066	20030529	00066		2003	5	29	HEEA086652       	4	20030521	G	2370	80510800001	DATA BOX        			BELL  	412   	412         	1182202	SW  										SKYWATCH	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2014K					33020				DATA BOX SKYWATCH FAILED IN FLIGHT.						1	G	7	2 	4U			 	H4SW    					 
2003052900079	20030529	00079		2003	5	29	HEEA086653       	4	20030521	G	3416	8800T	ENCODER         			BELL  	412   	412         	1182202	SW  										ALTIMETER	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				MESSAGE OUTSIDE ALTIMETER INOPERATIVE. REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2003052900081	20030529	00081	SW  	2003	5	29	HEEA086655       	1	20030521	G	3212	D24921119	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	FAILED          	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	2014K					33020				LT AFT FLOAT BAG FAILED 6 MONTH INSPECTION (LEAK).						1	G	7	2 	4U			 	H4SW    					 
2003052900082	20030529	00082	SW  	2003	5	29	HEEA086656       	1	20030521	G	3212	D24921119	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				EMERGENCY FLOAT LEAKING.						1	G	7	2 	4U			 	H4SW    					 
2003053000003	20030530	00003		2003	5	30	HEEA086665       	4	20030522	G	3454	071107600	INDICATOR       		KDA697      	BELL  	412   	412         	1182202	SW  										NR VOR	UNRELIABLE      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				NR 2 VOR NEEDLE UNRELIABLE - ERRATIC WITHIN 9 MILES OF VOR. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003061100091	20030611	00091	SW  	2003	6	11	HEEA086699       	1	20030522	G	3213	412321104	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P	602  				33012				CROSSTUBE CORRODED BEYOND LIMITS IN ZONE B. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003061100109	20030611	00109	EU  	2003	6	11	HEEA086713       	1	20030521	G	6420	112131521	BEARING         			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	133AE	9070 				S800				TAIL ROTOR HEAD HAS EXCESSIVE BEARING MOVEMENT. REPAIRED.						1	G	7	2 	3U			 	H3EU    					 
2003052800003	20030528	00003	EU  	2003	5	28	HEEA086728       	1	20030522	G	2435		BRUSHES         			AEROSP	AS355 	AS355*      	       	EU  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	973AE	381  			9224	3229				WORN BRUSHES.  UNIT WILL NOT START.  INSPECTED BY ACCESSORY SHOP AND FOUND COMMENTATOR PITTED AND BURNED. IN REPAIR.						1	G	7	2 	3U			 	H11EU   					 
2003052800054	20030528	00054	EU  	2003	5	28	HEEA086740       	1	20030522	G	2841	B19030MC02	DISPLAY         			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	973AE					3229				FUEL FLOW RESOLVER INOPERATIVE WITH FAILURE SHOWN ON SHUT DOWN. TO BE SENT TO VENDOR.						1	G	7	1 	3U			 	H9EU    					 
2003061900092	20030619	00092	SW  	2003	6	19	HEEA086932       	1	20030603	G	6420	206011728001	TRUNNION        			BELL  	407   	407         	1182206	SW  										T/R HEAD	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH					53399				TAIL ROTOR HEAD TRUNNION HAS EXCESSIVE WEAR.						1	G	7	1 	3U			O	H2SW    					 
2003070100035	20030701	00035	SW  	2003	7	1	HEEA086952       	1	20030603	G	3246	206053184121	SKID            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH					53401				DISSIMILAR METAL CORROSION AROUND THE FLOAT BAG MOUNT INSERTS. TO BE SENT TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2003070100053	20030701	00053	SW  	2003	7	1	HEEA086961       	1	20030603	G	7810	206064203101	DUCT            			BELL  	407   	407         	1182206	SW  										EXHAUST	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH					53461				EXHAUST DUCT CRACKED. REPLACED DUCT.						1	G	7	1 	3U			O	H2SW    					 
2003070100054	20030701	00054	SW  	2003	7	1	HEEA086962       	1	20030603	G	2820	206064264101	LINE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				DISSIMILAR METAL CORROSION DUE TO STEEL SLEEVE ON ALUMINUM TUBE.						1	G	7	1 	3U			O	H2SW    					 
2003070100055	20030701	00055	SW  	2003	7	1	HEEA086963       	1	20030603	G	5210	206064819031A	DOOR            			BELL  	407   	407         	1182206	SW  										CREW/PAX	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				PAX CREW DOOR CRACKED. REPLACED DOOR.						1	G	7	1 	3U			O	H2SW    					 
2003070100057	20030701	00057	SW  	2003	7	1	HEEA086964       	1	20030603	G	5320	206064902036S	CHANNEL         			BELL  	407   	407         	1182206	SW  										FUSELAGE	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				CHANNEL BROKEN. REPLACED CHANNEL.						1	G	7	1 	3U			O	H2SW    					 
2003070100058	20030701	00058	SW  	2003	7	1	HEEA086965       	1	20030603	G	7160	206064912103	SEAL            			BELL  	407   	407         	1182206	SW  										COWLING	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				COWLING SEAL TORN.  REPLACED SEAL.						1	G	7	1 	3U			O	H2SW    					 
2003070100059	20030701	00059	SW  	2003	7	1	HEEA086966       	1	20030603	G	2436	206075447101	VOLT REGULATOR  			BELL  	407   	407         	1182206	SW  										GENERATOR	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				GENERATOR FALLS OFF LINE INTERMITTENTLY. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	1 	3U			O	H2SW    					 
2003070100076	20030701	00076	SW  	2003	7	1	HEEA086967       	1	20030603	G	2424	206075447101	VOLT REGULATOR  			BELL  	407   	407         	1182206	SW  										GENERATOR	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	405PH					53207				VOLT REGULATOR TRIPS GEN FIELD CIRCUIT BREAKER. SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100077	20030701	00077	SW  	2003	7	1	HEEA086968       	1	20030603	G	2913	206076030117	PUMP            			BELL  	407   	407         	1182206	SW  										HYD SYSTEM	NOISY           	E			HEEA	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	03	495PH					53397				HYD SYSTEM PUMP PRODUCING A HIGH PITCH NOISE. SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100078	20030701	00078	SW  	2003	7	1	HEEA086969       	1	20030603	G	6730	206076062107	SERVO           			BELL  	407   	407         	1182206	SW  										CYCLIC	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404PH					53188				CYCLIC SERVO HAS A WORN BEARING. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100079	20030701	00079	SW  	2003	7	1	HEEA086970       	1	20030603	G	6730	206076062107	SERVO           			BELL  	407   	407         	1182206	SW  										CYCLIC	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH	3741 				53283				CYCLIC SERVO HAS A WORN BEARING. SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100080	20030701	00080	SW  	2003	7	1	HEEA086971       	1	20030603	G	6730		BEARING         			BELL  	407   	407         	1182206	SW  										CYCLIC SERVO	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH					53401				BEARING THAT RT CYCLIC CONTROL TUBE CONNECTS TO HAS EXCESSIVE RADIAL PLAY. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100081	20030701	00081	SW  	2003	7	1	HEEA086972       	1	20030603	G	2810	206362002103	CAP             			BELL  	407   	407         	1182206	SW  										FUEL CELL	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	720PH					53277				FUEL LEAKING FROM AROUND CAP. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100082	20030701	00082	SW  	2003	7	1	HEEA086973       	1	20030603	G	2810	206362002103	CAP             			BELL  	407   	407         	1182206	SW  										FUEL CELL	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH					53327				PIN AT FUEL CAP KEEPS FALLING OUT. REPLACED.						1	G	7	1 	3U			O	H2SW    					 
2003070100083	20030701	00083	SW  	2003	7	1	HEEA086974       	1	20030603	G	2931	212073905101	GAUGE           			BELL  	407   	407         	1182206	SW  										HYD PRESSURE	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	724PH					53327				HYDRAULIC FLUID LEAKING AT GAUGE. REPLACED.						1	G	7	1 	3U			O	H2SW    					 
2003070100084	20030701	00084	SW  	2003	7	1	HEEA086975       	1	20030603	G	6340		STUD            			BELL  	407   	407         	1182206	SW  										THERMOSWITCH	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH					53327				STUD SPINS IN HOUSING. REPLACED.						1	G	7	1 	3U			O	H2SW    					 
2003070100109	20030701	00109	SW  	2003	7	1	HEEA086976       	1	20030603	G	6340	214040806003	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										TRANSMISSION	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH					53399				TRANSMISSION PRESSURE SWITCH INTERMITTENTLY STICKS IN OPEN POSITION WHEN PRESSURE IS REMOVED. REPLACED.						1	G	7	1 	3U			O	H2SW    					 
2003070100112	20030701	00112	SW  	2003	7	1	HEEA086977       	1	20030603	G	2897	222366621103	CONNECTOR       			BELL  	407   	407         	1182206	SW  										FUEL FILTER	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH					53399				FUEL FILTER PIN IN CONNECTOR CORRODED OUT. REPLACED.						1	G	7	1 	3U			O	H2SW    					 
2003070100113	20030701	00113	SW  	2003	7	1	HEEA086978       	1	20030603	G	2810	222366649101	VALVE           			BELL  	407   	407         	1182206	SW  										SUMP	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				SUMP VALVE INOPERATIVE. REPLACED.						1	G	7	1 	3U			O	H2SW    					 
2003070100114	20030701	00114	SW  	2003	7	1	HEEA086979       	1	20030603	G	2844	222375077113	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										OIL PRESSURE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH					53401				TRANSMITTER INOPERATIVE, NO PRESSURE INDICATION. SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100115	20030701	00115	SW  	2003	7	1	HEEA086980       	1	20030603	G	7712	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										TORQUE	OUT OF ADJUST   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				TORQUE TRANSMITTER OUT OF LIMITS. SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100116	20030701	00116	SW  	2003	7	1	HEEA086981       	1	20030603	G	7712	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										TORQUE	ERRATIC         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				TORQUE TRANSMITTER MALFUNCTIONED, PRESSURE FLUCTUATES ERRATICALLY. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100117	20030701	00117	SW  	2003	7	1	HEEA086982       	1	20030603	G	6220	407010100115	BEARING         			BELL  	407   	407         	1182206	SW  										M/R HEAD	SEPARATED       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH	3265 				53396				BLUE BLADE FEATHERING BEARING SEPARATED.						1	G	7	1 	3U			O	H2SW    					 
2003070100118	20030701	00118	GL  	2003	7	1	HEEA086983       	2	20030603	G	7313	23001832	NOZZLE          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	BENT            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH					53396				FUEL NOZZEL BENT. SCRAPPED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100119	20030701	00119	GL  	2003	7	1	HEEA086984       	2	20030603	G	7313	23001832	NOZZLE          			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	BENT            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				ENGINE FUEL NOZZEL BENT. SCRAPPED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100120	20030701	00120	GL  	2003	7	1	HEEA086985       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				BLEED VALVE PRODUCING HIGH MGT AT CRUISE. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100132	20030701	00132	GL  	2003	7	1	HEEA086986       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03		13609								BLEED VALVE PRODUCING LOW POWER. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100133	20030701	00133	GL  	2003	7	1	HEEA086987       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH	9188 				53400				BLEED VALVE PRODUCING HIGH MGT. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100134	20030701	00134	GL  	2003	7	1	HEEA086988       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	467PH					53142				BLEED VALVE PRODUCING HIGH TOT. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E4CE				 
2003070100135	20030701	00135	GL  	2003	7	1	HEEA086989       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				BLEED VALVE PRODUCING HIGH MGT. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100136	20030701	00136	GL  	2003	7	1	HEEA086990       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				BLEED VALVE PRODUCING HIGH TOT. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100137	20030701	00137	GL  	2003	7	1	HEEA086991       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH	5650 				53199				BLEED VALVE PRODUCING HIGH TOT. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100138	20030701	00138	GL  	2003	7	1	HEEA086992       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH					53396				BLEED VALVE BODY EXCESSIVELY LOOSE. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100139	20030701	00139	GL  	2003	7	1	HEEA086993       	2	20030603	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH	4009 				53283				BLEED VALVE PRODUCING HIGH TOT. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003061000102	20030610	00102	GL  	2003	6	10	HEEA086996       	2	20030603	G	7250		STRUCTURE       			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C*       	 	GL  					CHECK VALVE	NICKED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				CHECK VALVE SEAT FACE NICKED AND SCORED. REPLACED.						1	G	7	1 	3U	3	U	O	H2SW    	E4CE				 
2003061000107	20030610	00107	SW  	2003	6	10	HEEA087003       	1	20030604	G	2432	31908001	BATTERY         			BELL  	407   	407         	1182206	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	741PH					53457				MAIN BATTERY DEAD. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003061000108	20030610	00108	SW  	2003	6	10	HEEA087004       	1	20030604	G	2432	31908001	BATTERY         			BELL  	407   	407         	1182206	SW  										MAIN	WEAK            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	719PH					53266				MAIN BATTERY WEAK. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003061000109	20030610	00109	SW  	2003	6	10	HEEA087005       	1	20030604	G	2431		CONNECTOR       			BELL  	407   	407         	1182206	SW  										BATTERY	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	467PH				9805883	53142				BATTERY TEMP CONNECTOR CRACKED. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003061000110	20030610	00110		2003	6	10	HEEA087006       	4	20030604	G	3442	4000038	CONTROL HEAD    			BELL  	407   	407         	1182206	SW  										WX RADAR SYS	ERRATIC         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				FM CONTROL HEAD VOLUME CONTROL ERRATIC. FOUND VOLUME KNOB LOOSE ON SHAFT AND IS SPINNING DUE TO BEING CRACKED.  REPLACED	 VOLUME KNOB.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	1 	3U			O	H2SW    					 
2003061000111	20030610	00111	SW  	2003	6	10	HEEA087008       	1	20030604	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	447PH	4828 				53114				MAIN ROTOR SWASHPLATE GREASE SEAL LEAKING. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003061000112	20030610	00112	SW  	2003	6	10	HEEA087009       	1	20030604	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	8595X	4288 				53267				MAIN ROTOR SWASHPLATE LEAKING GREASE. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003061000113	20030610	00113	SW  	2003	6	10	HEEA087010       	1	20030604	G	6220	406010413119	PITCH LINK      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH	4419 				53038				PITCHLINK HAS CORROSION ON ENDS OF TUBE.  DAMAGE NOT VISIBLE UNTIL PAINT WAS REMOVED.						1	G	7	1 	3U			O	H2SW    					 
2003061000114	20030610	00114	SW  	2003	6	10	HEEA087011       	1	20030604	G	6230	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				MAIN ROTOR LEVER ASSY HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2003061000115	20030610	00115	SW  	2003	6	10	HEEA087012       	1	20030604	G	6230	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH	964  				53114				WORN BUSHINGS. REPLACED 4 EACH BUSHINGS 406310406101 DUE TO WORN.  REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003061000117	20030610	00117	SW  	2003	6	10	HEEA087014       	1	20030604	G	6230	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH	625  				53147				WORN BUSHINGS. REPLACED 4 EACH BUSHINGS 406310406-101 DUE TO WORN.  REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003061000119	20030610	00119	SW  	2003	6	10	HEEA087016       	1	20030604	G	6230	406010426101	PITCH LINK      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				LINK ASSY HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2003061800018	20030618	00018		2003	6	18	HEEA087120       	4	20030609	G	2330		SWITCH          			SKRSKY	S76   	S76A        	8143006	NE  										PA SIREN	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911UK				1260	760275				BROKEN ON/OFF SWITCH. FOUND SWITCH S401 AND FUSE F101 BAD.  REPLACED.  REPAIRED.  BENCH CHECK GOOD.						1	G	7	2 	3U			 	H1NE    					 
2003061800021	20030618	00021		2003	6	18	HEEA087123       	4	20030610	G	2312	064100900	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										COMMS	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546G					760076				SIDETONE GARBLED AND SCRATCHY. SHOP REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2003061800064	20030618	00064		2003	6	18	HEEA087126       	4	20030610	G	3451	071121627	CONTROLLER      			SKRSKY	S76   	S76A        	8143006	NE  										DME	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	762P					760060				CONTROLLER CAUSING DME PROBLEM. SHOP REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2003061800066	20030618	00066		2003	6	18	HEEA087129       	4	20030610	G	3442	4000038	CONTROL HEAD    			SKRSKY	S76   	S76A        	8143006	NE  										WX RADAR SYS	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	762P					760060				TEST SWITCH STICKS INTERMITTENTLY. SHOP REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2003061800129	20030618	00129	NE  	2003	6	18	HEEA087137       	1	20030610	G	2910	7665009801105	MODULE          			SKRSKY	S76   	S76C        	8143008	NE  										HYD SYSTEM	CLOGGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	505PH					760505				RETURN FILTER CLOGGING. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2003061800132	20030618	00132	NE  	2003	6	18	HEEA087139       	1	20030610	G	6730	7826003	SERVO           			SKRSKY	S76   	S76C        	8143008	NE  										ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	505PH					760505				ROTOR SERVO LEAKING. REPLACED SERVO.						1	G	7	2 	3U			NC	H1NE    					 
2003061800167	20030618	00167		2003	6	18	HEEA087145       	4	20030609	G	2220	214074301105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										SCAS	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				DURING INSTALLATION THE SCAS WOULD NOT COME ON LINE WITH THIS AMP.  COULD NOT ALIGN SCAS.  ADJUSTMENTS COULD NOT BE MADE	 USING VARIABLE RESISTORS. SENT TO BELL HELICOPTER TEXTRON FOR WARRANTY REPAIR.  REFERENCE:  DMR 748396.					2	G	7	2 	4U			 	H10SW   					 
2003061800189	20030618	00189	SW  	2003	6	18	HEEA087155       	1	20030609	G	6710		BEARING         			BELL  	206   	206L3       	1182108	SW  										BELLCRANK ASSY	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				BELLCRANK ASSY HAS WORN BEARING. REPLACED BEARING MS27647-4 DUE TO WORN.  REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003061800214	20030618	00214	SW  	2003	6	18	HEEA087167       	1	20030609	G	6320	206031590003	BEARING         			BELL  	206   	206B3       	1181506	SW  										LINK ASSY	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22751				CT2933	3627				WORN CENTER BEARING. REPLACED BEARING 206031590003 DUE TO WORN; BUSHING 206-031-564-003 DUE TO WORN.  REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003061900002	20030619	00002	SW  	2003	6	19	HEEA087173       	1	20030609	G	6330		BEARING         			BELL  	206   	206L3       	1182108	SW  										SUPPORT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8587X					51464				ONE OF THE ELASTOMERIC BEARINGS SEPARATED 360 DEGREES. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003061900018	20030619	00018	SW  	2003	6	19	HEEA087181       	1	20030609	G	7933	206075680107	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TOT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	81671					51301				WRONG LIMITS FOR L-3 AIRCRAFT.						1	G	7	1 	3U			 	H2SW    					 
2003061900032	20030619	00032	SW  	2003	6	19	HEEA087186       	1	20030609	G	2844	206364601101	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										FUEL PRESSURE	FLUCTUATES      	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	6251X					51552				FUEL PRESSURE TRANSMITTER FLUCTUATES.						1	G	7	1 	3U			 	H2SW    					 
2003061900034	20030619	00034	SW  	2003	6	19	HEEA087188       	1	20030609	G	2912	2111328	FILTER ELEMENT  			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	30KH					51527				FILTER ELEMENT INOPERATIVE. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003061900047	20030619	00047	SW  	2003	6	19	HEEA087197       	1	20030609	G	7910	4369	CAP             			BELL  	206   	206L3       	1182108	SW  										OIL TANK	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	6748D					51106				OIL TANK CAP LEAKING THROUGH SHAFT. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2003061900053	20030619	00053	SW  	2003	6	19	HEEA087202       	1	20030609	G	7714	AG44A202	TACH GENERATOR  			BELL  	206   	206L3       	1182108	SW  										ENGINE	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6748D					51106				TACH GEN IS INTERMITTENT. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003061900065	20030619	00065		2003	6	19	HEEA087210       	4	20030609	G	2350	PHI001L0001201	MIXER BOX       			BELL  	206   	206L3       	1182108	SW  										VHF SYS	WEAK            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				COPILOT VHF SIDE TONE RECEPTION WEAK. REPLACED.						1	G	7	1 	3U			 	H2SW    					 
2003061900067	20030619	00067	SW  	2003	6	19	HEEA087212       	1	20030609	G	6230	PHI2062002	DRIVE LINK      			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR MAST	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31077					51520				OUTER SPLINE HALF LOOSE ON MAST. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003061900068	20030619	00068	SW  	2003	6	19	HEEA087213       	1	20030609	G	6520	PHI2062003	HOUSING         			BELL  	206   	206L3       	1182108	SW  										SEAL	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	6251X					51552				TAIL ROTOR GEARBOX SEAL LEAKING. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003061900069	20030619	00069	SW  	2003	6	19	HEEA087214       	1	20030609	G	6720	PHI206L3957	TUBE            			BELL  	206   	206L3       	1182108	SW  										PITCH CONTROL	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3107N					51512				CORROSION ON CONTROL TUBE. REPAIRED.						1	G	7	1 	3U			 	H2SW    					 
2003062000017	20030620	00017	GL  	2003	6	20	HEEA087236       	2	20030610	G	7314	3865005	PUMP            			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20J     	03013	GL  					FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2270G					3610				INTERMITTENT HANG STARTS ON FIRST START OF DAY. REPAIRED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2003070100044	20030701	00044	SW  	2003	7	1	HEEA087239       	1	20030610	G	6230		BEARING         			BELL  	412   	412         	1182202	SW  										DRIVE LINK	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D				A1570	33076				DRIVE LINK HAS A WORN BEARING. SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003070100045	20030701	00045	SW  	2003	7	1	HEEA087240       	1	20030610	G	6230	412010406109	DRIVE LINK      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				MAIN ROTOR DRIVE LINK HAS A WORN BEARING. SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003070100046	20030701	00046	SW  	2003	7	1	HEEA087241       	1	20030610	G	6230	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				LINK HAS A WORN BEARING. SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003070100047	20030701	00047	SW  	2003	7	1	HEEA087242       	1	20030610	G	6230	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				LINK HAS A WORN BEARING. SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003070100048	20030701	00048	SW  	2003	7	1	HEEA087243       	1	20030610	G	6230	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				LINK HAS A WORN BEARING. SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003070100049	20030701	00049	SW  	2003	7	1	HEEA087244       	1	20030610	G	3246	412050016101	SHOE            			BELL  	412   	412         	1182202	SW  										MLG SKID	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				MLG SKID TUBE SHOE IS WORN. SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2003070100050	20030701	00050	GL  	2003	7	1	HEEA087245       	2	20030610	G	7412	49522	EXCITER         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41791					51465				EXCITER, INOPERATIVE. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003070100051	20030701	00051		2003	7	1	HEEA087246       	4	20030610	G	3422	5050010902	GYRO            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					COCKPIT	PRECESSES       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	129MR					51129				DIRECTIONAL GYRO PRECESSES. SHOP REPAIR.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003070100052	20030701	00052	NE  	2003	7	1	HEEA087247       	2	20030610	G	7532	6064T56P04	BLEED VALVE     			BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT71        	30030	NE  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	5748M					28102				WITH ENGINE N1 ABOVE 90 PERCENT ANTI ICE LIGHT OFF CYCLED ANTI ICE SWITCH ON FUEL CONTROL. TO BE SENT TO VENDOR FOR REPA	IR.					2	G	7	2 	4U	4	U	 	H10SW   	E8NE				 
2003070100056	20030701	00056	NE  	2003	7	1	HEEA087248       	2	20030610	G	7532	6064T56P07	BLEED VALVE     			BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT71        	30030	NE  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5748M					28102				ENGINE BLEED VALVE MALFUNCTIONED, TEMPERATURE WOULD NOT RISE DURING ANTI ICE CHECK. TO BE SENT TO VENDOR FOR REPAIR.						2	G	7	2 	4U	4	U	 	H10SW   	E8NE				 
2003070100061	20030701	00061	SW  	2003	7	1	HEEA087249       	1	20030610	G	2913	206076022101	CLAMP           			CLARK 	1000  	1000CLARK   	2230102	SW  										PUMP	DEFORMED        	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03		10624								HYD PUMP HAS A DEFORMED CLAMP FROM SUPPLY P/N 8505075. TO BE SENT TO VENDOR.						1	Q	7	1 	3R			 	2A6     					 
2003070100062	20030701	00062		2003	7	1	HEEA087251       	4	20030610	G	2350	PHI001L0001201	MIXER BOX       			BELL  	206   	206L3       	1182108	SW  										COMMS SYSTEM	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41791					51465				MIXER BOX MALFUNCTIONED, CANNOT HEAR ON COPILOT SIDE. SHOP REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2003070100063	20030701	00063		2003	7	1	HEEA087252       	4	20030610	G	2561		LATCH           			BELL  	206   	206L3       	1182108	SW  										LIFE VEST	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6160Y					51609				ONE LATCH ON STRAP IS BROKEN. REPLACED LIFE VEST.						1	G	7	1 	3U			 	H2SW    					 
2003070100064	20030701	00064		2003	7	1	HEEA087254       	4	20030610	G	2561	PHI10090	LIFE VEST       			BELL  	206   	206L3       	1182108	SW  											LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6748D					51106				LIFE VEST LEAKING. REPLACED.						1	G	7	1 	3U			 	H2SW    					 
2003070100065	20030701	00065	SW  	2003	7	1	HEEA087255       	1	20030610	G	5302	PHI206L13115B	FITTING         			BELL  	206   	206L3       	1182108	SW  										TAILBOOM	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X					51552				CRACKED UPPER RIGHT TAILBOOM FITTING. SHOP REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2003070100066	20030701	00066	SW  	2003	7	1	HEEA087257       	1	20030611	G	6720	204001855001	BEARING         			BELL  	412   	412         	1182202	SW  										LEVER ASSY	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22347					36005				TEFLON BAD ON BEARING. REPLACED BEARING (2 EA) MS276434 DUE TO WEAR.  REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2003070100067	20030701	00067	SW  	2003	7	1	HEEA087258       	1	20030611	G	6230		SEAL            			CLARK 	1000  	1000CLARK   	2230102	SW  										SWASHPLATE	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	266P	574  			REFS298					LEAKING GREASE UNDER BOOT. REPLACED SEAL (2 EA) 206-010-460-001 DUE TO LEAKING AND WEAR.  REPAIRED.						1	Q	7	1 	3R			 	2A6     					 
2003070100094	20030701	00094	SW  	2003	7	1	HEEA087259       	1	20030611	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										IDLER ASSY	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH					53399				TAIL ROTOR IDLER ASSY HAS WORN BEARINGS. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003070100095	20030701	00095	SW  	2003	7	1	HEEA087260       	1	20030611	G	6510	407040303119A	BEARING         			BELL  	407   	407         	1182206	SW  										BLOWER SHAFT	ROUGH           	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	498PH					53399				FWD BEARING ROUGH; EXPELS DARK GREASE. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003070100096	20030701	00096		2003	7	1	HEEA087261       	4	20030611	G	3422	4020936904	TARSYN          			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				WILL NOT ERECT PROPERLY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2003070100097	20030701	00097	SW  	2003	7	1	HEEA087262       	1	20030611	G	2810	4369	CAP             			BELL  	206   	206L3       	1182108	SW  										FUEL CELL	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	129MR					51129				FUEL CAP LEAKING AROUND STEM. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2003070100098	20030701	00098	SW  	2003	7	1	HEEA087263       	1	20030611	G	3212	1100891S	FITTING         			BELL  	407   	407         	1182206	SW  										MLG FLOAT	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				MLG FLOAT FITTING CORRODED EXCESSIVELY,  DUE TO IMPROPER PROTECTION DURING THE MANUFACTURING PROCESS. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100099	20030701	00099	SW  	2003	7	1	HEEA087264       	1	20030611	G	5302	206032308121S	FRAME           			BELL  	407   	407         	1182206	SW  										TAILBOOM	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				TAILBOOM FRAME CRACKED AT UPPER RT MOUNT HOLE. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100100	20030701	00100	SW  	2003	7	1	HEEA087265       	1	20030611	G	3212	206050247131	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				LT FWD BAG COVER TORN AND DETERIORATED. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100101	20030701	00101	SW  	2003	7	1	HEEA087266       	1	20030611	G	3212	206050247132	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				RT FWD FLOAT BAG COVER TORN AND DETERIORATED. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100102	20030701	00102	SW  	2003	7	1	HEEA087267       	1	20030611	G	3212	206050247135	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				LT CENTER FLOAT BAG COVER TORN AND DETERIORATED. TO BE SENT TO BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW    					 
2003070100103	20030701	00103	SW  	2003	7	1	HEEA087268       	1	20030611	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				RIGHT AFT FLOAT BAG COVER TORN AND DETERIORATED. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100110	20030701	00110	SW  	2003	7	1	HEEA087269       	1	20030611	G	2435	206064203101	DUCT            			BELL  	407   	407         	1182206	SW  										START GEN	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				STARTER GENERATOR DUCT CRACKED AT SEVERAL AREAS. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100121	20030701	00121	SW  	2003	7	1	HEEA087270       	1	20030611	G	7160	206064909101	BELLMOUTH       			BELL  	407   	407         	1182206	SW  										FUSELAGE	CORRODED        	E			HEEA	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	03	8595X					53267				BELLMOUTH ASSY HAS CORROSION DUE TO IMPROPER PROTECTION DURING MANUFACTURER PROCESS. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100122	20030701	00122	SW  	2003	7	1	HEEA087271       	1	20030611	G	7110	206064912103	SEAL            			BELL  	407   	407         	1182206	SW  										COWLING	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				COWLING SEAL TORN. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100123	20030701	00123	SW  	2003	7	1	HEEA087272       	1	20030611	G	6310	206340300107	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				MAIN ROTOR GEARBOX DRIVE SHAFT HAS CORROSION ON EXTERIOR AND INTERIOR OF DRIVESHAFT. TO BE SENT TO BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW    					 
2003070100124	20030701	00124	SW  	2003	7	1	HEEA087273       	1	20030611	G	6340	214040806003	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				PRESSURE SWITCH INOPERATIVE, CAUTION LIGHT WILL NOT COME ON. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100125	20030701	00125	GL  	2003	7	1	HEEA087274       	2	20030611	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				BLEED VALVE PRODUCING HIGH TOT. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003070100126	20030701	00126	SW  	2003	7	1	HEEA087275       	1	20030611	G	7930	23066697	FILTER          			BELL  	407   	407         	1182206	SW  										OIL SYSTEM	BYPASSING       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				OIL FILTER INDICATOR POPPED. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100127	20030701	00127	SW  	2003	7	1	HEEA087277       	1	20030611	G	6210	406010120101	BOLT            			BELL  	407   	407         	1182206	SW  										BLADE	ERODED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				BLADE BOLT SURFACE COATING ERODING AT SHANK END.  SERIAL NUMBERS REMOVED ARE A-FS5891, A-FS5925 AND A-FS5927. TO BE SENT	 TO MFG.					1	G	7	1 	3U			O	H2SW    					 
2003070100144	20030701	00144	SW  	2003	7	1	HEEA087278       	1	20030611	G	6220	406010413119	PITCH LINK      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				PITCH LINK HAS CORROSION AT BARREL OF TUBE.  SERIAL NUMBERS REMOVED ARE A-6011, A6133, A6137 AND A6138. TO BE SENT TO MF	G.					1	G	7	1 	3U			O	H2SW    					 
2003070100145	20030701	00145	SW  	2003	7	1	HEEA087279       	1	20030611	G	6230	406010427109	GIMBAL RING     			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH	3360 				53386				GIMBAL RING, CORRODED. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100146	20030701	00146	SW  	2003	7	1	HEEA087280       	1	20030611	G	6230	406010428109	BUSHING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	GOUGED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				MASTER SPLINE GOUGED AND OVERSIZED HOLE. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100147	20030701	00147	SW  	2003	7	1	HEEA087281       	1	20030611	G	6230	406010428109	BUSHING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH	3360 				53386				WORN PIVOT BORE. TO BE SENT TO BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW    					 
2003070100148	20030701	00148	SW  	2003	7	1	HEEA087282       	1	20030611	G	6230	406010429101	PIN             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH	3360 				53386				WORN AND PITTED. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100149	20030701	00149	SW  	2003	7	1	HEEA087283       	1	20030611	G	6710	406012104103	PLATE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				MECHANICAL DAMAGE BEYOND LIMITS. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100150	20030701	00150	SW  	2003	7	1	HEEA087284       	1	20030611	G	6710	406012129101	LINK ASSY       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				AXIAL PLAY BEYOND LIMITS. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100151	20030701	00151	SW  	2003	7	1	HEEA087285       	1	20030611	G	6510	406040315111	SHAFT           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				TAIL ROTOR DRIVESHAFT CORRODED DUE TO IMPROPER PROTECTION DURING MFG. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100152	20030701	00152	SW  	2003	7	1	HEEA087286       	1	20030611	G	6230	406310411101	BOOT            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				MAIN ROTOR BOOT HAS LARGE HOLE/TORN. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003070100153	20030701	00153	SW  	2003	7	1	HEEA087287       	1	20030611	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										IDLER GEAR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				M/R GEARBOX IDLER GEAR HAS A WORN BEARING. TO BE SENT TO MFG.						1	G	7	1 	3U			O	H2SW    					 
2003061700164	20030617	00164	SW  	2003	6	17	HEEA087303       	1	20030611	G	6300	407010206103	BOOT            			BELL  	407   	407         	1182206	SW  										M/R DRIVE	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				MAIN ROTOR DRIVE RUBBER BOOT TORN AROUND CYLINDER.						1	G	7	1 	3U			O	H2SW    					 
2003061700335	20030617	00335	SW  	2003	6	17	HEEA087324       	1	20030611	G	5302	407030801107	SKIN            			BELL  	407   	407         	1182206	SW  										TAILBOOM ASSY	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	742PH					53461				CORRODED AROUND LARSEN ANT MOUNT. REPLACED.						1	G	7	1 	3U			O	H2SW    					 
2003061800048	20030618	00048	SW  	2003	6	18	HEEA087336       	1	20030611	G	6510	406040328103	BEARING         			BELL  	407   	407         	1182206	SW  										T/R DRIVE SHAFT	OVERHEATED      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH	2526 			A1939	53399				ROUGH AND GREASE TURNING BLACK. REPLACED ADAPTER 406040328103, S/N A-FS3404 DUE TO CORROSION AND BEARING 407340339101, S	/N ZV10920 DUE TO ROUGH ROTATION.  REPAIRED.					1	G	7	1 	3U			O	H2SW    					 
2003091000003	20030910	00003	SW  	2003	9	10	HEEA087362       	1	20030611	G	2520		STRUCTURE       			BELL  	407   	407         	1182206	SW  										STORAGE BIN	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				STORAGE BIN CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2003061900028	20030619	00028	SW  	2003	6	19	HEEA087377       	1	20030611	G	5210	407070620158	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				CREW DOOR PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2003061900063	20030619	00063	SW  	2003	6	19	HEEA087404       	1	20030611	G	6510	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										T/R DRIVE	OVERHEATED      	E			HEEA	O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			SW	03	723PH					53283				TAIL ROTOR DRIVE BEARING PRODUCED HIGH TEMPERATURE.						1	G	7	1 	3U			O	H2SW    					 
2003061900073	20030619	00073	SW  	2003	6	19	HEEA087407       	1	20030611	G	6510	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										T/R DRIVE	ROUGH           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				TAIL ROTOR DRIVE BEARING HAS A ROUGH SPOT.						1	G	7	1 	3U			O	H2SW    					 
2003070100060	20030701	00060	SW  	2003	7	1	HEEA087437       	1	20030612	G	6340	407375005101	INDICATOR       			BELL  	407   	407         	1182206	SW  										TRANS OIL TEMP	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				TRANSMISSION OIL TEMP INDICATOR LIGHT DIM. SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100068	20030701	00068	SW  	2003	7	1	HEEA087438       	1	20030612	G	2841	407375006101	INDICATOR       			BELL  	407   	407         	1182206	SW  										FUEL QTY	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				FUEL QTY INDICATOR DISPLAY DIM. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100069	20030701	00069	SW  	2003	7	1	HEEA087439       	1	20030612	G	2841	407375006101	INDICATOR       			BELL  	407   	407         	1182206	SW  										FUEL QTY	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	405PH					53207				FUEL QTY INDICATOR GOES BLANK. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100070	20030701	00070	SW  	2003	7	1	HEEA087440       	1	20030612	G	2844	407075024103	INDICATOR       			BELL  	407   	407         	1182206	SW  										FUEL PRESS AMP	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	490PH					53378				FUEL PRESS AMP INDICATOR INTERNAL LIGHTS TOO DIM TO SEE INSTRUMENTS. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100071	20030701	00071	SW  	2003	7	1	HEEA087441       	1	20030612	G	7714	407375012101	WIRE HARNESS    			BELL  	407   	407         	1182206	SW  										FADEC	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				FADEC DEGRADE LIGHT IN FLIGHT. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100072	20030701	00072	SW  	2003	7	1	HEEA087442       	1	20030612	G	2840	407375016103	SIGNAL COND UNIT			BELL  	407   	407         	1182206	SW  										FUEL INDICATION	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH					53399				FUEL LOW LIGHT REMAINS ON WITH FULL FUEL TANK. SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100073	20030701	00073	SW  	2003	7	1	HEEA087443       	1	20030612	G	3110	407375038101	PANEL           			BELL  	407   	407         	1182206	SW  										COCKPIT	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				LIGHTED PANEL IS BROKEN AT AFT END NEXT TO THROTTLE GRIP. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100074	20030701	00074	SW  	2003	7	1	HEEA087444       	1	20030612	G	3110	407375038101	PANEL           			BELL  	407   	407         	1182206	SW  										COCKPIT	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				PANEL CRACKED ALONG EDGE TWO PLACES. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100075	20030701	00075	SW  	2003	7	1	HEEA087445       	1	20030612	G	5210	407515108	CYLINDER        			BELL  	407   	407         	1182206	SW  										PAX DOOR	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				LT AFT DOOR GAS CYLINDER SAFETY HOLES FOR END FITTINGS BROKEN OUT. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100104	20030701	00104	SW  	2003	7	1	HEEA087446       	1	20030612	G	5210		ROD END         			BELL  	407   	407         	1182206	SW  										DOOR CYCLINDER	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				PAX DOOR GAS CYLINDER ROD ENDS WORN. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100105	20030701	00105	SW  	2003	7	1	HEEA087447       	1	20030612	G	5610	407541119	WINDOW          			BELL  	407   	407         	1182206	SW  										COCKPIT	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				COCKPIT SLIDER WINDOW CRACKED. TO BE SENT TO MFG FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100106	20030701	00106	SW  	2003	7	1	HEEA087448       	1	20030612	G	6730	41000413	SERVO VALVE     			CLARK 	1000  	1000CLARK   	2230102	SW  										MAIN ROTOR	BINDING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										STICKING AND BINDING UNDER PRESSURE DURING FINAL TEST OF SERVO. SENT FOR WARRANTY REPAIR.						1	Q	7	1 	3R			 	2A6     					 
2003070100107	20030701	00107	SW  	2003	7	1	HEEA087449       	1	20030612	G	6520	427042440103	ADAPTER         			BELL  	407   	407         	1182206	SW  										T/R GEARBOX	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH				A1109	53397				ADAPTER AND WEAR SLEEVE REMOVED DUE TO OIL LEAKING BETWEEN SLEEVE AND ADAPTER. TO BE SENT FOR CREDIT.						1	G	7	1 	3U			O	H2SW    					 
2003070100108	20030701	00108		2003	7	1	HEEA087450       	4	20030612	G	3421	50400179015	INDICATOR       			BELL  	407   	407         	1182206	SW  										COCKPIT	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	467PH					53142				ADI, WILL NOT CAGE WHILE ENERGIZED. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003070100111	20030701	00111		2003	7	1	HEEA087451       	4	20030612	G	3421	5040017901	INDICATOR       			BELL  	407   	407         	1182206	SW  										ATTITUDE	INACCURATE      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				ATTITUDE INDICATOR, SHOWS LEFT BANK IN CRUISE FLIGHT. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003070100128	20030701	00128		2003	7	1	HEEA087452       	4	20030612	G	3421		KNOB            			BELL  	407   	407         	1182206	SW  										ADI	SEPARATED       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH				2029	53398				ADI INDICATOR CAGING KNOB CAME OFF. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003070100129	20030701	00129		2003	7	1	HEEA087453       	4	20030612	G	3421	504001790116	GYRO            			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				HORIZON GYRO WILL NOT STAY ERECT. REPAIRED.						1	G	7	1 	3U			O	H2SW    					 
2003070100130	20030701	00130		2003	7	1	HEEA087454       	4	20030612	G	3422	5050010902	GYRO            			BELL  	407   	407         	1182206	SW  										COCKPIT	SPINNING        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH					53327				GYRO MODEL200DCL SPINS CONSTANTLY. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2003070100131	20030701	00131	GL  	2003	7	1	HEEA087455       	2	20030612	G	7420	53159	IGNITION LEAD   			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C20      	03013	GL  					IGNITER	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				INTERMITTENT STARTING PROBLEM. REPLACED IGNITER.						1	G	7	1 	3U	3	U	O	H2SW    	E4CE				 
2003061700124	20030617	00124	GL  	2003	6	17	HEEA087462       	2	20030612	G	7421	6899084	IGNITER         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				DELAYED LIGHT OFF. REPLACED IGNITER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2003061700167	20030617	00167	SW  	2003	6	17	HEEA087468       	1	20030612	G	2820	70079H000Y150	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	KINKED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				FUEL HOSE KINKED. REPLACED HOSE.						1	G	7	1 	3U			O	H2SW    					 
2003061700249	20030617	00249	SW  	2003	6	17	HEEA087478       	1	20030612	G	2497	BD131	CONNECTOR       			BELL  	407   	407         	1182206	SW  										ELECTRICAL	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				CONNECTOR CORRODED AND BURNED. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2003061800009	20030618	00009	SW  	2003	6	18	HEEA087487       	1	20030612	G	6240	M8353633003L	RELAY           			BELL  	407   	407         	1182206	SW  										ROTOR HORN	STUCK           	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	404PH					53188				ROTOR HORN RELAY STICKING.						1	G	7	1 	3U			O	H2SW    					 
2003061800012	20030618	00012		2003	6	18	HEEA087490       	4	20030612	G	3457	N0010001	CONTROL UNIT    			BELL  	407   	407         	1182206	SW  										GPS	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				GPS CONTROL UNIT WOULD NOT ACKNOWLEDGE COMMANDS. SENT TO OUTERLINK FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			O	H2SW    					 
2003061800178	20030618	00178		2003	6	18	HEEA087516       	4	20030610	G	2312	064105430	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										VHF SYS	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5031U					S678				TRANSCEIVER HAS AN INTERMITTENT SQUEAL. SHOP REPAIR.						1	G	7	2 	3U			 	H3EU    					 
2003061800179	20030618	00179	EU  	2003	6	18	HEEA087517       	1	20030610	G	7810	10562433	DUCT            			BOLKMS	105   	BO105S      	5626006	EU  										EXHAUST SYS	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3071K					S859				DUCT HALF ASSY ABESTOS TORN. SHOP REPAIR.						1	G	7	2 	3U			 	H3EU    					 
2003071700029	20030717	00029	SW  	2003	7	17	HEEA088006       	1	20030622	G	5610	407030118105	CHIN BUBBLE     			BELL  	407   	407         	1182206	SW  										COCKPIT	CRAZED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				LEFT CHIN BUBBLE CRAZED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2003071400152	20030714	00152	EU  	2003	7	14	HEEA088089       	1	20030708	G	6320	IFS010015	CLUTCH PLATE    			AEROSP	AS355 	AS355*      	       	EU  										TRANSMISSION	OVERHEATED      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	732AE					2873				CLUTCH WON'T HOLD AND OVERHEATED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H11EU   					 
2003091900067	20030919	00067	WP  	2003	9	19	HXS2003F00001    	1	20030603	G	6210	369D21100516A	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	B			HXSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	1088N	3465 				300679D				MAIN ROTOR BLADE CRACKED ON TOP ROOT FITTING IN THE AREA OF BOLTS IN A CORDWISE DIRECTION FOLLOWING AD 96-10-09(B).						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003091900068	20030919	00068	EU  	2003	9	19	HXS2003F00002    	1	20030521	G	7930	70BM055010	CHIP DETECTOR   			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	CONTAMINATED    	B			HXSR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AL	05	6094U	3683 				2751	4815			PILOT CALLED  IN AN AMBER CHIP LIGHT JUST AFTER LIFT OFF AND RETURNED TO BASE.  INSPECTED ENGINE CHIP PLUGS AND FOUND A 	SMALL PIECE OF MATERIAL IDENTIFIED AS A SMALL BLACK PARTICLE OF CARBON WHICH IN THE MAINTENANCE MANUAL PLACES IT AS CATE	GORY ONE.  CLEANED CHIP PLUG AND PLACED AIRCRAFT BACK INTO SERVICE IAW MM.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2003050900121	20030509	00121	SW  	2003	5	9	I05R086281       	1	20030425	G	6230	350A37112602	BUSHING         			CLARK 	1000  	1000CLARK   	2230102	SW  										MAIN ROTOR	LOOSE           	B			I05R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05		289  								BUSHING LOOSE REPLACED LINK AND SPACER.						1	Q	7	1 	3R			 	2A6     					 
2003050900122	20030509	00122	SW  	2003	5	9	I05R086282       	1	20030425	G	6320	704A33640021	SPACER          			CLARK 	1000  	1000CLARK   	2230102	SW  										SCISSOR LINK	STUCK           	B			I05R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05		289  								SPACER STUCK IN LOOSE BUSHING OF SCISSOR LINK.   REPLACED SCISSOR LINK AND BUSHING.						1	Q	7	1 	3R			 	2A6     					 
2003050900124	20030509	00124	EU  	2003	5	9	I05R086284       	1	20030425	G	7714	78899811	INDICATOR       			UROCOP	EC130 	EC130B4     	       	EU  	TMECA 	ARRIUS	ARRIUS2B1   		NE  					ENGINE NG	INOPERATIVE     	B			I05R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	26LB	290  				3514				FIRST AND SECOND DIGITS ARE INTERMITTENT, ONE N/R BAR INOPERATIVE REPLACED INDICATOR WITH SERVICABLE UNIT.						1	G	7	2 	3U	3	U		H9EU    	E34NE				 
2003050900125	20030509	00125	EU  	2003	5	9	I05R086285       	1	20030425	G	6320	1184964	OIL COOLER      			UROCOP	EC130 	EC130B4     	       	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					GEARBOX	LEAKING         	B			I05R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	26LB	683  				3514				OIL COOLER HAS FITTING LEAKING,  REPLACED COOLER.						1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
2003050900126	20030509	00126	EU  	2003	5	9	I05R086286       	1	20030425	G	2121	3972A010000	BLOWER          			UROCOP	EC130 	EC130B4     	       	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAIL BOOM	INOPERATIVE     	B			I05R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	29LB	15   				3560				SINCE A/C DELIVERY BLOWER HAS NOT BEEN OPERATIONAL.   REPLACED BLOWER.						1	G	7	2 	3U	3	U		H9EU    	E00054EN				 
2003043000231	20030430	00231	EU  	2003	4	30	I05R086287       	1	20030425	G	6330	L633M2010101	MOUNT           			UROCOP	EC135 	EC135P1     	8680990	EU  										GEARBOX	FAILED          	H			I05R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	551BA					188				MOUNT FAILED REPLACED MOUNT						1	G	7	2 	3U			O	H88EU   					 
2003091500027	20030915	00027	SO  	2003	9	15	IS4R20030806A    	1	20030806	G	2140	94E421	PRESSURE SWITCH 		B4500       	PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	CLOSED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09					A97100018					CUSTOMER BOUGHT EXCHANGE HEATER.  CORE RETURNED TO US HAD A DISTORTED COMBUSTION TUBE.  FOUND COMBUSTION AIR PRESSURE SW	ITCH IN THE CLOSED POSITION AT ALL TIMES.  THIS PARTICULAR SWITCH IS A NORMALLY OPEN SWITCH.  SWITCH CLOSES WHEN COMBUST	ION AIR PRESSURE INCREASES AND TELLS THE HEATER IT HAS COMBUSTION AIR.  THE COMBUSTION AIR BLOWER QUIT(FAILED) AND THIS 	SWITCH DID NOT SENSE THIS LACK OF COMBUSTION AIR PRESSURE AND CONTINUED TO SUPPLY FUEL TO THE HEATER.  BAD, BAD, BAD THI	S SWITCH DOES NOT GET TESTED IAW AD 96-20-07.   THIS FR65D79-3EL HEATER WAS BUILT IN OCTOBER 1997.		1	L	7	2 	3O				A20SO   					 
2003090300069	20030903	00069	CE  	2003	9	3	IS4R269M         	1	20030717	G	2140	51A45	COMBUSTION HEAD 			BEECH 	55    	95A55       	1152704	CE  										HEATER	DEFECTIVE       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09										HEATER CORE RETURNED TO US BY CUSTOMER AFTER PURCHASING AN EXCHANGE/OVERHAUL HEATER. TEAR-DOWN/CLEANING OF CORE REVEALED	 COMBUSTION HEAD WITH A 3/16 X 1/4 INCH HOLE IN THE WALL OF THE COMBUSTION HEAD. THIS IS THE THIRD HEAD WE HAVE FOUND WI	TH A HOLE IN IT. A PRESSURE DECAY CHECK OF THE HEATER ASSEMBLY WILL FIND THESE HOLES QUICKLY, IF PERFORMED. RECOMMEND PR	ESSURE CHECK OF ALL COMBUSTION AIRCRAFT HEATERS FOR CONTINUED SAFE HEATER OPERATION.			1	L	7	2 	3O			 	3A16    					 
2003052700119	20030527	00119	EA  	2003	5	27	ISO11030019      	2	20030520	G	8530	LW12416	EXHAUST VALVE   			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	BROKEN          	C				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SO	11	7355G	3449 				17259055	L2788227A			AIRCRAFT IN CRUISE AT 5000 FT., EXPERIENCED LOSS OF POWER, PILOT LANDED IN WHEAT FIELD, 2 POB, NO INJURIES, MINOR DAMAGE	.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2003092300003	20030923	00003	GL  	2003	9	23	JA00103          	1	20030816	G	3260	864203	PROXIMITY SENSOR			BOMBDR	BD700 	BD7001A10   	1390006	GL  										MLG	FALSE INDICATION	B				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			WP	01	67RX	840  				9067				(BRAKE FAULT) ADVISORY MESSAGE COMES ON AFTER LANDING AND LOSS OF LT INBD AND OUTBD BRAKES.  ON LGCEU FOUND LT MAIN GEAR	 INDICATOR AIR MODE, TARGETS OF BOTH SENSORS FOUND OUT OF PROXIMITY AND LT MAIN GEAR STRUT COMPLETELY DEPLETED, AFTER SE	RVICING OF STRUT, TARGETS OF PROX. SENSOR COMES TO NORMAL GROUND POSITION.  POTENTIAL BRAKE FAILURE OF LT AND RT MLG BRA	KES IN CASE OF PRESSURE LOSS ON BOTH MLG STRUTS!			2	L	7	2 	4F			RT	T00003NY					 
2003101000079	20031010	00079	CE  	2003	10	10	JV2R200300001    	1	20030919	G	5311	265312264004	FRAME           			RKWELL	NA265 	NA26565     	7630107	CE  										FUSELAGE	CRACKED         	B			JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	801SS	9808 	9808 			46540				CRACK FOUND UPON ROUTINE INSPECTION. CRACK IS APPOXIMATLY FOURTEEN INCHES INTO FRAME. APPOXIMATE LOCATION OF FRAME IS FS	 264.					2	L	7	2 	4J			 	A2WE    					 
2003091000004	20030910	00004	EU  	2003	9	10	KBMA088820       	1	20030726	G	6520	350A33215300	BEARING         			AEROSP	AS355 	AS355*      	       	EU  										TAIL ROTOR	WORN            	B			KBMA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	270SH					1864				LAMINATE BEARINGS WORN EXCESSIVELY. REPLACED WITH NEW.						1	G	7	2 	3U			 	H11EU   					 
2003091000005	20030910	00005	EU  	2003	9	10	KBMA088821       	1	20030726	G	6520	350A33215300	BEARING         			AEROSP	AS355 	AS355*      	       	EU  										TAIL ROTOR	WORN            	B			KBMA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	270SH					1864				LAMINATE BEARINGS WORN EXCESSIVELY. REPLACED WITH NEW.						1	G	7	2 	3U			 	H11EU   					 
2003102300085	20031023	00085	SO  	2003	10	23	KENT200300001    	1	20030925	G	5740		MOUNT           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					AIL BELLCRANK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	5FN					287625005				LEFT WING AILERON BELLCRANK MOUNT HOUSING IS CRACKED ON FWD HORIZONTAL FLANGE AT MOUNT BOLT LOCATION. TTAF 5665.7						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2003111400064	20031114	00064	CE  	2003	11	14	L2498            	1	20031031	G	5711	58221661	SPAR CAP        			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					ZONE 500	CORRODED        	B			LK0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	84LJ	5503 				4410084				DURING A ROUTINE INSPECTION SOME PAINT BLISTERING WAS NOTICED ALONG THE LT AFT SPAR UPPER CAP IN THE THE EXPOSED AREA OF	 THE LT WHEEL WELL. FURTHER INVESTIGATION REVEALED THAT THE SPAR CAP HAD SEVERE EXFOLIATION TYPE CORROSION AND WAS CAUSI	NG THE SPAR CAP TO FLAKE APART. ONCE THE AFT SECTION OF SKIN WAS REMOVED, IT WAS NOTICED THAT THE CORROSION HAD EXTENDED	 ALL THE WAY THOUGHT THE CAP. INSPECTION OF THE REMAINING SPAR CAPS REVEALED NO CORROSION.			1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2003091200079	20030912	00079	SO  	2003	9	12	LZ2R996K         	2	20030718	G	7497	10357281	WIRE            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					MAGNETO	SEPARATED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	27	2930V					347970384				ENGINE MISSING ON ONE MAGNETO; PULLED MAG AND FOUND WIRE SEPERATED FROM CAPACITOR.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2003090200086	20030902	00086	NM  	2003	9	2	M7103            	1	20030701	G	6320	A1814	BEARING         			ROBSIN	R22   	R22BETA     	7640110	NM  										ENGINE OUTPUT	FAILED          	G				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NM	01	8362L	838  	42   			2642				AIRCRAFT EXPERIENCED CLUTCH LIGHT DURING FLIGHT AND MADE PRECAUTIONARY LANDING IN PARKING LOT. NO DAMAGE TO AIRCRAFT DUE	 TO LANDING.  EXAMINATION OF AIRCRAFT FOUND LOWER DRIVE BELT PULLEY BEARING FAILURE.   PART TT 838.6,  OVERHAUL LIFE OF 	PART 2200 HOURS.  BEARING ASSEMBLY LAST INSPECTED 42.9 HOURS PRIOR TO FAILURE. ASSEMBLY PART NUMBER: A007-5				1	G	7	1 	3O			 	H10WE   					 
2003111300041	20031113	00041	CE  	2003	11	13	MD001            	1	20030918	G	2750		DRIVE SYSTEM    			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6*        	52043	EA  					TE FLAP	DAMAGED         	B				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			SO	17	290CC					LJ132				UPON APPROACH TO SUA A SPLIT FLAP CONDITION WAS REPORTED. THE AIRCRAFT LANDED WITHOUT INCIDENT.  SUBSEQUENT INVESTIGATIO	N REVEALED A SEPARATION OF THE SWAGED END FITTING TO THE FLAP ACTUATOR CAUSING A BIND IN THE LEFT FLAP SYSTEM.  P/N 1232	5Y116 FLAP DRIVE CABLE ASSEMBLY WAS REPLACED WITH NEW AND AN OVERHAULED FLAP ACTUATOR P/N 50-521198-3 WAS REPLACED AS A 	PRECAUTION.			1	L	7	2 	3T	3	T	 	3A20    	E2NE				 
2004122100075	20041221	00075	NE  	2004	12	21	MDR03038         	1	20031215	G	6210	151520604000	SPAR            			SKRSKY	S64   	S64E        	8142604	NE  										M/R BLADE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	CGESG	10450			64M50895463	64065				THE BLADE WAS INSPECTED DUE TO A BIM INDICATION IN THE FIELD.  DURING THE INSPECTION, A LEAK INDICATION WAS NOTED ON THE	 BOTTOM SIDE OF THE SPAR BETWEEN POCKETS 5 AND 6.  AFTER REMOVAL OF POCKETS 5 AND 6, AND FPI INSPECTION REVEALED A CRACK	 IN THE SPAR RUNNING CHORD WISE, BEGINNING .7500 INCH FROM THE BACK WALL EXTENDING  .8750 INCH TOWARD THE LEADING EDGE. 	 PROBABLE CAUSE IS CORROSION PIT ON SPAR .8750 INCH FROM THE BACK WALL.			2	G	7	2 	4U			 	H4EA    					 
2004122100048	20041221	00048	NE  	2004	12	21	MDR03039         	1	20031215	G	5320	642066340105	ATTACH ANGLE    			SKRSKY	S64   	CH54B       	8142610	NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					FUSELAGE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	158AC	13527				64081				DURING A SCHEDULED INSPECTION, LT ATTACH ANGLE, PN 6420-66340-105, WAS FOUND CRACKED AT STA 767.8 LBL 5.5, WL 177.1.  TH	E CRACK ORIGINATED AT THE BOTTOM HUCK FASTENER AND TRAVELED DOWN TO THE EDGE OF THE ANGLE.  THESE ANGLES ATTACH THE INTE	RCOSTALS TO THE CANTED WEB AT THE ABOVE-LISTED LOCATIONS.  PROBABLE CAUSE IS FATIGUE.  RECOMMENDATIONS TO PREVENT RECURR	ENCE, USE 7078-T6, .063 EXTRUSION, RATHER THAN ORIGINAL MATERIAL 7075-T6, .050 INCH BENT SHEET.			2	G	7	2 	4U	4	U	 	H6EA    	E15EA				 
2003060600089	20030606	00089	CE  	2003	6	6	N154DJ01         	1	20030521	G	7120	643042	BRACKET         			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE MOUNT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	154DJ	209  	209  			T30300230	246199R			THE AIRCRAFT IS ON ROUTINE 100 HR INSPECTION.  A CRACK WAS NOTED ON THE LOWER LT ENGINE MOUNT BRACKET.  A DIE PENETRANT 	CHECK REVEALED A TOTAL OF THREE CRACKS.  MFG HAS BEEN CONTACTED REGARDING THESES CRACKS, BUT WERE NOT INTERESTED AT ALL.	  AS THIS PART IS SUCH A LOW TIME ITEM (209HRS) MAYBE A FLEET WIDE CHECK SHOULD BE INITIATED.				1	L	7	2 	3O	3	O	 	A34CE   	E8CE				 
2003082600109	20030826	00109	CE  	2003	8	26	N3571Y           	1	20030610	G	2710	051316714	CONTROL WHEEL   			CESSNA	182   	182F        	2072714	CE  										COCKPIT	STRIPPED        	G				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			GL	19	3571Y					18254471				ON ROUTINE SKYDIVING FLIGHT, THE APPROPRIATELY RATED AND QUALIFIED PILOT ENTERED A CROSS CONTROL MANEUVER TO CLOSE CABIN	 DOOR.  UPON RETURNING TO NORMAL FLIGHT THE PIC EXPERIENCED LOSS OF AILERON CONTROL EXHIBITED BY CONTROL WHEEL ROTATING 	360 DEGREES WITH NO MOVEMENT OF AILERONS. AFTER LANDING, PILOT INSPECTED THE AIRCRAFT AND FOUND THAT THE 3, AN507-1032R6	 SCREWS THAT ATTACH CONTROL WHEEL ASSY (P/N 0513167-14) TO CONTROL COLUMN TUBE HAD BECOME LOOSE AND 2 HAD FALLEN OUT, TH	IS ALLOWED CONTROL WHEEL TO SPIN ON CONTROL COLUMN TUBE.  INSPECTION REVEALED THAT THREADS IN CAST ALUMINUM CONTROL WHEE	L WERE WORN AND STRIPPED OUT.	1	H	7	1 	3O			NT	3A13    					 
2004021800040	20040218	00040	EA  	2004	2	18	N4848M           	1	20031008	G	2432		CHARGER         			CURTIS	TRVAIR	TRVAIR2000  	2621606	EA  										MASTER BATTERY	BURNED          	P				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SO	19	4848									I PURCHASED A 24 VOLT CHARGER FROM AIRCRAFT SPRUCE ABOUT 6 MONTHS AGO.  IT WAS A PRISM BRAND IMPORTED BY CSB BATTERY IN 	FT. WORTH.  IT WAS ADVERTISED NOT TO OVERCHARGE IF LEFT CONNECTED INDEFINITELY.  I LEFT IT ON FOR 3 WEEKS WHILE I WAS TR	AVELING.  I RETURNED TO FIND THE ACID BOILED OUT OF THE BATTERY AND THE BATTERY MELTED.  I TRIED TO RESOLVE THE PROBLEM 	WITH ALL PARTIES.  I RETURNED THE CHARGER TO CSB.  THEY TOLD ME THEY INSPECTED IT AND THERE WAS NOTHING WRONG AND THE PR	OBLEM WAS WITH MY BATTERY.		1	Q	7	1 	3V			 	ATC30   					 
2003031300143	20030313	00143	EU  	2003	3	13	NASA51181        	2	20030307	G	7200	U125924	NUT             			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					ENGINE	MISSING         	C			NASA	K				NONE                    				C	W		F.O.D.                    	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	09	848NA	607  	607  			222	8978			IN JUNE 2000 DURING A ROUTINE POSTFLIGHT INSPECTION FOD WAS DISCOVERED ON THE LP COMPRESSOR 5TH STAGE BLADES. DURING A S	UBSQUENT TEARDOWN IT WAS DISCOVERED THAT A LP COMPRESSOR OGV BOLT AND NUT AND CAME LOOSE AND CAUSED THE DAMAGE TO THE EN	GINE. THE BOLT WAS FOUND LOOSE INSIDE THE LP COMPRSSOR DRUM BUT THE NUT AND WASHER WERE NOT FOUND. AT THE TIME, THE OVER	HAUL FACILITY, ROLLS ROYCE CANADA (RRC) AND ROLLS ROYCE UK, THE MANAFACTURER, CONSIDERED IT AN ISOLATED INCIDENT EVEN TH	OUGH THERE HAD BEEN TWO SERVICE BULLETINS ISSUED FOR THIS ITEM DURING THE YEARS AND THERE WERE SEVERAL OTHER DOCUMENTED 	OCCURRENCES OF THIS PROBLEM. THE ENGINE HAD 607.8 TSO.  IN MARCH 2002, SPEY ENGINE 8815 WHICH WAS INSTALLED ON ANOTHER G	2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2004051300021	20040513	00021	EU  	2004	5	13	NP0001           	1	20030707	G	2910	MY20751634	LINE            			AMD   	FALCON	FALCON20    	2730103	EU  	GARRTT	TFE731	TFE7312B    	 	WP  					HYD SYSTEM	CRACKED         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	384K	8679 				387				ON POST FLT INSPECTION FOUND HYDRAULIC FLUID UNDER AND AROUND AFT END OF LT HYDRAULIC RESERVOIR. CLEANED AREA AND FOUND 	SMALL CRACK IN HYD SYSTEM RETURN LINE. REMOVED AND REPLACED LINE.					2	L	7	2 	4F	4	F	RT	A7EU    	E6WE				 
2004051200030	20040512	00030	EU  	2004	5	12	NP0002           	1	20030909	G	2910	MY20751635	LINE            			AMD   	FALCON	FALCON20    	2730103	EU  										HYD SYSTEM	CRACKED         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	384K	8752 				387				FOUND HYDRAULIC FLUID AROUND AFT END OF LT HYDRAULIC RESERVOIR. CLEANED AREA AND FOUND NOTHING. PRESSURIZED THE NR 1 HYD	RAULIC SYST AND FOUND NO LEAK. AFTER SEVERAL FLIGHTS, FOUND SIMILAR HYDR  FLUID TRACES AROUND HYD RESERVOIR BUT FOUND NO	 CRACK. CLEANED AREA AND RAN BOTH ENGINES FOR 30 MINUTES BEFORE LEAK APPEARED. COULD NOT SEE A CRACK VISUALLY. REMOVED A	ND REPLACED LINE. AFTER REMOVING LINE, IT HAD TO BE BENT BACKWARDS BEFORE CRACK WAS VISIBLE.  THE ALUMINUM HYDRAULIC LIN	ES IN THE AFT COMPARTMENT ARE ON THE TOP TEN HIT LIST FOR FAILURES. SUGGEST BEING DILIGENT IN LOOKING FOR LEAKS IN THE A	FT COMPARTMENT.	2	L	7	2 	4F			RT	A7EU    					 
2003122900190	20031229	00190	CE  	2003	12	29	OSO0720040003    	1	20031201	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  										COCKPIT	FRACTURED       	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	07	207CW	2387 				BB1658				PILOTS FRONT WINDSHIELD SHATTERED AT ALTITUDE.  THIS IS THE SECOND PILOTS WINDSHIELD TO BE REPLACED SINCE THE AIRCRAFT W	AS MANUFACTURED IN 1999.  THE FIRST PILOTS WINDSHIELD WAS REPLACED ON 12/27/2000,AT 1035 CYC,1187 HRS.TTAF(REASON UNKNOW	N). THIS OCCURANCE HAPPENED AT TOTAL TIME OF AIR FRAME(TTAF)3574 HRS.AND CYCLES OF 3131. NO REASON GIVEN FOR FRACTURE OF	 W/S.			1	L	7	2 	4T			 	A24CE   					 
2003060500160	20030605	00160	CE  	2003	6	5	PG0306889        	1	20030519	G	5522		SKIN            			BEECH 	58    	58P         	1152744	CE  	CONT  	O550  	IO550*      	 	SO  					ELEVATOR	CRACKED         	B			HBKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	981SS	1363 			TH1857	TH1857				CRACK FOUND ON TOP SIDE OF LEFT HAND ELEVATOR, JUST FORWARD OF OUTBOARD END OF TRIM TAB. CRACK EXTENDS FORWARD INBOARD F	OR APPROXIMATELY THREE INCHES.					1	L	7	2 	3O	3	O	 	A23CE   	E3SO				 
2003070700149	20030707	00149	EU  	2003	7	7	R1561            	1	20030626	G	2720	F10A272129	PUSHROD TUBE    			AMD   	FALC10	FALCON10    	2730101	EU  										ELEVATOR	CHAFED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	982MC	8168 				114				DURING INSPECTION FOR HYDRAULIC SEEP AT BOTTOM OF RUDDER, FOUND ELEVATOR SERVO PRESSURE LINE CHAFFED THROUGH RUDDER PUSH	-PULL TUBE.  SUSPECTED LINE WAS TIGHTENED WITH A PRELOAD THAT TWISTED THE LINE TO CHAFE ON THE RUDDER PUSH-PULL TUBE.  T	HE LINE WAS LOOSENED AND REPOSITIONED ITSELF SO AS TO EXTEND AND RETRACT WITH CONTROL MOVEMENT WITHOUT INTERFERENCE WITH	 THE RUDDER PUSH-PULL TUBE.  PUSH-PULL TUBE HAD A HOLE CHAFED THROUGH AND REQUIRED REPLACEMENT.  THIS AREA IS ONLY INSPE	CTED DURING A 3B (3600 HOURS) OR C (6 YEARS) IAW THE MFG MM, CHAPTER 5-10-00.		2	L	7	2 	4F			 	A33EU   					 
2003111300060	20031113	00060	EU  	2003	11	13	R1765            	1	20031009	G	2720	F10A272129	PUSHROD TUBE    			AMD   	FALC10	FALCON10    	2730101	EU  										RUDDER	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	10HE	11476				111				INSPECTED RUDDER PUSH-PULL TUBE IAW SDRS AND ALERTS ARTICLE IN AVIATION MAINTENANCE MAGAZINE DATED OCTOBER 2003.  FOUND 	ELEVATOR SERVO PRESSURE LINE CHAFED RUDDER PUSH-PULL TUBE.  SUSPECTED LINE WAS TIGHTENED WITH A PRELOAD THAT TWISTED THE	 LINE TO RUB THE TUBE.  THE LINE WAS LOOSENED AND REPOSITIONED ITSELF SO AS TO EXTEND AND RETRACT WITH CONTROL MOVEMENT 	WITHOUT INTERFERENCE WITH THE RUDDER TUBE. TUBE PART NUMBER F10A272129 HAD TO BE REPLACED.			2	L	7	2 	4F			 	A33EU   					 
2003051300219	20030513	00219	WP  	2003	5	13	R5XR2000003      	2	20030422	G	7230		HOUSING         								ALIDSG	TFE731	TFE7313AR   	 	WP  					FAN SUPPORT	MISOVERHAULED   	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09										WHILE PERFORMING MODIFICATION TO 70821, THE EDM PROCEDURE BROKE THROUGH THE WALL OF THE HOUSING DUE TO ERROR IN SETUP OF	 EDM MACHINE.										4	F			E6WE				 
2003051300220	20030513	00220	WP  	2003	5	13	R5XR2000004      	2	20030422	G	7230	30721601	HOUSING         								ALIDSG	TFE731	TFE7313AR   	 	WP  					FAN SUPPORT	MISOVERHAULED   	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09							P75129			WHILE PERFORMING MODIFICATION TO 70821, THE EDM PROCEDURE BROKE THROUGH THE WALL OF THE HOUSING DUE TO ERROR IN SETUP OF	 EDM MACHINE.										4	F			E6WE				 
2003051300010	20030513	00010	SO  	2003	5	13	RE401338         	2	20030509	G	8520		LIFTER          			BEECH 	35    	V35A        	1151544	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	CHIPPED         	D			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	7653N	622  	622  			D8858	296565R			732 HRS TOTAL TIME,  622 HRS TIME SINCE OVERHAUL DUE TO PROP STRIKE.  DURING ANNUAL INSPECTION OF AIRCRAFT, NUMBER 3 CYL	INDER WAS REMOVED FOR LOW COMPRESSION 10/80.  FOUND METAL, STEEL, ON SKIRT OF CYLINDER.  NOTED VISUALLY THAT CAM WAS WOR	N DOWN IN CONTACT AREA OF LIFTER. REMOVED BOTH NR3 LIFTERS AND FOUND FACE PITTED (EST .030 INCH DEEP .040 DIA) AND EDGE 	OF FACE HAD SEVERAL PEICES CHIPPED OFF.  REPAIR STATION INFORMATION WAS THAT NEW LIFTERS AND CAM WERE INSTALLED AT SUDDE	N STOPAGE REPAIR.  ENGINE WAS REMOVED FOR OVERHAUL AND SENT TO REPAIR STATION.		1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2003020500032	20030205	00032	CE  	2003	2	5	ROCK012303       	1	20030123	G	2740	4014305	SWITCH          			RKWELL	NA265 	NA26565     	7630107	CE  	ALIDSG	TFE731	TFE7313AR   	 	WP  					STAB TRIM	INOPERATIVE     	B				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			CE	01	82CR	5320 				46549				PILOT'S TRIM SWITCH BECAME INTERMITTENT AND THEN FAILED TO OPERATE COMPLETELY IN FLIGHT.  CO-PILOT AND ALTERNATE TRIM SY	STEMS BOTH REMAINED FUNCTIONAL.  TESTED AND REPLACED PILOT'S TRIM SWITCH AT DESTINATION.  SYSTEM FUNCTIONED PROPERLY AFT	ER REPLACMENT OF SWITCH.				2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2003100900106	20031009	00106	WP  	2003	10	9	RX8R2003001      	1	20030915	G	5312	369A3018	FIREWALL        			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE BAY	CRACKED         	B			RX8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	7166M	5373 				0145E	CAE835438			UPON REMOVING THE UPPER ENGINE COMPARTMENT HEAT SHIELD FOR REPLACEMENT, A 4 INCH CRACK WAS DISCOVERED IN THE TOP OF THE 	ENGINE COMPARTMENT, ALONG THE RIVET LINE, WHERE THE TAIL BOOM STRUCTURE ATTACHES TO THE FIRESHIELD. OUR 2 OTHER M.D. 369	E HELICOPTERS WERE INSPECTED AND ALSO HAD SIMILAR CRACKS IN THE SAME AREA. (N5247S, SN 0119E, 6066.0 HRS. 11463 LANDINGS	 AND N6508U, SN 0084E, 2793.0 HRS. 6816 LANDINGS) THIS AREA IS USUALLY COVERED BY THE HEAT SHIELD BLANKET WHICH IS NOT R	EMOVED FOR NORMAL INSPECTIONS. RECOMMEND THE MANUFACTURER ISSUE A SB OR AD TO THE INSPECTION CHECKLIST TO INSPECT THIS A	REA PERIODICALLY.	1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003111300071	20031113	00071	EU  	2003	11	13	RX8R2003002      	1	20031106	G	6320	704A37630023	THERMOSWITCH    	UROCOP      		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					MAIN GEARBOX	INOPERATIVE     	B			RX8R	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SO	15	4048L	1658 			513	3020	9245			WHILE PERFORMING THE 6 YR. 2000 HR. INSPECTION TO TEST THE MAIN GEARBOX OIL TEMPERATURE PROBE, IT WAS DETERMINED THAT TH	E PROBE WAS INOPERATIVE AND HAD TO BE REPLACED. WE PERFORMED THE SAME TEST ON ANOTHER AS350B2 AIRCRAFT (N4043L, SN 3015)	 ON OCT. 23, 2003 AND FOUND THE SAME PROBLEM, THE PROBE WAS INOP. 6 YEARS IS A LONG TIME TO WAIT TO PERFORM THE TEST ON 	THE TEMP PROBE. IT IS IMPOSSIBLE TO SAY HOW LONG THESE PROBES HAVE BEEN INOP. AS EASY AS THE TEST IS, WE WOULD RECOMMEND	 THAT IT BE PERFORMED EACH 3 YEARS OR 1200 HRS. WHEN THE M.G.B. OIL IS CHANGED.		1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003020500033	20030205	00033	NE  	2003	2	5	S88R554J         	2	20030116	G	7261	0292100560	SEAL RING       			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D1   	 	NE  					OIL FILTER ASSY	DISTORTED       	B				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	21	5202Y					3085	9513			ENGINE OIL PRESSURE LOSS RESULTED FROM DISTORTION OF THE DRAIN VALVE SEALING RING WITHIN THE OIL FILTER ASSEMBLY. INDENT	ATIONS ON THE SEALING RING CORRESPONDING TO HOLES IN THE FILTER BASE BECAME MISALIGNED DURING FILTER ELEMENT INSPECTION 	AND FAILED TO PRESENT A FLAT REGISTER TO THE FILTER BASE. THE INDENTATIONS MAY BE ASSOCIATED WITH OVER-TIGHTENING OF THE	 FILTER BOLT DURING PRIOR MAINTENANCE. THE SEALING RING IS NOT NORMALLY REPLACED DURING OIL FILTER ELEMENT INSPECTION OR	 REPLACEMENT.		1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2003031300149	20030313	00149	CE  	2003	3	13	SDR21903         	1	20030219	G	7930	26060152	INDICATOR       			CESSNA	208   	208B        	2073701	CE  										INSTRUMENT PANEL	SHORTED         	E				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	17	90GL	11493				208B0229				PILOT OBSERVED SMOKE IN AND UPON SCANNING INSTRUMENTS, NOTICED LOWER THAN NORMAL OIL PRESSURE AND HIGHER THAN NORMAL OIL	 TEMP. ENGINE WAS SHUT DOWN. PILOT ALSO REPORTED FACE OF INSTRUMENT GLOWING AS CABIN FILLED WITH SMOKE. PILOT DONNED O2 	MASK AS SMOKE THICKENED. MASTER POWER WAS NEVER SHUTDOWN AND 5 AMP BREAKER NEVER OPENED AUTOMATICALLY NOR WAS IT PULLED.	 AFTER LANDING AND SECURING THE MASTER SWITCH THE SMOKE CLEARED.  ALL DAMAGE APPEARED TO BE CONTAINED INTERNALLY AND SMO	KE MOST LIKELY EXITED INSTRUMENT THRU THE VENT FITTING.		1	H	7	1 	3T			 	A37CE   					 
2003123000022	20031230	00022	SO  	2003	12	30	SLACK            	1	20031202	G	3213		STRUT           			PIPER 	PA28  	PA28140     	7102802	SO  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	15423	3690 				287325064				DURING 100 HR. INSPECTION IAW SB 1131 THE LT MAIN GEAR UPPER STRUT CYLINDER WAS CRACKED AS DEPICTED IN THE BULLETIN.  TH	E PART WAS DYE CHECKED AT THE PREVIOUS INSPECTION WITH NO CRACK EVIDENT.  THE CRACK IS APPROX. 2 IN. LONG STARTING AT TH	E BOTTOM OF THE OUTBOARD (EAR).				1	L	7	1 	3O			 	2A13    					 
2003123000071	20031230	00071	CE  	2003	12	30	SPT              	1	20031008	G	2432		CHARGER         			CESSNA	305   	305A        	2074002	CE  										MASTER BATTERY	BURNED          	P				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			SO	19	4848					N4848M				PURCHASED A 24 VOLT CHARGER ABOUT 6 MONTHS AGO.  IT WAS A PRISM BRAND IMPORTED BY CSB BATTERY IN FT. WORTH.  IT WAS ADVE	RTISED NOT TO OVERCHARGE IF LEFT CONNECTED INDEFINITELY.  I LEFT IT ON FOR 3 WEEKS WHILE I WAS TRAVELING.  I RETURNED TO	 FIND THE ACID BOILED OUT OF THE BATTERY AND THE BATTERY MELTED.  TRIED TO RESOLVE THE PROBLEM WITH ALL PARTIES. RETURNE	D THE CHARGER TO CSB.  THEY TOLD ME THEY INSPECTED IT AND THERE WAS NOTHING WRONG AND THE PROBLEM WAS WITH MY BATTERY.			1	H	7	1 	3O			 	5A5     					 
2003012300027	20030123	00027	NM  	2003	1	23	SROM200300018    	1	20030120	G	7110	6573773	RIB             			BOEING	737   	737205      	1384456	NM  										Zone 400	CHAFED          	A			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733PA		1310 			23466				During C check inspection found # 2 engine OB cowl # 3 rib chaffed 13" from lower edge.  Removed damage, fabricated part	s and installed fabricated parts per SRM 54-10-2, 51-40-4, 51-10-2 and 51-30-2.  Minor repair,					2	L	7	2 	4F			RT	A16WE   					 
2003042800109	20030428	00109		2003	4	28	SROM200300022    	4	20030407	G	3414	2083081	INDICATOR       			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					AIRSPEED	FAILED          	C			SROM	A				UNSCHED LANDING         				S			AFFECT SYSTEMS            			CL	CLIMB          	1			AL	03	733PA	23970	647  			23466				DURING CLIMB THE NR 2 MACH/AIRSPEED INDICATOR FAILED WITH FLAG PRESENT.  RETURNED TO DEPARTURE AIRPORT.  DURING APPROACH	, JUST PRIOR TO TOUCH DOWN FLAG WENT AWAY AND INDICATOR BEGAN WORKING PROPERLY.  REPLACED AIRSPEED/MACH INDICATOR. GROUN	D FUNCTION CHECKED OK.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2003082700055	20030827	00055	NM  	2003	8	27	SROM200300023    	1	20030623	G	5310	6624124	SHEAR TIE       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				SHEAR TIE AT STATION 616 BETWEEN STINGERS 7 AND 8L HAS .2500 INCH CRACK.  REMOVED AND REPLACED SHEAR TIE IAW MFG SRM 51-	10-1 AND 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003082700056	20030827	00056	NM  	2003	8	27	SROM200300024    	1	20030624	G	5320	693535214	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND STRINGER CLIP AT STA 616, STRINGER 8R WITH 1.5 INCH CRACK.  REMOVED AND REPLACED CLIP IA	W WITH MFG SRM 51-10-1 AND 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003090400204	20030904	00204	NM  	2003	9	4	SROM200300025    	1	20030625	G	5320	693535214	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND STINGER CLIP AT STA 616 AND STRINGER 8L WITH 1 FT CRACK.  REMOVED AND REPLACED IAW MFG S	RM 51-10-1 AND 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003082700057	20030827	00057	NM  	2003	8	27	SROM200300026    	1	20030625	G	5320	693535214	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND STRINGER CLIP AT STA 597 STINGER 8R CRACKED .3 INCH.  REMOVED AND REPLACED IAW B737 SRM 	51-10-1 AND 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003090200073	20030902	00073	NM  	2003	9	2	SROM200300027    	1	20030626	G	5320	693525214	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND STINGER CLIP AT STA 360 5L WITH A .25 INCH CRACK.  REPLACED CLIP IAW B737 SRM 51-10-1 AN	D 53-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003090200074	20030902	00074	NM  	2003	9	2	SROM200300028    	1	20030629	G	5313	654576820	STRINGER        			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND SEVERAL ELONGATED HOLES IN STRINGER 23R BETWEEN STA 360 AND 440.  REMOVED AND REPLACED S	TRINGER BETWEEN STA 360 AND 440 IAW SRM 51-30-2, 51-10-2 AND MM 51-21-171.					2	L	7	2 	4F			RT	A16WE   					 
2003090200075	20030902	00075	NM  	2003	9	2	SROM200300029    	1	20030629	G	5313	654576821	STRINGER        			BOEING	737   	737205      	1384456	NM  										FUSELAGE	MISREPAIRED     	C			SROM	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION ELECTED TO REPLACE STRINGER 23R BETWEEN STA 500 AND 540 DUE ELIMINATE A PREVIOUS REPAIR.  REMO	VED AND REPLACED STRINGER IAW WITH B737 SRM 51-30-2, 51-10-2 AND MM 51-21-171.					2	L	7	2 	4F			RT	A16WE   					 
2003090200076	20030902	00076	NM  	2003	9	2	SROM200300030    	1	20030629	G	5313	654576823	STINGER         			BOEING	737   	737205      	1384456	NM  										FUSELAGE	MISREPAIRED     	C			SROM	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION ELECTED TO REPLACE STINGER 24R FROM STA 500 TO 540 BECAUSE OF A PERVIOUS APPROVED REPAIR.  REP	LACED STRINGER IAW B737 SRM 51-10-2 AND MM 51-21-171.					2	L	7	2 	4F			RT	A16WE   					 
2003090400003	20030904	00003	NM  	2003	9	4	SROM200300031    	1	20030629	G	5347	654661513	SEAT TRACK      			BOEING	737   	737205      	1384456	NM  										FUSELAGE	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND GAUGES IN SEAT TRACK ALONG CENTER AND TOP FLANGES BETWEEN STA 540 AND 727.  REMOVED DAMA	GED SEAT RACK AND REPLACED IAW SRM 53-10-1, 51-30-2 AND 51-10-2.					2	L	7	2 	4F			RT	A16WE   					 
2003090200077	20030902	00077	NM  	2003	9	2	SROM200300032    	1	20030627	G	5320	694688216	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND STRINGER CLIP AT STA 360, STINGER 4 L CRACKED .25 INCH.  REPLACED CLIP IAW SRM 51-10-1 A	ND 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003070800011	20030708	00011	NM  	2003	7	8	SROM200300033    	1	20030629	G	5512	655482U34	SKIN            			BOEING	737   	737205      	1384456	NM  										HORIZONTAL STAB	SCRATCHED       	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND FOUND SEVERAL SCRATCHES IN LOWER AND UPPER SURFACES OF THE RT IB HORIZONTAL STABLIZER LE	ADING EDGE.  REMOVED AND REPLACED RT IB HORIZONTAL LEADING EDGE IAW  SRM 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003070800012	20030708	00012	NM  	2003	7	8	SROM200300034    	1	20030702	G	5347	654681513	SEAT TRACK      			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	GOUGED          	I			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND NUMEROUS GOUGES IN CENTER AND TOP OF SEAT TRACK BETWEEN BS 540 - 727, LBL 24.  REMOVED A	ND REPLACED SEAT TRACK BETWEEN BS 540 TO 727 IAW SRM 51-30-2, 51-10-2 AND MM 51-21-0.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2003090200141	20030902	00141	NM  	2003	9	2	SROM200300036    	1	20030703	G	5347	BAC1505100246	FLOORBEAM       			BOEING	737   	737205      	1384456	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND CORROSION ON FLOORBEAM UPPER CAP AT STA 344 FROM LBL 30 TO RBL 30.  REMOVED AND REPLACED	 DAMMAGED CAP IAW SRM 51-30-2, 51-10-6, 51-10-2 AND 53-10-1.CORROSION LEVEL 1					2	L	7	2 	4F			RT	A16WE   					 
2003090200142	20030902	00142	NM  	2003	9	2	SROM200300037    	1	20030706	G	5320	693555214	STRINGER CLIP   			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND DRILL BIT DAMAGE FROM A PREVIOUS REPAIR TO STRINGER CLIP AT STA 380 AND STRINGER 2 R.   	REMOVED AND REPLACED STRINGER CLIP IAW SRM 51-30-2 AND 51-10-1.					2	L	7	2 	4F			RT	A16WE   					 
2003090200143	20030902	00143	NM  	2003	9	2	SROM200300038    	1	20030701	G	5347	6546815145	SEAT TRACK      			BOEING	737   	737205      	1384456	NM  										FUSELAGE	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND BARE METAL AND GOUGES ON SEAT TRACK BETWEEN STAS 727 AND 947, RBL 45.5.  REMOVED AND REP	LACED SEAT TRACK IAW SRM 51-10-1, 51-30-2, 51-10-2 AND MM 51-21-171.					2	L	7	2 	4F			RT	A16WE   					 
2003090200171	20030902	00171	NM  	2003	9	2	SROM200300039    	1	20030709	G	5330	6545774	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND SKIN AT STA 846 BETWEEN STRINGER 24L AND 25L TO HAVE A SMALL DENT AND GOUGE.  REMOVED DA	MAGED AREA AND REPAIRED IAW B737 SRM 53-30-3, 53-30-2 AND 51-10-2.					2	L	7	2 	4F			RT	A16WE   					 
2003090300003	20030903	00003	NM  	2003	9	3	SROM200300040    	1	20030709	G	5310	BAC15061108	BEAM            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	GOUGED          	D			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6768 			23465				DURING D CHECK INSPECTION FOUND LONGITUDINAL BEAM AT STA 707, LBL 24, GOUGED AT FASTNER HOLE INBOARD FLANGE, WL 205.  RE	MOVED DAMAGE, FABRICATED AND INSTALLED REPAIR STRAPS IAW SRM 53-10-1, 53-10-2, EA 53-10-02240 AND AAR EA 05-53-EA239.					2	L	7	2 	4F			RT	A16WE   					 
2003090300056	20030903	00056	NM  	2003	9	3	SROM200300041    	1	20030714	G	5313	6573744157	STRINGER        			BOEING	737   	737205      	1384456	NM  										FUSELAGE	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND STRINGER 20R AT BS 500 GOUGED BEYOND ALLOWABLE LIMITS.  REMOVED DAMAGED AREA OF STINGER,	 FABRICATED AND INSTALLED REPAIR IAW B737 SRM 53-10-2, 51-10-3, 51-10-2, 51-10-3 AND MM 51-21-171.					2	L	7	2 	4F			RT	A16WE   					 
2003090300055	20030903	00055	NM  	2003	9	3	SROM200300042    	1	20030714	G	5347	654681513	SEAT TRACK      			BOEING	737   	737205      	1384456	NM  										FUSELAGE	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32953	6788 			23465				DURING D CHECK INSPECTION FOUND SEAT TRACK AT STA 540 TO 727, RBL 45 GOUGED ALONG CENTER AND TOP FLANGES IN NUMEROUS PLA	CES.  REMOVED AND REPLACED SEAT TRACK IAW B737 SRM 51-30-2, 51-30-5 AND 51-10-2.					2	L	7	2 	4F			RT	A16WE   					 
2003091200036	20030912	00036	NM  	2003	9	12	SROM200300043    	1	20030722	G	5533	6552490118	BEAM            			BOEING	737   	737205      	1384456	NM  										VERTICAL STAB	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND DENT IN RT TRAILING EDGE BEAM OF VERTICAL STABILIZER AT APPROX STA 17.25.  REFORMED  RT 	TRAILING EDGE BEAM IAW EA 5530-01100 AND EA 10007.					2	L	7	2 	4F			RT	A16WE   					 
2003091700043	20030917	00043	NM  	2003	9	17	SROM200300045    	1	20030728	G	5330	65C3584336	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION FOUND NUMEROUS DENTS IN FUSELAGE SKIN BETWEEN STR 18R & 20R STA 850 TO 890 THAT WERE OUT OF LI	MITS IAW B737 SRM 53-30-1.  REMOVED AND REPLACED SKIN PANEL AT STA 727 TO 907 STR 14R TO STR 20R IAW B737 SRM 51-30-2, 5	1-10-2.				2	L	7	2 	4F			RT	A16WE   					 
2003091700044	20030917	00044	NM  	2003	9	17	SROM200300046    	1	20030726	G	5230	6547952162	SKIN            			BOEING	737   	737205      	1384456	NM  										CARGO DOOR	DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP		6788 			23465				DURING D CHECK INSPECTION CUSTOMER REQUEST TO REMOVED AND REPLACED AFT CARGO DOOR SKIN DUE TO DENTS AND DINGS.  REMOVED 	AND REPLACED IAW B737 SRM 51-30-2, 51-30-5, MM 57-31-0.					2	L	7	2 	4F			RT	A16WE   					 
2003091200131	20030912	00131	NM  	2003	9	12	SROM200300047    	1	20030623	G	5330	65C36745116	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION CUSTOMER REQUESTED TO REMOVE AND REPLACE SKIN ASSY P/N 65C36745-116 LOCATED AT BS 908 TO 1016S	TG 20R TO 25R DUE TO PREVIOUS REPAIRS.  REMOVED AND REPLACED IAW B737 SRM 51-30-2					2	L	7	2 	4F			RT	A16WE   					 
2003091500011	20030915	00011	NM  	2003	9	15	SROM200300048    	1	20030728	G	5330	65C36745100	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION CUSTOMER REQUEST TO REMOVE AND REPLACE SKIN ASSY P/N 65C36745-100 LOCATED AT BS 727 TO 907 STR	 20R TO 25R DUE TO PREVIOUS REPAIRS.  REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003091200133	20030912	00133	NM  	2003	9	12	SROM200300049    	1	20030724	G	5310	65C3584318	SKIN            			BOEING	737   	737205      	1384456	NM  										FUSELAGE	DAMAGED         	G			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	32963	6788 			23465				DURING D CHECK INSPECTION CUSTOMER REQUEST TO REMOVE AND REPLACE SKIN ASSY P/N 65C35843-18 LOCATED AT BS 360 TO 540 STR 	19R TO 26R DUE TO PREVIOUS REPAIRS.  REMOVED AND REPLACED SKIN PANEL IAW B737 SRM 51-30-2.					2	L	7	2 	4F			RT	A16WE   					 
2003091200034	20030912	00034	NM  	2003	9	12	SROM200300051    	1	20030728	G	5330	6545777	SKIN            			BOEING	737   	737205      	1384456	NM  											DENTED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP					23465				DURING D CHECK, AFTER SKIN REPLACEMENT, FOUND DENT WITH GOUGE ON INNER SKIN AT BS 933.5 BETWEEN STR 22R AND 23R.  REPAIR	ED DENT IAW B737 SRM 53-30-3, 53-30-1, 51-30-2 AND 51-10-2.					2	L	7	2 	4F			RT	A16WE   					 
2003111300050	20031113	00050	NM  	2003	11	13	SROM200300052    	1	20031108	G	5330		SKIN            			BOEING	737   	737205      	1384456	NM  										ZONE 100	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	33329				23465				DURING AN A-3 CHECK FOUND A GOUGE IN BOTTOM OF FUSELAGE SKIN .375 INCH LONG BY .25 INCH.  INSPECTED AREA FOR CRACKS USIN	G HFEC.  NONE DETECTED.  REPAIRED GOUGE AREA WITH FLUSH PATCH PER B737 SRM 53-30-3.					2	L	7	2 	4F			RT	A16WE   					 
2003122900198	20031229	00198	NM  	2003	12	29	SROM200300053    	1	20031118	G	2121		FAN             			BOEING	737   	737205      	1384456	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	FAILED          	C			SROM	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AL	03	733PA					23466				DURING CRUISE FLIGHT AT 330 A BURNING ODOR WAS NOTED IN THE COCKPIT ONLY.  ALL SYSTEMS CONTINUED TO FUNCTION NORMAL.  PR	ECAUTIONARY LANDING AT FAI WAS MADE.  UPON LANDING MAINTENANCE WAS UNABLE TO FIND THE SOURCE OF THE SMELL AND ALL OPERAT	IONS NORMAL.  IT WAS DECIDED TO FERRY AIRCRAFT TO ANC FOR FURTHER INVESTIGATION.  DURING FLIGHT TO ANC ODOR WAS NOTICE M	OMENTARILY AND DISSIPATED.  NO OTHER PROBLEMS NOTED.  ANC MAINTENANCE WAS UNABLE TO CONFIRM SOURCE OF ODOR.  PRECAUTIONA	RY REPLACEMENT OF NORMAL ELECTRICAL EQUIPMENT BLOWER AND ITS CIRCUIT BREAKER WAS ACCOMPLISHED.  ON SUBSEQUENT FLIGHT NO 	PROBLEMS REPORTED.	2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2003123000010	20031230	00010	NM  	2003	12	30	SROM200300054    	1	20031204	G	3350	582212	POWER SUPPLY    			BOEING	737   	737205      	1384456	NM  										EMERGENCY LIGHT	INOPERATIVE     	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				DURING PREFLIGHT INSPECTION FORWARD SECTION OF FLOOR TRACK EMERGENCY LIGHTING AND EXIT SIGN AT L1 DOOR INOPERATIVE.  CHA	NGED EMERGENCY BATTERY OVER L1 DOOR.  SUSPECT MOISTURE IN THE LIGHT STRIP WAS A CONTRIBUTING, IF NO THE ROOT CAUSE OF TH	E PROBLEM.				2	L	7	2 	4F			RT	A16WE   					 
2003091200020	20030912	00020	EA  	2003	9	12	SROMDHC200301    	1	20030811	G	3251	711599	LEVER           			DHAV  	DHC6  	DHC6300     	2802606	EA  										NLG STEERING	BROKEN          	C			SROM	D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			AL	03	842AR	13235	1502 			842				DURING TAXI THE NOSE STEERING TILLER WENT HARD OVER WITH NO EFFECT TO STEERING INPUT.  FOUND STEERING LEVER WHICH TRANSF	ERS HYDRAULIC FORCE FROM STEERING ACTUATOR TO STEERING COLLAR ON STRUT TO BE TOTAL BROKE ON OPPOSITE SIDES OF PIVOT BEAR	ING BORE.  ONE SIDE APPEARS TO HAVE FRACTURED PREVIOUS DUE TO SLIGHT FRETTING IN BREAK AREA.				1	H	7	2 	3T			RT	A9EA    					 
2003123000011	20031230	00011		2003	12	30	TAM1112200301    	4	20031031	G	6113	U14426000	PLATE           			PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O320  	O320A2B     	41508	EA  	MCAULY	1A175	1A175*      	GL  	SPINNER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01										SPINNER BACKPLATE BRACKETS SEEM TO FAIL OFTEN, PICTURE NR 1.  THIS PARTICULAR BACKPLATE APPEARS VERY NEW, THE AIRCRAFT H	AS FLOWN 35 HOURS SINCE ANNUAL INSPECTION.  PICTURE NR 2 SHOWS HOW THE PROPELLER HITS THE BRACKET LEG AND PUSHES THE SPI	NNER BACKPLATE AFT, SLIGHTLY OUT OF ALIGNMENT.  PERHAPS THIS INTERFERENCE IS CAUSING ABNORMAL STRESS ON THE TAB ACUTE AN	GLE, THUS CAUSING THEM TO FAIL. A SUGGESTION TO PREVENT INTERFERENCE IS BY SLIGHTLY REWORKING THE BRACKET LEG AS IN PICT	URE NR 3.  PICTURE NR 4 SHOWS THE PROP MOUNTED FLUSH WITH THE BACKPLATE.		1	H	7	1 	3O	3	O	 	1A2     	E274	5	N	P857	 
2003031300152	20030313	00152	EA  	2003	3	13	TBM700           	2	20030221	G	7230	3041211	BLADE           	PWC         		SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6*        	52043	EA  					COMPRESSOR	FAILED          	G				E	B	A		ENGINE SHUTDOWN         	EMER. DESCENT           	UNSCHED LANDING         		X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			GL	19	12WY	1449 	25   			112				EXPERIENCED A TOTAL POWER FAILURE WHILE DESCENDING FROM FL250 TO FL240.  PILOT MADE A SUCCESSFUL DEAD STICK LANDING. INS	PECTION OF THE ENG REVEALED A CATASTROPHIC FAILURE OF A COMPRESSOR TURBINE BLADE WHICH RESULTED IN A COMPLETE ENGINE STO	PPAGE AND LOCKING UP THE POWER TURBINE. THIS RESULTS IN A LOSS OF PRESSURIZATION, ELECTRICAL GENERATOR POWER AND INSTRUM	ENT AIR POWER. LEARNED THAT PWC HAS FOUND MANY CT ASSEMBLIES CRACKED IN THE FIELD ON THE 60 SERIES ENGINES.			1	L	7	1 	3T	3	T	RT	A60EU   	E2NE				 
2003100600123	20031006	00123	GL  	2003	10	6	TR1031           	2	20030825	G	7230	23039797AL	COUPLING        	ALLSN       	A250C20     						ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	FRETTED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	XB-DK	1063 			CAC34134		CAE823092			COMPRESSOR COUPLING ADAPTER (P/N 23039797AL S/N CI17-406) HAS SEVERE FRETTING ON OD OF ADAPTER.  SEVERAL OEM ADAPTERS HA	VE FAILED AT THIS FRETTING AREA.										3	U			E4CE				 
2003090300041	20030903	00041		2003	9	3	UC2R20030001A    	4	20030715	G	3431		CLIP            			PIPER 	PA28  	PA28181     	7102807	SO  										NAV COM SYS	MISMANUFACTURED 	B				O				OTHER                   				L	S		NO TEST                   	AFFECT SYSTEMS            		NR	NOT REPORTED   	1			GL	19	4144K					2843145				NAVIGATION CONTROL OF NAV/COMM TOGGLED FREQUECY UNCOMMANDED, WHICH CAUSED LOSS OF OPERATION OF VOR/LOC DURING FLT.  OPER	ATOR COMPLAINED THAT THIS CONDITION MADE NAV UNRELIABLE FOR USE.  TRACED PROBLEM TO KHZ NAV FREQUENCY CONTROL VERY SUSCE	PTIBLE TO TRIGGERING FROM NORMAL VIBRATION DUE TO MATERIALS USED IN MANUFACTURE.  ASSEMBLY REQUIRES GREATER SECURITY IN 	ASSEMBLY OF FREQUENCY CONTROL SWITCH AT THE LOCKING SLEEVE AND THE "C" CLIP.  MOVEMENT ALLOWED BY IN EFFECTIVE ATTACHMEN	T BY THE "C" CLIP CAUSES PHOTO CELL TO TRIGGER, TOGGLING THE NAV FREQUENCY.  LOCKING SLEEVE NEEDS TIGHTER TOLERANCE WHER	E THE "C" CLIP ATTACHES.  IMPROVEMENT TO LOCKING SLEEVE MAY REQUIRE USE OF DIFFERENT MATERIAL, METAL IN PLACE OF NYLON.	1	L	7	1 	3O			 	2A13    					 
2003091600158	20030916	00158	GL  	2003	9	16	UIE2003F00000    	2	20030714	G	7200	FJ44	ENGINE          			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					RIGHT	FLAMED OUT      	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	1000E					5250077				DURING AN APPROACH TO LAND AT 5000 FT AGL, THE THROTTLES WERE RETARDED TO IDLE AND THE NR 2 ENGINE FLAMED OUT.  A SINGLE	 ENGINE LANDING WAS PERFORMED WITHOUT INCIDENT.  THE AIRCRAFT HAD RECENTLY BEEN THROUGH AN ENGINE CHANGE AFTER AN OVERHA	UL.  AFTER THE WORK WAS PERFORMED, IT WAS NOTICED THAT THE RIGHT THROTTLE WAS CREW AND PASSENGERS WERE DISEMBARKED FROM 	THE AIRCRAFT.  THE PILOT AND CO-PILOT CONSULTED WITH GROUND MAINTENANCE.   A VISUAL INSPECTION OF THE ENGINE AND ENGINE 	RUN REVEALED NO DISCREPANCIES.  THE AIRCRAFT ENGINE CONTROLS WERE RE-RIGGED AND THE ENGINE WAS TEST RUN ONCE AGAIN TO VE	RIFY PROPER RIGGING.  (SW15200317283)	1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2003101000062	20031010	00062		2003	10	10	VERTEX01         	4	20030919	G	2561		BATTERY PACK    																	LIFE VEST LIGHT	RUPTURED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09										EMERGENCY WATER ACTIVATED LIGHT FAILURE WITHIN ORIGINAL LIFE VEST. 17 OF 18 VEST INSPECTED SHOWED RUPTURED LIGHT BATTERY	 PACKS.																		 
2003102300005	20031023	00005	CE  	2003	10	23	VERTEX2          	1	20030924	G	2897		WIRE            			CESSNA	500   	550         	2076604	CE  										FUEL PUMP	SPARKS          	B				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	13	26496	5957 			10AD110	5500607				RIGHT BOOST PUMP WIRING CHAFED ON MOTIVE FLOW FEED LINE IN FUEL BAY. CHAFED WIRE CAUSED ELECTRICAL ARC DAMAGE TO FUEL LI	NE. THIS APPEARS TO BE AN ORIGINAL BOOST PUMP. PROBLEM WAS NOTED DURING DEFUELING USING THE BOOST PUMP TO REMOVE FUEL FO	R MAINTENANCE. THE 15 AMP BOOST PUMP CIRCUIT BREAKER POPPED WHEN THE FUEL REMAINING WAS APX 15 GALS. INSPECTION REVEILED	 THE ABOVE PROBLEM, BOTH THE BOOST PUMP AND FUEL LINE WERE REPLACED.  FIX: THE BOOST PUMP WIRING WAS DOUBLED BACK TO PUM	P HOUSING AND SECURED WITH A TIE WRAP/STAND OFF TO INSURE IT COULD NOT COME IN CONTACT WITH THE FUEL LINE IN THE FUTURE.		1	L	7	2 	4F			 	A22CE   					 
2003102300073	20031023	00073	CE  	2003	10	23	VERTEX3          	1	20030925	G	2822	10712	PUMP            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL BOOST	SCORED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	26496					5500607				AFTER FINDING CHAFED FUEL BOOST PUMP WIRING ARCING AGAINST MOTIVE FLOW FUEL SUPPLY LINE ON RT SIDE LT FUEL BOOST PUMP WA	S ALSO INSPECTED. WIRING ON LT (NO ARCING AT THIS TIME) HAD RUBBED INTO MOTIVE FLOW FUEL SUPPLY LINE TO A POINT THAT SUP	PLY LINE P/N 6526355-37 HAD TO BE REPLACED. ADDITIONALLY ELECTRICAL LINE HAD RUBBED THROUGHT PROTECTIVE COATING ON FLOOR	 OF FUEL COMPARTMENT NEXT TO BOOST PUMP (P/N 107-12). THIS WAS INSPECTED AND PROTECTIVE COATING REAPPLIED.  RECOMEND INS	PECT THESE FUEL BAYS. IT MAY BE REQUIRED TO REMOVE MOTIVE FLOW FUEL SUPPLY LINE FOR PROPER INSPECTION.  NOTE: RT HAND BO	OST PUMP P/N 1C7-12 WAS ORIGNAL AND THE LT HAND PUMP P/N 107-12 WAS A REPLACEMENT PUMP. TIME UNKNOWN AT THIS TIME.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2003090300066	20030903	00066	CE  	2003	9	3	VG4R595M         	1	20030415	G	3246	50300010133	WHEEL           			BEECH 	90    	C90A        	1152911	CE  										MLG	DAMAGED         	B			VG4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	35		423  				LJ1659				UPON TAKEOFF, THE LEFT MAIN WHEEL ASSEMBLY DEPARTED THE AIRCRAFT.  UPON INSPECTION, FOUND THE AXEL NUT WAS STILL ON, THE	 BEARINGS WERE DISINTEGRATED AND THE WHEEL WAS DAMAGED.					1	L	7	2 	3T			RT	3A20    					 
2004012000022	20040120	00022	CE  	2004	1	20	WVE2003F0000A    	1	20031123	G	2421	30728692	SPLINE ADAPTER  			LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					RT ENGINE	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	425FX					147				DURING 600 HOUR INSPECTION OF THE ALTERNATOR SPLINE ADAPTOR, DISCOVERED ADAPTER TO BE CRACKED IN TWO LOCATIONS.  PROBABL	E CAUSE: FATIGUE.					2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2003031400010	20030314	00010	EU  	2003	3	14	XG3R084688       	1	20030221	G	2121	3972A010000	BLOWER          			UROCOP	EC130 	EC130B4     	       	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAILBOOM	SHORTED         	H			XG3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	29LB	15   				3560	23004			SINCE DELIVERY OF THE AIRCRAFT THE CONDENSOR BLOWER HAS NOT BEEN OPERATIONAL. REPLACED BLOWER						1	G	7	2 	3U	3	U	 	H9EU    	E00054EN				 
2003031400011	20030314	00011	EU  	2003	3	14	XG3R084689       	1	20030221	G	7714	78899811	INDICATOR       			UROCOP	EC130 	EC130B4     	       	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					NR & NG	SHORTED         	H			XG3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	26LB					3514	23017			INSTRUMENT BEGAN TO FAIL INTERMITTENTLY.  FINALLY FAILED COMPLETELY. REPLACED INSTRUMENT WITH SERVICEABLE UNIT.						1	G	7	2 	3U	3	U	 	H9EU    	E00054EN				 
2003090200047	20030902	00047	WP  	2003	9	2	XMSR778K         	1	20030620	G	6210	369D21100517	BLADE           			HUGHES	369   	369E        	4470707	WP  	ALLSN 	25OC  	250C20R     	 	GL  					MAIN ROTOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	52550	2088 				0166E				CRACK FROM TRAILING EDGE TO SPAR BOTH BOTTOM AND TOP OF BLADE.  CRACK IS APPROX 19 INCHES OUTBOARD OF REAR BLADE PIN HOL	E.  CRACK 4.6250 INCHES LONG AND T (ED) OF 1.5000 EACH WAY ON THE BOTTOM AND ON TOP SIDE T 2 INCHES TOWARD OUTBOARD AND 	.5000 INCH TOWARD INBOARD.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2003122900201	20031229	00201		2003	12	29	YHLR200300001    	4	20031126	G	2300	6285437001	LEAD            			BEECH 	76    	76          	1153005	CE  										RADIO ANTENNA	UNBONDED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	6626Z					ME208				FOUND MOD-17 NOT PERFORMED IAW SB VHF251-SB17. GROUND STRAP FROM ANTENNA CONNECTOR P2 TO GROUND PLANE OF POWER AMPLIFIER	 ASSEMBLY A3. 2A(2) WAS NOT ACCOMPLISHED. UNIT HAD BEEN MARKED FOR MOD-17, AND WAS TAGGED BY REPAIR STATION, DATED 11/05	/2002. MOD-17 COMPLETED IAW SB VHF251-SB17.  PROBLEM COULD HAVE BEEN PREVENTED IF SERVICE BULLETIN HAD BEEN PROPERLY COM	PLIED WITH.			1	L	7	2 	3O			 	A29CE   					 
2003042300211	20030423	00211	NE  	2003	4	23	ZAVR192X         	2	20030225	G	7250	742198	SHAFT           								PWA   	JT8   	JT8D7B      	52053	NE  					LP TURBINE	CHAFED          	B			ZAVR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07							648906			TURBINE SHAFT APPROXIMATELY 2 FEET AFT OF THE SPLINED AREA, SHAFT SHOWS EVIDENCE OF TWISTING OR BLENDING THAT REMOVED MA	TERIAL.										4	F			E2EA